CN110556916A - Protection structure for preventing emergency power supply contactor of single-channel multi-electric-aircraft bus bar power controller from being disconnected due to faults - Google Patents
Protection structure for preventing emergency power supply contactor of single-channel multi-electric-aircraft bus bar power controller from being disconnected due to faults Download PDFInfo
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- CN110556916A CN110556916A CN201810550494.9A CN201810550494A CN110556916A CN 110556916 A CN110556916 A CN 110556916A CN 201810550494 A CN201810550494 A CN 201810550494A CN 110556916 A CN110556916 A CN 110556916A
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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
- H02J9/08—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 requiring starting of a prime-mover
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- Engineering & Computer Science (AREA)
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- Supply And Distribution Of Alternating Current (AREA)
- Electric Propulsion And Braking For Vehicles (AREA)
Abstract
The invention discloses a protection structure for an emergency power supply contactor of a single-channel multi-electric-aircraft bus bar power controller, which cannot be disconnected due to faults, wherein information acquisition points for the emergency power supply contactor E1 TRU Rly, which cannot be disconnected due to faults, are as follows: the E1 TRU Rly outputs a hold command, the E1 TRU Rly auxiliary contacts, and the ESS 235VAC Bus A-phase voltage to determine whether the E1 TRU Rly has not opened after receiving the open command. The action of this protection is to open and latch ESS ISO Rly within 2s and send an ESS TRU Rly protection trip request to the opposite side BPCU. The invention has the beneficial effect of matching with the realization of the protection and fault isolation functions of the BPCU.
Description
Technical Field
the invention relates to a protection structure for preventing an emergency power supply contactor of a single-channel multi-electric-aircraft bus bar power controller from being disconnected due to faults.
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. In the case of a multi-electric airplane, the BPCU has conventional control and protection functions, and also needs to be combined with the BPCU at the opposite side to realize fault location and isolation under the fault condition.
Disclosure of Invention
the invention provides a protection structure for preventing an emergency power supply contactor of a single-channel multi-electric-aircraft bus bar power controller from being disconnected due to faults, and the protection structure is matched with the realization of the protection and fault isolation functions of a BPCU. Including fault diagnosis and what actions should be taken in the event of a fault.
In order to achieve the purpose, the technical scheme of the invention is as follows: the protection structure for preventing the emergency power supply contactor of the single-channel multi-electric-aircraft bus bar power controller from being disconnected due to faults is characterized by comprising,
The main generator GEN L is connected with the first end of the circuit breaker L GCB, and the second end of the circuit breaker L GCB is connected with the Bus bar L235 VAC Bus;
the GEN R of the main generator is connected with the first end of the circuit breaker R GCB, and the second end of the circuit breaker R GCB is connected with the Bus bar R235 VAC Bus;
The auxiliary generator APU GEN is connected with the first end of the circuit breaker APB, the Bus bar L235 VAC Bus is connected with the first end of the contactor L BTB, the Bus bar R235 VAC Bus is connected with the first end of the contactor R BTB, and the second end of the contactor APB is connected with the second end of the contactor L BTB and the second end of the contactor R BTB respectively;
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 connected with an electric energy conversion device L ATU, the electric energy conversion device L ATU is connected with a first end of a contactor L BSB, and a second end of the contactor L BSB is connected with the Bus bar L115 VAC Bus;
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 connected with an electric energy conversion device R ATU, the electric energy conversion device R ATU is connected with a first end of a contactor R BSB, and a second end of the contactor R BSB is connected with the Bus bar R115 VAC Bus;
a ground power supply L FWD EP is connected with a first end of a contactor L EPC, and a second end of the contactor L EPC is connected with a first end of a contactor L BSB;
a ground power supply R FWD EP is connected with a first end of a contactor R EPC, and a second end of the contactor R EPC is connected with a first end of a contactor R BSB;
the Bus bar L235 VAC Bus is connected with the first end of the contactor LacT, the second end of the contactor LacT is connected with the first end of the contactor RacT, and the second end of the contactor RacT is connected with the Bus bar R235 VAC Bus;
the second end of the contactor L ATUC is connected with the first end of the contactor L TRU Rly, the second end of the contactor L TRU Rly is connected with the power conversion device TRU L, and the power conversion device TRU L is connected with the Bus bar L28 VDC Bus;
The second end of the contactor R ATUC is connected with the first end of the contactor R TRU Rly, the second end of the contactor R TRU Rly is connected with the power conversion device TRU R, and the power conversion device TRU R is connected with the Bus bar R28 VDC Bus;
The Bus bar L28 VDC Bus is connected with a first end of a contactor LdcT, a second end of the contactor LdcT is connected with a first end of a contactor RdcT, and a second end of the contactor RdcT is connected with the Bus bar R28 VDC Bus;
the second end of the contactor L ATUC is connected with the first end of the contactor E1 TRU ISO Rly, the second end of the contactor E1 TRU ISO Rly is respectively connected with the first ends of a power conversion device TRU 1 and a contactor E1 TRU Rly, the power conversion device TRU 1 is further connected with the first end of a Bus bar ESS 128 VDC Bus, the second end of the contactor ESS ISO Rly is connected with a Bus bar ESS 235VAC Bus, the Bus bar ESS 235VAC Bus is connected with a power conversion device TRU 2, and the power conversion device TRU E2 is further connected with the Bus bar ESS 228 VDC Bus;
the generator GEN RAT is connected with a first end of a contactor RCB, and a second end of the contactor RCB is connected with a Bus bar ESS 235VAC Bus;
bus ESS 128 VDC Bus is connected to the first terminal of contact E1T, the second terminal of contact E1T is connected to the first terminal of contact E2T, and the second terminal of contact E2T is connected to Bus ESS 228 VDC Bus;
Bus ESS 128 VDC Bus is connected to a first terminal of contactor MBR, and a second terminal of contactor MBR is connected to Bus Hot BB 1;
The bus bar Hot BB2 is connected with a first end of a contactor SPUC, a second end of the contactor SPUC is connected with an SPU, the SPU is connected with a first end of a contactor SPUB, and a second end of the contactor SPUB is connected with an ATRU R;
the Bus bar L235 VAC Bus is connected with a first end of a contactor L ATRUC, a second end of the contactor L ATRUC is connected with an autotransformer rectifier ATRU L, and the autotransformer rectifier ATRU L is connected with the Bus bar L270 VDC Bus;
the Bus bar R235 VAC Bus is connected with the first end of the contactor R ATRUC, the second end of the contactor R ATRUC is connected with the autotransformer rectifier ATRU R, and the autotransformer rectifier ATRU R is connected with the Bus bar R270 VDC Bus;
an external power supply L AFT EP is connected with a first end of a contactor L AEPC, and a second end of the contactor L AEPC is connected with an autotransformer rectifier ATRU L;
The information acquisition points of E1 TRU Rly which can not disconnect the protection due to failure are: the E1 TRU Rly outputs hold command, E1 TRU Rly auxiliary contacts, and ESS 235VAC Bus a phase voltage to determine if E1 TRU Rly has not opened after receiving the open command, the action of this protection is to open and latch ESS ISO Rly within 2s and send an essstru Rly protection trip request to the BPCU on the opposite side.
the power supply of the main generator GEN L and the power supply of the main generator GEN R are both variable frequency generators with rated power of 225kVA and rated voltage of 235 VAC; the auxiliary generator APU GEN is a variable frequency generator with rated power of 200kVA and rated voltage of 235 VAC; the generator GEN RAT is a variable frequency generator with rated power of 50kVA and rated voltage of 235 VAC; rated voltages of the ground power supply L FWDEP, the ground power supply R FWD EP and the third external power supply L AFT EP are 115 VAC; rated power of the ATRU L and the ATRU R is 150kVA, rated capacity of the ATU and the ATU is 60kVA, and rated output current of the TRU L, the TRU R, the TRU E1 and the TRU E2 is 240A; both the battery Main BAT and the battery APUBAT are batteries having a rated voltage of 28VDC and a capacity of 75 Ah.
Compared with the prior art, the invention has the beneficial effects that:
1. And the protection and fault isolation functions of the BPCU are realized in a matching manner.
2. Introducing a 235VAC bus bar to replace the 115VAC bus bar of a conventional aircraft, the power rating increases.
3. a 270VDC voltage level was introduced for speed regulation of large motors (air conditioning compressors, etc.).
