Design And Analysis Of The Measuring Structure Of Hinge Moment In The Aeroelastic Model

Aeroelastic model is widely used to investigate aero-elastic characteristics of the aero-plane model. Normally, the flutter performance is investigated in the wind-tunnel tests using the aero-elastic model. And the flutter characteristics will increase the amplitude of the vibration and the pressure over the structure surface rapidly, which would cause serious damage to the plane structures.The hinge moment test aiming at investigating the performance of the control surface is very crucial among wind tunnel tests. The controlling surface provides flight attitudes controlling feature which could make the plane fly in different flight conditions. So the hinge moment on the control surface can affect the flight attitude significantly. To verify the controlling characteristics, the hinge moment test is used to investigate the stability and the rigidity of the control surface.In order to investigate the hinge moment on controlling surface of the model, the FEM analysis and the experiment test were used in this investigation. First of all, two different kinds of measure structures were designed to satisfy the requirement of the test and the installation. The position accuracy of measuring structure in project one was ensured, and comparatively, the fastened plate in project two had stronger rigidity. A better project could be picked by comparing the results from the FEM analysis software. Secondly, the paper analyzed the frame structure of the controlling surface and the relation curve between the input hinge moment and the output force was revealed. Then the test system was used to measure the output force in several small deformation conditions. At last, the design of the structure was improved so the over-positioning effect in measuring structure could be eliminated and these improvements could make the measurement more accurate.