JP2007511404A - 大きな未硬化の複合積層板を移送する方法 - Google Patents
大きな未硬化の複合積層板を移送する方法 Download PDFInfo
- Publication number
- JP2007511404A JP2007511404A JP2006539567A JP2006539567A JP2007511404A JP 2007511404 A JP2007511404 A JP 2007511404A JP 2006539567 A JP2006539567 A JP 2006539567A JP 2006539567 A JP2006539567 A JP 2006539567A JP 2007511404 A JP2007511404 A JP 2007511404A
- Authority
- JP
- Japan
- Prior art keywords
- vacuum
- tool
- membrane
- layup
- zone
- 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
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
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
- B29C70/543—Fixing the position or configuration of fibrous reinforcements before or during moulding
-
- 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
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/56—Coatings, e.g. enameled or galvanised; Releasing, lubricating or separating agents
- B29C33/68—Release sheets
-
- 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
-
- 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
- B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
- B29C70/446—Moulding structures having an axis of symmetry or at least one channel, e.g. tubular structures, frames
-
- 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
- B29C37/00—Component parts, details, accessories or auxiliary operations, not covered by group B29C33/00 or B29C35/00
- B29C37/0003—Discharging moulded articles from the mould
-
- 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
- B29C53/00—Shaping by bending, folding, twisting, straightening or flattening; Apparatus therefor
- B29C53/56—Winding and joining, e.g. winding spirally
- B29C53/58—Winding and joining, e.g. winding spirally helically
- B29C53/60—Winding and joining, e.g. winding spirally helically using internal forming surfaces, e.g. mandrels
-
- 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
- B29C53/00—Shaping by bending, folding, twisting, straightening or flattening; Apparatus therefor
- B29C53/56—Winding and joining, e.g. winding spirally
- B29C53/58—Winding and joining, e.g. winding spirally helically
- B29C53/60—Winding and joining, e.g. winding spirally helically using internal forming surfaces, e.g. mandrels
- B29C53/68—Winding and joining, e.g. winding spirally helically using internal forming surfaces, e.g. mandrels with rotatable winding feed member
-
- 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
- Y10T29/49826—Assembling or joining
- Y10T29/49863—Assembling or joining with prestressing of part
- Y10T29/49867—Assembling or joining with prestressing of part of skin on frame member
-
- 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
- Y10T29/49879—Spaced wall tube or receptacle
-
- 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
- Y10T29/49895—Associating parts by use of aligning means [e.g., use of a drift pin or a "fixture"]
-
- 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
- Y10T29/49998—Work holding
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Textile Engineering (AREA)
- Moulding By Coating Moulds (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
Description
この出願は、以下の同時継続の米国特許出願、すなわち、2003年8月22日に出願された米国特許出願第10/646,509号、2003年8月22日に出願された米国特許出願第10/646,392号、2003年7月28日に出願された米国特許出願第10/630,594号、2003年8月22日に出願された米国特許出願第10/646,316号、および、2002年11月22日に出願された米国特許出願第10/301,949号に関する。
この発明は、概して、複合材料を用いて大型の構造物を製造することに関し、より特定的には、大きな航空機胴体区画の製造のために大きな未硬化の複合積層板を移送する方法に関する。
トクレーブ内部の圧力環境で実行される。外板積層板に対する圧縮力は、通常、パネルを「袋に入れる」ことによってもたらされ、この場合、プラスチック膜がパネルの上に配置され、工具に対して封止されている。次いで、封止されたプラスチック製の「袋」の内部で当該部分に真空を与えるが、この間、オートクレーブに圧力が加えられ、当該袋の外側には積層板を圧縮する差圧が生じる。この態様では、1気圧よりも高い圧縮圧力が達成され得る。パネル区画工具の内部に配置された複合材料については、パネルの空気面側は工具に接したままであり、当該パネルの非空気内面は真空バッグに面する。マンドレル工具の外側におけるバレル区画レイアップについては、バレル区画の内面が工具に接したままであり、パネルの外側の空気面は真空バッグに面する。
大きな航空宇宙用構成要素の外板を区画に切断し、レイアップ工具から未硬化の積層板を分離し、未硬化の積層区画を外側モールド線硬化工具に移送する方法、特に、積層板に皺を寄せずに移送する方法が必要とされる。マンドレル工具から積層板を確実かつ予測どおりに解放する、大きな未硬化の複合積層板の移送方法がまた必要とされる。さらに、マンドレル工具上の積層板のレイアップを妨げずにマンドレル工具から大きな未硬化の複合積層板を移送する方法が必要とされる。さらに、高速のテープレイアップに必要な機械の数を減らし、こうして、所要の工場スペースと必要とされる全体的な設備投資とを減らす、大きな未硬化の複合積層板の移送方法を含む複合材料作製プロセスが必要とされる。この発明の好ましい実施例は、航空宇宙応用例のための大型の複合材を作製するのに好適な工具およびプロセスで、これらの必要性のうちの1つまたはそれらの組合せに対処する。
プロセスのための、妨害されることのない手段をもたらさない。外板を移送するための特定の方法に有利なように、たとえば継目を円周方向に設けるかまたはレイアップを円周方向に不連続にすることによって円周方向のレイアップを妨害すると、製造効率が下がり、コストが高くなる。さらに、このような方策は外板のレイアップを妨害することとなる。たとえば、このような障害または不連続性のある付近のレイアップ面にある隆起は、当該隆起の上方において材料の橋をかけることに関する問題を引起し、当該隆起の上を通る材料送出ヘッドを邪魔する可能性がある。
おいて複合積層航空機外板を作製する方法は、複合積層航空機外板を完成したバレル区画としてレイアップするステップと、複合積層航空機外板を複数のパネルに切断するステップと、他のすべてのパネルとは個別であり当該パネルから独立しているパネルのうちの少なくとも1つをマンドレル工具のレイアップ面から空気面を有する硬化工具のうちの1つに移送するステップと、移送されたパネルを硬化するステップとを含み、ここで、当該硬化工具が、移送されたパネルの外側モールド線を規定および制御し、当該方法はさらに、移送されたパネルを硬化工具から取外すステップを含む。
状であるバレルを形成するためにマンドレル上に樹脂含浸テープを配置し、当該バレルを当該マンドレル上において少なくとも2つのパネルに切断し、当該パネルを1つずつ当該マンドレルから少なくとも1つの硬化工具に移送し、硬化された複合パネルを形成するために当該硬化工具上においてパネルを硬化し、硬化された複合パネルを当該硬化工具から取外すことによって製造される。当該硬化工具は、複合パネルの外側モールド線を規定および制御する。
以下の詳細な説明は、この発明を実施するための、現在企図されている最適の形態である。この説明は限定を意味するものと理解されるべきではなく、単にこの発明の一般原則を説明する目的でなされている。というのも、この発明の範囲は添付の特許請求の範囲によって最もよく規定されるからである。
製を容易にする。一実施例においては、この発明は、大型で(典型的には、直径または最大厚さが15フィートを上回り)、断面が一定であり、丸い形状、たとえば円形または楕円形の断面を有するマンドレルまたはレイアップ工具上での胴体区画の作製を容易にする。一実施例においては、この発明はまた、民間および軍事用の航空機の胴体構造の前部区画または後部区画などの一定の断面を持たない胴体構造などの大型部品を複合材料から作製する際に用いられてもよい。一実施例では、複合材料の完全な胴体バレル区画を積層し、当該バレル区画をサブパネルに切断し、残りのサブパネルをレイアップマンドレルに装着したままの状態で各サブパネルを連続して移送することが提供される。
ゾーンの数は、硬化させるために複合積層外板100が分離されることが望ましい部分、たとえば部分100aおよび100bなどの数に対応し得る。この数については、図1によって示される例では2つの真空ゾーンが用いられているが、たとえば3つ以上であってもよい。
触させることによって空気が閉じ込められているポケットが形成され得ないことを確実にすることである。
用いられてもよい。複合積層外板100は、所望の真空ゾーンの真空を解放するのに必要とされる場合に膜130または132などの膜に切れ目を入れることができるように十分に剥離され得る。
を含み得る。真空ポート114は、レイアップ面102を通り、図6Bに示されるマンドレル工具104の内部158に至る開口部156を含み得る。図6Bは、マンドレル工具104の内部158から見た真空ポート114を示す。真空ポート114は、開口部156に接続されたホース取付具160を含み得る。ホース162はホース取付具160に取付けられ得、そして、真空が開口部156を介してレイアップ面102に与えられ得るように真空源(図示せず)に接続され得る。
Claims (10)
- 真空膜を面(102)に封止する方法であって、
面(102)上において真空ゾーン(106)を規定するステップと、
前記真空ゾーン(106)内における面(102)の上にブリーザ(136)を配置するステップと、
前記ブリーザ(136)の上に膜(130)を配置するステップとを含み、前記膜(130)は前記真空ゾーン(106)を覆い、前記方法はさらに、
前記膜(130)と面(102)との間に真空シール(138)を形成するステップと、
前記真空シール(138)を積層板解放面(142)で覆うステップとを含む、方法。 - 前記真空ゾーン(106)を規定する前記ステップは、前記真空ゾーン(106)の境界(118)において面(102)上に両面接着テープ(134)を配置するステップを含む、請求項1に記載の方法。
- 前記ブリーザ(136)を配置する前記ステップは、前記真空ゾーン(106)内における面(102)に前記ブリーザ(136)を接着するステップを含む、請求項1または2に記載の方法。
- 前記真空シール(138)を形成する前記ステップは、前記真空ゾーン(106)の境界(118)において面(102)に接着された両面接着テープ(134)の露出された側に前記膜(130)を貼付けるステップを含む、請求項1から3のいずれかに記載の方法。
- 前記真空シール(138)を形成する前記ステップは、シールテープ(140)で前記膜(130)のエッジ(139)を覆うステップを含み、前記シールテープ(140)は前記膜(130)および面(102)に接着する、請求項1から4のいずれかに記載の方法。
- 前記真空シール(138)を覆う前記ステップは、テフロン(登録商標)テープ(143)で前記真空シール(138)を覆うステップを含む、請求項1から5のいずれかに記載の方法。
- 面(102)と前記膜(130)との間における内部空間に真空を与えるステップをさらに含む、請求項1から6のいずれかに記載の方法。
- 前記膜(130)の下と前記面(102)の上とに真空を与えることによって前記真空ゾーン(106)の上における面(102)上に前記膜(130)を保持するステップをさらに含む、請求項1から7のいずれかに記載の方法。
- 前記保持するステップは、真空ポート(114)を介してマンドレル工具(104)に前記真空を与えるステップを含む、請求項8に記載の方法。
- レイアップ面(102)上において第1の真空ゾーン(106)を規定するステップと、
レイアップ面(102)上において第2の真空ゾーン(108)を規定するステップと、
前記第1の真空ゾーン(106)内におけるレイアップ面(102)の上に第1のブリーザ(136)を配置するステップと、
前記第2の真空ゾーン(108)内におけるレイアップ面(102)の上に第2のブリーザ(136)を配置するステップと、
前記第1の真空ゾーン(106)を覆う第1の膜(130)を前記第1のブリーザ(136)の上に配置するステップと、
前記第2の真空ゾーン(108)を覆う第2の膜(132)を前記第2のブリーザ(136)の上に配置するステップと、
前記第1の膜(130)とレイアップ面(102)との間に第1の真空シール(126)を形成するステップと、
前記第2の膜(132)とレイアップ面(102)との間に第2の真空シール(128)を形成するステップと、
第1の積層板解放面(142)で前記第1の真空シール(126)を覆うステップと、
第2の積層板解放面(142)で前記第2の真空シール(128)を覆うステップとを含む、請求項1から9のいずれかに記載の、マンドレル工具(104)のレイアップ面(102)上に個々の真空ゾーンを形成する方法。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/717,030 US7228611B2 (en) | 2003-11-18 | 2003-11-18 | Method of transferring large uncured composite laminates |
PCT/US2004/036044 WO2005049304A1 (en) | 2003-11-18 | 2004-10-29 | Method of transferring large uncured composite laminates |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2007511404A true JP2007511404A (ja) | 2007-05-10 |
JP4646919B2 JP4646919B2 (ja) | 2011-03-09 |
Family
ID=34574503
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2006539567A Expired - Fee Related JP4646919B2 (ja) | 2003-11-18 | 2004-10-29 | 大きな未硬化の複合積層板を移送する方法 |
Country Status (4)
Country | Link |
---|---|
US (2) | US7228611B2 (ja) |
EP (1) | EP1691969B1 (ja) |
JP (1) | JP4646919B2 (ja) |
WO (1) | WO2005049304A1 (ja) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2009137578A (ja) * | 2007-12-07 | 2009-06-25 | Boeing Co:The | モジュラ複合製造方法 |
JP2009527401A (ja) * | 2006-02-16 | 2009-07-30 | ザ・ボーイング・カンパニー | 搬送ツール |
JP2012101787A (ja) * | 2010-11-11 | 2012-05-31 | Boeing Co:The | 多機能頂部を用いる胴体とその作製方法 |
Families Citing this family (62)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7137182B2 (en) * | 2002-11-22 | 2006-11-21 | The Boeing Company | Parallel configuration composite material fabricator |
US8336596B2 (en) * | 2002-11-22 | 2012-12-25 | The Boeing Company | Composite lamination using array of parallel material dispensing heads |
US7080441B2 (en) * | 2003-07-28 | 2006-07-25 | The Boeing Company | Composite fuselage machine and method of automated composite lay up |
US8934702B2 (en) | 2003-12-02 | 2015-01-13 | The Boeing Company | System and method for determining cumulative tow gap width |
US7289656B2 (en) * | 2003-12-02 | 2007-10-30 | The Boeing Company | Systems and methods for determining inconsistency characteristics of a composite structure |
US7134629B2 (en) * | 2004-04-06 | 2006-11-14 | The Boeing Company | Structural panels for use in aircraft fuselages and other 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 |
US7193696B2 (en) * | 2004-04-12 | 2007-03-20 | United Technologies Corporation | Systems and methods for using light to indicate defect locations on a composite structure |
US7325771B2 (en) | 2004-09-23 | 2008-02-05 | The Boeing Company | Splice joints for composite aircraft fuselages and other structures |
US7503368B2 (en) * | 2004-11-24 | 2009-03-17 | The Boeing Company | Composite sections for aircraft fuselages and other structures, and methods and systems for manufacturing such sections |
US20060108048A1 (en) | 2004-11-24 | 2006-05-25 | The Boeing Company | In-process vision detection of flaws and fod by back field illumination |
US7424902B2 (en) | 2004-11-24 | 2008-09-16 | The Boeing Company | In-process vision detection of flaw and FOD characteristics |
US7166251B2 (en) * | 2004-12-01 | 2007-01-23 | The Boeing Company | Segmented flexible barrel lay-up mandrel |
US7435947B2 (en) | 2005-10-31 | 2008-10-14 | The Boeing Company | Apparatus and methods for integrating encoding functions in material placement machines |
US7372556B2 (en) * | 2005-10-31 | 2008-05-13 | The Boeing Company | Apparatus and methods for inspecting a composite structure for inconsistencies |
JP2010507504A (ja) * | 2006-10-23 | 2010-03-11 | コンストリュクシオン・アンデュストリエル・ド・ラ・メディテラネ・セーエヌイーエム | シリンダー形状部を成型するための複合ツール |
GB0623328D0 (en) * | 2006-11-22 | 2007-01-03 | Airbus Uk Ltd | A method for forming a feature in a piece of composite material |
US7849729B2 (en) | 2006-12-22 | 2010-12-14 | The Boeing Company | Leak detection in vacuum bags |
US8388795B2 (en) | 2007-05-17 | 2013-03-05 | The Boeing Company | Nanotube-enhanced interlayers for composite structures |
US8568551B2 (en) | 2007-05-22 | 2013-10-29 | The Boeing Company | Pre-patterned layup kit and method of manufacture |
US9770871B2 (en) * | 2007-05-22 | 2017-09-26 | The Boeing Company | Method and apparatus for layup placement |
US8146231B2 (en) * | 2007-05-23 | 2012-04-03 | Cnh America Llc | Insertion tool for a rotary chopper element of an integral chopper assembly of a combine harvester |
US8333864B2 (en) | 2008-09-30 | 2012-12-18 | The Boeing Company | Compaction of prepreg plies on composite laminate structures |
US8707766B2 (en) | 2010-04-21 | 2014-04-29 | The Boeing Company | Leak detection in vacuum bags |
US8936695B2 (en) | 2007-07-28 | 2015-01-20 | The Boeing Company | Method for forming and applying composite layups having complex geometries |
US8016970B2 (en) * | 2007-08-02 | 2011-09-13 | The Boeing Company | Method for applying a pre-cured composite strip to a composite component to minimize inconsistencies appearing on a surface of the composite component |
US8042767B2 (en) | 2007-09-04 | 2011-10-25 | The Boeing Company | Composite fabric with rigid member structure |
GB0719269D0 (en) * | 2007-10-04 | 2007-11-14 | Airbus Uk Ltd | Method of moulding a charge |
US8752293B2 (en) | 2007-12-07 | 2014-06-17 | The Boeing Company | Method of fabricating structures using composite modules and structures made thereby |
US9346221B2 (en) | 2008-12-19 | 2016-05-24 | The Boeing Company | Composite stiffener positioning and vacuum bag installation |
US8454870B2 (en) * | 2008-12-19 | 2013-06-04 | The Boeing Company | Manufacturing one-piece composite sections using outer mold line tooling |
US20100186899A1 (en) * | 2009-01-15 | 2010-07-29 | Airtech International, Inc. | Thermoplastic mandrels for composite fabrication |
FR2944224A1 (fr) * | 2009-04-09 | 2010-10-15 | Mediterranee Const Ind | Outil pour le moulage d'une piece en matiere composite ayant une surface non developpable |
EP2283996A1 (en) * | 2009-08-13 | 2011-02-16 | Siemens Aktiengesellschaft | Method and arrangement to produce a wind-turbine-blade |
FR2953754B1 (fr) * | 2009-12-16 | 2018-03-02 | Airbus Operations | Outillage pour la fabrication d'un panneau en materiau composite, en particulier d'un fuselage d'aeronef |
BR112013032843B1 (pt) * | 2011-06-23 | 2020-11-03 | Hirata Corporation | aparelho de sustentação de trabalho |
US8955206B2 (en) | 2011-07-12 | 2015-02-17 | The Boeing Company | Method and apparatus for creating a layup of reinforcing fibers |
US8844108B2 (en) | 2011-07-12 | 2014-09-30 | The Boeing Company | Large area repair of composite aircraft |
US8728262B2 (en) | 2011-07-12 | 2014-05-20 | The Boeing Company | Rapid fabrication of a composite part |
US9248587B2 (en) | 2012-07-05 | 2016-02-02 | General Electric Company | Apparatus for manufacturing a flanged composite component and methods of manufacturing the same |
US8974618B1 (en) | 2012-12-04 | 2015-03-10 | The Boeing Company | Systems and methods for assembling a skin of a composite structure |
WO2014094903A1 (en) | 2012-12-21 | 2014-06-26 | Short Brothers Plc | Fabric handling apparatus |
US9314976B2 (en) | 2013-02-15 | 2016-04-19 | The Boeing Company | Systems and methods for compacting a charge of composite material |
ES2409068B1 (es) * | 2013-03-19 | 2014-04-01 | Manuel Torres Martínez | Máquina para fabricar piezas de materiales compuestos y proceso de fabricación de piezas con dicha máquina |
US9211679B1 (en) | 2013-05-03 | 2015-12-15 | The Boeing Company | Systems and methods of forming a skin for a composite structure and composite structures including the same |
US9375908B2 (en) | 2013-05-03 | 2016-06-28 | The Boeing Company | Flexible material transfer devices, flexible vacuum compaction devices, flexible vacuum chucks, and systems and methods including the same |
US9144959B1 (en) | 2013-09-04 | 2015-09-29 | The Boeing Company | Methods for assembling a skin of a composite structure |
