Electric helicopter electrical system and control method thereof

Abstract

The invention provides an electrical system of an electric helicopter. The electrical system comprises an electric power system, an intelligent control system, a water cooling system and a low-voltage power distribution system, the electric power system comprises a power battery, a high-voltage box, a controller and a motor and provides a power supply for the whole helicopter, and the transmission system transmits the capacity to the rotor wings to provide lift force for the helicopter; the power battery water cooling system comprises a large water pump, a large water pump controller and a power battery heat exchanger; the motor water cooling system comprises a small water pump, a small water pump controller, a controller heat exchanger, an overflow water tank, an expansion water tank and a radiator. The intelligent control system is composed of a comprehensive management computer and a rotor rotating speed monitor, and the low-voltage power distribution system comprises a 24V storage battery and onboard low-voltage electric equipment; meanwhile, the invention provides an electric helicopter electrical system control method.

Description

Technical Field

[0001] The present application belongs to the technical field of aviation electrical systems, and in particular, relates to an electrical system of an electric helicopter and a control method thereof. Background Art

[0002] An all-electric helicopter is a new type of helicopter that is completely powered by electricity. In the development of the aviation industry, more-electric and all-electric helicopters are important indicators of the fifth-generation helicopters. Replacing traditional secondary energy sources such as hydraulics, transmissions, and lubricating oils with electricity means higher transmission efficiency, more integrated control logic, and faster response control capabilities. At the same time, electricity, as the main energy source for helicopters, is also of great significance to environmental protection and green aviation. Summary of the invention

[0003] Purpose of the invention: To propose a helicopter electrical system which uses electricity as the main energy source and is composed of a power battery, a high-voltage box, a motor controller, a motor, a 24V battery, an integrated management computer, a water-cooling pump, a water-cooling motor, an expansion water tank, a radiator and other equipment.

[0004] In a first aspect, the present application provides an electrical system for an electric helicopter, including an electric power system, an intelligent control system, a water cooling system, and a low-voltage power distribution system;

[0005] The electric power system includes a power battery, a high-voltage box, a controller and a motor, which provide power for the whole machine, and the power is transmitted to the rotor by the transmission system to provide lift for the helicopter;

[0006] The water cooling system is divided into: the power battery water cooling system includes a large water pump, a large water pump controller, and a power battery heat exchanger; the motor water cooling system includes a small water pump, a small water pump controller, a controller heat exchanger, an overflow water tank, an expansion water tank, and a radiator;

[0007] The intelligent control system is composed of a comprehensive management computer and a rotor speed monitor.

[0008] Preferably, the low-voltage power distribution system includes a 24V battery and onboard low-voltage electrical equipment.

[0009] Preferably, the power battery is composed of four batteries connected in series, each battery is composed of several small batteries connected in series, and each battery is externally connected to a contactor and a diode. When a battery fails, the BMS issues a cut-off command to short-circuit the failed battery, and the remaining three power batteries provide kinetic energy for the entire machine. The positive power supply is connected to the high-voltage box, and the negative power supply is connected to the controller to provide a high-voltage power source for the entire machine.

[0010] Preferably, the BMS management module inside the power battery collects the capacity, voltage, current and temperature information of each power battery, determines the power quality and reports the information to the integrated management computer and displays it on the control screen. The power battery connection instruction is given manually and issued via the integrated management computer.

[0011] Preferably, the large and small water pumps are power equipment for providing circulating cooling water to the power battery and the motor respectively. The large and small water pump controllers collect the flow rate of the cooling water of the water pumps and provide electrical energy to the water pumps. At the same time, the collected flow rate is fed back to the integrated management computer, and the instructions of the integrated management computer are received to control the flow rate of the water pumps.

[0012] The controller heat exchanger, radiator and expansion water tank dissipate the heat of the hot cooling water flowing out of the equipment through the water pump, and transmit the cooled cooling water to the controller and motor through large and small water pumps to cool the equipment.

[0013] Preferably, the rotor speed controller collects the rotor speed and reports it to the integrated management computer. The integrated management computer compares the rotor speed with the motor speed, combines the motor working efficiency, and the rotor speed control signal as a reference, and corrects the rotor speed control signal.

[0014] The main function of the integrated management computer is to control the whole system equipment, transmit the collected physical quantities such as voltage, current, frequency, speed to the integrated management computer, and the integrated management computer monitors the physical quantities and issues control instructions to the equipment.

[0015] Preferably, the integrated management computer also has a power distribution function, which is mainly based on the bus input voltage, and controls the current of electrical energy distributed to the equipment through internal control boards and protection devices, and monitors this current, using the Irat curve as the protection basis to implement overcurrent and short-circuit protection functions for the equipment.

[0016] Preferably, the onboard low-voltage electrical equipment adopts the single-wire system used in traditional aviation, and according to the importance of the equipment power supply, the emergency equipment is set to two-way power distribution. The two-way power distribution is realized by two independent bus bars, both of which are powered by 24V batteries. One of the routes is powered by a 24V battery, which is connected to the integrated management computer, motor controller, and power battery BMS module through bus bar 1 and finally connected to the fuselage grounding point to complete a power distribution. This process is protected by a circuit breaker. The other route is provided by the integrated management computer, and the equipment power is supplied through a bus bar built into the integrated management computer and named bus bar 2. The control circuit and power are switched and adjusted through the solid-state power controller inside the integrated management computer to supply power to the load of the electrical equipment. The negative end of the load is also connected to the fuselage ground to form a loop.

[0017] In a second aspect, the present application also provides a method for controlling an electrical system of an electric helicopter, the method comprising:

[0018] Step 1: Connect the 24V battery, the integrated management computer and bus 2 are automatically connected, the operator connects the power battery, motor controller and rotor speed controller in turn by operating the integrated management computer, the BMS module collects and determines the single cell voltage, current and battery temperature information of the power battery and reports it to the integrated management computer;

[0019] Step 2: When the BMS module detects that a single cell has over-temperature, over-current or other serious problems that damage the battery, the BMS module will cut off the abnormal single cell by connecting the short-circuit current of the abnormal single cell, and report the alarm information and battery abnormal cut-off information to the integrated management computer;

[0020] Step 3: After the single battery is cut off, the remaining three power batteries continue to work. If a serious alarm signal such as over-temperature or over-current of the single battery appears again, the BMS module will no longer cut off the abnormal single battery, but will report this part of the content to the integrated management computer;

[0021] Step 4: After the power battery and the motor controller are connected, the motor controller converts the DC power of the power battery into AC power to drive the motor to rotate and then drive the rotor to rotate. The motor controller collects information such as motor speed, temperature, voltage, current, etc., and reports it to the integrated management computer. The integrated management computer judges the information uploaded by the rotor speed controller and corrects the control motor speed command;

[0022] Step 5: The integrated management computer will connect the water cooling system to cool down the power battery or the motor according to the lowest temperature of the single cell reported by the battery and the motor temperature according to the preset temperature threshold;

[0023] Step 6, the high-voltage power part on the aircraft adopts a two-wire circuit loop. The voltage output by the positive terminal of the power battery is transmitted to the motor controller through a high-voltage box composed of a contactor and a fuse. The motor controller has a built-in DC / AC converter, which converts the direct current output by the power battery into the three alternating currents required by the motor to drive the motor to rotate. The motor then drives the rotor to rotate through the on-board transmission part to provide lift for the helicopter and achieve flight;

[0024] Step 7: The onboard low-voltage power distribution system consists of two independent bus bars 1 and 2, both powered by 24V batteries. Bus bar 1 directly distributes power to key power-consuming equipment, and circuit breakers of different specifications are added to the distribution feeder circuit. Bus bar 2 is built into the integrated management computer and realizes overcurrent and short-circuit protection functions through the SSPC power distribution circuit. The negative end of the power-consuming equipment adopts the single-wire system of the traditional aviation system and is connected to the fuselage ground to form a loop.

[0025] Beneficial technical effects of this application:

[0026] 1. The power battery adopts the form of four batteries connected in series, and each battery is connected to a short circuit, so that any battery can be quickly cut off after failure, but it will not affect the other three batteries to continue to power the whole machine. It can improve the reliability and safety of the whole system, reduce the abnormality of a single device due to single point failure, and cut off the power supply network of the whole system.

[0027] The preferred short-circuit circuit is composed of a contactor and a diode. When a single battery is overheated or abnormally damaged, the short-circuit circuit is connected. However, since the short-circuit circuit has a diode, it can short-circuit the single battery in the entire electrical system and prevent the single battery from forming a loop with the short-circuit circuit.

[0028] 2. In order to reduce the impact of the temperature rise of the power battery, a water cooling system is integrated, and cooling water with different flow rates is used for cooling according to the different temperature rises of the power battery and the motor. Compared with the traditional onboard environmental control system, the two different water cooling systems can adjust the cooling water flow rate at all times according to the temperature changes of the water cooling equipment. This technology avoids energy waste and improves cooling efficiency.

[0029] 3. The highly integrated onboard control system combines energy distribution. Compared with the traditional aircraft systems with multiple computers and separate control and power distribution systems, it can better improve capacity utilization, increase the transmission efficiency of control signals, avoid multiple storage and transmission of signals and reduce unnecessary waste.

[0030] 4. The high and low voltage systems are separated, with the high voltage adopting a two-wire system and the low voltage adopting a traditional single-wire system. This can reduce weight, reduce the power and electrical energy consumption of the high voltage system, increase the energy reserve required for flight, and improve the reliability of the entire system.

[0031] 5. Compare the rotor speed with the motor speed for reference, which can improve the correction of motor speed control and reduce the misjudgment of speed. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 It is a schematic diagram of the principle of an electrical system suitable for an electric helicopter provided in an embodiment of the present application. DETAILED DESCRIPTION

[0033] This application uses a single-motor system drive to improve the overall reliability of the system; adds a water cooling system to improve the battery's ability to cool and dissipate heat, effectively suppressing the problem of battery temperature rise; adopts high and low voltage isolation, and the high-voltage power part adopts a two-wire system to improve the safety of the system. At the same time, the low-voltage electrical equipment adopts the single-wire system in the traditional aviation field, separating the high and low voltages to effectively solve the electromagnetic interference problem and reduce the consumption of high-voltage power battery capacity; uses a highly integrated integrated management computer to eliminate the state of multiple computers in traditional helicopters, and uses a highly integrated computer to improve control efficiency.

[0034] See also Figure 1 The electrical system of the helicopter provided in this application is composed of an electric power system, an intelligent control system, a water cooling system, and a low-voltage power distribution system.

[0035] 1. The electric power system includes power batteries, high-voltage boxes, controllers, motors and other equipment, which provide power for the entire aircraft, and the transmission system transfers the power to the rotor to provide lift for the helicopter.

[0036] The power battery consists of four batteries connected in series, and each battery is composed of several small batteries connected in series. Each battery is externally connected to a contactor and a diode. When a battery fails, the BMS issues a cut-off command to short-circuit the failed battery. The remaining three power batteries provide kinetic energy for the entire machine. The positive power supply is connected to the high-voltage box, and the negative power supply is connected to the controller, providing a high-voltage power source for the entire machine.

[0037] The BMS management module inside the power battery collects the capacity, voltage, current, temperature and other information of each power battery, determines the power quality and reports the information to the integrated management computer and displays it on the control screen. The power battery connection instruction is given manually and issued via the integrated management computer;

[0038] Inside the high-voltage box, there is a contactor and a fuse connected in series, which is connected to the positive terminal of the power battery. The other end is connected to the controller. In special circumstances such as a short circuit in the power battery and no reaction when cutting off one battery alone, the power supply line is disconnected to take the power battery off the grid, thus protecting the power battery.

[0039] The motor controller receives direct current from the power battery. It has a built-in DC / AC converter that converts the direct current of the power battery into alternating current and outputs it to the motor to drive the motor to work. It also collects the motor speed, temperature, voltage, and current values, and feeds the collected data back to the integrated management computer. It then receives instructions from the integrated management computer to control the motor speed, connection and other functions.

[0040] The motor receives three-phase AC power from the controller to drive the motor to rotate, and drives the rotor to rotate through the transmission system. It receives control instructions from the controller to work and be protected.

[0041] 2. The water cooling system is mainly divided into: the power battery water cooling system includes a large water pump, a large water pump controller, a power battery heat exchanger and other equipment; the motor water cooling system includes a small water pump, a small water pump controller, a controller heat exchanger and other equipment as well as an overflow water tank, an expansion water tank and a radiator.

[0042] The large and small water pumps are power devices that provide circulating cooling water to the power battery and motor respectively. The large and small water pump controllers collect the flow rate of the cooling water of the water pumps and provide electrical energy to the water pumps. At the same time, they feed back the collected flow rate to the integrated management computer and receive instructions from the integrated management computer to control the flow rate of the water pumps.

