飞机电气系统相关的专利数据

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	Method for high fidelity modeling of an aircraft electrical power system	EP13187576.7	2013-10-07	EP2738630B1	2016-08-10	Huang, Hao; Jia, Xiaochuan

62	METHOD FOR INSTALLING AN ELECTRIC SYSTEM INTO AN AIRCRAFT FUSELAGE	US14016829	2013-09-03	US20140167500A1	2014-06-19	Eckart Frankenberger
A method for installing an electric system into an aircraft fuselage. The object to provide a method for simply and quickly installing an electric system into an aircraft fuselage, wherein the electric system is as little heavy and space consuming as possible, and wherein a wide range of customized alternatives of the electric system is possible, is achieved by the steps of providing a fuselage element extending along an aircraft longitudinal axis and including an outer skin and an interior surface, providing a foil sheet of an electrically insulating substrate material, attaching said foil sheet on the inner side of said fuselage element, applying particles of electrically conductive material onto the inner surface of said attached foil sheet opposite the outer skin in a predetermined pattern, such that the accumulated particles of electrically conductive material form electric conductor elements along said inner surface of said foil sheet.
63	METHOD AND APPARATUS FOR TESTING AIRCRAFT ELECTRICAL SYSTEMS	US12744955	2007-11-29	US20110050244A1	2011-03-03	Sven Knoop; Mike Galinski
The present invention provides a method and apparatus for testing an aircraft control system. The method comprises the steps of: coupling a test device (1) to a plurality of separate test points in an aircraft control system simultaneously; selecting each of the plurality of test points individually, such that the test device is enabled for electrical connection with the selected one of the plurality of test points; conducting a test on the control system at each of the plurality of test points selected with the selector means (20,22) using the test device, including detecting a signal or voltage at the test point selected with the selector means; indicating a result of the test at the selected test point to an operator.
64	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.
65	System and method for detecting faults in an aircraft electrical power system	EP04016951.8	2004-07-19	EP1501167A3	2005-08-03	Kohlmeier-Beckman, Carsten, Dipl.-Ing.; Kessler, Jens
An aircraft electrical power system includes a monitored load (e.g. group of lightbulbs) connected through a sub_system power unit and a power distribution center to a power bus. A current monitor of the power distribution center is able to detect a total failure of the sub_system power unit and its connected monitored load, but is not able directly to detect the failure of a single load component (e.g. single lightbulb). The sub_system power unit includes a fault detector able to detect a fault or failure of a single load component (e.g. single lightbulb) in the monitored load. When the fault detector detects such a fault, the sub_system power unit generates a modulated current signal in the current drawn by the sub_system power unit, with a magnitude greater than the detection threshold of the power distribution center, which thus recognizes the detected fault based on the modulated current signal.
66	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.
67	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).
68	A GROUND FAULT INTERRUPT CIRCUIT APPARATUS FOR 400-Hz AIRCRAFT ELECTRICAL SYSTEMS	PCT/US1998/019515	1998-09-17	WO00079667A1	2000-12-28
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 (L1) which is implemented in the preferred embodiment disclosed herein as a multi-turn coil of a transformer through which 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 (U1) and applied to a thyristor (Q2), 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 (OP1) 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.
69	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.
70	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.
71	Aircraft crash or impact detecting device and electric system associated therewith	US21534651	1951-03-13	US2638286A	1953-05-12	ANDERS MATHISEN

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	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.
75	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.
76	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.
77	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.
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	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 (T_on) and is disconnected from the electric supply for a second period of time (T_off).
80	飞机遮光板光伏系统设计方法	CN201210341681.9	2012-09-17	CN103683352B	2016-01-06	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。

1 2 3 4 5 6 7 8 9 10

IPRDB

热门服务

关于我们

友情链接

联系方式