| 基于LSTM的落速控制最优制导策略研究 |
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| 引用本文： | 温求遒,黄文宇,卢宝钢.基于LSTM的落速控制最优制导策略研究[J].北京理工大学学报,2022,42(5):511-522. |
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| 作者姓名： | 温求遒 黄文宇 卢宝钢 |
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| 作者单位： | 1.北京理工大学 宇航学院，北京 100081 |
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| 基金项目： | 航空科学基金资助项目（202037012003）； |
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| 摘 要： | 针对高超声速飞行器末端速度控制的需求，在落角约束最优制导律的基础上，对制导律的量纲一过载特性进行分析，证明了通过调节制导参数，能够对飞行末端速度产生影响；进而提出了制导律末速控制的策略，并基于此提出了对气动偏差适应的制导律在线设计方案；采用LSTM深度神经网络，进行了制导律参数在线设计算法的实现；最后进行了弹道仿真，对所设计的制导参数在线设计算法进行验证. 仿真结果表明其在保证末端命中精度和落角满足指标要求的前提下，对弹道的末端速度控制能力有显著提升.
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| 关 键 词： | 飞行器控制 减速控制 落角约束最优制导律 在线设计 长短时记忆神经网络 |
| 收稿时间： | 2021-01-26 |
Research on Optimal Guidance Strategy of Terminal Speed Control Based on LSTM |
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| WEN Qiuqiu,HUANG Wenyu,LU Baogang.Research on Optimal Guidance Strategy of Terminal Speed Control Based on LSTM[J].Journal of Beijing Institute of Technology(Natural Science Edition),2022,42(5):511-522. |
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| Authors: | WEN Qiuqiu HUANG Wenyu LU Baogang |
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| Affiliation: | 1.School of Aerospace, Beijing Institute of Technology, Beijing 100081, China2.Beijing Institute of Space Long March Vehicle, Beijing 100076, China |
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| Abstract: | In response to the need for terminal speed control of hypersonic aircraft, the dimensionless overload characteristics of the guidance law were analyzed firstly on the basis of the optimal guidance law for landing angle constraints. The analysis results show that the guidance parameter adjustment can impact on the terminal speed. And then a terminal speed control strategy was proposed for the guidance law, and based on this, an online guidance law design strategy was proposed to adapt aerodynamic deviation. On this basis, a long short-term memory (LSTM) deep neural network algorithm was used to carry out online design algorithm of the guidance law parameters. Finally, a trajectory simulation was carried out to verify the online design algorithm of designed guidance parameter. The simulation results show that under the premise of ensuring the terminal accuracy and landing angle within the index requirements, the proposed method can significantly improve the ability of terminal speed control. |
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