Accession Number : AD0376230
Title : DEVELOPMENT OF A ROCKET MOTOR FOR CROW
Descriptive Note : Final rept.
Corporate Author : ROHM AND HAAS CO HUNTSVILLE AL REDSTONE RESEARCH LABS
Personal Author(s) : Stone, William C
PDF Url : AD0376230
Report Date : 10 Oct 1966
Pagination or Media Count : 42
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.
Descriptors : *SOLID PROPELLANT ROCKET ENGINES, BURNING RATE, CAPTIVE TESTS, DEGRADATION, FLIGHT TESTING, HEAT SHIELDS, HIGH EXPLOSIVE AMMUNITION, IMPACT PREDICTION, MISS DISTANCE, NOZZLE INSERTS, ROCKET ENGINE CASES, ROCKET IGNITERS, ROCKET PROPELLANT GRAINS, ROCKET TRAJECTORIES, ROCKET WARHEADS, SURFACE TO SURFACE, TEMPERATURE CONTROL, THERMAL INSULATION
Subject Categories : Ammunition and Explosives
Solid Propellant Rocket Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE