| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 61 | Auxiliary electrical generating system for jet aircraft | US3662975D | 1970-09-21 | US3662975A | 1972-05-16 | DRISKILL ROBERT E |
| An auxiliary electrical generating system for jet aircraft wherein compressed air is withdrawn from a jet engine and used to operate a pneumatic turbine which in turn drives a generator. An ancillary gas source may be included for supplying compressed gas to the turbine in the event of engine failure. This abstract is neither intended to define the invention of the application which, of course, is measured by the claims, nor is it intended to be limiting as to scope of the invention in any way.
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| 62 | Electrical system for starting up aircraft engines | US13143848 | 2010-01-08 | US08958181B2 | 2015-02-17 | Eric de Wergifosse |
| An electrical system for starting an engine is provided. The system includes: an AC/DC rectifier powered by an AC power network to deliver a first DC voltage Vdc, a DC/AC converter module for delivering an AC voltage for starting the engine from said first DC voltage Vdc, and k n-phase inverters arranged in parallel (k>1) and each delivering power no greater than half a maximum power Pmax required for starting the engine, and the two power supply lines of each of the inverters are connected to an electronic protection device receiving the first DC voltage Vdc, and the n outputs of each of the inverters delivering the AC voltage for starting the engine via n respective series inductors. | ||||||
| 63 | AIRCRAFT SELECTIVELY ENGAGEABLE ELECTRIC TAXI SYSTEM | US14099162 | 2013-12-06 | US20140332622A1 | 2014-11-13 | DAVID LANE CHARLES; DONALD JEFFREY CHRISTENSEN |
| An electric taxi system (ETS) for an aircraft may include an annular output gearbox positioned between a wheel and a main strut of a main landing gear of the aircraft. The output gearbox may surround a brake piston assembly of the wheel of the aircraft. One or more selectively operable engaging assemblies, for selectively coupling the ETS with the wheel of the aircraft, may be positioned between the output gearbox and the wheel of the aircraft. The one or more selectively operable engaging assemblies may be coupled with an output gear of the output gearbox to rotate with the output gear. | ||||||
| 64 | Observability of unmanned aircraft and aircraft without electrical systems | US12007872 | 2008-01-16 | US20100283661A1 | 2010-11-11 | Robert C. Strain; Matthew T. DeGarmo; John C. Moody |
| The present invention relates to a lightweight beacon system, affixable, for example, to UAS, aircraft without electrical systems, airport surface vehicles, skydivers, gliders, and/or balloons. The lightweight beacon system uses a small, low-powered, portable radio beacon to broadcast the location of the aircraft, vehicle, or person to which the beacon system is attached. The lightweight beacon system is compatible with the FAA's Automatic Dependent Surveillance-Broadcast (ADS-B) service, thereby providing a means for unmanned aircraft systems (UAS), aircraft without electrical systems, airport surface vehicles, or persons to be observable to other general aviation aircraft operating in their proximity. | ||||||
| 65 | Hydraulic and electrical system for aircraft belt loader | US18791 | 1987-02-24 | US4782938A | 1988-11-08 | Robert R. Cooper; William C. Dean |
| This invention relates generally to hydraulic and electrical systems for aircraft belt loaders and more particularly to such systems with interlocks to facilitate efficient and safe operation. The present invention provides a hydraulic and electrical system for battery powered aircraft belt loaders which precludes actuation of the electric traction drive motors when the brake is applied or set, or without the operator seat being occupied, which precludes actuation of the belt conveyor if the brake is not set, which controls conveyor run time and requires that the conveyor be reset to neutral before being actuated the hydraulic pump to permit power steering when the operator seat is occupied, and which requires that the directional control lever for traction drive be reset to neutral after demounting the seat before the electric traction drive motors can be energized. | ||||||
| 66 | ELECTRICAL SYSTEMS ARCHITECTURE FOR AN AIRCRAFT, AND RELATED OPERATING METHODS | US11944199 | 2007-11-21 | US20090127855A1 | 2009-05-21 | Mark S. Shander; Richard A. Cote; Michael L. Drake; Howard Carter, III; John T. Peters; Casey Y.K. Ng; Michael S. Hoag; John T. Paterson |
| An electrical architecture for an aircraft is provided. The electrical architecture is particularly suitable for relatively small, compact, and lightweight aircraft. In one embodiment, the electrical architecture includes an electrical generator component coupled to the aircraft engine, and an air compression system coupled to the electrical generator component. The electrical generator component is configured to receive mechanical power from the engine and to generate a constant frequency AC electrical power from the engine mechanical power, and the air compression system is configured to receive the constant frequency AC power as an input and, in response thereto, produce a pressurized air output having variable characteristics (for example, a variable flow rate or a variable air pressure). | ||||||
| 67 | Aircraft starter generator for variable frequency (vf) electrical system | US10178759 | 2002-06-24 | US06838779B1 | 2005-01-04 | Magdy A. Kandil; Keith R. Magnus; Don Baker |
| A starter-generator for an aircraft engine comprises a variable dynamoelectric machine alternatively operable as a motor or as a generator, having a rotor. A support motor is coupled to the variable dynamoelectric machine to assist the machine. A torque converter selectively couples and decouples the rotor to the engine, coupling the rotor to the engine at some point when the dynamoelectric machine is operated as a motor. The engine may be started by the dynamoelectric machine when operated as a motor through a first power train including the torque converter and may drive the dynamoelectric machine as a generator through a second power train. | ||||||
| 68 | Aircraft power system and apparatus for supplying power to an aircraft electrical system | US11693486 | 2007-03-29 | US07928607B2 | 2011-04-19 | Fred Oliver; Allan Saldecki |
| An aircraft power system is provided having an aircraft power supply and a bidirectional switch. The aircraft power supply includes an alternator, a battery and a load. The bidirectional switch is coupled between one of the alternator and the battery, and the load. The switch includes a first FET, a second FET and timing circuitry. A source of the first FET is coupled with a source of the second FET. A drain of the first FET is coupled with one of the alternator and the battery. A drain of the second FET is coupled with the load. The timing circuitry is configurable to generate a control signal deliverable to a gate of the first FET and the second FET for setting the first FET in selective on and off positions and the second FET in corresponding selective off and on position. | ||||||
| 69 | Aircraft Power System and Apparatus for Supplying Power to an Aircraft Electrical System | US11693486 | 2007-03-29 | US20080238201A1 | 2008-10-02 | Fred Oliver; Allan Saldecki |
| An aircraft power system is provided having an aircraft power supply and a bidirectional switch. The aircraft power supply includes an alternator, a battery and a load. The bidirectional switch is coupled between one of the alternator and the battery, and the load. The switch includes a first FET, a second FET and timing circuitry. A source of the first FET is coupled with a source of the second FET. A drain of the first FET is coupled with one of the alternator and the battery. A drain of the second FET is coupled with the load. The timing circuitry is configurable to generate a control signal deliverable to a gate of the first FET and the second FET for setting the first FET in selective on and off positions and the second FET in corresponding selective off and on position. | ||||||
| 70 | Control method and unit of an electric system for supplying power/electric current to sockets for the passengers of an aircraft | EP09170754.7 | 2009-09-18 | EP2166636A2 | 2010-03-24 | Galasso, Franco |
Control method and unit (10) of an electric system (7) for supplying power/electric current to sockets (9) for the passengers of an aircraft (1); the method comprises the steps of: setting a maximum power/electric current deliverable to the sockets (9); cyclically detecting the power/electric current absorbed by the sockets (9); if the power/electric current absorbed by the sockets (9) is higher than the maximum power/electric current, disconnecting one or more sockets (9) from the electric supply until the power/electric current absorbed by the sockets (9) is lower than the maximum power/electric current; if the power/electric current absorbed by the sockets (9) is remarkably lower than the maximum power/electric current, connecting again one or more sockets (9) from the electric supply until the power/electric current absorbed by the sockets (9) is close to the maximum power/electric current; and periodically varying the sockets (9) connected/disconnected to/from the electric supply so that each socket (9) is connected to the electric supply for a first period of time (Ton) and is disconnected from the electric supply for a second period of time (Toff).
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| 71 | Systems and methods for airplane electrical system connection routing and visualization with topology determination | US13093481 | 2011-04-25 | US09507908B2 | 2016-11-29 | Brent Louis Hadley; Patrick J. Eames; Michael Patrick Sciarra |
| A method for creating a computerized visualization of a wiring topology is described that includes combining three-dimensional wire harness data with logical wire content using a process executed on a computer processing device, and displaying a graphical wire topology, output from the process, within a three dimensional model of the platform within which the wiring topology is contained. | ||||||
| 72 | Aircraft starter/generator electrical system with mixed power architecture | US10890740 | 2004-07-14 | US20060012177A1 | 2006-01-19 | Richard Hoppe |
| A starter/generator electrical system for gas turbine powered aircraft with mixed power architecture to combine advantages of each. The mixed power architecture may be selected from constant frequency (CF), adjustable variable frequency (AVF) and narrow range variable frequency (NRVF) alternating current (AC) systems to suit aircraft requirements for on-board electric components and redundancy, with at least two separate power generation systems provided for each gas turbine engine on the aircraft. | ||||||
| 73 | Ground fault interrupt circuit apparatus for 400-Hz aircraft electrical systems | US888783 | 1997-07-07 | US5835322A | 1998-11-10 | Donald E. Smith; John F. Rix; Ray E. Freudenberg; David C. Randolph |
| A resettable ground fault circuit interrupter most advantageously suited for use with 400-Hz aircraft electrical systems and designed to interrupt the AC power between an aircraft electrical system and one or more electrical appliances being operated therein when a ground fault occurs. The circuit relies upon an imbalance sensor which is implemented in the preferred embodiment disclosed herein as a multi-turn coil of a transformer through which input wires connected to an AC input terminal are threaded so that an imbalance resulting from a ground fault can be detected by the coil. The signal generated by the coil as a result of such an imbalance is then amplified and applied to a thyristor, the conducting or non-conducting state of which determines whether or not the circuit is in a configuration for interrupting the AC signal or not interrupting the AC signal. Light emitting diodes are utilized to indicate the interruption status of the circuit. A reset switch is provided to reset the thyristor after an imbalance ceases because of removal of a ground fault that had previously occurred. | ||||||
| 74 | Aircraft crash or impact detecting device and electric system associated therewith | US21534651 | 1951-03-13 | US2638286A | 1953-05-12 | ANDERS MATHISEN |
| 75 | SYSTEM AND METHOD OF PROVIDING AN AUTOMATED DESIGN AND MODIFICATION OF AIRCRAFT ELECTRICAL SYSTEMS | US13649106 | 2012-10-10 | US20140100824A1 | 2014-04-10 | Douglas Andrew Bess |
| The present invention is a computer program product comprised of a non-transitory computer usable medium having a computer readable code embodied thereon provided to implement a method and system of designing and modifying aircraft electrical systems. The process provides for an automated electrical circuiting and production of detailed engineering “ECAD” drawings from several differing views of particular data. The present product provides a collaborative environment between management, engineers and technicians. It allows end user reporting that provides the entire organization with the ability to manage, search and view all information contained in the aircraft wiring diagram(s) for an entire project or electrical system. | ||||||
| 76 | METHOD AND DEVICE FOR PROVIDING AN ELECTRICAL SYSTEM ALTERNATING VOLTAGE IN AN AIRCRAFT | US13015645 | 2011-01-28 | US20110210606A1 | 2011-09-01 | Jens Selker |
| The present invention provides a method and a device for providing a three-phase electrical system alternating voltage for an electrical system of an aircraft, a plurality of voltage sources being provided which comprise at least one engine generator and a further voltage source, in particular a fuel cell, comprising one or more frequency converters for converting an alternating voltage of variable frequency provided by the respective engine generator into a first output alternating voltage and comprising at least one cyclo-inverter for cyclo-inverting a voltage provided by the respective further voltage source into a second output alternating voltage which is synchronous with the first output alternating voltage and constitutes the electrical system alternating voltage. | ||||||
| 77 | Aircraft electrical system providing emergency power and electric starting of propulsion engines | US589235 | 1996-01-22 | US5899411A | 1999-05-04 | Thomas S. Latos; Jeffrey D. Nelson; Gary E. Dickes |
| An aircraft is provided that includes one or more engines, an air-driven generator, and a start-circuit for operably connecting an electrical output of the air driven generator for starting one or more of the engines while the aircraft is in flight. Various embodiments also provide apparatus for cross-ship electric starting of multiple engines while the aircraft is in flight or on the ground using: an electrical output of a generator attached to another engine; on-board batteries; an on board auxiliary power unit; or power received from a ground source. A single start-converter is utilized to supply power to AC starter-motors for electric starting of the aircraft's engines. In some embodiments, the engine is soft-started with the air driven generator, by controlling blade pitch in an air driven turbine driving the air driven generator, without the use of the start converter. | ||||||
| 78 | Control method and unit of an electric system for supplying power/electric current to sockets for the passengers of an aircraft | US12586234 | 2009-09-18 | US20100133907A1 | 2010-06-03 | Franco Galasso |
| Control method and unit of an electric system for supplying power/electric current to sockets for the passengers of an aircraft; the method comprises the steps of: setting a maximum power/electric current deliverable to the sockets; cyclically detecting the power/electric current absorbed by the sockets; if the power/electric current absorbed by the sockets is higher than the maximum power/electric current, disconnecting one or more sockets from the electric supply until the power/electric current absorbed by the sockets is lower than the maximum power/electric current; if the power/electric current absorbed by the sockets is remarkably lower than the maximum power/electric current, connecting again one or more sockets from the electric supply until the power/electric current absorbed by the sockets is close to the maximum power/electric current; and periodically varying the sockets connected/disconnected to/from the electric supply so that each socket is connected to the electric supply for a first period of time and is disconnected from the electric supply for a second period of time. | ||||||
| 79 | METHOD FOR DETECTING A DEVICE THAT GENERATES SPURIOUS SIGNALS IN AN ELECTRICAL NETWORK, AN ELECTRICAL SYSTEM AND AN AIRCRAFT | US14034681 | 2013-09-24 | US20140084951A1 | 2014-03-27 | Henning Everth; Jens Schult |
| A method for detecting a device that generates spurious signals in an electrical network, to which several devices and at least one fault detection device are connected, includes the steps of monitoring the electrical network for electrical spurious signals, sequentially deactivating each device for a predetermined time T when an electrical spurious signal has been detected, and checking the electrical network for the disappearance of the respective spurious signal, and signaling as soon as the respective spurious signal has disappeared upon deactivating a respective device. This makes it possible to especially reliably detect a device in an electrical network that couples an undesired spurious signal into the network. | ||||||
| 80 | 飞机遮光板光伏系统设计方法 | CN201210341681.9 | 2012-09-17 | CN103683352A | 2014-03-26 | 张旭; 张楠; 赵冬梅 |
| 本发明属于新能源发电领域和飞机电气系统的设计领域。本发明涉及到飞机遮光板光伏系统的设计方法，提出了一种在飞机遮光板上安装光伏阵列并将其接入飞机电气系统的新型设计方案。该方案能够利用太阳能光伏发电系统为飞机上的设备供电，可以有效利用可再生能源，减轻了能源消耗和环境污染，并且提高了飞机电气系统的供电可靠性。具体的设计过程如下：首先研究飞机电气系统的设计原理以及将光伏系统接入的可行性；然后根据飞机遮光板的面积大致计算可安装的光伏系统容量，最后详细介绍有光伏接入的飞机电源系统整体电路结构。 | ||||||
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