CN105620712A - Large bend air inflow channel of foam interlayer structure and forming method for foam core of foam interlayer structure - Google Patents
Large bend air inflow channel of foam interlayer structure and forming method for foam core of foam interlayer structure Download PDFInfo
- Publication number
- CN105620712A CN105620712A CN201410589260.7A CN201410589260A CN105620712A CN 105620712 A CN105620712 A CN 105620712A CN 201410589260 A CN201410589260 A CN 201410589260A CN 105620712 A CN105620712 A CN 105620712A
- Authority
- CN
- China
- Prior art keywords
- foam
- interlayer structure
- foam core
- forming method
- foam interlayer
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Landscapes
- Laminated Bodies (AREA)
Abstract
The invention discloses a large bend air inflow channel of a foam interlayer structure and a forming method for a foam core of the foam interlayer structure. The foam interlayer structure is suitable for various air inflow channels, especially for the condition that the appearance is complex and a cambered surface is bent. The foam interlayer structure can provide large rigidity with low weight, and the beneficial effects that a composite material is high in specific strength and specific rigidity are brought into full play. The foam core is integrally mechanically formed, the defect that the complex appearance cannot be formed through other cores is overcome, and the beneficial effect that the composite material is suitable for a complex appearance structure is well shown.
Description
Technical field
The invention belongs to composite fuselage construction design, particularly to the forming method of the big inflection air intake duct of a kind of foamed sandwich structure and foam core thereof.
Background technology
At present, the current large-scale military, civilian aircraft commonly used metal structure of NACA air intake duct or honeycomb sandwich construction, typical metal structure has Type of Welding and splicing form, owing to often there are vibrations at air intake duct place, Type of Welding fatigue behaviour bad and welding be easily deformed, splicing form part is many, assembling complexity, and weight is big; Honeycomb sandwich construction is not suitable for complex contour, the air intake duct that inflection is many, because honeycomb cannot molding; This limits the NACA air intake duct use for composite of some complex contour to a certain extent.
Summary of the invention
The technical problem to be solved in the present invention is in that, when air intake duct complex contour, inflection are many, honeycomb cannot the problem of molding. A kind of big inflection air intake duct of foamed sandwich structure is provided for solving the problems referred to above technical solution of the present invention, foamed sandwich structure at inflection position application one curing molding, described foamed sandwich structure includes wainscot, outer panels and foam core, and described foam core is between wainscot and outer panels.
Technical solution of the present invention also provides for the forming method of a kind of foam core being applied to the big inflection air intake duct of described a kind of foamed sandwich structure, is first gluedd joint by number foamed materialss relatively thin soon, machine add-on type more afterwards.
Accompanying drawing explanation
Below in conjunction with attachedFigureSpecific embodiments of the present invention are further described in detail, wherein:
Figure1 is the big inflection air intake duct signal of a kind of foamed sandwich structureFigure;
Figure2 is foamed sandwich structure signalFigure;
Figure3 is the signal of foamed sandwich structure layingFigure��
Detailed description of the invention
First embodiment of the invention provides a kind of big inflection air intake duct of foamed sandwich structure, it by wainscot 1, outer panels 2, foam core 3, form, asFigure1��FigureShown in 2.
Described wainscot 1, outer panels 2 are carbon fiber layer laminated structure, laminated area wainscot 1 four layers, outer panels 2 five layers, froth zone wainscot 1 two-layer, outer panels 2 three layers, asFigureShown in 3, described foam core 3 is highly 15mm, and all bias are 30 ��.
Second embodiment of the invention provides the forming method of a kind of foam core being applied to the big inflection air intake duct of described a kind of foamed sandwich structure, asFigureShown in 3, in order to reduce the requirement to material stock thickness, first polylith thickness is gluedd joint molding than relatively thin raw material, be machined into required product integrated machine add-on type according still further to profile.
The big inflection air intake duct of described foamed sandwich structure, by wainscot 1, outer panels 2, foam core 3 co-curing molding together.
The present invention is applicable to all kinds of air intake ducts, particularly complex contour, and curved surface has the situation of inflection; Foamed sandwich structure, can provide bigger rigidity with less weight, fully play the advantage that composite specific strength is high, specific stiffness is high; Foam core material integrated machine add-on type, solve other cores for complex appearance cannot the shortcoming of molding, well embody composite and be applicable to the advantage of complex appearance structure.
Claims (2)
1. the big inflection air intake duct of foamed sandwich structure, it is characterized in that, foamed sandwich structure at inflection position application one curing molding, described foamed sandwich structure includes wainscot (1), outer panels (2) and foam core (3), and described foam core (3) is between wainscot (1) and outer panels (2).
2. the forming method of the foam core described in a claim 1, it is characterised in that first number foamed materialss relatively thin soon are gluedd joint, machine add-on type more afterwards.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410589260.7A CN105620712A (en) | 2014-10-28 | 2014-10-28 | Large bend air inflow channel of foam interlayer structure and forming method for foam core of foam interlayer structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410589260.7A CN105620712A (en) | 2014-10-28 | 2014-10-28 | Large bend air inflow channel of foam interlayer structure and forming method for foam core of foam interlayer structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105620712A true CN105620712A (en) | 2016-06-01 |
Family
ID=56036144
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410589260.7A Pending CN105620712A (en) | 2014-10-28 | 2014-10-28 | Large bend air inflow channel of foam interlayer structure and forming method for foam core of foam interlayer structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105620712A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111361743A (en) * | 2020-02-21 | 2020-07-03 | 中国电子科技集团公司第二十九研究所 | Composite material air inlet channel and preparation method thereof |
| CN111577464A (en) * | 2020-05-26 | 2020-08-25 | 中国航发沈阳发动机研究所 | Process air inlet channel for special engine test |
| CN113636089A (en) * | 2021-08-25 | 2021-11-12 | 成都飞机工业（集团）有限责任公司 | Slender double-engine air inlet structure and assembling method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6451231B1 (en) * | 1997-08-21 | 2002-09-17 | Henkel Corporation | Method of forming a high performance structural foam for stiffening parts |
| CN1775507A (en) * | 2005-10-18 | 2006-05-24 | 成都飞机工业（集团）有限责任公司 | Thermal forming method for PMI foam laminated structure |
| CN201745741U (en) * | 2010-07-20 | 2011-02-16 | 中国航空工业集团公司西安飞机设计研究所 | Overall thin-walled structure of composite machine body |
| CN203047528U (en) * | 2012-12-21 | 2013-07-10 | 中国直升机设计研究所 | Honeycomb sandwich structure piece containing reinforced core material |
| CN104097329A (en) * | 2014-06-16 | 2014-10-15 | 中国商用飞机有限责任公司 | Method for performing resin filling infusion pretreatment for foam material in formation of composite material foam sandwich structure |
-
2014
- 2014-10-28 CN CN201410589260.7A patent/CN105620712A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6451231B1 (en) * | 1997-08-21 | 2002-09-17 | Henkel Corporation | Method of forming a high performance structural foam for stiffening parts |
| CN1775507A (en) * | 2005-10-18 | 2006-05-24 | 成都飞机工业（集团）有限责任公司 | Thermal forming method for PMI foam laminated structure |
| CN201745741U (en) * | 2010-07-20 | 2011-02-16 | 中国航空工业集团公司西安飞机设计研究所 | Overall thin-walled structure of composite machine body |
| CN203047528U (en) * | 2012-12-21 | 2013-07-10 | 中国直升机设计研究所 | Honeycomb sandwich structure piece containing reinforced core material |
| CN104097329A (en) * | 2014-06-16 | 2014-10-15 | 中国商用飞机有限责任公司 | Method for performing resin filling infusion pretreatment for foam material in formation of composite material foam sandwich structure |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111361743A (en) * | 2020-02-21 | 2020-07-03 | 中国电子科技集团公司第二十九研究所 | Composite material air inlet channel and preparation method thereof |
| CN111577464A (en) * | 2020-05-26 | 2020-08-25 | 中国航发沈阳发动机研究所 | Process air inlet channel for special engine test |
| CN113636089A (en) * | 2021-08-25 | 2021-11-12 | 成都飞机工业（集团）有限责任公司 | Slender double-engine air inlet structure and assembling method |
| CN113636089B (en) * | 2021-08-25 | 2023-07-21 | 成都飞机工业（集团）有限责任公司 | Slender double-engine air inlet channel structure and assembly method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9573338B2 (en) | Composite sandwich panel with differential resin layers | |
| RU2593733C1 (en) | Interior panel of aircraft with acoustic materials | |
| US7575194B2 (en) | Apparatuses and methods for joining composite members and other structural members in aircraft wing boxes and other structures | |
| CN102639317B (en) | Sandwich structure having arrestment feature and method of making the same | |
| US10828870B2 (en) | Process for manufacturing apron board of high-speed rail equipment cabin using composite material | |
| WO2011058514A3 (en) | Panel for aircraft applications and the method for manufacturing the panel | |
| US10661530B2 (en) | Methods and apparatus to couple a decorative layer to a panel via a high-bond adhesive layer | |
| US9522504B2 (en) | Method for manufacturing an integrated composite trailing edge and integrated composite trailing edge | |
| WO2012001207A3 (en) | Aircraft fuselage made out with composite material and manufacturing processes | |
| CN203047528U (en) | Honeycomb sandwich structure piece containing reinforced core material | |
| JP2018094926A (en) | Bends in composite panels | |
| US20170297729A1 (en) | Panel and insert for corner radii | |
| CN101557979B (en) | Wing panel structure | |
| CN109532036B (en) | Full composite material wing glue joint method and full composite material wing | |
| RU2011145333A (en) | METHOD FOR PRODUCING THE ITEMS FROM COMPOSITE MATERIAL AND PRELIMINARY IMPREGNATION SHEET | |
| CN105620712A (en) | Large bend air inflow channel of foam interlayer structure and forming method for foam core of foam interlayer structure | |
| EP2676877A3 (en) | Composite structural panels and aircraft fuselages | |
| CN201745741U (en) | Overall thin-walled structure of composite machine body | |
| US20120282430A1 (en) | Composite material part with large variation in thickness | |
| CN104015377B (en) | Manufacturing process of large-damping high-rigidity composite material multi-layer sandwich precision instrument board | |
| US10632724B2 (en) | Process for manufacturing base board of high-speed rail equipment cabin using composite material | |
| CN204451340U (en) | A kind of high strength high rigidity lightweight wallboard | |
| WO2009071824A3 (en) | Method of creating composite components with a preform with hybrid layup | |
| CN106741823B (en) | By the unmanned plane body and preparation method thereof of composite material preparation | |
| CN215436905U (en) | Aircraft tail wing leading edge structure |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160601 |