초록 ▼

A yaw control system is provided for use in a hypersonic airborne mobile platform, for example a re-entry vehicle. The system includes an active movable yaw control flap positioned between passive/fixed yaw ear surfaces that border or frame the active yaw flaps. The yaw control system includes an a

A yaw control system is provided for use in a hypersonic airborne mobile platform, for example a re-entry vehicle. The system includes an active movable yaw control flap positioned between passive/fixed yaw ear surfaces that border or frame the active yaw flaps. The yaw control system includes an active yaw control flap embedded between passive/fixed yaw ear surfaces. The retracted active yaw control flap and passive/fixed yaw ear surfaces provide passive yaw damping during atmosphere reentry, bank-to-turn steering and midcourse fly-out/glide steering. The active yaw control flaps are preferably arranged on opposing sides of a re-entry vehicle, and may be independently extended to provide for steering the vehicle. The active yaw control flaps provide for active yaw control skid-to-turn terminal guidance to achieve a desired level of accuracy, such as needed when using the vehicle as a missile to strike a target.

대표청구항 ▼

What is claimed is: 1. A control system for controlling flight of a hypersonic vehicle, comprising: a movable yaw control surface disposed on a body portion of the vehicle; a pair of fixed yaw control surfaces disposed on said body portion of said vehicle adjacent to, and on opposite sides of, said

