CN117895638A - Aircraft power system architecture and power line communication network architecture - Google Patents
Aircraft power system architecture and power line communication network architecture Download PDFInfo
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Abstract
The invention provides an aircraft power system architecture and a power line communication network architecture, which comprise a direct current 28V bus bar, an electric load management center, a remote power distribution unit, a DC/DC converter, a storage battery charger, a bus bar power controller and a generator controller, wherein the power controller is connected with the power distribution unit; and constructing a PLC communication network by using a 28V power supply network, and sending a control instruction and collecting data information by the bus bar power controller through a 28V power supply network architecture. The aircraft power system utilizes a 28V power supply network, and the aircraft power supply and distribution system control and data collection and reporting are realized by using the power line communication device as backup communication.
Description
Technical Field
The invention belongs to the field of aircraft power system design, and particularly relates to an aircraft power system architecture and a power line communication network architecture.
Background
The aircraft power system refers to a general term of an aircraft power supply system and electric equipment, and consists of three subsystems of power supply, power distribution and power utilization. Load fault Prediction and Health Management (PHM) technology aims at maintaining and guaranteeing the safety, reliability and economic performance of aircraft electromechanical products and systems thereof, and is widely applied in the field of aircraft equipment at present. In order to realize load fault prediction and health management, load information needs to be collected, communication equipment and cables of a load and electric load management center are added, and the power line communication technology is adopted, so that not only can load dynamic information be collected, but also communication cables can be reduced, and the weight of an airplane is reduced. Meanwhile, the power line communication technology is adopted as a standby bus of the aircraft power supply and distribution system, so that the reliability of the aircraft power supply and distribution system is improved
Disclosure of Invention
Based on this, it is necessary to provide an aircraft power system architecture and a power line communication network architecture for the above technical problems, where the aircraft power system uses a 28V power supply network, and uses the power line communication device as backup communication to implement control and data collection and reporting of the aircraft power supply and distribution system.
The embodiment of the invention provides a power line communication network architecture of an aircraft power system, which comprises a first direct current 28V bus bar 9, a second direct current 28V bus bar 10, a first electric load management center 6, a second electric load management center 12, a first remote power distribution unit 7, a second remote power distribution unit 11, a third remote power distribution unit 23, a fourth remote power distribution unit 24, a fifth remote power distribution unit 25, a DC/DC converter 8, a high-voltage storage battery charger 21, a low-voltage storage battery charger 2, a bus bar power controller 14 and a generator controller 15; the first electrical load management center 6, the second electrical load management center 12, the first remote power distribution unit 7, the second remote power distribution unit 11, the third remote power distribution unit 23, the fourth remote power distribution unit 24, the fifth remote power distribution unit 25, the DC/DC converter 8, the high-voltage battery charger 21, the low-voltage battery charger 2, the bus bar power controller 14, and the generator controller 15 construct a PLC communication network using a 28V power supply network, and the bus bar power controller 14 transmits control instructions to the first electrical load management center 6, the second electrical load management center 12, the first remote power distribution unit 7, the second remote power distribution unit 11, the third remote power distribution unit 23, the fourth remote power distribution unit 24, the fifth remote power distribution unit 25, the DC/DC converter 8, the high-voltage battery charger 21, the low-voltage battery charger 2, and the generator controller 15 through the 28V power supply network architecture and collects data information.
Further, the first electric load management center 6, the second electric load management center 12, the first remote power distribution unit 7, the second remote power distribution unit 11, the third remote power distribution unit 23, the fourth remote power distribution unit 24, the fifth remote power distribution unit 25, the DC/DC converter 8, the high-voltage battery charger 21, the low-voltage battery charger 2, the bus bar power controller 14, and the generator controller 15 are supplied with power with redundancy 28V.
Furthermore, the first electrical load management center 6 and the second electrical load management center 12 both realize SSPC control and status monitoring through a CAN bus, and the bus bar power controller realizes electrical load tube control and load status monitoring through bus communication by taking TTP, 429 or 422 as a main communication mode; the electric load management center communicates with the bus bar power controller through a 28V power supply network as an auxiliary communication mode, receives a control instruction of the bus bar power controller and reports load state information; the bus bar power controller and the electric load management center realize intelligent power distribution of the aircraft power system.
