Adaptive sliding mode fault-tolerant control for hypersonic vehicle based on radial basis function neural networks

Rongyu Zhai,Ruiyun Qi,Bin Jiang

doi:10.1177/1729881416673783

Abstract

In this article, an adaptive sliding mode fault-tolerant control scheme is proposed to address the problem of robust and fast attitude tracking for a hypersonic vehicle in the presence of unknown e...

Highlights

Hypersonic vehicle, whose March number is over five, has important application values in military affair and civil area for their high speed, good break-defence capability and well-known attack performance, and the study of hypersonic vehicles has become a hot topic in the aerospace area
A backstepping controller was designed by Xu and Zhang[3] for the longitudinal dynamics of a generic hypersonic flight vehicle with neural networks, and to avoid the causality contradiction, the hypersonic flight dynamics were transformed into a strict-feedback form from which the virtual control was designed in this article
Inspired by the above researches, an adaptive sliding mode fault-tolerant control (FTC) scheme based on the radial basis function neural networks (RBFNNs) technique is proposed in this article to deal with the attitude tracking problem for a hypersonic vehicle with unknown external disturbances, additive fault and partial loss of effectiveness fault

Summary

Introduction

Hypersonic vehicle, whose March number is over five, has important application values in military affair and civil area for their high speed, good break-defence capability and well-known attack performance, and the study of hypersonic vehicles has become a hot topic in the aerospace area. Inspired by the above researches, an adaptive sliding mode FTC scheme based on the RBFNN technique is proposed in this article to deal with the attitude tracking problem for a hypersonic vehicle with unknown external disturbances, additive fault and partial loss of effectiveness fault. T in equation (5) such that all closed-loop signals are bounded and the desired attitude angle vector gd 1⁄4 1⁄2d; d; dT is robustly followed when there exist unknown external disturbances, additive and partial loss of effectiveness faults. The outer-loop sliding mode controller is designed to realize attitude tracking by taking the angular rate vector o as the virtual control input. The inner-loop sliding mode controller is designed so that the command angular rate vector oc is tracked. The moment of inertia tensor is given in the study by Shtessel and McDuffie[29] and taken as 2 554486

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Conclusions