A power management device for unmanned aerial vehicles

Abstract

This utility model belongs to the field of UAV battery management technology, specifically relating to a UAV power management device, including a PCB substrate with an integrated mechanical mounting structure; a power management circuit, integrated on the PCB substrate, including a reverse connection and surge protection circuit, an overvoltage and overcurrent protection circuit, a voltage and current detection circuit, and a multi-channel DC / DC output circuit; the reverse connection and surge protection circuit prevents reverse connection of the battery and suppresses surge impact; the overvoltage and overcurrent protection circuit shuts down the output when the voltage or current is abnormal; the voltage and current detection circuit monitors the voltage and current values ​​in real time; the multi-channel DC / DC output circuit converts the input battery voltage into at least two different DC voltage levels to supply different avionics equipment. This utility model solves the problems of scattered protection functions and low integration through the integrated design of multiple protection functions.

Description

Technical Field

[0001] This utility model belongs to the field of drone battery management technology, specifically relating to a drone power management device. Background Technology

[0002] With the rapid development of drone technology and the continuous expansion of its application fields, the application scenarios of drones are becoming increasingly diverse, placing higher demands on drone safety, especially in terms of power management technology. Currently, drones generally use power batteries for direct power supply, but existing drone power systems have the following problems: (1) Low integration and insufficient reliability caused by dispersed protection functions: Existing UAV power systems usually disperse protection functions such as reverse connection protection, surge protection, overvoltage and overcurrent protection as independent circuits or modules. Each functional module needs to occupy PCB space, connection lines and debugging interfaces separately, resulting in complex circuit layout and increased risk of signal interference. At the same time, the dispersed protection mechanisms are difficult to work together, the consistency of protection thresholds and response speed are limited, which reduces the overall reliability of the power system.

[0003] (2) The contradiction between low circuit integration and insufficient space utilization: Traditional power management circuits require additional configuration of multiple chips, passive components and connecting devices due to the separation of functional modules, resulting in a large PCB area; while the internal space of the UAV fuselage is limited, the dispersed circuit layout further compresses the space for other avionics equipment or batteries, which cannot meet the design requirements of high integration and miniaturization, and seriously restricts the functional expansion capability of the UAV.

[0004] (3) Poor installation compatibility and structural redundancy: Most existing power modules are independent functional units, and their size and interface form are poorly compatible with the structure of the UAV body. Additional installation brackets or adjustments to the body structure are required to fix the modules, which increases the assembly complexity and time cost. In addition, the connecting cables and interfaces between modules are easily loosened due to environmental factors such as vibration and impact, which further reduces the stability of the system.

[0005] (4) Weight and volume redundancy caused by power supply requirements of multiple devices: For different avionics devices (such as flight control, sensors, and image transmission modules), the existing solution requires separate power conversion modules, resulting in redundancy in the number of power management components. The superposition of these redundant modules significantly increases the overall weight and volume of the UAV, which not only reduces the endurance but also limits the payload capacity, which is contrary to the development trend of UAVs being lightweight and efficient.

[0006] Therefore, there is a need for a power management device for unmanned aerial vehicles (UAVs) that can integrate multiple protection functions, achieve integrated structural design, improve space utilization, and reduce system weight. Summary of the Invention

[0007] Purpose of the invention: The purpose of this utility model is to address the shortcomings of existing technologies by providing a power management device for unmanned aerial vehicles (UAVs). Through the integrated design of multiple protection functions, the integrated layout of the structure, and the optimization of compatibility for power supply to multiple devices, it systematically solves the technical problems of scattered protection functions, low integration, weight redundancy, and structural functional fragmentation in existing technologies, providing UAVs with a highly reliable, lightweight, and space-efficient power management solution.

[0008] Technical solution: The UAV power management device of this utility model includes: A PCB substrate, on which a mechanical mounting structure is integrated; The power management circuit is integrated on the PCB substrate, including reverse connection protection and surge protection circuit, overvoltage and overcurrent protection circuit, voltage and current detection circuit and multi-channel DC / DC output circuit. The reverse connection and surge protection circuit is connected to the input terminal of the power battery to prevent reverse connection and suppress surge impact; the overvoltage and overcurrent protection circuit is connected to the output terminal of the reverse connection and surge protection circuit to shut down the output when the voltage or current is abnormal; the voltage and current detection circuit is connected to the reverse connection and surge protection circuit to monitor the voltage and current values ​​in real time; and the multi-channel DC / DC output circuit is connected to the output terminal of the overvoltage and overcurrent protection circuit to convert the input battery voltage into at least two different DC voltage levels to supply different avionics equipment.

