ERV Team 2 Final Report Alicia Cole-Quigley James Gilson Erin Hammond Domenic Marcello Matt Miller Jeff Rosenberger

ERV Team 2 Final Report Alicia Cole-Quigley James Gilson Erin Hammond Domenic Marcello Matt Miller Jeff Rosenberger

Mission Overview  Send uncrewed Earth Return Vehicle (ERV) and In-Situ Resource Utilization (ISRU) Plant to Mars  26 months later, send crewed transport with 4 crewmembers and supplies  Crew spends 550 days on Martian surface and conducts scientific experiments  Crew returns to Earth in ERV

Primary Objective  The safe transport and return of the human crew for the duration of the defined mission.

Secondary Objectives  the investigation of extended duration human spaceflight  the efficient conversion of Martian atmosphere and resources to support mission objectives  the investigation of psychological effects of such a mission on the crew  successful return of experimental data regarding Mars and prolonged human exposure to low gravity  the promotion of global unity through exploration of the solar system and beyond  the ability to provide extra resources (10% more propellant than needed) for a Mars Rover

Launch Vehicle Interface  Inline core vehicle with two attached Shuttle boosters  Payload is aft mounted on expendable core vehicle  One-third launch costs of Titan IV with 5x the payload capability

Navigation/Attitude Control  4 Control Moment Gyros (CMGs)  Cold gas thrusters as failsafe for CMGs  3 Ball CT-633 Stellar Attitude Sensors  2 TNO Sun Acquisition Sensors  6 Honeywell QA3000 Accelerometers

Propulsion  3 RD-192 Methane Engines Liquid Methane/Liquid Oxygen Designed by Glushko Produces 2138 kN of thrust I sp of 356s Gimbaling capability ± 8 ° in 2 planes

Structure  “Banana split” configuration  3 floors Private areas Scientific experiments Common areas /marsbases/lores/s97_07837.jpg

Crew Accommodations & Human Factors  Crew composition: 2 male, 2 female  More private space than currently on ISS  Rear entry “climb in” EVA suits  ISS Fire Detection System  Solid Amine CO 2 scrubbers

Command, Control, & Communications  MOCC, SOCC, and POCC at NASA Johnson Space Center in Houston, Texas  2 LM RAD-6000 computers  2-way sound, video, text, and data capability  Low-gain antenna just after launch and into LEO  High-gain antenna using Deep Space Network for mission duration

Entry/Descent - Mars  Orbital maneuvering system (OMS) and aerobraking for entry into Martian orbit  Establish stable orbit  Fire retrorockets to descend  Combination parachute and retrorocket for landing

Landing Site on Mars  Daedalia Planum  Consists of old lava flows  25° South latitude; 127.5° West longitude  Good location in terms of both wind and solar power

Entry/Descent/Landing - Earth  OMS and aerobraking to enter low Earth orbit  Establish stability in LEO  Await taxi to return crew to Earth’s surface

Thermal Protection  Inconel 617 Density of 8.36 g/cm 3 Doubles as structural shell  Used and tested on X-33  Panels are easy to repair or replace

Power  SP100 Nuclear Reactor  Wind turbines (Lakota SC)  Exercise equipment  ISRU Technologies Sabatier Process Reverse Water Gas Shift Electrolysis

Future Work  Finish sensor trade study  Continue research on RD-192  Develop appropriate radiation shielding system for ERV  Investigate reentry dynamics  Study high energy transfer orbits  Calculate crew food, water, and fresh air requirements  Research Inconel manufacturing  Detailed numerical analysis of power subsystem  Landing “Banana Split”

Any questions?