Altitude Ignition Studies

Abstract

A facility for analyzing the effects of engine hardware parameters on the pulse characteristics of bipropellant attitude control thrusters in a space environments was constructed at the Air Force Rocket Propulsion Laboratory (AFRPL). In a series of tests involving 32 engine configurations, 17 engine parameters were varied. The propellants considered were N2H4-UDMH (50/50) and MMH fuels and NTO as the oxidizer. The experimental phase of the program was based on a statistical test matrix designed to minimize the number of firings and the hardware requirements. This report includes a detailed description of the altitude ignition facility and presents an analysis of the system and the data obtained. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1971
Accession Number
AD0885564

Entities

People

  • Charles R. Mastromonico

Organizations

  • Air Force Research Laboratory

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Accuracy
  • Air Force
  • Chemical Reactions
  • Combustion
  • Engineering
  • Flow Rate
  • Ignition Lag
  • Lead Time
  • Pressure Measurement
  • Pressurization
  • Propellant Tanks
  • Rocket Propulsion
  • Rockets
  • Steady State
  • Test And Evaluation
  • Thrust Chambers
  • Voltage

Fields of Study

  • Physics

Readers

  • Rocket Propulsion.
  • Systems Analysis and Design

Technology Areas

  • Space
  • Space - Hall-Effect Thruster