In this paper, the consensus tracking problem is investigated for a class of continuous switched stochastic nonlinear multiagent systems with an event-triggered control strategy. For continuous stochastic multiagent systems via event-triggered protocols, it is rather difficult to avoid the Zeno behavior by the existing methods. Thus, we propose a new protocol design framework for the underlying systems. It is proven that follower agents can almost surely track the given leader signal with bounded errors and no agent exhibits the Zeno behavior by the given control scheme. Finally, two numerical examples are given to illustrate the effectiveness and advantages of the new design techniques.

Consensus Tracking Control of Switched Stochastic Nonlinear Multiagent Systems via Event-Triggered Strategy

Nonlinear guidance laws that consider impact time constraints are proposed. Two-dimensional and three-dimensional impact time control guidance laws are derived using Lyapunov stability theory. Under the consideration of the nonlinear kinematics, it is shown that the missile states converge to the desired equilibrium point by the Lyapunov stability theory. The singularity issue of the proposed guidance laws is also analyzed. Numerical simulations are performed to verify the performance of the proposed guidance laws.

Lyapunov-based impact time control guidance laws against stationary targets

A novel prescribed performance neural controller with unknown initial errors is addressed for the longitudinal dynamic model of a flexible air-breathing hypersonic vehicle (FAHV) subject to parametric uncertainties. Different from traditional prescribed performance control (PPC) requiring that the initial errors have to be known accurately, this paper investigates the tracking control without accurate initial errors via exploiting a new performance function. A combined neural back-stepping and minimal learning parameter (MLP) technology is employed for exploring a prescribed performance controller that provides robust tracking of velocity and altitude reference trajectories. The highlight is that the transient performance of velocity and altitude tracking errors is satisfactory and the computational load of neural approximation is low. Finally, numerical simulation results from a nonlinear FAHV model demonstrate the efficacy of the proposed strategy.

Novel prescribed performance neural control of a flexible air-breathing hypersonic vehicle with unknown initial errors.

Three-dimensional cooperative guidance law for multiple missiles with finite-time convergence

Smooth Sliding Mode Control for Missile Interception with Finite-Time Convergence

A novel method of adaptive nonsingular terminal sliding mode control is proposed for a class of nonlinear systems subject to disturbances and uncertainties. The obtained results are applied to integrated guidance and control design for a missile. Using the Lyapunov stability theory, it is shown that the finite time convergence in both reaching and sliding phase is achieved by virtue of a terminal sliding surface and a switching controller that avoids singularity. With the assumption that the disturbances and uncertainties are bounded and the bounds are unknown, the adaptive method is incorporated with the controller design, which makes the proposed adaptive nonsingular terminal sliding mode control with better robustness. Due to the inherent property of time-scale separation between the translational and rotational dynamics, partial integrated guidance and control with a two-loop controller structure is designed for a missile based on the proposed adaptive nonsingular terminal sliding mode control. The ou...

Partial Integrated Missile Guidance and Control with Finite Time Convergence

A novel sliding mode observer for state and fault estimation in systems not satisfying matching and minimum phase conditions

A partial integrated guidance and control design for an interception with terminal impact angle constraints in three-dimensional space is presented in this paper A three-dimensional nonlinear engagement dynamic is considered here and full nonlinear six-degrees-of-freedom model of the interceptor with aerodynamic uncertainties has been accounted for The partial integrated guidance and control design contains a two-loop controller structure The outer loop, which generates directly the commanded body rates, is constructed, and then the inner loop is designed to track the outer loop commands The main feature of the partial integrated guidance and control design is that it accurately satisfies terminal impact angle constraints in both azimuth and elevation, in addition to being capable of hitting the target with high accuracy Moreover, the aerodynamic uncertainties and the target acceleration, which are assumed to be bounded, are considered by virtue of the proposed adaptive multiple input multiple output

Partial Integrated Guidance and Control for Missiles with Three-Dimensional Impact Angle Constraints

In this paper, a fault-tolerant control scheme is proposed for the rigid spacecraft attitude control system subject to external disturbances, multiple system uncertainties, and actuator faults. The angular velocity measurement is unavailable, which increases the complexity of the problem. An observer is first designed based on the super-twisting sliding mode method, which can provide accurate estimates of the angular velocity in finite time. Then, an adaptive fault-tolerant controller is proposed based on neural networks using the information from the observer. It is shown that the attitude orientations converge to the desired values exponentially. Finally, a simulation example is utilized to verify the effectiveness of the proposed scheme.

Fault-Tolerant Attitude Control for Rigid Spacecraft Without Angular Velocity Measurements

Novel sliding-mode control laws are proposed in this paper to stabilize a class of uncertain nonlinear systems. Considering that the sign function, which is often used in the sliding-mode control can cause chattering of control input, the saturation function is used to take its place in proposed controllers. What is more, not only the proposed controllers are continuous but also convergence to the origin asymptotically and in finite time can both be guaranteed in theory. For asymptotic convergence, it is only required that uncertainties and disturbances are bounded and the bounds may be unknown by virtue of adaptive laws. The obtained results are then applied to partial integrated guidance and control design for a missile, completing desired terminal impact angle and hit-to-kill interception. Finally, simulations are conducted on the nonlinear longitudinal missile model and results demonstrate the effectiveness of the proposed method.

Xianghua Wang

Papers

Partial Integrated Missile Guidance and Control with Finite Time Convergence

A novel sliding mode observer for state and fault estimation in systems not satisfying matching and minimum phase conditions

Partial Integrated Guidance and Control for Missiles with Three-Dimensional Impact Angle Constraints

Fault-Tolerant Attitude Control for Rigid Spacecraft Without Angular Velocity Measurements

Partial Integrated Guidance and Control with Impact Angle Constraints