Collision-geometry-based generalized optimal impact angle guidance for various missile and target motions

Chendi Li; Jiang Wang; Shaoming He; Chang Hun Lee

doi:10.1016/j.ast.2020.106204

Collision-geometry-based generalized optimal impact angle guidance for various missile and target motions

Chendi Li, Jiang Wang, Shaoming He^*, Chang Hun Lee

^*Corresponding author for this work

School of Aerospace Engineering

Research output: Contribution to journal › Article › peer-review

19 Citations (Scopus)

Abstract

A unified optimal impact angle guidance law is designed for different types of interceptors and targets. By solving a linear quadratic optimal control problem with the energy consumption weighted by an arbitrary positive function, the generalized guidance command is determined in a closed-loop feedback form. The main feature of the proposed algorithm is that it can be applied to varying-speed interceptors and targets. The weighting function also brings the command shaping capability of the proposed guidance law. To show the applicability of the proposed guidance law, several illustrative examples covering different types of interceptors and targets are provided. Numerical simulations are conducted to demonstrate the effectiveness of the proposed guidance algorithm.

Original language	English
Article number	106204
Journal	Aerospace Science and Technology
Volume	106
DOIs	https://doi.org/10.1016/j.ast.2020.106204
Publication status	Published - Nov 2020

Keywords

Impact angle control
Maneuvering target
Missile guidance
Optimal control
Speed-varying interceptor

UN SDGs

This output contributes to the following UN Sustainable Development Goals (SDGs)

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10.1016/j.ast.2020.106204

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title = "Collision-geometry-based generalized optimal impact angle guidance for various missile and target motions",

abstract = "A unified optimal impact angle guidance law is designed for different types of interceptors and targets. By solving a linear quadratic optimal control problem with the energy consumption weighted by an arbitrary positive function, the generalized guidance command is determined in a closed-loop feedback form. The main feature of the proposed algorithm is that it can be applied to varying-speed interceptors and targets. The weighting function also brings the command shaping capability of the proposed guidance law. To show the applicability of the proposed guidance law, several illustrative examples covering different types of interceptors and targets are provided. Numerical simulations are conducted to demonstrate the effectiveness of the proposed guidance algorithm.",

keywords = "Impact angle control, Maneuvering target, Missile guidance, Optimal control, Speed-varying interceptor",

author = "Chendi Li and Jiang Wang and Shaoming He and Lee, {Chang Hun}",

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year = "2020",

month = nov,

doi = "10.1016/j.ast.2020.106204",

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AU - Li, Chendi

AU - Wang, Jiang

AU - He, Shaoming

AU - Lee, Chang Hun

PY - 2020/11

Y1 - 2020/11

N2 - A unified optimal impact angle guidance law is designed for different types of interceptors and targets. By solving a linear quadratic optimal control problem with the energy consumption weighted by an arbitrary positive function, the generalized guidance command is determined in a closed-loop feedback form. The main feature of the proposed algorithm is that it can be applied to varying-speed interceptors and targets. The weighting function also brings the command shaping capability of the proposed guidance law. To show the applicability of the proposed guidance law, several illustrative examples covering different types of interceptors and targets are provided. Numerical simulations are conducted to demonstrate the effectiveness of the proposed guidance algorithm.

AB - A unified optimal impact angle guidance law is designed for different types of interceptors and targets. By solving a linear quadratic optimal control problem with the energy consumption weighted by an arbitrary positive function, the generalized guidance command is determined in a closed-loop feedback form. The main feature of the proposed algorithm is that it can be applied to varying-speed interceptors and targets. The weighting function also brings the command shaping capability of the proposed guidance law. To show the applicability of the proposed guidance law, several illustrative examples covering different types of interceptors and targets are provided. Numerical simulations are conducted to demonstrate the effectiveness of the proposed guidance algorithm.

KW - Impact angle control

KW - Maneuvering target

KW - Missile guidance

KW - Optimal control

KW - Speed-varying interceptor

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DO - 10.1016/j.ast.2020.106204

M3 - Article

AN - SCOPUS:85091595100

SN - 1270-9638

VL - 106

JO - Aerospace Science and Technology

JF - Aerospace Science and Technology

M1 - 106204

ER -

Collision-geometry-based generalized optimal impact angle guidance for various missile and target motions

Abstract

Keywords

UN SDGs

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