International Journal of Research and Innovation (IJRI)
International Journal of Research and Innovation (IJRI) 1401-1402
THERMAL INVESTIGATION ON PROPELANT TANK MATERIAL BY USING FEM APPROACH
Chellapilla Vamsi Krishna1, V.V.Kamesh2 , S.N.CH.Dattu.V3 1 Research Scholar, Department of Thermal Engineering, Aditya Engineering College, Surampalem, Andra Pradesh, India. 2 Associate Professor , Department of Mechanical Engineering, Aditya Engineering College, Surampalem, Andra Pradesh, India. 3 Assistant Professor, Department of Mechanical Engineering, Aditya Engineering College, Surampalem, Andra Pradesh, India.
Abstract Rocket propellant tanks are pressure vessels where liquid fuels are stored prior to use. They have to store the propellant; propellant combinations are used in rocket engines where the propellants spontaneously ignite when they come into contact with each other. The two propellant components usually consist of a fuel (Unsymmetrical dimethyl hydrazine (UDMH)) and an oxidizer (nitrogen tetroxide (N2O4)). The aim of the project work is to estimate failure locations by doing analysis work in terms of pressure & temperature. And also to suggest best suitable material. Presently tank is made with titanium and bladder with aluminum material it is having failures due to lower strength, project is to find the failure locations, analyzing tank with various materials to archive the goal. Coupled field and fatigue Analysis will be done to find the failure locations, thermal stress, deformation and, safety factor, model will be modified according to the obtained results. Analysis will be done to evaluate modified model and also to evaluate results for different materials conclusion will be made according to that. *Corresponding Author: Chellapilla Vamsi Krishna Research Scholar, Department of Thermal Engineering, Aditya Engineering College, Surampalem, Andra Pradesh, India. Published: October 29, 2015 Review Type: peer reviewed Volume: II, Issue : II Citation: Chellapilla Vamsi Krishna, THERMAL INVESTIGATION ON PROPELANT TANK MATERIAL BY USING FEM APPROACH
LITERATURE SURVEY Mr. Anu Retnakar and miss Jayasree Ramanujan done the research on “GEOMETRIC NONLINEAR ANALYSIS OF AN AXISYMMETRICALLY MODELLED CRYO PROPELLANT TANK” to describe about attributes of propellant tank while using LH2& Lox as storage liquid used in satellite launching vehicles these liquids are stored at cryogenic Temperature -253°C using ANSYS. As per their reaserch if tank is having more than 440Mpa of stress it causes failure for the tank with traditional materials. Mr. anu ratnakar and mr. ajin done the research on “Linear Analysis of a Cryo Propellant Tank” to suggest beast materials for the propellant tanks they have used axi-symmetrical modeling to work in analysis and linear analysis is conducted to obtain results.
Mr. R. Carina Ludwig and Michael Dreyer done the research on “Analyses of Cryogenic Propellant Tank Pressurization based Upon Experiments and Numerical Simulations” as per their research work they have concluded that “ The objective of this paper was to improve the understanding of the thermodynamic and fluid-dynamic phenomena of cryogenic propellant tank pressurization for the launcher application. Therefore, ground experiments were performed using liquid nitrogen as model propellant in order to investigate the initial active-pressurization process. As pressurant gases, gaseous nitrogen and gaseous helium were analyzed at di_erent inlet temperatures. The experimental set-up was described and the procedure for the experiments was presented. The evolution of the tank pressure and the temperatures in tank were investigated. The required pressurant gas mass was determined experimentally with regard to the used pressurant gas and pressurant gas temperature. For the gaseous nitrogen pressurization an increased pressurant gas temperature decreased the required pressurant gas mass, as it was already stated by Stochl et al. The reason for this, which was not mentioned by Stochl et al., is that for an increased pressurant gas temperatures the pressurization process is accelerated and therefore requires less pressurant gas mass.
They have used aluminum, alloy steel, titanium and stainless steel material as per their result propallent tank material should have a minimum yield strength of 671 MPa. 47
International Journal of Research and Innovation (IJRI)
INTRODUCTION Spacecraft Propellant Bladder Tanks: hydrazine bladder tanks are generally used in blow down or pressure regulated modes/ conditions.
Above placed image is showing bottem dish
Section Through Bladder Tank
“A bladder tank comprises a rigid vessel containing a flexible bladder and perforated axial stand-pipe. Propellant is contained in the bladder and pressurant gas within the tank occupies the volume between the tank wall and bladder”. the bladder forcing 'squeezes' propellant through the stand-pipe to achieve a positive expulsion of propellant using pressurant gas in a rocket engine or a set of thrusters. Operational Modes:
Above placed image is showing assembly view
2D DRAFTING OF PROPELLANT TANK
bladder tank can be operated in blow-down , or pressureregulated conditions. In blow-down condition, the tank is loaded with propellant and 'locked-up with a specified gas mass. :This mode avoids the need for additional gas pressurant vessels thereby reducing mass, volume and propulsion systems complexity. The fixed gas mass does however result in diminishing pressure during operation resulting in reducing thrust from Beginning of mission Life (BOL) to the End of Life (EOL). The reducing thrust level can however be very accurately predicted with guaranteed repeatability”. In pressure regulated condition, “the tank is pressurised from an independent pressurant vessel, via a pressure regulator, supplying a constant pressure from BOL to EOL. Consequently the propellant supply pressure, hence thrust, is constant throughout operational life.”
