A Thermal Stress Calculation for Rocket Propellent Charges.

Abstract

A simplified mathematical model is assumed for the calculation of thermal stress arising in the charges of solid propellent rockets when cooled to their storage temperature after manufacture. The inner surface of these charges is convoluted for design reasons and this has the effect of increasing the thermal stress so that splitting of the surface can occur. The partial differential equations of the mathematical model are solved numerically. (Author)

Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1971
Accession Number
AD0746640

Entities

People

  • M. R. Abbott

Organizations

  • Royal Aircraft Establishment

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Differential Equations
  • Equations
  • Mathematical Models
  • Mathematics
  • Models
  • Partial Differential Equations
  • Splitting
  • Stresses
  • Thermal Stresses

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Rocket Propulsion.