CN112072778B - 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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- CN112072778B CN112072778B CN202010889697.8A CN202010889697A CN112072778B CN 112072778 B CN112072778 B CN 112072778B CN 202010889697 A CN202010889697 A CN 202010889697A CN 112072778 B CN112072778 B CN 112072778B
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- 238000000034 method Methods 0.000 title abstract description 10
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 29
- 230000005540 biological transmission Effects 0.000 claims abstract description 13
- 238000007726 management method Methods 0.000 claims description 51
- 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 3
- 238000011161 development Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000003491 array Methods 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000004590 computer program Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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Classifications
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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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- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- 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 aircraft, wherein the power distribution management system comprises the following components: the data transmission module is connected with the flight control computer of the aircraft through a bus and transmits flight control instructions; the data acquisition module is connected with an airborne sensor of the aircraft and is used for acquiring airborne equipment signals of the aircraft; the comprehensive power distribution module is connected with the airborne equipment and supplies power for the airborne equipment; 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 signals, reconstructs the power distribution system according to the flight control instruction, and controls the comprehensive power distribution module to supply power to two generators, to supply power to a single generator or to supply power to an emergency. The device redundancy advantage of the double generators is reasonably utilized, a three-redundancy power distribution system for supplying power to the two generators of the double-generator aircraft, supplying power to the single generator and supplying power to the storage battery pack under emergency conditions is realized, and the power supply and distribution reliability is improved.
Description
Technical Field
The application relates to the technical field of aircraft power distribution, in particular to a power distribution management system and method of a double-engine aircraft.
Background
The power distribution system is used as an important component system of the aircraft and is used for transmitting and distributing electric energy provided by the generator to electric equipment of the aircraft, and has great significance for flight safety and autonomous flight of the aircraft. The control modes of the aircraft power distribution system comprise a centralized control mode, a decentralized control mode and a distributed control mode. Early aircraft basically used centralized control, i.e., power distribution through the cockpit. With the development and application of computer technology, the distributed control mode and the scattered control mode are successfully applied to the aircraft.
The unmanned aerial vehicle electrical system at home and abroad basically adopts the electrical system design of the unmanned aerial vehicle, and the electrical equipment is more and heavy, for example, bus bars adopt a disc box type design, the volume is larger, the assembly time is long, and the on-site wiring is required during installation; the whole machine is provided with a large number of relay boxes for power distribution, so that an onboard 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 using an electrical system of the unmanned aerial vehicle. However, the existing power distribution system is suitable for a small single-shot unmanned aerial vehicle, the power supply of the power distribution system is a low-voltage direct-current generator, and the emergency power supply is a storage battery pack.
Disclosure of Invention
Based on the power distribution management system and method of the double-generator aircraft, provided by the application, the equipment redundancy advantages of the double-generator aircraft are reasonably utilized, and the three-redundancy power distribution system of the double-generator aircraft, which is powered by two generators, by a single generator and by a storage battery pack in an emergency condition, is realized.
The application provides a power distribution management system of a double-engine aircraft, which comprises:
the data transmission module is connected with the flight control computer of the aircraft through a bus and transmits flight control instructions;
the data acquisition module is connected with an airborne sensor of the aircraft and is used for acquiring airborne equipment signals of the aircraft;
The comprehensive power distribution module is connected with the airborne equipment and supplies power for the airborne equipment;
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 signals, reconstructs the power distribution system according to the flight control instruction, and controls the comprehensive power distribution module to supply power to two generators, to supply power to a single generator or to supply power to an emergency.
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 the first circuit breaker and the second circuit breaker;
the first battery bus bar is connected to the second battery bus bar by a normally open contactor.
According to some embodiments of the 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;
a second uninterrupted bus bar connected to the second main bus bar and the second battery bus bar, respectively;
the first and second engine bus bars are connected to the first and second main bus bars, respectively.
According to some embodiments of the application, the integrated power distribution module further comprises:
A first ECUB bus bar, one end of which is connected with the first engine bus bar, and the other end of which is connected with the second engine bus bar;
and one end of the second ECUB bus bar is connected with the second engine bus bar, and the other end of the second ECUB bus bar is connected with the first engine bus bar.
According to some embodiments of the application, the integrated power distribution module further comprises:
first and second non-critical bus bars are connected to the first and second main bus bars by first and second SSPC channels, respectively.
According to some embodiments of the application, the power distribution management system further comprises:
And the power management module is connected with the control module and provides power supply for the control module.
According to another aspect of the present application, there is provided a power distribution management method for a two-shot aircraft, which is applied to the above power distribution management system, the power distribution management method including:
Under the normal running 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 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 fails, the corresponding first normally-closed contactor or second normally-closed contactor is controlled to be disconnected;
and when the first generator and the second generator are in failure, the first normally-closed contactor and the second normally-closed contactor are controlled to be disconnected.
According to some embodiments of the application, the power distribution management method further comprises:
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.
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 short-circuited, the first generator and/or the second generator is/are in fault, the normally open contactor is controlled 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 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 application.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for the description of the embodiments will be briefly described below, and it will be apparent that the drawings in the following description are only some embodiments of the present application, and that other drawings can be obtained according to these drawings by those skilled in the art without departing from the scope of the claimed application.
Fig. 1 shows a schematic diagram of a power distribution management system according to an example embodiment of the application.
Fig. 2 shows a block diagram of a power distribution management system according to an example embodiment of the application.
Fig. 3 shows a flow chart of a power distribution management method according to an example embodiment of the application.
Fig. 4 shows a flow chart of a power distribution management method according to another example embodiment of the application.
Fig. 5 shows a block diagram of a power distribution management electronic device according to an example embodiment of the application.
Detailed Description
The following description of the embodiments of the present application will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are some, but not all embodiments of the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
The power distribution power supply of the double-power unmanned aerial vehicle comprises two generators, so that the double-power unmanned aerial vehicle has the advantage of power supply redundancy. The existing single-shot unmanned aerial vehicle power distribution management system and method are not suitable for double-shot unmanned aerial vehicles, the power supply redundancy advantages of the double-shot unmanned aerial vehicles cannot be reasonably utilized, and reasonable distribution of a power supply system is achieved. In addition, when the double-shot unmanned aerial vehicle breaks down, the existing single-shot power distribution management system cannot perform reasonable and applicable system reconstruction and fault isolation.
Therefore, the inventor provides a power distribution management system and a power distribution management method suitable for the double-engine unmanned aerial vehicle aiming at the characteristics of the double-engine unmanned aerial vehicle, fully utilizes the power supply redundancy advantages of the double-engine unmanned aerial vehicle, realizes reasonable distribution of power supply and load, can complete fault positioning and isolation and system reconstruction when faults occur, and realizes three-redundancy power distribution of power supply of two generators, power supply of a single generator and power supply of a storage battery pack under emergency conditions, thereby ensuring uninterrupted power supply and improving fault tolerance level.
The technical scheme 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 application.
According to a first aspect of the present application, a power distribution management system 1000 for a two-shot aircraft is provided, 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 an integrated power distribution module 400.
The data transmission module 200 is connected with the flight control computer 2000 of the aircraft through a bus. The data acquisition module 300 is connected to the on-board sensor 3000 to acquire on-board equipment signals. And the comprehensive power distribution module is connected with the airborne equipment 4000 and supplies 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 airborne equipment signals acquired by the data acquisition module 300 to judge the fault condition; the fault condition is sent to the flight control computer 2000 through the data transmission module 200; the flight control calculation 2000 sends flight control instructions of fault isolation or system reconstruction 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 comprehensive power distribution module 400 to respectively supply power to two generators, supply power to a single generator and supply power to an emergency.
According to some embodiments of the present application, the power distribution management system 1000 further includes 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 monitors faults through the data acquisition module 300; after the fault is monitored, the fault condition is fed back to the flight control computer, fault isolation and system reconstruction are timely carried out according to the flight control instruction, and on the basis of reasonably utilizing the redundancy of the airborne equipment, the power distribution redundancy is combined with the redundancy of the airborne equipment, so that three redundancy power distribution of power supply of two generators, power supply of a single generator and power supply of a storage battery pack under emergency conditions is realized, and uninterrupted power supply and power distribution reliability are realized.
Fig. 2 shows a block diagram of a power distribution management system according to an example embodiment of the application.
As shown in fig. 2, the power distribution management system 1000 provided by the present application is configured such that, during an application process, an integrated power distribution module (not shown) performs power distribution through a set of bus bars. According to an example embodiment of the 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 the left generator 9000 and the right generator 8000 of the two engines through a first normally-closed contactor K2 and a second normally-closed contactor K3, respectively. The left and right generators 9000, 8000 supply power to the first and second main bus bars 410, 420 (left and right main bus bars), 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 the first and second circuit breakers B1 and B2, respectively. The first and second main bus bars 410, 420 supply power to the first and second battery bus bars 430 (left and right battery bus bars) 440, respectively.
The first battery bus bar 430 (left battery bus bar) and the second battery bus bar 440 (right battery bus bar) are connected to the first battery pack 7000 and the second battery pack 6000, respectively. The first battery pack 7000 and the second battery pack 6000 supply power to the first battery bus 430 (left battery bus) and the second battery bus 440 (right battery bus), respectively. First battery bus bar 430 is connected to second battery bus bar 440 by a normally open contact K1. Under the normal operation state of the unmanned aerial vehicle, the normally open contactor K1 is in an open state, and power distribution on two sides is not mutually interfered.
