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公开(公告)号：WO2017180392A1
公开(公告)日：2017-10-19
申请号：PCT/US2017/026146
申请日：2017-04-05
发明人： AL-SABAH, Nasser M.
IPC分类号： B64C3/38 , B64C3/34 , B64C9/00 , B64C9/32 , B64C13/00 , B64C13/20 , B64C39/02 , B64D15/00 , B64D27/02 , B64D27/14
CPC分类号： B64C3/38 , B64C1/26 , B64C3/34 , B64C5/06 , B64C9/00 , B64C9/326 , B64C13/00 , B64C13/20 , B64C39/024 , B64C2201/021 , B64C2201/048 , B64C2201/063 , B64C2201/104 , B64C2201/126 , B64C2201/141 , B64C2201/146 , B64C2201/16 , B64C2201/165 , B64C2211/00 , B64D15/00 , B64D27/02 , B64D27/14 , B64D27/20 , B64D37/00 , B64D39/00 , B64D47/08 , Y02T50/32
摘要： The modular aircraft system includes a single fuselage (10) having a permanently installed empennage (12) and plural sets of wing modules (46a, 46b, 66a, 66b, 68a, 68b) and engine modules (56, 60, 64), with each wing and engine module optimized for different flight conditions and missions. The fuselage (10) and each of the modules are configured for rapid removal and installation of the modules to minimize downtime for the aircraft. Short wings (46a, 46b) having relatively low aspect ratio are provided for relatively high speed flight when great endurance and/or weight carrying capacity are not of great concern. Long wings (68a, 68b) having high aspect ratio are provided for longer range and endurance flights where speed is not absolutely vital. A medium span wing module (66a, 66b) is also provided. Turboprop (56), single turbojet (60), and dual turbojet (64) engine modules are provided for installation depending upon mission requirements.
摘要翻译： 模块化飞行器系统包括具有永久安装的尾翼（12）和多组翼模块（46a，46b，66a，66b，68a，68b）的单个机身（10）和发动机模块 56,60,64），每个机翼和发动机模块针对不同的飞行条件和任务进行了优化。 机身（10）和每个模块被配置为用于模块的快速移除和安装以最小化飞行器的停机时间。 当高度耐力和/或重量承载能力不受重视时，提供具有相对低纵横比的短翼（46a，46b）用于相对高速飞行。 提供具有高纵横比的长翼（68a，68b）用于速度不是绝对重要的较长距离和耐力飞行。 还提供了中跨翼模块（66a，66b）。 根据任务要求，提供涡轮螺旋桨发动机（56），单涡轮喷气发动机（60）和双涡轮喷气发动机（64）发动机模块用于安装。
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公开(公告)号：WO2014199371A8
公开(公告)日：2014-12-18
申请号：PCT/IL2014/050513
申请日：2014-06-08
摘要： Two element aerofoils are provided, having an aerofoil chord, a primary element having a first leading edge and a first trailing edge, a secondary element having a second leading edge and a second trailing edge, a gap between the primary element and the secondary element, and an axial overlap between the first trailing edge and the second leading edge. The secondary element is deflectable with respect to the primary element about a fixed hinge point by a flap deflection angle. The secondary element is configured to operate in airbrake mode when deflected by a respective the flap deflection angle corresponding to a design airbrake deflection angle wherein to generate an airbrake drag. In at least some examples, the axial overlap is numerically greater than -0.5% of the aerofoil chord, at least for the design airbrake deflection angle. Also disclosed are methods for operating air vehicles, and methods for designing two-element aerofoils.
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3.发明申请
公开(公告)号：WO2014161794A1
公开(公告)日：2014-10-09
申请号：PCT/EP2014/056349
申请日：2014-03-28
申请人： ASTRIUM SAS
发明人： FERREIRA, Eugénio , SANTERRE, Angélique , FAURE, Benjamin , CHEVROLLIER, Samuel , PARPAITE, Pierre , FAVRE, Christophe
摘要： Aéronef spatial (10) adapté à un vol aéronautique comportant un corps et une voilure (15) définissant une surface portante inférieure ainsi que des moyens de contrôle d'attitude qui comporte un ou plusieurs volets (11) disposés sous sa surface portante inférieure et manoeuvrables entre une position rentrée et une position sortie inclinée de freinage aérodynamique lors de la transition d'une phase de vol spatial vers une phase de vol aéronautique de l'aéronef.
摘要翻译： 适用于航空飞行的太空飞机（10），包括主体和限定下翼面的翼（15），除了姿态控制装置之外，该姿态控制装置包括一个或多个百叶窗（11），该百叶窗（11）设置在其下翼面下面，并且可操作 在从空间飞行阶段到飞机航空飞行阶段的过渡期间，在收起位置和倾斜延伸位置之间进行空气动力学制动。
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公开(公告)号：WO2014155107A1
公开(公告)日：2014-10-02
申请号：PCT/GB2014/050958
申请日：2014-03-26
申请人： EADS UK LIMITED
发明人： ROLSTON, Stephen
摘要： Modern aircraft wings generally have a lower surface the rear part of which is concave over at least some of its length, for additional lift. Sometimes it is desirable to reduce the wing lift, for instance during turbulence. To this end the wing 1 has, located at least partly in or forward of this concave part and forward of the trailing edge, a spoiler device such as a deployable spoiler 20 operable to change between a configuration in which the surface is uninterrupted and one in which the device separates flow, so as to reduce local lift over the concave portion. An actuator 26 can be provided for deploying the spoiler, and an upper spoiler 40 can also be present, operated by the same or a separate actuator. Alternatively the spoiler device can include a flexible or deforming material 120 operable to protrude from the wing surface.
摘要翻译： 现代飞机机翼通常具有下表面，其后部的至少一部分在其长度上是凹的，用于额外的升力。 有时需要减少机翼升力，例如在湍流期间。 为此，机翼1至少部分地位于该凹部的前方或后方，并且位于后缘的前方，具有可展开扰流板20的扰流装置，其可操作以在表面不间断的结构和 该装置分离流动，以便减少凹部上的局部升力。 可以设置致动器26用于展开扰流器，并且上扰流器40也可以由相同或单独的致动器操作。 或者，扰流装置可以包括可操作以从机翼表面突出的柔性或变形材料120。
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公开(公告)号：WO2010094952A1
公开(公告)日：2010-08-26
申请号：PCT/GB2010/050253
申请日：2010-02-16
发明人： MATSUDA, Yukitaka
摘要： An aircraft wing load alleviation system incorporating a wing, a spoiler panel (14), a device (16, 17) which restricts circulation of air around a trailing edge of the spoiler and a control system. The spoiler panel is pivotally attached to the wing so that the spoiler panel can be rotated up from a lowered position to a raised position, thereby opening a void between the spoiler panel and the wing. The retractable device can be deployed from a retracted position to an extended position in which it restricts circulation of air around the trailing edge of the spoiler panel and into the void, thus reducing induced drag. The control system is configured to detect or predict an increase in the lift of the wing and rotate the spoiler panel to its raised position in response to a detected or predicted increase in the lift of the wing.
摘要翻译： 包括机翼，扰流板（14），限制扰流器后缘周围的空气循环的装置（16,17）和控制系统的飞机机翼负载减轻系统。 扰流面板枢转地附接到机翼，使得扰流板可以从降低的位置向上旋转到升高位置，从而在扰流板和机翼之间打开空隙。 可缩回装置可以从缩回位置展开到延伸位置，在该位置中，其限制了扰流板的后缘周围的空气的循环并进入空隙，从而减小了诱发的阻力。 控制系统被配置为检测或预测机翼的升力的增加，并且响应于机翼的升力的检测或预测的增加而将扰流板旋转到其升高位置。
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公开(公告)号：WO2022104273A1
公开(公告)日：2022-05-19
申请号：PCT/US2021/059540
申请日：2021-11-16
申请人： ZSM HOLDINGS LLC
摘要： During landing and rejected-takeoff flight phases, aircraft drag is a useful force to supplement braking and reduce stopping distance. During descents, aircraft drag is a useful force in steepening flight path angle and achieving higher rates of vertical descent speed at a trimmed forward flight speed in unaccelerated flight. A flight control system is detailed herein that deflects opposing flight control components in a symmetric fashion to increase aircraft drag, while maintaining controllability.
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公开(公告)号：WO2021122587A1
公开(公告)日：2021-06-24
申请号：PCT/EP2020/086206
申请日：2020-12-15
发明人： BISHOP, Benjamin
摘要： The present invention relates to the provision of a spoiler actuation apparatus for moving an aircraft spoiler. The spoiler is moveable between a stowed configuration and a deployed configuration. The spoiler actuation apparatus comprises a guide member (210), a rack (220) mounted on the guide member and slideable along a longitudinal axis of the guide member, and a gear (240) coupled to the rack, the gear arranged to move the spoiler (130) in response to sliding of the rack. The rack is held at a first position when the spoiler is in the stowed configuration. An actuator moves the rack from the first position to a second position along the longitudinal axis. When the rack is at the second position, the rack is operable to accelerate relative to the guide member away from the second position by an aerodynamic force acting on the spoiler.
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公开(公告)号：WO2016023056A1
公开(公告)日：2016-02-18
申请号：PCT/AT2015/050196
申请日：2015-08-11
申请人： FACC AG
发明人： SEIS, Michael , MEINDLHUMER, Martin
摘要： Steuerflächenelement (4) für ein Flugzeug, insbesondere Störklappe, mit einem eine luftumströmte Oberfläche (8) aufweisenden Faserverbundelement (3), mit einer Lagereinrichtung (5) zur beweglichen Lagerung des Faserverbundelements (3) an einem Strukturbauteil, und mit einer Versteifungsstruktur (9) zur Aussteifung des Faserverbundelements (3), wobei die Versteifungsstruktur (9) zumindest ein integral mit dem Faserverbundelement (3) gebildetes Versteifungselement aufweist, wobei die Versteifungsstruktur (9) ein zur Aufnahme von Hauptlasten eingerichtetes Primärversteifungselement (10) aufweist, welches mit zumindest einem zur Aufnahme von Nebenlasten eingerichteten Sekundärversteifungselement (11; 11', 11'') verbunden ist, wobeidas Faserverbundelement (3) zur integralen Ausbildung des Primärversteifungselements (10) eine Einbuchtung (15) aufweist.
摘要翻译： 凸轮构件（4）一种用于飞行器，尤其是扰流板，具有一个luftumströmte表面（8）纤维复合材料元件（3），与轴承装置（5），用于所述纤维复合材料元件（3）的结构部件的可动安装，并用一个加强结构（9） 对于所述纤维复合材料元件（3）的加强件，其中，所述加强结构（9）的至少一个一体地（3）具有形成加强元件的纤维复合材料元件，所述加强结构（9），其具有经装饰的用于接收主负载初级加固元件（10），其用于至少一个 连接，其中，所述纤维复合材料元件（3）的主要加强构件（10）的积分形成具有凹口（15）;接收由次要加强元件建立侧负载（11”，11' '11）。
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公开(公告)号：WO2014199371A1
公开(公告)日：2014-12-18
申请号：PCT/IL2014050513
申请日：2014-06-08
CPC分类号： B64C9/20 , B64C3/14 , B64C3/50 , B64C9/323 , B64C21/02 , B64C2003/147 , B64C2230/20 , Y02T50/12 , Y02T50/32
摘要： Two element aerofoils are provided, having an aerofoil chord, a primary element having a first leading edge and a first trailing edge, a secondary element having a second leading edge and a second trailing edge, a gap between the primary element and the secondary element, and an axial overlap between the first trailing edge and the second leading edge. The secondary element is deflectable with respect to the primary element about a fixed hinge point by a flap deflection angle. The secondary element is configured to operate in airbrake mode when deflected by a respective the flap deflection angle corresponding to a design airbrake deflection angle wherein to generate an airbrake drag. In at least some examples, the axial overlap is numerically greater than -0.5% of the aerofoil chord, at least for the design airbrake deflection angle. Also disclosed are methods for operating air vehicles, and methods for designing two-element aerofoils.
摘要翻译： 提供了两个元件翼型，其具有机翼弦，具有第一前缘和第一后缘的主要元件，具有第二前缘和第二后缘的次元件，主元件和次元件之间的间隙， 以及第一后缘和第二前缘之间的轴向重叠。 次要元件可通过翼片偏转角度相对于主要元件围绕固定铰链点偏转。 辅助元件被配置为在通过相应于对应于设计制动器偏转角的相应的翼片偏转角偏转时在空气制动器模式下操作，以产生空气制动阻力。 在至少一些示例中，轴向重叠数值上大于翼型翼弦的-0.5％，至少对于设计的制动偏转角。 还公开了用于操作空中飞行器的方法，以及用于设计双元件机翼的方法。
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10.发明申请
公开(公告)号：WO2009124025A1
公开(公告)日：2009-10-08
申请号：PCT/US2009/038917
申请日：2009-03-31
发明人： OYAMA, Hiroki
IPC分类号： B64C9/32
摘要： A speed brake apparatus reduces the airspeed of an aircraft by increasing aerodynamic drag. First and second brake panels are located on opposite sides of a portion of the aircraft, such as the fuselage, and are adapted to swing outward about a downstream hinge axis into deployed positions extending into the air stream. The panels are controlled by an operating device that includes a linear actuator. The actuator moves an operating head connected to a pair of toggle assemblies to convert linear movement of the operating head to the deployment and retraction movement of the brake panels.
摘要翻译： 速度制动装置通过增加空气动力学阻力来降低飞行器的空速。 第一和第二制动面板位于飞机的诸如机身的一部分的相对侧上，并且适于围绕下游铰链轴向外摆动到延伸到空气流中的展开位置。 面板由包括线性致动器的操作装置控制。 致动器移动连接到一对肘节组件的操作头，以将操作头的线性运动转换成制动面板的展开和缩回运动。
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