An electric aircraft power load controller system and its working method

Abstract

The present invention discloses an electric aircraft power load controller system and its operating method, belonging to the technical field of electric aircraft controllers. The system comprises a main power module, a pre-charge module, a discharge module, a monitoring and control module, a power supply module, a communication module, and a terminal. By connecting a solid-state power switch and a high-power mechanical switch in parallel and configuring the control timing of the two switches, the system is suitable for use in electric aircraft high-voltage, high-power electrical load applications. The system exhibits excellent capacitive load adaptability and arc protection. Furthermore, the pre-charge module utilizes the impedance characteristics of the semiconductor power switch in the saturation region to control the semiconductor power switch, achieving controllable pre-charging of the equivalent capacitance of the high-voltage line, thereby reducing the complexity and weight of the device.

Description

Technical Field

[0001] The present invention relates to the technical field of electric aircraft controllers, and in particular to an electric aircraft power load controller system and a working method thereof. Background Art

[0002] Green development is an inevitable requirement for achieving sustainable development in the aviation industry and a key factor in enhancing the future competitiveness of the aviation manufacturing industry. Electric aircraft are a key vehicle and core product for the development of green aviation and the low-altitude economy. The electric propulsion system within this system is a revolutionary system that distinguishes it from traditional aircraft. Electric aircraft propulsion systems require high power and high reliability, and typically utilize a high-voltage DC (HVDC) grid for energy transmission and control from the power battery to the propulsion unit. Due to the electrical characteristics of the HVDC system and electric drive, the HVDC bus exhibits capacitive characteristics. During system and equipment power-up, the system should first slowly charge the equivalent capacitor to prevent sudden high current shocks. During system and equipment power-down, the system should first release the energy stored in the equivalent capacitor to ensure system and personnel safety. Furthermore, the HVDC grid requires arc protection.

[0003] Currently, traditional mechanical power load controllers or solid-state power controllers (SSPC) are commonly used in aviation.

[0004] However, mechanical power load controllers have drawbacks such as slow response, limited mechanical control accuracy, high maintenance requirements, and significant electromagnetic interference. Solid-state power controllers (SSPCs) are primarily suitable for low-current loads. Existing mechanical power load controllers or solid-state power controllers struggle to meet the capacitive load and arc protection requirements of high-voltage DC grids for electric aircraft.

[0005] Based on this, the present invention designs an electric aircraft power load controller system and a working method thereof to solve the above problems. Summary of the Invention

[0006] In view of the above-mentioned shortcomings of the prior art, the present invention provides an electric aircraft power load controller system and a working method thereof.

[0007] To achieve the above objectives, the present invention is implemented through the following technical solutions:

[0008] An electric aircraft power load controller system includes the following parts:

[0009] Main power module, used to control the on / off of the high-voltage DC grid;

[0010] The pre-charge module slowly charges the equivalent capacitor or pre-charges it with a smaller current to prevent the system or load from being impacted or damaged by instantaneous large current.

[0011] The discharge module gradually reduces the load voltage to a safe level by first releasing the electrical energy stored in the equivalent capacitor, ensuring that the charge on the load is safely discharged, thereby avoiding high voltage or arcing when disconnecting;

[0012] The monitoring control module collects status parameters of the main power module, pre-charge module, discharge module, and power module, controls the working status of each module according to the aircraft's commands, and stores and reports the equipment status;

[0013] The power module is used to receive multiple redundant electric energies and supply power to the monitoring and control module;

[0014] Terminal, used to issue aircraft control instructions to the monitoring and control module and receive device status uploaded by the monitoring and control module;

[0015] Communication module, used for monitoring information transmission between the control module and the terminal;

[0016] The monitoring control module is electrically connected to the communication module, and the communication module is wirelessly connected to the terminal;

[0017] The power supply module is electrically connected to the monitoring and control module, the main power module is electrically connected to the pre-charging module and the discharge module, and the monitoring and control module is electrically connected to the main power module, the pre-charging module, and the discharge module.

[0018] Furthermore, the main power module includes an a terminal, a b terminal, a c terminal and a d terminal, the two ends of the pre-charge module are electrically connected to the a terminal and the c terminal of the main power module respectively, the two ends of the discharge module are electrically connected to the c terminal and the d terminal of the main power module respectively, and the c terminal and the d terminal of the main power module are electrically connected to the two ends of the load respectively.

[0019] Furthermore, the main power module adopts a high-power mechanical switch, and the pre-charging module includes a solid-state power switch and a current limiting resistor. The solid-state power switch is electrically connected to the current limiting resistor, the solid-state power switch is electrically connected to the A end of the main power module, and the current limiting resistor is electrically connected to the C end of the main power module.

[0020] Furthermore, high-power mechanical switches use contactors or relays.

[0021] Furthermore, the solid-state power switch adopts a semiconductor power triode switch.

[0022] In order to better achieve the purpose of the present invention, the present invention also provides a working method of an electric aircraft power load controller system, comprising the following steps:

[0023] Step 1: High-voltage electrical equipment is powered through the busbar;

[0024] Step 2: The monitoring control module receives instructions through external communication to determine whether the high-voltage electrical equipment needs to work;

[0025] Step 3: If the high-voltage electrical equipment needs to work, the solid-state power switch in the pre-charge module is closed, and the busbar supplies power to the capacitor in the high-voltage electrical equipment through the current-limiting resistor in the pre-charge module;

[0026] If the high-voltage electrical equipment does not need to work, the thread is terminated directly;

[0027] Step 4: After the busbar supplies power to the capacitor in the high-voltage electrical equipment through the current-limiting resistor in the pre-charge module, the monitoring and control module determines whether the pre-charge capacitor voltage in the pre-charge module reaches the power supply threshold;

[0028] Step 5: If the pre-charge capacitor voltage does not reach the power supply threshold, return to step 3;

[0029] If the pre-charge capacitor voltage reaches the power supply threshold, the solid-state power switch in the pre-charge module is disconnected, the high-power mechanical switch in the main power module is closed, and the busbar directly charges the high-voltage electrical equipment;

[0030] Step 6: After the busbar directly charges the high-voltage electrical equipment, the monitoring and control module receives instructions through external communication to determine whether the high-voltage electrical equipment has stopped working;

[0031] Step 7: If the high-voltage electrical equipment continues to work, return to step 5;

[0032] Step 8: If the high-voltage electrical equipment stops working, the capacitor or inductor in the high-voltage electrical equipment is discharged through the discharge module, and then the thread is terminated.

[0033] Compared with the prior art, the present invention has the following beneficial effects: 1. The load control device based on the hybrid power controller of the present invention, by connecting a solid-state power switch and a high-power mechanical switch in parallel and setting the control timing of the two switches, can be applied to the application scenario of high-voltage and high-power electrical loads of electric aircraft, has good capacitive load adaptability and arc protection, realizes dynamic management of loading and unloading of high-voltage and high-power electrical equipment, and also avoids high-voltage arc;

[0034] 2. The pre-charging module of the present invention utilizes the impedance characteristics of the semiconductor power switch in the saturation region to simulate the pre-charging resistance. By controlling the semiconductor power switch, the controllable pre-charging of the equivalent capacitance of the high-voltage line is achieved, thereby reducing the complexity and weight of the equipment. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] To more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. Those skilled in the art can also derive other drawings based on these drawings without inventive effort.

[0036] Figure 1 A connection block diagram of an electric aircraft power load controller system according to the present invention;

[0037] Figure 2 This is a connection diagram of the main power module, pre-charge module and discharge module of the present invention;

[0038] Figure 3 This is a working diagram of a power load controller system for an electric aircraft according to the present invention;

[0039] Figure 4 This is a diagram of the energy transmission path from the power battery to the motor of the present invention.

[0040] The numbers in the figure represent:

[0041] 1. Main power module; 2. Pre-charge module; 3. Discharge module; 4. Monitoring and control module; 5. Power module; 6. Communication module; 7. Terminal. DETAILED DESCRIPTION

[0042] To make the purpose, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making any creative efforts shall fall within the scope of protection of the present invention.

[0043] Example 1: In some embodiments, please refer to the accompanying drawings of the specification. Figure 1-Figure 3 , including the following parts:

[0044] Main power module 1, used for controlling the switching on or off of the high-voltage DC grid;

[0045] Pre-charge module 2, which slowly charges the equivalent capacitor or pre-charges it with a smaller current to prevent the system or load from being impacted or damaged by instantaneous large current;

[0046] Discharge module 3, which gradually reduces the load voltage to a safe level by first releasing the electrical energy stored in the equivalent capacitor, ensuring that the charge on the load is safely released, thereby avoiding high voltage or arcing when disconnecting;

[0047] The monitoring and control module 4 collects the status parameters of the main power module 1, pre-charge module 2, discharge module 3 and power module 5, controls the working status of each module according to the aircraft's commands, and stores and reports the equipment status;

[0048] The power supply module 5 is used to receive redundant power from multiple channels and supply power to the monitoring and control module 4;

[0049] Terminal 7, used to issue aircraft control instructions to the monitoring and control module 4 and receive device status uploaded by the monitoring and control module 4;

[0050] Communication module 6, used for monitoring information transmission between control module 4 and terminal 7;

[0051] The monitoring and control module 4 is electrically connected to the communication module 6, and the communication module 6 is wirelessly connected to the terminal 7;

[0052] The power module 5 is electrically connected to the monitoring and control module 4, the main power module 1 is electrically connected to the pre-charging module 2 and the discharge module 3, and the monitoring and control module 4 is electrically connected to the main power module 1, the pre-charging module 2, and the discharge module 3.

[0053] When the aircraft commands the high-voltage and high-power load to power on, the monitoring and control module 4 first sends a pre-charging instruction to the pre-charging module 2, and then closes the main power module 1 when the output voltage meets the requirements, and the high-voltage and high-power load enters the working state; when the aircraft commands the high-voltage and high-power load to power off, the monitoring and control module 4 first sends an instruction to discharge excess electric energy to the discharge module 3, and then disconnects the main power module 1 when the output voltage meets the requirements, and the high-voltage and high-power load shuts down.

[0054] Embodiment 2: In some embodiments, as Figure 1 and Figure 2 As shown, as a preferred embodiment of the present invention, the main power module 1 includes an a terminal, a b terminal, a c terminal and a d terminal, the two ends of the pre-charge module 2 are electrically connected to the a terminal and the c terminal of the main power module 1 respectively, the two ends of the discharge module 3 are electrically connected to the c terminal and the d terminal of the main power module 1 respectively, and the c terminal and the d terminal of the main power module 1 are electrically connected to the two ends of the load respectively.

[0055] The main power module 1 adopts a high-power mechanical switch, and the pre-charge module 2 includes a solid-state power switch and a current limiting resistor. The solid-state power switch is electrically connected to the current limiting resistor, the solid-state power switch is electrically connected to the a end of the main power module 1, and the current limiting resistor is electrically connected to the c end of the main power module 1.

[0056] The high-power mechanical switch and the solid-state power switch are connected in parallel.

[0057] The solid-state power switch uses a semiconductor power transistor switch. The pre-charge resistor is simulated by utilizing the impedance characteristics of the semiconductor power transistor switch in the saturation region (when the transistor base current increases to a certain level, the collector current no longer increases with the base current, but remains relatively constant near a certain value. At this point, the transistor loses its current amplification function and enters a saturated state. When saturated, both the transistor's emitter and collector junctions are at a forward voltage). By controlling the semiconductor power transistor switch, controllable pre-charging of the high-voltage line equivalent capacitance is achieved.

[0058] The circuit operation of the load, main power module 1, pre-charge module 2 and discharge module 3 is as follows:

[0059] 1. When the load needs to work, the high-power mechanical switch of the main power module 1 is disconnected, and the solid-state power switch in the pre-charge module 2 is closed, and the current is charged through the pre-charge module 2;

[0060] 2. When the load stops working, the high-power mechanical switch of the main power module 1 is disconnected, and the load charge is discharged through the discharge module 3;

[0061] 3. When the load is working, the high-power mechanical switch of the main power module 1 is closed, and the current only passes through the main power module 1, while the pre-charge module 2 and the discharge module 3 are both disconnected.

[0062] Embodiment 3: In some embodiments, as Figure 3 As shown, as a preferred embodiment of the present invention, a working method of an electric aircraft power load controller system includes the following steps:

[0063] Step 1: High-voltage electrical equipment is powered through the busbar;

[0064] Step 2: The monitoring control module 4 receives instructions through external communication to determine whether the high-voltage electrical equipment needs to work;

[0065] Step 3: If the high-voltage electrical equipment needs to work, the solid-state power switch in the pre-charge module 2 is closed, and the busbar supplies power to the capacitor in the high-voltage electrical equipment through the current-limiting resistor in the pre-charge module 2;

[0066] If the high-voltage electrical equipment does not need to work, the thread is terminated directly;

[0067] Step 4: After the busbar supplies power to the capacitor in the high-voltage electrical equipment through the current-limiting resistor in the pre-charge module 2, the monitoring and control module 4 determines whether the pre-charge capacitor voltage in the pre-charge module 2 reaches the power supply threshold;

[0068] Step 5: If the pre-charge capacitor voltage does not reach the power supply threshold, return to step 3;

[0069] If the pre-charge capacitor voltage reaches the power supply threshold, the solid-state power switch in the pre-charge module 2 is disconnected, the high-power mechanical switch in the main power module 1 is closed, and the busbar directly charges the high-voltage electrical equipment;

[0070] Step 6: After the busbar directly charges the high-voltage electrical equipment, the monitoring and control module 4 receives instructions through external communication to determine whether the high-voltage electrical equipment has stopped working;

[0071] Step 7: If the high-voltage electrical equipment continues to work, return to step 5;

[0072] Step 8: If the high-voltage electrical equipment stops working, the capacitor or inductor in the high-voltage electrical equipment is discharged through the discharge module 3, and then the thread ends.

[0073] Embodiment 4: In some embodiments, as Figure 4 As shown, attached Figure 4 This figure describes a DC high-voltage power grid for electric aircraft, including the energy transmission path from the power battery to the motor. The figure only shows a typical end-to-end power supply link and does not involve the overall power grid architecture. It is only for the purpose of illustrating typical application scenarios and is not limited to this type of power grid.

[0074] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the same. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements will not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims

1. An electric aircraft power load controller system, characterized in that: Includes the following sections: A main power module (1) is used for controlling the switching on or off of the high-voltage direct current grid; A pre-charge module (2) is used to slowly charge the equivalent capacitor or pre-charge it with a relatively small current to prevent the system or load from being impacted or damaged by a transient large current; The discharge module (3) gradually reduces the load voltage to a safe level by first releasing the electric energy stored in the equivalent capacitor, thereby ensuring that the charge on the load is safely released, thereby avoiding the generation of high voltage or arc when disconnecting; A monitoring control module (4) collects status parameters of the main power module (1), the pre-charge module (2), the discharge module (3) and the power module (5), controls the working status of each module according to the command of the aircraft, and stores and reports the equipment status; A power supply module (5) is used to receive multiple redundant electric energies and supply power to the monitoring and control module (4); The terminal (7) is used to issue control instructions of the aircraft to the monitoring and control module (4) and receive the device status uploaded by the monitoring and control module (4); A communication module (6) for monitoring information transmission between the control module (4) and the terminal (7); The monitoring and control module (4) is electrically connected to the communication module (6), and the communication module (6) is wirelessly connected to the terminal (7); The power supply module (5) is electrically connected to the monitoring and control module (4), the main power module (1) is electrically connected to the pre-charging module (2) and the discharge module (3), and the monitoring and control module (4) is electrically connected to the main power module (1), the pre-charging module (2), and the discharge module (3).

2. The electric aircraft power load controller system according to claim 1, characterized in that: The main power module (1) comprises an end a, an end b, an end c and an end d; the two ends of the pre-charge module (2) are respectively electrically connected to the end a and the end c of the main power module (1); the two ends of the discharge module (3) are respectively electrically connected to the end c and the end d of the main power module (1); and the end c and the end d of the main power module (1) are respectively electrically connected to the two ends of the load.

3. The electric aircraft power load controller system according to claim 2, characterized in that: The main power module (1) adopts a high-power mechanical switch.

4. The electric aircraft power load controller system according to claim 3, characterized in that: The pre-charge module (2) comprises a solid-state power switch and a current-limiting resistor, the solid-state power switch is electrically connected to the current-limiting resistor, the solid-state power switch is electrically connected to the A end of the main power module (1), and the current-limiting resistor is electrically connected to the C end of the main power module (1).

5. The electric aircraft power load controller system according to claim 4, characterized in that: The high-power mechanical switch and the solid-state power switch are connected in parallel.

6. The electric aircraft power load controller system according to claim 5, characterized in that: The high-power mechanical switch adopts a contactor or a relay.

7. The electric aircraft power load controller system according to claim 6, characterized in that: The solid-state power switch adopts a semiconductor power triode switch.

8. A method for operating an electric aircraft power load controller, used in the electric aircraft power load controller system according to claim 7, characterized in that: The following steps are involved: Step 1: High-voltage electrical equipment is powered through the busbar; Step 2: The monitoring control module (4) receives instructions through external communication to determine whether the high-voltage electrical equipment needs to work; Step 3: If the high-voltage electrical equipment needs to work, the solid-state power switch in the pre-charging module (2) is closed, and the busbar supplies power to the capacitor in the high-voltage electrical equipment through the current-limiting resistor in the pre-charging module (2); If the high-voltage electrical equipment does not need to work, the thread is terminated directly; Step 4: After the busbar supplies power to the capacitor in the high-voltage electrical equipment through the current-limiting resistor in the pre-charge module (2), the monitoring control module (4) determines whether the pre-charge capacitor voltage in the pre-charge module (2) reaches the power supply threshold; Step 5: If the pre-charge capacitor voltage does not reach the power supply threshold, return to step 3; If the pre-charge capacitor voltage reaches the power supply threshold, the solid-state power switch in the pre-charge module (2) is disconnected, the high-power mechanical switch in the main power module (1) is closed, and the busbar directly charges the high-voltage electrical equipment; Step 6: After the busbar directly charges the high-voltage electrical equipment, the monitoring control module (4) receives instructions through external communication to determine whether the high-voltage electrical equipment has stopped working; Step 7: If the high-voltage electrical equipment continues to work, return to step 5; Step 8: If the high-voltage electrical equipment stops working, the capacitor or inductor in the high-voltage electrical equipment is discharged through the discharge module (3), and then the thread ends.

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