Further, the first electrical load management center 6 and the second electrical load management center 12 have the same architecture, and include a first PLC module 61, a second PLC module 62, a third PLC module 66, a fourth PLC module 67, a power panel 63, a plurality of SSPC boards 65, and a control panel 64, wherein the third PLC module 66 is used for acquiring 28V load data through a 28V power line, and the fourth PLC module 67 is used for acquiring high voltage load data through a high voltage power line; the control board 64 analyzes the received information of the third PLC module 66 and the fourth PLC module 67, and the analyzed information feeds back the information and data of the electrical load management center and the information and data of the load to the bus bar power controller 14 through the first PLC module 61 and the second PLC module 62; the electrical load management center receives the bus bar power controller 14 control commands using the 28V power supply line through the first PLC module 61 and the second PLC module 62.
Further, the first electrical load management center 6 and the second electrical load management center 12 both adopt a time division multiplexing principle to receive load information.
Further, the first remote power distribution unit 7, the second remote power distribution unit 11, the third remote power distribution unit 23, the fourth remote power distribution unit 24 and the fifth remote power distribution unit 25 all adopt a TTP mode, a 429 mode or a 422 mode as a main communication mode, the bus bar power controller realizes high-power electric load tube control through bus communication, and the first remote power distribution unit 7, the second remote power distribution unit 11, the third remote power distribution unit 23, the fourth remote power distribution unit 24 and the fifth remote power distribution unit 25 feed back load state information to the bus bar power controller through main communication; the first remote power distribution unit 7, the second remote power distribution unit 11, the third remote power distribution unit 23, the fourth remote power distribution unit 24 and the fifth remote power distribution unit 25 all communicate with the bus bar power controller through a 28V power supply network as an auxiliary communication mode, receive a control command of the bus bar power controller and report load state information.
Further, the first remote power distribution unit 7, the second remote power distribution unit 11, the third remote power distribution unit 23, the fourth remote power distribution unit 24, the fifth remote power distribution unit 25, the DC/DC converter 8, the high-voltage battery charger 21, the low-voltage battery charger 2, the bus bar power controller 14, and the generator controller 15 all comprise at least a fifth PLC module 71, a sixth PLC module 72, a power panel 3, and a control panel 4; the bus bar power controller 14 control command is received by the fifth PLC module 71 and the sixth PLC module 72 using the 28V power supply line, and information and data of the electrical load management center, and information and data of the load are fed back thereto.
Furthermore, the low-voltage battery charger 2 and the high-voltage battery charger 21 adopt TTP, 429 or 422 modes as main communication modes, the bus bar power controller realizes battery charge and discharge control of the low-voltage battery charger 2 and the high-voltage battery charger 21 by bus communication, and parameter information, fault information and maintenance information of the battery pack are fed back to the bus bar power controller by the main communication; the low-voltage storage battery charger 2 and the high-voltage storage battery charger 21 are communicated with the bus bar power controller through a 28V power supply network as an auxiliary communication mode, receive control instructions of the bus bar power controller and report parameter information of the battery pack.
In a second aspect, the present invention provides an aircraft power system architecture, including the power line communication network architecture according to the first aspect, further including a first power generation system 1, a second power generation system 26, a first high voltage dc bus 3, a second high voltage dc bus 4, a third high voltage dc bus 5, a high voltage battery 22, and a low voltage battery 13; the generator controller 15 controls the first and second power generation systems 1 and 26 to supply power to the first and third high-voltage DC bus bars 3 and 5 through the contactors, the bus bar power controller 14 controls the first and second contactors 18 and 19 to supply power to the first and third high-voltage DC bus bars 3 and 5 and the second high-voltage DC bus bar 4, the DC/DC converter 8 converts the high-voltage DC power to 28V, the bus bar power controller 14 controls the DC/DC converter 8 to supply power to the fourth DC 28V bus bar 9, the bus bar power controller 14 controls the third contactor 20 to supply power to the fifth DC 28V bus bar 10, the high-voltage battery 22 supplies power to the second high-voltage DC bus bar 4 through the high-voltage battery charger 21, and the low-voltage battery 13 supplies power to the fifth DC 28V bus bar 10 through the low-voltage battery charger 2.
The technical scheme of the invention provides an aircraft power system architecture and a power line communication network architecture, wherein the aircraft power system utilizes a 28V power supply network, and the aircraft power supply and distribution system control and data collection and reporting are realized by using a power line communication device as backup communication, and the aircraft power system power line communication network design is based on power electricity and 28V control electricity, so that the aircraft power system architecture is suitable for various typical aircraft power systems.
Drawings
FIG. 1 is a diagram of an aircraft electrical system architecture provided in an embodiment of the present invention;
fig. 2 is a power line communication network architecture diagram of an aircraft power system according to an embodiment of the present invention;
fig. 3 is an electrical load management center architecture diagram.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application more apparent, the present application will be further described in detail with reference to the accompanying drawings and examples. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the present application.
The embodiment of the invention provides an aircraft power system architecture, which comprises a power generation system 1/26, a generator controller 15, a direct current 270V bus bar 3/4/5, an electric load management center 6/12, a remote power distribution unit 7/11/23/24/25, a DC/DC converter 8, a direct current 28V bus bar 9/10, a high-voltage storage battery 22, a high-voltage storage battery charger 21, a low-voltage storage battery 2 and a low-voltage storage battery charger 13, as shown in fig. 1.
The generator controller controls 1/26 to enable the generator 16/17 to supply power to the direct-current 270V bus bar 3/5 through the contactor, the bus bar power controller 14 controls the contactor 18/19 to control the direct-current 270V bus bar 3/5 to supply power to the direct-current 270V bus bar 4, the DC/DC converter 8 converts the direct-current 270V into 28V, the bus bar power controller 14 controls the DC/DC converter 8 to supply power to the direct-current 28V bus bar 9, the bus bar power controller 14 controls the contactor 20 to supply power to the direct-current 28V bus bar 10, the storage battery 22 supplies power to the direct-current 270V bus bar 4 through the storage battery controller 21, and the storage battery 13 supplies power to the direct-current 28V bus bar 10 through the storage battery controller 2.
An embodiment of the present invention provides an aircraft power system power line communication network architecture, as shown in fig. 2, including: the direct current 28V bus 9/10, the electric load management center 6/12, the remote power distribution unit 7/11/23/24/25, the DC/DC converter 8, the high-voltage storage battery charger 21, the low-voltage storage battery charger 13, the bus power controller 14 and the generator controller 15.
The electrical load management center 6/12, the remote power distribution unit 7/11/23/24/25, the DC/DC converter 8, the high-voltage battery charger 21, the low-voltage battery charger 13, the bus bar power controller 14 and the generator controller 15 construct a PLC communication network by using a 28V power supply network, and the bus bar power controller 14 transmits control instructions to the electrical load management center 6/12, the remote power distribution unit 7/11/23/24/25, the DC/DC converter 8, the high-voltage battery charger 21, the low-voltage battery charger 13 and the generator controller 15 through the 28V power supply network and collects data information.
The electric load management center 6/12, the remote power distribution unit 7/11/23/24/25, the DC/DC converter 8, the high-voltage battery charger 21, the low-voltage battery charger 13, the bus bar power controller 14 and the generator controller 15 are powered by 28V redundancy, so that the power line communication network is also redundancy communication.
An electrical load management center 6/12 architecture according to an embodiment of the present invention, as shown in fig. 3, includes: a PLC module 1, a PLC module 2, a PLC module 6, a PLC module 7, a power panel 3, an SSPC board 5 and a control panel 4. The PLC module 6 collects 28V load data through a 28V power line, and the PLC module 7 collects 270V load data through a 270V power line.
The electrical load management center receives control instructions of the bus bar power controller 14 through the PLC module 1 and the PLC module 2 by using 28V power supply lines, and feeds back the electrical load management center, load information and data to the electrical load management center. The electric load management center 6/12 has a large load quantity, a large amount of information superposition can interfere the 28V and 270V power quality, and the time-sharing multiplexing principle is adopted to accept load information, so that the interference is reduced.
The embodiment of the invention provides a remote power distribution unit 7/11/23/24/25, a DC/DC converter 8, a high-voltage battery charger 21, a low-voltage battery charger 13, a bus bar power controller 14, a generator controller 15 architecture, comprising: a PLC module 1, a PLC module 2, a power panel 3 and a control panel 4. Control instructions of the bus bar power controller 14 are received by the PLC module 1 and the PLC module 2 through 28V power supply lines, and the electric load management center, the load information and the data are fed back to the control instructions.
In one embodiment, as shown in fig. 1-3, an architecture of a power distribution control test platform for a multi-aircraft is provided, comprising:
the power generation system 1/26, the generator controller 15, the direct current 270V bus bar 3/4/5, the electric load management center 6/12, the remote power distribution unit 7/11/23/24/25, the DC/DC converter 8, the direct current 28V bus bar 9/10, the high-voltage storage battery 22, the high-voltage storage battery charger 21, the low-voltage storage battery 2 and the low-voltage storage battery charger 13.
The bus bar power controller 14 is a management component in the power distribution system, and is used as a core control component of the automatic power distribution system, and is required to receive a system state signal from the integrated avionics system, receive the structural layout of the power generation system and the power distribution system from the remote terminal, receive a load power supply request equation from the load management center, and send corresponding control commands to the load management center and the remote terminal after solving the load equation, and record the change of the system layout to the memory database, so that the normal operation of the system is realized; on the other hand, the terminal is used as a terminal on the upper comprehensive avionics system bus and is responsible for transmitting state data and fault information of the automatic power distribution system to the upper system in real time.
The bus bar power controller, the generator controller, the contactor and the like together realize the protection and control of the system so as to ensure the safe operation of the aircraft electrical system. Another main function of the bus bar power controller is to implement protection control of the system and automatic control of the load. The bus bar power controller collects voltage and current of bus bars in the multi-electric aircraft electrical system, monitors the running state of the aircraft electrical system in real time, and when overload or generator failure occurs, the detection device sends information to the management center to judge whether load shedding or fault isolation is needed. When the generator fails and cannot be recovered, the total power generation capacity of the aircraft is reduced, the power supply requirements of all equipment on the aircraft cannot be met, and the bus bar power controller can be unloaded according to the importance of the electric equipment, such as turning off kitchen loads and the like, so that the power supply of key loads is ensured. The bus bar power controller is communicated with the generator controller through a data bus to realize the reconstruction of an aircraft power system and receives motor state information.
The bus bar power controller is communicated with the generator controller in a main communication mode through TTP, 429, 422 and the like, and the bus bar power controller is communicated with the generator controller in a PLC auxiliary communication mode through a 28V power supply network.
The power generation system 1/26 is used for providing 270V power for an aircraft power system, and the generator controller 15 is used for coordinating and controlling the working conditions of a generator and a converter, so that the functions of controlling, protecting, self-checking, communicating and the like of the whole system are realized. The generator controller receives the bus power controller command to control the on/off of the contactor 18/19, thereby controlling the direct current 270V bus 3/5 to supply power to the direct current 270V bus 4.
The electric load management center is an important component of the advanced aircraft power distribution system and controls the distributed bus bar conversion and Solid State Power Controller (SSPC) according to the layout command and the load power supply request of the bus bar power controller and the current condition of the on-board load, so that the power supply of the on-board electric load is ensured and the power supply utilization rate is improved.
The electric load management center 6/12 mainly comprises a power distribution PLC module 1, a PLC module 2, a PLC module 6, a PLC module 7, a power panel 3, a plurality of SSPC boards 5 and a control panel 4. The electric load management center realizes SSPC control and state monitoring through the CAN bus, takes TTP, 429, 422 and the like as a main communication mode, and the bus bar power controller realizes electric load tube control and load state monitoring through bus communication. The electric load management center communicates with the bus bar power controller through the 28V power supply network as an auxiliary communication mode, receives a control instruction of the bus bar power controller and reports load state information. The bus bar power controller and the electric load management center realize intelligent power distribution of the aircraft power system.
