The M2 light sport aircraft structure is constructed of composite materials and designed in accordance with ASTM 2245-16 airworthiness specifications. The composite material is an anisotropic material, and environmental factors such as temperature and humidity will reduce the material properties. The environmental impact factor must be established, and the structural load after considering the environmental impact factor will increase. The wing loads need to consider bending, torsion and shear loads. The load conditions include maneuvering loads, gust loads, and inertial loads. The wing load distribution needs to consider the distribution of lift and gravity. The composite wing load was calculated by studying the M2 aircraft load envelope, environmental impact coefficient, limit load and ultimate load. The static test of the wing of the M2 aircraft is based on the symmetrical structure of the wing bearing force, and the sandbag loading on the wing is adopted; The wing root is fixedly supported, and the left and right wings are symmetrically loaded. The wing-limited load static test, the wing ultimate load static test and the wing damage load static test were carried out; The results of the wing static test show that the ultimate load of the M2 aircraft meets the test requirements, and the deviation of the composite wing test failure load relative to the design limit load is 2%. M2 aircraft composite wing structure design meets static strength design requirements. This paper has engineering guiding significance for the structural design of lightweight sports aircraft composites.