Sasakawa International Center for Space Architecture - Modular Space Architecture

MODULAR SPACE ARCHITECTURE MASTER‘s THESIS PROJECT!

Author:!

Nejc Trost" nejc@trost.si! !

Mentors:!

Larry Bell" Olga Bannova" Bob Sauls" !

Orbital mechanics:!

Chiharu Sasagawa, UCS ! !

Sasakawa International Center For Space Architecture (SICSA)!

University of Houston December 2, 2013!

PRESENTATION"

PHOBOS-­‐DEIMOS MISSION

MODULES CATALOGUE

MISSION COMPARISON

MISSION COMPARISON"

Year of study Number of people Doctor onboard Mission duraMon Venus swing-­‐by Total IMLEO

NASA Mars surface DRM 5

2009 10 ? ≈ 900 days NO ≈ 848 MT

Dr. Fred Singer PH-­‐D Proposal

1981/2013 5-­‐8 YES (2)

SICSA Phobos:Deimos Explorer v1 2012 3 NO (trained, assisted) ≈ 545 days

≈ 545 days YES (both YES (outbound) direcJons) ≈ 400 MT (est.) ≈ 222 MT

SICSA Phobos:Deimos Explorer v2 2013 2-­‐3 NO (trained, assisted) ≈ 545 days YES (outbound) ≈ 141 MT

!"

TITO Mars InspiraMon

2013 2 NO ≈ 501 days NO ≈ 10 MT

MISSION COMPARISON"

Payload mass Pre-­‐deployment at Mars vicinity Starts in LEO Number of deployments from LEO TMI propulsion H-­‐LiX launches (≈ 125 MT) SLS or FXH Crew launch (Falcon 9 or FH) Unmanned probes sent to Mars InternaMonal cooperaMon CooperaMon with private space comp.

Venus measurements HAB parking posiJon Stay at moons/ Mars

NASA Mars surface DRM 5 ?

YES YES 3 NTR 9 0 NO YES

NO NO MPO (Mars parking orbit) 500 days

Dr. Fred Singer SICSA SICSA TITO PH-­‐D Proposal Phobos:Deimos Phobos:Deimos Mars InspiraMon

Explorer v1 Explorer v2

≈ 50 MT + 50 MT ≈ 49 MT YES (nuclear reactor) YES

≈ 40 MT

NO

NO

YES

NO (GTO)

2

1

1

Chem / Solar

NTR

BNTR

5-­‐6

3

2

1-­‐2

1

1

YES (10-­‐20)

NO

NO

NO

NO

NO

YES

YES

YES

YES (2X) Deimos orbit (4 weeks) 2-­‐4 weeks

YES (1X) MPO (Mars parking orbit) 4 weeks

≈ 10 MT NO NO 1 EXCESS Delta-­‐V 0 1 NO NO

YES YES (1X) NO MPO (Mars parking orbit) NO 4 weeks 10 h

MISSION COMPARISON"

Deimos sample collecJon Manned mission to Phobos Phobos sample collecJon Manned mission to Mars Mars sample collecJon RadiaJon shielding by moons Leave large equipment EVA’s

NASA Mars surface DRM 5

NO NO NO (Mars) YES YES NO, Mars YES, Mars

NO Leave measuring instruments YES, Mars Control unmanned probes from Crew NO Assembly in LEO YES min 5 years (pre-­‐ Total Mission duraMon deploy)

Dr. Fred Singer PH-­‐D Proposal

YES

SICSA Phobos:Deimos Explorer v1 NO (remote)

SICSA Phobos:Deimos Explorer v2 NO (remote)

YES (few days)

YES (2 weeks)

YES (2 weeks)

YES UNMANNED YES (probes) YES (Deimos & Phobos) Reactor & lab at Deimos YES (sample collecJon) Mars, Phobos & Deimos YES

TITO Mars InspiraMon

NO

NO YES YES NO NO, SERVES AS NO, SERVES AS PRE-­‐ PRE-­‐MISSION MISSION NO NO NO YES (Phobos, 2 YES (Phobos, 2 weeks) weeks) PEV in MPO, HAB DEV, HAB IN LEO IN LEO NO (emergency NO (emergency only) only) Phobos & Phobos & Deimos Deimos NO

NO

6 months 1-­‐2 months IN GTO, SHORT min 3 years (pre-­‐ 1.7 years (direct) 1.5 years (direct) deploy)

NO NO NO NO NO NO NO 1.4 years (direct)

V.1 Launch 1: (FXH) -­‐ HAB -­‐ NODE -­‐ DEV -­‐ PEV

Launch 2: (FXH) -­‐ NTR -­‐ TEI LH2 Launch 3: (F9) -­‐ Dragon Launch 4: (FXH) -­‐ TMI LH2

