Tensile-shear test loading device with flight structure

A technology for loading devices and aeronautical structures, applied to measuring devices, using stable tension/pressure to test the strength of materials, instruments, etc., can solve the problems of not having a large-tonnage tensile testing machine
CN102607940AInactive Publication Date: 2012-07-25NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
Publication Date
2012-07-25
Estimated Expiration
Not applicable · inactive patent

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Abstract

The invention relates to a test loading device, in particular to a tensile-shear test loading device with a flight structure. Compression bars are arranged between stand columns, the upper ends of the compression bars are extended to form an upper beam, a compression plate is arranged on the top ends of the stand columns, a lower beam is arranged on the bottom ends of the stand columns, an upper cross type joint is arranged between the compression bars on the bottom end of the upper beam, a lower cross type joint is arranged on the upper end of the lower beam between the compression bars; and a fixture is arranged between the upper cross type joint and the lower cross type joint. The test loading device provided by the invention can be used for converting pressure of a compression tester into tensile of a test piece or realizing shear force of the test piece through the action of the fixture, and can be used for a tensile or shear test of stiffened wall plates and similar structures without being provided with a special large loading tensile testing machine independently.
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Description

technical field

[0001] The invention relates to a test loading device, in particular to a tensile-shear test loading device of an aeronautical structure. Background technique

[0002] Parts such as the fuselage, wings and empennage of the aircraft bear most of the load during flight. It can be seen from their structural characteristics that these parts are all thin-walled and reinforced structures. The main failure mode of this structure is buckling, which is manifested as deformation of the surface of the structure. For the wing structure, the deformation of the surface will affect the flow field, thereby affecting the force on the wing, and then affecting the flight safety of the aircraft. Therefore, in the aircraft airworthiness specification, the wing skin is generally not allowed Buckling occurs.

[0003] Existing tests are mainly aimed at the reinforced panel structure of the wing or fuselage, and the buckling load and failure load are measured through the buckling a...

Claims

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