Long-Life Monopropellant Hydrazine Engine Development Program

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 REA's to evaluate the relationship of propellant and catalyst temperatures upon catalyst life characteristics is also reported. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1971
Accession Number
AD0731287

Entities

People

  • Bruce W. Schmitz
  • Walter W. Wilson

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Accuracy
  • Body Weight
  • Data Acquisition
  • Digital Data
  • Failure Mode And Effect Analysis
  • Heat Transfer
  • Ignition Lag
  • Materials
  • Measurement
  • Physical Properties
  • Plastic Explosives
  • Propulsion Systems
  • Rocket Engines
  • Rocket Propulsion
  • Static Loads
  • Test And Evaluation
  • Test Facilities

Fields of Study

  • Physics

Readers

  • Rocket Propulsion.
  • Software Engineering

Technology Areas

  • Space
  • Space - Hall-Effect Thruster