Movable ground based recovery system for reuseable space flight hardware
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
G05D-001/00
G05D-003/00
G06F-007/00
G06F-017/00
출원번호
US-0213022
(2011-08-18)
등록번호
US-8498756
(2013-07-30)
발명자
/ 주소
Sarver, George L.
출원인 / 주소
The United States of America as Represented by the Adminstrator of the National Aeronautics & Space Administration (NASA)
대리인 / 주소
Schipper, John F.
인용정보
피인용 횟수 :
4인용 특허 :
4
초록▼
A reusable space flight launch system is configured to eliminate complex descent and landing systems from the space flight hardware and move them to maneuverable ground based systems. Precision landing of the reusable space flight hardware is enabled using a simple, light weight aerodynamic device o
A reusable space flight launch system is configured to eliminate complex descent and landing systems from the space flight hardware and move them to maneuverable ground based systems. Precision landing of the reusable space flight hardware is enabled using a simple, light weight aerodynamic device on board the flight hardware such as a parachute, and one or more translating ground based vehicles such as a hovercraft that include active speed, orientation and directional control. The ground based vehicle maneuvers itself into position beneath the descending flight hardware, matching its speed and direction and captures the flight hardware. The ground based vehicle will contain propulsion, command and GN&C functionality as well as space flight hardware landing cushioning and retaining hardware. The ground based vehicle propulsion system enables longitudinal and transverse maneuverability independent of its physical heading.
대표청구항▼
1. A method for capturing reusable space flight hardware that passes through an atmosphere in an approach to a terrestrial surface, the method comprising: estimating a trajectory of the space flight hardware as the hardware descends;identifying a target landing region on the terrestrial surface that
1. A method for capturing reusable space flight hardware that passes through an atmosphere in an approach to a terrestrial surface, the method comprising: estimating a trajectory of the space flight hardware as the hardware descends;identifying a target landing region on the terrestrial surface that the estimated trajectory will intersect as the hardware approaches the terrestrial surface;providing at least one ground based vehicle that is movable and maneuverable and that comprises a hovercraft having a landing platform on which the hardware is to be captured;pre-positioning the at least one ground based vehicle in the target landing region so that the estimated trajectory intersects at least a portion of the landing platform;providing an atmospheric deceleration system on the space flight hardware;activating the deceleration system on the space flight hardware as the hardware approaches the terrestrial surface;allowing the space flight hardware to descend in reaction to aerodynamic and gravitational forces acting upon the space flight hardware and the deceleration system;measuring relative positions of the space flight hardware and at least one of the landing platform and the ground based vehicle; andmaneuvering the ground based vehicle using measured relative positions and the estimated trajectory to capture the space flight hardware as the hardware descends to the terrestrial surface. 2. The method of claim 1, wherein said deceleration system comprises a simple parachute. 3. The method of claim 1, wherein said deceleration system comprises a variable ballistic coefficient parachute or parafoil that has limited steering and energy management capability. 4. The method of claim 1, wherein maneuvering said ground based vehicle comprises moving said ground based vehicle in at least two independent directions, drawn from forward direction, rearward direction, leftward direction, rightward direction and rotation about a selected axis that intersects said terrestrial surface. 5. The method of claim 1, further comprising providing a recovery guidance, navigation and control (GN&C) system on said at least one ground based vehicle. 6. The method of claim 5, wherein said GN&C system incorporates measurement of absolute and relative position and velocity information of the space flight hardware and ground based vehicle into its command guidance algorithm. 7. The method of claim 5, wherein said GN&C system enables position guidance information to control the ground based vehicle based upon the estimated trajectory of the space flight hardware. 8. The method of claim 1, wherein maneuvering said ground based vehicle comprises substantially matching the descending flight hardware ground position, ground speed, and ground heading at capture of said space flight hardware. 9. The method of claim 8, wherein said landing platform is oriented to match said descending space flight hardware principal longitudinal axis, aligning the space flight hardware center of mass with the center of the landing platform. 10. The method of claim 1, wherein said space flight hardware is a booster. 11. The method of claim 1, wherein said space flight hardware is a spacecraft. 12. The method of claim 1, wherein said space flight hardware is an engine or equipment pod. 13. A hardware capture system used to capture and recover space flight hardware that passes through an atmosphere in an approach to a terrestrial surface, the system comprising: a surface effect levitation system comprising one or more flexible skirts and a pressurization mechanism;a landing platform, comprising an energy absorbing open surface that comprises netting, to mechanically receive and capture the space flight hardware;a hovercraft propulsion system capable of maneuvering a hovercraft in forward/aft translation, left/right translation and directional rotation (compass heading) independently of each other;guidance, navigation and control (GN&C) hardware located on the hovercraft that directs motion of the hovercraft to maneuver itself beneath the descending space flight hardware, to approximately match the space flight hardware speed and direction when the space flight hardware approaches the landing platform. 14. The system of claim 13, wherein said landing platform is comprised of an energy absorbing open surface. 15. The system of claim 14, wherein said energy absorbing open surface comprises netting. 16. The system of claim 13, wherein said propulsion system comprises at least two propulsion units fixed relative to said hovercraft and configured to propel said hovercraft in forward, rearward, leftward and rightward translation, independent of rotation. 17. The system of claim 13, wherein said propulsion system includes at least two vectored thrust propulsion units configured to propel said hovercraft in forward, rearward, leftward and rightward translation, independent of rotation. 18. The system of claim 13, wherein said hovercraft includes an air cushion, the air cushion being subdivided into four or more chambers that are configured to provide roll and pitch stability. 19. A method for capturing reusable space flight hardware that passes through an atmosphere in an approach to a terrestrial surface, the method comprising: estimating a trajectory of the space flight hardware as the hardware descends;identifying a target landing region on the terrestrial surface that the estimated trajectory will intersect as the hardware approaches the terrestrial surface;providing at least one ground based vehicle that is movable and maneuverable and that provides a dry landing platform for the space flight hardware at an ocean landing site;pre-positioning the at least one ground based vehicle in the target landing region so that the estimated trajectory intersects at least a portion of the landing platform;providing an atmospheric deceleration system on the space flight hardware;activating the deceleration system on the space flight hardware as the hardware approaches the terrestrial surface;allowing the space flight hardware to descend in reaction to aerodynamic and gravitational forces acting upon the space flight hardware and the deceleration system;measuring relative positions of the space flight hardware and at least one of the landing platform and the ground based vehicle;maneuvering the ground based vehicle using the measured relative positions and the estimated trajectory to capture the space flight hardware as the hardware descends to the terrestrial surface.
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