IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0653912
(2007-01-17)
|
등록번호 |
US-7602349
(2009-10-28)
|
발명자
/ 주소 |
- Hentosh, David J.
- Edridge, Michael J.
|
출원인 / 주소 |
- Lockheed Martin Corporation
|
대리인 / 주소 |
McDermott Will & Emery LLP
|
인용정보 |
피인용 횟수 :
7 인용 특허 :
5 |
초록
▼
A spacecraft is provided that includes a spacecraft body, a phased array coupled to a side of the spacecraft body by a first deployment couple, and a reflector coupled to the side of the spacecraft body by a second deployment couple. The first and second deployment couples are configured to permit s
A spacecraft is provided that includes a spacecraft body, a phased array coupled to a side of the spacecraft body by a first deployment couple, and a reflector coupled to the side of the spacecraft body by a second deployment couple. The first and second deployment couples are configured to permit stowing the reflector and the phased array parallel to the side of the spacecraft body. The reflector and the phased array share a common launch restraint mounting point on the side of the spacecraft body. A spacecraft is also provided that includes a spacecraft body, a mounting platform coupled to a side of the spacecraft body by a deployment couple, and a plurality of phased array assemblies. Each phased array assembly has a face with elements, and is coupled to the mounting platform by a gimbal. The deployment couple and the gimbals are configured to permit stowing the phased array assemblies parallel to the side of the spacecraft body and with the face of each phased array assembly oriented in a first direction. The phased array assemblies share a common launch restraint mounting point on the side of the spacecraft body.
대표청구항
▼
What is claimed is: 1. A spacecraft comprising: a spacecraft body; a first phased array coupled to a first side of the spacecraft body; a first reflector coupled to the first side of the spacecraft body; a first deployment couple disposed between the first phased array and the first side of the spa
What is claimed is: 1. A spacecraft comprising: a spacecraft body; a first phased array coupled to a first side of the spacecraft body; a first reflector coupled to the first side of the spacecraft body; a first deployment couple disposed between the first phased array and the first side of the spacecraft body and coupled to the first phased array and the first side of the spacecraft body, the first deployment couple configured to permit stowing the first phased array parallel to the first side of the spacecraft body; a second deployment couple disposed between the first reflector and the first side of the spacecraft body and coupled to the first reflector and the first side of the spacecraft body, the second deployment couple configured to permit stowing the first reflector parallel to the first side of the spacecraft body; and a first common launch restraint system configured to secure the first phased array and the first reflector to the first side of the spacecraft body using at least one common launch restraint mounting point. 2. The spacecraft of claim 1, wherein the first deployment couple and the second deployment couple are configured to permit stowing the first reflector on top of the first phased array. 3. The spacecraft of claim 1, wherein the first phased array and the first reflector each include one or more launch restraint locations for securing the first phased array and the first reflector to the common launch restraint mounting point. 4. The spacecraft of claim 1, wherein the first phased array has a face with a plurality of elements, and wherein the first deployment couple includes a gimbal configured to permit stowing the first phased array parallel to the first side of the spacecraft body and with the face of the first phased array oriented away from the first side of the spacecraft body. 5. The spacecraft of claim 4, wherein the gimbal is configured to permit rotating the first phased array around an axis of the first deployment couple through an angle of at least 180°. 6. The spacecraft of claim 1, wherein the first phased array comprises a plurality of phased array assemblies, wherein each of the plurality of phased array assemblies are coupled to a mounting platform by a gimbal, and wherein the mounting platform is coupled to the first deployment couple. 7. The spacecraft of claim 6, wherein each of the plurality of phased array assemblies has a face with a plurality of elements, and wherein the first deployment couple and the gimbals of the plurality of phased array assemblies are configured to permit stowing the plurality of phased array assemblies parallel to the first side of the spacecraft body and with the face of each of the plurality of phased array assemblies oriented in a first direction. 8. The spacecraft of claim 6, wherein at least one of the plurality of gimbals is configured to permit rotating an associated phased array assembly around an axis parallel to an axis of the first deployment couple through an angle of at least 180°. 9. The spacecraft of claim 6, wherein at least one of the plurality of gimbals is a 2-axis gimbal configured to permit deploying an associated phased array assembly in a same plane as another one of the plurality of phased array assemblies and with a different axis of orientation as the other one of the plurality of phased array assemblies. 