Intelligent distributed power supply and distribution system for aircraft

Abstract

The invention relates to the technical field of power supply and distribution systems, in particular to an intelligent distributed power supply and distribution system for an aircraft, which comprises a generator control unit, a secondary power supply, a power supply system processor, a primary electric energy distribution center, a pulse power supply unit, a secondary power distribution unit, a standby power supply, a battery management unit, an inverter power supply, a cable network and a switch control unit, according to the system, the reliability of the system is improved through redundancy design and power supply priority management, fault isolation and uninterrupted power supply are realized through intelligent solid-state power distribution, and the sensing capability of the power supply and distribution system to the real-time working condition of a load is improved through high-speed sampling; real-time performance and reliability of data interaction between equipment of the power supply and distribution system are achieved through a dual-redundancy high-speed data bus, multi-level redundancy power supply is achieved, reliability and safety of the system are greatly improved, an electrical system is designed into a plurality of small modules with special functions, the advanced microelectronic technology and the computer control technology are utilized, and the system reliability and safety are improved. And intelligent management and control of an electrical system are realized.

Description

Technical Field

[0001] The present invention relates to the technical field of power supply and distribution systems, and in particular to an intelligent distributed power supply and distribution system for aircraft. Background Art

[0002] With the development of technologies such as microelectronics, materials, and computer control, multi-electrification, full electrification, and even electrification have become the main development trends of the secondary energy system of the new generation of aircraft. A multi-electric aircraft refers to an aircraft in which most of the secondary energy such as air pressure energy, hydraulic energy, and mechanical energy in the aircraft is replaced by electrical energy; a full-electric aircraft is an aircraft in which all the secondary energy in the aircraft is unified into electrical energy; and an electrified aircraft is an aircraft in which both the primary energy and the secondary energy of the aircraft are replaced by electrical energy. Due to the advantages of electrical energy in terms of conversion efficiency, control robustness, and reliability, aircraft use electrical energy as the basic energy source, and through the transmission, conversion, and control of electrical energy, it is converted into various forms of energy required by the aircraft and acts on various systems, which can achieve a comprehensive improvement in the overall performance of the aircraft.

[0003] However, compared with traditional airborne equipment that uses mechanical or hydraulic energy, although electric drive equipment has higher advantages in performance, life and reliability, if faults such as overcurrent or short circuit occur, it is more likely to affect the safe operation of other equipment. There is even a risk that the fault will expand to the entire power supply and distribution system, resulting in catastrophic consequences such as system power outages.

[0004] Therefore, how to improve the reliability and safety of the power supply and distribution system and achieve uninterrupted and reliable power supply is an important issue restricting the development of multi-electric, all-electric and electric aircraft. Summary of the invention

[0005] The purpose of the present invention is to provide an intelligent distributed power supply and distribution system for aircraft, aiming to improve the reliability and safety of the power supply and distribution system and achieve uninterrupted and reliable power supply, which is a constraint on the development of multi-electric, all-electric and electric aircraft.

[0006] To achieve the above-mentioned object, the present invention provides an intelligent distributed power supply and distribution system for aircraft, comprising a generator control unit, a secondary power supply, a power supply system processor, a primary power distribution center, a pulse power supply unit, a secondary power distribution unit, a backup power supply, a battery management unit, an inverter power supply, a cable network and a switch control unit;

[0007] The generator control unit is used to control the generator to drive the engine to work;

[0008] The secondary power supply is used to monitor the quality of the power output from the generator and convert the variable frequency and variable voltage power generated by the generator into a DC power supply;

[0009] The power supply system processor communicates with the host computer based on the data bus to complete the power supply and distribution control logic receiving and data reporting functions of the intelligent distributed power supply and distribution system, and communicates with the generator control unit, the secondary power supply, the primary power distribution center, the pulse power supply unit, the secondary power distribution unit, the backup power supply, the battery management unit and the inverter power supply through the dual-redundancy bus to send starting control instructions, power-on logic instructions, grid connection instructions, power supply and distribution control instructions, charge and discharge control instructions, emergency control instructions and the function of connecting data of each device, and can receive discrete quantity signals from the switch control unit to complete the power distribution control in the maintenance mode or manual control mode;

