A power battery management system for an aircraft

Abstract

The application discloses a power battery management system for an airplane, and technical scheme points of the application are as follows: the power battery management system comprises a BCMU master control unit, a wireless transmission module, a BMU acquisition module, a Switch physical switch, a PDU control box, an audible and visual alarm system, an external controller and a relay control module; the BCMU master control unit is used for acquiring acquisition data and performing self-checking when being powered on; the external controller performs self-checking when the BCMU master control unit completes self-checking; power-on is completed through the closure of the Switch physical switch, and the PDU control box controls the closure of an internal high-voltage relay; and a power-off signal is generated and power-off is controlled when the flight control module detects that flight is completed and a fault occurs. Safety control during power-on and power-off is realized.

Description

Technical Field

[0001] This invention relates to the field of flight control management system technology, and more specifically to a power battery management system for aircraft. Background Technology

[0002] With the development of aviation technology, the requirements for the energy use of aircraft are becoming increasingly stringent. Under the reform of new energy sources, aircraft are increasingly using battery energy for power supply. As a result, various new energy aircraft for operation have been developed and utilized. The combined use of hydrogen fuel cells and lithium batteries has become the most important energy output method for future aircraft.

[0003] While using batteries to power aircraft is more environmentally friendly, the unique operating environment of aircraft makes battery management much more challenging than conventional battery management. In particular, strict control is required when powering the system on and off to ensure the safe and normal operation of the aircraft and to prevent safety accidents caused by malfunctions due to accidental power-on or power-off. Therefore, a management system for power batteries used in aircraft is urgently needed to achieve safe control of power-on and power-off of the aircraft. Summary of the Invention

[0004] In view of the shortcomings of the existing technology, the purpose of this invention is to provide a power battery management system for aircraft, which has the effect of safely controlling the power-on and power-off of the aircraft.

[0005] To achieve the above objectives, the present invention provides the following technical solution:

[0006] An aircraft power battery management system includes a BCMU main control unit, a wireless transmission module, a BMU acquisition module, a switch physical switch, a PDU control box, an audible and visual alarm system, an external controller, and a relay control module.

[0007] The BMU acquisition module is used to collect the status of the battery cell and battery module and generate the acquisition data. The BMU acquisition module reports the acquisition data to the BCMU main control unit via wireless transmission. The Switch physical switch remains in a self-locking state when not powered on.

[0008] When the system is powered on, the BCMU main control unit is woken up. The BCMU main control unit is configured with a self-test strategy. The BCMU main control unit performs a self-test according to the self-test strategy and generates a main control self-test signal when the self-test is completed. When the external controller receives the main control self-test signal, it performs a self-test and generates an unlock command when the external controller passes the self-test. The Switch physical switch is unlocked. When the Switch physical switch is touched, a closing signal is generated. When the PDU control box receives the closing signal, it closes the internal high-voltage relay. The relay control module controls the relay to close to complete the power-on.

[0009] The audible and visual alarm system includes a buzzer and a prompting subsystem. If the BCMU main control unit fails to complete its self-test, it generates an alarm signal and controls the buzzer to sound an alarm. At the same time, it detects the faulty part of the system and prompts the fault location through the prompting subsystem.

[0010] It also includes a flight control module, which is used to detect flight status and fault monitoring in real time. If a flight completion or fault is detected, a power-down signal is generated. The BCMU main control management unit is also configured with a power-down execution strategy. The power-down execution strategy includes, when a power-down signal is received, controlling the relay control module to disconnect, controlling the buzzer to indicate that the battery has been powered down, and the Switch physical switch to disconnect and self-lock, thus completing the power-down.

[0011] As a further improvement of the present invention, the collected data includes the battery's current, voltage, and temperature.

[0012] As a further improvement of the present invention, a display module is also included. The display module includes an airborne display screen and a digital display model unit. The digital display model unit is used to retrieve the structural shape of the aircraft body and form an aircraft body model, retrieve the position information of the battery pack, load and form a battery mark in the aircraft body model, retrieve the aircraft body circuit diagram, and modularly divide the circuit diagram to form multiple sets of circuit model diagrams. Each of the circuit model diagrams includes several sub-circuit diagrams. It is also used to retrieve the external insulation layer of the aircraft body to form an insulation model, and load the battery mark, circuit model diagram and insulation model into the aircraft body model to form a digital display model diagram for display on the airborne display screen.

[0013] As a further improvement of the present invention, the BCMU main control unit is configured with self-test priority and self-test threshold. The self-test priority includes cell temperature, battery voltage, current information, insulation information, and ambient temperature. The self-test threshold represents the maximum value of the parameters included in the corresponding self-test priority. The self-test strategy is specifically as follows:

[0014] The system performs self-tests based on self-test priorities, determining whether each parameter in the self-test priority falls within the self-test threshold range. If it falls within the self-test threshold range, it passes and generates a main control self-test signal. If it exceeds the self-test threshold, it generates an alarm signal and retrieves the abnormal item in the corresponding self-test priority, generates an abnormal signal based on the corresponding item, and sends it to the display module.

[0015] As a further improvement of the present invention, when the display receives an abnormal signal, the control digital display model unit retrieves the abnormal item and forms a display mark. The digital display module in the airborne display screen magnifies and highlights the abnormal item, and generates abnormal data according to the abnormal item type.

[0016] As a further improvement of the present invention, the BCMU main control unit is also used to report abnormal data to the cloud system. The BCMU main control unit also generates aircraft information corresponding to the aircraft number. The cloud system generates a maintenance plan based on the abnormal data and sends it to the BCMU main control unit corresponding to the reported aircraft information through a wireless transmission module. The airborne display screen displays the maintenance plan.

[0017] As a further improvement of the present invention, the airborne display screen is also provided with a maintenance unit key, which includes a repair key and a shutdown maintenance key. Triggering the repair key indicates that the maintenance of the corresponding abnormal item is completed according to the maintenance plan. Triggering the shutdown maintenance key indicates that the machine needs to be shut down for maintenance according to the maintenance plan. When the shutdown maintenance key is triggered, a power-down signal is also generated to control the power off of the machine.

[0018] As a further improvement of the present invention, the external controller further includes a pre-inspection unit, which is used to provide external low-voltage pre-inspection to detect whether the circuit protection of the machine body is unobstructed, and generates an unlocking command when the pre-inspection unit completes the detection.

[0019] The beneficial effects of this invention are as follows: The BMU acquisition module collects real-time data on the battery cell voltage and temperature, as well as real-time voltage and current information from other modules within the aircraft. This data is then quickly and effectively uploaded to the BCMU main control unit via a wireless transmission module. The BCMU main control unit uses the collected battery information and other external information to determine the battery status, thereby controlling the status of the relays inside the PDU control box to achieve intelligent adjustment and control. Furthermore, during power-on, the BCMU main control unit and external controller perform self-checks before controlling the Switch physical switch to turn on, minimizing the risk of damage to electrical components during power-on failures. During power-off, status detection and individual power-off control are performed first, ensuring overall power-off safety when the battery is fully powered off, reducing the risk of short circuits. This achieves the effect of safe power-on and power-off control for the aircraft. Attached Figure Description

[0020] Figure 1 A system diagram illustrating the present invention;

[0021] Figure 2 To illustrate the power-on logic diagram;

[0022] Figure 3 To illustrate the power-down logic diagram. Detailed Implementation

[0023] The present invention will be further described in detail below with reference to the accompanying drawings and embodiments. Identical components are denoted by the same reference numerals. It should be noted that the terms "front," "rear," "left," "right," "upper," and "lower" used in the following description refer to directions in the accompanying drawings, and the terms "bottom surface," "top surface," "inner," and "outer" refer to directions toward or away from the geometric center of a specific component, respectively.

[0024] refer to Figures 1 to 3 The diagram illustrates a specific embodiment of an aircraft power battery management system according to the present invention. It includes a BCMU main control unit, a wireless transmission module, a BMU acquisition module, a Switch physical switch, a PDU control box, an audible and visual alarm system, an external controller, and a relay control module. The BMU acquisition module collects the status of the battery cells and battery modules and generates collected data. The BMU acquisition module reports the collected data to the BCMU main control unit via wireless transmission. The collected data includes the battery's current, voltage, and temperature. The Switch physical switch remains in a self-locking state when not powered on. The communication methods between the BCMU main control unit and the BMU acquisition module include CAN, RS232, and RS485.

[0025] When the system is powered on, the BCMU main control unit is woken up. The BCMU main control unit is configured with a self-test strategy. The BCMU main control unit performs a self-test according to the self-test strategy and generates a main control self-test signal when the self-test is completed. When the external controller receives the main control self-test signal, it performs a self-test and generates an unlock command when the external controller passes the self-test. The Switch physical switch is unlocked. When the Switch physical switch is touched, a closing signal is generated. When the PDU control box receives the closing signal, it closes the internal high-voltage relay. The relay control module controls the relay to close and complete the power-on.

[0026] The audible and visual alarm system includes a buzzer and a prompting subsystem. If the BCMU main control unit fails to complete its self-test, it generates an alarm signal and controls the buzzer to sound an alarm. At the same time, it detects the faulty part of the system and prompts the fault location through the prompting subsystem.

[0027] It also includes a flight control module, which is used to detect flight status and fault monitoring in real time. If a flight completion or fault is detected, a power-down signal is generated. The BCMU main control management unit is also configured with a power-down execution strategy. The power-down execution strategy includes, when a power-down signal is received, controlling the relay control module to disconnect, controlling the buzzer to indicate that the battery has been powered down, and the Switch physical switch to disconnect and self-lock, thus completing the power-down.

[0028] It also includes a display module, which comprises an airborne display screen and a digital display model unit. The digital display model unit is used to retrieve the structural shape of the aircraft and form an aircraft model, retrieve the position information of the battery pack, load and form battery markings in the aircraft model, retrieve the aircraft circuit diagram, and modularize the circuit diagram to form multiple sets of circuit model diagrams, each of which includes several sub-circuit diagrams. It is also used to retrieve the external insulation layer of the aircraft to form an insulation model, and load the battery markings, circuit model diagrams, and insulation model diagrams into the aircraft model to form a digital display model for display on the airborne display screen.

[0029] The BCMU main control unit is configured with self-test priorities and self-test thresholds. The self-test priorities include cell temperature, battery voltage, current information, insulation information, and ambient temperature. The self-test threshold represents the maximum value of the parameters included in the corresponding self-test priority. The self-test strategy is as follows:

[0030] The system performs self-tests based on self-test priorities, determining whether each parameter in the self-test priority falls within the self-test threshold range. If it falls within the self-test threshold range, it passes and generates a main control self-test signal. If it exceeds the self-test threshold, it generates an alarm signal and retrieves the abnormal item in the corresponding self-test priority, generates an abnormal signal based on the corresponding item, and sends it to the display module.

[0031] When the display receives an abnormal signal, the control digital display model unit retrieves the abnormal item and forms a display mark. The digital display module in the airborne display screen magnifies and highlights the abnormal item and generates abnormal data according to the abnormal item type.

[0032] The BCMU main control unit is also used to report abnormal data to the cloud system. The BCMU main control unit also generates aircraft information corresponding to the aircraft number. The cloud system generates a maintenance plan based on the abnormal data and sends it to the BCMU main control unit corresponding to the reported aircraft information through a wireless transmission module. The airborne display screen displays the maintenance plan.

[0033] The airborne display screen is also equipped with a maintenance unit key, which includes a repair key and a shutdown maintenance key. Triggering the repair key indicates that the corresponding abnormal item is repaired according to the maintenance plan. Triggering the shutdown maintenance key indicates that the machine needs to be shut down for maintenance according to the maintenance plan. Triggering the shutdown maintenance key also generates a power-down signal to control the machine to cut off power.

[0034] The external controller also includes a pre-inspection unit, which is used to provide external low-voltage pre-inspection to detect whether the circuit protection of the machine body is unobstructed, and generates an unlocking command when the pre-inspection unit completes the detection.

[0035] Working principle and its effects:

[0036] The BMU acquisition module collects real-time data on the battery cell voltage and temperature, as well as the real-time voltage and current information of other modules in the aircraft. This data is then quickly and efficiently uploaded to the BCMU main control unit via a wireless transmission module. The BCMU main control unit uses the collected battery information and other external data to determine the battery status and control the status of the relays inside the PDU control box to achieve intelligent adjustment and control. Furthermore, during power-on, the BCMU main control unit and external controller perform self-checks before controlling the Switch physical switch to turn on the power, minimizing the risk of damage to electrical components during power-on in case of malfunctions. During power-off, status detection and individual control power-off are performed first, ensuring overall power-off safety when the battery has finished de-energizing, reducing the risk of short circuits. This achieves the effect of safe power-on and power-off control for the aircraft.

