受扰挠性卫星全局稳定姿态跟踪控制

挠性卫星的姿态跟踪控制要求同时考虑卫星本体姿态跟踪和挠性附件振动对姿态跟踪影响。本文针对存在常值扰动和正弦扰动情况时的挠性卫星姿态跟踪控制问题，考虑目标姿态角速度可以时变的一般情形，设计了基于误差四元数的姿态跟踪控制律，并利用Barbalat引理证明了系统的全局稳定性。数学仿真结果表明该控制律能使闭环控制系统的姿态跟踪全局渐近稳定，从而有效消除常值干扰和正弦干扰，保证卫星本体跟踪精度。     

挠性卫星姿态机动三段式轨迹规划与滚动跟踪控制

以新颖成像模式对挠性敏捷卫星姿态的快速机动控制为需求,本文针对金字塔构型控制力矩陀螺(CMG)群为执行机构的挠性卫星,提出基于三段式正弦角加速度的姿态路径规划方法及具有滚动优化思想的跟踪算法。在姿态路径规划方法设计中,融合谱分析及非线性优化方法,设计了兼顾卫星姿态机动快速性及抑制挠性附件振动性能的姿态轨迹;为实现对规划姿态轨迹的高精度跟踪,综合加权优化指标及奇异性、执行机构能力等约束,设计了金字塔构型CMG群框架角速度的非线性模型预测(NMPC)跟踪控制律。在转动惯量存在测量误差及空间干扰情况下,多种姿态机动仿真表明,本文提出的控制方法是有效的,且表现出较强的鲁棒性。     

航天器输入受限的鲁棒自适应姿态跟踪控制

研究含模型不确定性的刚性航天器输入受限时的姿态跟踪控制设计问题.针对修改的罗德里格斯姿态参数描述的航天器姿态跟踪动力学模型,基于一种有界非线性连续函数和修改的罗德里格斯姿态参数自身有界性,设计鲁棒自适应状态反馈受限控制器,不确定参数的自适应更新律可保证在线估计参数的有界性.通过所提出的输入受限控制设计方法给出输入受限幅...     

具有不确定性的非线性系统自适应神经网络L2增益控制

针对存在不确定性的非线性系统,提出了自适应神经网络L2增益控制器设计方法,将基于Hamilton—Jacobi—Issacs（HJI）不等式和自适应神经网络策略相结合,有效地克服了需要被控对象精确建模的局限性．神经网络对系统模型的偏差进行拟合;为了补偿拟合误差,引入补偿控制器和神经网络权值自适应调节律,通过在线自适应修正神经网络权值,来保证闭环系统满足相应的L2性能准则．仿真结果表明提出的控制器设计方法是有效的,克服了一般方法需要被控对象精确建模的局限性．     

干扰环境下的挠性航天器姿态跟踪控制

挠性航天器在姿态机动过程会受环境干扰力矩的作用,研究有扰情况下挠性航天器的姿态跟踪控制问题.首先,设计了干扰观测器在线估计频率已知的外部干扰信号,然后,基于干扰观测器设计了非线性反馈姿态跟踪控制器以跟踪目标姿态,并且该控制器只需要误差四元数和角速度的反馈信息.其次,采用Lyapunov方程和Barbalat引理证明了控...     

挠性卫星姿态快速机动控制

挠性卫星在快速机动中既要满足快速性要求，又要抑制挠性附件产生的振动。本文提出了一种基于非约束模态方程的方波序列控制方法，并给出了最小机动时间的方波规划方法。该方法不仅保证机动后无余振，而且满足最快机动的要求，此外，由于控制输出为方波，因而适合卫星上的喷气椎力器控制模式和飞轮控制模式。最后通过数字仿真验证了方波序列控制的有效性。     

带有挠性附件卫星的自适应内模控制

挠性部件诱导的振动干扰有时严重影响大型卫星姿态指向和稳定度。为了保证姿态控制的高精度和高稳定度,本文导出了带有“拍打”运动的挠性卫星数学模型,并指出模型的不确定性;给出了卫星姿态控制器的基本形式,分析了控制器参数的选取准则以保证姿态控制系统的稳定性;进而利用在轨辨识在线修正控制器参数形成了卫星姿态的自适应内模控制器。分析和实验表明,本文提出的自适应内模控制器能够有效提高大型卫星的姿态指向精度和稳定度。     

三轴稳定挠性卫星姿态机动时变滑模变结构和主动振动控制

针对带有控制受限的挠性卫星的姿态机动和振动控制问题, 给出了一类仅利用输出信息的变结构控制和 基于智能材料的主动振动控制技术相结合的复合控制方法. 首先给出变结构姿态控制器的设计来完成卫星姿态机动, 并给出一种切换机制以实现挠性卫星快速姿态机动; 其次, 采用分布式压电元件作为作动器, 设计了应变速率反馈补偿器以增加挠性结构的阻尼, 使其振动能够很快衰减. 最后, 将本文提出的方法应用于三轴稳定挠性卫星的姿态机动控制, 仿真结果表明: 在推力器的控制受限条件下, 完成姿态机动的同时, 有效地抑制挠性附件的振动.     

