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An Attitude Control Design for the Cassini Spacecraft

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dc.contributor.author Wong, Edward en_US
dc.date.accessioned 2004-10-03T03:36:16Z
dc.date.available 2004-10-03T03:36:16Z
dc.date.issued 1995-05 en_US
dc.identifier.citation Baltimore, Maryland en_US
dc.identifier.clearanceno 95-0713 en_US
dc.identifier.uri http://hdl.handle.net/2014/30851
dc.description.abstract The Cassini planetary mission to Saturn and Titan requires accurate pointing and complex maneuvers of the spacecraft, which is comprised of a Saturn orbiter and Titan probe. An attitude control design is described to achieve the many capabilities of Cassini including thrust vector control, precision pointing and stability control for remote sciences, tracking of a probe released to the Titan atmosphere, and radar mapping of the Titan surface. Additional constraints for control design have been imposed by a high percentage of liquid propellant (60% at launch) land lowly damped flexible spacecraft appendages. Computer simulation results of attitude determination, pointing and maneuver controls are provided to demonstrate the design capability. en_US
dc.format.extent 543411 bytes
dc.format.mimetype application/pdf
dc.language.iso en_US
dc.subject.other Cassini Spacecraft en_US
dc.title An Attitude Control Design for the Cassini Spacecraft en_US


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