Gliding-Guided Projectile Attitude Tracking Controller Design Based on Improved Adaptive Twisting Sliding Mode Algorithm

Wenguang Zhang,Wenjun Yi,Antonio Concilio

doi:10.1155/2020/1480427

Abstract

The finite-time attitude tracking control for gliding-guided projectile with unmatched and matched disturbance is investigated. An adaptive variable observer is used to provide estimation for the unmeasured state which contains unmatched disturbance. Then, an improved adaptive twisting sliding mode algorithm is proposed to compensate for the matched disturbance dynamically with better transient quality. Finally, a proof of the finite-time convergence of the closed-loop system under the disturbance observer and the adaptive twisting sliding mode-based controller is derived using the Lyapunov technique. This attitude tracking control scheme does not require any information on the bounds of uncertainties. Simulation results demonstrate that the proposed method which is able to acquire the minimum possible values of the control gains guaranteeing the finite-time convergence performs well in chattering attenuation and tracking precision.

Highlights

The most significant difference between gliding-guided projectile (GGP) and traditional projectile is that the former one is equipped with wing assembly
The wing assembly makes the projectile be capable of gliding, which enables the gliding-guided projectile to strike the target from a greater distance
The wing assembly provides the projectile with the ability of controlling its flight path, which means that the gliding-guided projectile can achieve precise strikes [1, 2]

Summary

Introduction

The most significant difference between gliding-guided projectile (GGP) and traditional projectile is that the former one is equipped with wing assembly. The wing assembly provides the projectile with the ability of controlling its flight path, which means that the gliding-guided projectile can achieve precise strikes [1, 2]. Due to these advantages, the gliding-guided projectile has become the current research hotspot. The design of GGP, especially the design of the attitude controller, is a challenging task This is due to the fact that the GGP model suffers from high nonlinearity and strong coupling characteristics. A GGP is vulnerable to various disturbances during flight, such as the aerodynamic parameter perturbation, the unmodeled dynamics, and strong and sudden wind gusts which change greatly along the latitude and longitude [3]

Methods

Results

Conclusion