Finite element assisting for effective ground vibration test planning on very flexible aircraft

In the present investigation, we suggest a strategy for arranging the modal testing of unmanned aerial vehicles (UAVs) with high aspect ratio wings, such as excitation point, support, and measurement locations plan for the effective test configuration. As a basis for deciding the excitation, sensor placement, and support locations, a model in finite element was utilized to calculate the normal modes and frequencies. Using the modal assurance criteria (MAC) method, the sensor placement and excitation locations were evaluated. Several techniques, such as Normalized Kinetic Energy, Normalized Modal Displacements (NMD), and Mode Participation Analysis, were used to determine the appropriate excitation point positions. Using the sensor elimination by modal assurance criterion (SEAMAC), the optimum sensor location can be determined. Based on the results of this study on the location of the excitation point and the placement of the sensor, there is good mode shape independence for the five significant mode shapes.