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A life test of a 22-Newton (5-lbf) hydrazine rocketLife tests were conducted on a 22-N (5-lb) hydrazine rocket thruster which incorporates the latest technology to obtain long life from the catalyst bed. A spring mechanism surrounding the catalyst bed continually applies compression to the catalyst bed to prevent the formation of any void channels. The research rocket thruster was tested over an operational cycle of both steady state and pulse firing which simulated a possible space station duty cycle. The thruster ran as expected for about 40 hours, or 3.2 times 10 to the 6th power N-sec (7.2 times 10 to the 5th power lb-sec) total impulse. Subsequently, some thrust chamber pressure decreases were noted during long steady state test periods. After 60.2 hours of run time, tests had to be terminated due to a blockage in the propellant injector tube which occurred during heating of the thruster by a heat lamp. A chemical analysis of the catalyst indicated that iron and nickel metals had poisoned some of the catalyst, thereby causing a degradation in performance. It was determined that a contaminated barrel of hydrazine was the source of the metal poisoning.
Document ID
19880002368
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Meng, P. R. (NASA Lewis Research Center Cleveland, OH., United States)
Schneider, S. J. (NASA Lewis Research Center Cleveland, OH., United States)
Morgan, C. J. (NASA Lewis Research Center Cleveland, OH., United States)
Jones, R. E. (NASA Lewis Research Center Cleveland, OH., United States)
Pahl, D. A. (Rocket Research Corp. Redmond, Wash., United States)
Date Acquired
September 5, 2013
Publication Date
January 1, 1987
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NASA-TM-100232
NAS 1.15:100232
E-3857
Accession Number
88N11750
Funding Number(s)
PROJECT: RTOP 506-42-31
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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