Gaseous Secondary Injection Thrust Vector Control Device.
Abstract
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. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 25, 1982
- Accession Number
- ADD009345
Entities
People
- J. C. Dunaway
- Paul L. Jacobs
Organizations
- United States Army