CN109625251B - 用于流动控制的垂直尾翼单元 - Google Patents

用于流动控制的垂直尾翼单元 Download PDF

Info

Publication number
CN109625251B
CN109625251B CN201811172803.XA CN201811172803A CN109625251B CN 109625251 B CN109625251 B CN 109625251B CN 201811172803 A CN201811172803 A CN 201811172803A CN 109625251 B CN109625251 B CN 109625251B
Authority
CN
China
Prior art keywords
vertical tail
tail unit
pressure chamber
air
outer skin
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.)
Active
Application number
CN201811172803.XA
Other languages
English (en)
Other versions
CN109625251A (zh
Inventor
T·霍耶尔
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Operations GmbH
Original Assignee
Airbus Operations GmbH
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Airbus Operations GmbH filed Critical Airbus Operations GmbH
Publication of CN109625251A publication Critical patent/CN109625251A/zh
Application granted granted Critical
Publication of CN109625251B publication Critical patent/CN109625251B/zh
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C5/00—Stabilising surfaces
    • B64C5/02—Tailplanes
    • 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
    • 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
    • B64C21/025—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for simultaneous blowing and sucking
    • 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
    • B64C21/08—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like adjustable
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/06—Boundary layer controls by explicitly adjusting fluid flow, e.g. by using valves, variable aperture or slot areas, variable pump action or variable fluid pressure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/20—Boundary layer controls by passively inducing fluid flow, e.g. by means of a pressure difference between both ends of a slot or duct
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Seal Device For Vehicle (AREA)
  • Aeration Devices For Treatment Of Activated Polluted Sludge (AREA)
  • Air-Flow Control Members (AREA)
  • Superstructure Of Vehicle (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Tires In General (AREA)

Abstract

披露了一种用于流动控制的垂直尾翼单元(7)，所述垂直尾翼单元包括：外蒙皮(13)，其与周围气流(21)接触，其中，外蒙皮(13)在前缘(23)与后缘(25)之间延伸、并且包围内部空间(29)，并且其中，外蒙皮(13)在前缘(23)的区域中包括多孔区段(31)；压力腔室(15)，其被安排在所述内部空间(29)中，其中，压力腔室(15)流体连接至所述多孔区段(31)；进气口(17)，其被提供在外蒙皮(13)中，其中，进气口(17)流体连接至压力腔室(15)，其中，排气口(19)流体连接至压力腔室(15)。为垂直尾翼单元(7)提供减小的阻力和提高的效率的目的的实现是在于将进气口(17)形成为在前缘(23)处的外蒙皮(13)中的开口(35)。

