Servo loading device for large deformation wing static test

Abstract

The invention provides a servo loading device for large deformation wing static test and relates to the technical field of airplanes. The servo loading device comprises a support, a sliding table, a translation driving device, a clamping device, a loading device, a position detection device and a control device, wherein the support can be fixed on the ground; the sliding table is arranged on the support in a sliding manner and located above a wing; the translation driving device is arranged on the support, connected with the sliding table and used for driving the sliding table to move linearlyin the preset direction; the clamping device is used for clamping and fixing the wing; the loading device has a first end and a second end, the first end is hinged to the sliding table, the second end is connected with the clamping device by a connection part, and the loading device is used for towing the wing; the position detection device is used for detecting the position change of the clamping device and sending the displacement information; the control device is used for receiving the displacement information and accordingly controls the translation driving device to drive the sliding table to move linearly in the preset direction so that the connection part can be perpendicular to the wing always.

Description

technical field [0001] The invention relates to the technical field of aircraft, in particular to a dynamic loading device for a large deformation wing static test. Background technique [0002] With the continuous improvement of the comprehensive performance requirements of aircraft, large aspect ratio and large deformation wings are a major feature of the new generation of aircraft (especially unmanned aerial vehicles). Adoption has become the main indicator to measure the advancement of aircraft structure. Composite wings with a large aspect ratio are characterized by large root bending moments and large deformation of the wing bending structure, which poses a greater challenge to the static test of the wing. [0003] Existing loading equipment for large-deformation wing static tests can apply test loads at several positions on the wing, and the direction of the test load is fixed, so as to simulate the aerodynamic load of the wing during actual flight. In this way, the...

AI Technical Summary

Problems solved by technology

However, after the test load is applied to the wing, under the action of the test load, the wing usually undergoes bending deformation, especially for a wing with a large aspect ratio, the magnitude of the bending deformation is relatively large, so that the test load The direction of the direction of the aerodynamic load has a certain deviation

The greater the magnitude of the bending deformation of the wing, the more obvious the deviation, which eventually leads to a larger error between the data of the static test and the data of the theoretical calculation

Therefore, it is difficult to accurately verify the stiffness, stability and bearing capacity of the wing structure, which is not conducive to judging the performance of the wing, and is also not conducive to the design and improvement of the wing.

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