This paper proposes a novel composite integrated guidance and control (IGC) law for missile intercepting against unknown maneuvering target with multiple uncertainties and control constraint. First, by using back-stepping technique, the proposed IGC law design is separated into guidance loop and control loop. The unknown target maneuvers and variations of aerodynamics parameters in guidance and control loop are viewed as uncertainties, which are estimated and compensated by designed model-assisted reduced-order extended state observer (ESO). Second, based on the principle of active disturbance rejection control (ADRC), enhanced feedback linearization (FL) based control law is implemented for the IGC model using the estimates generated by reduced-order ESO. In addition, performance analysis and comparisons between ESO and reduced-order ESO are examined. Nonlinear tracking differentiator is employed to construct the derivative of virtual control command in the control loop. Third, the closed-loop stability for the considered system is established. Finally, the effectiveness of the proposed IGC law in enhanced interception performance such as smooth interception course, improved robustness against multiple uncertainties as well as reduced control consumption during initial phase are demonstrated through simulations.

Back-stepping active disturbance rejection control design for integrated missile guidance and control system via reduced-order ESO.

Three dimensional impact angle constrained integrated guidance and control for missiles with input saturation and actuator failure

Impact Angle Constrained Integrated Guidance and Control for Maneuvering Target Interception

A new sliding mode control design for integrated missile guidance and control system

In this paper, a novel cascade type design model is transformed from the simulation model, which has a broader scope of application, for integrated guidance and control (IGC). A novel non-singular terminal dynamic surface control based IGC method is proposed. It can guarantee the missile with multiple disturbances fast hits the target with high accuracy, while considering the terminal impact angular constraint commendably. And the stability of the closed-loop system is strictly proved. The essence of integrated guidance and control design philosophy is reached that establishing a direct relation between guidance and attitude equations by “intermediate states” and then designing an IGC law for the obtained integrated cascade design model. Finally, a series of simulations and comparisons with a 6-DOF nonlinear missile that includes all aerodynamic effects are demonstrated to illustrate the effectiveness and advantage of the proposed IGC method.

Non-singular terminal dynamic surface control based integrated guidance and control design and simulation

This paper presents an approach of integrated guidance and control (IGC) design for interception of maneuvering targets (evaders). An IGC model with uncertainties in the pitch plane is formulated, and, by adopting a backstepping scheme, an adaptive nonlinear IGC approach is developed. Theoretical analysis shows that the design approach makes the line-of-sight (LOS) rate be input-to-state stable (ISS) with respect to target maneuvers and missile model uncertainties, and the stability of the missile dynamics can be guaranteed as well. The numerical simulation confirms the effectiveness of the proposed design approach.

Adaptive Integrated Guidance and Control Based on Backstepping and Input‐to‐State Stability

The focus of this paper is to achieve opinion consensus for the opinion dynamics model in the network with stubborn individuals It has been shown in most of the existing works that the opinion dynamics model in the network with stubborn individuals usually could not achieve opinion consensus In contrast with these results, by adding an integral term that describes the historical knowledge of the neighboring opinions, we propose a modified model of the existing Taylor’s model The primary feature of this modified model is that as long as the underlying graph is connected, opinion consensus can be realized in the network with stubborn individuals we prove this opinion consensus by employing a Lyapunov function based method Finally, we present an example to illustrate our main result

Han Yan

Papers

Adaptive Integrated Guidance and Control Based on Backstepping and Input‐to‐State Stability

Achieving Consensus of Opinion Dynamics in Networks with Stubborn Individuals