Dissertation
Dissertation > Aviation, aerospace > Aerospace ( Astronauts ) > Space instrument,spacecraft devices,spacecraft guidance and control > Guidance and Control > Spacecraft guidance and control

Design and optimization of flexible satellite path for large angle maneuver

Author ZhengLiJun
Tutor GuoZuo
School Nanjing University of Technology and Engineering
Course Control Theory and Control Engineering
Keywords flexible satellite large-angle attitude maneuver path planning vibration suppression of panels spectrum analysis MOP
CLC V448.2
Type Master's thesis
Year 2012
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Along with the further exploring of the outer space, more and more space missions of the flexible satellites were demanded to achieve large angle attitude maneuver to meet kinds of mission requirements such as redirection and docking. Meanwhile, the process of maneuver should have high performance of rapid maneuver and quick stable. However, the acceleration was easily limited by the saturation of actuators and the angular velocity was easily limited by the measurement capabilities of measuring devices. According to those restrictions of the system, this paper mainly did the following several work after analyzing the existing maneuvering path planning and the structure characteristics of the attitude control system.Firstly, on account of the thought of soft change, the three-segment maneuvering path planning based on parabolic angle acceleration curve was proposed, which aimed at the problem that the mutation of the angle acceleration often leaded to strong vibration of the flexible panels. Basing on the ideas of the above path, a kind of seven-segment maneuvering path planning based on a curve of sinusoidal rate of acceleration change was proposed to further improve the quickness of maneuver. The effectiveness and the superiority of the routes proposed in this paper were verified by comparing with the existing maneuvering path.Secondly, the path parameters were optimized by multi-objective optimization algorithm, and through this algorithm, a group of optimization paths were found, which could significantly improve the efficiency of maneuver and the stability of the attitude. Meanwhile, considering the uncertainty of satellite inertia and the coupling coefficient between flexible solar panel and rigid body, the robust analysis was used to them. The simulation results showed that the optimistic paths proposed and optimized by this paper had good robustness.Finally, the spectral analysis method was used to analysis the spectrum characteristics of astral angular velocity to reveal the internal relations between the maneuvering path and the vibration of flexible accessories. Through the study of the spectrum distribution of different paths, the basic characteristics of the path which wouldn’t arouse the vibration of the panels were gained. It could be implemented to guide the parameter selection of the optimistic path.

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