Digital Computer Simulation of the Performance Small Solid Propellant Rocket Motors

Abstract

A mathematical model of a small solid propellant rocket was programmed for use with a Univac Solid State 90 digital computer by means of Fortran I and Fortran II. In addition to calculating the pressure-time and thrust-time transients, the program computes time-averaged pressure, thrust coefficient, thrust, flow rate, and burning rate, as well as total impulse and specific impulse. The report includes the derivation of equations, the method of solution, the program in Fortran I and Fortran II, an example solution compared with experiment, and a recommended procedure for use of the computer program in the design and development of a small solid propellant rocket motor.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1963
Accession Number
AD0425164

Entities

People

  • James M. De Leo

Organizations

  • Frankford Arsenal

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Air Force Facilities
  • Burning Rate
  • Combustion
  • Computer Programs
  • Crystal Structure
  • Digital Computers
  • Engineering
  • Flow Rate
  • Jet Propulsion
  • Mathematical Models
  • Propellant Grains
  • Propulsion Systems
  • Rocket Engines
  • Solid Propellants
  • Specific Impulse
  • Temperature Gradients

Fields of Study

  • Physics

Readers

  • Computer Science.
  • Fluid Dynamics.
  • Rocket Propulsion.