M&S를 이용한 항공기용 통합형 전기식 구동장치의 동적 안전성 연구

Electro-mechanical actuator installed on aircraft consists of a decelerator which magnifies the torquein order to rotate an axis connected with aircraft control surface, a control section which controls themotor assembly through receiving orders from cockpit and a motor assembly which rotates thedecelerator. Electro-mechanical actuator controls aircraft altitude, position, landing, takeoff, etc. It is animportant part of a aircraft. Aircraft maneuvering causes vibrations to electro-mechanical actuator. Vibrations may result in structural fatigue. For that reason, it is necessary to analyze the system structuralsafety. In order to analyze the system structural safety. It is needed reasonable finite elementmodel and structural response stress closed to real value. In this paper, analytic model is derived byusing the simplified finite element model, and damping ratio which is closely related to response stressis derived by using modal test. So, we developed analytic model in less than 10 % error rate, comparedwith modal test. Vibration response stress close to real value was estimated from analytic modelmodified with modal experimental damping ratio. Estimation method for damping ratio with empiricalformula was suggested partly. Finally, It was proved that electro-mechanical actuator had reasonablestructure margin of safety at environmental random 3σstress during life cycle.