This Conference along with the 63rd AeSI AGM was rescheduled to 1st and 2nd of June 2012 from the originally intended date of 26th & 27th of April 2012, due to the launch of ISRO’s PSLV-C19 Mission on 26th April 2012.
Š Aeronautical Society of India Thiruvananthapuram Branch May 2012
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Archana Datta (Mukhopadhyay) OSD (PR) to the President
President’s Secretariat, Rashtrapati Bhavan, New Delhi - 110004
Message
The President of India, Smt. Pratibha Devisingh Patil, is happy to know that the Thiruvananthapuram Branch of the Aeronautical Society of India is organising a National Conference on “Advances in Thermo Physics and Heat Transfer” (ASET-2012) and the 63rd AeSI National AGM on June 1-2, 2012 at Thiruvananthapuram. The President extends her warm greeting and felicitations to the organisers and the participants and wishes the events every success.
Officer on Special Duty (PR)
Tel 011-23016535(Direct), 23015321 Extn 4322. Fax 23794498, E-mail-osdad@rb.nic.in
®úIÉÉ ¨ÉÆjÉÒ ¦ÉÉ®úiÉ
MINISTER OF DEFENCE INDIA
Message 05 March 2012
I am very happy to be informed that The Aeronautical Society of India, Thiruvananthapuram branch has decided to organise a two day National Conference on “Advances in Thermo Physics & Heat Transfer”(ASET-2012) and the 63rd National AGM on 26th and 27th April 2012 at Thiruvananthapuram. It is heartening to note that a Souvenir containing scientific/technical papers selected for presentation during the Conference is being published. It is appropriate that the theme of the Conference is focusing on Heat transfer which is significant to aerospace applications area. It is also encouraging that the experts from various branches of the aerospace will explore various ways and means for the advancement of collaborative opportunities for the development and research work of the students. I wish the National Conference and also the publication of the Souvenir all success.
(A.K.Antony)
Office: 104, South Block, New Delhi -110011, Ph.: 23012286, 23019030 Fax: 23015403 Resi.: 9, Krishna Menon Marg, New Delhi - 110011. Ph.: 23013611. Fax: 23013612
OOMMEN CHANDY CHIEF MINISTER KERALA
Message
I am very happy to learn that The Aeronautical Society of India Thiruvananthapuram Branch is organizing a two-day National Conference on 窶連dvances in Thermo Physics and Heat Transfer (ASET-2012) in Thiruvananthapuram. I hope that the National Conference would provide opportunities for the participants to deliberate and share information with regard to trends, advancements and also challenges in the domain of Aerothermodynamics. I wish all success for the conference as well as for the activities of The Aeronautical Society of India.
OOMMEN CHANDY
Office : Secretariat, Thiruvananthapuram - 695 001
Phone : Office : 2333610, 2333812, 2333197, 2332148, 2333214, 2332682, 2332184 Fax : (0471) 2333489, Resi: (0471) 2345600, 2342602 & (0481) 2351135
Indian Space Research Organisation
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Department of Space Government of India Antariksh Bhavan New BEL Road, Bangalore - 560 231, India Telephone : +91-802341 5241 / 2217 2333 Fax : +91-80-2341 5328 e-mail : chairman@isro.gov.in
+xiÉÊ®úIÉ ´ÉÒ¦ÉÉMÉ ¦ÉÉ®úiÉ ºÉ®úEòÉ®ú +xiÉÊ®úIÉ ¦É´ÉxÉ xªÉÚ ¤ÉÒ <Ç B±É ®úÉäb÷, ¤ÉåMɱÉÚ®ú - 560 231, ¦ÉÉ®úiÉ nÚù®ú¦ÉɹÉÉ : +91-802341 5241 / 2217 2333 ¡èòCºÉ : +91-80-2341 5328
Dr. K. Radhakrishnan Chairman
Message
I am happy to note that The Aeronautical Society of India Thiruvananthapuram Branch is organising a two day National Conference on “ADVANCES IN THERMO PHYSICS and HEAT TRANSFER” (ASET-2012) at Thiruvananthapuram during June 1-2, 2012. The Indian Aerospace sector is moving forward with progress in the associated disciplines. Thermo physics and Heat Transfer is one vital area with application in aero-thermodynamics and re-entry, rocket engines, cryogenic systems and satellites. The importance of this discipline was underlined during the successful Space Capsule Recovery Experiment (SRE) and Chandrayaan-1 Missions, where the mechanisms of heat transfer and computational methods for thermal design and analysis played a crucial role in the design and development phases. The Aeronautical Society of India should be commended for their endeavors in promoting the advances in aerospace technology development. I am sure that this Conference will bring together scientists, engineers, technologists and academicians across the Country on a common platform to share experience and disseminate knowledge on the latest technological developments in heat transfer and thermo physics area, and also chalk out future directions and challenges. I convey my best wishes for the success of the Conference.
(K Radhakrishnan) 16th May 2012
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Dr. V.K. SARASWAT
Scientific Adviser to Raksha Mantri Secretary, Defence R&D and DG DRDO
¦ÉÉ®úiÉ ºÉ®úEòÉ®ú ®úIÉÉ ¨ÉÆjÉÉ±ÉªÉ ®úIÉÉ +xÉÖºÉÆvÉÉxÉ iÉlÉÉ Ê´ÉEòÉºÉ Ê´É¦ÉÉMÉ b÷Ò +É®ú b÷Ò +Éä ¦É´ÉxÉ, xÉ<Ç Ênù±±ÉÒ - 110 105
Government of India Ministry of Defence Department of Defence Research & Development DRDO Bhawan, New Delhi - 110 105 Tele : 23011519 Fax : 23018216 E-mail : vksaraswat@hqr.drdo.in
Message
I am pleased to learn that The Aeronautical Society of India, is organizing a two day National Conference on “Advances in Thermo Physics & Heat Transfer” (ASET-2012) with its 63rd Annual General Meeting on 26th April 2012. The Society has played a major role in the advancement and dissemination of aeronautical sciences in India and has provided an important platform for discussion of issues relevant to the aeronautical community.
New Delhi 28 March 2012
(VK Saraswat)
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Prof. Samir K. Brahmachari
Director General, CSIR & Secretary, Government of India Department of Scientific & Industrial Research
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Anusandhan Bhawan, 2, Rafi Marg, New Delhi - 110001
Message
It gives me great pleasure to learn that The Aeronautical Society of India, Thiruvananthapuram Branch is organizing a two-day National Conference on “Advances in Thermo-Physics and Heat Transfer” (ASET-2012) at Trivandrum during 26-27 April 2012. The research and application in the area of heat transfer and thermo-physics have made significant advances over the last few years, paving way for many innovative approaches, especially in areas specific to aerospace, defence, nuclear research and energy. Therefore, the conference merits great appreciation in the context of the topicality of the theme. I am certain that the conference will provide the perfect platform to bring together students, subject experts from across the country to exchange information about the advances in research and the progress made in this very important area. I wish the ASET 2012 all success.
New Delhi March 20, 2012
- 110001
COUNCIL OF SCIENTIFIC & INDUSTRIAL RESEARCH
(Samir K Brahmachari)
Telephone Office : 23710472, 23717053, Fax : 91-11-23710618; Residence : 91-11- 26834596 E-mail dgcsir@csir.res.in & dg@csir.res.in
BªÉ®ú SÉÒ¡ò ¨ÉɶÉÇ±É BxÉ B Eäò ¥ÉÉ=xÉ {É Ê´É ºÉä ¨Éä Ê´É ºÉä ¨Éä B b÷Ò ºÉÒ
Air Chief Marshal N A K Browne PVSM VSM ADC
Tel : (011) Off : 23012517 Res : 23017300 Fax : 23018853 Email : hawkeye@bol.net.in
´ÉɪÉÖ ºÉäxÉÉ ¨ÉÖJªÉÉ±ÉªÉ xÉ<Ç Ênù±±ÉÒ - 110 106
Air Headquarters New Delhi - 110 106
Message
1. I am pleased to learn that The Aeronautical Society of India, Thiruvananthapuram Branch is organising a National Conference on Advances in Thermo Physics & Heat Transfer (ASET-2012) on 26-27 Apr 12 and bringing out a souvenir on the occasion. 2. The modernisation programme of Indian Air Force hinges heavily on the support of a robust indigenous aerospace technology base. The key issue is to acquire core competency in certain critical aerospace technologies. Advanced aeroengine technology forms a vital part of our envisaged capability base. Towards this, the topics proposed for discussion during this seminar indicate that this intellectual forum would come out with a time bound action plan for developing our indigenous aeroengine production capability. 3. My best wishes to all members of the Society as well as the participants of the Conference. Jai Hind!
01 Apr 12
Air Chief Marshal Chief of the Air Staff
Air Marshal SP Singh AVSM VM Air Officer Commanding-in-Chief Southern Air Command Indian Air Force
Message
1.
Change is the only constant in human history. Aerospace power due to
exponential advancement of technology and changes in nature of warfare is evolving at a phenomenal pace. Our neighbors remain not-so-friendly and would not miss an opportunity to score if we let our guard down. 2. No country can become an influential power in regional or global politics unless it manufactures indigenous armaments and weapon delivery systems. The present era is full of opportunities for the modernisation of Indiaâ&#x20AC;&#x2122;s armed forces that must, formulate a plan that seeks specific investments in enhanced technology. 3. In harmony with its enlarging role in world affairs and the global economy, India requires the highest levels of technology and the ability to develop and meet its future needs indigenously and independently. Aeronautical Society of India plays a major role in promoting advancement & knowledge dissemination in aeronautical science & technology ventures on a common platform. I wish Aeronautical Society of India a successful conference.
(SP Singh)
Date: 20 Mar 12
Air Marshal Air Officer Commanding-in-Chief Southern Air Command, IAF
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15/1,
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¤ÉåMɱÉÚ®ú - 560 001
R K TYAGI
Hindustan aeronautics Limited
Chairman
15/1, Cubbon Road Bangalore - 560 001
14 Mar 2012
Message
It is heartening to note that The Aeronautical Society of India, Thiruvananthapuram Branch is organizing a two day National Conference - “Advances in Thermo Physics and Heat Transfer” (ASET-2012) along with 63rd National AGM on 26th and 27th April 2012 at Trivandrum. The Conference will provide a platform to bring together professionals in the field to exchange experience & expertise and to discuss new trends & challenges ahead. I am extremely happy to note that the topics being covered in ASET 2012 are vast and cover broad areas of Aerothermodynamics and Heat Transfer and I believe that the deliberations during the conference will benefit the Aerospace Industry immensely. My best wishes for the grand success of the Conference.
(R.K. Tyagi)
¡òÉäxÉ : EòɪÉÉÇ±ÉªÉ : + 91 80 2232 0105, 2232 0003 ¡èòCºÉ : + 91 80 2232 0240 Phone : (O) + 91 80 2232 0105, 2232 0003 Fax : + 91 80 2232 0240
Government of India Department of Space
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Vikram Sarabhai Space Centre
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Thiruvananthapuram - 695 022, India Phone : +91-471-2704412 +91-471-2565567 Fax : +91-471-2704105 e-mail : ps_veeraraghavan@vssc.gov.in
Êiɯû´ÉxÉxiÉ{ÉÖ®ú¨É - 695 022, ¦ÉÉ®úiÉ nÚù®ú¦ÉɹÉÉ : 0471-2704412 / 2565567 ¡èòCºÉ : 0471-2704105
P S Veeraraghavan Distinguished Scientist & Director
Message
I am very happy to note that The Aeronautical Society of India Thiruvananthapuram Branch is organizing two days National Conference on “Advances in Thermo Physics & Heat Transfer” (ASET-2012) at Thiruvananthapuram on 26th & 27th April, 2012. Advances in computational modelling of heat transfer processes and experimental measurement of thermo-physical and other related properties would considerably enhance the understanding of these problems, resulting in more comprehensive and accurate solutions. This will also help in the design and development of advanced sensors, better characterisation of material parameters and development of innovative thermal protection systems which could give a significant edge in ISRO’s future programmes on re-entry & re-usable technologies, interplanetary missions, human spaceflight programme, cryogenic & semi-cryo propulsion systems, etc. I am sure that this conference will give an excellent opportunity for the experts from academia, research establishments and industry to exchange and share their experiences and research observations, bringing out various challenges faced along with the solutions proposed. I wish this National Conference (ASET-2012) all success.
PS Veeraraghavan
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Indian Space Research Organisation
Government of India Department of Space
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Liquid Propulsion Systems Centre
pù´É xÉÉänùxÉ |ÉhÉɱÉÒ Eäòxpùù
Valiamala P.O. Thiruvananthapuram - 695 547, India Telephone : 0471+2567257 / 0472+2801210 Fax : 0471-2567242
´ÉʱɪɨɱÉÉ {ÉÉä.+Éä. Êiɯû´ÉxÉxiÉ{ÉÖ®ú¨É - 695 022, ¦ÉÉ®úiÉ nÚù®ú¦ÉɹÉÉ : 0471+2567257 / 0472+2801210 ¡èòCºÉ : 0471-2567242 S, RAMAKRISHNAN Director
May 7, 2012
Message
I am happy to note that The Aeronautical Society of India is organizing a National Conference on Advances in Thermophysics and Heat Transfer at Thiruvananthapuram as part of the General Body Meeting of the Society planned during 1st - 2nd June 2012. Thermophysics & Heat Transfer are core disciplines highly relevant to the field of Rocket Propulsion. Chemical rockets are perhaps the most power intensive thermodynamic devices handling Gigawatts of energy release and conversion in a confined volume of thrust chamber. The temperature extremes encountered especially in a cryogenic rocket engine poses several challenges in the design of these complex hardware. The characterization of the behavior of materials and modelling of Heat transfer mechanisms over the wide temperature range is essential for successful engineering and realization of these systems. As, LPSC is embarking on ambitious programmes of developing the 20 ton thrust Cryogenic Engine for the LVM3 project and the 200 ton thrust LOX-Kerosene Semi-Cryo engine, holding this National Conference at Thiruvananthapuram is quite timely and useful enabling many practicing engineers and professionals in the field to participate and share their knowledge and expertise. I wish the Conference all success.
[S. Ramakrishman]
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Indian Space Research Organisation
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Government of India Department of Space
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ISRO Satellite Centre
½þ´ÉÉ<Ç {ÉkÉxÉ ¨ÉÉMÉÇ, ʴɨÉÉxÉ{ÉÖ®úÉ {ÉÉäº]õ ¤ÉåMɱÉÚ®ú - 560 017, ¦ÉÉ®úiÉ
Airport Road, Vimanapura Post Bangalore - 560 017, India Telephone : +91-80-25205252, 25082102 Fax : +91-0471-25205251 email : tkalex@isac.gov.in
nÚù®ú¦ÉɹÉÉ : +91-80-25205252, 25082102 ¡èòCºÉ : 0471-25205251 <ǨÉä±É : tkalex@isac.gov.in
Dr. T.K. Alex Distinguished Scientist & DIRECTOR
Message
I am extremely glad to note that The Aeronautical Society of India Thiruvananthapuram Branch is organizing a Two day national Conference on “ADVANCES IN THERMO PHYSICS & HEAT TRANSFER” (ASET-2012) at Thiruvananthapuram on 26th & 27th April, 2012. One of the major prerequisite for a successful satellite mission lies in the accurate thermal modelling, analysis and prediction of the temperatures at the various critical locations on the bus systems and the payloads. The on-orbit thermal control methodology and the automated control procedures have to be well established and validated through extensive simulation and testing. The thermal management during the various phases of the mission influences the power systems design like the battery and solar panels, which in turn decides the overall size and mass of the spacecraft itself. Hence the advances in the computation methods, simulations techniques and measurement would definitely optimize the thermal control systems design, which would be cater to the ISRO’s deep space missions in a big way. On this occasion, I extend my sincere greetings and best wishes to the Aeronautical Society of India, Thiruvananthapuram chapter and wish the conference all success.
Date: March 26, 2012
¦ÉÉ®úiÉÒªÉ +xiÉÊ®úIÉ +xÉÖºÉÆvÉÉxÉ ºÉÆMÉ`öxÉ
(Dr. TK Alex)
Indian Space Research Organisation
Government of India Department of Space
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Satish Dhawan Space Centre
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SHAR
Sriharikota Range P.O. - 524 124 Sri Potti Sriramulu Nellore Dist. (A.P.) INDIA Telephones : +91 - 8623 - 225050 +91 - 44 - 25364450 Fax : +91 - 8623 - 225152 E-mail : director@shar.gov.in
- 524 124
¸ÉÒ {ÉÉä]Âõ]õÒ ¸ÉÒ®úɨÉÖ±ÉÖ xÉä±±ÉÚ®ú ÊVɱÉÉ (+ÉÆ.|É.) ¦ÉÉ®úiÉ ]äõʱɡòÉäxÉ : +91 - 8623 - 225050 +91 - 44 - 25364450
¡èòCºÉ : +91 - 8623 - 225152
E-mail : director@shar.gov.in
M C DAtHan Director
Message
I am very glad to note that The Aeronautical Society of India, Thiruvananthapuram Branch is organizing a Two day National Conference on “Advances in Thermophysics & Heat Transfer” (ASET-2012) at Thiruvananthapuram on 26th and 27th April. 2012. The theme of the Conference is highly relevant in expanding the knowledge in this core field of research and its applications in the direction of improved design concepts during the development of the next generation of ISRO’s Launch Vehicles and Satellites and also in the establishment of test facilities to simulate realistic conditions. Papers on Advanced Thermal Systems for Propulsion modules and Spacecrafts including the recent developments in the field with latest measurement techniques will definitely be useful for the participating teams. The interaction with national experts, researchers and scientists from the industries and academia, would definitely lead to a synergistic approach for the achievement of technological excellence in this field. While appreciating the efforts put forward by the Thiruvananthapuram Branch of AeSI in organizing useful conferences every year, I convey my best wishes for the successful conduct of this conference. [M C Dathan]
¦ÉÉ®úiÉÒªÉ +xiÉÊ®úIÉ +xÉÖºÉÆvÉÉxÉ ºÉÆMÉ`öxÉ
Indian Space Research Organisation
¦ÉÉ®úiÉ ºÉ®úEòÉ®ú GOVERNMENT OF INDIA +ÆiÉÊ®úIÉ Ê´É¦ÉÉMÉ DEPARTMENT OF SPACE
+ÆiÉÊ®úIÉ ={ɪÉÉäMÉ Eåòpù SPACE APPLICATIONS CENTRE AHMEDABAD - 380 015 (¦ÉÉ®úiÉ) (INDIA) nÚù®ú¦ÉɹÉÉ/PHONE : +91-79-26913344, 26928401 ¡èòCºÉ/FAX : +91-79-26915843 <Ç-¨Éä±É/E-mail: director@sac.isro.gov.in
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VÉªÉ Ê½þxnù
B.BºÉ. ÊEò®úhÉ EÖò¨ÉÉ®ú ÊxÉnäù¶ÉEò
A.S. Kiran Kumar Director
Message
It gives me immense pleasure to learn that The Aeronautical Society of India, Thiruvananthapuram is organising a National Conference on “Advances in Thermo Physics & Heat Transfer (ASET-2012)”. It is also interesting to note that the Aeronautical Society, Thiruvananthapuram branch is playing a vital role in spearheading the aerospace related activities at the National and International levels. The wide gamut of topics chosen as the conference theme is sure to ignite the imagination and spirit of inquisitiveness in the minds of the participants and provide impetus to fruitful interactions. I am sure that the deliberations at the conference will lead to a fruitful exchange of ideas and will immensely benefit the Aeronautical community. On this occasion, on behalf of Space Applications Centre and my personal behalf, I extend my sincere greetings and best wishes to the Aeronautical Society of India, Thiruvananthapuram branch and wish the function all success. With best regards,
Ahmedabad March 10, 2012
¦ÉÉ®úiÉÒªÉ +xiÉÊ®úIÉ +xÉÖºÉÆvÉÉxÉ ºÉÆMÉ`öxÉ
(A.S. Kiran Kumar)
Indian Space Research Organisation
®ú´ÉÒxpùxÉÉlÉ / RAVINDRANATH G ÊxÉnùä¶ÉEò / DIRECTOR
Message
I am extremely happy to note that The Aeronautical Society of India (AeSI), Thiruvananthapuram Branch is organizing its annual National Conference ASET 2012 on ‘Advances in Thermophysics and Heat Transfer’ on 26th and 27th April 2012 at Thiruvananthapuram. AeSI, Thiruvananthapuram Branch is always in the forefront in promoting space science and technology through such Conferences wherein exotic topics of technology relevance are discussed and debated. The topic chosen for the Conference is very apt when Nation is presently focusing in developing reentry technologies as a prelude to Human-in-Space Programme. Modeling and mapping aero-thermal structures, heat transfer design, measurement and analysis, thermal simulation and validation of computational techniques are some of the challenges faced by the aerospace community in space transportation. The Conference will indeed provide impetus to fruitful professional interactions between specialists from R & D Institutions and Academia, thereby enabling them to enrich their knowledge base in latest technologies and their application in the field of Thermophysics and Heat Transfer. I wish the Conference “ASET 2012” all success.
March 27, 2012
¦ÉÉ®úiÉÒªÉ +xiÉÊ®úIÉ +xÉÖºÉÆvÉÉxÉ ºÉÆMÉ`öxÉ
(Ravindranath G)
Indian Space Research Organisation
Message
I am happy to note that The Aeronautical Society of India (AeSI), Thiruvananthapuram (TVPM) branch is organizing a two day Conference on Advances in Thermo Physics and Heat Transfer (ASET 2012) and 63rd National AGM at Thiruvananthapuram during 26 to 27 April 2012. Decades of development in aeronautics and space technology has witnessed major strides in thermal engineering. Heat transfer in launch vehicles, rocket engines, cryo systems, satellites, re-entry vehicles, crewcabin, etc. includes extremes in temperature and heat flux. Excellent capabilities now exist in advanced thermal design and analysis of subsystems for aerospace applications. Varieties of new materials and innovative heat transfer systems have been developed and world class facilities established for thermal testing and qualification. This Conference, I am sure will provide an appropriate forum for the specialists to come together, discuss the state of art technologies, assess the future opportunities and contribute towards the technological challenges ahead in the field of Thermophysics and Heat transfer for aerospace applications. My best wishes to the organizers of the ASET-2012.
(Shyam Chetty)
THE AERONAUTICAL SOCIETY OF INDIA 13-B, INDRAPRASTHA ESTATE, NEW DELHI - 110002 Ph: 23370516, 23370058 Fax: 011-23370768 Email: aerosoc@bol.net.in Web: www.aerosocietyindia.in
Message
I take this opportunity to extend my hearty felicitations to all Members of our Society on the occasion of 63rd Annual General Meeting scheduled to be held on 26th and 27th April 2012 at Thiruvananthapuram. The Society is also organising a two day National Conference on “Advances in Thermo Physics & Heat Transfer” coinciding with the Annual General Meeting, a subject of great interest to a wide spectrum of our Members. The Society has played a significant role in nurturing the indigenous scientific talent and promoting professionalism in various disciplines of aeronautics and aerospace sciences. The country is proud of the achievements made in the field of scientific and technological developments and the catalytic role played by the Society I wish the organizers all the success in their endeavour’s.
(Dr. Vijay Mallya) PRESIDENT
THE AERONAUTICAL SOCIETY OF INDIA 13-B, INDRAPRASTHA ESTATE, NEW DELHI - 110002 Ph: 23370516, 23370058 Fax: 011-23370768 Email: aerosoc@bol.net.in Web: www.aerosocietyindia.in
Message
The Annual General Body Meeting of The Aeronautical Society of India and the Seminar planned by the Society on “Advances in Thermodynamics and in Heat Transfer”, being held on 26th & 27th April 2012 at Thiruvananthapuram in the ‘God’s own country’ are of special significance to the Aerospace community. Indian Aerospace Industry, be it in the field of Space, Defence, or Aviation, is poised to take great leaps due to the availability of substantial research, design, development and production capabilities established by the scientists, technologists, educationists and entrepreneurs. This event piloted by the Thiruvananthapuram Branch of our Society, provides aerospace professionals and other stakeholders an opportunity to update themselves as also for constructive and fruitful interactions. I wish the deliberations all success.
Sd/(G M Rao) Group Chairman, GMR Group & President-Elect, The Aeronautical Society of India
THE AERONAUTICAL SOCIETY OF INDIA 13-B, INDRAPRASTHA ESTATE, NEW DELHI - 110002 Ph: 23370516, 23370058 Fax: 011-23370768 Email: aerosoc@bol.net.in Web: www.aerosocietyindia.in
Message
It is a matter of great pleasure that Thiruvananthapuram Branch of our Society is organizing the 63rd Annual General Meeting along with a Seminar on “Advances in Thermo Physics & Heat Transfer” on 26th and 27th April 2012. For over six decades, The Aeronautical Society of India has rendered pioneering services to the nation in the field of aerospace sciences and in elevating aeronautical profession. Our Members have made invaluable contribution towards this cause through various promotional activities. I am sure that the Seminar on “Advances in Thermo Physics & Heat Transfer” would be a great occasion to learn about latest developments on this field and would be of great value to our Members. I convey my best wishes to all our Members on this occasion and wish the event a great success.
(Ashok Bhushan) Hony. Secretary General. Dated 20th March 2012.
THE AERONAUTICAL SOCIETY OF INDIA THIRUVANANTHAPURAM BRANCH www.aesitvpm.org
Head Office 13-B, Indraprastha Estate New Delhi - 110002
Branch Office AERO HOUSE, F-2, Future Point Edapazhanji, Thiruvananthapuram - 695010 e-mail: aesitvpm@gmail.com
FOREWORD The Aeronautical Society of India, Thiruvananthapuram Branch in its endeavor to promote advancement and dissemination of knowledge in aeronautical and aerospace science/technologies, has been conducting programs at school/college levels, seminars and national level conferences. The annual conference on emerging trends in Aerospace Technologies (ASET) is one such successful endeavor. This year AeSI, Thiruvananthapuram is organizing ASET 2012 national conference on Advances in Thermophysics and Heat transfer in aerospace. The topic is selected considering the great advancement in this field and its importance in aerospace systems design and development. Heat transfer in launch vehicles, rocket engines, cryo systems, satellites, re-entry vehicles, crew cabin, etc. includes extremes in temperature and heat flux. Advances in Thermal design and analysis capabilities have made the design and development cycle faster and with minimum testing. Varieties of new materials and innovative heat transfer systems have been developed and world class facilities established for thermal testing and qualification. The conference aims to provide opportunity to specialists in the field from organizations like ISRO, DRDO, NAL and Academic Institutions within the country to come together and discuss the state of the art technologies, assess the future direction and in the process encourage younger generation to take up the challenges ahead in the field of thermophysics and heat transfer for aerospace applications. AeSI, Thiruvananthapuram branch has been given the honor to host the National AGM of Aeronautical Society of India and the branch has taken up the challenge to conduct the AGM and ASET2012 conference in the capital city of Gods own Country. The Organising committee would like to express sincere gratitude and appreciation to all the invited speakers and dignitaries for responding spontaneously to our request to participate in the conference. The conference is supported by sponsorship from institutions and industries and their gesture is greatly appreciated. Further the various committees and individuals have contributed in a big way to organize the conference and AGM in a very successful manner. AeSI, Thiruvananthapuram branch specially acknowledges the office bearers of AeSI headquarters for providing all support for organising the AGM in a befitting manner. AeSI, Thiruvananthapuram Branch sincerely hopes that the national conference on Advances in Thermophysics and Heat transfer in aerospace will provide greater insight into the current developments paving way for imminent progress.
CH Kunhikammaran
Chairman, Organising Committee ASET 2012 & Aeronautical Society of India, Thiruvananthapuram Branch
The Aeronautical Society of India (AeSI), Thiruvananthapuram (TVPM) branch is one of the largest professional society of Aerospace community in Thiruvananthapuram with more than 580 members now which was started in October, 1972.
About AeSI
The objective of the Society is to promote the advancement and diffusion of the knowledge of Aeronautical Sciences and Aircraft Engineering as well as elevation of the Aeronautical profession. The Society is headquartered at New Delhi. The Patron In Chief of the society is the Prime Minister of India. It was founded in 1948 and the first meeting was held in Bangalore at the Puttanachetty Town Hall on December 27, 1948. The society is now with 16 branches all across India. The Society conducts lectures, seminars, workshops etc., periodically in various topics under the aegis of respective branches. It conducts examinations leading to the Associate Membership Certificate of the Aeronautical Society of India. This is recognized to be equivalent to a Bachelorâ&#x20AC;&#x2122;s degree in Aeronautical Engineering. The society recognizes professionals in engineering by grading its members into various categories such as, Fellows, Honorary Fellows, Members, Companions, Associate Members, Graduate Members and Student Members. At the annual general meeting held every year eminent personalities in the field of aeronautics who have made a significant contribution in their fields of specialization are honored by the Society. Two of the coveted prizes are the National Aeronautical Prize (AR & DB) and the Dr Biren Roy Trust Award. The Executive Committee of AeSI, Thiruvananthapuram Branch meets periodically to review the progresses of the activities planned and to plan new promotional activities. The Branch conducts lectures, seminars, workshops etc., periodically in various topics. We also associate with other professional bodies in arranging weekly talks, special lecture sessions etc. The Branch conducts every year one major conference in topics of relevant interest under the name of Aerospace Expanding frontiers: Technologies and challenges (ASET). The Aeronautical Society of India (AeSI) Thiruvananthapuram Branch has instituted a memorial lecture in honor of Late Dr S. Srinivasan, launch vehicle designer par excellence and former Director VSSC. Every year an eminent person, in any discipline of aerospace, will be selected to deliver the lecture.
About the Conference
The Aeronautical Society of India (AeSI), Thiruvananthapuram Branch spearheads aerospace activities in Thiruvananthapuram with various programmes including annual National Conference on Emerging Trends in Aerospace Technologies (ASET). â&#x20AC;&#x153;ASET 2012â&#x20AC;? will focus on advances in thermophysics and heat transfer in aerospace. Decades of development in aeronautics and space technology has witnessed major strides in thermal engineering. Heat transfer in launch vehicles, rocket engines, cryo systems, satellites, re-entry vehicles, crew cabin, etc. include extremes in temperature and heat flux. Excellent capabilities now exist in advanced thermal design and analysis of subsystems for aerospace application. Variety of new materials and innovative heat transfer systems have been developed and world class facilities established for thermal testing and qualification. Many organizations like ISRO, DRDO, NAL and academic institutions within the country are also working in the area of advanced heat transfer and thermophysics. This conference will provide an appropriate forum for the specialists to come together, discuss the state of art technologies, assess the future opportunities and contribute towards the technological challenges ahead in the field of Thermophysics and Heat transfer for aerospace applications. This conference will focus on the advancements, achievements and future challenges in aerothermodynamics, computational methods for thermal design and analysis, plasma dynamics and cryogenic heat transfer, measurement and visualization techniques, thermal simulation and testing of aerospace and propulsion systems, etc.
Indian Space Research Organisation Vikram Sarabhai Space Centre
Thiruvananthapuram
Liquid Propulsion Systems Centre
Sponsors
Antrix Corporation Limited
Bangalore
Thiruvananthapuram
Bangalore
Defence Research and Development Organisation
New Delhi
Indian Institute of Space Science and Technology
Thiruvananthapuram
ISRO Inertial Systems Unit
Thiruvananthapuram
The Aeronautical Society of India, HQ Hindustan Aeronautics Limited GMR Group of Companies Kingfisher Airlines
Mumbai
New Delhi
Bangalore
Bangalore
Dr. K Radhakrishnan . . . . . . . . Chairman
National Advisory Panel
Dr. VK Saraswat . . . . . . . . . . Scientific Advisor to Raksha Mantri Dr. TK Alex . . . . . . . . . . . . Director, ISAC Dr. RR Navalgund . . . . . . . . . Director, SAC Shri PS Veeraraghavan . . . . . . . Director, VSSC Shri S Ramakrishnan . . . . . . . . Director, LPSC Shri MC Dathan . . . . . . . . . . Director, SDSC/SHAR Dr. R.K. Sinha . . . . . . . . . . . Director, Bhabha Atomic Research Centre Dr. K.S.Dasgupta . . . . . . . . . Director, IIST Dr. V. Adimurthy . . . . . . . . . . Prof., IIST Shri. G.Ravindranath . . . . . . . . Director, IISU Air Marshal S P Singh . . . . . . . AVSM VM Dr. P Venugopalan . . . . . . . . . Director, DRDL Dr. VS Hegde . . . . . . . . . . . MD, ANTRIX Shri. Jophn P Zachariah . . . . . . AD, VSSC Prof. Shyam Chetty . . . . . . . . Director, NAL Shri. V. Ramachandra . . . . . . . Director, LVPO, ISRO HQ Prof. B.N. Reghunandan . . . . . . Department of Aerospace Engineering Dr. Subash Jacob . . . . . . . . . Professor, Centre for Cryogenic Technology Dr. T. Sundararajan . . . . . . . . . Professor, IIT, Madras Shri. V.Srinivasan . . . . . . . . . D D, PRSO, VSSC Shri. R.K. Srinivasan . . . . . . . . Deputy Director, MSA, ISAC Shri. P.A. Krishnamoorthy . . . . . Group Director, APRG Shri. CH Kunhikammaran . . . . . AD, LPSC
Chairman Shri. CH Kunhikammaran . . . . . . . . . . . LPSC
Organising Committee
Members Dr.K.Sivan . . . . . . . . . . . . . . . . . . .VSSC Dr.AK Anilkumar . . . . . . . . . . . . . . . .VSSC Shri.G.Ayyappan . . . . . . . . . . . . . . . .VSSC Shri.John Binoy Joseph . . . . . . . . . . . . ISRO HQ Dr.Anil.B . . . . . . . . . . . . . . . . . . . CET Dr.T.Jayachandran . . . . . . . . . . . . . . .VSSC Dr.N.Ashok Kumar . . . . . . . . . . . . . . .CET Shri.U Balagopalan . . . . . . . . . . . . . . RIE Shri.Vishnu Kartha N.R . . . . . . . . . . . . LPSC Shri.C.Radhakrishnapillai . . . . . . . . . . . .IISU Shri.Prasath M . . . . . . . . . . . . . . . . .VSSC Shri.Suresh Kumar .PT . . . . . . . . . . . . .VSSC Shri.Narayanan G . . . . . . . . . . . . . . .VSSC Shri.Srikanth A . . . . . . . . . . . . . . . . VSSC Dr.VK Janardhanan . . . . . . . . . . . . . . VSSC Shri.Mohankumar L . . . . . . . . . . . . . . VSSC Shri.Pradeep K . . . . . . . . . . . . . . . . VSSC Shri.Baiju Isac . . . . . . . . . . . . . . . . .LPSC Shri.P.Damodaran . . . . . . . . . . . . . . .VSSC Dr.T. John Tharakan . . . . . . . . . . . . . .LPSC Shri.Ganesh Pillai M . . . . . . . . . . . . . .LPSC Smt.AP.Beena . . . . . . . . . . . . . . . . .VSSC Shri.D.Dilip Kumar . . . . . . . . . . . . . . .Airport Authority of India Shri.KS Nandhakumar . . . . . . . . . . . . .IISU Shri.J.Joseph . . . . . . . . . . . . . . . . . VSSC Shri.Ashok Bhushan . . . . . . . . . . . . . .AeSI, HQ Shri.Yatindra Kumar . . . . . . . . . . . . . .AeSI, HQ Organizing Secretary Shri.M.Mohan . . . . . . . . . . . . . . . . . VSSC
Technical Shri./Smt/Dr. PA Krishnamoorthy, VSSC Asok V, VSSC Sunilkumar, LPSC N. Asok Kumar, CET T Jayachandran,VSSC PO Balachandran, VSSC
Sub Committees
MJ Chacko, VSSC Pradeep K , VSSC Praveen Nair, VSSC AK Anilkumar, VSSC
Programme AK Anilkumar, VSSC B Anil, CET Jasperlal C, VSSC Hemachandran.S, IISU Deependran B, VSSC AP Beena, VSSC KS Nandhakumar, IISU Prasath M, VSSC Pradeep .K, IISU
Souvenir & Proceedings SR Vijayamohanakumar, G Sunilkumar,VSSC T John Tharakan, VSSC Sundararajan, VSSC MP Dhanasekaran, VSSC Praveen Nair, VSSC G Narayanan, VSSC
Media & Publicity G.Ayyappan, VSSC D.Dilipkumar, AAI U Balagopal, RIE Ganesh Pillai, LPSC
Registration / Memento / Kit G Narayanan, VSSC P Damodaran, VSSC KR Rekha, LPSC Srikanth A, VSSC Prasath M , VSSC
Sub Committees
Mohankumar L , VSSC
Catering & Refreshments J.Joseph, VSSC PT Sureshkumar, VSSC Abraham Varghese, VSSC AK Sinha, VSSC Baiju Isac, LPSC
Accommodation & Transport VK Janardanan, VSSC Namboodiri,TOMD, VSSC Baiju Isac, LPSC Sudhir S Nair, VSSC R Sivanandan, VSSC
Finance S.Somanath, VSSC PV Venkitakrishnan, LPSC M.Mohan, VSSC G Ayyappan, VSSC PRatnakara Rao, VSSC S.Pandian, VSSC S.Rakesh, VSSC NR Vishnukartha, LPSC C Radhakrishnapillai, IISU CH Kunhikammaran, LPSC
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
AN APPROXIMATE METHOD FOR PREDICTING THE HOTSPOTS IN LARGE AIR COOLED CONTENTS ELECTRONIC SYSTEMS WITH REPEATED UNITS 1.
An Approximate Method for Predicting the Hotspots in Large Air Cooled
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Electronic Systems with Repeated Units ...................................................................................................................... 1 M. Tech, Aerospace Engg. B. Divya, K.M. Srikumar, S. Christopher & Indian Amit Kumar Institute of Technology, Madras Effect of Geometry on Variation of Heat Flux and Drag Chennai for Launch Vehicle .................................................... 2
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B. Divya
Rohan V. Kedare, Abhishek Jain & Dr. Vilas R. KalamkarK.M. Srikumar Scientist, CABS, DRDO Study on Factors Influencing Regenerative Cooling of Semi-Cryogenic Engine ................................................. 3 Bangalore B. Chiranjeevi Phanindra, Rishi Padmanabhan, R.R. Rahul Kumar Hrisheekesh Krishnan & Dr. T. Jayachandran
4. 5. 6.