Description

用于流动控制的垂直尾翼单元
技术领域
本发明涉及飞行器的垂直尾翼单元。垂直尾翼单元被配置成用于流动控制，优选地用于混合层流控制。本发明的另一方面涉及包括这种垂直尾翼单元的飞行器。
背景技术
垂直尾翼单元包括外蒙皮、压力腔室、进气口、以及排气口。优选地，垂直尾翼单元进一步包括从内部支撑外蒙皮的多个结构部件(例如加强件)。进一步优选的是，垂直尾翼单元由垂直安定面和枢转地安装至垂直安定面的方向舵构成。
外蒙皮与周围气流接触、并且在面向到来的流动的前缘与后缘之间延伸。进一步，外蒙皮具有两个相反的侧向侧、并且包围内部空间。外蒙皮进一步包括在前缘的区域中的多孔区段，以用于允许空气穿过外蒙皮。多孔区段可以例如形成为穿孔的蒙皮面板或形成为由多孔材料制成的蒙皮面板。
压力腔室被安排在内部空间中以用于保持相对于多孔区段的前方的周围气流的压力的超压或减压。压力腔室流体连接至多孔区段。
在外蒙皮中提供进气口，用于允许来自周围气流的空气进入。进气口流体连接至压力腔室、并且被配置成用于在相关的飞行器的飞行中引起压力腔室中的超压，使得来自压力腔室的空气通过多孔区段排放至周围气流。
在外蒙皮中提供排气口，以用于允许空气离开到周围气流中。排气口流体连接至压力腔室、并且被配置成用于在相关的飞行器的飞行中引起压力腔室中的减压，使得来自周围气流的空气通过多孔区段被吸入到压力腔室中。优选地，排气口被形成为可移动的翻板，该翻板是或可以是在后缘的方向上打开的。
现有技术中，这种垂直尾翼单元是已知的。已知的垂直尾翼单元的进气口经常被形成为风斗(air scoop)，该风斗从外蒙皮突出到周围气流中。然而，这种风斗在垂直尾翼单元处造成了额外的阻力，并且降低了效率。
发明内容
因此，本发明的目的是提供一种具有减小的阻力和提高的效率的垂直尾翼单元。
此目的的实现是在于将进气口形成为前缘处的外蒙皮中的开口。开口可以形成为外蒙皮中的孔，带有后续到垂直尾翼单元内部的通道。以此方式，进气口的任何部分都不会从外蒙皮突出到周围气流中，使得进气口不会导致额外的阻力或至少使额外的阻力最小化。
根据优选的实施例，进气口被安排在前缘的驻点处，即在撞击在前缘上的周围气流沿相反方向分开的点处。以此方式，相对较高的驻点压力可以用于给压力腔室加压。
根据另一个优选的实施例，进气口具有圆形形状或椭圆形形状。这种形状有助于压力腔室中的最小阻力和最大压力。然而，进气口还可以具有矩形形状，该矩形形状由于其简单的设计而是有利的。
根据另一个优选的实施例，所述进气口被安排成比所述多孔区段更靠近所述垂直尾翼单元的翼根。翼根涉及垂直尾翼单元的、所述垂直尾翼单元在此被或可以被连接至机身的部分。换言之，进气口被安排在多孔区段之下。以此方式，进气口和多孔区段不会彼此干扰。
根据进一步优选的实施例，进气口经由入口管道连接至压力腔室。优选地，入口管道从进气口向上行进至压力腔室。
特别地，排气口经由出口管道连接至压力腔室。优选地，至少部分的所述入口管道与所述出口管道一体形成。以此方式，需要最小量的结构和因此导致的重量。
根据另一个优选的实施例，进气口包括用于关闭该进气口的门。优选地，门被配置成用于部分地和完全地关闭进气口。以此方式，可以控制周围气流是否可以穿过外蒙皮进入垂直尾翼单元，并且可以控制周围气流可以穿过外蒙皮进入垂直尾翼单元的程度。
特别地，优选的是，门被安装至铰链，使得当打开门时，门能够枢转到通道内。以此方式，进气口的任何部分都不会从外蒙皮突出到周围气流中。进一步，启用了门的可靠密封。
进一步，优选的是，铰链具有水平铰链轴线地安装至进气口的底部边缘或顶部边缘。以此方式，启用了可以可靠地密封的对称的门。
可替代地，优选的是，铰链居中地延伸跨过进气口。门包括安装至铰链的两个门扇，使得每个门扇可以覆盖入口开口的一部分。以此方式，在门的关闭位置，周围气流的空气压力在两个门扇之间分开，使得门扇和致动器可以设计得不那么强力。
特别地，优选的是，铰链具有竖直或水平的铰链轴线。以此方式，启用了对称且简单设计的门扇。
本发明的另一方面涉及一种包括根据以上所描述的实施例中任一项所述的垂直尾翼单元的飞行器。上面提到的与垂直尾翼单元有关的特征和优点也适用于该飞行器。
附图说明
下文中，借助于附图更详细地描述了本发明的优选实施例。附图说明
图1：根据本发明的飞行器的尾翼区段的侧视图，
图2：图1中示出的飞行器所采用的进气口的第一实施例的详细侧视图，其中底部铰链和门处于关闭位置，
图3：图2中示出的进气口，其中门处于打开位置，
图4：图1中示出的飞行器所采用的进气口的第二实施例的详细侧视图，其中顶部铰链和门处于打开位置，
图5：图1中示出的飞行器所采用的进气口的第三实施例的详细侧视图，其中中央铰链和两个门扇处于关闭位置，
图6：图5中示出的进气口的俯视图。
具体实施方式
在图1中，展示了根据本发明的飞行器1的实施例。飞行器1包括机身3、水平尾翼单元5、以及根据本发明的实施例的垂直尾翼单元7。垂直尾翼单元7包括垂直安定面9和枢转地安装至垂直安定面9的方向舵11。垂直尾翼单元7被配置成用于混合层流控制，并且包括外蒙皮13、压力腔室15、进气口17、以及排气口19。
外蒙皮13与周围气流21接触、并且在前缘23与后缘25之间延伸。进一步，外蒙皮13具有两个相反的侧向侧27a、27b，并且包围内部空间29。外蒙皮13进一步包括在前缘23的区域中的多孔区段31，以用于允许空气穿过外蒙皮13。
压力腔室15被安排在内部空间29中用于相对于多孔区段31的前方的周围气流21的压力保持超压或减压。压力腔室15流体连接至多孔区段31。
排气口19被安排在外蒙皮13中，以用于允许空气离开到周围气流21中。排气口19流体连接至压力腔室15、并且被配置成用于在相关的飞行器1的飞行中在压力腔室15中引起减压，使得来自周围气流21的空气通过多孔区段31被吸入到压力腔室15中。排气口19包括可枢转的翻板33，该翻板可以在后缘25的方向上打开。
进气口17被安排在外蒙皮13中，以用于允许来自周围气流21的空气进入垂直尾翼单元7。进气口17流体连接至压力腔室15、并且被配置成用于在相关的飞行器1的飞行中引起压力腔室15的超压，使得来自压力腔室15的空气通过多孔区段31排放到周围气流21中。进气口17形成为在前缘23处的外蒙皮13中的开口35。开口35可以形成为外蒙皮13中的孔37，带有后续到垂直尾翼单元7内部的通道39。进气口17被安排在前缘23的驻点41处、并且具有圆形形状。
如图2至图6中所示出的，进气口17包括用于关闭进气口17的门43。门43被安装至铰链45，使得当门43打开时，门43能够枢转到通道39内。在图2和图3中示出的实施例中，铰链45具有水平铰链轴线49地安装至进气口17的底部边缘47，其中，图2示出门43处于关闭位置，并且图3示出门43处于打开位置。在图4中示出的实施例中，铰链45具有水平铰链轴线49地安装至进气口17的顶部边缘51。
在图5和图6中示出的实施例中，铰链45居中地延伸跨过进气口17。门43包括安装至铰链45的两个门扇53a、53b，使得每个门扇53a、53b可以覆盖开口35的一部分。铰链45具有竖直的铰链轴线49。
如图1中示出的，进气口17被安排成比多孔区段31更靠近垂直尾翼单元7的翼根55。进气口17经由入口管道57连接至压力腔室15，该入口管道从进气口17向上行进至压力腔室15。排气口19经由出口管道59连接至压力腔室15。入口管道57的宽部分与出口管道59一体形成。

Claims (10)

1.一种用于流动控制的垂直尾翼单元(7)，包括：
外蒙皮(13)，所述外蒙皮与周围气流(21)接触，其中，所述外蒙皮(13)在前缘(23)与后缘(25)之间延伸、并且包围内部空间(29)，并且其中，所述外蒙皮(13)在所述前缘(23)的区域中包括多孔区段(31)，
压力腔室(15)，所述压力腔室被安排在所述内部空间(29)中，其中，所述压力腔室(15)流体连接至所述多孔区段(31)，
进气口(17)，所述进气口被提供在所述外蒙皮(13)中，其中，所述进气口(17)流体连接至所述压力腔室(15)、并且被配置成用于在所述压力腔室(15)中引起超压，使得空气通过所述多孔区段(31)排出到所述周围气流(21)中，所述进气口(17)形成为所述前缘(23)处的所述外蒙皮(13)中的开口(35)，以及
排气口(19)，所述排气口被提供在所述外蒙皮(13)中，其中，所述排气口(19)经由出口管道(59)流体连接至所述压力腔室(15)、并且被配置成用于在所述压力腔室(15)中引起减压，使得通过所述多孔区段(31)吸入所述周围气流(21)的空气，
其中，所述进气口(17)包括用于关闭所述进气口(17)的门(43)，其中，所述门(43)被安装至铰链(45)，使得当所述门(43)打开时，所述门(43)能够枢转到所述垂直尾翼单元(7)的内部，从而在所述压力腔室(15)中形成所述超压，其中，所述进气口(17)位于所述垂直尾翼单元(7)的翼根(55)与所述多孔区段(31)之间，并且所述进气口(17)沿着所述前缘(23)与所述多孔区段(31)分开，并且
其中，所述排气口(19)包括被配置成用于关闭所述出口管道(59)的翻板(33)，所述翻板(33)打开以在所述压力腔室(15)中形成所述减压，使得所述周围气流(21)通过所述多孔区段(31)流入到所述压力腔室(15)中。
2.根据权利要求1所述的垂直尾翼单元，其中，所述进气口(17)被安排在所述前缘(23)的驻点(41)处。
3.根据权利要求1或2所述的垂直尾翼单元，其中，所述进气口(17)具有圆形形状或椭圆形形状。
4.根据权利要求1或2所述的垂直尾翼单元，其中，所述进气口(17)被安排成比所述多孔区段(31)更靠近所述垂直尾翼单元(7)的所述翼根(55)。
5.根据权利要求1或2所述的垂直尾翼单元，其中，所述进气口(17)经由入口管道(57)连接至所述压力腔室(15)。
6.根据权利要求5所述的垂直尾翼单元，其中，至少部分的所述入口管道(57)与所述出口管道(59)一体形成。
7.根据权利要求1所述的垂直尾翼单元，其中，所述铰链(45)具有水平铰链轴线(49)地安装至所述进气口(17)的底部边缘(47)或顶部边缘(51)。
8.根据权利要求1所述的垂直尾翼单元，其中，所述铰链(45)延伸跨过所述进气口(17)，并且所述门(43)包括安装至所述铰链(45)的两个门扇(53a，53b)，使得每个门扇(53a，53b)可以覆盖所述开口(35)的一部分。
9.根据权利要求8所述的垂直尾翼单元，其中，所述铰链(45)具有竖直的铰链轴线(49)。
10.一种包括根据权利要求1至9中任一项所述的垂直尾翼单元(7)的飞行器(1)。
CN201811172803.XA 2017-10-09 2018-10-09 用于流动控制的垂直尾翼单元 Active CN109625251B (zh)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102017123440 2017-10-09
DE102017123440.3 2017-10-09

Publications (2)

Publication Number Publication Date
CN109625251A CN109625251A (zh) 2019-04-16
CN109625251B true CN109625251B (zh) 2022-04-29

Family

ID=63713750

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201811172803.XA Active CN109625251B (zh) 2017-10-09 2018-10-09 用于流动控制的垂直尾翼单元

Country Status (5)

Country Link
US (2) US10974817B2 (zh)
EP (1) EP3466811B1 (zh)
CN (1) CN109625251B (zh)
BR (1) BR102018070539A2 (zh)
RU (1) RU2711821C1 (zh)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2557341A (en) * 2016-12-07 2018-06-20 Airbus Operations Ltd Aircraft wing assembly
EP3466811B1 (en) * 2017-10-09 2023-06-21 Airbus Operations GmbH Vertical tail unit for flow control
EP3466810B1 (en) * 2017-10-09 2022-07-13 Airbus Operations GmbH Vertical tail unit for flow control
ES2967158T3 (es) * 2018-06-22 2024-04-26 Airbus Operations Slu Sistema de admisión de aire

Family Cites Families (114)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2036891A (en) * 1935-05-01 1936-04-07 Ray G Sline Aeroplane wing
US2111530A (en) * 1935-06-29 1938-03-15 Seversky Alexander P De Lift intensifier for aircraft
US2742247A (en) * 1950-10-31 1956-04-17 Handley Page Ltd Outer surfaces for craft moving in one fluid
GB718421A (en) 1951-02-12 1954-11-17 Fairey Aviat Co Ltd Improvements relating to boundary layer control means for aerofoils and other boundary walls
US2776100A (en) * 1951-04-19 1957-01-01 Breguet Louis Aircraft structural elements and especially wings from reinforced concrete
US3213527A (en) * 1956-04-30 1965-10-26 Fort Wayne Metals Inc Method of making permeable airfoil skin material
US3770560A (en) * 1971-10-21 1973-11-06 American Cyanamid Co Composite laminate with a thin, perforated outer layer and cavitated bonded backing member
US3820628A (en) * 1972-10-02 1974-06-28 United Aircraft Corp Sound suppression means for rotating machinery
US4169567A (en) * 1974-12-13 1979-10-02 Tamura Raymond M Helicopter lifting and propelling apparatus
US4000869A (en) * 1975-10-21 1977-01-04 Northrop Corporation Strong shock boundary layer interaction control system
US4263842A (en) * 1978-08-02 1981-04-28 Moore Robert D Adjustable louver assembly
GB2108202B (en) * 1980-10-10 1984-05-10 Rolls Royce Air cooling systems for gas turbine engines
GB2234351A (en) 1989-06-05 1991-01-30 Medical & Diagnostic Systems L Pressure transducer system
FR2654411B1 (fr) * 1989-11-16 1992-01-17 Maciocia Yves Dispositif de securite pour l'alimentation en air d'un profil de parapente.
US5114100A (en) * 1989-12-29 1992-05-19 The Boeing Company Anti-icing system for aircraft
GB9111620D0 (en) 1991-05-30 1991-07-24 Short Brothers Plc Boundary layer control
US5263667A (en) * 1991-09-09 1993-11-23 The Boeing Company Perforated wing panel with variable porosity
US5366177A (en) * 1992-10-05 1994-11-22 Rockwell International Corporation Laminar flow control apparatus for aerodynamic surfaces
US5796612A (en) * 1992-11-18 1998-08-18 Aers/Midwest, Inc. Method for flight parameter monitoring and control
GB9300545D0 (en) * 1993-01-13 1993-03-10 Hurel Dubois Uk Ltd Carbon fibre panels
US5398410A (en) * 1993-03-19 1995-03-21 Mcdonnell Douglas Corporation Method of making a superplastically formed structure having a perforated skin
RU2070144C1 (ru) * 1993-06-28 1996-12-10 Мохаммед Аль-Хейли Шариф Высокоманевренный самолет
DE4436748C1 (de) 1994-10-14 1995-09-21 Daimler Benz Aerospace Airbus Verfahren zur Herstellung innenversteifter Hohlbauteile mit perforierter Wandung
US5590854A (en) * 1994-11-02 1997-01-07 Shatz; Solomon Movable sheet for laminar flow and deicing
GB9424495D0 (en) * 1994-12-05 1995-01-25 Short Brothers Plc Aerodynamic low drag structure
GB9504372D0 (en) * 1995-03-04 1995-04-26 British Aerospace A composite laminate
US5791601A (en) * 1995-08-22 1998-08-11 Dancila; D. Stefan Apparatus and method for aerodynamic blowing control using smart materials
US6142425A (en) * 1995-08-22 2000-11-07 Georgia Institute Of Technology Apparatus and method for aerodynamic blowing control using smart materials
BR9702347A (pt) * 1996-07-18 1999-12-28 Prospective Concepts Ag Asa pneumática adaptável para aeronaves de asa fixa
US5923003A (en) * 1996-09-09 1999-07-13 Northrop Grumman Corporation Extended reaction acoustic liner for jet engines and the like
US5813625A (en) * 1996-10-09 1998-09-29 Mcdonnell Douglas Helicopter Company Active blowing system for rotorcraft vortex interaction noise reduction
DE19643069C2 (de) * 1996-10-18 1999-03-25 Daimler Benz Aerospace Airbus Seitenleitwerksstrukur für ein Flugzeug
DE19649132C2 (de) * 1996-11-27 1999-09-02 Daimler Chrysler Aerospace Nase für eine aerodynamische Fläche und Verfahren zu ihrer Herstellung
GB2324351A (en) 1997-04-18 1998-10-21 British Aerospace Reducing drag in aircraft wing assembly
US6092990A (en) * 1997-06-05 2000-07-25 Mcdonnell Douglas Helicopter Company Oscillating air jets for helicopter rotor aerodynamic control and BVI noise reduction
US6234751B1 (en) * 1997-06-05 2001-05-22 Mcdonnell Douglas Helicopter Co. Oscillating air jets for reducing HSI noise
US5987880A (en) * 1997-07-08 1999-11-23 Mcdonnell Douglas Corporation Supersonic engine, multi-port thrust reversing system
US5971328A (en) * 1998-01-15 1999-10-26 Kota; Sridhar System for varying a surface contour
DE19804718C2 (de) * 1998-02-06 2001-09-13 Eurocopter Deutschland Schall absorbierende Sandwichwand
DE19820097C2 (de) * 1998-05-06 2003-02-13 Airbus Gmbh Anordnung zur Grenzschichtabsaugung und Stoßgrenzschichtkontrolle für ein Flugzeug
