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On-Board Propulsion System Analysis of High Density PropellantsThe impact of the performance and density of on-board propellants on science payload mass of Discovery Program class missions is evaluated. A propulsion system dry mass model, anchored on flight-weight system data from the Near Earth Asteroid Rendezvous mission is used. This model is used to evaluate the performance of liquid oxygen, hydrogen peroxide, hydroxylammonium nitrate, and oxygen difluoride oxidizers with hydrocarbon and metal hydride fuels. Results for the propellants evaluated indicate that the state-of-art, Earth Storable propellants with high performance rhenium engine technology in both the axial and attitude control systems has performance capabilities that can only be exceeded by liquid oxygen/hydrazine, liquid oxygen/diborane and oxygen difluoride/diborane propellant combinations. Potentially lower ground operations costs is the incentive for working with nontoxic propellant combinations.
Document ID
19980237012
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Schneider, Steven J. (NASA Lewis Research Center Cleveland, OH United States)
Date Acquired
September 6, 2013
Publication Date
October 1, 1998
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
E-11403
NAS 1.15:208811
AIAA Paper 98-3670
NASA/TM-1998-208811
Meeting Information
Meeting: Joint Propulsion Conference
Location: Cleveland, OH
Country: United States
Start Date: July 13, 1998
End Date: July 15, 1998
Sponsors: American Society of Mechanical Engineers, Society of Automotive Engineers, Inc., American Inst. of Aeronautics and Astronautics, American Society for Electrical Engineers
Funding Number(s)
PROJECT: RTOP 632-1B-1B
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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