Optimal Proportional-Integral Guidance Law

Shaoming He*, Chang Hun Lee, Hyo Sang Shin, Antonios Tsourdos

*此作品的通讯作者

科研成果: 书/报告/会议事项章节章节同行评审

摘要

This chapter proposes a new optimal guidance law based on PI concept to reduce the sensitivity to unknown target maneuvers. By augmenting the integral ZEM as a new system state, a linear quadratic optimization problem is formulated and then the proposed guidance law is analytically derived through optimal control theory. The closed-form solution of the proposed guidance law is presented to provide better insight of its properties. Additionally, the working principle of the integral command is investigated to show why the proposed guidance law can be utilized to reduce the sensitivity to unknown target maneuvers. The analytical results reveal that the proposed optimal guidance law is exactly the same as an instantaneous direct model reference adaptive guidance law with a specified reference model. The potential significance of the obtained results is that it can provide a point of connection between PI guidance laws and adaptive guidance laws. Therefore, it allows us to have better understanding of the physical meaning of both guidance laws and provides the possibility in designing a new guidance law that takes advantages of both approaches. Finally, the performance of the guidance law developed is demonstrated by nonlinear numerical simulations with extensive comparisons.

源语言英语
主期刊名Springer Aerospace Technology
出版商Springer Nature
91-110
页数20
DOI
出版状态已出版 - 2020

出版系列

姓名Springer Aerospace Technology
ISSN(印刷版)1869-1730
ISSN(电子版)1869-1749

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引用此

He, S., Lee, C. H., Shin, H. S., & Tsourdos, A. (2020). Optimal Proportional-Integral Guidance Law. 在 Springer Aerospace Technology (页码 91-110). (Springer Aerospace Technology). Springer Nature. https://doi.org/10.1007/978-3-030-47348-8_5