4. The number of external power supply sockets is changed from 1 socket of a traditional airplane to 2, and meanwhile, the voltage class and the capacity of the emergency power supply RAT are increased from the original 115VAC 30kVA to 235VAC 50 kVA.
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 schematic structural diagram according to an embodiment of the present invention.
fig. 2 is a schematic diagram of protection control logic according to an embodiment of the invention.
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.
the embodiment relates to a novel protection structure for preventing an emergency power supply contactor of a single-channel multi-electric-aircraft bus bar power controller from being disconnected due to faults. The system comprises a left variable-frequency main starting generator GEN L and a right variable-frequency main starting generator GEN R with the rated power of 225kVA, an APU starting generator with the rated power of 200kVA, and an RAT generator with the rated power of 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. 1, the main generator GEN L is connected to a first terminal of the circuit breaker L GCB, and a second terminal of the circuit breaker L GCB is connected to the Bus bar L235 VAC Bus.
The main generator GEN R is connected with the first end of the circuit breaker R GCB, and the second end of the circuit breaker R GCB is connected with the Bus bar R235 VAC Bus.
Auxiliary generator APU GEN links to each other with circuit breaker APB's first end, and busbar L235 VAC Bus links to each other with contactor L BTB's first end, and busbar R235 VAC Bus links to each other with contactor R BTB's first end, and contactor APB's second end links to each other with contactor L BTB's second end and contactor R BTB's second end respectively.
busbar L235 VAC Bus links to each other with contactor L ATUC's first end, and contactor L ATUC's second end links to each other with electric energy conversion device L ATU, and electric energy conversion device L ATU links to each other with contactor L BSB's first end again, and contactor L BSB's second end links to each other with busbar L115 VAC Bus.
busbar R235 VAC Bus links to each other with contactor R ATUC's first end, and contactor R ATUC's second end links to each other with electric energy conversion device R ATU, and electric energy conversion device R ATU links to each other with contactor R BSB's first end again, and contactor R BSB's second end links to each other with busbar R115 VAC Bus.
Ground power source L FWD EP is connected to a first terminal of contact L EPC, and a second terminal of contact L EPC is connected to a first terminal of contact L BSB.
A ground power source R FWD EP is connected to a first terminal of the contact R EPC, and a second terminal of the contact R EPC is connected to a first terminal of the contact R BSB.
bus bar L235 VAC Bus is connected with the first end of contactor LacT, and the second end of contactor LacT is connected with the first end of contactor RacT, and the second end of contactor RacT is connected with Bus bar R235 VAC Bus.
the second end of contactor L ATUC is connected to the first end of contactor L TRU Rly, and the second end of contactor L TRU Rly is connected to power conversion device TRU L, and power conversion device TRU L is connected to busbar L28 VDC Bus again.
the second end of contactor R ATUC links to each other with the first end of contactor R TRU Rly, and the second end of contactor R TRU Rly links to each other with power conversion device TRU R, and power conversion device TRU R links to each other with busbar R28 VDC Bus again.
bus bar L28 VDC Bus is connected to a first terminal of contact LdcT, a second terminal of contact LdcT is connected to a first terminal of contact RdcT, and a second terminal of contact RdcT is connected to Bus bar R28 VDC Bus.
the second end of the contactor L ATUC is connected to the first end of the contactor E1 TRU ISO Rly, the second end of the contactor E1 TRU ISO Rly is connected to the first ends of the power conversion device TRU E1 and the contactor E1 TRU Rly, respectively, the power conversion device TRU E1 is connected to the first end of the Bus bar ESS 128 VDC Bus, the second end of the contactor ESS ISO Rly is connected to the Bus bar ESS 235VAC Bus, the Bus bar ESS 235VAC Bus is connected to the power conversion device TRU 2, and the power conversion device TRU E2 is connected to the Bus bar ESS 228 VDC Bus.
The generator GEN RAT is connected to a first terminal of a contactor RCB, a second terminal of which is connected to a Bus bar ESS 235VAC Bus.
The Bus ESS 128 VDC Bus is connected to the first terminal of the contact E1T, the second terminal of the contact E1T is connected to the first terminal of the contact E2T, and the second terminal of the contact E2T is connected to the Bus ESS 228 VDC Bus.
