CN100436255C - 特别是机翼的飞机部件 - Google Patents

特别是机翼的飞机部件 Download PDF

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CN100436255C
CN100436255C CNB2005800144261A CN200580014426A CN100436255C CN 100436255 C CN100436255 C CN 100436255C CN B2005800144261 A CNB2005800144261 A CN B2005800144261A CN 200580014426 A CN200580014426 A CN 200580014426A CN 100436255 C CN100436255 C CN 100436255C
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pressure
valve
aircraft components
exposed
ambient air
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CN1950254A (zh
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于尔根·梅斯特
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Airbus Operations GmbH
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
    • B64D15/02—De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid
    • B64D15/04—Hot gas application
    • 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
    • B64C21/04—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for blowing
    • 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
    • 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
    • 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
    • B64C2230/22—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

Abstract

飞机部件，特别是带有用于附面层抽吸的穿孔(3)的机翼(1)。在双壁机翼(1)之间的空间(5)中，分隔壁形成了互相邻接并交替的压力通道(21)和抽吸通道(22)，所述通道(21、22)与穿孔(3)相连通。通过控制装置，压力通道(21)能够连接到热空气贮存器，而抽吸通道(22)能够连接到真空贮存器，并且它们能够通过短路阀(16)连接到相应的其它区域。

Description

特别是机翼的飞机部件
技术领域
本发明涉及暴露在流动的环境空气里的飞机部件，特别地涉及在外壳上具有穿孔以用于附面层抽吸的机翼。
背景技术
通过避免从层流到湍流的过早变化，从暴露到流动空气中的飞机部件的表面的附面层抽吸用于减小流阻并增大可获得的升力。在不利的环境条件下，在外壳上穿孔存在危险，该孔用于附面层抽吸、结冰或者用于不希望量的水进入连接到所述孔的真空通道系统。
发明内容
本发明的目的是设计一种飞机部件，以避免结冰以及由此而引起的孔的阻塞。
根据本发明，通过如下所述设计上述飞机部件来实现该目的：上述飞机部件设计有两个壁，并且在内壁元件和外壁元件之间的空间内插入有分隔壁，这些分隔壁通过结合到壁元件的一些部分而彼此邻接，从而形成交替的压力通道和抽吸通道，其中外壁元件的对应于抽吸通道的第一区域与对应于压力通道的第二区域相比明显占据更大的面积，并且其中借助控制装置，该压力通道可连接到热空气贮存器，而抽吸通道可连接到真空贮存器。
根据本发明所设计的飞机部件满足上述目的，例如来自飞机引擎的引气的热增压空气被供给到压力通道，并通过外壁元件第二区域中的孔排出到外界环境中。因为第二区域与穿孔的外壁元件的连接到抽吸通道的第一区域相比明显面积更小，因此在外壁元件中可提供足够的热量而不影响到附面层抽吸。
本发明的优选实施方式的特征在于：分隔壁由带有梯形波纹的整个薄板形成，所述薄板的底面交替地抵靠在部件的外壁元件和内壁元件上，并且包括与外壁元件的穿孔连通的开口。该分隔壁的设计具有与生产工艺相关的显著优点，因为单个部件，即带有梯形波纹的整个薄板，形成了多个压力通道和抽吸通道，并且提供了具有足够刚性的结构。用梯形波纹将薄板固定在内壁元件和外壁元件之间的空间内能够通过现有技术中的连接装置实现，例如铆接、焊接、粘接等。
本发明的另一有利的实施方式在于，具有梯形波纹的薄板的梯形轮廓的开口边比闭合底边长几倍。具有梯形波纹的薄板的此种设计以简单的方式获得了形成有与外壁元件的穿孔的相当大的区域连通的抽吸通道的构造，该抽吸通道包括外壁元件的第一区域。也就是说，在外壁元件的相当大的部分上能够通过抽吸通道产生附面层的直接抽吸。
根据本发明的另一实施方式，在连到压力通道或抽吸通道的供应管线中设置有可控阀，通过这些可控阀可由控制装置在抽吸通道内设置负压。当由于下雨或者冰的融化而在外壳上有大量的水时，由于抽吸通道中的过负压，此种设计能够避免所述水被抽吸到抽吸管道网络中，并且能够避免穿孔上结冰。如果外壳上的水量能够由适当的检测器进行记录，并且如果控制负压的相应信号可传送到控制装置，这将是有利的。
附图说明
附图示出了本发明的一个实施方式。该图示出了飞机机翼的横截面概略图。
具体实施方式
仅仅示出了机翼1的气流区域。机翼壳为双壁结构，包括外壁元件4和内壁元件6。在其压力侧上，外壁元件4包括微型穿孔3。虽然图中未示出，该微型穿孔3延伸通过机翼的整个宽度。具有梯形波纹的薄板2插入到位于外壁元件4和内壁元件6之间的空间5中。具有梯形波纹的薄板2的梯形轮廓的开口边29的长度是闭合底边28的长度的几倍。具有梯形波纹的薄板2的闭合边28抵靠在外壁元件4和内壁元件6的内表面上。具有梯形波纹的薄板2的抵靠在外壁元件4内侧的区域包括与外壁元件4中的微型穿孔3连通的开口。
这样，具有梯形波纹的薄板2或者其分隔壁形成了邻接通道，该通道朝向外壁元件逐渐变细，由于具有梯形波纹的薄板的底边中的开口，这些通道与微型穿孔连通，并且交替地形成向外延伸的通道，所述的后一个通道的外壁由开孔的壁元件4直接形成。这些后一个通道是标记为22的抽吸通道，该通道与外壁元件4的微型穿孔的区域A连接。这些朝向壁元件4向外逐渐变细的通道是压力通道21，该通道通过具有梯形波纹的薄板2内的开口与微型穿孔的区域B连通。
通过抽吸管线12，将抽吸通道22经由适当的抽吸管道系统S结合并连接到真空贮存器U。该抽吸管道系统包括止回阀14。通过相应的压力管线11，压力通道21经由压力管道系统P结合并连接到热空气贮存器W。该压力管道系统P包括可控压力阀13，该压力阀可由控制单元借助控制线15启动。最后，所示的实施方式在该抽吸管道系统S和该压力管道系统P之间还提供有短路管线，其中有可控短路阀16，该短路阀可由控制单元20借助控制线17启动。
在平稳飞行状态，其中既没有形成冰也没有从外围环境中产生过量的水，可控阀13是闭合的，且止回阀14打开，并且短路阀16选择性地打开，以使得附面层从区域A并且如果可用也可从区域B通过两个抽吸通道22和21和两个抽吸管线12和11朝向真空贮存器U抽吸。
一旦在机翼外侧产生结冰或者过量水的危险，可控压力阀13打开并且止回阀14关闭，以使得从热空气贮存器P通过压力管道11并且如果可用通过12将热空气引入到压力通道21和22，热空气从该压力通道穿过区域A和B中的微型穿孔而向外流动，其中该贮存器P中例如供应有来自飞机引擎的引气。在此设置中，压力阀13应该可控制为不会有太大量的压力空气引入到压力通道21和22中，从而防止机翼外侧的附面层被损坏。能够以协调的方式来控制阀13和14并且另外由短路阀16来支持。
需要注意的是，术语“包括”不排除其它的元件或步骤，并且“一个”不排除多个。而且在不同实施方式中描述的元件也可以结合。
还需要注意的是，权利要求中的附图标记不应理解为对权利要求的保护范围的限制。
附图标记列表：
1机翼
2分隔壁(具有梯形波纹的薄板)
3微型穿孔
4(机翼的)外壁元件
5空间
6内壁元件
11压力管线
12抽吸管线
13可控压力阀
14止回阀
15控制线
16短路阀
17控制线
20控制单元
21压力通道
22抽吸通道
28具有梯形波纹的薄板的底边
29具有梯形波纹的薄板的开口边

Claims (8)

1.一种暴露在流动的环境空气中的飞机部件，其中该部件设置有两个壁并且在内壁元件和外壁元件之间的空间内插入分隔壁，这些分隔壁通过结合壁元件的一些部分(A，B)而彼此邻接，从而形成交替的压力通道和抽吸通道，其中外壁元件的对应于抽吸通道的第一区域(A)与对应于压力通道的第二区域(B)相比明显要占据更大的面积，并且其中借助控制装置，该压力通道能够连接到热空气贮存器(W)，而抽吸通道能够连接到真空贮存器(U)。
2.如权利要求1所述的暴露在流动的环境空气中的飞机部件，其中所述分隔壁由带有梯形波纹的整个薄板形成，所述薄板的底面交替地抵靠在所述部件的外壁元件和内壁元件上，并且所述薄板包括与外壁元件的穿孔连通的开口。
3.如权利要求2所述的暴露在流动的环境空气中的飞机部件，其中具有梯形波纹的薄板的梯形轮廓的开口边比闭合底边长几倍。
4.如权利要求1至3中任一项所述的暴露在流动的环境空气中的飞机部件，其中在连到压力通道或抽吸通道的供应管线中设置有可控阀，通过这些可控阀能够由控制装置在抽吸通道内设置负压。
5.如权利要求4所述的暴露在流动的环境空气中的飞机部件，其中可控阀之一是压力阀并且另一个可控阀是止回阀，这两个阀都连接到控制单元，借助所述阀，可按需实现压力通道和抽吸通道的交替连接。
6.如权利要求5所述的暴露在流动的环境空气中的飞机部件，其中在压力管线和抽吸管线之间结合有作为短路阀的另一个可控阀，借助所述阀，实现第一区域(A)和第二区域(B)的抽吸操作和压力操作的交替。
7.如权利要求6所述的暴露在流动的环境空气中的飞机部件，其中压力阀和止回阀的控制是协调的，该控制由短路阀所支持。
8.如权利要求1所述的暴露在流动的环境空气中的飞机部件，其中所述飞机部件为在外壳上具有穿孔以用于附面层抽吸的机翼。
CNB2005800144261A 2004-05-13 2005-05-11 特别是机翼的飞机部件 Expired - Fee Related CN100436255C (zh)

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DE102004024007A DE102004024007B4 (de) 2004-05-13 2004-05-13 Flugzeugkomponente, insbesondere Flügel
DE102004024007.8 2004-05-13
US60/606,601 2004-09-02

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EP (1) EP1755947B1 (zh)
JP (1) JP4728325B2 (zh)
CN (1) CN100436255C (zh)
AT (1) ATE370886T1 (zh)
BR (1) BRPI0510705A (zh)
CA (1) CA2563572C (zh)
DE (1) DE102004024007B4 (zh)
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US20070221788A1 (en) 2007-09-27
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DE102004024007A1 (de) 2006-04-06
EP1755947A1 (en) 2007-02-28
CA2563572A1 (en) 2005-12-01
ATE370886T1 (de) 2007-09-15
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RU2006142915A (ru) 2008-06-20
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US7673832B2 (en) 2010-03-09
RU2362708C2 (ru) 2009-07-27
CA2563572C (en) 2014-07-08

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