CN100500510C - 用于控制飞行器襟翼和阻流板的系统和方法 - Google Patents

用于控制飞行器襟翼和阻流板的系统和方法 Download PDF

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CN100500510C
CN100500510C CNB2006800041310A CN200680004131A CN100500510C CN 100500510 C CN100500510 C CN 100500510C CN B2006800041310 A CNB2006800041310 A CN B2006800041310A CN 200680004131 A CN200680004131 A CN 200680004131A CN 100500510 C CN100500510 C CN 100500510C
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wing
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wing flap
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罗伯特·J·布利格
尼尔·V·休因
约翰·A·斯坦德利
斯科特·佩珀
布赖恩·L·博克希
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    • 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
    • B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C9/32—Air braking surfaces
    • B64C9/323—Air braking surfaces associated with wings
    • 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
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • B64D45/0005—Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear
    • B64D2045/001—Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear for indicating symmetry of flaps deflection
    • 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
    • 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

Abstract

本发明公开了用于控制飞行器襟翼和阻流板的系统和方法。根据一些实施例的系统(200)包括具有后缘(211)的机翼(210)以及襟翼(220)，该襟翼至少局部地设置在机翼后缘(211)的尾部，且在第一襟翼位置和第二襟翼位置之间通过第一致动器的操作相对于机翼(210)被展开。阻流板(230)至少紧接后缘(211)设置，且可在至少三个位置中移动，这三个位置包括第一阻流板位置，其中阻流板与机翼(210)的上表面形成大致连续的轮廓；第二阻流板位置，其中阻流板从第一阻流板位置向下偏转；以及第三阻流板位置，其中阻流板从第一阻流板位置向上偏转。第二致动器(231)可以机械上与襟翼的动作无关的方式被有效地连接到阻流板以在第一、第二和第三阻流板位置中移动阻流板。

