低轨无拖曳卫星的自适应神经网络控制器设计

低轨无拖曳(Drag-free)卫星为相对论的验证、引力波探测以及地球重力场的测量提供了低干扰的试验环境。目前已有的工作主要对无拖曳卫星模型进行线性化,然后进行控制器设计,此种方法忽略了无拖曳卫星控制系统的非线性环节,因此降低了控制器的精度。本文将基于Lyapunov稳定性理论和自适应反步控制,直接针对无拖曳卫星控制系统的非线性模型进行分析,设计一种自适应神经网络控制器。针对系统建模过程中的线性化和未建模动态,利用RBF神经网络对非线性项进行拟合和补偿,建立自适应神经网络权值自适应律,保证闭环系统具有较好的鲁棒稳定性能和抗干扰性能,实现无拖曳卫星控制系统的设计要求。仿真结果表明控制器的有效性,满足了无拖曳卫星的控制精度要求。     

小卫星的鲁棒自适应姿态控制

对于中低轨道的小卫星而言，设计能克服参数不确定性及非参数不确定性影响的鲁棒自适应控制器具有重要的工程意义和理论价值。考虑存在参数不确定性及非参数不确定性，本文分析了小卫星的姿态动力学及运动学方程，设计出了一种鲁棒自适应控制器，证明了该控制器可以保证控制系统全局一致最终有界稳定。仿真结果验证了该控制器的有效性。     

多不确定性战术导弹鲁棒控制器设计研究

研究了包含多种不确定性的战术导弹鲁棒控制器设计问题;首先介绍了μ分析与μ综合理论,给出了通过D-K迭代设计鲁棒控制器的方法;进而通过分析系统中存在的多种不确定性及其对受控系统的影响、建立包含多种不确定的被控对象、引入合适的评价权函,得到了扩展的广义受控系统,利用Matlab鲁棒控制工具箱设计了战术导弹俯仰通道鲁棒控制器;最后通过数值仿真,验证了设计的鲁棒控制器满足系统设计的性能指标要求,并且对系统中存在的多种不确定性和扰动具有较强的鲁棒性。     

具结构不确定性的卫星姿态控制问题探讨

本文对弱阻尼特性的卫星姿态的鲁棒控制问题进行了研究。先采用加权办法将对象参数不确定性转化成未建模动态,然后用 H~∞方法进行设计,最后编制了 Safonov 鲁棒稳定裕度k_m 的软件,并对所设计控制系统的鲁棒性能进行了检验和分析。     

双容液位系统鲁棒自适应容错控制

针对双容液位控制系统的泄漏等故障,通过线性化建模,研究了鲁棒自适应主动容错控制问题.首先在系统无故障正常运行情形,考虑建模误差和外界干扰等不确定性,利用不确定性上界自适应估计,设计了鲁棒自适应控制器.与此同时,对系统进行故障监控,设计了故障诊断滤波器,并利用对不确定性上界的估计终值提出了一种新的故障检测算法,进一步基于神经网络故障逼近,研究了一种修正控制律的自适应鲁棒容错控制器设计方法,该控制器通过补偿故障所带来的影响使闭环系统最终一致有界稳定.最后,通过仿真试验,验证了提出的方法的有效性.     

空间绳系机器人目标抓捕鲁棒自适应控制器设计

针对空间绳系机器人（Tethered space robot,TSR）目标抓捕过程中的稳定控制问题,建立空间绳系机器人系统模型,根据阻抗控制原理,设计基于位置的阻抗控制方法;针对空间绳系机器人系统的模型不确定性问题,利用神经网络对不确定性进行估计补偿,设计鲁棒项对空间系绳干扰和神经网络估计误差的影响进行抑制,在此基础上设计空间绳系机器人目标抓捕鲁棒自适应稳定控制器,并进行稳定性证明.最后对设计的控制器进行仿真验证.作为对比,对无鲁棒项自适应的稳定控制器进行仿真.仿真结果表明,设计的基于阻抗控制的鲁棒自适应控制可以实现对空间绳系机器人目标抓捕过程中的稳定控制,与无鲁棒项自适应的稳定控制器仿真结果相比,本文采用的鲁棒自适应控制方法可以有效地对不确定性进行补偿,控制过程中超调量更小,收敛时间更短,并且控制精度更高.     

