Clamping device for clamping test piece and use method of clamping device

Abstract

The invention provides a clamping device which comprises an upper clamping piece and a lower clamping piece .The upper clamping piece comprises an upper clamping piece body, upper clamping piece through holes are formed in the upper clamping piece body in the thickness direction, and one side face of the upper clamping piece body is provided with dovetail tenons; the lower clamping piece comprises a lower clamping piece body and a testing machine clamping part which is used for being clamped in an external testing machine, the lower clamping piece body further comprises a lower clamping piece body base part and a lower clamping piece body protruding part, lower clamping piece through holes are formed in the lower clamping piece body base part in the thickness direction, the lower clamping piece body protruding part is provided with dovetail mortises, and the depth of each dovetail mortise is equal to the height difference; the dovetail tenons can be aligned with the dovetail mortises, at the moment, the upper clamping piece through holes can be aligned with the lower clamping piece through holes .The clamping device has the advantages of being compact in structure and accurate in positioning .The invention further provides a corresponding clamping method, and the clamping stability and accuracy of a test piece to be tested are greatly improved.

Description

Technical field [0001] The invention relates to a clamping device for clamping a test piece and a use method thereof, in particular to a clamping device for clamping a thin-walled fatigue test piece and a use method thereof. Background technique [0002] In order to meet the comprehensive requirements of safety, economy, comfort, and environmental protection, in the selection of airframe materials and structures for new commercial aircraft, on the one hand, lightweight materials with low density and high specific strength such as aluminum alloy and aluminum-lithium alloy are selected, and a large number of Using multi-step thin-walled structures, such as the nose, middle and rear fuselage skins, etc., by partially thinning the skin panels to form a multi-step thin-walled structure, the weight of the skin panels can be reduced by more than 40%. [0003] Multi-step thin-walled structure is a typical lightweight structure of aircraft skin siding. In the past, the skin siding was chemi...

AI Technical Summary

Problems solved by technology

[0003] The multi-step thin-walled structure is a typical lightweight structure of aircraft skin panels. In the past, the skin panels were chemically milled to corrode part of the metal sheet to obtain the multi-step thin-walled parts required for the design. However, the chemical milling process The release of the anti-fatigue residual stress on the surface of the plate reduces the fatigue life, the dimensional accuracy of the parts is difficult to control, and the process pollution is serious, which does not meet the green and environmental protection manufacturing requirements. Multi-step structure, research on the fatigue performance and reliability of thin-walled flat parts after mechanical milling, and provide basic data for the design, forming and manufacturing process specifications of high-performance, long-life aluminum-lithium alloy skin panels and technical support

[0004] Due to the existence of milling slots, the size of the fatigue specimen designed in the fatigue test is relatively large, and the clamps of the general fatigue testing machine cannot meet the width requirements of the specimen; Sliding, so an effective and stable clamping method is the primary problem to be solved

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