US9511548B1 (en) | 2013-10-16 | 2016-12-06 | The Boeing Company | Systems and methods for assembling a skin of a composite structure |
US9566746B2 (en) | 2013-11-06 | 2017-02-14 | The Boeing Company | Methods and tools for forming contoured composite structures with shape memory alloy |
US9403334B1 (en) | 2013-11-18 | 2016-08-02 | The Boeing Company | Methods and tools for forming composite structures with non-planar patterns of contours |
CN105916787B (zh) | 2013-12-19 | 2018-08-28 | 肖特兄弟公司 | 织物定位装置 |
US9370922B1 (en) | 2014-03-18 | 2016-06-21 | The Boeing Company | Systems and methods for stretch-forming multi-thickness composite skins |
WO2016058975A2 (en) * | 2014-10-15 | 2016-04-21 | Media Lario | Process for forming an article with a precision surface |
US10800111B2 (en) * | 2015-06-16 | 2020-10-13 | The Boeing Company | Composite structure fabrication systems and methods |
US10926435B2 (en) | 2017-05-03 | 2021-02-23 | The Boeing Company | Foam mandrel assembly |
US11014315B2 (en) * | 2017-05-03 | 2021-05-25 | The Boeing Company | Compacted stringer packages |
US10752336B2 (en) | 2017-07-12 | 2020-08-25 | The Boeing Company | Composite support structures for composite integrated structure |
CN110891752A (zh) * | 2017-07-25 | 2020-03-17 | 株式会社斯巴鲁 | 复合材料成形夹具及复合材料成形方法 |
US11407185B2 (en) | 2017-12-18 | 2022-08-09 | The Boeing Company | Layup tools that facilitate transfer of laminates to cure tools |
US11247413B2 (en) | 2018-12-17 | 2022-02-15 | The Boeing Company | Composite parts including hybrid plies, methods of forming the composite parts, and systems for forming the composite parts |
CN110920927A (zh) * | 2019-11-06 | 2020-03-27 | 浙江大学 | 一种柔性壁板装配工装 |
US11660829B2 (en) * | 2021-02-09 | 2023-05-30 | Spirit Aerosystems, Inc. | Method of seamlessly bagging composite parts |
Citations (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3713753A (en) * | 1968-08-10 | 1973-01-30 | Messerschmitt Boelkow Blohm | Fiber reinforced plastic laminate construction of an airfoil wing type member |
US4200271A (en) * | 1977-07-11 | 1980-04-29 | Grumman Aerospace Corporation | Work table |
US4267147A (en) * | 1976-06-11 | 1981-05-12 | Messerschmit-Boelkow-Blohm GmbH | Method for producing fiber reinforced structure components |
US4475976A (en) * | 1983-12-23 | 1984-10-09 | The Boeing Company | Method and apparatus for forming composite material articles |
FR2597395A1 (fr) * | 1986-04-16 | 1987-10-23 | Man Technologie Gmbh | Procede de fabrication de pieces composites a fibres avec utilisation d'un agent de demoulage |
US5204033A (en) * | 1991-10-21 | 1993-04-20 | Brunswick Corporation | Method of fabricating a preform in a resin transfer molding process |
GB2310822A (en) * | 1996-03-07 | 1997-09-10 | Euro Projects Ltd | Moulding a structure from thermoplastics material |
WO2000018555A1 (en) * | 1998-10-01 | 2000-04-06 | Airtech International, Inc. | Method of molding or curing a resin material at high temperatures using a multilayer release film |
US6102241A (en) * | 1996-10-23 | 2000-08-15 | Palazzo; David T. | Extruded polymer tank and method of making same |
US6458309B1 (en) * | 1998-06-01 | 2002-10-01 | Rohr, Inc. | Method for fabricating an advanced composite aerostructure article having an integral co-cured fly away hollow mandrel |
US6510961B1 (en) * | 1999-04-14 | 2003-01-28 | A&P Technology | Integrally-reinforced braided tubular structure and method of producing the same |
Family Cites Families (39)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3085925A (en) * | 1957-02-20 | 1963-04-16 | Konenklijke Nl Vliegtuigenfabr | Method of forming an aircraft part having a pliable deicer boot thereon |
US3879245A (en) | 1972-06-27 | 1975-04-22 | Composite Structures Corp | Method of making composite cored structures |
US4066249A (en) * | 1977-05-11 | 1978-01-03 | Grumman Aerospace Corporation | Modular vacuum work area |
US4311661A (en) * | 1980-05-05 | 1982-01-19 | Mcdonnell Douglas Corporation | Resin impregnation process |
GB2124130B (en) * | 1982-07-24 | 1985-11-27 | Rolls Royce | Vacuum moulding fibre reinforced resin |
GB8305749D0 (en) * | 1983-03-02 | 1983-04-07 | British Aerospace | Tape laying apparatus |
DE3341564A1 (de) * | 1983-11-17 | 1985-05-30 | Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn | Gekruemmtes flaechenbauteil, insbesondere fuer luftfahrzeuge und vorrichtung zu deren herstellung |
US4657615A (en) * | 1984-08-20 | 1987-04-14 | The Boeing Company | Composite leading edge/spar member for an aircraft control surface |
US4780262A (en) | 1986-01-15 | 1988-10-25 | The Boeing Company | Method for making composite structures |
US4693678A (en) | 1986-01-15 | 1987-09-15 | The Boeing Company | Male layup-female molding system for fabricating reinforced composite structures |
US4765942A (en) * | 1986-09-30 | 1988-08-23 | The Boeing Company | Method of consolidating thermoplastic poly(amide-imide) components |
US4824631A (en) * | 1987-05-28 | 1989-04-25 | The Boeing Company | Method of manufacturing a contoured elastomeric pad |
EP0395585B1 (en) * | 1989-04-28 | 1994-07-27 | Fuji Seal Industry Co. Ltd. | Method of manufacturing labeled objects. method of manufacturing labelled containers utilizing said method, and labeling preformer apparatus for use in carrying out the method |
US5110395A (en) * | 1989-12-04 | 1992-05-05 | Cincinnati Milacron Inc. | Fiber placement head |
US5236646A (en) * | 1991-02-28 | 1993-08-17 | The United States Of America As Represented By The Secretary Of The Navy | Process for preparing thermoplastic composites |
US5116216A (en) * | 1991-02-28 | 1992-05-26 | The United States Of America As Represented By The Secretary Of The Navy | Apparatus for preparing thermoplastic composites |
US5203033A (en) * | 1991-07-25 | 1993-04-20 | Sheppard Sr David L | Camouflaged garment |
US6045651A (en) * | 1993-09-07 | 2000-04-04 | The Boeing Company | Hand assisted lamination system |
US5772950A (en) * | 1994-08-31 | 1998-06-30 | The Boeing Company | Method of vacuum forming a composite |
GB9504372D0 (en) * | 1995-03-04 | 1995-04-26 | British Aerospace | A composite laminate |
US5683646A (en) | 1995-05-10 | 1997-11-04 | Mcdonnell Douglas Corporation | Fabrication of large hollow composite structure with precisely defined outer surface |
US5651850A (en) * | 1996-01-11 | 1997-07-29 | The Boeing Company | Method of fabricating hybrid composite structures |
US5746553A (en) | 1996-04-08 | 1998-05-05 | The Boeing Company | Dual purpose lay-up tool |
US6017484A (en) * | 1997-01-21 | 2000-01-25 | Harold P. Hale | Method for manufacture of minimum porosity, wrinkle free composite parts |
WO1998050180A1 (en) | 1997-05-06 | 1998-11-12 | The Boeing Company | Hybrid lay-up tool |
US6073670A (en) * | 1997-10-31 | 2000-06-13 | Isogrid Composites, Inc. | Multiple fiber placement head arrangement for placing fibers into channels of a mold |
US5968445A (en) * | 1998-01-05 | 1999-10-19 | The Boeing Company | Method and apparatus for curing large composite panels |
US6591197B2 (en) * | 2000-05-02 | 2003-07-08 | Sikorsky Aircraft Corporation | Fiber orientation verification for a composite article |
GB0014113D0 (en) * | 2000-06-10 | 2000-08-02 | Gkn Westland Helicopters Ltd | Improvements in or relating to moulding |
US7162814B2 (en) * | 2000-11-13 | 2007-01-16 | David Berg | Shoe with interchangeable strap system |
US6743504B1 (en) * | 2001-03-01 | 2004-06-01 | Rohr, Inc. | Co-cured composite structures and method of making them |
US6627142B2 (en) * | 2001-08-01 | 2003-09-30 | Lockheed Martin Corporation | Apparatus for making composite structures and method for making same |
US6630095B2 (en) * | 2001-08-01 | 2003-10-07 | Lockheed Martin Corporation | Method for making composite structures |
US6823918B2 (en) * | 2001-12-28 | 2004-11-30 | Lockheed Martin Corporation | Integrally reinforced composite sandwich joint and process for making the same |
CA2436810C (en) * | 2002-08-08 | 2008-08-05 | Axel Siegfried Herrmann | Automated fabrication of an integral fiber reinforced composite structural component using a positioning and assembly support |
US7282107B2 (en) * | 2003-08-22 | 2007-10-16 | The Boeing Company | Multiple head automated composite laminating machine for the fabrication of large barrel section components |
US7083698B2 (en) * | 2003-08-22 | 2006-08-01 | The Boeing Company | Automated composite lay-up to an internal fuselage mandrel |
US7048024B2 (en) * | 2003-08-22 | 2006-05-23 | The Boeing Company | Unidirectional, multi-head fiber placement |
US7503368B2 (en) * | 2004-11-24 | 2009-03-17 | The Boeing Company | Composite sections for aircraft fuselages and other structures, and methods and systems for manufacturing such sections |
-
2003
- 2003-11-18 US US10/717,030 patent/US7228611B2/en not_active Expired - Fee Related
-
2004
- 2004-10-29 JP JP2006539567A patent/JP4646919B2/ja not_active Expired - Fee Related
- 2004-10-29 WO PCT/US2004/036044 patent/WO2005049304A1/en not_active Application Discontinuation
- 2004-10-29 EP EP04810121.6A patent/EP1691969B1/en active Active
-
2007
- 2007-04-02 US US11/695,561 patent/US7935289B2/en not_active Expired - Fee Related
Patent Citations (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3713753A (en) * | 1968-08-10 | 1973-01-30 | Messerschmitt Boelkow Blohm | Fiber reinforced plastic laminate construction of an airfoil wing type member |
US4267147A (en) * | 1976-06-11 | 1981-05-12 | Messerschmit-Boelkow-Blohm GmbH | Method for producing fiber reinforced structure components |
US4200271A (en) * | 1977-07-11 | 1980-04-29 | Grumman Aerospace Corporation | Work table |
US4475976A (en) * | 1983-12-23 | 1984-10-09 | The Boeing Company | Method and apparatus for forming composite material articles |
FR2597395A1 (fr) * | 1986-04-16 | 1987-10-23 | Man Technologie Gmbh | Procede de fabrication de pieces composites a fibres avec utilisation d'un agent de demoulage |
US5204033A (en) * | 1991-10-21 | 1993-04-20 | Brunswick Corporation | Method of fabricating a preform in a resin transfer molding process |
GB2310822A (en) * | 1996-03-07 | 1997-09-10 | Euro Projects Ltd | Moulding a structure from thermoplastics material |
US6102241A (en) * | 1996-10-23 | 2000-08-15 | Palazzo; David T. | Extruded polymer tank and method of making same |
US6458309B1 (en) * | 1998-06-01 | 2002-10-01 | Rohr, Inc. | Method for fabricating an advanced composite aerostructure article having an integral co-cured fly away hollow mandrel |
WO2000018555A1 (en) * | 1998-10-01 | 2000-04-06 | Airtech International, Inc. | Method of molding or curing a resin material at high temperatures using a multilayer release film |
US6510961B1 (en) * | 1999-04-14 | 2003-01-28 | A&P Technology | Integrally-reinforced braided tubular structure and method of producing the same |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2009527401A (ja) * | 2006-02-16 | 2009-07-30 | ザ・ボーイング・カンパニー | 搬送ツール |
JP2009137578A (ja) * | 2007-12-07 | 2009-06-25 | Boeing Co:The | モジュラ複合製造方法 |
JP2012101787A (ja) * | 2010-11-11 | 2012-05-31 | Boeing Co:The | 多機能頂部を用いる胴体とその作製方法 |
Also Published As
Publication number | Publication date |
---|---|
EP1691969B1 (en) | 2018-01-10 |
EP1691969A1 (en) | 2006-08-23 |
US20050102814A1 (en) | 2005-05-19 |
US7935289B2 (en) | 2011-05-03 |
US20070273067A1 (en) | 2007-11-29 |
JP4646919B2 (ja) | 2011-03-09 |
US7228611B2 (en) | 2007-06-12 |