Bus ESS 128 VDC Bus is connected to a first terminal of contactor MBR, and a second terminal of contactor MBR is connected to Bus Hot BB 1.
Busbar Hot BB2 links to each other with contactor SPUC's first end, and contactor SPUC's second end links to each other with the SPU, and the SPU links to each other with contactor SPUB's first end, and contactor SPUB's second end links to each other with self-coupling transformer rectifier ATRU R.
The Bus bar L235 VAC Bus is connected with the first end of the contactor L ATRUC, the second end of the contactor L ATRUC is connected with the autotransformer rectifier ATRU L, and the autotransformer rectifier ATRU L is connected with the Bus bar L270 VDC Bus.
The Bus bar R235 VAC Bus is connected with the first end of the contactor R ATRUC, the second end of the contactor R ATRUC is connected with the autotransformer rectifier ATRU R, and the autotransformer rectifier ATRU R is connected with the Bus bar R270 VDC Bus.
An external power source L AFT EP is connected with a first end of a contactor L AEPC, and a second end of the contactor L AEPC is connected with an autotransformer rectifier ATRU L.
The information acquisition points of E1 TRU Rly which can not disconnect the protection due to failure are: the E1 TRU Rly outputs a hold command, the E1 TRU Rly auxiliary contacts, and the ESS 235VAC Bus A-phase voltage to determine whether the E1 TRU Rly has not opened after receiving the open command.
The action of this protection is to open and latch ESS ISO Rly within 2s and send "ESS TRU Rly protection trip request" to the opposite side BPCU. The operating conditions of the protection are:
1) the output hold command of E1 TRU Rly is false; and the number of the first and second electrodes,
2) The E1 TRU Rly auxiliary contact status indicates that it is closed, or ESS 235VAC Bus has voltage on phase a prior to power transfer.
the opposite side BPCU responds to the request by opening and locking out ESS ISO Rly.
The R BPCU gives control of E1 TRU Rly and ESS ISO Rly to the L BPCU.
The protection control logic is shown in fig. 2.
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 (2)
1. The protection structure for preventing the emergency power supply contactor of the single-channel multi-electric-aircraft bus bar power controller from being disconnected due to faults is characterized by comprising,
The main generator GEN L is connected with the first end of the circuit breaker L GCB, and the second end of the circuit breaker L GCB is connected with the Bus bar L235 VAC Bus;
the GEN R of the main generator is connected with the first end of the circuit breaker R GCB, and the second end of the circuit breaker R GCB is connected with the Bus bar R235 VAC Bus;
The auxiliary generator APU GEN is connected with the first end of the circuit breaker APB, the Bus bar L235 VAC Bus is connected with the first end of the contactor L BTB, the Bus bar R235 VAC Bus is connected with the first end of the contactor R BTB, and the second end of the contactor APB is connected with the second end of the contactor L BTB and the second end of the contactor R BTB respectively;
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 connected with an electric energy conversion device L ATU, the electric energy conversion device L ATU is connected with a first end of a contactor L BSB, and a second end of the contactor L BSB is connected with the Bus bar L115 VAC Bus;
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 connected with an electric energy conversion device R ATU, the electric energy conversion device R ATU is connected with a first end of a contactor R BSB, and a second end of the contactor R BSB is connected with the Bus bar R115 VAC Bus;
a ground power supply L FWD EP is connected with a first end of a contactor L EPC, and a second end of the contactor L EPC is connected with a first end of a contactor L BSB;
A ground power supply R FWD EP is connected with a first end of a contactor R EPC, and a second end of the contactor R EPC is connected with a first end of a contactor R BSB;
The Bus bar L235 VAC Bus is connected with the first end of the contactor LacT, the second end of the contactor LacT is connected with the first end of the contactor RacT, and the second end of the contactor RacT is connected with the Bus bar R235 VAC Bus;
the second end of the contactor L ATUC is connected with the first end of the contactor L TRU Rly, the second end of the contactor L TRU Rly is connected with the power conversion device TRU L, and the power conversion device TRU L is connected with the Bus bar L28 VDC Bus;
The second end of the contactor R ATUC is connected with the first end of the contactor R TRU Rly, the second end of the contactor R TRU Rly is connected with the power conversion device TRU R, and the power conversion device TRU R is connected with the Bus bar R28 VDC Bus;
The Bus bar L28 VDC Bus is connected with a first end of a contactor LdcT, a second end of the contactor LdcT is connected with a first end of a contactor RdcT, and a second end of the contactor RdcT is connected with the Bus bar R28 VDC Bus;
The second end of the contactor L ATUC is connected with the first end of the contactor E1 TRU ISO Rly, the second end of the contactor E1 TRU ISO Rly is respectively connected with the first ends of a power conversion device TRU 1 and a contactor E1 TRU Rly, the power conversion device TRU 1 is further connected with the first end of a Bus bar ESS 128 VDC Bus, the second end of the contactor ESS ISO Rly is connected with a Bus bar ESS 235VAC Bus, the Bus bar ESS 235VAC Bus is connected with a power conversion device TRU 2, and the power conversion device TRU E2 is further connected with the Bus bar ESS 228 VDC Bus;
the generator GEN RAT is connected with a first end of a contactor RCB, and a second end of the contactor RCB is connected with a Bus bar ESS 235VAC Bus;
Bus ESS 128 VDC Bus is connected to the first terminal of contact E1T, the second terminal of contact E1T is connected to the first terminal of contact E2T, and the second terminal of contact E2T is connected to Bus ESS 228 VDC Bus;
bus ESS 128 VDC Bus is connected to a first terminal of contactor MBR, and a second terminal of contactor MBR is connected to Bus Hot BB 1;
The bus bar Hot BB2 is connected with a first end of a contactor SPUC, a second end of the contactor SPUC is connected with an SPU, the SPU is connected with a first end of a contactor SPUB, and a second end of the contactor SPUB is connected with an ATRU R;
The Bus bar L235 VAC Bus is connected with a first end of a contactor L ATRUC, a second end of the contactor L ATRUC is connected with an autotransformer rectifier ATRU L, and the autotransformer rectifier ATRU L is connected with the Bus bar L270 VDC Bus;
The Bus bar R235 VAC Bus is connected with the first end of the contactor R ATRUC, the second end of the contactor R ATRUC is connected with the autotransformer rectifier ATRU R, and the autotransformer rectifier ATRU R is connected with the Bus bar R270 VDC Bus;
an external power supply L AFT EP is connected with a first end of a contactor L AEPC, and a second end of the contactor L AEPC is connected with an autotransformer rectifier ATRU L;
The information acquisition points of E1 TRU Rly which can not disconnect the protection due to failure are: the E1 TRU Rly outputs hold command, E1 TRU Rly auxiliary contacts, and ESS 235VAC Bus a phase voltage to determine if E1 TRU Rly has not opened after receiving the open command, the action of this protection is to open and latch ESS ISO Rly within 2s and send an essstru Rly protection trip request to the BPCU on the opposite side.
2. the protection structure for the emergency power supply contactor of the single-channel multi-electric-aircraft bus bar power controller, which cannot be disconnected due to faults, of the single-channel multi-electric-aircraft bus bar power controller is characterized in that the power supply of the main generator GEN L and the power supply of the main generator GEN R are variable-frequency generators with the rated power of 225kVA and the rated voltage of 235 VAC; the auxiliary generator APU GEN is a variable frequency generator with rated power of 200kVA and rated voltage of 235 VAC; the generator GEN RAT is a variable frequency generator with rated power of 50kVA and rated voltage of 235 VAC; rated voltages of the ground power supply L FWD EP, the ground power supply R FWD EP and the third external power supply L AFT EP are 115 VAC; rated power of the ATRU L and the ATRU R is 150kVA, rated capacity of the ATU and the ATU is 60kVA, and rated output current of the TRU L, the TRU R, the TRU E1 and the TRU E2 is 240A; the storage battery Main BAT and the storage battery APU BAT are both storage batteries with rated voltage of 28VDC and capacity of 75 Ah.
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| CN201810550494.9A CN110556916B (en) | 2018-05-31 | 2018-05-31 | Protection structure for emergency power supply contactor incapable of being disconnected due to faults |
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| CN201810550494.9A CN110556916B (en) | 2018-05-31 | 2018-05-31 | Protection structure for emergency power supply contactor incapable of being disconnected due to faults |
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| CN110556916B (en) | 2023-08-25 |
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