[0010] The primary power distribution center receives power-on and power-off instructions from the power supply system processor based on the data bus, completes the power-on logic control of each AC and DC bus bar according to the established logic or receives the discrete quantity signal from the switch control unit, and monitors the working condition of each bus bar through the sensor;

[0011] The pulse power supply unit performs pulse discharge based on a predetermined logic or receiving instructions from the power supply system processor;

[0012] The secondary power distribution unit is used for the power supply system processor to instruct or control the corresponding solid power controller module to distribute power output according to a predetermined logic;

[0013] The backup power supply stores or releases electric energy based on the control of the battery management unit;

[0014] The battery management unit completes battery charging and discharging based on a predetermined logic or receiving instructions from the power supply system processor;

[0015] The inverter power supply is used to invert the DC power supply into AC power supply;

[0016] The cable network is used to define the input and output interfaces of various devices in the system for electrical connection;

[0017] The switch control unit is used to generate discrete quantity signals, send power-on and power-off analog signals in maintenance mode or manual control mode, and control the power supply system processor and the primary power distribution center to complete system power supply and distribution management.

[0018] Wherein, the secondary power distribution unit has overcurrent protection, short circuit protection, overvoltage and undervoltage protection functions.

[0019] The power supply system processor includes a main control subunit, a switch input subunit, a switch output subunit, an analog detection subunit, a temperature detection subunit, an RS422 bus subunit, a CAN bus subunit, a data storage subunit, a power conversion subunit, a connector and a housing;

[0020] The main control subunit is used to control the operation of the remaining subunits;

[0021] The switch input subunit is used to convert the action signal of the button switch into a level signal;

[0022] The switch output subunit is used to convert the control instruction or state threshold in the system into a level signal;

[0023] The analog detection subunit is used to condition the input level or current signal and then output it;

[0024] The temperature detection subunit is used for temperature monitoring of the system;

[0025] The RS422 bus subunit is used to communicate with the host computer, receive host computer instructions or upload system data;

[0026] The CAN bus subunit is used for the main control subunit to forward the host computer control instructions and also receives the data of the devices in the system through the established logic;

[0027] The data storage subunit is used to store status data in the system;

[0028] The power conversion subunit is used to convert the input power into the working voltage required by the main control subunit and other subunits;

[0029] The connector is used to connect the input and output electrical signals of the device to the cable network;

[0030] The housing is used to protect the internal circuits and components of the device and module.

[0031] Wherein, the main control subunit includes a DSP processor, a ferroelectric memory and peripheral circuits.

[0032] Among them, the primary power distribution center has status monitoring and fault diagnosis capabilities and automatic fault isolation capabilities.

[0033] The present invention provides an intelligent distributed power supply and distribution system for aircraft, wherein the generator control unit controls the starter generator to drive the engine to work; the secondary power supply is used to monitor the quality of the power output of the starter generator, and convert the variable frequency and voltage power generated by the starter generator into a DC power supply; the power supply system processor communicates with the host computer through a data bus to complete the power supply and distribution control logic receiving and data reporting functions of the intelligent distributed power supply and distribution system, and communicates with the generator control unit, the secondary power supply, the primary power distribution center, the pulse power supply unit, the secondary power distribution unit, the backup power supply, the battery management unit and the inverter power supply through a dual redundancy bus to send starting control instructions, power-on logic instructions, grid connection instructions, power supply and distribution control instructions, charge and discharge control instructions, emergency control instructions and the function of connecting data of each device, and can receive discrete quantity signals from the switch control unit to complete the power distribution control in the maintenance mode or the manual control mode; the primary power distribution center receives the power supply system processor based on the data bus The power-on and power-off instructions of the processor are received according to the established logic or the discrete quantity signal of the switch control unit to complete the power-on logic control of each AC and DC bus bar, and the working condition of each bus bar is monitored by the sensor; the pulse power supply unit completes the pulse discharge work based on the established logic or receives the instruction of the power supply system processor; the secondary power distribution unit is used to control the corresponding solid power controller module to distribute power output according to the instruction of the power supply system processor or according to the established logic; the backup power supply controls the storage or release of electric energy based on the battery management unit, and the battery management unit completes the battery charging and discharging work based on the established logic or receiving the instruction of the power supply system processor; the inverter power supply is used to invert the DC power supply into the AC power supply; the cable network is used for the electrical connection of the input and output interfaces of each device in the system, and the switch control unit is used to generate discrete quantity signals, send the power-on and power-off analog signals in the maintenance mode or manual control mode, and control the power supply system processor and the primary power distribution center to complete the system power supply and distribution management;

[0034] The system can complete the functions of power generation, conversion, transmission, distribution and transient energy management, mainly including ground self-test, ground start and air flight working modes. The specific working logic is as follows:

[0035] In the ground self-check working mode, the ground power supply is connected to the system through the primary power distribution center (PPDC), the flight control computer enters the ground self-check mode, the power supply system processor (PSP), the generator control unit (GCU), the secondary power supply (ARTU), the primary power distribution center (PPDC), the secondary power distribution unit (SPDU), the battery management unit (BMU) and the inverter power supply (IPU) perform self-check, and after the self-check is completed, the self-check information is reported to the power supply system processor, which is processed by the power supply system processor and reported to the flight control computer, completing the ground self-check work;

[0036] In the ground start working mode, after the aircraft passes the self-test, the ground power supply is connected to the primary power distribution center (PPDC), and the primary power distribution center receives the instruction of the power supply system processor to control the ground power supply to connect to the secondary power supply. After detecting that the power quality meets the requirements, the power supply system processor controls the generator control unit to control the starter generator to drive the engine to work; when the engine speed reaches the predetermined speed, the secondary power supply monitors the power quality of the starter generator output, and after meeting the grid-connecting conditions, the power supply system processor controls the secondary power supply and the primary power distribution center to complete the grid-connecting control, and the ground power supply stops supplying power, completing the ground start work;

[0037] In the aerial flight working mode, the system works according to the established logic; the secondary power supply converts the variable frequency and voltage power generated by the generator into a DC power supply; the primary power distribution center completes the power-on logic and power-on priority management; the secondary power distribution unit receives the control instruction of the power supply system processor to connect or shut down the load, and when the load has an overcurrent or short circuit fault, the fault is isolated to achieve uninterrupted power supply; the battery management unit completes the battery charging and discharging work according to the established logic or receives the instruction of the power supply system processor; when there is a pulse power load in the system, the pulse power supply unit (PPU) completes the pulse discharge work according to the established logic or receives the instruction of the power supply system processor to avoid large fluctuations in the system bus voltage when the pulse load is working; the inverter power supply (IPU) inverts the DC power supply into an AC power supply (115V, 400Hz), and the secondary power distribution unit completes the connection and shutdown of the AC load according to the established logic or receives the instruction of the power supply system processor, and isolates the fault when the load has an overcurrent or short circuit fault. In the flight working mode, when a fault that affects flight safety occurs, the system enters the emergency working mode, and the primary power distribution center shuts down the output of some buses (such as the main bus) according to the established logic or the instruction received from the power supply system processor PSP to ensure flight safety;

[0038] The system improves the power supply and distribution system's ability to perceive the real-time working conditions of the load through high-speed sampling, realizes the real-time and reliability of data interaction between the power supply and distribution system equipment through a dual-redundancy high-speed data bus, and provides graded redundant power supply, which greatly improves the system reliability and safety. The electrical system is designed into multiple miniaturized, function-specific modules, and uses advanced microelectronics technology and computer control technology to achieve intelligent management and control of the electrical system. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0040] Figure 1 It is a connection diagram of an intelligent distributed power supply and distribution system for an aircraft provided by the present invention.

[0041] Figure 2 It is a schematic diagram of a power supply system processor provided by the present invention.

[0042] Figure 3 It is a schematic diagram of a primary power distribution center main control subunit provided by the present invention.

[0043] Figure 4 It is a schematic diagram of a primary power distribution center bus switching subunit provided by the present invention.

[0044] Figure 5 It is a schematic diagram of a secondary power distribution unit provided by the present invention.

[0045] Figure 6 It is a schematic diagram of a main control subunit of a secondary power distribution unit provided by the present invention.

[0046] Figure 7 It is a schematic diagram of a power distribution subunit of a secondary power distribution unit provided by the present invention.

[0047] Figure 8 It is a schematic diagram of a switch control unit provided by the present invention.

[0048] Fig. 9 It is a schematic diagram of a power supply system processor provided by the present invention.

[0049] In the figure: 1-generator control unit, 2-secondary power supply, 3-power supply system processor, 4-primary power distribution center, 5-pulse power supply unit, 6-secondary power distribution unit, 7-backup power supply, 8-battery management unit, 9-inverter power supply, 10-cable network, 11-switch control unit, 12-main control subunit, 13-switch input subunit, 14-switch output subunit, 15-analog detection subunit, 16-temperature detection subunit, 17-RS422 bus subunit, 18-CAN bus subunit, 19-data storage subunit, 20-power conversion subunit, 21-connector, 22-housing. DETAILED DESCRIPTION

[0050] Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, and should not be construed as limiting the present invention.

[0051] See also Figures 1 to 9 The present invention provides an intelligent distributed power supply and distribution system for aircraft, including a generator control unit 1, a secondary power supply 2, a power supply system processor 3, a primary power distribution center 4, a pulse power supply unit 5, a secondary power distribution unit 6, a backup power supply 7, a battery management unit 8, an inverter power supply 9, a cable network 10 and a switch control unit 11;

[0052] The generator control unit 1 is used to control the generator and drive the engine to work;

[0053] The secondary power supply 2 is used to monitor the quality of the power output from the generator and convert the variable frequency and variable voltage power generated by the generator into a DC power supply;

[0054] The power supply system processor 3 communicates with the host computer based on the data bus to complete the power supply and distribution control logic receiving and data reporting functions of the intelligent distributed power supply and distribution system, and communicates with the generator control unit 1, the secondary power supply 2, the primary power distribution center 4, the pulse power supply unit 5, the secondary power distribution unit 6, the backup power supply 7, the battery management unit 8 and the inverter power supply 9 through the dual redundancy bus to send starting control instructions, power-on logic instructions, grid connection instructions, power supply and distribution control instructions, charge and discharge control instructions, emergency control instructions and the function of connecting data of each device, and can receive discrete quantity signals from the switch control unit to complete the power distribution control in the maintenance mode or manual control mode;

[0055] The primary power distribution center 4 receives the power-on and power-off instructions of the power supply system processor 3 based on the data bus, completes the power-on logic control of each AC and DC bus bar according to the established logic or receives the discrete quantity signal of the switch control unit 11, and monitors the working condition of each bus bar through the sensor;

[0056] The pulse power supply unit 5 performs pulse discharge work based on a predetermined logic or receiving instructions from the power supply system processor 3;

[0057] The secondary power distribution unit 6 is used for the power supply system processor 3 to instruct or control the corresponding solid power controller module to distribute power according to a predetermined logic;

[0058] The backup power supply 7 controls the storage or release of electric energy based on the battery management unit 8;

[0059] The battery management unit 8 completes battery charging and discharging based on a predetermined logic or receiving instructions from the power supply system processor 3;

[0060] The inverter power supply 9 is used to invert the DC power supply into an AC power supply;

[0061] The cable network 10 is used to define the input and output interfaces of various devices in the system for electrical connection;

[0062] The switch control unit 11 is used to generate discrete quantity signals, send power-on and power-off analog signals in maintenance mode or manual control mode, and control the power supply system processor 3 and the primary power distribution center 4 to complete system power supply and distribution management.

