CN104646976A - Quick profile manufacturing method of composite material thin-shell mold for aircraft - Google Patents
Quick profile manufacturing method of composite material thin-shell mold for aircraft Download PDFInfo
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- CN104646976A CN104646976A CN201510076876.9A CN201510076876A CN104646976A CN 104646976 A CN104646976 A CN 104646976A CN 201510076876 A CN201510076876 A CN 201510076876A CN 104646976 A CN104646976 A CN 104646976A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/24—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass dies
Abstract
The invention relates to a quick profile manufacturing method of a composite material thin-shell mold for an aircraft. Aiming at the defects of higher deformation and the like caused by high material cost and higher thermal capacity due to the fact that a mold is ordinarily manufactured by entirely cutting a metal material such as Q235A and Invar and the thickness of a mold tool is larger in the forming process of large-sized and precise composite materials, the invention provides the quick profile manufacturing method of the thin-shell mold. Thinner sheet metal of which the thickness is 10-12mm is selected as a raw material and is subjected to wrinkling preprocessing, heating die assembly forming, cooling, seam welding and numerical control finishing forming to manufacture the thin-shell mold of which the thickness is at least 4mm by performing profile compensation shape modifying and plastic cloth film coating test on a simple special mold, the profile thickness of the manufactured thin-shell mold is small and uniform, the material cost is reduced, the thermal capacity is lower, thermal deformation generated during the manufacturing of composite material parts is lower, and the manufacturing accuracy of the composite material parts is improved.
Description
Technical field
The present invention relates to a kind of aircraft composite shell die face method for fast mfg.
Background technology
At present, aircraft composite material shaping mould mainly adopts the overall machining manufacture of metal material at present, due to features such as the metal materials such as Q235A, Invar are high temperature resistant, wear-resistant, life cycle is long, therefore become the main material that composite material mould frock manufactures.Q235A has the advantages such as thickness is complete in specifications, with low cost, in liberal supply, is material the most frequently used in actual production, but differs comparatively large with product due to its thermal coefficient of expansion, is therefore not suitable for manufacturing large-scale, accurate composite material parts; And thermal coefficient of expansion and the close mold materials Invar high cost of product, and thickness specification is limited, there is larger difficulty by machining mfg. moulding die profile.Therefore, ensureing under the prerequisite that part accuracy requires, how more scientific effective mfg. moulding die profile, reduce die cost, be a difficult problem urgently to be resolved hurrily in composite material mould Design and manufacture process.
The present invention relates to the manufacture method of composite material mould profile, and when carrying out patent retrieval with keyword ' composite ' and ' mould ', retrieve patent of invention 26, utility model patent 14, have no patent similar to the present invention.
Summary of the invention
Technical problem to be solved by this invention is large-scale, in accurate composite material parts forming process, mold materials generally adopts Invar, material cost and processing and manufacturing high cost, frock thickness again due to manufactured is larger, its thermal capacity is larger, therefore the product deformation effect precision caused is the subject matter existed in actual production, the present invention proposes to adopt the method for thermoforming to manufacture shell die face, namely the metallic sheet material for the manufacture of die face is heated, take out after arriving uniform temperature, be placed in and simple forming mould fix and pressurizes, the die face that numerical control fine finishining obtains for composite material forming is carried out again after cooling forming.
The object of the invention is for existing in the above-described shortcoming of large-scale composite material mould and deficiency, the present invention proposes a kind of novel die profile method for fast mfg, effectively can improve part accuracy, ensure product quality, save mold materials, reduce costs, there is the features such as structure is simple, safe and reliable, the scope of application is wide.
The technical solution adopted for the present invention to solve the technical problems is:
A kind of aircraft composite shell die face method for fast mfg, the mode of thermoforming is adopted to manufacture the die face that thickness is at least 4mm, thinner sheet metal can be selected to make raw material, material plate thickness specification is 10 ~ 12mm, avoid and adopt integral metal material excessive through shaping the caused blank dimension of machining in the past, the shortcoming that material cost is high; And it is even because manufactured die face thickness is thin, its thermal capacity is less, therefore the thermal deformation produced when making composite material parts is also less, significantly can improve the precision of composite product, save mold materials, reduce die manufacturing cost, realize precisely shaping object, the method comprises the steps:
(1) choose the material specification for the manufacture of die face, according to die needed profile size, select the sheet material of suitable flat size, thickness specification elects 10 ~ 12mm as;
(2) simple die profile compensates and repaiies type, according to the thermal coefficient of expansion of mold materials, process is compensated to composite material mould profile, concrete way carries out scale amplifying to composite material mould profile by the thermal coefficient of expansion of mold materials, obtain the profile of simple die, the ratio of amplification is Δ L, and the expression formula of Δ L is Δ L=1+ β × Δ T, wherein β is the thermal coefficient of expansion of mold materials, and Δ T is the difference of forming temperature and room temperature;
(3) wrinkling place pretreatment, namely to the cutting process playing fold place in sheet material heat forming processes, in order to reduce tension-thining and wrinkling, therefore need to anticipate the part of wrinkling windrow, remove unnecessary material, for this reason, before the forming, the mode first adopting the Polypropylence Sheet of existing sheet material same size to paste Polypropylence Sheet film (2) in simple die (1) profile has found out fold position and dimensional parameters, and selected sheet material raw material is removed unnecessary material by the fold corresponding site cutting that rises of Polypropylence Sheet;
(4) sheet material heating, puts into dielectric heating oven by wrinkling pretreated sheet material, to its heating that heats up after requiring the setting parameter such as heating-up temperature and time according to the concrete shaping difference of mould;
(5) matched moulds is shaping, is taken out by the sheet material after heating, be placed on simple and easy mould assembly mould by dielectric heating oven, and matched moulds pressurization is fixing, and itself and die face are fitted;
(6) cooling after take out weld, matched moulds is shaping to be reduced to after normal value until temperature, opens mould, take out shaping after material, the gap that pretreatment cutting part is formed is welded;
(7) numerical control fine finishining, carries out the numerical control polishing fine finishining of die face to the sheet material after welding, ensure that the mold thickness after numerical control machine-shaping is at least 4mm, is final required shell die face.
Accompanying drawing explanation
Fig. 1 is the flow chart of shell die face method for fast mfg of the present invention
Fig. 2 is the raw material schematic diagram of manufacture shell die face of the present invention.
Simple forming mould of the present invention pastes Polypropylence Sheet film test schematic diagram to Fig. 3.
Fig. 4 is the cutting process schematic diagram that shell die face raw material of the present invention play fold place.
Fig. 5 is dielectric heating oven of the present invention heating schematic diagram.
Fig. 6 is matched moulds shaping schematic view of the present invention.
Fig. 7 is shell mould structure schematic diagram of the present invention.
1-simple die, 2-Polypropylence Sheet film, 3-play fold place, 4-otch gap, 5-dielectric heating oven, the wrinkling pretreated sheet material of 6-, the simple and easy mould assembly mould of 7-, 8-shell mould.
Detailed description of the invention
The technical program can also be realized by following technical measures and the invention will be further described below in conjunction with accompanying drawing:
Fig. 1 is the flow chart of shell die face method for fast mfg of the present invention, and the method comprises the steps:
(1) choose the material specification for the manufacture of die face, according to die needed profile size, select the sheet material of suitable flat size, thickness specification elects 10 ~ 12mm as;
(2) simple die profile compensates and repaiies type, according to the thermal coefficient of expansion of mold materials, process is compensated to composite material mould profile, concrete way carries out scale amplifying to composite material mould profile by the thermal coefficient of expansion of mold materials, obtain the profile of simple die, the ratio of amplification is Δ L, and the expression formula of Δ L is Δ L=1+ β × Δ T, wherein β is the thermal coefficient of expansion of mold materials, and Δ T is the difference of forming temperature and room temperature;
(3) wrinkling place pretreatment, namely to the cutting process playing fold place in sheet material heat forming processes, in order to reduce tension-thining and wrinkling, therefore need to anticipate the part of wrinkling windrow, remove unnecessary material, for this reason, before the forming, the mode first adopting the Polypropylence Sheet of existing sheet material same size to paste Polypropylence Sheet film (2) in simple die (1) profile has found out fold position and dimensional parameters, and selected sheet material raw material is removed unnecessary material by the fold corresponding site cutting that rises of Polypropylence Sheet;
(4) sheet material heating, puts into dielectric heating oven by wrinkling pretreated sheet material, to its heating that heats up after requiring the setting parameter such as heating-up temperature and time according to the concrete shaping difference of mould;
(5) matched moulds is shaping, is taken out by the sheet material after heating, be placed on simple and easy mould assembly mould by dielectric heating oven, and matched moulds pressurization is fixing, and itself and die face are fitted;
(6) cooling after take out weld, matched moulds is shaping to be reduced to after normal value until temperature, opens mould, take out shaping after material, the gap that pretreatment cutting part is formed is welded;
(7) numerical control fine finishining and repair type, carries out the numerical control polishing fine finishining of die face to the sheet material after welding, ensure digital control processing and type of repairing shaping after mold thickness be at least 4mm, be final needed for shell die face.
Fig. 2 is manufacture shell die face raw material schematic diagram of the present invention, mainly chooses the material specification for the manufacture of die face, and according to die needed profile size, select the sheet material of suitable flat size, thickness specification elects 10 ~ 12mm as.
Fig. 3 of the present inventionly pastes Polypropylence Sheet film test schematic diagram on simple die, Fig. 4 is the cutting process schematic diagram that shell die face raw material of the present invention play fold place, carry out the compensation of simple die (1) profile and repair type and the pretreatment of wrinkling place, according to the thermal coefficient of expansion of mold materials, process is compensated to composite material mould profile, concrete way carries out scale amplifying to composite material mould profile by the thermal coefficient of expansion of mold materials, obtain the profile of simple die, the ratio of amplifying is Δ L, the expression formula of Δ L is Δ L=1+ β × Δ T, wherein β is the thermal coefficient of expansion of mold materials, Δ T is the difference of forming temperature and room temperature, to the cutting process playing fold place (3) in sheet material heat forming processes, in order to reduce tension-thining and wrinkling, therefore need to anticipate the part of wrinkling windrow, remove unnecessary material, for this reason, before the forming, the mode first adopting the Polypropylence Sheet film (2) of existing sheet material same size to paste Polypropylence Sheet film (2) in simple die (1) profile has found out fold position and dimensional parameters, selected sheet material raw material is removed unnecessary material by the corresponding site cutting playing fold place (3) of Polypropylence Sheet film (2), defines otch gap (4).
Fig. 5 is dielectric heating oven of the present invention heating schematic diagram, sheet material heating is carried out at dielectric heating oven (5), wrinkling pretreated sheet material (6) is put into dielectric heating oven, to its heating that heats up after requiring the setting parameter such as heating-up temperature and time according to the concrete shaping difference of mould.
Fig. 6 is the shaping schematic diagram of matched moulds of the present invention, Fig. 6 is the shell mould structure schematic diagram of required profile of the present invention, sheet material after heating is taken out by dielectric heating oven (5), be placed on shaping simple die (7), matched moulds pressurization is fixing, and itself and die face are fitted; Matched moulds is shaping to be reduced to after normal value until temperature, opens mould, take out shaping after material, the gap that pretreatment cutting part is formed is welded; Sheet material after welding is carried out to the numerical control polishing fine finishining of die face, ensure that the mold thickness after numerical control machine-shaping is at least 4mm, be final required shell mould (8) profile.
