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US 4,063,685 AGranted
Thrust vector control by circulation control over aerodynamic surfaces in a supersonic nozzle
AssigneeThe United States of America as represented by the Secretary of the Army
InventorPaul L. Jacobs
Life of this patent
Estimating the term…
Abstract
Aerodynamic surfaces are fixedly mounted in the diverging section of a rot nozzle and a fluid is injected through the fixed jet vane to flow about the vane. Fluid flow is controlled to make it appear that from upstream the jet vane is at an angle of attack. This deflects the main flow and produces side force. A minimum of injection flow enables high side forces to be obtained for missile control.
Claims3
A thrust vector control system for a rocket having a converging-diverging nozzle for expulsion of propulsive gases therefrom comprising:
- a. a source of gas;
- b. four jet vanes fixedly secured in said diverging portion of said portion of said nozzle in equally spaced relation, each said jet vane having a pair of spaced surfaces disposed in angular relation to the longitudinal axis of said vane, and, a row of openings extending in spaced relation along said spaced surfaces, said jet vanes having passages therethrough in communication with said source of gas and said openings to selectively direct gas through the desired row of said openings;
- c. fluid amplifier means for directing said gas through said jet vanes for controlled flow of said gas about said jet vanes whereby a side force is developed to simulate an angle of attack of said jet vanes without physical movement thereof.
Dependencies are inferred from the claim text.