What is claimed is: 1. A control system for controlling flight of a hypersonic vehicle, comprising: a movable yaw control surface disposed on a body portion of the vehicle; a pair of fixed yaw control surfaces disposed on said body portion of said vehicle adjacent to, and on opposite sides of, said movable yaw control surface, and projecting outwardly from said body portion, the pair of fixed yaw control surfaces disposed closely adjacent and generally parallel to side portions of the movable yaw control surface to shield portions of the movable yaw control surface from erosion resulting from entry into a planetary atmosphere, such that substantially all of the movable yaw control surfaces are preserved to provide maximum maneuverability for the vehicle; and said movable yaw control surface being controllably movable between at least one deployed position projecting outwardly from said body portion, and a retracted position, for controlling at least one of a flight path and attitude of said vehicle during flight. 2. The control system of claim 1, wherein said control system uses said fixed yaw control surface to effect passive yaw stabilization during bank-to-turn steering of said vehicle during re-entry and midcourse fly-out glide steering of the vehicle in a planetary atmosphere during flight. 3. The control system of claim 1, wherein said control system uses said movable yaw control surface to effect skid-to-turn terminal guidance to steer the vehicle. 4. The control system of claim 1, further comprising right and left movable yaw control surfaces disposed on opposite sides of the vehicle, and first and second pairs of fixed yaw control surfaces disposed on opposite sides of the vehicle adjacent respective ones of the movable yaw control surfaces. 5. The control system of claim 1, wherein the fixed yaw control surface bordering the movable yaw control surface receives a portion of aero-heating induced erosion that results from re-entry into a planetary atmosphere, to preserve the movable yaw control surface for maintaining maneuverability of the vehicle. 6. The control system of claim 1, wherein the fixed yaw control surface reduces the need for activating the movable yaw control surface during re-entry flight into the atmosphere. 7. A yaw control system for a hypersonic, re-entry vehicle, comprising: at least two movable yaw control surfaces arranged on generally opposite sides of the vehicle, each said movable yaw control surface being capable of moving independently of the other between at least one extended position that operates to apply a turning moment to the vehicle, and a retracted position; and two pairs of fixed yaw control surfaces that each border opposite sides of a respective one of the movable yaw control surfaces and that project outwardly from an outer surface of a body of the vehicle; each said pair of fixed yaw control surfaces together with its respective said movable yaw control surface, when said movable yaw control surface is in its retracted position, providing passive yaw stabilization for maneuvering when entering a planetary atmosphere; and wherein the fixed yaw control surfaces operate to shield the movable yaw control surfaces from erosion resulting from entry into the planetary atmosphere, such that substantially all of each of the movable yaw control surfaces are preserved. 8. The yaw control system of claim 7, wherein each said pair of the fixed yaw control surfaces, together with its respective said movable yaw control surface, when in its retracted position, provides passive yaw stabilization for the vehicle. 9. The yaw control system of claim 7, wherein the at least two movable yaw control surfaces may both be extended for use in increasing drag to reduce the speed of the aerodynamic vehicle. 10. The yaw control system of claim 7, wherein the fixed yaw control surfaces bordering one of said movable yaw control surface receive the brunt of the aero-heating induced erosion that results from re-entry flight of the vehicle into the planetary atmosphere, to preserve substantially all of the movable yaw control surface for maintaining maneuverability of the vehicle during terminal approach towards an intended destination. 11. The yaw control system of claim 10, wherein the fixed yaw control surfaces reduce the need for extending the movable yaw control surfaces during re-entry into the planetary atmosphere. 12. The yaw control system of claim 10, wherein the fixed yaw control surfaces provide passive yaw dampening for bank-to-turn maneuvers during re-entry flight of the vehicle into the planetary atmosphere and during midcourse flight. 13. The yaw control system of claim 11, wherein the movable yaw control surfaces are independently extended to perform skid-to-turn steering maneuvers with a faster response time for guiding the vehicle on terminal flight towards the destination. 14. A hypersonic vehicle comprising: a body having an outer surface defining a generally tapered conical shape; at least two movable yaw control surfaces arranged at spaced apart locations on said body, with each said movable yaw control surface being moveable between an extended position that operates to apply a turning moment to the body during flight of the vehicle, and a retracted position; and a pair of fixed yaw control surfaces associated with each one of said movable yaw control surfaces, each said pair of fixed yaw control surfaces being positioned adjacent to the sides of an associated one of said movable yaw control surfaces and projecting from said outer surface of said body; when each of said movable yaw control surfaces is in said retracted position, its respective pair of fixed yaw control surfaces provide passive yaw stabilization for the vehicle during flight of the vehicle; and each said pair of fixed yaw control surfaces adapted to shield side portions of its associated said movable yaw control surface from erosion resulting from heat generation during entry into a planetary atmosphere. 15. The hypersonic vehicle of claim 14, wherein the two movable yaw control surfaces may both be extended to increase drag to reduce the speed of the vehicle. 16. The hypersonic vehicle of claim 14, wherein each said pair of fixed yaw control surfaces border at least two sides of its said respective movable yaw control surface to shield the movable yaw control surface from erosion resulting from entry into a planetary atmosphere, such that substantially all of the movable yaw control surfaces are preserved to provide maximum maneuverability for the vehicle. 17. The hypersonic vehicle of claim 16, wherein the fixed yaw control surfaces and the movable yaw control surfaces enable the vehicle to achieve a guidance accuracy of less than about 5 meters Circular Error Probable (CEP). 18. The hypersonic vehicle of claim 14, wherein the fixed yaw control surfaces together with the movable yaw control surface, in its retracted position, provide passive yaw stabilization for the vehicle. 19. The hypersonic vehicle of claim 16, wherein the fixed yaw control surfaces bordering the movable yaw control surface receive a majority of aero-heating induced erosion that results from re-entry of the vehicle into the planetary atmosphere, to preserve substantially all of the movable yaw control surfaces for maintaining maneuverability of the vehicle during terminal approach towards an intended destination. 20. The hypersonic vehicle of claim 17 wherein a battery is used to power at least the steering of the vehicle, and the fixed yaw control surfaces reduce the frequency of extending the movable yaw control surfaces during re-entry into the planetary atmosphere, thereby reducing the amount of battery power utilized for steering. 21. The hypersonic vehicle of claim 17 wherein the fixed yaw control surfaces provide yaw dampening for bank-to-turn maneuvers during re-entry of the vehicle into the planetary atmosphere and during a midcourse phase of vehicle flight. 22. The hypersonic vehicle of claim 18, wherein the movable yaw control surfaces are individually extendable to perform skid-to-turn steering maneuvers with a faster response time for guiding the vehicle on terminal flight towards the destination. 23. The hypersonic vehicle of claim 18, wherein the movable yaw control surfaces are maintained in a retracted position flush with the fixed yaw control surfaces during re-entry into an atmosphere and bank-to-turn maneuvers during midcourse flight, to preserve the movable yaw control surfaces for use during terminal guidance towards the destination. 24. A method for controlling the operation of a hypersonic vehicle having at least one movable control surface, the method comprising: using at least a pair of fixed control surfaces disposed closely adjacent to side portions of the at least one movable control surface to cover the side portions of the at least one movable control surface when the at least one movable control surface is in a retracted position, the fixed control surfaces projecting from an outer surface of the vehicle and assisting in providing yaw control of the vehicle; maintaining the at least one movable control surface in a stowed position, in which the at least one movable control surface is generally flush with the adjacent fixed control surface, until the vehicle has completed entry into the earth's atmosphere; and subsequently controlling the extension and retraction of the at least one movable control surface as needed to provide skid-to-turn maneuvering for guiding the vehicle towards a target.