含有参数不确定性的挠性航天器姿态跟踪滑模控制

对有不确定参数的挠性航天器姿态跟踪控制, 提出了一种基于滑模控制的姿态跟踪控制律. 挠性航天器动力学采用混合坐标法进行建模; 构造挠性模态观测器对挠性模态变量进行观测. 基于Lyapunov稳定性原理得到含有挠性模态观测器的滑模控制律, 并给出了全局渐近稳定性的证明. 对各个仿真结果进行比较, 显示出本文提出的滑模控制律针对航天器惯量阵不确定性具有良好的鲁棒性, 而且具有较强的扰动抑制能力.     

欠驱动AUV模糊神经网络L2增益鲁棒跟踪控制

提出基于模糊神经网络欠驱动水下自主机器人(AUV)的L2增益鲁棒跟踪控制方法,该方法通过在线学习逼近动力学模型的不确定项.控制器克服了由于缺少横向推力对跟踪误差的影响,在考虑未知海流干扰情况下,实现了系统对模糊神经网络逼近误差的L2增益小于γ.利用Lyapunov稳定性理论证明了闭环控制系统误差信号一致最终有界.最后,通过精确模型参数和参数扰动仿真实验验证了该控制方法具有很好的跟踪效果和较强的鲁棒性.     

Robust attitude tracking control of flexible spacecraft for achieving globally asymptotic stability

The three‐axis attitude tracking control problem in the presence of parameter uncertainties and external disturbances for a spacecraft with flexible appendages is investigated in this paper. Novel simple robust Lyapunov‐based controllers that require only the attitude and angular velocity measurement are proposed. The first controller is a discontinuous one composed of a nonlinear PD part plus a sign function, whereas the second one is continuous or even smooth by modifying the discontinuous part of the first one. For a general desired trajectory, both controllers can achieve globally asymptotic stability of the attitude and angular velocity tracking errors instead of ultimate boundedness. By using a two‐step proof technique, the partial stability of the proposed controllers for the resulting closed‐loop systems in the face of model uncertainties and unexpected disturbances is proven theoretically. To further enhance the control performance, a continuous controller is presented that utilizes the tracking errors for estimating the external disturbances. In addition, stability analysis is done. For all the developed controllers, numerical simulation results are provided to demonstrate their performance. Copyright © 2008 John Wiley & Sons, Ltd.     

Output attitude tracking for flexible spacecraft

In this work a class of nonlinear controllers has been derived for spacecraft with flexible appendages. The control aim is to track a given desired attitude. First, a static controller based on the measure of the whole state is determined. Then, a dynamic controller is designed; this controller does not use measures from the modal variables, and the variables measured are the parameters describing the attitude and the spacecraft angular velocity. Finally, it is shown that a relaxed version of the tracking problem can be solved when the only measured variable is the spacecraft angular velocity. Simulations show the performances of such control schemes.     

Distributed attitude synchronization control for multiple flexible spacecraft without modal variable measurement

This paper solves the attitude synchronization and tracking problem for a group of flexible spacecraft without flexible‐mode variable measurement. The spacecraft formation is studied in a leader‐following synchronization scheme with a dynamic virtual leader. With the application of adaptive sliding‐mode control technique, a distributed modified Rodriguez parameters‐based dynamic controller is proposed for flexible spacecraft without requiring modal variable measurement. It is proved that the attitude synchronization and tracking can be achieved asymptotically under the control strategy through the Lyapunov's stability analysis. Furthermore, a distributed robust continuous control algorithm is designed to guarantee the ultimate boundedness of both the attitude tracking error and the modal variable observation error when bounded external disturbances exist. Some numerical simulation examples for multiple flexible spacecraft formation are given to demonstrate the effectiveness of the proposed method.     

