CN112072778A - Power distribution management system and method for double-engine aircraft - Google Patents
Power distribution management system and method for double-engine aircraft Download PDFInfo
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- CN112072778A CN112072778A CN202010889697.8A CN202010889697A CN112072778A CN 112072778 A CN112072778 A CN 112072778A CN 202010889697 A CN202010889697 A CN 202010889697A CN 112072778 A CN112072778 A CN 112072778A
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- 230000005540 biological transmission Effects 0.000 claims abstract description 13
- 238000007726 management method Methods 0.000 claims description 54
- 238000002955 isolation Methods 0.000 claims description 9
- 238000010586 diagram Methods 0.000 description 6
- 238000012545 processing Methods 0.000 description 6
- 238000013461 design Methods 0.000 description 2
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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
- H02J9/066—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 characterised by the use of dynamo-electric machines
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- 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
- H02H7/22—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 distribution gear, e.g. bus-bar systems; for switching devices
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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
- H02J1/00—Circuit arrangements for dc mains or dc distribution networks
- H02J1/10—Parallel operation of dc sources
- H02J1/109—Scheduling or re-scheduling the operation of the DC sources in a particular order, e.g. connecting or disconnecting the sources in sequential, alternating or in subsets, to meet a given demand
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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
- H02J9/061—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 for DC powered loads
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- Business, Economics & Management (AREA)
- Emergency Management (AREA)
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
The application provides a power distribution management system and a method for a double-engine airplane, wherein the power distribution management system comprises: the data transmission module is connected with a flight control computer of the airplane through a bus and transmits a flight control instruction; the data acquisition module is connected with an airborne sensor of the airplane and used for acquiring airborne equipment signals of the airplane; the comprehensive power distribution module is connected with the airborne equipment and supplies power to the airborne equipment; and the control module is respectively connected with the data transmission module, the data acquisition module and the comprehensive power distribution module, judges the fault condition according to the acquired airborne equipment signal, reconstructs a power distribution system according to the flight control instruction, and controls the comprehensive power distribution module to supply power for two generators, a single generator or emergency power supply. The redundancy advantages of the double generators are reasonably utilized, the triple-redundancy power distribution system with two generators of the double-generator airplane for power supply, a single generator for power supply and storage battery for power supply under emergency conditions is realized, and the reliability of power supply and distribution is improved.
Description
Technical Field
The application relates to the technical field of airplane power distribution, in particular to a power distribution management system and method for a double-engine airplane.
Background
The power distribution system is used as an important component system of the airplane, is used for transmitting and distributing the electric energy provided by the generator to each electric device of the airplane, and has very important significance for the flight safety and the autonomous flight of the airplane. The control modes of the airplane power distribution system include a centralized control mode, a distributed control mode and a distributed control mode. Early airplanes generally used a centralized control approach, i.e., power distribution through the cockpit. With the development and application of computer technology, a distributed control mode and a distributed control mode are successfully applied to airplanes.
The electric system of the unmanned aerial vehicle at home and abroad is basically designed by the electric system of the manned aircraft, the electric equipment is more and heavy, if the bus bar adopts a box-type design, the volume is larger, the assembly time is long, and the on-site wiring is needed when the unmanned aerial vehicle is installed; the whole machine is provided with a large number of relay boxes for power distribution, so that an airborne power grid is complex, and the power supply reliability is reduced.
With the development of unmanned aerial vehicles, the power distribution control technology gradually replaces the traditional design mode of following the electric system of the manned aircraft. But current distribution system is applicable to small-size single unmanned aerial vehicle, and its power is a low-voltage DC generator, and emergency power source is a storage battery.
Disclosure of Invention
Based on the above, the application provides a power distribution management system and method for a double-generator aircraft, which reasonably utilize the equipment redundancy advantages of the double-generator aircraft and realize a three-redundancy power distribution system with two generators of the double-generator aircraft supplying power, a single generator supplying power and a storage battery supplying power under emergency conditions.
The application provides a power distribution management system of two airplanes, includes:
the data transmission module is connected with a flight control computer of the airplane through a bus and transmits a flight control instruction;
the data acquisition module is connected with an airborne sensor of the airplane and used for acquiring airborne equipment signals of the airplane;
the comprehensive power distribution module is connected with the airborne equipment and supplies power to the airborne equipment;
and the control module is respectively connected with the data transmission module, the data acquisition module and the comprehensive power distribution module, judges the fault condition according to the acquired airborne equipment signal, reconstructs a power distribution system according to the flight control instruction, and controls the comprehensive power distribution module to supply power for two generators, a single generator or emergency power supply.
According to some embodiments of the application, the integrated power distribution module comprises:
the first main bus bar and the second main bus bar are respectively connected with the generators of the two engines through a first normally closed contactor and a second normally closed contactor;
the first storage battery bus bar and the second storage battery bus bar are respectively connected with the first main bus bar and the second main bus bar through a first circuit breaker and a second circuit breaker;
the first battery bus bar is connected to the second battery bus bar through a normally open contactor.
According to some embodiments of the present application, the integrated power distribution module further comprises:
a first uninterrupted bus bar connected to the first main bus bar and the first battery bus bar, respectively;
the second uninterrupted bus bar is respectively connected with the second main bus bar and the second storage battery bus bar;
and a first engine bus bar and a second engine bus bar connected to the first main bus bar and the second main bus bar, respectively.
According to some embodiments of the present application, the integrated power distribution module further comprises:
a first ECUB bus bar having one end connected to the first engine bus bar and the other end connected to the second engine bus bar;
a second ECUB bus bar having one end connected to the second engine bus bar and the other end connected to the first engine bus bar.
According to some embodiments of the present application, the integrated power distribution module further comprises:
first and second non-critical bus bars connected to the first and second main bus bars through first and second SSPC channels, respectively.
According to some embodiments of the present application, the power distribution management system further comprises:
and the power supply management module is connected with the control module and provides a power supply for the control module.
According to another aspect of the present application, there is provided a power distribution management method for a dual-engine aircraft, which is applied to the power distribution management system, the power distribution management method including:
under the normal operation state of the two engines, the normally open contactor is disconnected, the first normally closed contactor and the second normally closed contactor are closed, and the first circuit breaker and the second circuit breaker are conducted;
when the first main bus bar or the second main bus bar is short-circuited, the corresponding first circuit breaker or second circuit breaker is actively disconnected;
when the first generator or the second generator has faults, the corresponding first normally closed contactor or the corresponding second normally closed contactor is controlled to be disconnected;
and when the first generator and the second generator both have faults, the first normally closed contactor and the second normally closed contactor are controlled to be disconnected.
According to some embodiments of the present application, the power distribution management method further comprises:
and when the first generator and the second generator both have faults, disconnecting the first SSPC channel and the second SSPC channel between the first non-critical bus bar and the first main bus bar and between the second non-critical bus bar and the second main bus bar.
According to some embodiments of the application, the power distribution management method further comprises:
and when the first main bus bar or the second main bus bar is in short circuit and the first generator and/or the second generator are/is in fault, controlling the normally open contactor to be closed.
According to some embodiments of the application, the power distribution management method further comprises:
the data acquisition module acquires electrical parameters of a power interface, a bus bar and electric equipment in the power distribution system and transmits the electrical parameters to the control module;
the control module carries out fault judgment according to the electrical parameters and transmits a fault judgment result to the flight control computer through the data transmission module;
and the flight control computer transmits an isolation instruction or a reconstruction instruction to the control module according to the fault result.
Additional aspects and advantages of the present application 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 present application.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without exceeding the protection scope of the present application.
Fig. 1 shows a schematic diagram of a power distribution management system according to an example embodiment of the present application.
Fig. 2 illustrates a power distribution management system block diagram according to an example embodiment of the present application.
Fig. 3 shows a flow chart of a power distribution management method according to an example embodiment of the present application.
Fig. 4 shows a flow chart of a power distribution management method according to another example embodiment of the present application.
Fig. 5 shows a block diagram of power distribution management electronics, according to an example embodiment of the present application.
Detailed Description
The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some, but not all, embodiments of the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
The power distribution power supply of the double-generator unmanned aerial vehicle comprises two generators, so that the power redundancy advantage is achieved. The existing power distribution management system and method for the single unmanned aerial vehicle are not suitable for double unmanned aerial vehicles, and the power redundancy advantage of the double unmanned aerial vehicle cannot be reasonably utilized to realize reasonable distribution of a power supply system. In addition, when two unmanned aerial vehicles broke down, current single power distribution management system also can't carry out reasonable and suitable system reconstruction and fault isolation.