The electrical load management center 6/12 collects 28V load data through a 28V power line by using the PLC module 6, and collects 270V load data through a 270V power line by using the PLC module 7. The control board 4 analyzes and receives the information of the PLC modules 6 and 7, and the analyzed information feeds back the electrical load management center, load information and data to the bus bar power controller 14 through the PLC modules 1 and 2. The electrical load management center receives control commands from the bus bar power controller 14 through the PLC module 1 and the PLC module 2 using 28V power supply lines.
The electrical load management center receives control instructions of the bus bar power controller 14 through the PLC module 1 and the PLC module 2 by using 28V power supply lines, and feeds back the electrical load management center, load information and data to the electrical load management center. The electric load management center 6/12 has a large load quantity, a large amount of information superposition can interfere the 28V and 270V power quality, and the time-sharing multiplexing principle is adopted to accept load information, so that the interference is reduced.
The remote power distribution management unit comprises a 270V remote power distribution unit and a 28V remote power distribution unit, and comprises a power panel 4, a control panel 3, a PLC module 1 and a PLC module 2, wherein the remote power distribution management unit adopts TTP, 429, 422 and other modes as main communication modes, the bus bar power controller realizes high-power electric load tube control through bus communication, and the remote power distribution management unit feeds back load state information to the bus bar power controller through main communication. The remote power distribution management unit is used for communicating with the bus bar power controller in an auxiliary communication mode through a 28V power supply network, receiving a control instruction of the bus bar power controller and reporting load state information.
The remote power distribution management unit receives control instructions of the bus bar power controller 14 through the PLC module 1 and the PLC module 2 by utilizing 28V power supply lines, and feeds back the electric load management center, load information and data to the bus bar power controller.
The DC/DC converter 8 converts 270V power electricity into 28V power electricity, the DC/DC converter adopts TTP, 429, 422 and other modes as a main communication mode, the bus bar power controller realizes the control of the DC/DC converter through bus communication, and the DC/DC converter feeds back load state information to the bus bar power controller through the main communication. The DC/DC converter is used for communicating with the bus bar power controller in an auxiliary communication mode through a 28V power supply network, receiving a control instruction of the bus bar power controller and reporting state information.
The main uses of the aviation storage battery are as follows: when the main power supply of the aircraft cannot work normally or fails, the aviation storage battery is used as an auxiliary power supply or an emergency power supply for supplying power to important electric equipment on the aircraft, or is used as a starting power supply of an engine of the aircraft, or is used as a power supply for checking the small-power electric equipment on the aircraft before flying under special conditions (such as the field without power supply).
The function of the storage battery controller is to send the parameter state, the working state, the device state, the maintenance state and the like of the battery pack to the aircraft host through the agreed bus communication protocol, and the aircraft host analyzes the received data frame according to the corresponding protocol format of the storage battery controller and displays the data frame on a screen, wherein the information comprises the parameter information, the fault information, the maintenance information and the like of the battery pack. By analyzing the information, the aircraft host transmits corresponding maintenance, control and other commands to the storage battery controller so as to perform corresponding maintenance and control, and the use safety of the aviation battery pack is ensured.
The storage battery controller comprises a 270V storage battery controller and a 28V storage battery controller, and comprises a power panel 4, a control panel 3, a PLC module 1 and a PLC module 2, wherein the storage battery controller adopts TTP, 429, 422 and the like as main communication modes, and the bus bar power controller realizes the storage battery charge and discharge control of the storage battery controller by bus communication, and feeds back parameter information, fault information, maintenance information and the like of a battery pack to the bus bar power controller by using the main communication. The storage battery controller is communicated with the bus bar power controller through a 28V power supply network as an auxiliary communication mode, receives a control instruction of the bus bar power controller and reports parameter information of the battery pack.
The battery controller receives the control command of the bus bar power controller 14 through the PLC module 1 and the PLC module 2 by using the 28V power supply line, and feeds back parameter information, fault information, maintenance information, and the like of the battery pack thereto.
The technical scheme of the invention provides an aircraft power system architecture and a power line communication network architecture, wherein the aircraft power system utilizes a 28V power supply network, and the aircraft power supply and distribution system control and data collection and reporting are realized by using a power line communication device as backup communication, and the aircraft power system power line communication network design is based on power electricity and 28V control electricity, so that the aircraft power system architecture is suitable for various typical aircraft power systems.
Claims (9)
1. The power line communication network architecture of the aircraft power system is characterized by comprising a first direct current 28V bus bar (9), a second direct current 28V bus bar (10), a first electric load management center (6), a second electric load management center (12), a first remote power distribution unit (7), a second remote power distribution unit (11), a third remote power distribution unit (23), a fourth remote power distribution unit (24), a fifth remote power distribution unit (25), a DC/DC converter (8), a high-voltage battery charger (21), a low-voltage battery charger (2), a bus bar power controller (14) and a generator controller (15); the system comprises a first electric load management center (6), a second electric load management center (12), a first remote power distribution unit (7), a second remote power distribution unit (11), a third remote power distribution unit (23), a fourth remote power distribution unit (24), a fifth remote power distribution unit (25), a DC/DC converter (8), a high-voltage storage battery charger (21), a low-voltage storage battery charger (2), a bus bar power controller (14) and a generator controller (15), wherein a PLC communication network is constructed by using a 28V power supply network, the bus bar power controller (14) sends control instructions to the first electric load management center (6), the second electric load management center (12), the first remote power distribution unit (7), the second remote power distribution unit (11), the third remote power distribution unit (23), the fourth remote power distribution unit (24), the fifth remote power distribution unit (25), the DC/DC converter (8), the high-voltage storage battery charger (21), the low-voltage storage battery charger (2) and the generator controller (15) through the 28V power supply network architecture, and data information is collected.
2. An aircraft power system power line communication network architecture according to claim 1, characterized in that the first electrical load management center (6), the second electrical load management center (12), the first remote power distribution unit (7), the second remote power distribution unit (11), the third remote power distribution unit (23), the fourth remote power distribution unit (24), the fifth remote power distribution unit (25), the DC/DC converter (8), the high voltage battery charger (21), the low voltage battery charger (2), the bus bar power controller (14), the generator controller (15) are powered with a redundancy of 28V.
3. The aircraft power system power line communication network architecture of claim 1,
the first electric load management center (6) and the second electric load management center (12) realize SSPC control and state monitoring through a CAN bus, and the bus bar power controller realizes electric load tube control and load state monitoring through bus communication by taking TTP, 429 or 422 modes as a main communication mode; the electric load management center communicates with the bus bar power controller through a 28V power supply network as an auxiliary communication mode, receives a control instruction of the bus bar power controller and reports load state information;
the bus bar power controller and the electric load management center realize intelligent power distribution of the aircraft power system.
4. A power line communication network architecture of an aircraft power system according to claim 3, wherein the first electrical load management center (6) and the second electrical load management center (12) have the same architecture, and include a first PLC module (61), a second PLC module (62), a third PLC module (66), a fourth PLC module (67), a power panel (63), a plurality of SSPC boards (65), and a control panel (64), and the third PLC module (66) is used to collect 28V load data through a 28V power line, and the fourth PLC module (67) is used to collect high voltage load data through a high voltage power line; the control board (64) analyzes the received information of the third PLC module (66) and the fourth PLC module (67), and the analyzed information feeds back the information and data of the electric load management center and the information and data of the load to the bus bar power controller (14) through the first PLC module (61) and the second PLC module (62); the electrical load management center receives control instructions of the bus bar power controller (14) through the first PLC module (61) and the second PLC module (62) by utilizing 28V power supply lines.
5. An aircraft power system power line communication network architecture according to claim 3, wherein the first electrical load management center (6) and the second electrical load management center (12) each receive load information using a time division multiplexing principle.
