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Loading method and loading device for static strength test of aircraft wing

A loading device and static strength technology, which is applied in the field of aeronautical experiments and testing, can solve problems such as the inability to ensure that the loading direction is always perpendicular to the surface of the wing, and the loading force is evenly distributed, so as to achieve high stability and stiffness, reduce experimental errors, and improve The effect of experimental precision

Active Publication Date: 2022-05-10
YANSHAN UNIV
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  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The invention provides a four-degree-of-freedom wing experimental loading device, which aims to solve the problem that the loading direction cannot always be perpendicular to the wing surface and the problem that the loading force is uniformly distributed when performing the wing static test by other loading methods

Method used

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  • Loading method and loading device for static strength test of aircraft wing
  • Loading method and loading device for static strength test of aircraft wing
  • Loading method and loading device for static strength test of aircraft wing

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Embodiment 1

[0041] A plurality of wing static strength test loading devices 23 based on parallel mechanisms and lever systems are selected to carry out relevant static test loading on the aircraft wing 22. The loading platform 6 has four degrees of freedom, which are respectively two translational degrees of freedom and two degrees of freedom. rotational degrees of freedom.

[0042] S1. Carry out theoretical analysis on the aircraft wing 22, preset the force that needs to be loaded theoretically and the pose that needs to be achieved by the wing static test loading device 23, and measure the corresponding force through the first force sensor 10 installed on the branch. The force state on the branch, after detecting the force state on the branch, through the force conversion equation Calculate the size and direction of the loading platform 6 being subjected to the reaction force of the aircraft wing 22, where F is the reaction force of the wing to the loading device, For the gravity of ...

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Abstract

The invention proposes a loading method and device for a static strength test of an aircraft wing, which includes a two-rotation and two-shift four-degree-of-freedom parallel loading device and a two-stage lever system. The parallel loading device includes a fixed platform, a loading platform, a force sensor, a first motion branch, a second motion branch, a third motion branch, and a fourth motion branch. The loading platform and the fixed platform are connected through four motion branches, and two secondary The lever system is located on the loading platform, symmetrically distributed on both sides above the loading platform, each secondary lever system has four loading points, and the whole device has a total of eight loading points. Force sensors are installed on the four motion branches. The drives of the four motion branches all choose to drive the moving pair, which is driven by hydraulic cylinders. The invention can simultaneously adjust the direction and magnitude of the loading force during the loading process of the wing static test, effectively reducing the error of the test.

Description

technical field [0001] The invention relates to the field of aviation experiment testing, in particular to a loading method and a loading device for an aircraft wing static strength experiment based on a parallel mechanism and a lever system. Background technique [0002] In the ground strength test of the aircraft structure, the static test of the whole aircraft is an important test item for checking the bearing capacity, stiffness and other characteristics of the aircraft structure. In the whole machine static test, in order to simulate the loading force on the wing in flight, it is necessary to adjust the loading direction to ensure that the loading force is perpendicular to the wing surface. [0003] At present, the loading device for static experiments on aircraft wings is mainly the adhesive tape-lever loading system. Other common static loading methods for wings include pallet loading and airbag loading. The tape-lever system requires tape to be applied to the surfac...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M13/00G01N3/08B64F5/60
CPCG01N3/08G01M13/00B64F5/60G01N2203/0676G01N2203/0682
Inventor 陈子明徐宗国刘建鑫张政杨文韬安俊杰殷鹏叶文凯张忠坡闫浩
Owner YANSHAN UNIV
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