[특허]Isolating positioning boom for instrument platform

Northrop Grumman Corporation

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Isolating positioning boom for instrument platform

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64G-001/00
미국특허분류(USC)	244/172.6
출원번호	US-0964849 (2004-10-13)
등록번호	US-7270304 (2007-09-18)
발명자 / 주소	Dailey,Dean R. Lillie,Charles F. Flannery,Martin Arenberg,Jonathan W. Bronowicki,Allen J.
출원인 / 주소	Northrop Grumman Corporation
대리인 / 주소	Carmen B. Patti & Assoc., LLC
인용정보	피인용 횟수 : 3 인용 특허 : 9

초록
▼

A positioning boom disposed between a space-based observatory platform and its instrument payload provides thermal and dynamic isolation as well as fine pointing and momentum control. The inventive system isolates a sensitive payload from a warm, dynamically noisy spacecraft, which includes a sunshield. Isolation is required in terms of dynamics and heat flow, both in terms of the absolute level and its variance (thermal isolation). The present invention provides intrinsic control over momentum buildup (which is due to the separation of the center of pre...

대표
청구항
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What is claimed is: 1. An improved space-based observatory platform having an instrument payload and a sunshield, wherein the improvement comprises: a gimbaled positioning boom having a length-to-width aspect ratio in a range between 30 and 60 to 1 coupling the instrument payload to the observatory platform, the boom having a natural frequency below a frequency of dynamic noise such that the boom minimizes transmission of the dynamic noise between the instrument payload and the observatory platform; the positioning boom further including a plurality of piezoelectric patches disposed thereupon to provide active damping, where stresses along the boom caused by flexing are transmitted to a proximate first piezoelectric sensor that is an element of one of the plurality of piezoelectric patches, and a corresponding in actuator that is an element of the same piezoelectric patch of which the first piezoelectric sensor is an element provides a force acting on the boom in a direction substantially opposite to a direction of flexing sensed by the first piezoelectric sensor; wherein the positioning boom is articulated to position the instrument payload center of gravity with respect to the sunshield center of solar pressure in at least five degrees of freedom to maintain a predetermined relationship between payload center of gravity and solar pressure force center, thus minimizing momentum buildup. 2. The improved space-based observatory platform of claim 1, wherein the positioning boom includes an articulation actuator at the point of articulation. 3. The improved space-based observatory platform of claim 2, wherein the articulation actuator is a piezoelectric actuator. 4. The improved space-based observatory platform of claim 1, wherein the positioning boom further includes biaxial gimbal drives positioned proximate the instrument payload to provide rotation capability about both an elevation axis and an instrument boresight axis. 5. The improved space-based observatory platform of claim 4, wherein the gimbal drives include piezoelectric stack actuators. 6. The improved space-based observatory platform of claim 1, wherein the positioning boom positions the instrument payload at a distance from the sunshield sufficient for thermal decoupling. 7. The improved space-based observatory platform of claim 1, wherein an attitude control system associated with the platform provides rotational motion control about the solar axis that extends from the sun, through the sunshield, to the instrument payload. 8. The improved space-based observatory platform of claim 7, wherein the attitude control system includes reaction wheels. 9. The improved space-based observatory platform of claim 1, wherein the positioning boom is coupled to the observatory platform at two points of the observatory platform structure using highly damped bipod flexures to provide z-axis stability. 10. The improved space-based observatory platform of claim 1, wherein the positioning boom is layered with visco-elastic material to provide passive damping. 11. A space-based observatory platform comprising: an instrument payload; a sunshield; a gimbaled positioning boom having a length-to-width aspect ratio in a range between 30 and 60 to 1 coupling the instrument payload to the observatory platform, the positioning boom articulated to position the instrument payload center of gravity with respect to the sunshield center of solar pressure in at least five degrees of freedom to maintain a predetermined relationship between payload center of gravity and solar pressure force center, thus minimizing momentum buildup, and further including biaxial gimbal drives positioned proximate the instrument payload to provide rotation capability about both an elevation axis and an instrument boresight axis; the boom having a natural frequency below a frequency of dynamic noise such that the boom minimizes transmission of dynamic noise between the instrument payload and the observatory platform; the positioning boom further including a plurality of piezoelectric patches disposed thereupon to provide active damping, where stresses along the boom caused by flexing are transmitted to a proximate first piezoelectric sensor that is an element of one of the plurality of piezoelectric patches, and a corresponding damping actuator that is an element of the same piezoelectric patch of which the first piezoelectric sensor is an element provides a force acting on the boom in a direction substantially opposite to a direction of flexing sensed by the first piezoelectric sensor. 12. The space-based observatory platform of claim 11, wherein the positioning boom includes an articulation actuator at the point of articulation. 13. The space-based observatory platform of claim 12, wherein the articulation actuator is a piezoelectric actuator. 14. The space-based observatory platform of claim 11, wherein the gimbal drives include piezoelectric stack actuators. 15. The space-based observatory platform of claim 11, wherein the positioning boom positions the instrument payload at a distance from the sunshield sufficient for thermal decoupling. 16. The space-based observatory platform of claim 11, wherein an attitude control system associated with the platform provides rotational motion control about the solar axis that extends from the sun, through the sunshield, to the instrument payload. 17. The space-based observatory platform of claim 16, wherein the attitude control system includes reaction wheels. 18. The space-based observatory platform of claim 11, wherein the positioning boom is coupled to the observatory platform at two points of the observatory platform structure using highly damped bipod flexures to provide z-axis stability. 19. The space-based observatory platform of claim 11, wherein the positioning boom is layered with visco-elastic material to provide passive damping. 20. A space-based observatory platform comprising: an instrument payload; a sunshield; a gimbaled positioning boom having a length-to-width aspect ratio in a range between 30 and 60 to 1 coupling the instrument payload to the observatory platform, the positioning boom articulated to position the instrument payload center of gravity with respect to the sunshield center of solar pressure in at least five degrees of freedom to maintain a predetermined relationship between payload center of gravity and solar pressure force center, thus minimizing momentum buildup, and further including biaxial gimbal drives positioned proximate the instrument payload to provide rotation capability about both an elevation axis and an instrument boresight axis; and an attitude control system associated with the platform providing rotational motion control about the solar axis that extends from the sun, through the sunshield, to the instrument payload; the boom having a natural frequency below a frequency of dynamic noise such that the boom minimizes transmission of dynamic noise between the instrument payload and the observatory platform; the positioning boom further including a plurality of piezoelectric patches disposed thereupon to provide active damping, where stresses along the boom caused by flexing are transmitted to a proximate first piezoelectric sensor that is an element of one of the plurality of piezoelectric patches, and a corresponding damping actuator that is an element of the same piezoelectric patch of which the first piezoelectric sensor is an element provides a force acting on the boom in a direction substantially opposite to a direction of flexing sensed by the first piezoelectric sensor.

이 특허에 인용된 특허 (9)

이 특허를 인용한 특허 피인용횟수: 3

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특허 상세정보

Isolating positioning boom for instrument platform

초록
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청구항
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이 특허에 인용된 특허 (9)

이 특허를 인용한 특허 피인용횟수: 3

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Isolating positioning boom for instrument platform

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대표청구항 ▼

이 특허에 인용된 특허 (9)

이 특허를 인용한 특허 피인용횟수: 3

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

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