基于改进预测校正的时间协同再入制导方法

For the hypersonic vehicle, a time coordination predictor-corrector guidance approach based on an open-loop coordination structure is presented to achieve the time coordination of the entry gliding process. The guidance method does not depend on real-time communication between the vehicles. The longitudinal guidance is modified on the basis of the traditional predictor-corrector guidance method. The normalized weighted error is introduced to consider both the remaining range error and flight time error obtained by calculating the full ballistic integral. To implement longitudinal guiding, Newton’s iterative approach is used to calculate the bank angle amplitude in each guidance circle. The simulations show that the guidance method can effectively adjust the flight time of the vehicle and guide multiple vehicles to reach the entry point at the expected flight time. The Monte Carlo results also demonstrate the robustness of the proposed guidance method.