For air defense missile, a terminal guidance law based on variable structure control theory is designed. The terminal guidance law considers the target maneuverability and the relative velocity of the missile by using variable structure control. Under the condition that the target acceleration is regarded as bounded interference, the guidance law is designed and the zero speed of sight range is realized. The simulation results show that the miss distance of the guidance law is better than the traditional PN guidance law, which verifies the effectiveness of the guidance law.
Design of Terminal Guidance Law for Air Defense Missile Based on Variable Structure Control Theory
Lect. Notes Electrical Eng.
Chinese Intelligent Systems Conference ; 2023 ; Ningbo, China October 14, 2023 - October 15, 2023
2023-10-08
8 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
Optimal Guidance and Control in a Missile Defense System
NTIS | 1967
|Missile guidance for low altitude air defense
AIAA | 1978
|