双容液位系统的不确定时滞的鲁棒容错控制

针对双容液位控制系统的执行器失效等故障,通过线性化建模,研究了鲁棒自适应容错控制问题。首先在系统无故障正常工作时,考虑建模误差、输入信号的稳定性、系统参数等不确定性因素,利用不确定性上界自适应估计,设计了不确定时滞鲁棒控制器。同时,对系统进行故障检测,研究了一种修正控制律的自适应鲁棒容错控制器设计方法,该控制器通过修补执行器故障所带来的影响使该系统最终有界稳定。最后,通过仿真试验,验证了提出的方法的有效性。     

双容液位系统的不确定时滞的鲁棒容错控制

针对双容液位控制系统的执行器失效等故障,通过线性化建模,研究了鲁棒自适应容错控制问题。首先在系统无故障正常工作时,考虑建模误差、输入信号的稳定性、系统参数等不确定性因素,利用不确定性上界自适应估计,设计了不确定时滞鲁棒控制器。同时,对系统进行故障检测,研究了一种修正控制律的自适应鲁棒容错控制器设计方法,该控制器通过修补执行器故障所带来的影响使该系统最终有界稳定。最后,通过仿真实验,验证了提出方法的有效性。     

基于T-S模糊模型的复杂系统的灵敏度分析

为模拟空间对接强制校正阶段的推出和拉近过程,提出基于六自由度并联机器人位置内环的柔顺力控制策略.综合考虑参数变化、模型变动和外来干扰等不确定性,利用μ综合控制理论设计鲁棒力控制器,并通过μ分析比较鲁棒力控制器和经典力控制器的鲁棒稳定性和鲁棒性能.鲁棒力控制器和经典力控制器的实验结果,表明了所设计鲁棒力控制器的有效性和优越性.     

挠性飞行器姿态稳定鲁棒变结构控制

针对三轴稳定卫星的模型参数存在不确定性,设计了一种鲁棒变结构控制器,它能确保系统在一定条件下具有全局渐近稳定性,并且系统在一定条件下能在有限的时间内到达滑动平面,具有鲁棒到达条件,同时控制律实现简单,采用积分型滑动平面,能保证系统在到达滑动平面后具有良好的性能,最后根据卫星参数给出了具体的数值算例,数值仿真结果良好,从数值仿真结果来看控制器在存在较大不确定性情况下（考虑系统转动惯量有5％的不确定性）依然保持良好性能,具有很强的鲁棒稳定性,而且,采用边界层改进控制器后,能有效地解决抖振问题,同时控制器的性能基本保持不变,说明鲁棒变结构控制器的设计是有效的。     

Trapping—A control phenomenon of spinning drag-free satellites

A drag-free satellite contains a proof mass in an internal cavity and is controlled in translation so that it never touches the proof mass. The satellite shields the proof mass from external forces, thus allowing the proof mass to follow a drag-free orbit. Spinning the satellite is desirable because it attenuates the effect of proof mass disturbing forces and simplifiies the attitude control. The design of a translation controller for a spinning drag-free satellite typically includes a deadspace to eliminate chatter. This design feature and the inability to locate precisely the mass center give rise to a phenomenon called trapping that potentially could waste significant amounts of propellant. A theory is developed and experimentally verified that explains the role of these factors and provides insight into the effect of other control parameters. An analog application of estimation theory to observe the center-of-mass location was evaluated and found to be a practical method to eliminate mass center uncertainties as a cause of trapping and its associated propellant wastage. It is further concluded that, by proper selection of control parameters and deadspace shape, translation control of a spinning satellite is quite feasible.     

饱和约束测量扩张状态滤波与无拖曳卫星位姿自抗扰控制

无拖曳卫星的本体姿态、卫星本体与测试质量间的相对位移及相对姿态的联合控制受到外部扰动、输入噪声、测量噪声及饱和约束、输入耦合以及状态耦合等因素的影响, 控制器的设计面临挑战. 本文采用基于扩张状态的卡尔曼滤波对系统状态和系统扰动进行实时估计, 引入自抗扰控制策略进行了控制器设计. 针对无拖曳控制子系统设计了测量饱和受限下的扩张状态估计算法, 并进行了信息融合. 在设计控制律时不仅考虑了对外部扰动的补偿, 还将系统状态间的耦合关系看成内部扰动进行补偿, 使得被控系统等价为“积分串联型系统”, 在此基础上实现了无拖曳卫星的联合控制. 数值仿真验证了方法的有效性和合理性.     

