erv - 1 end of semester presentation 12-09-03 brad buchanan – group leader dominic amaturo

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

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ERV - 1

End of Semester Presentation

12-09-03

Brad Buchanan – Group Leader

Dominic Amaturo

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

Structures

• ~ 25 feet diameter, 80 feet long• Sepcore semi-ablative heat shield• Graphite/Magnesium metal matrix

composite• Individual bulkheads

Launch Vehicle• Magnum Booster

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

Ground Control

• Locations of MCC, SOCC, and POCC are to be determined next semester

• Deep Space Network

• Remote Agent System

Communications

• Optical Communication

• 1% antenna area

• Narrow Beam Divergence

Source: http://lasers.jpl.nasa.gov/

C & DH

• Final processor not chosen yet

• RAD 6000

– 32 bit processor

– 128 Megabytes

GNC

• DSN

• Sun/Star Sensors (MANS)– Autonomous– Lightweight– Low power requirements

Power

• Main Power / Secondary Power

• Hydrogen fuel cells

• 4 Pu-238 RTG’s

Source: history.nasa.gov/ SP-349/ch3.htm

Power

• 378 kW required

• 400kW generated

System Power Required (kW)

Propulsion 352

Attitude Control 2.4

Communications 1

C&DH 1

ECLSS 10

Fuel Generation 3

Thermal 7

Thermal

• Radiators

• Multi-Layer Insulation (MLI)

• Silver coated Teflon on outside of ERV

ECLSS

• Atmosphere Revitalization System (ARS)

• Active Thermal Control System

• Atmosphere Revitalization Pressure Control System (ARPCS)

• Water Recycling System

• Artificial Gravity?

Scientific Instruments

• Sabatier reactor

– CO2 + 4H2 CH4 + 2H2O

• Electrolysis

– 2H2O 2H2 + O2

• 92,000 kg O2

• 13,000 kg CH4

• Total mass of propellant – 105,000 kg

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

Questions?