A three-point bending buckling fatigue test fixture for wing spar
A technology of fatigue test and three-point bending, which is applied in the direction of aircraft component testing, instruments, measuring devices, etc., can solve the problems of no technical solution disclosure, and achieve the effect of simple structure, low cost and easy disassembly
Active Publication Date: 2022-08-09
CHINA AIRPLANT STRENGTH RES INST
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Problems solved by technology
For the wing spar test piece, how to realize the three-point bending loading, there is no relevant technical solution disclosed at this stage
Method used
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[0029] The present invention will be further introduced below in conjunction with the accompanying drawings, refer to figure 1 , the wing spar three-point bending buckling fatigue test fixture of the present invention consists of a loading chuck 1, a loading end clamp 2, a wing spar test piece 3, a support end clamp 4, a side vertical plate 5, a support pad 6, a support The seat 7 and the base 8 are composed.
[0030] The two ends of the base 8 are provided with two symmetrical elongated holes, each elongated hole is provided with a support seat 7 and two side vertical plates 5, and the two side vertical plates 5 are located in the support seat 7. On the outside, a wing spar test piece 3 is fixed above the two support bases 7, and the two ends of the wing spar test piece 3 are respectively fixedly connected with the two side vertical plates 5 on each elongated hole, so The front and rear surfaces of the middle part of the described wing spar test piece 3 are respectively prov...
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The present invention disclosed a kind of bending and fatigue test fixture of the wing beam, including the base. There are two symmetrical long holes at both ends of the base.The two side boards are located on the outside of the support seat. The two supporting seats are fixed above the seat with wing beam testing parts. Both ends of the wing beam test parts are fixed with the two side plates on each long hole.There are two load -end splints in the middle of the beam testing parts, respectively, the top splint on the load end is equipped with a loaded chip. There is a supportable end plywood before and after both ends of the wing beam test.The invention of the structure of the wing beam is suffered from large load and large deformation, and the problem of flexion and fatigue under large deformation has formed the test ability of the three -point bending and fatigue of the wing beam test parts. At the same timeThe constraints improve the accuracy of load, displacement and life data in the piercing and fatigue test of the wing beam.
Description
technical field [0001] The invention relates to the technical field of aircraft structure fatigue test, in particular to a three-point bending buckling fatigue test fixture of a wing spar. Background technique [0002] Most of the aircraft body structure and its typical components are thin-walled structures, especially for general-purpose aircraft, such as fuselage wing panels, wing spar webs, etc. Modern aircraft structures increasingly tend to use thin-walled, lightweight components composed of high-strength materials to give full play to the material's load-bearing capacity. During the take-off-cruise-landing process of the aircraft, the wing spar is mainly subjected to the repeated action of shear and bending loads, and the web of the wing spar is prone to buckling fatigue damage under the action of shear fatigue load. Therefore, it is of great significance to study the buckling fatigue performance of aircraft wing spars. [0003] At present, there are many mechanical ...
Claims
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IPC IPC(8): B64F5/60G01N3/04
CPCG01N3/04B64F5/60
Inventor 陈安董登科臧伟锋廖江海
Owner CHINA AIRPLANT STRENGTH RES INST