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1. 发明申请

WO2023041893A1 CAVITY ACOUSTIC TONES SUPPRESSION 审中-公开
公开(公告)号：WO2023041893A1
公开(公告)日：2023-03-23
申请号：PCT/GB2022/052156
申请日：2022-08-19
申请人： BAE SYSTEMS PLC
发明人： SPICER, Stephen John
IPC分类号： B64C21/02 , B60J7/22 , B64C23/06 , B64C25/00
摘要： A cavity system (300-600) is provided. The cavity system comprises a cavity (2) and a spoiler (304-604). The spoiler (304-604) comprises at least one plate (4) having a front surface and a rear surface, and an undulating edge. The spoiler (304-604) is positioned in the proximity of a leading edge (14) of the cavity (2), the leading edge (14) being relative to an actual or intended flow direction (3) of a fluid over the cavity (2), and the spoiler (304-604) is arranged with its longitudinal axis (1) perpendicular to or at an oblique angle to the actual or intended flow direction (3) such that the front surface faces towards the flow direction (3).

2. 发明申请

WO2021248003A1 IMPROVED GAS SENSING FOR FIXED WING DRONES USING SCOOPS 审中-公开
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
申请人： SAUDI ARABIAN OIL COMPANY , ARAMCO SERVICES COMPANY
发明人： PARROTT, Brian , ABDELLATIF, Fadl
IPC分类号： 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
摘要： 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.

3. 发明申请

WO2021007216A1 DRAG RECOVERY SCHEME USING BOUNDARY LAYER INGESTION 审中-公开
公开(公告)号：WO2021007216A1
公开(公告)日：2021-01-14
申请号：PCT/US2020/041018
申请日：2020-07-07
申请人： DZYNE TECHNOLOGIES INCORPORATED
发明人： PAGE, Mark, A.
IPC分类号： F02C7/04 , B64D33/02 , B64C21/02 , B64B1/24 , B64D27/00 , B64D29/00
摘要： Technologies are described herein for a drag recovery scheme using a boundary layer bypass duct system. In some examples, boundary layer air is routed around the intake of one or more of the engines and reintroduced aft of the engine fan in the nozzle duct in a mixer-ejector scheme. Mixer-ejectors mix the boundary layer flow to increase mass flow.

4. 发明申请

WO2020124172A1 AERODYNAMIC SEALS TO REDUCE AERODYNAMIC NOISE ASSOCIATED WITH AIRCRAFT HIGH LIFT CONTROL SURFACES 审中-公开
公开(公告)号：WO2020124172A1
公开(公告)日：2020-06-25
申请号：PCT/BR2018/000077
申请日：2018-12-20
申请人： EMBRAER S.A. , UNIVERSIDADE DE SÃO PAULO - USP
发明人： REIS, Danilo Cafaldo dos , SIMÕES, Leandro Guilherme Crenite , CARMO, Micael Gianini Valle do , COELHO, Eduardo Lobão Capucho , KLUG, Francisco Keller , CATALANO, Fernando Martini , SOUZA, Joabe Marcos de , PEREIRA, Lourenço Tércio Lima
IPC分类号： B64C21/02
摘要： Aircraft wings and aircraft comprising the same include at least one high-lift system(e.g., a high-lift flap) and an aerodynamic seal associated operatively with the high-lift system, the aerodynamic seal includes a non-planra angulated plate structure which has an outwardly extended planr section having a proximal edge joined to the at least one high-lift flap at the outboard and/or inboard ends thereof, and a downwardly extended planar section joined at an angle to a terminal edge of the outwardly extended planar section.

5. 发明申请

WO2020058344A1 LEADING EDGE STRUCTURE FOR A FLOW CONTROL SYSTEM OF AN AIRCRAFT 审中-公开
公开(公告)号：WO2020058344A1
公开(公告)日：2020-03-26
申请号：PCT/EP2019/075025
申请日：2019-09-18
申请人： AIRBUS OPERATIONS GMBH
发明人： BÜSCHER, Alexander
IPC分类号： B64C21/08 , B64C21/02 , B64C3/28
摘要： Disclosed is a leading edge structure (n) for a flow control system of an aircraft (1), comprising a leading edge panel (13) that surrounds a plenum (17), wherein the leading edge panel (13) has a first side portion (21), a second side portion (27) opposite the first side portion (21), an inner surface (33) facing the plenum (17) and an outer surface (37) in contact with an ambient flow (39), and wherein the leading edge panel (13) comprises a plurality of micro pores (45) forming a fluid connection between the plenum (17) and the ambient flow (39), wherein the plenum (17) is connected to an air outlet arrangement (49) configured for causing an underpressure in the plenum (17), so that air from the ambient flow (39) is drawn through the micro pores (45) into the plenum (17) and from there discharged through the air outlet arrangement (49) into the ambient flow (39). The object to provide a simpler leading edge structure with a reduced weight, is achieved in that the air outlet arrangement (49) is configured to operate in a flow control mode where a first mass flow rate of air from the ambient flow (39) is drawn through the micro pores (45) into the plenum (17), and in a cleaning mode where a second mass flow rate of air from the ambient flow (39) is drawn through the micro pores (45) into the plenum (17), wherein the second mass flow rate is greater than the first mass flow rate.

6. 发明申请

WO2017068292A1 AERONEF A VOILURE FIXE ET A STABILITE STATIQUE ACCRUE 审中-公开
标题翻译：具有固定航行和增加静态稳定性的飞机
公开(公告)号：WO2017068292A1
公开(公告)日：2017-04-27
申请号：PCT/FR2016/052720
申请日：2016-10-21
申请人： DANIELSON AIRCRAFT SYSTEMS
发明人： HUBSCHWERLEN, Frédéric
IPC分类号： B64C21/02 , B64C23/06 , B64C39/06
CPC分类号： B64C39/068 , B64C21/02 , B64C23/076 , Y02T50/164 , Y02T50/166
摘要： L'invention concerne un aéronef présentant au moins une aile (5) comprenant, à chacune de ses extrémités, une ailette (6) formant un angle compris entre 0° et 45° par rapport à la verticale. Selon l'invention, chaque ailette (6) présente un bord d'attaque (7) qui comprend au moins une fente (8) ménagée le long dudit bord d'attaque (7) et orientée pour faire circuler un flux d'air au travers dudit bord d'attaque (7) à partir d'une face externe (6a) de l'ailette (6) jusqu'à une face interne (6b).
摘要翻译：本发明涉及一种具有至少一个机翼（5）的飞机，其包括：其每个末端，翅片（6）形成0°C和0°C之间的角度; 和45°; 关于＆agr; 垂直。根据本发明，每个翅片（6）具有前缘（7），所述前缘（7）包括至少一个沿所述前缘（7）侧接且定向于使空气流循环通过所述前缘（7）。从叶片（6）的外表面（6a）延伸到端部; 一个内面（6b）。

7. 发明申请

WO2014023951A1 AIRCRAFT WING WITH SYSTEM ESTABLISHING A LAMINAR BOUNDARY LAYER FLOW 审中-公开
标题翻译：飞机与系统建立层状边界层流动
公开(公告)号：WO2014023951A1
公开(公告)日：2014-02-13
申请号：PCT/GB2013/052098
申请日：2013-08-06
申请人： EADS UK LIMITED
发明人： ROLSTON, Stephen
IPC分类号： B64C21/02 , B64C21/06 , B64C9/24
CPC分类号： B64C21/06 , B64C9/24 , B64C21/08 , B64C2230/22 , Y02T50/166 , Y02T50/32
摘要： For establishment of a laminar attachment line flow, the invention proposes an aircraft wing (10) comprising: a leading edge (12), the leading edge (12) including an attachment line (14),being a region where air impinging on the region flows in a boundary layer spanwise along the leading edge (12), a first slat (22) and a second slat (24),wherein the leading edge (12) and the attachment line (14) are at least partially formed at the first and second slats (22,24), the second slat (24) is located adjacent to the first slat (22) in the downstream direction of the attachment line flow, so that the leading edge (12) includes a slat-to-slat junction (26), and a slat cavity (30) is formed at the slat-to- slat junction (26) beneath a skin area (36) of at least one of the first and the second slats (22, 24), and a duct (38) having a duct entrance (40) at the slat-to-slat junction (26) for receiving spanwise flow along the leading edge (12) of the wing (10), the duct (38) beings at least partly formed by said slat cavity (30), wherein the duct entrance (40) extends around the leading edge (12) and over the range of positions of the attachment line (14) at the slat-to-slat junction (26).
摘要翻译：为了建立层流连接线流，本发明提出了一种飞机机翼（10），包括：前缘（12），所述前缘（12）包括附接线（14），所述连接线（14）是空气冲击所述区域沿着前缘（12），第一板条（22）和第二板条（24）沿翼展方向流动在边界层中，其中前缘（12）和连接线（14）至少部分地形成在第一和第二板条（22,24），所述第二板条（24）在所述连接线流动的下游方向上邻近所述第一板条（22）定位，使得所述前缘（12）包括板条 - 板条在所述第一和第二板条（22,24）中的至少一个的皮肤区域（36）下方的所述板条 - 缝合连接处（26）处形成有缝合线（26）和板条腔（30），以及管道（38），其在所述板条 - 缝翼连接处（26）处具有用于沿着所述翼（10）的前缘（12）的横向流动的管道入口（40），所述管道（38）至少部分地由所述板条腔（30）形成，其中所述管道入口（40）围绕所述前缘（12）延伸并且在所述连接线（14）在所述板条 - 缝合连接处（26）处的位置范围之间延伸。

8. 发明申请

WO2011120128A1 DUCT FOR HARNESSING ENERGY FROM FLUID THROUGH WHICH CONVEYANCE PASSES 审中-公开
标题翻译：通过输送通过流体对流体进行加热的管道
公开(公告)号：WO2011120128A1
公开(公告)日：2011-10-06
申请号：PCT/CA2011/000301
申请日：2011-03-23
申请人： NOWAK, Klaus, F.
发明人： NOWAK, Klaus, F.
IPC分类号： F15D1/10 , B61D17/02 , B62D35/00 , B62D39/00 , B63B1/32 , B64C21/02 , F15D1/02
CPC分类号： B62D35/001 , B62D35/00 , B63B1/32 , B64B1/06 , F15D1/10 , Y02T70/12
摘要： A duct provides a passageway for a portion of the fluid which contacts the upstream end of a conveyance such as a ship, motor vehicle, train or airship. The intake of the duct is located on the front wall of the conveyance and its outlet is located on its side, top or bottom wall downstream of the inlet. The duct has a convergent-divergent nozzle and a segment which increases in cross-section downstream of the nozzle. The duct serves not only to improve the efficiency of fuel required to power the conveyance but also to reduce the output of pollutants generated as the fuel is consumed.
摘要翻译：管道为与输送机例如船舶，机动车辆，火车或飞艇的上游端接触的一部分流体提供通道。管道的入口位于输送器的前壁上，其出口位于入口下游的侧面，顶部或底部壁上。管道具有会聚扩散喷嘴和在喷嘴下游的横截面增大的段。该管道不仅用于提高为运输提供动力所需的燃料效率，而且还可以减少燃料消耗时产生的污染物的产出。

9. 发明申请

WO2010099967A1 TRAGFLÜGEL EINES FLUGZEUGS SOWIE ANORDNUNG EINES TRAGFLÜGELS MIT EINER VORRICHTUNG ZUR STRÖMUNGSBEEINFLUSSUNG 审中-公开
标题翻译：飞机与水翼翼与设备流量的影响ORDER
公开(公告)号：WO2010099967A1
公开(公告)日：2010-09-10
申请号：PCT/EP2010/001364
申请日：2010-03-04
申请人： AIRBUS OPERATIONS GMBH , FREY, Jürgen , GÖLLING, Burkhard , HANSEN, Heinz , HILDEBRAND, Veit , NEITZKE, Klaus-Peter
发明人： FREY, Jürgen , GÖLLING, Burkhard , HANSEN, Heinz , HILDEBRAND, Veit , NEITZKE, Klaus-Peter
IPC分类号： B64C21/08 , B64C21/02
CPC分类号： B64C9/16 , B64C21/025 , B64C21/04 , B64C21/06 , B64C21/08 , B64C2230/04 , B64C2230/06 , Y02T50/166 , Y02T50/32 , Y02T50/44
摘要： Tragflügel (T) eines Flugzeugs, aufweisend: einen Hauptflügel (10), zumindest eine zwischen einer eingefahrenen und einer ausgefahrenen Stellung bewegbar an dem Hauptflügel (10) angekoppelte Hochauftriebsklappe (20) und zumindest einen Spoiler (30), wobei: - der Hauptflügel (10) eine Mehrzahl von Ausblasöffnungen (11) aufweist, von denen mehrere entlang der Hauptflügel-Spannweitenrichtung (HS) nebeneinander und in der Hauptflügel-Tiefenrichtung (HT) angeordnet sind und die über eine Luftleitung (13) in einer Strömungsverbindung mit der Auslassvorrichtung (P2) eines am Hauptflügel (10) oder am Spoiler (30) angeordneten Strömungsförderantriebs-Vorrichtung (P) stehen, - der Spoiler (30) eine Mehrzahl von Einlassöffnungen (31) zum Einlassen von Luft aufweist, die jeweils über eine Luftleitung (40, 50) in einer Strömungsverbindung mit der Einlassvorrichtung (P1) der Strömungsförderantriebs-Vorrichtung (P) stehen, - die Strömungsförderantriebs-Vorrichtung (P) eine Empfangsvorrichtung zum Empfang von Kommandosignalen zur Einstellung der Strömungsförderantriebs-Vorrichtung (P) aufweist; sowie Anordnung eines Tragflügels (T) mit einer Vorrichtung zur Strömungsbeeinflussung mit einem solchen Tragflügel (T).
摘要翻译：水翼（T）的飞行器的方法，包括：主翼（10），在缩回位置和在主翼的延伸位置之间的至少一个可移动的（10），其耦合高升力翼片（20）和至少一个导流板（30），其中： - 所述主翼（ 10）具有与所述出口装置P2的流动连通的排气口11），其沿所述主翼跨度方向HS）（彼此相邻，和（在主翼深度方向HT）几个布置和（经由空气管线13）（多个（）一个（主翼10）的或在扰流板（30），布置流量传送机驱动装置（P）设置， - 所述扰流板（30）包括入口开口31的多个（），用于允许空气，每个经由空气管线（40，50 ）（在流体输送驱动装置的与入口装置P1的流通信）被提供，（P） - 的流体输送驱动装置（P）的接收装置具有接收命令信号用于调节流体输送驱动装置（P）; 和机翼组件（T）具有用于与这样的翼（T）影响流动的装置。

10. 发明申请

WO2010005341A3 HOLLOW WING WITH AN AIR INTAKE IN THE LEADING EDGE 审中-公开
标题翻译：空气中的空气在领先的边缘
公开(公告)号：WO2010005341A3
公开(公告)日：2010-03-04
申请号：PCT/RU2009000335
申请日：2009-07-03
申请人： SHVED YURIY VITALIEVICH
发明人： SHVED YURIY VITALIEVICH
IPC分类号： B64C3/48 , B64C21/02 , B64C31/036
CPC分类号： B64C21/04 , Y02T50/166
摘要： The invention relates to the field of aviation. The hollow wing with an air intake in the leading edge comprises a lower surface and an upper surface. The upper surface is provided with pockets that form corresponding narrowing channels with an outlet for the flow via a slit in the upper surface of the wing. The invention is to intended to provide improved aerodynamic characteristics.
摘要翻译：本发明涉及航空领域。在前缘具有进气口的空心翼包括下表面和上表面。上表面设置有形成相应的狭窄通道的口袋，其具有用于通过翼的上表面中的狭缝流动的出口。本发明旨在提供改进的空气动力特性。

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