移动卫星天线的自适应鲁棒控制系统

为了改善移动卫星天线的控制性能和稳定性,本文进行移动卫星天线的自适应鲁棒控制系统的研究．首先针对移动卫星天线数学模型,设计自适应鲁棒控制器和控制系统,所提出的自适应鲁棒控制律和控制系统不仅保证了闭环系统的稳定性,而且实现了所期望的性能,最后通过试验结果证明该控制算法的有效性,尽管外界环境道路条件的变化不同,移动卫星天线控制系统表现了满意的控制性能．     

Minimum thrust levels for spinning drag-free satellites

A drag-free satellite, which contains an internal unsupported proof mass, is shielded from external forces such as solar pressure. Thrustors force the satellite to follow the proof mass and hence the satellite follows an almost purely gravitational orbit. The dominant internal disturbing force is the mass attraction of the satellite on the proof mass. Spinning the satellite reduces this force and it has been investigated what the size of the thrustors must be in this case. This size is much smaller than originally thought. Its impact on some other features is shown.     

Robust PID controller for flexible satellite attitude control under angular velocity and control torque constraint

A PID controller for flexible satellite attitude control with unknown perturbation is proposed in this paper. System inertia uncertainty, stochastic disturbance torque, and perturbation of flexible deformation are discussed, and the controller proposed in this paper is robust to these perturbations. A novel integral term is designed; hence the Lyapunov function structure is modified and the stability proof is simplified. The angular velocity constraint is discussed and a novel method to solve the angular velocity saturation issue is given. The control torque saturation issue is also taken into consideration. Stability for all conditions considered in this paper is proved by the Lyapunov method. The performance of the controller is demonstrated by numerical simulation.     

Drag-free and attitude control for the GOCE satellite

The paper concerns Drag-Free and Attitude Control of the European satellite Gravity field and steady-state Ocean Circulation Explorer (GOCE) during the science phase. Design has followed Embedded Model Control, where a spacecraft/environment discrete-time model becomes the real-time control core and is interfaced to actuators and sensors via tuneable feedback laws. Drag-free control implies cancelling non-gravitational forces and all torques, leaving the satellite to free fall subject only to gravity. In addition, for reasons of science, the spacecraft must be carefully aligned to the local orbital frame, retrieved from range and rate of a Global Positioning System receiver. Accurate drag-free and attitude control requires proportional and low-noise thrusting, which in turn raises the problem of propellant saving. Six-axis drag-free control is driven by accurate acceleration measurements provided by the mission payload. Their angular components must be combined with the star-tracker attitude so as to compensate accelerometer drift. Simulated results are presented and discussed.     

Adaptive control of rigid body satellite

The minimal controller synthesis （MCS） is an extension of the hyperstable model reference adaptive control algorithm. The aim of minimal controller synthesis is to achieve excellent closed-loop control despite the presence of plant parameter variations, external disturbances, dynamic coupling within the plant and plant nonlinearities. The minimal controller synthesis algorithm was successfully applied to the problem of decentralized adaptive schemes. The decentralized minimal controller synthesis adaptive control strategy for controlling the attitude of a rigid body satellite is adopted in this paper. A model reference adaptive control strategy which uses one single three-axis slew is proposed for the purpose of controlling the attitude of a rigid body satellite. The simulation results are excellent and show that the controlled system is robust against disturbances.     

一类不确定系统的鲁棒D-稳定保守性研究

针对一类多面体不确定线性连续系统,研究了系统鲁棒D-稳定问题.为降低设计的保守性,引入参数相关Lyapunov函数,给出了系统鲁棒D-稳定的充分条件.通过求解一组线性矩阵不等式,得到了系统鲁棒D-稳定的状态反馈控制器,使得闭环系统鲁棒D-稳定.对某卫星姿态控制系统的仿真结果表明了该方法的有效性.     

Robust stability—degree assignment and its applications to the control of flexible structures

A new method of robust controller synthesis is introduced which is an extension of robust stabilization to robust stability-degree assignment. This method guarantees a lower bound of stability degree for all uncertainties within a prescribed magnitude band. The method is applied to the control of four types of flexible structures, namely, colocated beam, non-colocated beam, beam with moving base and large scale satellite model. Excellent performances have been obtained experimentally with respect to the response speed and the robustness.