GB9914652D0 (en) * 1999-06-24 1999-08-25 British Aerospace Laminar flow control system and suction panel for use therein
US6983821B2 (en) * 1999-10-01 2006-01-10 Awi Licensing Company Acoustical panel having a honeycomb structure and method of making the same
US6622973B2 (en) * 2000-05-05 2003-09-23 King Fahd University Of Petroleum And Minerals Movable surface plane
GB0016149D0 (en) * 2000-06-30 2000-08-23 Short Brothers Plc A noise attenuation panel
US7017234B2 (en) * 2001-06-18 2006-03-28 Anderson Brent L Folding tools with locking hinges
US6612524B2 (en) 2002-01-17 2003-09-02 The Boeing Company Forebody vortex alleviation device
GB2402196B (en) 2003-05-29 2006-05-17 Rolls Royce Plc A laminar flow nacelle for an aircraft engine
GB2404234A (en) * 2003-07-19 2005-01-26 Rolls Royce Plc A laminar flow surface for an aircraft
DE102004024007B4 (de) * 2004-05-13 2007-10-11 Airbus Deutschland Gmbh Flugzeugkomponente, insbesondere Flügel
GB0412125D0 (en) * 2004-05-29 2004-06-30 Univ Liverpool Porous metallic materials and method of production thereof
DE102005016570A1 (de) * 2005-04-11 2006-10-19 Airbus Deutschland Gmbh Reduzierung von Reibungsverlusten im Bereich von Grenzschichten an fluidumströmten Oberflächen
US20060272279A1 (en) * 2005-05-13 2006-12-07 Administrator Of The National Aeronautics And Space Administration Composite panel having subsonic transverse wave speed characteristics
EP1749740B1 (en) * 2005-08-02 2011-02-09 Universität Stuttgart Flow surface for a three-dimensional boundary-layer flow, especially on a swept wing, a swept tail plane or a rotor
US7305893B2 (en) * 2005-08-11 2007-12-11 The Boeing Company Oscillating vane actuator apparatus and method for active flow control
US7631727B2 (en) * 2006-05-24 2009-12-15 Airbus Deutschland Gmbh Sandwich structure with frequency-selective double wall behavior
ITMI20061214A1 (it) * 2006-06-23 2007-12-24 Dada S P A Armadio o mobile similare con sportelli pieghevoli e scorrevoli a scomparsa
GB2443830B (en) * 2006-11-15 2010-01-20 Rolls Royce Plc Cowling arrangement
US7766280B2 (en) * 2007-05-29 2010-08-03 United Technologies Corporation Integral suction device with acoustic panel
US7866609B2 (en) * 2007-06-15 2011-01-11 The Boeing Company Passive removal of suction air for laminar flow control, and associated systems and methods
US9004399B2 (en) 2007-11-13 2015-04-14 United Technologies Corporation Nacelle flow assembly
US20090210103A1 (en) * 2007-12-03 2009-08-20 Mr. Michael Cook Controlling aircraft aerial movements, defeating icing on aircraft surfaces, aiding decontamination, and damping turbulence effects on aircraft by the method of micro-perforated airfoil coordinated precision flow management
DE102007060662B4 (de) * 2007-12-17 2014-07-24 Airbus Operations Gmbh Flugzeugkabinenpaneel
DE102007061590A1 (de) * 2007-12-20 2009-08-13 Airbus Deutschland Gmbh Hochauftriebssystem für ein Flugzeug mit einem Hauptflügel und einem verstellbaren Vorflügel
US8042772B2 (en) * 2008-03-05 2011-10-25 The Boeing Company System and method for pneumatically actuating a control surface of an airfoil
DE102008017357B4 (de) * 2008-04-04 2014-01-16 Airbus Operations Gmbh Akustisch optimiertes Kabinenwandelement und seine Verwendung
US8251317B2 (en) * 2008-04-18 2012-08-28 The Boeing Company System and method for varying the porosity of an aerodynamic surface
WO2009134732A2 (en) * 2008-04-29 2009-11-05 Virginia Tech Intellectual Properties, Inc. Open pore ceramic matrix foams coated with metal or metal alloys and methods of making same
DE102008042036A1 (de) * 2008-09-12 2010-03-25 Airbus Deutschland Gmbh Stange zur Abstützung von Bauteilen innerhalb einer Rumpfzellenstruktur eines Flugzeugs
GB2464540B (en) * 2008-10-20 2013-03-13 Acell Group Ltd Patterned composite product
DE102008056417B4 (de) * 2008-11-07 2010-11-11 Airbus Deutschland Gmbh Verfahren und System zur Notbelüftung einer Flugzeugkabine
DE102008062701A1 (de) * 2008-12-17 2010-07-01 Airbus Deutschland Gmbh Flugzeugkabinenpaneel mit Kerntaschen zur Schallabsorption
DE102008062703A1 (de) * 2008-12-17 2010-07-01 Airbus Deutschland Gmbh Flugzeugkabinenpaneel zur Schallabsorption
US8245976B2 (en) * 2009-01-19 2012-08-21 The Boeing Company Door assembly for laminar flow control system
US8128037B2 (en) * 2009-01-19 2012-03-06 The Boeing Company Apparatus and method for passive purging of micro-perforated aerodynamic surfaces
US8668166B2 (en) * 2009-01-29 2014-03-11 The Boeing Company Shape memory riblets
US8678316B2 (en) * 2009-01-29 2014-03-25 The Boeing Company Amorphous metal riblets
DE102009010150B4 (de) * 2009-02-23 2013-09-19 Airbus Operations Gmbh System und Verfahren zur Notbelüftung einer Flugzeugkabine
DE102009022174B4 (de) 2009-05-20 2019-12-12 Airbus Operations Gmbh Vorrichtung zur Verringerung des Luftwiderstandes einer Anströmfläche eines Flugzeugs
DE102009043489A1 (de) * 2009-09-30 2011-03-31 Airbus Operations Gmbh Vorrichtung zur Grenzschichtabsaugung und Verbundbauteil hierfür
DE102009049049A1 (de) * 2009-10-12 2011-04-14 Airbus Operations Gmbh Strömungskörper insbesondere für Luftfahrzeuge
DE102010014640A1 (de) 2010-04-12 2011-10-13 Airbus Operations Gmbh Strukturbauteil zur Verwendung für Strömungsbauteile von Flugzeugen sowie Verfahren zu dessen Herstellen
DE102010014641A1 (de) 2010-04-12 2011-10-13 Airbus Operations Gmbh Wandabschnitt und Strukturbauteil zur Verwendung für Strömungsbauteile von Flugzeugen sowie Verfahren zu dessen Herstellung
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
US8783624B2 (en) * 2010-08-15 2014-07-22 The Boeing Company Laminar flow panel
US10556670B2 (en) * 2010-08-15 2020-02-11 The Boeing Company Laminar flow panel
DE102010036154B4 (de) * 2010-09-02 2017-01-26 Airbus Operations Gmbh Luft absaugende Fahrzeugrumpfkomponente, Verfahren zum Herstellen einer Luft absaugenden Fahrzeugrumpfkomponente und Fahrzeug, insbesondere Flugzeug, mit einer Luft absaugenden Fahrzeugrumpfkomponente
US8974177B2 (en) * 2010-09-28 2015-03-10 United Technologies Corporation Nacelle with porous surfaces
US9227719B2 (en) * 2011-03-11 2016-01-05 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Reactive orthotropic lattice diffuser for noise reduction
US9623952B1 (en) * 2011-03-11 2017-04-18 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration External acoustic liners for multi-functional aircraft noise reduction
US9132909B1 (en) * 2011-03-11 2015-09-15 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Flap edge noise reduction fins
DE102011115536A1 (de) * 2011-08-17 2013-02-21 Weinor Gmbh & Co. Kg Schiebefalttürsystem
DE102012006194B4 (de) * 2012-03-27 2021-02-04 Airbus Operations Gmbh Flugzeug mit einem Flugzeugrumpf und einer Luft absaugenden Flugzeugrumpfkomponente
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
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
EP2786935B1 (en) * 2013-04-02 2016-09-07 Airbus Operations GmbH Ram air channel assembly and method for operating a ram air channel assembly
US9670706B2 (en) * 2013-07-02 2017-06-06 Henry Kong Sun Ching Portable door guard hinge security device
US9097048B2 (en) * 2013-08-13 2015-08-04 FlatZen, Inc. Hinge mechanisms and foldable furniture
US9272773B2 (en) * 2013-09-25 2016-03-01 The Boeing Company Apparatus and methods to operate laminar flow control doors
EP2886452B1 (en) 2013-12-18 2017-09-13 Airbus Operations GmbH Flow body, method for manufacturing a flow body and aircraft having such a flow body
EP2886453B1 (en) * 2013-12-18 2019-06-12 Airbus Operations GmbH Boundary layer control system and aircraft having such a boundary layer control system
EP2955108B1 (en) * 2014-06-13 2018-02-21 Airbus Operations GmbH Leading edge nose structure on the vertical stabilizer of an aircraft
EP2995552B1 (en) * 2014-09-09 2018-05-02 Airbus Defence and Space GmbH Chamber in an airfoil
GB2533115A (en) 2014-12-09 2016-06-15 Airbusgroup Ltd Aircraft wing rib
EP3233626B1 (en) * 2014-12-18 2019-09-25 Bombardier Inc. Sound absorbers for airframe components
EP3040270B1 (en) * 2014-12-31 2020-09-30 Rolls-Royce North American Technologies, Inc. Fluid-vectoring system
WO2015198296A2 (en) * 2015-05-19 2015-12-30 Yousef Hani Air intake structure and airflow control system
DE102015110782A1 (de) * 2015-07-03 2017-01-05 Airbus Operations Gmbh Integrales Bauteil mit einer Einrichtung zur aktiven Strömungskontrolle
EP3192736B1 (en) * 2016-01-12 2018-07-11 Airbus Operations, S.L. A leading edge with laminar flow control and manufacturing method thereof
EP3199450B1 (en) * 2016-01-29 2019-05-15 Airbus Operations GmbH Flow body for an aircraft for passive boundary layer suction
EP3466810B1 (en) * 2017-10-09 2022-07-13 Airbus Operations GmbH Vertical tail unit for flow control
EP3466811B1 (en) * 2017-10-09 2023-06-21 Airbus Operations GmbH Vertical tail unit for flow control
CN111670141A (zh) * 2018-01-31 2020-09-15 空中客车德国运营有限责任公司 用于流动控制的翼型件
US20190256201A1 (en) * 2018-02-20 2019-08-22 Global Energy Transmission, Co. Rotor assembly with overlapping rotors
DE102018218715A1 (de) * 2018-10-31 2020-04-30 Airbus Defence and Space GmbH Verfahren zum Betrieb eines zumindest zeitweise unbemannten Luftfahrzeugs sowie ein derartiges Luftfahrzeug

