Computer Program for Sizing and Performance Analysis of Solid Propellant Rocket Motors

Abstract

A FORTRAN digital computer program was developed which is generally applicable for preliminary design tradeoff analyses of solid-propellant rocket motors for a variety of applications. The program computes rocket motor length, propellant and inert component weights, mass fraction, burn time, specific impulse, ideal stage burnout velocity, and other performance parameters as a function of input motor diameter, chamber pressure, thrust, payload mass, propellant ballistic properties, propellant web fraction, port-to-throat area ratio, and other required parameters. Either conical or contoured nozzle exit geometries may be analyzed. Options are available for considering a head-end propellant web and inert residual slivers.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1972
Accession Number
AD0907326

Entities

People

  • J. L. Thurman

Organizations

  • Teledyne Technologies

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Attachment
  • Burning Rate
  • Combustion
  • Computer Programs
  • Computers
  • Diameters
  • Digital Computers
  • Engineering
  • Geometry
  • Materials
  • Payload
  • Physical Properties
  • Propellants
  • Rocket Engines
  • Rockets
  • Solid Propellants
  • Specific Impulse

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Computer Science.
  • Rocket Propulsion.