飞行制导控制一体化设计方法综述

从系统模型和控制设计方法两个方面综述了飞行器制导控制一体化设计方法的研究现状. 论述了制导控制一体化设计中的关键问题, 即系统具有较高的阶数和系统存在大量不确定性. 提出了基于自抗扰控制的三维制导控制一体化设计方法. 该控制方法具有简明的线性结构, 并且可以对飞行控制系统中的非线性时变不确定性进行实时估计和补偿. 仿真结果表明该方法可以对付大范围的不确定性, 具有很好的鲁棒性.     

碟形飞行器的广义预测控制方法研究

研究飞行器机动飞行优化控制,针对碟形飞行器复合控制系统是一个高度非线性的多输入系统,为了提高飞行器动态特性,通过对碟形飞行器所受合外力和力矩的分析并根据纵向运动假设得到碟形飞行器纵向运动简化方程,进行小偏差线性化得到纵向通道变质量矩/推力矢量复合控制线性化方程.由于线性系统是静不稳定的并且是非最小相位系统,传统的控制方法无法直接使用,针对碟形飞行器变质量矩/推力矢量复合控制系统,设计了可以处理这类问题的广义预测控制器并进行了仿真,结果与 PD 控制的仿真结果进行了对比,结果表明广义预测控制可以提升系统的响应速度,为设计提供了参考依据.     

一种多旋翼飞行器的设计及实验验证

传统多旋翼机具有欠驱动特性,且平移、旋转运动均存在强耦合,极大地限制了飞行器的机动性能．为此本文设计了一种具备全向运动、推力矢量控制飞行、倾转悬停功能的多旋翼飞行器．该飞行器结构为正四面体,4个倾转旋翼模组分别固定于该四面体的4个顶点．每个倾转旋翼模组能够提供矢量推力,从结构上实现了飞行器姿态控制和位置控制的解耦,使得飞行器能够实现3维空间中全姿态的轨迹跟踪．为避免欧拉角控制产生的奇异性,设计了基于四元数的姿态控制器．利用可控性原理分析了旋翼发生故障时飞行器的可控性,证明了相比传统飞行器它具有更高的容错性．样机实验测试了该飞行器的大角度复杂机动动作以及推力矢量控制飞行能力,可实现最大70°的倾转悬停．实验结果表明,该飞行器相比于传统的四旋翼飞行器具备更高的机动性．     

基于变结构控制碟形飞行器复合控制方法研究

针对多输入系统的自由递阶变结构控制方法对碟形飞行器的复合控制问题进行了研究,问题在于如何协调执行机构之间的关系.为了优化系统的稳定性,通过对碟形飞行器所受合外力和力矩的分析可以得到碟形飞行器动质心运动动力学方程、动质心运动学方程、绕动质心转动的动力学和运动学方程、以及角度关系方程等数学模型,再进行小偏差线性化,得到纵向通道变质量矩/推力矢量复合控制线性化方程.其次,针对碟形飞行器变质量矩/推力矢量复合控制系统,设计了关于双输入系统的自由递阶变结构控制器,并进行了仿真.结果证明,与传统的PD控制器的仿真结果进行了对比.自由递阶变结构控制器对于正弦波的跟踪效果更好.     

双桨倾转旋翼飞行器的最优飞行控制

对最新发展的双发倾转旋翼飞行器进行了研究,建立了旋翼飞行器推力矢量控制系统的数学模型,得到了两个最优飞行控制定理.由这两个定理建立了最优起飞巡航飞行轨迹.分析结果表明,该飞行器具有节约动力能源,机动性好和多用途等优点.计算机仿真证实了飞行控制系统的最优性和有效性.     

