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91. 发明授权

US08935987B2 Apparatus for increasing the visibility of an aircraft winglet 有权
标题翻译：用于增加飞机小翼的可视性的装置
公开(公告)号：US08935987B2
公开(公告)日：2015-01-20
申请号：US13714893
申请日：2012-12-14
申请人： Aviation Applications Corporation
发明人： John W. Edwards , Alexander Christopher Edwards , Perry Keith Jones
IPC分类号： B64D45/00 , B64D47/00 , G01D13/00
CPC分类号： G01D13/00 , B64D45/00
摘要： An apparatus for increasing the visibility of an aircraft winglet comprising a saddle piece configured to fit on top of a winglet, the saddle piece comprising a horizontal strap configured to fit around a trailing edge of the winglet, an anchor member comprising a horizontal strap configured to fit around a trailing edge of the winglet, and an adjustable strap connecting the saddle piece to the anchor member. The anchor member is situated on the winglet a certain distance below the saddle piece, and the adjustable strap adjusts the vertical distance between the saddle piece and the anchor member.
摘要翻译：一种用于增加飞行器小翼的可视性的装置，包括构造成装配在小翼顶部上的鞍形件，所述鞍形件包括构造成围绕所述小翼的后缘配合的水平带，锚定构件，包括水平带，围绕小翼的后缘安装，以及将鞍形件连接到锚定构件的可调节带。锚定构件位于小翼上方的鞍座下方一定距离处，并且可调节带调节鞍形件与锚定构件之间的垂直距离。

92. 发明申请

US20140263819A1 HELICOPTER DRIP PAN 有权
标题翻译：直升机DRIP PAN
公开(公告)号：US20140263819A1
公开(公告)日：2014-09-18
申请号：US13839551
申请日：2013-03-15
申请人： PHOENIX PRODUCTS, INC.
发明人： Thomas Gray Wilson
IPC分类号： F16N31/00 , B64D47/00
CPC分类号： F16N31/006 , B64C27/04 , B64D27/00 , B64D47/00 , F16N31/002 , F16N2210/08 , Y10T29/49826
摘要： A drip pan apparatus for use in a helicopter includes a drip pan and a frame having a plurality of frame sides and a plurality of frame corners that define an inwardly-facing peripheral surface. A first frame angle is formed between a first inwardly-facing surface and a second inwardly-facing surface. The first frame angle is an acute angle. The drip pan has an outwardly-facing peripheral surface. The outwardly-facing peripheral surface defines a plurality of sides, including a first side and a second side, to cooperate with the inwardly-facing peripheral surface of the frame. A first angle is formed between the first side and the second side. The first angle is an acute angle. A method of installing a drip pan includes modifying at least a portion of a skirt on the helicopter and then securing the frame to one or both of the modified skirt and the helicopter structure.
摘要翻译：用于直升机的滴水盘装置包括滴水盘和具有多个框架侧面的框架和限定向内的周向表面的多个框架拐角。在第一向内的表面和第二向内的表面之间形成第一框架角度。第一帧角度是锐角。滴水盘具有向外的外围表面。面向外的外围表面限定了包括第一侧和第二侧的多个侧面，以与框架的向内的外周表面配合。在第一侧和第二侧之间形成第一角度。第一个角度是一个锐角。安装滴水盘的方法包括修改直升机上的裙部的至少一部分，然后将框架固定到修改的裙部和直升机结构中的一个或两个上。

93. 发明授权

US08733699B2 Overhead luggage compartment 有权
标题翻译：架空行李箱
公开(公告)号：US08733699B2
公开(公告)日：2014-05-27
申请号：US13207932
申请日：2011-08-11
申请人： Markus Rafler , Michael Klas , Dietmar Stroebele
发明人： Markus Rafler , Michael Klas , Dietmar Stroebele
IPC分类号： B64C1/20 , B64C1/22 , B64D47/00
CPC分类号： B61D37/003 , B64D11/003 , H02G3/22
摘要： An overhead luggage compartment for a vehicle cabin is provided. In the compartment, a ledge provided with an electrical component is pivotably held in a housing half-shell about a pivot axis. The pivot axis extends through two axles connecting the ledge to the housing half-shell. For connecting the electrical component to a cable, one of the axles has a through-hole extending in the axial direction, through which the cable is guided for connecting the component.
摘要翻译：提供了一种用于车厢的高架行李箱。在隔室中，设置有电气部件的凸缘围绕枢转轴线可枢转地保持在壳体半壳体中。枢转轴线延伸穿过将凸缘连接到壳体半壳体的两个轴。为了将电气部件连接到电缆，其中一个轴具有沿轴向延伸的通孔，电缆通过该通孔被引导以连接部件。

94. 发明申请

US20140117163A1 CRYOGENIC TANK 审中-公开
标题翻译：低温罐
公开(公告)号：US20140117163A1
公开(公告)日：2014-05-01
申请号：US13665901
申请日：2012-10-31
申请人： GENERAL ELECTRIC COMPANY
发明人： James Edward Simpson
IPC分类号： B64D37/06 , B64D37/08 , B64D47/00 , F17C5/02 , F17C13/08
CPC分类号： B64D37/06 , B64D37/30 , F17C1/14 , F17C2201/0152 , F17C2201/054 , F17C2203/013 , F17C2203/0325 , F17C2203/0329 , F17C2203/035 , F17C2203/0383 , F17C2203/0391 , F17C2203/0629 , F17C2203/0636 , F17C2203/0646 , F17C2203/0648 , F17C2205/018 , F17C2221/033 , F17C2223/0161 , F17C2223/033 , F17C2223/035 , F17C2260/011 , F17C2270/0189
摘要： A cryogenic tank includes a shell having an interior side, an exterior side, and an internal volume that is bounded by the interior side. The shell has a shape that includes at least two elongated lobes that are defined by partial cylinders that intersect each other. The partial cylinders extend lengths along central longitudinal axes that are offset from each other. The lobes include opposite domes that extend at opposite ends of the length of the corresponding partial cylinder. The cryogenic tank includes an internal reinforcement frame having a web of elongate frame members extending within the internal volume. The frame members extend along the interior side of the shell such that lengths of the frame members extend along paths that follow the profile of the interior side of the shell. The internal reinforcement frame is configured to distribute loads exerted on the shell along at least three different directions.
摘要翻译：低温罐包括具有内侧，外侧和由内侧限定的内部容积的外壳。壳体具有包括由彼此相交的部分气缸限定的至少两个细长的凸角的形状。部分气缸沿着相互偏移的中心纵向轴线延伸长度。叶片包括在对应的部分圆柱体的长度的相对端延伸的相对的圆顶。低温罐包括内部增强框架，其具有在内部体积内延伸的细长框架构件的腹板。框架构件沿着壳体的内侧延伸，使得框架构件的长度沿着沿着壳体的内侧的轮廓的路径延伸。内部加强框架构造成沿着至少三个不同的方向分布施加在壳体上的载荷。

95. 发明授权

US08636240B2 Aircraft ground maintenance tether assembly 有权
标题翻译：飞机地面维修系绳总成
公开(公告)号：US08636240B2
公开(公告)日：2014-01-28
申请号：US13869548
申请日：2013-04-24
申请人： Ernest T. Jefferson , James H. Van Dis
发明人： Ernest T. Jefferson , James H. Van Dis
IPC分类号： B64D47/00
CPC分类号： B64C25/26 , B64C25/28 , B64D45/00 , B64F1/005
摘要： A ground maintenance assembly for an aircraft generally including a support member provided with a longitudinal bore and a rigid post portion, a first inner member provided with a longitudinal bore disposed in and secured in such support member and a second inner member provided with a longitudinal recess adapted to receive a pitot tube of such aircraft.
摘要翻译：通常包括设置有纵向孔和刚性柱部分的支撑构件的飞机的地面维护组件，设置有设置在该支撑构件中并固定在该支撑构件中的纵向孔的第一内部构件和设置有纵向凹部适于接收这种飞机的皮托管。

96. 发明申请

US20130161940A1 DEVICE FOR FASTENING A FLUID TRANSPORT CIRCUIT TO AN ELEMENT OF THE STRUCTURE OF AN AIRCRAFT AND RELATED AIRCRAFT 有权
标题翻译：将液体运输电路用于飞机和相关飞机结构的一部分的装置
公开(公告)号：US20130161940A1
公开(公告)日：2013-06-27
申请号：US13688851
申请日：2012-11-29
申请人： AIRBUS OPERATIONS
发明人： Robert ROSSATO , Alexis Courpet
IPC分类号： B64D47/00
CPC分类号： B64D47/00 , B64D45/02 , F16L3/1222 , F16L39/005
摘要： The invention concerns a fastening device (10) for a fluid transport circuit to an element of the structure of an aircraft, with the fluid transport to circuit containing several portions (23, 42), each of which is made up of an external tube (22, 44) positioned around an internal tube (21, 43). The fastening device (10) is characterized in that the fastening device (10) is positioned at a connection (40) between two portions (23, 42) of the fluid transport circuit, and it contains a body (26) with a plate (27) intended to attach the fastening device (10) to the element (61) of the structure of the aircraft, this body (26) providing at least one sealed connection between the external tubes (22, 44) of the two portions (23, 42) and a support system guaranteeing appreciably constant radial clearance between the internal tube (21, 43) and the external tube (22, 44) of the two portions (23, 42) of the fluid transport circuit.
摘要翻译：本发明涉及一种用于流体传输电路到飞行器结构的元件的紧固装置（10），其中流体输送到电路包含若干部分（23,42），每个部分由外管（ 22,44）定位在内管（21,43）周围。紧固装置（10）的特征在于，紧固装置（10）位于流体输送回路的两个部分（23,42）之间的连接（40）处，并且其包含具有板的主体（26）旨在将紧固装置（10）附接到飞行器的结构的元件（61），该主体（26）提供两个部分（23）的外部管（22,44）之间的至少一个密封连接，42）和保证流体输送回路的两个部分（23,42）的内管（21,43）和外管（22,44）之间明显恒定的径向间隙的支撑系统。

97. 发明授权

US08452525B2 Weighing system and methods of operating such weighing system 有权
标题翻译：称重系统及操作方法
公开(公告)号：US08452525B2
公开(公告)日：2013-05-28
申请号：US13239451
申请日：2011-09-22
申请人： Johann Sendlinger , Markus Wahnfried
发明人： Johann Sendlinger , Markus Wahnfried
IPC分类号： G06F19/00 , B64D47/00 , B64C25/52 , G01M1/12 , G01G19/07
CPC分类号： G01M1/125 , G01G19/07
摘要： A weighing system for detecting total weight, including optional external loads, and monitoring of center of gravity of a helicopter (2), comprising a fuselage (1), a landing gear (4), mounted to the fuselage (1) by flanges (10-13) and weighing cells (41-44). The weighing cells (41-44) are integral with the flanges (10-13) between the fuselage (1) and the landing gear (4). Attachment means are provided at the landing gear (4) for external loads (39, 40).
摘要翻译：一种称重系统，用于检测总重量，包括可选的外部载荷，以及监测直升机（2）的重心，包括机身（1），起落架（4），通过法兰（1）安装到机身 10-13）和称重池（41-44）。称重传感器（41-44）与机身（1）和起落架（4）之间的凸缘（10-13）是一体的。在起落架（4）处设有用于外部负载（39,40）的附接装置。

98. 发明授权

US08403253B1 Active IR signature target simulation system and a method thereof 有权
标题翻译：主动红外签名目标仿真系统及其方法
公开(公告)号：US08403253B1
公开(公告)日：2013-03-26
申请号：US12406485
申请日：2009-03-18
申请人： Shimon Cohen , Edi Maor
发明人： Shimon Cohen , Edi Maor
IPC分类号： B64D47/00 , F42B12/00 , F41G3/26
CPC分类号： F41J2/02 , F41J9/08
摘要： An active IR signature target simulation system which includes: a platform having a known temperature profile and a preplanned flight trajectory; a heat source carried onboard the platform, capable of producing heat following a controlled heating plan; and a control unit connected to the heat source and configured for initiating the heat source, thereby modifying the known temperature profile and generating a desired temperature profile required for sensing a simulated target IR signature during a simulation time window at a desired line of sight from the platform to an observing sensor, wherein the platform is an exo-atmospheric missile which includes an inner shell and a perforated outer shell, and wherein the heat source is a thermally active material disposed between at least a part of the inner shell and a part of the outer shell.
摘要翻译：一种主动的IR特征目标模拟系统，其包括：具有已知温度曲线和预计划飞行轨迹的平台; 在平台上携带的热源，能够按照受控的加热计划产生热量; 以及控制单元，其连接到所述热源并且被配置为启动所述热源，从而修改所述已知温度分布并且在从所述热源的期望视线的模拟时间窗口期间产生感测模拟目标IR签名所需的期望温度分布观测传感器的平台，其中所述平台是包括内壳和穿孔外壳的外部大气导弹，并且其中所述热源是设置在所述内壳的至少一部分和所述内壳的一部分之间的热活性材料外壳。

99. 发明申请

US20130037234A1 AIRCRAFT SUPPLEMENTAL LIQUID COOLER AND METHOD 有权
标题翻译：飞机辅助液体冷却器及方法
公开(公告)号：US20130037234A1
公开(公告)日：2013-02-14
申请号：US13205366
申请日：2011-08-08
申请人： Steven George Mackin
发明人： Steven George Mackin
IPC分类号： B64D47/00
CPC分类号： B64D13/08 , B64D2013/0614 , B64D2013/0674 , Y02T50/44
摘要： An aircraft may include an interior and a deployable liquid cooler. The deployable liquid cooler may include a deployable heat exchanger that may be fluidly coupled to at least one heat source of the aircraft. The deployable liquid cooler may receive a cooling system fluid from the heat source for circulation through the deployable heat exchanger. The deployable heat exchanger may be movable between a stowed position in the aircraft interior and a deployed position outside the aircraft. The deployable heat exchanger may transfer heat of the cooling system fluid to an environment outside of the aircraft when the deployable heat exchanger is in the deployed position.
摘要翻译：飞机可以包括内部和可展开的液体冷却器。可展开的液体冷却器可以包括可展开的热交换器，其可以流体地联接到飞行器的至少一个热源。可展开的液体冷却器可以从热源接收冷却系统流体，以循环通过可展开的热交换器。可展开的热交换器可以在飞行器内部的收起位置和飞行器外的展开位置之间移动。当可展开的热交换器处于展开位置时，可展开的热交换器可以将冷却系统流体的热量传递到飞机外部的环境。

100. 发明申请

US20110278393A1 AERODYNAMICALLY STABILIZED INSTRUMENT PLATFORM 有权
标题翻译：自动稳定仪器平台
公开(公告)号：US20110278393A1
公开(公告)日：2011-11-17
申请号：US12779494
申请日：2010-05-13
申请人： Geoffrey L. Bland , Ted K. Miles
发明人： Geoffrey L. Bland , Ted K. Miles
IPC分类号： B64D47/00
CPC分类号： B64D47/00 , B64B1/50 , B64C31/06 , B64C39/022
摘要： A suspension apparatus for suspending instrumentation from an airborne platform may include a generally longitudinal boom having a payload end and a tail end. Yaw and pitch stabilizers may be disposed at the tail end of the boom. A mast that may be selectively translatable on the boom may connect the boom to a tether line of the airborne platform. The payload may be attached to the payload end of the boom. The mast may be positioned axially along the boom at the center of gravity of the combination of the payload, boom, pitch stabilizer, and yaw stabilizer.
摘要翻译：用于从机载平台悬挂仪器的悬挂装置可以包括具有有效载荷端部和尾端部的大致纵向的悬臂。俯仰和俯仰稳定器可以设置在起重臂的尾端。可以在起重臂上选择性地平移的桅杆可以将起重臂连接到机载平台的系绳线。有效载荷可以附接到吊杆的有效载荷端。桅杆可以在有效载荷，起重臂，俯仰稳定器和偏航稳定器的组合的重心处沿着悬臂轴向定位。

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