The first uninterrupted bus 470 is connected to the first main bus 410 and the first battery bus 430 via diodes D1 and D2, respectively. The first uninterrupted bus 470 is powered by the first main bus 410, the first battery bus 430.
The second ups bus 480 is connected to the second main bus 420 and the second battery bus 440 by diodes D3, D4, respectively. The second uninterruptible bus 480 is powered by the second main bus 420, the second battery bus 440.
The first and second engine bus bars 450, 460 are connected to the first and second main bus bars 410, 420 by diodes D5, D6, respectively. The first engine bus 450 and the second engine bus 460 are powered by the first main bus 410 and the second main bus 420, respectively.
In the power distribution management system provided by the application, the power distribution bus bars are divided into key equipment and non-key equipment according to the grades of power supply equipment, and the bus bars are 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, a second ECUB bus bar 4040, and the like.
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 by a first SSPC channel and a second SSPC channel, respectively. The first non-critical bus bar 4010 and the second non-critical bus bar 4020 are powered by the first main bus bar 410 and the second main bus bar 420, respectively.
The first ECUB bus 4030 is connected to the first engine bus 450 at one end and to the second engine bus 460 at the other end via diode D8. The second ECUB bus 4040 is connected at one end to the second engine bus 460 and at the other end to the first engine bus 450 via diode D7. Thus, the first engine bus 450 provides power to the first ECUB bus 4030 while providing power to the second ECUB bus 4040 through the diode. The second engine bus 460 simultaneously supplies power to the second ECUB bus 4040 while supplying power to the first ECUB bus 4030 through a diode.
Fig. 3 shows a flow chart of a power distribution management method according to an example embodiment of the application.
According to an exemplary 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 electric equipment 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, in the normal running 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 conducted. In this state, the two generators supply power, and the power distribution on both sides of the normally open contactor K1 is not interfered 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 opened. Under the state, a single generator power supply mode is entered, and the side of the main bus bar which does not have short circuit fault normally supplies 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 second normally-closed contactor is controlled to be opened. When one side of the generator fails, the control module uploads a failure signal of the generator to the flight control computer, the flight control computer sends out a generator isolation instruction, and the control module breaks off a normally closed contactor at one side of the failed generator, so that the failure is isolated. In this state, a single generator power supply mode is entered, and the power supply is normally performed on the side of the generator where no failure occurs.
In step S340, when both the first generator and the second generator fail, 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 all 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, and 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 power is supplied by the first storage battery pack and the second storage battery pack.
Fig. 4 shows a flow chart of a power distribution management method according to another example embodiment of the application.
According to another exemplary embodiment of the present application, as shown in fig. 4, the above 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-critical bus bar disconnection instruction, and the control module simultaneously disconnects the power supply of the non-critical bus bar by controlling the first SSPC channel and the second SSPC channel. In the emergency power supply mode, the power supply of the non-key power supply equipment is disconnected, so that the normal power supply of the key power supply equipment is ensured.
In step S360, the normally open contactor is controlled to close when the first or second main bus bar is shorted, the first generator and/or the second generator fails. In the operation process, when detecting that the left/right main bus bar is short-circuited, a single generator is failed or both generators are failed, the flight control computer sends out a reconstruction instruction, the control module controls the normally open contactor to be closed, and at the moment, the effective power supplies on the left side and the right side simultaneously supply power for the airborne equipment on the left uninterrupted bus bar and the right uninterrupted bus bar, so that the unmanned aerial vehicle can safely operate.
Fig. 5 shows a block diagram of a power distribution management electronic device according to an example embodiment of the application.
The application also provides power distribution management electronic equipment 700 of the double-engine aircraft. The electronic device 700 shown in fig. 5 is merely an example, and should not be construed as limiting the functionality and scope of use of embodiments of the present application.
As shown in fig. 5, the electronic device 700 is embodied in the form of a general purpose computing device. Components of 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 connecting the different system components, including the memory unit 720 and the processing unit 710, etc.
The storage unit 720 stores program codes that can be executed by the processing unit 710, so that the processing unit 710 performs the methods according to the above-described embodiments of the present application described in the present specification.
The memory unit 720 may include readable media in the form of volatile memory units, such as Random Access Memory (RAM) 7201 and/or cache memory 7202, and may further include Read Only Memory (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 or some combination of which may include an implementation of a network environment.
Bus 730 may be a bus representing one or more of several types of bus structures including a memory unit bus or memory unit controller, a peripheral bus, an accelerated graphics port, a processing unit, or a local bus using any of a variety of bus architectures.
The electronic device 700 may also communicate with one or more external devices 7001 (e.g., touch screen, keyboard, pointing device, bluetooth device, etc.), one or more devices that enable a user to interact with the electronic device 700, and/or any device (e.g., router, modem, etc.) that enables the electronic device 700 to communicate with one or more other computing devices. Such communication may occur through an input/output (I/O) interface 750. Also, electronic device 700 may communicate with one or more networks such as a Local Area Network (LAN), a Wide Area Network (WAN) and/or a public network, such as the Internet, through network adapter 760. Network adapter 760 may communicate with other modules of electronic device 700 via bus 730. It should be appreciated that although not shown, other hardware and/or software modules may be used in connection with electronic device 700, including, but not limited to: microcode, device drivers, redundant processing units, external disk drive arrays, RAID systems, tape drives, data backup storage systems, and the like.
The present application is also a computer-readable medium having stored thereon a computer program which, when executed by a processor, implements the above-described power distribution management method.
According to the power distribution management system and method of the double-engine aircraft, the main bus bar, the uninterrupted bus bar, the engine bus bar, the non-key bus bar and the like are integrated according to the equipment redundancy characteristics of the double-engine unmanned aerial vehicle, the left and right generators and the storage battery power supply are reasonably distributed according to the flight control computer instructions, the power supply redundancy is combined with the airborne equipment redundancy, the advantages of the double generators are reasonably utilized, the three-redundancy power distribution management of the double-engine unmanned aerial vehicle is realized, and the grading and staged power distribution management of the airborne equipment is realized.
The foregoing has outlined rather broadly the more detailed description of embodiments of the application in order that the detailed description of the principles and embodiments of the application may be implemented in conjunction with the detailed description of embodiments of the application that follows. Meanwhile, based on the idea of the present application, those skilled in the art can make changes or modifications on the specific embodiments and application scope of the present application, which belong to the protection scope of the present application. In view of the foregoing, this description should not be construed as limiting the application.
Claims (6)
1. A power distribution management system for a twin aircraft, comprising:
the data transmission module is connected with the flight control computer of the aircraft through a bus and transmits flight control instructions;
the data acquisition module is connected with an airborne sensor on the aircraft and used for acquiring airborne equipment signals of the aircraft;
The comprehensive power distribution module is connected with the airborne equipment and supplies power for the airborne equipment;
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 signals, reconstructs the power distribution system according to the flight control instruction, and controls the comprehensive power distribution module to supply power to two generators, a single generator or an emergency power supply;
The comprehensive 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 the first circuit breaker and the second circuit breaker;
The first storage battery bus bar is connected with the second storage battery bus bar through a normally open contactor;
A first uninterrupted bus bar connected to the first main bus bar and the first battery bus bar, respectively;
a second uninterrupted bus bar connected to the second main bus bar and the second battery bus bar, respectively;
first and second engine bus bars connected to the first and second main bus bars, respectively;
A first ECUB bus bar, one end of which is connected with the first engine bus bar, and the other end of which is connected with the second engine bus bar;
a second ECUB bus bar, one end of which is connected with the second engine bus bar, and the other end of which is connected with the first engine bus bar;
first and second non-critical bus bars are connected to the first and second main bus bars by first and second SSPC channels, respectively.
2. The power distribution management system of claim 1, further comprising:
And the power management module is connected with the control module and provides power supply for the control module.
3. A power distribution management method of a double-engine aircraft, applied to the power distribution management system of any one of claims 1-2, comprising:
Under the normal running 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 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 fails, the corresponding first normally-closed contactor or second normally-closed contactor is controlled to be disconnected;
and when the first generator and the second generator are in failure, the first normally-closed contactor and the second normally-closed contactor are controlled to be disconnected.
4. The power distribution management method according to claim 3, wherein when both the first generator and the second generator fail, further comprising:
The first SSPC channel and the second SSPC channel are disconnected between the first non-critical bus bar, the second non-critical bus bar, and the first main bus bar, the second main bus bar.
5. The power distribution management method according to claim 3, further comprising:
And when the first main bus bar or the second main bus bar is short-circuited, the first generator and/or the second generator is/are in fault, the normally open contactor is controlled to be closed.
6. The power distribution management method according to claim 3, 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 CN112072778B (en) | 2020-08-28 | 2020-08-28 | Power distribution management system and method for double-engine aircraft |
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| CN204089325U (en) * | 2014-08-18 | 2015-01-07 | 江西洪都航空工业集团有限责任公司 | The novel power supply circuits of a kind of flight control system |
| CN104659900A (en) * | 2013-11-25 | 2015-05-27 | 中国直升机设计研究所 | Power supply system of unmanned helicopter |
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| US10601218B2 (en) * | 2017-05-25 | 2020-03-24 | Ge Aviation Systems Llc | Power management and fault detection system |
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| 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 |
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