Micro-Rocket Impulsive Thrusters

Abstract

Light weight solid propellant motors which supply high thrusts (greater than 500 lbf) for durations on the order 0.010 sec. (referred to as impulsive thrusters) require special analysis of items such as internal ballistics, propellant combustion, ignition stimuli, exhaust plume envelope, and inert hardware. A survey of the rocket motor concepts revealed that the desired thrust versus time program can be achieved by internal burning grains and existing high burning rate composite propellants. The mathematical model for transient internal ballistics developed during the study can be applied to a wide range of high preformance rocket motors which experience rapid ignition and pressurization transients.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1971
Accession Number
AD0735381

Entities

People

  • Leonard H. Caveny
  • Martin Summerfield

Organizations

  • Princeton University

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Ammonium Perchlorate
  • Burning Rate
  • Combustion
  • Composite Propellants
  • Exhaust Plumes
  • Fuel Additives
  • Heat Transfer
  • High Pressure
  • Ignition Lag
  • Manufacturing
  • Materials Laboratories
  • Materials Processing
  • Metal Oxides
  • Pressure Distribution
  • Pressurization
  • Propulsion Systems
  • Solid Propellants

Fields of Study

  • Physics

Readers

  • Aerospace Propulsion Engineering.
  • Rocket Propulsion.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster