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1. 发明申请

WO2013007849A3 FUSELAJE DE AERONAVE REFORZADO 审中-公开
公开(公告)号：WO2013007849A3
公开(公告)日：2013-01-17
申请号：PCT/ES2012/070481
申请日：2012-06-28
申请人： AIRBUS OPERATIONS, S.L. , LLAMAS SANDÍN, Raúl Carlos , MARTÍNEZ MUÑOZ, José Luis
发明人： LLAMAS SANDÍN, Raúl Carlos , MARTÍNEZ MUÑOZ, José Luis
IPC分类号： B64C1/26 , B64C5/06
摘要： Fuselaje de aeronave reforzado. La invención se refiere a una aeronave con un sistema de propulsión (13) unido al fuselaje trasero (31) por medio de unos pilones delanteros (17); comprendiendo la aeronave un estabilizador vertical de cola (21) unido al fuselaje trasero (31); extendiéndose el fuselaje trasero (31) desde el mamparo de presión trasero (27) hasta la cola (29) de la aeronave, comprendiendo un revestimiento (35), una pluralidad de cuadernas (37, 37', 37'') y teniendo una forma curva; comprendiendo el estabilizador vertical de cola (21) un cajón de torsión con revestimientos izquierdo y derecho, largueros frontal y trasero (51, 53) y una pluralidad de costillas (55); comprendiendo también una estructura resistente conectando dicho estabilizador vertical de cola (21) con el fuselaje trasero (31) que actúa como un camino de carga redundante en eventos de fallo del sistema de propulsión (13) que pueden producir daños en el fuselaje trasero (31).

2. 发明申请

WO2007107521A1 BOLTED JOINT 审中-公开
标题翻译：螺栓接头
公开(公告)号：WO2007107521A1
公开(公告)日：2007-09-27
申请号：PCT/EP2007/052526
申请日：2007-03-16
申请人： AIRBUS DEUTSCHLAND GMBH , STEINKE, Uwe
发明人： STEINKE, Uwe
IPC分类号： B64C1/00 , B64C5/06 , F16B2/04 , F16B43/02
CPC分类号： B64C1/06 , B64C2001/0072 , B64C2001/0081 , F16B3/06 , F16B35/041 , F16C11/045 , Y02T50/43
摘要： In double-shear bolted joints for connecting load-transferring structural parts on an aircraft, wherein a first structural part having a bolt eye with a bushing is connected by means of a bolt to a second, generally fork-shaped structural part having two bolt eyes and the first structural part acts upon the bolt at an angle ≠ 90°, it was previously disadvantageous that, in the surrounds of the particular bolt eye with the bushing, a material thickening was necessary. In order to avoid this thickening, it is proposed that the first structural part (6) has a constant thickness and the bushing (10) is inserted perpendicular to the surface of the structural part (6), the axis (A) of the bore within the bushing (10) for receiving the bolt (1) running obliquely to the surface of the structural part (6) and obliquely to the end face of the bushing (10). The result is that advantages are obtained in terms of manufacturing costs and weight of the bolted joint.
摘要翻译：在用于连接飞行器上的负载传递结构部件的双剪切螺栓接头中，其中具有带衬套的螺栓眼的第一结构部件通过螺栓连接到具有两个螺栓眼睛的第二大体上叉形的结构部件并且第一结构部件以一定的角度作用在螺栓上 90°，以前不利的是，在具有衬套的特定螺栓眼的环绕中，需要增厚材料。为了避免这种增厚，建议第一结构部件（6）具有恒定的厚度，并且衬套（10）垂直于结构部件（6）的表面插入，孔（10）的轴线（A）在衬套（10）内用于接收倾斜地延伸到结构部件（6）的表面并且倾斜于衬套（10）的端面的螺栓（1）。结果是在制造成本和螺栓接头的重量方面获得了优点。

3. 发明申请

WO0009392A3 TWIN ENGINE AIRCRAFT 审中-公开
标题翻译：双引擎飞机
公开(公告)号：WO0009392A3
公开(公告)日：2000-05-18
申请号：PCT/US9917316
申请日：1999-07-29
申请人： WILLIAMS INTERNATIONAL COMPANY
发明人： WILLIAMS SAMUEL BARLOW
IPC分类号： B64C1/00 , B64C5/02 , B64C5/06 , B64C23/00 , B64D27/02 , B64D27/20 , B64D29/04 , B64D33/02 , B64C27/02
CPC分类号： B64C1/00 , B64C5/02 , B64C5/06 , B64C23/00 , B64C2001/0045 , B64D27/02 , B64D27/20 , B64D29/04 , B64D33/02 , B64D2033/022 , B64D2033/0286
摘要： A jet aircraft (10) has a generally conical front fuselage section (14), a cylindrical intermediate fuselage section (16) defining a passenger compartment, a generally conical aft fuselage section (18), and a single vertical stabilizer (20). The aircraft's propulsion engines (30 and 32) are mounted on pylons (33) on the conical aft fuselage section (18) with the air inlets (34 and 36) thereof disposed entirely within a rearward projection (37) of the lateral cross section of the intermediate fuselage section (16) thereby to preclude the ingestion of foreign objects into the engines (30 and 32) while minimizing the effect of boundary layer airflow. The exhaust nozzles (50 and 52) extend rearwardly past the vertical stabilizer (20) to minimize side line noise.
摘要翻译：喷气式飞机（10）具有大致圆锥形的前机身部分（14），限定乘客舱的圆柱形中间机身部分（16），大致圆锥形的机身后部（18）和单个垂直稳定器（20）。该飞机的推进发动机（30和32）安装在圆锥形尾部机身部分（18）上的塔架（33）上，其进气口（34和36）完全布置在下述横向截面的向后突出部（37）中间机身段（16）由此阻止异物进入发动机（30和32），同时最小化边界层气流的影响。排气喷嘴（50和52）向后延伸超过垂直稳定器（20）以使侧线噪音最小化。

4. 发明申请

WO2012109355A2 VORTEX-INDUCED VIBRATION SUPPRESSION DEVICE AND MATING COLLAR SYSTEM 审中-公开
标题翻译： VORTEX诱发的振动抑制装置和主要系统
公开(公告)号：WO2012109355A2
公开(公告)日：2012-08-16
申请号：PCT/US2012/024329
申请日：2012-02-08
申请人： VIV SOLUTIONS LLC , WEST, William, Andrew , ALLEN, Donald, Wayne , HENNING, Dean Leroy
发明人： WEST, William, Andrew , ALLEN, Donald, Wayne , HENNING, Dean Leroy
IPC分类号： B64C5/06
CPC分类号： F16B7/0406 , F15D1/10 , Y10T403/64 , Y10T403/642
摘要： A system including a vortex-induced vibration (VIV) suppression device dimensioned to suppress a vortex induced vibration of a support structure, the VIV suppression device having a base portion that encircles at least a portion of the support structure and a support member formed along the base portion. The system further including a collar having a body portion defining an annular channel and a flange portion extending outwardly from the annular channel, the flange portion dimensioned to form a receiving channel around the support structure for receiving the support member. The support member is received within the receiving channel to secure the VIV suppression device to the support structure and the VIV suppression device is capable of rotating around the support structure along the receiving channel.
摘要翻译：一种包括涡流诱导振动（VIV）抑制装置的系统，其尺寸设计成抑制支撑结构的涡流引起的振动，所述VIV抑制装置具有围绕所述支撑结构的至少一部分的基部和沿着所述支撑结构形成的支撑构件基部。所述系统还包括具有限定环形通道的主体部分和从所述环形通道向外延伸的凸缘部分的凸缘，所述凸缘部分的尺寸被设计成围绕所述支撑结构形成用于接收所述支撑构件的接收通道。支撑构件被容纳在接收通道内，以将VIV抑制装置固定到支撑结构，并且VIV抑制装置能够沿着接收通道围绕支撑结构转动。

