Accession Number : AD0377072

Title :   HOT GAS SECONDARY INJECTION THRUST VECTOR CONTROL DEMONSTRATION PROGRAM PROJECT 2000.

Descriptive Note : Quarterly technical rept. no. 2, 1 Jun-30 Sep 66,

Corporate Author : THIOKOL CHEMICAL CORP BRIGHAM CITY UTAH WASATCH DIV

Personal Author(s) : Nance,Paul D.

Report Date : 20 OCT 1966

Pagination or Media Count : 144

Abstract : This program has the end objective of demonstrating a flightweight hot gas secondary injection thrust vector control (HGSITVC) for large solid propellant rocket motors. Effort reviewed in the second quarterly report includes the design of a full scale test pintle valve to be used in the development testing. Two of the test pintle valves were fabricated and tested on a 6,000 lb class demonstration test motor. Test results indicate that the pintle valve design is highly satisfactory for continuation of testing in the subscale test motor development program. During the first static test, valve No. 1 was exposed to low mass flow and long duration to insure survivability of the pintle valve. Valve No. 2 was exposed to approximately the same mass flow planned for the full scale 120 in. demonstration test motor. Test data verify that the valve successfully held up under simulated large motor environment. Test results will be utilized to improve the test motor design and incorporate slight modifications in pintle valves No. 3 and 4 for the second test motor. The second demonstration test (TU-521.02 motor) is scheduled for testing during the third quarter of the program.

Descriptors :   (*THRUST VECTOR CONTROL SYSTEMS, *SECONDARY INJECTION), (*SOLID PROPELLANT ROCKET ENGINES, THRUST VECTOR CONTROL SYSTEMS), EXHAUST GASES, GAS FLOW, ROCKET ENGINE CASES, VALVES, SHEAR STRESSES, ROCKET NOZZLES (U) TUNGSTEN, NICKEL ALLOYS, CHROMIUM ALLOYS, COBALT ALLOYS, MOLYBDENUM, CARBON, SILICON COMPOUNDS, OXIDES, SERVOMECHANISMS, DIAPHRAGMS(MECHANICS)

Subject Categories : Solid Propellant Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE