On the dynamics of spacecraft with a slewing appendage
A relatively general formulation for studying librational dynamics of a rigid satellite with a rigid appendage free to undergo any arbitrary slewing motion is developed. The governing nonlinear, nonautonomous and coupled equations are solved numerically. A parametric study suggests that the system c...
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| Language: | English |
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University of British Columbia
2010
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| Online Access: | http://hdl.handle.net/2429/26312 |