[0009] To further improve the above technical solution, the middle part of the PCB substrate is the circuit layout area of ​​the power management circuit, and the mechanical mounting structure includes arm mounting holes set on the edge of the PCB substrate, inter-board connection slots for engaging and fixing with the upper plate of the machine body, and leg mounting holes. The synchronous assembly of electrical connection and mechanical fixation is achieved through the cooperation of the circuit layout area and the mechanical mounting structure.

[0010] Furthermore, the reverse connection and surge protection circuit includes a sampling resistor R1, a PMOS transistor Q1, a Zener diode D1, resistors R2 and R3, and a TVS transient diode D2. The sampling resistor R1 is connected in series between the positive terminal of the power battery and the main circuit. The drain (D) of the PMOS transistor Q1 is connected to the rear end of the sampling resistor R1, the source (S) is connected to the positive terminal of the battery, and the gate (G) is grounded through the resistor R3. The Zener diode D1 and the resistor R2 are connected in parallel between the source (S) and gate (G) of the PMOS transistor Q1. The TVS transient diode D2 is connected in parallel between the positive terminal of the power battery and ground to suppress surges; the gate-source voltage of the PMOS transistor Q1 is controlled by the polarity of the power battery to cut off the main circuit when the power battery is reversed; the resistor R3 is connected in series between the gate of the PMOS transistor Q1 and ground to form a reverse connection protection control circuit.

[0011] Furthermore, the overvoltage and overcurrent protection circuit includes a resettable fuse F1, a PMOS transistor Q2, a Zener diode D3, a Zener diode D4, resistors R4, R5, R6, R7, and R8, a transistor Q3, and capacitors C1, C2, C3, C4, C5, and C6. The drain (D) of the PMOS transistor Q2 is connected to the input terminal of the subsequent circuit. The Zener diode D3, capacitor C1, and resistor R5 are connected in parallel between the gate (G) and source (S) of the PMOS transistor Q2. The collector of the transistor Q3 is connected to the gate (G) of the PMOS transistor Q2 through resistor R7, the base is connected to ground through resistor R6 and the Zener diode D4, and the emitter is connected to the output terminal of the reverse connection and surge protection circuit. The self-resetting fuse F1 is connected in series between the output terminal of the reverse connection and surge protection circuit and the source terminal of the PMOS transistor Q2 to achieve overcurrent protection; the capacitor C1 gradually turns on the PMOS transistor Q2 through the resistor-capacitor charging method to avoid the current surge at the moment of power-on.

[0012] Furthermore, the voltage and current detection circuit includes: The sampling resistor R1 is connected in series with the positive input terminal of the power battery; The detection chip U1 has its differential input pin connected in parallel across the sampling resistor R1 to acquire voltage and current signals. The SDA and SCL signal pins of the detection chip U1 are used to transmit the acquired voltage and current values ​​to the flight controller via the I2C protocol.

[0013] Furthermore, the multi-channel DC / DC output circuit includes a 5V output circuit, a 12V output circuit, and a 15V output circuit.

[0014] Furthermore, the 5V output circuit includes a power chip U2, capacitors C8, C9, C10, and C11, an inductor L1, and resistors R12 and R13. The input terminal of the power chip U2 is connected to the output terminal of the overvoltage and overcurrent protection circuit, and capacitors C8 and C9 are connected in parallel for input filtering. The output terminal of the power chip U2 is connected to the inductor L1 and resistor R12 to achieve 5V voltage conversion. Capacitors C10 and C11 are connected in parallel at the output terminal for output filtering and decoupling. Resistor R13 is used for current limiting. The 12V output circuit includes a power chip U3, capacitors C12, C13, C14, and C15, an inductor L2, and resistors R14, R15, R16, R17, and R18. The input terminal of the power chip U3 is connected to the output terminal of the overvoltage and overcurrent protection circuit, and capacitors C12 and C13 are connected in parallel for input filtering. The output terminal of the power chip U3 is connected to inductor L2, resistor R14, and capacitor C14 to achieve 12V voltage conversion. Resistor R16 and capacitor C15 are connected in parallel and then in series with resistor R18 at the output terminal to adjust the output voltage value. Resistor R15 is connected in series between the 12V output ground and ground. Resistor R17 is used for current limiting. The 15V output circuit includes a power chip U4, capacitors C16, C17, C18, and C19, an inductor L3, and resistors R19, R20, R21, R22, and R23. The input terminal of the power chip U4 is connected to the output terminal of the overvoltage and overcurrent protection circuit, and capacitors C16 and C17 are connected in parallel for input filtering. The output terminal of the power chip U4 is connected to inductor L3, resistor R19, and capacitor C18 to achieve 15V voltage conversion. Resistor R21 is connected in parallel with capacitor C19 and then in series with resistor R23 at the output terminal to adjust the output voltage value. Resistor R20 is connected in series between the 15V output ground and ground. Resistor R22 is used for current limiting.

[0015] Furthermore, each output terminal of the 5V output circuit, 12V output circuit, and 15V output circuit is connected in parallel with an LED indicator to indicate the normal operating status of the corresponding output channel.

[0016] Furthermore, the PCB substrate is made of FR-4 material.

[0017] Furthermore, at least one wiring layer of the PCB substrate is provided with a large copper area, which is thermally connected to the heat-generating element in the power management circuit, and heat dissipation is achieved by the PCB substrate itself.

[0018] Beneficial effects: Compared with the prior art, the advantages of this utility model are: (1) Significantly improved system reliability: Compared with the traditional solution where the protection functions such as reverse connection protection, surge protection, overvoltage and overcurrent protection are implemented by independent circuits or modules, this utility model integrates the above protection functions on the same power management board, and greatly improves the system reliability by optimizing the circuit layout.

[0019] (2) Space utilization and lightweight advantages: Compared with traditional power modules, which require separate PCB area and installation space due to their dispersed functions and require additional brackets for fixation, this utility model adopts an integrated circuit and structure design, directly incorporating the power management board as part of the chassis. This not only retains the circuit function but also replaces the structural components of the traditional chassis, saving internal space, effectively reducing the weight of the whole machine, and improving battery life.

[0020] (3) Comprehensive power supply compatibility: Compared with the existing technology where different avionics equipment needs to be configured with independent DC / DC modules, this utility model supports multiple voltage levels of 5V / 12V / 15V output through the integrated design of multi-channel DC / DC output circuits, and a single power management board can meet the power supply needs of all avionics equipment in the aircraft.

[0021] (4) Significantly improved maintenance convenience: Compared with traditional distributed power modules, which are susceptible to changes such as drone vibration due to multiple interfaces and long connecting lines, this utility model adopts an integrated structural design, with all circuit interfaces integrated into one power management board. The integrated design of the protection circuit makes fault detection more centralized. By monitoring the status indicator light of the power management board, the problem can be quickly located. During maintenance, there is no need to disassemble multiple modules, which greatly shortens the fault location time and reduces the repair and maintenance cost. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the structure of this utility model.

[0023] Figure 2 This is a schematic diagram of the reverse connection and surge protection circuit of this utility model.

[0024] Figure 3 This is a schematic diagram of the overvoltage and overcurrent protection circuit of this utility model.

[0025] Figure 4 This is a schematic diagram of the voltage and current detection circuit of this utility model.

[0026] Figure 5 This is a schematic diagram of the 5V output circuit of this utility model.

[0027] Figure 6 This is a schematic diagram of the 12V output circuit of this utility model.

[0028] Figure 7 This is a schematic diagram of the 15V output circuit of this utility model. Detailed Implementation

[0029] The technical solution of this utility model will be described in detail below with reference to the accompanying drawings, but the protection scope of this utility model is not limited to the described embodiments.

[0030] Example 1: This utility model provides a power management device for unmanned aerial vehicles with multiple protections and integrated structure, mainly including integrated structural design, reverse connection and surge protection circuit, overvoltage and overcurrent protection circuit, voltage and current detection circuit and multi-channel DC / DC output circuit.

[0031] like Figure 1 As shown, the core carrier of the integrated structural design is an FR-4 PCB substrate, whose functional layer and mechanical structure layer are deeply integrated. The front edge of the PCB substrate has mounting holes for the drone's carbon fiber arms; the bottom has mounting holes for the landing gear; there are fixing slots between the boards for securing it to the upper carbon fiber plate of the drone body; and there are also solder points for the power battery input. The circuit layout is located in the central area of ​​the PCB substrate, with the power management core circuitry on the front and a large copper area on the back to aid in heat dissipation for heat-generating components.

[0032] like Figure 2 As shown, the reverse connection and surge protection circuit is designed to prevent damage to downstream circuitry from reverse battery connection and to suppress surge impact. A sampling resistor R1 is connected in series between the battery's positive terminal (BAT+) and the subsequent circuitry for current sampling; a TVS transient diode D2 is connected in parallel between BAT+ and GND to absorb surge energy; the drain (D) of PMOS transistor Q1 is connected to the rear of R1, the source (S) is connected to BAT+, and the gate (G) is grounded through resistor R3; a Zener diode D1 and resistor R2 are connected in parallel between the source (S) and gate (G) of Q1 to limit the gate-source voltage of Q1.

[0033] The reverse connection and surge protection circuit operates as follows: Under normal power supply, the battery BAT+ provides a positive bias voltage to the gate of Q1 through R2, Q1 conducts, and POUT+ outputs the 6S battery voltage. If the battery is reverse connected, i.e., BAT- is connected to the drain of Q1, the gate-source voltage of Q1 is reverse biased, Q1 is cut off, and the subsequent output is cut off. When a surge occurs, the TVS transient diode D2 quickly conducts to discharge energy, while D1 limits the gate-source voltage of Q1 to prevent Q1 from being mis-conducted.

[0034] like Figure 3 As shown, the overvoltage and overcurrent protection circuit shuts off the output to protect downstream devices when the POUT voltage or current is abnormal. A resettable fuse F1 is connected in series between POUT+ and the source (S) of PMOS transistor Q2. The drain (D) of PMOS transistor Q2 is connected to the downstream circuit input VIN+, and the gate (G) is grounded through resistors R7 and R8. A Zener diode D3, capacitor C1, and resistor R5 are connected in parallel between the gate (G) and source (S) of Q2. The collector of PNP transistor Q3 is connected to the gate (G) of Q2 through resistor R7, and the base of Q3 is connected to GND through resistor R6 and Zener diode D4. The emitter of Q3 is connected to the POUT terminal. Capacitors C2, C3, C4, C5, and C6 are used for filtering and decoupling. Zener diode D3 is used to protect the gate-source voltage of the PMOS transistor.

[0035] The overvoltage and overcurrent protection circuit operates as follows: When power is supplied, capacitor C1 charges, and the gate-source voltage of Q2 gradually increases to the conduction threshold, achieving a soft start. When the POUT current exceeds the maximum current of the resettable fuse F1, F1 blows, shutting off subsequent outputs and achieving overcurrent protection. When the POUT voltage is normal, Zener diode D4 is not reverse-biased, transistor Q3 is not conducting, PMOS transistor Q2 is conducting, and VIN+ is normal. When the POUT voltage exceeds the reverse breakdown voltage of Zener diode D4, transistor Q3 conducts, the gate and source voltages of PMOS transistor Q2 are equal, PMOS transistor Q2 is cut off, shutting off subsequent outputs and achieving overvoltage protection. After the fault is cleared, the resettable fuse F1 automatically resets, capacitor C1 is recharged, and the circuit returns to normal.

[0036] like Figure 4 As shown, the voltage and current detection circuit monitors the current and voltage values ​​in the circuit in real time and transmits them to the flight controller via the I2C protocol. Specifically, it includes a detection chip U1, model INA226. Pins 9 and 10 are connected in parallel across the sampling resistor R1. Pin 4 (SDA) is connected to the SDA pin of the flight controller via a series resistor R10, and pin 5 (SCL) is connected to the SCL pin of the flight controller via a series resistor R11, thus realizing the I2C protocol data transmission. Pull-up resistors R10 and R11 ensure that the I2C bus is at a high level when idle.

[0037] The working logic of the voltage and current detection circuit is as follows: the detection chip U1 converts the voltage signal of the sampling resistor R1 into an analog quantity, samples it through the internal ADC, transmits the current value through I2C, and monitors the transmitted voltage value through the voltage divider of the internal sampling resistor. The flight controller can then receive the current and voltage data in the circuit.

[0038] The multi-channel DC / DC output circuit converts the 6S battery voltage to 5V, 12V, and 15V to meet the needs of different avionics equipment.

[0039] like Figure 5 As shown, the 5V output circuit includes a power chip U2, with its input connected to VIN+ and parallel capacitors C8 and C9 for input filtering. The output is connected to inductor L1 and resistor R12. Capacitors C10 and C11 are used for output filtering and decoupling. LED1 is connected in series with resistor R13 and then in parallel to the 5V output. Resistor R13 is used for current limiting. Under normal conditions, the LED is lit.

[0040] like Figure 6As shown, the 12V output circuit includes a power chip U3, with its input connected to VIN+ and capacitors C12 and C13 connected in parallel for input filtering. The output is connected to inductor L2, resistor R14, and capacitor C14. Resistor R16 and capacitor C15 are connected in parallel and then in series with R18 at the output. Adjusting the resistance value adjusts the output voltage. Resistor R15 is connected in series between the 12V output ground and GND. LED2 is connected in series with resistor R17 and then in parallel to the 12V output. Resistor R17 is used for current limiting; the LED is lit under normal conditions.

[0041] like Figure 7 As shown, the 15V output circuit includes a power chip U4, with its input connected to VIN+ and capacitors C16 and C17 connected in parallel for input filtering. The output is connected to inductor L3, resistor R19, and capacitor C18. Resistor R21 and capacitor C19 are connected in parallel and then in series with R23 at the output. Adjusting the resistance value adjusts the output voltage. Resistor R20 is connected in series between the 15V output ground and GND. LED3 is connected in series with resistor R22 and then in parallel to the 15V output. Resistor R22 is used for current limiting; the LED is lit under normal conditions.

[0042] Overall operation: When the 6S lithium battery pack is connected via the positive and negative terminals, the reverse connection and surge protection circuit is activated first. The sampling resistor R1 monitors the current direction in real time. If reverse current is detected (i.e., the battery polarity is reversed), the gate voltage of the PMOS transistor Q1 is pulled low to ground, and Q1 quickly turns off, cutting off the output path and preventing reverse current from damaging the downstream circuitry. When a surge occurs, the TVS transient diode D2 quickly conducts to dissipate the surge energy. Simultaneously, the overvoltage and overcurrent protection circuit monitors the circuit current and voltage in real time to ensure they do not exceed the set maximum values ​​and includes a soft-start mechanism to prevent sudden current changes from damaging the equipment.

[0043] After the battery is connected and operating normally, the voltage and current detection circuit acquires current and voltage signals through the detection chip U1, processes them internally, and then transmits them to the flight controller via the I2C protocol. Furthermore, the multi-channel DC / DC output circuit converts the 6S battery voltage to the 5V, 12V, and 15V voltages commonly used in avionics equipment.

[0044] The present invention involves laying a large area of ​​copper on the back of the PCB substrate to conduct the heat of heat-generating components such as PMOS transistors and power chips to the chassis frame, and achieves passive heat dissipation by combining air convection.

[0045] As described above, although the present invention has been shown and described with reference to specific preferred embodiments, it should not be construed as limiting the present invention itself. Various changes in form and detail may be made to the present invention without departing from the spirit and scope of the appended claims.

Claims

1. A power management device for unmanned aerial vehicles (UAVs), characterized in that, include: A PCB substrate, on which a mechanical mounting structure is integrated; The power management circuit is integrated on the PCB substrate, including reverse connection protection and surge protection circuit, overvoltage and overcurrent protection circuit, voltage and current detection circuit and multi-channel DC / DC output circuit. The reverse connection and surge protection circuit is connected to the input terminal of the power battery to prevent reverse connection of the battery and suppress surge impact; the overvoltage and overcurrent protection circuit is connected to the output terminal of the reverse connection and surge protection circuit to shut down the output when the voltage or current is abnormal; the voltage and current detection circuit is connected to the reverse connection and surge protection circuit to monitor the voltage and current values ​​in real time. The multi-channel DC / DC output circuit is connected to the output terminal of the overvoltage and overcurrent protection circuit, and is used to convert the input battery voltage into DC levels of at least two different voltage values ​​to supply different avionics equipment.

2. The UAV power management device according to claim 1, characterized in that, The PCB substrate has a circuit layout area in the middle, which is the power management circuit. The mechanical mounting structure includes arm mounting holes on the edge of the PCB substrate, inter-board connection slots for engaging and fixing with the upper board of the machine body, and leg mounting holes. The electrical connection and mechanical fixation are assembled synchronously through the cooperation of the circuit layout area and the mechanical mounting structure.

3. The UAV power management device according to claim 1, characterized in that, The reverse connection and surge protection circuit includes a sampling resistor R1, a PMOS transistor Q1, a Zener diode D1, resistors R2 and R3, and a TVS transient diode D2. The sampling resistor R1 is connected in series between the positive terminal of the power battery and the main circuit. The drain (D) of the PMOS transistor Q1 is connected to the rear end of the sampling resistor R1, the source (S) is connected to the positive terminal of the battery, and the gate (G) is grounded through the resistor R3. The Zener diode D1 and the resistor R2 are connected in parallel between the source (S) and gate (G) of the PMOS transistor Q1. The TVS transient diode D2 is connected in parallel between the positive terminal of the power battery and ground to suppress surges; the gate-source voltage of the PMOS transistor Q1 is controlled by the polarity of the power battery to cut off the main circuit when the power battery is reversed; the resistor R3 is connected in series between the gate of the PMOS transistor Q1 and ground to form a reverse connection protection control circuit.

