Abstract: As one key structure of the general aircraft, the wing unit has a significant impact on the flight safety performance of the whole aircraft. In order to evaluate the static structural strength of the all-composite wing of a general aircraft, the finite element model of the whole structure of the wing unit is established by using shell elements in MSC. Patran software. The finite element analysis of the wing unit under the critical load is carried out, and the stress and strain results of the wing unit are given. The test parts and equipment of the wing unit were designed and manufactured, and the test verification was performed. The experimental results are basically in good agreement with the theoretical calculation values, which shows that the finite element model and analysis method of the wing unit are correct and feasible, and provides a basis for the optimization and improvement of the structure in the future.

Key words: wing unit, finite element analysis, stress test, test verification