Accession Number : AD0374231

Title :   HOT GAS SECONDARY INJECTION THRUST VECTOR CONTROL DEMONSTRATION PROGRAM.

Descriptive Note : Quarterly technical rept. no. 1, 15 Feb-31 May 66,

Corporate Author : THIOKOL CHEMICAL CORP BRIGHAM CITY UTAH WASATCH DIV

Personal Author(s) : Nance,Paul D.

Report Date : 30 JUN 1966

Pagination or Media Count : 81

Abstract : This program was established to design, develop, and demonstrate a hot gas secondary injection thrust vector control system (HGSITVC) for large solid propellant rocket motors. Phase 1 of the program is concerned with the design, analysis, and optimization of a 156 in. dia motor HGSITVC system. The data from this baseline design will be used to design six test pintle valves for demonstration on 65 in. dia test motors. Phase 2 consists of designing a four-valve 120 in. dia motor HGSITVC system using the basic designs and design data developed under Phase 1. The 120 in. dia test motor will be designed, fabricated, and tested to demonstrate four full scale 156 in. dia motor pintle valves. The pintle valve will use a proven tungsten-to-tungsten valve seating arrangement and a pressure balance technique to minimize actuation force requirements. A baseline 156 in. dia demonstration test motor which uses available proven MINUTEMAN hardware was designed. The test motor will expose the full scale 156 in. pintle valve to simulated flow and operational pressure environments. The propellant for the demonstration test motor was tailored to define the required formulation, and the major components for the first Phase 1 test were ordered. Four satisfactory orifice forgings were shipped.

Descriptors :   (*SECONDARY INJECTION, *SOLID PROPELLANT ROCKET ENGINES), RESEARCH MANAGEMENT, DESIGN, OPTIMIZATION, VALVES, TUNGSTEN, SOLID ROCKET PROPELLANTS, ROCKET COMPONENTS, ORIFICES, FORGING, PRESSURE, GAS FLOW, THRUST VECTOR CONTROL SYSTEMS (U) AMMONIUM COMPOUNDS, PERCHLORATES, ALUMINIZED EXPLOSIVES, COMBUSTION CHAMBERS, BURNING RATE, NOZZLE CLOSURES, ROCKET PROPELLANT GRAINS, PYROGEN IGNITERS, HYDRAULIC ACTUATORS, DIAPHRAGMS(MECHANICS)

Subject Categories : Solid Propellant Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE