Optimal Error Dynamics in Missile Guidance

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

3 引用 (Scopus)

摘要

This chapter investigates the optimal convergence pattern of the tracking error that frequently appears in missile guidance problems and proposes an optimal error dynamics for guidance law design to achieve various operational objectives. The proposed optimal error dynamics is derived by solving a linear quadratic optimal control problem through Schwarz’s inequality approach. The properties of the proposed optimal error dynamics are discussed. The significant contribution of the proposed result lies in that it can provide a link between existing nonlinear guidance laws and optimal guidance laws for missile systems. Therefore, the advantages of both techniques can be fully exploited by using the proposed approach: existing nonlinear guidance laws can be converted to their optimal forms and the physical meaning of them can then be easily explained. Four illustration examples, including zero zero-effort-miss (ZEM) guidance, impact angle guidance, impact time control, impact angle control as well as impact angle and impact time control, are provided to show how the proposed results can be applied to missile guidance law design. The performance of the new guidance laws is demonstrated by numerical simulation.

源语言英语
主期刊名Springer Aerospace Technology
出版商Springer Nature
9-39
页数31
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

指纹

探究 'Optimal Error Dynamics in Missile Guidance' 的科研主题。它们共同构成独一无二的指纹。

引用此