JPH03272829A - Method and device for integral molding of composite material multi-cross-beam structure - Google Patents
Method and device for integral molding of composite material multi-cross-beam structureInfo
- Publication number
- JPH03272829A JPH03272829A JP2072662A JP7266290A JPH03272829A JP H03272829 A JPH03272829 A JP H03272829A JP 2072662 A JP2072662 A JP 2072662A JP 7266290 A JP7266290 A JP 7266290A JP H03272829 A JPH03272829 A JP H03272829A
- Authority
- JP
- Japan
- Prior art keywords
- composite material
- composite
- beam structure
- frame
- cross beam
- 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.)
- Granted
Links
- 239000002131 composite material Substances 0.000 title claims abstract description 80
- 238000000465 moulding Methods 0.000 title claims abstract description 29
- 238000000034 method Methods 0.000 title claims description 21
- 238000010438 heat treatment Methods 0.000 claims abstract description 4
- 210000000988 bone and bone Anatomy 0.000 claims description 20
- 238000005304 joining Methods 0.000 claims description 3
- 239000011248 coating agent Substances 0.000 abstract 1
- 238000000576 coating method Methods 0.000 abstract 1
- 238000009461 vacuum packaging Methods 0.000 abstract 1
- 239000000463 material Substances 0.000 description 9
- 229920001971 elastomer Polymers 0.000 description 8
- 239000000806 elastomer Substances 0.000 description 8
- 238000004519 manufacturing process Methods 0.000 description 7
- 229920002430 Fibre-reinforced plastic Polymers 0.000 description 4
- 239000000853 adhesive Substances 0.000 description 4
- 230000001070 adhesive effect Effects 0.000 description 4
- 239000011151 fibre-reinforced plastic Substances 0.000 description 4
- 239000002689 soil Substances 0.000 description 4
- 229910000831 Steel Inorganic materials 0.000 description 3
- 150000001875 compounds Chemical class 0.000 description 3
- 238000005520 cutting process Methods 0.000 description 3
- 239000010959 steel Substances 0.000 description 3
- 229920001296 polysiloxane Polymers 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 239000003566 sealing material Substances 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 241001342895 Chorus Species 0.000 description 1
- 240000005109 Cryptomeria japonica Species 0.000 description 1
- 235000008375 Decussocarpus nagi Nutrition 0.000 description 1
- 244000309456 Decussocarpus nagi Species 0.000 description 1
- 208000029497 Elastoma Diseases 0.000 description 1
- PEDCQBHIVMGVHV-UHFFFAOYSA-N Glycerine Chemical compound OCC(O)CO PEDCQBHIVMGVHV-UHFFFAOYSA-N 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 239000002390 adhesive tape Substances 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- HAORKNGNJCEJBX-UHFFFAOYSA-N cyprodinil Chemical compound N=1C(C)=CC(C2CC2)=NC=1NC1=CC=CC=C1 HAORKNGNJCEJBX-UHFFFAOYSA-N 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000006866 deterioration Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 239000000945 filler Substances 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 239000011888 foil Substances 0.000 description 1
- 210000003127 knee Anatomy 0.000 description 1
- 210000004072 lung Anatomy 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 230000014759 maintenance of location Effects 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 239000012783 reinforcing fiber Substances 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- 235000013522 vodka Nutrition 0.000 description 1
- 230000037303 wrinkles Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
- B29C43/02—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor of articles of definite length, i.e. discrete articles
- B29C43/10—Isostatic pressing, i.e. using non-rigid pressure-exerting members against rigid parts or dies
- B29C43/12—Isostatic pressing, i.e. using non-rigid pressure-exerting members against rigid parts or dies using bags surrounding the moulding material or using membranes contacting the moulding material
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D99/00—Subject matter not provided for in other groups of this subclass
- B29D99/001—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings
- B29D99/0014—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings provided with ridges or ribs, e.g. joined ribs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
- B29C43/32—Component parts, details or accessories; Auxiliary operations
- B29C43/36—Moulds for making articles of definite length, i.e. discrete articles
- B29C43/3642—Bags, bleeder sheets or cauls for isostatic pressing
- B29C2043/3644—Vacuum bags; Details thereof, e.g. fixing or clamping
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/46—Shaping 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/001—Profiled members, e.g. beams, sections
- B29L2031/003—Profiled members, e.g. beams, sections having a profiled transverse cross-section
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Architecture (AREA)
- Civil Engineering (AREA)
- Structural Engineering (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
- Moulding By Coating Moulds (AREA)
- Lining Or Joining Of Plastics Or The Like (AREA)
Abstract
Description
【発明の詳細な説明】
〔発明のＩＩ的〕
（ｆｒ業」二の利用分野）
本発明は、航空機等の一次構造月に適用される複合材多
桁構造の一体成形方法および−・体成形装置１ご関する
。DETAILED DESCRIPTION OF THE INVENTION [Part II of the invention] (Second field of application of FR industry) The present invention relates to a method for integrally forming a composite multi-girder structure applied to a primary structure such as an aircraft, and a method for integrally forming a body. Regarding device 1.
（従来の技術）
従来航空機等の構造部材として、アルミやチタンのよう
な金属材料や、繊維強化プラスチツク系の複合材料が使
用されているか、航空機構造等の重量軽減の見地から、
比強度、比剛性の高い繊維強化プラスチツク系複合材料
の翼構造等の一次構迅材への通則化が進み、最近では、
外板と多数０祈丁および小骨を接着剤を使用することな
く、−度に接着組み立てられる多桁一体構造が大川され
つつある。(Prior art) Metal materials such as aluminum and titanium, and composite materials such as fiber-reinforced plastics have been used as structural members of aircraft, etc., from the standpoint of reducing the weight of aircraft structures.
The standardization of fiber-reinforced plastic composite materials with high specific strength and specific stiffness for primary structural materials such as wing structures has progressed, and recently,
Multi-girder integrated structures are now being developed in which the outer panel, numerous cross-pieces, and small bones can be assembled in one go without the use of adhesives.
このような複合材多桁構造の一体成形方法とし。This is an integral molding method for such a composite multi-digit structure.
て、柘や小骨のつ］ｌ−ブ面に、繊維強化ブラ又グ・・
ツク製スティフニングダイヤプラムという部品のＩＶ滑
度を保持する治具を用いて、シリコーン製ブラダモール
ドを介してオー トラ１ノーブ圧力をｔ１荷するように
した技術１段は、ＡＩＡＡレボ−１・８〇−０７４４（
翼と胴体の一体桔へ）に記載されＣいる。Fiber-reinforced bra...
The first stage of the technology, which uses a jig to maintain the IV slippage of a part called a stiffening diaphragm made by Tsuku, and applies t1 of autora 1 knob pressure through a silicone bladder mold, is the AIAA Revo-1. 80-0744 (
It is written on the integral part of the wing and fuselage).
また外板、桁、小骨の組み付１．フ品に、ハキＪ−ムフ
ィルムまたはブラダモールドを直接適用しｒ１オートク
レーブ圧力４．負荷するよ・）ようにし、た複合材材料
製品の−・体成形方法は、特開昭５８−＝２０５７３０
号公報に記載さｎ−ｒいる。Also, assembling the outer panels, girders, and small bones 1. Directly apply a film film or bladder mold to the product and apply autoclave pressure 4. A method for forming a body of a composite material product under a load is disclosed in Japanese Patent Application Laid-Open No. 58-205730.
It is described in the publication No. nr.
また複合ｉｆ１部利をエラストマ系材料て形成１、た成
形治具を用いて、成形か・′つ組みイ４けＥ２、さらに
純量なく、′ｒ−ラストマ系治具を話め込んこ、真空ノ
（ラグフィルムを介し、ヱ加熱し、コーラス］・マ系４
４料の熱膨張圧を利用するようにした複合材構造部品の
一体成形方法は、特開昭！５５−４１２１．０号公報に
記載されている。In addition, a composite IF1 part was formed using an elastomer material 1, and a molding jig was used to mold it. Vacuum (via rag film, heat, chorus)・M system 4
A method for integrally molding composite structural parts that utilizes the thermal expansion pressure of four materials is disclosed in JP-A-Sho! It is described in No. 55-4121.0.
さらに部品同士の接音廂（桁）うンジ［ｔ！ｌ）にシー
ル溝を切削加ＬＬ、このシール溝にシール材を充填する
技術手段は発知てあり、これを改良しで部品単体で接合
面（Ｊシール溝を一体成形するようにした成形方法がた
とえばＰｒｏｃ ＩｎｓｔｎＭｅｅｈ Ｅｎｇｆｓ
Ｖｏ １２００ （１９８６）に開示されている。Furthermore, the contact distance between the parts [t! The technical means of cutting a seal groove in L) and filling this seal groove with sealing material is known, and by improving this, we have developed a molding method in which the joint surface (J seal groove) is integrally molded on a single component. For example, Proc InstnMeeh Engfs
Vo 1200 (1986).
−ｈＡＩＡＡｌ／ボート８Ｏ−０７４４（翼と胴体（７
）一体結Ｄ ）に記載されマニいる複合材多桁構造の一
体成形装置は、外板の外面形状を形成するような複曲面
を有するスチールベースと、外板と詩う桁および小骨の
フランジ而を形成省るような複曲翻を白゛するサボーと
、サボーの形状を保持Ｌ７バキユー人マニホールドとし
でも作用する複曲面４−ずｆするアッパーツーリングプ
レートとＦ＃ｉ”］２て構成され、ザボ−の°フランジ
に接する商およびアッパーツーリングブし・−トに接４
″る１ｈ」は複曲面とな一１ｃている。-hAIAAl/Boat 8O-0744 (wings and fuselage (7
) Integral construction D) The integrated molding device with a composite multi-girder structure described in (D) consists of a steel base with a multi-curved surface that forms the external shape of the skin, and flanges of girders and small bones that connect with the skin. It consists of a sabot that has a double curve that eliminates the formation of a cylindrical shape, an upper tooling plate with a double curved surface that holds the shape of the sabot, and also acts as a manifold for the L7 Bakyu manifold, The quotient in contact with the flange of the bottom and the contact with the upper tooling butt 4
``1h'' is a compound curved surface 1c.
（発明が解決しようとする課題）
拓や小骨のウェブ面に、スデイフー二一ングダイヤフラ
ムを設ｉｊ１ シリコーン製ブラダモールドを介してオ
ートクレーブ圧力を１′１荷するよつにした杉−術手段
では、スティフニングダイヤフラムの外周部てオー ト
クレープ圧力の不均一か発生し、桁や小骨のウェブ面の
変形あるいは積層成形品内部の強化繊維の蛇行等の品質
低下を招き、外板が複雑曲面を有しＣいる場合には、桁
や小骨が外板の而にχ・ｔ［２て直角に配置されないた
め、硬化中は不安定となり、また桁と小・円の接合部で
は、ステイソ；６ングダイヤ゛ノラムかむい／、−め、
小さな圧力半均・−ｒも成形品に大きな変形か生１３．
て（、まう。(Problems to be Solved by the Invention) In the Sugi technique, a sudaihu double diaphragm is installed on the web surface of the ossicles and the autoclave pressure is applied 1'1 through a silicone bladder mold. Uneven autoclaving pressure occurs around the outer periphery of the stiffening diaphragm, leading to quality deterioration such as deformation of the web surface of girders and small bones, meandering of reinforcing fibers inside the laminated molded product, and the possibility that the outer panel has a complex curved surface. In the case of C, the girders and small bones are not placed at right angles to the outer skin, making it unstable during hardening, and at the joints of the girders and small circles, stays; Noram Kamui/,-me,
Even a small pressure half-uniform -r can cause large deformation of the molded product.13.
Te(, mau.
まｔ外板、Ｒ１、弔問の組ろイ・１け品に、バキュ人ソ
イル１．まｔ４−はブラダモールドを直接適用し２て、
オートクレーブ圧力を負荷ｔよ〕ようよフにした複へ材
材料製品Ｑ）一体成形り法では、硬化時に成形部材の形
状保持のための治具か配置されていないため、成形品に
人きな変形か牛し、よた外板、桁、小骨にバキ−１−１
、フィルムまたはブうダモールトを直接接触するため、
積層品にしわや繊維の蛇行か発生ずるこまかある。Outer board, R1, condolence assembly, 1 item, Bakyujin soil 1. For t4-, directly apply the bladder mold 2,
Composite material product made by applying autoclave pressure to the load t) Q) In the integral molding method, there is no jig in place to maintain the shape of the molded part during curing, so there is no chance of people touching the molded product. It is deformed, and the outside plate, girder, and small bones are damaged - 1-1
, for direct contact with film or vodka mold,
Laminated products have wrinkles and meandering of fibers.
またＩｊＦ占４４部材を毛うλトマ系＋Ｉ料て形成した
成形治具を用い、さらに′隙間なくエラストマ系冶具を
詰め込んで、真空バッグフィル人を介（２て加熱し２、
エラストマ系材料の熱膨張圧を利用する複合材構造部品
の一体成形方法では、エラストマ系材料の熱膨張による
硬化圧のため、硬化中の温度差により圧力が異なり、変
形や内部品質不良の原因となり、またエラストマ系治具
は熱容量が大きいため、昇温効率が悪く、温度不均一が
発生したリ、オＬ）すＬ／・−ブや硬化炉の消費エネル
ギが人きくな・−）でし、よう。In addition, a molding jig made of IjF 44 material and λ toma + I material was used, and an elastomer jig was packed without any gaps, and then heated in a vacuum bag (2).
In the integral molding method of composite structural parts that utilizes the thermal expansion pressure of the elastomer material, the curing pressure is due to the thermal expansion of the elastomer material, so the pressure varies depending on the temperature difference during curing, which can cause deformation and internal quality defects. In addition, since elastomer jigs have a large heat capacity, they have poor heating efficiency, resulting in uneven temperature. , Yo.
ざらに部品同士ω接０面１．゛シール溝を切削加］ニア
し、このシール溝にシール材を充埴する技術手段では、
シール溝を切削加りするために、専用の治具およびＮ／
Ｃプログラミングが必要となり、コスト高となってしま
う。また部品単体の接合向にシール溝を一体代形する成
形方法では、部材同士を連接する際に、部斗４形状のば
らつきによる溝装置のずれ等が発生ずる場Ａには、この
シール溝を修１丁しなければなＪ）ず、製品全体の品質
を安カ′、〜せるこたがむすかし、い。Roughly the parts are in ω contact with each other on the 0 plane 1. With the technical means of "cutting the seal groove" and filling the seal groove with sealing material,
In order to cut the seal groove, a special jig and N/
C programming is required, resulting in high costs. In addition, in the molding method in which a seal groove is integrally formed in the joining direction of individual parts, this seal groove is used in case A where deviation of the groove device due to variations in the shape of the part 4 occurs when connecting the parts. I have to make some repairs, but the overall quality of the product is cheap.
またＡＩＡＡ１ノボ−ト８０−０７４４の複合相多桁構
造の一体成形装置”では、フリンジ商の精度を確保する
ために、サボーとアッパーツーリングプレートと０間に
隙間が生Ｌ］ないように、曲面形状のアッパーツーリン
グブし・−トのににザボーを積層し、て製作イるかザボ
ーを１′商形状に製作しｒ後にアッパーツーリングプレ
ー １・の曲面形状（、′合うように曲面切削する工程
を必要とし、長期の製造ｌｌ数を要［７、また勺ボーは
製品との熱膨張イーをｔよくまために複音イ、（てｆ’
ｔられているの１、Ｉ′対し、てアッパーツーリングプ
レート・はスヂール製であるから、オートクレーブ硬化
時に、→プボーと°ｊ′ツノく・−ツリングブレー」・
の熱膨張差により接触面にずわか生１２、ザボーの変形
ない【フラッジ面の粘瓜：不良を招く。（６かもアッパ
ーツーリングブｌ、−１−は中空断面であるために、後
間１ｆｉ１’：ｉ：）じ成するには、曲６＋＝成形した
板を溶接するか、板を溶接ｔ、た後にこの板を切削する
工程を必廿とし長期の製造Ｆ−１数を要し２、またブラ
ダ４．−ルドを使用し゛ご複合材多積構造を真′皇・減
圧する場畠には、アノ／ζ−ツーリングプレートの上側
°（゛シールし、°ζ゛、気密性を保持しなければなら
なＬ）が、アッパ・−ツー リングブＬ／トが後間１１
ｆｉＴあるから、粘看デーブや機械的クラ：／ブ装置を
用い−６も、完全な気密性を確保ｊることか難しく、製
品の品質に影響をＶ４ ｘることになる。In addition, in order to ensure the accuracy of the fringe quotient, the AIAA1 Novot 80-0744 "integral molding device with a composite phase multi-digit structure" is designed to prevent gaps between the sabot, the upper tooling plate, and the The upper tooling plate is laminated on top of the upper tooling plate of the shape, or the plate is made into a 1' quotient shape, and then the upper tooling plate is cut to fit the curved surface shape of 1. It requires a long manufacturing process and a large number of production units.
1, I', whereas the upper tooling plate is made of steel, so when it is cured in an autoclave, the upper tooling plate is hardened.
Due to the difference in thermal expansion, the contact surface will be slushy (12), and there will be no deformation of the sagbo. (6) Since the upper tooling block 1, -1- has a hollow cross section, the rear 1fi1':i:) can be achieved by welding the formed plate or by welding the plate. Later, a process of cutting this plate is required, which requires a long period of time for manufacturing F-1.2, and the bladder4. When truly compressing or depressurizing a composite multi-layer structure using a shield, the upper part of the tooling plate must be sealed and kept airtight. L) is upper - touring B/L is rear 11
Due to the fiT, it is difficult to ensure complete airtightness using adhesive tape or mechanical clamping equipment, which may affect the quality of the product.
本発明は上記した点に鑑みてなき４またもので、硬化中
の相、小間の形状保持わよび月］力均−化および槓と小
骨の接合部の圧力均一化を図り、品質の安定した複合材
多桁構造をｍ＝体成形するようにし、た複合材多桁構造
の・一体成形ノノ？去および、−９体成形装置を捉供す
ることを口約４とする。The present invention has been developed in view of the above-mentioned points and is unique in that it aims to equalize the phase during hardening, the shape retention of the booth, the force equalization, and the pressure at the joint between the ram and the small bones, thereby achieving stable quality. The composite material multi-digit structure is molded into m = body, and the composite material multi-digit structure is integrally molded. It takes about 4 hours to remove and provide a -9 body forming device.
［発明の構成１
（課題を解決するための手段）
本発明の複合材多桁構造の一体成形力法は、フランジを
（ｉする小間の枠と枠内に小判を縦横に配置（また複合
材の多桁構造体に、曲面を（する複呂・材の外板を、加
熱、加圧、硬化処理し、で接合する複合材多桁構造の一
体成形方法においで、に記複合材列仮を、この外板の形
状に倣−）た面をｈ゛すＺ）成形型ベースの上に置き、
このｈ ９材外板の上に上記複合ヰ４多術構造体を配置
し、この複合相多桁構造体の１部フランジの両端より複
合相外板全体にわたりコールシートを配置し、複合材多
桁構造体の小骨の左右内側全体に一定数１ｖのパッドを
被せ、複合材多桁構造体のＬ部フランジの上面に、」二
部フランジの形状に倣った面を６する成形型のＬ型を置
き、この毛割の上に押さえ枠を置き、これら全体を真空
バッグ用フィルムで覆いか一つ小・目０左７１”内側（
！′１部フラフランＦＩＴ１ｉを剛性ロケータで押さえ
、し、かる後、加輛、加ｆｆ、硬化処理して接ｎ″４る
複合材多桁構造体一体成形方法。[Structure 1 of the Invention (Means for Solving the Problems) The integral forming force method of the composite multi-digit structure of the present invention is based on the integrated forming force method of the composite material multi-digit structure. In the integral molding method of composite multi-digit structure, which involves heating, pressurizing, hardening, and bonding the curved surface of the multi-digit outer panel to the multi-digit structure, Place the surface that follows the shape of this outer plate on the mold base,
The above-mentioned composite 4 multi-layer structure is placed on top of this H9 material outer panel, and a call sheet is placed over the entire composite layer outer panel from both ends of the 1 part flange of this composite layer multi-girder structure. A fixed number of 1V pads are placed over the entire left and right inner sides of the small bones of the girder structure, and an L-shaped mold is placed on the upper surface of the L flange of the composite multi-girder structure, with a surface that follows the shape of the two-part flange. , place a presser frame on top of this hair split, and cover the whole with vacuum bag film.
! A method for integrally molding a composite multi-digit structure in which a part fluff flan FIT1i is held down with a rigid locator, and then applied, applied, and hardened to be connected.
本発明σ）一体成形形装置は、゛７ラニ、７′を１ｉ１
′する小十１の枠ど枠内に小骨を縦横に配設した複合材
の多桁構造体に、曲面を有する複合Ｈの外板を接合する
複合＋Ａ多ｋｙ構造の一体ｆ＞！２ ＋＋、）装Ｈにお
いて、複音ヰ号外板の形状に倣った成１［７型用・＼−
−−・−と、複合相多桁構造体の小ｆ１の左右内ＩＩＩ
全体に披せら才１ろパッドと、複合＋、１多桁構込体の
小・［１のフラン１．に彼せられ小４″１゛の−１−面
を同−曲ｉ’、ｆｉｉ内に４１’ｔ、置させる土７型Ｊ
７、このｌ二ｇＪの土に配、置され」−型の上面を開平
面内に位置さぜる押さ２枠とを（ｊＬ−で構成される。The present invention σ) integrally molded device has 7 rays and 7′ in 1 i 1
An integrated composite + A multi-digit structure in which a composite H outer panel with a curved surface is joined to a composite multi-girder structure in which small bones are arranged vertically and horizontally within a small frame. 2 ++,) In the case of
--・- and the left and right inner III of the small f1 of the composite phase multi-digit structure
The entire body is made up of 1 rotor pad, composite +, 1 multi-digit structure, and 1 flan 1. Place the -1-side of the small 4"1" in the same song i', fii at 41't, type 7 J.
7. Place and place on this l2gJ soil and press two frames to position the upper surface of the mold in the open plane (jL-).
