Carbon-based Mars ISRU Rocket Technology (CMIRT)

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: N/A
Agency Tracking Number: NASA1937
Amount: $70,000.00
Phase: Phase I
Program: SBIR
Awards Year: 2001
Solicitation Year: N/A
Solicitation Topic Code: N/A
Solicitation Number: N/A
Small Business Information
Space Center, 1212 Fourier Drive, Madison, WI, 53717
DUNS: N/A
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Dr. Rice
 President/CEO
 (608) 827-5000
 ricee@orbitec.com
Business Contact
 Dr. Eric E Rice
Title: President/CEO
Phone: (608) 827-5000
Email: ricee@orbitec.com
Research Institution
N/A
Abstract
The innovation is a unique Carbon-based Mars ISRU Rocket Technology (CMIRT) that can greatly reduce vehicle size, complexity, support systems, and Earth launch mass requirements for a variety of human and robotic Mars missions, where propulsion systems use propellants from indigenous materials on Mars. CMIRT propellants are simply derived from the CO2 or H2O in the Mars atmosphere or from H2O found in the Mars soil or subsurface. The CMIRT innova-tion consists of efficiently packaged solid carbon-based fuel (with various percentages of hydrogen)/liquid oxygen inte-grated into ORBITEC's cryogenic hybrid with a vortex feed system. The ISRU-based propellant family and the unique vortex-fed hybrid propulsion system approach proposed here has many advantages over other Earth-derived propellants and conventional propulsion systems. ORBITEC's experience and capability in advanced propulsion and ISRU sys-tems will allow much to be accomplished during the Phase I effort. During Phase, I ORBITEC proposes to: (1) conduct test firings in the ORBITEC Mark II hybrid engine to measure regression rates of the carbon-based propellants, (2) de-sign the vortex advanced cryogenic hybrid engine that will integrate into the Mark II system, (3) construct/fabricate and test the vortex advanced cryogenic hybrid engine, (4) conduct test firings in the vortex engine, and (5) analyze test firing results and recommend Phase II propellant selection and flexible propulsion systems that can use many of the carbon-based fuels with oxygen. Phase II will result in the final designs, construction, parametric testing, and larger-scale test firings of selected CMIRT propellant systems.

* Information listed above is at the time of submission. *

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