Above placed image is showing bottem dish
3D MODELING OF PROPELLANT TANK
Above placed image is showing top dish
Above placed image is showing bottem dish base revolve
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International Journal of Research and Innovation (IJRI)
Above placed image is showing top dish adopter
Above placed image is showing meshed model
INTRODUCTION TO ANSYS Ansys is one of the famous FEM based numerical analysis software which is used to calculate structural, thermal, vibrational, and electromagnetic problems. Complex models are divided into number of elements and nodes which in turns used to deconstruct calculations to simplify the critical problem. Workbench involve all the material property’s like yield strength, compressive strength, tensile strength, thermal property’s and S-N curve to provide accurate results. In Ansys models can be built using mechanical model generator or we can import in the formats of IGES. Parasolid, step and other….
Above placed image is showing load applied
BOUNDARY CONDITIONS Constrains: center with weld constrain Pressure on inner surface Coupled field analysis of propellant tank using material titanium
Above placed image is showing temperature
Above placed image is showing imported model
Above placed image is showing total heat flux
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International Journal of Research and Innovation (IJRI)
Coupled field analysis of propellant tank using material aluminum
Above placed image is showing total heat flux Above placed image is showing temperature
Above placed image is showing total deformation
Above placed image is showing total heat flux
Coupled field analysis of propellant tank using material s2 glass carbon composite
Above placed image is showing stress RESULT TABLE COUPLED FIELD
Above placed image is showing temperature
Titanium
Aluminium
S2 glass carbon composite
Temperature
-139.22
-150.57
-139.22
Total heat flux
0.000944
0.0097717
0.00944
Thermal error
5.9055e5
2.8578e5
5.9055e5
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International Journal of Research and Innovation (IJRI)
Coupled field analysis on modified model of propellant tank using material s2 glass carbon composite
The above graph shows total heat flux
Above placed image is showing temperature
CONCLUSION Present project work deals with (FAILURE CASE ESTIMATION AND RECTIFICATION OF PROPELLANT TANK USING GEOMETRIC OPTIMIZATION AND FOR THE SELECTION OF SUSTAINABLE MATERIAL.) Above placed image is showing total heat flux
COUPLED FIELD Titanium
Aluminium
S2 glass carbon composite
S2 Glassmodified Model
Temperature
-139.22
-150.57
-139.22
-59.498
Total heat flux
0.000944
0.0097717
0.00944
0.01388
Thermal error
5.9055e5
2.8578e5
5.9055e5
6.5509e6
GRAPHS COUPLED FIELD
Generally propellant tanks are causes to damage and required high level insulation to reduce heat transfer rate, this types of tanks are also called as cryogenic tanks which contains negative temperatures fluids(-1650c). In the present project work data collection and literature survey is done for the observation of previous studies/ research and for the selection of material . In the next stage 3d modeling is done to conduct further analysis in Ansys. Static, model fatigue and coupled field analysis is done on object to find failure locations and heat transfer rate. Geometrically modifications are done at top end and bottom positions of tank and thickness is increase to increase insulation quality. As per the analysis results modified model along with s2 glass carbon composite is a best option. By increasing the thickness it is showing 60% more efficiency as insulated ,and s2glass is stronger & liter than aluminium and tungstenbut it is having higher frequency value, by increasing the thickness value and by doing geometric modifications and frequency will be reduced than original model. And also weight is reduced by 60% even after increasing thickness (while comparing with titanium tank)
The above graph shows Temperature
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International Journal of Research and Innovation (IJRI)
REFERENCES
Author
1. GEOMETRIC NONLINEAR ANALYSIS OF AN AXISYMMETRICALLY MODELLED CRYO PROPELLANT TANK AnuRetnakar 1, JayasreeRamanujan 2, Ajin A.S 3, G. Jeganlal 4 2. Linear Analysis of a Cryo Propellant Tank *AnuRetnakar **Ajin A.S 3. Design and FE Analysis of Anti-Slosh Baffles for Fourth Stage of PSLV C. Bhavya, Sanya Maria Gomez and R. Krishnakumar 4. Analyses of Cryogenic Propellant Tank Pressurization based upon Experiments and Numerical Simulations Carina Ludwig?and Michael Dreyer??
Chellapilla Vamsi Krishna, Research Scholar, Department of Thermal Engineering, Aditya Engineering College, Surampalem, Andra Pradesh, India.
5. PROPELLANT TANK PRESSURIZATION MODELING FOR A HYBRID ROCKET Margaret Mary Fernandez 6. NUMERICAL MODELING OF PROPELLANT BOIL-OFF IN A CRYOGENIC STORAGE TANK A.K. Majumdar1, T.E. Steadman2, J.L. Maroney2, J.P. Sass3 and J.E. Fesmire3 7. Review and Evaluation of Models for Self-Pressurizing Propellant Tank Dynamics Jonah E. Zimmerman_, Benjamin S. Waxmany, and Brian J. Cantwellz
V.V.Kamesh Associate Professor , Department of Mechanical Engineering, Aditya Engineering College, Surampalem, Andra Pradesh, India.
8. Bringing a PMD Propellant Tank Assembly to the Marketplace: A Model of US-Europe-Industry-Academia Collaboration Walter Tam1, Manoj Bhatia2, Haroon Ali3, and Brian Wise4 9.THERMAL–STRUCTURAL OPTIMIZATION OF INTEGRATED CRYOGENIC PROPELLANT TANK CONCEPTS FOR A REUSABLE LAUNCH VEHICLE1 Theodore F. Johnson and W. Allen Waters
S.N.CH.Dattu.V, Assistant Professor, Department of Mechanical Engineering, Aditya Engineering College, Surampalem, Andra Pradesh, India.
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