Distributed tracking for networked Euler-Lagrange systems without velocity measurements

The problem of distributed coordinated tracking control for networked Euler-Lagrange systems without velocity measurements is investigated. Under the condition that only a portion of the followers have access to the leader, sliding mode estimators are developed to estimate the states of the dynamic leader in finite time. To cope with the absence of velocity measurements, the distributed observers which only use position information are designed. Based on the outputs of the estimators and observers, distributed tracking control laws are proposed such that all the fol- lowers with parameter uncertainties can track the dynamic leader under a directed graph containing a spanning tree. It is shown that the distributed observer-controller guarantees asymptotical stability of the closed-loop system. Numerical simulations are worked out to illustrate the effectiveness of the control laws.     

Adaptive actuator failure compensation and disturbance rejection scheme for spacecraft

An adaptive actuator failure compensation scheme is proposed for attitude tracking control of spacecraft with unknown disturbances and uncertain actuator failures. A new feature of this adaptive control scheme is the adaptation of the failure pattern parameter estimates, as well as the failure signal parameter estimates, for direct adaptive actuator failure compensation. Based on an adaptive backstepping control design, the estimates of the disturbance parameters are used to solve the disturbance rejection problem. The unknown disturbances are compensated completely with the stability of the whole closed-loop system. The scheme is not only able to accommodate uncertain actuator failures, but also robust against unknown external disturbances. Simulation results verify the desired adaptive actuator failure compensation performance.     

Nonlinear autopilot design for interceptors with tail fins and pulse thrusters via θ-D approach

The missile autopilot for an interceptor with tail fins and pulse thrusters is designed via the θ-D approach. The nonlin- ear dynamic model of the pitch and yaw motion of the missile is transformed into a linear-like structure with state-dependent coef- ficient （SDC） matrices. Based on the linear-like structure, a θ-D feedback controller is designed to steer the missile to track refer- ence acceleration commands. A sufficient condition that ensures the asymptotic stability of the tracking system is given based on Lyapunov＇s theorem. Numerical results show that the proposed autopilot achieves good tracking performance and the closed-loop tracking system is asymptotically stable.     

Comparison of time optimal control for two level quantum systems

The time optimal problem for a two level quantum sys-tem is studied. We compare two different control strategies of bang-bang control and the geometric control, respectively, es-pecial y in the case of minimizing the time of steering the state from North Pole to South Pole on the Bloch sphere with bounded control. The time performances are compared for different param-eters by the individual numerical simulation experiments, and the experimental results are analyzed. The results show that the ge-ometric control spends less time than the bang-bang control does.     

High-order sliding mode attitude controller design for reentry flight

A novel high-order sliding mode control strategy is proposed for the attitude control problem of reentry vehicles in the presence of parametric uncertainties and external disturbances, which results in the robust and accurate tracking of the aerodynamic angle commands with the finite time convergence. The proposed control strategy is developed on the basis of integral sliding mode philosophy, which combines conventional sliding mode control and a linear quadratic regulator over a finite time interval with a free-final-state and allows the finite-time establishment of a high-order sliding mode. Firstly, a second-order sliding mode attitude controller is designed in the proposed high-order siding mode control framework. Then, to address the control chattering problem, a virtual control is introduced in the control design and hence a third-order sliding mode attitude controller is developed, leading to the chattering reduction as well as the control accuracy improvement. Finally, simulation examples are given to illustrate the effectiveness of the theoretical results.     

基于非线性干扰观测器的高超声速飞行器反演滑模控制

针对高超声速飞行器非线性动力学系统中存在的高度非线性、多变量耦合及参数不确定等特点,利用非线性干扰观测器对各种干扰的逼近特性,结合反演滑模控制,设计了一种飞行器反演滑模控制器。该方法首先利用干扰观测器观测出系统的干扰,未观测出的部分干扰使用反演滑模控制进行补偿,避免了累积误差,实现对制导指令的鲁棒输出跟踪,并证明了系统稳定性。仿真结果验证了该方法能较理想地观测干扰,保证系统良好的鲁棒性。     

Finite-time coordination control for formation flying spacecraft

This paper investigates a distributed coordination control scheme using an adaptive terminal sliding mode for formation flying spacecraft with coupled attitude and translational dynamics. In order to overcome the singularity of the traditional fast terminal sliding manifold, a novel fast terminal sliding manifold is given. And then, based on the adaptive control method, a continuous robust coordinated controller is designed to compensate external disturbances and to alleviate the chattering phenomenon. The theoretical analysis shows that the coordinated controller can guarantee the finite-time stability of the overall closed-loop system through local information exchange, and numerical simulations also demonstrate its effectiveness.     

