DEVELOPMENT OF A ROCKET MOTOR FOR CROW

Abstract

A rocket motor for the CROW missile was developed in a time period of approximately four months. The motor was 2.54 inches in diameter and 20 inches in length. The motor contained 3.1 pounds of plastisol nitrocellulose composite propellant in a rod-and-tube grain design and weighed six pounds ready to fire. The high-strength steel case and aluminum nozzle were insulated to prevent excessive heating of the motor case. Nineteen motors were static tested and five were successfully flight tested at accelerations of approximately 110 g's. The motor produced an average thrust of 4300 for a burning time of 175 microsec, and delivered a total impulse of 805 ft lb-sec/thousand lb. The operating pressure was 4000 lb/sq. in absolute.

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Document Details

Document Type
Technical Report
Publication Date
Oct 10, 1966
Accession Number
AD0376230

Entities

People

  • William C. Stone

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Burning Rate
  • Composite Materials
  • Composite Propellants
  • Diameters
  • Fabrication
  • Geometry
  • High Explosives
  • Ignition Systems
  • Materials
  • Materials Laboratories
  • Materials Processing
  • Metals
  • New York
  • Physical Properties
  • Propellants
  • Rocket Engines
  • Rockets

Fields of Study

  • Physics

Readers

  • Mathematics or Statistics
  • Rocket Propulsion.

Technology Areas

  • Microelectronics
  • Microelectronics - Microelectromechanical Systems