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Aircraft large-size panel shear loading apparatus

A large-scale wall plate and loading device technology, applied in the direction of applying stable shear force to test the strength of materials, can solve problems such as the effect of shear uniformity, and achieve the effect of simplified scale and good uniformity

Active Publication Date: 2015-11-11
CHINA AIRPLANT STRENGTH RES INST
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Problems solved by technology

Due to the influence of the boundary conditions of the wall plate specimen, the uniform pure shear area obtained by the specimen is relatively small, and the E-fixture device applies shear loads around the wall plate, but the acting points of the load are all resultant force points. Uniformity of cut has a great influence

Method used

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  • Aircraft large-size panel shear loading apparatus
  • Aircraft large-size panel shear loading apparatus
  • Aircraft large-size panel shear loading apparatus

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Embodiment Construction

[0022] In order to better understand the aircraft large panel shear loading device according to the scheme of the present invention, below in conjunction with Attached picture A preferred embodiment of the large-scale aircraft panel shear loading device of the present invention is further elaborated.

[0023] refer to figure 1 - Figure 7 , The aircraft large panel shear loading device provided by the present invention comprises a first straight-side loading assembly 100, a second straight-side loading assembly 600, a curved-side loading assembly 300, a wall panel test piece 400, a first second force bar assembly 200, a second Two two force bar assemblies 500, wherein, the first straight loading assembly 100 has the same structure as the second straight loading assembly 600 and is antisymmetrically arranged on both sides of the loading frame of the curved loading assembly 300, the first straight loading assembly 100 passes through The first two-force bar assembly 200 is...

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Abstract

The invention relates to the technical field of shear load loading of an aircraft large-size panel and particularly relates to an aircraft large-size panel shear loading apparatus. The apparatus includes a panel test member (400) and a lug piece arranged thereon, a first straight edge shear loading assembly (100) and a second straight edge shear loading assembly (600) which are arranged at two sides of a curve edge shear loading assembly (300), are arranged symmetrically to each other relative to the curve edge shear loading assembly (300) and are respectively connected to the curve edge shear loading assembly (300) through a first two-force bar assembly (200) and a second two-force bar assembly (500). Each of the first two-force bar assembly (200) and the second two-force bar assembly (500) is composed of a plurality of two-force bars. The aircraft large-size panel shear loading apparatus, when being used for performing a test, is simplified in scale and can achieve better uniformity. The main framework of the curve edge shear loading assembly is assembled in a manner of multi-section jointing, so that the apparatus is available in test members in different sizes just by changing a few parts, thereby providing technical guarantee for aircraft models being researched.

Description

Technical field [0001] The invention involves the technology field of shear load loading of large aircraft wall boards. Specifically, it involves a large aircraft large wall sheet shear and loading device. Background technique [0002] The structure of the fuselage wall is a very typical and important structural form in the aircraft structure, which is complicated, including stretch / compression, shear, bending, and gas load.The strength test of the fuselage wall board is an important basis for the design of the aircraft body. Among them, the shear load loading technology is one of the key technologies in the test verification technology. At present, there are two main methods for the application method of cutting loads of the wall board. One is to useApplying the load to the wall board on the end of the test parts to the end of the trial part, and the second is to apply shear load directly on the side of the wall board. [0003] In response to the application method of the above ...

Claims

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Application Information

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IPC IPC(8): G01N3/24
Inventor 柴亚南陈丽敏李崇邓凡臣陈向明
Owner CHINA AIRPLANT STRENGTH RES INST
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