Miniature unmanned aerial vehicle power supply management system

Abstract

The invention relates to the field of unmanned aerial vehicle control systems, in particular to a miniature unmanned aerial vehicle power supply management system, which comprises a single-chip microcomputer minimum system used for controlling the on-off of a circuit and communicating with a flight control computer; the voltage reduction circuit is used for reducing the voltage of the output end of the airborne battery, then supplying power to the single-chip microcomputer minimum system and supplying power to the flight control computer and the electronic speed regulator through the voltage driving circuit; the voltage driving circuit is used for supplying power to the flight control computer and the electronic speed regulator; the serial port communication circuit is used for realizing communication between the single-chip microcomputer minimum system and a flight control computer; the switching circuit is used for inputting a key signal to the single chip microcomputer minimum system; and the electric quantity measuring circuit is used for acquiring voltage data of the airborne battery in real time. Through modular design and domestic component application, a miniature unmanned aerial vehicle power supply management system integrating power supply control, one-key power-on and power-off, electric quantity monitoring and communication interaction is constructed.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) control systems, and more specifically to a power management system for a micro unmanned aerial vehicle (UAV). Background Technology

[0002] Amidst the global technological revolution and industrial transformation, the low-altitude economy, as a strategic emerging industry, is experiencing explosive growth. According to authoritative forecasts, the global low-altitude economy market will exceed one trillion US dollars by 2030, with the drone industry serving as a core pillar, boasting an average annual compound growth rate exceeding 30%. Drone technology is expanding from traditional aerial photography and agricultural plant protection to broader application scenarios, including urban logistics, emergency rescue, and public safety monitoring.

[0003] Miniaturization of unmanned aerial vehicles (UAVs) is a significant trend in current technological development. Micro-UAVs, with their small size, light weight, and high maneuverability, demonstrate unique technological advantages and cost-effectiveness in the consumer market, military reconnaissance, indoor operations, and portable missions. Especially in the military field, micro-UAVs can perform tasks such as covert reconnaissance and target location, becoming an important component of modern combat systems.

[0004] The avionics system is a core component of unmanned aerial vehicles (UAVs), responsible for flight control, navigation, communication, mission execution, and data management. With the miniaturization, intelligence, and multi-functionality of UAVs, avionics systems are also becoming increasingly modular, lightweight, and domestically produced. However, current power management systems for micro-UAVs still face the following technical bottlenecks: Outdated power control methods: Traditional drone power management often uses mechanical switches or simple electronic switches, which cannot achieve one-button power-on / off functionality, are cumbersome to operate, and have low reliability. In complex environments, mechanical switches are prone to problems such as poor contact and wear, affecting the normal operation of the drone.

[0005] Lack of intelligent monitoring and communication capabilities: Most micro-drone power management systems only have basic power supply functions and cannot monitor parameters such as battery voltage and current in real time, nor can they communicate with the flight control computer. When the battery power is low, they cannot issue early warning information in time, resulting in delayed return to base and increasing flight risks.

[0006] Low localization rate of components: In the process of military research and development, the requirements for independent control of components are increasing. However, the power management systems of some micro-drones still rely on imported components, posing a supply chain security risk. Summary of the Invention

[0007] To address the aforementioned issues, a micro UAV power management system is provided. Through modular design and the application of domestically produced components, a micro UAV power management system integrating power supply control, one-button power-on / off, power monitoring, and communication interaction is constructed.

[0008] To address the problems of existing technologies, this invention provides a power management system for micro unmanned aerial vehicles (UAVs), electrically connected to the onboard power supply and providing power to the flight control computer and electronic speed controller of the micro UAV, comprising: The microcontroller minimum system is used to control the on / off state of the circuit and communicate with the flight control computer. The step-down circuit is used to step down the output voltage of the airborne battery to power the minimum system of the microcontroller and to power the flight control computer and electronic speed controller via the voltage drive circuit. Voltage drive circuit, used to supply power to the flight control computer and electronic speed controller; The serial communication circuit is used to enable communication between the microcontroller minimum system and the flight control computer. A switching circuit is used to input key signals to the microcontroller minimum system. A power measurement circuit is used to collect real-time voltage data of the onboard battery. The charging circuit is used to charge the onboard battery.

[0009] In some examples of the present invention, the input terminal of the step-down circuit is connected to the voltage output terminal of the airborne battery, and the output terminal of the step-down circuit is connected to the voltage input terminal of the voltage drive circuit and the voltage input terminal of the microcontroller minimum system, respectively.

[0010] In some examples of the present invention, the input terminal of the power measurement circuit is electrically connected to the onboard battery, and the output terminal of the power measurement circuit is electrically connected to the microcontroller minimum system.

[0011] In some examples of the present invention, the signal input terminal of the voltage drive circuit is connected to the microcontroller minimum system, and the voltage output terminal of the voltage drive circuit is connected to the voltage input terminal of the flight control computer and the voltage input terminal of the electronic speed controller, respectively.

[0012] In some examples of the present invention, the serial communication circuit realizes the communication connection between the flight control computer and the microcontroller minimum system through TTL signals, and is used for information transmission and control between the flight control computer and the microcontroller minimum system.

[0013] In some examples of the present invention, the microcontroller minimum system uses HC32L130F8UA as the core processor.

[0014] In some examples of the present invention, the step-down circuit includes a first-stage step-down circuit and a second-stage step-down circuit, wherein the first-stage step-down circuit reduces the voltage of the onboard battery's output terminal to 5V as the input voltage of the second-stage step-down circuit, and the second-stage step-down circuit reduces the 5V voltage to 3.3V as the input voltage of the microcontroller's minimum system.

[0015] In some examples of the present invention, the first-stage buck circuit includes a DC-DC buck chip that outputs a voltage of up to 38V to power the flight control computer and electronic speed controller.

[0016] In some examples of the present invention, the switching circuit includes a push-button switch and an NMOS transistor. The gate of the NMOS transistor is connected to the PWR_EN pin of the microcontroller in the minimum system of the microcontroller. The drain of the NMOS transistor is connected to the second pin of the push-button switch and to the KEY_ON pin of the microcontroller through a first diode. The first pin of the push-button switch is connected to the voltage output terminal of the airborne power supply.

[0017] In some examples of the present invention, the switching circuit further includes an OR gate circuit composed of a first diode and a second diode, wherein the anode of the first diode is connected to the second pin of the push-button switch, the cathode of the first diode is connected to the OPEN_EN pin of the DC-DC step-down chip, the anode of the second diode is connected to the PWR_EN pin of the microcontroller, and the cathode of the second diode is connected to the OPEN_EN pin of the DC-DC step-down chip.

[0018] The advantages of this invention compared to the prior art are: (1) Improved ease of operation This invention enables one-button power-on / off functionality, allowing users to easily turn the drone's power on and off with a simple button press, eliminating the need for complex setup or specialized knowledge. This design significantly simplifies the user experience, lowers the barrier to entry, and makes it easy for even beginners to use. Furthermore, the one-button operation reduces the possibility of accidental operation, improving the system's reliability and security.

[0019] (2) Intelligent monitoring and early warning By integrating a power measurement unit and a serial communication circuit, this invention enables real-time monitoring and intelligent early warning of battery power. The system can promptly detect low battery levels and issue warning messages to the operator via the flight control computer. This allows the operator to take timely measures, such as arranging for the drone to return to base, avoiding accidents caused by battery depletion, and ensuring the successful completion of flight missions.

[0020] (3) Improved charging convenience The inclusion of a dedicated external charging port allows users to charge the drone without removing the battery. This design not only saves time and effort but also reduces the risk of damage from frequent battery removal. Users can conveniently recharge the drone at any time, improving its efficiency and flexibility.

[0021] (4) Localization ensures supply chain security By employing domestically produced microcontrollers and components, the system achieves complete independent control, avoiding reliance on imported components. This not only reduces supply chain risks but also improves system security and reliability. In fields such as military R&D where high levels of independent control over components are required, this invention has significant application value.