4. The UAV power management device according to claim 3, characterized in that, The overvoltage and overcurrent protection circuit includes a resettable fuse F1, a PMOS transistor Q2, a Zener diode D3, a Zener diode D4, resistors R4, R5, R6, R7, and R8, a transistor Q3, and capacitors C1, C2, C3, C4, C5, and C6. The drain (D) of the PMOS transistor Q2 is connected to the input terminal of the subsequent circuit. The Zener diode D3, capacitor C1, and resistor R5 are connected in parallel between the gate (G) and source (S) of the PMOS transistor Q2. The collector of the transistor Q3 is connected to the gate (G) of the PMOS transistor Q2 through resistor R7, the base is connected to ground through resistor R6 and the Zener diode D4, and the emitter is connected to the output terminal of the reverse connection and surge protection circuit. The self-resetting fuse F1 is connected in series between the output terminal of the reverse connection and surge protection circuit and the source terminal of the PMOS transistor Q2 to achieve overcurrent protection; the capacitor C1 gradually turns on the PMOS transistor Q2 through the resistor-capacitor charging method to avoid the current surge at the moment of power-on.

5. The UAV power management device according to claim 1, characterized in that, The voltage and current detection circuit includes: The sampling resistor R1 is connected in series with the positive input terminal of the power battery; The detection chip U1 has its differential input pin connected in parallel across the sampling resistor R1 to acquire voltage and current signals. The SDA and SCL signal pins of the detection chip U1 are used to transmit the acquired voltage and current values ​​to the flight controller via the I2C protocol.

6. The UAV power management device according to claim 1, characterized in that, The multi-channel DC / DC output circuit includes a 5V output circuit, a 12V output circuit, and a 15V output circuit.

7. The UAV power management device according to claim 6, characterized in that, The 5V output circuit includes a power chip U2, capacitors C8, C9, C10, and C11, an inductor L1, and resistors R12 and R13. The input terminal of the power chip U2 is connected to the output terminal of the overvoltage and overcurrent protection circuit, and capacitors C8 and C9 are connected in parallel for input filtering. The output terminal of the power chip U2 is connected to the inductor L1 and resistor R12 for 5V voltage conversion. Capacitors C10 and C11 are connected in parallel at the output terminal for output filtering and decoupling. Resistor R13 is used for current limiting. The 12V output circuit includes a power chip U3, capacitors C12, C13, C14, and C15, an inductor L2, and resistors R14, R15, R16, R17, and R18. The input terminal of the power chip U3 is connected to the output terminal of the overvoltage and overcurrent protection circuit, and capacitors C12 and C13 are connected in parallel for input filtering. The output terminal of the power chip U3 is connected to inductor L2, resistor R14, and capacitor C14 to achieve 12V voltage conversion. Resistor R16 and capacitor C15 are connected in parallel and then in series with resistor R18 at the output terminal to adjust the output voltage value. Resistor R15 is connected in series between the 12V output ground and ground. Resistor R17 is used for current limiting. The 15V output circuit includes a power chip U4, capacitors C16, C17, C18, and C19, an inductor L3, and resistors R19, R20, R21, R22, and R23. The input terminal of the power chip U4 is connected to the output terminal of the overvoltage and overcurrent protection circuit, and capacitors C16 and C17 are connected in parallel for input filtering. The output terminal of the power chip U4 is connected to inductor L3, resistor R19, and capacitor C18 to achieve 15V voltage conversion. Resistor R21 is connected in parallel with capacitor C19 and then in series with resistor R23 at the output terminal to adjust the output voltage value. Resistor R20 is connected in series between the 15V output ground and ground. Resistor R22 is used for current limiting.

8. The UAV power management device according to claim 7, characterized in that, Each output terminal of the 5V output circuit, 12V output circuit, and 15V output circuit is connected in parallel with an LED indicator to indicate the normal operating status of the corresponding output channel.

9. The UAV power management device according to claim 1, characterized in that, The PCB substrate is made of FR-4 material.

10. The UAV power management device according to claim 1, characterized in that, At least one wiring layer of the PCB substrate has a large copper area, which is thermally connected to the heat-generating element in the power management circuit, and the PCB substrate body is used for heat dissipation.

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