JP2000513673A - 航空機翼の組立体 - Google Patents
航空機翼の組立体Info
- Publication number
- JP2000513673A JP2000513673A JP10545284A JP54528498A JP2000513673A JP 2000513673 A JP2000513673 A JP 2000513673A JP 10545284 A JP10545284 A JP 10545284A JP 54528498 A JP54528498 A JP 54528498A JP 2000513673 A JP2000513673 A JP 2000513673A
- Authority
- JP
- Japan
- Prior art keywords
- wing
- aircraft
- lift
- aircraft wing
- section
- 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
- 239000012530 fluid Substances 0.000 claims abstract description 9
- 238000004891 communication Methods 0.000 claims abstract description 8
- 238000007789 sealing Methods 0.000 claims description 2
- 230000007480 spreading Effects 0.000 claims description 2
- 238000000034 method Methods 0.000 abstract description 7
- 238000013461 design Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 230000000712 assembly Effects 0.000 description 3
- 238000000429 assembly Methods 0.000 description 3
- 238000012546 transfer Methods 0.000 description 3
- 241000700159 Rattus Species 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 241001422033 Thestylus Species 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000001934 delay Effects 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000003032 molecular docking Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/22—Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
- B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
- B64C21/06—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for sucking
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C2230/00—Boundary layer controls
- B64C2230/04—Boundary layer controls by actively generating fluid flow
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C2230/00—Boundary layer controls
- B64C2230/22—Boundary layer controls by using a surface having multiple apertures of relatively small openings other than slots
-
- 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
- Y02T50/10—Drag 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
- 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
- Y02T50/30—Wing lift efficiency
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Toys (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Hooks, Suction Cups, And Attachment By Adhesive Means (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
Description
Claims (1)
- 【特許請求の範囲】 1.主翼部分(10)と、通常主翼部分と組合わさる収納位置とそこから前方の配置 位置との間で可動な前縁高揚力部分(12)を備えた航空機翼の組立体において、 上記の高揚力部分の、上表面(22)の少なくとも実質的な部分が通気可能であるか 孔があけられており、上記の高揚力部分に関連した吸気路(30)と流体連結し、そ れによって飛行時に、上翼面と下翼面上の少なくとも一つにおいて、乱流境界層 が翼弦方向に広がるのを、少なくとも減少させるために上記の吸気路に吸気を生 じさせることを特徴とする航空機翼の組立体。 2.露出した表面(22)上の、特定の点あるいは領域における吸気の程度を制御す る装置を備えることを特徴とする請求の範囲1に記載の航空機翼組立体。 3.上記の制御装置が、上記の高揚力部分(12)内で延びる複数のチャンバ(28)を 備えており、露出した表面(22)の通気可能であるか孔があけられた部分と、上記 の吸気路(30)と流体連結していることを特徴とする請求の範囲2に記載の航空機 翼の組立体。 4.上記の制御装置が、一つかそれ以上のオリフィス(36)または一つかそれ以上 の上記のチャンバ(28)と連結するように画定された通路手段を備え、上記のチャ ンバから出入りする流体を制御することを特徴とする、請求の範囲3に記載の航 空機翼の組立体。 5.上記のチャンバ(28)が通常翼幅方向に仲張且つ延び ていることを特徴とする請求の範囲3または4に記載の航空機翼の組立体。 6.上記の前縁高揚力部分が後縁領域(40)を備えたスラット(12)を持ち、その後 縁領域はスラットが収納位置にある場合に主翼部分と接触しているか、或いは付 近に隣接しており、さらに上記のスラットの後縁領域と、主翼部分(10)間の接合 部(41)の領域で空気を吸込んだり吸気するための通路または孔あけ手段(42)を備 えることを特徴とする請求の範囲1〜5のいずれか1つに記載の、航空機翼の組立 体。 7.上記の通路または孔が、主翼部分(10)に面したスラット(12)の表面(20)にオ リフィス(36)を含んでおり、上記のオリフィスが上記の吸気路(30)と流体連結し ていることを特徴とする請求の範囲6に記載の航空機翼の組立体。 8.上記の通路または孔が、主翼部分(10)の隣接表面と協働する上記のスラット の後縁領域(40)に通常翼幅方向に、間隔をあけて配置した複数の溝(42)を含み、 スラット(12)が収縮位置にある時に、上記の接合部(41)に複数ある吸気ポートを 画定することを特徴とする、請求の範囲7に記載の航空機翼の組立体。 9.スラット(12)が収納位置にあるとき、スラットの後表面(20)との主翼部分(10 )の間を密封するよう通常翼幅方向に延びるシール手段(44)を備えることを特徴 とする請求の範囲6〜8のいずれか1つに記載の航空機翼の組立 体。 10.上記の吸気路(30)に吸気するための一つか或いはそれ以上の吸気ポンプ装置 (50)を備えることを特徴とする請求の範囲1〜9のいずれか1つに記載の航空機翼 の組立体。 11.上記の吸気ポンプ装置(50)が上記の主翼部分(19)に位置し、上記の高揚力部 分(12)と、主翼部分と高揚力部分との間で延びる伸張可能な吸気導管装置(46)を 経由して流体連結していることを特徴とする請求の範囲10に記載の航空機翼の組 立体。 12.一つか更にそれ以上の上記の高揚力部分(12)を備え、その高揚力部分は互い に翼幅方向に配置されており、各高揚力部分が、少なくとも他の一つの高揚力部 分の吸気路(30)と流体連結している上記の吸気路(30)を備えていることを特徴と する請求の範囲1〜11のいずれか1つに記載の航空機翼の組立体。 13.隣り合う高揚力部分の間で作動する一つのシール部材を経由して上記の少な くとも一つの他の高揚力装置の吸気路(30)と流体連結することを特徴とする請求 の範囲12に記載の航空機翼の組立体。 14.請求の範囲1〜13のいずれか一つに記載の翼組立体と結合したことを特徴と する請求の範囲1〜13のいずれか一つに記載の航空機。 15.収納位置と配備位置との間で可動な主翼部分(10)に利用される高揚力装置(1 2)において、高揚力装置の上方 表面(22)の、少なくとも実質的な部分が通気可能であるか或いは孔があけられて おり且つ上記の高揚力装置における吸気路(30)と流体連結し、それによって飛行 時に、上翼面と下翼面の少なくとも一つにおいて、乱流境界層の翼弦方向の広が りを少なくとも減少させるように負の圧力差を生じさせるため吸気が行われるこ とを特徴とする前縁高揚力装置。 16.後縁領域(40)に通常の翼幅方向に間隔をあけて配置した一連の溝(42)を備え ることを特徴とする請求の範囲15に記載の前縁高揚力装置。 17.高揚力装置の上方露出表面(22)の実質的部分に通気可能であるか孔があけら れた表面を設けて、上翼面と下翼面の少なくとも一つにおいて、乱流境界層の翼 弦方向の広がりを少なくとも減少させるため上記の表面を通して吸気を行うこと を特徴とする前縁高揚力装置(12)を備えた航空機翼に関する抗力を減少させる方 法。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB9707888A GB2324351A (en) | 1997-04-18 | 1997-04-18 | Reducing drag in aircraft wing assembly |
GB9707888.5 | 1997-04-18 | ||
PCT/GB1998/001146 WO1998047761A1 (en) | 1997-04-18 | 1998-04-20 | Leading edge high lift devices with laminar flow control |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2000513673A true JP2000513673A (ja) | 2000-10-17 |
JP3320072B2 JP3320072B2 (ja) | 2002-09-03 |
Family
ID=10810995
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP54528498A Expired - Fee Related JP3320072B2 (ja) | 1997-04-18 | 1998-04-20 | 航空機翼の組立体 |
Country Status (15)
Country | Link |
---|---|
US (1) | US6135395A (ja) |
EP (1) | EP1019283B1 (ja) |
JP (1) | JP3320072B2 (ja) |
KR (1) | KR100435312B1 (ja) |
CN (1) | CN1086664C (ja) |
AU (1) | AU724415B2 (ja) |
BR (1) | BR9806725A (ja) |
CA (1) | CA2276438A1 (ja) |
DE (1) | DE69801589T2 (ja) |
EA (1) | EA000814B1 (ja) |
ES (1) | ES2159947T3 (ja) |
GB (1) | GB2324351A (ja) |
MY (1) | MY115402A (ja) |
TW (1) | TW408077B (ja) |
WO (1) | WO1998047761A1 (ja) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2007518626A (ja) * | 2004-01-22 | 2007-07-12 | ソナカ・ソシエテ・アノニム | 航空機のエアロフォイルの主翼用の可動前縁フラップ及びそのような可動前縁フラップを設けた主翼 |
JP2009504511A (ja) * | 2005-08-09 | 2009-02-05 | ザ・ボーイング・カンパニー | 揚力増大システムおよび関連する方法 |
JP2015038377A (ja) * | 2013-08-15 | 2015-02-26 | ロッキード・マーチン・コーポレーション | エーロフォイル用能動抽気 |
Families Citing this family (51)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2324351A (en) * | 1997-04-18 | 1998-10-21 | British Aerospace | Reducing drag in aircraft wing assembly |
DE10019185C2 (de) * | 2000-04-17 | 2003-06-05 | Airbus Gmbh | Anordnung zur aerodynamischen Lärmminderung von Vorflügeln eines Verkehrsflugzeuges |
DE10019187C1 (de) * | 2000-04-17 | 2002-01-03 | Airbus Gmbh | Drucksteuerung für einen Verdrängungskörper |
BE1014570A4 (fr) | 2002-01-11 | 2004-01-13 | Sonaca Sa | Procede de fabrication d'une structure cannelee et structure obtenue par ce procede. |
US6805325B1 (en) | 2003-04-03 | 2004-10-19 | Rockwell Scientific Licensing, Llc. | Surface plasma discharge for controlling leading edge contamination and crossflow instabilities for laminar flow |
US6899302B1 (en) * | 2003-12-12 | 2005-05-31 | The Boeing Company | Method and device for altering the separation characteristics of flow over an aerodynamic surface via hybrid intermittent blowing and suction |
BE1016117A3 (fr) * | 2004-07-09 | 2006-03-07 | Sonaca Sa | Volet mobile de bord d'attaque d'une aile principale de la voilure d'un aeronef. |
US7255309B2 (en) * | 2004-07-14 | 2007-08-14 | The Boeing Company | Vernier active flow control effector |
US20060102801A1 (en) * | 2004-11-01 | 2006-05-18 | The Boeing Company | High-lift distributed active flow control system and method |
US7635107B2 (en) * | 2005-08-09 | 2009-12-22 | The Boeing Company | System for aerodynamic flows and associated method |
FR2896228B1 (fr) * | 2006-01-16 | 2008-02-15 | Airbus France Sas | Procede de degivrage du bord d'attaque d'une surface aerodynamique et aeronef mettant en oeuvre un tel procede. |
ES2315108B1 (es) * | 2006-06-30 | 2010-01-12 | Aibus España, S.L. | Sistema de fijacion de un borde de ataque a la estructura de un plano sustentador de un avion. |
US8016245B2 (en) * | 2006-10-18 | 2011-09-13 | The Boeing Company | Dynamic bumps for drag reduction at transonic-supersonic speeds |
US7748958B2 (en) * | 2006-12-13 | 2010-07-06 | The Boeing Company | Vortex generators on rotor blades to delay an onset of large oscillatory pitching moments and increase maximum lift |
EP2242685B2 (en) | 2008-02-12 | 2019-01-23 | Bombardier Inc. | Improved slat configuration for fixed-wing aircraft |
DE102008017574A1 (de) * | 2008-04-07 | 2009-10-15 | Airbus Deutschland Gmbh | Strömungskörper und Hochauftriebssystem mit einem solchen Strömungskörper |
CA2716169C (en) * | 2008-05-09 | 2013-12-17 | The Boeing Company | Aircraft fillet fairings with fixed and moveable portions, and associated systems and methods |
DE102008050544A1 (de) | 2008-10-06 | 2010-04-29 | Airbus Deutschland Gmbh | An der Tragfläche eines Flugzeugs angeordneter Vorflügel |
ES2689399T3 (es) * | 2010-04-12 | 2018-11-13 | Airbus Operations Gmbh | Sección de placas perfiladas para su empleo como pared exterior de un cuerpo aerodinámico, así como componente de cuerpo dinámico con un dispositivo de aspiración de fluidos |
CN102009744A (zh) * | 2010-07-01 | 2011-04-13 | 北京航空航天大学 | 飞机操纵舵面流动分离的吹/吸气控制方法 |
DE102010026162A1 (de) | 2010-07-06 | 2012-01-12 | Airbus Operations Gmbh | Flugzeug mit Tragflügeln und einem System zur Minimierung des Einflusses von instationären Anströmzuständen |
DE102010063769B4 (de) | 2010-12-21 | 2018-05-03 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Aerodynamikbauteil |
DE102011018907A1 (de) * | 2011-04-28 | 2012-10-31 | Airbus Operations Gmbh | Hochauftriebskomponente für ein Flugzeug, Hochauftriebssystem, Verfahren zum Beeinflussen der Hochauftriebseigenschaften eines Flugzeugs und Flugzeug |
CN103253366A (zh) * | 2012-02-15 | 2013-08-21 | 北京航空航天大学 | 一种新型的基于气动力和直接力的复合控制舵面 |
WO2013172914A2 (en) * | 2012-02-27 | 2013-11-21 | Sinhatech | Self adjusting deturbulator enhanced flap and wind deflector |
EP2644497B1 (en) * | 2012-03-29 | 2016-01-20 | Airbus Operations GmbH | Wing for an aircraft, aircraft and method for reducing aerodynamic drag and improving maximum lift |
