专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US4598890A Avionic control system 失效
公开(公告)号：US4598890A
公开(公告)日：1986-07-08
申请号：US519288
申请日：1983-08-01
申请人： Hans K. Herzog , Seiya Sakurai
发明人： Hans K. Herzog , Seiya Sakurai
IPC分类号： B64C13/50 , G05D1/00
CPC分类号： B64C13/503 , G05D1/0077 , Y02T50/54 , Y02T50/545
摘要： An all-electric powered flight control system for an aircraft incorporating fault-tolerant avionics combined with a redundant power actuation control system utilizing electro-mechanical devices for actuating aerodynamic control surfaces; and wherein, the redundancy is implemented through the division of the total aerodynamic surface area to be actuated into multi-segments, with each control segment having its own channel in the avionic control system. The avionic control system is effective in minimizing the effects of power actuated control loads reacting through aircraft structure by the incorporation of an electronic gain control power module which is positioned between the power output side of an actuator (e.g., an electro-mechanical or electro-hydraulic device) and the aerodynamic control surface or segment being actuated. Further, the avionic control system includes means for passivating a single control segment of the multi-segmented aerodynamic control surface upon the malfunction of either its avionic control channel or its power actuator output.

2. 发明授权

US4546939A Energy efficient ECS powered by a variable voltage/variable frequency power system 失效
标题翻译：节能ECS由可变电压/变频电力系统供电
公开(公告)号：US4546939A
公开(公告)日：1985-10-15
申请号：US584699
申请日：1984-02-29
申请人： Michael J. Cronin
发明人： Michael J. Cronin
IPC分类号： B64D13/06 , F04D27/02 , F25B9/00 , B64D13/02
CPC分类号： F25B9/004 , B64D13/06 , F04D27/0261 , B64D2013/0644 , Y02T50/54 , Y02T50/545 , Y02T50/56
摘要： The invention is an ECS system designed to utilize an induction motor (12) and a cabin compressor (14) for providing pressurized air that serves as a source of energy for heating, cooling, pressurizing and other air needs of modern aircraft. An aircraft engine driven generator, preferably a permanent-magnet generator (of the samarium-cobalt, SmCo, type), furnishes variable-voltage/variable frequency, VV/VF, power to the motor (12). The electric motor itself in the preferred embodiment is a highly reliable squirrel-cage induction motor (12) powered directly from the VV/VF supply, with the result that its speed is proportional to the generator frequency, which in turn is dependent on the aircraft engine speed. The main cabin compressor (14) and a secondary (auxiliary) supercharging compressor (18) are both mounted on the motor shaft. The motor-compressor configuration is further characterized in that the ac motor has pole-changing winding (typically two), which permits two speed operation, while the cabin compressor is provided with inlet guide vanes (16). The interactive combination of these two features makes it possible to furnish the requisite air mass flow and pressurization levels over the conditions of variable air density and variable atmospheric pressure, as the airplane operates throughout its flight envelope.
摘要翻译：本发明是一种设计用于利用感应电动机（12）和客舱压缩机（14）的ECS系统，用于提供用作现代飞机的加热，冷却，加压和其它空气需求的能量来源的加压空气。飞机发动机驱动的发电机，优选地是钐 - 钴的SmCo型永磁发电机，为电动机（12）提供可变电压/可变频率VV / VF。在优选实施例中的电动机本身是直接从VV / VF电源供电的高度可靠的鼠笼式感应电机（12），结果是其速度与发电机频率成正比，发电机频率依赖于飞行器引擎速度。主机舱压缩机（14）和次级（辅助）增压压缩机18都安装在电动机轴上。电动机 - 压缩机结构的特征还在于，交流电动机具有变速绕组（通常为两个），其允许两个速度的操作，而机舱压缩机设置有入口导向叶片（16）。这两个特征的交互式组合使得当飞机在整个飞行包线上运行时，可以在可变空气密度和可变大气压力的条件下提供所需的空气质量流量和加压水平。

3. 发明授权

US4434624A Energy-efficient all-electric ECS for aircraft 失效
标题翻译：飞机节能全电动ECS
公开(公告)号：US4434624A
公开(公告)日：1984-03-06
申请号：US248603
申请日：1981-03-27
申请人： Michael J. Cronin , Gordon Seid
发明人： Michael J. Cronin , Gordon Seid
IPC分类号： B64D13/06 , F25B5/02 , F25B27/00 , F28B9/00
CPC分类号： B64D13/06 , F25B27/00 , F25B5/02 , B64D2013/0644 , B64D2013/0674 , B64D2013/0688 , Y02T50/44 , Y02T50/54 , Y02T50/545 , Y02T50/56
摘要： The invention is an energy-efficient all-electric environmental control system (70). The system includes a cabin compressor (16) and a Freon compressor (14), both of which are commonly driven by a two-speed electric motor (12). The motor (12) operates at low speed at low altitudes and on the ground to drive the Freon compressor (14). Freon fluid then cools the electric motor (12) and the cabin (18) and avionics (56) by means of the evaporator dehumidifier systems (72) and (74), respectively. At high altitudes the electric motor (12) runs at high speed to drive the cabin compressor (16) to provide pressurization for the cabin (18). In this operation mode, the Freon compressor can be disconnected via an electromagnetic clutch (48).The ECS (70) also includes a liquid Freon pump (52) which can be utilized when the Freon compressor is disconnected or bypassed to circulate liquid Freon to cool the electric motor (12) and to circulate through the evaporators (38) and (76). The pump (52) is driven by an ac or dc motor (54).
摘要翻译：本发明是一种节能全电动环境控制系统（70）。该系统包括舱室压缩机（16）和氟利昂压缩机（14），两者都通常由双速电动机（12）驱动。马达（12）在低海拔低速运行，并在地面上运行以驱动氟利昂压缩机（14）。然后，氟利昂液体分别通过蒸发器除湿器系统（72）和（74）冷却电动机（12）和机舱（18）和航空电子设备（56）。在高海拔处，电动机（12）以高速运行以驱动机舱压缩机（16），以为舱室（18）提供加压。在该操作模式中，可通过电磁离合器（48）断开氟利昂压缩机。 ECS（70）还包括液体氟利昂泵（52），当氟利昂压缩机断开或旁路以循环氟利昂以冷却电动机（12）并循环通过蒸发器（38）和（76 ）。泵（52）由交流或直流电动机（54）驱动。

4. 发明公开

EP0422135A4 NO BREAK POWER TRANSFER CONTROL FOR A VSCF POWER GENERATING SYSTEM 失效
标题翻译： VSCF发电系统不用断电
公开(公告)号：EP0422135A4
公开(公告)日：1993-05-05
申请号：EP90901385
申请日：1989-12-08
申请人： SUNDSTRAND CORPORATION
发明人： RECKER, BRADLEY, J. , ROZMAN, CHRISTOPHER, J. , ROE, DERRICK, I.
IPC分类号： H02J3/42 , H02J3/38 , H02J9/00
CPC分类号： H02J3/42 , Y02T50/54 , Y02T50/545 , Y10T307/313 , Y10T307/516 , Y10T307/735
摘要： In aircraft applications, it may be necessary or desirable to transfer one or more loads between a variable speed, constant frequency (VSCF) power generating system and a further source of AC power. Prior controls for effecting such transfer, however, have been unduly complex. In order to overcome this problem, a control for a VSCF system senses the deviation of a parameter of the power developed by an inverter of the system relative to a parameter of the power developed by an AC power source and controls the inverter in accordance with such deviation to cause the parameter of the power developed thereby to approach the parameter of the power developed by the AC power source. The inverter and the AC power source are connected in parallel across one or more loads when the parameter deviation is within a certain range. Either the inverter or the AC power source is thereafter disconnected a certain time after the two were connected in parallel to complete the power transfer.

5. 发明申请

WO2006024005A2 ELECTRICAL STARTING, GENERATION, CONVERSION AND DISTRIBUTION SYSTEM ARCHITECTURE FOR A MORE ELECTRIC VEHICLE 审中-公开
标题翻译：更多电动车的电气起动，产生，转换和分配系统架构
公开(公告)号：WO2006024005A2
公开(公告)日：2006-03-02
申请号：PCT/US2005030221
申请日：2005-08-24
申请人： HONEYWELL INT INC , MICHALKO RODNEY G
发明人： MICHALKO RODNEY G
CPC分类号： H02J4/00 , B64D2221/00 , Y02T50/54 , Y02T50/545 , Y10T307/50 , Y10T307/625 , Y10T307/718
摘要： A system (200) for distributing electrical power, includes: a first high voltage AC power distributing unit (210a) including a first high voltage AC bus (214a-1, 214a-2), which is selectively connected to a first high voltage AC generator (224a), and a first start bus (212a); a second high voltage AC power distributing unit (210b) including a second high voltage AC bus (214b-1, 214b-2), which is selectively connected to a second high voltage AC generator (224b), and a second start bus (212b); a first high voltage DC power distributing unit (240a) including, a first high voltage DC bus (246a), and a second high voltage DC power distributing unit (240b) including a second high voltage DC bus (246b). The first high voltage AC bus (214a-1, 214a-2) is selectively connectable to the second high voltage AC bus (214b-1, 214b-2), such that the system (200) provides redundancy for high voltage power distribution.
摘要翻译：一种用于分配电力的系统（200），包括：第一高压交流电力分配单元（210a），其包括第一高压AC总线（214a-1,214a-2），其被选择性地连接到第一高压AC 发电机（224a）和第一起动总线（212a）; 包括选择性地连接到第二高压AC发电机（224b）的第二高压AC总线（214b-1,214b-2）的第二高压交流配电单元（210b）和第二起动总线）; 包括第一高压DC总线（246a）和包括第二高压DC总线（246b）的第二高压直流配电单元（240b）的第一高压直流配电单元（240a）。第一高压AC总线（214a-1,214a-2）可选择性地连接到第二高压AC总线（214b-1,214b-2），使得系统（200）为高压配电提供冗余。

6. 发明申请

WO2009068807A3 METHOD FOR CONTROLLING THERMAL EFFLUENTS GENERATED BY AN AIRCRAFT AND COOLING DEVICE FOR AN AIRCRAFT IMPLEMENTING SAID METHOD 审中-公开
标题翻译：用于控制飞行器产生的热流的方法和用于飞机的冷却装置实施所述方法
公开(公告)号：WO2009068807A3
公开(公告)日：2009-12-03
申请号：PCT/FR2008052028
申请日：2008-11-12
申请人： AIRBUS OPERATIONS SAS , AIRBUS GMBH , BULIN GUILLAUME , DITTMAR JAN
发明人： BULIN GUILLAUME , DITTMAR JAN
IPC分类号： B64D37/34 , F02C7/18
CPC分类号： B64D37/34 , B64D33/10 , B64D2013/0614 , B64D2013/0659 , F02C7/224 , Y02T50/54 , Y02T50/545 , Y02T50/671
摘要： The invention relates to a method for controlling the thermal effluents of an aircraft including an airframe (110) and at least one propulsion unit (112), wherein said at least one propulsion unit (112) includes a turbomachine (116) supplied with fuel via a fuel supply circuit (122) extending from a tank (124) provided at the airframe (110), said airframe (110) including at least one thermal effluent source (134), characterised in that it comprises scattering at least partially, at the level of at least one propulsion unit (112), the thermal effluents generated at the airframe (110) by using the fuel used for supplying the turbomachine (116) as a heat-carrier fluid.
摘要翻译：本发明涉及一种用于控制飞行器的热流出物的方法，所述飞机包括机身（110）和至少一个推进单元（112），其中所述至少一个推进单元（112）包括涡轮机（116）（110）延伸的燃料供应回路（122），所述机身（110）包括至少一个热流出物源（134），其特征在于，所述燃料供应回路包括至少部分地在所述通过使用用于供应涡轮机械（116）的燃料作为热载体流体而在机身（110）处产生热流出物。

7. 发明申请

WO02066323A2 IMPROVED AIRCRAFT ARCHITECTURE WITH A REDUCED BLEED AIRCRAFT SECONDARY POWER SYSTEM 审中-公开
标题翻译：改进的飞机架构与减少的飞机二次电源系统
公开(公告)号：WO02066323A2
公开(公告)日：2002-08-29
申请号：PCT/US0204734
申请日：2002-02-14
申请人： UNITED TECHNOLOGIES CORP
发明人： ALBERO JOSE , LENTS CHARLES E , SAHM MICHAEL K , WELCH RICHARD C
IPC分类号： B64D13/06 , F02C7/32 , B64D
CPC分类号： F02C7/32 , B64D13/06 , B64D2013/0611 , B64D2013/0618 , B64D2013/064 , B64D2013/0644 , Y02T50/54 , Y02T50/545 , 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。

8. 发明申请

WO0120187A9 INTEGRATED AIRCRAFT WHEEL, BRAKE AND AXLE FOR ALL-ELECTRIC AIRCRAFT BRAKING SYSTEM 审中-公开
标题翻译：全电动制动系统集成飞轮，制动和轴
公开(公告)号：WO0120187A9
公开(公告)日：2002-10-03
申请号：PCT/US0024944
申请日：2000-09-12
申请人： GOODRICH CO B F
发明人： BADEN BRADLEY J
IPC分类号： B64C25/36 , F16D55/00 , F16D55/36 , F16D65/14 , F16D65/18 , F16D65/847
CPC分类号： F16D65/847 , B64C25/36 , F16D55/36 , F16D65/186 , F16D2055/0058 , F16D2055/0091 , F16D2065/785 , F16D2121/24 , F16D2125/40 , Y02T50/54 , Y02T50/545
摘要： An integrated wheel, brake and axle structure (10) for an aircraft comprises a tubular axle (24), and a wheel hub (44) rotatably mounted interiorly of the tubular axle and accessible at an axial end thereof for mounting of a wheel (18) thereto. A brake disk stack (74), having front and rear axial ends, includes alternating rotor and stator disks (78, 80) mounted with respect to the wheel support and wheel for relative axial movement. Each rotor disk is coupled to the wheel for rotation therewith and each stator disk is coupled to the axle for support against rotation. In such arrangement, the wheel web (62) functions as a back pressure member for applying force to the outboard end of the disk stack. A cooling fan (140) is provided interior of the axle for generating a cooling flow of air across the brake disk stack.
摘要翻译：一种用于飞行器的集成轮，制动器和轴结构（10）包括管状轴（24）和轮毂（44），所述轮毂（44）可旋转地安装在所述管状轴的内部并且可在其轴向端部接近以安装轮（18 ）。具有前后轴向端的制动盘叠（74）包括相对于车轮支撑件和车轮安装的相对轴向运动的交替的转子和定子盘（78,80）。每个转子盘联接到车轮以与其一起旋转，并且每个定子盘联接到车轴以防止旋转。在这种布置中，轮网（62）用作用于向盘堆的外侧端施加力的背压构件。冷却风扇（140）设置在轴的内部，用于产生穿过制动盘组的空气的冷却流。

9. 发明授权

US5914542A Super capacitor charging 失效
标题翻译：超级电容器充电
公开(公告)号：US5914542A
公开(公告)日：1999-06-22
申请号：US843406
申请日：1997-04-15
申请人： Joseph A. Weimer , Bick T. Nguyen , Marian K. Kazimierczuk , Brett A. Jordan
发明人： Joseph A. Weimer , Bick T. Nguyen , Marian K. Kazimierczuk , Brett A. Jordan
IPC分类号： H02J7/34 , H01H47/00
CPC分类号： H02J7/345 , B64D2221/00 , Y02T50/54 , Y02T50/545 , Y10T307/344 , Y10T307/50 , Y10T307/615 , Y10T307/707 , Y10T307/724 , Y10T307/826
摘要： An aircraft electrical energy supply bus supplementing arrangement based on large capacitor or super capacitor storage of electrical energy for bus supplementation. Supplying of bus energy to the large capacitor is addressed in the invention. In this supplying energy is removed from the aircraft bus during quiescent conditions under the control of a energy coupling circuit which has a plurality of different energy removal rates, rates which are selected in response to the yet needed amount of capacitor charging and in a time-constant-controlled manner. Feedback control of this charging time constant selection is employed along with passive electrical device dissipation of major fractions of the time constant apparatus energy losses.
摘要翻译：基于大容量电容器或超级电容器存储用于总线补充的电能的飞机电能供应总线补充装置。在本发明中解决了向大电容器提供总线能量。在能量耦合电路的控制下，在静态条件下，在具有多个不同的能量去除率的速率的静态条件下，这种供电能量被从飞机母线上移除，这些速率是响应于所需的电容器充电量而选择的，恒定控制的方式。采用这种充电时间常数选择的反馈控制以及时间常数设备能量损耗的主要部分的被动电气设备耗散。

10. 发明授权

US4937462A No break power transfer control for a VSCF power generating system 失效
标题翻译： VSCF发电系统不断断电力传输控制
公开(公告)号：US4937462A
公开(公告)日：1990-06-26
申请号：US300820
申请日：1989-01-23
申请人： Bradley J. Recker , Christopher J. Rozman , Derrick I. Roe
发明人： Bradley J. Recker , Christopher J. Rozman , Derrick I. Roe
IPC分类号： H02J3/42
CPC分类号： H02J3/42 , Y02T50/54 , Y02T50/545 , Y10T307/313 , Y10T307/516 , Y10T307/735
摘要： In aircraft applications, it may be necessary or desirable to transfer one or more loads between a variable speed, constant frequency (VSCF) power generating system and a further source of AC power. Prior controls for effecting such transfer, however, have been unduly complex. In order to overcome this problem, a control for a VSCF system senses the deviation of a parameter of the power developed by an inverter of the system relative to a parameter of the power developed by an AC power source and controls the inverter in accordance with such deviation to cause the parameter of the power developed thereby to approach the parameter of the power developed by the AC power source. The inverter and the AC power source are connected in parallel across one or more loads when the parameter deviation is within a certain range. Either the inverter or the AC power source is thereafter disconnected a certain time after the two were connected in parallel to complete the power transfer.
摘要翻译：在飞机应用中，可能需要或希望在变速，恒定频率（VSCF）发电系统和另外的交流电源之间传送一个或多个负载。然而，进行此类转移的先前控制措施过于复杂。为了解决这个问题，VSCF系统的控制意识到由系统的逆变器开发的功率参数相对于由AC电源产生的功率的参数的偏差，并根据这种控制来控制逆变器导致由此产生的功率的参数接近由AC电源产生的功率的参数的偏差。当参数偏差在一定范围内时，逆变器和交流电源并联连接一个或多个负载。此后，在两个并联连接之后，变频器或交流电源断开一定时间以完成电力传输。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式