CN105423116A - Hood adopting longitudinal-transverse reinforced rib structure and adopting RTM entire shaping technology and manufacturing method of hood - Google Patents

Hood adopting longitudinal-transverse reinforced rib structure and adopting RTM entire shaping technology and manufacturing method of hood Download PDF

Info

Publication number
CN105423116A
CN105423116A CN201510743538.6A CN201510743538A CN105423116A CN 105423116 A CN105423116 A CN 105423116A CN 201510743538 A CN201510743538 A CN 201510743538A CN 105423116 A CN105423116 A CN 105423116A
Authority
CN
China
Prior art keywords
rtm
horizontal bar
longitudinal rib
hood
cover
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
Application number
CN201510743538.6A
Other languages
Chinese (zh)
Inventor
李四杰
高秋艳
刘军
杨现伟
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Jiangsu Hengshen Co Ltd
Original Assignee
Jiangsu Hengshen Co Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Jiangsu Hengshen Co Ltd filed Critical Jiangsu Hengshen Co Ltd
Priority to CN201510743538.6A priority Critical patent/CN105423116A/en
Publication of CN105423116A publication Critical patent/CN105423116A/en
Pending legal-status Critical Current

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29BPREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
    • B29B11/00Making preforms
    • 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
    • B29C70/40Shaping or impregnating by compression not applied
    • B29C70/42Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B29C70/46Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
    • B29C70/48Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM], e.g. by vacuum
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16SCONSTRUCTIONAL ELEMENTS IN GENERAL; STRUCTURES BUILT-UP FROM SUCH ELEMENTS, IN GENERAL
    • F16S3/00Elongated members, e.g. profiled members; Assemblies thereof; Gratings or grilles
    • F16S3/06Assemblies of elongated members
    • F16S3/08Assemblies of elongated members forming frameworks, e.g. gratings

Abstract

The invention provides a hood adopting a longitudinal-transverse reinforced rib structure and adopting an RTM entire shaping technology and a manufacturing method of the hood. According to the hood, carbon fiber textiles are used as a material, the textiles are fixed by adopting a hot melting type fixative, material preparation is performed according to the design of a paved layer, and the textiles are cut; the cut textiles are paved and pasted to a hood mold for preparing preforms, then the preforms are assembled and matched, the RTM entire shaping technology is adopted, under 2-10 bar pressure, resin is poured into the hood mold in which the preforms are paved, finally the resin is solidified and shaped in a curing furnace, and the shaped resin is demolded after solidification so as to obtain the hood with the longitudinal-transverse reinforced rib structure and adopting the RTM entire shaping technology. According to the hood disclosed by the invention, the precision of external dimensions of products can be guaranteed; the continuity of longitudinal and transverse reinforced ribs and a panel is guaranteed through the entire shaping technology method; besides, second cementation shaping is not needed, the apparent mass is better, the dimensions of the products are high in precision, the fiber volume fraction is high, the porosity is low, and the cost of the mold can be reduced through batch production.

Description

RTM global formation orthogonal stiffeners structure member (cover) and manufacture method thereof
Technical field
The present invention relates to a kind of RTM global formation orthogonal stiffeners structure member (cover) and manufacture method thereof.
Background technique
Carbon fiber enhancement resin base composite material (CFRP) is one of current state-of-the-art composite material, there is the unique advantages such as high specific strength, high ratio modulus, fatigue resistance, heat resistant, designability, since coming out, be just subject to the concern and the attention that weight, performance are had to the aerospace community of rigors always.Advanced composite material fast development in recent years becomes one of four macrostructure materials after aluminium, steel, titanium, and becomes strategic material indispensable in the structures such as aircraft, space ship, rocket and man-made satellite.
The U.S. from F-14, F-15 fighter just adopt carbon fiber-epoxy composite material, comprise tailplane, rudder, the vertical fuselage such as steadying plate, airbrake at F-18 fighter especially wing to use in a large number, account for 10.3% of structure gross weight, F-117 aircraft have employed the composite material of nearly 40% structure weight.F-22 fighter adopts fibre reinforced toughness BMI composite material, and nearly cover, as all surfaces structures such as wing cover, forebody, empennage, frame, beam, wallboards, makes its operational mobility obtain and fully plays.And for example the central wing box of the airliner A380 of the up-to-date development of Air Passenger company and part outer wing, vertical tail and tailplane, joist and consequence press box, various cowlings etc. are all be made up of carbon fiber composite, and consumption accounts for 16% more than of structure weight.
Advanced composite material technology is the new technology that an application is very strong, but a large amount of practical applications also has high cost price, govern the development of advanced composite material, especially along with advanced composite material is widely accepted at civil area, cost benefit factor becomes its further broaden application market, asks for the bottleneck of great development.Therefore low cost composite technology becomes the key problem of world today's composite technology developmental research.And the core developing low cost composite technology is low-cost manufacturing technique, as RTM and derivative liquid condition shaping technique etc. thereof reduce equipment cost and energy consumption cost effectively, improve shaping efficiency.
Develop from wet lamination and Shooting Technique and the resin pouring and forming process (i.e. RTM technique) that the comes composite material process planning that to be of growing up gradually in recent years new.The Making mold of RTM technique and Material selec-tion are day by day flexible, can manufacture the complex component with excellent surface quality, high dimensional accuracy, have more advantage at the manufacture view of large component, and batch production can obtain best production economy benefit.Its technological principle is: lay reinforcing material preshaped body core and embedded part in advance in die cavity, then under pressure or vacuum force by resin injection closed mould cavity, wetting fibre, curing and demolding, then carry out the postprocessing working procedures such as secondary operations, final molding.
Lid is the cover plate structure or aircraft windows structure etc. of general carbon fiber casing, and be similar to cell structure, be generally made up of panel, frame, orthogonal stiffeners, this class formation first often adopts metal material, heavier mass; General frame and horizontal bar and longitudinal rib bear resistance to compression and anti-shearing effect, panel can realize sealing and transmitted load effect with miscellaneous part, the more employing vacuum aided importing of this class formation at present or autoclave molding complete panel and muscle structure respectively, and orthogonal stiffeners is by secondary cementation and formation.This process program advantage of lower cost, but orthogonal stiffeners and panel poor continuity, require higher, and bonding quality is uneven, does not meet aviation usage requirement to secondary cementation process.
Summary of the invention
The object of this invention is to provide the orthogonal stiffeners and panel poor continuity that exist in a kind of RTM global formation orthogonal stiffeners structure member (cover) and manufacture method solution prior art thereof, require higher to secondary cementation process, and bonding quality is uneven, do not meet the problems such as aviation usage requirement.
The manufacture method of a kind of RTM global formation of the present invention orthogonal stiffeners structure member (cover), process controllability is strong, can produce excellent surface quality and the higher lid goods of dimensional accuracy, fibre content is also higher, goods porosity ratio is lower, and lid quality of item stability is high, meets aviation usage requirement.
Technical solution of the present invention is:
A kind of RTM global formation orthogonal stiffeners structure member (cover), comprise panel, frame, horizontal bar and longitudinal rib, panel is located in frame, and horizontal bar and longitudinal rib are all located on panel, horizontal bar and longitudinal rib are mutually vertical to be arranged, and adopts the form that horizontal bar is continuous, longitudinal rib disconnects; This lid take carbon fibre fabric as material, by adopting heat molten type setting agent pattern bonded fabrics, according to Lay up design blanking and cutting fabric, lid mould carries out paving and prepares preshaped body, then assemble matched moulds, adopt RTM integral forming technique, by the lid mould of resin injection lay precast body under 2 ~ 10bar pressure, finally solidifying in curing oven, completes curing and demolding and obtains RTM global formation orthogonal stiffeners structure member (cover).
Further, carbon fibre fabric material is carbon fiber twilled cloth.Carbon fiber twilled cloth can provide stronger compression shear strength, has the paving that good deformability is convenient to precast body simultaneously and covers.
Further, the concrete grammar adopting heat molten type setting agent to prepare pre-setting fabric is: be positioned over by carbon fibre fabric reel on the station of hot melt powder boarding machine, take off roll drive carbon fibre fabric by powder spray room, then heat fused in drying room, then by cooling roll rolling.
Further, blanking adopts automatic fabric cutter to carry out, on die insert, first carry out the laying of horizontal bar and longitudinal rib, the fabric completing blanking is carried out flange process downwards in insert, the flange of insert surrounding becomes a part for horizontal bar and longitudinal rib, and then supplement strengthen horizontal bar and longitudinal rib everywhere, finally by panel lay on horizontal bar and longitudinal rib.
Adopt panel downwards, longitudinal rib and horizontal bar structure injection process upwards, heating mould solidifying in curing oven, demoulding reprocessing obtains lid goods.
Further, assembling matched moulds is specially: carry out matched moulds to upper die tooling and bed die, inspection tightness is not less than 0.98bar, and internal drop in five minutes is no more than 170mbar, first adopt negative pressure of vacuum to import resin during injecting glue, then increase injection pressure to 2 ~ 10bar gradually, fiber is fully infiltrated, bubble side by side, row's bubble is still to mould discharges.
Further, the middle position of the side of frame is provided with gum-injecting port, gum exudation mouth is furnished with respectively at the opposite side of longitudinal rib and horizontal bar infall and frame, glue-feeder runner design will compared with the short 3 ~ 6cm of frame article length, be beneficial to resin abundant wetting fibre gradually, and contribute to bubble and discharge from mould cavity.
A kind of manufacture method of RTM global formation orthogonal stiffeners structure member (cover), take carbon fibre fabric as material, by adopting heat molten type setting agent pattern bonded fabrics, according to Lay up design blanking and cutting fabric, lid mould carries out paving and prepares preshaped body, then matched moulds is assembled, adopt RTM integral forming technique, by in the lid mould of resin injection lay precast body under 2 ~ 10bar pressure, finally solidifying in curing oven, completes curing and demolding and obtains RTM global formation orthogonal stiffeners structure member (cover).
Further, carbon fibre fabric material is carbon fiber twilled cloth.
Further, the concrete grammar adopting heat molten type setting agent to prepare pre-setting fabric is: be positioned over by carbon fibre fabric reel on the station of hot melt powder boarding machine, take off roll drive carbon fibre fabric by powder spray room, then heat fused in drying room, then by cooling roll rolling;
Blanking adopts automatic fabric cutter to carry out, on die insert, first carry out the laying of horizontal bar and longitudinal rib, the fabric completing blanking is carried out flange process downwards in insert, the flange of insert surrounding becomes a part for horizontal bar and longitudinal rib, and then supplement strengthen horizontal bar and longitudinal rib everywhere, finally by panel lay on horizontal bar and longitudinal rib;
Assembling matched moulds is specially: carry out matched moulds to upper die tooling and bed die, inspection tightness is not less than 0.98bar, and internal drop in five minutes is no more than 170mbar, negative pressure of vacuum is first adopted to import resin during injecting glue, then injection pressure to 2 ~ 10bar is increased gradually, fiber is fully infiltrated, side by side bubble, row's bubble is still to mould discharges.
Further, the middle position of the side of frame is provided with gum-injecting port, gum exudation mouth is furnished with respectively at the opposite side of longitudinal rib and horizontal bar infall and frame, glue-feeder runner design will compared with the short 3 ~ 6cm of frame article length, be beneficial to resin abundant wetting fibre gradually, and contribute to bubble and discharge from mould cavity.
This kind of RTM global formation orthogonal stiffeners structure member (cover), provides a kind of precast body laying method, and a kind of low cost RTM integral forming technique manufacturing technology.Adopt carbon fibre fabric as raw material, prepare preshaped body by repeatedly pre-heat setting, by RTM integral forming technique resin by injection, improve precast body fibre content, reduce porosity ratio, finally ensure that the mechanical property of goods meets the requirement of port cover structure to load.Can aluminum die be adopted, effectively reduce Design of Dies weight, be convenient to die flip lifting operation.
The invention has the beneficial effects as follows: this kind of RTM global formation orthogonal stiffeners structure member (cover) and manufacture method thereof, take carbon fibre fabric as raw material, adopt two-sided RTM mould closing mould, ensure the boundary dimension precision of goods, weight about 15% is reduced than fabricated metals, compared with hot-press tank technique, this moulding process is adopted to reduce batch production cost, integral forming technique technology improves continuity and the join strength of orthogonal stiffeners structure and panel, fiber volume fraction is higher, porosity ratio is lower, through static test, result meets the loading demands of carbon fiber lid as box sealing lid completely.This manufacture method, ensure that the continuity of orthogonal stiffeners and panel from the technological method of global formation, and does not need secondary cementation and formation, apparent mass is better, and product's dimensional precision is high, and fiber volume fraction is high, porosity ratio is lower, and batch production also can save die cost.
Accompanying drawing explanation
Fig. 1 is the structural representation of embodiment of the present invention orthogonal stiffeners lid;
Wherein: 1-frame, 2-panel, 3-horizontal bar, 4-longitudinal rib.
Embodiment
The preferred embodiments of the present invention are described in detail below in conjunction with accompanying drawing.
Embodiment
A kind of RTM global formation orthogonal stiffeners structure member (cover), comprise panel 2, frame 1, horizontal bar 3 and longitudinal rib 4, panel 2 is located in frame 1, horizontal bar 3 and longitudinal rib 4 are all located on panel 2, horizontal bar 3 and longitudinal rib 4 vertical setting mutually, and adopt the form that horizontal bar 3 is continuous, longitudinal rib 4 disconnects; This lid take carbon fibre fabric as material, by adopting heat molten type setting agent pattern bonded fabrics, according to Lay up design blanking and cutting fabric, lid mould carries out paving and prepares preshaped body, then assemble matched moulds, adopt RTM integral forming technique, by the lid mould of resin injection lay precast body under 2 ~ 10bar pressure, finally solidifying in curing oven, completes curing and demolding and obtains RTM global formation orthogonal stiffeners structure member (cover).
Carbon fibre fabric material is carbon fiber twilled cloth.Carbon fiber twilled cloth can provide stronger compression shear strength, has the paving that good deformability is convenient to precast body simultaneously and covers.Adopt carbon fiber composite structure, not only can meet under lid carries various load-up condition, loss of weight more than 15% can also be realized.
The concrete grammar adopting heat molten type setting agent to prepare pre-setting fabric is: be positioned over by carbon fibre fabric reel on the station of hot melt powder boarding machine, take off roll drive carbon fibre fabric by powder spray room, then heat fused in drying room, then by cooling roll rolling.
Automatic fabric cutter is adopted to carry out blanking, on die insert, first carry out the laying of horizontal bar 3 and longitudinal rib 4, the fabric completing blanking is carried out flange process downwards in insert, the flange of insert surrounding becomes a part for horizontal bar 3 and longitudinal rib 4, and then supplement strengthen horizontal bar 3 and longitudinal rib 4 everywhere, finally by panel 2 lay on horizontal bar 3 and longitudinal rib 4.
Adopt panel 2 downwards, longitudinal rib 4 and horizontal bar 3 structure injection process upwards, heating mould solidifying in curing oven, demoulding reprocessing obtains lid goods.
Assembling matched moulds is specially: carry out matched moulds to upper die tooling and bed die, inspection tightness is not less than 0.98bar, and internal drop in five minutes is no more than 170mbar, negative pressure of vacuum is first adopted to import resin during injecting glue, then injection pressure to 2 ~ 10bar is increased gradually, fiber is fully infiltrated, side by side bubble, row's bubble is still to mould discharges.
On mould, the middle position of the side of frame 1 is provided with gum-injecting port, gum exudation mouth is furnished with respectively at longitudinal rib 4 and the opposite side of horizontal bar 3 infall and frame 1, glue-feeder runner design will compared with the short 3 ~ 6cm of frame 1 article length, be beneficial to resin abundant wetting fibre gradually, and contribute to bubble and discharge from mould cavity.
Wherein, embodiment can adopt punching block or aluminum dipping form mould, accurately can control boundary dimension and the outward appearance of lid, reduces goods postprocessing working procedures, is beneficial to later stage assembling and mass production.
A manufacture method for RTM global formation orthogonal stiffeners structure member (cover), rolling of being shaped on hot melt powder boarding machine by carbon fibre fabric, carries out blanking according to laying blanking figure on automatic cutting machines; According to design ply stacking-sequence, on mould, carry out the paving of fabric successively, and prepare beam preshaped body through repeatedly pre-heat setting; Adopt RTM integral forming technique, on the lid preshaped body prepared, matched moulds is carried out to mould, in curing oven, carry out resin by injection, solidifying; Complete curing and demolding and obtain RTM global formation orthogonal stiffeners structure member (cover).
As shown in Figure 1, the manufacture method of this kind of RTM global formation orthogonal stiffeners structure member (cover), lid mould carries out the paving of precast body, first by first layer paving on mould, carry out vacuum bag and press pre-heat setting; Treat that mould is down to room temperature and is started successively paving, after completing part panels 2 and orthogonal stiffeners laying, carry out vacuum bag and press pre-heat setting; Then all the other orthogonal stiffenerses are completed paving, finally cover remaining panel 2 laying group, complete precast body paving.Mould matched moulds is overturn 180 °, hangs in curing oven, connection glue injection pipeline and excessive sebific duct road, heating injecting glue solidifying; Finally carry out demoulding reprocessing, complete lid preparation.
During injecting glue, gum-injecting port is set at frame 1 one middle side part, jointing place and frame 1 opposite side establish excessive Jiao Kou in length and breadth, detect mould degree of vacuum during injecting glue and be not less than 0.98bar, internal drop in five minutes is no more than 170mbar, then adopts negative pressure of vacuum to import resin, fill up after die cavity until resin and raise injection pressure 2 ~ 10bar gradually, repeatedly arrange bubble, by bubble emptying between fiber in mould, then start solidifying.
The process employs optimization Lay up design, effectively strengthen the continuity of orthogonal stiffeners and panel 2, and carrying out simplifying operation in paving process, be conducive to Design of Dies and technological forming; This RTM integral forming technique feature is mainly manifested in: the die cavity that the size everywhere of these goods is formed by upper/lower die matched moulds ensures, RTM global formation effectively ensures article construction intensity and mass stability, and RTM technological forming injection pressure is up to 10bar, the abundant infiltration of effective promotion fiber and resin, and effectively reduce the porosity ratio of goods, improve goods fiber volume fraction.The features such as the carbon fiber lid prepared by the present invention has smooth outer surface, and size accurately controls, stable mechanical property, bearing capacity are large, intensity is high, lightweight.
The manufacture method of this kind of RTM global formation orthogonal stiffeners structure member (cover), adopt RTM integral forming technique first, batch micro operations cost is reduced relative to traditional hot-press tank technique, and integral forming technique ensure that the quality of goods does not affect by secondary bonding quality, and the goods of this manufacture technics have lower porosity ratio and higher fiber volume fraction.The internal soundness zero defect of goods can be checked by harmless scanning.
The bearing capacity of embodiment's gained orthogonal stiffeners lid is large, good rigidly, can meet the various load working conditions that certain casing of aviation uses, and relative to metallic article from heavy and light, simple to operate, manufacturing efficiency is high, cost is low, can realize mass production.
In addition to the implementation, patented product of the present invention can also have other mode of executions.All employings are equal to the technological scheme of replacement or equivalent transformation formation, all drop in the protection domain of application claims.

Claims (10)

1. a RTM global formation orthogonal stiffeners structure member (cover), it is characterized in that: comprise panel, frame, horizontal bar and longitudinal rib, panel is located in frame, horizontal bar and longitudinal rib are all located on panel, horizontal bar and longitudinal rib are mutually vertical to be arranged, and adopts the form that horizontal bar is continuous, longitudinal rib disconnects; This lid take carbon fibre fabric as material, by adopting heat molten type setting agent pattern bonded fabrics, according to Lay up design blanking and cutting fabric, lid mould carries out paving and prepares preshaped body, then assemble matched moulds, adopt RTM integral forming technique, by the lid mould of resin injection lay precast body under 2 ~ 10bar pressure, finally solidifying in curing oven, completes curing and demolding and obtains RTM global formation orthogonal stiffeners structure member (cover).
2. RTM global formation orthogonal stiffeners structure member (cover) as claimed in claim 1, is characterized in that: carbon fibre fabric material is carbon fiber twilled cloth.
3. RTM global formation orthogonal stiffeners structure member (cover) as claimed in claim 1, it is characterized in that, the concrete grammar adopting heat molten type setting agent to prepare pre-setting fabric is: be positioned over by carbon fibre fabric reel on the station of hot melt powder boarding machine, take off roll drive carbon fibre fabric by powder spray room, then heat fused in drying room, then by cooling roll rolling.
4. the RTM global formation orthogonal stiffeners structure member (cover) as described in any one of claim 1-3, it is characterized in that: blanking adopts automatic fabric cutter to carry out, on die insert, first carry out the laying of horizontal bar and longitudinal rib, the fabric completing blanking is carried out flange process downwards in insert, the flange of insert surrounding becomes a part for horizontal bar and longitudinal rib, and then supplement strengthen horizontal bar and longitudinal rib everywhere, finally by panel lay on horizontal bar and longitudinal rib.
5. the RTM global formation orthogonal stiffeners structure member (cover) as described in any one of claim 1-3, it is characterized in that, assembling matched moulds is specially: carry out matched moulds to upper die tooling and bed die, inspection tightness is not less than 0.98bar, and internal drop in five minutes is no more than 170mbar, first adopts negative pressure of vacuum to import resin during injecting glue, then injection pressure to 2 ~ 10bar is increased gradually, fiber is fully infiltrated, side by side bubble, row's bubble is still to mould discharges.
6. the RTM global formation orthogonal stiffeners structure member (cover) as described in any one of claim 1-3, it is characterized in that: the middle position of the side of frame is provided with gum-injecting port, be furnished with gum exudation mouth respectively at the opposite side of longitudinal rib and horizontal bar infall and frame, glue-feeder runner design will compared with the short 3 ~ 6cm of frame article length.
7. the manufacture method of RTM global formation orthogonal stiffeners structure member (cover) described in an any one of claim 1-6, it is characterized in that, take carbon fibre fabric as material, by adopting heat molten type setting agent pattern bonded fabrics, according to Lay up design blanking and cutting fabric, lid mould carries out paving and prepares preshaped body, then matched moulds is assembled, adopt RTM integral forming technique, by in the lid mould of resin injection lay precast body under 2 ~ 10bar pressure, finally solidifying in curing oven, completes curing and demolding and obtains RTM global formation orthogonal stiffeners structure member (cover).
8. the manufacture method of RTM global formation orthogonal stiffeners structure member (cover) as claimed in claim 1, is characterized in that: carbon fibre fabric material is carbon fiber twilled cloth.
9. the manufacture method of RTM global formation orthogonal stiffeners structure member (cover) as claimed in claim 1, it is characterized in that: the concrete grammar adopting heat molten type setting agent to prepare pre-setting fabric is: be positioned over by carbon fibre fabric reel on the station of hot melt powder boarding machine, take off roll drive carbon fibre fabric by powder spray room, then heat fused in drying room, then by cooling roll rolling;
Blanking adopts automatic fabric cutter to carry out, on die insert, first carry out the laying of horizontal bar and longitudinal rib, the fabric completing blanking is carried out flange process downwards in insert, the flange of insert surrounding becomes a part for horizontal bar and longitudinal rib, and then supplement strengthen horizontal bar and longitudinal rib everywhere, finally by panel lay on horizontal bar and longitudinal rib;
Assembling matched moulds is specially: carry out matched moulds to upper die tooling and bed die, inspection tightness is not less than 0.98bar, and internal drop in five minutes is no more than 170mbar, negative pressure of vacuum is first adopted to import resin during injecting glue, then injection pressure to 2 ~ 10bar is increased gradually, fiber is fully infiltrated, side by side bubble, row's bubble is still to mould discharges.
10. the manufacture method of RTM global formation orthogonal stiffeners structure member (cover) as claimed in claim 1, it is characterized in that: the middle position of the side of frame is provided with gum-injecting port, be furnished with gum exudation mouth respectively at the opposite side of longitudinal rib and horizontal bar infall and frame, glue-feeder runner design will compared with the short 3 ~ 6cm of frame article length.
CN201510743538.6A 2015-11-05 2015-11-05 Hood adopting longitudinal-transverse reinforced rib structure and adopting RTM entire shaping technology and manufacturing method of hood Pending CN105423116A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201510743538.6A CN105423116A (en) 2015-11-05 2015-11-05 Hood adopting longitudinal-transverse reinforced rib structure and adopting RTM entire shaping technology and manufacturing method of hood

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201510743538.6A CN105423116A (en) 2015-11-05 2015-11-05 Hood adopting longitudinal-transverse reinforced rib structure and adopting RTM entire shaping technology and manufacturing method of hood

Publications (1)

Publication Number Publication Date
CN105423116A true CN105423116A (en) 2016-03-23

Family

ID=55501534

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201510743538.6A Pending CN105423116A (en) 2015-11-05 2015-11-05 Hood adopting longitudinal-transverse reinforced rib structure and adopting RTM entire shaping technology and manufacturing method of hood

Country Status (1)

Country Link
CN (1) CN105423116A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108000894A (en) * 2017-11-08 2018-05-08 江西洪都航空工业集团有限责任公司 A kind of continuous load-carrying construction of global formation composite material orthogonal muscle
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
CN110978568A (en) * 2019-12-18 2020-04-10 航天特种材料及工艺技术研究所 Textile rigid thermal protection material and RTM forming method thereof

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN201014174Y (en) * 2007-03-16 2008-01-30 杨勇新 Basalt fibre grille
CN101885215A (en) * 2009-05-12 2010-11-17 上海复合材料科技有限公司 Forming method of composite material leaf grille for controlling speed of aviation aircraft
US20130344291A1 (en) * 2012-06-24 2013-12-26 The Boeing Company Composite Hat Stiffener, Composite Hat-Stiffened Pressure Webs, and Methods of Making the Same
DE102013209183A1 (en) * 2013-05-17 2014-11-20 Bayerische Motoren Werke Aktiengesellschaft Offended business repair
CN105216345A (en) * 2015-10-30 2016-01-06 江苏恒神股份有限公司 RTM global formation orthogonal stiffeners structure member (cover) and manufacture method thereof

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN201014174Y (en) * 2007-03-16 2008-01-30 杨勇新 Basalt fibre grille
CN101885215A (en) * 2009-05-12 2010-11-17 上海复合材料科技有限公司 Forming method of composite material leaf grille for controlling speed of aviation aircraft
US20130344291A1 (en) * 2012-06-24 2013-12-26 The Boeing Company Composite Hat Stiffener, Composite Hat-Stiffened Pressure Webs, and Methods of Making the Same
DE102013209183A1 (en) * 2013-05-17 2014-11-20 Bayerische Motoren Werke Aktiengesellschaft Offended business repair
CN105216345A (en) * 2015-10-30 2016-01-06 江苏恒神股份有限公司 RTM global formation orthogonal stiffeners structure member (cover) and manufacture method thereof

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108000894A (en) * 2017-11-08 2018-05-08 江西洪都航空工业集团有限责任公司 A kind of continuous load-carrying construction of global formation composite material orthogonal muscle
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
CN110978568A (en) * 2019-12-18 2020-04-10 航天特种材料及工艺技术研究所 Textile rigid thermal protection material and RTM forming method thereof
CN110978568B (en) * 2019-12-18 2022-04-08 航天特种材料及工艺技术研究所 Textile rigid thermal protection material and RTM forming method thereof

Similar Documents

Publication Publication Date Title
CN105216345A (en) RTM global formation orthogonal stiffeners structure member (cover) and manufacture method thereof
McIlhagger et al. Manufacturing processes for composite materials and components for aerospace applications
CN103407175B (en) A kind of integral forming method of fiber-reinforced resin matrix compound material wing box
CN103963319B (en) A kind of matrix material adds prepreg/Resin Film Infusion curing molding method altogether of muscle wallboard
CN106182801A (en) A kind of aircraft foam core filled composite material rudder face forming method
US9180629B2 (en) Method for producing an integral fiber composite part
CN103342167B (en) Method for making scaled composite material wing model
CN105235237A (en) Molding technology and molding tool of composite material J-shaped stiffened wallboard
CN103407173B (en) A kind of integral forming method of fiber-reinforced resin matrix compound material wing
CN102729482B (en) Composite heatproof bearing cylinder and preparation method thereof
CN106553357A (en) Hollow multi-cavity abnormal shape surface composite material complex structural member integral forming technique
CN106182805A (en) A kind of manufacturing process of the isometrical tubular structure of carbon fibre composite
CN104626605A (en) Composite material wing integral molding technological method and composite material wing integral molding tool
CN105423116A (en) Hood adopting longitudinal-transverse reinforced rib structure and adopting RTM entire shaping technology and manufacturing method of hood
CN101484291A (en) Method for producing a fibre composite component using a moulding core, and said moulding core
CN107521124A (en) Carbon fiber dual platen reinforced structure part and its manufacture method
CN102114706A (en) Method for forming frame, stringer and covering of composite material component through integrated co-curing
CN103538715A (en) Composite material pi-type lug interface and integral co-curing forming method
CN110181835A (en) A kind of variable cross-section double tapered aramid fiber honeycomb sandwich construction forming method
CN109562578A (en) The manufacturing method of composite material structure and composite material structure
CN109367071A (en) The production method of fibre reinforced composites ejection push arm
CN206528102U (en) A kind of T-shaped Material Stiffened Panel forming frock of composite
CN108943766A (en) A kind of composite material T-type Material Stiffened Panel is glued moulding process altogether
CN202702639U (en) Molding device of aircraft wing-shaped member pelvic fin
CN102501389B (en) Method for preparing composite material lamination structure through interlamination heat slip

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: 20160323