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Noncatalytic hydrazine thruster development - 0.050 to 5.0 pounds thrustNoncatalytic (thermal-decompositon) hydrazine thrusters can operate in both the pulsing and steady-state modes to meet the propulsive requirements of long-life spacecraft. The thermal decomposition mode yields higher specific impulse than is characteristic of catalytic thrusters at similar thrust levels. This performance gain is the result of higher temperature operation and a lower fraction of ammonia dissociation. Some life limiting factors of catalytic thrusters are eliminated.
Document ID
19760059451
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Murch, C. K. (NASA Goddard Space Flight Center Greenbelt, MD, United States)
Sackheim, R. L. (NASA Goddard Space Flight Center Greenbelt, MD, United States)
Kuenzly, J. D. (TRW Defense and Space Systems Redondo Beach, Calif., United States)
Callens, R. A. (NASA Goddard Space Flight Center Auxiliary Propulsion Branch, Greenbelt, Md., United States)
Date Acquired
August 8, 2013
Publication Date
July 1, 1976
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 76-658
Meeting Information
Meeting: Propulsion Conference
Location: Palo Alto, CA
Start Date: July 26, 1976
End Date: July 29, 1976
Sponsors: American Institute of Aeronautics and Astronautics and Society of Automotive Engineers
Accession Number
76A42417
Funding Number(s)
CONTRACT_GRANT: NAS5-11417
CONTRACT_GRANT: NAS5-20824
CONTRACT_GRANT: NAS5-23202
Distribution Limits
Public
Copyright
Other

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