四旋翼飞行器非线性轨迹跟踪控制

针对四旋翼飞行器在复杂飞行条件下速度不可测的轨迹跟踪控制问题,考虑系统存在外界未知干扰和模型参数不确定的情况,提出了一种基于扩张观测器的轨迹跟踪控制方法。该方法设计了积分型反步法跟踪控制器,以降低系统的稳态误差,并引入了状态扩张观测器,来估计系统未知速度信息,同时对干扰和模型参数不确定因素进行实时估计并给予补偿;最后,选取李雅普诺夫函数证明了该控制系统的稳定性。以Quanser公司的Qball2四旋翼飞行器为研究对象和飞行实验平台,对所设计的控制器进行验证。实验结果表明,本文所设计的基于扩张观测器的轨迹跟踪控制器,能够有效地估计轨迹跟踪控制过程中的未知速度信息,解决外界未知干扰和模型参数不确定的问题,增强对环境的适应能力,有效提高了飞行器对未知干扰的鲁棒性和轨迹跟踪控制的精确性。     

四旋翼飞行器的滑模PID轨迹跟踪控制

针对传统PID在四旋翼飞行器轨迹跟踪控制方面存在的精度不高、鲁棒性差等不足,提出了一种滑模PID算法。并根据建立的四旋翼欧拉-庞卡莱动力学模型,设计滑模PID轨迹跟踪控制器。与传统PID算法相比,该算法通过选取PID滑模面,有效地提高系统的响应速度以及抗干扰的能力。通过MATLAB/Simulink,在不同条件下,分别对滑模PID和传统PID算法设计的控制系统进行仿真。仿真结果表明,该算法能够更为精确地跟踪期望轨迹,同时具有响应时间短,超调量小,鲁棒性强等优点。     

四旋翼飞行器轨迹跟踪控制器的设计与验证

为了解决四旋翼飞行器在外界扰动影响和系统模型参数存在不确定性情况下的精确轨迹跟踪控制问题,设计并验证了一种四旋翼飞行器的非线性轨迹跟踪控制器。首先建立了考虑执行机构特性的四旋翼飞行器数学模型,并将虚拟控制量映射到了实际中对电机的控制;然后通过在反步法轨迹跟踪控制中加入积分项,设计了一种基于积分型反步法的非线性轨迹跟踪控制器,消除模型参数不确定性及外界干扰引起的误差,仿真结果验证了该方法的可行性;最后,利用QBall2四旋翼飞行实验平台,对所设计的非线性轨迹跟踪控制器进行验证,实际飞行实验结果表明了所设计控制器的有效性,提高了实际飞行过程中外界干扰和不确定性下的四旋翼飞行器轨迹跟踪控制的精度。     

基于积分滑模的四轮移动机器人轨迹跟踪控制

针对一类具有有界扰动和不确定性的四轮移动机器人轨迹跟踪问题,提出了一种具有鲁棒性的积分滑模控制策略.首先,提出了四轮移动机器人的运动学和动力学模型,推导出机器人轨迹跟踪误差表示式.然后分别针对机器人的运动学模型和动力学模型给出了相应的运动算法和积分滑模控制律.通过Lyapunov稳定性理论证明了四轮移动机器人轨迹跟踪误...     

基于Simscape的四旋翼无人机建模与仿真

为了加速并简化四旋翼无人机的设计以及进行相关控制算法的实验仿真和验证,针对四旋翼飞行器的机械结构和飞行原理分析了其系统动力学模型,利用牛顿-欧拉方法推导得到机体非线性动力学方程。为了提高四轴飞行器的建模精度和系统完整性,联合计算机辅助设计(CAD)软件和Matlab/Simscape工具箱进行物理系统建模。利用CAD软件搭建的四旋翼三维实体模型导入到Simscape仿真平台构建四旋翼的机体以及动力系统模型,并在此基础上将Simulink设计的控制算法添加到仿真平台,方便进行实验验证和参数整定。仿真结果表明,所设计的飞行器能够较好地实现悬停和轨迹跟踪,满足系统的控制性能要求。     

基于干扰观测器的无人机固定时间位姿一体化控制方法

针对存在外部干扰的倾转四旋翼无人机飞行控制问题,提出一种基于干扰观测器和积分终端滑模的固定时间六自由度位姿一体化控制方法。首先,利用对偶四元数建立了倾转四旋翼无人机六自由度飞行控制系统模型。继而,利用固定时间干扰观测器实时估计的外部扰动信息,设计一种基于积分终端滑模的固定时间控制方案,实现无人机的轨迹跟踪控制,并通过Lyapunov理论分析闭环控制系统的固定时间收敛性能。最后,数值仿真结果验证了该控制方法的有效性与正确性。     

纵向打滑状态下轮式移动机器人轨迹跟踪控制

针对轮式移动机器人纵向打滑状态下滑动参数未知的轨迹跟踪控制问题,提出了一种轨迹跟踪控制方法。建立了纵向打滑状态下移动机器人的运动学模型,用滑动 参数表示左右轮的打滑程度;设计合适的滑模观测器对未知的滑动参数进行估计,并通过低通滤波器减少抖振对估计结果产生的影响;基于Lyapunov直接法设计轨迹跟踪控制律,并提出了一种根据控制系统的极点分布确定控制参数的方法。仿真结果验证了所提方法的准确性和有效性。     

挖掘机基于干扰观测器的滑模控制

针对挖掘机工作装置的参数不确定和存在干扰的问题,将滑模控制用于挖掘机工作装置的轨迹跟踪控制中。为了削弱滑模控制中存在的抖振,设计了干扰观测器,对干扰项进行有效估计以降低滑模控制中的切换增益。利用Matlab／Simulink工具箱对所设计的控制器进行了仿真,给出了基于干扰观测器的滑模控制的跟踪性能及误差。     

基于事件触发和扩展状态观测器的液压位置跟踪系统控制研究

基于网络控制技术的液压控制系统具有远程控制、模块化、资源共享等优点。然而,液压控制系统本身具有强非线性和参数不确定性等特点,结合网络控制系统具有的通信带宽受限等问题,导致控制效果不好而限制了应用。针对以上问题,提出一种具有事件触发机制和扩展状态观测器(Extended state observer, ESO)的自适应鲁棒控制策略。通过引入事件触发机制过滤大量的冗余数据,提高通信带宽的利用率。基于模型设计出一种扩展状态观测器,同时对速度值和不匹配外干扰进行估计。通过自适应算法在线估计液压控制系统的不确定参数。通过Lyapunov稳定性理论分析闭环系统的全局稳定性。试验表明所设计的算法在减少了大量数据传输量的同时,具有良好的位置跟踪控制性能。     

基于视觉的小型四旋翼无人机自主飞行控制

提出为实现小型四旋翼无人机自主飞行控制,设计一种基于视觉的飞行控制方法,并搭建嵌入式控制架构飞行试验平台。在控制过程中,光流信息与姿态角信息进行融合用于估计无人机水平位置信息,利用获取到的水平位置信息作为内外环结构的比例微分积分(Proportion integration differentiation,PID)控制器外环反馈信息。不同于传统的基于地面站的控制架构试验平台,该飞行系统中采用了一个嵌入式控制架构的试验平台。该平台依靠机载嵌入计算机进行光流计算、运动状态估计,并采用机载飞行控制器执行控制算法。这种嵌入式控制架构工程实现难度高,但更利于实现四旋翼无人机的全自主飞行控制。试验结果表明,提出的设计方法取得了较好全自主飞行控制效果。     

Hybrid finite-time trajectory tracking control of a quadrotor

In this paper, accurate trajectory tracking control problem of a quadrotor with unknown dynamics and disturbances is addressed by devising a hybrid finite-time control (HFTC) approach. An adaptive integral sliding mode (AISM) control law is proposed for altitude subsystem of the quadrotor, whereby underactuated characteristics can decoupled. Backstepping technique is further deployed to control the horizontal position subsystem. To exactly attenuate external disturbances, a finite-time disturbance observer (FDO) combining with nonsingular terminal sliding mode (NTSM) control strategy is constructed for attitude subsystem, and thereby achieve finite-time stability. Using the compounded control scheme, trajectory tracking errors can be stabilized rapidly. Simulation results and comprehensive comparisons show that the proposed HFTC scheme has remarkably superior performance.     

Robust guaranteed cost tracking control of quadrotor UAV with uncertainties

In this paper, a robust guaranteed cost controller (RGCC) is proposed for quadrotor UAV system with uncertainties to address set-point tracking problem. A sufficient condition of the existence for RGCC is derived by Lyapunov stability theorem. The designed RGCC not only guarantees the whole closed-loop system asymptotically stable but also makes the quadratic performance level built for the closed-loop system have an upper bound irrespective to all admissible parameter uncertainties. Then, an optimal robust guaranteed cost controller is developed to minimize the upper bound of performance level. Simulation results verify the presented control algorithms possess small overshoot and short setting time, with which the quadrotor has ability to perform set-point tracking task well.     

Composite disturbance rejection control based on generalized extended state observer

Traditional extended state observer (ESO) design method does not focus on analysis of system reconstruction strategy. The prior information of the controlled system cannot be used for ESO implementation to improve the control accuracy. In this paper, composite disturbance rejection control strategy is proposed based on generalized ESO. First, the disturbance rejection performance of traditional ESO is analyzed to show the essence of the reconstruction strategy. Then, the system is reconstructed based on the equivalent disturbance model. The generalized ESO is proposed based on the reconstructed model, while convergence of the proposed ESO is analyzed along with the outer loop feedback controller. Simulation results on a second order mechanical system show that the proposed generalized ESO can deal with the external disturbance with known model successfully. Experiment of attitude tracking task on an aircraft is also carried out to show the effectiveness of the proposed method.     