[0043] The controller heat exchanger, radiator and expansion water tank dissipate the heat of the hot cooling water flowing out of the equipment through the water pump, and transmit the cooled cooling water to the controller and motor through large and small water pumps to cool the equipment.

[0044] 3. The intelligent control system is mainly composed of integrated management computers, rotor speed monitors and other equipment.

[0045] The rotor speed controller collects the rotor speed and reports it to the integrated management computer. The integrated management computer compares the rotor speed with the motor speed, combines the motor efficiency, and the rotor speed control signal as a reference, and corrects the rotor speed control signal.

[0046] The main function of the integrated management computer is to control the whole system equipment, transmit the collected physical quantities such as voltage, current, frequency, speed to the integrated management computer, and the integrated management computer monitors the physical quantities and issues control instructions to the equipment;

[0047] The integrated management computer also has the function of power distribution, which is mainly based on the bus input voltage. It controls the current of electrical energy distributed to the equipment through internal control boards and protection devices, monitors the current, and uses the I rat curve as the protection basis to implement overcurrent and short-circuit protection functions for the equipment.

[0048] 4. The onboard low-voltage power distribution system consists of a 24V battery, an integrated management computer and onboard low-voltage electrical equipment. The onboard low-voltage electrical equipment adopts the single-wire system used in traditional aviation, and according to the importance of equipment power supply, the emergency equipment is set to two-way power distribution. The two-way power distribution is realized by two independent bus bars, both of which are powered by 24V batteries. One of the routes is powered by a 24V battery, which is connected to the grounding point of the fuselage through bus bar 1 to the integrated management computer, motor controller and other equipment to complete a power distribution. This process is protected by a circuit breaker. The other route is provided by the integrated management computer. The equipment power is supplied through a bus bar built into the integrated management computer and named bus bar 2. The solid-state power controller inside the integrated management computer switches and adjusts the control circuit and power to supply power to the load of the electrical equipment. The negative end of the load is also connected to the fuselage ground to form a loop.

[0049] It should be noted that: 1. The power battery is in the form of four batteries connected in series, and each battery is connected to a short-circuit circuit, so that if any battery fails, it can be quickly cut off without affecting the remaining three batteries to continue to power the entire machine.

[0050] 2. In order to reduce the impact of the temperature rise of the power battery, a water cooling system is integrated, and cooling water with different flow rates is used for cooling according to the different temperature rises of the power battery and motor.

[0051] 3. Use a highly integrated intelligent control system. This system replaces the situation where multiple computers on traditional helicopters control each other separately. The use of high integration avoids the waste of transmission signals caused by multiple transmissions of information.

[0052] 4. Integrate the control system of the integrated management computer with the power distribution system, which not only strengthens the control ability of electrical equipment, but also integrates energy distribution and control signals to improve capacity utilization and reduce unnecessary waste.

[0053] 5. Separating the high and low voltage power supply systems can reduce the energy waste of the high voltage system and use the traditional aviation single-line power supply system to reduce weight. The separation of the two independent systems can improve the reliability of the electrical system.

[0054] 6. Comparing the speed signal of the speed controller with the click speed signal can reduce the misjudgment of the speed by the integrated management computer.

[0055] See also Figure 1In order to complete the design of the all-electric helicopter system, and also to solve the temperature rise problem that is difficult to solve in the design of the all-electric system, and to improve the safety and reliability of the system, the present invention provides a set of electrical system designs with water cooling function and high reliability. As shown in the figure, the electrical system is divided into an electric power system, a water cooling system, an intelligent control system, and a low-voltage power distribution system. For accurate description, the three parts of the onboard control part, the high-voltage power part, and the low-voltage power part will be introduced:

[0056] In the on-board control part, first connect the 24V battery, and the integrated management computer and bus 2 can be connected. The operator then operates the refrigeration on the integrated management computer to control the power battery, motor and other parts to be connected in turn. The power battery connection signal is transmitted from the integrated management computer to the BMS block. At the same time, the BMS module collects the single cell voltage, current and battery temperature of the power battery, and determines whether these data meet the design requirements, and reports the collected information after judgment to the integrated management computer. The integrated management computer displays this part of the content on the screen. If the single cell has problems such as overtemperature and overcurrent that seriously damage the battery, the BMS module will automatically disconnect the abnormal single cell, and report the alarm information and battery abnormality disconnection information to the integrated management computer. When only three power batteries are working, if there are serious alarm signals such as single cell overtemperature and overcurrent, the BMS module will no longer cut off the abnormal single cell, but will report this part of the content to the integrated management computer.

