【作者】 吴海亮；

【导师】 王惠南；

【作者基本信息】 南京航空航天大学 ， 精密仪器及机械， 2008， 硕士

【摘要】 微小卫星具有重量轻、体积小、研制成本低等特点,在完成空间任务中起着独特的作用。姿态控制系统是微小卫星完成各种任务的基本前提,是微小卫星的关键技术之一和研究重点。卫星姿态测控系统包括姿态的确定和具体的姿态控制两部分,姿态的确定是根据姿态传感器来获得卫星实时的姿态参数,而姿态控制是指卫星从当前姿态向某一个目标姿态的定向过程。本文系统地研究了三轴稳定卫星的姿态确定及姿态控制系统,提出了基于粒子滤波的姿态参数处理方法,同时,对各主要控制模式进行了详尽的理论分析和具体的仿真研究,并在仿真研究的基础上对姿态控制的软件设计方面进行了较为深入的研究。首先,文章采用太阳敏感器、磁强计定姿方案,并结合新兴的粒子滤波算法对实时的姿态参数进行处理,给出了不同粒子数目下粒子滤波的性能比较。并将粒子滤波算法与EKF滤波算法进行了性能对照,验证了粒子滤波算法对于低精度微小卫星姿态控制的可行性。其次,本文对姿态控制过程中涉及各控制模式进行了仿真研究,并给出了基于磁力矩器的动量轮卸载以及稳态控制模式中的章、进动控制的仿真结果。同时,对卫星姿态机动模式进行了初步的探讨,并对卫星小角度姿态机动进行了仿真,仿真效果良好。最后,本文对姿态控制的软件设计进行了深入研究,根据是否有地面遥控的不同情况,详细的讨论了两种不同的软件设计方法以及具体的实现过程,同时给出了软件运行的最终结果。总之,文章较深入的研究了微卫星姿态控制系统,并对姿态控制系统的软件设计给出了具体的设计方案,对一般卫星姿态控制系统设计及其软件实现具有很好的指导意义。更多还原

【Abstract】 Micro-satellite, a kind of modern small satellite, has advantages of light weight, small size, low cost and so on. It plays a more and more important role in various space missions. The attitude control system is the precondition of fulfilling all kinds of tasks, is the key technology and emphasis of interrelated research.Attitude determination and control system of a satellite contains two parts, one is the attitude determination system and the other is the attitude control system. The determination of attitude is the process of getting attitude parameter of satellite by certain sense organ while the control of attitude is the research about attitude orientation to a target attitude.Based on the research of the attitude determination and control system, the author uses particle filter to deal with the attitude parameters and simulates the main control models with the detailed theory analyse.besides, this paper still studies the software design of the attitude determination system.This article established a model with magnetometers as well as sun sensors and used Particle Filter to complete the attitude estimate. The final result compared the filter capability in two different mumble of particles. Besides this, the article also compares Particle Filter to EKF algorithm, the estimate result validates that Particle Filter can fulfill the control desire of low precision Micro-satellite.After this, this paper simulate the main modes contained in attitude control process and analyses the simulation result of the unloading of momentum wheel by magnetic torque, however ,the simulation result of nutation and precession damping is also given. Meanwhile, this paper analyses the attitude maneuver of micro-satellite with a little angle and also gives the simulation result.Finally, the paper studies the software design of the attitude determination system and supplies two different actualize methods based on whether there exits a telecontrol come from ground.This article researches the attitude determination and control methods of micro-satellite and analyses the software design of the attitude control system. It can be used as reference in other micro-satellite.更多还原