（作 用）
本発明のｙＪ、合材多桁横進の 体成形ｌｊ法において
は、複ａ＋４外板と複合材多相構造体を接合する際に、
複ｉＭ’ Ｕ外板側にこの外板の形状に倣−ノた成形型
のべ一＝スを配置するとともに、複合材多１１ｉ１構遺
体の小骨のｈ行内側全体に被さるように一定板厚のパッ
ドを配置１３．た０“ζ、硬化中に生じる圧力不均一に
什う変形が補正され、複合材多積構造体の小骨および桁
に均一な圧力が加λＩ？）れ、また複合材多桁構造体の
」二部フランジ側に上部”フランジの形状に倣−）た成
形９の１型を配置し、か−）こい−Ｌ型の上に押さλ枠
を置き、これら全体を真空バッグ用フィル人で覆いか一
つ小骨の左右内側と上部フランジ下面を剛性ロケータで
押さえることで、圧力不均一で変形しようとする接舎部
を正規な形状を保持（１１、軽量で品質の向４二した複
雑曲面をもつ複合材多桁構造体を成形できる。(Function) In the yJ and composite material multi-digit lateral movement body forming method of the present invention, when joining the composite A+4 outer panel and the composite material multiphase structure,
A mold base is placed on the outer panel side of the compound IM'U, following the shape of this outer panel, and a plate with a constant thickness is placed so as to cover the entire inner side of the h-row of the small bones of the composite material multi-11i1 structure body. Place the pad 13. 0"ζ, the deformation due to uneven pressure that occurs during curing is corrected, and uniform pressure is applied to the bones and girders of the composite multi-layer structure. Place mold 1 of molding 9 that follows the shape of the upper flange on the second part flange side, place the pressed λ frame on top of the L shape, and cover the whole with a vacuum bag filler. By holding down the left and right inner sides of the small bones and the lower surface of the upper flange with rigid locators, the normal shape of the joint part, which tends to deform due to uneven pressure, is maintained (11, complex curved surfaces with light weight and quality improvements 42) Composite multi-digit structures can be molded.
本発明の複合材多桁構造の一体成形装置においでは、成
形品ε接触する向を複曲面としその他の面を平面とする
ことで、装置の製作期間か大幅に短縮され、装置の製造
コストか下がり、またシール面を平面状とすることて真
空バソグブイル！、による気密性の確保ができ、軽量で
品質の向上［、た複雑曲面をもつ複合材多桁構造体を成
形できる。In the composite multi-digit structure integral molding device of the present invention, by making the direction in which the molded product ε contacts a multi-curved surface and the other surfaces being flat, the manufacturing period of the device can be significantly shortened and the manufacturing cost of the device can be reduced. Vacuum bathogbuil by lowering and making the sealing surface flat! , it is possible to ensure airtightness, reduce weight and improve quality [and also make it possible to form composite multi-digit structures with complex curved surfaces.
（実施例） ↓１下本発明の一実施例を図面に一つき説明する。(Example) ↓1 Below, one embodiment of the present invention will be explained with reference to the drawings.
第１図は本発明による複合材多桁構造の一体成形方法に
より作られた複合材多桁構造の−・例を示すものであり
、この複合材多桁構造１は、外板２とＦ＜ｉ ３ε小骨
４とから形成きれ、桁３と不倒・４を一体成形装置５（
第２図）に表り外板２に対し５て直角てない角度に配置
し７、接着剤を用いることなく一度にオートクレーブ硬
化することにより成形される。FIG. 1 shows an example of a composite multi-digit structure made by the method of integrally molding a composite multi-digit structure according to the present invention. i 3ε is formed from the small bones 4, and the girder 3 and the inverter 4 are integrally molded by the device 5 (
As shown in FIG. 2), it is placed at an angle 5 which is not perpendicular to the outer panel 2, and is molded by curing in an autoclave at once without using an adhesive.
上記−・体成形ｇ置５は、第２図ないし第４図に示すよ
）に、複含ヰ４外板の形状に倣った而をａ（７外板２の
形状を保持ｊるための成形型用ハく一ス６ε、バキュー
ムマニホールドの作用を兼ねる上面治具７と、桁３およ
び小骨４の上面側の曲面形状を保持するサボー８と、桁
３および小−１’ｔ４の“フランジ面やウェブ面に均一
なオートクレーブ圧力を法えかつ硬化中の桁３および小
骨４の形状を保持する一定板厚のエラストマ製バッド９
と、外板２に均一な圧力を伝えかつ真空引き時の補助杓
料等ωＬ５わが外板２に転写しないようにするフールシ
）−１０と、Ａ空引き時の気密袋を形成するエラストマ
製ブラダモールドまブニは真空バッグ用フィルト］１を
有（５ている。上記ザボー８の上面は、上面治具７に対
しζ平面°Ｃ接触するような形状をなし°Ｃおり、硬化
時の熱膨張差によるザボー８と上面治具７の間に形成さ
れる隙間にょるサボー８の変形をなくすようにしている
。また上面治具′７の上面は甲面とねっていで、真空バ
ッグ用フィルム１１εのシール性を確保するよ・）にり
、−Ｃいる。The above-mentioned body shaping position 5 is shown in Figs. 2 to 4), and the compound part 4 follows the shape of the outer panel 2. A molding tool box 6ε, an upper surface jig 7 that also functions as a vacuum manifold, a sabot 8 that maintains the curved shape of the upper surface of the girder 3 and the small ribs 4, and a "flange" of the girder 3 and the small -1't4. An elastomer pad 9 with a constant thickness that applies uniform autoclave pressure to the surface and web surface and maintains the shape of the girders 3 and small bones 4 during hardening.
, A foil sheet that transmits uniform pressure to the outer panel 2 and prevents the auxiliary ladle material etc. from being transferred to the outer panel 2 during vacuum evacuation (ωL5)-10, and an elastomer bladder that forms an airtight bag during vacuum evacuation. The mold assembly has a vacuum bag filter 1 (5).The upper surface of the bag 8 has a shape that makes contact with the upper surface jig 7 on the ζ plane °C, and thermal expansion during curing. The deformation of the sabot 8 due to the gap formed between the sabot 8 and the top jig 7 due to the difference is eliminated.The top surface of the top jig '7 is bent with the shell surface, and the vacuum bag film 11ε It will ensure the sealing performance of -C.
一方桁３と小骨４か十字形に接ρｉする部位には、第３
図に示すように、ブラダモールド９の外側にロケータ］
２を配置する。このロケータ１２はスチールまたはカー
ボ〉繊維強化ブフスチックから形成されでいる。Ｌ記ロ
ケータ１２は、成形型用ベース６または１面治具７に固
定され、真空減圧度、オートクレーブ圧力の差異か大き
い部位に配置され、真空引き時やオートクレーブ硬化時
に桁３の変形を防止するよう作用する。On the other hand, there is a third
Locator on the outside of the bladder mold 9 as shown]
Place 2. The locator 12 is made of steel or carbon fiber reinforced buffstick. The L-marked locator 12 is fixed to the mold base 6 or one-sided jig 7, and is placed at a location where the difference in the degree of vacuum reduction and autoclave pressure is large to prevent deformation of the girder 3 during evacuation or autoclave curing. It works like this.
また桁３と小ｔｔ４か十字形に直交でなく交差接合する
部分では、庫力均−化が一層むすかしくなるので、この
ような部位につい〔も、第４図に示すように、スチール
またはカーポジ繊維強化プラスチックから形成されるロ
ゲ〜 タ゛１３ｔブラダモールドＱ（７’）外側よりＦ
ｒｉ ３と小骨４の接音部を挟め込むようにセットし、
真空引き時やオートクＬ−、−ブ硬化時に、圧力不均一
て桁３や小骨４が突形するのを防ぐようにし、でいる。In addition, it is more difficult to equalize the storage force in the parts where the girder 3 and the small tt4 are not perpendicular to each other in the cross shape but are cross-joined. Loge made from fiber reinforced plastic ~ 13t bladder mold Q (7') F from outside
Set so that the contact parts of ri 3 and small bone 4 are sandwiched,
This is done to prevent the beams 3 and small bones 4 from becoming protruding due to uneven pressure during vacuuming and hardening of the autoclave L- and -B.
この［フヶータ１３はオ−トクレーブ硬化時に動かない
よ−）に、上］ｈｌ冶具７に固定される。This holder 13 is fixed to the upper hl jig 7 so that it does not move during autoclave curing.
つぎに作用を説１１ＪＩ ｉる。Next, I will explain the action.
まず複合材多桁構造の一体成形装置の成形型用ベース６
の上面に複合ヰ４外板２を置き、この複合４イ外板２の
上にフランジを有する小ｉｔの枠と枠内に小骨を縦横に
配設しまた複合材の多桁構造体を配置し、ついて複合材
多桁構造体の下部７ランジの両端より複合材外板全体に
わたりコールシート１０を配置するとともに、複合材多
桁構造体の小骨の左右内側全体に一定板厚のバッド９を
被せる。First, base 6 for the mold of the integrated molding device with composite multi-digit structure.
A composite 4 outer panel 2 is placed on the upper surface, and on top of this composite 4 outer panel 2, a frame of a small IT having a flange and small ribs are arranged vertically and horizontally within the frame, and a multi-girder structure made of composite material is also arranged. Then, a call sheet 10 is placed over the entire composite outer panel from both ends of the lower 7 lunges of the composite multi-digit structure, and pads 9 of a constant thickness are placed on the entire left and right inner sides of the small bones of the composite multi-digit structure. Cover.
１いてこの組立て体の複合材多桁構造体の上部フランノ
、Ｉ商に、成形型σ）−Ｌ型゛Ｃある土面治具７４置き
、さらにこの」−面治具７の上に押さえ枠を置き、【、
かる後これら全体を真空バッグ用フィルム１１で覆いか
一つ小月の！、−右内側と上部°′ノフンンＦ而面剛性
「１ケータ１２て押さλ、オー、−トウ１フープにおい
て加熱、加圧、硬化処理を施ずことに」り複音ヰ４多格
構造が成形される。1 Place the molding mold σ)-L-shaped soil surface jig 74 on the upper flange and I section of the composite multi-girder structure of this assembly, and then place the holding frame on top of this surface jig 7. Place [,
After that, cover the whole thing with vacuum bag film 11 or make a small moon! , -Right inner side and upper part 〇〇 be done.
第５図ないし第６図は本発明の変形例を示し、第５図に
＞］＜ず変形例では、成形型用ベース０の変形を防１１
−７するために、成形型用べ・−ス６のｆ曲と同じ１曲
率面を有する補強紹立て体１２を成形制用ベース６にト
ｊ設しか一つ上動治具７と真空バッグ用フィル人１１０
間に粘着ナー＝ブ１３を設けることで、土１角治具７と
真空バッグ用フィルム１１８の間をシールするようにし
、て％、ｚる。5 and 6 show modified examples of the present invention. In the modified example shown in FIG.
-7, a reinforcing frame 12 having the same curvature surface as the f curve of the mold base 6 is installed on the mold base 6, and only one upper moving jig 7 and a vacuum bag are installed on the mold base 6. Phil person 110
By providing an adhesive nub 13 between them, a seal is formed between the soil one-sided jig 7 and the vacuum bag film 118.
第０図に示す変形例では、柘３および小骨４のフランジ
部１４の−１、面に門／ｇ１５を設けるとともに、す、
ｊζ−８の１・面にＬ記１１１１溝１５１．：、対ｔ；
Ｌ ｔニー ｒ！’Ｆ＋部１６を設置ｊ、これにより
二次的に満を切削加工する王程が不必要となりかつ溝イ
・１きσ）４を体部刊を組み文でる時に生じる満ダ）・
）なぎ１−１の孝ゞれがムく、また溝部分に成形Ｌトカ
か１Ｊ〜・に作用し、製品の品質の安定化を１′■る。In the modified example shown in FIG.
L marking 1111 groove 151 on the 1 side of jζ-8. :, versus t;
L t knee r! 'F+ part 16 is installed, this makes it unnecessary to perform secondary machining, and also removes the need to cut the groove A).
) The filtration of Nagi 1-1 is suppressed, and the molding L toka 1J~. in the groove portion also acts to stabilize the quality of the product.
以上述べたよ・）に本定明によれば、ファスナや接着剤
（７）使用を排除することで、構造Φ量の大幅軽減と組
み１′して王（♀σ）コスト低減を図り、また島容量の
大きいエラストマ＋４１−↓の使用を最小限にし繊維強
化プラスチックを多用づることで、オーｌ＝クレープ硬
化時の昇隣温効率が１モ］上１，２、スペック要求にχ
・ｊ応した硬化条件を満配でき、成形品の品質の安定お
よびオートクレーブの消費エネルギの低減ができる。As mentioned above, according to Sadaaki Moto, by eliminating the use of fasteners and adhesives (7), it is possible to significantly reduce the amount of structural Φ and reduce costs by combining 1' with By minimizing the use of elastomer +41-↓ with large island capacity and making extensive use of fiber-reinforced plastic, the efficiency of temperature increase during curing of crepe is 1 mo] Above 1, 2, χ to the specification requirements
・It is possible to adjust the curing conditions according to the conditions, stabilize the quality of the molded product, and reduce the energy consumption of the autoclave.
また成形品と接触する面を複曲面としその他の面を平面
とするごとて、装置０製作期間が大幅に短縮され、装置
の製造コストか下がり、しかもシル曲を平曲状とするこ
とて真空バッグブイルムによる気密性の確保ができ、軽
量で品質の向上した複雑曲面をもつ複合材多桁構造体を
成形できる。In addition, by making the surface in contact with the molded product a multi-curved surface and the other surfaces flat, the manufacturing period of the device is greatly shortened and the manufacturing cost of the device is reduced.Moreover, by making the sill curve into a flat curved shape, the vacuum Airtightness can be ensured by bag builm, and composite multi-digit structures with complex curved surfaces can be molded with light weight and improved quality.
第１図は本発明による複合材多桁構造の一体成形方法に
より成形された複合材多桁構造の斜視図、第２図は第１
図のＡ 、−、−Ａ線に沿った断面図、第３図は第１図
のＢ −Ｂ線に沿った断商図、第４図は第１−図のＣ部
分の拡大図、第５図および第６Ｍは本発明の他の変形例
を示す図である。
１・・ 複合材多桁構造１．２・・・外板２、゛づ・・
桁、４・・小月、５・・・一体成形装置、６・・成形型
用ベス、７・上ｉｄ治具、８・・−ザボ〜、９・エラス
ト・マ製ベツド、１０・・コール′ンート、１１・真空
・）ラグ用フィルム、１２・・・ロケ〜 タ。FIG. 1 is a perspective view of a composite multi-digit structure molded by the method of integrally molding a composite multi-digit structure according to the present invention, and FIG.
3 is a sectional view taken along lines A, -, and -A in the figure; Figure 3 is a sectional view taken along line B-B in Figure 1; Figure 4 is an enlarged view of part C in Figure 1; 5 and 6M are diagrams showing other modifications of the present invention. 1. Composite multi-digit structure 1.2... Outer panel 2...
Girder, 4...Kozuki, 5...Integrated molding device, 6...Best for mold, 7...Upper ID jig, 8...-Zabo~, 9...Elastoma bed, 10...Cole 11・Vacuum・）Lug film, 12...Location~ta.
Claims (1)
設した複合材の多桁構造体に、曲面を有する複合材の外
板を、加熱、加圧、硬化処理して接合する複合材多桁構
造の一体成形方法において、上記複合材外板を、この外
板の形状に倣った面を有する成形型ベースの上に置き、
この複合材外板の上に上記複合材多桁構造体を配置し、
この複合材多桁構造体の下部フランジの両端より複合材
外板全体にわたりコールシートを配置し、複合材多桁構
造体の小骨の左右内側全体に一定板厚のパッドを被せ、
複合材多桁構造体の上部フランジの上面に、上部フラン
ジの形状に倣った面を有する成形型の上型を置き、この
上型の上に押さえ枠を置き、これら全体を真空バッグ用
フィルムで覆いかつ小骨の左右内側と上部フランジ下面
を剛性ロケータで押さえ、しかる後、加熱、加圧、硬化
処理して接合する複合材多桁構造の一体成形方法。 ２、フランジを有する小骨の枠と枠内に小骨を縦横に配
設した複合材の多桁構造体に、曲面を有する複合材の外
板を接合する複合材多桁構造の一体成形装置において、
複合材外板の形状に倣った面を有する成形型用ベースと
、複合材多桁構造体の小骨の左右内側全体に被せられる
パッドと、複合材多桁構造体の小骨のフランジに被せら
れ小骨の上面を同一曲面内に位置させる上型と、上型の
上面を同一平面内に位置するように上型の上に配置され
る押さえ枠とを有する一体成形装置。[Claims] 1. A composite material multi-digit structure with a frame of ossicles having flanges and ossicles arranged vertically and horizontally within the frame, and a composite material outer plate having a curved surface being heated, pressurized, and hardened. In the integral molding method of a composite multi-digit structure that is processed and joined, the composite skin is placed on a mold base having a surface that follows the shape of the skin,
The composite multi-digit structure is placed on this composite outer panel,
A call sheet is placed over the entire composite outer panel from both ends of the lower flange of this composite multi-digit structure, and a pad of a constant thickness is placed over the entire left and right inner sides of the small bones of the composite multi-digit structure.
An upper die of a forming mold having a surface that follows the shape of the upper flange is placed on the upper surface of the upper flange of the composite multi-digit structure, a presser frame is placed on top of this upper die, and the whole is covered with a vacuum bag film. A method for integrally molding a composite multi-digit structure, covering and holding down the left and right inner sides of the ossicles and the lower surface of the upper flange with rigid locators, and then joining them by heating, pressurizing, and hardening. 2. In an integrated molding device for a composite multi-digit structure that joins a composite material outer panel having a curved surface to a composite material multi-digit structure in which a frame of small bones has flanges and small bones are arranged vertically and horizontally within the frame,
A mold base having a surface that follows the shape of the composite outer plate; a pad that covers the entire left and right inner sides of the ossicles of the composite multi-digit structure; and a pad that covers the flanges of the ossicles of the composite multi-digit structure. An integral molding device that includes an upper mold whose upper surface is located within the same curved surface, and a presser frame which is placed on the upper mold so that the upper surface of the upper mold is located within the same plane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2072662A JP2815665B2 (en) | 1990-03-22 | 1990-03-22 | Integral molding method and integral molding apparatus for composite multi-girder structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2072662A JP2815665B2 (en) | 1990-03-22 | 1990-03-22 | Integral molding method and integral molding apparatus for composite multi-girder structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH03272829A true JPH03272829A (en) | 1991-12-04 |
| JP2815665B2 JP2815665B2 (en) | 1998-10-27 |
Family
ID=13495805
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2072662A Expired - Fee Related JP2815665B2 (en) | 1990-03-22 | 1990-03-22 | Integral molding method and integral molding apparatus for composite multi-girder structure |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2815665B2 (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2004041516A1 (en) * | 2002-11-07 | 2004-05-21 | France (Qld) Pty Ltd | Vacuum form covered structural elements |
| JP2011507738A (en) * | 2007-12-28 | 2011-03-10 | エアバス オペラツィオンス ゲゼルシャフト ミット ベシュレンクテル ハフツング | Method for producing a profile from a fiber composite material |
| CN104626606A (en) * | 2015-01-04 | 2015-05-20 | 哈尔滨飞机工业集团有限责任公司 | Carbon fiber composite material forming tool |
| JP2016060112A (en) * | 2014-09-18 | 2016-04-25 | ザ・ボーイング・カンパニーＴｈｅ Ｂｏｅｉｎｇ Ｃｏｍｐａｎｙ | Fabrication of stiffened composite panel |
-
1990
- 1990-03-22 JP JP2072662A patent/JP2815665B2/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2004041516A1 (en) * | 2002-11-07 | 2004-05-21 | France (Qld) Pty Ltd | Vacuum form covered structural elements |
| JP2011507738A (en) * | 2007-12-28 | 2011-03-10 | エアバス オペラツィオンス ゲゼルシャフト ミット ベシュレンクテル ハフツング | Method for producing a profile from a fiber composite material |
| JP2016060112A (en) * | 2014-09-18 | 2016-04-25 | ザ・ボーイング・カンパニーＴｈｅ Ｂｏｅｉｎｇ Ｃｏｍｐａｎｙ | Fabrication of stiffened composite panel |
| CN104626606A (en) * | 2015-01-04 | 2015-05-20 | 哈尔滨飞机工业集团有限责任公司 | Carbon fiber composite material forming tool |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2815665B2 (en) | 1998-10-27 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP0976650A2 (en) | Composite aircraft structures and their fabrication methods | |
| CA2692990A1 (en) | A method of manufacturing an integral profile monolithic wing structure | |
| JPH02299820A (en) | Divided mandrel | |
| CN112537047B (en) | Forming and assembling method for composite material reflector | |
| JP2005059596A (en) | Method for forming stepped laminate | |
| JP2016210401A (en) | Device or method for manufacturing structure | |
| CN110480149A (en) | A kind of Ti2Four layers of hollow structure of AlNb based alloy and its manufacturing method | |
| US20120128408A1 (en) | Composite sandwich shell edge joint | |
| JP2002302097A (en) | Wing made of composite material, and manufacturing method therefor | |
| US3814653A (en) | Method of laminating structural members | |
| JPH03272829A (en) | Method and device for integral molding of composite material multi-cross-beam structure | |
| JP2007230036A (en) | Molding method of structural member using composite material and structural member using composite material | |
| JPS58205730A (en) | Forming method of composite product | |
| US10576698B2 (en) | Composite structures | |
| JPH04320826A (en) | Integral forming method of composite material | |
| JPH0517211Y2 (en) | ||
| JP2517634B2 (en) | Method of molding composite material products | |
| IT202000018139A1 (en) | PROCEDURE FOR THE MANUFACTURING OF A STRUCTURAL COMPONENT IN COMPOSITE MATERIAL STRENGTHENED WITH AT LEAST ONE BEAM | |
| GB2041861A (en) | Composite Honeycomb Core Structures and Single Stage Hot Bonding Method of Producing Such Structures | |
| JPH0429833A (en) | Molding of thermoplastic resin composite material | |
| JP4316067B2 (en) | COMPOSITE WING AND METHOD FOR MOLDING THE SAME | |
| JPH03292131A (en) | Manufacture of fiber-reinforced resin laminated body | |
| JP2740219B2 (en) | Method for manufacturing composite material structure | |
| Heier | Method of laminating structural members | |
| Royster et al. | FABRICATION AND EVALUATION OF SUPERPLASTICALLY FORMED/WELD BRAZED CORRUGATED COMPRESSION PANELS WITH BEADED WEBS |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20080814 Year of fee payment: 10 |
|
| LAPS | Cancellation because of no payment of annual fees |