公开(公告)号：US20090108142A1

公开(公告)日：2009-04-30

申请号：US12230553

申请日：2008-08-29

申请人： Philip Wright ,  Edmund Kay

发明人： Philip Wright ,  Edmund Kay

IPC分类号： B64C3/50

CPC分类号： B64C9/18 ,  B64C9/14 ,  B64C9/24

摘要： An aircraft wing comprising: a leading element; a trailing element positioned behind the leading element relative to a direction of movement of the aircraft; an actuation system for moving one of the elements between a retracted position and an extended position in which there is an air gap between a lower surface of the leading element and a surface of the trailing element. Two or more elongate stiffening ridges extend downwards from the lower surface of the leading element, and each adjacent pair of ridges is separated by a channel.The leading element is shaped to provide an improved air gap, preferably one which is parallel or convergent in all positions.Typically the volume of at least one of the ridges is less than the 50% of the volume of a channel defined by that ridge; the thickness of the leading element at the base of at least one of the channels is less than the depth of the channel at the same point; and each channel has an open rear end which is positioned substantially at a trailing edge of the leading element.

摘要翻译： 一种飞机机翼，包括：主导元件; 相对于飞行器的运动方向定位在引导元件后面的拖尾元件; 用于在缩回位置和延伸位置之间移动元件之一的致动系统，其中在前导元件的下表面和后元件的表面之间存在气隙。 两个或更多个细长的加强脊从引导元件的下表面向下延伸，并且每个相邻的一对脊由通道分开。 引导元件被成形为提供改进的气隙，优选地在所有位置平行或会聚的气隙。 通常，脊中的至少一个的体积小于由该脊限定的通道的体积的50％; 在至少一个通道的基部处的引导元件的厚度小于在相同点处的通道的深度; 并且每个通道具有敞开的后端，其基本位于所述引导元件的后缘。

公开(公告)号：US20090101759A1

公开(公告)日：2009-04-23

申请号：US12212755

申请日：2008-09-18

申请人： Colin John WEST ,  David Alistair SUTTON ,  Fariborz F. BOOZARI

发明人： Colin John WEST ,  David Alistair SUTTON ,  Fariborz F. BOOZARI

IPC分类号： B64C3/50 ,  B32B38/10

CPC分类号： B64C3/26 ,  B64C3/28 ,  B64C9/22

摘要： An aircraft leading edge panel having an outer aerodynamic surface; and an inner surface carrying the elastomeric impact protection membrane. The membrane comprises a woven or knitted fabric which is impregnated with an elastomeric material. The membrane and the panel may be bonded by an adhesive or co-cured to bond the membrane to the panel. The membrane provides impact protection to the panel by de-bonding from the face of the panel and absorbing at least part of the energy of an object impacting the panel.

摘要翻译： 具有外部空气动力学表面的飞行器前缘面板; 以及承载弹性体冲击保护膜的内表面。 该膜包括用弹性体材料浸渍的织造或针织织物。 膜和面板可以通过粘合剂粘合或共同固化以将膜粘合到面板上。 膜通过从面板的表面去粘合并吸收影响面板的物体的至少一部分能量来向面板提供冲击保护。

公开(公告)号：US20090084894A1

公开(公告)日：2009-04-02

申请号：US12200596

申请日：2008-08-28

申请人： Christopher Neil Wood

发明人： Christopher Neil Wood

IPC分类号： B64C25/10 ,  B64C7/00

CPC分类号： B64C25/001 ,  B64C7/00 ,  B64C2025/003

摘要： An aircraft landing gear is arranged such that in its deployed position it is configured to reduce, during the approach on landing, the noise generated by the interaction of the landing gear and the air flowing past the landing gear. Various means are described to reduce the amount of turbulent air flow generated in the region of the landing gear, including inverting and fairing the nose-gear shock-absorbing leg, providing faired twin in-line oleos and providing fairings that produce shielding air curtains.

摘要翻译： 飞机起落架被布置成使得在其展开位置中，其被构造成在起落架接近期间降低由起落架和流过起落架的空气的相互作用产生的噪声。 描述了各种手段以减少起落架区域中产生的湍流空气流量，包括翻转和整流起落架的减震腿，提供流线型的双列直插油墨并提供产生屏蔽气帘的整流罩。

公开(公告)号：US20090076668A1

公开(公告)日：2009-03-19

申请号：US12230176

申请日：2008-08-25

申请人： Christopher Lynas ,  Iain Morgan

发明人： Christopher Lynas ,  Iain Morgan

IPC分类号： B64C25/10 ,  G06F17/00

CPC分类号： B64C25/42 ,  B64C25/22 ,  B64C25/24 ,  B64C25/405 ,  B64D41/00 ,  Y02T50/823

摘要： A method and apparatus is disclosed in which an aircraft system such as the landing gear system or braking system is operated at least partially under power provided by a generator driven by the wheels of the landing gear.

摘要翻译： 公开了一种方法和装置，其中诸如起落架系统或制动系统的飞行器系统至少部分地由由起落架的车轮驱动的发电机提供的动力下操作。

公开(公告)号：US07484688B2

公开(公告)日：2009-02-03

申请号：US10533376

申请日：2003-10-23

申请人： Leung Choi Chow ,  Christopher Neil Wood

发明人： Leung Choi Chow ,  Christopher Neil Wood

IPC分类号： B64C25/04

CPC分类号： B64C25/16 ,  B64C7/00 ,  B64C2025/003

摘要： An aircraft landing gear (1) is described including a noise-reducing element that includes an air-deflecting surface, in the form of a fairing (4), and a perforated airflow-reducing region (8). In use, some air passes through the perforations, whilst other air is deflected by the fairing away from a noise-generating region of the landing gear. Noise caused by the passing of the landing gear through the air is therefore reduced.

摘要翻译： 描述了一种飞机起落架（1），其包括减振元件，其包括整流罩（4）形式的空气偏转表面和穿孔的气流减少区域（8）。 在使用中，一些空气穿过穿孔，而其他空气被整流罩偏离起落架的噪声产生区域。 因此，通过空气通过起落架引起的噪音降低了。

公开(公告)号：US20090026313A1

公开(公告)日：2009-01-29

申请号：US12216195

申请日：2008-07-01

申请人： Stephen Briancourt ,  Trajan Seymour

发明人： Stephen Briancourt ,  Trajan Seymour

IPC分类号： B64C25/02 ,  G02B6/00

CPC分类号： B64C25/00 ,  B64D2045/008

摘要： An aircraft landing gear comprising a fibre optic load sensor for monitoring load in a component of the landing gear, such as an axle. The fibre optic cable is mounted on an inner surface of the component of the landing gear. Typically the fibre optic load sensor comprises one or more Bragg Grating sensors.

摘要翻译： 一种飞机起落架，包括用于监测起落架（例如轴）的部件中的载荷的光纤负载传感器。 光纤电缆安装在起落架部件的内表面上。 通常，光纤负载传感器包括一个或多个布拉格光栅传感器。

公开(公告)号：US20090021092A1

公开(公告)日：2009-01-22

申请号：US12279729

申请日：2007-03-01

申请人： Nicholas Elliott ,  Arnaud Didey

发明人： Nicholas Elliott ,  Arnaud Didey

IPC分类号： H02K7/116

CPC分类号： F16H25/205 ,  B64C13/28 ,  B64C25/30 ,  F16H2025/2059 ,  Y10T74/18576 ,  Y10T74/18672

摘要： An actuator comprises first and second linear motion devices, each able to extend the actuator and arranged such that jamming of one of the first and second linear motion devices does not preclude operation of the other. The first linear motion device comprises a first linear screw, a first nut, and a first prime mover arranged to impart relative linear motion between the screw and nut. Similarly, the second linear motion device comprises a second linear screw, a second nut, and a second prime mover arranged to impart relative linear motion between the second screw and nut. The first linear screw may have a bore in which the second linear screw is accommodated when the actuator is in the retracted position.

摘要翻译： 致动器包括第一和第二直线运动装置，每个装置能够延伸致动器并且布置成使得第一和第二直线运动装置中的一个的卡住不排除另一个的运行。 第一线性运动装置包括第一线性螺钉，第一螺母和第一原动机，其布置成在螺钉和螺母之间施加相对的线性运动。 类似地，第二线性运动装置包括布置成在第二螺钉和螺母之间施加相对线性运动的第二线性螺钉，第二螺母和第二原动机。 当致动器处于缩回位置时，第一直线螺杆可以具有孔，第二线性螺钉容纳在该孔中。

公开(公告)号：US20080302486A1

公开(公告)日：2008-12-11

申请号：US12120760

申请日：2008-05-15

申请人： Chistopher David Jones ,  Simon John Astwood ,  Steven Matthew Evans

发明人： Chistopher David Jones ,  Simon John Astwood ,  Steven Matthew Evans

IPC分类号： B29C53/60

CPC分类号： B29C70/38 ,  B29C33/301 ,  B29C33/76 ,  Y10T29/49826

摘要： A fibre placement tool comprising a plurality of tool segments, each tool segment having an outer surface defining a predetermined profile, each tool segment being removably mounted on at least one elongate shaft.

摘要翻译： 一种纤维布置工具，其包括多个工具段，每个工具段具有限定预定轮廓的外表面，每个工具段可移除地安装在至少一个细长轴上。

公开(公告)号：US20080292427A1

公开(公告)日：2008-11-27

申请号：US12095363

申请日：2006-12-14

申请人： James Henry Rowe ,  John Moore

发明人： James Henry Rowe ,  John Moore

IPC分类号： F16B35/04 ,  F16B5/02

CPC分类号： F16B5/025 ,  F16B35/041 ,  F16B37/00 ,  F16B43/00 ,  Y10T29/49948

摘要： A fastener assembly includes a bolt having first and second ends and comprising a bolt head at the first end, a first shank portion having a smooth circumferential surface of a first diameter and a second shank portion coaxial with the first shank portion and of a second diameter smaller than the first diameter. At least a part of the second shank portion is externally screw threaded and the first shank portion is positioned between the bolt head and the second shank portion. A nut has first and second ends and includes a first bore extending from the first end of the nut and of a diameter greater than the first diameter for fitting over part of the first shank portion of the bolt, and, in the region of the second end, a screw threaded bore for screw threaded engagement with the screw threaded second shank portion, the screw threaded bore being coaxial with and leading into the first bore.

摘要翻译： 紧固件组件包括具有第一端和第二端并且在第一端处包括螺栓头的螺栓，具有第一直径的平滑圆周表面的第一柄部分和与第一柄部分同轴的第二柄部分， 小于第一直径。 第二柄部的至少一部分是外螺纹的，第一柄部位于螺栓头和第二柄部之间。 螺母具有第一和第二端，并且包括从螺母的第一端延伸并且具有大于第一直径的直径的第一孔，用于装配在螺栓的第一柄部分的一部分上，并且在第二孔的第二区域中 螺纹孔与螺纹的第二柄部螺纹接合，螺纹孔与第一孔同轴并通向第一孔。

公开(公告)号：US20080272237A1

公开(公告)日：2008-11-06

申请号：US12158061

申请日：2006-12-01

申请人： Franklin George Tichborne ,  Kim Michael Ley

发明人： Franklin George Tichborne ,  Kim Michael Ley

IPC分类号： B64D37/02 ,  G01F23/00

CPC分类号： B64D37/00 ,  G01F9/00 ,  G01F23/0076

摘要： One or more main aircraft fuel tanks are provided with one or more fuel gauges arranged to provide a measure of the amount of fuel in said one or more main fuel tanks. One or more auxiliary fuel tanks are also provided. The aircraft uses fuel during a first phase of fuel consumption, upon commencement of which phase the auxiliary fuel tanks hold fuel. After the first phase said one or more auxiliary fuel tanks are empty and a second phase commences. During the first phase, an indication of the amount of fuel carried by the aircraft is provided by means of summing (i) the amount of fuel in the main fuel tanks as measured by said one or more fuel gauges and (ii) the amount of fuel remaining in said one or more auxiliary fuel tanks as calculated using a measure relating to the fuel consumption rate. During the second phase of fuel consumption, an indication of the amount of fuel carried by the aircraft is provided on the basis of the amount of fuel measured by said one or more fuel gauges.

摘要翻译： 一个或多个主飞行器燃料箱设置有一个或多个燃料计量器，其布置成提供所述一个或多个主燃料箱中的燃料量的量度。 还提供一个或多个辅助燃料箱。 在燃料消耗的第一阶段，飞机使用燃料，在辅助燃料箱开始阶段，燃料储存在燃料中。 第一阶段说，一个或多个辅助燃料箱是空的，第二阶段开始。 在第一阶段期间，通过以下方式提供飞行器携带的燃料量的指示：（i）由所述一个或多个燃料计测量的主燃料箱中的燃料量，以及（ii） 所述一个或多个辅助燃料箱中残留的燃料是使用与燃料消耗率相关的措施来计算的。 在燃料消耗的第二阶段期间，基于由所述一个或多个燃料计测量的燃料量来提供飞行器携带的燃料量的指示。