6. The aircraft power system power line communication network architecture according to claim 1, wherein the first remote power distribution unit (7), the second remote power distribution unit (11), the third remote power distribution unit (23), the fourth remote power distribution unit (24) and the fifth remote power distribution unit (25) all adopt TTP, 429 or 422 as main communication modes, the bus bar power controller realizes high-power electric load tube control through bus communication, and the first remote power distribution unit (7), the second remote power distribution unit (11), the third remote power distribution unit (23), the fourth remote power distribution unit (24) and the fifth remote power distribution unit (25) all feed back load state information to the bus bar power controller by using the main communication; the first remote power distribution unit (7), the second remote power distribution unit (11), the third remote power distribution unit (23), the fourth remote power distribution unit (24) and the fifth remote power distribution unit (25) are communicated with the bus bar power controller through a 28V power supply network as an auxiliary communication mode, receive a control command of the bus bar power controller and report load state information.
7. The aircraft power system power line communication network architecture according to claim 6, wherein the architectures of the first remote power distribution unit (7), the second remote power distribution unit (11), the third remote power distribution unit (23), the fourth remote power distribution unit (24), the fifth remote power distribution unit (25), the DC/DC converter (8), the high-voltage battery charger (21), the low-voltage battery charger (2), the bus bar power controller (14) and the generator controller (15) all comprise at least a fifth PLC module (71), a sixth PLC module (72), a power panel (3) and a control panel (4); the control command of the bus bar power controller (14) is received by the fifth PLC module (71) and the sixth PLC module (72) through the 28V power supply line, and information and data of the electric load management center and information and data of the load are fed back to the bus bar power controller.
8. The aircraft power system power line communication network architecture according to claim 1, wherein the low-voltage battery charger (2) and the high-voltage battery charger (21) both adopt a TTP mode, a 429 mode or a 422 mode as a main communication mode, and the bus bar power controller realizes battery charging and discharging control of the low-voltage battery charger (2) and the high-voltage battery charger (21) by bus communication, and the parameter information, fault information and maintenance information of the battery pack are fed back to the bus bar power controller by using the main communication; the low-voltage storage battery charger (2) and the high-voltage storage battery charger (21) are communicated with the bus bar power controller through a 28V power supply network as an auxiliary communication mode, receive control instructions of the bus bar power controller and report parameter information of the battery pack.
9. An aircraft power system architecture, characterized by comprising a power line communication network architecture according to any one of claims 1-8, further comprising a first power generation system (1), a second power generation system (26), a first high voltage direct current bus bar (3), a second high voltage direct current bus bar (4), a third high voltage direct current bus bar (5), a high voltage battery (22), a low voltage battery (13); the generator controller (15) controls the first generator system (1) and the second generator system (26) to enable the first generator (16) and the second generator (17) to supply power to the first high-voltage direct-current bus bar (3) and the third high-voltage direct-current bus bar (5) through contactors, the bus bar power controller (14) controls the first contactor (18) and the second contactor (19), controls the first high-voltage direct-current bus bar (3) and the third high-voltage direct-current bus bar (5) to supply power to the second high-voltage direct-current bus bar (4), the DC/DC converter (8) converts high-voltage direct current into 28V, the bus bar power controller (14) controls the DC/DC converter (8) to supply power to the fourth direct-current 28V bus bar (9), the bus bar power controller (14) controls the third contactor (20) to supply power to the fifth direct-current 28V bus bar (10), the high-voltage storage battery (22) supplies power to the second high-voltage direct-current bus bar (4) through the high-voltage storage battery charger (21), and the low-voltage storage battery (13) supplies power to the fifth direct-current (28V) through the low-voltage storage battery charger (28).
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| CN202311524459.7A CN117895638A (en) | 2023-11-15 | 2023-11-15 | Aircraft power system architecture and power line communication network architecture |
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| CN202311524459.7A CN117895638A (en) | 2023-11-15 | 2023-11-15 | Aircraft power system architecture and power line communication network architecture |
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| CN202311524459.7A Pending CN117895638A (en) | 2023-11-15 | 2023-11-15 | Aircraft power system architecture and power line communication network architecture |
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| Country | Link |
|---|---|
| CN (1) | CN117895638A (en) |
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2023
- 2023-11-15 CN CN202311524459.7A patent/CN117895638A/en active Pending
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