Accession Number : AD0613689

Title :   SECONDARY INJECTION THRUST VECTOR CONTROL,

Corporate Author : LOCKHEED MISSILES AND SPACE CO SUNNYVALE CALIF

Personal Author(s) : Zimmerman,C. A. ; Starrett,D. ; Vellinga,J. M.

Report Date : 1964

Pagination or Media Count : 28

Abstract : On the basis of experimentally acquired data, thrust vector control systems utilizing secondary injection of fluids into supersonic nozzles have been developed. Several widely divergent theoretical and analytical treatments of the phenomena have appeared as new applications were proposed. The paper reviews the several theories and attempts correlation with the experimental data. Secondary injection thrust vector control results from the injection of fluid (gas or liquid) into the primary exhaust stream of the rocket motor through ports in the divergent section of the nozzle. A shock is induced resulting in a pressure unbalance in the exit cone. The resultant side force, controllable in magnitude and direction, can be utilized for precise vehicle control. (Author)

Descriptors :   (*SECONDARY INJECTION, THRUST VECTOR CONTROL SYSTEMS), (*THRUST VECTOR CONTROL SYSTEMS, SECONDARY INJECTION), (*ROCKET NOZZLES, THRUST VECTOR CONTROL SYSTEMS), SHOCK WAVES, PERTURBATION THEORY, SUPERSONIC NOZZLES, HEAT TRANSFER, BLUNT BODIES, CORRELATION TECHNIQUES, EXPERIMENTAL DATA, THEORY

Distribution Statement : APPROVED FOR PUBLIC RELEASE