Also Published As

Publication number Publication date
BR102018070539A2 (pt) 2019-06-04
CN109625251A (zh) 2019-04-16
US20190106202A1 (en) 2019-04-11
US20210214072A1 (en) 2021-07-15
EP3466811B1 (en) 2023-06-21
RU2711821C1 (ru) 2020-01-22
US10974817B2 (en) 2021-04-13
EP3466811A1 (en) 2019-04-10
US11565795B2 (en) 2023-01-31

Similar Documents

Publication Publication Date Title
CN109625251B (zh) 用于流动控制的垂直尾翼单元
RU2723371C2 (ru) Выпускные клапаны восстановления тяги для использования с летательным аппаратом
JP5368452B2 (ja) 航空機用流出弁
US20180265208A1 (en) Air intake structure and airflow control system
US6901737B2 (en) Air intake for an auxiliary power unit in an aircraft
CN109625250B (zh) 用于流动控制的垂直尾翼单元
EP2886453A1 (en) Boundary layer control system and aircraft having such a boundary layer control system
RU2010146140A (ru) Воздушный впускной клапан для самолета и способ его изготовления
US11584514B2 (en) Airfoil for flow control including a common inlet/outlet device connected to a porous section
US11155342B2 (en) Leading edge structure for a flow control system of an aircraft
US11052996B2 (en) Lifting surface
CN202337358U (zh) 一种定常微射流武器舱噪声抑制装置
US20230294819A1 (en) A leading edge structure for a flow control system of an aircraft
KR20170108678A (ko) 유량 극대화 환기팬
CN110576978A (zh) 一种进气道辅助进气装置及具有其的飞机
US20200115041A1 (en) Leading edge structure for a flow control system of an aircraft
PL229546B1 (pl) Element aerodynamiczny o zmiennych właściwościach aerodynamicznych
EP4148245A3 (en) Aircraft propulsion system with variable area inlet

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant