Accession Number : AD0376230

Title :   DEVELOPMENT OF A ROCKET MOTOR FOR CROW.

Descriptive Note : Final rept.,

Corporate Author : ROHM AND HAAS CO HUNTSVILLE ALA REDSTONE RESEARCH LABS

Personal Author(s) : Stone,William C.

Report Date : 10 OCT 1966

Pagination or Media Count : 40

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. (Author)

Descriptors :   (*SOLID PROPELLANT ROCKET ENGINES, RESEARCH MANAGEMENT) (U) *ARTILLERY ROCKETS, FLIGHT TESTING, CAPTIVE TESTS, SURFACE TO SURFACE, IMPACT PREDICTION, ROCKET TRAJECTORIES, MISS DISTANCE, ROCKET WARHEADS, HIGH EXPLOSIVE AMMUNITION, DEGRADATION, ROCKET PROPELLANT GRAINS, BURNING RATE, TEMPERATURE CONTROL, CONFIGURATION, HEAT SHIELDS, NOZZLE INSERTS, ROCKET ENGINE CASES, THERMAL INSULATION, ROCKET IGNITERS

Subject Categories : Ammunition and Explosives
      Rockets
      Thermodynamics
      Solid Propellant Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE