CN113964783A - Automatic management method for large aircraft kitchen electrical load - Google Patents
Automatic management method for large aircraft kitchen electrical load Download PDFInfo
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- CN113964783A CN113964783A CN202111077023.9A CN202111077023A CN113964783A CN 113964783 A CN113964783 A CN 113964783A CN 202111077023 A CN202111077023 A CN 202111077023A CN 113964783 A CN113964783 A CN 113964783A
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- 238000007726 management method Methods 0.000 title claims abstract description 53
- 238000012545 processing Methods 0.000 claims description 33
- 239000000203 mixture Substances 0.000 claims 1
- 239000002994 raw material Substances 0.000 claims 1
- 230000005283 ground state Effects 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 3
- 238000013459 approach Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02H—EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS
- H02H3/00—Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition with or without subsequent reconnection ; integrated protection
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D11/00—Passenger or crew accommodation; Flight-deck installations not otherwise provided for
- B64D11/04—Galleys
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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
- H02J3/00—Circuit arrangements for ac mains or ac distribution networks
- H02J3/12—Circuit arrangements for ac mains or ac distribution networks for adjusting voltage in ac networks by changing a characteristic of the network load
- H02J3/14—Circuit arrangements for ac mains or ac distribution networks for adjusting voltage in ac networks by changing a characteristic of the network load by switching loads on to, or off from, network, e.g. progressively balanced loading
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- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Supply And Distribution Of Alternating Current (AREA)
Abstract
The application relates to the field of airplane power supply systems, in particular to an automatic management method for large airplane kitchen electrical loads, which comprises the steps of receiving power supply state information sent by controllers connected with power supplies in real time; judging whether the power supply is in the air or not when the power supply fails, and if so, carrying out load management; judging whether the power failure is positioned at the same side of an alternating current main power supply connected with a kitchen or not, and if so, disconnecting the kitchen load; and when the number of the faults of the AC main power supply and the APU power supply on the other side connected with the kitchen is judged to be more than 2, the kitchen load is disconnected. The system can shut down the kitchen load when the power supply power is insufficient when the alternating current power supply system fails so as to ensure the normal work of important loads on the airplane.
Description
Technical Field
The application belongs to the field of airplane power supply systems, and particularly relates to an automatic management method for large airplane kitchen electric loads.
Background
The alternating current power supply of the large aircraft power supply system comprises an alternating current main power supply, an auxiliary power supply and an external power supply, and the alternating current main power supply and the auxiliary power supply can supply power to an alternating current network on an aircraft in each aircraft working stage except that the external power supply is only used on the ground.
Therefore, according to various different working states of the ac main power supply and the auxiliary power supply, a single main generator may only supply power to a single ac main bus bar, may also supply power to two ac main bus bars, and may even supply power to all four ac main bus bars simultaneously; the auxiliary generator may also supply power to the same ac main bus bar or all ac main bus bars on both sides. That is, in the event of various faults in the ac main power system, a single main generator or auxiliary generator may become overloaded, carrying ac loads beyond its rated capacity.
The AC load must be managed according to the importance of power supply, and when the AC power supply system fails, the power supply of part of the AC load is cut off, so that the remaining generators which normally work are prevented from being overloaded, and the more serious consequences can be caused to endanger the safety of the airplane. The kitchen load has high power, no safety influence on the flight and low power supply priority, and can be removed firstly through management when the generator fails, so that the load of the kitchen load is automatically managed when the alternating current power supply fails.
Disclosure of Invention
The application aims to provide an automatic management method for large aircraft kitchen electric loads, and the automatic management method is used for solving the problem that in the prior art, when an alternating current power supply system fails, kitchen loads cannot be selectively cut off, so that the normal work of important parts is guaranteed.
The technical scheme of the application is as follows: a large aircraft kitchen electrical load automatic management method comprises the steps of receiving power supply state information sent by controllers connected with power supplies in real time; judging whether the power supply is in the air or not when the power supply fails, and if so, carrying out load management; judging whether the power failure is positioned at the same side of an alternating current main power supply connected with a kitchen or not, and if so, disconnecting the kitchen load; and when the number of the faults of the AC main power supply and the APU power supply on the other side connected with the kitchen is judged to be more than 2, the kitchen load is disconnected.
Preferably, a contactor is arranged on a kitchen load, a power supply management processor 1 is arranged on an alternating current main power supply connected with a kitchen, a power generator controller 1, a power generator controller 2, a power generator controller 3, a power generator controller 4, an auxiliary power supply controller and a ground power supply controller are respectively arranged on each alternating current main power supply, an APU power supply and a ground power supply, the kitchen load and the power generator controller 1 are correspondingly arranged, the power generator controller 1 and the power generator controller 2 are positioned on the same side of the auxiliary power supply controllers, and the power supply management processor 1 acquires working state information and airplane vacant ground state information of each controller and sends a control signal to the contactor when the kitchen load is cut off through logic processing.
Preferably, the power sources corresponding to the No. 1 generator controller, the No. 2 generator controller, the No. 3 generator controller and the No. 4 generator controller are the No. 1 alternating current power source, the No. 2 alternating current power source, the No. 3 alternating current power source and the No. 4 alternating current power source respectively.
Preferably, the No. 1 power supply management processor includes a second signal receiving module, a signal storage module, a second signal processing module and a signal sending module, the second signal receiving module is configured to receive power status information sent by each controller, the signal storage module is configured to store the power status information of each controller, the second signal processing module is configured to process the power status information in the signal storage module, and the signal sending module is configured to send a control signal according to a processing result of the second signal processing module.
Preferably, the signal storage module is used for storing information received by different controllers in a classified manner, the power supply management processor # 1 is used for marking the information of each controller before storage and recording the address information stored in the controller, and the second signal processing module is used for calling corresponding controller data according to the corresponding marks and the address information.
Preferably, the signal storage module marks the controller corresponding to the faulty power supply, and when the second signal processing module receives the normal data information of the controller again, the control signal sending module sends a control signal to the contactor to control the contactor to open the kitchen load.
Preferably, the contactor comprises a first signal receiving module and a first signal processing module; the first signal receiving module is used for receiving a control signal sent by the No. 1 power supply management processor, and the first signal processing module is used for turning on or turning off a kitchen load according to the control signal sent by the No. 1 power supply management processor.
A power supply system for large aircraft, comprising an AC main power supply, an auxiliary power supply and an external power supply, wherein the AC main power supply, the auxiliary power supply and the external power supply are supplied by adopting the automatic management method for kitchen electric loads as claimed in any one of claims 1 to 7.
According to the automatic management method for the large aircraft kitchen electric load, the power state information is received in real time, when the number of faults of two alternating current main power supplies positioned on one side of a kitchen load or two alternating current main power supplies positioned on the other side of the kitchen load and an APU power supply is larger than 2, the kitchen load can be automatically disconnected, the power supplies transmit electric energy to important loads of an aircraft, and the capacity of an aircraft working power supply is fully utilized.
Preferably, the controller corresponding to the failed power supply is marked, so that the normal work of the kitchen load can be timely recovered after the failed power supply is repaired or replaced.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a schematic overall flow diagram of the present application;
FIG. 2 is a schematic diagram of the overall structure of the present application;
fig. 3 is a schematic structural diagram of a system of the power management processor and the contactor of the application No. 1.
1. A No. 1 AC power supply; 2. no. 2 AC power supply; 3. a No. 3 AC power supply; 4. a No. 4 AC power supply; 5. an APU power supply; 6. a number 1 generator controller; 7. a number 2 generator controller; 8. a number 3 generator controller; 9. a number 4 generator controller; 10. an auxiliary power supply controller; 11. a contactor; 12. no. 1 power supply management processor; 13. a second signal receiving module; 14. a signal storage module; 15. a second signal processing module; 16. a signal transmitting module; 17. a first signal receiving module; 18. a first signal processing module.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
An automatic management method for large kitchen electric loads, as shown in fig. 1 and 2, comprises,
step S100, receiving power supply state information sent by each controller connected with each power supply in real time;
step S200, judging whether the power supply is in the air when the power supply fails, if so, carrying out load management, and if not, not carrying out load management;
step S300, judging whether the power failure is positioned at the same side of an alternating current main power supply connected with a kitchen, if so, disconnecting a kitchen load, otherwise, the kitchen load works normally;
and step S400, when the number of the faults of the AC main power supply and the APU power supply 5 on the other side connected with the kitchen is judged to be more than 2, the kitchen load is disconnected.
In load management, the following design needs to be considered:
1. the approach load management is used in the air when the power supply fails, and because the ground state aircraft does not run, the load management is not performed in the ground state and the load management is not performed in the ground power supply state;
2. according to the configuration on the airplane, the kitchen load is supplied with power by the No. 1 AC bus bar installed on the left side of the airplane through the contactor 11, when other generators fail, the No. 1 generator needs to supply power to important loads of other channels, and because the capacity of the No. 1 generator is limited, the kitchen load is preferentially and automatically cut off when the left side power supply fails or when the right side power supply and the APU power supply 5 both fail, so that the No. 1 generator is ensured not to be overloaded.
After the kitchen load is automatically disconnected, important loads can be effectively powered, the normal and stable operation of the airplane is guaranteed, the real-time effective automatic management of the loads is realized, the capacity of the working power supply of the airplane is fully utilized, and the reliability of the airplane for completing tasks and the safety of the airplane are improved.
Preferably, a contactor 11 is arranged on a kitchen load, a power supply management processor 12 No. 1 is arranged on an alternating current main power supply connected with a kitchen, each alternating current main power supply, an APU power supply 5 and a ground power supply are respectively provided with a power generator controller 6 No. 1, a power generator controller 2 No. 7, a power generator controller 3, a power generator controller 4, an auxiliary power supply controller 10 and a ground power supply controller, the kitchen load and the power generator controller 6 No. 1 are correspondingly arranged, the power generator controller 6 No. 1 and the power generator controller 6 No. 1 are positioned on the same side of the auxiliary power supply controller 10, and the power supply management processor 12 No. 1 acquires working state information and airplane vacant ground state information of each controller and sends a control signal to the contactor 11 when the kitchen load is cut off through logic processing.
The No. 1 power supply management processor 12 receives the working state information and the aircraft air ground state information of each controller and then performs state filtering processing, and the No. 1 power supply management processor 12 can process each signal in real time and can accurately judge whether the load needs to be disconnected.
Preferably, the power sources corresponding to the generator controller No. 16, the generator controller No. 2, the generator controller No. 3, and the generator controller No. 4 9 are the ac power source No. 1, the ac power source No. 2, the ac power source No. 3, and the ac power source No. 4, respectively.
As shown in fig. 2 and 3, preferably, the power supply management processor No. 1 includes a second signal receiving module 13, a signal storage module 14, a second signal processing module 15, and a signal sending module 16, where the second signal receiving module 13 is configured to receive power status information sent by each controller, the signal storage module 14 is configured to store the power status information of each controller, the second signal processing module 15 is configured to process the power status information in the signal storage module 14, and the signal sending module 16 is configured to send a control signal according to a processing result of the second signal processing module 15. All modules work coordinately, can carry out high-efficient stable processing to each signal that receives to through the data information who transfers signal storage module 14 storage, can make things convenient for the staff to look up and handle the problem.
Preferably, the signal storage module 14 stores the information received by different controllers in a classified manner, the information of each controller is marked before the power supply management processor No. 1 12 stores the data, and the address information stored in the information is recorded, and the second signal processing module 15 retrieves the corresponding controller data according to the corresponding mark and the address information. By marking and storing the data on each controller respectively, the staff can quickly search the related data according to the marking information.
Preferably, the signal storage module 14 marks the controller corresponding to the failed power supply, and when the second signal processing module 15 receives the normal data information of the controller again, the control signal starting module sends a control signal to the contactor 11 to control the contactor 11 to open the kitchen load. By adopting the method, the kitchen load can be timely recovered after the corresponding fault power supply is repaired or replaced.
Preferably, the contactor 11 includes a first signal receiving module 17 and a second signal processing module 15, the first signal receiving module 17 is configured to receive a control signal initiated by the power supply management processor No. 1 12, and the first signal processing module 18 is configured to process the control signal sent by the power supply management processor No. 1 12 and determine whether to disconnect the kitchen load. The second signal processing module 15 turns off the kitchen load when the condition for turning off the kitchen load is satisfied; when the power supply in the fault is repaired or replaced, the contactor 11 opens the kitchen load, and stable control over the kitchen load is achieved.
The automatic management method of the kitchen electrical load is adopted by the AC main power supply, the auxiliary power supply and the external power supply, and can timely shut down the kitchen load when the power supply is insufficient in order to ensure the normal work of important loads on the airplane when the power supply fails so as to ensure the reliability of the airplane to complete tasks and the safety of the airplane.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. A large aircraft kitchen electrical load automatic management method is characterized in that: comprises the steps of (a) preparing a mixture of a plurality of raw materials,
receiving power supply state information sent by each controller connected with each power supply in real time;
judging whether the power supply is in the air or not when the power supply fails, and if so, carrying out load management;
judging whether the power failure is positioned at the same side of an alternating current main power supply connected with a kitchen or not, and if so, disconnecting the kitchen load;
and when the number of the faults of the AC main power supply and the APU power supply (5) on the other side connected with the kitchen is judged to be more than 2, the kitchen load is disconnected.
2. A large aircraft galley electrical load automatic management method according to claim 1, characterized by: a contactor (11) is arranged on a kitchen load, a No. 1 power supply management processor (12) is arranged on an alternating current main power supply connected with a kitchen, each alternating current main power supply, an APU power supply (5) and a ground power supply are respectively provided with a No. 1 generator controller (6), a No. 2 generator controller (7), a No. 3 generator controller (8), a No. 4 generator controller (9), an auxiliary power supply controller (10) and a ground power supply controller, the kitchen load is arranged corresponding to the No. 1 generator controller (6), the No. 1 generator controller (6) and the No. 2 generator controller (7) are positioned on the same side of the auxiliary power supply controller (10), the No. 1 power supply management processor (12) collects the working state information and the airplane air-ground state information of each controller, and sends a control signal to the contactor (11) when the kitchen load is cut off through logic processing.
3. A large aircraft galley electrical load automatic management method according to claim 2, characterized by: no. 1 generator controller (6), No. 2 generator controller (7), No. 3 generator controller (8), No. 4 generator controller (9) correspond the power and are No. 1 alternating current power supply (1), No. 2 alternating current power supply (2), No. 3 alternating current power supply (3) and No. 4 alternating current power supply (4) respectively.
4. A large aircraft galley electrical load automatic management method according to claim 2, characterized by: the No. 1 power supply management processor (12) comprises a second signal receiving module (13), a signal storage module (14), a second signal processing module (15) and a signal sending module (16), wherein the second signal receiving module (13) is used for receiving power state information sent by each controller, the signal storage module (14) is used for storing the power state information of each controller, the second signal processing module (15) is used for processing the power state information in the signal storage module (14), and the signal sending module (16) is used for sending a control signal according to a processing result of the second signal processing module (15).
5. A large aircraft galley electrical load automatic management method according to claim 4, characterized in that: the signal storage module (14) is used for classifying and storing information received by different controllers, the No. 1 power supply management processor (12) marks the information of each controller before storage and records the address information stored by the controller, and the second signal processing module (15) is used for calling corresponding controller data according to the corresponding marks and the address information.
6. A large aircraft galley electrical load automatic management method according to claim 4, characterized in that: the signal storage module (14) marks the controller corresponding to the fault power supply, and when the second signal processing module (15) receives the normal data information of the controller again, the control signal sending module (16) sends a control signal to the contactor (11) to control the contactor (11) to open the kitchen load.
7. A large aircraft galley electrical load automatic management method according to claim 2, characterized by: the contactor (11) comprises a first signal receiving module (17) and a first signal processing module (18); the first signal receiving module (17) is used for receiving a control signal sent by the No. 1 power supply management processor (12), and the first signal processing module (18) turns on or off a kitchen load according to the control signal sent by the No. 1 power supply management processor (12).
8. A large aircraft power supply system characterized by: the kitchen electric load automatic management system comprises an alternating current main power supply, an auxiliary power supply and an external power supply, wherein the alternating current main power supply, the auxiliary power supply and the external power supply adopt the kitchen electric load automatic management method of any one of claims 1 to 7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202111077023.9A CN113964783A (en) | 2021-09-15 | 2021-09-15 | Automatic management method for large aircraft kitchen electrical load |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111077023.9A CN113964783A (en) | 2021-09-15 | 2021-09-15 | Automatic management method for large aircraft kitchen electrical load |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100079003A1 (en) * | 2008-10-01 | 2010-04-01 | Bethel Jeffrey D | Airborne power system disconnect system and method |
| CN102336275A (en) * | 2010-07-15 | 2012-02-01 | 哈米尔顿森德斯特兰德公司 | Method for aircraft emergency power management |
| US20130099560A1 (en) * | 2011-10-24 | 2013-04-25 | Ge Aviation Systems Limited | Multiple source electrical power distribution in aircraft |
| CN111740402A (en) * | 2020-06-02 | 2020-10-02 | 南京航空航天大学 | Automatic distribution management control method of airplane energy network |
-
2021
- 2021-09-15 CN CN202111077023.9A patent/CN113964783A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100079003A1 (en) * | 2008-10-01 | 2010-04-01 | Bethel Jeffrey D | Airborne power system disconnect system and method |
| CN102336275A (en) * | 2010-07-15 | 2012-02-01 | 哈米尔顿森德斯特兰德公司 | Method for aircraft emergency power management |
| US20130099560A1 (en) * | 2011-10-24 | 2013-04-25 | Ge Aviation Systems Limited | Multiple source electrical power distribution in aircraft |
| CN111740402A (en) * | 2020-06-02 | 2020-10-02 | 南京航空航天大学 | Automatic distribution management control method of airplane energy network |
Non-Patent Citations (3)
| Title |
|---|
| 张苗欢: "未来飞机动态配电管理技术", 《科技视界》, 15 September 2015 (2015-09-15), pages 95 - 96 * |
| 樊智勇，等: "基于背包问题的多电飞机负载管理方法的研究", 《计算机仿真》, vol. 35, no. 11, 15 November 2018 (2018-11-15), pages 66 - 71 * |
| 顾公兵: "飞机自动配电技术研究", 飞机设计, vol. 38, no. 4, 31 August 2018 (2018-08-31), pages 37 - 41 * |
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