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Loading device for large deformation wing

A loading device and large deformation technology, applied in the direction of measuring devices, using stable tension/pressure testing material strength, instruments, etc., can solve the problem of not being able to verify the force of the aircraft, and achieve the effect of improving accuracy

Inactive Publication Date: 2019-01-08
CHINA AIRPLANT STRENGTH RES INST
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Problems solved by technology

However, during the entire loading process, the load is not perpendicular to the wing surface, and it is also impossible to verify the real force of the aircraft

Method used

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  • Loading device for large deformation wing
  • Loading device for large deformation wing
  • Loading device for large deformation wing

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Embodiment Construction

[0032] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below ...

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Abstract

The invention relates to the field of aircraft structural strength test, in particular to a loading device for a large deformation wing. The loading device comprises a frame (1), a platform (2), a platform driving actuator cylinder (3), a wing loading actuator cylinder (4), an angular displacement sensor (5), and a control mechanism, wherein the platform (2) is mounted on the frame (1), and the platform driving actuator cylinder (3) can drive the platform (2) to move; one end of the wing loading actuator cylinder (4) is arranged on the platform (2) through a base, and the other end of the wingloading actuator cylinder (4) is connected to the wing; the angular displacement sensor (5) monitors the angle between the wing loading actuator cylinder (4) and the wing; the controller (6) is connected to the platform driving actuator cylinder (3), and the controller (6) can control the platform driving actuator cylinder (3) according to the feedback of the angular displacement sensor (5). Theloading device can ensure that the load is perpendicular to the wing surface in real time, improves the accuracy of the load to the most extent, and ensures that the verification test simulates the actual wing loading situation.

Description

technical field [0001] The invention relates to the field of aircraft structure strength testing, in particular to a loading device for a large deformation wing. Background technique [0002] The aircraft structure strength test is to apply simulated loads to the aircraft structure and measure mechanical parameters such as stress, strain and displacement, so as to make a correct evaluation and estimation of the bearing capacity and structural life of the structure, and provide reliable information for verifying and optimizing the structural design. basis. In the static strength verification test, two methods of direct loading or preset angle loading are generally used in the wing loading process, and the preset angle loading method is widely used for wings with large deformation. In the fatigue strength test, the direct loading method is generally adopted. [0003] The loading method of direct loading is to load the actuator at the initial position and install it verticall...

Claims

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Application Information

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IPC IPC(8): G01N3/02G01N3/08
CPCG01N3/02G01N3/08G01N2203/0003G01N2203/0019G01N2203/0075G01N2203/0676G01N2203/0682
Inventor 高建贺谦杜星
Owner CHINA AIRPLANT STRENGTH RES INST
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