5. 发明申请

WO2006078651A1 CONTROL SURFACE ASSEMBLIES WITH TORQUE TUBE BASE 审中-公开
标题翻译：带扭矩管座的控制面组件
公开(公告)号：WO2006078651A1
公开(公告)日：2006-07-27
申请号：PCT/US2006/001601
申请日：2006-01-17
申请人： THE BOEING COMPANY , RUSSOM, Jeffery, D. , WHITE, Lawrence, R. , GREENWOOD, James
发明人： RUSSOM, Jeffery, D. , WHITE, Lawrence, R. , GREENWOOD, James
IPC分类号： B64C5/06 , B64C1/26 , F42B10/04
CPC分类号： F42B10/04 , B64C1/26 , B64C5/00 , B64C5/06 , B64C9/02 , Y02T50/44
摘要： Control surface assemblies (300) having a torque tube base (304) are disclosed. In one embodiment, a control surface assembly (300) includes a control surface portion (302) and a base portion (304) . The base portion (304) has a hollow, shell-like base portion (314) coupled to a first end portion of the control surface portion (302) , and is adapted to be coupled to a supporting structure (306) such that the control surface portion (302) projects outwardly from the supporting structure (306) . In one aspect, the base portion (304) includes an elongated, closed section portion adapted to b coupled to the supporting structure (306) . In a further aspect, the base portion includes an elongated, closed section portion adapted to be coupled t the supporting structure (306) , and a pair of tapered end portions (310) formed at opposing ends of the closed section portion.
摘要翻译：公开了具有扭矩管基座（304）的控制表面组件（300）。在一个实施例中，控制表面组件（300）包括控制表面部分（302）和基部（304）。基部（304）具有联接到控制表面部分（302）的第一端部分的中空的壳状基部（314），并且适于联接到支撑结构（306），使得控制表面部分（302）从支撑结构（306）向外伸出。在一个方面，基部（304）包括适于联接到支撑结构（306）的细长的闭合部分部分。在另一方面，基部包括适于联接到支撑结构（306）的细长的闭合部分部分和形成在闭合部分部分的相对端处的一对锥形端部部分（310）。

6. 发明申请

WO00007875A1 AN AIRCRAFT FIN AND RUDDER 审中-公开
标题翻译：飞机火炬和雷达
公开(公告)号：WO00007875A1
公开(公告)日：2000-02-17
申请号：PCT/GB1999/002568
申请日：1999-08-03
IPC分类号： B64C5/02 , B64C5/06 , B64C9/00
CPC分类号： B64C9/00 , B64C5/06
摘要： The fin (12) has an end plate (16) mounted at its upper end and the end plate covers the upper end of the rudder, so that the rudder (14) seals against the end plate at all rudder deflections. The fin and rudder lift curved slopes are increased by the effect of the end plate (16).
摘要翻译：翅片（12）具有安装在其上端的端板（16），并且端板覆盖舵的上端，使得方向舵（14）在所有舵偏转下都密封在端板上。通过端板（16）的作用，翅片和方向舵提升弯曲斜坡增加。

7. 发明申请

WO2020180373A3 AIRCRAFT CONTROL SYSTEM AND METHOD 审中-公开
公开(公告)号：WO2020180373A3
公开(公告)日：2020-09-10
申请号：PCT/US2019/065301
申请日：2019-12-09
申请人： JOBY AERO, INC.
发明人： ENGLISH, Blake , BEVIRT, JoeBen
IPC分类号： B64C29/00 , B64C5/06
摘要： The unified command system and/or method includes an input mechanism, a flight processor that receives input from the input mechanism and translates the input into control output, and effectors that are actuated according to the control output. The system can optionally include: one or more sensors, a vehicle navigation system which determines a vehicle state and/or flight regime based on data from the one or more sensors, and a vehicle guidance system which determines a flightpath for the aircraft.

8. 发明申请

WO2016134433A1 AIRFRAME-INTEGRATED PROPELLER-DRIVEN PROPULSION SYSTEMS 审中-公开
标题翻译： AIRFRAME-INTEGRATED螺旋桨驱动推进系统
公开(公告)号：WO2016134433A1
公开(公告)日：2016-09-01
申请号：PCT/BR2016/000016
申请日：2016-02-19
申请人： EMBRAER S.A.
发明人： HIRANO, Helio , TRAPP, Luis Gustavo
IPC分类号： B64C5/02 , B64C5/06 , B64D27/04 , B64D27/10
CPC分类号： B64C11/46 , B64C5/02 , B64C5/06 , B64C23/005 , B64D27/04 , B64D27/10
摘要： Propeller-driven craft (e.g., aircraft) are provided with at least one propulsion system having at least one engine and at least one aerial tractor propeller which generates a propeller propwash airflow when driven by the engine. At least one airfoil is disposed in the propeller propwash airflow of the at least one aerial tractor propeller. The airfoil is contoured and oriented relative to a swirl rotation angle (ω) of the propeller propwash airflow in order to induce a forward force component on the craft in response to the propeller propwash airflow over the at least one airfoil, thus improving the craft's performance and/or reducing fuel consumption.
摘要翻译：螺旋桨驱动的工艺（例如飞行器）具有至少一个具有至少一个发动机和至少一个空中拖拉机螺旋桨的推进系统，其在由发动机驱动时产生螺旋桨推动气流。至少一个翼型件设置在至少一个空中拖拉机螺旋桨的螺旋桨推动气流中。翼型件相对于螺旋桨推流气流的旋转旋转角度（ω）成形和定向，以便响应于至少一个翼型上的螺旋桨推动气流而引起飞行器上的向前力分量，从而提高飞行器的性能和/或降低燃料消耗。

9. 发明申请

WO2007107520A2 BOLTED JOINT 审中-公开
标题翻译：螺栓连接
公开(公告)号：WO2007107520A2
公开(公告)日：2007-09-27
申请号：PCT/EP2007/052525
申请日：2007-03-16
申请人： AIRBUS DEUTSCHLAND GMBH , STEINKE, Uwe
发明人： STEINKE, Uwe
IPC分类号： B64C1/00 , B64C5/06 , F16B2/04 , F16B43/00
CPC分类号： B64C1/06 , B64C2001/0081 , F16B3/06 , F16B5/025 , F16B35/041 , F16B39/101 , Y10T403/645 , Y10T403/7058 , Y10T403/75
摘要： In bolted joints having a plurality of bolts, the receiving bores for the bolts in the parts to be joined are usually made by joint boring of the bolt eyes of these parts. In cases in which this approach is not possible, an offset of the bolt bores arises. The proposed solution is intended to compensate for this offset during the assembly of the parts. In order to bring about this compensation, it is provided that slotted eccentric bushings (24, 25, 26, 27, 28, 29) are inserted into the finished-size bores of the bolt eyes (1a, 1b, 2a, 2b, 2c, 2d), which bores respectively receive a bolt (3, 4), and are adjustable by rotation such that the axes of their inner bores coincide, so that the bolt (3, 4) is insertable which establishes the joint. This solution is suitable for all bolted joints having a plurality of bolts, in which the parts to be joined cannot be jointly bored.
摘要翻译：在具有多个螺栓的螺栓连接中，用于要连接的部件中的螺栓的接收孔通常通过这些部件的螺栓眼的连接钻孔来制造。在这种方法不可行的情况下，会出现螺栓孔的偏移。所提出的解决方案旨在补偿部件组装期间的这种偏移。为了实现这种补偿，规定将开槽偏心衬套（24,25,26,27,28,29）插入到螺栓孔（1a，1b，2a，2b，2c）的成品孔中，2d），这些孔分别容纳一个螺栓（3,4），并且可以通过旋转进行调节，使得它们的内孔的轴线重合，从而使螺栓（3,4）能够插入，从而形成接头。该解决方案适用于具有多个螺栓的所有螺栓连接，其中要连接的零件不能共同钻孔。

10. 发明申请

WO0009392A8 TWIN ENGINE AIRCRAFT 审中-公开
标题翻译：双发动机飞机
公开(公告)号：WO0009392A8
公开(公告)日：2000-07-13
申请号：PCT/US9917316
申请日：1999-07-29
申请人： WILLIAMS INTERNATIONAL COMPANY
发明人： WILLIAMS SAMUEL BARLOW
IPC分类号： B64C1/00 , B64C5/02 , B64C5/06 , B64C23/00 , B64D27/02 , B64D27/20 , B64D29/04 , B64D33/02 , B64C27/02
CPC分类号： B64C1/00 , B64C5/02 , B64C5/06 , B64C23/00 , B64C2001/0045 , B64D27/02 , B64D27/20 , B64D29/04 , B64D33/02 , B64D2033/022 , B64D2033/0286
摘要： A jet aircraft (10) has a generally conical front fuselage section (14), a cylindrical intermediate fuselage section (16) defining a passenger compartment, a generally conical aft fuselage section (18), and a single vertical stabilizer (20). The aircraft's propulsion engines (30 and 32) are mounted on pylons (33) on the conical aft fuselage section (18) with the air inlets (34 and 36) thereof disposed entirely within a rearward projection (37) of the lateral cross section of the intermediate fuselage section (16) thereby to preclude the ingestion of foreign objects into the engines (30 and 32) while minimizing the effect of boundary layer airflow. The exhaust nozzles (50 and 52) extend rearwardly past the vertical stabilizer (20) to minimize side line noise.
摘要翻译：喷气式飞机（10）具有大致圆锥形的前机身部分（14），限定乘客舱的圆柱形中间机身部分（16），大体上圆锥形的后机身部分（18）和单个垂直稳定器（20）。飞机的推进发动机（30和32）安装在圆锥形后机身部分（18）上的塔架（33）上，其空气入口（34和36）完全设置在横向截面的后向突出部（37）内中间机身部分（16）从而防止异物进入发动机（30和32），同时使边界层气流的影响最小化。排气喷嘴（50和52）向后延伸超过垂直稳定器（20），以使侧线噪声最小化。

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