Therefore, the invention provides a power distribution management system and method suitable for a double-power unmanned aerial vehicle aiming at the characteristics of the double-power unmanned aerial vehicle, the power redundancy advantages of the double-power unmanned aerial vehicle are fully utilized, reasonable distribution of power and loads is realized, fault location, isolation and system reconstruction can be completed when a fault occurs, three-redundancy power distribution of power supply of two generators, power supply of a single generator and power supply of a storage battery under an emergency condition is realized, and accordingly, uninterrupted power supply is guaranteed and the fault tolerance level is improved.
The technical solution of the present application will be described in detail below with reference to the accompanying drawings.
Fig. 1 shows a schematic diagram of a power distribution management system according to an example embodiment of the present application.
According to a first aspect of the present application, there is provided a power distribution management system 1000 for a dual-engine aircraft, as shown in fig. 1. The power distribution management system 1000 includes a control module 100, a data transmission module 200, a data acquisition module 300, and a comprehensive power distribution module 400.
And the data transmission module 200 is connected with the flight control computer 2000 of the airplane through a bus. The data acquisition module 300 is connected to the onboard sensor 3000 and acquires onboard device signals. And the comprehensive power distribution module is connected with the airborne equipment 4000 and used for supplying power to the airborne equipment 4000.
The control module 100 is respectively connected with the data transmission module 200, the data acquisition module 300 and the comprehensive power distribution module 400. The control module 100 receives the onboard equipment signal acquired by the data acquisition module 300 to judge a fault condition; sending the fault condition to the flight control computer 2000 through the data transmission module 200; the flight control calculation 2000 sends a flight control instruction of fault isolation or system reconfiguration to the control module 100 through operation; the control module 100 reconstructs the power distribution system according to the flight control instruction, and controls the integrated power distribution module 400 to supply power to two generators, supply power to a single generator and supply power for emergency.
According to some embodiments of the present application, the power distribution management system 1000 further comprises a power management module 500, one end of which is connected to the control module 100 and the other end of which is connected to the external power system 5000 to provide power to the control module 100.
The power distribution management system 1000 provided by the application performs fault monitoring through the data acquisition module 300; when a fault is monitored, the fault condition is fed back to the flight control computer, fault isolation and system reconstruction are carried out in time according to a flight control instruction, and on the basis of reasonably utilizing the redundancy of the airborne equipment, the power distribution redundancy and the redundancy of the airborne equipment are combined to realize three-redundancy power distribution of power supply of two generators, power supply of a single generator and power supply of a storage battery under the emergency condition, so that uninterrupted power supply is realized, and the reliability of power distribution is improved.
Fig. 2 illustrates a power distribution management system block diagram according to an example embodiment of the present application.
As shown in fig. 2, the power distribution management system 1000 provided by the present application is applied in a process in which an integrated power distribution module (not shown) distributes power through a set of bus bars. According to an example embodiment of the present application, the integrated power distribution module 400 includes a first main bus bar 410, a second main bus bar 420, a first battery bus bar 430, a second battery bus bar 440, a first engine bus bar 450, a second engine bus bar 460, a first uninterruptible bus bar 470, and a second uninterruptible bus bar 480.
The first main bus bar 410 and the second main bus bar 420 are connected to a left generator 9000 and a right generator 8000 of the two engines through a first normally closed contactor K2 and a second normally closed contactor K3, respectively. Left generator 9000 and right generator 8000 provide power to first main bus bar 410 (left main bus bar) and second main bus bar 420 (right main bus bar), respectively.
The first and second battery bus bars 430 and 440 are connected to the first and second main bus bars 410 and 420 through first and second circuit breakers B1 and B2, respectively. First and second main bus bars 410, 420 respectively supply power to first battery bus bar 430 (left battery bus bar) and second battery bus bar 440 (right battery bus bar).
First battery bus bar 430 (left battery bus bar) and second battery bus bar 440 (right battery bus bar) are connected to first battery pack 7000 and second battery pack 6000, respectively. First battery pack 7000 and second battery pack 6000 supply power to first battery bus bar 430 (left battery bus bar) and second battery bus bar 440 (right battery bus bar), respectively. First battery bus bar 430 is connected to second battery bus bar 440 via normally open contactor K1. Under unmanned aerial vehicle normal operating condition, normally open contactor K1 is in the off-state, and the distribution of both sides is mutual noninterference.
The first uninterruptible bus bar 470 is connected to the first main bus bar 410 and the first battery bus bar 430 through diodes D1 and D2, respectively. Power is supplied to the first uninterruptible bus bar 470 by the first main bus bar 410, the first battery bus bar 430.
And a second uninterruptible bus bar 480 connected to the second main bus bar 420 and the second battery bus bar 440 through diodes D3 and D4, respectively. Power is supplied to the second uninterruptible bus bar 480 from the second main bus bar 420 and the second battery bus bar 440.
The first and second engine bus bars 450, 460 are connected to the first and second main bus bars 410, 420 through diodes D5, D6, respectively. Power is supplied to the first and second engine bus bars 450 and 460 from the first and second master bus bars 410 and 420, respectively.
In the power distribution management system provided by the application, the power distribution bus bar is divided into the key equipment and the non-key equipment according to the grade of the power supply equipment, and the bus bar is the key equipment. In addition, the integrated power distribution module further includes non-critical devices such as a first non-critical bus bar 4010, a second non-critical bus bar 4020, a first ECUB bus bar 4030, and a second ECUB bus bar 4040.
The first non-critical bus bar 4010 and the second non-critical bus bar 4020 are connected to the first main bus bar 410 and the second main bus bar 420 through the first SSPC channel and the second SSPC channel, respectively. Power is supplied to the first non-critical bus bar 4010 and the second non-critical bus bar 4020 from the first main bus bar 410 and the second main bus bar 420, respectively.
First ECUB bus 4030 is connected at one end to first engine bus 450 and at the other end to second engine bus 460 via diode D8. Second ECUB bus bar 4040 is connected at one end to second engine bus bar 460 and at the other end to first engine bus bar 450 via diode D7. Thus, the first engine bus bar 450 supplies power to the first ECUB bus bar 4030 while supplying power to the second ECUB bus bar 4040 through the diode. The second engine bus bar 460 simultaneously supplies power to the second ECUB bus bar 4040, and simultaneously supplies power to the first ECUB bus bar 4030 through the diode.
Fig. 3 shows a flow chart of a power distribution management method according to an example embodiment of the present application.
According to an example embodiment of the present application, a power distribution management method is provided, which is applied to a power distribution management system as shown in fig. 2, wherein a data acquisition module acquires electrical parameters of a power interface, a bus bar and a powered device in the power distribution system and transmits the electrical parameters to a control module; the control module carries out fault judgment according to the electrical parameters and transmits a fault judgment result to the flight control computer through the data transmission module; and the flight control computer transmits an isolation instruction or a reconstruction instruction to the control module according to the fault result. The power distribution management method comprises the following steps:
in step S310, under the normal operating state of the two engines, the normally open contactor is opened, the first normally closed contactor and the second normally closed contactor are closed, and the first circuit breaker and the second circuit breaker are turned on. In this state, the two generators supply power, and the power distribution on the two sides of the normally open contactor K1 does not interfere with each other.
In step S320, when the first main bus bar or the second main bus bar is short-circuited, the corresponding first circuit breaker or second circuit breaker is actively turned off. Under the state, a single generator power supply mode is entered, and the main bus bar side without short circuit fault is normally supplied with power, so that the normal operation of the whole power distribution management system can be protected.
In step S330, when the first generator or the second generator fails, the corresponding first normally closed contactor or the second normally closed contactor is controlled to be opened. When the generator on one side has a fault, the control module uploads a fault signal of the generator to the flight control computer, the flight control computer sends out a generator isolation instruction, and the control module disconnects the normally closed contactor on one side of the fault generator, so that the fault is isolated. In this state, the power supply mode of a single generator is entered, and the side of the generator without fault is normally supplied with power.
In step S340, when both the first generator and the second generator have faults, the first normally closed contactor and the second normally closed contactor are controlled to be opened. When the generators on the left side and the right side are in fault, the control module uploads the fault signals of the generators on the left side and the right side to the flight control computer, the flight control computer sends out a generator isolation instruction, and the control module disconnects the first normally-closed contactor and the second normally-closed contactor. Therefore, the emergency power supply mode is entered, and the first storage battery pack and the second storage battery pack supply power.
Fig. 4 shows a flow chart of a power distribution management method according to another example embodiment of the present application.
According to another exemplary embodiment of the present application, as shown in fig. 4, the power distribution management method further includes:
in step S350, when both the first generator and the second generator fail, the first SSPC channel and the second SSPC channel between the first non-critical bus bar, the second non-critical bus bar and the first main bus bar, the second main bus bar are disconnected. The flight control computer sends out a non-key bus bar disconnection instruction, and the control module simultaneously disconnects the power supply of the non-key bus bar by controlling the first SSPC channel and the second SSPC channel. And in the emergency power supply mode, the non-critical power supply equipment is disconnected for supplying power so as to ensure the normal power supply of the critical equipment.
In step S360, when the first main bus bar or the second main bus bar is short-circuited and the first generator and/or the second generator fails, the normally open contactor is controlled to be closed. In the operation process, when detecting left/right main busbar short circuit, single generator trouble or two generators all break down, the flight control computer sends the reconsitution instruction, and control module control normally open contactor is closed, and the effective power supply of the left and right sides will be simultaneously for controlling the airborne equipment power supply on the incessant busbar this moment, guarantees that unmanned aerial vehicle can the safe operation.
Fig. 5 shows a block diagram of power distribution management electronics, according to an example embodiment of the present application.
The present application further provides a power distribution management electronic device 700 for a dual-engine aircraft. The electronic device 700 shown in fig. 5 is only an example, and should not bring any limitation to the functions and the scope of use of the embodiments of the present application.
As shown in fig. 5, electronic device 700 is embodied in the form of a general purpose computing device. The components of the electronic device 700 may include, but are not limited to: at least one processing unit 710, at least one memory unit 720, a bus 730 that couples various system components including the memory unit 720 and the processing unit 710, and the like.
The storage unit 720 stores program codes, which can be executed by the processing unit 710 to cause the processing unit 710 to execute the methods according to the above-mentioned embodiments of the present application described in the present specification.
The storage unit 720 may include readable media in the form of volatile memory units, such as a random access memory unit (RAM)7201 and/or a cache memory unit 7202, and may further include a read only memory unit (ROM) 7203.
The storage unit 720 may also include a program/utility 7204 having a set (at least one) of program modules 7205, such program modules 7205 including, but not limited to: an operating system, one or more application programs, other program modules, and program data, each of which, or some combination thereof, may comprise an implementation of a network environment.
The electronic device 700 may also communicate with one or more external devices 7001 (e.g., touch screen, keyboard, pointing device, bluetooth device, etc.), with one or more devices that enable a user to interact with the electronic device 700, and/or with any devices (e.g., router, modem, etc.) that enable the electronic device 700 to communicate with one or more other computing devices. Such communication may occur via an input/output (I/O) interface 750. Also, the electronic device 700 may communicate with one or more networks (e.g., a Local Area Network (LAN), a Wide Area Network (WAN), and/or a public network such as the internet) via the network adapter 760. The network adapter 760 may communicate with other modules of the electronic device 700 via the bus 730. It should be appreciated that although not shown in the figures, other hardware and/or software modules may be used in conjunction with the electronic device 700, including but not limited to: microcode, device drivers, redundant processing units, external disk drive arrays, RAID systems, tape drives, and data backup storage systems, among others.
The present application also relates to a computer-readable medium, on which a computer program is stored, which program, when being executed by a processor, is adapted to carry out the above-mentioned power distribution management method.
The utility model provides a distribution management system and method of two aircrafts send out according to the equipment redundancy characteristics of two unmanned aerial vehicle, integrated main busbar, incessant busbar, engine busbar, non-key busbar etc. according to flying control computer instruction with left and right generator and storage battery power rational distribution, combine power redundancy and airborne equipment redundancy, the advantage of two generators of rational utilization, realize two unmanned aerial vehicle's three redundancy distribution management, and realize airborne equipment is hierarchical, distribution management stage by stage.
The foregoing detailed description of the embodiments of the present application has been presented to illustrate the principles and implementations of the present application, and the description of the embodiments is only intended to facilitate the understanding of the methods and their core concepts of the present application. Meanwhile, a person skilled in the art should, according to the idea of the present application, change or modify the embodiments and applications of the present application based on the scope of the present application. In view of the above, the description should not be taken as limiting the application.
Claims (10)
1. A power distribution management system for a dual-engine aircraft, comprising:
the data transmission module is connected with a flight control computer of the airplane through a bus and transmits a flight control instruction;
the data acquisition module is connected with an airborne sensor on the airplane and used for acquiring airborne equipment signals of the airplane;
the comprehensive power distribution module is connected with the airborne equipment and supplies power to the airborne equipment;
and the control module is respectively connected with the data transmission module, the data acquisition module and the comprehensive power distribution module, judges the fault condition according to the acquired airborne equipment signal, reconstructs a power distribution system according to a flight control instruction, and controls the comprehensive power distribution module to supply power for two generators, a single generator or emergency power supply.
2. The power distribution management system of claim 1, wherein the integrated power distribution module comprises:
the first main bus bar and the second main bus bar are respectively connected with the generators of the two engines through a first normally closed contactor and a second normally closed contactor;
the first storage battery bus bar and the second storage battery bus bar are respectively connected with the first main bus bar and the second main bus bar through a first circuit breaker and a second circuit breaker;
the first battery bus bar is connected to the second battery bus bar through a normally open contactor.
3. The power distribution management system of claim 2, wherein the integrated power distribution module further comprises:
a first uninterrupted bus bar connected to the first main bus bar and the first battery bus bar, respectively;
the second uninterrupted bus bar is respectively connected with the second main bus bar and the second storage battery bus bar;
and a first engine bus bar and a second engine bus bar connected to the first main bus bar and the second main bus bar, respectively.
4. The power distribution management system of claim 3, wherein the integrated power distribution module further comprises:
a first ECUB bus bar having one end connected to the first engine bus bar and the other end connected to the second engine bus bar;
a second ECUB bus bar having one end connected to the second engine bus bar and the other end connected to the first engine bus bar.
5. The power distribution management system of claim 2, wherein the integrated power distribution module further comprises:
first and second non-critical bus bars connected to the first and second main bus bars through first and second SSPC channels, respectively.
6. The power distribution management system of claim 1, further comprising:
and the power supply management module is connected with the control module and provides a power supply for the control module.
7. A power distribution management method for a dual-engine aircraft, applied to the power distribution management system of claim 6, comprising:
under the normal operation state of the two engines, the normally open contactor is disconnected, the first normally closed contactor and the second normally closed contactor are closed, and the first circuit breaker and the second circuit breaker are conducted;
when the first main bus bar or the second main bus bar is short-circuited, the corresponding first circuit breaker or second circuit breaker is actively disconnected;
when the first generator or the second generator has faults, the corresponding first normally closed contactor or the corresponding second normally closed contactor is controlled to be disconnected;
and when the first generator and the second generator both have faults, the first normally closed contactor and the second normally closed contactor are controlled to be disconnected.
8. The power distribution management method of claim 7, wherein when both the first generator and the second generator fail, further comprising:
disconnecting the first and second SSPC channels between the first and second non-critical bus bars and the first and second main bus bars.
9. The power distribution management method of claim 7, further comprising:
and when the first main bus bar or the second main bus bar is in short circuit and the first generator and/or the second generator are/is in fault, controlling the normally open contactor to be closed.
10. The power distribution management method of claim 7, further comprising:
the data acquisition module acquires electrical parameters of a power interface, a bus bar and electric equipment in the power distribution system and transmits the electrical parameters to the control module;
the control module carries out fault judgment according to the electrical parameters and transmits a fault judgment result to the flight control computer through the data transmission module;
and the flight control computer transmits an isolation instruction or a reconstruction instruction to the control module according to the fault result.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010889697.8A CN112072778A (en) | 2020-08-28 | 2020-08-28 | Power distribution management system and method for double-engine aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
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| US5715124A (en) * | 1996-04-08 | 1998-02-03 | Sundstrand Corporation | System and method of isolation for detecting a passive protective function failure for an electric power generating system |
| 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 |
| CN104659900A (en) * | 2013-11-25 | 2015-05-27 | 中国直升机设计研究所 | Power supply system of unmanned helicopter |
| CN108964004A (en) * | 2017-05-25 | 2018-12-07 | 通用电气航空系统有限责任公司 | Distribution system and the method with electricity condition for indicating wherein power device |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5715124A (en) * | 1996-04-08 | 1998-02-03 | Sundstrand Corporation | System and method of isolation for detecting a passive protective function failure for an electric power generating system |
| CN104659900A (en) * | 2013-11-25 | 2015-05-27 | 中国直升机设计研究所 | Power supply system of unmanned helicopter |
| 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 |
| CN108964004A (en) * | 2017-05-25 | 2018-12-07 | 通用电气航空系统有限责任公司 | Distribution system and the method with electricity condition for indicating wherein power device |
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