[특허]Spacecraft disturbance trimming system

Lockheed Martin Corporation

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Spacecraft disturbance trimming system

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64G-001/24
미국특허분류(USC)	244/168; 244/172.7
출원번호	US-0910582 (2004-08-04)
발명자 / 주소	Goodzeit,Neil E. Ratan,Santosh
출원인 / 주소	Lockheed Martin Corporation
대리인 / 주소	McDermott Will &
인용정보	피인용 횟수 : 9 인용 특허 : 17

초록
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A spacecraft comprises a main body; at least one elongated solar wing extending from the main body, defining a generally flat plane and comprising a pair of longitudinally extending side edges; at least one other component or structure extending from the main body and spaced at a separation distance from the at least one solar wing; and at least one solar trim tab coupled to the at least one solar wing, linearly elongated and extending in the generally flat plane in a direction transversely away from one of the longitudinally extending side edges, and si...

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청구항
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What is claimed is: 1. A spacecraft comprising: (a) a main body; (b) at least one elongated solar wing extending from said main body, defining a generally flat plane and comprising a pair of longitudinally extending side edges; (c) at least one other component or structure extending from said main body and spaced at a separation distance from said at least one solar wing; and (d) at least two solar trim tabs coupled to said at least one solar wing, said at least two solar trim tabs being linearly elongated and extending in said generally flat plane in a same direction that is transversely away from, and perpendicular to, one of said longitudinally extending side edges, said at least two solar trim tabs tab being sized and positioned along said one longitudinally extending side edge for counteracting or compensating for one or more types of disturbance pitch torques. 2. The spacecraft as in claim 1, wherein: said at least one solar wing includes a plurality of photovoltaic solar cells arranged in said generally flat plane. 3. The spacecraft as in claim 1, wherein: said at least one solar wing comprises a pair of oppositely extending, linearly elongated solar wings, each said oppositely extending solar wing including at least one of said linearly elongated solar trim tabs positioned at a substantially similar distance along an extending linear axis of each said oppositely extending solar wing. 4. The spacecraft as in claim 1, wherein: said at least one solar wing comprises a plurality of rollable, collapsible, or foldable array of solar cell panels and includes a mechanism for deploying said elongated solar wing subsequent to launch of said spacecraft. 5. The spacecraft as in claim 4, wherein: said at least one solar wing comprises a release mechanism for deploying said at least two solar trim tabs subsequent to launch of said spacecraft. 6. The spacecraft as in claim 5, wherein: said release mechanism further includes a mechanism for controllably transversely extending each said solar trim tab for a predetermined distance from said one longitudinally extending side edge. 7. The spacecraft as in claim 1, wherein: said at least one other component or structure comprises a reflector or antenna. 8. The spacecraft as in claim 7, wherein: said at least one other component or structure comprises a pair of reflectors or antennas spaced apart at a separation distance. 9. The spacecraft as in claim 1, wherein: each of said at least two solar trim tabs comprises a polyimide material. 10. The spacecraft as in claim 1, wherein: said spacecraft is a GEO spacecraft included in a MUOS system. 11. The spacecraft as in claim 3, wherein: each said oppositely extending solar wing includes a plurality of said linearly elongated solar trim tabs disposed at substantially similar positions along the extending linear axis of each said oppositely extending solar wing, said plurality of solar trim tabs disposed on each said oppositely extending solar wing collectively acting to counteract one or more types of disturbance pitch torques. 12. A solar array adapted for use with a spacecraft, comprising: (a) an elongated solar wing defining a generally flat plane and comprising a pair of longitudinally extending side edges; and (b) at least two solar trim tabs coupled to said solar wing, said at least two solar trim tabs being linearly elongated and extending in said generally flat plane in a same direction that is transversely away from, and perpendicular to, one of said longitudinally extending side edges, said at least two solar trim tabs sized and positioned along said one longitudinally extending side edge for counteracting or compensating for one or more types of distance pitch torques. 13. The solar array as in claim 12, wherein: said solar wing includes a plurality of photovoltaic solar cells arranged in said generally flat plane. 14. The solar array as in claim 13, wherein: said solar wing comprises a plurality of rollable, collapsible, or foldable array of solar cell panels and includes a mechanism for deploying said elongated solar wing subsequent to launch of said spacecraft. 15. The solar array as in claim 14, wherein: said solar wing comprises a release mechanism for deploying said at least two solar trim tabs subsequent to launch of said spacecraft. 16. The solar array as in claim 15, wherein: said release mechanism further includes a mechanism for controllably transversely extending each said solar trim tab for a predetermined distance from said one longitudinally extending side edge. 17. A method for operating a spacecraft in orbit around a body, comprising steps of: (a) providing a spacecraft in orbit around said body, said spacecraft including: (i) a main body; (ii) at least one elongated solar wing extending from said main body, comprising a plurality of photovoltaic solar cells defining a generally flat plane and including a pair of longitudinally extending side edges; (iii) at least one other component or structure extending from said main body and spaced at a separation distance from said at least one solar wing; and (iv) at least two solar trim tabs coupled to said at least one solar wing, said at least two solar trim tabs being linearly elongated and extending in said generally flat plane in a same direction that is transversely away from, perpendicular to one of said longitudinally extending side edges; and (b) utilizing said at least two solar trim tabs for counteracting or compensating for one or more types of disturbance pitch torques. 18. The method according to claim 17, wherein: step (a) comprises providing a spacecraft including a pair of oppositely extending, linearly elongated solar wings, each said oppositely extending solar wing including at least one of said linearly elongated solar trim tabs positioned at a substantially similar distance along an extending linear axis of each said oppositely extending solar wing. 19. The method according to claim 17, wherein: step (a) comprises providing a spacecraft including a mechanism for controllably transversely extending each said solar trim tab for a predetermined distance from said one longitudinally extending side edge. 20. The method according to claim 17, wherein: step (a) comprises providing a spacecraft wherein said at least one other component or structure comprises a reflector or antenna. 21. The method according to claim 20, wherein: step (a) comprises providing a GEO spacecraft including a MUOS system; and step (b) comprises utilizing said at least two solar trim tabs for counteracting or compensating for at least one of: (1) a gravity-gradient disturbance torque resulting from the separation distance between the at least one solar wing and the at least one other component or structure when the spacecraft is in orbit about a body; (2) a yaw/roil disturbance torque; (3) an RF transmission pitch torque; and (4) other environmental disturbance torques. 22. A spacecraft comprising: (a) a main body; (b) at least one elongated solar wing extending from said main body, defining a generally flat plane and comprising a pair of longitudinally extending side edges; (c) at least one other component or structure extending from said main body and spaced at a separation distance from said at least one solar wing; and (d) at least one solar trim tab coupled to said at least one solar wing, said at least one solar trim tab being linearly elongated and extending in said generally flat plane in a direction transversely away from one of said longitudinally extending side edges, said at least one solar trim tab sized and positioned along said one longitudinally extending side edge for counteracting or compensating for one or more types of disturbance pitch torques.

이 특허에 인용된 특허 (17)

이 특허를 인용한 특허 피인용횟수: 9

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특허 상세정보

Spacecraft disturbance trimming system

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이 특허에 인용된 특허 (17)

이 특허를 인용한 특허 피인용횟수: 9

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Spacecraft disturbance trimming system

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이 특허에 인용된 특허 (17)

이 특허를 인용한 특허 피인용횟수: 9

IPC 상위 출원인

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IPC 상세정보(version : 201201)

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