WO2005049304A1 (en) | 2005-06-02 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JP4646919B2 (ja) | 大きな未硬化の複合積層板を移送する方法 | |
KR102027013B1 (ko) | 형상화된 복합재 구조물을 제조하는 방법, 장치 및 그에 의해 생산된 구조물 | |
US20180093752A1 (en) | System and method for fabricating a composite material assembly | |
EP2436595B1 (en) | Method for manufacturing composite barrel sections for aircraft fuselages | |
EP2452807B1 (en) | Method for minimizing fiber distortion during fabrication of one-piece composite barrel section | |
JP5628214B2 (ja) | 輪郭成形複合構造物を製造する方法 | |
EP2976212B1 (en) | Method and apparatus for reducing ply wrinkling of composite laminates during forming | |
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 | |
US11220353B2 (en) | Method of fabricating a composite structure | |
JPH04301410A (ja) | 複雑な形状の複合材製品の製造方法 | |
US10179438B2 (en) | Method and assembly for manufacturing door skin and wall with doorway | |
EP2821210B1 (en) | Vacuum bag processing of composite parts using a conformable vacuum bag assembly | |
WO1998032589A1 (en) | Method and apparatus for manufacturing composite structures | |
US11738526B2 (en) | Method for using composite tooling to manufacture composite parts | |
US20230033757A1 (en) | Method for securing core to tool during machining | |
CN116945648A (zh) | 一种大芯格带曲率蜂窝夹芯复合材料制件的成型方法 | |
JP4213443B2 (ja) | 複合材補強パネルの製造方法 | |
JP6426414B2 (ja) | 補強付き複合材料パネルの製造 |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
A621 | Written request for application examination |
Free format text: JAPANESE INTERMEDIATE CODE: A621 Effective date: 20070921 |
|
RD03 | Notification of appointment of power of attorney |
Free format text: JAPANESE INTERMEDIATE CODE: A7423 Effective date: 20091111 |
|
A521 | Request for written amendment filed |
Free format text: JAPANESE INTERMEDIATE CODE: A821 Effective date: 20100203 |
|
RD04 | Notification of resignation of power of attorney |
Free format text: JAPANESE INTERMEDIATE CODE: A7424 Effective date: 20100203 |
|
A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20100330 |
|
A601 | Written request for extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A601 Effective date: 20100628 |
|
A602 | Written permission of extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A602 Effective date: 20100705 |
|
A601 | Written request for extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A601 Effective date: 20100730 |
|
A602 | Written permission of extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A602 Effective date: 20100806 |
|
A601 | Written request for extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A601 Effective date: 20100830 |
|
A602 | Written permission of extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A602 Effective date: 20100909 |
|
A521 | Request for written amendment filed |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20100930 |
|
TRDD | Decision of grant or rejection written | ||
A01 | Written decision to grant a patent or to grant a registration (utility model) |
Free format text: JAPANESE INTERMEDIATE CODE: A01 Effective date: 20101109 |
|
A01 | Written decision to grant a patent or to grant a registration (utility model) |
Free format text: JAPANESE INTERMEDIATE CODE: A01 |
|
A61 | First payment of annual fees (during grant procedure) |
Free format text: JAPANESE INTERMEDIATE CODE: A61 Effective date: 20101207 |
|
FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20131217 Year of fee payment: 3 |
|
R150 | Certificate of patent or registration of utility model |
Ref document number: 4646919 Country of ref document: JP Free format text: JAPANESE INTERMEDIATE CODE: R150 Free format text: JAPANESE INTERMEDIATE CODE: R150 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
LAPS | Cancellation because of no payment of annual fees |