| 摘要: |
| 带导弹落角约束的导引律求解需要已知导弹飞行剩余时间。针对弯曲弹道，一般的剩余时间估计方法精度较低，在假设导弹速度一定的前提下，采用n阶多项式函数近似表示剩余路径，给出了一种基于近似闭环轨迹的实用剩余时间估计方法。仿真结果表明，剩余时间估计精度平均提高了13倍以上，且计算量可以满足实时性要求。 |
| 关键词: 时间权函数 落角约束 导引律 剩余时间估计 |
| DOI： |
|
| 基金项目:国家自然科学基金(61273058) |
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| Time-to-go Estimation for Time-to-go Weighted Optimal Guidance with Impact Angle Constraints |
| LIANG Yong,ZHANG You-an,ZHAO He-wei |
| (Coast Defense Force College, Naval Aviation University, Yantai 264001, China;Department of Electrical and Electronic Engineering, Yantai Nanshan University, Yantai 265713, China) |
| Abstract: |
| The missile time-to-go is needed to solve the guidance law with the impact angle constraint. Because of the curved trajectory, the accuracy of the general time-to-go estimation is low. To solve the problem, a simple time-to-go estimation based on approximate closed-loop trajectory is proposed， in which the remaining path is approximately described by n-order polynomial func-tion under the assumption of a certain missile speed. The simulation results show that the time-to-go estimation accuracy is increased by more than 13 times on average and the amount of computation can meet the real-time requirement. |
| Key words: Time-to-go weighted function Impact angle constraint Guidance law Time-to-go estimation |
