This paper combines the key items of national high technical spaceflight fields , some beneficial approaches are proceeded for attitude control research aspect with mobile bodies . this paper aims at designing and developing our national missile early - warning satellite and supplying some effective technologies 本文结合国家高技术航天领域重点项目,以研制我国自己的导弹预警卫星为背景,对预警卫星在有转动部件影响下的姿态控制系统研究方面进行一些有益的探讨,以期为我国预警卫星的设计与研制提供一些行之有效的技术手段。
Using quaternion as attitude representation , the attitude kinematics function is established . 2 . several kinds of disturbance torques affecting the satellite attitude are directly computed through the models described in the paper , forming a closed loop stabilization system dumped by magnetic torques and provided with initial torques through flywheels , but other simulations only estimate it by experience ( 2 )很多仿真是根据经验估算卫星所受的干扰力矩，本文以某对地观测小卫星为背景，利用所建力学模型对卫星所受数种干扰力矩进行计算，形成了一个以飞轮作为主动力矩、通过磁力矩卸载的闭环而且稳定的姿态控制系统。
Its results of application turn out to be satisfactory , especially in eliminating the outlier . in order to analyze and verify the telemetering data of the attitude control system , this dissertation uses mathematic simulation to acquire the standard data . the t - verification and correlation coefficient method are used to analyze the data consistency for analyzing the operating quality 为定量地分析和检验卫星姿态控制系统的遥测数据,本文采用数学仿真的办法模拟实际飞行过程,得出相对标准的数据;采用t检验、相关系数法等办法对其与遥测数据做一致性检验,以分析遥测数据的合理性及系统的工作性能。
Attitude detemination and control system of a satellite contains two parts , one is the attitude detemination system and the other is the attitude control system . detemination of attitude is the search about attitude arientation on a benchmark . control of attitude is the access of direction on the predefine way . this paper only refer the system of attitude control for lace of space . if there is no special explain , the control system refered in this paper does ’ t contain attitude detemination system 卫星的姿态控制系统包括姿态的确定和姿态的控制两部分,姿态的确定是研究卫星相对于某个基准的姿态定位,而姿态控制是指卫星在某个规定或预先确定的方向上定向的过程。本文限于篇幅,仅对姿态的控制部分进行了分析,如果没有特殊说明,文中所说的姿态控制系统均不包括姿态的确定部分。
Based on the requirements of high precision pointing / targeting of advanced spacecraft , dynamic modeling of spacecraft with flexible appendages bonded with piezoelectric sensors / actuators , attitude control and active vibration suppression theory are studied deeply in this dissertation , which is funded by the research fund for the doctoral program of higher education of china item ? “ large flexible multi - bodies structure spacecraft active vibration control technology ” ( 20050213010 ) . the main contents of this dissertation are as the follows : an approximate analytical dynamic model of a flexible spacecraft with surface bonded piezoelectric sensors and actuators is derived using hamilton ’ s principle with discretization by the assumed mode method . the model is then converted to state - space form for the purpose of control design 本学位论文结合高等学校博士学科点专项科研基金“挠性多体结构卫星主动振动控制技术研究” ( 20050213010 )课题,从理论上对粘贴有压电智能元件的挠性航天器的建模、姿态控制和主动振动控制理论等展开了深入的研究,其研究内容主要包括以下几个方面:利用hamilton原理推导了挠性航天器的动力学模型、压电元件的作动方程及检测方程,并采用模态分析方法,进一步将挠性航天器的耦合方程规范化,使之适应于姿态控制系统的分析和设计。
The air bearing is the most important part of an attitude control system simulator for simulating a satellite moving in the weightless circumstance . performance of a satellite attitude simulation system based on air bearing is decided by the inertia matrix and gravity disturbance torque arising from a difference between mass center and rotation center , and air bearing can be used to simulate the algorithm of on - line mass - property parameters identification on the ground . so the problem of mass - property and gravity disturbance torque identification for satellite and air bearing is studied in this thesis 气浮台能够模拟卫星在轨失重条件下的姿态运动,是卫星姿态控制系统物理仿真的核心部件,其转动惯量和质心偏移引起的重力干扰力矩等决定了基于气浮台的卫星姿态物理仿真系统的性能,并且利用气浮台可以实现卫星质量特性在线辨识算法的地面物理仿真验证,因此本文对卫星和气浮台的质量特性及干扰力矩在线辨识问题进行深入研究。
This thesis contains six chapters . the first chapter is introduction ; the second chapter is the proposal and resolution of attitude control ; the third chapter deals with the design method of attitude control system ; chapter four discusses matlab simulation and laboratory simulation ; chapter five involves self - tuning parameters for controller and its procedure ; the last chapter is conclusion 第一章是绪论；第二章是姿态控制的提出与实现方案；第三章是模糊控制用于姿态控制系统的设计；第四章是matlab仿真与实验室仿真；第五章是参数自整定模糊控制器及其实现；第六章是结论。
At present , fes technology has been successfully applied in many fields such as uninterruptable power supply ( ups ) systems , electric power systems , hybrid electric vehicles , etc . researches indicate that in energy sources and attitude control system of satellites , by fess both energy storage and attitude control can be accomplished . it would be remarkable to improve global performance of satellites , so aeronautics & astronautics departments attach great importance to fess 研究表明，在卫星能源和姿态控制系统中，利用飞轮储能系统可以同时完成能量储存和姿态控制两方面的功能，这对于提高卫星的总体性能有着显著的意义，因而得到航空航天部门的重视，并成为该研究方向的前沿课题，但目前尚未进入实用阶段。
Based on the spaceflight technology innovation program of “ research on the testing method of reliability - - - - research on the fault diagnostic expert system and neural network ” and the pre - research defense projects of “ research on longevous service and high reliability of satellites ” of the national tenth - five - year plan , taking attitude control system of a satellite as object , the theories and the applications of the neural networks and expert system in the fault diagnosis are studied in this dissertation 本文以航天技术创新基金项目“可靠性试验方法研究? ?故障诊断的专家系统神经网络技术研究”和国家武器装备“十五”预研项目“卫星长寿命高可靠性技术”为背景,以卫星姿态控制系统为研究对象,在理论和实践两个方面对神经网络和专家系统相结合的故障诊断技术及其在卫星中的应用进行了研究。
The aim of this dissertation research is focused on the pre - research defense projects of “ research on longevous service and high reliability of satellite ” of the national tenth - five - year plan . for improving the capability of fault diagnosis for un - presuppose faults , we propose a new fault reconstruction technique which suits to satellite attitude control system and four novel techniques under this frame work is investigated in this dissertation 本文以国防十五预研项目“卫星长寿命高可靠性技术”为研究背景,为提高目前卫星对无故障模式故障的诊断能力,提出了一套适合卫星姿态控制系统的故障重构框架体系,并研究了四项关键技术作为该框架的支撑。
