CN110635451A - Differential protection structure of single-channel multi-electric aircraft bus bar power controller - Google Patents
Differential protection structure of single-channel multi-electric aircraft bus bar power controller Download PDFInfo
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- CN110635451A CN110635451A CN201810549337.6A CN201810549337A CN110635451A CN 110635451 A CN110635451 A CN 110635451A CN 201810549337 A CN201810549337 A CN 201810549337A CN 110635451 A CN110635451 A CN 110635451A
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- contactor
- bus bar
- current transformer
- tru
- differential protection
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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
- H02H3/26—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 responsive to difference between voltages or between currents; responsive to phase angle between voltages or between currents
- H02H3/32—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 responsive to difference between voltages or between currents; responsive to phase angle between voltages or between currents involving comparison of the voltage or current values at corresponding points in different conductors of a single system, e.g. of currents in go and return conductors
- H02H3/325—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 responsive to difference between voltages or between currents; responsive to phase angle between voltages or between currents involving comparison of the voltage or current values at corresponding points in different conductors of a single system, e.g. of currents in go and return conductors involving voltage comparison
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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
- H02J3/38—Arrangements for parallely feeding a single network by two or more generators, converters or transformers
- H02J3/46—Controlling of the sharing of output between the generators, converters, or transformers
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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
- H02J5/00—Circuit arrangements for transfer of electric power between ac networks and dc networks
Abstract
The invention discloses a differential protection structure of a single-channel multi-electric-aircraft bus bar power controller.A BPCU can monitor the current of an input feeder line of a distribution board box (realized by a CT connected in a loop in series). The output connections of these ct (current transformer) are of particular concern, the sum of their output currents passing through a load resistor. As long as the current flowing into the distribution box is equal to the current flowing out of the distribution box, the voltage difference detected across the load resistor is 0, i.e. there is no differential fault condition. The three-phase current input to the feeder is monitored. If the DP (differential protection) differential current of any phase is greater than 40A, the BPCU protection is triggered, the L/R EPC, the corresponding L/R BSB and L/R ATUC are switched off and locked, and the maximum delay time is 100 ms.
Description
Technical Field
The invention relates to a differential protection structure of a single-channel multi-electric aircraft bus bar power controller.
Background
The Bus Power Control Unit (BPCU) has two functions, one is to realize load-oriented Power transmission through Control of the aircraft grid Power switch under normal conditions, and the other is to provide protection for the distribution Bus and the Power elements.
The power grid configuration of the traditional airplane is simple, and the protection and control functions of the BPCU are not complicated. Under the multi-electric airplane system, besides the conventional control and protection functions, the BPCU also needs to be matched with the BPCU at the opposite side to realize fault location and isolation under the fault condition.
Disclosure of Invention
The invention implements protection by detecting whether the current flowing into the distribution box is equal to the current flowing out of the distribution box, can effectively avoid the occurrence of ground faults, and provides a novel differential protection structure of a single-channel multi-electric-aircraft bus bar power controller.
In order to achieve the purpose, the technical scheme of the invention is as follows: a differential protection structure of a single-channel multi-electric aircraft bus bar power controller comprises,
the Bus bar L235 VAC Bus is connected with a first end of a contactor L ATUC, a second end of the contactor L ATUC is respectively connected with a first end of an electric energy conversion device L ATU, a first end of a contactor L TUR Rly and a first end of a contactor E1 TRU ISO Rly, the electric energy conversion device L ATU is further connected with a first end of a contactor L BSB and a first end of a contactor L EPC, a second end of the contactor L BSB is connected with the Bus bar L115 VAC Bus, a second end of the contactor L EPC is connected with a ground power supply L FWD EP, a second end of the contactor L TRU Rly is connected with a power supply conversion device TRU L, and a second end of the contactor E1 TRU ISO Rly is connected with a power supply conversion device TRU E1;
the Bus bar R235 VAC Bus is connected with a first end of a contactor R ATUC, a second end of the contactor R ATUC is respectively connected with an electric energy conversion device R ATU, a first end of the contactor R TUR Rly and a first end of the contactor E2 TRU ISO Rly, the electric energy conversion device R ATU is further connected with a first end of a contactor R BSB and a first end of a contactor R EPC, a second end of the contactor R BSB is connected with the Bus bar R115 VAC Bus, a second end of the contactor R EPC is connected with a ground power supply R FWD EP, a second end of the contactor R TRU Rly is connected with a power supply conversion device TRU R, and a second end of the contactor E2 TRU RISO is connected with a power supply conversion device TRU 2;
the left Bus bar power control assembly is provided with a Bus bar power controller L BPCU, a left first current transformer arranged on a Bus bar L235 VAC Bus output feeder, a left second current transformer arranged on a power converter TRU L28 VDC input feeder, a left third current transformer arranged on a power converter TRU E128 VDC input feeder, a left fourth current transformer arranged on a LATU 115VAC input feeder and a left differential protection sampling resistor DP, and the left differential protection sampling resistor DP is respectively connected with the left first current transformer, the left second current transformer, the left third current transformer and the left fourth current transformer; and the number of the first and second groups,
the right Bus bar power control assembly is provided with a Bus bar power controller R BPCU, a right first current transformer arranged on a Bus bar R235 VAC Bus output feeder, a right second current transformer arranged on a power converter TRU R28 VDC input feeder, a right third current transformer arranged on a power converter TRU E228 VDC input feeder, a right fourth current transformer and a right differential protection sampling resistor DP arranged on a RATU 115VAC input feeder, and the right differential protection sampling resistor DP is respectively connected with the right first current transformer, the right second current transformer, the right third current transformer and the right fourth current transformer.
As a preferred scheme of the differential protection structure of the single-channel multi-electric-aircraft bus bar power controller, if the voltage drop of the left differential protection sampling resistor DP is converted into a current larger than 40A, the bus bar power controller L BPCU opens and locks the contactors LEPC and L BSB, and simultaneously sends a differential protection L BSB trip request to the bus bar power controller R BPCU through the communication bus and sends a DP protection ATUC trip request to the L GCU; the bus bar power controller R BPCU responds to the request, opening and latching the contactor L BSB; the L GCU will also open and latch the contactor L ATUC in response to the received request.
As a preferred scheme of the differential protection structure of the single-channel multi-electric-aircraft bus bar power controller, if the voltage drop of the right differential protection sampling resistor DP is converted into a current larger than 40A, the bus bar power controller R BPCU opens and locks the contactors REPC and R BSB, and simultaneously sends a differential protection R BSB trip request to the bus bar power controller L BPCU through the communication bus and sends a DP protection ATUC trip request to the R GCU; the bus bar power controller L BPCU responds to the request, opening and latching the contactor R BSB; the rgcu will also open and latch the contactor rtauc in response to the received request.
Compared with the prior art, the invention has the beneficial effects that the protection is implemented by detecting whether the currents flowing into the distribution board box and flowing out of the distribution board box are equal, so that the occurrence of ground faults can be effectively avoided.
In addition to the technical problems addressed by the present invention, the technical features constituting the technical solutions, and the advantageous effects brought by the technical features of the technical solutions described above, other technical problems solved by the present invention, other technical features included in the technical solutions, and advantageous effects brought by the technical features will be described in further detail with reference to the accompanying drawings.
Drawings
Fig. 1 is a power system architecture for a single-channel multi-electric aircraft.
FIG. 2 illustrates a Differential Protection (DP) protected point of acquisition.
Fig. 3 is a differential protection control logic for the L BPCU.
FIG. 4 is a differential protection control logic for the R BPCU.
Detailed Description
The present invention will be described in further detail below with reference to specific embodiments and drawings. Here, the description of the embodiments is provided to help understanding of the present invention, but the present invention is not limited thereto. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
Referring to fig. 1, the generator includes left and right 2 variable frequency main starting generators GEN L and GEN R rated at 225kVA, an APU starting generator rated at 200kVA, and an RAT generator rated at 50 kVA. There are also three external power sources, L FWD EP, R FWD EP and L AFT EP, respectively, the outlets of each of which can support a maximum of 90kVA of power. The rated voltages of the main starter generator, the APU starter generator and the RAT generator are all 235VAC, and the rated voltages of the three external power supplies are 115 VAC.
GEN L, GEN R and APU GEN are provided with respective generator breakers L GCB, R GCB and APB to control the switching of the generators, and in addition, the 3 generators are also provided with corresponding contactors L GNR, R GNR and A GNR to control the connection with a ground network.
The three external power supplies also have corresponding contactors for controlling the access of the power supplies, namely L EPC, R EPC and L AEPC.
The secondary power supply of the power supply system comprises 2 ATRUs with rated power of 150kVA, two ATUs with rated capacity of 60kVA and 4 TRUs with rated output current of 240A. Wherein, the ATRU converts 235VAC into +/-270VDC, and respectively outputs the +/-270VDC to the left and right buses for supplying power to multi-electrical loads (flight control actuation, electrical ring control and the like); the ATU converts 230VAC into 115VAC, and respectively outputs the 115VAC to the left and right 115VAC bus bars; the TRU converts 235VAC into 28VDC, and outputs the 28VDC normal bus bars and the 28VDC emergency bus bars to the left and right.
The power supply system has two batteries with the rated voltage of 28VDC and the capacity of 75Ah, namely a main battery and an APU battery, and the batteries can supply power to key electronic equipment before the aircraft generator is started. Meanwhile, the APU battery can also be used to start the APU.
Referring to fig. 2, a Differential Protection (DP) protected point of acquisition.
The BPCU monitors the current in the distribution box input feed line, which is achieved by a CT connected in series in the loop. The output wiring of these CTs is of particular concern, and the sum of their output currents will pass through a load resistor. As long as the current flowing into the distribution box is equal to the current flowing out of the distribution box, the voltage difference detected across the load resistor is 0, i.e. there is no differential fault condition. The three-phase current input to the feeder is monitored.
If the DP differential current of any phase is larger than 40A, the BPCU protection is triggered, the L/R EPC, the corresponding L/R BSB and the L/R ATUC are switched off and locked, and the maximum delay time is 100 ms.
Current transformers are mounted on the 235VAC Bus output feeder, the TRU L28 VDC input feeder, the TRU E128 VDC input feeder, and the L ATU 115VAC input feeder. The output terminals of these current transformers are collected to a differential protection sampling resistor. Normally, when the 235VAC Bus output current is equal to the sum of the TRU L28 VDC, TRU E128 VDC input currents, and the L ATU 115VAC input current, the resulting voltage drop across the DP sampling resistor is 0.
When the voltage drop generated in the DP is larger than 40A when converted into a current, the differential protection operates.
The protection function is based on two configurations, L BPCU and R BPCU, which are described separately below.
1 L BPCU
If a DP fault protection condition exists, the L BPCU will disconnect and lock the L EPC, L BSB, while sending a differential protection L BSB trip request to the R BPCU over the communication bus and a DP protection ATUC trip request to the L GCU. The R BPCU will respond to the request, open and block the L BSB; the L GCU will also disconnect and lock the L ATUC in response to the received request.
The DP protection control logic of the L BPCU is shown in fig. 3.
2 R BPCU
If a DP fault protection condition exists, the R BPCU will open and lock the R EPC, R BSB, and send a differential protection R BSB trip request to the L BPCU through the communication bus, and a DP protection ATUC trip request to the R GCU. The L BPCU will respond to the request, open and block the R BSB; the rgcu will also open and block the rtauc in response to the received request.
The DP protection control logic of the R BPCU is shown in fig. 4.
The foregoing merely represents embodiments of the present invention, which are described in some detail and detail, and therefore should not be construed as limiting the scope of the invention. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the inventive concept, which falls within the scope of the present invention. Therefore, the protection scope of the present patent shall be subject to the appended claims.
Claims (3)
1. The differential protection structure of the single-channel multi-electric aircraft bus bar power controller is characterized by comprising,
the Bus bar L235 VAC Bus is connected with a first end of a contactor L ATUC, a second end of the contactor L ATUC is respectively connected with a first end of an electric energy conversion device L ATU, a first end of a contactor L TUR Rly and a first end of a contactor E1 TRU ISO Rly, the electric energy conversion device L ATU is further connected with a first end of a contactor L BSB and a first end of a contactor L EPC, a second end of the contactor L BSB is connected with the Bus bar L115 VAC Bus, a second end of the contactor L EPC is connected with a ground power supply L FWD EP, a second end of the contactor L TRU Rly is connected with a power supply conversion device TRU L, and a second end of the contactor E1 TRU ISO Rly is connected with a power supply conversion device TRU E1;
the Bus bar R235 VAC Bus is connected with a first end of a contactor R ATUC, a second end of the contactor R ATUC is respectively connected with an electric energy conversion device R ATU, a first end of the contactor R TUR Rly and a first end of the contactor E2 TRU ISO Rly, the electric energy conversion device R ATU is further connected with a first end of a contactor R BSB and a first end of a contactor R EPC, a second end of the contactor R BSB is connected with the Bus bar R115 VAC Bus, a second end of the contactor R EPC is connected with a ground power supply R FWD EP, a second end of the contactor R TRU Rly is connected with a power supply conversion device TRU R, and a second end of the contactor E2 TRU RISO is connected with a power supply conversion device TRU 2;
the left Bus bar power control assembly is provided with a Bus bar power controller L BPCU, a left first current transformer arranged on a Bus bar L235 VAC Bus output feeder, a left second current transformer arranged on a power converter TRU L28 VDC input feeder, a left third current transformer arranged on a power converter TRU E128 VDC input feeder, a left fourth current transformer arranged on a LATU 115VAC input feeder and a left differential protection sampling resistor DP, and the left differential protection sampling resistor DP is respectively connected with the left first current transformer, the left second current transformer, the left third current transformer and the left fourth current transformer; and the number of the first and second groups,
the right Bus bar power control assembly is provided with a Bus bar power controller R BPCU, a right first current transformer arranged on a Bus bar R235 VAC Bus output feeder, a right second current transformer arranged on a power converter TRU R28 VDC input feeder, a right third current transformer arranged on a power converter TRU E228 VDC input feeder, a right fourth current transformer and a right differential protection sampling resistor DP arranged on a RATU 115VAC input feeder, and the right differential protection sampling resistor DP is respectively connected with the right first current transformer, the right second current transformer, the right third current transformer and the right fourth current transformer.
2. The differential protection architecture for a single channel multi-airplane bus bar power controller of claim 1, wherein if the voltage drop across the left differential protection sampling resistor DP translates to a current greater than 40A, the bus bar power controller L BPCU opens and locks the contactors L EPC and L BSB, while sending a differential protection L BSB trip request to the bus bar power controller R BPCU over the communications bus, sending a DP protection ATUC trip request to the L GCU; the bus bar power controller R BPCU responds to the request, opening and latching the contactor L BSB; the L GCU will also open and latch the contactor L ATUC in response to the received request.
3. The differential protection architecture for a single channel multi-airplane bus bar power controller of claim 1, wherein if the voltage drop across the right differential protection sampling resistor DP translates to a current greater than 40A, the bus bar power controller R BPCU opens and locks contactors R EPC and R BSB, while sending a differential protection R BSB trip request to the bus bar power controller L BPCU over the communications bus, a DP protection ATUC trip request to the R GCU; the bus bar power controller L BPCU responds to the request, opening and latching the contactor R BSB; the rgcu will also open and latch the contactor rtauc in response to the received request.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810549337.6A CN110635451B (en) | 2018-05-31 | 2018-05-31 | Differential protection structure of single-channel multi-electric aircraft bus bar power controller |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810549337.6A CN110635451B (en) | 2018-05-31 | 2018-05-31 | Differential protection structure of single-channel multi-electric aircraft bus bar power controller |
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| CN110635451A true CN110635451A (en) | 2019-12-31 |
| CN110635451B CN110635451B (en) | 2022-08-09 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117439022A (en) * | 2023-12-20 | 2024-01-23 | 天津航空机电有限公司 | Distribution board box protection structure and protection method |
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| US20140104734A1 (en) * | 2012-10-11 | 2014-04-17 | Airbus Operations (Sas) | Protection method and device of an electrical network for aircraft |
| US20160048186A1 (en) * | 2014-08-14 | 2016-02-18 | Zodiac Aero Electric | Electrical distribution system for an aircraft |
| CN107264812A (en) * | 2016-04-08 | 2017-10-20 | 陕西飞机工业（集团）有限公司 | A kind of emergent redundance power supply circuit of aircraft |
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2018
- 2018-05-31 CN CN201810549337.6A patent/CN110635451B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4321645A (en) * | 1980-02-26 | 1982-03-23 | Sundstrand Corporation | Differential fault current protection of a multiprocessor controlled electric power generating system |
| US5729059A (en) * | 1995-06-07 | 1998-03-17 | Kilroy; Donald G. | Digital no-break power transfer system |
| US20090190279A1 (en) * | 2008-01-24 | 2009-07-30 | Ileana Rusan | Electronic load control unit (elcu) used as bus tie breaker in electrical power distribution systems |
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| US20140104734A1 (en) * | 2012-10-11 | 2014-04-17 | Airbus Operations (Sas) | Protection method and device of an electrical network for aircraft |
| US20160048186A1 (en) * | 2014-08-14 | 2016-02-18 | Zodiac Aero Electric | Electrical distribution system for an aircraft |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117439022A (en) * | 2023-12-20 | 2024-01-23 | 天津航空机电有限公司 | Distribution board box protection structure and protection method |
| CN117439022B (en) * | 2023-12-20 | 2024-04-09 | 天津航空机电有限公司 | Distribution board box protection structure and protection method |
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| CN110635451B (en) | 2022-08-09 |
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