Adaptive fin failures tolerant integrated guidance and control based on backstepping sliding mode

Abstract

An integrated guidance and control (IGC) is designed in this study for a surface-to-air missile considering burned or broken fin as a fault. The IGC model in the pitch plane is developed with various uncertainties in the presence of fin failure. The considered fault may cause a change in the vehicle’s shape that leads to a change in aerodynamic coefficients and consequently in the model. To identify the new model, aerodynamic coefficients are estimated using an estimator and the result is sent to the controller. Then, an adaptive robust controller is designed using the combination of backstepping and sliding mode scheme to compensate fin failure and changes in the dynamic. The simulation results show the capability of the proposed approach, not only in normal condition but also while a part of the missile’s fin is destroyed.

Keywords

Fin failure tolerant control robust integrated guidance and control backstepping sliding mode aerodynamic coefficients estimation parameter estimation spherical unscented Kalman filter

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