Linear Quadratic Optimal Control-Based Missile Guidance Law With Obstacle Avoidance

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...

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Bibliographic Details
Published inIEEE transactions on aerospace and electronic systems Vol. 55; no. 1; pp. 205 - 214
Main Authors Weiss, Martin, Shima, Tal
Format Journal Article
LanguageEnglish
Published New York IEEE 01.02.2019
The Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Subjects
Acceleration
Algorithms
Collision avoidance
Computer simulation
Guidance (motion)
Guidance systems
Missile control
Missiles
Numerical models
Obstacle avoidance
Optimal control
Planning
Proportional navigation
Rendezvous guidance
Trajectory
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Summary: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.
ISSN:0018-9251
1557-9603
DOI:10.1109/TAES.2018.2849901