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?