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A heat-resistant load-bearing integrated structure for aircraft and its forming method

A molding method and technology for aircraft, applied in applications, household appliances, household components, etc., can solve the problems of poor product dimensional stability, low product molding accuracy, low product molding quality, etc., to improve molding accuracy and molding quality, and reduce the structure. The effect of excessive springback deformation and stable size

Active Publication Date: 2022-03-04
BEIJING INST OF ELECTRONICS SYST ENG
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, when the shape of the aircraft cabin section is not a complete revolving body structure, but a special-shaped revolving body structure, if the co-curing or secondary co-curing process of the prior art is directly used to form the heat-resistant load-bearing integrated structure, It will lead to problems such as low molding precision of the final product, poor dimensional stability of the product, large interface stress, and low molding quality of the product.

Method used

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  • A heat-resistant load-bearing integrated structure for aircraft and its forming method
  • A heat-resistant load-bearing integrated structure for aircraft and its forming method
  • A heat-resistant load-bearing integrated structure for aircraft and its forming method

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Embodiment 1

[0080] An embodiment of the present invention is as figure 2 The forming method of the heat-resistant load-bearing integrated structure shown, the heat-resistant load-bearing integrated structure includes a first revolving body segment 11, a second revolving body segment 12 and a third revolving body segment 13, wherein the first revolving body segment 11 is a semiconical truncated cone, the second revolving body section 12 is a semicylindrical shape, the third revolving body section 13 is a semiconical frustum shape, and the diameter of the second revolving body section 12 is φ390mm.

[0081] S1. Infiltrate the reinforcing material in the glue tank with the matrix resin, dry it, and wind it up to obtain a continuous prepreg;

[0082] S2. Cutting the continuous prepreg cloth to obtain a prepreg cloth tape, and continuous winding after bonding to obtain a prepreg cloth tape;

[0083] S3. Laying the prepreg tape to obtain a semi-open laminated skin;

[0084] S4, placing the s...

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Abstract

The embodiment of the present invention discloses an integrated heat-resistant load-bearing structure for an aircraft and a forming method thereof. The integrated heat-resistant load-bearing structure includes a main body; the main body is sequentially provided with a load-bearing layer, glue layer and a heat-proof layer, the load-bearing layer and the heat-proof layer are connected by an adhesive layer; the body part includes an axially symmetrical first half body part and a second half body part; the first half body part and the second half body respectively include several revolution body segments formed by generatrix lines with different slopes. Through the integrated heat-resistant load-bearing structure provided by the present invention, the lightweight and high-rigidity performance of the integrated heat-resistant load-bearing structure can be further improved; at the same time, the forming method of the integrated heat-resistant load-bearing structure can effectively solve the problem of the integrated heat-resistant load-bearing structure. Low molding precision, poor dimensional stability of the product, large interface stress, and low molding quality of the product have significantly improved the molding accuracy and molding quality of the heat-resistant load-bearing integrated structure.

Description

technical field [0001] The invention relates to the technical field of aircraft thermal protection, in particular to an integrated heat-resistant load-bearing structure for an aircraft and a forming method thereof. Background technique [0002] The integrated heat-resistant load-bearing structure is a major trend in the structural design and application of high-speed aircraft in the aerospace field today. The integrated heat-resistant load-bearing structure can make the aircraft structure have both heat-resistant performance and load-bearing performance, and at the same time greatly reduce the system cost of the aircraft structure. Weight, increase the payload ratio, so as to ensure that the aircraft is advanced, reliable and economical. [0003] The combination of the shell skeleton of the aircraft and the heat-resistant load-bearing integrated structure is a commonly used structural form of the aircraft cabin. In addition to aerodynamic pressure loads, the heat-resistant ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29C70/34B29C70/54B29B11/16B29B15/12B29L31/30
CPCB29C70/342B29C70/54B29B11/16B29B15/125B29L2031/3082
Inventor 辛玲杨宁王大奎李君龙
Owner BEIJING INST OF ELECTRONICS SYST ENG
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