[특허]Bidirectional control surfaces for use with high speed vehicles, and associated systems and methods

Blue Origin, LLC

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특허 상세정보

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Bidirectional control surfaces for use with high speed vehicles, and associated systems and methods

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64G-001/62 F42B-010/06 F42B-010/64 B64G-001/24 B64G-001/00 B64C-009/00 B64G-001/40
미국특허분류(USC)	244/158.9; 244/003.21
출원번호	US-0968326 (2013-08-15)
등록번호	US-8876059 (2014-11-04)
발명자 / 주소	Featherstone, Mark
출원인 / 주소	Blue Origin, LLC
대리인 / 주소	Perkins Coie LLP
인용정보	피인용 횟수 : 4 인용 특허 : 23

초록

Vehicles with bidirectional control surfaces and associated systems and methods are disclosed. In a particular embodiment, a rocket can include a plurality of bidirectional control surfaces positioned toward an aft portion of the rocket. In this embodiment, the bidirectional control surfaces can be operable to control the orientation and/or flight path of the rocket during both ascent, in a nose-first orientation, and descent, in a tail-first orientation for, e.g., a tail-down landing.

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1. A method for controlling a rocket having a first end portion, a second end portion, and at least one moveable control surface, wherein the at least one moveable control surface has a first edge portion and a second edge portion, the method comprising: aerodynamically controlling the rocket with the at least one moveable control surface when the rocket is flying in a first orientation in which the first end portion leads the second end portion and the first edge portion leads the second edge portion; andaerodynamically controlling the rocket with the at least one moveable control surface when the rocket is flying in a second orientation in which the second end portion leads the first end portion;wherein aerodynamically controlling the rocket with the at least one moveable control surface when the rocket is flying in the first and second orientations includes pivoting the at least one moveable control surface about a pivot axis that extends between the first and second edge portions. 2. The method of claim 1, wherein aerodynamically controlling the rocket when the rocket is flying in the first orientation includes aerodynamically controlling the rocket during ascent, and aerodynamically controlling the rocket when the rocket is flying in the second orientation includes aerodynamically controlling the rocket during descent. 3. The method of claim 2 wherein aerodynamically controlling the rocket during ascent includes controlling the rocket in supersonic flight. 4. The method of claim 2, wherein aerodynamically controlling the rocket during descent includes controlling the rocket in subsonic flight. 5. The method of claim 1, further comprising: operably coupling a rocket exhaust nozzle toward the second end portion; andoperably coupling the at least one moveable control surface toward the second end portion. 6. The method of claim 1 wherein the at least one moveable control surface includes a plurality of fins, and wherein the method further comprises: operably coupling at least one rocket exhaust nozzle toward the second end portion; andpivotally coupling the plurality of fins toward the second end portion. 7. The method of claim 1, further comprising landing the rocket in a vertical orientation. 8. The method of claim 1, wherein pivoting the at least one moveable control surface about a pivot axis includes pivoting at least 180 degrees about the pivot axis. 9. The method of claim 1 wherein pivoting the at least one moveable control surface about a pivot axis includes rotating the control surface about an axis that extends perpendicular to a longitudinal axis of the rocket. 10. The method of claim 1 wherein the second edge portion leads the first edge portion when the rocket is flying in the second orientation. 11. The method of claim 1 wherein the at least one moveable control surface further includes: a root portion; anda distal tip portion spaced apart from the root portion, wherein the first and second edge portions extend between the root portion and the tip portion, and wherein the second edge portion leads the first edge portion when the rocket is flying in the second orientation. 12. A method of operating a rocket having a forward end portion and one or more rocket engines positioned toward an aft end portion, the method comprising: igniting the one or more rocket engines to launch the rocket from Earth in a first orientation in which the forward end portion leads the aft end portion, wherein the rocket includes a bidirectional control surface having a first edge portion and a second edge portion, and wherein the first edge portion leads the second edge portion when the rocket is in the first orientation;aerodynamically controlling the rocket during ascent through Earth's atmosphere in the first orientation by pivoting the bidirectional control surface about a pivot axis that extends between the first and second edge portions;reorienting the rocket from the first orientation to a second orientation in which the aft end portion leads the forward end portion; andaerodynamically controlling the rocket during descent through the Earth's atmosphere in the second orientation by pivoting the bidirectional control surface about the pivot axis. 13. The method of claim 12 wherein pivoting the bidirectional control surface includes pivoting a control fin that extends outwardly from the aft end portion of the rocket. 