Application of an optimal control algorithm for a gyroscope system of a homing air-to-air missile

Missile homing precision depends mainly on the correct determination of the current angle between the Gyroscope System Axis (GSA) and the target line-of-sight (LOS). A gyroscope automatic control system shall ensure spontaneous levelling of this angle, hence, constant homing of the gyroscope system...

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Main Authors: Izabela Krzysztofik, Zbigniew Koruba
Format: Article
Language:English
Published: Vilnius Gediminas Technical University 2021-04-01
Series:Aviation
Subjects:
Online Access:https://journals.vgtu.lt/index.php/Aviation/article/view/13899
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spelling doaj-779f0bd19df9435cb3728a22c60f7ace2021-08-17T10:59:14ZengVilnius Gediminas Technical UniversityAviation1648-77881822-41802021-04-01251414910.3846/aviation.2021.1389913899Application of an optimal control algorithm for a gyroscope system of a homing air-to-air missileIzabela Krzysztofik0Zbigniew Koruba1Department of Applied Computer Science and Armament Engineering, Faculty of Mechatronics and Mechanical Engineering, Kielce University of Technology, Kielce, PolandDepartment of Applied Computer Science and Armament Engineering, Faculty of Mechatronics and Mechanical Engineering, Kielce University of Technology, Kielce, PolandMissile homing precision depends mainly on the correct determination of the current angle between the Gyroscope System Axis (GSA) and the target line-of-sight (LOS). A gyroscope automatic control system shall ensure spontaneous levelling of this angle, hence, constant homing of the gyroscope system axis in on the LOS, i.e. tracking the target by the head. The available literature on the subject lacks a description of how to use the controlled gyro system in the process of guiding the missile onto the target. In this paper, the authors present the original development of an optimal control algorithm for a gyro system with a square quality indicator in conditions of interference and kinematic influence of the missile deck. A comparative analysis of the LQR with the PD regulator was made. PD regulator parameters are also selected optimally, using the Golubencev method, so that the transition process of the homing system fades over a minimal time, while simultaneously ensuring the overlapping of the gyroscope axis with the target line-of-sight. The computer simulation results have been obtained in a Matlab-Simulink environment and are presented in a graphic form.https://journals.vgtu.lt/index.php/Aviation/article/view/13899non-linear dynamicsgyroscope systemoptimal regulatorguidancemissile flight
collection DOAJ
language English
format Article
sources DOAJ
author Izabela Krzysztofik
Zbigniew Koruba
spellingShingle Izabela Krzysztofik
Zbigniew Koruba
Application of an optimal control algorithm for a gyroscope system of a homing air-to-air missile
Aviation
non-linear dynamics
gyroscope system
optimal regulator
guidance
missile flight
author_facet Izabela Krzysztofik
Zbigniew Koruba
author_sort Izabela Krzysztofik
title Application of an optimal control algorithm for a gyroscope system of a homing air-to-air missile
title_short Application of an optimal control algorithm for a gyroscope system of a homing air-to-air missile
title_full Application of an optimal control algorithm for a gyroscope system of a homing air-to-air missile
title_fullStr Application of an optimal control algorithm for a gyroscope system of a homing air-to-air missile
title_full_unstemmed Application of an optimal control algorithm for a gyroscope system of a homing air-to-air missile
title_sort application of an optimal control algorithm for a gyroscope system of a homing air-to-air missile
publisher Vilnius Gediminas Technical University
series Aviation
issn 1648-7788
1822-4180
publishDate 2021-04-01
description Missile homing precision depends mainly on the correct determination of the current angle between the Gyroscope System Axis (GSA) and the target line-of-sight (LOS). A gyroscope automatic control system shall ensure spontaneous levelling of this angle, hence, constant homing of the gyroscope system axis in on the LOS, i.e. tracking the target by the head. The available literature on the subject lacks a description of how to use the controlled gyro system in the process of guiding the missile onto the target. In this paper, the authors present the original development of an optimal control algorithm for a gyro system with a square quality indicator in conditions of interference and kinematic influence of the missile deck. A comparative analysis of the LQR with the PD regulator was made. PD regulator parameters are also selected optimally, using the Golubencev method, so that the transition process of the homing system fades over a minimal time, while simultaneously ensuring the overlapping of the gyroscope axis with the target line-of-sight. The computer simulation results have been obtained in a Matlab-Simulink environment and are presented in a graphic form.
topic non-linear dynamics
gyroscope system
optimal regulator
guidance
missile flight
url https://journals.vgtu.lt/index.php/Aviation/article/view/13899
work_keys_str_mv AT izabelakrzysztofik applicationofanoptimalcontrolalgorithmforagyroscopesystemofahomingairtoairmissile
AT zbigniewkoruba applicationofanoptimalcontrolalgorithmforagyroscopesystemofahomingairtoairmissile
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