带有干扰观测器的高超声速飞行器滑模控制

针对高超声速飞行器非线性和易受干扰影响的特点,提出了带有扩张状态干扰观测器的连续滑模控制方法.在对飞行器非线性模型做线性化处理的基础上,设计了一种连续时间滑模控制器.该控制器在对不确定性和未知动态保持鲁棒性的基础上,消除了传统滑模中存在的抖振现象.对系统中存在的外加干扰,设计了扩张状态干扰观测器.将外加干扰作为系统的一个状态变量被估计出来,再将估计值用作滑模控制器的补偿量,进而达到消除外干扰的目的.在高超声速飞行器巡航飞行状态的基础上进行了仿真.仿真结果表明,所提出的方案能够满足控制要求.     

基于ADRC的四旋翼飞行器抗干扰控制研究

近年来随着自动控制技术的飞速发展,四旋翼飞行器在军事领域和民用方面均得到了广泛应用。飞行器控制系统的抗干扰能力决定了四旋翼飞行器飞行性能的稳定性和可靠性。飞行器控制系统常采用经典PID(Proportional Integral Derivative)方法,该方法容易受到外界的干扰,增大了控制难度。本文采用自抗扰控制(Auto Disturbances Rejection Control,ADRC)算法对四旋翼飞行器模型的飞行位置和姿态进行了控制。通过与PID算法控制结果对比,可以得到以下结论:基于ADRC算法控制的四旋翼飞行器起飞1-2s后,其飞行位置、姿态、位置和姿态回路扰动均与期望值有较高的重叠性,同时飞行器的水平和空间飞行轨迹呈现出圆滑、平稳。因此,ADRC能够有效地解决飞行器的内部通道耦合和外部干扰等问题,使得四旋翼飞行器能更加方便、可靠、稳定地应用于各个领域。     

基于微分观测器的飞行模拟转台伺服系统非线性控制

飞行模拟器转台伺服系统是导弹飞行的重要模拟设备,用于获取实验数据。针对飞行模拟转台伺服系统在跟踪控制过程中存在参数不确定性、非线性摩擦等不确定性问题,提出了一种基于微分观测器的飞行模拟转台伺服系统非线性控制方法;考虑系统在跟踪控制过程中存在不确定性问题,设计了微分观测器来估计复合不确定扰动;设计非线性控制器来控制飞行模拟转台伺服系统,使得系统可以收敛到期望位置转角信号;通过李雅普洛夫稳定性证明控制器作用在系统条件下的鲁棒性;通过MATLAB/Simulink仿真试验平台验证了文中提出的控制策略能够使系统有效跟踪期望位置转角,具有一定工程应用价值;     

主动变形四旋翼自抗扰飞行控制方法

为了获得更好的环境适应性,研究设计了一种主动变形四旋翼飞行器.飞行器的变形主要分为两种:机臂伸缩和折叠.为抑制系统所受内外扰动影响,设计了基于自抗扰控制(ADRC)技术的飞行控制器.首先对主动变形四旋翼结构进行设计,使用牛顿欧拉法建立风扰下系统动力学模型,然后分析阵风对系统影响以及动态变形时重心位置、惯性张量等参数的变化,接着将主动变形四旋翼系统解耦成6个SISO系统的组合并设计位姿自抗扰控制器,最后分别利用扩张状态观测器和非线性状态误差反馈律对系统所受扰动进行观测和补偿.仿真结果表明,本文所设计的基于ADRC飞行控制器的主动变形四旋翼具有优秀的位姿控制能力,在飞行过程中可以良好地进行变形,能够有效地观测变形的扰动和紊流风扰,具有较强的稳定性和抗扰性,同时对系统部分动力失效故障有较强的鲁棒性.     

推力矢量可倾转四旋翼自抗扰飞行控制方法

针对常规四旋翼难以实现位置和姿态独立控制问题, 研究了一种具有全向推力矢量的可倾转四旋翼飞行 器系统. 为克服系统的大范围不确定性、强耦合性及外部风扰影响, 设计了基于自抗扰控制(ADRC)技术的飞行控 制器. 通过建立风扰下的系统动力学模型, 分析阵风对旋翼气动力的影响. 接着将系统解耦为六通道单回路结构并 分别设计自抗扰控制器, 引入扩张状态观测器估计系统的内外扰动, 利用非线性状态误差反馈律输出扰动补偿控 制. 在此基础上, 通过变量代换线性化控制分配矩阵, 将控制器输出直接映射到旋翼转速和倾转角. 仿真结果表明, 所设计的自抗扰飞行控制器具有良好的位置和姿态独立控制能力, 能够有效地估计和补偿紊流风扰动, 同时对系统 的部分动力失效故障有较强的鲁棒性.     

Altitude control for flexible wing unmanned aerial vehicle based on active disturbance rejection control and feedforward compensation

For achieving the accurate trajectory tracking of the flexible wing unmanned aerial vehicle in the complicated missions, especially the vertical component, a feedforward compensation unit–based active disturbance rejection control (ADRC) is proposed. In ADRC, the internal dynamics and complicated influence of the total disturbance will be estimated and dynamically compensated by extended state observer (ESO). It puts a very high request on the observation ability of ESO with the unpredictable external disturbance, complex internal coupling influence, and the strong nonlinear characteristic of the proposed system. For this reason, by deeply analyzing the model of this system, the varying attitude influence on the altitude control will be deduced. Then, this influence will be compensated previously by a feedforward compensation unit. Through the previous compensation of the calculable part of the internal dynamics and total disturbance, the burden of ESO can be reduced largely. In this way, it improves the control effect of the ADRC with better observation precision of ESO. After that, based on the hardware‐in‐the‐loop simulation, the effectiveness of the proposed method is verified completely with the complicated flight missions. The robustness of the control effect and observation ability of ESO are also verified by the Monte Carlo simulation. At last, the results of actual flight experiment prove the advancement and practicability of the proposed ADRC method.     

基于扩张状态观测器的车辆横摆稳定模型预测控制器设计

针对车辆横摆稳定性控制问题,本文提出一种基于扩张状态观测器的线性模型预测控制器设计方法.首先,将非线性车辆模型线性化,建立带有模型误差干扰项的线性模型,其中线性化导致的模型误差采用扩张状态观测器估计得到,并证明了观测器的稳定性.然后基于此模型设计线性预测控制器,近似实现了非线性预测控制器的控制效果,同时降低了计算量.最后,通过不同路况下的仿真实验结果,验证了所提方法的计算性能和控制效果.     

Sliding mode disturbance observer-based backstepping control for a transport aircraft

This paper presents a novel control method by integrating the sliding mode disturbance observer- based control and the backstepping control technique, and successfully applies it to a flight control system for heavy cargo airdrop operations. The super-twisting second order sliding mode disturbance observer （SOSMDO） is employed to estimate bounded but otherwise arbitrary disturbances, thus ensuring asymptotic convergence of the estimation error to zero in a finite time. Besides, the integrated controller can significantly improve the robustness of the flight control system to modeling uncertainty and external disturbance in the presence of state/control constraints. The closed-loop stability is guaranteed in the sense of Lyapunov. In addition, the proposed approach can considerably reduce design cycles. The performance of the proposed control method is demonstrated in a very low altitude extraction airdrop simulation with a high-fidelity six-degree-of-freedom transport aircraft model.     

Disturbance Decoupling Control for Flexible Air‐Breathing Hypersonic Vehicles with Mismatched Condition

The disturbance decoupling control method is investigated for flight control of a flexible air‐breathing hypersonic vehicle (FAHV). First, the longitudinal dynamics of the FAHV are simplified into nonlinear forms with mismatched system disturbances. Then a new nonlinear disturbance observer base on hyperbolic sine function is applied to estimate the mismatched disturbances. The disturbance decoupling control law for flight control of FAHV is deduced theoretically and its proof is provided. Finally, the stability of the closed‐loop control system under the action of disturbance decoupling control law is proved by Lyapunov stability theory. Simulation results exhibit the performance and effectiveness of the proposed disturbance decoupling control law.     

Direct self-repairing control for a helicopter via quantum multi-model and disturbance observer

In this paper, a new direct self-repairing control scheme is developed for a helicopter flight control system with unknown actuator faults and external disturbance. The design of multi-model-based adaptive control is used to accommodate the faulty system under different fault conditions. By appropriate switching based on quantum information technique, the system can be converted to the best model and the corresponding controller. Asymptotic model following performance and system stability is guaranteed. A disturbance observer is introduced to observe the disturbance of the system, which can produce corresponding control signals according to the disturbance. The results including a numerical simulation and a semi-physical verification demonstrate the effectiveness of the proposed self-repairing control approach for the helicopter flight control system.     

Vibration control of vehicle active suspension system using a new robust neural network control system

The main problem of vehicle vibration comes from road roughness. For that reason, it is necessary to control vibration of vehicle’s suspension by using a robust artificial neural network control system scheme. Neural network based robust control system is designed to control vibration of vehicle’s suspensions for full suspension system. Moreover, the full vehicle system has seven degrees of freedom on the vertical direction of vehicle’s chassis, on the angular variation around X-axis and on the angular variation around Y-axis. The proposed control system is consisted of a robust controller, a neural controller, a model neural network of vehicle’s suspension system. On the other hand, standard PID controller is also used to control whole vehicle’s suspension system for comparison.Consequently, random road roughnesses are used as disturbance of control system. The simulation results are indicated that the proposed control system has superior performance at adapting random road disturbance for vehicle’s suspension.     

无级变速汽车的自适应模糊控制研究

为提高无级变速汽车控制系统对外界负荷扰动和各种运行工况的自适应能力,本文在简单的无级变速系统模型的基础上,设计了无级变速汽车的自适应模糊控制系统.所设计的自适应模糊控制系统由参数自调节油门模糊控制器和混合型模糊-PID的无级变速器速比和制动控制器构成,该控制系统只与汽车的瞬时运行状态有关而与汽车的参数无关,因此它对不确定的汽车参数和外界负荷的扰动具有良好的鲁棒性.仿真结果表明所设计的模糊控制系统具有良好的自适应能力.     

高超声速飞行器飞行轨迹的模糊控制设计

针对高超声速飞行器飞行过程中因干扰造成的飞行轨迹散布问题,提出了采用飞行器飞行轨迹的模糊控制设计方法。方法以高超声速飞行器飞行轨迹线偏差和线偏差变化率作为模糊控制器输入,采用模糊推理设计飞行控制系统。在完成高超声速飞行轨迹控制系统数学建模的基础上,结合自动驾驶仪特点对飞行轨迹模糊控制系统进行了设计。结论通过仿真表明所设计的飞行控制系统满足飞行轨迹及攻角性能要求,验证了方法的正确性。     

Flexible modelling and altitude control for powered parafoil system based on active disturbance rejection control

For the accurate altitude control of the powered parafoil system, a novel modelling method and control methodology are designed in this paper. Firstly, based on computational fluid dynamics, the proposed model can accurately simulate the actual flight state of the powered parafoil system. Then, the double closed-loop controller based on active disturbance rejection control is designed. With this methodology, the precise altitude control can be realised. By analysing the theory of active disturbance rejection control, the proposed control method will be stable and valid. At last, after the detailed verification in the hardware-in-the-loop simulations, the flight experiment is carried out. After the simulation with the proposed model, the adjusted controller parameters can be applied directly in the actual experiment. The results show that the proposed method can provide effective guidance to the flight experiment. It also proves the validity and effectiveness of the proposed modelling and control method.     

