A study of confined jet thrust vector control (CJTVC) is presented. By isolating an area of flow separation within the body of a nozzle, CJTVC has the advantage over other thrust vector controls using secondary injection (SI) in that it can operate independent of altitude. This makes it ideal for applications in small missiles and spacecraft attitude control. In this study, axial thrust, side force, and pressure distribution across the nozzle were measured. The parameters were SI pressure, primary short supply pressure, and SI port area. Results indicate that there is a lower limit to the supply pressure ratio (SI pressure to primary pressure) and SI mass flow below which, the nozzle will not produce side force. Also, above a primary pressure of 200 psig, thhe undeflected jet exhibits instabilities. Without SI, a 4 Hz oscillation occurs in the nozzle and switching jet attachment occurs near the throat.
Characteristics of a Confined Jet Thrust Vector Control Nozzle
1984
69 pages
Report
Keine Angabe
Englisch
Missile Technology , Space Technology , Rocket Engines & Motors , Fluid Mechanics , Jet flow , Nozzles , Thrust vector control systems , Secondary injection , Jet propulsion , Confinement(General) , Pressure measurement , Oscillation , Nozzle throats , Isolation , Flow separation , Guided missiles , Axes , Thrust , Mass flow , Pressure distribution , Loads(Forces) , Sides , Attitude control systems , Spacecraft , Side forces , CJTVC(Confined Jet Thrust Vector Control)
Confined jet thrust vector control nozzle studies
AIAA | 1992
|Confined jet thrust vector control nozzle studies
AIAA | 1990
|