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WILTON MAK
Wing Model
The purpose of this project was to design a model wing for an aircraft aimed to serve as competitor of the Cessna TTX. Thus, the geometric properties of the wing had design specifications similar to that of this aircraft. The model wing was composed of a wing foam core with composite skin containing unidirectional and woven fibers. During the design of the wing model, a MATLAB code was utilized to calculate the strength and capabilities of composite design. The stiffness of the laminate, moment of inertia, maximum load, and deflection of the wing were calculated and tested for.
In the manufacturing process of the model wing, a wet layup and vacuum bagging procedure was utilized. Lamina of corresponding fibers were measured and segmented. Epoxy resin served as the bonding matrix between the lamina and the wing foam core. The fiberglass layup called for juxtaposition directly onto the foam core starting at the trailing edge, wrapping around the leading edge, and returning back to the trailing edge. Once all plies were placed, the wet fibers were cured in a vacuum process.
 Wing Foam Core with Dry Fibers |  Wet Layup |
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 Vacuum Bagging |  Vacuum Sealing Process |
 Wing After Vacuum Process |  Final Wing |
In the testing process, the model wing was loaded as a three point simply supported beam and essentially simulated two point loads at the tip of the wings. The load was applied to the wing model at the midspan, and testing of the wing included maximum deflection and ultimate failure load.
 Three-Point Testing Simulation |  Experimental Testing |
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 Laminate Failure |
After testing, the wing model was thoroughly analyzed. The wing design displayed signs of matrix debonding and observed failure appeared only on the top two plies directly along the center line where load was applied. The upper surface of the wing model experienced high compression; the top two plies of unidirectional fibers in the wing have high tensile strength but low compressive strength.