基于改进预测校正的时间协同再入制导方法

Improved predictor-corrector guidance method for time-coordination entry

针对高超声速飞行器再入滑翔过程的时间协同问题,提出一种基于开环式协同结构的时间协同预测校正制导律。所提制导律不依赖于各飞行器之间的实时通信,通过预先设置期望飞行时间进行协同信息共享。纵向制导律在传统预测校正的基础上进行改进,引入归一化加权误差,同时考虑剩余航程误差与剩余飞行时间误差,采用全弹道积分预测剩余航程和剩余飞行时间,每个制导周期通过牛顿迭代法求解倾侧角幅值,完成兼顾时间协同和空间精度的纵向制导过程。仿真实例表明:通过选择合适的加权误差系数,所提制导律可实现对再入飞行时间的有效调节,导引多飞行器在期望飞行时间到达指定再入交班点。蒙特卡罗仿真验证了所提制导律的鲁棒性。

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.