太阳帆航天器轨道和姿态耦合设计与优化

发布时间：2019-05-27 04:52

【摘要】：太阳帆以其无燃料推进、比冲无限大、任务丰富等优势,最有可能成为未来深空探测实际而有效的推进方式之一。太阳帆轨道和姿态耦合设计与优化对太阳帆系统设计有着至关重要的意义和实际工程价值。本文在考虑太阳帆轨道和姿态耦合情况下,系统地研究了悬浮轨道设计与控制、转移轨道设计与优化、柔性太阳帆动力学与控制问题,开发了工具软件。主要研究内容如下:首先,研究了太阳帆日心悬浮轨道和姿态耦合设计与控制问题。基于日心悬浮轨道稳定性条件,设计了仅要求姿态角保持不变的被动控制律,仿真表明该控制律可使太阳帆稳定在悬浮轨道附近。研究了基于LQR的主动控制律,取得了较高的悬浮轨道控制精度。通过研究悬浮轨道和开普勒轨道空间位置关系,提出了悬浮轨道参数和开普勒轨道六根数之间的关系式以及悬浮轨道之间拼接的条件。其次,研究了太阳帆转移轨道和姿态耦合设计和优化问题。基于能量变化率最大的控制律设计逃逸地球影响球轨道,比较了理想和非理性帆面、考虑地影和不考虑地影时对飞行时间的影响。提出了太阳帆行星际转移轨道全局优化算法,地球到火星转移算例验证了该算法的有效性。针对太阳帆飞向日心悬浮轨道的转移轨道问题,提出了通过将姿态角离散成分段函数,并利用遗传算法和SQP联合运算获得全局高精度解的方法,该方法在满足悬浮轨道约束下能够快速获取转移轨道。提出了附加行星借力和太阳光压辅助的太阳帆逃逸太阳系转移方法,并与直接逃逸和仅太阳光压辅助逃逸这两种方法进行了比较,仿真表明联合借力所需飞行时间最少。针对太阳帆转移轨道任务设计周期长和分析能力有限的问题,提出了基于STK的太阳帆转移轨道任务仿真方法,该方法能够快速而灵活地支持复杂太阳帆任务,并增强了任务场景的可视化,易于工程应用。再次,研究了柔性太阳帆动力学与控制问题。设计了太阳帆姿态控制系统的敏感器配置、执行机构和控制器方案。通过有限元仿真分析表明太阳帆可视为中心刚体附加挠性附件模型来计算耦合系数。针对刚体太阳帆模型对挠性帆面振动的缺失,建立的中心刚体附加挠性附件形式的柔性太阳帆姿态动力学模型既能足够准确地描述太阳帆姿态运动,又便于进行姿态控制,仿真结果具有一定的工程参考价值。针对太阳帆高精度长期飞行的需求,建立的全柔性太阳帆动力学模型体现了轨道、姿态和振动耦合的全部特性,分析表明忽略太阳帆柔性振动的影响,将导致星际转移轨道和姿态偏离理论轨道和姿态数据,并最终影响飞行任务。最后,开发了太阳帆轨道和姿态耦合仿真的工具软件。介绍了“太阳帆航天器轨道设计与控制软件”、“太阳帆航天器姿态控制仿真系统”和“采用引力辅助和太阳光压辅助的太阳帆飞往外太阳系任务仿真软件”的软件功能和软件结构,结合文中部分算例给出了相应的操作说明。完成了软件升级版本“太阳帆航天器轨道和姿态耦合仿真软件”的架构设计、用户界面和相关操作。
[Abstract]:The solar sail has the advantages of no fuel propulsion, infinite impulse and rich task, and is most likely to be one of the practical and effective ways to detect the future deep space. The design and optimization of the solar sail rail and attitude coupling are of great importance to the design of the solar sail system and the practical engineering value. In this paper, the design and control of the suspension rail, the design and optimization of the transfer track, the dynamics and control of the flexible solar sail are systematically studied in the light of the orbital and attitude coupling of the solar sail, and the tool software is developed. The main contents of the study are as follows: First, the design and control of the sun-sail sun-core suspension orbit and the attitude coupling are studied. Based on the stability of the sun-core suspension orbit, a passive control law is designed to keep the attitude angle unchanged, and the simulation shows that the control law can stabilize the solar sail near the levitation track. The active control law based on LQR is studied, and the control precision of the suspension track is obtained. By studying the relation between the suspension orbit and the Kepler orbit space, the relation between the suspension orbit parameter and the six-root number of Kepler orbit and the condition of the joint between the suspended track and the floating track are put forward. Secondly, the design and optimization of the transfer orbit and attitude of the solar sail are studied. The control law based on the maximum energy change rate is designed to escape the earth to influence the ball track, and the ideal and non-rational sailplane is compared, and the effect on the time of flight is considered when the shadow is taken into account and the shadow is not taken into account. In this paper, a global optimization algorithm for the interplanetary transfer orbit of the solar sail is proposed, and the validity of the algorithm is verified by an example of the earth-to-Mars transition. In order to solve the problem of the transfer orbit of the sun-sail to the sun-core suspension orbit, a method for obtaining a global high-precision solution by combining the position-angle discrete component function and the combination of genetic algorithm and SQP is proposed. The method can quickly acquire the transfer orbit under the constraint of the suspension orbit. The method of the solar-sail escape solar system with additional planetary force and sunlight pressure is proposed, and the two methods are compared with the direct-escape and the solar-pressure-assisted escape, and the simulation results show that the flying time required by the combined borrowing force is the least. Aiming at the problems of long design period and limited analytical capacity of the solar sail transfer orbit task, a method for simulating the task of a sun-sail transfer orbit based on STK is proposed, which can support the task of the complex solar sail quickly and flexibly, and enhance the visualization of the task scene and is easy for engineering application. Thirdly, the dynamics and control of the flexible solar sail are studied. The sensor configuration, actuator and controller scheme of the attitude control system of the solar sail are designed. The finite element simulation analysis shows that the solar sail can be regarded as an additional flexible attachment model of the central rigid body to calculate the coupling coefficient. aiming at the deficiency of the rigid body solar sail model to the vibration of the flexible sail surface, the flexible solar sail attitude dynamic model in the form of an additional flexible attachment of the central rigid body can not only accurately describe the attitude movement of the solar sail, but also facilitate the attitude control, The simulation results are of certain reference value. Aiming at the requirement of high-precision long-term flying of the solar sail, the full-flexible solar-sail dynamic model is established, and all the characteristics of the orbit, the attitude and the vibration coupling are reflected, the analysis shows that the influence of the flexible vibration of the solar sail is ignored, and the interplanetary transfer orbit and the attitude deviation are caused to deviate from the theoretical track and the attitude data, And ultimately affect the mission. Finally, the tool software for the simulation of the solar sail orbit and the attitude coupling is developed. The software functions and software structure of the "The orbit design and control software of the solar-sail spacecraft", the "Attitude control simulation system for solar-sail spacecraft" and the "Simulation software of solar sail to external solar system by using gravity-assisted and solar-pressure-assisted sun-sail" are introduced, and the corresponding operation instructions are given in the paper. The architecture design, user interface, and related operations of the software upgrade version "Simulation software for orbital and attitude coupling of solar-sail spacecraft" are completed.
【学位授予单位】：中国科学院研究生院(空间科学与应用研究中心)
【学位级别】：博士
【学位授予年份】：2015
【分类号】：V448.2

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