A technique is presented for achieving active control of nutation on a dual-spin spacecraft with an articulated payload through use of the payload's control system. Using the Orbiting Solar Observatory (OSO)-8 as an illustration, the closed-form solution to the nutation/control system dynamic interaction is presented. Control system design criteria are developed which establish the basic stability of the interaction. Design procedures are described to achieve the most effective nutation damping. Limitations on the amount of damping which can be achieved are characterized as functions of spacecraft and payload mass properties and servo-design parameters. The design techniques presented are verified through a series of on-orbit tests recently conducted on the OSO-8 spacecraft.
Dual-spin spacecraft nutation control using articulated payloads
1980-01-01
Miscellaneous
No indication
English
Dual-spin-spacecraft nutation control using articulated payloads
Tema Archive | 1980
|Nutation-damper design for dual-spin spacecraft
NTRS | 1971
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IEEE | 1970
|A nutation damper for a dual-spin spacecraft
NTRS | 1970
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