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dc.contributor.authorAgrawal, B.N.
dc.dateFebruary 3-6, 1992
dc.date.accessioned2013-07-18T19:18:18Z
dc.date.available2013-07-18T19:18:18Z
dc.date.issued1992
dc.identifier.citationAIAA Aerospace Design Conference, Irvine, CA, February 3-6, 1992.
dc.identifier.urihttp://hdl.handle.net/10945/34476
dc.descriptionThe article of record as published may be found at http://dx.doi.org/10.2514/6.1992-980en_US
dc.description.abstractThis paper investigates alternate control techniques for the attitude control of a three axis stabilized flexible communications satellite consisting of a large reflector and a solar array. The control configurations consisted of three classes: Class 1 - sensors and actuators co-located on the central body, Class 2 - actuator on the central body and sensors distributed, and Class 3 -actuators and sensors distributed. Criteria are developed for modal truncation. The results indicate that Class 2 can cause instability and. is not generally a desirable design approach. An experimental setup to study the effects of flexibility on attitude control per-formance during slew maneuvers and wheel desaturation is also discussed. This paper investigates alternate control techniques for the attitude control of a three axis stabilized flexible communications satellite consisting of a large reflector and a solar array. The control configurations consisted of three classes: Class 1 - sensors and actuators co-located on the central body, Class 2 - actuator on the central body and sensors distributed, and Class 3 -actuators and sensors distributed. Criteria are developed for modal truncation. The results indicate that Class 2 can cause instability and. is not generally a desirable design approach. An experimental setup to study the effects of flexibility on attitude control per-formance during slew maneuvers and wheel desaturation is also discussed. This paper investigates alternate control techniques for the attitude control of a three axis stabilized flexible communications satellite consisting of a large reflector and a solar array. The control configurations consisted of three classes: Class 1 - sensors and actuators co-located on the central body, Class 2 - actuator on the central body and sensors distributed, and Class 3 -actuators and sensors distributed. Criteria are developed for modal truncation. The results indicate that Class 2 can cause instability and. is not generally a desirable design approach. An experimental setup to study the effects of flexibility on attitude control per-formance during slew maneuvers and wheel desaturation is also discussed. This paper investigates alternate control techniques for the attitude control of a three axis stabilized flexible communications satellite consisting of a large reflector and a solar array. The control configurations consisted of three classes: Class 1 - sensors and actuators co-located on the central body, Class 2 - actuator on the central body and sensors distributed, and Class 3 -actuators and sensors distributed. Criteria are developed for modal truncation. The results indicate that Class 2 can cause instability and. is not generally a desirable design approach. An experimental setup to study the effects of flexibility on attitude control per-formance during slew maneuvers and wheel desaturation is also discussed. This paper investigates alternate control techniques for the attitude control of a three axis stabilized flexible communications satellite consisting of a large reflector and a solar array. The control configurations consisted of three classes: Class 1 - sensors and actuators co-located on the central body, Class 2 - actuator on the central body and sensors distributed, and Class 3 -actuators and sensors distributed. Criteria are developed for modal truncation. The results indicate that Class 2 can cause instability and. is not generally a desirable design approach. An experimental setup to study the effects of flexibility on attitude control per-formance during slew maneuvers and wheel desaturation is also discussed. This paper investigates alternate control techniques for the attitude control of a three axis stabilized flexible communications satellite consisting of a large reflector and a solar array. The control configurations consisted of three classes: Class 1 - sensors and actuators co-located on the central body, Class 2 - actuator on the central body and sensors distributed, and Class 3 -actuators and sensors distributed. Criteria are developed for modal truncation. The results indicate that Class 2 can cause instability and. is not generally a desirable design approach. An experimental setup to study the effects of flexibility on attitude control per-formance during slew maneuvers and wheel desaturation is also discussed.en_US
dc.rightsThis publication is a work of the U.S. Government as defined
in Title 17, United States Code, Section 101. As such, it is in the
public domain, and under the provisions of Title 17, United States
Code, Section 105, is not copyrighted in the U.S.en_US
dc.titleDesign of Multi-Mission Spacecraft BUSen_US
dc.contributor.departmentDepartment of Mechanical and Aerospace Engineering


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