Heat Conduction and Stress Analysis of Solid Propellant Rocket Motor Nozzles.

Abstract

A series of three computer programs has been developed that greatly simplify the stress analysis of solid propellant rocket nozzles. The first of these programs is an axisymmetric finite element heat conduction program that is used to generate the time dependent temperature distributions in the nozzle. The second program is an axisymmetric finite element stress analysis program which uses the temperature distribution determined by the first program in addition to mechanical loadings to determine the stresses, strains, and displacements throughout the nozzle. The third program is a data reduction program which has, as output, plots of stress and strain contours in the nozzle. The heat conduction and stress analysis programs may be used separately if desired. If they are used together, information is passed from the first to the second by magnetic tape. (Author)

Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1969
Accession Number
AD0848594

Entities

People

  • John J. Brisbane

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Axisymmetric
  • Computer Programs
  • Computers
  • Data Reduction
  • Gas Turbine Nozzles
  • Magnetic Tape
  • Nozzles
  • Propellants
  • Rocket Engines
  • Rocket Nozzles
  • Rockets
  • Solid Propellants
  • Stress Analysis
  • Stresses

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Mechanical Engineering/Mechanics of Materials.
  • Technical Research and Report Writing.