CN112615420A - General aircraft power distribution system - Google Patents
General aircraft power distribution system Download PDFInfo
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- CN112615420A CN112615420A CN202011550021.2A CN202011550021A CN112615420A CN 112615420 A CN112615420 A CN 112615420A CN 202011550021 A CN202011550021 A CN 202011550021A CN 112615420 A CN112615420 A CN 112615420A
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- bus bar
- power supply
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- control device
- distribution system
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- 230000005540 biological transmission Effects 0.000 description 5
- 238000006243 chemical reaction Methods 0.000 description 5
- 230000005611 electricity Effects 0.000 description 2
- 238000001514 detection method Methods 0.000 description 1
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- 230000000694 effects Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
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- 230000004048 modification Effects 0.000 description 1
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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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- Stand-By Power Supply Arrangements (AREA)
Abstract
The invention discloses a general airplane power distribution system, which relates to the technical field of aircraft electrical, in particular to a general airplane power distribution system, comprising: a first power bus bar, a bus bar switch, and a consumer bus bar; according to the bus bar switch redundancy design of the airplane power distribution system, when one bus bar switch fails, the electric equipment bus bar directly connected with the bus bar switch can be supplied with power by other bus bar switches, so that the continuous power supply of the electric equipment bus bar is ensured, and the reliability and the design flexibility of the system are improved. The control device of the universal aircraft power distribution system is used for detecting and identifying the fault of the main power supply and switching to the emergency power supply to supply power when the fault occurs, so that the possibility of power failure of the whole system is reduced, the control device automatically switches the power supply and outputs the power supply to the electric equipment, and precious time is provided for safe landing of the aircraft.
Description
Technical Field
The invention relates to the technical field of aircraft electrical, in particular to a general aircraft power distribution system.
Background
As an important component of an aircraft electrical system, the main function of an aircraft power distribution system is to transmit electrical energy generated by an aircraft generator or emergency power supply to a bus bar in different power distribution manners, and then to each electrical device via the bus bar. The aircraft power distribution system mainly comprises a power transmission line, a power supply and distribution management device, a protection device and the like, wherein a collection position of electric energy in an aircraft power grid is called as a bus bar and is a part of the power transmission line. Aircraft are typically provided with power supply bus bars and electrical equipment bus bars. The power transmission line is also provided with power switch equipment for controlling the power supply and the power consumption equipment to supply or cut off power and controlling the switching of the power supply line, such as a conventional circuit breaker, a contactor or a modern solid-state power controller. The power supply and distribution management device is a control management center for determining the correct closing or opening of power switch equipment in a power transmission line of an airplane power distribution system. Under normal state, it can realize the normal conversion of power supply, such as the conversion between external power supply and main power supply of airplane, the conversion between auxiliary power supply and main power supply, the conversion between external power supply and auxiliary power supply, etc.
According to the design requirement of a certain general airplane, a new design scheme of the power distribution system is provided, and the reliability and the flexibility of the power distribution system can be improved.
Disclosure of Invention
The invention provides a general airplane power distribution system, which is used for solving the problem that the airplane power distribution system in the prior art is insufficient in reliability and flexibility.
The invention adopts the following technical scheme:
a universal aircraft power distribution system comprising: the power supply device comprises a first power supply bus bar, bus bar switches and electrical equipment bus bars, wherein the number of the electrical equipment bus bars is at least two, and the number of the bus bar switches is at least two;
the first end of the bus bar switch is electrically connected with the first power supply bus bar, the second end of the bus bar switch is electrically connected with at least two electric equipment bus bars, and the electric equipment bus bars are electrically connected with the second ends of the at least two bus bar switches.
Further, still include: a control device for switching to an emergency power supply when a primary power supply fails, the control device comprising: the emergency power supply comprises a main power supply input end, an emergency power supply input end and a first output end, wherein the first output end of the control device is electrically connected with the first power supply bus bar.
Further, still include: and one end of the equipment switch is electrically connected with the electric equipment bus bar.
Further, still include: a second power supply bus bar, the control device further comprising: a second output electrically connected with the second power bus bar.
Further, the control device further includes: the voltage meter is used for collecting and displaying the voltage of the first output end and the second output end of the control device, the current meter is used for collecting and displaying the current of the first output end and the second output end of the control device, the voltage meter is electrically connected with the first output end and the second output end of the control device, and the current meter is electrically connected with the first output end and the second output end of the control device.
The invention has the following positive effects:
a universal aircraft power distribution system, comprising: a first power bus bar, a bus bar switch, and a consumer bus bar; according to the bus bar switch redundancy design of the airplane power distribution system, when one bus bar switch fails, the electric equipment bus bar directly connected with the bus bar switch can be supplied with power by other bus bar switches, so that the continuous power supply of the electric equipment bus bar is ensured, and the reliability and the design flexibility of the system are improved.
The control device of the universal aircraft power distribution system is used for detecting and identifying the fault of the main power supply and switching to the emergency power supply to supply power when the fault occurs, so that the possibility of power failure of all equipment on the aircraft is reduced, the control device automatically switches the power supply and outputs the power supply to the electric equipment, and precious time is provided for safe landing of the aircraft.
The novel control device for the universal aircraft power distribution system can meet the working requirements of the aircraft power distribution system, can realize the conversion among an external power supply, a main power supply and an emergency power supply, and is convenient to detect and maintain. The redundancy design of the bus bar control switch not only improves the reliability of a power distribution system, but also enables other switches to supply power to the bus bar when partial bus bar switches fail; in an emergency state, the power supply of non-emergency equipment can be directly cut off; moreover, the redundant design of the switch between different bus bars can be carried out according to the actual requirements of different aircraft power distribution systems.
In the design of the power distribution system, the bus bar switch is designed in a redundancy way, and when part of the bus bar switches are in failure, other switches can still supply power to the bus bar; for some non-critical equipment that needs to be shut down in special situations, such as propeller de-icing systems, it is designed to be powered solely by an additional power bus bar, and to disconnect the non-critical equipment in an emergency. Separate from the equipment normally used on aircraft. The reliability and the flexibility of the power distribution system are improved, and the use and the maintenance are more convenient.
Drawings
FIG. 1 is a schematic diagram of an embodiment of the present invention.
In the figure:
1 a first power bus bar;
2 a bus bar switch;
3 consumer bus bars;
4 a control device;
5, a device switch;
6 second power bus bar.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the detailed description and specific examples, while indicating the invention, are intended for purposes of illustration only and are not intended to limit the scope of the invention.
As shown in fig. 1, a general aircraft power distribution system includes: the power supply comprises a first power supply bus bar 1, bus bar switches 2 and electric equipment bus bars 3, wherein the number of the electric equipment bus bars 3 is at least two, and the number of the bus bar switches 2 is at least two;
the first end of the bus bar switch 2 is electrically connected with the first power supply bus bar 1, the second end of the bus bar switch 2 is electrically connected with at least two electric equipment bus bars 3, and the electric equipment bus bars 3 are electrically connected with at least two second ends of the bus bar switch 2.
More specifically, the first power bus bar 1 and the electrical equipment bus bar 3 are electrical connection nodes, and are generally used for connecting a plurality of power sources and/or electrical equipment, the bus bar switch 2 is generally a contact of a circuit breaker, a switch or a relay, and the bus bar switch 2 includes a first end and a second end, and plays a role of connecting or disconnecting two ends of the first end and the second end in an electric circuit.
In the present embodiment, the second end of each bus bar switch 2 is electrically connected to three electric-equipment bus bars 3, taking the bus bar switch 2 in the first row and the bus bar switch 2 in the second row as an example, the second end of the bus bar switch 2 in the first row is electrically connected to the electric-equipment bus bar 3 in the third row and the bus bar in the fifth row, the second end of the bus bar switch 2 in the second row is electrically connected to the electric-equipment bus bar 3 in the fourth row and the bus bar in the sixth row, and so on for the bus bar switch 2 in the third row, the bus bar switch 2 in the fourth row, the bus bar switch 2 in the fifth row, and the bus bar switch 2 in the sixth row.
First power bus bar 1 accepts the power access from the outside, then inserts each bus bar switch 2's first end with external power source, and during normal work, each bus bar switch 2 is closed, and consumer bus bar 3 gets electric, with the equipment of electric energy transmission to next stage.
It can be seen that for the second end of each bus bar switch 2, there are at least two, and specifically three, consumer bus bars 3 electrically connected to the second end of each bus bar switch 2, and for each consumer bus bar 3, there are at least two, and specifically three, second ends of the bus bar switches 2 electrically connected to the second end of each consumer bus bar switch.
When a fault occurs, for example, the bus bar switch 2 in the third row has a fault, at this time, the power supply can still access the electrical equipment bus bar 3 in the third row through the bus bar switch 2 in the first row, and the electrical equipment in the third row is ensured to work normally.
According to the redundancy design of the bus bar switches 2 of the aircraft power distribution system, when one bus bar switch 2 fails, the electric equipment bus bar 3 directly connected with the bus bar switch 2 can be supplied with power by virtue of other bus bar switches 2, so that the continuous power supply of the electric equipment bus bar 3 is ensured, and the reliability and the design flexibility of the system are improved.
Further, still include: a control device 4, said control device 4 being adapted to switch to emergency power when a primary power source fails, said control device 4 comprising: the emergency power supply comprises a main power supply input end, an emergency power supply input end and a first output end, wherein the first output end of the control device 4 is electrically connected with the first power supply bus bar 1.
More specifically, in one embodiment, the control device 4 is a control board which takes a single chip microcomputer as a core, the control board is provided with a detection circuit for detecting a main power input end, the main power input end and an emergency power input end are both provided with switches, when it is detected that the voltage of the main power input end is low, the control device 4 controls the switch of the main power input end to be switched off, and the switch of the emergency power input end to be switched on, so that the effects of cutting off the power supply of the main power and supplying the power by the emergency power supply. The switch of the main power supply input end and the switch of the emergency power supply can be a normally open contact or a normally closed contact of a relay in implementation, and the control device 4 controls the switch to be closed or opened by controlling the attraction or release of the relay.
The control device 4 is used for detecting and identifying that the main power supply fails and switching to an emergency power supply to supply power when the main power supply fails, so that the possibility of power failure of the whole system is reduced, the control device 4 automatically switches the power supply and outputs the power supply to the electric equipment, and precious time is provided for safe landing of the airplane.
Further, still include: and one end of the equipment switch 5 is electrically connected with the electric equipment bus bar 3.
More specifically, the device switch 5 is used to control the electric device located at the next stage of the electric device bus bar 3, forming an individual control of the electric device. The appliance switch 5 is typically a conventional circuit breaker or a miniature switch, such as a wall switch or the like.
Further, still include: a second power supply bus bar 6, the control device 4 further comprising: a second output terminal electrically connected to the second power supply bus bar 6.
More specifically, the second power supply bus bar 6 is used to access some non-critical devices, and a switch is provided at the second output of the control device 4, which switch is turned off, and the second output of the control device 4 stops outputting. The switch of the second output terminal of the control device 4 is implemented as a normally open contact of a relay, and the control device controls the switch to be closed or opened by controlling the actuation of a coil of the relay. The second power supply bus bar 6 is usually connected with some devices which do not affect the flight of the airplane due to short-term power failure, such as a propeller deicing system, the system needs a separate power supply bus bar for supplying power, is separated from other electric devices on the airplane, and stops the power output of the power supply bus bar in an emergency state, so that the situation that the other electric devices on the airplane cannot work normally due to non-critical device power utilization is avoided.
Further, the control device 4 further includes: voltmeter and ampere meter, the voltmeter is used for gathering and showing the voltage of 4 first outputs of controlling means and second output, the ampere meter is used for gathering and showing the electric current of 4 first outputs of controlling means and second output, the voltmeter with 4 first outputs of controlling means and second output electricity are connected, the ampere meter with 4 first outputs of controlling means and second output electricity are connected.
More specifically, the control device 4 is further provided with a voltmeter and an ammeter, and the voltmeter and the ammeter are respectively used for acquiring the voltage and the current at the output end of the control device 4; one embodiment is that the voltmeter can detect the voltage of two ways of outputs simultaneously, including two ways of input ends, every input end includes two input terminals, wherein two input terminals of one way of input end connect in parallel at the first output, two input terminals of another way of input end connect in parallel at the second output to acquire and show the voltage of first output and the voltage of second output. The ammeter can simultaneously collect two paths of current, and the ammeter comprises two input ends, wherein each input end comprises two input terminals, and the two input ends of the ammeter are respectively connected in series to the first output end and the second output end. The working state of the airplane power distribution system can be monitored by workers according to the parameters displayed by the voltmeter and the ammeter, and the loops with problems can be checked according to the voltmeter and the ammeter.
The embodiments described above are only preferred embodiments of the invention and are not exhaustive of the possible implementations of the invention. Any obvious modifications to the above would be obvious to those of ordinary skill in the art, but would not bring the invention so modified beyond the spirit and scope of the present invention.
Claims (5)
1. A universal aircraft power distribution system, comprising: the power supply system comprises a first power supply bus bar (1), bus bar switches (2) and electric equipment bus bars (3), wherein the number of the electric equipment bus bars (3) is at least two, and the number of the bus bar switches (2) is at least two;
the first end of the bus bar switch (2) is electrically connected with the first power supply bus bar (1), the second end of the bus bar switch (2) is electrically connected with at least two electric equipment bus bars (3), and the electric equipment bus bars (3) are electrically connected with the second ends of the bus bar switches (2).
2. A universal aircraft power distribution system as claimed in claim 1, further comprising: -a control device (4), said control device (4) being intended to switch to an emergency power supply in the event of a failure of the main power supply, said control device (4) comprising: the emergency power supply comprises a main power supply input end, an emergency power supply input end and a first output end, wherein the first output end of the control device (4) is electrically connected with the first power supply bus bar (1).
3. A universal aircraft power distribution system as claimed in claim 2, further comprising: and one end of the equipment switch (5) is electrically connected with the electric equipment bus bar (3).
4. A universal aircraft power distribution system as claimed in claim 3, further comprising: a second power supply bus bar (6), the control device (4) further comprising: a second output electrically connected with the second power supply bus bar (6).
5. A general aircraft power distribution system according to claim 4, characterized in that the control device (4) further comprises: the voltage meter is used for collecting and displaying the voltage of the first output end and the second output end of the control device (4), the current meter is used for collecting and displaying the current of the first output end and the second output end of the control device (4), the voltage meter is electrically connected with the first output end and the second output end of the control device (4), and the current meter is electrically connected with the first output end and the second output end of the control device (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011550021.2A CN112615420A (en) | 2020-12-24 | 2020-12-24 | General aircraft power distribution system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011550021.2A CN112615420A (en) | 2020-12-24 | 2020-12-24 | General aircraft power distribution system |
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| Publication Number | Publication Date |
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| CN112615420A true CN112615420A (en) | 2021-04-06 |
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| CN202011550021.2A Pending CN112615420A (en) | 2020-12-24 | 2020-12-24 | General aircraft power distribution system |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114132514A (en) * | 2021-12-27 | 2022-03-04 | 西安羚控电子科技有限公司 | Fault processing method and device for avionics system of fixed-wing unmanned aerial vehicle |
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| US20130169036A1 (en) * | 2010-09-21 | 2013-07-04 | Airbus Operations Gmbh | Aircraft power distribution network |
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| CN110139429A (en) * | 2019-04-29 | 2019-08-16 | 山东三晶照明科技有限公司 | A kind of tunnel redundant direct current power supply system and method for supplying power to |
| CN214626489U (en) * | 2020-12-24 | 2021-11-05 | 石家庄飞机工业有限责任公司 | General aircraft power distribution system |
-
2020
- 2020-12-24 CN CN202011550021.2A patent/CN112615420A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101136557A (en) * | 2006-09-01 | 2008-03-05 | 力博特公司 | Uninterrupted power supply and its configuration method |
| US20130169036A1 (en) * | 2010-09-21 | 2013-07-04 | Airbus Operations Gmbh | Aircraft power distribution network |
| CN104617655A (en) * | 2014-12-19 | 2015-05-13 | 北京百度网讯科技有限公司 | Method and device for automatically controlling switch unit in electrical power system |
| CN104953478A (en) * | 2015-06-12 | 2015-09-30 | 内蒙古电力勘测设计院有限责任公司 | Hybrid-wiring high-voltage distribution device and expansion and reconstruction method thereof |
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| CN214626489U (en) * | 2020-12-24 | 2021-11-05 | 石家庄飞机工业有限责任公司 | General aircraft power distribution system |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114132514A (en) * | 2021-12-27 | 2022-03-04 | 西安羚控电子科技有限公司 | Fault processing method and device for avionics system of fixed-wing unmanned aerial vehicle |
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