Description

用于控制飞行器襟翼和阻流板的系统和方法
技术领域
本发明涉及用于控制飞行器襟翼和阻流板的系统和方法。
背景技术
当前商业运输飞行器典型地包括可展开的大升力设备，其根据飞行状况而改变飞行器机翼形状。这些设备可包括前缘襟翼且/或缝翼，以及后缘襟翼，在起飞和降落期间它们伸展来增加升力，在飞行期间被收起来减少飞行器阻力。商业运输飞行器也可包括阻流板，在下降、降落、侧滚操纵以及中止起飞期间用来选择性地减小升力。
图1A是根据现有技术形成的机翼110的部分示意性的横截面视图。该机翼110可包括后缘111、延伸后缘111的尾部的向前襟翼120a、以及延伸向前襟翼120a尾部的尾部襟翼120b。机械联动装置122连接向前襟翼120a和尾部襟翼120b到致动器121。图1B说明了具有向前襟翼120a和尾部襟翼120b的飞行器机翼110被展开来产生大升力的构型。在此构型中，襟翼120a、120b可形成向前襟翼间隙124a和尾部襟翼间隙124b，分别在向前襟翼120a和尾部襟翼120b上提供受控的附体流。相应地，这种双槽机翼结构可有效地在起飞和降落期间为大运输飞行器提供大升力(当襟翼120展开时)，并且对飞行器阻力产生明显减小的影响(当襟翼120收起时)。
显示在图1A和1B中的机翼110的一个潜在缺点是机械联动装置122相对复杂且因此构造和操作稍微昂贵及较重。相应地，其它不太复杂的装置也被开发用于给大飞行器提供大升力性能。美国专利No.4120470公开了一种这样的装置，该专利转让给本发明的受让人。该’470专利公开了一种单个的后缘襟翼和控制该单个后缘襟翼和机翼之间的间隙大小的阻流板。该装置比参考图1A和1B的上述的装置要简单，因为单个襟翼比双襟翼装置需要更少的移动件。然而，该装置采用柔性面板和与襟翼致动装置结合的阻流板致动器。在一些情况下，这些特征可增加系统复杂性和重量，同时减少系统的通用性。
发明内容
本发明大致涉及用于控制飞行器襟翼和阻流板的系统和方法。根据本发明的一个方面的系统包括具有后缘的机翼，以及设置成紧接机翼后缘的襟翼。襟翼在第一致动器的作用下在第一襟翼位置和第二襟翼位置之间可相对于机翼展开。该系统进一步包括至少紧接襟翼设置的阻流板，该阻流板可在至少三个位置中移动，这三个位置包括第一阻流板位置，其中阻流板与机翼的上表面形成大致连续的轮廓；第二阻流板位置，其中阻流板从第一阻流板位置向下偏转；以及第三阻流板位置，其中阻流板从第一阻流板位置向上偏转。第二致动器可被有效地连接到阻流板以在第一、第二和第三阻流板位置中移动阻流板，在机械上与襟翼的动作无关。第二致动器被构造为与所述襟翼无关地移动所述阻流板，并且其中所述第二致动器被构造为释放施加到所述阻流板上的力，允许当所述襟翼从所述第二襟翼位置移动到所述第一襟翼位置时所述阻流板通过直接机械接触襟翼而驱动从第一阻流板位置到第二阻流板位置。在本发明的另一方面中，控制器可被有效地连接到第一和第二致动器上。在又一个方面中，阻流板可被枢转地连接到机翼上，而没有柔性面板与机翼和阻流板配合。
本发明提供了一种用于控制飞行器机翼的系统，包括：控制器，有效地与襟翼致动器和阻流板致动器连接，所述控制器被编程具有指令以：通过引导所述襟翼致动器使所述襟翼向下偏转而与所述机翼的后缘形成间隙，以及通过引导所述阻流板致动器使所述阻流板向下偏转而与所述襟翼形成间隙，在机械上不将所述襟翼的动作与所述阻流板的动作相关联，而将所述机翼设置在大升力构型中；以及通过引导所述襟翼致动器使所述襟翼向下偏转，以及通过引导所述阻流板致动器使所述阻流板向上偏转，在机械上不将所述襟翼的动作与所述阻流板的动作相关联，而将所述机翼设置在减速器构型中，阻流板致动器被构造为与所述襟翼无关地移动所述阻流板，并且所述阻流板致动器被构造为释放施加到所述阻流板上的力，允许所述襟翼机械地接触和驱动所述阻流板。
本发明提供了一种用于操作飞行器机翼系统的方法，包括：通过使所述襟翼向下偏转以与所述机翼的后缘形成间隙，以及通过使所述阻流板向下偏转以与所述襟翼形成间隙，在机械上不将所述襟翼的动作与所述阻流板的动作相联系，而将所述机翼设置在大升力构型中；以及通过使所述襟翼向下偏转以及使所述阻流板向上偏转，在机械上不将所述襟翼的动作与所述阻流板的动作相联系，而将所述机翼设置在减速器构型中，阻流板致动器与所述襟翼无关地移动所述阻流板，所述阻流板致动器释放施加到所述阻流板上的力，允许所述襟翼机械地接触和驱动所述阻流板。
本发明提供了一种飞行器机翼系统，包括：具有后缘的机翼；襟翼，设置成紧接所述机翼后缘且相对于所述机翼可被展开；第一致动器，有效地连接到所述襟翼以相对于所述机翼移动所述襟翼；阻流板，至少紧接所述襟翼设置，所述阻流板相对于所述机翼可被展开；以及第二致动器，有效地连接到所述阻流板以在第一操作模式期间驱动所述阻流板，所述第二致动器构造为在第二操作模式期间释放施加到所述阻流板上的驱动力的至少一部分，以允许所述襟翼机械地接触和驱动所述阻流板。
本发明的还涉及操作飞行器机翼系统的方法。一种用于操作飞行器的机翼系统的方法，包括：通过在第一操作模式期间使襟翼向下偏转以与所述机翼的后缘形成间隙，并且通过使阻流板向下偏转以与所述襟翼形成间隙，而将所述机翼设置在大升力构型中；以及在允许所述襟翼机械地接触和驱动所述阻流板的第二操作模式期间，释放施加到所述阻流板上的驱动力的至少一部分。在一实施例中，该方法包括以如下方式在大升力构型中设置机翼，即通过使襟翼向下偏转与机翼的后缘形成间隙，并且通过使阻流板向下偏转与襟翼形成间隙，而不将襟翼的动作与阻流板的动作在机械上相联系。该方法可进一步包括在减速器构型中如下设置机翼，即通过使襟翼向下偏转以及使阻流板向上偏转，而再一次不将襟翼的动作与阻流板的动作在机械上相联系。在本发明的再一个方面中，该方法可进一步包括控制电磁信号通过非机械的连接从控制器到连接襟翼的第一致动器及连接阻流板的第二致动器。
附图说明
图1A和1B说明了根据现有技术形成的具有襟翼的机翼；
图2是具有可致动且在机械上没有彼此联系的襟翼和阻流板的机翼的部分示意性的横截面图；
图3A和3B示出了图2所示的机翼，其襟翼展开到大升力位置；
图4示出了图2所示的机翼，其阻流板展开到减速器且/或滚动控制位置；
图5示出了图2所示的机翼，其襟翼和阻流板展开到减速器构型；
图6是包括控制器和与参考图2-5描述的那些机翼构型大致相似的机翼的飞行器的部分示意性的俯视图。
具体实施方式
本发明内容描述了用于控制飞行器襟翼和阻流板的系统和方法，包括襟翼的致动与阻流板的致动机械上无关的构型。在随后的描述和图2-6中说明了某些特定的细节，以彻底理解本发明的各种实施例。众所周知的结构、系统和与系统相关的方法没有被详细显示或描述，以避免不必要的使本发明的各种实施例的描述模糊。此外，本领域技术人员可理解本发明的附加的实施例没有下面描述的一些细节也可实现。
下面描述的本发明的许多实施例可采用这种形式的控制器，其包括计算机可执行的指令，包括由可编程的计算机执行，或者作为替换地，由非可编程的电子设备执行的程序。本领域技术人员将意识到本发明可被应用到计算机系统或并非如下所述的控制器。本发明在特定目的的计算机、控制器或数据处理器中实施，该特定目的的计算机、控制器或数据处理器被特定编程、设定或构造来执行一条或多条下面描述的计算机可执行的指令。相应地，控制器或其它计算机设备可包括被设定来执行计算机可执行的指令的各种数据处理器的任一种。相应于这些控制器的信息可呈现在任何合适的显示媒体上，包括CRT显示器或LCD。
图2是根据本发明实施例的用于控制飞行器升力和阻力的系统200的部分示意性的横截面图。在本实施例的一个方面中，系统200可包括具有上表面212和具有固定后缘211的下表面213的机翼210。襟翼220设置成紧接后缘211，并且阻流板230设置在上表面212上紧接襟翼220。阻流板230通过连接到阻流板230上的阻流板致动器231而可在不同的位置中移动。控制器201通过沿阻流板信号连接器233传送信号控制阻流板致动器231的致动。在本实施例的特殊方面中，该阻流板信号连接器233是非机械的连接器(例如，电缆、光缆、或其它设定来传送控制器201和阻流板致动器231之间的电磁信号的连接器)。控制器201可接收来自飞行员或其它飞行器操作者的操纵输入202，并且可进一步从一个或多个传感器205接收输入。操纵输入202可包括(但不限于)指令的襟翼设置、指令的阻流板设置(例如指令的减速器输入)和滚转角指令。传感器205可提供襟翼位置指示且/或襟翼偏转(例如任何襟翼展开到非指令设置的程度，特别是相对于邻近的襟翼)、且/或其它相关数据。基于来自飞行员且/或传感器205的输入，控制器201通过阻流板致动器231可指挥阻流板230的动作。
襟翼220可以与上面参考阻流板230的描述大致相类似的方式被致动和控制。相应地，系统200可包括用襟翼连接器222连接到襟翼220的襟翼致动器221。图2所示的截面图是穿过阻流板致动器231而不是穿过襟翼致动器221得到的，襟翼致动器221沿翼展方向与阻流板致动器231偏移，且相应地在图2中被显示为虚线。参考图3B下面提供了襟翼致动器221的进一步细节。襟翼致动器221也可通过襟翼信号连接器223(例如非机械连接器)连接到控制器201。相应地，控制器201可独立地控制阻流板致动器231和襟翼致动器221的动作来产生期望的机翼形状。在一些实施例中，襟翼220和阻流板230的动作可被控制器201协调，但是一个控制器的动作不依赖于另一个的动作，并且相应地襟翼220和阻流板230不需要通过可展开的机械联动装置而彼此连接。
图2示出了在巡航或中性位置时的襟翼220和阻流板230。在此位置，阻流板230和襟翼220的上表面与机翼的上表面212形成大致平滑的上轮廓214。襟翼220的下表面与机翼210的下表面213形成大致平滑的下轮廓215。
图3A示出了襟翼220和阻流板230展开到大升力构型的系统200。在此构型中，襟翼致动器221使襟翼220从显示在图2中的位置向下移动。阻流板致动器231使阻流板230相对于显示在图2中的位置向下移动以此来控制阻流板230和襟翼220之间间隙224的大小。在此位置，阻流板230引导气流越过机翼的上表面212，同时间隙224的大小控制从机翼下表面213到上表面的气流量，因此当空气流过襟翼220时其保持附在翼型表面上。间隙224可具有一定大小和位置，其可被选定为在襟翼220上产生最佳的或有条件的最佳流体流动。为了达到选定的间隙大小，控制器201可根据预定的基于襟翼220的位置的计划表操纵阻流板230移动。控制器201可从一个或多个传感器205(可包括襟翼位置传感器)接收襟翼位置的指示。
传感器205可被设置来检测襟翼位置，如上所述，和/或其它系统参数，包括襟翼偏转。襟翼偏转通常指的是襟翼的至少一端没有移动到其指令位置的情况。如果该情况被检测到，系统200可自动地阻止任何刚好位于受影响的襟翼前的阻流板230的运动。相应地，如果特定的襟翼220并不是一直移动到指令的向下展开状态，相关联的阻流板230可被阻止向下移动一定的量，这一移动量会导致襟翼220和阻流板230之间的机械干扰。
现在一起参考图2和图3A，襟翼致动器221可被启动来移动襟翼220返回到显示在图2中的位置。在正常操作期间，信号被传送到襟翼致动器221和阻流板致动器231，因此襟翼220和阻流板230退回而没有干扰彼此。在本实施例的一方面，系统200可被构造成允许此动作，即使因为一些原因退回信号没有被传送到阻流板致动器231。例如，阻流板致动器231可被“反驱动”，在该模式操作期间，当襟翼220移动到其退回位置时襟翼220与阻流板230物理接触且推动阻流板230到其退回位置。如果阻流板致动器231被液压驱动，其可包括释放值，其释放施加到阻流板230上的液压压力且允许阻流板230被反驱动而没有干扰阻流板致动器231。如果阻流板致动器231被机械驱动(例如通过导杆)，其可包括允许阻流板230被反驱动而不与阻流板致动器231发生干涉的离合器机构。在其它实施例中，其它类型的阻流板致动器可包括相应的释放机构。在这些实施例的任何一个中，此设置可减少或消除襟翼220和阻流板230之间的机械连接，在信号失败情况下不会使襟翼220受阻流板230的干扰。
图3B是机翼210的截面图，其在与图3A所示稍微不同的翼展方向上截取，以致于穿过襟翼致动器221。襟翼致动器221可包括一个或多个连接到襟翼220的机械连接器。如上说述，襟翼致动器221和襟翼220的相关连接在机械上与阻流板致动器231和阻流板230的相关连接无关(图2)。
图4是根据本发明实施例的具有阻流板230向上展开的在与显示在图2中大致上相同的截面位置的机翼210的截面图。在本实施例的一方面中，在飞行器飞行期间阻流板230可被向上设置以作为减速器(或其它飞行器控制设备)，同时襟翼220保持在巡航或中性位置。相应地，位于飞行器纵向中心线的相对两侧的阻流板230可被展开同样的量来提供空气动力减速效应，而不会产生偏航或侧滚力矩。在其它实施例中，位于飞行器纵向中心线一侧的阻流板230可被展开，同时位于飞行器中心线相对侧的阻流板230可保持未展开，或可被展开到较小的程度，来产生帮助飞行员翻转飞行器的偏航和/或侧滚力矩。
图5是机翼210的截面图，其中襟翼220设置在大升力构型中，并且阻流板230设置在减速器或地面阻流板构型中。襟翼和阻流板设置的组合可用于在降落操纵期间飞行器接触到地面后立即减小飞行器速度和在地的空气动力升力。襟翼和阻流板设置的相似组合可用于在被拒绝的起飞操纵中减小飞行器速度和在地的空气动力升力。相应地，襟翼220和阻流板230可沿相反方向被展开来产生减速效应，同时襟翼220被延伸。
图6为具有机翼210的飞行器603的等比示意图，每个机翼包括多个与如上所述大致相似的襟翼220和阻流板230。飞行器603可进一步包括飞行甲板604，操纵输入202可从飞行甲板604被引导到控制器201。控制器201然后可以对称的方式(例如提供统一的大升力和减速效应)且/或非对称的方式(提供侧滚且/或偏航力矩)引导信号到襟翼220和阻流板230如上所述。
在图6所示的实施例的具体方面中，控制器201可包括接收操纵输入202和来自传感器205的信号的接收部606。控制器201还可包括可以协同方式操作来引导合适的信号到襟翼220和阻流板230的襟翼控制部607和阻流板控制部608。
取决于具体的安装方式，各个阻流板230可被相同的或不同类型的致动器致动。例如，飞行器603可包括14个阻流板(由标号230a-230n区别)，一些阻流板(例如阻流板230d、230e、230j和230k)由电气致动器驱动，并且剩余的阻流板被液压致动器驱动。至少阻流板230的一些(至少在一个实施例中为全部)可从邻近的襟翼220被机械地连接，且相应地可具有简化致动配置，如上所述。此外，简化的机械配置(例如分开地致动的襟翼和阻流板连接)可以更容易地安装在机翼210的厚度内。相应地，在一些传统配置中覆盖阻流板和襟翼之间的机械连接器的整流罩可除去，这减小了飞行器重量和阻力。
在具体实施例中，控制器201提供的功能可被分摊。相应地，控制器201可包括中心或联合控制器(例如设置在飞行器603的机身中)和多个局部控制器(例如，一个局部控制器201b与每个襟翼致动器和每个阻流致动器相关)。中心控制器可以是通过数据总线传送数字信号的数字控制器。每个局部控制器可包括数字/模拟转换器来提供模拟信号到相应的致动器。
上述系统的实施例的另一特征在于，在需要大升力的飞行器动作期间(例如起飞和降落期间)，可在每个翼展方向包括单独的襟翼220来提供大升力性能。此配置的优点在于具有单独向前间隙224的单独襟翼220与双槽襟翼相比具有更少部件，且相应地除了具有更轻重量之外可更简单和较少花费来安装和维护。相应地，此配置可减少飞行器购买和操作成本。
上述系统的实施例的另一特征在于，其可包括分开的致动器用于阻流板230和襟翼220。在此实施例的另一方面中，在正常操纵中一个设备(例如襟翼220)的致动并不影响其它(例如阻流板230)的动作。这不同于一些现有设备，在现有设备中至少阻流板的部分动作与襟翼的动作在机械上直接联系。相应地，不同于这些传统系统，本发明的实施例可通过运行襟翼220和阻流板230展开到任何位置而不要求其它设备的相应动作来提供增加的操作灵活性。
在一些实施例中，襟翼220和阻流板230的操作可被协同，例如该协同产生空气动力学上的有益效果。在这些实施例中，可编程控制器201可通过与阻流板致动器231和襟翼致动器221的电磁连接提供必要协同。这种“通过电线传送(fly by wire)”的配置的优点在于可减少机翼系统的机械复杂性，反过来又减少生产系统的初始成本和随着时间的推移维护系统的成本。因此，操作包括机翼系统的飞行器可比操作现有飞行器系统更有效。
上述特征的另一优点在于减少部件不仅可导致制造和维护成本的减少而且可导致整个飞行器重量的减少。有助于此优点的附加因素在于系统不需要包括柔性面板来密封阻流板和机翼之间的间隙。特别地，阻流板可被设置成移动足够控制阻流板的间隙尾的量，而没有大到使阻流板向前的间隙(例如阻流板和机翼的后缘之间)必须被密封的量。通过消除对柔性面板需要，此配置可进一步减少飞行器的部件数、成本和重量。当飞行器的重量减少，整个操作成本(例如燃料成本)可被减少，这导致与系统有关的进一步效率。
从如上的描述可意识到本发明的具体实施例为了说明的目的在此已被描述，但是在未脱离本发明的精神和范围的前提下可以进行各种修改。在具体实施例的上下文中描述的本发明的各方面可在其它实施例中被组合或去掉。尽管与本发明的某些实施例有关的优点已在这些实施例的上下文中被描述，其它实施例也可展现这些优点。此外，任一前述的实施例均非必需展现这些优点才落入本发明的范围。相应地，本发明仅由所附的权利要求限定。

Claims (30)

1.一种飞行器机翼系统，包括：
具有后缘的机翼；
襟翼，设置成紧接所述机翼后缘且在第一襟翼位置和第二襟翼位置之间相对于所述机翼可展开；
第一致动器，有效地连接到所述襟翼以在所述第一襟翼位置和第二襟翼位置之间移动所述襟翼；
阻流板，至少紧接所述襟翼设置，所述阻流板可在至少三个位置中移动，包括第一阻流板位置，其中所述阻流板与所述机翼的上表面形成连续的轮廓；第二阻流板位置，其中所述阻流板从所述第一阻流板位置向下偏转；以及第三阻流板位置，其中所述阻流板从所述第一阻流板位置向上偏转；以及
第二致动器，有效地连接到所述阻流板以在所述第一、第二和第三阻流板位置中移动所述阻流板，而在机械上与所述襟翼的动作无关，
其中所述第二致动器被构造为与所述襟翼无关地移动所述阻流板，并且其中所述第二致动器被构造为释放施加到所述阻流板上的力，允许当所述襟翼从所述第二襟翼位置移动到所述第一襟翼位置时所述阻流板通过直接机械接触襟翼而驱动从第一阻流板位置到第二阻流板位置。
2.如权利要求1所述的系统，其中所述第二致动器连接到所述机翼且包括连接到所述阻流板的连接器，且其中所述机翼不包括收容所述连接器的整流罩。
3.如权利要求1所述的系统，进一步包括有效地连接到所述第一和第二致动器的控制器，其中所述控制器被构造成引导所述阻流板在巡航期间到达所述第一阻流板位置，在起飞和降落期间到达所述第二阻流板位置，在减速和侧滚动作期间到达所述第三阻流板位置。
4.如权利要求1所述的系统，其中所述襟翼机械连接到所述机翼，且所述阻流板机械连接到所述机翼，但是所述阻流板不是机械地直接连接到所述襟翼。
5.如权利要求1所述的系统，进一步包括有效地连接到所述第一和第二致动器来协调所述第一和第二致动器的动作的控制器。
6.如权利要求1所述的系统，进一步包括用非机械连接器有效地连接到所述第一和第二致动器来协调所述第一和第二致动器的动作的控制器。
7.如权利要求1所述的系统，其中所述机翼具有后缘和弦线并且其中所述襟翼是设置成在所述弦线处紧接所述机翼后缘的单独襟翼。
8.一种用于控制飞行器机翼的系统，包括：
控制器，有效地与襟翼致动器和阻流板致动器连接，所述控制器被编程具有指令以：
通过引导所述襟翼致动器使所述襟翼向下偏转而与所述机翼的后缘形成间隙，以及通过引导所述阻流板致动器使所述阻流板向下偏转而与所述襟翼形成间隙，在机械上不将所述襟翼的动作与所述阻流板的动作相关联，而将所述机翼设置在大升力构型中；以及
通过引导所述襟翼致动器使所述襟翼向下偏转，以及通过引导所述阻流板致动器使所述阻流板向上偏转，在机械上不将所述襟翼的动作与所述阻流板的动作相关联，而将所述机翼设置在减速器构型中，
阻流板致动器被构造为与所述襟翼无关地移动所述阻流板，并且所述阻流板致动器被构造为释放施加到所述阻流板上的力，允许所述襟翼机械地接触和驱动所述阻流板。
9.如权利要求8所述的系统，其中所述控制器构造为接收对应于所述襟翼的位置的信号，并且构造为根据阻流板和襟翼的位置的计划表来引导所述阻流板致动器。
10.如权利要求8所述的系统，其中所述控制器构造为接收对应于所述襟翼的位置的信号，并且构造为如果所述襟翼未能移动到命令位置至少限制所述阻流板的动作。
11.如权利要求8所述的系统，其中所述控制器被编程具有指令以独立于襟翼的位置而移动所述阻流板。
12.一种用于操作飞行器机翼系统的方法，包括：
通过使所述襟翼向下偏转以与所述机翼的后缘形成间隙，以及通过使所述阻流板向下偏转以与所述襟翼形成间隙，在机械上不将所述襟翼的动作与所述阻流板的动作相联系，而将所述机翼设置在大升力构型中；以及
通过使所述襟翼向下偏转以及使所述阻流板向上偏转，在机械上不将所述襟翼的动作与所述阻流板的动作相联系，而将所述机翼设置在减速器构型中，阻流板致动器与所述襟翼无关地移动所述阻流板，所述阻流板致动器释放施加到所述阻流板上的力，允许所述襟翼机械地接触和驱动所述阻流板。
13.如权利要求12所述的方法，其中将所述机翼设置在大升力构型中包括通过非机械连接器引导非机械信号从控制器到连接所述襟翼的第一致动器和连接所述阻流板的第二致动器。
14.如权利要求12所述的方法，进一步包括通过将所述襟翼设置在中性位置以及设置所述阻流板与所述机翼的上表面来形成连续的轮廓，在机械上不将所述襟翼的动作与所述阻流板的动作相联系，而将所述机翼设置在巡航构型中。
15.如权利要求12所述的方法，进一步包括通过使位于飞行器纵向中心线一侧的阻流板以第一量向上偏转，并且引导位于飞行器中心线相对侧的阻流板以第二量偏转或不偏转，而控制所述飞行器的侧滚动作。
16.如权利要求12所述的方法，进一步包括从襟翼位置传感器接收所述襟翼的位置的指示，并且根据所述襟翼位置和阻流板位置的计划表使所述阻流板向下偏转。
17.如权利要求12所述的方法，进一步包括：
通过将所述襟翼设置在中性位置且设置所述阻流板与所述机翼的上表面形成连续的轮廓，在机械上不将所述襟翼的动作与所述阻流板的动作相联系，而将所述机翼设置在巡航构型中；以及
通过使位于飞行器纵向中心线一侧的阻流板以第一量向上偏转，并且引导位于飞行器中心线相对侧的阻流板以比所述第一量少的第二量偏转或不偏转，而控制所述飞行器的侧滚动作。
18.一种飞行器机翼系统，包括：
具有后缘的机翼；
襟翼，设置成紧接所述机翼后缘且相对于所述机翼可被展开；
第一致动器，有效地连接到所述襟翼以相对于所述机翼移动所述襟翼；
阻流板，至少紧接所述襟翼设置，所述阻流板相对于所述机翼可被展开；以及
第二致动器，有效地连接到所述阻流板以在第一操作模式期间驱动所述阻流板，所述第二致动器构造为在第二操作模式期间释放施加到所述阻流板上的驱动力的至少一部分，以允许所述襟翼机械地接触和驱动所述阻流板。
