Nonlinear Analysis of Solid Rocket Combustion Instability. Volume I.

Abstract

The primary objective of the current effort was to improve the utility, efficiency and accuracy of the previously developed nonlinear longitudinal combustion instability program. A finite difference procedure has been substituted for the method of characteristics solution of the governing equations of motion. The range of allowable motor and grain geometries has been greatly extended. In addition, the two-phase analysis has been extended to multiple particle sizes. A comparison with data from a small laboratory pulse motor has demonstrated that the present nonlinear model is capable of quantitatively predicting limiting amplitude when the combustion response of the propellant is adequately characterized. The program has also been modified to make it applicable to T-burners. A vent model which accounts for acoustic radiation losses has been developed. Separate nonlinear particle damping and uncoupled nonlinear combustion response studies have been carried out. (Modified author abstract)

Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1974
Accession Number
AD0786924

Entities

People

  • F. E. C. Culick
  • Jay N. Levine

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Abstracts
  • Accuracy
  • Amplitude
  • Buildings And Structures
  • Combustion
  • Efficiency
  • Equations
  • Equations Of Motion
  • Geometry
  • Instability
  • Mathematics
  • Method Of Characteristics
  • Nonlinear Analysis
  • Nonlinear Dynamics
  • Particle Size
  • Particles

Fields of Study

  • Physics

Readers

  • Computational Modeling and Simulation
  • Control Systems Engineering.
  • Rocket Propulsion.