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Helicopter composite material paddle fatigue test piece molding method

A technology of composite materials and forming methods, which is applied in the testing of mechanical components, testing of machine/structural components, preparation of test samples, etc., and can solve the problems of difficulty in ensuring the symmetry of assembly splints, the influence of verticality of bore holes, and the problems of whole paddles. Leaf scrapping and other issues, to achieve the effect of improving the pass rate of one-time inspection, ensuring stability and smoothness, and shortening the manufacturing cycle

Inactive Publication Date: 2013-08-07
中航直升机股份有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0028] With this method, it is easy to mill off the latitude-free tape when milling the plane, which will greatly weaken the rigidity and strength of the blade fatigue test piece; it is also difficult to ensure the symmetry when assembling the splint, which makes the verticality of the boring hole also large. Affected
In addition, the balance of the blade fatigue test piece prepared by this method is also difficult to guarantee, and there will be different degrees of deviation each time. No matter whether the deviation is large or small, it will have an impact on the final experimental performance of the fatigue test piece, and even cause Scrapping of a whole blade

Method used

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  • Helicopter composite material paddle fatigue test piece molding method
  • Helicopter composite material paddle fatigue test piece molding method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment

[0079] 1. Blade cutting, hollowing out

[0080] Remove the iron covering from the formed molded blade, and draw the blade cutting reference line Zx on the blade according to the design requirements, taking the 0-section position of the blade as the reference 1 、Zx 2 , cut off the molded paddle according to the reference line and remove the burrs, and hollow out the foam in the inner cavity of the end of the molded paddle according to the design requirements;

[0081] 2. Paddle filling

[0082] Fill the cavity at the end of the specimen with the chopped fiber mixture, remove air bubbles, and smooth it. Tape the foam blocks at the ends to prevent the flow of the chopped fiber mixture, waiting to cure;

[0083] 3. Paste the vacuum bag, solidify, open the mold

[0084] Curing: heat up to 100±5°C and keep the temperature constant for 6 hours

[0085] 4. Drilling holes for paddle 1

[0086] Use the fatigue test piece drilling jig to determine the hole position required by the ...

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Abstract

The invention belongs to a composite material molding technology, and relates to helicopter composite material paddle fatigue test piece molding technological process which is suitable for helicopter composite material technological process molding. According to the invention, a platform thickness spacing tool is adopted, an interval between two splints of a paddle fatigue test piece is effectively ensured, and simultaneously the positioning of the spacing tool can insure symmetry of the two splints; and a working procedure of numerical control processing is directly omitted from a technical process, furthermore a manufacturing cycle is also shortened, once alternating detection qualification rate of the paddle fatigue test piece is improved, the rejection rate of the paddle fatigue test piece is zero, and the stability and the smoothness of the assembly process of the paddle fatigue test piece are ensured.

Description

technical field [0001] The invention belongs to composite material forming technology, and relates to a forming process method for a helicopter composite material blade fatigue test piece suitable for forming a helicopter composite material blade fatigue test piece. Background technique [0002] The rotor blade is a flexible, slender elastic body with low natural frequency. When working, the high-speed rotating blade is subjected to high centrifugal force load and alternating aerodynamic load, resulting in high alternating stress. Therefore, during the exploratory period of helicopter development, the blades were easily broken. The fatigue test results carried out on a special fatigue test bench are the most direct indicators to reflect the performance of the blade. Therefore, it is the most critical to manufacture the blade fatigue test piece with excellent fatigue performance. [0003] The traditional process for preparing the blade fatigue test piece is, [0004] 1. Bl...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01N1/28G01M13/00
Inventor 李丽丽宋文娟李硕强
Owner 中航直升机股份有限公司
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