公开(公告)号：WO2021248003A1

公开(公告)日：2021-12-09

申请号：PCT/US2021/035911

申请日：2021-06-04

Applicant: SAUDI ARABIAN OIL COMPANY ,  ARAMCO SERVICES COMPANY

Inventor： PARROTT, Brian ,  ABDELLATIF, Fadl

IPC: B64C9/14 ,  B64C21/02 ,  B64C39/02 ,  B64D1/00 ,  B64C39/10 ,  G01N1/22 ,  G01N1/00 ,  G01N33/00 ,  B64C3/14 ,  B64C21/08 ,  B64C2201/021 ,  B64C2201/027 ,  B64C2201/028 ,  B64C2201/104 ,  B64C2201/12 ,  B64C39/024 ,  G01N1/2273 ,  G01N2001/2279 ,  G01N33/0004 ,  G01N33/0009

Abstract: A fixed wing drone comprises an air channel embedded therein. The air channel has an upstream an air inlet. A microcontroller mounted within the drone is configured to control navigation of the drone. An air scoop having a section positioned adjacent the inlet to the air channel is adjustable between a first position to capture and divert air into the inlet and thereby to air channel and a second position to block air flow into the air inlet. The air scoop is positioned to divert air flow into the air channel and to the gas sensor during forward flight of the drone. In one embodiment, the fixed wing drone comprises an aircraft having a fuselage and at least two wings. In another embodiment, the fixed wing drone has a flying wing construction, that is, is a tailless design.

公开(公告)号：WO2020174084A1

公开(公告)日：2020-09-03

申请号：PCT/EP2020/055279

申请日：2020-02-28

Applicant: AIRBUS OPERATIONS GMBH

Inventor： BENSMANN, Stefan ,  ERBAN, Marcus ,  FEES, Martin

IPC: B64C3/50 ,  B64C9/22 ,  B64C9/14

Abstract: A wing leading-edge device (2, 42) is proposed, which comprises a slat body (4, 42) having a front side (6) with a forward skin (8) and a back side (10) with a rearward skin (12), and at least a drive arrangement (14) having at least one lug (18, 20) and a slat track (16), wherein the back side (10) extends between an upper spanwise edge (26) of the forward skin (8) and a lower spanwise edge (28) of the forward skin (8), wherein the back side (10) is defined by a continuously curved profile contour for receiving a fixed leading edge (32), wherein the at least one lug (18, 20) is at least partially arranged between the back side (10) and the front side (6), and wherein the slat track (16) is coupled with the at least one lug (18, 20). The connection points to the slat body (4, 42) are shifted far forward to improve the load introduction and reduce moments acting on the drive mechanism.

公开(公告)号：WO2006056160A1

公开(公告)日：2006-06-01

申请号：PCT/DE2005/002003

申请日：2005-11-09

Applicant: EADS DEUTSCHLAND GMBH ,  LORKOWSKI, Thomas ,  GROHMANN, Boris

Inventor： LORKOWSKI, Thomas ,  GROHMANN, Boris

IPC: B64C3/50 ,  B64C9/14

CPC classification number: B64C3/50 ,  B64C9/14 ,  B64C2009/143

Abstract: Eine Anordnung zur Minderung des aerodynamischen Lärms an einem Zusatzflügel (1; 11) eines Flugzeugs, der an einen Hauptflügel (2) angelenkt und unter Freigabe eines Spaltbereichs (9) zwischen dem Hauptflügel (2) und dem Zusatzflügel (1 ) ausfahrbar ist, umfassend eine Trennfläche (6; 7), die bei ausgefahrenem Zusatzflügel (1 ; 11 ) in den Spaltbereich (9) verlagerbar ist und sich zumindest teilweise entlang einer Trennstromlinie (13) zwischen einem Wirbelströmungsgebiet (12) und einer Spaltströmung (10) der im Spaltbereich (9) zwischen Zusatzflügel (1 ; 11 ) und Hauptflügel (2) strömenden Luft erstreckt. Erfindungsgemäß ist die Trennfläche (6; 7) eine n-stabile Fläche, die mittels Aktuatoreinrichtung (3; 3a, 3b; 4; 4a, 4b; 5; 5a, 5b) zwischen mindestens einem der stabilen Zustände und mindestens einem weiteren Zustand verlagerbar ist.

Abstract translation: （1; 11）包括附连到主翼（2）被铰接和间隙区域用于在飞行器的辅助翼降低空气动力噪音的装置，（9）是主翼（2）和附加的翼型件（1），包括之间伸展 一个分离面（6; 7），当所述附加叶片（1; 11）是在该间隙区域（9）移位并且沿着涡流流动区域（12）和在间隙区域中的间隙流（10）之间的间隔流动管线（13）至少部分地延伸 （1; 11）（9）所述附加翼与主翼（2）之间延伸的流动空气。 根据本发明的分离面（6; 7）是n稳定的表面，通过致动器装置的装置（3; 3A，3B; 4; 4A，4B，图5，图5a，5b）是稳定状态中的至少一个和至少一个另外的状态之间移动 ，

公开(公告)号：WO2016125094A1

公开(公告)日：2016-08-11

申请号：PCT/IB2016/050551

申请日：2016-02-03

Applicant: BOMBARDIER INC. ,  SHORT BROTHERS PLC

Inventor： GALLIEN, Daniel ,  HUMPHRIS, Russell Coln ,  LE, Dung Van ,  KHO, Cedric Ngo ,  TATOSSIAN, Charles

IPC: B64C9/14 ,  B64D15/04

CPC classification number: B64C9/14 ,  B64D15/04

Abstract: Apparatus for obstructing air flow through an aperture in an aircraft wing where a movable anti-icing duct extends through the aperture are disclosed. An exemplary apparatus comprises a base member (40) configured to be secured to the duct and a first seal member (42) configured to obstruct air flow through the aperture. The first seal member comprises a proximal portion (42A) connected to the base member and a distal portion (42B) configured to movably contact an inner surface of a skin of the wing. The use of such apparatus may reduce the amount of leakage flow from the high pressure lower wing surface to the low pressure upper wing surface through the aperture and thereby reduce the loss of lift associated with such leakage flow.

Abstract translation: 公开了用于阻挡空气流过飞机机翼中的孔的装置，其中可移动防冰导管延伸穿过孔。 示例性装置包括构造成固定到管道的基部构件（40）和被配置为阻止空气流过孔的第一密封构件（42）。 第一密封构件包括连接到基座构件的近端部分（42A）和构造成可移动地接触机翼的皮肤的内表面的远端部分（42B）。 使用这种装置可以减少通过孔径从高压下翼面到低压上翼面的泄漏量，从而减少与这种泄漏流相关的升力损失。

公开(公告)号：WO2007054150A1

公开(公告)日：2007-05-18

申请号：PCT/EP2006/009067

申请日：2006-09-18

Applicant: AIRBUS DEUTSCHLAND GMBH ,  RECKZEH, Daniel ,  SCHLIPF, Bernhard, Rainer ,  ANDREANI, Luc ,  SUTCLIFFE, Mark

Inventor： RECKZEH, Daniel ,  SCHLIPF, Bernhard, Rainer ,  ANDREANI, Luc ,  SUTCLIFFE, Mark

IPC: B64C9/14 ,  B64C9/18 ,  B64C21/02

CPC classification number: B64C9/14 ,  B64C9/18 ,  Y02T50/32 ,  Y02T50/44

Abstract: Eine fortschrittliche Flügelhinterkante am Flügel eines Flugzeugs, mit einem Flügel (1), einer an der Hinterkante des Flügels (l) angeordneten, in Spannweitenrichtung verlaufenden, auf unterschiedliche Ausschläge einstellbaren Klappe (4) , einer an der Oberseite zwischen dem Flügel (1) und der Klappe (4) angeordneten schwenkbar beweglichen Abdichtklappe (7) und eine an der Unterseite zwischen dem, Flügel (1) und der Klappe (4) angeordneten schwenkbar beweglichen Belüftungsklappe (5). Erfndungsgemäß ist es vorgesehen, dass die Klappe (4) sowohl über positive Klappenausschläge nach unten als auch negative Klappenausschläge nach oben einstellbar ist, wobei für eine Nutzung der Klappe (4) als Steuerklappe mit Einstellungen der Klappe zwischen negativen und kleinen positiven Klappenausschlägen das Flügelprofil an der Oberseite durch die Abdichtklappe (7) und an der Unterseite durch die Belüftungsklappe (5) geschlossen ist und für eine Nutzung der Klappe (4) als auftriebserhöhende Klappe mit Einstellungen der Klappe (4) zwischen kleinen positiven und großen positiven Klappenausschlägen die Belüftungsklappe (5) eine Strömung von der Unterseite des Flügels (1) zur Oberseite der Klappe (4) freigibt und die Abdichtklappe (7) zur Freigabe eines Abstroms von der Oberseite der Klappe (4) um einen vorgegebenen Spalt entfernt wird.

Abstract translation: 在飞机的机翼设置一个先进的后缘，具有翼（1），在翼展方向延伸的一个在机翼（L）的后缘，可调节到不同的偏转襟翼（4），一个在翼之间的上侧（1）和 翼片（4）枢转地设置活动密封翼片（7），并在，叶片（1）和（4），其布置枢转地移动通风阀片翼片之间的底部（5）。 Erfndungsgemäß意图是翼片（4）是可调节的向上均通过向下正襟翼偏转或负折板，其中所述用于使用所述襟翼（4），为具有负和小的正瓣之间的翼片的调节的控制襟翼的偏转翼型 上侧由密封翼片（7）和由所述通风阀片的底面（5）关闭，使用的活盖（4）作为升力襟翼与小的正，和大的正襟翼偏转，通风阀片之间的折片（4）的调整（5 ）从机翼的下侧流（1）（在翼片4）的版本和用于释放的流出物（从盖4的上密封折片（7）的上侧）通过预定的间隙去除。

公开(公告)号：WO2007001735A3

公开(公告)日：2007-02-22

申请号：PCT/US2006021499

申请日：2006-06-02

Applicant: BOEING CO ,  HARRIGAN JEFFERY S ,  BEAUFRERE HENRY L

Inventor： HARRIGAN JEFFERY S ,  BEAUFRERE HENRY L

IPC: B64C9/00 ,  B64C9/14 ,  B64C9/34

CPC classification number: B64C9/146 ,  B64C9/34 ,  B64C13/16 ,  Y02T50/32 ,  Y02T50/44

Abstract: Aerospace vehicle yaw generating systems and associated methods are disclosed herein. One aspect of the invention is directed toward a yaw generating system that can include an aerospace vehicle having a fuselage (101) with a first portion (111) and a second portion (112) . The system can further include a movable control surface (142a, 142b) coupled to the fuselage and extending generally in a horizontal plane . The control surface can be movable to a deflected position in which the control surface can be positioned to create a flow pattern proximate to the fuselage when the aerospace vehicle is located in a flow field. The flow pattern can be positioned to create a pressure differential between the first portion (111) of the fuselage and the second portion (112) of the fuselage. The first and second portions can be located so that the pressure differential produces a yawing moment (Rmr) on the aerospace vehicle .

Abstract translation: 本文公开了航空航天车辆偏航发生系统及相关方法。 本发明的一个方面涉及一种偏航生成系统，其可以包括具有机身（101）的航空航天车辆，其具有第一部分（111）和第二部分（112）。 该系统还可以包括耦合到机身并且大致在水平面上延伸的可移动控制表面（142a，142b）。 控制表面可以移动到偏转位置，在偏转位置，当航空航天飞行器位于流场中时，控制表面可以被定位以产生靠近机身的流动模式。 可以将流动图案定位成在机身的第一部分（111）和机身的第二部分（112）之间产生压力差。 第一和第二部分可以被定位成使得压力差在航空航天器上产生偏转力矩（Rmr）。

公开(公告)号：WO2006108579B1

公开(公告)日：2007-01-11

申请号：PCT/EP2006003212

申请日：2006-04-07

Applicant: AIRBUS GMBH ,  BENDER KLAUS ,  BOETTGER OLE

Inventor： BENDER KLAUS ,  BOETTGER OLE

IPC: B64C9/14

CPC classification number: B64C9/20 ,  B64C9/02 ,  B64C9/18 ,  B64C2009/143 ,  Y02T50/44

Abstract: The present invention relates to a device for adjusting the lift characteristics of an aircraft with a high lift device (2) that is movably attachable to a wing element (1) and that comprises at least one slot covering device (3; 4), wherein the at least one slot covering device (3; 4), is movably attachable to the wing element (1). The slot covering device (3; 4) is designed to regulate the size of a slot (7) between the wing element (1) and the high lift device (2).

Abstract translation: 本发明涉及一种用于通过具有可移动地附接到翼元件（1）并且包括至少一个狭槽覆盖装置（3; 4）的高升降装置（2）来调节飞行器的提升特性的装置，其中 所述至少一个狭槽覆盖装置（3; 4）可移动地附接到所述翼元件（1）。 狭槽覆盖装置（3; 4）被设计成调节翼元件（1）和高升降装置（2）之间的狭槽（7）的尺寸。

公开(公告)号：WO2019203673A1

公开(公告)日：2019-10-24

申请号：PCT/RO2019/000011

申请日：2019-04-11

Applicant: SABIE, Razvan

Inventor： SABIE, Razvan

IPC: B64C29/00 ,  B64C9/14 ,  B64C21/04 ,  B64C39/00 ,  B64C39/08 ,  B64C11/00

Abstract: A personal flight apparatus with vertical take-off and landing conceived as a biplane apparatus constituted by two distinct parts articulated there between, the first distinct part consisting of the cockpit (1), which is hinged to the second part of the latter, which is formed of the wings assembly (6),the cockpit 1 being attached to the wings assembly (6) by two hinges (3) fixed in the upright central vertical supports (7) of the wings, and in this way the cockpit having a limited swing possibility inside of the wings support structure which in turn they are provided with four propellers (9), of ducted type and driven by electric engines (20) disposed two on the top wing and two on the bottom wing, thus forming a kind of quadcopter, the duct (10) of each propeller being provided on the inlet lip with an annular ejection slit (11), and the electrical energy required to operate the apparatus is provided by the batteries (14) placed under the pilot's seat which through the speed regulators transmit the electric energy to the engines, the entire operation of the apparatus being managed by means of a flight computer (17) disposed in the central part of the upper wing of the biplane, and the taking off being made with the wings and the engines vertically oriented, the flight apparatus being laid on the ground by means of a landing gear (15) fixed in the wing extremities, the flight apparatus taking off as a quadcopter, and the transition to the cruise flight is made by reducing the angle of incidence of the wings, this angle decreasing naturally due to the increased resistance to advancement of the wings concurrently with the speed of translation of the flight apparatus, and in the meantime the cockpit (1) remains in a vertical position due to its lower center of gravity and due to the joints (3) which allow it to rotate relative to the wings assembly (6) and the landing is made similarly to a quadcopter, slowing down the speed leading to increasing the incidence angle of the wings until they return to the vertical plane required for landing.

公开(公告)号：WO2018083077A1

公开(公告)日：2018-05-11

申请号：PCT/EP2017/077853

申请日：2017-10-31

Applicant: AIRBUS OPERATIONS LIMITED

Inventor： BLADES, Paul

IPC: B64C23/00 ,  B64C9/18 ,  B64C9/02 ,  B64C1/14 ,  B64C7/00 ,  B64C9/14

Abstract: The present invention is concerned with actuating aircraft components to tailor their configuration to achieve improved performance in one or more flight phases. In general terms, the invention provides a method and system for actuating an aircraft component comprising an actuating material in which an actual deformation change undergone by the actuating material in response to an activation input signal is determined by analysis of an output signal generated by the actuating material in response to the actual deformation. A first aspect of the invention provides a method of actuating an aircraft component, at least a portion of the aircraft component comprising an actuating material which undergoes deformation in response to the application of an electrical signal thereto, and which generates an electrical signal in response to a deformation of the actuating material, the method comprising the steps of: applying an activation input signal to the actuating material of the aircraft component, the activation input signal corresponding to a desired deformation of the actuating material, the actuating material of the aircraft component undergoing an actual deformation in response to the activation input signal; and generating an output signal representative of the actual deformation of the actuating material.

Abstract translation: 本发明涉及致动飞行器部件以调整其配置以在一个或多个飞行阶段实现改进的性能。 总的来说，本发明提供了一种用于致动包括致动材料的飞行器部件的方法和系统，其中响应于致动输入信号的致动材料经历的实际变形是通过分析致动输出信号产生的输出信号来确定的 材料响应于实际变形。 本发明的第一方面提供了一种致动飞机部件的方法，所述飞机部件的至少一部分包括致动材料，所述致动材料响应于向其施加电信号而经历变形，并且响应于所述致动材料而产生电信号 所述方法包括以下步骤：向所述飞机部件的所述致动材料施加激活输入信号，所述激活输入信号对应于所述致动材料的期望变形，所述飞行器部件的所述致动材料经历 响应于激活输入信号的实际变形; 并产生表示致动材料的实际变形的输出信号。

公开(公告)号：WO2008057065A2

公开(公告)日：2008-05-15

申请号：PCT/US2006/029092

申请日：2006-07-26

Applicant: THE BOEING COMPANY ,  SHMILOVICH, Arvin ,  YADLIN, Yoram ,  CLARK, Roger, W.

Inventor： SHMILOVICH, Arvin ,  YADLIN, Yoram ,  CLARK, Roger, W.

IPC: B64C9/14

CPC classification number: B64C9/16 ,  B64C9/22 ,  B64C21/025 ,  B64C2230/04 ,  B64C2230/06 ,  B64C2230/18 ,  Y02T50/166 ,  Y02T50/32 ,  Y02T50/44

Abstract: A system and method for generating lift provided by a multi-element aircraft wing are provided. The system includes a main wing element, a slat interconnected to the main wing element, and a flap interconnected to the main wing element. The system also includes at least one port defined in at least one of the slat, main wing element, and flap. In addition, the system includes at least one fluidic device operable to regulate fluid flow into and out of the at least one port to control boundary layer flow over at least one of the slat, main wing element, and flap.

Abstract translation: 提供了一种用于产生由多元件飞机机翼提供的升降机的系统和方法。 该系统包括主翼元件，与主翼元件相互连接的板条以及与主翼元件互连的翼片。 该系统还包括限定在板条，主翼元件和翼片中的至少一个中的至少一个端口。 此外，该系统包括至少一个流体装置，其可操作以调节进入和离开至少一个端口的流体流动，以控制边界层在板条，主翼元件和翼片中的至少一个上的流动。