19.如权利要求18所述的系统，其中所述襟翼在第一襟翼位置和第二襟翼位置之间可展开，并且其中所述阻流板在至少三个位置中可展开，包括第一阻流板位置，其中所述阻流板与所述机翼的上表面形成连续的轮廓；第二阻流板位置，其中所述阻流板从所述第一阻流板位置向下偏转；以及第三阻流板位置，其中所述阻流板从所述第一阻流板位置向上偏转。
20.如权利要求18所述的系统，其中在第一操作模式期间所述襟翼和阻流板在机械上彼此独立地运动。
21.如权利要求18所述的系统，进一步包括用第一非机械连接器有效连接到所述第一致动器的控制器，并且其中所述控制器用第二非机械连接器被有效连接到所述第二致动器。
22.如权利要求18所述的系统，其中第二致动器包括液压致动器，并且其中所述液压致动器包括在第二模式的操作期间至少限制施加到所述阻流板上的力的安全阀。
23.如权利要求18所述的系统，其中第二致动器包括机械致动器，并且其中所述机械致动器包括在第二模式的操作期间至少减小施加到所述阻流板上的力的离合器。
24.如权利要求18所述的系统，进一步包括有效地连接到所述第一和第二致动器来传送操作信号到所述第一和第二致动器的控制器，并且当操作信号没有传送到所述第二致动器时所述系统构造为进入第二模式。
25.如权利要求18所述的系统，进一步包括在第二操作模式期间用于限制施加到所述阻流板上的力的装置。
26.一种用于操作飞行器的机翼系统的方法，包括：
通过在第一操作模式期间使襟翼向下偏转以与所述机翼的后缘形成间隙，并且通过使阻流板向下偏转以与所述襟翼形成间隙，而将所述机翼设置在大升力构型中；以及
在允许所述襟翼机械地接触和驱动所述阻流板的第二操作模式期间，释放施加到所述阻流板上的驱动力的至少一部分。
27.如权利要求26所述的方法，其中将所述机翼设置到大升力构型中包括在第一操作模式期间偏转所述襟翼和阻流板且在机械上不将所述襟翼的动作与所述阻流板的动作相联系。
28.如权利要求26所述的方法，其中将所述机翼设置到大升力构型中包括通过第一非机械连接器引导第一信号到连接所述襟翼的第一致动器，并且通过第二非机械连接器引导第二信号到连接所述阻流板的第二致动器。
29.如权利要求26所述的方法，其中所述阻流板被液压致动器移动，并且其中所述方法包括使液压致动器的安全阀释放，以致在第二模式的操作期间至少减小施加到所述阻流板上的力。
30.如权利要求26所述的方法，其中所述阻流板被机械致动器移动，并且其中所述方法包括使机械致动器的离合器滑动，以致在第二模式的操作期间至少减小施加到所述阻流板上的力。
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CA2593915C (en) 2010-09-07
CA2706676A1 (en) 2006-08-10
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US20060175468A1 (en) 2006-08-10
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CN101115655A (zh) 2008-01-30
ATE467555T1 (de) 2010-05-15
WO2006084157A3 (en) 2007-04-12
JP5201997B2 (ja) 2013-06-05
CA2593915A1 (en) 2006-08-10
US7891611B2 (en) 2011-02-22
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US7338018B2 (en) 2008-03-04

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