基于姿态角估计的四旋翼飞行器多传感器故障诊断方法

针对无法直接测量得到姿态角的四旋翼飞行器多传感器偏差故障检测与诊断问题,提出一种基于姿态角估计的多传感器故障同时发生的故障检测与隔离以及故障偏差值估计的方法。首先,在考虑模型误差的前提下,建立四旋翼飞行器动力学模型和传感器模型,构建四旋翼飞行器故障检测与诊断系统。其次,在利用基于滑模观测器得到姿态角估计值的基础上,设计非线性故障观测器对故障进行检测与隔离。最后,构建非线性自适应观测器实现未知故障偏差值的估计,并证明自适应律的稳定性和参数收敛性。实验结果表明,该方法能实现多传感器偏差故障检测与隔离,并在5 s之内实现对传感器多故障偏差的估计与跟踪,且估计误差有界,该方法有效性得以验证。     

猎雷声纳基阵姿态稳定系统自适应反步法控制

针对带非线性摩擦力矩和负载扰动的高精度猎雷声纳基阵姿态稳定系统,提出了一种基于神经网络的自适应反步法控制方法。其中神经网络用于估计未知非线性摩擦力矩,进而设计反步法控制器和参数自适应律来对神经网络估计误差和负载扰动进行补偿。最后应用Lyapunov方法证明了所提出的自适应控制器能保证闭环系统的稳定性,并且可以通过选择适当的控制器参数来调整收敛率。仿真结果表明,基于神经网络的自适应反步法控制方法与PID控制相比,系统的动、静态性能指标及鲁棒性得到了全面的改善,与双闭环PID控制相比,跟踪精度提高了3倍多。     

四旋翼无人机模糊自抗扰姿态控制及稳定性分析

针对四旋翼无人机姿态控制问题,设计了一种基于模糊自抗扰控制的四旋翼姿态控制器。分析了四旋翼无人机的动力学模型,给出了基于模糊自抗扰控制算法的姿态控制方案,并设计了对应的模糊自抗扰控制算法的扩张状态观测器和模糊状态误差反馈控制器。通过稳定性分析,得出了扩张状态观测器估计误差是有界的,同时给出了反馈误差稳定的充分条件。仿真结果表明,所设计的模糊自抗扰控制器,同经典自抗扰控制器相比,系统平均超调量减小约75%,降低了扰动造成的输出波动幅值约30%,表明该控制系统提高了系统稳定性和对干扰抑制能力,满足对四旋翼姿态控制要求。     

基于指数收敛的四旋翼无人机鲁棒自适应飞行控制

针对四旋翼无人机鲁棒自适应飞行问题,提出了一种基于指数收敛的控制方法。考虑到四旋翼系统的欠驱动、强耦合等非线性特性,采用线性化反馈控制策略实现对其轨迹追踪飞行能力的基本控制;针对线性化反馈控制易受系统内外部未知干扰等影响,采用基于指数收敛干扰观测器组合控制设计,实现四旋翼飞行的鲁棒与自适应控制;线性反馈及状态观测器控制系统基于指数收敛稳定。进行了仿真分析,结果表明,干扰观测器对四旋翼系统中存在的未知干扰具有很好的估计能力,所设计的基于指数收敛控制系统,结构简单,且具有较强的干扰抑制能力和较高的系统稳定性,满足四旋翼无人机的鲁棒及自适应飞行能力要求。     

基于扰动观测器的卫星姿态控制系统自适应有限时间容错控制

针对具有状态时变时滞、系统不确定性、可建模扰动、运行噪声和执行器故障的卫星姿态控制系统,提出一种基于扰动观测器的自适应有限时间复合主动容错控制策略。针对可建模扰动设计扰动观测器,然后基于扰动估计误差设计了主动容错控制器。该时滞依赖控制器包含反馈控制项、扰动补偿项和快速自适应故障补偿项。提出的容错控制策略不仅保证闭环系统动态方程的有限时间有界性,而且保证闭环测量输出对于系统不确定性、运行噪声、执行器故障等的鲁棒性。给出控制器增益限制矩阵存在的充分条件及其线性矩阵不等式形式,进而给出仿真算例。仿真结果表明,基于扰动观测器方法,设计的自适应有限时间容错控制器能够快速估计可建模扰动,进而有效地实现系统的闭环容错控制。相较于基于非复合的自适应有限容错控制器,提出的方法对于状态变量的估计均方根误差分别降低了28.9%、4.7%和36.0%;对于可建模扰动估计的均方根误差降低了38.8%。仿真验证了所提方法的有效性。     

基于扩张观测器的四旋翼无人机轨迹鲁棒滑模控制

针对四旋翼无人机轨迹追踪问题,提出了一种基于扩张状态观测器的鲁棒滑模控制方法。考虑无人机系统受到内外部扰动、线速度未知等不确定性影响,通过引入扩张状态观测器,对系统不确定因素进行实时估计并给予补偿,实现了系统对扰动的鲁棒性和对环境的高度适应性。同时,滑模控制通过引入切换函数来消除干扰及不确定项,但较大的切换增益会引起系统颤振,因此,干扰和不确定项是颤振的主要来源,利用扩张状态观测器来估计干扰及不确定项并加以补偿,消除了颤振。利用Lyapunov理论,证明了控制系统的稳定性。系统仿真实验结果表明,所提出的控制方法能够保证四旋翼无人机轨迹追踪的鲁棒性,旋翼转速最大跳变幅值降低86.4%~94.5%,提高了系统稳定性。     

基于四元数的SINS/SAR组合导航系统

传统的SINS误差模型是基于小姿态误差角假设下的线性化误差模型,由于忽略了高阶项,因而不能精确描述系统的非线性特征,易造成较大的导航估计误差甚至滤波器发散。为了克服SINS线性化误差模型的缺点,建立了基于四元数的SINS/SAR组合导航系统非线性模型,并将自适应UPF滤波算法应用于该组合系统。仿真结果表明,建立的基于四元数的组合导航系统模型,不但能有效减小导航误差,提高导航定位精度,而且具有良好的实时性。     

基于扰动观测器的AUV固定时间积分滑模控制方法

针对自主水下航行器（AUV）在参数不确定性和外界干扰下水平轨迹跟踪控制问题，提出一种基于扰动观测器的固定时间积分滑模控制方法。首先将参数不确定性和外界干扰视为复合扰动，设计固定时间扰动观测器对其进行估计。然后在反步法设计框架下，结合固定时间理论和全局积分滑模控制，设计了固定时间积分滑模控制器。轨迹跟踪仿真结果表明，相比于传统滑模控制器，所设计的扰动观测器和控制器可以使位置和姿态的跟踪误差收敛至零域的速度由5.2 s缩短至约2.5 s，并且在没有观测器的帮助下跟踪误差也能收敛至稳定，具有更快的收敛速度和更高的鲁棒性。     

导弹编队协同攻击分布式鲁棒自适应控制

在有向通信拓扑下研究了导弹编队的鲁棒自适应协同跟踪控制问题。针对导弹编队系统中队形跟踪、外部扰动和模型不确定性的情况,通过选取包含位置跟踪误差和速度跟踪误差的辅助变量,提出了一种基于有向通信拓扑的鲁棒自适应编队控制策略。提出了自适应律对未知参数进行估计,并且利用Lyapunov稳定性理论分析了闭环系统的渐近稳定性。进一步,对于通信时滞的情况,给出了系统渐近稳定所需要满足的条件。与滑模控制等传统鲁棒控制不同,所设计的鲁棒自适应控制器是连续的,更便于导弹编队系统的实现。数值仿真结果表明,队形跟踪误差小于0.03 m,队形保持误差小于0.07 m,所设计的控制器能实现高精度的编队跟踪控制。     

航天器有限时间自适应容错姿态控制

针对存在执行器故障、转动惯量偏差以及外部扰动等系统不确定性的航天器姿态跟踪问题,提出一种有限时间自适应容错姿态控制方法。建立基于四元数的航天器姿态动力学模型、执行器故障模型和系统不确定性模型,并将执行器故障分为乘性故障和加性故障两大类;利用滑模控制和有限时间控制理论设计有限时间姿态控制器,并通过设计自适应变量及更新方法对执行器故障以及系统不确定性引起的控制偏差上界进行估计和补偿,使姿态控制器对故障和扰动具有良好的适应性和鲁棒性。得到的新型有限时间自适应容错姿态控制器能够保证航天器在执行器故障以及系统不确定性条件下在有限时间内精确收敛到期望值。利用Lyapunov稳定性理论证明了系统的渐进稳定性和有限时间稳定性,数值仿真验证了所提出方法的可行性和有效性。     

Decentralized adaptive attitude synchronization control for spacecraft formation using nonsingular fast terminal sliding mode

This paper studies the attitude synchronization control problem for a group of spacecraft. Considering inertia uncertainties and external disturbances with unknown bounds, a decentralized adaptive control scheme is developed using nonsingular fast terminal sliding mode (NFTSM). A multispacecraft NFTSM is firstly designed, which contains the advantages of the nonsingular terminal sliding mode and the traditional linear sliding mode together. Then, the continuous decentralized adaptive NFTSM control laws with boundary layer by employing NFTSM associated with novel adaptive architecture are proposed, which can eliminate the chattering, and guarantee the attitude tracking errors converge to the regions containing the origin in finite time. At last, numerical simulations are presented to demonstrate the performance of the proposed control strategy.     

Adaptive sliding mode control of uncertain chaotic systems with input nonlinearity

This paper is concerned with the stabilization problem of uncertain chaotic systems with input nonlinearity. The slope parameters of this nonlinearity are unmeasured. A new sliding function is designed, then an adaptive sliding mode controller is established such that the trajectory of the system converges to the sliding surface in a finite time and finite-time reachability is theoretically proved. Using a virtual state feedback control technique, sufficient condition for the asymptotic stability of sliding mode dynamics is derived via linear matrix inequality (LMI). Then the results can be extended to uncertain chaotic systems with disturbances and adaptive sliding mode H _∞ controllers are designed. Finally, a simulation example is presented to show the validity and advantage of the proposed method.     

Fuzzy adaptive high-gain-based observer backstepping control for SISO nonlinear systems with dynamical uncertainties

In this paper, a fuzzy adaptive output feedback control approach is developed for a class of SISO strict-feedback nonlinear systems with unmeasured states, unmodeled dynamics, and dynamical disturbances. In the backstepping recursive design, fuzzy logic systems are used to approximate the unknown nonlinear functions, a fuzzy adaptive high-gain observer is designed to estimate the unmeasured states; a dynamic signal is incorporated into the control scheme to dominate the dynamic uncertainties. Using the states estimates and combining the backstepping design technique, a fuzzy adaptive output feedback control is constructed recursively. It is proved that the proposed fuzzy adaptive output feedback control scheme can guarantee the all signals in the closed-loop system are semiglobally uniformly ultimately bounded (SUUB), and the observer and tracking error converges to a small neighborhood of the origin. The effectiveness of the proposed approach is illustrated via an example.     

Adaptive interval type-2 fuzzy sliding mode control for unknown chaotic system

In this paper, a novel adaptive interval type-2 fuzzy sliding mode control (AIT2FSMC) methodology is proposed based on the integration of sliding mode control and adaptive interval type-2 fuzzy control for chaotic system. The AIT2FSMC system is comprised of a fuzzy control design and a hitting control design. In the fuzzy control design, an interval type-2 fuzzy controller is designed to mimic a feedback linearization (FL) control law. In the hitting control design, a hitting controller is designed to compensate the approximation error between the FL control law and the interval type-2 fuzzy controller. The parameters of the interval type-2 fuzzy controller, as well as the uncertainty bound of the approximation error, are tuned adaptively. The adaptive laws are derived in the sense of Lyapunov stability theorem, thus the stability of the system can be guaranteed. The proposed control system compared to adaptive fuzzy sliding mode control (AFSMC). Simulation results show that the proposed control systems can achieve favorable performance and robust with respect to system uncertainties and external disturbances.     

Robust finite-time control allocation in spacecraft attitude stabilization under actuator misalignment

A novel combination of finite time control and control allocation with uncertain configuration matrix due to actuator misalignment is investigated for attitude stabilization of a rigid spacecraft. Finite time controller using nonsingular terminal sliding mode technique is firstly designed as virtual control of control allocator to produce the three axis torques, and can guarantee finite time reachability of given attitude motion of spacecraft in the presence of external disturbances. The convergences of this feedback controller for the resulting closed loop systems are also proven theoretically. Then, under the condition of uncertainty included in the configuration matrix due to actuator misalignment, a robust least squares-based control allocation is employed to deal with the problem of distributing the three axis torques over the available actuators under redundancy, in which the focus of this control allocation is to find the optimal control vector of actuator by minimizing the worst-case residual, under the condition of the uncertainty included in actuator configuration matrix and control constraints like saturation. Simulation results using the orbiting spacecraft model show good performance under external disturbances and even uncertain configuration matrix, which validates the effectiveness and feasibility of the proposed scheme.     

基于反演滑模的机动飞行器横向回路控制设计

针对再入机动飞行器模型的参数不确定性以及外界干扰对飞行器控制性能的影响,基于反演控制和滑模控制理论,结合飞行器的动态特性要求,设计了一种基于标称模型的再入机动飞行器横向回路姿态控制方案,并基于Lyapunov方法,给出了整个系统的稳定性证明。控制系统阶跃响应仿真结果表明:系统响应无超调,调节时间为0.6 s,稳态误差为1%,优于指标要求的超调量15%,调节时间1 s,稳态误差5%,证明所提方法对模型参数大范围摄动具有强鲁棒性,且在较大程度上提高了系统的动态性能,最终达到姿态指令的快速高精度跟踪效果。     

Adaptive sliding mode control of dynamic system using RBF neural network

This paper presents a robust adaptive sliding mode control strategy using radial basis function (RBF) neural network (NN) for a class of time varying system in the presence of model uncertainties and external disturbance. Adaptive RBF neural network controller that can learn the unknown upper bound of model uncertainties and external disturbances is incorporated into the adaptive sliding mode control system in the same Lyapunov framework. The proposed adaptive sliding mode controller can on line update the estimates of system dynamics. The asymptotical stability of the closed-loop system, the convergence of the neural network weight-updating process, and the boundedness of the neural network weight estimation errors can be strictly guaranteed. Numerical simulation for a MEMS triaxial angular velocity sensor is investigated to verify the effectiveness of the proposed adaptive RBF sliding mode control scheme.     

A robust attitude control strategy with guaranteed transient performance via modified Lyapunov-based control and integral sliding mode control

In this paper, a robust control strategy with guaranteed transient performance is presented for spacecraft attitude maneuvers. Firstly, a Lyapunov-based controller is designed to achieve high-performance attitude control in the absence of disturbance and parameter variation. Unlike most existing designs, the feedback gains in the proposed controller increase with the attitude error convergence. Consequently, the system response can be accelerated without increasing the control torque at large attitude error. The overshooting phenomenon is also avoided by imposing a restriction on the parameter selection. Then, the integral sliding mode control technique is employed to preserve the desired transient characteristics and improve the robustness. Furthermore, by combining an adaptive scheme with the boundary layer method, the conservativeness in the switching gain selection is reduced and the chattering is also suppressed. Theoretical analysis and simulation results verify the effectiveness of the proposed strategy.     

Fault-tolerant sliding mode attitude control for flexible spacecraft under loss of actuator effectiveness

In this paper, a novel fault-tolerant attitude control synthesis is carried out for a flexible spacecraft subject to actuator faults and uncertain inertia parameters. Based on the sliding mode control, a fault-tolerant control law for the attitude stabilization is first derived to protect against the partial loss of actuator effectiveness. Then the result is extended to address the problem that the actual output of the actuators is constrained. It is shown that the presented controller can accommodate the actuator faults, even while rejecting external disturbances. Moreover, the developed control law can rigorously enforce actuator-magnitude constraints. An additional advantage of the proposed fault-tolerant control strategy is that the control design does not require a fault detection and isolation mechanism to detect, separate, and identify the actuator faults on-line; the knowledge of certain bounds on the effectiveness factors of the actuator is not used via the adaptive estimate method. The associated stability proof is constructive and accomplished by the development of the Lyapunov function candidate, which shows that the attitude orientation and angular velocity will globally asymptotically converge to zero. Numerical simulation results are also presented which not only highlight the ensured closed-loop performance benefits from the control law derived here, but also illustrate its superior fault tolerance and robustness in the face of external disturbances when compared with the conventional approaches for spacecraft attitude stabilization control.