EP2644496B1 (en) * | 2012-03-29 | 2015-07-01 | Airbus Operations GmbH | Surface element for an aircraft, aircraft and method for improving high-lift generation on a surface element |
US9505485B2 (en) * | 2012-05-08 | 2016-11-29 | Lockheed Martin Corporation | Vortex generation |
GB2504744B (en) | 2012-08-08 | 2014-06-25 | Eads Uk Ltd | Aircraft wing with slat arrangement establishing laminar boundary layer flow |
US9701399B1 (en) | 2013-03-18 | 2017-07-11 | Techdyne Llc | Parasitic drag induced boundary layer reduction system and method |
US9487288B2 (en) * | 2013-06-04 | 2016-11-08 | The Boeing Company | Apparatus and methods for extending hybrid laminar flow control |
US10251400B2 (en) | 2014-05-23 | 2019-04-09 | Basf Se | Mixtures comprising a Bacillus strain and a pesticide |
EP3159259B1 (en) * | 2015-10-20 | 2019-02-20 | Airbus Operations, S.L. | Leading edge with laminar flow control and manufacturing method thereof |
EP3192736B1 (en) * | 2016-01-12 | 2018-07-11 | Airbus Operations, S.L. | A leading edge with laminar flow control and manufacturing method thereof |
US10099771B2 (en) * | 2016-03-14 | 2018-10-16 | The Boeing Company | Aircraft wing structure and associated method for addressing lift and drag |
DE102016121507B4 (de) | 2016-11-10 | 2020-07-02 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Tragflügel mit droop nose und hybrider laminisierung der strömung durch absaugung sowie verkehrsflugzeug mit einem paar solcher tragflügel |
GB2557341A (en) | 2016-12-07 | 2018-06-20 | Airbus Operations Ltd | Aircraft wing assembly |
GB2561880A (en) | 2017-04-27 | 2018-10-31 | Airbus Operations Ltd | Aerodynamic body |
EP3428062A1 (en) | 2017-07-11 | 2019-01-16 | Airbus Operations GmbH | A leading edge structure for a flow control system of an aircraft |
EP3466811B1 (en) | 2017-10-09 | 2023-06-21 | Airbus Operations GmbH | Vertical tail unit for flow control |
ES2927476T3 (es) | 2017-10-09 | 2022-11-07 | Airbus Operations Gmbh | Unidad de cola vertical para control de flujo |
GB2567683A (en) | 2017-10-20 | 2019-04-24 | Airbus Operations Ltd | Apparatus for laminar flow control |
ES2943266T3 (es) | 2017-12-28 | 2023-06-12 | Airbus Operations Gmbh | Estructura de borde de ataque para un sistema de control de flujo de una aeronave |
EP3702263A1 (en) * | 2019-02-28 | 2020-09-02 | Airbus Operations GmbH | Aircraft structure for flow control |
FR3094342B1 (fr) | 2019-04-01 | 2021-04-23 | Airbus Operations Sas | Structure aérodynamique d’écoulement laminaire. |
GB2588762A (en) * | 2019-10-31 | 2021-05-12 | Airbus Operations Ltd | Leading edge flap |
FR3103175A1 (fr) * | 2019-11-18 | 2021-05-21 | Airbus | Élément aérodynamique, en particulier pour aéronef, comportant deux pièces aérodynamiques formant une jonction de profil ascendant. |
CN114476020B (zh) * | 2021-12-20 | 2024-01-16 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | 一种机翼用增升装置及飞机 |
CN114379769B (zh) * | 2022-01-20 | 2024-06-28 | 中国商用飞机有限责任公司 | 缝翼支撑限位装置 |
EP4303123A1 (en) * | 2022-07-07 | 2024-01-10 | Airbus Operations GmbH | Wing for an aircraft |
CN117818871B (zh) * | 2024-03-04 | 2024-05-17 | 中国空气动力研究与发展中心高速空气动力研究所 | 被动式混合层流短舱应用方法 |
Family Cites Families (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1917428A (en) * | 1927-12-17 | 1933-07-11 | Uppercu Burnelli Corp | Aircraft |
US1829616A (en) * | 1929-03-28 | 1931-10-27 | Edward A Stalker | Airplane |
GB675994A (en) * | 1947-07-31 | 1952-07-23 | Onera (Off Nat Aerospatiale) | Improvements in or relating to aircraft wings |
GB998895A (en) * | 1960-08-04 | 1965-07-21 | Dehavilland Aircraft | Improvements relating to aircraft |
GB1164353A (en) * | 1966-07-01 | 1969-09-17 | Hermann Papst | Improvements in Bodies for Immersion in Fluid Streams. |
DE1781303A1 (de) * | 1968-09-25 | 1970-12-03 | Hamburger Flugzeugbau Gmbh | Luftfahrzeug mit Absaug- und Ausblaseinrichtung |
US3917193A (en) * | 1974-01-21 | 1975-11-04 | Boeing Co | Boundary layer control and anti-icing apparatus for an aircraft wing |
US4285482A (en) * | 1979-08-10 | 1981-08-25 | The Boeing Company | Wing leading edge high lift device |
US4398688A (en) * | 1979-12-26 | 1983-08-16 | Lockheed Corporation | Leading edge flap for an airfoil |
US4813631A (en) * | 1982-09-13 | 1989-03-21 | The Boeing Company | Laminar flow control airfoil |
US4575030A (en) * | 1982-09-13 | 1986-03-11 | The Boeing Company | Laminar flow control airfoil |
US4993663A (en) * | 1989-06-01 | 1991-02-19 | General Electric Company | Hybrid laminar flow nacelle |
US5263667A (en) * | 1991-09-09 | 1993-11-23 | The Boeing Company | Perforated wing panel with variable porosity |
US5348256A (en) * | 1992-05-13 | 1994-09-20 | The Boeing Company | Supersonic aircraft and method |
AU5923096A (en) * | 1995-05-19 | 1996-11-29 | Mcdonnell Douglas Corporation | Airfoil lift management device |
US5772156A (en) * | 1995-11-30 | 1998-06-30 | The Boeing Company | Aircraft boundary layer control system with discharge transpiration panel |
US5927656A (en) * | 1996-06-26 | 1999-07-27 | The Boeing Company | Wing leading edge flap and method therefor |
GB2324351A (en) * | 1997-04-18 | 1998-10-21 | British Aerospace | Reducing drag in aircraft wing assembly |
-
1997
- 1997-04-18 GB GB9707888A patent/GB2324351A/en not_active Withdrawn
-
1998
- 1998-04-18 TW TW087105959A patent/TW408077B/zh not_active IP Right Cessation
- 1998-04-18 MY MYPI98001743A patent/MY115402A/en unknown
- 1998-04-20 EA EA199900555A patent/EA000814B1/ru not_active IP Right Cessation
- 1998-04-20 EP EP98917413A patent/EP1019283B1/en not_active Expired - Lifetime
- 1998-04-20 DE DE69801589T patent/DE69801589T2/de not_active Expired - Lifetime
- 1998-04-20 ES ES98917413T patent/ES2159947T3/es not_active Expired - Lifetime
- 1998-04-20 KR KR10-1999-7006020A patent/KR100435312B1/ko not_active IP Right Cessation
- 1998-04-20 WO PCT/GB1998/001146 patent/WO1998047761A1/en active IP Right Grant
- 1998-04-20 JP JP54528498A patent/JP3320072B2/ja not_active Expired - Fee Related
- 1998-04-20 CN CN98801639A patent/CN1086664C/zh not_active Expired - Fee Related
- 1998-04-20 CA CA002276438A patent/CA2276438A1/en not_active Abandoned
- 1998-04-20 BR BR9806725-7A patent/BR9806725A/pt not_active IP Right Cessation
- 1998-04-20 AU AU70646/98A patent/AU724415B2/en not_active Ceased
-
1999
- 1999-07-08 US US09/349,453 patent/US6135395A/en not_active Expired - Lifetime
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2007518626A (ja) * | 2004-01-22 | 2007-07-12 | ソナカ・ソシエテ・アノニム | 航空機のエアロフォイルの主翼用の可動前縁フラップ及びそのような可動前縁フラップを設けた主翼 |
JP2009504511A (ja) * | 2005-08-09 | 2009-02-05 | ザ・ボーイング・カンパニー | 揚力増大システムおよび関連する方法 |
JP2013216316A (ja) * | 2005-08-09 | 2013-10-24 | Boeing Co:The | 揚力増大システムおよび関連する方法 |
JP2015038377A (ja) * | 2013-08-15 | 2015-02-26 | ロッキード・マーチン・コーポレーション | エーロフォイル用能動抽気 |
Also Published As
Publication number | Publication date |
---|---|
EA000814B1 (ru) | 2000-04-24 |
TW408077B (en) | 2000-10-11 |
DE69801589D1 (de) | 2001-10-11 |
AU7064698A (en) | 1998-11-13 |
EP1019283A1 (en) | 2000-07-19 |
CA2276438A1 (en) | 1998-10-29 |
DE69801589T2 (de) | 2002-04-18 |
AU724415B2 (en) | 2000-09-21 |
WO1998047761A1 (en) | 1998-10-29 |
EP1019283B1 (en) | 2001-09-05 |
GB9707888D0 (en) | 1997-06-04 |
JP3320072B2 (ja) | 2002-09-03 |
GB2324351A (en) | 1998-10-21 |
KR100435312B1 (ko) | 2004-06-10 |
BR9806725A (pt) | 2000-04-04 |
CN1086664C (zh) | 2002-06-26 |
EA199900555A1 (ru) | 2000-02-28 |
ES2159947T3 (es) | 2001-10-16 |
US6135395A (en) | 2000-10-24 |
CN1243485A (zh) | 2000-02-02 |
MY115402A (en) | 2003-05-31 |
KR20000062411A (ko) | 2000-10-25 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JP2000513673A (ja) | 航空機翼の組立体 | |
US7322547B2 (en) | Aerospace vehicle leading edge slat devices and corresponding methods | |
US9586677B2 (en) | Aircraft wing with system establishing a laminar boundary layer flow | |
CA2565897C (en) | High-lift device for an aircraft | |
EP3031713B1 (en) | Aircraft wing rib | |
US2841344A (en) | Boundary layer control | |
US20110260008A1 (en) | Fluid flow control device for an aerofoil | |
JPS62157898A (ja) | 航空機の前縁組立体 | |
US9896190B1 (en) | Wing leading edge architecture suitable for laminar flow | |
US20180265208A1 (en) | Air intake structure and airflow control system | |
CN107021207B (zh) | 用于被动式边界层吸入的飞行器用流装置 | |
CN110546066B (zh) | 空气动力学本体 | |
US5178348A (en) | Contoured wing/flap assembly and method | |
US9701399B1 (en) | Parasitic drag induced boundary layer reduction system and method | |
CN110049918B (zh) | 飞行器机翼组件 | |
US20200277039A1 (en) | Wing Leading Edge Device And A Wing Having Such A Wing Leading Edge Device | |
US20230286647A1 (en) | Leading edge flap |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
S111 | Request for change of ownership or part of ownership |
Free format text: JAPANESE INTERMEDIATE CODE: R313113 |
|
S531 | Written request for registration of change of domicile |
Free format text: JAPANESE INTERMEDIATE CODE: R313531 |
|
R350 | Written notification of registration of transfer |
Free format text: JAPANESE INTERMEDIATE CODE: R350 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20090621 Year of fee payment: 7 |
|
FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20100621 Year of fee payment: 8 |
|
FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20110621 Year of fee payment: 9 |
|
S533 | Written request for registration of change of name |
Free format text: JAPANESE INTERMEDIATE CODE: R313533 |
|
FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20110621 Year of fee payment: 9 |
|
R350 | Written notification of registration of transfer |
Free format text: JAPANESE INTERMEDIATE CODE: R350 |
|
FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20110621 Year of fee payment: 9 |
|
FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20120621 Year of fee payment: 10 |
|
FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20120621 Year of fee payment: 10 |
|
FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20130621 Year of fee payment: 11 |
|
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 |