CN106182805A - A kind of manufacturing process of the isometrical tubular structure of carbon fibre composite - Google Patents

A kind of manufacturing process of the isometrical tubular structure of carbon fibre composite Download PDF

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Publication number
CN106182805A
CN106182805A CN201610814508.4A CN201610814508A CN106182805A CN 106182805 A CN106182805 A CN 106182805A CN 201610814508 A CN201610814508 A CN 201610814508A CN 106182805 A CN106182805 A CN 106182805A
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China
Prior art keywords
former
prepreg
tubular
mould
silicone rubber
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CN201610814508.4A
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Chinese (zh)
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CN106182805B (en
Inventor
段国晨
张明
赵景丽
林宇
赵伟超
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Northwestern Polytechnical University
Xian Aisheng Technology Group Co Ltd
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Northwestern Polytechnical University
Xian Aisheng Technology Group Co Ltd
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    • BPERFORMING OPERATIONS; TRANSPORTING
    • B29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29CSHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28Shaping operations therefor
    • B29C70/30Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/34Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
    • B29C70/342Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29CSHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C33/00Moulds or cores; Details thereof or accessories therefor
    • B29C33/38Moulds or cores; Details thereof or accessories therefor characterised by the material or the manufacturing process
    • B29C33/3842Manufacturing moulds, e.g. shaping the mould surface by machining
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29CSHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28Shaping operations therefor
    • B29C70/54Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29LINDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2023/00Tubular articles

Abstract

The present invention relates to the manufacturing process of the isometrical tubular structure of a kind of carbon fibre composite, combination former is used to control the outside dimension of product, prepare the combination plug of metal bar and silicone rubber as core, prepreg is in the continuous paving of core, expand pressure by silicone rubber after matched moulds, obtain the product of stable performance.The present invention is compared with CN 103802329 A and traditional handicraft, the dimensional accuracy solving product shape face is inaccurate, the problem being difficult to the demoulding, can ensure that the flatness of surfaces externally and internally simultaneously, reduce rigging error, need not solidify at autoclave, reduce manufacturing cost, meet the manufacture claim of certain type unmanned plane shoe pipe.

Description

A kind of manufacturing process of the isometrical tubular structure of carbon fibre composite
Technical field
The invention belongs to aircraft industry advanced composite material molding technology thereof field, relate to a kind of carbon fibre composite The manufacturing process of isometrical tubular structure.
Background technology
Advanced composite material not only has that specific strength is big, specific modulus is high, resisting fatigue, the characteristic such as anticorrosive, and has the strongest Designability.Reasonably design application, construction weight can be greatly reduced, improve the combination property of body, mission payload, In cruising time etc., therefore obtain increasing application in fields such as Aeronautics and Astronautics, automobile, steamer, medical treatment, physical culture.B787 Composite accounts for aero-structure weight and is up to 50%, and A400M large-scale military transportation airplane composite consumption is more than 35%, and unmanned Machine almost can reach full composite material housing construction.At present, preparing advanced composite structure has multiple moulding process, than As, autoclave vacuum-bag process technique, hands stick with paste fiberglass molding, pultrusion, RTM molding, VARTM etc., come from mode of operation See there are the modes such as manual paving, automatic winding, automated tape-laying.
Traditional advanced composite material tubular structure, has certain tapering, has drafting angle, can use metal core die Design, manual paving or automatic winding paving, ± 45 °, 0 °, 90 ° etc., utilize stripper apparatus to carry out the demoulding, manufacture product.But It is, for carbon fiber tubular structure for waiting gauge structure, there is no draft angle, and external diameter dimensional accuracy is had strict demand, use The process of conventional metals plug cannot realize at all.
Patent CN 103802329 A uses metal bar to prepare pipe as core, silicone rubber as pudendum mould, it is ensured that Internal diameter size, this method uncontrollable product outside dimension precision, demoulding difficulty.
Summary of the invention
Solve the technical problem that
In place of the deficiencies in the prior art, the present invention proposes the isometrical tubular structure of a kind of carbon fibre composite Manufacturing process, solve isometrical tubular structure cannot the demoulding, outside dimension inaccurate wait technological problems.
Technical scheme
The manufacturing process of the isometrical tubular structure of a kind of carbon fibre composite, it is characterised in that step is as follows:
Step 1, the involutory former of making carbon fiber tubular structure: involutory former is divided into former 1 and lower former 2;Upper the moon Mould 1 2-in-1 with lower former hold together after inner chamber profile consistent with tubular products overall dimensions, mould both sides leave guarantee prepreg flange The surplus in space;
The two ends of involutory former are provided with left end first speed plate (10) and right end baffle plate (12), are provided with location in the middle part of the baffle plate of termination Circular groove and through hole are used for controlling the position of metal mandrel (6);
Step 2, manufacture composite core formwork: at the inner chamber paving carbon ribbon prepreg of upper former and lower former, at carbon ribbon prepreg Upper paving glass cloth prepreg, forms bogusware and it is carried out solidification of hot-press tank;
Left end first speed plate (10) and right end baffle plate (12) is used to carry out upper former 1 and the lower 2-in-1 mould of former, by metal mandrel (6) put in mould, be positioned in the location circular groove of left end first speed plate (10);
Silicone rubber is poured in metal mandrel (6) and bogusware gap, uses right end baffle plate (12) to carry out sealing and determining Position metal mandrel (6), carries out solidification according to the silicone rubber solidifying requirements used and completes, obtain metal mandrel (6) outer cladding silicon The composite core formwork of rubber;
The number of plies of described carbon ribbon prepreg and thickness meet the design thickness of tubular products, the number of plies of glass cloth prepreg and Thickness meets the silicone rubber expansion process gap that product uses;
Step 3: former (1) and the bogusware of lower former (2) in removal, and inner chamber is cleaned and demoulding process;Then Use ± 45 ° of paving modes docked with 90 ° of wide beds and 0 ° at the inner chamber paving carbon fiber prepreg of lower former (2), paving Carbon fiber prepreg is more than the inner chamber of lower former (2);
Composite core formwork is placed on lower former (2), turns on composite core formwork more than the carbon fiber of the inner chamber of lower former (2) And it is coated with completely, it is ensured that the seriality of carbon fiber;
By upper former 1 and lower former (2) matched moulds, left end first speed plate (10) and right end baffle plate (12) are fixed on two ends and adopt Fix with fixture;
Step 4: solidified by the mould that matched moulds is good, has solidified the rear demoulding and has obtained the isometrical tubulose of carbon fibre composite Infrastructure product.
Described mould uses steel-frame structure.
The solidification of hot-press tank technological parameter of described step 2 is: pressure 0.4MPa, 1 DEG C/min of heating rate, rate of temperature fall 1 DEG C/min, 120 DEG C keep 1 hour, and 60 DEG C go out tank, are naturally down to room temperature.
The curing process parameter of described step 4 is: 3 DEG C/min of heating rate;120 DEG C of constant temperature keep 1 hour;Cooling speed 3 DEG C/min of rate, is cooled to 60 DEG C and goes out tank natural cooling, is cooled to room temperature and carries out the demoulding.
Beneficial effect
The manufacturing process of the isometrical tubular structure of a kind of carbon fibre composite that the present invention proposes, uses combination former to control The outside dimension of product, prepares the combination plug of metal bar and silicone rubber as core, and prepreg is at the continuous paving of core, matched moulds Expand pressure by silicone rubber afterwards, obtain the product of stable performance.
Use metal bar and silicone rubber as plug, the bigger thermal expansion stresses of silicone rubber can be passed through, it is achieved drying Case low cost prepares the isometrical tubular structure of high-performance advanced composite material, compared with CN 103802329A and traditional handicraft, solves The dimensional accuracy in product shape face is inaccurate, it is difficult to the problem of the demoulding, can ensure that the flatness of surfaces externally and internally simultaneously, reduces Rigging error, it is not necessary to solidify at autoclave, reduces manufacturing cost, and the development meeting certain type unmanned plane shoe pipe is wanted Ask.
Accompanying drawing explanation
Fig. 1: process chart
Fig. 2: embodiment carbon fiber tubular structure
Fig. 3: embodiment frock mould-matching structure
A: matched moulds, b: left view, c: right view, d: interior metal bar structure
Fig. 4: embodiment silicone rubber perfusion schematic diagram
The metal bar of Fig. 5: embodiment molding and rubber composition core
Fig. 6: embodiment carbon ribbon prepreg typical case's laying schematic diagram
The upper former of 1-, former under 2-, 3-process gap, 4-bogusware, 5-silicone rubber, 6-metal bar, 7-carbon fiber prepreg, 8-lifting bolt, 9-hexagon-headed bolt (M10*35), 10-termination baffle plate, 11-locating slot, 12-termination baffle plate, 13-positions hole, 14-orienting locator, 15-hexagon-headed bolt (M6*12), 16-notes rubber hole, and 17-prepreg back lining materials, 18-carbon ribbon is pre- Leaching material, 19-isolating membrane, 20-prepreg flange tooling face.
Detailed description of the invention
In conjunction with embodiment, accompanying drawing, the invention will be further described:
The first step, outer former manufactures and designs.Product external diameter R=35mm, length L=850mm, thickness δ=0.975mm.Adopt By the involutory former of CATIA three-dimensional software design carbon fiber tubular structure, frock profile and product design consistent size, such as Fig. 2 Shown in, this involutory former is made up of two parts, is upper former 1 and lower former 2 respectively.Mould uses steel-frame structure, frame-type Structure is primarily to meet the uniformity that mould hot-fluid in an oven is smooth.Enough surpluses 15 are left in mould both sides, it is ensured that pre- Leaching material flange space, die face uses digital control processing to shape, and mould designs termination baffle plate 10, termination baffle plate 12, locating slot 11, orienting locator 14, hexagon-headed bolt 9, hexagon-headed bolt 15, lifting bolt 8.
Second step, composite core formwork manufacture.Use three-dimensional software design metal mandrel, Φ 20mm, digital control processing.The present invention adopts With Airtech company of U.S. Aircast3700 silicone rubber, Aircast 3700 is A, B two-component silicone rubber, Part A:Part B (blue)=100:12, hot strength: 4.28MPa, shear strength: 0.45MPa, rupture rate elongation: 180%.First at Shang Yin Mould and 8 layers of carbon ribbon prepreg (product thickness) of the lower each paving of former, and 3 layers of glass cloth prepreg are (between silicone rubber expansion process Gap 3), it is simply that so-called bogusware 4.Every paving 3 layers carries out evacuation pre-compacted 1 time, and paving terminates to carry out vacuum bag process combination, Solidification of hot-press tank, pressure 0.4MPa, 1 DEG C/min of heating rate, 1 DEG C/min of rate of temperature fall, 120 DEG C keep 1 hour, and 60 DEG C go out Tank, is naturally down to room temperature, the not demoulding, periphery surplus is fallen clearly, and sand milling is smooth.At 1 layer of frock release cloth of surface paving.On carrying out Lower former matched moulds, utilizes orienting locator 14 that upper former 1 is placed accurate location, then uses hexagon-headed bolt 9 to clamp, uses spiral shell Nail fixing termination baffle plate 10.Then mould is disposed vertically, metal bar 6 is vertically put in mould inside, use locating slot 11 right Its location.The silicone rubber configured slowly is irrigated from hole for injecting glue 16, until overflow, hang on, until silicone rubber not under Heavy, wipe unnecessary spilling silicone rubber off, perfusion termination, side baffle plate 12 seals, and sees Fig. 4.It is little that room temperature stands 24 naturally Time, carry out the demoulding, take out core, as shown in Figure 5.Core frock apposition position glue rib employing fine sandpaper is carried out sand milling to smooth shape State, waits to be used.Use the process of bogusware perfusion silicone rubber, the frock of perfusion silicone rubber can be saved, work can be regulated Skill gap, there is presently no the report of related fields.
3rd step, release agent application.Dip in a small amount of acetone with clean veil upper former profile 1 and lower former profile 2 to be wiped Wiping clean, surface, without the exotic such as oil stain, dust, is dried the most naturally.Liquid release agent is prone to coating, it is also possible to play increase The effect of smoothness, the suggestion of this technique uses liquid release agent.Release agent application in strict accordance with the operating procedure code of releasing agent, Thus reach to smear uniform, exhaustive.Patent of the present invention uses willing sky FLEX-Z 5.0 liquid release agent system, and uses Waterclean deep clean agent and Sealer GP hole sealing agent, apply 4 times hole sealing agents and 2 times releasing agents, each interlayer It is spaced 15 minutes, waits 30 minutes paving products.
4th step, paving.At lower female mold surfaces paving carbon fiber prepreg, carbon fiber paving angle is respectively [-45/02/ 90/02/45], this patent uses the carbon ribbon prepreg of ACG company of Britain, MTM28-1-33%-12KT700SC-125- 600 in order to ensure that prepreg is the most docile, not the defect such as bridge formation, and this technique uses at lower former and silicon Rubber surface paving rather than carry out paving at silastic surface completely, does not also have the report of related fields.For ensureing fiber Seriality, as shown in Figure 6, carbon ribbon prepreg 18 (± 45 ° and 90 °) uses the full wafer wide bed, and carbon ribbon prepreg 18 (0 °) is along fiber Direction two panels is horizontally-spliced.Such as, paving the 1st layer 45 °, retain side back lining materials, in lower female mold surfaces paving, by unnecessary pre- Leaching material strip back lining materials turns to prepreg flange tooling face 15, at 1 layer of isolating membrane 19 of prepreg flange tooling face 20 region paving; 2nd layer, the 3rd layer of 0 ° of prepreg 18 only at the lower former wide bed to method seamed edge, carry out pre-compacted.90 ° and ± 45 ° of laying complete classes Seemingly, 0 ° of laying all fours, can stagger abutment joint.
5th step, places combination.After under core, the paving of former eyelid covering terminates, by plug (metal bar+silicone rubber) under On former, before placement, check that mandrel surface is the most jagged, corner angle, foreign material etc., don't fail to clean out exotic.
6th step, flange prepreg.Rubber surface is turned to by last 1 layer-45 °, overlap joint, tears isolating membrane, scrapes with scraper plate Flat.Then at 0 ° of carbon ribbon prepreg of silastic surface paving two-layer, with lower former paving 0 ° splicing.90 ° and+45 ° of layings with- 45 ° are similar to, and unique difference is exactly fiber docking.Remaining 0 ° of paving is similar to, and laterally docks at method seamed edge, 0 ° of burst paving and 45 ° Fig. 6 is shown in by full wafer wide bed schematic diagram.
7th step, matched moulds.As shown in Figure 2.After the complete paving of product terminates, carry out matched moulds.Upper former 1 is disposed vertically On lower former 2, it is to avoid rub product side, utilize orienting locator 14 to ensure the position of two frocks, use hexagon-headed bolt 9 Upper/lower die is locked, fixing two ends fixed dam 10 and fixed dam 12.Matched moulds is an important process, closes The bad overall dimensions that can affect product of mould, it is necessary to judge that upper and lower surface is fitted completely, entirely without gap.
8th step, solidification and the demoulding.The product that matched moulds is good is pushed into baking oven, uses low cost baking oven to solidify.Heat up 3 DEG C/min of speed;120 DEG C of constant temperature keep 1 hour;3 DEG C/min of rate of temperature fall, is cooled to 60 DEG C and goes out tank natural cooling, cooling To room temperature situation, carry out the demoulding.Owing to silicone rubber has bigger thermal coefficient of expansion, it is down to room temperature and will recover process gap, As long as the metal bar drawing centre just can realize the demoulding.This process uses thermal expansion of silicone rubber pressurization, so only needing Baking oven is wanted to provide the temperature required for solidification, it is achieved that the low cost manufacture of advanced composite material.
By above step, qualified isometrical tubular structure can be prepared, as shown in Figure 2.

