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A kind of integral sealed cabin and preparation method thereof

A technology of integral sealing and cabin body, which is applied in space navigation equipment, space navigation equipment, and space navigation vehicles, etc., and can solve the problems of long-term use and maintenance inconvenience of the structure, increase of structural weight and cost, hidden danger of leakage of assembly connection holes, etc. , to achieve the effects of repeated use and maintenance, improved maintainability, and reduced assembly workload

Active Publication Date: 2022-08-02
DONGHUA UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, for composite parts with complex structures, the manufacturing integrity of the autoclave forming process is poor, and it is often necessary to disassemble the structure into multiple parts and manufacture them separately, and then perform assembly (such as screwing, riveting) to form the final product. Parts, resulting in reduced manufacturing efficiency, the use of a large number of fasteners, resulting in structural weight and cost increases and other issues
In addition, the use of commonly used assembly methods such as screw joints and riveting will inevitably produce a large number of connection holes on the composite material structure. The hidden danger of leakage is extremely inconvenient for the long-term use and maintenance of the structure

Method used

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  • A kind of integral sealed cabin and preparation method thereof
  • A kind of integral sealed cabin and preparation method thereof
  • A kind of integral sealed cabin and preparation method thereof

Examples

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preparation example Construction

[0044] The present invention also provides the preparation method of the integral sealed cabin described in the above technical solution, comprising the following steps:

[0045] Lay the prepreg at the position of the longitudinal stiffener of the mandrel, and fill the cavity of the longitudinal stiffener with the second foam; Filling the cavity with the first foam; then laying the outer skin with the first fiber fabric to obtain a preform;

[0046] Using resin transfer molding method to inject resin into the preform, after curing and demoulding, the capsule is obtained;

[0047] Holes are made at specified positions of the rear end flanging of the cabin body, and are connected with the metal rear end cover by bolts; the maintenance port cover and the metal rear end cover are connected by bolts to obtain an integrally sealed cabin.

[0048] In the present invention, prepreg is spread at the position of the longitudinal reinforcing rib of the core mold, and the second foam is ...

Embodiment 1

[0069] Integral sealed cabin: the total thickness of the cabin is 5mm, of which: the inner skin is 2mm and the outer skin is 3mm; the size of the cabin is 400mm×400mm×600mm.

[0070] The annular reinforcing rib is located in the middle of the interior length direction of the cabin;

[0071] The longitudinal reinforcing ribs are arranged in the middle of the four inner sides of the cabin; and there are two longitudinal reinforcing ribs located on the same inner side of the cabin, which are divided into two sides of the annular reinforcing ribs; the annular reinforcing ribs The parameters of the Ω-type annular stiffener and the Ω-type longitudinal stiffener include: thickness 2mm, trapezoidal section upper bottom 20mm, bottom bottom 30mm, height 15mm; longitudinal stiffener width 80mm, length 240mm .

[0072] The depth of the sealing groove of the metal rear end cap is 4.9mm and the width is 7.4mm;

[0073] The size of the metal rear end cap is 360mm×360mm;

[0074] The size ...

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Abstract

The invention provides an integral sealed cabin and a preparation method thereof, belonging to the technical field of aerospace high-performance composite materials. The invention adopts an integral outer skin, and replaces the metal front end cover of the existing airtight cabin with an outer skin, and replaces the independent annular rib with an integral annular reinforcing rib and longitudinal reinforcing rib, which greatly improves the structural integrity of the airtight cabin. The assembly workload is reduced; moreover, the number of assembly connection holes and fasteners is reduced, the structural weight of the sealed cabin is reduced, the structural efficiency is further improved, and at the same time, the risk of sealing leakage is effectively reduced, which is conducive to the repeated use and maintenance. Secondly, the present invention realizes the sealing assembly connection between the metal rear end cover and the cabin by arranging the maintenance cover on the metal rear end cover; in addition, the overall sealing cabin structure provided by the present invention is conducive to the RTM process forming, and simplifies the overall sealing cabin preparation method.

Description

technical field [0001] The invention belongs to the technical field of aerospace high-performance composite materials, and relates to an integral sealed cabin and a preparation method thereof. Background technique [0002] At present, in the field of aerospace high-performance composite material manufacturing technology, the traditional prepreg autoclave forming process is the most widely used and most mature manufacturing method. The composite material produced by the autoclave molding process has the advantages of high fiber volume fraction, excellent mechanical properties, and stable internal quality. However, for composite parts with complex structures, the manufacturing integrity of the autoclave forming process is poor, and the structure often needs to be split into multiple parts to be manufactured separately, and then assembled (such as screwing, riveting) to form the final Parts, resulting in reduced manufacturing efficiency, the use of a large number of fasteners,...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64D37/02B64D37/06B64G1/40
CPCB64D37/02B64D37/06B64G1/402Y02T50/40
Inventor 张金栋刘刚马驰姚佳楠
Owner DONGHUA UNIV
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