CN105619834A

CN105619834A - Application of curing furnace forming technology to airplane composite material pressurized cabin

Info

Publication number: CN105619834A
Application number: CN201410591384.9A
Authority: CN
Inventors: 曾小苗; 吴昊; 姜华强
Original assignee: China Aviation Industry General Aircraft Co Ltd
Current assignee: China Aviation Industry General Aircraft Co Ltd
Priority date: 2014-10-28
Filing date: 2014-10-28
Publication date: 2016-06-01

Abstract

The invention discloses application of a curing furnace forming technology to an airplane composite material pressurized cabin. The application comprises a medium-temperature low-pressure curing furnace forming method, and the airplane composite material pressurized cabin is integrally formed through co-curing. The airplane composite material pressurized cabin is a main force bearing member of an airplane, the airplane composite material pressurized cabin is formed through curing with a medium-temperature low-pressure curing furnace, only vacuum pressure is added during curing, and the curing temperature is not higher than 140 DEG C. The airplane composite material pressurized cabin is integrally formed through an upper half mould and a lower half mould, and a windshield opening, window openings and cabin door openings are formed through milling by means of a milling mould after the parts are formed.

Description

The utilization on technique for aircraft composite pressure cabin of a kind of curing oven forming technique

Technical field

Patent of the present invention is the utilization on technique for aircraft composite pressure cabin of a kind of curing oven forming technique

Background technology

The main load parts of general technique for aircraft composite all adopt the forming method of autoclave (High Temperature High Pressure) for the product quality obtained, autoclave equipment cost is high, use cost is high, utilization rate of equipment and installations is low, forming part size is limited by autoclave equipment, and forming parts frock is also required that height. General technique for aircraft composite pressure cabin all adopts frame girder structure, is connected by securing member and forms an entirety, this scheme Heavy Weight, easily there is fatigue rupture in junction, and frame girder structure reduces passenger cabin and uses space, adds number of parts, assembly tooling. Composite airplane manufacturing cost is remained high, and is difficult to parts large-scale production.

Summary of the invention

For the defect of the main bearing member forming technique of composite and the deficiency of existing aircraft, patent of the present invention is to be provided is the utilization in technique for aircraft composite pressure cabin molding of the low-cost solidification stove forming technique.

In order to solve above-mentioned technical problem, patent of the present invention the technical scheme is that and adopts a kind of tubular sandwich for technique for aircraft composite pressure cabin, tubular sandwich pressure cabin is divided into the paving molding respectively of upper female die, by upper female die matched moulds, vacuum solidification. Curing oven adopts the middle temperature not higher than 140 �� to carry out curing molding. Significantly alleviating with existing frame beam type pressure cabin phase weight/power ratio, the version of integration saves assembly tooling, and the production cycle is greatly shortened, and is especially advantageous for product large-scale production.

For prior art, patent of the present invention provides the benefit that: be substantially reduced composite airplane manufacturing cost, saves assembly tooling and time, it is achieved composite airplane integrative design, large-scale production. And better product quality can be obtained.

Accompanying drawing explanation

Fig. 1 is pressure cabin structural representation

Fig. 2 is Fig. 1 die joint place connection diagram

In figure, 1 is die joint, and 2 is upper half pressure cabin, and 3 is lower half pressure cabin, and 4 is windscreen opening,

5 is window opening, and 6 is emergency hatch opening, and 7 is passenger door opening, and 8 is rear pressure frame opening.

9. female die mould, 10. upper mold section mould, 11. honeycomb splicing glue, 12. upper mold section outer surface layings,

13. upper mold section honeycomb core, 14. upper mold section inner surface layings, 15. female die outer surface layings,

16. female die honeycomb core, 17. female die inner surface layings, 18. splicing honeycomb cores, 19. enhancement Layers

Detailed description of the invention

The detailed description of the invention of patent of the present invention is further illustrated below in conjunction with accompanying drawing.

Refer to shown in Fig. 1 Fig. 2, the paving molding in described upper mold section mould 10 of described upper half pressure cabin 2; The paving molding in described female die mould 9 of described lower half pressure cabin 3; Described windscreen opening 4, described window opening 5, described emergency hatch opening 6, described passenger door opening 7 milling after pressure cabin curing molding. 2, after 3 pavings complete, by 9,10 matched moulds, first described upper mold section outer surface laying 12 and described female die outer surface laying 15 are overlapped after matched moulds, and with described honeycomb splicing glue 11, described splicing honeycomb core 18 is spliced with described upper mold section honeycomb core 13 and described female die honeycomb core 16, then with described enhancement Layer 19, described upper mold section inner surface laying 14 and described female die inner surface laying 17 are connected. Paving utilizes vacuum bag, evacuation compacting after completing, enter curing oven by composite material solidification curve about 12 hours, solidification temperature less than 140 ��, curing molding, treat that die surface is cooled to 35 �㡫50 �� parts and comes out of the stove, the demoulding, cutting, Non-Destructive Testing.

The above is the preferred embodiment of the present invention; it should be pointed out that, for those skilled in the art, under the premise without departing from the principles of the invention; can also making some improvements and modifications, these improvements and modifications are also considered as protection scope of the present invention.

Claims

1. a curing oven forming technique uses on technique for aircraft composite pressure cabin, it is characterised in that: including middle temperature low pressure curing type stove forming method, technique for aircraft composite pressure cabin co-curing is one-body molded.

2. the middle temperature low pressure curing type stove forming method application according to right 1, it is characterized in that: technique for aircraft composite pressure cabin molding is the curing oven forming method solidification of warm low pressure in adopting, it is that one only adds vacuum pressure, the solidification temperature composite material forming method not higher than 140 ��, is the composite material forming method of a kind of low cost relative to current autoclave molding.

3. the technique for aircraft composite tubular pressure cabin curing oven co-curing according to right 1 and 2 is one-body molded, it is characterised in that: technique for aircraft composite pressure cabin is the important stressed member of aircraft, and whole pressure cabin adopts upper female die co-curing one-body molded.