TOTAL PAYLOAD: 67 MT TOTAL LH2: 155 MT TOTAL LEO: 222 MT

V.2 Launch 1: (FXH) -­‐ HAB -­‐ RING -­‐ TMI LH2

Launch 2: (FXH) -­‐ NTR -­‐ TEI LH2 Launch 3: (FH) -­‐ Dragon

TOTAL PAYLOAD: 56 MT TOTAL LH2: 85 MT TOTAL LEO: 141 MT

EXCESS LAUNCH DELTA-V"

SLS OR FUTURE FALCON ROCKET PAYLOAD TO LEO ≈ 130 MT Volume: 673 m3 LH2 density: 70 kg/m3 Total propellant: 47 MT Structure: 6 MT Remains: 70 MT Excess Delta-­‐V: 1.9 km/s

Delta-­‐V from LEO to GEO ≈ 2.8 km/s Delta-­‐V from GEO to MPO ≈ 1.2 km/s (only!)

26.0 m [85 X]

10 m [32 X]

ROAD MAP V.2

1. NUMBER OF LAUNCHES 2. ASSEMBLY LOCATION – GTO 3. DEIMOS AFTER PHOBOS

VAN ALLEN BELTS" - Increased radiation when passing through Van Allen Belt!

- Crew stays in orbit for limited time!

- Assembly in higher orbits is better for assembly regarding LH2 boiloff problem!

- LEO is the least desirable orbit for fuel storage!

- SPE and GCR Radiation protection solutions have to be provided for overall trip!

ANIMATION"

MODULAR PAYLOAD SYSTEM"

1. " Cylindrical/payload level !

2. " Floor level!

3. " Compartment level !

CATALOGUE"

EXCESS LAUNCH DELTA-V"

130" 120" 110" 100" 90" 80" 70" 60" 50" 40" 30" 20" 10" 0"

HA B$ 1 HA U' B$ 2 HA U' B$ 3 HA U' B$ 4 HA U' B$ 5 HA U' B$ 6 HA U' B$ 7U LH ' 2$ 1U LH ' 2$ 2U LH ' 2$ 3U LH ' 2$ 4U LH ' 2$ 5U LH ' 2$ 6U LH ' 2$ 7 LA U' N$ 1 LA U' N$ 2 LA U' N$ 3 LA U' N$ 4 LA U' N$ 5 LA U' N$ 6 LA U' N$ 7 NT U' R$ 1 NT U' R$ 2 NT U' R$ 3 NT U' R$ 4 NT U' R$ 5 NT U' R$ 6 NT U' R$ 7U '

-

Due to low LH2 density (70kg/m3) not all LV lift capability can be used!

The average payload mass is ≈ 62MT (42%), leaving almost 68MT unused (48%) from total launch capability of 130MT! Less initial launch mass gives the opportunity for higher orbits!

TOTAL'IMLEO'(MT)'

- -

PROPELLANT DENSITY" 400"

Bulk%density%(kg/m3)%

350" 300"

Large Volume Low mass

Small Volume High mass

250" 200" 150" 100" 50" 0" VASIMR"(Xenon)"

NTR"(LH2)"

Chemical"(LH2+O2)"

EXCESS LAUNCH DELTA-V" SCENARIOS

Hofmann7transfer7(theHsameHdelta,v'sHandHdurationHforHallHengines)

nb.

1 2 3 4 5 6 7 8

Destination Moon Deimos Phobos Mars Ganymede Europa Saturn Titan

Surface7 lander7delta: v7(km/s) 1.66 0.00 0.00 3.49 1.92 1.41 , 1.85

ChemHEngine,HIsp=450sH[LH2+O2] NuclearHThermalHRocketHNTR,HIsp=980sH[LH2] VASIMR,HIsp=5000sH[ArgonHorHXenon] Spaceship7 Total7 Spaceship7 Total7 Spaceship7 Total7 Duration7 Duration7 delta:v7 required7Fuel7 Duration7 Duration7 delta:v7 required7Fuel7 Duration7 Duration7 delta:v7 required7Fuel7 (days) (years) (km/s) (MT) (days) (years) (km/s) (MT) (days) (years) (km/s) (MT) 10 0.03 5.41 34.69 , , , , , , , , 1106 3.0 6.77 177.08 1106 3.0 6.77 42.28 1106 3.0 6.77 6.19 1106 3.0 6.77 231.54 1106 3.0 6.77 51.19 1106 3.0 6.77 7.01 1106 3.0 6.77 177.08 1106 3.0 6.77 42.28 1106 3.0 6.77 6.19 2179 6.0 14.51 7495.36 2179 6.0 14.51 610.73 2179 6.0 14.51 51.62 2179 6.0 16.60 5510.02 2179 6.0 16.60 323.40 2179 6.0 16.60 27.10 4600 12.6 14.72 7149.69 4600 12.6 14.72 444.13 4600 12.6 14.72 38.00 4600 12.6 14.72 7149.69 4600 12.6 14.72 444.13 4600 6.0 14.72 38.00

Optimized7trajectory7/7flybys

nb.

1 2 3 4 5 6 7 8

nb.

1 2 3 4 5 6 7 8

Destination Moon Deimos Phobos Mars Ganymede Europa Saturn Titan

Surface7 lander7delta: v7(km/s) 1.66 0.00 0.00 3.49 1.92 1.41 , 1.85

Destination Moon Deimos Phobos Mars Ganymede Europa Saturn Titan

Surface7 lander7delta: v7(km/s) 1.66 0.00 0.00 3.49 1.92 1.41 , 1.85

ChemHEngine,HIsp=450sH[LH2+O2] NuclearHThermalHRocketHNTR,HIsp=980sH[LH2] VASIMR,HIsp=5000sH[ArgonHorHXenon]H(delta,vHfixed) Spaceship7 Total7 Total7 Total7 Duration7 Duration7 delta:v7 required7Fuel7 Duration7 Duration7 Delta:v7 required7Fuel7 Duration7 Duration7 Delta:v7 required7Fuel7 (days) (years) (km/s) (MT) (days) (years) (km/s) (MT) (days) (years) (km/s) (MT) 10 0.03 5.41 34.69 , , , , , , , , 509 1.39 10.80 596.95 509 1.4 10.80 94.61 509 1.39 10.80 10.92 509 1.39 11.64 739.16 509 1.4 11.64 112.22 509 1.39 11.64 11.87 509 1.39 10.80 596.95 509 1.4 10.80 94.61 509 1.39 10.80 10.92 2179 5.97 14.51 7495.36 2179 6.0 14.51 610.73 2179 5.97 14.51 519.21 2179 5.97 16.60 5510.02 2179 6.0 14.51 323.40 2179 5.97 14.51 220.02 3622 9.92 15.20 9232.99 3622 9.9 15.20 495.12 3622 9.92 15.20 39.51 3622 9.92 15.20 9232.99 3622 9.9 15.20 495.12 3622 9.92 15.20 39.51 VASIMR,HIsp=5000sH[ArgonHorHXenon]H(MpHfixed) Total7 Duration7 Duration7 Delta:v7 required7Fuel7 (days) (years) (km/s) (MT) , , , , 216 0.6 55.1 94.61 204 0.6 59.2 112.22 216 0.6 55.1 94.61 514 1.4 131.4 610.73 514 1.4 131.4 323.40 1241 3.4 77.5 495.12 1241 3.4 77.5 495.12

HOFMANN TRANSFER" Hofmann(Transfer(&(Delta&v( 14.0#

18.00# 16.00#

12.0#

Years(

10.0#

12.00#

8.0#

10.00#

6.0#

8.00# 6.00#

4.0#

4.00# 2.0#

2.00#

0.0#

0.00# Moon#

Deimos#

Phobos#

Mars#

Dura?on#(years)#

Ganymede# Europa#

Saturn#

Spaceship#deltaDv#(km/s)#

Titan#

Delta&V((km/s)(

14.00#

HOFMANN TRANSFER" Hofmann*Transfer*/*propellant*requirements* Propellant*total*mas*IMELO*(MT)*

8000" 7000" 6000" 5000" 4000" 3000" 2000" 1000" 0" Moon"

Deimos"

Phobos"

Mars"

Chem"Engine"

Ganymede" NTR"

VASIMR"

Europa"

Saturn"

Titan"

HOFMANN TRANSFER" Hofmann*Transfer*/*propellant*requirements* Propellant*total*mas*IMELO*(MT)*

700" 600" 500" 400" 300" 200" 100" 0" Moon"

Deimos"

Phobos"

Mars" NTR"

Ganymede" VASIMR"

Europa"

Saturn"

Titan"

HOFMANN TRANSFER" * Excluding chemical engine!

Hofmann*Transfer*/*propellant*requirements*

Propellant*total*mas*IMELO*(MT)*

250"

200"

150"

100"

50"

0" Moon"

Deimos" Chem"Engine"

Phobos" NTR"

VASIMR"

Mars"

OPTIMIZED TRAJECTORIES" 12.0#

140.00#

10.0#

120.00# 100.00#

8.0#

80.00# 6.0# 60.00# 4.0#

40.00#

2.0#

20.00#

0.0#

0.00# Moon# Chem#

Deimos# NTR#

Phobos# VASIMR#

Mars#

Ganymede# Europa#

Chem#DeltaFv#

Saturn#

NTR#DeltaFv#

Titan# VASIMR#DeltaFv#

Delta&V((km/s)(

Travel(2me((Years)(

Op2mized(Trajectrory(

OPTIMIZED TRAJECTORIES" Op6mized*Trajectrory* 700"

