JP2009501665A - 一体型自己補剛パネル - Google Patents
一体型自己補剛パネル Download PDFInfo
- Publication number
- JP2009501665A JP2009501665A JP2008521941A JP2008521941A JP2009501665A JP 2009501665 A JP2009501665 A JP 2009501665A JP 2008521941 A JP2008521941 A JP 2008521941A JP 2008521941 A JP2008521941 A JP 2008521941A JP 2009501665 A JP2009501665 A JP 2009501665A
- Authority
- JP
- Japan
- Prior art keywords
- skin
- panel
- composite panel
- wall
- coupling
- 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 claims abstract description 24
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 8
- 229910052751 metal Inorganic materials 0.000 claims description 28
- 239000002184 metal Substances 0.000 claims description 26
- 230000008878 coupling Effects 0.000 claims description 21
- 238000010168 coupling process Methods 0.000 claims description 21
- 238000005859 coupling reaction Methods 0.000 claims description 21
- 239000003351 stiffener Substances 0.000 claims description 16
- 239000011159 matrix material Substances 0.000 claims description 3
- 229920001169 thermoplastic Polymers 0.000 claims description 3
- 239000004416 thermosoftening plastic Substances 0.000 claims description 3
- 230000007704 transition Effects 0.000 claims description 2
- 230000000750 progressive effect Effects 0.000 claims 1
- 230000002787 reinforcement Effects 0.000 abstract description 6
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000010276 construction Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/16—Fairings movable in conjunction with undercarriage elements
-
- 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
- B64C1/12—Construction or attachment of skin panels
-
- 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
-
- 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
- B64C2001/0081—Fuselage structures substantially made from particular materials from metallic 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Laminated Bodies (AREA)
- Connection Of Plates (AREA)
- Securing Of Glass Panes Or The Like (AREA)
- Underground Structures, Protecting, Testing And Restoring Foundations (AREA)
- Panels For Use In Building Construction (AREA)
- Sampling And Sample Adjustment (AREA)
- Body Structure For Vehicles (AREA)
- Superstructure Of Vehicle (AREA)
- Blow-Moulding Or Thermoforming Of Plastics Or The Like (AREA)
Abstract
【解決手段】第1スキンへの固定用フランジエッジ(4a、4b)と、上面(5)と呼ばれる面と、前記フランジエッジ(4a、4b)と前記上面(5)との間の結合ウォール(6、6a、6b、6c、6d、6e、7)とを具備するハーフボックス(3)形状の内部補強フレーム(2)を構成するよう、第2スキンが中空状に形成され、第1および第2スキンは自己補剛パネルを構成し、得られたハーフボックス形状の内部補強フレームは、該フレーム(2)を構成する中空ビームの部分により画定される切り抜き部(8)を特に含む。
【選択図】図2
Description
1a 内部リム
2 内部補強フレーム
3 ボックスビーム
4a、4b フランジエッジ
5 上面
6 結合ウォール
6a〜6e 結合ウォール
7 結合ウォール
8 切り抜き部
9、10、11 結合金具要素
12 内部対金具
12a 第1側面分岐部
12b 中央分岐部
12c 第2側面分岐部
13 外部金具
14 ボルト締め
15 補強インサート
16、17 穴
Claims (11)
- 下面(1)と呼ばれるパネルの外壁を形成する第1スキンと、パネルの内壁の一部を形成する第2スキンとを含む複合パネルにおいて、第1スキンへの固定用フランジエッジ(4a、4b)と、上面(5)と呼ばれる面と、前記フランジエッジ(4a、4b)と前記上面(5)との間の結合ウォール(6、6a、6b、6c、6d、6e、7)とを具備する少なくとも1つの中空形状スティフナー(3)を形成する内部補強フレーム(2)を構成するよう、第2スキンが中空状に形成されることを特徴とする複合パネル。
- 内部補強フレームが、パネルの外周に分布する複数の中空形状スティフナーを構成することを特徴とする請求項1に記載の複合パネル。
