JP2012532785A - ストリンガ、複合構造、航空機、及びストリンガの製造方法 - Google Patents
ストリンガ、複合構造、航空機、及びストリンガの製造方法 Download PDFInfo
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- JP2012532785A JP2012532785A JP2012518931A JP2012518931A JP2012532785A JP 2012532785 A JP2012532785 A JP 2012532785A JP 2012518931 A JP2012518931 A JP 2012518931A JP 2012518931 A JP2012518931 A JP 2012518931A JP 2012532785 A JP2012532785 A JP 2012532785A
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- stringer
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- 239000002131 composite material Substances 0.000 title claims abstract description 41
- 238000000034 method Methods 0.000 title claims abstract description 11
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 8
- 230000007423 decrease Effects 0.000 claims description 15
- 238000005520 cutting process Methods 0.000 claims description 4
- 239000000945 filler Substances 0.000 claims description 4
- 238000005304 joining Methods 0.000 claims description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 2
- 230000003247 decreasing effect Effects 0.000 claims 2
- 229920005989 resin Polymers 0.000 description 5
- 239000011347 resin Substances 0.000 description 5
- 239000012779 reinforcing material Substances 0.000 description 3
- 239000000835 fiber Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 235000012149 noodles Nutrition 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical group [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000003822 epoxy resin Substances 0.000 description 1
- 239000002657 fibrous material Substances 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
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- 229920000647 polyepoxide Polymers 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Images
Classifications
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- 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
- 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
- B29C70/30—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
- B29C70/302—Details of the edges of fibre composites, e.g. edge finishing or means to avoid delamination
-
- 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
-
- 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
- Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
- Y10T156/10—Methods of surface bonding and/or assembly therefor
- Y10T156/1052—Methods of surface bonding and/or assembly therefor with cutting, punching, tearing or severing
- Y10T156/1062—Prior to assembly
-
- 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.]
- Y10T428/24479—Structurally defined web or sheet [e.g., overall dimension, etc.] including variation in thickness
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Aviation & Aerospace Engineering (AREA)
- Architecture (AREA)
- Civil Engineering (AREA)
- Structural Engineering (AREA)
- Moulding By Coating Moulds (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
Description
Claims (20)
- 長手方向の一端に終端部を有し、複合構造のプライのスタックを有する積層複合構造のストリンガであって、前記スタックの内部のプライが前記ストリンガの終端部に向けて連続的に終端されて、前記スタックの厚さが減少するテーパを提供するようにした、ストリンガ。
- フランジを有し、前記スタックのテーパは前記フランジに設けられる、請求項1に記載のストリンガ。
- 前記フランジにおける前記スタックのテーパは、長手方向及び/または横方向に設けられる、請求項2に記載のストリンガ。
- 直立ウェブを有し、前記スタックのテーパは前記ウェブに設けられる、請求項1乃至3のいずれかに記載のストリンガ。
- 前記ウェブは前記終端で分岐され、当該分岐したウェブに非構造の充填材が設けられる、請求項4に記載のストリンガ。
- 複合構造のプライを積層したほぼL字状の一対のスタックを背中合わせに結合させて形成したフランジと直立ウェブとを有する、請求項1乃至5のいずれかに記載のストリンガ。
- 前記L字状スタックの間の隙間に非構造の充填材が設けられる、請求項4に記載のストリンガ。
- 直立ウェブを有し、当該ウェブは、高さが前記終端部で減少するテーパを有する、請求項1乃至7のいずれかに記載のストリンガ。
- フランジを有し、当該フランジは、前記終端部で幅が狭くなるテーパを有する、 請求項1乃至8のいずれかに記載のストリンガ。
- フランジを有し、前記終端部の直ぐ内側のフランジの幅は、前記終端部のさらに内側のフランジの幅よりも大きい、請求項1乃至9のいずれかに記載のストリンガ。
- パネルと、当該パネルに接合される請求項1乃至11のいずれかに記載のストリンガとを有する複合構造。
- 前記スタックの厚さが減少するテーパは、前記パネルに最も近いプライから先に終端させることで達成される、請求項11に記載の複合構造。
- 前記スタックの厚さが減少するテーパは、前記パネルから最も遠いプライから先に終端させることで達成される、請求項11に記載の複合構造。
- 請求項11乃至13のいずれかに記載の複合構造を有する航空機。
- 長手方向の一端に終端部を有するとともに複合構造のプライの積層スタックを有している積層複合構造のストリンガにして、前記スタックの内部のプライは前記ストリンガの終端部に向けて連続的に終端されて、前記スタックの厚さが減少するようなテーパを提供するようにした、ストリンガの製造方法であって、
前記複合構造プライを所望の終端輪郭に切断するステップと、
前記複合構造プライを積み重ねるステップと、
を備えるストリンガの製造方法。 - 前記プライは、レーザまたはウォータージェットで切断される、請求項15に記載の方法。
- 前記個々のプライは、前記スタックに積み重ねるときに切断される、請求項15または16に記載の方法。
- 完成ストリンガにおける最大の前記プライは前記スタックに最初に載置される、請求項15乃至17のいずれかに記載の方法。
- 完成ストリンガにおける最小のプライは前記スタックに最初に載置される、請求項15乃至17のいずれかに記載の方法。
- 前記複合構造のプライのスタックを硬化するステップをさらに備えている、請求項15乃至19のいずれかに記載の方法。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GBGB0912015.5A GB0912015D0 (en) | 2009-07-10 | 2009-07-10 | Stringer |
GB0912015.5 | 2009-07-10 | ||
PCT/EP2010/059521 WO2011003844A2 (en) | 2009-07-10 | 2010-07-05 | Stringer |
Publications (1)
Publication Number | Publication Date |
---|---|
JP2012532785A true JP2012532785A (ja) | 2012-12-20 |
Family
ID=41022469
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2012518931A Pending JP2012532785A (ja) | 2009-07-10 | 2010-07-05 | ストリンガ、複合構造、航空機、及びストリンガの製造方法 |
Country Status (6)
Country | Link |
---|---|
US (1) | US20120100343A1 (ja) |
EP (1) | EP2451703B1 (ja) |
JP (1) | JP2012532785A (ja) |
CN (1) | CN102470915B (ja) |
GB (1) | GB0912015D0 (ja) |
WO (1) | WO2011003844A2 (ja) |
Cited By (11)
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JP2013227014A (ja) * | 2012-04-25 | 2013-11-07 | Boeing Co:The | 耐ディスボンド複合スチフナランアウト |
JP2014097786A (ja) * | 2012-11-13 | 2014-05-29 | Boeing Co | 複合材翼のための継手 |
JP2015036294A (ja) * | 2013-08-09 | 2015-02-23 | ザ・ボーイング・カンパニーTheBoeing Company | 航空機の本体連結部の側部 |
JP2015085627A (ja) * | 2013-10-31 | 2015-05-07 | 株式会社豊田自動織機 | 補強梁材 |
JP2015105450A (ja) * | 2013-12-02 | 2015-06-08 | 株式会社豊田自動織機 | 三次元繊維構造体及び補強材 |
JP2016534295A (ja) * | 2013-08-09 | 2016-11-04 | ザ・ボーイング・カンパニーThe Boeing Company | 補強複合材パネル |
JP2017114115A (ja) * | 2015-11-30 | 2017-06-29 | ザ・ボーイング・カンパニーThe Boeing Company | 積層された炭素繊維強化プラスチック(cfrp)ヌードルを用いた、cfrpストリンガーの終端の柔軟化 |
WO2018016050A1 (ja) * | 2016-07-21 | 2018-01-25 | 株式会社ジャムコ | Cfrp部材及びラティス構造体 |
JP2018083362A (ja) * | 2016-11-24 | 2018-05-31 | 三菱重工業株式会社 | 複合材及び複合材の成形方法 |
WO2019044161A1 (ja) * | 2017-08-30 | 2019-03-07 | 三菱重工業株式会社 | 複合材の構造体 |
JP2020055268A (ja) * | 2018-10-04 | 2020-04-09 | 三菱重工業株式会社 | 複合材を用いた構造体の製造方法 |
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GB0912015D0 (en) * | 2009-07-10 | 2009-08-19 | Airbus Operations Ltd | Stringer |
JP5455541B2 (ja) * | 2009-10-14 | 2014-03-26 | 三菱重工業株式会社 | ストリンガーの製造方法 |
ES2392236B1 (es) * | 2010-01-15 | 2013-10-09 | Airbus Operations, S.L. | Componente de aeronave con paneles rigidizados con larguerillos. |
US8940213B2 (en) | 2010-06-25 | 2015-01-27 | The Boeing Company | Resin infusion of composite parts using a perforated caul sheet |
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2009
- 2009-07-10 GB GBGB0912015.5A patent/GB0912015D0/en not_active Ceased
-
2010
- 2010-07-05 JP JP2012518931A patent/JP2012532785A/ja active Pending
- 2010-07-05 EP EP10731504.6A patent/EP2451703B1/en active Active
- 2010-07-05 US US13/380,285 patent/US20120100343A1/en not_active Abandoned
- 2010-07-05 CN CN201080030987.1A patent/CN102470915B/zh not_active Expired - Fee Related
- 2010-07-05 WO PCT/EP2010/059521 patent/WO2011003844A2/en active Application Filing
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Cited By (24)
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JP2013227014A (ja) * | 2012-04-25 | 2013-11-07 | Boeing Co:The | 耐ディスボンド複合スチフナランアウト |
JP2014097786A (ja) * | 2012-11-13 | 2014-05-29 | Boeing Co | 複合材翼のための継手 |
US10029780B2 (en) | 2013-08-09 | 2018-07-24 | The Boeing Company | Stiffened composite panels |
KR20150018364A (ko) | 2013-08-09 | 2015-02-23 | 더 보잉 컴파니 | 항공기 바디 조인트의 측면 |
JP2015036294A (ja) * | 2013-08-09 | 2015-02-23 | ザ・ボーイング・カンパニーTheBoeing Company | 航空機の本体連結部の側部 |
KR102143251B1 (ko) * | 2013-08-09 | 2020-08-11 | 더 보잉 컴파니 | 스트링거 빔 조인트 및 항공기 날개 조립체 |
JP2016534295A (ja) * | 2013-08-09 | 2016-11-04 | ザ・ボーイング・カンパニーThe Boeing Company | 補強複合材パネル |
US10717511B2 (en) | 2013-08-09 | 2020-07-21 | The Boeing Company | Aircraft side of body joint |
US10479475B2 (en) | 2013-08-09 | 2019-11-19 | The Boeing Company | Composite stringer beam joint structure of an aircraft |
JP2015085627A (ja) * | 2013-10-31 | 2015-05-07 | 株式会社豊田自動織機 | 補強梁材 |
JP2015105450A (ja) * | 2013-12-02 | 2015-06-08 | 株式会社豊田自動織機 | 三次元繊維構造体及び補強材 |
JP2017114115A (ja) * | 2015-11-30 | 2017-06-29 | ザ・ボーイング・カンパニーThe Boeing Company | 積層された炭素繊維強化プラスチック(cfrp)ヌードルを用いた、cfrpストリンガーの終端の柔軟化 |
JP6298901B1 (ja) * | 2016-07-21 | 2018-03-20 | 株式会社ジャムコ | Cfrp部材及びラティス構造体 |
WO2018016050A1 (ja) * | 2016-07-21 | 2018-01-25 | 株式会社ジャムコ | Cfrp部材及びラティス構造体 |
JP2018083362A (ja) * | 2016-11-24 | 2018-05-31 | 三菱重工業株式会社 | 複合材及び複合材の成形方法 |
WO2018096933A1 (ja) * | 2016-11-24 | 2018-05-31 | 三菱重工業株式会社 | 複合材及び複合材の成形方法 |
JP2019042934A (ja) * | 2017-08-30 | 2019-03-22 | 三菱重工業株式会社 | 複合材の構造体 |
JP7090409B2 (ja) | 2017-08-30 | 2022-06-24 | 三菱重工業株式会社 | 複合材の構造体 |
US10994513B2 (en) | 2017-08-30 | 2021-05-04 | Mitsubishi Heavy Industries, Ltd. | Composite structure |
WO2019044161A1 (ja) * | 2017-08-30 | 2019-03-07 | 三菱重工業株式会社 | 複合材の構造体 |
JP2020055268A (ja) * | 2018-10-04 | 2020-04-09 | 三菱重工業株式会社 | 複合材を用いた構造体の製造方法 |
WO2020071016A1 (ja) * | 2018-10-04 | 2020-04-09 | 三菱重工業株式会社 | 複合材を用いた構造体の製造方法 |
JP7019539B2 (ja) | 2018-10-04 | 2022-02-15 | 三菱重工業株式会社 | 複合材を用いた構造体の製造方法 |
US11298893B2 (en) | 2018-10-04 | 2022-04-12 | Mitsubishi Heavy Industries, Ltd. | Method for manufacturing structure using composite material |
Also Published As
Publication number | Publication date |
---|---|
GB0912015D0 (en) | 2009-08-19 |
CN102470915A (zh) | 2012-05-23 |
WO2011003844A2 (en) | 2011-01-13 |
CN102470915B (zh) | 2016-03-30 |
US20120100343A1 (en) | 2012-04-26 |
EP2451703B1 (en) | 2016-04-27 |
EP2451703A2 (en) | 2012-05-16 |
WO2011003844A3 (en) | 2011-06-30 |
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