基于观测器的一类不确定非线性系统自适应输出反馈控制

针对一类不确定非线性系统,基于非线性状态观测器采用回馈递推(Backstepping)设计方法提出了一种鲁棒自适应L2增益控制方案。该控制方案首先对系统的不可观测状态设计非线性状态观测器,在此基础上通过多步递推得到系统的控制律并设计了未知干扰的参数自适应律,使系统具有L2增益性能。同时把采用常规设计方法需要对过多参数进行辨识问题简化为只需对与未知干扰个数相同的参数进行辨识的问题,简化了控制器结构。最后通过仿真算例验证了所设计控制方案的有效性。     

Adaptive stabilization for cascade nonlinear systems

An adaptive controller of full state feedback for certain cascade nonlinear systems achieving input-to-state stability with respect to unknown bounded disturbance is designed using backstepping and control Lyapunov function (CLF) techniques. We show that unknown bounded disturbance can be estimated by update laws, which requires less information on unknown disturbance, as a part of stabilizing control. The design method achieves the desired property: global robust stability. Our contribution is illustrated with the example of a disturbed pendulum.     

基于递归神经网络的伺服系统自适应反步控制

针对伺服系统的系统参数摄动和非线性动态摩擦补偿问题,提出基于递归神经网络(RNN)的自适应反步控制(RNABC)系统设计方法.RNABC系统由反步控制器和鲁棒控制器组成,反步控制器包含RNN不确定观测器,鲁棒控制器则用来消除由于引入不确定观测器而带来的逼近误差.由于自适应反步控制的自适应律源于Lyapunoy函数的,因此系统的稳定性得到了保证.仿真结果表明,对于系统参数摄动和非线性摩擦干扰RNABC能使伺服系统具有很好的跟踪性能.     

Direct adaptive control for a class of MIMO nonlinear discrete-time systems

This paper considers the problem of adaptive con-trol for a class of multiple input multiple output （MIMO） nonlinear discrete-time systems based on input-output model with unknown interconnections between subsystems. Based on the Taylor ex-pand technology, an equivalent model in affine-like form is derived for the original nonaffine nonlinear system. Then a direct adap-tive neural network （NN） control er is implemented based on the affine-like model. By finding an orthogonal matrix to tune the NN weights, the closed-loop system is proven to be semiglobal y uni-formly ultimately bounded. The σ-modification technique is used to remove the requirement of persistence excitation during the adaptation. The control performance of the closed-loop system is guaranteed by suitably choosing the design parameters.     

Computational mission analysis and conceptual system design for super low altitude satellite

This paper deals with system engineering and design methodology for super low altitude satel ites in the view of the com-putational mission analysis. Due to the slight advance of imaging instruments, such as the focus of camera and the image element of charge coupled device （CCD）, it is an innovative and economical way to improve the camera’s resolution to enforce the satel ite to fly on the lower altitude orbit. DFH-3, the mature satel ite bus de-veloped by Chinese Academy of Space Technology, is employed to define the mass and power budgets for the computational mis-sion analysis and the detailed engineering design for super low altitude satel ites. An effective iterative algorithm is proposed to solve the ergodic representation of feasible mass and power bud-gets at the flight altitude under constraints. Besides, boundaries of mass or power exist for every altitude, where the upper boundary is derived from the maximum power, while the minimum thrust force holds the lower boundary before the power reaching the initial value. What’s more, an analytical algorithm is employed to numerical y investigate the coverage percentage over the altitude, so that the nominal altitude could be selected from al the feasi-ble altitudes based on both the mass and power budgets and the repetitive ground traces. The local time at the descending node is chosen for the nominal sun-synchronous orbit based on the average evaluation function. After determining the key orbital ele-ments based on the computational mission analysis, the detailed engineering design on the configuration and other subsystems, like power, telemetry telecontrol and communication （TT＆amp;C）, and attitude determination and control system （ADCS）, is performed based on the benchmark bus, besides, some improvements to the bus are also implemented to accommodate the flight at a super low altitude. Two operation strategies, drag-free closed-loop mode and on/off open-loop mode, are presented to maintain the satel-lite’s altitude. Final y, a flight planning schedule for the satel ite is demonstrated from its launch into the initial altitude at the very beginning to its decay to death in the end.     

Shape control on probability density function in stochastic systems

A novel strategy of probability density function （PDF） shape control is proposed in stochastic systems. The control er is designed whose parameters are optimal y obtained through the improved particle swarm optimization algorithm. The parameters of the control er are viewed as the space position of a particle in particle swarm optimization algorithm and updated continual y until the control er makes the PDF of the state variable as close as possible to the expected PDF. The proposed PDF shape control technique is compared with the equivalent linearization technique through simulation experiments. The results show the superiority and the effectiveness of the proposed method. The control er is excellent in making the state PDF fol ow the expected PDF and has the very smal error between the state PDF and the expected PDF, solving the control problem of the PDF shape in stochastic systems effectively.     

超机动飞行的非线性鲁棒自适应控制系统研究

针对飞机模型中存在气动参数不确定性以及外界干扰等影响因素,设计了一种超机动飞行的非线性鲁棒自适应控制系统。控制系统设计过程中,模型不确定性和外界干扰由RBF神经网络在线补偿,控制律及神经网络权值自适应律由反步法得到。解决了系统中控制增益矩阵未知,同时存在外界干扰情况下的鲁棒飞行控制系统设计,并证明了闭环系统所有信号有界,系统跟踪误差和神经网络权值估计误差指数收敛到有界紧集内。对所研究的飞行控制系统进行了过失速Herbst机动仿真,结果验证了该系统在过失速机动条件下具有良好的控制性能。     

航天器非线性鲁棒自适应姿态机动控制律

针对存在未知转动惯量和外部干扰力矩的敏捷航天器快速大角度姿态机动问题,结合非线性反步法和Lyapunovo稳定性分析方法设计控制力矩和转动惯量估计值的非线性鲁棒自适应控制律。在控制力矩控制律中,加入非线性阻尼项对外部干扰力矩进行补偿,证明了系统的全局一致最终有界稳定性。引入非线性动系数增加系统的动态性能,提高了姿态快速机动后的快速稳定能力。在Maltlab/Simulink环境下进行航天器姿态机动控制仿真研究,仿真结果验证了所设计控制器的有效性和可行性。     

基于NDO的飞行模拟转台伺服系统跟踪控制

针对飞行模拟转台伺服系统跟踪控制问题,提出了一种基于非线性干扰观测器(nonlinear disturbance observer, NDO)的反推全局滑模控制方案。该方案利用NDO观测系统的参数不确定性及非线性摩擦干扰,通过选择适当的设计参数使观测误差指数收敛,进而对引入NDO的系统采用反推全局滑模设计控制器,控制律的设计保证了闭环系统的稳定性。仿真结果表明,所提控制方案能够有效克服参数不确定性及非线性摩擦干扰的影响,实现了转角位置的精确跟踪,并且有效去除了控制抖振。     

Weighted average consensus problem in networks of agents with diverse time-delays

This paper studies the weighted average consensus problem for networks of agents with fixed directed asymmetric unbalance information exchange topology. We suppose that the classical distributed consensus protocol is destroyed by diverse time-delays which include communication time-delay and self time-delay. Based on the generalized Nyquist stability criterion and the Gerschgorin disk theorem, some sufficient conditions for the consensus of multi-agent systems are obtained. And we give the expression of the weighted average consensus value for our consensus protocol. Finally, numerical examples are presented to illustrate the theoretical results.     

考虑滞回非线性的飞行姿态backstepping全局滑模控制

针对存在不确定性和滞回非线性的三代战机姿态稳定控制问题,提出一种基于非线性干扰观测器的backstepping全局滑模控制策略。利用非线性干扰观测器对系统不确定性和滞回非线性部分进行观测补偿,取消了不确定项变化缓慢的限制条件。借鉴动态面控制思想,引入一阶滤波器降低了backstepping控制器的复杂程度。利用Lyapunov定理证明了系统的稳定性。仿真结果表明了该控制方案对不确定干扰的有效抑制和闭环系统良好的跟踪性能。     

基于后推技术的直接鲁棒自适应模糊控制

针对一类带摄动的严格反馈非线性系统,基于后推设计方法,利用第一类模糊系统的逼近能力,提出了一种新的直接自适应控制方案。该方案中引入连续鲁棒项对系统的摄动部分进行抑制,并在自适应律中利用了leakage项以防止参数漂移。通过理论分析,证明了闭环系统是半全局一致终结有界的,跟踪误差收敛到一个小的残差集内。仿真结果表明了该方法的有效性。     

基于有限时间收敛干扰观测器的探导控一体化设计

针对滚仰式半捷联寻的制导导弹, 提出一种基于有限时间干扰观测器(finite time disturbance observer, FTDO)的探导控一体化滑模控制器设计方法。首先基于滚仰式半捷联导引头动力学模型和导弹制导控制模型, 建立了全状态耦合探测、制导、控制一体化控制模型。在模型中将不确定项和误差视为干扰, 通过有限时间收敛干扰观测器对干扰进行估计。对探导控一体化模型进行分块反演滑模控制律设计, 并验证了控制器的稳定性。仿真结果表明, 一体化控制方法提高了导弹对目标机动的响应能力和目标跟踪的稳定性, 并实现了比传统级联控制方法更小的脱靶量。