Fuselage panel combined load test device

A composite load and test device technology, which is applied in the field of strength test technology research, can solve problems such as uneven shear strain, difficulty in test control, and inability to realize the deformation process of fuselage panels, so as to improve the design level and shorten the design cycle. Effect

Active Publication Date: 2015-07-29
CHINA AIRPLANT STRENGTH RES INST
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Problems solved by technology

The Boeing Company of the United States discloses a device E-fixture for the test of curved plate assemblies. Due to the use of an actuator to apply axial loads, the axial strain distribution of the test piece is not uniform enough, and the device adopts the method of applying A torque approach to achieve shear load application results in uneven shear strain
The 5th generation fuselage panel test device ...

Method used

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  • Fuselage panel combined load test device
  • Fuselage panel combined load test device
  • Fuselage panel combined load test device

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Embodiment Construction

[0030] In order to better understand the fuselage panel composite load test device according to the solution of the present invention, a preferred embodiment of the fuselage panel composite load test device of the present invention will be further described below in conjunction with the accompanying drawings.

[0031] refer to Figure 1-Figure 12, the fuselage panel composite load test device provided by the present invention includes an axial load application assembly 100, a shear load application assembly 200, an air pressure and hoop load balance assembly 300, and a counterweight assembly 400, wherein the axial load application The assembly 100 is provided with a loading platform 101, a fixed end, a sliding end, and a hydraulic actuator assembly; the shear load application assembly 200 is provided with a straight edge shear load application assembly 1, a curved edge load application assembly 2, and a two-force rod assembly 3. The air pressure and hoop load applying assembly...

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Abstract

The invention relates to an aircraft fuselage panel test device, in particular to a fuselage panel combined load test device. The fuselage panel combined load test device comprises an axial load applying assembly (100), a shear load applying assembly (200), an air pressure and circumferential load balance assembly (300) and a counterweight assembly (400), wherein single load can be applied among the assemblies, and the assemblies can be freely combined to apply load. Stretching/compressing, shearing and airtight load can be applied to a fuselage panel at the same time for static force and fatigue experiments, and static force, fatigue and damage tolerance tests related to the fuselage panel can be performed, so that the design level is promoted, and the design period is shortened.

Description

technical field [0001] The invention relates to the field of strength test technology research, in particular to a composite load test device for fuselage panels. Background technique [0002] Developed countries in Europe and the United States have carried out research on the strength test technology of fuselage panels under the combined effects of tension / compression, shear and internal pressure for many years, and accumulated a lot of static, fatigue, fracture mechanics and damage of fuselage panels. With the technology and experience of tolerance characteristics, several sets of fatigue and damage tolerance test devices for fuselage panels have been developed, among which the E-fixtur of Boeing Company of the United States and the fifth-generation fuselage panel of IMA of Germany are representative. test device. The Boeing Company of the United States discloses a device E-fixture for the test of curved plate assemblies. Due to the use of an actuator to apply axial loads...

Claims

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Application Information

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IPC IPC(8): G01N3/00
Inventor 柴亚南邓凡臣李崇陈向明陈丽敏
Owner CHINA AIRPLANT STRENGTH RES INST
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