An Optimal Geometrical Guidance Law for Impact Time and Angle Control

This article proposes an impact time and angle control guidance law based on geometry without estimating the time-to-go. A moving virtual target is artificially placed on the desired collision line, and the missile pursues the virtual target to satisfy the desired impact angle. The moving speed of t...

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Veröffentlicht in:IEEE transactions on aerospace and electronic systems Jg. 59; H. 6; S. 1 - 10
Hauptverfasser: Hou, Libing, Luo, Haowen, Shi, Heng, Shin, Hyo-Sang, He, Shaoming
Format: Journal Article
Sprache:Englisch
Veröffentlicht: New York IEEE 01.12.2023
The Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Schlagworte:
Collision dynamics
Estimation
Geometrical method
Heuristic algorithms
impact angle control
impact time control
Missiles
Numerical simulation
Optimal control
optimal guidance
Target tracking
Terminal guidance
Trajectory
ISSN:0018-9251, 1557-9603
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Zusammenfassung:This article proposes an impact time and angle control guidance law based on geometry without estimating the time-to-go. A moving virtual target is artificially placed on the desired collision line, and the missile pursues the virtual target to satisfy the desired impact angle. The moving speed of the virtual target is also dynamically adjusted to cater for the impact time constraint. We prove that the proposed geometrical rule ensures target capturability and zero terminal guidance command. Then, the standard optimal control is leveraged to develop an analytical guidance command that drives the missile to converge to the desired collision course. Numerical simulations are conducted to validate the proposed guidance law.
Bibliographie:ObjectType-Article-1
SourceType-Scholarly Journals-1
ObjectType-Feature-2
content type line 14
ISSN:0018-9251
1557-9603
DOI:10.1109/TAES.2023.3305974