ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Design of guidance law with precise impact angle and time control
Received date: 2024-06-04
Revised date: 2024-06-24
Accepted date: 2024-07-19
Online published: 2024-07-23
Supported by
National Science Fund for Distinguished Young Scholars(62025301);National Natural Science Foundation of China(62373055);Postdoctoral Innovative Talents Support Program(BX20230461);China Postdoctoral Science Foundation(2023M740249)
Spatial-temporal constrained guidance is a method that simultaneously meets impact angle and time constraints. To address the problem of missile terminal guidance， a spatial-temporal constrained guidance law with precise control capability is designed in this paper. First， based on the time-to-go estimation of the optimal impact angle constrained guidance law， a varying-gain impact angle constrained guidance law whose time-to-go can be precisely predicted is inversely derived without any small angle approximation. Second， an impact-time error feedback term is added to the above guidance law to obtain the singularity-free spatial-temporal guidance law for simultaneous precise control of impact angle and time. Third， by introducing the remaining trajectory length as an independent variable， the proposed spatial-temporal guidance law is extended to practical scenarios with missile speed variation. Finally， the effectiveness and advantages of the proposed guidance law are verified through several numerical simulations.
Wei DONG , Xin YI , Houjun ZHANG , Chunyan WANG , Fang DENG . Design of guidance law with precise impact angle and time control[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2025 , 46(4) : 330787 -330787 . DOI: 10.7527/S1000-6893.2024.30787
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