Orbital Maneuver Optimization And Attitude Control Of Spacecraft

Along with the continuous development of aerospace science and technology, the requirements of effectively prolong the life and repeat utilization of the spacecraft,reduce and save the loss caused by failure of the spacecraft has become more and more high, the concept of on-orbit service come into being and get great development. At the same time, low-thrust propulsion technology with higher specific impulse, longer life and lighter quality, gradually come into people’s horizons, which can bring a larger payloads into the orbit. Now it has been widely used in deep space exploration, the control of near-earth spacecraft and even as the main thrust system in the interstellar travel. Under the background of on-orbit service, this thesis has done an in-depth study on trajectory optimization problem with low-thrust aerospace propulsion system and attitude tracking control problem with external interference.Firstly, a simple introduction is given to some of the basic theory involved,including coordinate systems, the orbital kinematics equation, the attitude kinematics equation, Gaussian pseudo-spectral method and nonlinear programming problem, et al,the basic idea and method of the adaptive control, the terminal sliding mode control as well.Secondly, this thesis has studied the trajectory optimization problem with low-thrust propulsion system. To begin with the deduce of the principle and process of Gaussian pseudo-spectral discretization for the optimal control problem, and the prove of the validity. Then Gaussian pseudo-spectral method is used to solve the trajectory optimization problem, which has been proved by simulation.Finally, this thesis has done some research on the finite time control of attitude tracking control problem. First of all, when the upper bound of the perturbation and the rotary inertia are known, this article designs a controller using fast terminal sliding mode theory in order to make the state variables of the system converge to a desired state in a limited time. After that, when the upper bound of the perturbation and the rotary inertia are unknown, this article designs a controller combine adaptive control and terminal sliding mode so as to lead the system error to a finite time convergence. In the end, it evaluates the advantages and disadvantages of the controller designed by means of the analysis of the results.