A Study on Attitude Stabilization Technique When Deploying Gliding Wing for Gliding Guided Munitions

Abstract

This paper deals with the analysis of flight stability and the design of a nonlinear attitude stabilization loop during the wing deployment for gliding guided munitions. The changes in the center of pressure (CP) location according to the wing deployment angle are first analyzed to determine if the flight stability can be ensured during the wing deployment. Additionally, an angular velocity stabilization loop is designed using the feedback linearization control methodology with a specific form of error dynamics in order to compensate for the flight instability that occurs during the wing deployment. Through an analysis of the angular velocity tracking error, it is analytically proven that the proposed attitude stabilization loop can effectively compensate for the aerodynamic moment disturbance caused by the changes in the CP location during the wing deployment. Finally, numerical simulations are conducted to validate the analysis results obtained in this study and the performance of the proposed angular velocity stabilization loop.