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ERV - 1 End of Semester Presentation 12-09-03 Brad Buchanan – Group Leader Dominic Amaturo.

Published byColin Potter Modified over 8 years ago

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Presentation on theme: "ERV - 1 End of Semester Presentation 12-09-03 Brad Buchanan – Group Leader Dominic Amaturo."— Presentation transcript:

1 ERV - 1 End of Semester Presentation 12-09-03 Brad Buchanan – Group Leader Dominic Amaturo

2 Misson Architecture 2 launches using Magnum Booster ~ 243 day Hohmann Transfer to Mars 740 day stay to generate fuel/water/oxygen Crew arrives, stay for 550 days Liftoff from Mars ~ 243 day Hohmann Transfer return to Earth Return to Earth in LEO

3 Structures ~ 25 feet diameter, 80 feet long Sepcore semi-ablative heat shield Graphite/Magnesium metal matrix composite Individual bulkheads

4 Launch Vehicle Magnum Booster

5 Propulsion Four Pratt & Whitney RL10-series engines modified to use methane for main engines –Isp of 376 seconds –155 kN of thrust per engine –2 meters long, 1 meter diameter, 363 kg

6 Ground Control Locations of MCC, SOCC, and POCC are to be determined next semester Deep Space Network Remote Agent System

7 Communications Optical Communication 1% antenna area Narrow Beam Divergence Source: http://lasers.jpl.nasa.gov/

8 C & DH Final processor not chosen yet RAD 6000 –32 bit processor –128 Megabytes

9 GNC DSN Sun/Star Sensors (MANS) –Autonomous –Lightweight –Low power requirements

10 Power Main Power / Secondary Power Hydrogen fuel cells 4 Pu-238 RTG’s Source: history.nasa.gov/ SP-349/ch3.htm

11 Power 378 kW required 400kW generated SystemPower Required (kW) Propulsion352 Attitude Control2.4 Communications 1 C&DH 1 ECLSS 10 Fuel Generation 3 Thermal 7

12 Radiators Multi-Layer Insulation (MLI) Silver coated Teflon on outside of ERV

13 ECLSS Atmosphere Revitalization System (ARS) Active Thermal Control System Atmosphere Revitalization Pressure Control System (ARPCS) Water Recycling System Artificial Gravity?

14 Scientific Instruments Sabatier reactor –CO 2 + 4H 2  CH 4 + 2H 2 O Electrolysis –2H 2 O  2H 2 + O 2 92,000 kg O 2 13,000 kg CH 4 Total mass of propellant – 105,000 kg

15 Future Work Integration of all systems into C&DH MCC, SOCC, POCC located and defined More research into C&DH GNC system chosen Trade studies for various components of each system Artificial Gravity researched

16 Questions?

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