[0057] After the power battery is connected normally, the operator connects the motor contactor inside the motor controller through the integrated management computer control part. The motor controller converts the DC power of the power battery into AC power and controls the battery connection through the motor contactor. At the same time, it collects information such as motor speed, temperature, voltage, current, etc. and reports it to the integrated management computer. The integrated management computer judges this part of information and outputs the control output motor speed command. The motor speed information is also used as a reference by the rotor speed signal collected by the rotor speed controller, and the output motor speed command is corrected.

[0058] The integrated management computer will connect the water cooling system to cool the power battery or motor according to the lowest temperature of the single cell reported by the battery and the motor temperature according to the preset temperature threshold.

[0059] The high-voltage power part on the aircraft adopts a two-wire circuit loop. The voltage output from the positive end of the power battery is transmitted to the motor controller through a high-voltage box composed of a contactor and a fuse. The motor controller has a built-in DC / AC converter, which converts the direct current output by the power battery into the three alternating currents required by the motor to drive the motor to rotate. The motor then drives the rotor to rotate through the on-board transmission part to provide lift for the helicopter and achieve flight. The internal fuse of the high-voltage box will cut off the power battery when the output current of the power battery is abnormally large, thereby achieving the purpose of protecting the battery. The power battery is composed of four single cells in series, and each single cell is connected in series with a contactor and a diode. When it is judged that the single cell is overheated, overcurrent or abnormally damaged, the BMS module will control the contactor to connect, thereby achieving the effect of short-circuiting the single cell. At the same time, a diode is connected in series to avoid the single cell and the short-circuit line forming a loop when the single cell is short-circuited, which damages the battery.

[0060] The low-voltage power distribution system on board consists of two independent busbars 1 and 2, both powered by 24V batteries. Busbar 1 directly distributes power to key power-consuming equipment, and different specifications of circuit breakers are added to the feeder circuit of the power distribution. In the event of a short circuit in the power-consuming equipment, the circuit breaker will be disconnected, thereby preventing the entire aircraft electrical system network from being affected by abnormal circuits of some equipment. Busbar 2 is built into the integrated management computer, and distributes power to the power load according to the I rat curve through the SSPC power distribution circuit, and has functions such as overcurrent and short-circuit protection. The negative end of the power-consuming equipment adopts the single-wire system of the traditional aviation system, which is connected to the fuselage ground to form a loop.

Claims

1. An electrical system for an electric helicopter, characterized in that: Including electric power system, intelligent control system, water cooling system and low-voltage power distribution system; The electric power system includes a power battery, a high-voltage box, a controller and a motor, which provide power for the whole machine, and the power is transmitted to the rotor by the transmission system to provide lift for the helicopter; The water cooling system is divided into: the power battery water cooling system includes a large water pump, a large water pump controller, and a power battery heat exchanger; the motor water cooling system includes a small water pump, a small water pump controller, a controller heat exchanger, an overflow water tank, an expansion water tank, and a radiator; The intelligent control system is composed of a comprehensive management computer and a rotor speed monitor.

2. The electric helicopter electrical system according to claim 1, characterized in that: The low-voltage power distribution system includes a 24V battery and low-voltage electrical equipment on board.

3. The electric helicopter electrical system according to claim 2, characterized in that: The power battery is composed of four batteries connected in series, and each battery is composed of several small batteries connected in series. Each battery is externally connected to a contactor and a diode. When a battery fails, the BMS issues a cut-off command to short-circuit the failed battery. The remaining three power batteries provide kinetic energy for the entire machine. The positive power supply is connected to the high-voltage box, and the negative power supply is connected to the controller to provide a high-voltage power source for the entire machine.

4. The electric helicopter electrical system according to claim 3, characterized in that: The BMS management module inside the power battery collects the capacity, voltage, current and temperature information of each power battery, determines the power quality and reports the information to the integrated management computer and displays it on the control screen. The power battery connection instruction is given manually and issued via the integrated management computer.

