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11. 发明授权

US4649484A Avionic control system 失效
标题翻译：航空电子控制系统
公开(公告)号：US4649484A
公开(公告)日：1987-03-10
申请号：US754330
申请日：1985-07-12
申请人： Hans K. Herzog , Seiya Sakurai
发明人： Hans K. Herzog , Seiya Sakurai
IPC分类号： B64C13/50 , G05D1/00 , G06F15/50
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.
摘要翻译：一种用于搭载容错航空电子设备的飞机的全电动飞行控制系统，结合利用机电装置致动空气动力学控制表面的冗余动力驱动控制系统; 并且其中，冗余通过将待致动的总空气动力学表面积的划分实现为多段，每个控制段在航空电子控制系统中具有其自己的通道。航空电子控制系统通过结合位于致动器的功率输出侧（例如机电或电动机械）之间的电子增益控制功率模块来最小化通过飞行器结构反应的动力驱动的控制负载的影响，液压装置）和空气动力学控制表面或段被致动。此外，航空电子控制系统包括用于在其航空电子控制通道或其动力致动器输出的故障时钝化多段气动控制表面的单个控制段的装置。

12. 发明授权

US4572053A Ordnance ejector system 失效
标题翻译：装备喷射器系统
公开(公告)号：US4572053A
公开(公告)日：1986-02-25
申请号：US583718
申请日：1984-02-27
申请人： Joseph A. Sosnowski , Gary Black , Robert J. Pritchard
发明人： Joseph A. Sosnowski , Gary Black , Robert J. Pritchard
IPC分类号： B64D1/06 , H02K41/025 , F41F5/02
CPC分类号： H02K41/025 , B64D1/06 , Y02T50/54 , Y02T50/545 , Y10T74/18696 , Y10T74/19721
摘要： An energy storage and release system (10) in combination with an aircraft (11) for ejecting an ordnance from the aircraft, the system (10) including a housing (22) mounted in the aircraft (11) and a drive shaft (24) having an outer end (26) and inner end (28) supported within the housing (22) for reciprocating axial movement of the outer end (26) into and out of the housing (22). An energy storage system including a flywheel (30) rotatably mounted within the housing (22) and operatively connected to the drive shaft (24) moves the outer end (26) of the drive shaft (24) axially out of the housing (22) to eject an ordnance (18). A linear induction motor (16) powers the flywheel (30).
摘要翻译：一种与用于从飞机弹出弹药的飞行器（11）组合的能量储存和释放系统（10），所述系统（10）包括安装在飞机（11）中的壳体（22）和驱动轴（24）具有支撑在壳体（22）内的外端（26）和内端（28），用于使外端（26）进入和离开壳体（22）的往复轴向运动。包括可旋转地安装在壳体（22）内并且可操作地连接到驱动轴（24）的飞轮（30）的能量存储系统使驱动轴（24）的外端（26）轴向移动离开壳体（22），弹出弹药（18）。线性感应电动机（16）为飞轮（30）供电。

13. 发明授权

US4462561A 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：US4462561A
公开(公告)日：1984-07-31
申请号：US382491
申请日：1982-05-27
申请人： Michael J. Cronin
发明人： Michael J. Cronin
IPC分类号： B64D13/06 , F04D27/02 , F25B9/00 , B64D13/08 , B64D13/02
CPC分类号： B64D13/06 , F04D27/0261 , B64D2013/0644 , F25B9/004 , Y02T50/54 , Y02T50/545 , Y02T50/56 , Y10S62/05
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，SmCo型的永磁发电机，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。

14. 发明授权

US5813630A Multi-mode secondary power unit 失效
标题翻译：多模二次电源单元
公开(公告)号：US5813630A
公开(公告)日：1998-09-29
申请号：US721907
申请日：1996-09-27
申请人： Kenneth R. Williams
发明人： Kenneth R. Williams
IPC分类号： B64D13/06 , B64D41/00 , B64D13/00
CPC分类号： B64D13/06 , B64D41/00 , B64D2013/0611 , Y02T50/54 , Y02T50/545 , Y02T50/56
摘要： The present invention provides a multi-mode secondary power unit comprising a first starter/generator unit operably coupled to a shaft. The first starter/generator motor is operable in a motor mode for causing rotational movement of the shaft and is operable in a generator mode for generating electric power from rotational movement of the shaft. A thermal engine is operably coupled to the shaft and is operable in a fuel burning mode for causing rotational movement of said shaft and is operable in a non fuel burning mode for receiving rotational movement from the shaft. A load compressor is operably coupled to the shaft for pressurizing air to a predetermined level.
摘要翻译：本发明提供一种多模次级动力单元，其包括可操作地联接到轴的第一起动/发电机单元。第一起动/发电电动机可以在电动机模式下操作以引起轴的旋转运动，并且可以在发电机模式下操作以从轴的旋转运动产生电力。热引擎可操作地联接到轴上，并且可在燃料燃烧模式下操作以引起所述轴的旋转运动，并且可在非燃料燃烧模式下操作以接收来自轴的旋转运动。负载压缩机可操作地联接到轴上以将空气加压到预定水平。

15. 发明授权

US5317500A Active no-break power transfer control for a VSCF power generating system 失效
标题翻译： VSCF发电系统的主动无断开电力传输控制
公开(公告)号：US5317500A
公开(公告)日：1994-05-31
申请号：US926608
申请日：1992-08-06
申请人： Steven M. Iden , Edwin J. Shires , Waleed Said
发明人： Steven M. Iden , Edwin J. Shires , Waleed Said
IPC分类号： H02J3/04 , H02J9/06 , H02M7/537
CPC分类号： H02J9/062 , H02J3/04 , Y02T50/54 , Y02T50/545 , Y10T307/313 , Y10T307/625 , Y10T307/735
摘要： An improvement in a control for a DC link power converter includes a phase command signal generator responsive to DC power on a DC link wherein the phase command signal generator develops a phase command signal for a control of the power converter whereby a parameter the DC power is caused to approach a certain level.
摘要翻译：对DC链路功率转换器的控制的改进包括响应于DC链路上的DC电力的相位指令信号发生器，其中相位指令信号发生器产生用于功率转换器的控制的相位指令信号，导致达到一定水平。

16. 发明授权

US4575027A Electromechanical actuator system with anti-jamming features 失效
标题翻译：具有抗干扰功能的机电执行器系统
公开(公告)号：US4575027A
公开(公告)日：1986-03-11
申请号：US495013
申请日：1983-05-16
申请人： Michael J. Cronin
发明人： Michael J. Cronin
IPC分类号： B64C13/42
CPC分类号： B64C13/42 , Y02T50/54 , Y02T50/545 , Y10T74/20213
摘要： An actuator system for controlling the position of an aerodynamic control surface of an aircraft is disclosed. The actuator system (10) comprises a rotary actuator (12) rotatably mounted to the aircraft structure (20) with the actuator having an output member (22) adapted to be coupled to the control surface. A latch assembly (37) is provided which is mounted to the structure which releasably engages the actuator. Preferably, the latch assembly (37) comprises a grooved flange (38) mounted on the actuator (12) and a solenoid (47) mounted to the aircraft structure which is adapted to move a locking pin (44) from a first position in engagement with the grooved flange (38) to a second position out of engagement with the groove. In a second embodiment, a second rotary actuator (114) is mounted to the aircraft structure and is adapted to rotate the actuator (81) upon its failure and after the latch assembly is activated. In a third embodiment a second rotary actuator (164) is coupled to the input shaft (160) of the actuator (150) and after the latch assembly is activated rotation of the actuator (150) is accomplished by the second rotary actuator (164) via the input shaft. In addition, should the actuator assembly fail electrically, and not be jammed, the second actuator (164) drives the input shaft which in turn drives the output member and thus the latch assembly need not be activated.
摘要翻译：公开了一种用于控制飞行器的空气动力学控制表面的位置的致动器系统。致动器系统（10）包括可旋转地安装到飞机结构（20）的旋转致动器（12），致动器具有适于联接到控制表面的输出构件（22）。提供了一种闩锁组件（37），其安装到可释放地接合致动器的结构。优选地，闩锁组件（37）包括安装在致动器（12）上的槽形凸缘（38）和安装到飞行器结构的螺线管（47），其适于使锁定销（44）从第一位置移动接合其中带槽的凸缘（38）到与槽不接合的第二位置。在第二实施例中，第二旋转致动器（114）安装到飞机结构，并且适于在致动器（81）的故障时和在闩锁组件被启动之后旋转致动器（81）。在第三实施例中，第二旋转致动器（164）联接到致动器（150）的输入轴（160），并且在闩锁组件被激活后，致动器（150）的旋转由第二旋转致动器（164）完成，通过输入轴。此外，如果致动器组件电动失效，并且不卡住，则第二致动器（164）驱动输入轴，其又驱动输出构件，因此闩锁组件不需要被激活。

17. 发明授权

US4487034A 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：US4487034A
公开(公告)日：1984-12-11
申请号：US519798
申请日：1983-08-03
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 , F25D9/00
CPC分类号： B64D13/06 , F25B27/00 , F25B5/02 , B64D2013/0614 , B64D2013/0644 , 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。

18. 发明授权

US1222428A Wheeled scraper. 失效
标题翻译：轮式刮刀
公开(公告)号：US1222428A
公开(公告)日：1917-04-10
申请号：US11960116
申请日：1916-09-11
申请人： LIDDELL MOSES V
发明人： LIDDELL MOSES V
CPC分类号： E02F3/6463 , Y02T50/545

19. 发明专利

JP2011143922A Flight control system for aircraft 有权
标题翻译：飞机飞行控制系统
公开(公告)号：JP2011143922A
公开(公告)日：2011-07-28
申请号：JP2011006078
申请日：2011-01-14
申请人： Airbus Operations , エアバス・オペレーションズ
发明人： FERVEL MARC , LECANU ARNAUD , MAUSSION ANTOINE , ANDRIEU LAURENT
IPC分类号： B64C13/50
CPC分类号： B64C13/50 , B64C9/02 , B64C9/04 , G05D1/0077 , Y02T50/44 , Y02T50/54 , Y02T50/545
摘要： PROBLEM TO BE SOLVED: To provide a robust and simple flight control system showing high reliability in operation. SOLUTION: This invention relates to a flight control system for aircraft that comprises flight operation boards (111, 211, 331, 431, 541, 121-225) and actuators cooperating with the flight operation boards so as to control flight functions such as rolling, yawing, pitching and aerodynamic control for an aircraft. All the actuators (111a1-211a1, 121a-225a) for use in controlling at least one of the flight functions are electro-mechanical actuators. A part of the flight operation boards cooperated with the electro-mechanical actuators are divided flight operation boards (111, 211, 331, 431, 541) and each of the divided flight operation boards comprises at least two independent flight operation boards (113, 114, ..., 545). COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：提供一种强大而简单的飞行控制系统，显示出高可靠性的运行。解决方案：本发明涉及一种用于飞机的飞行控制系统，其包括飞行操作板（111,211,331,431,541,121-225）和与飞行操作板协作的致动器，以便控制飞行操作板作为飞机的滚动，偏航，俯仰和空气动力学控制。用于控制至少一个飞行功能的所有致动器（111a1-211a1,121a-225a）都是机电致动器。与机电致动器协作的飞行操作板的一部分是分开的飞行操作板（111,211,331,431,541），并且每个分开的飞行操作板包括至少两个独立的飞行操作板（113,114 ，...，545）。版权所有（C）2011，JPO＆INPIT

20. 发明专利

JP2009533267A Device and method for emergency power supply of the aircraft 有权
标题翻译：空值
公开(公告)号：JP2009533267A
公开(公告)日：2009-09-17
申请号：JP2009504663
申请日：2007-03-13
申请人：エアバス・フランス
发明人：エティエンヌ・フォッシュ , オリヴィエ・ラングロワ
IPC分类号： B64D41/00
CPC分类号： B64D41/00 , B64D41/007 , B64D2041/002 , B64D2221/00 , F03D9/12 , F03D9/25 , F05B2220/50 , Y02E10/725 , Y02E60/16 , Y02T50/44 , Y02T50/54 , Y02T50/545
摘要：本発明は、航空機の「本質的な」電気システムに供給可能である航空機搭載の待機パワーサプライ用のデバイスおよび方法に関する。前記デバイスは、フライホイール（ＲＩ）に関連付けられた、別個に給電される同期機（ＭＳＩ）とフライホイールを回転させ、その回転を維持するための補助デバイス（３０）とを備える。
摘要翻译：一种用于飞机上的紧急电力供应的装置和方法，能够提供飞机电力电路的一部分。该装置包括具有与飞轮相关联的单独激励的同步机，以及用于将飞轮旋转并保持飞轮旋转的辅助装置。

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