Feedback control law design for the dual-spin turn of spacecraft

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A new feedback control law design for the dual-spin turn maneuver of spinning spacecraft is discussed, The control law design study is motivated by stability analysis of dual-spin spacecraft, The feedback control law is based on the relationship between nutational stability and system energy associated with the rotational motion of spacecraft and a momentum wheel. The applied torque to the momentum wheel is adjusted in a feedback control form, for which the control law is expressed as a function of spacecraft angular velocity components, as well aci the momentum wheel speed, Furthermore, a two-stage control strategy, which consists of conventional open-loop maneuver and a new feedback technique, is developed. The new strategy is verified by simulation study using Koreasat mass property data.
Publisher
AMER INST AERONAUT ASTRONAUT
Issue Date
1997
Language
English
Article Type
Article
Citation

JOURNAL OF GUIDANCE CONTROL AND DYNAMICS, v.20, no.3, pp.450 - 456

ISSN
0731-5090
DOI
10.2514/2.4096
URI
http://hdl.handle.net/10203/76179
Appears in Collection
AE-Journal Papers(저널논문)
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