At last , this paper realizes the sonar array attitude stabilization system based on the simulation circuitry and introduces the method of how to make control system with pc / 104 . the attitude stabilization system is debugged successfully . 最后，对上述声纳基阵姿态稳定系统进行了基于模拟电路的硬件实现，应用pc 104实现控制规律，并对整个系统进行调试。
The dynamic model of the satellite with a flexible appendage has been studied in this thesis . also , the techniques of the satellite earth acquisition and three - axis attitude stabilization of both the rigid satellite and the liquid - filled satellite have been researched 本文针对单翼大挠性太阳帆板卫星，建立了挠性卫星动力学模型，在此基础上，研究了地球捕获、刚体卫星三轴姿态稳定、充液卫星三轴姿态稳定问题。
In conformity with this means , we study that the changing of radar and platform coefficients influences the target location , and present the way to analyze the location accuracy through the platform position accuracy , platform attitude stability and radar timing accuracy 在此基础上，论文剖析了雷达及平台参数变化对目标定位的影响，提出了通过平台位置精度、平台姿态稳定精度和雷达定时精度来分析目标定位精度的方法。
The magnetic suspension momentum wheel has better performance than the conventional ball bearing momentum wheel , and one gimbaling magnetic suspension momentum wheel whose rotation axis can be deflected can perform three axes attitude stability and control of spacecraft in high precision 采用磁悬浮轴承支撑的飞轮比传统滚珠轴承飞轮有着更高的性能,而具有框架功能的单个转轴可偏置磁悬浮飞轮就可以实现航天器的高精度三轴姿态稳定控制。
Through the analysis of the attitude dynamic equation , the potential energy function is derived . the relationships of attitude varieties are derived from energy function and angle momentum equation and thus the attitude control laws of bias momentum satellite are put forward 通过对卫星姿态动力学方程分析，得出卫星的势函数，结合卫星的势函数和角动量方程导出各姿态之间变化关系，提出利用地磁场实现偏置动量轮卫星姿态稳定的控制规律。
It is a crucial question to stabilize missiles under stronger interactions , which has been hardly studied before . in this dissertation many significant result are given from the research of several correlative dynamic and control topics . an exhaustive summarization is made for free flight motion of spinning missiles 导弹自旋飞行引起的运动耦合、控制耦合及其它效应容易导致弹体失稳,实现较强耦合作用下弹道导弹自旋飞行姿态稳定控制是亟待解决的问题。
The antenna pointing control accuracy can satisfy the design specification and it is validated to be appropriate and effective . at last , the designed user satellites complex control system is simulated based on xpc target which is used for hardware - in - the - loop simulation 4 .基于xpc实时仿真平台,充分利用实验室条件,搭建了用户星天线样机在回路中的半物理仿真实验,将天线指向控制系统和星体姿态稳定控制系统联合起来,组成中继卫星复合控制系统进行近一步的验证。
Mixed weights cgpc is constructed for constrained cgpc , which has advantage in simplicity and efficiency . performance of ballistic missile ’ s servo system is improved by approximate constrained arithmetic . the effect of side force on stability of spinning missiles is studied by routh criterion , which proved to be more universal than others ’ work 针对线性角运动模型,直接采用劳斯方法,与前人工作相比具有更好的通用性和精确性;借此方法近似分析了侧向力对自旋弹道导弹稳定性的影响;研究了内模控制在弹道导弹姿态稳定系统中的应用。
The system based on pid control theory has characteristics of fast response speed and higher peak overshoot , and it also has a good performance of tracking , but it is lack of ability of disturbance rejection . because smvs control method is insensitive to the variations of the model parameters , nonlinear and exterior noises , the attitude stabilization system designed based on smvs has fast response speed , higher ability of disturbance rejection and has no peak overshoot , namely , the system is robust 仿真结果表明，基于pid控制规律设计的系统具有响应速度快但超调大的特点，系统的跟踪性能较好，但抗干扰能力较差；滑模变结构控制方法因为其对模型参数的变化、非线性和外扰噪声的不敏感性，设计的声纳基阵姿态稳定系统无超调，响应速度快而且抗干扰能力强，具有很好的鲁棒性。
A multiloop antenna pointing controller has been designed while three feedforward schemes are used in this control design . the simulation results show that the antenna pointing control system can improve the precision of the attitude angle and the attitude angle rate , and the antenna can slew to the neighborhood of tdrs fast , search and then track tdrs 在设计好的天线跟踪指向控制系统基础上,采用前馈+反馈的复合控制策略设计了复合控制器,仿真结果表明设计的天线指向控制系统能够较好的提高星体的姿态稳定度和控制精度,天线能够快速回扫至中继卫星附近并进行跟踪,天线指向精度满足设计要求,表明了所设计的天线指向控制系统的合理性和有效性。