基于有限时间预设性能的高超声速飞行器反演控制

针对存在参数不确定以及外界干扰的高超声速飞行器跟踪性能问题,提出一种基于有限时间预设性能的反演控制方案.首先,为便于控制器设计,将高超声速飞行器模型划分为速度和高度子系统,针对子系统分别设计预设性能控制器以提高系统的瞬态和稳态性能;然后,通过设计一种有限时间性能函数,使得跟踪误差能够在预设时间内收敛至稳态值;接着,考虑到反演设计中虚拟指令导数难以获取以及干扰项对系统的影响,基于干扰观测器提出一种扰动估计方法,目的是在取得良好的观测扰动效果的同时,使得控制器设计流程简化、复杂度降低;最后,基于Lyapunov稳定理论证明系统的跟踪误差最终一致有界,并通过仿真验证该方法的有效性.     

An adaptive vision-based autopilot for mini flying machines guidance,navigation and control

The design of reliable navigation and control systems for Unmanned Aerial Vehicles (UAVs) based only on visual cues and inertial data has many unsolved challenging problems, ranging from hardware and software development to pure control-theoretical issues. This paper addresses these issues by developing and implementing an adaptive vision-based autopilot for navigation and control of small and mini rotorcraft UAVs. The proposed autopilot includes a Visual Odometer (VO) for navigation in GPS-denied environments and a nonlinear control system for flight control and target tracking. The VO estimates the rotorcraft ego-motion by identifying and tracking visual features in the environment, using a single camera mounted on-board the vehicle. The VO has been augmented by an adaptive mechanism that fuses optic flow and inertial measurements to determine the range and to recover the 3D position and velocity of the vehicle. The adaptive VO pose estimates are then exploited by a nonlinear hierarchical controller for achieving various navigational tasks such as take-off, landing, hovering, trajectory tracking, target tracking, etc. Furthermore, the asymptotic stability of the entire closed-loop system has been established using systems in cascade and adaptive control theories. Experimental flight test data over various ranges of the flight envelope illustrate that the proposed vision-based autopilot performs well and allows a mini rotorcraft UAV to achieve autonomously advanced flight behaviours by using vision.     

自主式水下航行器三维路径跟踪的神经网络H∞鲁棒自适应控制方法

本文研究了存在模型不确定以及外界未知扰动情况下的自主式水下航行器(AUV)的三维路径跟踪控制问题. 针对此问题, 首先利用时标分离原理及正交投影Serret-Frenet坐标系建立了描述AUV质心运动及姿态运动的的仿射非线性数学模型. 其次, 在控制器设计中运用神经网络H∞鲁棒自适应算法克服了模型的不确定性及扰动, 同时在控制器设计中利用了主导输入的思想, 降低了闭环系统的复杂度, 减少了实时计算工作量, 便于工程应用. 基于Lyapunov理论的分析保证了系统的稳定性. 仿真结果表明, 路径跟踪控制律可以保证AUV沿期望路径运动, 并且具有良好的动态性能.     

Adaptive dynamic surface control of a hypersonic flight vehicle with improved tracking

This work presents a nonlinear adaptive dynamic surface air speed and a flight path angle control design procedure for the longitudinal dynamics of a generic hypersonic flight vehicle. The proposed design scheme takes into account the magnitude, rate, and bandwidth constraints on the actuator signals. A new approach is used to enhance tracking performance and avoid a large initial control signal. The uncertain nonlinear functions in the flight vehicle model are approximated by using radial basis function neural networks. A detailed stability analysis of the designed controllers shows that all the signals of the closed‐loop system are uniformly ultimately bounded. The robust performance of the design scheme is verified through numerical simulations of the flight vehicle model for various parameter variation test cases. Copyright © 2011 John Wiley and Sons Asia Pte Ltd and Chinese Automatic Control Society     

基于反步法的高超音速飞机纵向逆飞行控制

针对高超音速飞机纵向运动的数学模型具有严重非线性、不稳定、多变量耦合以及不确定的气动参数等特点,采用非线性动态逆控制与反步法相结合的方法为其设计飞行控制系统．该系统以非线性动态逆控制作为控制内环,通过将非线性的多输入多输出系统进行精确线性化,解除了多变量之间的强耦合关系;并以反步法作为控制外环．保证系统的全局稳定以及抑制不确定参数的扰动．仿真研究表明．所提出的控制方法可以确保高超音速飞机的纵向稳定性．改善其飞行品质．