SECONDARY INJECTION THRUST VECTOR CONTROL,
Abstract
On the basis of experimentally acquired data, thrust vector control systems utilizing secondary injection of fluids into supersonic nozzles have been developed. Several widely divergent theoretical and analytical treatments of the phenomena have appeared as new applications were proposed. The paper reviews the several theories and attempts correlation with the experimental data. Secondary injection thrust vector control results from the injection of fluid (gas or liquid) into the primary exhaust stream of the rocket motor through ports in the divergent section of the nozzle. A shock is induced resulting in a pressure unbalance in the exit cone. The resultant side force, controllable in magnitude and direction, can be utilized for precise vehicle control. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1964
- Accession Number
- AD0613689
Entities
People
- C. A. Zimmerman
- D. Starrett
- J. M. Vellinga
Organizations
- Lockheed Martin Missiles and Space