- フレーム(2)が、ボックスビームの部分によって画定された切り抜き部(8)を含むことを特徴とする請求項1または2に記載の複合パネル。
- フレーム(2)が第2スキンのスタンピングにより作製されることを特徴とする請求項1、2または3に記載の複合パネル。
- スキンが熱可塑性マトリックス複合材料により作製されることを特徴とする請求項1から4のいずれか1項に記載の複合パネル。
- 内部対金具(12)と外部金具(13)とで作製された結合金具を有する結合金具要素(9、10、11)を含むことを特徴とする請求項1から5のいずれか1項に記載の複合パネル。
- 内部対金具(12)が、第1側面分岐部(12a)が第1スキンの内面に支承され、中央分岐部(12b)がスティフナーのウォールに支承され、第2側面分岐部(12c)が、パネルの内面を形成するスティフナーの上面の内壁に支承される、U字形の全体形状を含むことを特徴とする請求項6に記載の複合パネル。
- 外部金具(13)が、第1スキンの内面と1つの結合ウォール(6)の外面とで構成されたパネルの内部リム(1a)に押圧されることを特徴とする請求項6または7に記載の複合パネル。
- 対金具および外部金具が結合ウォールを通してボルト締め(14)として固定されることを特徴とする請求項7および8に記載の複合パネル。
- 結合金具要素(9、10、11)の受け入れゾーンに対向するフレームのビーム内に配置される補強インサート(15)を構成するよう、複数の金具同士が結合されることを特徴とする請求項6から9のいずれか1項に記載の複合パネル。
- 結合金具要素(9、10、11)の軸に対しほぼ直角な方向に向けられた少なくとも1つの結合ウォール(6、6a、6b、6c、6d、6e、7)が、空力的形状を構成するよう、外側スキンと上面との間に漸進的移行傾斜表面を構成することを特徴とする請求1から10のいずれか1項に記載の複合パネル。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0552255A FR2888816B1 (fr) | 2005-07-20 | 2005-07-20 | Panneau auto-raidi monolithique |
FR0552255 | 2005-07-20 | ||
PCT/EP2006/064154 WO2007009923A2 (fr) | 2005-07-20 | 2006-07-12 | Panneau auto-raidi monolithique |
Publications (3)
Publication Number | Publication Date |
---|---|
JP2009501665A true JP2009501665A (ja) | 2009-01-22 |
JP2009501665A5 JP2009501665A5 (ja) | 2012-02-16 |
JP5027806B2 JP5027806B2 (ja) | 2012-09-19 |
Family
ID=36121279
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2008521941A Expired - Fee Related JP5027806B2 (ja) | 2005-07-20 | 2006-07-12 | 一体型自己補剛パネル |
Country Status (11)
Country | Link |
---|---|
US (1) | US8083182B2 (ja) |
EP (1) | EP1904366B1 (ja) |
JP (1) | JP5027806B2 (ja) |
CN (1) | CN101223080B (ja) |
AT (1) | ATE452821T1 (ja) |
BR (1) | BRPI0613628A2 (ja) |
CA (1) | CA2614448C (ja) |
DE (1) | DE602006011324D1 (ja) |
FR (1) | FR2888816B1 (ja) |
RU (1) | RU2434783C2 (ja) |
WO (1) | WO2007009923A2 (ja) |
Families Citing this family (23)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7766277B2 (en) * | 2006-01-19 | 2010-08-03 | The Boeing Company | Deformable forward pressure bulkhead for an aircraft |
DE102006026168A1 (de) | 2006-06-06 | 2008-01-31 | Airbus Deutschland Gmbh | Flugzeugrumpfstruktur und Verfahren zu deren Herstellung |
DE102006026169B4 (de) * | 2006-06-06 | 2012-06-21 | Airbus Operations Gmbh | Flugzeugrumpfstruktur und Verfahren zu deren Herstellung |
DE102006026170B4 (de) * | 2006-06-06 | 2012-06-21 | Airbus Operations Gmbh | Flugzeugrumpfstruktur und Verfahren zu deren Herstellung |
US7861969B2 (en) * | 2007-05-24 | 2011-01-04 | The Boeing Company | Shaped composite stringers and methods of making |
JP5616220B2 (ja) | 2007-06-01 | 2014-10-29 | ザ トラスティーズ オブ プリンストン ユニバーシティ | 宿主細胞代謝経路の調節によるウイルス感染治療 |
US7879276B2 (en) | 2007-11-08 | 2011-02-01 | The Boeing Company | Foam stiffened hollow composite stringer |
US8540921B2 (en) | 2008-11-25 | 2013-09-24 | The Boeing Company | Method of forming a reinforced foam-filled composite stringer |
DE102009023401B4 (de) * | 2009-05-29 | 2014-06-26 | Airbus Operations Gmbh | Halter zur Befestigung einer zur Montage in einem Flugzeugrumpfelement vorgesehenen Interieurkomponente an einer Transportvorrichtung sowie Transportvorrichtung |
US8500066B2 (en) | 2009-06-12 | 2013-08-06 | The Boeing Company | Method and apparatus for wireless aircraft communications and power system using fuselage stringers |
US8570152B2 (en) | 2009-07-23 | 2013-10-29 | The Boeing Company | Method and apparatus for wireless sensing with power harvesting of a wireless signal |
US8617687B2 (en) | 2009-08-03 | 2013-12-31 | The Boeing Company | Multi-functional aircraft structures |
GB0921960D0 (en) * | 2009-12-16 | 2010-02-03 | Airbus Operations Ltd | Landing gear with noise reduction apparatus |
CN103523201B (zh) * | 2012-07-06 | 2015-12-02 | 哈尔滨飞机工业集团有限责任公司 | 直升机壁板 |
CN106995049A (zh) * | 2017-03-23 | 2017-08-01 | 西安飞机工业(集团)有限责任公司 | 一种飞机匣体结构 |
EP3403917A1 (en) * | 2017-05-18 | 2018-11-21 | BAE SYSTEMS plc | Door assembly for a vehicle |
EP3625122B1 (en) * | 2017-05-18 | 2024-08-28 | BAE Systems PLC | Door assembly for a vehicle |
EP3456624B1 (en) | 2017-09-14 | 2020-01-01 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A composite sandwich panel with a sandwich area |
GB2583751B (en) * | 2019-05-09 | 2022-02-02 | Safran Nacelles Ltd | Acoustic panel |
GB2588204B (en) | 2019-10-15 | 2022-09-14 | Safran Nacelles Ltd | Aircraft nacelle inlet |
FR3103782B1 (fr) | 2019-12-02 | 2024-03-15 | Latecoere | Porte de cabine pressurisée d’aéronef à structure formée de poutres à section évolutive |
EP4296156A1 (en) * | 2022-06-20 | 2023-12-27 | Airbus Operations GmbH | Thermoplastic cover panel for a structure in an interior space of an aircraft |
CN115384806A (zh) * | 2022-08-19 | 2022-11-25 | 大连长丰实业总公司 | 一种飞机座舱盖再制造过程的弧框开度控制方法 |
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US3995080A (en) * | 1974-10-07 | 1976-11-30 | General Dynamics Corporation | Filament reinforced structural shapes |
US4471609A (en) * | 1982-08-23 | 1984-09-18 | The Boeing Company | Apparatus and method for minimizing engine backbone bending |
JPS63108872U (ja) * | 1987-01-07 | 1988-07-13 |
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US1469220A (en) * | 1919-01-25 | 1923-10-02 | Westinghouse Electric & Mfg Co | Structural element and method of making the same |
US2258858A (en) * | 1939-03-15 | 1941-10-14 | Budd Edward G Mfg Co | Sheathing |
US3195841A (en) * | 1962-11-21 | 1965-07-20 | Gen Dynamics Corp | Double wall cellular beam structure |
US3775238A (en) * | 1971-06-24 | 1973-11-27 | J Lyman | Structural composite material |
US4749155A (en) * | 1985-09-30 | 1988-06-07 | The Boeing Company | Method of making wing box cover panel |
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DE10035334B4 (de) * | 2000-07-20 | 2007-11-29 | Eurocopter Deutschland Gmbh | Flugzeugtür und eine Außenhaut einer Flugzeugtür |
JP4526698B2 (ja) * | 2000-12-22 | 2010-08-18 | 富士重工業株式会社 | 複合材成形品及びその製造方法 |
ATE284346T1 (de) * | 2001-01-26 | 2004-12-15 | Fischer Adv Components Gmbh | Einrichtung zum verbinden beweglicher teile mit strukturbauteilen von flugzeugen od. dgl. |
JP4574086B2 (ja) * | 2001-09-03 | 2010-11-04 | 富士重工業株式会社 | 複合材翼の製造方法および複合材翼 |
