Linear quadratic optimal control-based missile guidance law with obstacle avoidance

Martin Weiss; Tal Shima

doi:10.1109/TAES.2018.2849901

Linear quadratic optimal control-based missile guidance law with obstacle avoidance

Martin Weiss, Tal Shima

Aerospace Engineering

Technion - Israel Institute of Technology

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

Abstract

Two missile guidance algorithms are proposed for the intercept and for the rendezvous of a maneuvering target, while avoiding a static obstacle by a specified avoidance distance. The guidance algorithms are derived as solutions of a linear quadratic optimal control problem and they are expressed as formulas reminiscent of the classical (augmented) proportional navigation type guidance laws. These formulas include correction terms that are responsible for obstacle avoidance and are parameterized by the minimum avoidance distance. Simulation results are used to demonstrate the performance of the two algorithms.

Original language	English
Article number	8395008
Pages (from-to)	205-214
Number of pages	10
Journal	IEEE Transactions on Aerospace and Electronic Systems
Volume	55
Issue number	1
DOIs	https://doi.org/10.1109/TAES.2018.2849901
State	Published - Feb 2019

All Science Journal Classification (ASJC) codes

Aerospace Engineering
Electrical and Electronic Engineering

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10.1109/TAES.2018.2849901

Cite this

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abstract = "Two missile guidance algorithms are proposed for the intercept and for the rendezvous of a maneuvering target, while avoiding a static obstacle by a specified avoidance distance. The guidance algorithms are derived as solutions of a linear quadratic optimal control problem and they are expressed as formulas reminiscent of the classical (augmented) proportional navigation type guidance laws. These formulas include correction terms that are responsible for obstacle avoidance and are parameterized by the minimum avoidance distance. Simulation results are used to demonstrate the performance of the two algorithms.",

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Linear quadratic optimal control-based missile guidance law with obstacle avoidance

Abstract

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