Fault-tolerant guidance for hypersonic vehicle based on predictor-corrector strategy

Abstract

A fault-tolerant guidance law using the predictor-corrector theory for a hypersonic vehicle (HSV) is designed to solve the problem of online trajectory planning under faults in reentry phase. Once the fault occurs, based on the quasi equilibrium glide condition (QEGC), the new limitations of reentry corridor are transformed into the constraints of attack angle, which are used to obtain the prediction of attack angle with Newton iterative method. Then, with the attack angle obtained, the roll angle is predicted based on the range-to-go by iteration. Eventually, the attitude guidance of HSV is achieved to meet the demands of reentry corridor constraints combined with limits of fault. By continuous iteration, the predictor-corrector possesses a strong ability of fault-tolerant. Besides, it also does not need the stand trajectory, which makes it suitable to on-line trajectory planning, especially under fault situations. In this paper, compared with the stand model of attack angle, the simulation results show that the guidance provided in this paper is real-time and effective.