Adaptive integrated guidance and control for impact angle constrained interception with actuator saturation

Abstract

This paper considers the integrated guidance and control (IGC) problem for impact angle constrained interception against manoeuvring targets with actuator saturation constraint. Based on the backstepping technique, an adaptive IGC law is presented to address this problem, where a fixed-time differentiator is proposed to estimate the derivatives of virtual control inputs to avoid the inherent problem of “explosion of complexity” suffered by the typical backstepping. Furthermore, an auxiliary first-order filter is introduced into the IGC law to cope with the actuator saturation constraint. The stability of the closed-loop system is strictly proved. Finally, the superiority of the proposed IGC law is verified by comparison simulations.

A Low-Order Partial Integrated Guidance and Control Scheme for Diving Hypersonic Vehicles to Impact Ground Maneuver Target

“…In equation ( 25), δ a , δ e , and δ r are the right elevon, left elevon, and rudder fin deflections of the GHV, respectively. In equation (27), m i,j , i � x, y, z, j � 1, 2, 3 are the coefficients related to first-degree control surface fin deflections.…”

“…In recent years, most studies on the design of the G&C system for air vehicles to impact maneuver target are based on the full-state coupled high-order IGC design model, which contains angles of line-of-sight (LOS), rotational Euler angles of the air vehicle, three-channel body rates, and other motion state variables. e IGC system design is accomplished through the backstepping control method or dynamic surface control method, and the uncertainties containing acceleration components of the target are estimated through some techniques, such as ESO [18][19][20][21][22][23][24], sliding mode observer [25,26], and adaptive law [27]. e effectiveness of this kind of design method has been verified by nonlinear simulation results in the published literatures.…”

Full state‐constrained integrated guidance and control for aerial interceptors with tunnel prescribed performance using integral barrier Lyapunov function

“…The Nussbaum function combined with a hyperbolic tangent function was an effective method to cope with the input-saturated problems, 18 where the hyperbolic tangent function was used to approximate the saturation function, and the approximation error was compensated by the Nussbaum function. [19][20][21] What is more, the IGC schema incorporated with an auxiliary first-order system 22 was another valid method to deal with this issue, where the discrepancy of the saturated input signals was compensated in a feedback manner.…”

Robust Adaptive Composite Learning Integrated Guidance and Control for Skid-to-Turn Interceptors Subjected to Multiple Uncertainties and Constraints

“…Although the future course of action of the target in [16], as a type of uncertainty, cannot be predicted, the effect of the target maneuver can be counteracted by utilizing adaptive control techniques. Meanwhile, many control algorithms have been reported based on adaptive control [17], DSC [18,19], command filtered control [20], sliding mode control [21,22], barrier Lyapunov function (BLF) [23,24], and a fixed-time differentiator [25] for the constrained variables of IGC system. In [26], a three-dimensional integrated guidance and control law is developed, which relies on the advantage of dynamic surface control and extended state observer techniques to address input saturation and actuator failure.…”