Research on Sliding Mode Method about Three-Dimensional Integrated Guidance and Control for Air-to-Ground Missile

Zhikai Wang,Jianwei Ma,Jiangtao Fu

doi:10.5028/jatm.v11.982

Abstract

Based on adaptive sliding mode-control and back-stepping design method, an integrated guidance and control method with less calculation is proposed, which is designed for air-to-ground missile during the terminal course in threedimensional space. The model of the control system with nonlinear and coupling is simplified, then the integrated guidance and control model in pitch and yaw channel is established. The coupling terms and modeling error between channels is considered as unknown bounded disturbance. An extended state observer is developed to estimate and compensate the unknown disturbance. In the design process, the block dynamic surface method is adopted, and the first order low pass filter is introduced to avoid the problem of differential explosion present in the traditional back-stepping design method during the process of differentiating virtual control variable. The Lyapunov stability theory is used to prove the stability of the system. Finally, in the case of nominal and positive and negative perturbations of model parameters, the simulation experiments are carried outto verify the effectiveness of the proposed IGC algorithm.

Highlights

The traditional design method of the missile guidance and control system is based on the idea of separation; the system is divided into fast loop and slow loop
An IGC model in pitch and yaw channel is designed for air-to-ground missile during the terminal course in three-dimensional space, considering the precise control of rolling channel
The back-stepping method and the adaptive proximity law sliding mode control method is adopted based on this model, the ESO is introduced to estimate the state value and disturbance value

Summary

Introduction

The traditional design method of the missile guidance and control system is based on the idea of separation; the system is divided into fast loop (control loop) and slow loop (guidance loop). When using the Slide-To-Turn (STT) method, the model can be established with lower order equation, because the roll channel is relatively stable and only the pitch and yaw channels are considered (Chao et al 2014; Lee et al 2016). The modeling error and coupling between pitch and yaw channel are treated as an unknown disturbance, and the disturbance with nonlinear uncertainty is estimated with the ESO and compensated in the controller through feedback.

Results

Conclusion