[0037] The above description is merely a preferred embodiment of the present invention. The scope of protection of the present invention is not limited to the above embodiments. All technical solutions falling within the scope of the present invention's concept are within the scope of protection of the present invention. It should be noted that for those skilled in the art, any improvements and modifications made without departing from the principles of the present invention should also be considered within the scope of protection of the present invention.

Claims

1. A power battery management system for aircraft, characterized in that: It includes the BCMU main control unit, wireless transmission module, BMU acquisition module, Switch physical switch, PDU control box, audible and visual alarm system, external controller, relay control module, flight control module and display module; The display module includes an airborne display screen and a digital display model unit. The digital display model unit is used to retrieve the structural shape of the aircraft and form an aircraft model, retrieve the position information of the battery pack, load and form battery markings in the aircraft model, retrieve the aircraft circuit diagram, and modularize the circuit diagram to form multiple sets of circuit model diagrams. Each circuit model diagram includes several sub-circuit diagrams. It is also used to retrieve the external insulation layer of the aircraft to form an insulation model, and load the battery markings, circuit model diagrams, and insulation model diagrams into the aircraft model to form a digital display model diagram for display on the airborne display screen. The BMU acquisition module is used to collect the status of the battery cell and battery module and generate the acquisition data. The BMU acquisition module reports the acquisition data to the BCMU main control unit via wireless transmission. The Switch physical switch remains in a self-locking state when not powered on. The BCMU main control unit is configured with a self-test strategy, self-test priority, and self-test threshold. The self-test priority includes cell temperature, battery voltage, current information, insulation information, and ambient temperature. The self-test threshold represents the maximum value of the parameters included in the corresponding self-test priority. When the system is powered on, the BCMU main control unit is woken up. The BCMU main control unit performs a self-test according to the self-test priority and determines whether each parameter in the self-test priority is within the self-test threshold range. If it is within the self-test threshold range, it passes and generates a main control self-test signal. If it exceeds the self-test threshold, it generates an alarm signal and retrieves the abnormal item in the corresponding self-test priority, generates an abnormal signal according to the corresponding item and sends it to the display module. When the display module receives an abnormal signal, it controls the digital display model unit to retrieve the abnormal item and form a display mark. The digital display model in the airborne display screen enlarges and highlights the abnormal item and generates abnormal data according to the abnormal item type. When the external controller receives the main control self-test signal, it performs a self-test and generates an unlock command when the external controller passes the self-test. The external controller also includes a pre-test unit, which provides external low-voltage pre-test to check whether the circuit protection is working properly. When the pre-test unit completes the test, it generates an unlock command. The Switch physical switch releases its self-lock according to the unlock command. When the Switch physical switch is touched, it generates a closing signal. When the PDU control box receives the closing signal, it closes the internal high-voltage relay. The relay control module controls the relay to close and complete the power-on process. The audible and visual alarm system includes a buzzer and a prompting subsystem. If the BCMU main control unit fails to complete its self-test, it generates an alarm signal and controls the buzzer to sound an alarm. At the same time, it detects the faulty part of the system and prompts the fault location through the prompting subsystem. The flight control module is used to detect flight status and fault monitoring in real time. If a flight completion or fault is detected, a power-down signal is generated. The BCMU main control management unit is also configured with a power-down execution strategy. The power-down execution strategy includes controlling the relay control module to disconnect when a power-down signal is received, controlling the buzzer to indicate that the battery has been powered down, and the Switch physical switch to disconnect and self-lock, thus completing the power-down.

2. The aircraft power battery management system according to claim 1, characterized in that: The collected data includes the battery's current, voltage, and temperature.

3. The aircraft power battery management system according to claim 1, characterized in that: The BCMU main control unit is also used to report abnormal data to the cloud system. The BCMU main control unit also generates aircraft information corresponding to the aircraft number. The cloud system generates a maintenance plan based on the abnormal data and sends it to the BCMU main control unit corresponding to the reported aircraft information through a wireless transmission module. The airborne display screen displays the maintenance plan.

4. The aircraft power battery management system according to claim 3, characterized in that: The airborne display screen is also equipped with a maintenance unit key, which includes a repair key and a shutdown maintenance key. Triggering the repair key indicates that the corresponding abnormal item is repaired according to the maintenance plan. Triggering the shutdown maintenance key indicates that the machine needs to be shut down for maintenance according to the maintenance plan. Triggering the shutdown maintenance key also generates a power-down signal to control the machine to cut off power.

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