S. Christopher
Director, CABS, DRDO Bangalore...................................................................... 4 Thermal Propellant Gauging System for Geostationary Spacecraft S.V. Bindagi, Chaitanya B.S, S.G. Barvea, P. Venkat ReddyAmit & R. Shashishekar Kumar Associate Professor Thermal Control Design of Payload Interface in Cartosat-2 Series Spacecraft ................................................ 5 Aerospace Engg. K. Karthikeyan & S.G. Barvea Indian Institute of Technology Madras Application of Miniature Heat Pipes for Thermal ControlChennai of Spacecraft Subsystem Packages ...................... 6 S.S. Manna, A. Mohammed Ali, V.K. Hariharan, G.V.C. Rajan K.V. Govinda, Dinesh Kumar & A.R. Anand
ABSTRACT
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Performance Evaluation of Solid Motor Thermal Protection System Materials ................................................ 7 The active antenna unit N. (AAAU) is an airborne antenna array unit used for airborne Vinay Unnikrishnan, K. Krishnaraj, R.S.array Pugazenthi, Sreenivas
early warning control. Appropriate cooling of electronic components inside AAAU is crucial for L. Aravindakshan Pillaiand & P.A. Krishnamoorthy its effective functioning and hence the mission. This study is taken up to estimate the maximum Development of Plasma Wind Tunnel Facility for Qualification of surface temperatures attained by electronic components during operation of AAAU. The electronic Reentry Thermal Protections Systems .......................................................................................................................... 8 systems such as AAAU have massive structure for which a full simulation of conjugate heat transfer L. Aravindakshan Pillai, N. Sreenivas, K. Krishnaraj, R.S. Pugazenthi (conduction + forced convection) is at present computationally prohibitive, therefore an approximate Vinay Unnikrishnan & P.A. Krishnamoorthy approach is adopted here. This approach involves a combination of detailed flow simulation of the High Resolution and Heat Usinga parametric study of flow and temperature full AAAU forTemperature estimating flow and Transfer pressureMeasurements distribution and Liquid Thermography .......................................................................................................................................... 9 on Crystal individual components with detailed conjugate heat transfer simulations. The information from M.D. Shaukat Ali, along A. Tariqwith & B.K. Gandhiheat transfer analysis can be used to get an estimate on the location the former lumped
10.
and magnitude of hotspots that can occur within the system. Cure Cycle Optimization of A Solid Propellant ....................................................................................................... 10 Jose Paul & K.P. Subhajayan
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Effect of Hydrogen Injection Temperature on Swirl Co-axial Injector Element Combustion Behavior ..................................................................................................................... 11 V. Arun, Sreeram Banerjee, R. Sujithkumar & P.A. Krishnamoorthy The Aeronautical Society of India, Thiruvananthapuram Branch
The Aeronautical Society of India, Thiruvananthapuram Branch
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National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
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Design, Realisation and Qualification of A Conductively Cooled Cryostat for Igniter Cold Soak/Firing Test at Low Temperatures ....................................................................................... 12 12. Design, Realisation and Qualification of A Conductively Cooled Cryostat R. Sujithkumar, Abhishek Kumar, V. Arun & Sreeram Banerjee for Igniter Cold Soak/Firing Test at Low Temperatures ....................................................................................... 12 Heat Transfer Analysis of An Ablative Throat Insert for Liquid Engine with Film Cooling .......................... 13 R. Sujithkumar, Abhishek Kumar, V. Arun & Sreeram Banerjee R. Harikrishnan 13. Heat Transfer Analysis of An Ablative Throat Insert for Liquid Engine with Film Cooling .......................... 13 Impact of Cryo Temperature on Separation Connectors of A Launch Vehicle .............................................. 14 R. Harikrishnan K.S. Lakshmi, P. Anoop, B. Sundar & M.J. Chacko 14. Impact of Cryo Temperature on Separation Connectors of A Launch Vehicle .............................................. 14 Thermal Structural Analysis of A Cryogenic Engine Turbopump Impeller ........................................................ 15 K.S. Lakshmi, P. Anoop, B. Sundar & M.J. Chacko Krishnajith Jayamani, A.K. Asraff, R. Muthukumar, T.M. Phillip 15. Thermal Structural Analysis of A Cryogenic Engine Turbopump Impeller ........................................................ 15 Experimental Investigation on the Convective Heat Transfer from Krishnajith Jayamani, A.K. Asraff, R. Muthukumar, T.M. Phillip A 3D Heated Block Subjected to Impingement Cooling ....................................................................................... 16 16. Experimental Investigation on the Convective Heat Transfer from Ullekh Pandey, Philip George, M. Ram Prabhu, T.V. Radhakrishnan & M.J. Chacko A 3D Heated Block Subjected to Impingement Cooling ....................................................................................... 16 Conjugate Study of A Pyrovalve and Experimental Validation by IR Heating ................................................... 17 Ullekh Pandey, Philip George, M. Ram Prabhu, T.V. Radhakrishnan & M.J. Chacko Suveer Singh, Md Moinuddin Hassan, Ani D. Kurien, H. Kumar 17. Conjugate Study of A Pyrovalve and Experimental Validation by IR Heating ................................................... 17 Dr. A.G. Rajendran, K.P. Subhajayan & C. Jasperlal Suveer Singh, Md Moinuddin Hassan, Ani D. Kurien, H. Kumar Application of GPGPU Programming to Numerical Simulation of Dr. A.G. Rajendran, K.P. Subhajayan & C. Jasperlal Steady-State Heat Conduction Problems ................................................................................................................... 18 18. Application of GPGPU Programming to Numerical Simulation of K. Rakesh, M. Ajith, Dr. T. Jayachandran & Dr. Raju K. George Steady-State Heat Conduction Problems ................................................................................................................... 18 Thermo-Structural Design and Analysis of A Supersonic Diffuser K. Rakesh, M. Ajith, Dr. T. Jayachandran & Dr. Raju K. George for High Temperature Applications ............................................................................................................................. 19 19. Thermo-Structural Design and Analysis of A Supersonic Diffuser Atha Ur Rahman Khan, A. Yezhil Arasu, Thomas Kurian, P.J. Abraham & V. Srinivasan for High Temperature Applications ............................................................................................................................. 19 Thermophysical Properties Measurement of Aerospace Material ...................................................................... 20 Atha Ur Rahman Khan, A. Yezhil Arasu, Thomas Kurian, P.J. Abraham & V. Srinivasan Fazil Mohammad, K.P. Subhajayan, T.P. Shivadasan, S. Krishnamoorthy 20. Thermophysical Properties Measurement of Aerospace Material ...................................................................... 20 C. Jasperlal, P.O. Balachandran & P.A. Krishnamoorthy Fazil Mohammad, K.P. Subhajayan, T.P. Shivadasan, S. Krishnamoorthy Solid Rocket Booster Flex Seal Moulding â&#x20AC;&#x201C; Cure Cycle Estimation ................................................................... 21 C. Jasperlal, P.O. Balachandran & P.A. Krishnamoorthy Jose Paul, S. Kartheekeyan, V. Mahesh, K.P. Subhajayan, V. Eswaran & V. Srinivasan 21. Solid Rocket Booster Flex Seal Moulding â&#x20AC;&#x201C; Cure Cycle Estimation ................................................................... 21 High Temperature Storage Heater Design for Propulsion Facility ..................................................................... 22 Jose Paul, S. Kartheekeyan, V. Mahesh, K.P. Subhajayan, V. Eswaran & V. Srinivasan Samik Jash, Jose Paul, Praveen Kumar, C. Jasperlal, Dr. T. Jayachandran 22. High Temperature Storage Heater Design for Propulsion Facility ..................................................................... 22 P.O. Balachandran & P.A. Krishnamoorthy Samik Jash, Jose Paul, Praveen Kumar, C. Jasperlal, Dr. T. Jayachandran Performance Evaluation of Thermal Control System of A Typical Manned Spacecraft ................................. 23 P.O. Balachandran & P.A. Krishnamoorthy Samik Jash, C. Pedda Peeraiah, Dr. T. Jayachandran & P.A. Krishnamoorthy 23. Performance Evaluation of Thermal Control System of A Typical Manned Spacecraft ................................. 23 Samik Jash, C. Pedda Peeraiah, Dr. T. Jayachandran & P.A. Krishnamoorthy The Aeronautical Society of India, Thiruvananthapuram Branch The Aeronautical Society of India, Thiruvananthapuram Branch
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
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AN APPROXIMATE METHOD FOR PREDICTING Experimental Studies for Estimating Heat Flux Due to IN LARGE AIR COOLED THE HOTSPOTS Twin-Nozzle Plume Interaction and Impingement .................................................................................................. 24 ELECTRONIC SYSTEMS WITH REPEATED UNITS P. Sridharan, K. Krishnaraj, C. Jasperlal & P.A. Krishnamoorthy Experimental Studies on Supersonic Film Cooling Effectiveness for Large Area Ratio Nozzles ................. 25 B. Divya M. Tech, Aerospace Engg. K. Krishnaraj, R. Sujith Kumar, P. Sridharan, C. Jasperlal & P.A. Krishnamoorthy Indian Institute of Technology, Madras Aero Thermo Structural Analysis of A Sub-Scale Model of Cryogenic Nozzle ............................................... 26 Chennai Vinay Kumar Srivastava, Shailesh Prasad, K. Jagannathan & Dr. S.B. Tiwari
K.M. Srikumar
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Scientist, CABS, DRDO Heat Flux Distribution on A Hypersonic Air Intake ............................................................................................... 27 Bangalore R. Saravanan, J.A. Tennyson, S. Gnanasekar & S. Subramanian
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Advanced Designs of Regenerative Cooling for High Heat Flux Liquid Engines Director, CABS, DRDO for Improved Engine Life Cycle .................................................................................................................................... 28 Bangalore A.P. Baiju, G. Remesh, Dr. V. Narayanan & C.H. Kunhikammaran
S. Christopher Amit Kumar
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Associate Professor Electron Density Computations for Langmuir Probe under Plasma Flow Conditions .................................. 29 Engg. N. Uday Bhaskar, C. Unnikrishnan & L. AravindakshanAerospace Pillai Indian Institute of Technology Madras Innovative Thermal Distortion Management Technique for Very High Power (260W) Chennai Narrow Band - Wave Guide Band Pass Filters for Space Use .............................................................................. 30 K. Karthik, Rajnikant & A.V. Pathak
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ABSTRACT
Testing and Evaluation of Thermal Protection System Materials under
The active antenna array unit (AAAU) is an airborne antenna array unit used31for airborne Simulated Re-Entry Thermal Environments ............................................................................................................... early warning and control. Appropriate of electronic components inside AAAU is crucial for N. Sreenivas, K. Krishnaraj, L. Aravindakshan Pillai & cooling P.A. Krishnamoorthy 32.
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its effective functioning and hence the mission. This study is taken up to estimate the maximum Experimental Verification of Effectiveness of Spray Cooling System .................................................................. 32 surface temperatures attained by electronic components during operation of AAAU. The electronic Jose Paul, K.P. Subhajayan, C. Jasperlal & P.O. Balachandran systems such as AAAU have massive structure for which a full simulation of conjugate heat transfer Transient Performance of Cross-Flow Plate-Fin Heat Exchangers for HSP Mission ...................................... (conduction + forced convection) is at present computationally prohibitive, therefore an33approximate approach is adopted here. This approach involves a combination of detailed flow simulation of the N. Mansu & P.O. Balachandran full AAAU for estimating flow and pressure distribution and a parametric study of flow and temperature on individual components with detailed conjugate heat transfer simulations. The information from the former along with lumped heat transfer analysis can be used to get an estimate on the location and magnitude of hotspots that can occur within the system.
The Aeronautical Society of India, Thiruvananthapuram Branch The Aeronautical Society of India, Thiruvananthapuram Branch
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National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
AN APPROXIMATE METHOD FOR PREDICTING THE HOTSPOTS IN LARGE AIR COOLED AN APPROXIMATE METHOD FOR PREDICTING ELECTRONIC SYSTEMS WITH THE HOTSPOTS IN LARGE AIR REPEATED COOLED UNITS ELECTRONIC SYSTEMS WITH REPEATED UNITS B. Divya M. Tech, Aerospace Engg. Divya of Technology, Madras IndianB. Institute M. Tech, Aerospace Engg. Chennai Indian Institute of Technology, Madras K.M. Srikumar Chennai Scientist, CABS, DRDO
K.M. Srikumar Bangalore
Scientist, CABS, DRDO S. Christopher Bangalore Director, CABS, DRDO
S. Christopher Bangalore
Director, CABS, DRDO Amit Kumar Bangalore Associate Professor
Amit Kumar Aerospace Engg.
Associate Professor Indian Institute of Technology Madras Aerospace Engg. Chennai Indian Institute of Technology Madras Chennai
ABSTRACT
The active antenna array ABSTRACT unit (AAAU) is an airborne antenna array unit used for airborne early warning and control. Appropriate cooling of electronic components inside AAAU is crucial for The active antenna array and unit hence (AAAU)the is mission. an airborne used for airborne its effective functioning Thisantenna study isarray takenunit up to estimate the maximum early warning and control. Appropriate cooling of electronic components inside AAAU is crucial surface temperatures attained by electronic components during operation of AAAU. Thefor electronic its effective functioning and hence the mission. This study is taken up to estimate the maximum systems such as AAAU have massive structure for which a full simulation of conjugate heat transfer surface temperatures by electronic during operation of AAAU.therefore The electronic (conduction + attained forced convection) is atcomponents present computationally prohibitive, an approximate systems such as AAAU have massive structure for which a full simulation of conjugate heat transfer approach is adopted here. This approach involves a combination of detailed flow simulation of the (conduction + forced is atand present computationally prohibitive, therefore approximate full AAAU forconvection) estimating flow pressure distribution and a parametric study an of flow and temperature approachonis individual adopted here. This approach involves a combination of detailed flow simulation of the components with detailed conjugate heat transfer simulations. The information from full AAAUthe for former estimating flow and pressure distribution and a parametric study of flow and temperature along with lumped heat transfer analysis can be used to get an estimate on the location on individual components detailed transfer simulations. The information from and magnitude of with hotspots that conjugate can occur heat within the system. the former along with lumped heat transfer analysis can be used to get an estimate on the location and magnitude of hotspots that can occur within the system.
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The Aeronautical Society of India, Thiruvananthapuram Branch The Aeronautical Society of India, Thiruvananthapuram Branch
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National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
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Design, Realisation and Qualification of A Conductively Cooled Cryostat for Igniter Cold Soak/Firing Test at Low Temperatures ....................................................................................... 12
EFFECT OF GEOMETRY ON VARIATION OF Heat Transfer Analysis ofFLUX An AblativeAND Throat Insert for LiquidFOR Engine with Film Cooling .......................... 13 HEAT DRAG LAUNCH VEHICLE
R. Sujithkumar, Abhishek Kumar, V. Arun & Sreeram Banerjee 13.
R. Harikrishnan
Rohan V. Kedare
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Impact of Cryo Temperature on Separation Connectors of A Launch Vehicle .............................................. 14 Post-Graduate Student, SPCE K.S. Lakshmi, P. Anoop, B. Sundar & M.J. Chacko Mumbai, Maharashtra
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Thermal Structural Analysis of A Cryogenic Engine Turbopump Abhishek Impeller Jain ........................................................ 15
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Numerix Pvt. Ltd. Krishnajith Jayamani, A.K. Asraff, R. Muthukumar, Zeus T.M. Phillip Mumbai, Maharashtra Experimental Investigation on the Convective Heat Transfer from
Dr. Vilas R. Kalamkar
A 3D Heated Block Subjected to Impingement Cooling ....................................................................................... 16 Associate Professor, SPCE Ullekh Pandey, Philip George, M. Ram Prabhu, T.V. Radhakrishnan & M.J. Chacko Mumbai, Maharashtra 17.
Conjugate Study of A Pyrovalve and Experimental Validation by IR Heating ................................................... 17
ABSTRACT
Suveer Singh, Md Moinuddin Hassan, Ani D. Kurien, H. Kumar Dr. A.G. Rajendran, K.P. Subhajayan & C. Jasperlal 18.
19.
objective of the to project wasSimulation to numerically simulate the flow over a launch vehicle Application The of GPGPU Programming Numerical of without fins and to estimate drag coefficient and heat flux on surface. Studies have been made to Steady-State Heat Conduction Problems ................................................................................................................... 18 investigate the effect of different nose radius on heat flux and drag coefficient at Mach 8 and flight K. Rakesh, M. Ajith, Dr. T. Jayachandran & Dr. Raju K. George altitude of 20km. A commercial code CFDExpertâ&#x201E;˘ was used to carry out simulation. To gain confidence Thermo-Structural and Analysis A Supersonic Diffuser out on standard hyper-ballistic model (HB-2). in simulation,Design validation studiesof have been carried for Results High Temperature 19 radius and have beenApplications tabulated............................................................................................................................. for variation of heat flux and drag due to change in nose Athablend Ur Rahman Khan, A. Yezhil Arasu, Thomas Kurian, P.J. Abraham & V. Srinivasan surface shape.
20.
Thermophysical Properties Measurement of Aerospace Material ...................................................................... 20 Fazil Mohammad, K.P. Subhajayan, T.P. Shivadasan, S. Krishnamoorthy C. Jasperlal, P.O. Balachandran & P.A. Krishnamoorthy
21.
Solid Rocket Booster Flex Seal Moulding â&#x20AC;&#x201C; Cure Cycle Estimation ................................................................... 21 Jose Paul, S. Kartheekeyan, V. Mahesh, K.P. Subhajayan, V. Eswaran & V. Srinivasan
22.
High Temperature Storage Heater Design for Propulsion Facility ..................................................................... 22 Samik Jash, Jose Paul, Praveen Kumar, C. Jasperlal, Dr. T. Jayachandran P.O. Balachandran & P.A. Krishnamoorthy
23.
Performance Evaluation of Thermal Control System of A Typical Manned Spacecraft ................................. 23 Samik Jash, C. Pedda Peeraiah, Dr. T. Jayachandran & P.A. Krishnamoorthy
The Aeronautical Society of India, Thiruvananthapuram Branch
2
The Aeronautical Society of India, Thiruvananthapuram Branch
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
AN APPROXIMATE METHOD FOR PREDICTING HOTSPOTS IN LARGEREGENERATIVE AIR COOLED STUDY ONTHE FACTORS INFLUENCING ELECTRONIC SYSTEMS WITH REPEATED COOLING OF SEMI-CRYOGENIC ENGINE UNITS B. Divya R.R. Rahul Kumar B. Chiranjeevi Phanindra, Rishi Padmanabhan, M. Tech, Engg. Hrisheekesh Krishnan & Dr.Aerospace T. Jayachandran Indian Institute of Technology, Madras Vikram Sarabhai Space Centre Chennai Thiruvananthapuram
K.M. Srikumar
Scientist, CABS, DRDO
ABSTRACT Bangalore
S. Christopher
Optimization of regenerative coolant channels for liquid engines is a very involved problem Director, CABS, DRDO which requires deciding on a number of parameters such as number of cooling channels, channel Bangalore aspect ratio (AR), helical angles needed etc. Usually mass flow rate, allowable pressure drop, Amit Kumar maximum allowable temperature and manufacturability put severe constraints on the designer. In Associate Professor the present study a CFD analysis is carried out to understand how various factors such as curvature, Aerospace Engg. aspect ratio, mass flow rate and flow routing hydrodynamic and thermal behavior in Indian influences Institute ofthe Technology Madras regeneratively cooled semi-cryogenic engine. A portion of a typical semi cryogenic engine profile Chennai has been adopted for the study and numerical simulations are carried out using FLUENT 速. The secondary motions in cooling channel curvatures, reported as Dean vortices in literature, are observed. ABSTRACT Studies carried out using varying aspect ratios suggest an optimum value for the selected contour, beyond which pressure drop penalty becomes large. Influence of varying mass flow rate was studied The active antenna array unit (AAAU) is an airborne antenna array unit used for airborne to simulate the conditions of up-rating or down-rating of the engine. A case with constant heat flux early warning and control. Appropriate cooling of electronic components inside AAAU is crucial for at the bottom wall is also simulated and the effect of thermal stratification and mixing due to its effective functioning and hence the mission. This study is taken up to estimate the maximum secondary flow are visualized. Tangential velocity vectors plotted along with radial temperature surface temperatures attained by electronic components during operation of AAAU. The electronic distribution verifies the effect of the secondary flow fields on heat transfer. Even though their systems such as AAAU have massive structure for which a full simulation of conjugate heat transfer magnitude is small compared to axial velocity, their effects on the wall temperature are pronounced. (conduction + forced convection) is at present computationally prohibitive, therefore an approximate approach is adopted here. This approach involves a combination of detailed flow simulation of the full AAAU for estimating flow and pressure distribution and a parametric study of flow and temperature on individual components with detailed conjugate heat transfer simulations. The information from the former along with lumped heat transfer analysis can be used to get an estimate on the location and magnitude of hotspots that can occur within the system.
1
The Aeronautical Society of India, Thiruvananthapuram Branch The Aeronautical Society of India, Thiruvananthapuram Branch
3
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
12.
Design, Realisation and Qualification of A Conductively Cooled Cryostat for Igniter Cold Soak/Firing Test at Low Temperatures ....................................................................................... 12
THERMAL PROPELLANT GAUGING SYSTEM Heat Transfer Analysis FOR of An Ablative Throat Insert for Liquid Engine with Film Cooling .......................... 13 GEOSTATIONARY SPACECRAFT
R. Sujithkumar, Abhishek Kumar, V. Arun & Sreeram Banerjee 13.
R. Harikrishnan
S.V. Bindagi, Chaitanya B.S. & S.G. Barvea
14.
Impact of Cryo Temperature on Separation Connectors of A Launch Vehicle .............................................. 14 ISRO Satellite Centre K.S. Lakshmi, P. Anoop, B. Sundar & M.J. Chacko Bangalore
15.
Thermal Structural Analysis of A Cryogenic Engine Turbopump Impeller ........................................................ 15
16.
Krishnajith Jayamani, A.K. Asraff, R. Muthukumar, Liquid T.M. Phillip Propulsion Centre Bangalore Experimental Investigation on the Convective Heat Transfer from
P. Venkat Reddy & R. Shashishekar
A 3D Heated Block Subjected to Impingement Cooling ....................................................................................... 16
ABSTRACT
Ullekh Pandey, Philip George, M. Ram Prabhu, T.V. Radhakrishnan & M.J. Chacko 17.
18.
Conjugate Study of A Pyrovalve and Experimental Validation by IR Heating ................................................... 17 The knowledge of remaining propellant in a communication satellite especially at the end of Suveer Singh, Md Moinuddin Hassan, Ani D. Kurien, H. Kumar life is very essential for operational planning. Thermal propellant gauging system (TPGS) is a technique Dr. A.G. Rajendran, K.P. Subhajayan & C. Jasperlal by which the propellant available in the spacecraft is ascertained. During first phase of development, Application GPGPU Programming to Numerical Simulation of of the TPGS using water in place of propellant several of ground tests were conducted on the test model Steady-State HeatasConduction Problems and helium a pressurant. The ................................................................................................................... mathematical model was validated in these tests. In 18 the 2nd phase
19.
