DYNAMIC PROPERTY ANALYSIS FOR SPACECRAFT WITH BEAM-LIKE DEPLOYING APPENDAGES
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Abstract: This paper studies the attitude dynamics and vibration of appendages of spacecraft with deploying appendages. A spacecraft model of a center rigid body with some deployable beams are considered. The governing equations are derived based on characteristic function of bending beam, and the effects of deploying rate and disturbance on system behavior are investigated to find the criteria of the selection of deploying rate. The numerical simulation results are also presented.
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Key words:
- Spacecraft dynamics /
- Deploying /
- Flexible appendages
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