erv team 2 final report
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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. - PowerPoint PPT PresentationTRANSCRIPT
ERV Team 2 Final Report
Alicia Cole-QuigleyJames Gilson
Erin HammondDomenic Marcello
Matt MillerJeff Rosenberger
ERV Team 2 Final Report
Alicia Cole-QuigleyJames Gilson
Erin HammondDomenic Marcello
Matt MillerJeff 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.
http://floridalawfirm.com/mars.jpg
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 http://www.space.com/images/
h_magnum_03.jpg
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
http://centauri.larc.nasa.gov/issvc97/cmg.gif
Propulsion
3 RD-192 Methane Engines Liquid Methane/Liquid Oxygen Designed by Glushko Produces 2138 kN of thrust Isp of 356s Gimbaling capability ± 8° in 2 planes
Structure
“Banana split” configuration
3 floors Private areas Scientific
experiments Common areas
http://spaceflight.nasa.gov/gallery/images/mars/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 CO2 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/cm3
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 http://www.truenorthpower.com/
products_turbines.htm
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?