14. The method of claim 11, further comprising: aerodynamically controlling a flight path of the rocket to a landing site in the second orientation by moving the bidirectional control surface; andlanding the rocket at the landing site in a vertical orientation. 15. The method of claim 14, wherein landing the rocket in a vertical orientation further includes providing rocket engine thrust. 16. The method of claim 12, further comprising, after aerodynamically controlling the rocket during ascent and before aerodynamically controlling the rocket during descent, pivoting the bidirectional control surface at least 180 degrees about the pivot axis. 17. The method of claim 12 wherein the second edge portion leads the first edge portion when the rocket is descending through the Earth's atmosphere in the second orientation. 18. A method of controlling an airborne vehicle, the method comprising: propelling the airborne vehicle using at least one rocket stage;steering the vehicle in an ascent orientation using one or more moveable bidirectional control surfaces, each control surface having a first edge and a second edge that trails the first edge when the vehicle is in the ascent orientation;steering the vehicle in a descent orientation using the same one or more control surfaces used to steer the vehicle in the ascent orientation, wherein the second edge leads the first edge when the vehicle is in the descent orientation; andsteering the vehicle toward a vertical landing using the same one or more control surfaces used to steer the vehicle in the ascent and descent orientations. 19. The method of claim 18, wherein steering the vehicle further comprises pivoting the one or more moveable bidirectional control surfaces about a pivot axis. 20. The method of claim 18, wherein steering the vehicle using the one or more moveable bidirectional control surfaces further comprises demonstrating a first lift slope of each control surface when the vehicle is in the ascent orientation and demonstrating a second lift slope of each control surface when the vehicle is in the descent orientation, wherein the first lift slope is different from the second lift slope. 21. The method of claim 18, wherein propelling the airborne vehicle includes propelling the vehicle into space. 22. The method of claim 18, wherein propelling the vehicle using at least one rocket stage includes providing thrust from the rocket stage when the vehicle is in the ascent orientation, and wherein the method further comprises providing thrust from the rocket stage when the vehicle is in the descent orientation. 23. The method of claim 18, wherein steering the vehicle comprises operating any of the control surfaces independently of any other control surfaces. 24. A method for controlling a rocket having a first end portion and a second end portion, the method comprising: aerodynamically controlling the rocket with one or more moveable control surfaces when the rocket is flying in a first orientation in which the first end portion leads the second end portion; andaerodynamically controlling the rocket with the one or more moveable control surfaces when the rocket is flying in a second orientation in which the second end portion leads the first end portion;wherein aerodynamically controlling the rocket with the one or more moveable control surfaces comprises pivoting the one or more moveable control surfaces about a pivot axis that extends radially outward from a longitudinal axis of the rocket. 25. The method of claim 24, wherein the pivot axis intersects the longitudinal axis of the rocket. 26. The method of claim 24, wherein the pivot axis is perpendicular to the longitudinal axis of the rocket. 27. The method of claim 24, further comprising: aerodynamically controlling a flight path of the rocket to a landing site in the second orientation by pivoting the one or more moveable control surfaces about the pivot axis; andlanding the rocket at the landing site in the second orientation. 28. The method of claim 24, further comprising providing rocket engine thrust when the rocket is flying in the second orientation.

이 특허에 인용된 특허 (23)

이 특허를 인용한 특허 피인용횟수: 4

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Bidirectional control surfaces for use with high speed vehicles, and associated systems and methods

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Bidirectional control surfaces for use with high speed vehicles, and associated systems and methods

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이 특허에 인용된 특허 (23)

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