Load-bearing Analysis Of Foam-filled Rigidizable Wing

The technology of unmanned aerial vehicle(UAV) plays an increasingly important role in the modern military, in order to further improve the high-altitude and long-endurance flight ability of the UAV, and it needs lightweight design. This thesis is based on the use of the wing of the solar UAV’s lightweight design, researching load-bearing properties of foam-filled rigidizable wing, and then we got the flexural properties of the wing.The actual inner structure of rigid polyurethane foam(PU foam) material was observed by microscope. Based on this, an equivalent model(Kelvin model) was bulit to research this kind of closed-cell foam, then giving the equivalent machanical properties to research this model. Tensile test, compression test and flexrual test were done in order to get the stress-strain of the PU foam.The foam-filled beam was simulated by ANSYS based on parameters obtained by theoretical derivation and experimental test, comparing with the test results by total station. Natural frequency of the foam-filled beam’s vibration was measured by VIC-3D non-contact overall strain measurement system, comparing with the results of simulation. The results were in good agreement.The wing structure was designed based on the actual requirement. Then the wing model was made according to the designed airfoil NACA0016. Bending test was carried out on the wing model, comparing with the rusults simulated by ANSYS. The pressure and velocity on the airfoil surface in some flight speed and attack angle were computed through the analysis of the aerodynamic performance of two dimensional airfoil by Fluent software, analyzing the bending performance in the aerodynamic load of the wing.