It occur that the loading point changes with the test piece in the aircraft structure test. In particularly, the large deformation of the wing will cause the issue that loading point is not perpendicular with the flat of the wing. In this paper, a kind of servo loading systems is applied in composite materials airplane wing. The wing is divided into N characteristic of flying points by using the method of finite element analysis. To keep all levels of loading points are vertical with the flat of wing we keep the fly points move with loading. It implements vertical following loading. This system is used to complete the highSaspectSratio test. The test results show that the system can realize the test of the UAV by using the servo load systems,and the laoding procedure is smooth. The test piece is no jitter, its deformation is uniform, and the strain data meets the test requirements which can offer a reference for the analogous loading systems and has a large practical significance and application value.