10. The spacecraft of claim 1, wherein the second deployment couple includes a 2-axis gimbal configured to permit deploying the first reflector in a same plane as the first phased array and with a different axis of orientation as the first phased array. 11. The spacecraft of claim 1, further comprising: a second phased array coupled to a second side of the spacecraft body; a second reflector coupled to the second side of the spacecraft body; a third deployment couple disposed between the second phased array and the second side of the spacecraft body and coupled to the second phased array and the second side of the spacecraft body, the third deployment couple configured to permit stowing the second phased array parallel to the second side of the spacecraft body; a fourth deployment couple disposed between the second reflector and the second side of the spacecraft body and coupled to the second reflector and the second side of the spacecraft body, the fourth deployment couple configured to permit stowing the second reflector parallel to the second side of the spacecraft body; and a second common launch restraint system configured to secure the second phased array and the second reflector to the second side of the spacecraft body using a second at least one common launch restraint mounting point. 12. The spacecraft of claim 11, wherein the first side of the spacecraft body and the second side of the spacecraft body are opposite one another. 13. A spacecraft comprising: a spacecraft body; a first mounting platform coupled to a first side of the spacecraft body; a first deployment couple disposed between the first mounting platform and the first side of the spacecraft body and coupled to the first mounting platform and the first side of the spacecraft body; a first plurality of phased array assemblies, each of the first plurality of phased array assemblies having a face with a plurality of elements, each of the first plurality of phased array assemblies being coupled to the first mounting platform by a gimbal; and a first common launch restraint system configured to secure the first plurality of phased array assemblies to the first side of the spacecraft body using at least one common launch restraint mounting point, wherein the first deployment couple and the first plurality of gimbals are configured to permit stowing the first plurality of phased array assemblies parallel to the first side of the spacecraft body and with the face of each of the first plurality of phased array assemblies oriented in a first direction. 14. The spacecraft of claim 13, wherein at least one of the plurality of gimbals is configured to permit rotating an associated phased array assembly around an axis parallel to an axis of the first deployment couple through an angle of at least 180°. 15. The spacecraft of claim 13, wherein at least one of the plurality of gimbals is a 2-axis gimbal configured to permit deploying an associated phased array assembly in a same plane as another one of the plurality of phased array assemblies and with a different axis of orientation as the other one of the plurality of phased array assemblies. 16. The spacecraft of claim 15, further comprising a plurality of motor assemblies corresponding to the plurality of phased array assemblies, each motor assembly being configured to independently steer a corresponding phased array assembly. 17. The spacecraft of claim 13, further comprising: a second mounting platform coupled to a second side of the spacecraft body; a second deployment couple disposed between the second mounting platform and the second side of the spacecraft body and coupled to the second mounting platform and the second side of the spacecraft body; a second plurality of phased array assemblies, each of the second plurality of phased array assemblies having a face with a plurality of elements, each of the second plurality of phased array assemblies being coupled to the second mounting platform by a gimbal; and a second common launch restraint system configured to secure the second plurality of phased array assemblies to the second side of the spacecraft body using at least one common launch restraint mounting point, wherein the second deployment couple and the second plurality of gimbals are configured to permit stowing the second plurality of phased array assemblies parallel to the second side of the spacecraft body and with the face of each of the second plurality of phased array assemblies oriented in a second direction. 18. The spacecraft of claim 17, wherein the first side of the spacecraft body and the second side of the spacecraft body are opposite one another. 19. The spacecraft of claim 13, wherein each of the first plurality of phased array assemblies includes one or more launch restraint locations for mounting the first plurality of phased array assemblies to the common launch restraint mounting point with a launch restraint system. 20. The spacecraft of claim 13, further comprising a reflector coupled to the first side of the spacecraft body by a second deployment couple. 21. The spacecraft of claim 20, wherein the reflector shares the first common launch restraint mounting point with the first plurality of phased array assemblies.
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