10.0"

600"

Travel*6me*(Years)*

9.0" 8.0"

500"

7.0" 6.0"

400"

5.0"

300"

4.0"

200"

3.0" 2.0"

100"

1.0" 0.0"

0" Moon"

Deimos"

Phobos"

NTR"Propellant"(LH2)"

Mars"

Ganymede"

Europa"

VASIMR"Propellant"(Xenon)"

Saturn" VASIMR"

Titan" NTR"

Propellant*total*mas*IMELO*(MT)*

11.0"

HOFMANN TRANSFER" Hofmann*Transfer*/*propellant*requirements* Propellant*total*mas*IMELO*(MT)*

8000" 7000" 6000" 5000" 4000" 3000" 2000" 1000" 0" Moon"

Deimos"

Phobos"

Mars"

Chem"Engine"

Ganymede" NTR"

VASIMR"

Europa"

Saturn"

Titan"

MOON"

PHOBOS/DEIMOS/MARS"

EUROPA"

TITAN"

V.1

HAB INTERIOR"

V.2 Crew quarters, quiet!

Command & Control!

LAB, Toilet, Hygiene, Noisy!

FLOOR PLAN"

Floor area ≈ 538 ft2 ≈ 50 m2 !

PEV transfer propellant!

LEO propulsive braking propellant!

Total floor area ≈ 50 m2 ≈ 538 ft2!

Total volume ≈ 284 m3 ≈ 10,029 ft3!

Storage avaliable ≈ 165 m3 ≈ 5,827 ft3!

Storage used ≈ 101 m3 ≈ 3,567 ft3 !

Free volume ≈ 183 m3 ≈ 6,463 ft3 !

Dragon – 7.0 m3!

DEV propellant!

Storage 1 – 20 x 1.9 m3!

Water tank!

Storage 2 – 20 x 1.0 m3!

Open areas!

Floor storage!

Storage 3 – 30 x 0.3 m3!

Storage 4 – 30 x 3.1 m3!

Water tank!

Storage 5 – 3 x 0.3 m3!

Storage 6 – 2 x 2.5 m3!

STORAGE VOLUMES"

Water tanks, Avionics, Guidance, NavigaJon and Control, CommunicaJons and Tracking Command and Data Handling Maintenance / All Repairs in Habitable Areas Environmental Control and Life Supp. Sys. ECLSS Electrical Power Systems, Thermal Control System

EVA Systems Clothing

RadiaJon protecJon Other

Water tanks Waste collecJon system

Galley and Food Systems Personal Hygiene Maintenance / All Repairs in Habitable Areas Crew Health Care, Housekeeping Environmental Control and Life Supp. Sys. ECLSS Science Equipment and Lab

Housekeeping, Photography OperaJonal Supplies & Restraints RecreaJonal equipment & Personal Stowage

SYSTEM’s VOLUMES"

C&C, GALLEY"

CENTER CORRIDOR AND RADIATION PROTECTION"

CREW QUARTER"

CREW QUARTER FROM THE INSIDE"

CREW QUARTER FROM THE INSIDE"

ROTATED AXIS"

CENTER CORRIDOR AND RADIATION PROTECTION"

REFERENCES" Abumeri, G. H., & Roche, J. M. 2006. Parametric Sizing of Composite Metal Lined Tanks for Bimodal Nuclear Thermal Propulsion Applica>ons. AIP Conference Proceedings, 813(1): 811-­‐818.

ChrisFe, R. J., & Plachta, D. W. 2006. Zero boil-­‐off system design and thermal analysis of the bimodal thermal nuclear rocket. Paper presented at the AIP Conference Proceedings, 813.

Group, M. A. S., & Headquarters, N. 2009. Human Explora>on of Mars Design Reference Architecture 5.0. In B. G. Drake (Ed.), Human ExploraFon of Mars Design Reference Architecture 5.0. Houston, Texas: NASA Johnson Space Center.

Singer , S. F., & Emeritus. 2012. Manned Space Goals: Science and Adventure to Mars via its moon Deimos. In t. M. Conference (Ed.), Science & Environmental Policy Project. Pasadena, CA.

Tito, D. A., Anderson, G., John P. Carrico, J., Clark, J., Finger, B., Lantz, G. A., Loucks, M. E., MacCallum, T., Poynter, J., Squire, T. H., & Worden, S. P. 2013. Feasibility Analysis for a Manned Mars Free-­‐Return Mission in 2018. Pacific Palisades, CA.

THANK YOU!"

VIDEO h`ps://vimeo.com/80031823

PAPER h`p://www.uh.edu/sicsa/

EMAIL nejc@trost.si