Reduction of UAV vibration response by addition of T-Spar in wing structure

Abstract This study is performed to evaluate the vibration response of UAVs during flight tests. The UAV’s vibration response is measured using the existing accelerometer installed on the UAV flight controller. An additional accelerometer is placed inside the UAV fuselage near the flight controller board for high-frequency vibration measurement. The vibration response analysis shows that the maximum acceleration response occurs when a UAV is flying in turning mode. An additional T spar is added between two existing tubular spars in the UAV wing to increase the wing stiffness. It was shown from the flight test that the acceleration response amplitude reduces by 26,84% when using T spar on the wing structure.