Claims (1)
1. an aircraft composite shell die face method for fast mfg, it is characterized in that: adopt the mode of thermoforming to manufacture the shell die face that thickness is at least 4mm, thinner sheet metal is selected to make raw material, material plate thickness specification is 10 ~ 12mm, avoid and adopt integral metal material excessive through shaping the caused blank dimension of machining in the past, the shortcoming that material cost is high, and it is even because manufactured die face thickness is thin, its thermal capacity is less, therefore the thermal deformation produced when making composite material parts is also less, significantly can improve the precision of composite product, save mold materials, reduce die manufacturing cost, realize precisely shaping object, the method comprises the steps:
(1) choose the material specification for the manufacture of die face, according to die needed profile size, select the sheet material of suitable flat size, thickness specification elects 10 ~ 12mm as;
(2) simple die profile compensates and repaiies type, according to the thermal coefficient of expansion of mold materials, process is compensated to composite material mould profile, concrete way carries out scale amplifying to composite material mould profile by the thermal coefficient of expansion of mold materials, obtain the profile of simple die, the ratio of amplification is Δ L, and the expression formula of Δ L is Δ L=1+ β × Δ T, wherein β is the thermal coefficient of expansion of mold materials, and Δ T is the difference of forming temperature and room temperature;
(3) wrinkling place pretreatment, namely to the cutting process playing fold place in sheet material heat forming processes, in order to reduce tension-thining and wrinkling, therefore need to anticipate the part of wrinkling windrow, remove unnecessary material, for this reason, before the forming, the mode first adopting the Polypropylence Sheet of existing sheet material same size to paste Polypropylence Sheet film in simple die profile has found out fold position and dimensional parameters, and selected sheet material raw material is removed unnecessary material by the corresponding site cutting playing fold of Polypropylence Sheet;
(4) sheet material heating, puts into dielectric heating oven by wrinkling pretreated plate, to its heating that heats up after requiring the setting parameter such as heating-up temperature and time according to the concrete shaping difference of mould;
(5) matched moulds is shaping, is taken out by the sheet material after heating, be placed on simple and easy mould assembly mould by dielectric heating oven, and matched moulds pressurization is fixing, and itself and die face are fitted;
(6) cooling after take out weld, matched moulds is shaping to be reduced to after normal value until temperature, opens mould, take out shaping after sheet material, the gap that pretreatment cutting part is formed is welded;
(7) numerical control fine finishining, carries out the numerical control polishing fine finishining of die face to the sheet material after welding, ensure that the mold thickness value after numerical control machine-shaping is at least 4mm, is final required shell die face.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201510076876.9A CN104646976B (en) | 2015-02-13 | 2015-02-13 | Aircraft composite shell die face method for fast mfg |
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| CN201510076876.9A CN104646976B (en) | 2015-02-13 | 2015-02-13 | Aircraft composite shell die face method for fast mfg |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104942554A (en) * | 2015-06-17 | 2015-09-30 | 沈阳飞机工业（集团）有限公司 | Method for sinking formation of composite material wallboard tool |
| CN109622778A (en) * | 2018-11-12 | 2019-04-16 | 东风模具冲压技术有限公司 | A kind of type face compensation method for die debugging |
| CN109877535A (en) * | 2019-01-23 | 2019-06-14 | 常德翔宇设备制造有限公司 | Preparation process of double-layer water-cooling honeycomb hole panel |
| CN114310207A (en) * | 2020-09-30 | 2022-04-12 | 通用汽车环球科技运作有限责任公司 | Method and system for reporting stretching fault in stamping die development |
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| DE3206365A1 (en) * | 1982-02-22 | 1983-09-01 | Ludwig Edel GmbH & Co, 7988 Wangen | Method of fastening tube shells to the outer wall of a process container and a tube shell for use with the method |
