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Research on Orbital Control Method for Space Rendezvous and Docking

Author: TianChuang
Tutor: MaGuangCheng
School: Harbin Institute of Technology
Course: Control Science and Engineering
Keywords: space rendezvous and docking the beeline guidance rule the digital simulation the semi-physics simulation
CLC: V526
Type: Master's thesis
Year: 2008
Downloads: 262
Quote: 1
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The research on orbital control method for space rendezvous and docking has an important role in promoting our space technology, because the pros and cons of orbital control method directly relate to the success or failure of the whole rendezvous and docking process. The final approaching stage is an important stage in the space rendezvous and docking activities. In this thesis some research is done on the final approaching stage, a beeline guidance rule is designed and the simulation completed.Firstly, in this thesis the model of aerocraft dynamics and the model of actuator are given. The relative orbital dynamics model we chosen is Hill equation and the actuator is thruster. Based on the models above, a kind of beeline guidance rule is designed. Considering its stability, the guidance which combines initiative safety with passive safety is designed, and CAM under initiative safety is designed, so the guidance has advantages of both initiative safety and passive safety.Secondly, in this thesis a digital simulation flat is established and the stability of the flat is analyzed. The various parts of the design processes and principles for the digital simulation flat are explained, including the choice of the actuator, the implementation method of the thruster, the design of the controller, the translational dynamic equation and the implementation method of PWPF (Pulse Width pulse Frequency) regulator and so on.Finally, in the thesis the beeline guidance rule is verified by the semi-physics simulation flat. The frame and function of the semi-physics simulation are given; the impacts of the delay which is produced by position feedback are researched. The system with delay of less than 200ms is still safe under certain parameters. Effectiveness and stability are verified by the results of the digital simulation and the semi-physics simulation.

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CLC: > Aviation, aerospace > Aerospace ( Astronauts ) > Aerospace surgery > Docking technology
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