JP2011251677A - 湾曲複合フレーム及び湾曲複合フレームの製造方法 - Google Patents
湾曲複合フレーム及び湾曲複合フレームの製造方法 Download PDFInfo
- Publication number
- JP2011251677A JP2011251677A JP2011104200A JP2011104200A JP2011251677A JP 2011251677 A JP2011251677 A JP 2011251677A JP 2011104200 A JP2011104200 A JP 2011104200A JP 2011104200 A JP2011104200 A JP 2011104200A JP 2011251677 A JP2011251677 A JP 2011251677A
- Authority
- JP
- Japan
- Prior art keywords
- frame
- layer
- web
- laminate
- cord
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000002131 composite material Substances 0.000 title claims abstract description 42
- 238000004519 manufacturing process Methods 0.000 title description 14
- 239000012783 reinforcing fiber Substances 0.000 claims abstract description 20
- 239000000835 fiber Substances 0.000 claims description 54
- 238000000034 method Methods 0.000 claims description 54
- 238000012545 processing Methods 0.000 claims description 14
- 229920005989 resin Polymers 0.000 claims description 6
- 239000011347 resin Substances 0.000 claims description 6
- 238000005452 bending Methods 0.000 claims description 5
- 239000011159 matrix material Substances 0.000 claims description 3
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 2
- 239000004593 Epoxy Substances 0.000 claims description 2
- 239000004917 carbon fiber Substances 0.000 claims description 2
- 229920000642 polymer Polymers 0.000 claims 1
- 239000000463 material Substances 0.000 abstract description 6
- 238000000465 moulding Methods 0.000 description 19
- 230000008569 process Effects 0.000 description 16
- 239000012528 membrane Substances 0.000 description 12
- 239000000758 substrate Substances 0.000 description 9
- 238000010586 diagram Methods 0.000 description 8
- 238000010030 laminating Methods 0.000 description 8
- 239000004812 Fluorinated ethylene propylene Substances 0.000 description 6
- 229920009441 perflouroethylene propylene Polymers 0.000 description 6
- 238000013461 design Methods 0.000 description 5
- 238000005520 cutting process Methods 0.000 description 4
- 239000003365 glass fiber Substances 0.000 description 4
- 238000012423 maintenance Methods 0.000 description 4
- 238000003475 lamination Methods 0.000 description 3
- 230000007246 mechanism Effects 0.000 description 3
- HQQADJVZYDDRJT-UHFFFAOYSA-N ethene;prop-1-ene Chemical group C=C.CC=C HQQADJVZYDDRJT-UHFFFAOYSA-N 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 238000007689 inspection Methods 0.000 description 2
- 238000003672 processing method Methods 0.000 description 2
- 229910052710 silicon Inorganic materials 0.000 description 2
- 239000010703 silicon Substances 0.000 description 2
- 229920003002 synthetic resin Polymers 0.000 description 2
- 239000000057 synthetic resin Substances 0.000 description 2
- 229920006362 Teflon® Polymers 0.000 description 1
- 238000013475 authorization Methods 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 239000003245 coal Substances 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000005034 decoration Methods 0.000 description 1
- 230000001066 destructive effect Effects 0.000 description 1
- 239000012636 effector Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000011152 fibreglass Substances 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 238000009419 refurbishment Methods 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 239000000565 sealant Substances 0.000 description 1
- 239000003351 stiffener Substances 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
- 230000037373 wrinkle formation Effects 0.000 description 1
Images
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
- 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
- B29C70/06—Fibrous reinforcements only
- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
- B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
- B29C70/20—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in a single direction, e.g. roofing or other parallel fibres
- B29C70/205—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in a single direction, e.g. roofing or other parallel fibres the structure being shaped to form a three-dimensional configuration
- B29C70/207—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in a single direction, e.g. roofing or other parallel fibres the structure being shaped to form a three-dimensional configuration arranged in parallel planes of fibres crossing at substantial angles
-
- 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
- B29C70/30—Shaping 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
- B29C70/304—In-plane lamination by juxtaposing or interleaving of plies, e.g. scarf joining
-
- 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
- B29C70/30—Shaping 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
- B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
-
- 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
- B29D99/0003—Producing profiled members, e.g. beams
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/061—Frames
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/064—Stringers; Longerons
-
- 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
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
- B29L2031/3082—Fuselages
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
-
- 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
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49616—Structural member making
- Y10T29/49622—Vehicular structural member making
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49801—Shaping fiber or fibered material
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49826—Assembling or joining
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
- Y10T428/24628—Nonplanar uniform thickness material
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Aviation & Aerospace Engineering (AREA)
- Textile Engineering (AREA)
- Robotics (AREA)
- Moulding By Coating Moulds (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
- Laminated Bodies (AREA)
Abstract
【解決手段】航空機の湾曲した複合フレーム36は、おおむねZ形状の断面を有する複数層の複合積層体を含む。少なくとも特定の積層体の層は、フレームの湾曲に沿ったほぼ全てのポイントにおいて実質的に接触している単向性強化用繊維を含む。
【選択図】図2
Description
第1及び第2端部を有するウェブと、
ウェブの第1端部の内側コードと、
ウェブの第2端部の外側コード
を含み、
ウェブ、内側コード及び外側コードは繊維強化樹脂の積層体で一体型にできており、おおむねZ及びJの内の一つの形状の断面を有する。
上述したフレームは、少なくとも特定の層がウェブ、内側コード及び外側コードを通じてほぼ連続的に延在するものであってよい。
上述したフレームは、ウェブ、内側コード及び外側コードの各々が、フレームの湾曲に実質的に接触する単向性強化用繊維を有する層を含むものであってよい。
上述したフレームは、ウェブが、ウェブを強化する層ダブラーのパッドアップ部分を含むものであってよい。
胴体の外板に固定されるように構成されているウェブ、内側コード及び外側コードを画定する断面を有し、内側及び外側コードがそれぞれウェブの反対端に位置づけされ、ウェブから反対方向に外向きに延在している、一体構造の複数層の積層体
を含む。
上述したフレームは、積層体が、実質的にZ及びJの内の一つの形状の断面を有するものであってよい。
各々単向性強化用繊維を有する複合層の積層体を作製し、これには、少なくとも特定の層を、層の強化用繊維がフレームの湾曲に沿ったほぼ全てのポイントで実質的に接触するように配置することが含まれるステップと;
湾曲ツール上の積層体を、ウェブと、ウェブの反対端でそれぞれ反対の位置に延在するコードを有する断面形状に成形するステップ
を含む。
上述した方法は、層の作製が、フレームの湾曲を画定する極座標基準系を使用して行われるものであってよい。
極座標基準系を使用してフレームの湾曲を画定するステップと;
複合積層体を作製するステップであって−
単向性繊維で強化された樹脂を含む複合材料の複数層を積層し、各層は傾斜した繊維配向性を有し、
層が積層されている間に、極座標基準系を使用して、フレームの湾曲に対して各層を配向させ、これにはコンピュータ制御の自動繊維配置機械を使用して、繊維が湾曲に沿ったほぼ全てのポイントにおいてフレームの湾曲に実質的に接触するように、ツール上に複合繊維を置くことが含まれる
ことを含むステップと;
第1、 第2及び第3ツール表面を有するツール上に積層体を配置するステップと;
ツール上の積層体を真空バッグ成形するステップであって、積層体を第1ツール表面上に引き下げて内側コードを成形し、積層体を第2表面上に引き下げて外側コードを成形し、積層体を第3表面に引き下げて、内側及び外側コードをつなぐウェブを成形することが含まれるステップと;
成形された積層体を硬化させる
ステップを含む。
ウェブ、内側コード及び外側コードを画定するほぼZ形断面を有する複数層の複合積層体であって、外側コードが外板に固定されるように構成され、ウェブの一端から上向きに横方向に延在しており、内側コードがウェブの別の端から外側コードの方向とは反対の方向に外向きに横方向に延在している複数層の複合積層体と、
フレームの湾曲を画定する極座標基準系内で配向する単向性強化用繊維を有する層を含む、各ウェブ、内側コード及び外側コード、
湾曲の全長にほぼ沿ってフレームの湾曲に実質的に接触するように配向した強化用繊維を含む、少なくとも特定の層
を含む。
32 フレーム構造物
32a バレルフレーム
32b ストリンガー
33 内側コード
34 外板
35 極座標系
36 フレーム部分、コード
37 フレーム部分36の湾曲
38 外側コード、シャータイ
39 極
40 内側コード
41 上部客室フロア
42 ウェブ
43 下部の貨物フロア
44 パッドアップ
45 スタンション
46 全体層
47 デカルト座標系
48 部分層
49 フープ方向
50 平坦な層のスタック
50a 層のスタック50の外側縁部
52 ストリンガーの切抜き部分、繊維トウが0度に配向している層
53 ストリンガーの切抜き部分
54 繊維トウが−45度に配向している層
55 セグメント
56 繊維トウが+45度に配向している層
58 AFP機械
60 ロボット
62 プリプレグ・トウ
64 コーム
70 従属ローラ
72 切断されたトウ
74 セグメント
75 ウェッジ
80 成形マンドレル
80a 成形マンドレル80の上部の平面
80b 成形マンドレル80の湾曲した又は輪郭成形された表面
82 グラスファイバーブリーザ
84 真空バッグツール
86 積層シェルフ
88 真空バッグ
90 ブリーザ
92 FEP(フッ素化エチレンプロピレン)の層
96 ドレープ成形装置
98 真空テーブル
100 レッグ
102 フレーム
106 成形/硬化マンドレル
106a 平坦な上部ツール面
106b ツール面
106c ツール面
110 ブリーザ
112 輪郭成形ブロック
118 ブリーザ
120 半径増圧器
122 内側コードの半径
123 FEPの追加層
124 ドレープ成形装置
126 上部の回転フレーム
128 下部フレーム
130 加熱真空テーブル
132 気体不浸透性膜
134 レッグ
176 C形状
178 J形状
180 L形状
182 I形状
184 変更されたJ形状
186 U形状
188 層セグメント
190 極座標系
192 中央線
196 パイ型の重なり部分
198 パイ型の隙間
201 輪郭成形された層
204 重なり部分
208 自動テープ配置機械
210 ヘッド
212 ヘッド
214 ガントリー
Claims (9)
- 航空機の湾曲した複合フレームであって:
少なくとも特定の積層体の層がフレームの湾曲に沿ったほぼすべてのポイントで実質的に接触している単向性強化用繊維を含んでいる複数層の複合積層体
を含むフレーム。 - 積層体が、一体構造の単一構造物でできており、Z及びJのうちの一つの形状の断面を有する、請求項1に記載のフレーム。
- 積層体が:
ウェブ、
ウェブと一体的に形成され、ウェブの一端から外向きに横方向に延在する内側コード、
航空機の外板に固定されるように構成されており、ウェブと一体的に形成され、ウェブの別の端から、内側コードの方向とは反対の方向に外向きに横方向に延在する外側コード
を含む、請求項1に記載のフレーム。 - 少なくとも特定の層が、ウェブ、内側コード及び外側コードを通じてフレームの湾曲方向にほぼ連続的に延在する、請求項3に記載のフレーム。
- 層が各々ポリマーマトリクスを含み、
繊維がエポキシマトリクス内部に保持されるカーボンファイバーを含む、
請求項1に記載のフレーム。 - 各層が、フレームの湾曲を画定する極座標基準系内で位置合わせされた繊維配向性を有する、請求項1に記載のフレーム。
- 航空機の胴体の、湾曲した一体構造の複合フレームを加工する方法であって:
フレームの湾曲を画定する極座標系を使用して繊維強化樹脂層の積層体を作製することであって、フレームの湾曲に実質的に接触している少なくとも特定の層の単向性強化用繊維を配向させることが含まれること、並びに
積層体をウェブ、内側コード及び外側コードを含む形状に成形すること
を含む方法。 - フレームの湾曲に実質的に接触している単向性強化用繊維を配向させることを、コンピュータで制御された自動繊維配置機械を使用して行う、請求項7に記載の方法。
- 積層体を成形することが、ツールの上で積層体の縁部を曲げることを含む、請求項7に記載の方法。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/776,781 US8349105B2 (en) | 2008-04-17 | 2010-05-10 | Curved composite frames and method of making the same |
US12/776,781 | 2010-05-10 |
Publications (1)
Publication Number | Publication Date |
---|---|
JP2011251677A true JP2011251677A (ja) | 2011-12-15 |
Family
ID=44358061
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2011104200A Pending JP2011251677A (ja) | 2010-05-10 | 2011-05-09 | 湾曲複合フレーム及び湾曲複合フレームの製造方法 |
Country Status (5)
Country | Link |
---|---|
US (2) | US8349105B2 (ja) |
EP (1) | EP2386483B1 (ja) |
JP (1) | JP2011251677A (ja) |
CN (1) | CN102241275B (ja) |
CA (1) | CA2732391C (ja) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2014019024A (ja) * | 2012-07-17 | 2014-02-03 | Fuji Heavy Ind Ltd | 複合材の成形治具及び複合材の成形方法 |
JP2015057340A (ja) * | 2013-09-16 | 2015-03-26 | ザ・ボーイング・カンパニーTheBoeing Company | 一体の貨物支柱およびc−スプライスを有する炭素繊維強化高分子貨物ビーム |
WO2021200047A1 (ja) * | 2020-03-31 | 2021-10-07 | 川崎重工業株式会社 | 航空機部品の中間生成品の製造方法および航空機部品 |
Families Citing this family (64)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9586699B1 (en) | 1999-08-16 | 2017-03-07 | Smart Drilling And Completion, Inc. | Methods and apparatus for monitoring and fixing holes in composite aircraft |
US9625361B1 (en) | 2001-08-19 | 2017-04-18 | Smart Drilling And Completion, Inc. | Methods and apparatus to prevent failures of fiber-reinforced composite materials under compressive stresses caused by fluids and gases invading microfractures in the materials |
US8632653B2 (en) | 2005-05-03 | 2014-01-21 | The Boeing Company | Method of manufacturing curved composite structural elements |
US9782951B2 (en) * | 2007-07-18 | 2017-10-10 | The Boeing Company | Composite structure having ceramic truss core and method for making the same |
US8431214B2 (en) | 2007-07-31 | 2013-04-30 | The Boeing Company | Composite structure having reinforced core and method of making same |
US8512853B2 (en) | 2007-07-31 | 2013-08-20 | The Boeing Company | Composite structure having reinforced core |
US8349105B2 (en) | 2008-04-17 | 2013-01-08 | The Boeing Company | Curved composite frames and method of making the same |
US8932423B2 (en) * | 2008-04-17 | 2015-01-13 | The Boeing Company | Method for producing contoured composite structures and structures produced thereby |
US9090028B2 (en) * | 2008-04-17 | 2015-07-28 | The Boeing Company | Method for producing contoured composite structures and structures produced thereby |
US9278484B2 (en) | 2008-04-17 | 2016-03-08 | The Boeing Company | Method and apparatus for producing contoured composite structures and structures produced thereby |
US8585856B1 (en) | 2010-05-13 | 2013-11-19 | Textron Innovations Inc. | Process for fabricating aircraft parts using an integrated form |
US9387657B2 (en) | 2010-11-12 | 2016-07-12 | The Boeing Company | Method of fabricating a curved composite structure using composite prepreg tape |
US8551380B2 (en) | 2010-11-12 | 2013-10-08 | The Boeing Company | Method of laying up prepreg plies on contoured tools using a deformable carrier film |
US9701067B2 (en) | 2010-11-12 | 2017-07-11 | The Boeing Company | Method of laying up prepreg plies on contoured tools using a deformable carrier film |
US9254907B2 (en) * | 2011-03-07 | 2016-02-09 | Ppg Industries Ohio, Inc. | Hoop load bearing aircraft transparency |
US9238338B2 (en) * | 2011-12-07 | 2016-01-19 | The Boeing Company | Method of fabricating composite laminate structures allowing ply slippage during forming |
US9545757B1 (en) | 2012-02-08 | 2017-01-17 | Textron Innovations, Inc. | Composite lay up and method of forming |
US9050757B1 (en) | 2012-02-08 | 2015-06-09 | Textron Innovations, Inc. | System and method for curing composites |
US9302455B1 (en) | 2012-02-08 | 2016-04-05 | Textron Innovations, Inc. | Fast cure process |
US9051062B1 (en) | 2012-02-08 | 2015-06-09 | Textron Innovations, Inc. | Assembly using skeleton structure |
US9649820B1 (en) | 2012-02-08 | 2017-05-16 | Textron Innovations, Inc. | Assembly using skeleton structure |
ES2432090B2 (es) | 2012-03-26 | 2015-04-27 | Airbus Operations, S.L. | Procedimiento de fabricación de piezas realizadas en material compuesto y dispositivo empleado. |
FR2991624B1 (fr) * | 2012-06-12 | 2015-03-06 | Airbus Operations Sas | Procede de realisation d'un profile courbe en materiau composite a partir d'une preforme rectiligne de nappes de fibres |
US9120276B2 (en) * | 2012-07-25 | 2015-09-01 | The Boeing Company | Laminated composite bending and stiffening members with reinforcement by inter-laminar metal sheets |
FR2993856B1 (fr) * | 2012-07-30 | 2015-09-18 | Airbus Operations Sas | Element de structure de fuselage d'aeronef a section evolutive |
US8826957B2 (en) * | 2012-08-31 | 2014-09-09 | General Electric Company | Methods and systems for automated ply layup for composites |
US9120275B2 (en) | 2012-10-30 | 2015-09-01 | The Boeing Company | Composite layer forming system |
ES2576508T3 (es) * | 2012-12-26 | 2016-07-07 | Airbus Operations S.L. | Larguerillo reforzado y su procedimiento de fabricación |
US9314974B2 (en) | 2013-01-07 | 2016-04-19 | The Boeing Company | Method and apparatus for fabricating contoured laminate structures |
US10828846B2 (en) | 2013-01-07 | 2020-11-10 | The Boeing Company | Method and apparatus for fabricating contoured laminate structures |
US9291060B2 (en) * | 2013-03-14 | 2016-03-22 | Rolls-Royce Corporation | High strength joints in ceramic matrix composite preforms |
US9573301B2 (en) | 2013-03-19 | 2017-02-21 | The Boeing Company | Methodfor reducing ply wrinkling of composite laminates during forming |
US10150233B2 (en) * | 2013-03-19 | 2018-12-11 | The Boeing Company | Method and apparatus for reducing ply wrinkling of composite laminates during forming |
FR3009273B1 (fr) * | 2013-07-30 | 2017-07-28 | Eurocopter France | Cadre en materiaux composites stratifies pour fuselage d'aeronef, comportant des zones de renfort courbes a rayon de courbure evolutif |
DE102014205479A1 (de) * | 2014-03-25 | 2015-10-01 | Bayerische Motoren Werke Aktiengesellschaft | Verfahren zur Herstellung eines Faservorformlings für ein Faserverbundbauteil |
US10399284B2 (en) | 2014-05-16 | 2019-09-03 | The Boeing Company | Method and apparatus for forming contoured composite laminates |
US9782937B1 (en) | 2014-05-16 | 2017-10-10 | The Boeing Company | Apparatus for forming contoured composite laminates |
US9464975B2 (en) * | 2014-08-13 | 2016-10-11 | The Boeing Company | Composite test specimen |
US10093406B2 (en) | 2014-12-10 | 2018-10-09 | The Boeing Company | Aircraft frame for tailstrike angle enhancement |
US10040537B2 (en) * | 2015-01-15 | 2018-08-07 | The Boeing Company | Laminate composite wing structures |
US9545759B2 (en) * | 2015-01-30 | 2017-01-17 | CGTech | Automated fiber placement with course trajectory compensation |
US10434726B1 (en) | 2015-07-13 | 2019-10-08 | The Boeing Company | Forming thermoplastic composite parts having steered fiber orientations |
US9809297B2 (en) * | 2015-08-26 | 2017-11-07 | The Boeing Company | Structures containing stiffeners having transition portions |
US10005267B1 (en) | 2015-09-22 | 2018-06-26 | Textron Innovations, Inc. | Formation of complex composite structures using laminate templates |
US9926066B2 (en) * | 2015-10-14 | 2018-03-27 | The Boeing Company | Corner tension fitting |
EP3372396A1 (en) | 2017-03-06 | 2018-09-12 | Airbus Operations, S.L. | A curved composite part and method for manufacturing thereof |
US20180327071A1 (en) * | 2017-05-10 | 2018-11-15 | The Boeing Company | Systems and methods for aircraft integrated composite frames |
US20180345604A1 (en) | 2017-06-02 | 2018-12-06 | Arris Composites Llc | Aligned fiber reinforced molding |
US20190118221A1 (en) | 2017-10-24 | 2019-04-25 | The Boeing Company | Conformal fluoropolymer coatings |
GB2571911A (en) | 2017-12-21 | 2019-09-18 | Airbus Operations Gmbh | A Stiffener for an Aircraft Assembly |
ES2948928T3 (es) * | 2018-06-19 | 2023-09-21 | Airbus Operations Slu | Procedimiento de fabricación de una caja multi-larguero con cubierta superior de revestimiento continuo de una sección de cono de cola para un extremo posterior de una aeronave y un conjunto de material compuesto |
US11014314B2 (en) | 2018-06-28 | 2021-05-25 | The Boeing Company | End effector for forming prepreg plies on highly contoured surfaces |
EP3597525B1 (en) * | 2018-07-19 | 2020-12-09 | Airbus Operations, S.L.U. | Curved composite part and manufacturing method thereof |
ES2880625T3 (es) * | 2018-09-11 | 2021-11-25 | Airbus Operations Sl | Métodos para la fabricación de larguerillos curvos en omega y larguerillos en forma de Z de material compuesto y para la fabricación de un panel rigidizado de material compuesto con curvatura |
US11001363B2 (en) * | 2018-11-08 | 2021-05-11 | The Boeing Company | Composite spar for aircraft wing |
US11180238B2 (en) * | 2018-11-19 | 2021-11-23 | The Boeing Company | Shear ties for aircraft wing |
US11305498B2 (en) | 2018-12-21 | 2022-04-19 | The Boeing Company | System and method for fabricating a composite ply layup |
US11318689B2 (en) | 2018-12-21 | 2022-05-03 | The Boeing Company | Ply transporting and compacting apparatus and method therefor |
US11745442B2 (en) | 2019-08-22 | 2023-09-05 | The Boeing Company | Highly contoured composite structures and system and method for making the same |
US11298902B2 (en) * | 2019-09-19 | 2022-04-12 | Spirit Aerosystems, Inc. | Continuous manufacturing process for composite parts |
EP4107058A4 (en) * | 2020-02-17 | 2023-11-22 | Saab Ab | CURVED AEROSPACE PROFILE ARTICLE AND METHOD FOR MANUFACTURING THE ARTICLE |
CN112356458B (zh) * | 2020-10-16 | 2023-03-31 | 中车青岛四方机车车辆股份有限公司 | 轨道车辆的部件的液体成型工艺 |
IT202000028046A1 (it) * | 2020-11-23 | 2022-05-23 | Leonardo Spa | Metodo e dispositivo per la fabbricazione di un elemento strutturale in materiale composito con profilo a z |
CN116628866B (zh) * | 2023-07-26 | 2023-10-27 | 北京航空航天大学 | 一种用于航空发动机总体结构设计的控制框架 |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2008543670A (ja) * | 2005-06-22 | 2008-12-04 | エアバス ドイッチュラント ゲゼルシャフト ミット ベシュレンクテル ハフツング | 補強ビームおよび補強ビームを製造するための方法ならびに繊維積層物 |
JP2009191092A (ja) * | 2008-02-12 | 2009-08-27 | Toray Ind Inc | Frp製部材用プリフォームおよびその製造方法並びにその方法を用いたfrp製部材の製造方法 |
Family Cites Families (75)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB763972A (en) | 1953-09-30 | 1956-12-19 | Andre Rubber Co | Improvements in or relating to flexible couplings for pipes |
US3042562A (en) * | 1959-05-04 | 1962-07-03 | Dow Chemical Co | Product and method for production of articles having compound curves |
US3259021A (en) * | 1961-05-05 | 1966-07-05 | North American Aviation Inc | Multiple purpose fabrication apparatus and method |
US3556922A (en) * | 1968-08-27 | 1971-01-19 | Du Pont | Fiber-resin composite of polyamide and inorganic fibers |
US3775219A (en) * | 1971-04-05 | 1973-11-27 | Goldsworthy Eng Inc | Composite-tape placement head |
US4133711A (en) * | 1977-07-11 | 1979-01-09 | Grumman Aerospace Corporation | Automated integrated composite lamination system |
US4208238A (en) * | 1977-07-11 | 1980-06-17 | Grumman Aerospace Corporation | Gantry for use in the manufacture of laminar structures |
US4249704A (en) * | 1978-04-25 | 1981-02-10 | Mitsubishi Denki Kabushiki Kaisha | Automatic taping apparatus |
US4305903A (en) * | 1980-02-25 | 1981-12-15 | Norris Industries, Inc. | Composite fiber reinforced member and method |
GB2101519B (en) | 1981-06-22 | 1986-03-19 | Vought Corp | Apparatus for tape laying and manufacture of composite structures |
DE3249987C2 (de) | 1981-06-22 | 1995-08-17 | Vought Aircraft Co | Vorrichtung für die Herstellung eines Formteils |
US4591402A (en) * | 1981-06-22 | 1986-05-27 | Ltv Aerospace And Defense Company | Apparatus and method for manufacturing composite structures |
GB8305749D0 (en) * | 1983-03-02 | 1983-04-07 | British Aerospace | Tape laying apparatus |
US4588466A (en) * | 1983-04-08 | 1986-05-13 | Vektronics Manufacturing, Inc. | Tape laying method and apparatus |
US4576849A (en) | 1983-06-06 | 1986-03-18 | Hercules Incorporated | Curved composite beam |
US4475976A (en) * | 1983-12-23 | 1984-10-09 | The Boeing Company | Method and apparatus for forming composite material articles |
US4726924A (en) * | 1984-06-28 | 1988-02-23 | The Boeing Company | Method of planar forming of zero degree composite tape |
US4720255A (en) * | 1984-06-28 | 1988-01-19 | The Boeing Company | Apparatus for planar forming of zero degree composite tape |
US4696707A (en) * | 1987-08-18 | 1987-09-29 | The Ingersoll Milling Machine Company | Composite tape placement apparatus with natural path generation means |
FR2590069B1 (fr) * | 1985-11-14 | 1987-12-11 | Alsthom | Enrubanneuse pour l'enrubannage a chaud d'un conducteur electrique |
US4955803A (en) * | 1986-02-03 | 1990-09-11 | The Board Of Trustees Of The Leland Stanford Junior University | Apparatus for forming fiber composite materials |
US4750965A (en) * | 1986-03-28 | 1988-06-14 | The Ingersoll Milling Machine Company | Adaptive control for tape laying head having natural path generation |
US4867834A (en) * | 1986-04-07 | 1989-09-19 | Hercules | Filament winding system |
US4847063A (en) * | 1987-12-02 | 1989-07-11 | Fiber Materials, Inc. | Hollow composite body having an axis of symmetry |
FR2635484B1 (fr) | 1988-08-18 | 1991-04-05 | Aerospatiale | Procede et dispositifs de fabrication de pieces planes incurvees en materiau composite |
US5038291A (en) * | 1989-04-03 | 1991-08-06 | General Electric Company | Computerized ply pattern generation |
US5338806A (en) | 1989-11-02 | 1994-08-16 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Tough, processable simultaneous semi-interpenetrating polyimides |
US5431984A (en) * | 1990-12-11 | 1995-07-11 | Avco Corporation | Composite preforms with groves for fibers and groves for off-gassing |
EP0496695A3 (en) | 1991-01-15 | 1993-04-21 | United Technologies Corporation | A unitary, multi-legged helicopter rotor flexbeam made solely of composite materials and the method of manufacturing same |
US5292475A (en) * | 1992-03-06 | 1994-03-08 | Northrop Corporation | Tooling and process for variability reduction of composite structures |
US5242523A (en) * | 1992-05-14 | 1993-09-07 | The Boeing Company | Caul and method for bonding and curing intricate composite structures |
US5431749A (en) * | 1993-09-30 | 1995-07-11 | The Ingersoll Milling Machine Company | Tape laying head with curved tape laying capability and improved adaptive steering |
US5538589A (en) * | 1994-08-31 | 1996-07-23 | The Boeing Company | Composite stringer assembly machine |
US5648109A (en) * | 1995-05-03 | 1997-07-15 | Massachusetts Institute Of Technology | Apparatus for diaphragm forming |
FR2766407B1 (fr) * | 1997-07-22 | 1999-10-15 | Aerospatiale | Procede de fabrication de pieces de grandes dimensions en materiau composite a matrice thermoplastique, telles que des troncons de fuselage d'aeronefs |
CA2308615A1 (en) | 1997-11-05 | 1999-05-14 | Sikorsky Aircraft Corporation | Feed control system for fiber placement machines |
GB9828368D0 (en) * | 1998-12-22 | 1999-02-17 | British Aerospace | Forming reinforcing components |
DE19909869C2 (de) | 1999-03-08 | 2001-05-10 | Daimler Chrysler Ag | Verfahren zur Herstellung eines Verkleidungsteils |
FR2808472B1 (fr) * | 2000-05-05 | 2003-02-28 | Aerospatiale Matra Airbus | Procede de fabrication d'un panneau en materiau composite a bandes raidisseurs et panneau ainsi obtenu |
US6451152B1 (en) * | 2000-05-24 | 2002-09-17 | The Boeing Company | Method for heating and controlling temperature of composite material during automated placement |
DE10031510A1 (de) * | 2000-06-28 | 2002-01-17 | Airbus Gmbh | Strukturbauteil für ein Flugzeug |
US6454893B1 (en) | 2000-08-24 | 2002-09-24 | Lockheed Martin Corporation | Method of shaping continuous fiber lamina to an undulated surface by cutting individual fibers |
CZ306276B6 (cs) * | 2000-11-21 | 2016-11-09 | Airbus Defence and Space GmbH | Konfekčně-technický způsob, napínací modul a šicí rám k vytváření textilních předforem k výrobě plastových, vlákny zesílených konstrukčních prvků |
US6723271B2 (en) * | 2001-04-16 | 2004-04-20 | W. Scott Hemphill | Method and apparatus for making composite parts |
US6648273B2 (en) * | 2001-10-30 | 2003-11-18 | The Boeing Company | Light weight and high strength fuselage |
EP1342553B1 (de) * | 2002-03-08 | 2016-05-18 | Airbus Operations GmbH | Verfahren zum Herstellen eines Fensterrahmens für Flugzeuge aus faserverstärktem Kunststoff und Vorrichtung zur Durchführung des Verfahrens |
EP1342554B1 (de) * | 2002-03-08 | 2010-02-03 | Airbus Deutschland GmbH | Verfahren zum Herstellen textiler Vorformlinge aus textilen Halbzeugen |
JP3999031B2 (ja) | 2002-04-26 | 2007-10-31 | 東京特殊電線株式会社 | 角形断面マグネットワイヤの製造方法 |
JP4309339B2 (ja) | 2002-05-29 | 2009-08-05 | ソシエテ ド テクノロジー ミシュラン | ストリップを回転表面に取り付けるための装置および方法 |
US7137182B2 (en) * | 2002-11-22 | 2006-11-21 | The Boeing Company | Parallel configuration composite material fabricator |
JP4286563B2 (ja) | 2003-03-14 | 2009-07-01 | シキボウ株式会社 | 複合材料用ドライプリフォームとその製造方法および製造装置 |
FR2853914B1 (fr) * | 2003-04-17 | 2005-11-25 | Hexcel Fabrics | Procede et installation de fabrication d'une preforme de renfort |
US7249943B2 (en) | 2003-08-01 | 2007-07-31 | Alliant Techsystems Inc. | Apparatus for forming composite stiffeners and reinforcing structures |
US7527222B2 (en) * | 2004-04-06 | 2009-05-05 | The Boeing Company | Composite barrel sections for aircraft fuselages and other structures, and methods and systems for manufacturing such barrel sections |
US7134629B2 (en) * | 2004-04-06 | 2006-11-14 | The Boeing Company | Structural panels for use in aircraft fuselages and other structures |
US7842145B2 (en) * | 2004-10-05 | 2010-11-30 | The Boeing Company | Method for laying composite tape |
EP1666353B1 (en) | 2004-12-06 | 2010-02-10 | Saab Ab | Method for fabricating a curved beam from composite material |
ES2267367B1 (es) | 2004-12-30 | 2009-05-01 | Airbus España S.L. | Procedimiento y util para el encintado de moldes de piezas curvas. |
DE602005027434D1 (de) * | 2005-02-01 | 2011-05-26 | Honda Motor Co Ltd | Verfahren zur Herstellung faserverstärkter Verbundwerkstoffen |
US7943076B1 (en) | 2005-05-03 | 2011-05-17 | The Boeing Company | Method of manufacturing curved composite structural elements |
US8632653B2 (en) | 2005-05-03 | 2014-01-21 | The Boeing Company | Method of manufacturing curved composite structural elements |
US7469735B2 (en) * | 2005-08-03 | 2008-12-30 | The Boeing Corporation | Composite structural element fabricating device and method |
ATE409577T1 (de) * | 2005-12-20 | 2008-10-15 | Saab Ab | Versteifungselement und verfahren zu dessen herstellung |
US7747421B2 (en) | 2005-12-23 | 2010-06-29 | The Boeing Company | Head assignment modeling and simulation |
WO2007074179A1 (es) * | 2005-12-29 | 2007-07-05 | Airbus España, S.L. | Procedimiento y útiles para la fabricación de cuadernas de material compuesto |
US8333858B2 (en) * | 2006-02-02 | 2012-12-18 | The Boeing Company | Method for fabricating curved thermoplastic composite parts |
JP4867917B2 (ja) | 2006-03-08 | 2012-02-01 | 東レ株式会社 | 強化繊維成形体の製造方法および製造装置 |
US8449709B2 (en) | 2007-05-25 | 2013-05-28 | The Boeing Company | Method of fabricating fiber reinforced composite structure having stepped surface |
US8916010B2 (en) * | 2007-12-07 | 2014-12-23 | The Boeing Company | Composite manufacturing method |
EP2233625B1 (en) | 2008-01-11 | 2019-03-13 | Toray Industries, Inc. | Process for producing reinforcing fiber base of curved shape |
US8932423B2 (en) | 2008-04-17 | 2015-01-13 | The Boeing Company | Method for producing contoured composite structures and structures produced thereby |
US8349105B2 (en) | 2008-04-17 | 2013-01-08 | The Boeing Company | Curved composite frames and method of making the same |
US9090028B2 (en) * | 2008-04-17 | 2015-07-28 | The Boeing Company | Method for producing contoured composite structures and structures produced thereby |
US9278484B2 (en) | 2008-04-17 | 2016-03-08 | The Boeing Company | Method and apparatus for producing contoured composite structures and structures produced thereby |
US20090301648A1 (en) * | 2008-06-05 | 2009-12-10 | Merrill Wilson Hogg | Tight constellation composite tape-laying machine |
-
2010
- 2010-05-10 US US12/776,781 patent/US8349105B2/en active Active
-
2011
- 2011-02-22 CA CA2732391A patent/CA2732391C/en active Active
- 2011-04-08 CN CN201110092546.0A patent/CN102241275B/zh active Active
- 2011-05-09 JP JP2011104200A patent/JP2011251677A/ja active Pending
- 2011-05-10 EP EP11165592.4A patent/EP2386483B1/en active Active
-
2012
- 2012-11-26 US US13/684,988 patent/US9096305B2/en active Active
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2008543670A (ja) * | 2005-06-22 | 2008-12-04 | エアバス ドイッチュラント ゲゼルシャフト ミット ベシュレンクテル ハフツング | 補強ビームおよび補強ビームを製造するための方法ならびに繊維積層物 |
JP2009191092A (ja) * | 2008-02-12 | 2009-08-27 | Toray Ind Inc | Frp製部材用プリフォームおよびその製造方法並びにその方法を用いたfrp製部材の製造方法 |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2014019024A (ja) * | 2012-07-17 | 2014-02-03 | Fuji Heavy Ind Ltd | 複合材の成形治具及び複合材の成形方法 |
JP2015057340A (ja) * | 2013-09-16 | 2015-03-26 | ザ・ボーイング・カンパニーTheBoeing Company | 一体の貨物支柱およびc−スプライスを有する炭素繊維強化高分子貨物ビーム |
WO2021200047A1 (ja) * | 2020-03-31 | 2021-10-07 | 川崎重工業株式会社 | 航空機部品の中間生成品の製造方法および航空機部品 |
Also Published As
Publication number | Publication date |
---|---|
EP2386483A3 (en) | 2017-05-03 |
EP2386483B1 (en) | 2021-10-13 |
US9096305B2 (en) | 2015-08-04 |
US20130084434A1 (en) | 2013-04-04 |
EP2386483A2 (en) | 2011-11-16 |
US20110097554A1 (en) | 2011-04-28 |
CA2732391A1 (en) | 2011-11-10 |
US8349105B2 (en) | 2013-01-08 |
CA2732391C (en) | 2015-01-27 |
CN102241275B (zh) | 2016-08-03 |
CN102241275A (zh) | 2011-11-16 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JP5628214B2 (ja) | 輪郭成形複合構造物を製造する方法 | |
JP2011251677A (ja) | 湾曲複合フレーム及び湾曲複合フレームの製造方法 | |
EP2285670B1 (en) | Method for producing contoured composite structures | |
KR102027013B1 (ko) | 형상화된 복합재 구조물을 제조하는 방법, 장치 및 그에 의해 생산된 구조물 | |
EP2433781B1 (en) | Method and apparatus for fabricating highly contoured composite stiffeners with reduced wrinkling | |
EP2436595B1 (en) | Method for manufacturing composite barrel sections for aircraft fuselages | |
EP2121288B1 (en) | Method for minimizing fiber distortion during fabrication of one-piece composite barrel section | |
KR102296770B1 (ko) | 큰 각도 천이 영역에 수지함침 토우의 배치방법 | |
US11964442B2 (en) | Forming apparatus, method, and system | |
KR20240015011A (ko) | 복합 적층 구조물의 고속 제조를 위한 방법 및 장치 |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
A621 | Written request for application examination |
Free format text: JAPANESE INTERMEDIATE CODE: A621 Effective date: 20140509 |
|
A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20150127 |
|
A977 | Report on retrieval |
Free format text: JAPANESE INTERMEDIATE CODE: A971007 Effective date: 20150129 |
|
A601 | Written request for extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A601 Effective date: 20150424 |
|
A521 | Request for written amendment filed |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20150525 |
|
A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20151020 |
|
A601 | Written request for extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A601 Effective date: 20160120 |
|
A521 | Request for written amendment filed |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20160216 |
|
A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20160712 |
|
A601 | Written request for extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A601 Effective date: 20161012 |
|
A521 | Request for written amendment filed |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20161201 |
|
A02 | Decision of refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A02 Effective date: 20170307 |