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On the dynamics of spacecraft with a slewing appendage

University of British Columbia

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 can become unstable under critical combinations of inertia, geometric, orbital and slewing time history parameters. The fundamental information is relevant to the design of satellites and the Orbiter based experiments, and construction of the proposed space station, which would involve complex slewing motion of structural components.

Text

2010-07-10

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http://hdl.handle.net/2429/26312

Mechanical Engineering

University of British Columbia

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