طراحي و تحليل سازه بال كامپوزيتي يك پهپاد خاص با نسبت منظري بالا

The purpose of this study is to design the composite wing structure of a special UAV with a high aspect ratio. Loads entranced on the wings are calculated, and what distinguishes this design process with similar samples is the use of compression loading on the entire surface of the wing. Load on the wing is calculated in without mounted wing on the fuselage mode. an‎d the structure of the wing has been analyzed in term of strength and displacement in mode of loading. In fact, it can be argued that the use of compressive loading in the wing design is an advantage for the aerodynamic and structural group. Because the pressure data is provided at many points on the wing surface, which will make the results much more accurate. Then, the design of ABAQUS finite element software is analyzed and the design is validated to calculate the margin of safety and fracture of the layers in different parts of the structure of the wing. The margins safety in the structure are all positive and are on average higher than , and the fracture results based on the Tsai Hill criterion are all below .