Accession Number:

AD0731287

Title:

Long-Life Monopropellant Hydrazine Engine Development Program

Descriptive Note:

Final rept. 6 Apr 1970-25 Jun 1971

Corporate Author:

ROCKET RESEARCH CO REDMOND WA

Personal Author(s):

Report Date:

1971-09-01

Pagination or Media Count:

185.0

Abstract:

The objective of the program was to demonstrate the capability of 1, 000,000 pulses without performance loss on a flightweight monopropellant hydrazine 5-lbf thruster. This report describes the design, analysis, and tests which evolved into the final flightweight rocket engine assembly REA design during Phase I of the program. Phase IA testing of this REA accumulated 400,000 cycles of operation while delivering in excess of 80,000 lbf-sec with 20 ambient 40F cold starts prior to performance degradation. Results of the testing are presented, together with recommendations for extending life capability on the basis of REA teardown and failure analysis. Concurrent testing of workhorse REAs to evaluate the relationship of propellant and catalyst temperatures upon catalyst life characteristics is also reported. Author

Subject Categories:

  • Liquid Propellant Rocket Engines
  • Unmanned Spacecraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE