Abstract: The test technology of the trailing edge of a full-size variable camber wing with the structural characteristics of large deformation is studied in the paper. Based on the comparative study of several tracking-loading methods, a tracking-loading scheme based on the joint active control of screw module and force control actuator is proposed. The method is verified by the ground test of the trailing edge structure of variable camber wing. The test results show that the loading accuracy and measurement results meet the test requirements, and the aerodynamic load can be accurately applied by using this method, which provides a reference for the load application of movable wing surface. The experimental data can provide a basis for the design and modification of the trailing edge of variable camber wing.