Accession Number : AD0163922

Title :   Thrust Vectoring Control System for Rocket Nozzles.

Descriptive Note : Patent,

Corporate Author : DEPARTMENT OF THE NAVY WASHINGTON D C

Personal Author(s) : Miltenberger,Louis E.

Report Date : 10 APR 1973

Pagination or Media Count : 7

Abstract : The patent concerns a system for providing a rocket powered vehicle with complete thrust vectoring capabilities including a convergent-divergent nozzle attached to a motor casing by a flexible joint member. The flexible joint member includes a laminar structure comprising a series of alternate annular elastomeric and metallic shim members. The elastomeric shim members provide omnidirectional flexible capabilities for the nozzle. Integrally connected to the nozzle is a hydraulically controlled pintle member movable along the axis of the nozzle which varies the effective cross-sectional area of the throat of the nozzle and thereby varies the magnitude of the resulting thrust.

Descriptors :   (*THRUST VECTOR CONTROL SYSTEMS, *PATENTS), (*ROCKET ENGINES, *ROCKET NOZZLES), CONVERGENT DIVERGENT NOZZLES, VARIABLE AREA NOZZLES, VERNIER ROCKET ENGINES, ACTUATORS, FLEXIBLE COUPLINGS

Subject Categories : Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE