CN111756284B - Dual-channel aircraft generator control device with dual redundancy design - Google Patents
Dual-channel aircraft generator control device with dual redundancy design Download PDFInfo
- Publication number
- CN111756284B CN111756284B CN202010553430.1A CN202010553430A CN111756284B CN 111756284 B CN111756284 B CN 111756284B CN 202010553430 A CN202010553430 A CN 202010553430A CN 111756284 B CN111756284 B CN 111756284B
- Authority
- CN
- China
- Prior art keywords
- channel
- relay
- generator
- backup
- main control
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 230000009977 dual effect Effects 0.000 title claims description 3
- 238000006243 chemical reaction Methods 0.000 claims abstract description 8
- 238000010248 power generation Methods 0.000 claims abstract description 4
- 238000002955 isolation Methods 0.000 claims description 41
- 238000012423 maintenance Methods 0.000 claims description 10
- 230000005284 excitation Effects 0.000 description 3
- 230000002159 abnormal effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 208000024891 symptom Diseases 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Classifications
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
- H02P9/00—Arrangements for controlling electric generators for the purpose of obtaining a desired output
- H02P9/08—Control of generator circuit during starting or stopping of driving means, e.g. for initiating excitation
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02H—EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS
- H02H7/00—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions
- H02H7/06—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for dynamo-electric generators; for synchronous capacitors
-
- 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
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
- H02P9/00—Arrangements for controlling electric generators for the purpose of obtaining a desired output
- H02P9/10—Control effected upon generator excitation circuit to reduce harmful effects of overloads or transients, e.g. sudden application of load, sudden removal of load, sudden change of load
Landscapes
- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Business, Economics & Management (AREA)
- Emergency Management (AREA)
- Safety Devices In Control Systems (AREA)
Abstract
The invention provides a double-channel aircraft generator control device with double redundancy design, which is characterized in that a channel with the same composition and function is added on the basis of a single channel of an original generator control device, the device is provided with a main control channel and a backup channel, a conversion control circuit is designed between the two control channels, when an aircraft power supply system is started, the backup channel of the generator control device is used for completing the voltage establishment of a generator, the voltage establishment is automatically converted to the main control channel, the main control channel is used for normally controlling a direct current power generation system, and the conversion to the backup channel is automatically performed when the main control channel fails. The device has reliable and effective design principle, can effectively reduce the faults of the generator control device, further improve the reliability of the aircraft power supply system and improve the maintainability.
Description
Technical Field
The invention belongs to the field of circuit design, and particularly relates to a double-channel aircraft generator control device with double redundancy design.
Background
In general, a single-engine aircraft is designed with one generator and a generator control circuit, and compared with a double-engine aircraft designed with two generators and generator control circuits, the safety margin is poor, and the probability of power failure of a power supply system is high. In fact, the single-shot aircraft has occurred for many times, and the aircraft is powered off in the air and has flight accident symptoms caused by the failure of the generator control circuit, so that the flight safety is seriously endangered.
In order to solve the problems, a digital dual-redundancy generator control device (CN 202997682U) is designed, and a dual-channel, dual-power and digital control technical scheme is adopted.
The technical scheme of the double-channel aircraft generator control device with double redundancy design is designed, and a single power supply and an analog conversion control circuit are adopted, so that the device is provided with a main control channel and a backup channel, when a main channel circuit in the generator control device fails, the operation of the backup channel can be automatically converted, the continuous power supply of the generator to an aircraft power grid is ensured, the implementation is easier, the cost is reduced, and the reliability is improved.
Disclosure of Invention
In order to solve the defects in the prior art, the invention provides the double-channel aircraft generator control device with double redundancy design, which is provided with the main control channel and the backup channel, and can automatically switch to the backup channel to work when the main control channel in the generator control device fails, so that the generator is ensured to continuously supply power to an aircraft power grid.
In order to solve the technical problems, the device is provided with a channel with the same composition and function on the basis of the original generator control device, and is provided with a main control channel and a backup channel, each channel has the functions of voltage regulation, overvoltage protection and reset, differential pressure connection and reverse current protection, emergency tripping, overvoltage self-checking and the like, meanwhile, a conversion control circuit is designed between the two control channels, when an aircraft power supply system is started, the backup channel of the generator control device completes the voltage establishment of the generator, the backup channel is automatically converted to the main control channel after the voltage establishment is completed, the main control channel normally controls a direct current power generation system, and the backup channel is automatically converted when the main control channel fails.
Further, the generator control device comprises a main control channel C1, a backup channel C2, a channel control relay J1, a channel isolation relay J2, a channel isolation relay J3, an isolation diode E1, an isolation diode E2, an isolation diode E3, a magnetic latching relay J4, a maintenance button K and a signal interface C3. The generator control device is connected with the bus bar 4P, the contactor 3P and the generator 1P, and realizes the control of the generator by the generator control device.
Inside the generator control device, a main control channel C1 and a backup channel C2 are connected with a signal interface C3 through a channel control relay J1, a channel isolation relay J2 and a channel isolation relay J3, and control signals are output.
The switching of the main control channel C1 and the backup channel C2 controls the contact on-off of the relay J1 through signals output by the No. 18 ends of the main control channel C1 and the backup channel C2, so that the output control of the main control channel C1 and the backup channel C2 is realized, and meanwhile, the channel isolation is carried out through the channel isolation relay J2 and the channel isolation relay J3, so that the relay clapping caused by the sudden working of a channel which is not working due to faults is prevented.
The magnetic latching relay J4 realizes the function of indicating the work of the backup channel C2, and works by receiving the backup channel C2 signals output by the channel control relay J1, the channel isolation relay J2 and the channel isolation relay J3, and outputs the backup channel C2 working signals to the signal interface C3 to realize the state indication. The maintenance button K is used for releasing the operation of the magnetic latching relay J4 and stopping outputting the operation signal of the backup channel C2 after the maintenance personnel presses the maintenance button K.
In the technical scheme, the designed double-channel aircraft generator control device with double redundancy design has reliable and effective design principle, can effectively reduce the faults of the generator control device, further improve the reliability of an aircraft power supply system, improve the maintainability and has great significance for ensuring the flight safety.
Drawings
FIG. 1 is a cross-sectional view of an aircraft generator control system of the present invention.
Fig. 2 is a schematic diagram of the internal channel switching of the aircraft generator control device according to the invention.
Detailed Description
The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to fig. 1 and 2, and it is obvious that the described embodiments are only a specific embodiment of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
As shown in fig. 1 and fig. 2, when the aircraft power supply system is started, the backup channel C2 of the generator control device completes the voltage establishment of the generator, and after the voltage establishment is completed, the voltage is automatically converted to the main control channel C1, and the main control channel C1 performs normal control on the direct current power generation system. When the main control channel C1 fails, the system automatically switches to the backup channel C2, and meanwhile, a state switching indication signal is provided to monitor the working state of the generator control device. The generator control device performs self-checking on the state of the backup channel C2, and can reliably work when the backup channel C2 is required to work.
1. Control of the generator control device to throw net work principle
As shown in fig. 1, during normal operation, the B end of the 2P generator control device is connected to the 4P bus bar, the M end of the 2P generator control device is connected to the positive end of the 1P generator, and when the voltage of the 1P generator is close to the voltage of the 4P bus bar on the machine, the H end of the 2P generator control device outputs high voltage, and controls the 3P main contactor to be connected so as to supply power to the 1P generator in a network; when the 2P generator control device is sensitive to abnormal power supply (such as overvoltage, overexcitation and the like) of the power supply system or faults occur in the 2P generator control device, the H end stops outputting, so that the 1P generator is withdrawn from the power grid; when the storage battery is in reverse current to the direct-current generator, the reverse current protection action enables the 1P generator to withdraw from the power grid.
2. Working principle of channel switching function of generator control device
(1) The backup channel C2 completes the voltage establishment of the generator
As shown in fig. 2, at the beginning of the start of the aircraft power supply system, the contact of the channel control relay J1 is in the normally open state shown in fig. 2, and the No.5 end of the main control channel C1 cannot output an excitation signal, so that only the backup channel C2 is normally put into operation to build up voltage for the generator. The specific current flow direction of the excitation signal output by the backup channel C2 is as follows: the end 5 of the backup channel C2- & gt the contact B3 of the channel control relay J1- & gt the contact B2 of the channel control relay J1- & gt the N hole of the signal interface C3- & gt the 1P generator.
(2) After the pressure is built, the main control channel C1 is automatically switched
When the generator meets the on-board network throwing working condition, the 18 # end of the main control channel C1 outputs a signal to supply power to the +x1 end of the channel control relay J1 coil, the contact of the channel control relay J1 is in attraction, the 18 # end of the backup channel C2 is connected with the A1 end of the channel control relay J1, the loop is disconnected, the backup channel C2 is cut off to enable the backup channel C2 to withdraw from working, and the main control channel C1 is put into working. The specific current flow direction of the main control channel C1 when in operation is as follows: the No. 18 end of the main control channel C1, the isolation diode E1, the H hole of the signal interface C3 and the 3P main contactor.
Meanwhile, the channel isolation relay J2 acts, and the +X1 end voltage signal flow direction of the channel isolation relay J2 is as follows: 4P bus bar in FIG. 1, B hole of signal interface C3, C2 contact of channel control relay J1, C1 contact of channel control relay J1, +X1 terminal of channel isolation relay J2. The contact of the channel isolation relay J2 is absorbed and self-locked, so that preparation is made for the channel isolation relay J3 to act and isolate the main control channel C1 when the backup channel C2 is put into operation.
The specific current flow direction of the excitation signal output by the main control channel C1 is as follows: the method comprises the steps of a No. 5 end of a main control channel C1, a B1 contact of a channel control relay J1, a B2 contact of the channel control relay J1, an N hole of a signal interface C3 and a 1P generator.
(3) Automatic switching to backup channel C2 when master channel C1 fails
When the main control channel C1 fails, the No. 18 end stops outputting signals, the main control channel C1 loses control over the channel control relay J1, the contacts of the channel control relay J1 are released, and the backup channel C2 is put into operation.
The specific current flow direction of the backup channel C2 when in operation is as follows: 18 # end of backup channel C2- & gt A2 contact of channel control relay J1- & gt A3 contact of channel control relay J1- & gt isolation diode E3- & gt H hole of signal interface C3- & gt 3P main contactor.
The output signal of the 18 # end of the backup channel C2 enables the channel isolation relay J3 to be connected, and the +x1 end voltage signal flow direction of the channel isolation relay J3 is as follows: backup channel C218 # end- & gt the A2 contact of channel control relay J1- & gt the A3 contact of channel control relay J1- & gt the B2 contact of channel isolation relay J2- & gt the B1 contact of channel isolation relay J2- & gt the +x1 end of channel isolation relay J3.
The connection of the channel isolation relay J3 enables the No. 18 end of the main control channel C1 to be disconnected, the automatic conversion from the main control channel C1 to the backup channel C2 is completed, the control signal (No. 18 output) of the main control channel C1 which is in failure is isolated, and the channel control relay J1 clapping caused by the secondary output of the control signal of the main control channel C1 is avoided.
3. Working principle of state conversion indication function of generator control device
When the generator control device is in the backup channel C2 to work, a signal is output to the magnetic latching relay J4, so that the contact of the magnetic latching relay J4 acts (the state can be maintained), and the +x1 terminal voltage signal of the magnetic latching relay J4 flows to the following state: 18 # end of backup channel C2- & gt A2 contact of channel control relay J1- & gt A3 contact of channel control relay J1- & gt B2 contact of channel isolation relay J2- & gt B1 contact of channel isolation relay J2- & gt B2 contact of channel isolation relay J3- & gt B1 contact of channel isolation relay J3- & gt +x1 end of magnetic latching relay J4.
The magnetic latching relay J4 outputs a state transition indication signal to the signal lamp C4 from the L-shaped end of the generator control device, and the current flow direction of the signal lamp C4 is as follows: 4P bus bar in FIG. 1, B hole of signal interface C3, A2 contact of magnetic latching relay J4, A1 contact of magnetic latching relay J4, L hole of signal interface C3, signal lamp C4.
The signal lamp C4 is lighted to remind the ground service maintainer that the 2P generator control device is in the working state of the backup channel C2 and maintenance is needed.
After the backup running state of the generator control device is confirmed, a ground service maintainer can press a maintenance button K on the product shell to release the output state conversion indication signal.
Claims (1)
1. A binary channels aircraft generator controlling means of dual redundancy design, its characterized in that: the device is characterized in that a channel with the same composition and function is added on the basis of a single channel of an original generator control device, the device is provided with a main control channel and a backup channel, each channel is provided with voltage regulation, overvoltage protection and reset, differential pressure connection and reverse current protection, emergency trip and overvoltage self-checking functions, meanwhile, a conversion control circuit is designed between the two control channels, when an aircraft power supply system is started, the backup channel of the generator control device is used for completing the voltage establishment of a generator, the voltage establishment is automatically converted to the main control channel, the main control channel is used for normally controlling a direct current power generation system, and the main control channel is automatically converted to the backup channel when the main control channel fails;
The generator control device comprises a main control channel C1, a backup channel C2, a channel control relay J1, a channel isolation relay J2, a channel isolation relay J3, an isolation diode E1, an isolation diode E2, an isolation diode E3, a magnetic latching relay J4, a maintenance button K and a signal interface C3, wherein the generator control device is connected with a bus bar 4P, a contactor 3P and a generator 1P to realize the control of the generator control device on the generator;
Inside the generator control device, a main control channel C1 and a backup channel C2 are connected with a signal interface C3 through a channel control relay J1, a channel isolation relay J2 and a channel isolation relay J3, and control signals are output;
The switching of the main control channel C1 and the backup channel C2 controls the on-off of contacts of the relay J1 through signals output by the No. 18 ends of the main control channel C1 and the backup channel C2, so that the output control of the main control channel C1 and the backup channel C2 is realized, and meanwhile, the channel isolation is carried out through the channel isolation relay J2 and the channel isolation relay J3, so that the relay clapping caused by the sudden working of a channel which is not working due to faults is prevented;
The magnetic latching relay J4 realizes the function of indicating the work of the backup channel C2, and works by receiving the backup channel C2 signals output by the channel control relay J1, the channel isolation relay J2 and the channel isolation relay J3, and outputs the backup channel C2 working signals to the signal interface C3 to realize the state indication; the maintenance button K is used for releasing the operation of the magnetic latching relay J4 and stopping outputting the operation signal of the backup channel C2 after the maintenance personnel presses the maintenance button K.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010553430.1A CN111756284B (en) | 2020-06-17 | 2020-06-17 | Dual-channel aircraft generator control device with dual redundancy design |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010553430.1A CN111756284B (en) | 2020-06-17 | 2020-06-17 | Dual-channel aircraft generator control device with dual redundancy design |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111756284A CN111756284A (en) | 2020-10-09 |
| CN111756284B true CN111756284B (en) | 2024-07-16 |
Family
ID=72675297
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010553430.1A Active CN111756284B (en) | 2020-06-17 | 2020-06-17 | Dual-channel aircraft generator control device with dual redundancy design |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111756284B (en) |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103036306A (en) * | 2012-11-29 | 2013-04-10 | 湖北航达科技有限公司 | Digital dual-redundancy generator control system |
Family Cites Families (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2694588Y (en) * | 2004-03-26 | 2005-04-20 | 佛山市创电电源设备有限公司 | Uninterruption power source two-way input automatic switching equipment |
| JP2008061351A (en) * | 2006-08-30 | 2008-03-13 | Toshiba Corp | Power supply switching system |
| FR2909233B1 (en) * | 2006-11-23 | 2011-03-04 | Hispano Suiza Sa | POWERING AN AIRCRAFT IN ELECTRICAL ENERGY |
| CN106688334B (en) * | 2007-12-17 | 2012-05-16 | 中国航天空气动力技术研究院 | Redundance type low-voltage direct electricity generation system |
| CA2719434A1 (en) * | 2008-03-28 | 2009-10-01 | Ingeteam Energy, S.A. | Wind turbine operation method and system |
| CN203747712U (en) * | 2014-04-01 | 2014-07-30 | 长江三峡能事达电气股份有限公司 | Bi-channel full electrical-isolated excitation controller |
| 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 |
| US10000296B2 (en) * | 2015-02-18 | 2018-06-19 | Hamilton Sundstrand Corporation | Electrical control system |
| CN105024452B (en) * | 2015-08-11 | 2017-04-19 | 中国航空工业集团公司西安飞机设计研究所 | DC uninterrupted power supply method and line |
| KR101751387B1 (en) * | 2015-12-08 | 2017-06-28 | 한국항공우주산업 주식회사 | Apparatus for controlling and power supply for instrumentation of aircraft |
| CN107528382B (en) * | 2017-09-30 | 2020-11-24 | 江西洪都航空工业集团有限责任公司 | Power supply self-locking method for fly-by-wire flight control system |
| CN110347095B (en) * | 2019-08-07 | 2022-02-11 | 天津津航计算技术研究所 | Three-redundancy switching circuit applied to aviation electric heating control system |
| CN110601621B (en) * | 2019-09-10 | 2020-12-08 | 陕西航空电气有限责任公司 | Voltage regulation dual-redundancy control method for aviation power supply system |
| CN110979706B (en) * | 2019-10-11 | 2022-12-30 | 中国直升机设计研究所 | Dual-voltage helicopter power supply system |
| CN110994540A (en) * | 2019-12-04 | 2020-04-10 | 贵阳航空电机有限公司 | Dual-redundancy control system of airborne direct current control protector |
| CN111181241A (en) * | 2019-12-31 | 2020-05-19 | 焦仲德 | Bidirectional conversion circuit for dual-source power supply |
-
2020
- 2020-06-17 CN CN202010553430.1A patent/CN111756284B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103036306A (en) * | 2012-11-29 | 2013-04-10 | 湖北航达科技有限公司 | Digital dual-redundancy generator control system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111756284A (en) | 2020-10-09 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111648911B (en) | Control method for preventing high-rotating-speed brake application of mechanical brake of hydropower station unit | |
| CN201197086Y (en) | Redundant power supply used for digital electro-hydraulic control system of turbine | |
| CN111756284B (en) | Dual-channel aircraft generator control device with dual redundancy design | |
| CN206939100U (en) | Telemetry circuit on the machine of solid state distribution device SSPC passages | |
| CN117833757B (en) | Control device and method for power transformer cooler | |
| CN101888084A (en) | Open phase protector of motor | |
| CN202260420U (en) | Protection circuit of opening and closing coil | |
| CN109193583B (en) | Control circuit for self-adaptive switching of inner bridge connection short lead protection | |
| CN201797302U (en) | Protective device for lifting of heavy crown block | |
| CN100550245C (en) | A kind of control device for vacuum circuit breaker | |
| CN201741014U (en) | Three-step soft switch | |
| CN108053899B (en) | Reactor shutdown circuit breaker test circuit | |
| CN201388081Y (en) | Two-set DC bus fault automatic mutual operation device | |
| CN110120269A (en) | One kind effectively eliminating the extended shutdown design method of nuclear power plant's reactor rod drop time | |
| CN206179699U (en) | High voltage circuit breaker tank circuit with voltage monitor function | |
| CN201069463Y (en) | Quick diagnosis instrument for power loss of low-voltage control line | |
| CN205647006U (en) | Extremely fast combined electrical apparatus that suits | |
| CN215183625U (en) | Control box type maintenance power supply device | |
| CN2169207Y (en) | Automatic dual fused switching and alarming device | |
| CN216871832U (en) | Single-pole triple-throw isolating switch with mutual standby output | |
| CN216436879U (en) | Emergent power supply control circuit of aircraft | |
| CN203367985U (en) | Motor dual protection belt alarm automation control device | |
| CN219322070U (en) | Comprehensive protection monitoring circuit for motor | |
| CN205355796U (en) | High voltage direct current engineering cooling tower fan monitoring system | |
| CN107905894A (en) | Diesel engine stops in emergency Electromagnetic Valve Circuit failover, warning circuit and its method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |