【作者】 高巍；

【导师】 耿云海；

【作者基本信息】 哈尔滨工业大学 ， 飞行器设计， 2008， 硕士

【摘要】 自20世纪80年代美国军方提出了现代小卫星的概念以来,其技术发展非常迅速,目前已经成为航天器发展的一个重要方向。作为现代微小卫星的关键部分,其姿态控制系统需具有结构简单、质量轻、可靠性高和低成本等特点。本文以HIT-1号微型小卫星方案论证为背景,对微小卫星的姿态确定技术、主动磁控技术和姿态算法的硬件实现问题进行了研究。主要研究工作如下:论文首先对HIT-1号进行总体任务分析,明确总体方案对卫星姿控系统的要求。在对现有的姿态测量与控制方法分析与比较后,提出一种可行的姿控系统总体方案:以“地磁强度矢量+太阳方位矢量”作为基本姿态测量手段,以“俯仰偏置动量轮+三轴磁力矩器”作为卫星的姿态控制系统。对HIT-1进行了姿态确定系统方案设计:依照结构复用思想,将卫星的太阳电池片复用为太阳敏感器解算太阳方位矢量。讨论了基于“磁强计与太阳敏感器(电池片)的TRIAD双矢量定姿算法和基于扩展卡尔曼滤波的联合滤波定姿算法,解决了卫星在无角速率敏感条件下姿态测量和姿态确定的问题。通过仿真算例对定姿算法的定姿精度和适用范围进行了验证。对HIT-1进行了姿态控制系统方案设计:以俯仰偏置动量轮组合三轴磁力矩器构成控制系统主体,分别设计动量轮起旋阶段、入轨阶段、三轴稳定阶段的相关控制规律,并进行了数学仿真验证。同时对动量轮和三轴磁力矩器进行了参数设计。论文最后利用DSP及其它数字电路技术设计了HIT-1号姿控系统的主控板。以TI公司DSP系列TMS320LF2407芯片作为目标器件,利用地面仿真计算机结合Matlab/Simulink和CCS,构建了基于“CCSLINK for DSP”的微小卫星姿态控制仿真系统,对本文所设计的控制算法进行了功能级的仿真验证。更多还原

【Abstract】 Microsatellite technology undergoes rapid development and becomes a leading technology in aerospace industry, since the concept of "modern satellite " has been proposed by US Air Force in 1980s. Attitude Determination Control Subsystem of modern micro-satellite, as a major component of microsatellite, should possess simple, light, reliable and low-cost features. The paper analyzes the attitude determination system, active magnetic control and realization of control algorithm hardware with the case of HIT-1 micro-satellite.Firstly, the paper confirms satellite’s general requirement to attitude determination and control system on the analysis of HIT-1. It points out a practical general system proposal on the comparison between attitude measurement and control method: taking "vector of geomagnetic intensity and vector of sun orientation" as basic attitude measurement method, taking "pitching bias momentum flywheel and three-axis magnetic-coil" as attitude control system.As for attitude determination subsystem, the paper analyzes two attitude sensors. It takes satellite’s solar battery multiplexing as solar sensor to calculate sun orientation on the basis of structure multiplexing concept. It solves the problems of attitude measurement and determination under the non-direction sensitive conditions. It checked the precision and application scope of attitude determination algorithm by mathematical simulation experiment.As for attitude control subsystem, the paper takes three-axis magnetic-coil combined by pitching biased momentum flywheel as main part of control system. It points out the stages of spinup, rotation, and three-axis stabilizing. Meanwhile, it checked by mathematical simulation experiment and made parameters design of momentum wheel and three-axis magnetic-coil.Finally, the paper designs main control board and its main functional module for HIT-1 attitude determination and control system based on DSP and other digital circuit technology. It chose related device, and interface. Besides, it made a preliminary analysis of DSP control algorithm hardware based on DSP: it realized "pinup, rotation, and three-axis stabilizing" by hardware language with the objective device of TI company’s DSP series TMS320LF2407 CMOS chip. It set micro-satellite attitude control simulation system based on CCSLINK for DSP, with the help of ground simulation computer making kinematics and dynamics modeling and made approximate simulation of solar vector and geomagnetism vector’s Matlab/Simulink and CCS. The paper makes functional level simulation experiments of designed control algorithm.更多还原