基于模糊不确定观测器的四旋翼飞行器自适应动态面轨迹跟踪控制

针对具有未知外界扰动和系统不确定性的四旋翼飞行器,提出了一种基于模糊不确定观测器（Fuzzy uncertainty observer,FUO）的自适应动态面轨迹跟踪控制方法.通过将四旋翼飞行器系统分解为位置、姿态角和角速率三个动态子系统,使得各子系统虚拟控制器能够充分考虑欠驱动约束;采用一阶低通滤波器重构虚拟控制信号及其一阶导数,实现四旋翼跟踪控制设计的迭代解耦;设计了一种模糊不确定观测器,用以估计和补偿未知外界扰动与系统不确定性,从而确保闭环系统的稳定性和跟踪误差与其他系统信号的一致有界性.仿真研究验证了所提出的控制方法的有效性和优越性.     

一种基于Daisy-chain的推力矢量协调控制方法

推力矢量技术作为先进战斗机最重要的技术之一,可以大大提高飞机可控迎角的范围,增强战斗机的过失速机动能力.然而目前我国可借鉴国外重要机型推力矢量技术的实现是通过在驾驶舱中增加相应的矢量操纵机构实现的,在很大程度上增加了飞行员的驾驶负担.如何取消该操纵机构并将其对于推力矢量的控制综合协调进飞控系统中,以减轻操作负担,成为一个亟待解决的重要问题.现提出了一种基于Daisy-chain分配、动态逆控制的推力矢量协调控制方法.方法 基于模块化的控制-分配设计思想,采用链式分配与非线性反馈线性化的方法,能够将推力矢量控制融合到阻尼增稳系统中去,并实现对矢量操纵面与气动操纵的协调控制,因而能取消推力矢量操纵机构,减轻了飞行员的工作负担.仿真结果表明,上述方法能有效地实现推力矢量的协调控制,并且基于Daisy-chain的设计方法还实现了最小推力矢量控制,因而有效降低飞机操控对于推力矢量机构的工作负担,减少发动机的维护成本.     

基于非线性干扰观测器的高超声速飞行器滑模反演控制

针对高超声速飞行器非线性、强耦合和参数不确定弹性体模型,提出了一种基于非线性干扰观测器的滑模反演控制方法.将飞行器曲线拟合模型分解为速度子系统和高度相关子系统并表示为严格反馈形式,分别采用滑模和反演方法设计实际控制量与虚拟控制量.采用1阶低通滤波器获取虚拟控制量的导数,解决了传统反演控制方法"微分项膨胀"问题.基于改进滑模微分器设计了一种新型非线性干扰观测器,以此对模型不确定项进行估计和补偿.仿真结果表明,该控制器对模型不确定性和气动弹性影响具有鲁棒性,且实现了对速度和高度参考输入的稳定跟踪.     

四旋翼飞行器自适应动态面轨迹跟踪控制

针对具有未知外界扰动和系统不确定性集总未知非线性的四旋翼飞行器,提出了一种采用自适应不确定性补偿器的自适应动态面轨迹跟踪方法.通过将四旋翼飞行器系统分解为位置、欧拉角和角速率3个动态子系统,使各子系统虚拟控制器设计能充分考虑欠驱动约束;结合动态面控制技术,通过采用一阶低通滤波器,避免对虚拟控制信号求导;进而设计自适应不确定性补偿器,处理未知外界扰动和系统不确定性,最终确保闭环控制系统的稳定性、跟踪误差一致最终有界和系统所有状态信号有界.仿真研究和实验结果验证了本文提出控制方法的有效性和优越性.     

基于参数依赖滚动时域H∞控制的高超声速飞行器控制

针对输入受限的高超声速飞行器强耦合、强非线性以及严重不确定性的特点,提出一种参数依赖滚动时域?∞控制(PD-RHHC)的方法.首先在考虑控制输入约束的条件下,引入参数依赖Lyapunov函数和松弛因子并提出了基于LMI优化的PD-RHHC;然后采用函数替换方法,结合张量积模型转换方法实现高超声速飞行器(HSV)纵向非线性弹性模型的LPV描述,并将PD-RHHC应用到高超声速飞行器纵向控制中,以实现HSV在大飞行包线内的机动飞行;最后通过仿真实验验证了所提出算法的有效性.     

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.     

