Technology of Static Test for Slat on Large-Aspect-Ration Wing

The slat is an important component of the aircraft high lift system, which play a crucial role in the takeoff and landing process of an aircraft. The slat structure of aircraft in service may undergoes significant deformation and inclination due to the wing deformation for civil airliners with high aspect ratio wings, which make the test load on the wing and the direction of the test load on the slat must be adjusted in the static strength test. To ensure the simulation of the loading boundary and the application of loads for each section of the slat structure accurately, the structure strength test schemes of slat based on high aspect ratio wing that meets airworthiness requirements was proposed, which taking into account the deformation characteristics and structure of the slat in service under various loading conditions. Through the technical research such as specimen support, boundary simulation, load processing and load application design, a comprehensive load process flow of test and principle for slat test were established, and the key technologies such as precise load application under large deformation states and complex boundary simulation were broken through at the same time. Based on the above technical scheme, multiple assessment condition of tests such as packed up and unfolded status of slat were successfully completed on a certain type of passenger aircraft. The test results showed that the proposed test scheme is reasonable, the test fixture and loading system are reliable, and the accuracy of the control system and the load system in the test meet the error requirements and airworthiness regulations. In addition, the test results can be used to evaluate the strength and stiffness performance of the slat structure, and provide support for correction of finite element model and optimization of test measurement and control parameters, which can improve the development progress and quality of the model effectively.