公开(公告)号：US20030230671A1

公开(公告)日：2003-12-18

申请号：US10431052

申请日：2003-05-06

发明人： James P. Dunn

IPC分类号： B64B001/24

CPC分类号： B64D27/24 ,  B64D2041/005 ,  Y02T50/44 ,  Y02T50/64 ,  Y02T90/36

摘要： Electrically powered aircraft having fuel cells as at least a partial source of electrical energy. In many instances the electrical energy powers an electric motor used to propel the aircraft. In some instances, the electric output from the fuel cell would be augmented by power from special high power nullsurgenull batteries for critical takeoff and climbing, where the maximum electric power is required. In preferred embodiments, such fuel cell powered aircraft will supply oxygen to the fuel cell either from a container of oxygen carried on board the aircraft, or from a ram scoop which directs air through which the aircraft is moving to the fuel cell.

摘要翻译： 电动飞机具有至少部分电能源的燃料电池。 在许多情况下，电能为用于推进飞机的电动机供电。 在某些情况下，来自燃料电池的电力输出将通过来自特殊大功率“浪涌”电池的功率增加，用于需要最大功率的关键起飞和爬升。 在优选实施例中，这种燃料电池供电的飞行器将从飞机上承载的氧气容器或从引导飞机正在移动到燃料电池的空气的冲击勺向燃料电池供应氧气。

公开(公告)号：US20010032906A1

公开(公告)日：2001-10-25

申请号：US09791442

申请日：2001-02-23

发明人： Thomas R. Weneck ,  Mickey A. Williamson

IPC分类号： B64B001/24 ,  B64D027/00 ,  B64D029/00 ,  B64D031/00 ,  B64D033/00 ,  B64D035/00

CPC分类号： B64F5/10

摘要： An access platform comprising a series of stackable polyurethane foam block assemblies that when properly secured to each other creates a set of steps and handholds similar to a ladder. At the top of the platform a maintenance person can stand on a nonskid surface and perform the work needed at any required height. The ladder is radially curved to fit between the thrust reverser sleeve (deployed) and the inner fan duct wall. This radial diameter between the GE, Rolls Royce and Pratt Whitney engines varies within inches. The main access blocks of the access platform can be used on all three engines by using different foam wedges and wall blocks to secure the assembly tightly in place. Over 70% of the blocks are useable on all three engine types, thus reducing the number of overall parts required. Importantly, a special use tool is provided comprising interlocking foam block modules that are built up in place, are shaped to conform to the engine's inner nacelle wall and are used as a support scaffold for maintenance personnel.

摘要翻译： 一种进入平台，包括一系列可堆叠的聚氨酯泡沫块组件，当彼此适当地固定到彼此时产生类似于梯子的一组步骤和扶手。 在平台的顶部，维护人员可以站在不起眼的表面上，并执行任何所需高度所需的工作。 梯子径向弯曲以配合在推力反向器套筒（展开）和内部风扇管道壁之间。 GE，劳斯莱斯和普拉特惠特尼发动机之间的径向直径在英寸之内变化。 通过使用不同的泡沫楔块和墙体块，可将所有三个发动机的主要通道块用于所有三个发动机，以将组件紧固到位。 所有三种发动机类型都可以使用70％以上的油箱，从而减少了所需的总体零件数量。 重要的是，提供了一种特殊用途工具，其包括互锁的泡沫块模块，其被构建在适当的位置，成形为符合发动机的内部机舱壁并用作维护人员的支撑脚手架。

公开(公告)号：US20040065775A1

公开(公告)日：2004-04-08

申请号：US10606794

申请日：2003-06-27

发明人： Michel Buge ,  Jacques Lalane ,  Alain Porte ,  Eric Rambaud

IPC分类号： B64B001/24

CPC分类号： F02C7/04 ,  B29C53/824 ,  B29L2031/087 ,  B64D33/02 ,  B64F5/10 ,  F01D25/285 ,  F05D2230/64

摘要： Tooling for molding with keys for the production of air intakes without clips of substantially tubular shape, comprises a self-supporting mandrel with keys comprising at least three sectors in the form of panels, namely at least two articulated sectors (3) retractable toward the center of the mandrel and a key sector independent from the other sectors and insertable between these latter, thereby, by abutment, to define, by their external surfaces, a continuous surface corresponding to the internal surface of the air intake, elements to lock in abutted position the sectors, and a control device, disconnectable from the mandrel, of the relative displacement of the movable sectors to place them either in a molding position by abutment of the sectors, or in an unmolding position by retraction of the sectors toward the interior of the mandrel.

摘要翻译： 包括用于生产不具有基本管状形状的夹子的进气口的用于模制的模具，包括具有键的至少三个扇区的至少三个扇区的自支撑心轴，即至少两个铰接的扇区（3），其可朝着中心缩回 心轴和与其它扇区独立的键扇区，并且可插入其间，从而通过邻接，通过它们的外表面限定对应于进气口的内表面的连续表面，以锁定在邻接位置 扇区和可与芯轴断开的控制装置的可移动扇区的相对位移，以便通过扇区的邻接将它们置于模制位置，或者通过将扇区朝向内部的内部缩回而处于未模制位置 心轴。

公开(公告)号：US20030178529A1

公开(公告)日：2003-09-25

申请号：US10390908

申请日：2003-03-19

申请人： AIRBUS FRANCE

发明人： Lucien Chevalier

IPC分类号： B64B001/24

CPC分类号： B21C37/28 ,  B21C23/12 ,  B29C65/08 ,  B29C66/45 ,  B29C66/69 ,  B29C66/836

摘要： The object of the invention is a process for forming sectors of the air intake lip of an aircraft nacelle, of U-shaped cross-section, characterized in that it comprises producing, from a cylindrical billet (11) of a suitable material, by hot die pressing, a tubular profile (12) of U-shaped cross-section whose ends are interconnected, a portion of the section formed by the U having a development less by several percent than the development of the smallest cross-section of the lip sector to be obtained, in giving to the profile (12) at the outlet of the die (15) a curvature whose radius is substantially equal to the mean radius of said sector, then in forming and calibrating the profile (12) to the final shapes of the sector by hydraulic expansion in a matrix whose interior corresponds to the external volume of said sector; increased by the resilient return of the material to be expanded, and finally, cutting off the tubular product thus formed to separate the portion of U-shaped cross-section constituting said lip sector.

摘要翻译： 本发明的目的是一种用于形成U形横截面的飞机机舱的进气口的扇区的方法，其特征在于，其包括通过热的方式从适当材料的圆柱形坯料（11） 模压，U形横截面的管状轮廓（12）的端部相互连接，由U形成的部分的部分的开发比唇部部分的最小横截面的发展少几百倍 要在模具（15）的出口处向轮廓（12）提供半径大致等于所述扇区的平均半径的曲率，则在将轮廓（12）形成和校准到最终形状 通过液体膨胀在其内部对应于所述扇区的外部体积的矩阵中; 通过待膨胀的材料的弹性回复而增加，最后，切断如此形成的管状产品以分离构成所述唇缘部分的U形横截面的部分。

公开(公告)号：US20020113167A1

公开(公告)日：2002-08-22

申请号：US10076898

申请日：2002-02-14

发明人： Jose Albero ,  Charles E. Lents ,  Michael K. Sahm ,  Richard C. Welch

IPC分类号： B64B001/24 ,  B64D027/00 ,  B64D029/00 ,  B64D031/00 ,  B64D033/00 ,  B64D035/00

CPC分类号： F02C7/32 ,  B64D13/06 ,  B64D2013/0611 ,  B64D2013/0618 ,  B64D2013/064 ,  B64D2013/0644 ,  Y02T50/54 ,  Y02T50/56

摘要： The present invention relates to an improved architecture for an aircraft. The aircraft has a first engine, a first gearbox associated with the first engine, a first starter/generator associated with the gearbox, and a first motor drive connected to the first starter/generator for providing the starter/generator with electric power to start the first engine and to receive electric power from the starter/generator after the engine has been started to operate electrically driven systems onboard the aircraft. The aircraft preferably further has at least one other engine which has a gearbox and a starter/generator associated with it and at least a second motor drive connected to the starter/generator. The electrically driven systems operated by the motor drive(s) include an environmental control system, a wing anti-icing system, an aircraft control system, and the aircraft fuel system. The aircraft also includes an auxiliary power unit for supplying electrical power to at least the first motor drive for initiating operation of the first engine.

摘要翻译： 本发明涉及一种用于飞机的改进的架构。 飞机具有第一发动机，与第一发动机相关联的第一变速箱，与变速箱相关联的第一起动/发电机，以及连接到第一起动器/发电机的第一电动机驱动器，用于向起动器/发电机提供电力以启动 第一发动机，并且在发动机起动之后从起动器/发电机接收电力来操作飞机上的电驱动系统。 飞机优选地还具有至少一个其它发动机，其具有齿轮箱和与其相关联的起动器/发电机以及连接到起动器/发电机的至少第二马达驱动器。 由电动机驱动器操作的电驱动系统包括环境控制系统，机翼防冰系统，飞机控制系统和飞机燃料系统。 该飞机还包括辅助动力单元，用于向至少第一马达驱动器提供电力以启动第一发动机的操作。

公开(公告)号：US20040079834A1

公开(公告)日：2004-04-29

申请号：US10280411

申请日：2002-10-25

发明人： Arvin Shmilovich ,  Yoram Yadlin ,  David M. Smith ,  Roger W. Clark

IPC分类号： B64B001/24

CPC分类号： F02K3/06 ,  B64D33/02 ,  B64D2033/022 ,  F02C7/04 ,  F02C7/042 ,  F02C7/05

摘要： The active system for the wide area suppression of a ground vortex generated by the engine of an aircraft includes an actuator assembly in fluid communication with a fluid source; and, at least one nozzle assembly, including at least one movable nozzle. The movable nozzle is in fluid communication with the actuator assembly for receiving fluid from the actuator assembly. The actuator assembly controls the motion of the movable nozzle, wherein fluid is injected over a desired region relative to an inlet of the engine to disrupt the flow structure of a ground vortex, thus mitigating ground vortex ingestion. This ensures the operational health of the engine during airplane maneuvering on the ground.

摘要翻译： 用于广泛地抑制由飞行器的发动机产生的地面涡流的主动系统包括与流体源流体连通的致动器组件; 以及包括至少一个可移动喷嘴的至少一个喷嘴组件。 可移动喷嘴与致动器组件流体连通，用于从致动器组件接收流体。 致动器组件控制可移动喷嘴的运动，其中流体相对于发动机的入口喷射在期望的区域上，以破坏地面涡流的流动结构，从而减轻地面涡旋摄取。 这确保了在飞机在地面上操纵时发动机的运行健康。

公开(公告)号：US20030205641A1

公开(公告)日：2003-11-06

申请号：US10299863

申请日：2002-11-20

申请人： Ion America Corporation

发明人： James McElroy ,  Matthias Gottmann

IPC分类号： B64B001/24

CPC分类号： B64D27/24 ,  B64C39/024 ,  B64C2201/042 ,  B64D2041/005 ,  B64D2211/00 ,  H01M8/04201 ,  H01M16/00 ,  H01M2008/1293 ,  H01M2250/20 ,  Y02E60/525 ,  Y02T50/44 ,  Y02T50/55 ,  Y02T50/62 ,  Y02T90/32 ,  Y02T90/36

摘要： A Solid Oxide Regenerative Fuel Cell (SORFC) or a Solid Oxide Fuel Cell (SOFC) is incorporated into an electrically powered airplane to provide either regenerative or primary electrical energy. The SORFC, the SOFC, or any other suitable fuel cell within an airplane may also be used to heat payload or equipment within the airplane. The SORFC is not only capable of generating electrical energy from fuel and a suitable oxidizer, but can also generate fuel through electrolysis of oxidized fuel. Thus, the SORFC system powering an airplane can obtain oxygen oxidant reactant from the air and avoid the complexity, weight, volume, and cost associated with oxygen storage.

摘要翻译： 将固体氧化物再生燃料电池（SORFC）或固体氧化物燃料电池（SOFC）并入电动飞机中以提供再生或初级电能。 飞机内的SORFC，SOFC或任何其他合适的燃料电池也可用于加热飞机内的有效载荷或设备。 SORFC不仅能够从燃料和合适的氧化剂产生电能，而且还可以通过电解氧化燃料产生燃料。 因此，为飞机供电的SORFC系统可以从空气中获得氧氧化剂反应物，并避免与储氧相关的复杂性，重量，体积和成本。

公开(公告)号：US20020162914A1

公开(公告)日：2002-11-07

申请号：US10077277

申请日：2002-02-14

发明人： Jose Albero ,  Louis J. Bruno ,  Richard Dussault ,  Charles E. Lents ,  Wayne A. Thresher ,  Michael K. Sahm ,  Robert G. Thompson

IPC分类号： B64B001/24 ,  B64D027/00 ,  B64D029/00 ,  B64D031/00

CPC分类号： B64D15/04 ,  B64D13/06 ,  B64D27/16 ,  B64D41/00 ,  B64D2013/0611 ,  B64D2013/064 ,  B64D2013/0644 ,  F02C7/32 ,  F05D2220/50 ,  Y02T50/44 ,  Y02T50/56 ,  Y02T50/671

摘要： The present invention relates to an integrated aircraft system which comprises an aircraft frame, a nacelle cowl mounted to the aircraft frame, a primary gas turbine engine mounted within the nacelle cowl, a secondary power system incorporated within the nacelle cowl and being driven by a flow of air created by or through the engine, and an electrical power and cooling unit for supplying electrical power and cabin cooling air. The electrical power and cooling unit is pneumatically driven by engine bleed air.

摘要翻译： 本发明涉及一种集成的飞行器系统，其包括飞机框架，安装到飞行器机架的机舱罩，安装在机舱罩内的主要燃气涡轮发动机，并入机舱罩内的二次电力系统，并由流动 由发动机产生或通过发动机产生的空气，以及用于供应电力和舱室冷却空气的电力和冷却单元。 电力和冷却单元由发动机排放气体气动驱动。

公开(公告)号：US20040060548A1

公开(公告)日：2004-04-01

申请号：US10255189

申请日：2002-09-26

发明人： Ernest A. Carroll

IPC分类号： B64B001/24 ,  F02B033/00

CPC分类号： F02B33/40 ,  F02B33/446

摘要： A supercharging system for supplying pressurized combustion air to a reciprocating piston engine of an aircraft at high altitudes. The engine has an output shaft on which the propeller is supported, together with a small ducted centrifugal fan. The duct leads to the intake side of the engine. A diverter is movable to one position constraining pressurized air to enter the engine through the intake side, and a second position which diverts compressed air away from the intake side. Preferably, the diverter also opens the intake side to unpressurized atmospheric air in the first position, so that the engine is naturally aspirated. Natural aspiration is employed at low altitudes and supercharging is employed at altitudes wherein there is an oxygen deficiency. Preferably, the centrifugal fan is located between the propeller and the engine block, has blades staggered from those of the propeller so as to be directly exposed to incoming air. The centrifugal fan blades are preferably of different pitch than the propeller blades.

摘要翻译： 一种用于向高空飞行器的往复活塞发动机提供加压燃烧空气的增压系统。 发动机具有输出轴，螺旋桨被支撑在该输出轴上，与小风管离心风扇一起。 管道通向发动机的进气侧。 分流器可移动到限制加压空气的一个位置，以通过进气侧进入发动机，以及将压缩空气从进气侧分流的第二位置。 优选地，分流器还将第一位置的未加压大气的进气侧打开，使得发动机被自然地吸气。 在低海拔地区采用天然吸气，在有缺氧的高海拔地区采用增压。 优选地，离心风扇位于推进器和发动机缸体之间，具有与螺旋桨的叶片交错的叶片，以便直接暴露于进入的空气中。 离心风扇叶片优选地具有与螺旋桨叶片不同的桨距。

公开(公告)号：US20020134887A1

公开(公告)日：2002-09-26

申请号：US09816598

申请日：2001-03-22

发明人： Hersheng Lin ,  Shen-Yeh Chen

IPC分类号： B64B001/24 ,  B64D027/00 ,  B64D029/00

CPC分类号： F01D21/045 ,  B64D7/00 ,  B64D35/08

摘要： A ballistic shield containment system for preventing fragments expelled from an engine assembly from penetrating the casing of an adjacently disposed engine is provided. In a turboprop engine assembly having two power sections connected through a combining gearbox to a single propeller shaft, it is imperative that failure of the rotor disks in one engine not cause failure of the remaining engine. A substantially rectangular shaped panel member is supported at approximately the mid-point between the power sections by a support truss system extending from the panel to a space frame. The space frame is supported by a separate truss system connected to fixed bulkhead. The panel includes reinforcing ribs to prevent fragment penetration and excessive deformation. Each of the truss members is attached at either end to a spherical bearing capable of transmitting force loads while preventing transmission of moment loads.

摘要翻译： 提供了一种用于防止从发动机组件排出的碎片渗透相邻设置的发动机的壳体的防弹屏蔽容纳系统。 在具有通过组合齿轮箱连接到单个螺旋桨轴的两个动力部分的涡轮螺旋桨发动机组件中，必须使一个发动机中的转子盘的故障不会导致剩余发动机的故障。 大致矩形形状的面板构件通过从面板延伸到空间框架的支撑桁架系统大致在功率部分之间的中点处被支撑。 空间框架由连接到固定隔板的单独的桁架系统支撑。 面板包括加强肋，以防止碎片穿透和过度变形。 每个桁架构件的任一端附接到能够传递力载荷的球面轴承，同时防止力矩载荷的传递。