Virtual control strategy and conditioning technique for tracking and learning controls under input restrictions

The virtual control strategy for mechanical systems has been recently proposed (Gnucci and Marino, 2021) in the context of under-actuated mechanical systems. Such a strategy views and represents an under-actuated mechanical system as a fully actuated system with virtually added inputs and outputs having to satisfy, through a suitable choice of the virtual output reference signals, the virtual input zero-equality constraint: the related adaptive tracking control problem is then solved through standard design techniques. This paper exhibits a twofold aim. The first one is: to enlarge the concept of zero-input constraint and thus naturally adapt the virtual control approach to the case in which an actuator fault can occur. The second aim is: to show how the application and transposition of such an adaptation to two well-known classes of nonlinear systems (special systems in multi-variable tracking form with two inputs and outputs under actuator faults; one-relative-degree, single-input, single-output systems in output feedback form under input saturation) not only own strong connections with the conditioning technique, originally conceived in the context of anti-windup problems under input constraints, but they also gain original results.     

Fault-tolerant control strategy for multicylinder hydraulic press machine based on dynamic control allocation and adjustable multiobjective optimization

A hierarchical controller is proposed for achieving high-accuracy control and the dynamic balance with the presence of multiple faults of actuator, the external disturbance, and the model uncertainties in multicylinder hydraulic press machine (MCHPM). The method divides the controller design into three steps: Virtual fault-tolerant control law, control allocation algorithm, and actuator control law, which are progressive. First, to precisely compensate the lumped disturbances including the multiple faults of actuator, the external disturbance, and the model uncertainties, a disturbance observer (DO) is developed. By combining the observer with the sliding mode control (SMC), a virtual fault-tolerant control law is designed. Second, a highly integrated control allocation algorithm for the virtual fault-tolerant control law is proposed to get the desired driving force, taking into account dynamic control allocation (DCA), multiobjective optimization (MOO) and Analytic Hierarchy Process (AHP) simultaneously. Third, taking the driving force obtained from above control allocation algorithm as the desired target, the control law of each cylinder is calculated. The global stability for the whole system is proved by the Lyapunov theory. Lastly, results of simulation and experiment show that the proposed controller can effectively handle different faults and have more superior control performance.     

Robust control approach for input–output linearizable nonlinear systems using high‐gain disturbance observer

This paper addresses a robust control approach for a class of input–output linearizable nonlinear systems with uncertainties and modeling errors considered as unknown inputs. As known, the exact feedback linearization method can be applied to control input–output linearizable nonlinear systems, if all the states are available and modeling errors are negligible. The mentioned two prerequisites denote important problems in the field of classical nonlinear control. The solution approach developed in this contribution is using disturbance rejection by applying feedback of the uncertainties and modeling errors estimated by a specific high‐gain disturbance observer as unknown inputs. At the same time, the nonmeasured states can be calculated from the estimation of the transformed system states. The feasibility and conditions for the application of the approach on mechanical systems are discussed. A nonlinear multi‐input multi‐output mechanical system is taken as a simulation example to illustrate the application. The results show the robustness of the control design and plausible estimations of full‐rank disturbances.Copyright © 2012 John Wiley & Sons, Ltd.     

Sliding‐mode fault‐tolerant control using the control allocation scheme

This paper is devoted to the design of a novel fault‐tolerant control (FTC) using the combination of a robust sliding‐mode control (SMC) strategy and a control allocation (CA) algorithm, referred to as a CA‐based sliding‐mode FTC (SMFTC). The proposed SMFTC can also be considered a modular‐design control strategy. In this approach, first, a high‐level SMC, designed without detailed knowledge of systems' actuators/effectors, commands a vector of virtual control signals to meet the overall control objectives. Then, a CA algorithm distributes the virtual control efforts among the healthy actuators/effectors using the real‐time information obtained from a fault detection and reconstruction mechanism. As the underlying system is not assumed to have a rank‐deficient input matrix, the control allocator module is visible to the SMC module resulting in an uncertainty. Hence, the virtual control, in this scheme, is designed to be robust against uncertainties emanating from the visibility of the control allocator to the controller and imperfections in the estimated effectiveness gain. The proposed CA‐based SMFTC scheme is a unified FTC, which does not need to reconfigure the control system in the case of actuator fault or failure. Additionally, to cope with actuator saturation limits, a novel redistributed pseudoinverse‐based CA mechanism is proposed. The effectiveness of the proposed schemes is discussed with a numerical example.     

