航天器姿态跟踪系统的自适应滑模控制

针对存在不确定惯量矩阵和外干扰的刚体航天器姿态跟踪系统,提出了一种自适应滑模控制方法。首先建立了姿态跟踪误差动力学方程,并对刚体航天器跟踪误差动力学定义了滑模,设计了自适应滑模控制律,该控制律的优点在于可以估计系统不确定块,消除了传统滑模控制中对不确定界的要求。Lyapunov分析表明了提出的自适应滑模控制器确保闭环系统取得渐近稳定性。仿真结果验证了提出的控制策略的有效性。     

Spacecraft Anti‐Unwinding Attitude Control Using Second‐Order Sliding Mode

This paper presents an anti‐unwinding control method for the attitude stabilization of a rigid spacecraft. Quaternion has double stable equilibrium and this may cause unwinding problems in spacecraft attitude control if both the equilibria are not considered in control design. Here, the initial condition of scalar quaternion is included in sliding surface and an anti‐unwinding control method is formulated in second‐order sliding mode. The presented second‐order sliding mode controller can alleviate chattering and ensure a smooth control for actuator. Further, to eliminate the need of advance information about bounds of uncertainty and external disturbance, adaptive laws are applied to estimate the controller gains. The closed‐loop stability is proved using the Lyapunov stability theory. In conclusion, a simulation is conducted in the presence of inertia uncertainty and external disturbances and it is found that the presented control method is efficient to negate the effect of inertia uncertainty and external disturbances, alleviate chattering, eliminate unwinding, and ensure high accuracy and steady state precision.     

Adaptive Fault‐Tolerant Attitude Tracking Control of Rigid Spacecraft on Lie Group with Fixed‐Time Convergence

This paper investigates the fixed‐time attitude tracking problem for rigid spacecraft in the presence of inertial uncertainties, external disturbances, actuator faults, and input saturation constraints. The logarithm map is first utilized to transform the tracking problem on SO(3) into the stabilization one on its associated Lie algebra ( ). A novel nonsingular fixed‐time‐based sliding mode is designed, which not only avoids the singularity but also guarantees that the convergence time of tracking errors along the sliding surface is independent of the state value. Then, an adaptive fault‐tolerant control law is constructed, in which an online adaptive law is incorporated to estimate the upper boundary of the lumped uncertainties. The combined control scheme enforces the system state to reach a neighborhood of the sliding surface in the sense of the fixed‐time concept. The key feature of the resulting control scheme is that it can accommodate actuator failures under limited control torque without the knowledge of fault information. Numerical simulations are finally performed to demonstrate the effectiveness of the proposed fixed‐time controllers.     

Terminal滑模自适应控制实现一类不确定混沌系统的同步

应用Terminal滑模控制技术和选择指数趋近律来综合滑模控制器,实现一类混沌系统的状态同步．在控制器中引入一类简单的自适应律,用以在线估计界参数．该设计方案消除了滑模控制的到达阶段,状态始终保持在滑模面上,并能在有限时间内趋近于原点．与一般滑模控制同步实现相比,具有更小的同步时间和鲁棒性．通过对Duffing—Holmes系统的同步仿真,验证了该方法的可行性．     

时变终端滑模自适应有限时间控制算法

为实现非线性系统输出对期望轨迹的有限时间内精确跟踪,提出一种有限时间鲁棒控制算法。通过设计一种无到达过程的时变终端滑模面,在保证有限时间收敛的基础上,消除了传统滑模控制中固有的稳态误差,实现系统输出对期望轨迹的精确跟踪。设计了自适应更新律补偿由参数摄动导致的系统扰动,增强系统对内部未知参数摄动的鲁棒性。对比仿真结果表明:时变终端滑模控制比线性滑模控制的轨迹跟踪时间快41. 5%;线性滑模控制器下的轨迹跟踪稳态误差为0. 005,时变滑模控制器使轨迹跟踪的稳态误差降为0,实现精确跟踪。     

农用拖拉机的自适应二阶滑模路径跟踪控制

针对农用拖拉机在未知扰动影响下的路径跟踪控制问题,本文提出了基于自适应二阶滑模和扰动观测技术的路径跟踪控制策略.首先,建立含有未知扰动项的路径跟踪偏差模型,通过利用自适应控制和改进的加幂积分技术,构造自适应二阶滑模路径跟踪控制方法,该控制方法削弱了滑模控制中存在的抖振影响.其次,为了解决大扰动下控制增益调整过度的问题,通过将鲁棒精确微分器和自适应二阶滑模控制结合,构造复合的路径跟踪控制方法.严格的Lyapunov分析表明横向偏差和航向偏差均在有限时间内稳定到原点.最后,仿真结果验证了本文设计的制导方法能够保证农用拖拉机快速且稳定地跟踪上任意弯曲的参考路径.     

Robust Adaptive Fractional‐Order Terminal Sliding Mode Control for Lower‐Limb Exoskeleton

This paper introduces a robust adaptive fractional‐order non‐singular fast terminal sliding mode control (RFO‐TSM) for a lower‐limb exoskeleton system subject to unknown external disturbances and uncertainties. The referred RFO‐TSM is developed in consideration of the advantages of fractional‐order and non‐singular fast terminal sliding mode control (FONTSM): fractional‐order is used to obtain good tracking performance, while the non‐singular fast TSM is employed to achieve fast finite‐time convergence, non‐singularity and reducing chattering phenomenon in control input. In particular, an adaptive scheme is formulated with FONTSM to deal with uncertain dynamics of exoskeleton under unknown external disturbances, which makes the system robust. Moreover, an asymptotical stability analysis of the closed‐loop system is validated by Lyapunov proposition, which guarantees the sliding condition. Lastly, the efficacy of the proposed method is verified through numerical simulations in comparison with advanced and classical methods.     

防空导弹姿态控制系统终态滑模变结构设计

针对防空导弹垂直发射姿态调转时的快速性要求,研究了快速姿态调转的控制问题.首先基于一类多输入多输出高阶非线性系统的Teminal(终态)滑模变结构控制方法,对垂直发射防空导弹的滚动和俯仰、偏航通道所呈现的非线性、强耦合性进行了分析,并设计了一种新型滑模控制器.控制器设计方案消除了滑模控制的到达阶段,系统的初始状态始终保持在滑模面上,确保了系统的全局鲁棒性和稳定性,且能在有限且可控时间内使跟踪误差趋近于零.最后通过数字仿真验证了系统在不确定因素情况下具有强鲁棒性和适应性,可用于防空导弹短时间姿态调转控制.     

Two‐Layer Terminal Sliding Mode Attitude Control of Satellites Equipped with Reaction Wheels

This paper addresses the global stability and robust attitude tracking problem of a near polar orbit satellite subject to unknown disturbances and uncertainties. It is assumed that the satellite is fully actuated by a set of reaction wheels (RW) as control actuators because of their relative simplicity, versatility and high accuracy. The terminal sliding mode control (TSMC) approach is utilized in a two‐level architecture to achieve control objectives. In the lower layer a detumbling‐like controller is designed which guarantees the finite‐time detumbling and tracking of the desired angular velocities and based on this result a robust attitude tracking controller is designed in the upper layer to achieve 3‐axis attitude tracking in the presence of unknown disturbances and bounded uncertainties. Robust stability and tracking properties of designed controllers are proved using the Lyapunov theory. Finally, a set of numerical simulation results are provided to illustrate the effectiveness and performance of the proposed control method.     

利用滑模变结构控制的混沌同步控制

利用滑动模态控制研究了含有不确定性的混沌系统的同步控制问题。用极点配置和LMI方法设计的切换函数保证了带有非线性项的滑动模态混沌同步,用指数滑模到达条件给出了鲁棒混沌同步控制器设计。由于控制器的设计是基于滑动模态的不变性和线性矩阵不等式方法给出的,与常规方法相比较,给出的控制器滑动模态不受干扰的影响,系统有很好的鲁棒性和快速跟踪能力;切换函数的参数可用线性矩阵不等式求解得出,计算方便,所得结果保守性小。最后以Chen系统为例,进行了混沌同步仿真,仿真结果表明所给出的方法是有效的。     

不确定扰动分数阶混沌系统自适应Terminal滑模同步

针对带扰动不确定分数阶混沌系统的同步问题,基于自适应Terminal滑模控制,设计了一种分数阶非奇异Terminal滑模面,保证误差系统沿着滑模面在有限时间内稳定至平衡点,在系统外部扰动和不确定性的边界事先未知的情况,设计了自适应控制率,在线估计未知边界,使得同步误差轨迹能到达滑模面。最后,以三维分数阶Chen系统和四维分数阶Lorenz超混沌系统为例,利用所设计的自适应Terminal滑模控制器进行同步仿真,验证了所给方法是有效性和可行性。     

Adaptive Terminal Sliding Mode Control for Motion Tracking of a Micropositioning System

This paper presents the design of a novel adaptive terminal sliding mode controller (ATSMC) and its application to motion tracking control of a piezoelectric‐driven micropositioning system. A nonsingular terminal sliding surface is used to achieve fast and finite‐time convergence for the trajectory tracking, and also to avoid the singularity phenomenon in traditional terminal sliding mode design. An adaptive gain law is developed to update the gain of the proposed controller and to provide stable and chattering‐free control action. The stability of the control system has been demonstrated in the sense of Lyapunov. The ATSMC scheme is established based on the output feedback only, which does not require a state observer and facilitates an easy implementation. The proposed controller is implemented on a field‐programmable gate array (FPGA) platform. Comparison study with three conventional controllers has been conducted. Experimental results show the feasibility and effectiveness of the proposed control strategy.     

