Structure And Strength Analysis Of DF-1 Light Sport Aircraft

Advanced composites has been widely used in aircraft structure design for its high ratio of strength to stiffness, performance designability, forming integriry and many other excellent features. Because of the simple structure and small flight loads of light sport aircraft, composite material can be used in its main structure. The usage and application parts of composite material in aircraft have become important indicators of advanced aircraft structures.DF-1 light sport aircraft has canard configuration and all fiberglass honeycomb materials. In this thesis, a three-dimensional modeling of DF-1 light aircraft was created firstly with CATIA, then, according to Standard Specification for Design and Performance of a Light Sport Airplane and Primary Category Aircraft Airworthiness Standards-Very Light Airplane, aircraft's flight loads have been calculated, and the dangerous loads also have been selected. The finite element model of the canard wing, main wing and fuselage of DF-1 were created and analysised with MSC.Patran & Nastran.The structural stress and deformation data has been worked out. The strength ratio can be got from the data based on the Tsai-Hill strength theory of composites material mechanics. The residual strength of the structure can be assessed. The results indicate that the strength of the various components of the the aircraft meets the requirements. The stress distribution of the canard wing, main wings and fuselage of DF-1 is reasonable. The structural deformation meets the requirements and the fuselage has sufficient residual strength.