US7134629B2 (en) * | 2004-04-06 | 2006-11-14 | The Boeing Company | Structural panels for use in aircraft fuselages and other structures |
WO2006024727A1 (fr) * | 2004-08-03 | 2006-03-09 | Airbus | Porte renforcee |
CA2576760C (en) * | 2004-08-03 | 2013-09-10 | Airbus | Door for closing an opening inside an aircraft |
CA2576757C (en) * | 2004-08-03 | 2013-07-02 | Airbus | Safety inside door for an aircraft |
FI118122B (fi) * | 2004-10-08 | 2007-07-13 | Patria Aerostructures Oy | Ilma-aluksen kääntyvä paneeli ja komposiittirakenteinen tukikappale |
FR2893587B1 (fr) * | 2005-11-21 | 2009-06-05 | Airbus France Sas | Case de train a structure dissociee |
US7721995B2 (en) * | 2006-12-13 | 2010-05-25 | The Boeing Company | Rib support for wing panels |
US7861969B2 (en) * | 2007-05-24 | 2011-01-04 | The Boeing Company | Shaped composite stringers and methods of making |
US7851048B2 (en) * | 2008-02-12 | 2010-12-14 | Milliken & Co. | Fiber reinforced core panel |
FR2928620B1 (fr) * | 2008-03-14 | 2012-02-03 | Latecoere | Panneau ouvrant d'aeronef, notamment une porte de cabine d'avion |
-
2005
- 2005-07-20 FR FR0552255A patent/FR2888816B1/fr not_active Expired - Fee Related
-
2006
- 2006-07-12 DE DE602006011324T patent/DE602006011324D1/de active Active
- 2006-07-12 JP JP2008521941A patent/JP5027806B2/ja not_active Expired - Fee Related
- 2006-07-12 CN CN2006800261325A patent/CN101223080B/zh not_active Expired - Fee Related
- 2006-07-12 WO PCT/EP2006/064154 patent/WO2007009923A2/fr active Application Filing
- 2006-07-12 RU RU2008106430/11A patent/RU2434783C2/ru not_active IP Right Cessation
- 2006-07-12 AT AT06777729T patent/ATE452821T1/de not_active IP Right Cessation
- 2006-07-12 US US11/996,302 patent/US8083182B2/en not_active Expired - Fee Related
- 2006-07-12 EP EP06777729A patent/EP1904366B1/fr not_active Not-in-force
- 2006-07-12 BR BRPI0613628-1A patent/BRPI0613628A2/pt not_active IP Right Cessation
- 2006-07-12 CA CA2614448A patent/CA2614448C/fr not_active Expired - Fee Related
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3995080A (en) * | 1974-10-07 | 1976-11-30 | General Dynamics Corporation | Filament reinforced structural shapes |
US4471609A (en) * | 1982-08-23 | 1984-09-18 | The Boeing Company | Apparatus and method for minimizing engine backbone bending |
JPS63108872U (ja) * | 1987-01-07 | 1988-07-13 |
Also Published As
Publication number | Publication date |
---|---|
FR2888816B1 (fr) | 2007-08-31 |
DE602006011324D1 (de) | 2010-02-04 |
WO2007009923A3 (fr) | 2007-04-26 |
FR2888816A1 (fr) | 2007-01-26 |
RU2434783C2 (ru) | 2011-11-27 |
RU2008106430A (ru) | 2009-08-27 |
WO2007009923A2 (fr) | 2007-01-25 |
CN101223080A (zh) | 2008-07-16 |
BRPI0613628A2 (pt) | 2012-11-06 |
EP1904366B1 (fr) | 2009-12-23 |
CA2614448C (fr) | 2013-12-17 |
US20090101756A1 (en) | 2009-04-23 |
ATE452821T1 (de) | 2010-01-15 |
US8083182B2 (en) | 2011-12-27 |
EP1904366A2 (fr) | 2008-04-02 |
CN101223080B (zh) | 2012-12-26 |
JP5027806B2 (ja) | 2012-09-19 |
CA2614448A1 (fr) | 2007-01-25 |
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