Gaseous secondary injection thrust vector control device

Apparatus for modulating the thrust vector of a rocket motor by injecting hot gas into the divergent section of the rocket nozzle and modulating injection of the hot gas by varying the flow from a solid propellant gas generator by controlling its flow rate with a vortex throttling valve arrangement.

Saved in:
Bibliographic Details
Main Authors DUNAWAY; J. C, JACOBS; PAUL L
Format Patent
LanguageEnglish
Published 18.08.1987
Edition4
Subjects
BLASTING
COMBUSTION ENGINES
GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC
GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
JET-PROPULSION PLANTS
LIGHTING
MECHANICAL ENGINEERING
TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
TECHNICAL SUBJECTS COVERED BY FORMER USPC
TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
WEAPONS
Online AccessGet full text

Cover

More Information
Summary:Apparatus for modulating the thrust vector of a rocket motor by injecting hot gas into the divergent section of the rocket nozzle and modulating injection of the hot gas by varying the flow from a solid propellant gas generator by controlling its flow rate with a vortex throttling valve arrangement.
Bibliography:Application Number: US19820362017