20.
of development, is the main matter of this paper, it is planned to conduct the ground K. Rakesh, M. Ajith, Dr. T.which Jayachandran & Dr. subject Raju K. George experiments using actual propellants such as MON3 and MMH for further validation of mathematical Thermo-Structural Design and Analysis of A Supersonic Diffuser model. This paper presents detailed analyses for two fill fractions for both of the propellants, using for High Temperature Applications ............................................................................................................................. 19 the mathematical model that was validated in the 1st phase. Also, the change in thermal response Atha Ur Rahman Khan, A. Yezhil Arasu, Thomas Kurian, P.J. Abraham & V. Srinivasan from ground to space is compared. Importance of liquid gas interface under micro 'g' is emphasized. This paper also gives the predictedofthermal response the ground tests to be conducted Thermophysical Properties Measurement Aerospace Material for ...................................................................... 20 with MMH MON3. K.P. Subhajayan, T.P. Shivadasan, S. Krishnamoorthy Faziland Mohammad, C. Jasperlal, P.O. Balachandran & P.A. Krishnamoorthy
21.
Solid Rocket Booster Flex Seal Moulding â&#x20AC;&#x201C; Cure Cycle Estimation ................................................................... 21 Jose Paul, S. Kartheekeyan, V. Mahesh, K.P. Subhajayan, V. Eswaran & V. Srinivasan
22.
High Temperature Storage Heater Design for Propulsion Facility ..................................................................... 22 Samik Jash, Jose Paul, Praveen Kumar, C. Jasperlal, Dr. T. Jayachandran P.O. Balachandran & P.A. Krishnamoorthy
23.
Performance Evaluation of Thermal Control System of A Typical Manned Spacecraft ................................. 23 Samik Jash, C. Pedda Peeraiah, Dr. T. Jayachandran & P.A. Krishnamoorthy
The Aeronautical Society of India, Thiruvananthapuram Branch
4
The Aeronautical Society of India, Thiruvananthapuram Branch
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
AN APPROXIMATE METHOD FOR PREDICTING THE CONTROL HOTSPOTSDESIGN IN LARGE COOLED THERMAL OF AIR PAYLOAD ELECTRONIC SYSTEMS SERIES WITH REPEATED UNITS INTERFACE IN CARTOSAT-2 SPACECRAFT B. Divya K. Karthikeyan & S.G. Barvea
M. Tech,Centre Aerospace Engg. ISRO Satellite IndianBangalore Institute of Technology, Madras Chennai
K.M. Srikumar
ABSTRACT Scientist, CABS, DRDO Bangalore CARTOSAT-2A/2B is an advanced Indian Remote Sensing satellite for providing multi-spot S. Christopher scene-specific high resolution imageries in the panchromatic band. It is placed in 630 km nearly Director, CABS, DRDO 0 and equatorial crossing time of 09:30 hours. circular Sun-synchronous orbit with inclination of 97.9Bangalore The camera provides across track resolution of 1 m by optical design and about 1 m along track Amit Kumar resolution by step and stare technique with virtual velocity reduction mode. This calls for high agility Associate Professor to steer along and across the track, which imposes a constraint Aerospace Engg.of low mass and low moment of inertia for the spacecraft. Hence, the satellite is hexagonal shaped with fixed solar panels, with the Indian Institute of Technology Madras payload centrally located and the spacecraft bus built around Chennaithe payload. The payload temperature has to be maintained close to 200C with stringent gradient requirements. Because of the centrally located payload, the bulk temperature of the spacecraft bus must be maintained below 20 0C from ABSTRACT thermal point of view. In addition, the spacecraft is Sun-oriented in view of fixed solar panels. The payload is mounted onto the interface ring of the Spacecraft using titanium tabs. The diameter of The active antenna array unit (AAAU) is an airborne antenna array unit used for airborne the interface ring is close to 1 m with half the portion exposed to Sun load and remaining portion early warning and control. Appropriate cooling of electronic components inside AAAU is crucial for seeing deep space. This will cause large temperature gradients in the interface ring. In order to its effective functioning and hence the mission. This study is taken up to estimate the maximum have accurate focusing, the temperature gradient in the interface ring should be less than 20C. This surface temperatures attained by electronic components during operation of AAAU. The electronic stringent temperature specification for the payload interface, i.e. the interface ring poses a challenge systems such as AAAU have massive structure for which a full simulation of conjugate heat transfer to the Thermal design. This paper detail the thermal design and In-orbit performance of Payload (conduction + forced convection) is at present computationally prohibitive, therefore an approximate interface of Cartosat-2/2A/2B spacecraft and the corresponding performance. approach is adopted here. This approach involves a combination of detailed flow simulation of the full AAAU for estimating flow and pressure distribution and a parametric study of flow and temperature on individual components with detailed conjugate heat transfer simulations. The information from the former along with lumped heat transfer analysis can be used to get an estimate on the location and magnitude of hotspots that can occur within the system.
1
The Aeronautical Society of India, Thiruvananthapuram Branch The Aeronautical Society of India, Thiruvananthapuram Branch
5
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
12.
Design, Realisation and Qualification of A Conductively Cooled Cryostat for Igniter Cold Soak/Firing Test at Low Temperatures ....................................................................................... 12
13.
APPLICATION OF MINIATURE HEAT PIPES Heat Transfer Analysis Ablative Throat Insert for Liquid Engine with Cooling .......................... 13 FORof An THERMAL CONTROL OFFilmSPACECRAFT R. Harikrishnan SUBSYSTEM PACKAGES
14.
Impact of Cryo Temperature on Separation Connectors of A Launch Vehicle .............................................. 14
15.
Manna, A. Mohammed K.S. Lakshmi,S.S. P. Anoop, B. Sundar & M.J. Chacko Ali, V.K. Hariharan, G.V.C. Rajan & K.V. Govinda Systems Integration Group Thermal Structural Analysis of A Cryogenic Engine Turbopump Impeller ........................................................ 15 ISRO Satellite Centre, Bangalore Krishnajith Jayamani, A.K. Asraff, R. Muthukumar, T.M. Phillip
R. Sujithkumar, Abhishek Kumar, V. Arun & Sreeram Banerjee
Dinesh Kumar & A.R. Anand
16.
Experimental Investigation on the Convective Heat Transfer from Thermal Systems Group A 3D Heated Block Subjected to Impingement ....................................................................................... 16 ISROCooling Satellite Centre, Bangalore Ullekh Pandey, Philip George, M. Ram Prabhu, T.V. Radhakrishnan & M.J. Chacko
17.
Conjugate Study of A Pyrovalve and Experimental Validation by IR Heating ................................................... 17
ABSTRACT
Suveer Singh, Md Moinuddin Hassan, Ani D. Kurien, H. Kumar
The design of mechanical housing for electronic packages has undergone numerous Dr. A.G. Rajendran, K.P. Subhajayan & C. Jasperlal 18.
19.
developments to resolve various types of thermal issues faced in space application. Direct heat Application of GPGPU Programming to Numerical Simulation of conduction to the mounting interface of the spacecraft deck or providing the integral heat-sink Steady-State Heat Conduction Problems ................................................................................................................... 18 have so far become the conventional techniques used in maintaining the temperature of electronic K. Rakesh, M. Ajith, Dr. T. Jayachandran & Dr. Raju K. George components [1]. These methods can no more be profitable and advisable with increased heat flux Thermo-Structural Design heat-fluxes and Analysis ofcan A Supersonic density. The higher result in Diffuser increase of local temperature above the permissible and ultimately lead to failure of the electronic devices. To tackle this problem a Miniature Heat for limit High Temperature Applications ............................................................................................................................. 19 (MHP) Khan, of outer diameter 5 mmKurian, with P.J. suitable mounting flange has been proposed for use in AthaPipe Ur Rahman A. Yezhil Arasu, Thomas Abraham & V. Srinivasan
20.
mechanical housing to simulate the thermal performance of the overall package. This can efficiently Thermophysical Properties Measurement of Aerospace Material ...................................................................... 20 transport the heat from the hot spots to the base of the package to achieve good performance of Fazil Mohammad, K.P. Subhajayan, T.P. Shivadasan, S. Krishnamoorthy electronic components placed within the mechanical housings to meet the design requirement. By C. Jasperlal, P.O. Balachandran & P.A. Krishnamoorthy simulating the varying thermal loads at the source end, the temperature variations at different
21.
parts of the mechanical housing â&#x20AC;&#x201C;have and compared with the conventional Solid Rocket Booster Flex Seal Moulding Curebeen Cyclestudied Estimation ................................................................... 21 methods. presentsV.the details the experimental work carried out on these aspects. JoseThis Paul, paper S. Kartheekeyan, Mahesh, K.P.of Subhajayan, V. Eswaran & V. Srinivasan
22.
High Temperature Storage Heater Design for Propulsion Facility ..................................................................... 22 Samik Jash, Jose Paul, Praveen Kumar, C. Jasperlal, Dr. T. Jayachandran P.O. Balachandran & P.A. Krishnamoorthy
23.
Performance Evaluation of Thermal Control System of A Typical Manned Spacecraft ................................. 23 Samik Jash, C. Pedda Peeraiah, Dr. T. Jayachandran & P.A. Krishnamoorthy
The Aeronautical Society of India, Thiruvananthapuram Branch
6
The Aeronautical Society of India, Thiruvananthapuram Branch
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
AN APPROXIMATE METHOD FOR PREDICTING THE HOTSPOTS IN LARGE AIR COOLED PERFORMANCE EVALUATION OF SOLID MOTOR ELECTRONIC SYSTEMS WITH REPEATED THERMAL PROTECTION SYSTEM MATERIALSUNITS B. Divya Vinay Unnikrishnan, K. Krishnaraj, R.S. Pugazenthi M. Tech, Aerospace Engg. N. Sreenivas, L. Aravindakshan Pillai & P.A. Krishnamoorthy Indian Institute of Technology, Madras Vikram Sarabhai Space Centre Chennai Thiruvananthapuram
K.M. Srikumar
Scientist, CABS, DRDO
ABSTRACT Bangalore
S. Christopher
Identifying candidate Thermal Protection System (TPS) materials, its validation, optimization Director, CABS, DRDO and flight qualification require ground based test facilities which can closely reproduce the thermal Bangalore regimes encountered in launch vehicle propulsion systems. Arc heated facilities are extensively used Amit Kumar world over for the ground based simulation of thermal regimes. TPS materials are then qualified Associate Professor using subscale motors before its use in the actual motor. The 50 kW Arc Jet facility was established Aerospace Engg. in VSSC to cater to the needs of TPS testing qualification. The facility Indianand Institute of Technology Madrascan replicate heat flux conditions prevalent in launch vehicle propulsion systems on a specimen level. Comparative thermal Chennai performance evaluation of materials is carried out by measuring parameters like erosion rate, heat of ablation, char depths, temperature response etc. Subsequently subscale motor tests are conducted ABSTRACT to qualify TPS materials under actual rocket motor operating conditions. This paper describes test facilities, simulation capabilities, test schemes, typical tests conducted for the development of The active antenna array unit (AAAU) is an airborne antenna array unit used for airborne efficient TPS systems for solid propulsion motors used in ISRO's launch vehicles. early warning and control. Appropriate cooling of electronic components inside AAAU is crucial for its effective functioning and hence the mission. This study is taken up to estimate the maximum surface temperatures attained by electronic components during operation of AAAU. The electronic systems such as AAAU have massive structure for which a full simulation of conjugate heat transfer (conduction + forced convection) is at present computationally prohibitive, therefore an approximate approach is adopted here. This approach involves a combination of detailed flow simulation of the full AAAU for estimating flow and pressure distribution and a parametric study of flow and temperature on individual components with detailed conjugate heat transfer simulations. The information from the former along with lumped heat transfer analysis can be used to get an estimate on the location and magnitude of hotspots that can occur within the system.
1
The Aeronautical Society of India, Thiruvananthapuram Branch The Aeronautical Society of India, Thiruvananthapuram Branch
7
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
12.
Design, Realisation and Qualification of A Conductively Cooled Cryostat for Igniter Cold Soak/Firing Test at Low Temperatures ....................................................................................... 12
13.
DEVELOPMENT OF PLASMA WIND TUNNEL Heat TransferFACILITY Analysis of An Ablative Throat QUALIFICATION Insert for Liquid Engine with Film Cooling 13 FOR OF .......................... REENTRY R. Harikrishnan THERMAL PROTECTION SYSTEMS
14.
Impact of Cryo Temperature on Separation Connectors of A Launch Vehicle .............................................. 14
R. Sujithkumar, Abhishek Kumar, V. Arun & Sreeram Banerjee
L. Aravindakshan K.S. Lakshmi, P. Anoop, B. Sundar & M.J. Chacko
Pillai, N. Sreenivas, K. Krishnaraj R.S. Pugazenthi, Vinay Unnikrishnan & P.A. Krishnamoorthy
15.
Thermal Structural Analysis of A Cryogenic Engine Turbopump Impeller ........................................................ 15 Vikram Sarabhai Space Centre Krishnajith Jayamani, A.K. Asraff, R. Muthukumar, T.M. Phillip Thiruvananthapuram
16.
Experimental Investigation on the Convective Heat Transfer from
ABSTRACT
A 3D Heated Block Subjected to Impingement Cooling ....................................................................................... 16 Ullekh Pandey, Philip George, M. Ram Prabhu, T.V. Radhakrishnan & M.J. Chacko 17.
18.
Qualification of reentry thermalValidation protection warrants Plasma Wind17Tunnels for Conjugate Study of A Pyrovalve and Experimental by IR systems Heating ................................................... simulating thermal environments. Through a dedicated R&D effort, a 6 MW Plasma Wind Tunnel Suveer Singh, Md Moinuddin Hassan, Ani D. Kurien, H. Kumar (PWT) was established indigenously and all facility characterization tests carried out for the system Dr. A.G. Rajendran, K.P. Subhajayan & C. Jasperlal level qualification of reentry TPS used in ISRO's reentry missions. This paper presents the facility Application of GPGPU Programming Numerical of details and its capabilities forto carrying outSimulation reentry simulation testing. From the performance studies Steady-State Conduction Problems ................................................................................................................... 18 and test Heat results, it is concluded that the facility can support all the testing requirements for our K. Rakesh, M. Ajith, Dr. T. missions. Jayachandran & Dr. Raju K. George futuristic reentry
19.
Thermo-Structural Design and Analysis of A Supersonic Diffuser for High Temperature Applications ............................................................................................................................. 19 Atha Ur Rahman Khan, A. Yezhil Arasu, Thomas Kurian, P.J. Abraham & V. Srinivasan
20.
Thermophysical Properties Measurement of Aerospace Material ...................................................................... 20 Fazil Mohammad, K.P. Subhajayan, T.P. Shivadasan, S. Krishnamoorthy C. Jasperlal, P.O. Balachandran & P.A. Krishnamoorthy
21.
Solid Rocket Booster Flex Seal Moulding â&#x20AC;&#x201C; Cure Cycle Estimation ................................................................... 21 Jose Paul, S. Kartheekeyan, V. Mahesh, K.P. Subhajayan, V. Eswaran & V. Srinivasan
22.
High Temperature Storage Heater Design for Propulsion Facility ..................................................................... 22 Samik Jash, Jose Paul, Praveen Kumar, C. Jasperlal, Dr. T. Jayachandran P.O. Balachandran & P.A. Krishnamoorthy
23.
Performance Evaluation of Thermal Control System of A Typical Manned Spacecraft ................................. 23 Samik Jash, C. Pedda Peeraiah, Dr. T. Jayachandran & P.A. Krishnamoorthy
The Aeronautical Society of India, Thiruvananthapuram Branch
8
The Aeronautical Society of India, Thiruvananthapuram Branch
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
AN APPROXIMATE METHOD FOR PREDICTING HOTSPOTSTEMPERATURE IN LARGE AIR AND COOLED HIGHTHE RESOLUTION ELECTRONIC SYSTEMS WITH REPEATED HEAT TRANSFER MEASUREMENTS USING UNITS LIQUID CRYSTAL THERMOGRAPHY B. Divya M. Tech, Aerospace Engg. M.D. Shaukat Ali,Institute A. Tariqof&Technology, B.K. Gandhi Indian Madras Mechanical and Industrial Engineering Department Chennai IIT Roorkee, K.M. Uttarakhand Srikumar Scientist, CABS, DRDO Bangalore ABSTRACT
S. Christopher
CABS, Liquid crystal thermography (LCT) hasDirector, been used forDRDO the mapping of full-field surface temperatures with high temporal as well as spatialBangalore resolution. The surface temperature of the Amit liquid Kumar heating section has been sequentially captured by using crystal sheets along with the 3-CCD Associate Professor camera supported imaging system. This time dependent temperature change has been used to Engg.of the semi-infinite solid exposed calculate the heat transfer coefficient distributionAerospace on the surface Indian Institute of Technology Madras to surface convection. Chennai
ABSTRACT The active antenna array unit (AAAU) is an airborne antenna array unit used for airborne early warning and control. Appropriate cooling of electronic components inside AAAU is crucial for its effective functioning and hence the mission. This study is taken up to estimate the maximum surface temperatures attained by electronic components during operation of AAAU. The electronic systems such as AAAU have massive structure for which a full simulation of conjugate heat transfer (conduction + forced convection) is at present computationally prohibitive, therefore an approximate approach is adopted here. This approach involves a combination of detailed flow simulation of the full AAAU for estimating flow and pressure distribution and a parametric study of flow and temperature on individual components with detailed conjugate heat transfer simulations. The information from the former along with lumped heat transfer analysis can be used to get an estimate on the location and magnitude of hotspots that can occur within the system.
1
The Aeronautical Society of India, Thiruvananthapuram Branch The Aeronautical Society of India, Thiruvananthapuram Branch
9
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
12.
Design, Realisation and Qualification of A Conductively Cooled Cryostat for Igniter Cold Soak/Firing Test at Low Temperatures ....................................................................................... 12
CURE CYCLE OPTIMIZATION OF Heat Transfer Analysis of An AblativeA Throat Insert for Liquid Engine with Film Cooling .......................... 13 SOLID PROPELLANT
R. Sujithkumar, Abhishek Kumar, V. Arun & Sreeram Banerjee 13.
R. Harikrishnan
Jose Paul & K.P. Subhajayan
14.
Impact of Cryo Temperature on Separation Connectors of A Launch Vehicle .............................................. 14 Vikram Sarabhai Space Centre K.S. Lakshmi, P. Anoop, B. Sundar & M.J. Chacko Thiruvananthapuram
15.
Thermal Structural Analysis of A Cryogenic Engine Turbopump Impeller ........................................................ 15
ABSTRACT
Krishnajith Jayamani, A.K. Asraff, R. Muthukumar, T.M. Phillip 16.
17.
Experimental Investigation on the Convective Heat Transfer from Solid aretonormally cured at elevated temperature. The cure cycle 16 consists of a A 3D Heated Blockmotors Subjected Impingement Cooling .......................................................................................
heating dwell phase a cooling phase. The cure cycle is finalized based on heat transfer Ullekh Pandey,phase Philip George, M. Ramand Prabhu, T.V. Radhakrishnan & M.J. Chacko analysis of the system. This paper gives the details of experimental verification of the analysis using Conjugate of A Pyrovalve and Experimental Validation in-situ Study temperature measurements during curing.by IR Heating ................................................... 17 Suveer Singh, Md Moinuddin Hassan, Ani D. Kurien, H. Kumar Dr. A.G. Rajendran, K.P. Subhajayan & C. Jasperlal
18.
Application of GPGPU Programming to Numerical Simulation of Steady-State Heat Conduction Problems ................................................................................................................... 18 K. Rakesh, M. Ajith, Dr. T. Jayachandran & Dr. Raju K. George
19.
Thermo-Structural Design and Analysis of A Supersonic Diffuser for High Temperature Applications ............................................................................................................................. 19 Atha Ur Rahman Khan, A. Yezhil Arasu, Thomas Kurian, P.J. Abraham & V. Srinivasan
20.
Thermophysical Properties Measurement of Aerospace Material ...................................................................... 20 Fazil Mohammad, K.P. Subhajayan, T.P. Shivadasan, S. Krishnamoorthy C. Jasperlal, P.O. Balachandran & P.A. Krishnamoorthy
21.
Solid Rocket Booster Flex Seal Moulding â&#x20AC;&#x201C; Cure Cycle Estimation ................................................................... 21 Jose Paul, S. Kartheekeyan, V. Mahesh, K.P. Subhajayan, V. Eswaran & V. Srinivasan
22.
High Temperature Storage Heater Design for Propulsion Facility ..................................................................... 22 Samik Jash, Jose Paul, Praveen Kumar, C. Jasperlal, Dr. T. Jayachandran P.O. Balachandran & P.A. Krishnamoorthy
23.
Performance Evaluation of Thermal Control System of A Typical Manned Spacecraft ................................. 23 Samik Jash, C. Pedda Peeraiah, Dr. T. Jayachandran & P.A. Krishnamoorthy
The Aeronautical Society of India, Thiruvananthapuram Branch
10
The Aeronautical Society of India, Thiruvananthapuram Branch
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
AN APPROXIMATE METHOD FOR PREDICTING HOTSPOTS IN LARGETEMPERATURE AIR COOLED EFFECT OFTHE HYDROGEN INJECTION SYSTEMS WITH REPEATED ONELECTRONIC SWIRL CO-AXIAL INJECTOR ELEMENT UNITS COMBUSTION B. BEHAVIOR Divya M. Tech, Aerospace Engg. V. Arun, Sreeram Banerjee, R.Institute Sujithkumar & P.A. Krishnamoorthy Indian of Technology, Madras Vikram Sarabhai Space Centre Chennai Thiruvananthapuram K.M. Srikumar Scientist, CABS, DRDO Bangalore ABSTRACT
S. Christopher
Director, CABS, DRDO To study the effect of gaseous hydrogen injection temperature on combustion behavior, hydrogen injection temperature ramping tests were Bangalore conducted with swirl co-axial injectors. Tests 38 barKumar chamber pressure at an engine mixture are carried out with LO2 and GH2 as propellants at Amit Associate Professor ratio of 6. Swirl coaxial injectors with LOx Post recess depth of 1.0mm and 1.6mm are used for the Engg. injection temperature ramping test. A test facility is established with provision forAerospace gaseous hydrogen Indian Institute of Technology Madras through a shell and tube type heat exchanger. Results showed that combustion chamber pressure Chennai oscillations increase with decrease of gaseous hydrogen injection temperature for both types of injectors. It is also observed from the experimental study that the cryogenic transition temperature for chamber pressure oscillation is lower for a swirlABSTRACT coaxial injector with 1.0mm recess as compared to 1.6mm recess. This coupled effects of LOx post recess depth and gaseous hydrogen injection temperature areThe tooactive complex to allow easy accurate of stability margins an airborne antenna array unitand (AAAU) is andetermination airborne antenna array unit usedoffor injector early at its warning operating conditions hence the experimental observations are only presented. and control. and Appropriate cooling of electronic components inside AAAU is crucial for its effective functioning and hence the mission. This study is taken up to estimate the maximum surface temperatures attained by electronic components during operation of AAAU. The electronic systems such as AAAU have massive structure for which a full simulation of conjugate heat transfer (conduction + forced convection) is at present computationally prohibitive, therefore an approximate approach is adopted here. This approach involves a combination of detailed flow simulation of the full AAAU for estimating flow and pressure distribution and a parametric study of flow and temperature on individual components with detailed conjugate heat transfer simulations. The information from the former along with lumped heat transfer analysis can be used to get an estimate on the location and magnitude of hotspots that can occur within the system.
1
The Aeronautical Society of India, Thiruvananthapuram Branch The Aeronautical Society of India, Thiruvananthapuram Branch
11
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
12.
Design, Realisation and Qualification of A Conductively Cooled Cryostat for Igniter Cold Soak/Firing Test at Low Temperatures ....................................................................................... 12
13.
DESIGN, REALISATION AND QUALIFICATION OF Heat Transfer Analysis of An Ablative ThroatCOOLED Insert for Liquid Engine with Film Cooling FOR .......................... 13 A CONDUCTIVELY CRYOSTAT IGNITER R. Harikrishnan COLD SOAK/FIRING TEST AT LOW TEMPERATURES
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Impact of Cryo Temperature on Separation Connectors of A Launch Vehicle .............................................. 14
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Abhishek Kumar, V. Arun & Sreeram Banerjee K.S. Lakshmi, P. Anoop,R.B.Sujithkumar, Sundar & M.J. Chacko Vikram Sarabhai Space Centre Thermal Structural Analysis of A Cryogenic Engine Turbopump Impeller ........................................................ 15 Thiruvananthapuram Krishnajith Jayamani, A.K. Asraff, R. Muthukumar, T.M. Phillip
16.
Experimental Investigation on the Convective Heat Transfer from
R. Sujithkumar, Abhishek Kumar, V. Arun & Sreeram Banerjee
ABSTRACT
A 3D Heated Block Subjected to Impingement Cooling ....................................................................................... 16 Ullekh Pandey, George, M. Ram Prabhu, T.V. Radhakrishnan & M.J.out Chacko A Philip conductively cooled cryostat for carrying initiator cold soak/firing test at low 17.
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temperatures to 10and K isExperimental designed, realised Bruceton tests and bridge Conjugate Study of down A Pyrovalve Validationand by IRqualified. Heating ................................................... 17 wire fuse time evaluation testsHassan, were Ani carried out H. using the cryostat for fixing the all fire current for igniter Suveer Singh, Md Moinuddin D. Kurien, Kumar formulation and also to ensure initiator performance at low temperature. The cryostat consist of Dr. A.G. Rajendran, K.P. Subhajayan & C. Jasperlal two compartments, the inner one for mounting the initiator cartridges that are cooled by liquid Application GPGPU Programming Numericalheat Simulation of 77 K thermal shield with liquid nitrogen. The helium of and the outer one fortoproviding sink of
Steady-State Heat Conduction Problems 18 outer chamber is provided with ................................................................................................................... PUIR insulation and vapour protection coating to suppress heat in K. Rakesh, M. Ajith, T. Jayachandran & Dr. Raju K. George leak into the Dr. system from ambient. The size of the cryostat is Ă&#x2DC;160mm x 125mm height and can 19.
accommodate Design nine initiators at of a time for testDiffuser with a liquid helium consumption rate of 57g/sec. In Thermo-Structural and Analysis A Supersonic this article, design features, structural and thermal analysis of the cryostat are discussed. for High Temperature Applications ............................................................................................................................. 19 Atha Ur Rahman Khan, A. Yezhil Arasu, Thomas Kurian, P.J. Abraham & V. Srinivasan
20.
Thermophysical Properties Measurement of Aerospace Material ...................................................................... 20 Fazil Mohammad, K.P. Subhajayan, T.P. Shivadasan, S. Krishnamoorthy C. Jasperlal, P.O. Balachandran & P.A. Krishnamoorthy
21.
Solid Rocket Booster Flex Seal Moulding â&#x20AC;&#x201C; Cure Cycle Estimation ................................................................... 21 Jose Paul, S. Kartheekeyan, V. Mahesh, K.P. Subhajayan, V. Eswaran & V. Srinivasan
22.
High Temperature Storage Heater Design for Propulsion Facility ..................................................................... 22 Samik Jash, Jose Paul, Praveen Kumar, C. Jasperlal, Dr. T. Jayachandran P.O. Balachandran & P.A. Krishnamoorthy
23.
Performance Evaluation of Thermal Control System of A Typical Manned Spacecraft ................................. 23 Samik Jash, C. Pedda Peeraiah, Dr. T. Jayachandran & P.A. Krishnamoorthy
The Aeronautical Society of India, Thiruvananthapuram Branch
12
The Aeronautical Society of India, Thiruvananthapuram Branch
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
AN APPROXIMATE METHOD FOR PREDICTING THETRANSFER HOTSPOTSANALYSIS IN LARGEOF AIRAN COOLED HEAT ELECTRONIC SYSTEMS INSERT WITH REPEATED UNITS ABLATIVE THROAT FOR LIQUID ENGINE WITHB. FILM Divya COOLING M. Tech, Aerospace Engg. R. Harikrishnan Indian Institute of Technology, Madras Vikram Sarabhai Space Centre Chennai Thiruvananthapuram K.M. Srikumar Scientist, CABS, DRDO Bangalore ABSTRACT
S. Christopher
Director, CABS, DRDOliner with 600 ply orientation as The high thrust liquid engine employs silica phenolic ablative Bangalore the throat insert. However, when the engine was up-rated for higher pressure and longer duration, Amit Kumar due to axial heating effects and the original ablative throat insert was found to be inadequate subsequent charring in the aft side of the throatAssociate insert. Professor Aerospace Engg. A dual ply throat insert was proposed for the engine and theoretical studies were carried out Indian Institute of Technology Madras to estimate the optimum ply angle combination for the throat insert by carrying out thermal Chennai simulation studies. The recommendations were incorporated in engine level testing and a very close match was observed between the theoretically estimated and measured thermal performance of ABSTRACT the throat insert. The active antenna array unit (AAAU) is an airborne antenna array unit used for airborne early warning and control. Appropriate cooling of electronic components inside AAAU is crucial for its effective functioning and hence the mission. This study is taken up to estimate the maximum surface temperatures attained by electronic components during operation of AAAU. The electronic systems such as AAAU have massive structure for which a full simulation of conjugate heat transfer (conduction + forced convection) is at present computationally prohibitive, therefore an approximate approach is adopted here. This approach involves a combination of detailed flow simulation of the full AAAU for estimating flow and pressure distribution and a parametric study of flow and temperature on individual components with detailed conjugate heat transfer simulations. The information from the former along with lumped heat transfer analysis can be used to get an estimate on the location and magnitude of hotspots that can occur within the system.
1
The Aeronautical Society of India, Thiruvananthapuram Branch The Aeronautical Society of India, Thiruvananthapuram Branch
13
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
12.
Design, Realisation and Qualification of A Conductively Cooled Cryostat for Igniter Cold Soak/Firing Test at Low Temperatures ....................................................................................... 12
IMPACT OF CRYO TEMPERATURE ON SEPARATION Heat Transfer Analysis of An Ablative Throat InsertOF for Liquid with Film Cooling .......................... 13 CONNECTORS A Engine LAUNCH VEHICLE
R. Sujithkumar, Abhishek Kumar, V. Arun & Sreeram Banerjee 13.
R. Harikrishnan
K.S. Lakshmi, P. Anoop, B. Sundar & M.J. Chacko
14.
Impact of Cryo Temperature on Separation Connectors of A Launch Vehicle .............................................. 14 Vikram Sarabhai Space Centre K.S. Lakshmi, P. Anoop, B. Sundar & M.J. Chacko Thiruvananthapuram
15.
Thermal Structural Analysis of A Cryogenic Engine Turbopump Impeller ........................................................ 15
ABSTRACT
Krishnajith Jayamani, A.K. Asraff, R. Muthukumar, T.M. Phillip 16.
17.
Experimental Investigation on the Convective Heat Transfer from There manytosubsystems, interfaces and attachments housed in the cryogenic stage A 3D Heated Blockare Subjected Impingement Cooling ....................................................................................... 16
which arePhilip critical forM.aRam successful mission. These&elements Ullekh Pandey, George, Prabhu, T.V. Radhakrishnan M.J. Chackoare subjected to cryo temperatures ranging from 20 K to 78 K. Therefore it is essential to evaluate the thermal environments of these Conjugate Study of A Pyrovalve andtemperatures. Experimental Validation IR Heating ................................................... 17to estimate elements subjected to cryo For the by design of the elements, it is essential Suveer Md Moinuddin Hassan, Ani D. Kurien, H. Kumar theSingh, temperature distribution considering the thermal environments. For an optimum design, suitable Dr. insulation A.G. Rajendran, K.P. Subhajayan & C.the Jasperlal scheme to isolate elements from cryo temperature can be thought of which will
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reduce of theGPGPU gradients across the elements.Simulation of Application Programming to Numerical Steady-StateInHeat Problems ................................................................................................................... 18 thisConduction paper, impact of cryo temperature on subsystem is analysed. The subsystem consists
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of electrical carrying control from equipment bay to lower stages, and snaps K. Rakesh, M. Ajith,connectors Dr. T. Jayachandran & Dr. Raju K.commands George during stage separation. These connectors are attached to the cryo tankages through brackets. Thermo-Structural Design and Analysis of A Supersonic Diffuser Thermal environments during pre-launch phase of flight is identified and quantified and three for High Temperature Applications ............................................................................................................................. 19 dimensional finite element thermal analysis of the bracket housing the connectors is carried out. It Atha Ur Rahman Khan, A. Yezhil Arasu, Thomas Kurian, P.J. Abraham & V. Srinivasan is seen that separation connector remains at ambient temperature ensuring its proper functioning Thermophysical PropertiestoMeasurement of Aerospace 20 connector and is not subjected low temperature. This isMaterial mainly...................................................................... because the bracket and separation
thermal energy byT.P. radiation from wire tunnel cover which is at ambient temperature. Also Fazilreceives Mohammad, K.P. Subhajayan, Shivadasan, S. Krishnamoorthy thermalP.O. bridge connecting and tank reduces large temperature gradients between bracket C. Jasperlal, Balachandran & P.A.bracket Krishnamoorthy 21.
and tank and this is essential for mounting attachments on the cryo tankages. Tests carried out also Solid Rocket Booster Flex Seal Moulding â&#x20AC;&#x201C; Cure Cycle Estimation ................................................................... 21 confirmed the theoretical predictions. Jose Paul, S. Kartheekeyan, V. Mahesh, K.P. Subhajayan, V. Eswaran & V. Srinivasan
22.
High Temperature Storage Heater Design for Propulsion Facility ..................................................................... 22 Samik Jash, Jose Paul, Praveen Kumar, C. Jasperlal, Dr. T. Jayachandran P.O. Balachandran & P.A. Krishnamoorthy
23.
Performance Evaluation of Thermal Control System of A Typical Manned Spacecraft ................................. 23 Samik Jash, C. Pedda Peeraiah, Dr. T. Jayachandran & P.A. Krishnamoorthy
The Aeronautical Society of India, Thiruvananthapuram Branch
14
The Aeronautical Society of India, Thiruvananthapuram Branch
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
AN APPROXIMATE METHOD FOR PREDICTING THE HOTSPOTS IN LARGE AIROF COOLED THERMAL STRUCTURAL ANALYSIS A ELECTRONIC SYSTEMS WITH REPEATED CRYOGENIC ENGINE TURBOPUMP IMPELLERUNITS B. Divya Krishnajith Jayamani
Tech, Aerospace Engineer, Structural M. Dynamics & Analysis Engg. Division Indian Institute of Technology, Madras A.K. Asraff Chennai Head, Structural Dynamics & Analysis Division
K.M. Srikumar R. Muthukumar
Scientist, CABS, DRDO Group Director, Mechanical Design and Analysis Group Bangalore
T.M. Phillip S. Christopher
Deputy Division Head, Turbo Pump Division Director, CABS, DRDO Liquid Propulsion Systems Centre Bangalore ISRO, Valiamala, Thiruvananthapuram
Amit Kumar
Associate Professor
ABSTRACT Aerospace Engg.
Indian Institute of Technology Madras Turbopumps are crucial components of all primary propulsion systems powered by liquid Chennai rocket engines. One of ISRO's cryogenic turbopump impellers needs to be spin tested at room temperature for qualifying it for operation at cryogenic temperature. The spin test speed of the ABSTRACT impeller is worked out considering the changes in operating conditions, stresses induced and material properties associated therewith. Based on three dimensional finite element analysis, the spin speed The active antenna array unit (AAAU) is an airborne antenna array unit used for airborne is worked out so as to get a load factor of 1.5 times of when the impeller is run at actual operating early warning and control. Appropriate cooling of electronic components inside AAAU is crucial for conditions. High performance computing studies made with two different computer systems for its effective functioning and hence the mission. This study is taken up to estimate the maximum stress analysis of the impeller is also presented and conclusions drawn. surface temperatures attained by electronic components during operation of AAAU. The electronic systems such as AAAU have massive structure for which a full simulation of conjugate heat transfer (conduction + forced convection) is at present computationally prohibitive, therefore an approximate approach is adopted here. This approach involves a combination of detailed flow simulation of the full AAAU for estimating flow and pressure distribution and a parametric study of flow and temperature on individual components with detailed conjugate heat transfer simulations. The information from the former along with lumped heat transfer analysis can be used to get an estimate on the location and magnitude of hotspots that can occur within the system.
1
The Aeronautical Society of India, Thiruvananthapuram Branch The Aeronautical Society of India, Thiruvananthapuram Branch
15
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
12.
Design, Realisation and Qualification of A Conductively Cooled Cryostat for Igniter Cold Soak/Firing Test at Low Temperatures ....................................................................................... 12
EXPERIMENTAL INVESTIGATION ON THE Heat Transfer Analysis of An Ablative Throat Insert for LiquidTRANSFER Engine with Film Cooling .......................... CONVECTIVE HEAT FROM A 13 R. Harikrishnan 3D HEATED BLOCK SUBJECTED TO Impact of Cryo Temperature on Separation Connectors of A Launch Vehicle .............................................. 14 IMPINGEMENT COOLING K.S. Lakshmi, P. Anoop, B. Sundar & M.J. Chacko R. Sujithkumar, Abhishek Kumar, V. Arun & Sreeram Banerjee
13.
14.
15.
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Thermal Structural Analysis of AUllekh Cryogenic Engine Philip Turbopump Impeller 15 Pandey, George, M......................................................... Ram Prabhu
T.V. Radhakrishnan & M.J. Chacko Krishnajith Jayamani, A.K. Asraff, R. Muthukumar, T.M. Phillip Vikram Sarabhai Space Centre Experimental Investigation on the Convective Heat Transfer from Thiruvananthapuram A 3D Heated Block Subjected to Impingement Cooling ....................................................................................... 16 Ullekh Pandey, Philip George, M. Ram Prabhu, T.V. Radhakrishnan & M.J. Chacko
17.
ABSTRACT
Conjugate Study of A Pyrovalve and Experimental Validation by IR Heating ................................................... 17 Suveer Singh,Experimental Md Moinuddin Hassan, Kurien, H. Kumar studiesAni areD.carried out to determine the convective heat transfer coefficients Dr. for A.G. aRajendran, K.P. block Subhajayan & C. Jasperlal 3D heated subjected to jet impingement. Two different orientations of the block with
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respectoftoGPGPU incoming jet are to considered. Reynoldsof number based on pipe diameter is varied as Application Programming Numerical Simulation 1100, 1730, 2860 & 4400 and the distance between pipe exit and impingement surface is varied as Steady-State Heat Conduction Problems ................................................................................................................... 18 1.0, 2.0, 4.17 & 8.33 pipe diameters. Average convective heat transfer coefficients on exposed K. Rakesh, M. Ajith, Dr. T. Jayachandran & Dr. Raju K. George surfaces and overall convective heat transfer coefficients for the 3D block are compared for different Thermo-Structural orientations. Design and Analysis of A Supersonic Diffuser for High Temperature Applications ............................................................................................................................. 19 Atha Ur Rahman Khan, A. Yezhil Arasu, Thomas Kurian, P.J. Abraham & V. Srinivasan
20.
Thermophysical Properties Measurement of Aerospace Material ...................................................................... 20 Fazil Mohammad, K.P. Subhajayan, T.P. Shivadasan, S. Krishnamoorthy C. Jasperlal, P.O. Balachandran & P.A. Krishnamoorthy
21.
Solid Rocket Booster Flex Seal Moulding â&#x20AC;&#x201C; Cure Cycle Estimation ................................................................... 21 Jose Paul, S. Kartheekeyan, V. Mahesh, K.P. Subhajayan, V. Eswaran & V. Srinivasan
22.
High Temperature Storage Heater Design for Propulsion Facility ..................................................................... 22 Samik Jash, Jose Paul, Praveen Kumar, C. Jasperlal, Dr. T. Jayachandran P.O. Balachandran & P.A. Krishnamoorthy
23.
Performance Evaluation of Thermal Control System of A Typical Manned Spacecraft ................................. 23 Samik Jash, C. Pedda Peeraiah, Dr. T. Jayachandran & P.A. Krishnamoorthy
The Aeronautical Society of India, Thiruvananthapuram Branch
16
The Aeronautical Society of India, Thiruvananthapuram Branch
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
AN APPROXIMATE METHOD FOR PREDICTING THE HOTSPOTS AIR COOLED CONJUGATE STUDY OFINA LARGE PYROVALVE AND ELECTRONIC VALIDATION SYSTEMS WITH REPEATED EXPERIMENTAL BY IR HEATING UNITS B. Divya Suveer Singh, Md Moinuddin Hassan, Ani D. Kurien, H. Kumar M. Tech, Aerospace Engg. Dr. A.G. Rajendran, K.P. Subhajayan & C. Jasperlal Indian Institute of Technology, Madras Vikram Sarabhai Space Centre Chennai Thiruvananthapuram
K.M. Srikumar
Scientist, CABS, DRDO
ABSTRACT Bangalore
S. Christopher
The applications of pyro devices in launch vehicles and satellites are mainly limited by the Director, CABS, DRDO upper limit of safe operating temperature for explosive cartridge, which is 343 K (approx.) for Bangalore most of the pyro cartridges. Beyond this, depending upon duration of thermal exposure, the Amit Kumar explosive element may either undergo slow thermal degradation, hampering the performance, or in Associate Professor the worst case, may even get triggered, which is, sometimes, unsafe. Aerospace Engg. Indian Institute of Technology Madras The Pyrovalve (PV) under study here is used in engine ground tests for emergency venting of Chennai working fluid in case of losing control of test or engine malfunction. During such tests of 100 s maximum duration, Pyrovalve inlet holds Gas Generator (GG) gas at 50 bar and 900 K, which will be vented to atmosphere in case of emergency by opening the valve flow path with in 40 ms of valve ABSTRACT actuation. The active antenna array unitof(AAAU) is antemperature airborne antenna array unit used for airborne Present work involves a quantification valve body rise due to direct exposure andGG control. of electronic components inside aAAAU is crucial for of valve early inlet warning to stagnant gas atAppropriate 900 K over cooling the entire test duration by performing transient itsheat effective functioning andPyrovalve. hence theThe mission. Thisofstudy is taken up to estimate the in maximum conjugate transfer analysis of necessity an inbuilt purge cooling system temperatures attained by electronic duringis operation of with AAAU.IR The electronic the valvesurface is studied and an experimental simulation components of valve heating conducted (Infra systems such as AAAU have massive structure for which a full simulation of conjugate heat transfer Red) heating. (conduction + forced convection) is at present computationally prohibitive, therefore an approximate To predict Pyrovalve transient thermal response under IR heating as well as to demonstrate approach is adopted here. This approach involves a combination of detailed flow simulation of the the thermal equivalence /severity of IR heating scheme vis-Ă -vis stagnant gas heating, a transient full AAAU for estimating flow and pressure distribution and a parametric study of flow and temperature radiation heating analysis is also performed. Results of conjugate analysis and radiative heating on individual components with detailed conjugate heat transfer simulations. The information from analysis are compared with IR heating test results. the former along with lumped heat transfer analysis can be used to get an estimate on the location The heating test demonstrate the design and safe operation of Pyrovalve andIRmagnitude of results hotspots that can occur within adequacy the system. for given thermal environment and test duration, even without purge cooling. Also, the predicted temperature profiles from stagnant gas conjugate analysis and IR heating analysis are generally in good agreement with experimental results over 3/4th length of Pyrovalve.
1
The Aeronautical Society of India, Thiruvananthapuram Branch The Aeronautical Society of India, Thiruvananthapuram Branch
17
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
12.
Design, Realisation and Qualification of A Conductively Cooled Cryostat for Igniter Cold Soak/Firing Test at Low Temperatures ....................................................................................... 12
13.
APPLICATION OF GPGPU PROGRAMMING TO Heat Transfer NUMERICAL Analysis of An Ablative Throat Insert for Liquid EngineOF with Film Cooling .......................... 13 SIMULATION STEADY-STATE R. Harikrishnan HEAT CONDUCTION PROBLEMS
14.
Impact of Cryo Temperature on Separation Connectors of A Launch Vehicle .............................................. 14
15.
K.S. Lakshmi, P. Anoop, B. Sundar &K. M.J.Rakesh, Chacko M. Ajith & Dr. T. Jayachandran Vikram Sarabhai Space Centre Thermal Structural Analysis of A Cryogenic Engine Turbopump Impeller ........................................................ 15 Thiruvananthapuram Krishnajith Jayamani, A.K. Asraff, R. Muthukumar, T.M. Phillip
R. Sujithkumar, Abhishek Kumar, V. Arun & Sreeram Banerjee
Dr. Raju K. George
16.
Experimental Investigation on the Convective Heat Transfer Professor, Dept. from of Mathematics Institute Cooling of Space Science and Technology(IIST) A 3D Heated Block SubjectedIndian to Impingement ....................................................................................... 16 Ullekh Pandey, Philip George, M. Ram Prabhu, T.V. Radhakrishnan & M.J. Chacko
ABSTRACT
17.
Conjugate Study of A Pyrovalve and Experimental Validation by IR Heating ................................................... 17
18.
Suveer Singh, Md Moinuddin Hassan, Ani D. Kurien, H. Kumar The use of Graphical Processing Units (GPUs) for solving steady state heat conduction problem Dr. A.G. Rajendran, K.P. Subhajayan & C. Jasperlal using finite element method is demonstrated in the present paper. Element-by-element (EbE) Application GPGPUtechnique, Programmingintowhich Numerical Simulation ofconjugate gradient (CG) type iterative solution FEM is aof known a matrix-free Steady-State Heatbe Conduction Problems ................................................................................................................... 18 scheme can entirely decomposed into element-level computations, i.e., without assembling the K. Rakesh, Ajith, Dr. T. Jayachandran & Dr. Raju K. George global M. system matrix. In our implementation NVIDIA's parallel computing platform, called Compute
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Unified DeviceDesign Architecture (CUDA) is used toDiffuser perform the required element-wise computations in Thermo-Structural and Analysis of A Supersonic parallel. The element matrices are stored in lower packed storage mode, so that the CUDA memory for High Temperature Applications ............................................................................................................................. 19 latency can be kept extremely low. It is shown that this low-storage but computation-intensive Atha Ur Rahman Khan, A. Yezhil Arasu, Thomas Kurian, P.J. Abraham & V. Srinivasan technique is better suited for GPUs than those requiring the massive manipulation of large data Thermophysical Properties Measurement of Aerospace Material ...................................................................... 20 sets. Fazil Mohammad, K.P. Subhajayan, T.P. Shivadasan, S. Krishnamoorthy C. Jasperlal, P.O. Balachandran & P.A. Krishnamoorthy
21.
Solid Rocket Booster Flex Seal Moulding â&#x20AC;&#x201C; Cure Cycle Estimation ................................................................... 21 Jose Paul, S. Kartheekeyan, V. Mahesh, K.P. Subhajayan, V. Eswaran & V. Srinivasan
22.
High Temperature Storage Heater Design for Propulsion Facility ..................................................................... 22 Samik Jash, Jose Paul, Praveen Kumar, C. Jasperlal, Dr. T. Jayachandran P.O. Balachandran & P.A. Krishnamoorthy
23.
Performance Evaluation of Thermal Control System of A Typical Manned Spacecraft ................................. 23 Samik Jash, C. Pedda Peeraiah, Dr. T. Jayachandran & P.A. Krishnamoorthy
The Aeronautical Society of India, Thiruvananthapuram Branch
18
The Aeronautical Society of India, Thiruvananthapuram Branch
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
AN APPROXIMATE METHOD FOR PREDICTING THE HOTSPOTSDESIGN IN LARGE AIR COOLED THERMO-STRUCTURAL AND ANALYSIS ELECTRONIC SYSTEMS WITH REPEATED UNITS OF A SUPERSONIC DIFFUSER FOR HIGH TEMPERATUREB. APPLICATIONS Divya M. Tech, Aerospace Engg. Atha Ur Rahman Khan, Yezhilof Arasu, Thomas Kurian IndianA. Institute Technology, Madras P.J. Abraham & V. Chennai Srinivasan Vikram SarabhaiK.M. Space Centre Srikumar Thiruvananthapuram Scientist, CABS, DRDO Bangalore
S. Christopher ABSTRACT
Director, CABS, DRDO Aerodynamic studies for various internal andBangalore external flows rely heavily on experimental data obtained from wind tunnel tests. Most testing facilities used for high speed testing are designed Amit Kumar Associate to operate in Blow-down mode in which the desired MachProfessor number is obtained by maintaining the Aerospace Engg. a high pressure chamber in the required pressure difference across the test specimen by using Indian Institute of Technology Madras upstream and a vacuum chamber downstream of the test specimen. Furthermore, the working Chennai fluid is preheated to prevent liquefaction on expansion. In a supersonic test facility, the Diffuser Duct serves the function of recovering pressure by decelerating the working gas after exit from the test chamber. The Diffuser Duct is subjected to a near vacuum pressure on its inside and is exposed ABSTRACT to high temperature from the hot gas flow. The thermal expansion associated with elevated temperatures induces thermal stresses in the Diffuser which usually exceedarray the allowable The active antenna array unit (AAAU)Duct is an airborne antenna unit usedlimits for airborne for typical structural steels. This imposes an interesting engineering challenge and calls for a early warning and control. Appropriate cooling of electronic components inside AAAU is crucial for comprehensive procedure for design and analysis of such a complex system. This paper discusses its effective functioning and hence the mission. This study is taken up to estimate the maximum the structural of the attained diffuser by duct and thecomponents complementary analysis, surfacedesign temperatures electronic duringthermostructural operation of AAAU. The electronic encompassing elements from ASME design guidelines and Finite Element Method. The critical choice systems such as AAAU have massive structure for which a full simulation of conjugate heat transfer of material selection+isforced carefully assessedisinatlight of design principles and finite element analysis. (conduction convection) present computationally prohibitive, therefore an approximate approach is adopted here. This approach involves a combination of detailed flow simulation of the full AAAU for estimating flow and pressure distribution and a parametric study of flow and temperature on individual components with detailed conjugate heat transfer simulations. The information from the former along with lumped heat transfer analysis can be used to get an estimate on the location and magnitude of hotspots that can occur within the system.
1
The Aeronautical Society of India, Thiruvananthapuram Branch The Aeronautical Society of India, Thiruvananthapuram Branch
19
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
12.
Design, Realisation and Qualification of A Conductively Cooled Cryostat for Igniter Cold Soak/Firing Test at Low Temperatures ....................................................................................... 12
THERMOPHYSICAL PROPERTIES MEASUREMENT Heat Transfer Analysis of An Ablative Insert for Liquid Engine with Film Cooling .......................... 13 OFThroat AEROSPACE MATERIAL
R. Sujithkumar, Abhishek Kumar, V. Arun & Sreeram Banerjee 13.
R. Harikrishnan
Fazil Mohammad, K.P. Subhajayan, T.P. Shivadasan, S. Krishnamoorthy C. Jasperlal, P.O. Balachandran & P.A. Krishnamoorthy
14.
Impact of Cryo Temperature on Separation Connectors of A Launch Vehicle .............................................. 14
15.
K.S. Lakshmi, P. Anoop, B. Sundar & M.J. Chacko Vikram Sarabhai Space Centre Thiruvananthapuram Thermal Structural Analysis of A Cryogenic Engine Turbopump Impeller ........................................................ 15 Krishnajith Jayamani, A.K. Asraff, R. Muthukumar, T.M. Phillip
ABSTRACT
16.
Experimental Investigation on the Convective Heat Transfer from
17.
A 3D Heated Block Subjected to Impingement Cooling ....................................................................................... 16 The important thermo physical properties which determine the thermal performance of a Ullekh Pandey, Philip George, M. Ram Prabhu, T.V. Radhakrishnan & M.J. Chacko material are thermal conductivity, thermal diffusivity and specific heat. The accurate measurement Conjugate Study of A Pyrovalve and Experimental Validation byanalysis IR Heating ................................................... of these properties is essential for any engineering and optimised design. The17Guarded hot Suveer Singh, Md Moinuddin Ani apparatus D. Kurien, H.which Kumarwere developed in house along with the Laser flash plate apparatus and Hassan, hot wire Dr. apparatus A.G. Rajendran, K.P. it Subhajayan C. Jasperlal make possible&for the complete thermal characterization of material. The laser flash
18.
19.
apparatus and hot wire apparatus utilizeSimulation transient Application of GPGPU Programming to Numerical of techniques, the guarded hot plate apparatus employs steady state method. The materials tested using above methods includes alloys, composites, Steady-State Heat Conduction Problems ................................................................................................................... 18 ceramics, fibre insulations etc. The present paper describes these apparatus, their working principle K. Rakesh, M. Ajith, Dr. T. Jayachandran & Dr. Raju K. George and highlights some test results. Thermo-Structural Design and Analysis of A Supersonic Diffuser for High Temperature Applications ............................................................................................................................. 19 Atha Ur Rahman Khan, A. Yezhil Arasu, Thomas Kurian, P.J. Abraham & V. Srinivasan
20.
Thermophysical Properties Measurement of Aerospace Material ...................................................................... 20 Fazil Mohammad, K.P. Subhajayan, T.P. Shivadasan, S. Krishnamoorthy C. Jasperlal, P.O. Balachandran & P.A. Krishnamoorthy
21.
Solid Rocket Booster Flex Seal Moulding â&#x20AC;&#x201C; Cure Cycle Estimation ................................................................... 21 Jose Paul, S. Kartheekeyan, V. Mahesh, K.P. Subhajayan, V. Eswaran & V. Srinivasan
22.
High Temperature Storage Heater Design for Propulsion Facility ..................................................................... 22 Samik Jash, Jose Paul, Praveen Kumar, C. Jasperlal, Dr. T. Jayachandran P.O. Balachandran & P.A. Krishnamoorthy
23.
Performance Evaluation of Thermal Control System of A Typical Manned Spacecraft ................................. 23 Samik Jash, C. Pedda Peeraiah, Dr. T. Jayachandran & P.A. Krishnamoorthy
The Aeronautical Society of India, Thiruvananthapuram Branch
20
The Aeronautical Society of India, Thiruvananthapuram Branch
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
AN APPROXIMATE METHOD FOR PREDICTING THE HOTSPOTS IN LARGE COOLEDâ&#x20AC;&#x201C; SOLID ROCKET BOOSTER FLEX SEAL AIR MOULDING ELECTRONIC SYSTEMS WITH REPEATED UNITS CURE CYCLE ESTIMATION B. Divya Jose Paul, S. Kartheekeyan, V. Mahesh M. Tech, Aerospace Engg. K.P. Subhajayan, V. Eswaran & V. Srinivasan
Indian Institute of Technology, Madras Vikram Sarabhai Space Centre Chennai Thiruvananthapuram
K.M. Srikumar
Scientist, CABS, DRDO
ABSTRACT Bangalore
S. Christopher
Large booster flex seal is realized through compression moulding technique, which has been Director, CABS, DRDO evolved through successful development of moulding technique for the smaller flex seals employed Bangalore in Ď&#x2020;1m/2m solid rocket motors. Unlike the moulding process established for smaller flex seals, Amit Kumar development of process parameters for large booster flex seals posed several challenges. One of Associate Professor them is the cure cycle optimization carried out and implemented to ensure minimum temperature Aerospace Engg. gradient across the cross section of theIndian mouldInstitute and flexofseal which isMadras an essential requirement to Technology avoid over cure of seal elastomer, a natural rubber based compound. Chennai This paper details out on the generation of cure cycle for large sized flex seals. Thermal analysis is carried out for optimizing the constraint of minimal cure reversal so that there is no ABSTRACT degradation of properties of the elastomer pads occur. Trial mouldings were carried out for the validation of the cycles and realized cure cycles areairborne simulated. A good match noticed Thecure active antenna array unit (AAAU) is an antenna array unitisused for airborne betweenearly the computed and the measured temperature transients based on realized cure cycle. warning and control. Appropriate cooling of electronic components inside AAAU is crucial for its effective functioning and hence the mission. This study is taken up to estimate the maximum surface temperatures attained by electronic components during operation of AAAU. The electronic systems such as AAAU have massive structure for which a full simulation of conjugate heat transfer (conduction + forced convection) is at present computationally prohibitive, therefore an approximate approach is adopted here. This approach involves a combination of detailed flow simulation of the full AAAU for estimating flow and pressure distribution and a parametric study of flow and temperature on individual components with detailed conjugate heat transfer simulations. The information from the former along with lumped heat transfer analysis can be used to get an estimate on the location and magnitude of hotspots that can occur within the system.
1
The Aeronautical Society of India, Thiruvananthapuram Branch The Aeronautical Society of India, Thiruvananthapuram Branch
21
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
12.
Design, Realisation and Qualification of A Conductively Cooled Cryostat for Igniter Cold Soak/Firing Test at Low Temperatures ....................................................................................... 12
HIGH TEMPERATURE STORAGE HEATER Heat Transfer AnalysisDESIGN of An Ablative Throat InsertPROPULSION for Liquid Engine with Film Cooling .......................... 13 FOR FACILITY
R. Sujithkumar, Abhishek Kumar, V. Arun & Sreeram Banerjee 13.
R. Harikrishnan
Samik Jash, Jose Paul, Praveen Kumar, C. Jasperlal Dr. T. Jayachandran, P.O. Balachandran & P. A. Krishnamoorthy
14.
Impact of Cryo Temperature on Separation Connectors of A Launch Vehicle .............................................. 14
15.
K.S. Lakshmi, P. Anoop, B. Sundar & M.J. Chacko Advance Propulsion Research Group Sarabhai Space Centre Thermal Structural Analysis of A CryogenicVikram Engine Turbopump Impeller ........................................................ 15 Thiruvananthapuram Krishnajith Jayamani, A.K. Asraff, R. Muthukumar, T.M. Phillip
16.
Experimental Investigation on the Convective Heat Transfer from
ABSTRACT
A 3D Heated Block Subjected to Impingement Cooling ....................................................................................... 16
17.
Ullekh Pandey, Philip George, M. Ram Prabhu, T.V. Radhakrishnan & M.J. Chacko The design of a high temperature graphite drilled core induction storage heater, meant for Conjugate Study A Pyrovalvefacility and Experimental Validation IR Heating 17 heater has a hypersonicofpropulsion is discussed in thisbypaper. The................................................... final configuration of the Suveer Singh, Md Moinuddin Hassan, and Ani D.exhaustive Kurien, H. Kumar been arrived after detailed study of various configurations of the same. The critical Dr. aspects A.G. Rajendran, Subhajayan C. Jasperlal of theK.P.design viz.,&sizing of the heater, insulation system design for the induction copper
18.
coils, thermal protection system design for the heater domes, the axial and radial temperature Application of GPGPU Programming to Numerical Simulation of gradients in the graphite blocks, are discussed in details. Steady-State Heat Conduction Problems ................................................................................................................... 18 K. Rakesh, M. Ajith, Dr. T. Jayachandran & Dr. Raju K. George
19.
Thermo-Structural Design and Analysis of A Supersonic Diffuser for High Temperature Applications ............................................................................................................................. 19 Atha Ur Rahman Khan, A. Yezhil Arasu, Thomas Kurian, P.J. Abraham & V. Srinivasan
20.
Thermophysical Properties Measurement of Aerospace Material ...................................................................... 20 Fazil Mohammad, K.P. Subhajayan, T.P. Shivadasan, S. Krishnamoorthy C. Jasperlal, P.O. Balachandran & P.A. Krishnamoorthy
21.
Solid Rocket Booster Flex Seal Moulding â&#x20AC;&#x201C; Cure Cycle Estimation ................................................................... 21 Jose Paul, S. Kartheekeyan, V. Mahesh, K.P. Subhajayan, V. Eswaran & V. Srinivasan
22.
High Temperature Storage Heater Design for Propulsion Facility ..................................................................... 22 Samik Jash, Jose Paul, Praveen Kumar, C. Jasperlal, Dr. T. Jayachandran P.O. Balachandran & P.A. Krishnamoorthy
23.
Performance Evaluation of Thermal Control System of A Typical Manned Spacecraft ................................. 23 Samik Jash, C. Pedda Peeraiah, Dr. T. Jayachandran & P.A. Krishnamoorthy
The Aeronautical Society of India, Thiruvananthapuram Branch
22
The Aeronautical Society of India, Thiruvananthapuram Branch
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
AN APPROXIMATE METHOD FOR PREDICTING THE HOTSPOTSEVALUATION IN LARGE AIR PERFORMANCE OFCOOLED ELECTRONIC SYSTEMS WITH REPEATED UNITS THERMAL CONTROL SYSTEM OF A TYPICAL MANNEDB. Divya SPACECRAFT M. Tech, Aerospace Engg. Samik Jash, C. Pedda Peeraiah, Dr.Institute T. Jayachandran & P.Madras A. Krishnamoorthy Indian of Technology, Advance Propulsion Research Group Chennai Vikram SarabhaiK.M. Space Centre Srikumar Thiruvananthapuram Scientist, CABS, DRDO Bangalore
S. Christopher ABSTRACT
Director, CABS, DRDO Bangalore The most critical aspect of a manned spacecraft is the presence of a reliable and efficient Environment Control and Life Support System (ECLSS) ensure comfortable environment inside AmittoKumar Associate Professor the crew cabin by effectively controlling pressure, temperature and humidity. The Thermal Control Aerospace Engg. System (TCS) is one of the major subsystems of the ECLSS and is responsible for maintaining the Indian Institute of Technology Madras temperature and humidity of the cabin within the desired limits during all phases of the mission. Chennai The system mainly consists of a closed loop coolant system wherein the heat from the cabin is taken by liquid coolant using heat exchangers and is rejected to the outer space through radiators mounted on the outer side of the service modules. The present paper presents the development of a suitable ABSTRACT numerical methodology for an system level integrated thermal analysis for a typical two fluid based TCS system. The active antenna array unit (AAAU) is an airborne antenna array unit used for airborne early warning and control. Appropriate cooling of electronic components inside AAAU is crucial for its effective functioning and hence the mission. This study is taken up to estimate the maximum surface temperatures attained by electronic components during operation of AAAU. The electronic systems such as AAAU have massive structure for which a full simulation of conjugate heat transfer (conduction + forced convection) is at present computationally prohibitive, therefore an approximate approach is adopted here. This approach involves a combination of detailed flow simulation of the full AAAU for estimating flow and pressure distribution and a parametric study of flow and temperature on individual components with detailed conjugate heat transfer simulations. The information from the former along with lumped heat transfer analysis can be used to get an estimate on the location and magnitude of hotspots that can occur within the system.
1
The Aeronautical Society of India, Thiruvananthapuram Branch The Aeronautical Society of India, Thiruvananthapuram Branch
23
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
12.
Design, Realisation and Qualification of A Conductively Cooled Cryostat for Igniter Cold Soak/Firing Test at Low Temperatures ....................................................................................... 12
13.
EXPERIMENTAL STUDIES FOR ESTIMATING Heat Transfer Analysis of AnFLUX Ablative Throat Insert TO for Liquid Engine with Film Cooling .......................... 13 HEAT DUE TWIN-NOZZLE PLUME R. Harikrishnan INTERACTION AND IMPINGEMENT
14.
Impact of Cryo Temperature on Separation Connectors of A Launch Vehicle .............................................. 14
15.
P. B.Sridharan, Krishnaraj, C.Jasperlal & P.A. Krishnamoorthy K.S. Lakshmi, P. Anoop, Sundar & M.J.K. Chacko Vikram Sarabhai Space Centre Thermal Structural Analysis of A Cryogenic Engine Turbopump Impeller ........................................................ 15 Thiruvananthapuram Krishnajith Jayamani, A.K. Asraff, R. Muthukumar, T.M. Phillip
16.
Experimental Investigation on the Convective Heat Transfer from
R. Sujithkumar, Abhishek Kumar, V. Arun & Sreeram Banerjee
ABSTRACT
A 3D Heated Block Subjected to Impingement Cooling ....................................................................................... 16 Ullekh Pandey, Ram Prabhu, T.V.vehicle Radhakrishnan & M.J. Chacko In Philip one George, of our M. planned launch configuration, the exhaust plume from a twin engine 17.
18.
liquid rocket interacts and impinges on the by outer surface of the 2 strap on solid 17 rocket nozzle Conjugate Study ofnozzle A Pyrovalve and Experimental Validation IR Heating ................................................... divergents about 20 seconds an altitude of 40 kms. The solid rocket nozzle divergents have to Suveer Singh, Mdfor Moinuddin Hassan, Ani D.atKurien, H. Kumar be thermally protected. In order to determine the impinging heat flux and pressure due to plume Dr. A.G. Rajendran, K.P. Subhajayan & C. Jasperlal impingement and to generate design inputs for theoretical validation, scale down simulation tests Application of GPGPU to Numerical of the ambient conditions. Instrumented models were carried in anProgramming environmental chamberSimulation simulating
Steady-State Heat Problems ................................................................................................................... 18 test article simulating theConduction nozzle divergent were positioned downstream of the twin nozzle. The K. Rakesh, M. Ajith, Dr. instrumented T. Jayachandran & Raju K. George was extensively toDr. evaluate heat flux distribution. Maximum heat flux occurred at 00 19.
20.
plane indicating maximum plume impingement in that region and the jet impinging Thermo-Structural Design and Analysis of interaction A Supersonic and Diffuser pressures were also recorded. Experimental results were useful for evolving a suitable thermal for High Temperature Applications ............................................................................................................................. 19 protection system design needed in the nozzle divergent. Atha Ur Rahman Khan, A. Yezhil Arasu, Thomas Kurian, P.J. Abraham & V. Srinivasan Thermophysical Properties Measurement of Aerospace Material ...................................................................... 20 Fazil Mohammad, K.P. Subhajayan, T.P. Shivadasan, S. Krishnamoorthy C. Jasperlal, P.O. Balachandran & P.A. Krishnamoorthy
21.
Solid Rocket Booster Flex Seal Moulding â&#x20AC;&#x201C; Cure Cycle Estimation ................................................................... 21 Jose Paul, S. Kartheekeyan, V. Mahesh, K.P. Subhajayan, V. Eswaran & V. Srinivasan
22.
High Temperature Storage Heater Design for Propulsion Facility ..................................................................... 22 Samik Jash, Jose Paul, Praveen Kumar, C. Jasperlal, Dr. T. Jayachandran P.O. Balachandran & P.A. Krishnamoorthy
23.
Performance Evaluation of Thermal Control System of A Typical Manned Spacecraft ................................. 23 Samik Jash, C. Pedda Peeraiah, Dr. T. Jayachandran & P.A. Krishnamoorthy
The Aeronautical Society of India, Thiruvananthapuram Branch
24
The Aeronautical Society of India, Thiruvananthapuram Branch
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
AN APPROXIMATE METHOD FOR PREDICTING THE HOTSPOTS IN ON LARGE AIR COOLED EXPERIMENTAL STUDIES SUPERSONIC ELECTRONIC SYSTEMS WITH REPEATED UNITS FILM COOLING EFFECTIVENESS FOR LARGE AREA RATIO NOZZLES B. Divya M. Tech, Aerospace Engg. K. Krishnaraj, R. Sujith Kumar, P. Sridharan Indian Institute of Technology, Madras C.Jasperlal & P.A. Krishnamoorthy Chennai Vikram SarabhaiK.M. Space Centre Srikumar Thiruvananthapuram Scientist, CABS, DRDO Bangalore
S. Christopher ABSTRACT
Director, CABS, DRDO Bangalore Injection of turbine exhaust gas into the nozzle divergent is an attractive option for film cooling of nozzle divergent of advanced cryo engines. has got twin advantages in terms of AmitThis Kumar Associate Professorspecific impulse for the engines. hardware weight reduction and marginal improvement in realizable Aerospace Engg. In order to demonstrate the supersonic film cooling effectiveness in the nozzle divergent, experimental Indian Institute of Technology programme was undertaken wherein tests were carried out using 50Madras area ratio and 70 area ratio Chennai nozzles in a high altitude test facility having self starting diffuser system. A solid motor with non aluminized propellant system and a large area ratio nozzle with provision for injection of gaseous hydrogen at area ratio 10 was used for the tests. Measurements for determining the heat flux along ABSTRACT the nozzle wall down stream of injection point were carried out. The test data clearly established supersonic film The cooling effectiveness downunit stream of the up array to nozzle active antenna array (AAAU) is aninjection airbornepoint antenna unit exit. used This for airborne concept early study warning has shown that supersonic film cooling is very promising and can be used in the cryo and control. Appropriate cooling of electronic components inside AAAU is crucial for engine having higher area ratio nozzles for performance its effective functioning and hence the mission. gain/gain This studyinispayload. taken up to estimate the maximum surface temperatures attained by electronic components during operation of AAAU. The electronic systems such as AAAU have massive structure for which a full simulation of conjugate heat transfer (conduction + forced convection) is at present computationally prohibitive, therefore an approximate approach is adopted here. This approach involves a combination of detailed flow simulation of the full AAAU for estimating flow and pressure distribution and a parametric study of flow and temperature on individual components with detailed conjugate heat transfer simulations. The information from the former along with lumped heat transfer analysis can be used to get an estimate on the location and magnitude of hotspots that can occur within the system.
1
The Aeronautical Society of India, Thiruvananthapuram Branch The Aeronautical Society of India, Thiruvananthapuram Branch
25
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
12.
Design, Realisation and Qualification of A Conductively Cooled Cryostat for Igniter Cold Soak/Firing Test at Low Temperatures ....................................................................................... 12
AERO THERMO STRUCTURAL ANALYSIS OF A Heat Transfer SUB-SCALE Analysis of An Ablative Throat Insert for Liquid with Film Cooling .......................... 13 MODEL OF Engine CRYOGENIC NOZZLE
R. Sujithkumar, Abhishek Kumar, V. Arun & Sreeram Banerjee 13.
R. Harikrishnan
Vinay Kumar Srivastava, Shailesh Prasad, K. Jagannathan & Dr. S.B. Tiwari
14.
Impact of Cryo Temperature on Separation Connectors of A Launch Vehicle .............................................. 14 Vikram Sarabhai Space Centre K.S. Lakshmi, P. Anoop, B. Sundar & M.J. Chacko Thiruvananthapuram
15.
Thermal Structural Analysis of A Cryogenic Engine Turbopump Impeller ........................................................ 15
ABSTRACT
Krishnajith Jayamani, A.K. Asraff, R. Muthukumar, T.M. Phillip 16.
17.
Experimental Investigation on the Convective Heat Transfer from Cryogenic engines the key Cooling option ....................................................................................... available for the upper stages of space missions. Due A 3D Heated Block Subjected to are Impingement 16
to the working conditions forPrabhu, cryogenic engine the &temperature Ullekh Pandey, Philip George, M. Ram T.V. Radhakrishnan M.J. Chacko in the nozzle can be above 2500K. With such high temperature the material and structure are subjected to extreme conditions. This Conjugate Study A Pyrovalve and Experimental Validation by IR Heating ................................................... requires an of effective cooling technique like regenerative cooling in convergent area,17dumped and Suveer Singh, Md Moinuddin Ani D. Kurien, Kumar material and structural integrity. Supersonic film radiative cooling in Hassan, divergent area to H. ensure Dr. cooling A.G. Rajendran, Subhajayan & C. Jasperlal is alsoK.P. one of the effective techniques which can be used for cooling the divergent area of
18.
19.
nozzle in dumped cooling. To study the flow Application of place GPGPUofProgramming to Numerical Simulation of parameters of supersonic film cooled nozzle experimentally, the subProblems scale model of cryogenic nozzle is designed [1]. The objective of the Steady-State Heat Conduction ................................................................................................................... 18
present work is to simulate the sub scale nozzle through analysis for thermal and structural loads. K. Rakesh, M. Ajith, Dr. T. Jayachandran & Dr. Raju K. George The flow parameters of the model are obtained using computational fluid dynamics software FLUENT Thermo-Structural and Analysis of A Supersonic Diffuser for two, cases Design namely nozzle without cooling and double wall nozzle with water cooling. The surface for heat High Temperature Applicationsand ............................................................................................................................. 19 analysis. transfer coefficient gas temperature on nozzle wall are obtained from flow AthaTransient Ur Rahmanthermal Khan, A. Yezhil Arasu,is Thomas Kurian, & V. Srinivasan analysis carried out P.J. to Abraham obtain the temperature distribution. The pressure
20.
21.
variation along the axis of the nozzle obtained from flow analysis and temperature distribution Thermophysical Properties Measurement of Aerospace Material ...................................................................... 20 from thermal analysis is used for the thermo structural analysis. Thermo-structural analysis was Fazil Mohammad, K.P. Subhajayan, T.P. Shivadasan, S. Krishnamoorthy carried out for two different materials, Stainless Steel and Inconel. Thickness of material has been C. Jasperlal, P.O. Balachandran & P.A. Krishnamoorthy worked out for pressure and thermal loads corresponding the operating conditions of nozzle. Solid Rocket Booster Flex Seal Moulding â&#x20AC;&#x201C; Cure Cycle Estimation ................................................................... 21 Jose Paul, S. Kartheekeyan, V. Mahesh, K.P. Subhajayan, V. Eswaran & V. Srinivasan
22.
High Temperature Storage Heater Design for Propulsion Facility ..................................................................... 22 Samik Jash, Jose Paul, Praveen Kumar, C. Jasperlal, Dr. T. Jayachandran P.O. Balachandran & P.A. Krishnamoorthy
23.
Performance Evaluation of Thermal Control System of A Typical Manned Spacecraft ................................. 23 Samik Jash, C. Pedda Peeraiah, Dr. T. Jayachandran & P.A. Krishnamoorthy
The Aeronautical Society of India, Thiruvananthapuram Branch
26
The Aeronautical Society of India, Thiruvananthapuram Branch
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
AN APPROXIMATE METHOD FOR PREDICTING THE HOTSPOTS IN LARGE AIR HEAT FLUX DISTRIBUTION ON COOLED ELECTRONIC SYSTEMS REPEATED UNITS A HYPERSONIC AIRWITH INTAKE B. Divya & S. Subramanian R. Saravanan, J.A. Tennyson, S. Gnanasekar M. Tech, Aerospace Vikram Sarabhai Space Centre Engg. Indian Institute of Technology, Madras Thiruvananthapuram Chennai
K.M. Srikumar
ABSTRACT Scientist, CABS, DRDO Bangalore Prediction of heat flux distribution on hypersonic air intake plays a vital role in providing S. Christopher input for selection of suitable thermal protection system. Hypersonic air intake has higher heat Director, CABS, DRDO transfer rates due to flow speed, shock-shock interactions, shock-boundary layer interaction, flow Bangalore reattachment, etc. Hence empirical methods are not amenable for prediction of wall heat transfer Amit Kumar inside the hypersonic air intake. Experimental study is carried out to predict heat flux distribution Associate Professor on a hypersonic air intake. The geometry considered for the study Aerospace Engg. consists of external compression ramps, drooped cowl, expansion rampsIndian and fuel injection struts. Experiment Institute of Technology Madras is carried out in the shock tunnel facility at Mach 6, flow enthalpy varied between 1.5 to 2.3 MJ/kg and Reynolds Chennai number is 0.2 million (based on ramp length) which indicate the flow is laminar. Heat transfer rates are obtained from temperature measurements using fast response co-axial thermocouples and are ABSTRACT measured at critical locations such as flow separation, shock impingement, shock-BL interaction, etc. High heat transfer rate of about 100W/cm2 is observed at reattachment region near expansion The active antenna array unit (AAAU) is an airborne antenna array unit used for airborne corner due to shock-boundary layer interaction. Shock-shock interaction at flow blockage region is early warning and control. Appropriate cooling of electronic components inside AAAU is crucial for also experiencing high heat flux levels of about 75 W/cm 2. Lower heat loads are observed at its effective functioning and hence the mission. This study is taken up to estimate the maximum expansion corners. surface temperatures attained by electronic components during operation of AAAU. The electronic systems such as AAAU have massive structure for which a full simulation of conjugate heat transfer (conduction + forced convection) is at present computationally prohibitive, therefore an approximate approach is adopted here. This approach involves a combination of detailed flow simulation of the full AAAU for estimating flow and pressure distribution and a parametric study of flow and temperature on individual components with detailed conjugate heat transfer simulations. The information from the former along with lumped heat transfer analysis can be used to get an estimate on the location and magnitude of hotspots that can occur within the system.
1
The Aeronautical Society of India, Thiruvananthapuram Branch The Aeronautical Society of India, Thiruvananthapuram Branch
27
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
12.
Design, Realisation and Qualification of A Conductively Cooled Cryostat for Igniter Cold Soak/Firing Test at Low Temperatures ....................................................................................... 12
13.
ADVANCED DESIGNS OF REGENERATIVE Heat Transfer Analysis of An Ablative Insert for Liquid Engine with FilmLIQUID Cooling .......................... 13 COOLING FORThroat HIGH HEAT FLUX ENGINES R. Harikrishnan FOR IMPROVED ENGINE LIFE CYCLE
14.
Impact of Cryo Temperature on Separation Connectors of A Launch Vehicle .............................................. 14
15.
A.P. Dr. V. Narayanan & C.H. Kunhikammaran K.S. Lakshmi, P. Anoop, B. Baiju, Sundar &G. M.J.Remesh, Chacko Liquid propulsion systems centre Thermal Structural Analysis of A Cryogenic Engine Turbopump Impeller ........................................................ 15 Thiruvananthapuram Krishnajith Jayamani, A.K. Asraff, R. Muthukumar, T.M. Phillip
16.
Experimental Investigation on the Convective Heat Transfer from
R. Sujithkumar, Abhishek Kumar, V. Arun & Sreeram Banerjee
ABSTRACT
A 3D Heated Block Subjected to Impingement Cooling ....................................................................................... 16 Ullekh Pandey, Philip George, Ram Prabhu, T.V. Radhakrishnan & M.J. Chacko Liquid rocket M. engines are providing the highest performance even in the booster stages 17.
18.
where Study high thrust is essentially required. Validation Hence either propellant engines or semi Conjugate of A Pyrovalve and Experimental by IR storable Heating ................................................... 17 cryogenic propellant evenAni cryogenic Suveer Singh, Md engines Moinuddinor Hassan, D. Kurien, engines H. Kumar are considered as the candidate for the booster engines. The liquid high thrust engine demands higher combustion chamber pressure, which generates Dr. A.G. Rajendran, K.P. Subhajayan & C. Jasperlal extreme levels of heat flux, specifically at the throat of the chamber. Most of the engines are Application of GPGPU Programming to Numerical Simulation of regenerative cooled one, wherein one of the propellants (generally fuel) is used as the regenerative Steady-State Conduction coolant, Heat passing throughProblems coolant................................................................................................................... channels which absorbs the heat energy from the 18 chamber and K. Rakesh, M. cooling Ajith, Dr. T.effect Jayachandran & Dr. Raju Since K. George thereby is generated. the absorbed energy augments the enthalpy of the
19.
20.
coolant, which is ultimately in to the chamber for combustion and thereby energy is Thermo-Structural Design and Analysisinjected of A Supersonic Diffuser regenerated, resulting in an improved engine performance. The coolant channel design plays the for High Temperature Applications ............................................................................................................................. 19 most key role in the regenerative cooling performance. The different improved channel designs Atha Ur Rahman Khan, A. Yezhil Arasu, Thomas Kurian, P.J. Abraham & V. Srinivasan based on the need aspect of the thrust chamber and use are summarized. This include helical Thermophysical Properties Measurement of Aerospace Material ...................................................................... channels, high aspect ratio coolant passages, artificial roughness on the channels,20foam filled Fazilchannels, Mohammad, K.P. Subhajayan, T.P. Shivadasan, Krishnamoorthy transpiration cooled channels S.and doubling of coolant channels. Each case is technically C. Jasperlal, P.O.with Balachandran & P.A. described its merits for Krishnamoorthy the intended objective and the limitations as well. The modern designs
21.
of the coolant channels for regenerative cooling with its technical merits and limitations are presented Solid Rocket Booster Flex Seal Moulding â&#x20AC;&#x201C; Cure Cycle Estimation ................................................................... 21 in this paper. Jose Paul, S. Kartheekeyan, V. Mahesh, K.P. Subhajayan, V. Eswaran & V. Srinivasan
22.
High Temperature Storage Heater Design for Propulsion Facility ..................................................................... 22 Samik Jash, Jose Paul, Praveen Kumar, C. Jasperlal, Dr. T. Jayachandran P.O. Balachandran & P.A. Krishnamoorthy
23.
Performance Evaluation of Thermal Control System of A Typical Manned Spacecraft ................................. 23 Samik Jash, C. Pedda Peeraiah, Dr. T. Jayachandran & P.A. Krishnamoorthy
The Aeronautical Society of India, Thiruvananthapuram Branch
28
The Aeronautical Society of India, Thiruvananthapuram Branch
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
AN APPROXIMATE METHOD FOR PREDICTING THE HOTSPOTS LARGE AIR COOLED ELECTRON DENSITYINCOMPUTATIONS ELECTRONIC SYSTEMS WITH REPEATED UNITS FOR LANGMUIR PROBE UNDER PLASMA FLOW CONDITIONS B. Divya M. Tech, Aerospace Engg. N. Uday Bhaskar, C. Indian Unnikrishnan Aravindakshan Institute & of L. Technology, Madras Pillai Vikram Sarabhai Space Centre Chennai Thiruvananthapuram K.M. Srikumar Scientist, CABS, DRDO Bangalore ABSTRACT
S. Christopher
Director, CABS, DRDO Electron density is computed on a rounded wedge model under plasma flow conditions of Bangalore high enthalpy facility with real gas effects using UNS3D solver. UNS3D is an in-house code, well Amit Kumar CFD analysis for electron number validated for hypersonic flows with equilibrium air computations. Professor density is done in two steps, first axi-symmetricAssociate nozzle flow conditions are simulated from plasma Engg. conditions for 2D analysis for chamber and then the nozzle exit conditions areAerospace used as upstream Indian Institute of Technology Madras flow past the rounded wedge model on which Langmuir probe is located. Computed electron number Chennai density compare well with experimental measurements. Langmuir probe is an electrostatic probe, widely used for measurement of electron density in the flows at elevated temperatures. Electrode, ABSTRACT which is the sensing element of Langmuir probe protrudes out in the normal direction to the surface of the wedge model at slanted region, it is the The active array unit (AAAU) airborne array unit used for airborne tip of the protrusion where,antenna computed electron densityisisan reported in antenna this particular work. early warning and control. Appropriate cooling of electronic components inside AAAU is crucial for its effective functioning and hence the mission. This study is taken up to estimate the maximum surface temperatures attained by electronic components during operation of AAAU. The electronic systems such as AAAU have massive structure for which a full simulation of conjugate heat transfer (conduction + forced convection) is at present computationally prohibitive, therefore an approximate approach is adopted here. This approach involves a combination of detailed flow simulation of the full AAAU for estimating flow and pressure distribution and a parametric study of flow and temperature on individual components with detailed conjugate heat transfer simulations. The information from the former along with lumped heat transfer analysis can be used to get an estimate on the location and magnitude of hotspots that can occur within the system.