一类非线性互联系统的间接自适应模糊滑模跟踪控制

基于模糊逻辑逼近原理,针对非线性动态未知互联系统,设计一种新的模糊分散控制器.讨论了互联项满足或不满足一般性约束条件的两种情形,用不同方法来补偿其对大系统的影响.同时利用模式转换函数来实现间接自适应控制与模糊滑模控制之间的转换,使系统的状态在有界闭集内变化,并依据Lyapunov方法证明了闭环系统稳定,跟踪误差收敛到零的一个小邻域内.仿真结果证明所设计的模糊控制器的有效性.     

不确定混沌系统的自适应滑模变结构同步

针对一类不确定混沌系统,运用自适应滑模变结构控制方法,设计了相应的控制器和自适应律,实现了混沌系统的主从同步控制.通过构造Lyapunov函数在理论上证明了该同步方法的有效性,并且在不确定项上界未知的情况下,对系统未建模部分和噪声干扰具有很强的鲁棒性.最后以Duffing-Holmes系统为例,进行了混沌同步仿真,仿真结果表明该方法的有效性.     

欠驱动刚体航天器姿态机动滑模控制研究

针对欠驱动刚体航天器的姿态机动控制问题,提出一种滑模变结构姿态控制器的设计方法.首先给出3轴稳定的欠驱动航天器姿态动力学和运动学模型,分析其模型特点;然后,设计了欠驱动刚体航天器的渐近稳定滑模控制律,并证明了其李雅普诺夫意义下的全局渐近稳定性.最后的仿真结果表明,该方法能够有效实现欠驱动航天器的姿态控制,且系统具有全局稳定性和鲁棒性.     

Finite‐Time Sliding Mode Trajectory Tracking Control of Uncertain Mechanical Systems

The problem of finite‐time tracking control is studied for uncertain nonlinear mechanical systems. To achieve finite‐time convergence of tracking errors, a simple linear sliding surface based on polynomial reference trajectory is proposed to enable the trajectory tracking errors to converge to zero in a finite time, which is assigned arbitrarily in advance. The sliding mode control technique is employed in the development of the finite‐time controller to guarantee the excellent robustness of the closed‐loop system. The proposed sliding mode scheme eliminates the reaching phase problem, so that the closed‐loop system always holds the invariance property to parametric uncertainties and external disturbances. Lyapunov stability analysis is performed to show the global finite‐time convergence of the tracking errors. A numerical example of a rigid spacecraft attitude tracking problem demonstrates the effectiveness of the proposed controller.     

Sliding-Mode-Based Attitude Tracking Control of Spacecraft Under Reaction Wheel Uncertainties

The attitude tracking operations of an on-orbit spacecraft with degraded performance exhibited by potential actuator uncertainties (including failures and misalignments) can be extraordinarily challenging. Thus, the control law development for the attitude tracking task of spacecraft subject to actuator (namely reaction wheel) uncertainties is addressed in this paper. More specially, the attitude dynamics model of the spacecraft is firstly established under actuator failures and misalignment (without a small angle approximation operation). Then, a new non-singular sliding manifold with fixed time convergence and anti-unwinding properties is proposed, and an adaptive sliding mode control (SMC) strategy is introduced to handle actuator uncertainties, model uncertainties and external disturbances simultaneously. Among this, an explicit misalignment angles range that could be treated herein is offered. Lyapunov-based stability analyses are employed to verify that the reaching phase of the sliding manifold is completed in finite time, and the attitude tracking errors are ensured to converge to a small region of the closest equilibrium point in fixed time once the sliding manifold enters the reaching phase. Finally, the beneficial features of the designed controller are manifested via detailed numerical simulation tests.      

Attitude Control of Multiple Rigid Bodies with Uncertainties and Disturbances

Decentralized attitude synchronization and tracking control for multiple rigid bodies are investigated in this paper. In the presence of inertia uncertainties and environmental disturbances, we propose a class of decentralized adaptive sliding mode control laws. An adaptive control strategy is adopted to reject the uncertainties and disturbances. Using the Lyapunov approach and graph theory, it is shown that the control laws can guarantee a group of rigid bodies to track the desired time-varying attitude and angular velocity while maintaining attitude synchronization with other rigid bodies in the formation. Simulation examples are provided to illustrate the feasibility and advantage of the control algorithm.      

不确定非线性系统的自适应最终滑模控制──Backstepping方法(英)

对具有参数不确定与未知非线性的一类非线性系统，本文通过引入快慢两种切换线给出了一种自适应有限时间滑模控制机制．Backstepping方法被应用到设计中．此种控制机制保证了闭环系统的稳定性并使状态在有限时间内收敛到原点．仿真结果表明该控制机制的有效性．     

非匹配不确定系统的自适应反演准滑模控制

对于一类n阶非线性系统,提出一种自适应反演准滑模控制方法,控制的前n-1步采用自适应反演算法消除非匹配不确定性的影响,在最后一步,为改进跟踪效果,结合了可变边界层的思想,设计了准滑模控制方法,达到系统的n个状态快速收敛的目的.最终系统中不满足匹配条件的部分也具有较好的鲁棒性.与自适应反演线性滑模方法相比具有更好的跟踪性,理论分析证明了控制系统在削弱抖振的同时也能保证稳态精度,仿真实验证明了该方法的可行性.