Reusable flyback rocket booster and method for recovering same
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-037/02
B64G-001/00
출원번호
US-0178428
(2002-06-24)
발명자
/ 주소
Barnes, Kenneth H.
Butler, William M.
Hagseth, Paul E.
출원인 / 주소
Lockheed Martin Corporation
대리인 / 주소
Baker Botts L.L.P.
인용정보
피인용 횟수 :
16인용 특허 :
3
초록▼
According to one embodiment of the invention, a rocket booster for launching a payload into space includes a fuselage adapted to support one or more fuel tanks inside the fuselage and a booster engine coupled to an aft portion of the fuselage. The booster engine is operable to provide thrust during
According to one embodiment of the invention, a rocket booster for launching a payload into space includes a fuselage adapted to support one or more fuel tanks inside the fuselage and a booster engine coupled to an aft portion of the fuselage. The booster engine is operable to provide thrust during an ascent phase of operation of the rocket booster. The rocket booster further includes a nacelle coupled to a forward portion of the fuselage and a flyback engine disposed within and coupled to the nacelle. The flyback engine is operable to provide thrust during a flyback phase of operation of the rocket booster. The rocket booster also includes one or more control surfaces coupled to the fuselage that are operable to control a flight pattern of the rocket booster during the flyback phase of operation. The flyback engine of the rocket booster is located forward of an aerodynamic center of the rocket booster.
대표청구항▼
According to one embodiment of the invention, a rocket booster for launching a payload into space includes a fuselage adapted to support one or more fuel tanks inside the fuselage and a booster engine coupled to an aft portion of the fuselage. The booster engine is operable to provide thrust during
According to one embodiment of the invention, a rocket booster for launching a payload into space includes a fuselage adapted to support one or more fuel tanks inside the fuselage and a booster engine coupled to an aft portion of the fuselage. The booster engine is operable to provide thrust during an ascent phase of operation of the rocket booster. The rocket booster further includes a nacelle coupled to a forward portion of the fuselage and a flyback engine disposed within and coupled to the nacelle. The flyback engine is operable to provide thrust during a flyback phase of operation of the rocket booster. The rocket booster also includes one or more control surfaces coupled to the fuselage that are operable to control a flight pattern of the rocket booster during the flyback phase of operation. The flyback engine of the rocket booster is located forward of an aerodynamic center of the rocket booster. nnular flange on the sleeve. 6. The instrument of claim 2, wherein the stop means comprises a plug carried by the rod and extending radially therefrom, and the sleeve having a longitudinal closed slot for slidably receiving the plug. d the second set of curvilinear elements comprise a second thickness, the first thickness being smaller than the second thickness. 14. A stent, comprising a plurality of tubular segments defining a circumference and a longitudinal axis, each tubular segment including an alternating pattern of curvilinear elements extending about the circumference, the alternating pattern including a first set of curvilinear elements having a first resistance to expansion and a second set of curvilinear elements having a second resistance to expansion substantially higher than the first resistance to expansion, each tubular segment being expandable between a contracted condition, a first expanded condition, and a second expanded condition, the first expanded condition being achieved when a radial force exceeding the first resistance to expansion is applied to the tubular segment, the second expanded condition being achieved when a radial force exceeding the second resistance to expansion is applied to the tubular segment. 15. The stent of claim 14, wherein each tubular segment comprises a continuous alternating amplitude zigzag pattern comprising the first and second set of curvilinear elements. 16. The stent of claim 15, wherein first and second sets of curvilinear elements comprise "U" shaped elements. 17. The stent of claim 15, wherein the first set of curvilinear elements define a first amplitude and the second set of curvilinear elements define a second amplitude of the zigzag pattern, the first amplitude being longer than the second amplitude. 18. The stent of claim 15, wherein the first set of curvilinear elements comprises a first thickness and the second set of curvilinear elements comprise a second thickness, the first thickness being smaller than the second thickness. 19. The stent of claim 14, further comprising a connector extending between tubular segments that are adjacent to one another. 20. The stent of claim 14, wherein each tubular segment is plastically deformable between the contracted condition, the first expanded condition, and the second expanded condition. 21. A stent, comprising: a plurality of tubular segments defining a circumference and a longitudinal axis, each tubular segment comprising a zigzag pattern extending about the circumference, the zigzag pattern comprising first and second set of curvilinear elements, the first set of curvilinear elements defining a first amplitude of the zigzag pattern, and the second set of curvilinear elements defining a second amplitude of the zigzag pattern, the first amplitude being shorter than the second amplitude; and a connector extending between tubular segments that are adjacent to one another. 22. The stent of claim 21, wherein the first set of curvilinear elements has a first resistance to expansion and the second set of curvilinear elements has a second resistance to expansion substantially higher than the first resistance to expansion, each tubular segment being expandable between a contracted condition, a first expanded condition, and a second expanded condition, the first expanded condition being achieved when a radial force exceeding the first resistance to expansion is applied to the tubular segment, the second expanded condition being achieved when a radial force exceeding the second resistance to expansion is applied to the tubular segment. 23. The stent of claim 21, wherein first and second sets of curvilinear elements comprise "U" shaped elements. 24. The stent of claim 21, wherein each tubular segment is plastically deformable between the contracted condition, the first expanded condition, and the second expanded condition. 25. A stent, comprising a plurality of tubular segments defining a circumference and a longitudinal axis, each tubular segment comprising a zigzag pattern including alternating first and second sets of struts extending about the circumference, the first set of struts having a first length and the second set of struts having a second len
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이 특허에 인용된 특허 (3)
Robert B. Spencer ; Thomas D. Megna ; James R. Greenwood ; Daniel J. Laintz, Fly back booster.
Anatoly Ivanovich Kiselev RU; Alexandr Alexeevich Medvedev RU; Jury Nikolaevich Trufanov RU; Igor Sergeevich Radugin RU; Jury Leonidovich Kuznetsov RU; Alexandr Alexandrovich Pankevich RU; Genn, Reusable booster for the first stage of a launcher.
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