Trajectory linearization control of an aerospace vehicle based on RBF neural network

An enhanced trajectory linearization control （TLC） structure based on radial basis function neural network （RBFNN） and its application on an aerospace vehicle （ASV） flight control system are presensted. The influence of unknown disturbances and uncertainties is reduced by RBFNN thanks to its approaching ability, and a robustifying itera is used to overcome the approximate error of RBFNN. The parameters adaptive adjusting laws are designed on the Lyapunov theory. The uniform ultimate boundedness of all signals of the composite closed-loop system is proved based on Lyapunov theory. Finally, the flight control system of an ASV is designed based on the proposed method. Simulation results demonstrate the effectiveness and robustness of the designed approach.

Research of robust adaptive trajectory linearization control based on T-S fuzzy system

A robust adaptive trajectory linearization control （RATLC） algorithm for a class of nonlinear systems with uncertainty and disturbance based on the T-S fuzzy system is presented. The unknown disturbance and uncertainty are estimated by the T-S fuzzy system, and a robust adaptive control law is designed by the Lyapunov theory. Irrespective of whether the dimensions of the system and the rules of the fuzzy system are large or small, there is only one parameter adjusting on line. Uniformly ultimately boundedness of all signals of the composite closed-loop system are proved by theory analysis. Finally, a numerical example is studied based on the proposed method. The simulation results demonstrate the effectiveness and robustness of the control scheme.

New trajectory linearization control for nonlinear systems undergoing harmonic disturbance

This paper presents a new trajectory linearization control scheme for a class of nonlinear systems subject to harmonic disturbance. It is supposed that the frequency of the disturbance is known, but the amplitude and the phase are unknown. A disturbance observer dynamics is constructed to estimate the harmonic disturbance, and then the estimation is used to implement a compensation control law to cancel the disturbance. By Lyapunov＇s direct method, a rigorous poof shows that the composite error of the closed-loop system can approach zero exponentially. Finally, the proposed method is illustrated by the application to control of an inverted pendulum. Compared with two existing methods, the proposed method demonstrates better performance in tracking error and response time.

Adaptive trajectory linearization control for hypersonic reentry vehicle

This paper presents an improved design for the hypersonic reentry vehicle(HRV) by the trajectory linearization control(TLC) technology for the design of HRV. The physics-based model fails to take into account the external disturbance in the flight envelope in which the stability and control derivatives prove to be nonlinear and time-varying, which is likely in turn to increase the difficulty in keeping the stability of the attitude control system. Therefore, it is of great significance to modulate the unsteady and nonlinear characteristic features of the system parameters so as to overcome the disadvantages of the conventional TLC technology that can only be valid and efficient in the cases when there may exist any minor uncertainties. It is just for this kind of necessity that we have developed a fuzzy-neural disturbance observer(FNDO) based on the B-spline to estimate such uncertainties and disturbances concerned by establishing a new dynamic system. The simulation results gained by using the aforementioned technology and the observer show that it is just due to the innovation of the adaptive trajectory linearization control(ATLC) system. Significant improvement has been realized in the performance and the robustness of the system in addition to its fault tolerance.

Quaternion-based Nonlinear Trajectory Tracking Control of a Quadrotor Unmanned Aerial Vehicle

At present, most controllers of quadrotor unmanned aerial vehicles（UAVs） use Euler angles to express attitude. These controllers suffer a singularity problem when the pitch angle is near 90°, which limits the maneuverability of the UAV. To overcome this problem, based on the quatemion attitude representation, a 6 degree of freedom（DOF） nonlinear controller of a quadrotor UAV is designed using the trajectory linearization control（TLC） method. The overall controller contains a position sub-controller and an attitude sub-controller. The two controllers regulate the translational and rotational motion of the UAV, respectively. The controller is improved by using the commanded value instead of the nominal value as the input of the inner control loop. The performance of controller is tested by simulation before and after the improvement, the results show that the improved controller is better. The proposed controller is also tested via numerical simulation and real flights and is compared with the traditional controller based on Euler angles. The test results confirm the feasibility and the robustness of the proposed nonlinear controller. The proposed controller can successfully solve the singularity problem that usually occurs in the current attitude control of UAV and it is easy to be realized.

Trajectory tracking control based on linear active disturbance rejection controller for 6-DOF robot manipulator

The trajectory tracking control for a 6-DOF robot manipulator with multiple inputs and outputs,non-linearity and strong coupling is studied.Firstly,a dynamical model for the 6-DOF robot manipulator is designed.From the view point of practical engineering,considering the model uncertainties and external disturbances,the robot manipulator is divided into 6 independent joint subsystems,and a linear active disturbance rejection controller(LADRC)is developed to track trajectory for each subsystem respectively.LADRC has few parameters that are easy to be adjusted in engineering.Linear expansion state observer(LESO)as the uncertainty observer is able to estimate the general uncertainties effectively.Eventually,the validity and robustness of the proposed method adopted in 6-DOF robot manipulator are demonstrated via numerical simulations and 6-DOF robot manipulator experiments,which is of practical value in engineering application.

基于反馈线性化的广义预测控制机械臂轨迹跟踪算法

分析了机械臂轨迹跟踪控制问题的特点,建立了二自由度机械臂动力学模型。为解决广义预测控制(generalized predictive control,GPC)算法难以适用于非线性系统的问题,在现有的GPC算法基础上,设计了基于反馈线性化的广义预测控制(feedback linearization-generalized predictive control,FL-GPC)算法框架,即底层为线性系统预测控制,非线性项使用预估值来进行代替,高层为迭代修正预估量,使用迭代计算的方式对非线性项进行预估。使用FL-GPC算法对二自由度机械臂的静态、动态轨迹跟踪任务进行了仿真。仿真结果表明,算法可以进行有效的机械臂轨迹跟踪控制。

基于SMDO-TLC的高超声速飞行器姿态控制

针对高超声速飞行器快时变、强耦合以及存在参数不确定和外部干扰情况下的姿态控制问题,同时考虑到执行机构动态和输入受限,提出了基于滑模干扰观测器-轨迹线性化(SMDO-TLC,Sliding-Mode Disturbance Observer-Trajectory Linearization Control)的高超声速姿态控制方法.首先,引入二阶线性微分器(SOLD,Second-Order Linear Differentiator)的概念,通过理论分析指出了当前TLC中采用一阶惯性+伪微分器求取输入指令的微分信号时会存在与SOLD类似的峰值现象,随后利用韩式跟踪微分器求取姿态标称指令及其微分信号,可有效解决过渡过程中执行机构饱和问题;接着,分别在姿态和角速率回路设计二阶滑模干扰观测器,利用符号函数积分来重构内外回路的复合干扰,在此基础上设计补偿控制律,以实现姿态控制器设计.仿真结果表明,所提出的方法能够克服时变干扰及气动参数大范围摄动的影响,同时兼具良好的动态特性与静态品质,能够满足高超声速飞行器的快时变、高精度以及强鲁棒的控制需求.

无人车换道轨迹与跟踪控制研究

无人车换道是自动驾驶领域的关键技术,针对无人车换道轨迹规划与跟踪控制问题,选择纯电动汽车作为研究对象,设计了一种考虑横纵向协同控制的轨迹跟踪控制器。首先,通过解耦将车辆换道简化为横向运动和纵向运动。根据路径跟踪误差动力学模型设计了线性二次型调节器路径跟踪控制器,并引入前馈控制设计了前馈-反馈LQR横向控制器,以此降低系统稳态误差。随后,考虑位置-速度误差设计了双PID纵向控制器,对车辆速度进行跟踪。选用五次多项式曲线规划换道轨迹。最后,通过Matlab和CarSim搭建联合仿真平台,对所设计的换道轨迹跟踪横纵向协同控制器进行测试研究。结果表明:在双车道换道工况下,该控制器能够较高精度地跟踪换道轨迹,车辆的距离偏差和航向角偏差最大分别为0.01 m和0.007 rad,可见具有良好的精确性和稳定性。

基于GA-PSO的智能汽车横向LQR控制器优化设计

针对线性二次型调节器(LQR)在智能汽车横向控制中,系数矩阵Q和R选取困难导致的控制精度低和参数整定效率低的问题,提出了一种遗传粒子混合优化(GA-PSO)方法。基于车辆二自由度模型设计了横向LQR控制器和前馈控制器,以该模型下控制器自身能量损失函数作为代价函数对系数矩阵进行优化,并对比了GA-PSO和粒子群优化(PSO)算法的优化效果。CarSim/Simulink联合仿真结果表明,经GA-PSO算法优化后的控制器跟踪精度和计算效率分别提高了47.06%和63.54%,且优化后的控制器具有较强的鲁棒性。

基于多胞体系统的FWID EV鲁棒加权增益调度轨迹跟踪控制

为了提高四轮独立驱动电动汽车(FWID EV)轨迹跟踪控制性能,针对车辆横向运动系统的不确定性与非线性问题,考虑转向执行机构的动态特性,提出了基于线性变参数(LPV)的鲁棒加权增益调度轨迹跟踪控制策略。首先利用凸分解技术将LPV系统转化为有限多胞顶点凸组合的多胞体系统,然后基于离线设计的每个多胞顶点控制器和线性组合在线计算任意时变参数对应的系统控制器参数,并利用MATLAB和CarSim进行联合仿真。结果表明:在加速变道场景下,所设计的控制器可以保证横向偏移误差不超过2 cm,横向偏移平均绝对误差不超过0.9 cm的较高跟踪精度及行驶稳定性和鲁棒性。

随机参数摄动下的高超声速飞行器姿态控制

针对高超声速飞行器随机参数摄动的姿态控制问题,提出一种基于轨迹线性化和扩展卡尔曼滤波(extended Kalman filter,EKF)的预测滑模控制方法。首先,针对随机参数摄动的高超声速飞行器非线性模型,采用轨迹线性化方法建立线性时变误差调节模型。通过分析参数误差的统计特性,将统计信息以参数协方差矩阵的形式进行表示,并设计EKF对受扰误差状态进行滤波。然后,采用预测滑模控制方法设计误差稳定调节器,使系统快速趋于稳定。所提方法对随机参数摄动和非线性干扰都具有强鲁棒性。仿真验证了所提方法的有效性。

篮球投篮机器人手臂运动轨迹优化方法研究

篮球投篮机器人是对投篮动作进行规划和控制的机械装置,而手臂是机器人投篮过程中的关键部位。在投篮过程中,机器人手臂易发生非可抗振动,影响机器人投篮轨迹的参数起伏较大。提出了一种篮球投篮机器人手臂运动轨迹优化控制方法。该方法建立了篮球投篮机器人手臂的运动模型和反馈模型,获取投篮机器人在运动过程中的相关数据。以此为依据采用五次多项式插值方法,结合粒子群优化算法和迭代方法,优化控制篮球投篮机器人手臂运动轨迹。实验结果表明,所提方法能够有效优化控制机器人手臂运动轨迹,在运动过程中保持轨迹的角位移、角速度、角加速度和振动响应起伏稳定。

非线性递减权值PSO优化下的LQR轨迹跟踪研究

针对二次线性调节器(LQR)权重矩阵选取困难导致的自动驾驶车辆控制精度低、系统适应度欠佳等问题,设计了一种非线性递减权值粒子群算法(NLDW-PSO)。基于二自由度车辆动力学模型,构建了横向跟踪误差模型,设计了前馈控制消除了LQR稳态误差;并设计以横向偏差、航向偏差和前轮转向角为评价函数,将系统输出误差状态量反馈至NLDW-PSO算法,所设计的非线性递减惯性权重因子通过提升粒子群体寻优性能,从而自适应调整LQR权重系数更新策略,形成闭环优化控制,最终求解得到系统目标函数极值。将所设计控制器的跟踪效果进行了对比,Carsim/Smulink联合仿真结果表明所提出NLDW-PSO优化LQR算法的跟踪控制效果最优,横向距离偏差最大值为0.076 m,横向距离偏差均值相较于固定权重系数LQR降低了69.74%,显著提高了车辆跟踪控制精度和自适应能力,且对速度变化具有较强鲁棒性。

基于OTC改进的半桥LLC变换器软启动控制

目前传统指数降频的轨迹优化控制方法有效减少了谐振电流峰值,但存在空载或轻载时输出电压超调,软启动时间长等问题。此处基于轨迹优化控制(OTC)提出了一种改进的软启动方法,解释了空载和满载下输出电压稳态调节的频率不同,引入线性补偿解决输出电压超调的问题,分析了LLC谐振变换器在启动过程中的阻抗特性和电流冲击特性,提出平方降频函数实现快速软启动。最后搭建了一台功率为185W用于半导体激光器供电电源的实验样机,验证了所提方法的可行性和有效性。实验结果表明,相比于传统指数降频的轨迹优化控制,所提出的方法在启动过程中实现了输出电压的快速响应和稳态调节。

基于模型预测控制算法的精确着舰控制方法

针对舰载机着舰过程中的航母运动、舰尾流扰动等影响,提出一种基于模型预测控制-线性二次型高斯(MPC-LQG)算法的精确着舰控制方法,开展飞机纵向通道的精确着舰控制研究。对飞机纵向动力学、舰尾流、航母运动、轨迹跟踪等,进行建模和分析。对MPC-LQG算法进行融合,以实现轨迹跟踪控制,核心思想是:模型预测控制进行航母运动补偿;设计全维状态观测,实现全状态反馈,以实现最优着舰控制。对不同的着舰情况和初始条件进行算法仿真,并与其他算法进行仿真比较。仿真结果表明,所提方法的轨迹跟踪效果很好,高度偏差0.1~0.2 m;相比传统着舰控制,所提方法动态响应快、着舰精度高。

基于线性自抗扰控制的纵向舰载机直接升力全自动着舰控制

舰载机的最终着舰过程受到强烈的舰尾流的干扰,为了抑制舰尾流扰动,本文提出一种基于径向基函数神经网络(radial basis functions neural network,RBFNN)结合线性自抗扰控制(liner active disturbance rejection control,LADRC)的创新设计方法,确保舰载机直接升力控制自动着舰系统的鲁棒性。LADRC将阵风扰动和系统不确定项作为总扰动,通过线性扩展状态观测器(liner extended state observer,LESO)对总扰动进行估计,并通过线性反馈控制律进行补偿,然后根据系统状态利用RBFNN在线调整LADRC控制器的参数,并构建Lyapunov函数以证明闭环系统的稳定性。舰载机跟踪理想下滑道的仿真结果表明,RBF-LADRC的抗干扰性、鲁棒性和跟踪精度均优于与之对比的控制方法。

基于LESO的轮式移动机器人滑模轨迹跟踪控制

针对轮式移动机器人在车轮打滑情况下的轨迹跟踪控制问题,提出了一种利用线性扩张状态观测器(Linear Extended State Observer,LESO)和积分滑模面的控制方案。首先,根据车轮打滑情况下的非完整约束条件建立轮式移动机器人的运动学模型。根据动能函数和拉格朗日方程建立其动力学模型。将这两种模型相结合得到力矩与速度相关的数学模型。其次,利用LESO对该数学模型进行扩张,并对总扰动进行估计。基于实际速度与虚拟速度之差设计带有积分项的滑模面,将扰动估计值前馈结合滑模面设计动力学控制器,并给出速度跟踪误差在有限时间内收敛的证明。最后,与基于超螺旋干扰观测器设计的控制方案仿真相比,所提出方案角速度跟踪误差在1 s左右时已趋于零,车轮力矩值稳定在3 N·m左右,且无锯齿抖动,扰动误差在1~5 s时波动更小,5~20 s时未出现明显锯齿抖动,仿真结果表明所提方案跟踪效果更好,抗干扰能力更强,观测精度更高。

采用TLC方法的超机动飞行控制系统设计

基于轨迹线性化控制(Trajectory linearization control,TLC)方法,研究了超机动飞机飞行控制系统的设计问题。首先简要介绍了TLC方法的设计思想;然后根据奇异摄动理论,将超机动飞行控制系统分成快慢两个回路,并为其分别设计了轨迹线性化控制器;最后分别用所设计的控制器和已有的动态逆控制器对某型歼击机进行了赫布斯特机动仿真。仿真结果和对比分析表明,所设计的TLC控制器是有效的,且比动态逆控制器具有更好的控制跟踪性能。

基于TLC方法的空-空导弹三维末制导律研究

针对导弹与目标之间的非线性运动学关系,在平行接近原理的基础上,结合轨迹线性化控制(TLC,trajectory linearization control)方法,为某型空-空导弹研究设计了一种新型的三维末制导律。仿真结果表明,所设计的基于TLC方法的制导律是有效的,且在目标机动情况下比传统的比例制导律以及滑模变结构制导律具有更好的制导性能。