5. The electric helicopter electrical system according to claim 4, characterized in that: The large and small water pumps are power equipment that provide circulating cooling water to the power battery and the motor respectively. The large and small water pump controllers collect the flow rate of the cooling water of the water pumps and provide electrical energy to the water pumps. At the same time, the collected flow rate is fed back to the integrated management computer, and the instructions of the integrated management computer are received to control the flow rate of the water pumps. The controller heat exchanger, radiator and expansion water tank dissipate the heat of the hot cooling water flowing out of the equipment through the water pump, and transmit the cooled cooling water to the controller and motor through large and small water pumps to cool the equipment.

6. The electric helicopter electrical system according to claim 5, characterized in that: The rotor speed controller collects the rotor speed and reports it to the integrated management computer. The integrated management computer compares the rotor speed with the motor speed, combines the motor efficiency, and the rotor speed control signal as a reference, and corrects the rotor speed control signal. The main function of the integrated management computer is to control the whole system equipment, transmit the collected physical quantities such as voltage, current, frequency, speed to the integrated management computer, and the integrated management computer monitors the physical quantities and issues control instructions to the equipment.

7. The electric helicopter electrical system according to claim 6, characterized in that: The integrated management computer also has a power distribution function, which is mainly based on the bus input voltage. It controls the current of electrical energy distributed to the equipment through internal control boards and protection devices, monitors the current, and implements overcurrent and short-circuit protection functions for the equipment based on the Irat curve.

8. The electric helicopter electrical system according to claim 7, characterized in that: The low-voltage electrical equipment on board adopts the single-wire system used in traditional aviation, and according to the importance of equipment power supply, the emergency equipment is set to two-way power distribution. The two-way power distribution is realized by two independent bus bars, both of which are powered by 24V batteries. One of the routes is powered by a 24V battery, which is connected to the integrated management computer, motor controller, and power battery BMS module through bus bar 1 and finally connected to the fuselage grounding point to complete a power distribution. This process is protected by a circuit breaker. The other route is provided by the integrated management computer. The equipment power is supplied through a bus bar built into the integrated management computer and named bus bar 2. The solid-state power controller inside the integrated management computer switches and adjusts the control circuit and power to supply power to the load of the electrical equipment. The negative end of the load is also connected to the fuselage ground to form a loop.

9. A method for controlling an electrical system of an electric helicopter, characterized in that: The method comprises: Step 1: Connect the 24V battery, the integrated management computer and bus 2 are automatically connected, the operator connects the power battery, motor controller and rotor speed controller in turn by operating the integrated management computer, the BMS module collects and determines the single cell voltage, current and battery temperature information of the power battery and reports it to the integrated management computer; Step 2: When the BMS module detects that a single cell has over-temperature, over-current or other serious problems that damage the battery, the BMS module will cut off the abnormal single cell by connecting the short-circuit current of the abnormal single cell, and report the alarm information and battery abnormal cut-off information to the integrated management computer; Step 3: After the single battery is cut off, the remaining three power batteries continue to work. If a serious alarm signal such as over-temperature or over-current of the single battery appears again, the BMS module will no longer cut off the abnormal single battery, but will report this part of the content to the integrated management computer; Step 4: After the power battery and the motor controller are connected, the motor controller converts the DC power of the power battery into AC power to drive the motor to rotate and then drive the rotor to rotate. The motor controller collects information such as motor speed, temperature, voltage, current, etc., and reports it to the integrated management computer. The integrated management computer judges the information uploaded by the rotor speed controller and corrects the control motor speed command; Step 5: The integrated management computer will connect the water cooling system to cool down the power battery or the motor according to the lowest temperature of the single cell reported by the battery and the motor temperature according to the preset temperature threshold; Step 6, the high-voltage power part on the aircraft adopts a two-wire circuit loop. The voltage output by the positive terminal of the power battery is transmitted to the motor controller through a high-voltage box composed of a contactor and a fuse. The motor controller has a built-in DC / AC converter, which converts the direct current output by the power battery into the three alternating currents required by the motor to drive the motor to rotate. The motor then drives the rotor to rotate through the on-board transmission part to provide lift for the helicopter and achieve flight; Step 7: The onboard low-voltage power distribution system consists of two independent bus bars 1 and 2, both powered by 24V batteries. Bus bar 1 directly distributes power to key power-consuming equipment, and circuit breakers of different specifications are added to the distribution feeder circuit. Bus bar 2 is built into the integrated management computer and realizes overcurrent and short-circuit protection functions through the SSPC power distribution circuit. The negative end of the power-consuming equipment adopts the single-wire system of the traditional aviation system and is connected to the fuselage ground to form a loop.

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