Claims (4)

1. the manufacturing process of the isometrical tubular structure of carbon fibre composite, it is characterised in that step is as follows:
Step 1, the involutory former of making carbon fiber tubular structure: involutory former is divided into former (1) and lower former (2);Upper the moon Inner chamber profile after mould (1) closes up with lower former (2) is consistent with tubular products overall dimensions, and guarantee prepreg is left in mould both sides The surplus in flange space;
The two ends of involutory former are provided with left end first speed plate (10) and right end baffle plate (12), are provided with location circular groove in the middle part of the baffle plate of termination And through hole is used for controlling the position of metal mandrel (6);
Step 2, manufacture composite core formwork: at the inner chamber paving carbon ribbon prepreg of upper former and lower former, on carbon ribbon prepreg upper berth Patch glass cloth prepreg, forms bogusware and it is carried out solidification of hot-press tank;
Left end first speed plate (10) and right end baffle plate (12) is used to carry out upper former 1 and the lower 2-in-1 mould of former, by metal mandrel (6) Put in mould, be positioned in the location circular groove of left end first speed plate (10);
Silicone rubber is poured in metal mandrel (6) and bogusware gap, uses right end baffle plate (12) to carry out sealing and positioning gold Belong to plug (6), carry out solidification according to the silicone rubber solidifying requirements used and complete, obtain metal mandrel (6) outer cladding silicone rubber Composite core formwork;
The number of plies of described carbon ribbon prepreg and thickness meet the design thickness of tubular products, the number of plies of glass cloth prepreg and thickness Meet the silicone rubber expansion process gap that product uses;
Step 3: former (1) and the bogusware of lower former (2) in removal, and inner chamber is cleaned and demoulding process;Then use ± 45 ° of paving modes docked with 90 ° of wide beds and 0 ° are at the inner chamber paving carbon fiber prepreg of lower former (2), and the carbon of paving is fine Dimension prepreg is more than the inner chamber of lower former (2);
Composite core formwork is placed on lower former (2), turns on composite core formwork more than the carbon fiber of the inner chamber of lower former (2) and incite somebody to action It is coated with completely, it is ensured that the seriality of carbon fiber;
By upper former 1 and lower former (2) matched moulds, left end first speed plate (10) and right end baffle plate (12) are fixed on two ends and use solid Locking member is fixed;
Step 4: solidified by the mould that matched moulds is good, has solidified the rear demoulding and has obtained the isometrical tubular structure of carbon fibre composite Product.
The manufacturing process of the isometrical tubular structure of carbon fibre composite the most according to claim 1, it is characterised in that: described mould Tool uses steel-frame structure.
The manufacturing process of the isometrical tubular structure of carbon fibre composite the most according to claim 1, it is characterised in that: described step The solidification of hot-press tank technological parameter of rapid 2 is: pressure 0.4MPa, 1 DEG C/min of heating rate, 1 DEG C/min of rate of temperature fall, 120 DEG C of guarantors Holding 1 hour, 60 DEG C go out tank, are naturally down to room temperature.
The manufacturing process of the isometrical tubular structure of carbon fibre composite the most according to claim 1, it is characterised in that: described step The curing process parameter of rapid 4 is: 3 DEG C/min of heating rate;120 DEG C of constant temperature keep 1 hour;3 DEG C/min of rate of temperature fall, cooling Go out tank natural cooling to 60 DEG C, be cooled to room temperature and carry out the demoulding.
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CN106827583A (en) * 2017-01-23 2017-06-13 上海航秦新材料有限责任公司 A kind of composite material transmission shaft and its manufacture method
CN108943769A (en) * 2018-06-21 2018-12-07 西安爱生技术集团公司 The manufacturing method of the non-isometrical enclosed type square tube type carbon fiber girder construction product of unmanned plane
CN109049753A (en) * 2018-07-12 2018-12-21 江苏新扬新材料股份有限公司 A kind of preparation method of heat-resisting nose cone
CN109177225A (en) * 2018-08-24 2019-01-11 西安爱生技术集团公司 The manufacturing method of carbon fibre composite closure profiled beam
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CN109367054A (en) * 2018-11-07 2019-02-22 昌河飞机工业(集团)有限责任公司 A kind of forming method of the narrow chamber shape tube beam class composite element of heavy wall
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CN106827583A (en) * 2017-01-23 2017-06-13 上海航秦新材料有限责任公司 A kind of composite material transmission shaft and its manufacture method
CN108943769B (en) * 2018-06-21 2020-05-12 西安爱生技术集团公司 Manufacturing method of non-equal-diameter closed square tubular carbon fiber beam structural part of unmanned aerial vehicle
CN108943769A (en) * 2018-06-21 2018-12-07 西安爱生技术集团公司 The manufacturing method of the non-isometrical enclosed type square tube type carbon fiber girder construction product of unmanned plane
CN109049753A (en) * 2018-07-12 2018-12-21 江苏新扬新材料股份有限公司 A kind of preparation method of heat-resisting nose cone
CN109177225A (en) * 2018-08-24 2019-01-11 西安爱生技术集团公司 The manufacturing method of carbon fibre composite closure profiled beam
CN109203577A (en) * 2018-10-24 2019-01-15 郑州郑飞木业有限责任公司 A kind of manufacture craft of container outer rim precast body
CN109367054A (en) * 2018-11-07 2019-02-22 昌河飞机工业(集团)有限责任公司 A kind of forming method of the narrow chamber shape tube beam class composite element of heavy wall
CN110802850A (en) * 2019-10-12 2020-02-18 航天材料及工艺研究所 Forming method of composite material pipe with large slenderness ratio
CN111086128A (en) * 2019-12-27 2020-05-01 湖北航聚科技有限公司 Core mold for manufacturing solid rocket engine and forming method thereof
CN111391362A (en) * 2020-06-04 2020-07-10 沈阳西子航空产业有限公司 Thermal expansion and pressure forming method for flat tail silicone rubber of unmanned aerial vehicle composite material
CN112477192A (en) * 2020-10-22 2021-03-12 南京东聚碳纤维复合材料研究院有限公司 Forming method of high-rigidity conical-structure carbon fiber composite material pipe
CN112477193A (en) * 2020-10-22 2021-03-12 南京东聚碳纤维复合材料研究院有限公司 Composite material pipe forming tool system
CN112922947A (en) * 2021-01-20 2021-06-08 中国科学院国家天文台南京天文光学技术研究所 Carbon fiber thread bushing and application thereof
CN113290771A (en) * 2021-07-27 2021-08-24 宁波曙翔新材料股份有限公司 Method for manufacturing air inlet channel by using silica gel core layer die

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