| CN101318279A (en) * | 2007-06-08 | 2008-12-10 | 鞍钢建设集团有限公司 | One-time material clearing hot press molding process for circular arc zone of furnace jacket of blast furnace hot blast stove |
| CN101653791A (en) * | 2008-08-20 | 2010-02-24 | 鞍钢重型机械有限责任公司 | Converter-shell varied arc-segment hot compacting positioner and positioner manufacturing method |
| CN101920562A (en) * | 2010-08-02 | 2010-12-22 | 国营江北机械厂 | Clear dimension compression molding method for phenolic resin based complex profile product |
| CN103331581A (en) * | 2013-07-02 | 2013-10-02 | 无锡吉兴汽车部件有限公司 | Production method of car engine compartment cover assembly |
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2015
- 2015-02-13 CN CN201510076876.9A patent/CN104646976B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3206365A1 (en) * | 1982-02-22 | 1983-09-01 | Ludwig Edel GmbH & Co, 7988 Wangen | Method of fastening tube shells to the outer wall of a process container and a tube shell for use with the method |
| CN101318279A (en) * | 2007-06-08 | 2008-12-10 | 鞍钢建设集团有限公司 | One-time material clearing hot press molding process for circular arc zone of furnace jacket of blast furnace hot blast stove |
| CN101653791A (en) * | 2008-08-20 | 2010-02-24 | 鞍钢重型机械有限责任公司 | Converter-shell varied arc-segment hot compacting positioner and positioner manufacturing method |
| CN101920562A (en) * | 2010-08-02 | 2010-12-22 | 国营江北机械厂 | Clear dimension compression molding method for phenolic resin based complex profile product |
| CN103331581A (en) * | 2013-07-02 | 2013-10-02 | 无锡吉兴汽车部件有限公司 | Production method of car engine compartment cover assembly |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104942554A (en) * | 2015-06-17 | 2015-09-30 | 沈阳飞机工业（集团）有限公司 | Method for sinking formation of composite material wallboard tool |
| CN104942554B (en) * | 2015-06-17 | 2017-04-26 | 沈阳飞机工业（集团）有限公司 | Method for sinking formation of composite material wallboard tool |
| CN109622778A (en) * | 2018-11-12 | 2019-04-16 | 东风模具冲压技术有限公司 | A kind of type face compensation method for die debugging |
| CN109877535A (en) * | 2019-01-23 | 2019-06-14 | 常德翔宇设备制造有限公司 | Preparation process of double-layer water-cooling honeycomb hole panel |
| CN114310207A (en) * | 2020-09-30 | 2022-04-12 | 通用汽车环球科技运作有限责任公司 | Method and system for reporting stretching fault in stamping die development |
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Inventor after: Xu Yingjie Inventor after: Ding Zhide Inventor after: Hu Xinjian Inventor after: Zhang Lian Inventor after: Zhou Lizhong Inventor after: Jiang Shiying Inventor after: Wang Yishuang Inventor after: Yang Changbing Inventor after: Zhao Xin Inventor after: Wang Xi Inventor after: Sun Long Inventor after: Han Zhiren Inventor after: Wu Jichao Inventor after: Zhang Yanlong Inventor after: Jiang Tao Inventor after: Wang Qing Inventor after: Liu Baoming Inventor after: Liu Jianbo Inventor after: Wu Zibin Inventor after: Lin Ming Inventor after: Zhang Desheng Inventor after: Xu Xuanquan Inventor before: Xu Yingjie Inventor before: Ding Zhide Inventor before: Hu Xinjian Inventor before: Zhang Lian Inventor before: Zhou Lizhong Inventor before: Jiang Shiying Inventor before: Wang Yishuang Inventor before: Yang Changbing Inventor before: Zhao Xin Inventor before: Wang Xi Inventor before: Sun Long Inventor before: Han Zhiren Inventor before: Wu Jichao Inventor before: Zhang Yanlong Inventor before: Jiang Tao Inventor before: Wu Zibin Inventor before: Liu Baoming Inventor before: Liu Jianbo Inventor before: Wang Qing Inventor before: Lin Ming Inventor before: Zhang Desheng Inventor before: Xu Xuanquan |
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Free format text: CORRECT: INVENTOR; FROM: XU YINGJIE HAN ZHIREN WU ZIBIN LIU BAOMING LIU JIANBO WANG QING LIN MING ZHANG DESHENG XU FUQUAN DING ZHIDE HU XINJIAN ZHANG LIAN ZHOU LIZHONG JIANG SHIYING WANG YISHUANG YANG CHANGBING ZHAO XIN WANG XI SUN LONG WU JICHAO ZHANG YANLONG JIANG TAO TO: XU YINGJIE HAN ZHIREN WANG QING LIU BAOMING LIU JIANBO WU ZIBIN LIN MING ZHANG DESHENG XU FUQUAN DING ZHIDE HU XINJIAN ZHANG LIAN ZHOU LIZHONG JIANG SHIYING WANG YISHUANG YANG CHANGBING ZHAO XIN WANG XI SUN LONG WU JICHAO ZHANG YANLONG JIANG TAO |
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