基于滑模和扩张状态观测器的双绕组无轴承磁通 切换电机转子悬浮控制策略研究

双绕组无轴承磁通切换电机是非线性多变量的复杂对象,传统的转速PI与径向位移PI控制存在超调大,系统易受外界扰动影响等缺点。基于滑模变结构控制思想,提出一种转子径向位移滑模控制策略。针对滑模控制中存在建模不准确,以及转子动力学模型中存在陀螺效应等问题,通过建立一种扩张状态观测器对系统扰动进行观测,并在滑模控制基础上加入扰动前馈补偿,设计出一种径向位移滑模控制与扩张状态观测器的复合控制策略。实验结果表明,所提径向位移滑模控制相比传统PI控制具有响应速度快、径向位移脉动小、抗负载扰动性强等优点。所提径向位移滑模与扩张状态观测器的复合控制策略,相比于径向位移滑模控制可有效减小转子径向位移脉动约30%,进一步增强了系统的鲁棒性。     

Robust partial integrated guidance and control for missiles via extended state observer

A novel extended state observer (ESO) based control is proposed for a class of nonlinear systems subject to multiple uncertainties, and then applied to partial integrated guidance and control (PIGC) design for a missile. The proposed control strategy incorporates both an ESO and an adaptive sliding mode control law. The multiple uncertainties are treated as an extended state of the plant, and then estimate them using the ESO and compensate for them in the control action, in real time. Based on the output of the ESO, the resulting adaptive sliding mode control law is inherently continuous and differentiable. Strict proof is given to show that the estimation error of the ESO can be arbitrarily small in a finite time. In addition, the adaptive sliding mode control law can achieve finite time convergence to a neighborhood of the origin, and the accurate expression of the convergent region is given. Finally, simulations are conducted on the planar missile–target engagement geometry. The effectiveness of the proposed control strategy in enhanced interception performance and improved robustness against multiple uncertainties are demonstrated.     

基于扩张状态观测器的故障诊断方法研究

在分析现有基于观测器故障诊断方法的基础上,提出基于扩张状态观测器(ESO)故障诊断新方法.该方法利用ESO估计出系统的动态特性,完成对动态系统的故障检测与识别,同时,由于ESO只依赖于系统的输入参数b.和观测器的整定参数ω,因而具有很强的鲁棒性.最后,借助于三水箱非线性动态系统验证了算法的有效性.     

Second order sliding mode control for a quadrotor UAV

A method based on second order sliding mode control (2-SMC) is proposed to design controllers for a small quadrotor UAV. For the switching sliding manifold design, the selection of the coefficients of the switching sliding manifold is in general a sophisticated issue because the coefficients are nonlinear. In this work, in order to perform the position and attitude tracking control of the quadrotor perfectly, the dynamical model of the quadrotor is divided into two subsystems, i.e., a fully actuated subsystem and an underactuated subsystem. For the former, a sliding manifold is defined by combining the position and velocity tracking errors of one state variable, i.e., the sliding manifold has two coefficients. For the latter, a sliding manifold is constructed via a linear combination of position and velocity tracking errors of two state variables, i.e., the sliding manifold has four coefficients. In order to further obtain the nonlinear coefficients of the sliding manifold, Hurwitz stability analysis is used to the solving process. In addition, the flight controllers are derived by using Lyapunov theory, which guarantees that all system state trajectories reach and stay on the sliding surfaces. Extensive simulation results are given to illustrate the effectiveness of the proposed control method.     

Sliding mode based trajectory linearization control for hypersonic reentry vehicle via extended disturbance observer

This paper proposes a novel hybrid control framework by combing observer-based sliding mode control (SMC) with trajectory linearization control (TLC) for hypersonic reentry vehicle (HRV) attitude tracking problem. First, fewer control consumption is achieved using nonlinear tracking differentiator (TD) in the attitude loop. Second, a novel SMC that employs extended disturbance observer (EDO) to counteract the effect of uncertainties using a new sliding surface which includes the estimation error is integrated to address the tracking error stabilization issues in the attitude and angular rate loop, respectively. In addition, new results associated with EDO are examined in terms of dynamic response and noise-tolerant performance, as well as estimation accuracy. The key feature of the proposed compound control approach is that chattering free tracking performance with high accuracy can be ensured for HRV in the presence of multiple uncertainties under control constraints. Based on finite time convergence stability theory, the stability of the resulting closed-loop system is well established. Also, comparisons and extensive simulation results are presented to demonstrate the effectiveness of the control strategy.