This program was established to design, develop, and demonstrate a hot gas secondary injection thrust vector control system (HGSITVC) for large solid propellant rocket motors. Phase I of the program was the design, analysis, and optimization of a 156 in. diameter motor HGSITVC system. The data from this baseline design was used to design four test pintle valves for demonstration on 65 in. diameter test motors. Phase II consisted of designing a four valve, 120 in. diameter motor HGSITVC system using the basic designs and design data developed under Phase I. The 120 in. diameter test motor demonstrated four full scale 156 in. diameter motor pintle valves. The 156 in. diameter motor uses 16 pintle valves of the design tested. (Author)
Hot Gas Secondary Injection Thrust Vector Control Demonstration Program. Volume III
1968
99 pages
Report
Keine Angabe
Englisch
Rocket Engines & Motors , Thrust vector control systems , Solid propellant rocket engines , Movable nozzles , Design , Liquid jets , Secondary injection , Valves , Orifices , Rocket nozzles , Booster rockets , Payload , Costs , Reliability , Third stage engines , Surface to surface missiles , Optimization , Gas turbines , Hot gas thrust vector control , Pintle valves , 156-in. rocket motors , Computer aided design , Litvc(Liquid injection thrust vector control) , Minuteman , Minuteman 3 missiles , Strap on motors
Secondary-injection thrust vector control systems.
NTRS | 1969
|Thrust vector control technology demonstration
AIAA | 1986
|