NONLINEAR ASPECTS OF COMBUSTION INSTABILITY IN LIQUID PROPELLANT ROCKET MOTORS

Abstract

An optical model of a no-flow rocket motor was completely designed: (1) to establish the characteristics of the incoming perturbation - in the current system a perturbation produced by a pulse generator utilizing blank cartridges and precision diaphragms, (2) to aid in evaluating the velocity probe prior to its insertion into a hot rocket motor, and (3) to observe, for the applied perturbation, the shock wave patterns produced and the time for decay under varying rocket motor conditions. Nonlinear rocket tests so far have consisted of rechecking one chamberinjector combination to determine the stability limits prior to the introduction of nonlinear perturbations. A solution to the theoretical model based on strong shock waves rotating in the chamber is being attempted using IBM 650 equipment.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1961
Accession Number
AD0262335

Entities

People

  • David T. Harrje

Organizations

  • Princeton University

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aeronautical Engineering
  • Air Force
  • Cameras
  • Ceramic Materials
  • Chambers
  • Combustion
  • Combustion Chambers
  • Engineering
  • Government Procurement
  • Materials Laboratories
  • New Jersey
  • New York
  • Photographic Equipment
  • Physics Laboratories
  • Rocket Engines
  • Rockets
  • Shock Waves

Fields of Study

  • Physics

Readers

  • Computer Science/Computer Engineering/Data Science/Digital Signal Processing.
  • Fluid Dynamics.
  • Rocket Propulsion.