Design And Optimization Of Orbit Transfer And Flying Trajectory Of Spacecraft

As the vigorous development of China's aerospace industry, the diversity of space mission has become prominent. In the previous, the spacecraft which have been completed the maneuver from the orbit around the earth to the orbit around the moon has been launched. The next step,the trial about rendezvous and docking technology will be taken in the"Temple One"which will be launched. This is a complex system which involved many subject, such as the analysis of system structure and system modeling, relative motion of two or satellites, autonomous relative navigation guidance and algorithm, autonomous approach algorithm, final trajectory planning and optimization from autonomous orbit approach to rendezvous and docking. In view of above problems, further study has been done as follows:Aimed at the problem of orbit maneuvering of tracking spacecraft with that of target spacecraft. This article modeling the relative dynamics model first, assuming the orbit around the earth is circular orbit, the relative distance between two spacecraft smaller than the geocentric distance of target spacecraft, and does not consider the impact of perturbation. The dynamics model which meet to the accuracy requirement of orbit transfer is getted, the accumulated error in the orbit transfer is compensated by additional compensation mechanism. Based on the C-W equation, research the large distance maneuvering, multi-pulse maneuvering, glideslope maneuvering algorithm, and potential energy function maneuvering algorithm. In view of the actual demand of different maneuvering segments of tracking spacecraft. The maneuvering switching strategy of orbit transfer algorithm is described, it is that the long-distance maneuvering approach is used in the middle, when arrive at the switching point, it will automatically switch to the potential function maneuvering algorithm, in the end, simulation results are given.Aimed at the actual situation of fuel limited which the spacecraft carried, the optimization method is adopted to design the optimization orbit transfer method. Take the terminal state, transfer time and energy consumption standard as constraint condition, a method of design the optimal energy transfer orbit is given, a transfer orbit based on continuous velocity pulse maneuver is getted and diminish the energy consumption in the orbit transfer. It is limited to use continuous pulse maneuver in the actual space mission, a nonlinear programming is used, the optimal interval of adjacent velocity pulse points are getted, In the end, simulation results and analysis are given and compare with the multi-pluse.Aimed at the problem of capture the natural flying trajectory, according to the initial velocity constraint of natural flying trajectory, a velocity compensation method and optimal selection mechanism of the position of entry point are given. For the formation and reconfiguration of two spacecraft, some formation configuration design methods such as rhombus formation, pattern formation and square formation are given. Aimed at the formation keeping and orbit control of the flying trajectory of two spacecraft, a closed-loop control law based on optimal quadratic regulation, the analysis method about design control method when the constant disturb exist.