CN107919725B - Aviation power supply control box adopting staggered control configuration - Google Patents
Aviation power supply control box adopting staggered control configuration Download PDFInfo
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- CN107919725B CN107919725B CN201711136065.9A CN201711136065A CN107919725B CN 107919725 B CN107919725 B CN 107919725B CN 201711136065 A CN201711136065 A CN 201711136065A CN 107919725 B CN107919725 B CN 107919725B
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J9/00—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
- H02J9/04—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source
- H02J9/06—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems
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- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Supply And Distribution Of Alternating Current (AREA)
- Control Of Vehicle Engines Or Engines For Specific Uses (AREA)
Abstract
The invention provides an aviation power supply control box adopting a staggered control configuration, which comprises a left connecting contactor, a right connecting contactor, a left load contactor, a right load contactor, a ground power supply contactor and a current transformer group, wherein the left connecting contactor is connected with a right generator controller of an aviation power supply; when the two channels supply power independently, the left connecting contactor and the right connecting contactor are both in a closed state; the invention solves the problem of one-class (losing control over the contactor) fault on the original airplane by using a new control logic circuit configuration of staggered control, changes and optimizes the structure of logic control, achieves the error-free conversion of left and right channel conversion, and ensures that one channel supplies power to the whole airplane.
Description
Technical Field
The invention belongs to the technical field of aviation power supply system control, and relates to a novel staggered control circuit configuration of an alternating current power supply control box of a dual-channel aircraft power supply system, which is used for a control circuit of an aviation power supply system.
Background
An airplane adopts a non-parallel power supply alternating current power supply system consisting of two power generation channels and can supply power to airplane electric equipment. Each power generation channel consists of a power generator and a power generator controller. Each channel has a generator network-casting control function and has a protection function, a power channel conversion function and a power system self-detection function. The aircraft double-channel alternating-current power generation system is composed of the two power generation channels, the ground power supply monitoring device and the power supply control box, and after the system is composed of the devices, the control box is required to disconnect the side when a certain channel load or a power supply fails, so that the single-channel power supply for the whole aircraft is realized.
However, there is a case in the existing conversion control logic: when the control fault of the contactor is lost in one side channel (for example, the fault of the generator controller itself, and the fault of other components of the power generation channel such as the disconnection of the generator, the transformer, and the feeder line), the control signal cannot be sent to disconnect the connection contactor, only the load contactor of the side channel can be disconnected, so that the bus bar connection contactor of the side channel cannot be disconnected, and then the bus bar of the fault channel cannot be communicated with the fault-free channel. Therefore, by adopting the current conversion control logic, when the generator controller fails, the on-board power failure fault which is caused by the fact that the power supply channel cannot be converted can be caused.
Disclosure of Invention
The invention designs a power supply control box with staggered control logic by analyzing the error frequently occurring in the double-channel conversion of the conventional aviation power supply system to control the conventional mainstream double-channel power supply system, thereby perfecting the control protection logic of the power supply system and also improving the fault-tolerant power supply capability under the condition of power supply system failure. And because the components of the aircraft power generation systems are basically similar, for other aircraft power generation systems adopting double channels, after the power supply control box adopting the staggered control logic provided by the invention is adopted, staggered control can be realized by controlling the main contactor of the channel and the connecting contactors of other channels, and the fault-tolerant power supply capability is improved.
The technical scheme of the invention is as follows:
the aviation power supply control box adopting the staggered control configuration comprises a left connecting contactor, a right connecting contactor, a left load contactor, a right load contactor, a ground power supply contactor and a current transformer group; the method is characterized in that: the left connecting contactor is connected with a right generator controller of the aviation power supply, and the right generator controller provides an on-off control signal for the left connecting contactor; the right connecting contactor is connected with a left generator controller of the aviation power supply, and the left generator controller provides on-off control signals to the right connecting contactor; the left load contactor is connected with the left generator controller, and the right load contactor is connected with the right generator controller; when the two channels supply power independently, the left connecting contactor and the right connecting contactor are both in a closed state; one end of a normally closed contact of the left connecting contactor is connected with the right generator, and one end of a normally closed contact of the right connecting contactor is connected with the left generator; one end of a normally open contact of the left load contactor is connected with one end of a common contact of the left connecting contactor, and one end of a normally open contact of the right load contactor is connected with one end of a common contact of the right connecting contactor; the left load contactor is connected with a left generator controller of the aviation power supply, the left generator controller provides an on-off control signal for the left load contactor, and when the left generator controller fails, the left load contactor is automatically switched from a closed state to an open state; the right load contactor is connected with a right generator controller of the aviation power supply, the right generator controller provides an on-off control signal for the right load contactor, and when the right generator controller fails, the right load contactor is automatically switched from a closed state to an open state.
Advantageous effects
The invention solves the problem of one-class (losing control over the contactor) fault on the original airplane by using a new control logic circuit configuration of staggered control, changes and optimizes the structure of logic control, achieves the error-free conversion of left and right channel conversion, and ensures that one channel supplies power to the whole airplane.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
FIG. 1: when the double channels supply power independently, the wiring of the control box and the position diagram of the contactor are simplified;
FIG. 2: the left channel has faults (including generator controller faults), and the right channel has a simplified diagram of the wiring of the control box and the position of the contactor when the whole machine is supplied with power.
Detailed Description
The following detailed description of embodiments of the invention is intended to be illustrative, and not to be construed as limiting the invention.
The invention designs a power supply control box with staggered control logic by analyzing the error frequently occurring in the double-channel conversion of the conventional aviation power supply system to control the conventional mainstream double-channel power supply system, thereby perfecting the control protection logic of the power supply system and also improving the fault-tolerant power supply capability under the condition of power supply system failure. And because the components of the aircraft power generation systems are basically similar, for other aircraft power generation systems adopting double channels, after the power supply control box adopting the staggered control logic provided by the invention is adopted, staggered control can be realized by controlling the main contactor of the channel and the connecting contactors of other channels, and the fault-tolerant power supply capability is improved.
The specific aviation power supply control box comprises a left connecting contactor, a right connecting contactor, a left load contactor, a right load contactor, a ground power supply contactor and a current transformer group.
As shown in fig. 1, the left connecting contactor is connected with a right generator controller of the aviation power supply, and the right generator controller provides an on-off control signal for the left connecting contactor; the right connecting contactor is connected with a left generator controller of the aviation power supply, and the left generator controller provides on-off control signals to the right connecting contactor.
The left load contactor is connected with the left generator controller, and the right load contactor is connected with the right generator controller; and when the two channels supply power independently, the left connecting contactor and the right connecting contactor are both in a closed state.
One end of a normally closed contact of the left connecting contactor is connected with the right generator, and one end of a normally closed contact of the right connecting contactor is connected with the left generator; one end of a normally open contact of the left load contactor is connected with one end of a common contact of the left connecting contactor, and one end of a normally open contact of the right load contactor is connected with one end of a common contact of the right connecting contactor.
The left load contactor is connected with a left generator controller of the aviation power supply, the left generator controller provides an on-off control signal for the left load contactor, and when the left generator controller fails, the left load contactor is automatically switched from a closed state to an open state; the right load contactor is connected with a right generator controller of the aviation power supply, the right generator controller provides an on-off control signal for the right load contactor, and when the right generator controller fails, the right load contactor is automatically switched from a closed state to an open state.
As shown in fig. 2, when the failure mode of the left generator controller is that the control of the contactor is lost (when other components of the power generation channel have faults such as the disconnection of a generator, a transformer and a feeder), the generator controller can disconnect the load contactor GCB and the connection contactor BTB according to a predetermined logic, thereby ensuring that the right power generation channel supplies power for the dual channels. Therefore, the failure of any part of the single channel is realized, the channel can supply power to the whole machine in any failure mode, the power failure caused by the failure of the generator controller is solved in principle, and the problem of the failure is solved.
When the aircraft power supply dual-channel conversion is carried out, the power supply system ensures that the single-side generator supplies power for the whole aircraft to the greatest extent. Due to the fact that the control logic of staggered control is used, the problem of conversion error fault when a single channel of a conventional dual-channel power supply system fails is solved, the structure of logic control is optimized, and conversion without errors of conversion of left and right channels is achieved. The aircraft dual-channel power supply system can effectively shield the faults without changing other components and increasing the complexity and the weight of the system, improves the reliability of products, perfects the control protection logic of a power supply system, and also improves the fault-tolerant power supply capacity under the condition of the power supply system faults. The AC power supply control box is used on a power supply system of an airplane, the problems of channel non-conversion and power failure caused by the fault of a generator controller are completely solved, the fault rate of the power supply system is obviously reduced, and other matched components are not changed.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.
Claims (1)
1. An aviation power supply control box adopting a staggered control configuration comprises a left connecting contactor, a right connecting contactor, a left load contactor, a right load contactor, a ground power supply contactor and a current transformer group; the method is characterized in that: the left connecting contactor is connected with a right generator controller of the aviation power supply, and the right generator controller provides an on-off control signal for the left connecting contactor; the right connecting contactor is connected with a left generator controller of the aviation power supply, and the left generator controller provides on-off control signals to the right connecting contactor; the left load contactor is connected with the left generator controller, and the right load contactor is connected with the right generator controller; when the two channels supply power independently, the left connecting contactor and the right connecting contactor are in a normally open contact disconnection state, and the normally closed contact is in a closed state; one end of a normally closed contact of the left connecting contactor is connected with the right generator, and one end of a normally closed contact of the right connecting contactor is connected with the left generator; one end of a normally open contact of the left load contactor is connected with one end of a common contact of the left connecting contactor, and one end of a normally open contact of the right load contactor is connected with one end of a common contact of the right connecting contactor; the left load contactor is connected with a left generator controller of the aviation power supply, the left generator controller provides an on-off control signal for the left load contactor, and when the left generator controller fails, the left load contactor is automatically switched from a normally closed contact closed state and a normally open contact open state to a normally closed contact open state and a normally open contact closed state; the right load contactor is connected with a right generator controller of the aviation power supply, the right generator controller provides on-off control signals for the right load contactor, and when the right generator controller fails, the right load contactor is automatically switched to a normally closed contact open state and a normally open contact closed state from a normally closed contact closed state and a normally open contact open state.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711136065.9A CN107919725B (en) | 2017-11-16 | 2017-11-16 | Aviation power supply control box adopting staggered control configuration |
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| CN201711136065.9A CN107919725B (en) | 2017-11-16 | 2017-11-16 | Aviation power supply control box adopting staggered control configuration |
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| CN107919725A CN107919725A (en) | 2018-04-17 |
| CN107919725B true CN107919725B (en) | 2021-01-05 |
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| CN110844094B (en) * | 2019-10-25 | 2022-10-11 | 天津航空机电有限公司 | Double-channel aviation digital power supply control method |
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| CN204089325U (en) * | 2014-08-18 | 2015-01-07 | 江西洪都航空工业集团有限责任公司 | The novel power supply circuits of a kind of flight control system |
| CN204290479U (en) * | 2014-12-31 | 2015-04-22 | 广东易事特电源股份有限公司 | EPS output circuit |
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| WO2016181642A1 (en) * | 2015-05-12 | 2016-11-17 | 日本電気株式会社 | Power supply path-switching device, power supply path-switching system, and power supply path-switching method |
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| JPH0236729A (en) * | 1988-07-25 | 1990-02-06 | Nec Corp | Operation controller for three diesel generators |
| CN1457123A (en) * | 2003-05-08 | 2003-11-19 | 沈阳工业学院 | Intelligent transformer and distribution device |
| CN101391842B (en) * | 2008-07-31 | 2011-04-20 | 上海市环境科学研究院 | Control and protection device of aeration aerating machine with wind and solar mutual-complementing power supply |
| CN201298750Y (en) * | 2008-10-09 | 2009-08-26 | 郎定川 | Double-power-supply quick automatic switching device |
| CN202817885U (en) * | 2012-08-27 | 2013-03-20 | 新疆中泰化学（集团）股份有限公司 | Switching apparatus between dual supply systems for isolated network operation |
| CN203251096U (en) * | 2013-05-14 | 2013-10-23 | 中国电力工程顾问集团西南电力设计院 | Factory-used electric wiring circuit |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204089325U (en) * | 2014-08-18 | 2015-01-07 | 江西洪都航空工业集团有限责任公司 | The novel power supply circuits of a kind of flight control system |
| CN204290479U (en) * | 2014-12-31 | 2015-04-22 | 广东易事特电源股份有限公司 | EPS output circuit |
| WO2016181642A1 (en) * | 2015-05-12 | 2016-11-17 | 日本電気株式会社 | Power supply path-switching device, power supply path-switching system, and power supply path-switching method |
| CN205544569U (en) * | 2016-03-22 | 2016-08-31 | 中国南方电网有限责任公司调峰调频发电公司鲁布革水力发电厂 | Direct current dual supply meets incessant power supply unit |
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| CN107919725A (en) | 2018-04-17 |
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