Thrust-vectored differential turns

Differential-turning games played with thrust vectoring as an aid to maneuvering are examined in an extension of the research of a companion paper which reports a study of thrust-vectored maneuvering in energy approximation. The benefits are found to be major when there is a sufficient margin of thrust over weight to permit hover. Families of turning duels between a conventional aircraft and a thrust-vectored opponent are described in a computational example.     

舵鳍联合自抗扰主从控制策略设计

在分析舰船航行中所受干扰特性的基础上,针对目前舵鳍联合控制中存在的问题,以虚拟控制力作为中间变量,设计了主从结构的舵鳍联合控制策略.主控制器采用非线性干扰观测器对环境扰动和模型不确定性进行估计,在此基础上以虚拟控制力作为控制量采用自抗扰结构,对船舶三自由度运动进行联合控制.同时,在主控制器设计中包含了舵/鳍伺服系统的实际约束,保证了从控制器解的可行性.基于遗传算法设计了数值反演从控制器,求取最终的控制量.通过船模试验和仿真对所设计的控制器进行了验证,试验和仿真结果表明所设计的两步主从控制策略具有较好的控制效果.     

基于滑模控制的折叠翼飞行器辅助机动研究

基于滑模控制策略,研究了折叠翼飞行器辅助机动问题.分析了系统折叠角与气动参数的关系,把机翼折叠角看成额外的控制输入,构造了包含折叠辅助机动的飞行器动力学模型.针对非线性系统,加入混合干扰,设计了非奇异动态终端滑模控制(NDTSMC)器,能够较好地抑制折叠翼飞行器的不确定性,同时完成姿态跟踪控制.仿真结果表明,NDTSMC改善了折叠翼飞行器的控制精度和鲁棒性能,具有较好的抖振消除效果.与传统飞行器相比,加入折叠辅助机动的折叠翼飞行器拥有更高的机动性和抗干扰能力.     

Adaptive control for autonomous ships with uncertain model and unknown propeller dynamics

Motion control is one of the most critical aspects in the design of autonomous ships. During maneuvering, the dynamics of propellers as well as the craft hydrodynamical specifications experience severe uncertainties. In this paper, an adaptive control approach is proposed to control the motion and trajectory tracking of an autonomous vessel by adopting neural networks that is used for estimating the dynamics of the propellers and handling hydrodynamical uncertainties. Considering that the maneuvering model of a vessel resemble a nonlinear non-affine-in-control system, the proposed neural-based adaptive control algorithm is designed to estimate the nonlinear influence of the input function which in this case is the dynamics of propellers and thrusters. It is also shown that the proposed methodology is capable of handling state dependent uncertainties within the ship maneuvering model. A Lyapunov-based technique and Uniform Ultimate Boundedness are used to prove the correctness of the algorithm. To assess the method’s performance, several experiments are considered including trajectory tracking simulations in the port of Rotterdam.     

考虑作动器动态补偿的飞机增量滤波非线性控制

针对飞机大迎角机动存在的模型参数不确定问题,提出了一种考虑作动器动态补偿的增量滤波非线性控制方法.基于推力矢量飞机姿态控制模型,利用Taylor级数展开和状态导数反馈分别设计了增量形式的气流角和角速度控制器.针对低通滤波求取状态导数产生的延迟,通过对控制量进行滤波补偿保证了状态导数反馈和控制量反馈的时间同步性.在此基础上分析了作动器动态对角速度闭环控制性能的影响,通过补偿器设计使系统具有期望的作动器动态,克服了增量式控制方法对作动器高带宽的限制.仿真结果表明本文提出的增量滤波非线性控制方法具有强鲁棒性和快速动态响应能力.