Nonlinear momentum transfer control of spacecraft by feedback linearization

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The momentum transfer problem between a single momentum wheel and a rigid spacecraft is investigated. A feedback linearizing control is used for the momentum wheel. The proposed control law is a function of the spacecraft angular velocity vector components, as well as the inertia properties. The total initial angular momentum of the spacecraft is absorbed into the wheel, so that the spacecraft comes to rest at the steady state. The angular momentum component of the spacecraft and that of the wheel spin axis are selected as the primary control variables. A reference angular momentum history is predefined that leads to a smoothed control torque profile. The proposed control method produces a very small notation angle at the completion of the momentum transfer maneuver. In addition, a two-stage control law switching strategy is proposed to complete the momentum transfer maneuver.
Publisher
AMER INST AERONAUT ASTRONAUT
Issue Date
2002-11
Language
English
Article Type
Article; Proceedings Paper
Keywords

STABILITY

Citation

JOURNAL OF SPACECRAFT AND ROCKETS, v.39, no.6, pp.866 - 873

ISSN
0022-4650
URI
http://hdl.handle.net/10203/78392
Appears in Collection
AE-Journal Papers(저널논문)
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