1
The Aeronautical Society of India, Thiruvananthapuram Branch The Aeronautical Society of India, Thiruvananthapuram Branch
29
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
12.
Design, Realisation and Qualification of A Conductively Cooled Cryostat for Igniter Cold Soak/Firing Test at Low Temperatures ....................................................................................... 12
INNOVATIVE THERMAL DISTORTION Heat Transfer MANAGEMENT Analysis of An Ablative Throat Insert for Liquid Engine with Film Cooling .......................... 13 TECHNIQUE FOR VERY HIGH R. Harikrishnan POWER (260W) NARROW BAND - WAVE GUIDE Impact of Cryo Temperature on Separation Connectors of A Launch Vehicle .............................................. 14 BAND PASS FILTERS FOR SPACE USE K.S. Lakshmi, P. Anoop, B. Sundar & M.J. Chacko R. Sujithkumar, Abhishek Kumar, V. Arun & Sreeram Banerjee
13.
14.
15.
Thermal Structural Analysis of A Cryogenic Engine Turbopump ........................................................ 15 K. Karthik, RajnikantImpeller & A.V. Pathak
16.
Applications Centre Krishnajith Jayamani, A.K. Asraff, R. Muthukumar,Space T.M. Phillip Ahmedabad Experimental Investigation on the Convective Heat Transfer from A 3D Heated Block Subjected to Impingement Cooling ....................................................................................... 16
ABSTRACT
Ullekh Pandey, Philip George, M. Ram Prabhu, T.V. Radhakrishnan & M.J. Chacko 17.
18.
19.
20.
21.
22.
23.
Conjugate Study A Pyrovalve and Experimental Validation IR Heating ................................................... 17 High ofpower Waveguide Band Pass Filters by (BPF) are an integral part of a communication Suveer Singh, Md Moinuddin Hassan, D. Kurien, H. Kumar satellite transponder. As anyAni typical narrow band microwave filter, the high power BPF's are highly Dr. sensitive A.G. Rajendran, K.P. Subhajayan C. Jasperlal to dimensions and&shape of the enclosure which needs to be controlled in the order of 20 microns. The main cause of dimensional deviations is the payload operating temperature range Application of GPGPU Programming to Numerical Simulation of i.e -5 Deg C to +65 Deg C. When the BPF operates in this wide range, it becomes a challenging task Steady-State Heat Conduction Problems ................................................................................................................... 18 to restrict the dimensional variation of the enclosure within 20 microns. K. Rakesh, M. Ajith, Dr. T. Jayachandran & Dr. Raju K. George To achieve good dimensional stability over a wide temperature range, Invar alloy is used to Thermo-Structural Design and of A Supersonic Diffuserof thermal expansion (CTE-1.5 x 10-6 ppm/0C). fabricate the filters dueAnalysis to its very low co-efficient for The High Insertion Temperature 19 has to be lossApplications (IL) of the............................................................................................................................. BPF during operation is dissipated in the form of heat and Athatransported Ur Rahman Khan, A. space Yezhil Arasu, Kurian, P.J. Abraham & V.pipes, Srinivasan to the craft Thomas panel embedded with heat which acts as a heat sink. But invar being a poor conductor of heat (thermal conductivity11 W/m.k), the removal of heat Thermophysical Properties Measurement of Aerospace Material ...................................................................... 20 from the BPF becomes a challenge since conduction and radiation are the only modes of heat transfer Fazil Mohammad, K.P. Subhajayan, T.P. Shivadasan, S. Krishnamoorthy available in vacuum. The traditional design uses high thermal conductivity Al-alloy 6061 support C. Jasperlal, P.O. Balachandran & P.A. Krishnamoorthy brackets to remove heat from BPF. The brackets are a dual purpose component which plays the role Solid Booster Flex Seal Moulding â&#x20AC;&#x201C; Cure ................................................................... ofRocket heat conductor between the BPF and Cycle SpaceEstimation craft panel as well as structural support21to withstand loads. The traditional design caters only to&wide band filters, whose heat dissipation is Joselaunch Paul, S. Kartheekeyan, V. Mahesh, K.P. Subhajayan, V. Eswaran V. Srinivasan considerably less. High Temperature Storage Heater Design for Propulsion Facility ..................................................................... 22 ThePaul, difference in thermal expansion of Invar alloy and Al alloy (CTE- 1.5 ppm / 0C) and Samik Jash, Jose Praveen Kumar, C. Jasperlal, Dr. T. Jayachandran Al-6061 (CTE- 23.4 ppm / 0C) results in a complex thermal-structural problem which makes the P.O. Balachandran & P.A. Krishnamoorthy design challenging. To remove heat effectively from the BPF, higher contact area at the BPFPerformance Evaluation ofand Thermal System A Typical Manned Spacecraft ................................. 23 bracket interface thickControl brackets are ofpre-requisites. But doing so results in higher thermal Samik Jash, C. Pedda Peeraiah, Dr. T. Jayachandran & P.A. Krishnamoorthy stresses at the interfaces and distortion of the BPF enclosure.
A novel design solution for controlling thermal distortion in high power narrow band BPF's has been demonstrated using CAD/CAE tools which satisfies both thermal and structural requirements. The Aeronautical Society of India, Thiruvananthapuram Branch
30
The Aeronautical Society of India, Thiruvananthapuram Branch
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
AN APPROXIMATE METHOD FOR PREDICTING THEAND HOTSPOTS IN LARGE AIR COOLED TESTING EVALUATION OF THERMAL ELECTRONICSYSTEM SYSTEMS WITH REPEATED PROTECTION MATERIALS UNDER UNITS SIMULATED RE-ENTRY THERMAL B. Divya ENVIRONMENTS M. Tech, Aerospace Engg. N. Sreenivas, K. Krishnaraj, Indian L. Aravindakshan Pillai & P.A. Krishnamoorthy Institute of Technology, Madras Vikram Sarabhai Space Centre Chennai Thiruvananthapuram K.M. Srikumar Scientist, CABS, DRDO Bangalore ABSTRACT
S. Christopher
Director, CABS, DRDO when it is subjected to low Thermal protection system (TPS) materials behave uniquely density high enthalpy flow environment existing duringBangalore atmospheric entry. Their qualification requires Amit KumarArc heated high enthalpy facilities ground simulation of such extreme aero-thermal environment. Associate Professor are the only means for ground simulation of these environment on the test models for sufficiently Engg. long test durations. Such facilities are extensively Aerospace used for the last five decades for this purpose. In Indian Institute of Technology Madrasand made operational Vikram Sarabhai Space Centre, arc heated test facilities were developed Chennai through in-house R&D programs and cater to qualification requirements of TPS materials for ISRO's present and future atmospheric entry missions. In this paper, details of arc heated 1 MW high enthalpy facility, its simulation capabilities and typical tests carried out are explained. ABSTRACT The active antenna array unit (AAAU) is an airborne antenna array unit used for airborne early warning and control. Appropriate cooling of electronic components inside AAAU is crucial for its effective functioning and hence the mission. This study is taken up to estimate the maximum surface temperatures attained by electronic components during operation of AAAU. The electronic systems such as AAAU have massive structure for which a full simulation of conjugate heat transfer (conduction + forced convection) is at present computationally prohibitive, therefore an approximate approach is adopted here. This approach involves a combination of detailed flow simulation of the full AAAU for estimating flow and pressure distribution and a parametric study of flow and temperature on individual components with detailed conjugate heat transfer simulations. The information from the former along with lumped heat transfer analysis can be used to get an estimate on the location and magnitude of hotspots that can occur within the system.
1
The Aeronautical Society of India, Thiruvananthapuram Branch The Aeronautical Society of India, Thiruvananthapuram Branch
31
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
12.
Design, Realisation and Qualification of A Conductively Cooled Cryostat for Igniter Cold Soak/Firing Test at Low Temperatures ....................................................................................... 12
EXPERIMENTAL VERIFICATION OF EFFECTIVENESS Heat Transfer Analysis of An Ablative Throat Insert for Liquid Engine with SYSTEM Film Cooling .......................... 13 OF SPRAY COOLING
R. Sujithkumar, Abhishek Kumar, V. Arun & Sreeram Banerjee 13.
R. Harikrishnan
Jose Paul, K.P. Subhajayan, C. Jasperlal & P.O. Balachandran
14.
Impact of Cryo Temperature on Separation Connectors of A Launch Vehicle .............................................. 14 Vikram Sarabhai Space Centre K.S. Lakshmi, P. Anoop, B. Sundar & M.J. Chacko Thiruvananthapuram
15.
Thermal Structural Analysis of A Cryogenic Engine Turbopump Impeller ........................................................ 15
ABSTRACT
Krishnajith Jayamani, A.K. Asraff, R. Muthukumar, T.M. Phillip 16.
Experimental Investigation on the Convective Heat Transfer from In Block horizontal mode static testing of solid motors with submerged nozzle; after A 3D Heated Subjected to Impingement Cooling ....................................................................................... 16 motor burn
17.
out, the entrapped (slag) in the submerged nozzle region will flow back to bottom Ullekh Pandey, Philip George,molten M. Ramalumina Prabhu, T.V. Radhakrishnan & M.J. Chacko of the segments. For S200 motor tested by ISRO, this problem has resulted in severe damage of the Conjugate StudyHence of A Pyrovalve andcooling Experimental Validation by IR Heating ................................................... 17 hardware. an active system was designed for preventing this.
18.
Suveer Singh, Md Moinuddin Hassan, Ani D. Kurien, H. Kumar A series of simulation tests has been carried out to study the effectiveness of the spray Dr. A.G. Rajendran, K.P. Subhajayan & C. Jasperlal cooling system. This paper describes the cooling system conceptual design, heat transfer analysis Application GPGPU Programming to Numerical Simulation of cooling system. and theoftests carried out to verify the efficacy of the Steady-State Heat Conduction Problems ................................................................................................................... 18 K. Rakesh, M. Ajith, Dr. T. Jayachandran & Dr. Raju K. George
19.
Thermo-Structural Design and Analysis of A Supersonic Diffuser for High Temperature Applications ............................................................................................................................. 19 Atha Ur Rahman Khan, A. Yezhil Arasu, Thomas Kurian, P.J. Abraham & V. Srinivasan
20.
Thermophysical Properties Measurement of Aerospace Material ...................................................................... 20 Fazil Mohammad, K.P. Subhajayan, T.P. Shivadasan, S. Krishnamoorthy C. Jasperlal, P.O. Balachandran & P.A. Krishnamoorthy
21.
Solid Rocket Booster Flex Seal Moulding â&#x20AC;&#x201C; Cure Cycle Estimation ................................................................... 21 Jose Paul, S. Kartheekeyan, V. Mahesh, K.P. Subhajayan, V. Eswaran & V. Srinivasan
22.
High Temperature Storage Heater Design for Propulsion Facility ..................................................................... 22 Samik Jash, Jose Paul, Praveen Kumar, C. Jasperlal, Dr. T. Jayachandran P.O. Balachandran & P.A. Krishnamoorthy
23.
Performance Evaluation of Thermal Control System of A Typical Manned Spacecraft ................................. 23 Samik Jash, C. Pedda Peeraiah, Dr. T. Jayachandran & P.A. Krishnamoorthy
The Aeronautical Society of India, Thiruvananthapuram Branch
32
The Aeronautical Society of India, Thiruvananthapuram Branch
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
AN APPROXIMATE METHOD FOR PREDICTING THE PERFORMANCE HOTSPOTS IN LARGE AIR COOLED TRANSIENT OF CROSS-FLOW ELECTRONIC SYSTEMS WITH UNITS PLATE-FIN HEAT EXCHANGERS FORREPEATED HSP MISSION B. Divya N. Mansu & P.O. Balachandran
M. Tech, Aerospace Vikram Sarabhai Space Centre Engg. Indian Institute of Technology, Madras Thiruvananthapuram Chennai
K.M. Srikumar
ABSTRACT Scientist, CABS, DRDO Bangalore ISRO has initiated a program for manned space missions. A very critical requirement for a S. Christopher manned space mission is a crew cabin environmental conditioning, which primarily involves ensuring Director, CABS, DRDO oxygen availability, temperature and humidity control for crew safety and comfort. The systems Bangalore must necessarily be compact and light weight. The present work highlights a prediction scheme for Amit Kumar a compact heat exchanger - an essential component of thermal control system. The heat exchanger Associate Professor is conceived for temperature control of air in the Aerospace crew cabin.Engg. The heat exchanger, a plate fin type ethylene glycol-water mixture to cool cabin air. We have with compactness of 1680 m2/m3, usesIndian Institute of Technology Madras considered the energy balance for both fluids as well as for the separating plate. The algorithm has Chennai been further extended for transient analysis of the multipass flow arrangement.
ABSTRACT The active antenna array unit (AAAU) is an airborne antenna array unit used for airborne early warning and control. Appropriate cooling of electronic components inside AAAU is crucial for its effective functioning and hence the mission. This study is taken up to estimate the maximum surface temperatures attained by electronic components during operation of AAAU. The electronic systems such as AAAU have massive structure for which a full simulation of conjugate heat transfer (conduction + forced convection) is at present computationally prohibitive, therefore an approximate approach is adopted here. This approach involves a combination of detailed flow simulation of the full AAAU for estimating flow and pressure distribution and a parametric study of flow and temperature on individual components with detailed conjugate heat transfer simulations. The information from the former along with lumped heat transfer analysis can be used to get an estimate on the location and magnitude of hotspots that can occur within the system.
1
The Aeronautical Society of India, Thiruvananthapuram Branch The Aeronautical Society of India, Thiruvananthapuram Branch
33
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
12.
Design, Realisation and Qualification of A Conductively Cooled Cryostat for Igniter Cold Soak/Firing Test at Low Temperatures ....................................................................................... 12
AUTHOR INDEX
R. Sujithkumar, Abhishek Kumar, V. Arun & Sreeram Banerjee 13.
14.
15.
16.
Heat Transfer Analysis of An Ablative Throat Insert for Liquid Engine with Film Cooling .......................... 13
H A R. Harikrishnan Abhishek Jain 2 Hariharan V K 6 Impact of Cryo Temperature on Separation Connectors of A Launch Vehicle .............................................. 14 Abhishek Kumar 12 Harikrishnan R 13 K.S.Abraham Lakshmi,P P. Anoop, B. Sundar & M.J. Chacko J 19 Hrisheekesh Krishnan 3 Ajith MStructural 18 Thermal Analysis of A Cryogenic Engine Turbopump Impeller ........................................................ 15 J Amit Kumar 1 Krishnajith Jayamani, A.K. Asraff, R. Muthukumar, T.M. Phillip Jagannathan K 26 Anand A R 6 Jasperlal C 17,20,24,25,32 Experimental on the Convective Heat Transfer from Ani D KurienInvestigation 17 Jayachandran,Dr.T 3,18,22,23 A 3D Heated Anoop P 14Block Subjected to Impingement Cooling ....................................................................................... 16 Jose Paul 10,21,22,32 Ullekh Pandey, Philip M. Ram Prabhu, T.V. Radhakrishnan & M.J. Chacko Aravindakshan PillaiGeorge, 7,8,11,12,29,31 K
17.
18.
19.
20.
21.
22.
23.
Arun V 11,12 Conjugate Study of A Pyrovalve and Experimental Validation byKartheekeyan IR Heating ................................................... 17 S 21 Asraff A K 15 Suveer Singh, Md Moinuddin Hassan, Ani D. Kurien, H. Kumar Karthik K 30 Atha Ur Rahman Khan 19 Dr. A.G. Rajendran, K.P. Subhajayan & C. Jasperlal Karthikeyan K 5 B Krishnajith Jayamani 15 Application Baiju A P of28GPGPU Programming to Numerical Simulation of Krishnamoorthy P A 7,8,11,20,22,23,24,25,31 Steady-State Heat Balachandran P OConduction 20,22,32,33Problems ................................................................................................................... 18 Krishnamoorthy S 20 K. Rakesh, Ajith, Dr. T. Jayachandran & Dr. Raju K. George Barve S M. G 4,5 Krishnaraj K 7,8,24,25,31 Bindagi S V 4 Kumar H 17 Thermo-Structural Design and Analysis of A Supersonic Diffuser C Kunhikammaran C H 28 for High Temperature Applications ............................................................................................................................. 19 Chacko M J 14,16 Atha Ur Rahman Khan, A. Yezhil Arasu, Thomas Kurian, P.J. AbrahamL & V. Srinivasan Chaitanya B S 4 Lakshmi K S 14 Thermophysical Properties Chiranjeevi Phanindra B 3 Measurement of Aerospace Material ...................................................................... 20 M FazilChristopher Mohammad, S 1K.P. Subhajayan, T.P. Shivadasan, S. Krishnamoorthy Mahesh V 21 C. Jasperlal, P.O. Balachandran & P.A. Krishnamoorthy D Manna S S 6 Dinesh Kumar 6 Solid Rocket Booster Flex Seal Moulding â&#x20AC;&#x201C; Cure Cycle Estimation ................................................................... 21 Mansu N 33 Divya B 1 Jose Paul, S. Kartheekeyan, V. Mahesh, K.P. Subhajayan, V. EswaranMd & Moinuddin V. Srinivasan Hassan 17 E Md...................................................................... Shaukat Ali 9 High Temperature Storage Heater Design for Propulsion Facility 22 Eswaran V 21 Mohammed Ali A 6 Samik Jash, Jose Paul, Praveen Kumar, C. Jasperlal, Dr. T. Jayachandran Muthukumar R 15 F P.O. Balachandran & P.A. Krishnamoorthy N FazilMohammad 20 Performance Evaluation of Thermal Control System of A Typical MannedDr. Spacecraft Narayanan V 28 ................................. 23 G Samik Jash, C. Pedda Peeraiah, Dr. T. Jayachandran & P.A. Krishnamoorthy P Gandhi B K 9 Gnanasekar S 24 Pathak A V 30 Govinda V 6 Pedda Peeraiah C 23 The Aeronautical Society of India, Thiruvananthapuram Branch
34
The Aeronautical Society of India, Thiruvananthapuram Branch
National Conference on Advances in Thermophysics and Heat Transfer National Conference on Advances in Thermophysics and Heat Transfer
AN APPROXIMATE METHOD FOR PREDICTING Philip George 16 KM 1 THE HOTSPOTS Srikumar IN LARGE AIR COOLED Phillip T M 15 Srinivasan V 19 WITH REPEATED UNITS Praveen Kumar 22 ELECTRONIC SYSTEMS Subhajayan K P 10,17,20,21,32 Pugazenthi R S 7,8
R Radhakrishnan T V 16 Rahul Kumar R. R 3 Rajan GVC 6 Rajendran Dr A G 17 Rajnikant 30 Raju K George Dr 18 Rakesh K 18 Ram Prabhu M 16 Remesh G 28 Rishi Padmanabhan 3 Rohan V Kedare 2
Subramanian S 27 B. Divya Sujithkumar R 11,12,25 M. Tech, Aerospace Engg. Sundar B 14 Indian Institute ofSingh Technology, Madras Suveer 17 Chennai
S
T
K.M. Srikumar
Tariq A 9 Scientist, CABS, DRDO Tennyson J A 27 Bangalore Thomas Kurian 19 S.Tiwari Christopher Dr S B 26 Director, CABS, DRDO UBangalore Uday Bhaskar N 29 Amit Kumar Ullekh Pandey 16 Associate Professor UnnikrishnanEngg. C 29 Aerospace
V of Technology Madras Indian Institute Samik Jash 22,23 Chennai Venkat Reddy P 4 Saravanan R 27 Vilas R Kalamkar, Dr 2 Shailesh Prasad 26 Vinay Kumar Srivastava 26 Shashishekar R 4 ABSTRACT Vinay Unnikrishnan 7,8 Shivadasan TP 20 Sreenivas N 7,8,31 The active antenna array unit (AAAU) Y is an airborne antenna array unit used for airborne Sreeram Banerjee 11,12 Yezhil of Arasu A 19 early warning and control. Appropriate cooling electronic components inside AAAU is crucial for Sridharan P 24,25 its effective functioning and hence the mission. This study is taken up to estimate the maximum surface temperatures attained by electronic components during operation of AAAU. The electronic systems such as AAAU have massive structure for which a full simulation of conjugate heat transfer (conduction + forced convection) is at present computationally prohibitive, therefore an approximate approach is adopted here. This approach involves a combination of detailed flow simulation of the full AAAU for estimating flow and pressure distribution and a parametric study of flow and temperature on individual components with detailed conjugate heat transfer simulations. The information from the former along with lumped heat transfer analysis can be used to get an estimate on the location and magnitude of hotspots that can occur within the system.
1
The Aeronautical Society of India, Thiruvananthapuram Branch The Aeronautical Society of India, Thiruvananthapuram Branch
35
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