复杂约束下的挠性航天器姿态参考管理控制

本文提出了一种基于显式参考管理与模态观测器的挠性航天器姿态机动控制方法. 首先, 采用改进的罗德里格斯参数建立了航天器的运动学和动力学模型, 分析了存在的控制约束和角速度约束. 在此基础上, 设计了基于显式参考管理的约束挠性航天器姿态重定向控制算法. 由于挠性模态不能直接测量, 内层设计了模态观测器, 并将观测器观测得到的模态坐标作为内层无约束控制器的输入. 随后, 外层导航模块根据所需满足的约束条件设计了相应的动态路径, 该路径可以根据当前状态以合适的速率收敛到最终状态, 通过跟踪该路径, 航天器姿态就可以在满足约束的情况下快速到达期望位置. 通过构造合适的李雅普诺夫函数, 严格证明了该挠性航天器显式参考管理姿态控制算法的稳定性. 最后, 仿真结果进一步验证所设计算法的约束处理效果与振动抑制能力.     

基于动态滑模控制的挠性航天器姿态控制

本文采用滑动模态控制方法对挠性航天器设计了姿态镇定控制律.首先,建立了挠性航天器的数学模型.其中,挠性航天器的运动学方程采用姿态四元数描述.然后,通过引入动态切换函数,设计挠性航天器的动态滑模姿态控制律.该控制律能对滑模姿态控制律中由符号函数项引起的抖振进行抑制.采用Lyapunov方法证明了所设计的动态滑模姿态控制律能使闭环航天器姿态系统稳定.最后,通过数值仿真例子验证了所提出方法的有效性.     

Robust adaptive attitude control for flexible spacecraft in the presence of SGCMG friction nonlinearity

This paper investigates attitude maneuver control issues of a flexible spacecraft with pyramid‐type single gimbaled control moment gyroscopes (SGCMGs) as the actuator. The LuGre friction model is adopted to precisely describe the nonlinearity of the SGCMG gimbal friction. Aiming at restraining the adverse effects of the friction existed in SGCMG on the attitude control performance, a robust adaptive attitude controller is proposed, and projection‐based adaptive laws are presented to estimate the friction parametric uncertainties and the bound of friction nonlinearity. By treating the flexible mode coupling effect and external disturbances as lump disturbances, the inertia uncertainties and the bound of the lump disturbances are also estimated and compensated simultaneously to reduce their adverse effect on the system. With the Lyapunov technique, the states of flexible spacecraft control system are proved to be uniformly ultimately bounded. Numerical simulations demonstrate the effectiveness of the proposed scheme.     

Adaptive robust attitude control of a flexible spacecraft

A new attitude control strategy for rotational manoeuvre of an elastic spacecraft is presented. Adaptive sliding mode control with hybrid sliding surface (HSS) is used to minimize the effects of uncertainties, disturbances and the difficulties arising from measurement of flexible dynamic co‐ordinates. The model of the spacecraft considered as rigid central hub and two elastic appendages. Collocated actuators and sensors are placed on the rigid central hub. Stability proof of the overall closed‐loop system is given via Lyapunov analysis. Numerical simulations show that the attitude manoeuvres can be performed precisely and the elastic deformations of the flexible substructures are suppressed as well. Copyright © 2006 John Wiley & Sons, Ltd.     

转动惯量存在不确定性的挠性航天器滑模姿态控制

在转动惯量存在不确定性时,采用滑动模态控制方法对挠性航天器设计了姿态镇定控制律.由于挠性模态是不可量测的,首先设计了部分状态观测器对挠性模态进行估计.进而结合滑模控制方法,提出了基于观测器的滑模姿态控制律.采用Lyapunov方法证明了在存在转动惯量不确定性时,所设计的滑模姿态控制律能使闭环航天器姿态系统稳定.最后,通过数值仿真例子验证了所提出方法的有效性.     

Inertia‐free attitude stabilization for flexible spacecraft with active vibration suppression

This paper addresses the inertia‐free attitude control problem for flexible spacecraft in the presence of inertia uncertainties, external disturbances, actuator faults, measurement errors, and input magnitude and rate constraints (MRCs). By analyzing the influence of external disturbances, faulty signals, and actual inertial matrix, a lumped disturbance is reconstructed to facilitate the controller design. Then, a new intermediate observer is developed to estimate the attitude and modal information and the lumped disturbance. The Lyapunov stability analysis shows that the developed controller can achieve the objectives of the attitude stabilization and vibration suppression with input MRCs. Finally, numerical simulations are performed to demonstrate the effectiveness and superiority of the proposed control method.