空间碎片环境对高姿态精度航天器指向性能的影响研究

发布时间：2018-03-22 13:30

本文选题：空间碎片环境　切入点：高姿态精度航天器　出处：《哈尔滨工业大学》2017年硕士论文　论文类型：学位论文

【摘要】：近地轨道空间碎片环境不断恶化,而用于激光通讯、对地观测、天文探测等的高姿态精度航天器对指向性能的要求却不断提高。数量众多的微小空间碎片会不时地撞击航天器,碎片撞击对各种微小扰动很敏感的高姿态精度航天器后其指向性能会受到影响。目前国内外针对空间碎片对航天器姿态影响的研究很少,只有少数文献涉及微流星体对航天器姿态的影响。本文运用航天器姿态运动的相关理论知识建立了空间碎片撞击航天器的动力学模型,提出了根据SDEEM空间碎片环境工程模型输出的航天器空间碎片环境、航天器的几何模型及逆转法生成随机数的思想随机生成撞击传递角动量的方法,解决了空间碎片多次撞击时时间间隔的随机生成及不同坐标系之间的转换问题,从而利用蒙特卡洛数值仿真方法获得空间碎片单次随机撞击、多次随机撞击对高姿态精度航天器指向性能影响的统计特性。首先介绍了研究中用到的SDEEM软件航天器评估模式及其输出量相对通量,相对通量是定义在航天器轨道坐标系下的。在此基础上,根据航天器姿态动力学相关理论知识建立了空间碎片撞击航天器的姿态动力学模型,并设计了航天器指向性能的评价指标。然后利用SDEEM软件得到哈勃的空间碎片环境并选取典型空间碎片,编程仿真研究了典型空间碎片单次撞击对给定姿态的哈勃观测轴指向变化及变化率的影响。接着提出了根据空间碎片环境数据文件及利用逆转法生成随机数的思想随机生成碎片尺寸和撞击方位角的方法;提出了根据撞击动量方向随机产生碎片对航天器撞击位置的方法;以哈勃为例利用蒙特卡洛数值仿真方法获得了微小空间碎片单次随机撞击对哈勃指向性能影响的统计特性。最后提出了空间碎片连续撞击航天器过程是复合泊松过程,由此得到碎片连续撞击时间间隔服从指数分布;研究了多次随机撞击过程中不同坐标系进行转换的求法;以哈勃为例利用蒙特卡洛数值仿真方法获得了微小空间碎片多次随机撞击对航天器指向性能累积影响的统计特性。
[Abstract]:The environment of low-Earth orbit space debris is deteriorating, but the requirements for pointing performance of high-attitude spacecraft for laser communication, earth observation, astronomical exploration, and so on are increasing. A large number of tiny space debris will impact the spacecraft from time to time. The pointing performance of high-attitude spacecraft which is sensitive to a variety of micro-disturbances will be affected by debris impact. At present, there are few researches on the impact of space debris on spacecraft attitude at home and abroad. There are only a few literatures on the influence of micrometeoroids on spacecraft attitude. In this paper, the dynamic model of space debris impact on spacecraft is established by using the relevant theoretical knowledge of spacecraft attitude motion. According to the environment of spacecraft space debris output from SDEEM space debris environment, the geometric model of spacecraft and the idea of generating random number by reverse method, the method of randomly generating impact transfer angular momentum is proposed. The random generation of time interval and the conversion between different coordinate systems during multiple impact of space debris are solved, and the single random impact of space debris is obtained by Monte Carlo numerical simulation. The statistical characteristics of the effects of multiple random impacts on the pointing performance of a spacecraft with high attitude accuracy are presented. Firstly, the SDEEM software spacecraft evaluation model and the relative flux of its output are introduced. The relative flux is defined in the spacecraft orbit coordinate system. Based on the theory of spacecraft attitude dynamics, the attitude dynamics model of space debris impact spacecraft is established. The evaluation index of spacecraft pointing performance is designed, and then the Hubble space debris environment is obtained by using SDEEM software and typical space debris is selected. The effects of a typical single impact of space debris on the direction change and the change rate of the Hubble observation axis in a given attitude are studied by programming simulation. Then the idea of generating random numbers based on the space debris environment data file and by using the reversal method is proposed. A method for randomly generating fragment size and impact azimuth; In this paper, a method of randomly generating debris into spacecraft impact position according to the direction of impact momentum is proposed. Taking Hubble as an example, the statistical characteristics of single random impact of small space debris on Hubble pointing performance are obtained by using Monte Carlo numerical simulation method. Finally, it is proposed that the continuous impact of space debris on spacecraft is a complex Poisson process. The exponential distribution of the time interval of debris continuous impact is obtained, and the transformation of different coordinate systems in the process of multiple random impacts is studied. Taking Hubble as an example, the statistical characteristics of the cumulative effects of multiple random impacts of small space debris on the pointing performance of spacecraft are obtained by Monte Carlo numerical 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】：2017
【分类号】：V528;V412.4

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