电动太阳风帆地球同步日心悬浮轨道编队控制研究

发布时间：2019-04-21 19:04

【摘要】：随着科技的发展,人类探索深空的热情日益增高。传统航天器比冲小,若进行深空探测,必将携带过多的燃料。而一类新型飞行器——电动太阳风帆航天器具有无限大比冲,对于深空探测有很大的潜力。电动太阳风帆通过反射太阳风中的等离子体来提供推力,适用于很多非开普勒轨道的探测任务,例如日心悬浮轨道。近年来欧空局和美国宇航局相继开展了电动太阳风帆的研究及相关试验。本文以电动太阳风帆航天器为研究对象,以其日心悬浮轨道及其相关任务为背景,对任务相关可行性、轨迹规划以及编队控制方法进行研究:首先,针对单根金属链的推力模型,推导出整个电动太阳风帆的推力和力矩方程,建立了相应轨道动力学方程。然后,推导了电动太阳风帆日心悬浮轨道保持的动力学方程,并针对三种不同电动太阳风帆日心悬浮轨道可行性进行了分析。应用高斯伪谱法针对电动太阳风帆从地球到地球同步日心悬浮轨道的转移轨迹进行了优化,并将非线性规划问题应用遗传算法以及序列二次规划的方法求解。最后,针对两个电动太阳风帆在地球同步日心悬浮轨道的编队问题,建立了子航天器在主航天器附近运动的相对运动学方程,针对该相对运动模型线性化且应用李雅普诺夫方法分析了稳定性,设计了线性二次型控制器并进行了仿真验证。对速度不可测量的情况设计了自抗扰控制器,又针对速度未知且模型不精确的情况进行了控制器设计,仿真验证了控制系统有效性。
[Abstract]:With the development of science and technology, the enthusiasm of human beings to explore deep space is increasing day by day. Traditional spacecraft will carry too much fuel if deep space exploration is carried out. However, a new type of aircraft, electric solar sail spacecraft, has infinite specific impulse, which has great potential for deep space exploration. The electric solar sail provides thrust by reflecting the plasma in the solar wind, and is suitable for many non-Kepler orbit detection missions, such as the heliocentric suspension orbit. In recent years, ESA and NASA have carried out electric solar sail research and related experiments. Taking the electric solar sail spacecraft as the research object and taking its heliocentric orbit and its related tasks as the background, this paper studies the mission-related feasibility, trajectory planning and formation control methods: first of all, According to the thrust model of a single metal chain, the thrust and torque equations of the whole electric solar sail are derived, and the corresponding orbital dynamics equations are established. Then, the dynamic equations for maintaining the heliocentric levitation orbit of electric solar sail are derived, and the feasibility of three kinds of heliocentric levitation orbit of electric solar sail is analyzed. Gao Si pseudospectral method is used to optimize the transfer trajectory from earth to geosynchronous heliocentric orbit of electric solar sail. The nonlinear programming problem is solved by genetic algorithm and sequential quadratic programming. Finally, aiming at the formation problem of two electric solar sails in geosynchronous heliocentric orbit, the relative kinematics equations of the sub-spacecraft moving near the main heliocentric are established. The relative motion model is linearized and the stability is analyzed by Lyapunov method. A linear quadratic controller is designed and verified by simulation. An active disturbance rejection controller (ADRC) is designed for the condition that the velocity is not measurable, and the controller is designed for the case of unknown speed and imprecise model. The effectiveness of the control system is verified by simulation.
【学位授予单位】：哈尔滨工业大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V448.2

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