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
21	一种飞机电子电气系统布线的支撑固定装置	CN200920306199.5	2009-07-14	CN201435573Y	2010-03-31	唐伟; 谢丹贤
本实用新型公开了一种飞机电子电气系统布线的支撑固定装置，该装置由圆筒形状的并可以开合的整体式的波纹管尼龙卡箍构成，在波纹管尼龙卡箍的圆筒内壁上设有至少一条凸出的螺旋式的波纹筋，在波纹管尼龙卡箍的开合口处两端分别设有固定支撑柄，在固定支撑柄上设有安装孔。本实用新型的装置在工作时，其套在布线上的波纹管在波纹管尼龙卡箍波纹筋的作用下，使波纹管稳定可靠的固定在适当位置。在振动时也不会滑动或松脱。本实用新型的装置安装在飞机上可以将复杂的电子电气系统线路有条不紊的分开固定，可方便飞机的电子电气系统线路的检修维护，大大提高了飞机的维护效率。
22	一种飞机电子电气系统布线的支撑固定装置	CN202022697865.1	2020-11-19	CN213879188U	2021-08-03	郭晓科
本实用新型公开了一种飞机电子电气系统布线的支撑固定装置，具体涉及飞机电子布线领域，包括连接柱，伸缩结构包括基板和限位板，基板与限位板之间固定安装有伸缩管，伸缩结构的一侧固定安装有第一固定机构和第二固定机构，第一固定机构包括中心柱，中心柱的外侧固定安装有固定组件，固定组件的外侧固定连接有连接组件。本实用新型通过第一固定机构和第二固定机构的结构设计，利用多个固定组件、对称分布的第一固定机构和第二固定机构对电线进行限位锁定，减小了布线的使用空间，提高了飞机电子电气系统布线的有序度；通过伸缩结构和第一固定机构的结构设计，简化了飞机电子电气系统的布线过程和检修过程，提高了工作效率。
23	一种便于扩展的通用飞机电气系统汇流条装置	CN202023207269.7	2020-12-28	CN214625644U	2021-11-05	杨瑞赓; 肖芬; 谢勇; 孙璐; 王嘉为
本实用新型涉及一种便于扩展的通用飞机电气系统汇流条装置，其包括设置在底座上的绝缘支架、固定在绝缘支架上的汇流条、设置在绝缘支架一侧的限幅杆支架、设置在限幅杆支架上的限幅杆、连接在限幅杆上的接线端子以及两端分别与汇流条和接线端子连接的保险丝；本实用新型在使用时，汇流条固定在绝缘支架上，绝缘支架通过铆钉固定在底座上，各汇流条彼此绝缘且便于安装，并且带有外壳，壳上留有布线孔，可以根据需要进行布线调整。本实用新型的汇流条长度可根据需要进行扩展，只需调整绝缘支架的安装位置即可，扩展性能好且便于使用和维护。
24	Electrical system for an aircraft	US13718836	2012-12-18	US09302636B2	2016-04-05	Jens Schult; Henning Everth; Fabian Kraus
An electrical system for an aircraft is provided. The system comprises an inverter for transforming a first alternating current from an on-board network having a variable frequency into a second alternating current, and at least a first electrical load and at least a second electrical load, which are configured to be operated simultaneously by the second alternating current.
25	AIRCRAFT ELECTRICAL SYSTEM	US14266366	2014-04-30	US20140333127A1	2014-11-13	Huw EDWARDS
An aircraft electrical network including a first starter generator mechanically coupled to a first shaft of an aircraft main engine. The first starter generator is configured to turn the first shaft of the main engine in a starting mode, and to generate electricity from the first shaft of the gas turbine engine in a generating mode. The network further includes a DC electrical bus electrical coupled to one or more electrical loads and an AC electrical bus electrically coupled to the first starter generator. The DC electrical bus is electrically coupled to the AC electrical bus via a bi-directional AC/DC converter, which is configured to provide AC electrical power from the DC electrical bus to power the first starter generator when the first starter generator is in a starting mode, and DC electrical power to the DC electrical bus when the first starter generator is in a generating mode.
26	An electrical system for an aircraft	EP13005197.2	2013-11-04	EP2727838A3	2018-01-03	Vyas, Parag
The invention relates to an electrical system (310) for an aircraft, comprising: a first main generator (314a) connected to at least one load via a first bus; a second main generator (314b) connected to at least one load via a second bus; a first and a second auxiliary generator (316a,316b) associated with the first and second buses, the auxiliary generators being driven by a common prime mover (326).
27	Aircraft electrical system	US69035457	1957-10-15	US2892098A	1959-06-23	BERGVALL ROYAL C

28	航空機エンジンを始動させるための電気システム	JP2011544908	2010-01-08	JP5754597B2	2015-07-29	ドウ・ウエルジフオセ,エリツク

29	Aircraft Electrical System Evaluation	US11875816	2007-10-19	US20080036624A1	2008-02-14	Marc Ausman; Kevin DeVries
A computer implemented function monitors the position of the magneto switch in an aircraft to provide real-time feedback of engine RPM drop during a magneto (mag) check and communicates whether parameters are within limits. The function can also monitor engine and groundspeed/airspeed data in an aircraft to verify the magneto switch is in the correct position during engine start, takeoff and flight and can provide an alert to the pilot if the switch is not in the correct position. The automated magneto check function provides an easy way to test the operation of the aircraft's engine-driven magnetos and provides additional safety by alerting the pilot to unsafe positioning of the switch.
30	Electrical system for aeroplanes and the like	US15446717	1917-03-13	US1362380A	1920-12-14	WOLFFSOHN LIONEL M

31	Aircraft electrical system evaluation	US11875816	2007-10-19	US07796054B2	2010-09-14	Marc Ausman; Kevin DeVries
A computer implemented function monitors the position of the magneto switch in an aircraft to provide real-time feedback of engine RPM drop during a magneto (mag) check and communicates whether parameters are within limits. The function can also monitor engine and groundspeed/airspeed data in an aircraft to verify the magneto switch is in the correct position during engine start, takeoff and flight and can provide an alert to the pilot if the switch is not in the correct position. The automated magneto check function provides an easy way to test the operation of the aircraft's engine-driven magnetos and provides additional safety by alerting the pilot to unsafe positioning of the switch.
32	ELECTRICAL SYSTEM FOR AN AIRCRAFT	US13718836	2012-12-18	US20130154357A1	2013-06-20	Jens Schult; Henning Everth; Fabian Kraus
An electrical system for an aircraft is provided. The system comprises an inverter for transforming a first alternating current from an on-board network having a variable frequency into a second alternating current, and at least a first electrical load and at least a second electrical load, which are configured to be operated simultaneously by the second alternating current.
33	ELECTRICAL SYSTEM FOR AN AIRCRAFT	US14069881	2013-11-01	US20140333126A1	2014-11-13	Parag VYAS
This invention relates to an electrical system for an aircraft, comprising: a first main generator connected to at least one load via a first bus; a second main generator connected to at least one load via a second bus; a first and a second auxiliary generator associated with the first and second buses, the auxiliary generators being driven by a common prime mover.
34	Aircraft electrical system tester	US10109	1979-02-07	US4251765A	1981-02-17	Shawn P. Mears
A portable tester for trouble shooting aircraft electrical systems, particularly condition warning systems including a housing having a plug, adapted to connect a wiring harness from the master controlling display unit, and circuitry which simulates various conditions causing the display panel to react in a known manner. Failure of the display panel to react correctly indicates electrical malfunction.
35	ELECTRICAL SYSTEM FOR STARTING UP AIRCRAFT ENGINES	PCT/FR2010050026	2010-01-08	WO2010079308A2	2010-07-15	DE WERGIFOSSE ERIC
The invention relates to an electrical system for starting up an engine (18, 20, 22), including: an AC/DC rectifier (12), supplied with power by an AC power network (14) in order to generate a first DC voltage Vdc; a DC/AC conversion module (12) for generating, on the basis of said first DC voltage Vdc, an AC voltage for starting up the engine, comprising n phase k inverters arrange in parallel (k>1) and generating power at least two times less than a maximum power Pmax that is required to start up the engine. The two power supply lines of each inverter are connected to an electronic protection device that receives the first DC voltage Vdc, and the n outputs of each inverter generate the AC voltage for starting up the engine by means of n inductors in series.
36	Aircraft electrical system operating method	US14247708	2014-04-08	US09394084B1	2016-07-19	Huw Llewellyn Edwards; Parag Vyas
A method of controlling an aircraft electrical system (40). The electrical system (40) comprises an alternating current electrical machine (56, 58) comprising a plurality of phases, each phase having a power rating, the electrical machine (56, 58) being configured to operate on failure of one or more phases. The method comprises: determining a power requirement; sensing a fault of one or more phases of the electrical machine (56, 58), and controlling the electrical machine (56, 58) to operate in a fault condition, in which the remaining phases of the electrical machine (56, 58) provide the electrical power requirement; and providing an overrating signal to a flight computer (66) of the aircraft (2) where the power provided by each phase exceeds the power rating of the respective phase.
37	AIRCRAFT ELECTRICAL SYSTEM OPERATING METHOD	US14247708	2014-04-08	US20160185462A1	2016-06-30	Huw Llewellyn EDWARDS; Parag VYAS
A method of controlling an aircraft electrical system (40). The electrical system (40) comprises an alternating current electrical machine (56, 58) comprising a plurality of phases, each phase having a power rating, the electrical machine (56, 58) being configured to operate on failure of one or more phases. The method comprises: determining a power requirement; sensing a fault of one or more phases of the electrical machine (56, 58), and controlling the electrical machine (56, 58) to operate in a fault condition, in which the remaining phases of the electrical machine (56, 58) provide the electrical power requirement; and providing an overrating signal to a flight computer (66) of the aircraft (2) where the power provided by each phase exceeds the power rating of the respective phase.
38	Electric System Stabilizing System for Aircraft	US14418075	2013-07-29	US20150183385A1	2015-07-02	Atsushi Iwashima; Kazushige Sugimoto; Kazuya Matsuo; Joseph S. Breit; Farhad Nozari
A power stabilizing device in a system includes as a portion of a power converter section, a second PWM converter provided between a second primary AC bus and a second DC bus in an electric system and configured to perform mutual conversion between DC power and AC power. A power stabilizing control section in the power stabilizing device controls charging and discharging of a secondary battery based on a voltage and a frequency in the second primary AC bus, thereby stabilizing the electric system.
39	Electric System Stabilizing System for Aircraft	US14418074	2013-07-29	US20150165990A1	2015-06-18	Atsushi Iwashima; Kazushige Sugimoto; Kazuya Matsuo; Joseph S. Breit; Farhad Nozari
An electric system of an aircraft includes a power stabilizing device connected to a primary AC bus and a secondary battery. The secondary battery has a rated voltage which allows the secondary battery to absorb regenerative power from a control surface actuator. Based on a voltage and a frequency in the primary AC bus, charging/discharging of the secondary battery is controlled to stabilize the electric system.
40	ELECTRIC SYSTEM STABILIZING SYSTEM FOR AIRCRAFT	PCT/US2013052596	2013-07-29	WO2014062269A3	2014-07-03	IWASHIMA ATSUSHI; SUGIMOTO KAZUSHIGE; MATSUO KAZUYA; BREIT JOSEPH S; NOZARI FARHAD
An electric system of an aircraft includes a power stabilizing device connected to a primary AC bus and a secondary battery. The secondary battery has a rated voltage which allows the secondary battery to absorb regenerative power from a control surface actuator. Based on a voltage and a frequency in the primary AC bus, charging/discharging of the secondary battery is controlled to stabilize the electric system.

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