Terminal guidance method with impact angle constraints for hypersonic morphing vehicle
Aimed at solving the terminal guidance problem of hypersonic morphing vehicles,a ter-minal guidance method based on proportional control and predictor-corrector concept is proposed,which can enhance the flight effect under the constraints of impact angle.Based on the dynamic e-quations of hypersonic flight vehicles,the mathematical representation of guidance command was constructed with the framework of three-dimensional biased proportional guidance method.The bias terms of the guidance law were corrected online by predicting the deviation of the impact angle and target angle in real time.Simulation tests under nominal and mission-change conditions were carried out.Targeting simulation experiments were completed under Monte Carlo disturbance conditions.The simulation results show that the terminal guidance method has high accuracy and strong anti-dis-turbance capability.It has autonomy and can adapt to the mission-change condition.The guidance law takes advantage of the morphing vehicles,which has a better terminal flight effect compared with traditional vehicles.
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