[0063] In this embodiment, the generator control unit 1 controls the starting generator to drive the engine to work; the secondary power supply 2 is used to monitor the quality of the starting generator output power supply, and convert the variable frequency and voltage power supply generated by the starting generator into a DC power supply; the power supply system processor 3 communicates with the host computer based on the data bus to complete the power supply and distribution control logic receiving and data reporting functions of the intelligent distributed power supply and distribution system, and communicates with the generator control unit 1, the secondary power supply 2, the primary power distribution center 4, the pulse power supply unit 5, the secondary power distribution unit 6, the backup power supply 7, the battery management unit 8 and the inverter power supply 9 through a dual redundancy bus to send starting control instructions, power-on logic instructions, grid connection instructions, power supply and distribution control instructions, charging and discharging control instructions, emergency control instructions and the function of connecting data of each device, and can receive discrete quantity signals from the switch control unit to complete the power distribution control in maintenance mode or manual control mode; the primary power distribution center 4 receives the power on and off instructions of the power supply system processor 3 based on the data bus, The power-on logic control of each AC / DC busbar is completed according to the established logic or by receiving the discrete quantity signal of the switch control unit 11, and the working condition of each busbar is monitored by the sensor; the pulse power supply unit 5 completes the pulse discharge work based on the established logic or receiving the instruction of the power supply system processor 3; the secondary power distribution unit 6 is used to control the corresponding solid power controller module to distribute power output according to the instruction of the power supply system processor 3 or according to the established logic; the backup power supply 7 controls the storage or release of electric energy based on the battery management unit 8, and the battery management unit 8 completes the battery charging and discharging work based on the established logic or receiving the instruction of the power supply system processor 3; the inverter power supply 9 is used to invert the DC power supply into the AC power supply; the cable network 10 is used to make electrical connections for the input and output interface definitions of each device in the system, and the switch control unit 11 is used to generate discrete quantity signals, send up and down power analog signals in the maintenance mode or manual control mode, and control the power supply system processor 3 and the primary power distribution center 4 to complete the system power supply and distribution management;

[0064] The system can complete the functions of power generation, conversion, transmission, distribution and transient energy management, mainly including ground self-test, ground start and air flight working modes. The specific working logic is as follows:

[0065] In the ground self-check working mode, the ground power supply is connected to the system through the primary power distribution center 4 (PPDC), the flight control computer enters the ground self-check mode, the power supply system processor 3 (PSP), the generator control unit 1 (GCU), the secondary power supply 2 (ARTU), the primary power distribution center 4 (PPDC), the secondary power distribution unit 6 (SPDU), the battery management unit 8 (BMU) and the inverter power supply 9 (IPU) perform self-check, and after the self-check is completed, the self-check information is reported to the power supply system processor 3, and the power supply system processor 3 processes it and reports it to the flight control computer, completing the ground self-check work;

[0066] In the ground start working mode, after the aircraft passes the self-test, the ground power supply is connected to the primary power distribution center 4 (PPDC), and the primary power distribution center 4 receives the instruction of the power supply system processor 3 to control the ground power supply to connect to the secondary power supply 2. After detecting that the power quality meets the requirements, the power supply system processor 3 controls the generator control unit 1 to control the starter generator to drive the engine to work; when the engine speed reaches the predetermined speed, the secondary power supply 2 monitors the power quality of the starter generator output, and after meeting the grid-connecting conditions, the power supply system processor 3 controls the secondary power supply 2 and the primary power distribution center 4 to complete the grid-connecting control, and the ground power supply stops supplying power, completing the ground start work;

[0067] In the aerial flight working mode, the system works according to the established logic; the secondary power supply 2 converts the variable frequency and voltage power generated by the generator into a DC power supply; the primary power distribution center 4 completes the power-on logic and power-on priority management; the secondary power distribution unit 6 receives the control instruction of the power supply system processor 3 to connect or shut down the load, and when the load has a fault such as overcurrent or short circuit, the fault is isolated to achieve uninterrupted power supply; the battery management unit 8 completes the battery charging and discharging work according to the established logic or receives the instruction of the power supply system processor 3; when there is a pulse power load in the system, the pulse power supply unit 5 (PPU) completes the pulse discharge work according to the established logic or receives the instruction of the power supply system processor 3 to avoid large fluctuations in the system bus voltage when the pulse load is working; the inverter power supply 9 (IPU) inverts the DC power supply into an AC power supply (115V, 400Hz), and the secondary power distribution unit 6 completes the connection and shutdown of the AC load according to the established logic or receives the instruction of the power supply system processor 3, and isolates the fault when the load has a fault such as overcurrent or short circuit. In the flight working mode, when a fault that affects flight safety occurs, the system enters the emergency working mode, and the primary power distribution center 4 shuts down the output of some buses (such as the main bus) according to the established logic or the instruction received from the power supply system processor 3PSP to ensure flight safety;

[0068] The system improves the power supply and distribution system's ability to perceive the real-time working conditions of the load through high-speed sampling, realizes the real-time and reliability of data interaction between the power supply and distribution system equipment through a dual-redundancy high-speed data bus, and provides graded redundant power supply, which greatly improves the system reliability and safety. The electrical system is designed into multiple miniaturized, function-specific modules, and uses advanced microelectronics technology and computer control technology to achieve intelligent management and control of the electrical system.

[0069] Further, the power supply system processor 3 includes a main control subunit 12, a switch input subunit 13, a switch output subunit 14, an analog detection subunit 15, a temperature detection subunit 16, an RS422 bus subunit 17, a CAN bus subunit 18, a data storage subunit 19, a power conversion subunit 20, a connector 21 and a housing 22;

[0070] The main control subunit 12 is used to control the operation of the remaining subunits;

[0071] The switch input subunit 13 is used to convert the action signal of the button switch into a level signal;

[0072] The switch output subunit 14 is used to convert the control instruction or state threshold in the system into a level signal;

[0073] The analog detection subunit 15 is used to condition the input level or current signal and then output it;

[0074] The temperature detection subunit 16 is used for temperature monitoring of the system;

[0075] The RS422 bus subunit 17 is used to communicate with the host computer, receive host computer instructions or upload system data;

[0076] The CAN bus subunit 18 is used for the main control subunit 12 to forward the host computer control instructions and also receives the data of the devices in the system through the established logic;

[0077] The data storage subunit 19 is used to store status data in the system;

[0078] The power conversion subunit 20 is used to convert the input power into the working voltage required by the main control subunit 12 and other subunits;

[0079] The connector 21 is used to connect the input and output electrical signals of the device to the cable network;

[0080] The housing 22 is used to protect the internal circuits and components of the device and module.

[0081] In this embodiment, the main control subunit 12 is the control core of the power supply system processor 3, and communicates with the host computer by controlling the RS422 bus subunit 17, receives host computer instructions or uploads system data; at the same time, the main control subunit 12 communicates with the primary power distribution center 4, the secondary power distribution unit 6 and other equipment through the CAN bus subunit 18, forwards host computer control instructions, and also receives data from equipment in the system through established logic. The switch input subunit 13 mainly converts action signals such as button switches into level signals, so that the main control subunit 12 can judge the state of the switch by judging its level characteristics. The switch output subunit 14 is mainly composed of an optocoupler or a solid-state switch circuit. The main control subunit 12 can control the output characteristics of the switch output subunit 14 through the IO port. The analog detection subunit 15 is mainly composed of a conditioning circuit, etc., which conditions the input level or current signal and outputs it to the AD port of the main control subunit 12. The temperature detection subunit 16 is mainly composed of a temperature sensor and peripheral circuits to complete system temperature monitoring. The data storage subunit 19 mainly stores status data in the system. The power conversion subunit 20 converts the input power into the working voltage required by the main control subunit 12 and other subunits.

[0082] Furthermore, as a core product that affects flight safety, the primary power distribution center 4 (PPDC) should take adequate measures to ensure product safety and mission reliability, including but not limited to the following aspects:

[0083] 1. From the perspective of system architecture, the power supply and distribution adopt a dual-redundancy design, and adopt corresponding redundancy design to eliminate single-point failure links as much as possible; if single-point links are unavoidable, conduct a full failure mode and impact analysis on them, and take measures to reduce risks as much as possible;

[0084] 2. For redundancy selection control (including secondary redundancy selection), the master-slave (hot backup) mode is adopted, and the channel selection is determined based on its own status. The host computer (PSP) can select the working channel through pure hardware;

[0085] 3. The main control parameters of the main and standby channels are transmitted to each other and compared for consistency according to certain rules (pay attention to eliminating the influence of data errors, time sequence, etc.). When inconsistency occurs, an alarm is issued to the upper computer;

[0086] 4. Have relatively complete status monitoring and fault diagnosis capabilities;

[0087] 5. It has a certain automatic fault isolation capability, and can also complete fault isolation through external control of the host computer;

[0088] 6. Clear fault: used to clear fault flags. The main channel and backup channel are controlled by host computer commands respectively.

[0089] Furthermore, the secondary power distribution unit 6 (SPDU) has overcurrent, short circuit protection, overvoltage and undervoltage protection functions, and can automatically shut down or protect the corresponding power distribution output when any load fails.

[0090] SPDU is based on the Solid State Power Controller (SSPC), which transmits the electric energy from the primary power distribution center 4 to the power load after protection and control by the SSPC. SPDU is interconnected with PSP through the CAN bus subunit 18, and controls the SSPC to be turned on and off according to the initial configuration and the flight control instructions forwarded by the PSP, thereby controlling the power on and off of the load. SSPC has the functions of load current monitoring, overcurrent protection and short circuit protection.

[0091] SPDU has the following features:

[0092] 1. The power distribution output has over-current and short-circuit protection functions;

[0093] 2. Users can configure power supply protection parameters, initial status and other configuration parameters, tentatively implemented by loading configuration files;

[0094] 3. Set the hardware address code. When the power is turned on and initialized, the product identity is identified according to the hardware address code. Based on this, the configuration parameters of this product are selected in the configuration file. After the selection is completed, no changes are allowed during this power-on process;

[0095] 4. After completing the address code recognition and configuration parameter selection, report its own status to the upper computer. Only after receiving the confirmation reply from the upper computer can it start the power distribution output according to the configuration parameters;

[0096] 5. During the working process, the power distribution output state is changed according to the power-on / power-off instructions of the host computer corresponding to each independent channel;

[0097] 6. Measures should be taken to reduce the state changes caused by bit errors, such as increasing the code distance, multiple shot continuous judgment, etc.

[0098] 7. When bus communication is abnormal, the power distribution output status remains in the latest valid state;

[0099] 8. SPDU collects all product parameters as comprehensively as possible, especially those related to control logic and working status monitoring;

[0100] IX. SPDU communicates with PSP through two independent CAN buses, receives control instructions and loads parameters, and feeds back various parameters of this product; SPDU takes adequate measures to ensure the safety and mission reliability of the product, including but not limited to the following aspects:

[0101] a: Adopt redundancy design to eliminate single point failure links as much as possible;

[0102] b: For redundancy selection control, the main standby (hot standby) mode is adopted in principle. The channel selection is determined based on its own status, and the upper computer can force the selection of the working channel;

[0103] c: Have relatively complete status monitoring and fault diagnosis capabilities;

[0104] d: It has a certain automatic fault isolation capability, and can also complete fault isolation through external control of the host computer;

[0105] e: It has the function of clearing faults, which is used to clear fault flags. It is controlled by the host computer command and forwarded by PSP.

[0106] 10. It has self-detection function, including power-on self-detection and periodic self-detection, and can upload the detection results;

[0107] 11. It has maintenance and testing functions, and sets software and hardware protection for maintenance mode to prevent accidental entry into the mode;

[0108] 12. Have the ability to load and upgrade software, and upload the software version to the host computer through digital communication.

[0109] 13. It should have strong logical robustness to prevent logic errors caused by transient interference, accidental bit errors, etc. Measures include but are not limited to software and hardware filtering, multi-beat continuous effectiveness, etc.

[0110] SSPC can monitor the output voltage and current of the corresponding circuit, and provide overvoltage, overcurrent and other protections, upload sampling information and fault information to the main control module, and upload the operating status information of each electrical device to the host computer through the CAN bus subunit 18.

[0111] The internal switch of SSPC is implemented by solid-state power switch device MOSFET. When SSPC receives the bus connection instruction, the microprocessor controls the output of the drive circuit, outputs the voltage to the G pole of MOSFET, MOSFET is saturated and turned on, that is, the switch is closed, and SSPC has output; when SSPC receives the bus shutdown instruction, MOSFET is disconnected, and SSPC has no output. During the operation of SSPC, the voltage, current, and temperature are sampled in real time through the sampling circuit. When the voltage, current, and temperature exceed the set overvoltage, overcurrent, and overtemperature protection values, the drive circuit is controlled to shut down the output, so that the MOSFET is turned off, thereby protecting SSPC.

[0112] The main control subunit 12 performs comprehensive processing on the data and status information of each power distribution module of the power distribution box, reports the processed data according to the protocol, obtains the host computer instructions from the data bus, and sends the control instructions to the power distribution module after processing. The main control subunit 12 is mainly composed of a DSP processor, a ferroelectric memory and its peripheral circuits.

[0113] The switch control unit 11 serves as a human-machine interaction interface and is configured with n manual control switches and n status indicator lights.

[0114] What is disclosed above is only a preferred embodiment of an intelligent distributed power supply and distribution system for aircraft of the present invention. Of course, it cannot be used to limit the scope of rights of the present invention. Ordinary technicians in this field can understand that all or part of the processes of the above embodiments and equivalent changes made according to the claims of the present invention are still within the scope of the invention.

Claims

1. An intelligent distributed power supply and distribution system for aircraft, characterized in that: It includes generator control unit, secondary power supply, power supply system processor, primary power distribution center, pulse power supply unit, secondary power distribution unit, backup power supply, battery management unit, inverter power supply, cable network and switch control unit; The generator control unit is used to control the generator to drive the engine to work; The secondary power supply is used to monitor the quality of the power output from the generator and convert the variable frequency and variable voltage power generated by the generator into a DC power supply; The power supply system processor communicates with the host computer based on the data bus to complete the power supply and distribution control logic receiving and data reporting functions of the intelligent distributed power supply and distribution system, and communicates with the generator control unit, the secondary power supply, the primary power distribution center, the pulse power supply unit, the secondary power distribution unit, the backup power supply, the battery management unit and the inverter power supply through the dual-redundancy bus to send starting control instructions, power-on logic instructions, grid connection instructions, power supply and distribution control instructions, charge and discharge control instructions, emergency control instructions and the function of connecting data of each device, and can receive discrete quantity signals from the switch control unit to complete the power distribution control in the maintenance mode or manual control mode; The primary power distribution center receives power-on and power-off instructions from the power supply system processor based on the data bus, completes the power-on logic control of each AC and DC bus bar according to the established logic or receives the discrete quantity signal from the switch control unit, and monitors the working condition of each bus bar through the sensor; The pulse power supply unit performs pulse discharge based on a predetermined logic or receiving instructions from the power supply system processor; The secondary power distribution unit is used for the power supply system processor to instruct or control the corresponding solid power controller module to distribute power output according to a predetermined logic; The backup power supply stores or releases electric energy based on the control of the battery management unit; The battery management unit completes battery charging and discharging based on a predetermined logic or receiving instructions from the power supply system processor; The inverter power supply is used to invert the DC power supply into AC power supply; The cable network is used for electrical connection of input and output interfaces of various devices in the system; The switch control unit is used to generate discrete quantity signals, send power-on and power-off analog signals in maintenance mode or manual control mode, and control the power supply system processor and the primary power distribution center to complete system power supply and distribution management.

2. An intelligent distributed power supply and distribution system for aircraft according to claim 1, characterized in that: The secondary power distribution unit has overcurrent protection, short circuit protection, overvoltage protection and undervoltage protection functions.

3. The intelligent distributed power supply and distribution system for aircraft according to claim 1, characterized in that: The power supply system processor includes a main control subunit, a switch input subunit, a switch output subunit, an analog detection subunit, a temperature detection subunit, an RS422 bus subunit, a CAN bus subunit, a data storage subunit, a power conversion subunit, a connector and a housing; The main control subunit is used to control the operation of the remaining subunits; The switch input subunit is used to convert the action signal of the button switch into a level signal; The switch output subunit is used to convert the control instruction or state threshold in the system into a level signal; The analog detection subunit is used to condition the input level or current signal and then output it; The temperature detection subunit is used for temperature monitoring of the system; The RS422 bus subunit is used to communicate with the host computer, receive host computer instructions or upload system data; The CAN bus subunit is used for the main control subunit to forward the host computer control instructions and also receives the data of the devices in the system through the established logic; The data storage subunit is used to store status data in the system; The power conversion subunit is used to convert the input power into the working voltage required by the main control subunit and other subunits; The connector is used to connect the input and output electrical signals of the device to the cable network; The housing is used to protect the internal circuits and components of the device and module.

4. An intelligent distributed power supply and distribution system for aircraft as claimed in claim 3, characterized in that: The main control subunit includes a DSP processor, a ferroelectric memory and a peripheral circuit.

5. The intelligent distributed power supply and distribution system for aircraft according to claim 1, characterized in that: The primary power distribution center has status monitoring and fault diagnosis capabilities and automatic fault isolation capabilities.

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