활공형 유도탄약의 천이 구간 자세안정화 연구

Abstract

This study deals with the flight stability analysis and the attitude stabilization technique for gliding guided projectiles when deploying the main wing. The flight stability is analyzed using aerodynamic data determined according to the sweep angle of the main wing, and the disturbance characteristics of the pitch rate dynamics caused by the center of pressure uncertainty are investigated. Based on the investigation results, we then design a feedback linearization-based attitude stabilization controller that stabilizes the angular rate when the main wing is deployed. Additionally, the attitude stabilization performance according to the main wing deployment time is examined. In this paper, we show that the proposed method can effectively compensate for the disturbance induced during the deployment of the main wing through analytical methods and numerical simulations.