[0022] (5) Flexibility of power supply control for multiple devices The voltage-driven circuit design enables the system to independently control the power supply status of multiple devices. Users can flexibly turn the power on or off of different devices according to actual needs, achieving precise control of the drone's functions. This design improves the system's flexibility and scalability, meeting the usage requirements in different scenarios. Attached Figure Description

[0023] Figure 1 This is a flowchart illustrating the power management system for a micro unmanned aerial vehicle (UAV) according to the present invention. Figure 2 This is a circuit diagram of a step-down circuit in a power management system for a micro unmanned aerial vehicle (UAV) according to the present invention. Figure 3 This is a circuit diagram of a switching circuit in a power management system for a micro unmanned aerial vehicle (UAV) according to the present invention. Figure 4 This is a circuit diagram of a voltage drive circuit in a power management system for a micro unmanned aerial vehicle (UAV) according to the present invention. Figure 5 This is a circuit diagram of the power detection circuit in a power management system for a micro unmanned aerial vehicle (UAV) according to the present invention. Detailed Implementation To further understand the features, technical means, and specific objectives and functions achieved by the present invention, the present invention will be described in further detail below with reference to the accompanying drawings and specific embodiments.

[0024] Reference Figure 1 The illustrated power management system for a micro unmanned aerial vehicle (UAV) is electrically connected to the onboard power supply and provides power to the UAV's flight control computer and electronic speed controller (and also includes power for such...). Figure 1The smoke generator shown (which powers the device or other peripherals) includes: a microcontroller minimum system for controlling circuit switching and communicating with the flight control computer; a step-down circuit for stepping down the output voltage of the airborne battery to power the microcontroller minimum system and for powering the flight control computer and electronic speed controller via a voltage drive circuit; a voltage drive circuit for powering the flight control computer and electronic speed controller; a serial communication circuit for enabling communication between the microcontroller minimum system and the flight control computer; a switch circuit for inputting button signals to the microcontroller minimum system; a power measurement circuit for real-time acquisition of airborne voltage data; and a charging circuit for charging the airborne battery.

[0025] Specifically, the input terminal of the step-down circuit is connected to the voltage output terminal of the airborne battery, and the output terminal of the step-down circuit is connected to the voltage input terminal of the voltage drive circuit and the voltage input terminal of the microcontroller minimum system.

[0026] Specifically, the input terminal of the power measurement circuit is electrically connected to the onboard battery, and the output terminal of the power measurement circuit is electrically connected to the microcontroller minimum system.

[0027] Specifically, the signal input terminal of the voltage drive circuit is connected to the microcontroller minimum system, and the voltage output terminal of the voltage drive circuit is connected to the voltage input terminal of the flight control computer and the voltage input terminal of the electronic speed controller, respectively.

[0028] Specifically, the serial communication circuit uses TTL signals to establish a communication connection between the flight control computer and the microcontroller minimum system, which is used for information transmission and control between the flight control computer and the microcontroller minimum system.

[0029] Specifically, the microcontroller minimum system uses HC32L130F8UA as the core processor.

[0030] In some examples of the present invention, reference is made to Figure 2 As shown, the step-down circuit includes a step-down circuit and a secondary step-down circuit. The step-down circuit reduces the voltage of the onboard battery's output terminal to 5V as the input voltage of the secondary step-down circuit, and the secondary step-down circuit reduces the 5V voltage to 3.3V as the input voltage of the microcontroller's minimum system.

[0031] In some examples of the present invention, the first-stage buck circuit includes a DC-DC buck chip that outputs a voltage of up to 38V to power the flight control computer and electronic speed controller.

[0032] Specifically, the step-down circuit unit is a two-stage step-down circuit: first, the onboard battery voltage is stepped down to 5V by the circuit composed of DC-DC step-down chip 2, and the selected chip supports a wide voltage input of up to 38V; then, it is transformed into 3.3V by the LDO circuit composed of linear regulator 3 to meet the normal operating voltage of the microcontroller minimum system.

[0033] In some examples of the present invention, reference is made to Figure 3 As shown, the switching circuit includes a push-button switch and an NMOS transistor. The gate of the NMOS transistor is connected to the PWR_EN pin of the microcontroller in the minimum system of the microcontroller. The drain of the NMOS transistor is connected to the second pin of the push-button switch and to the KEY_ON pin of the microcontroller through the first diode. The first pin of the push-button switch is connected to the voltage output terminal of the airborne power supply.

[0034] In some examples of the present invention, the switching circuit further includes an OR gate circuit composed of a first diode and a second diode, wherein the anode of the first diode is connected to the second pin of the push-button switch, the cathode of the first diode is connected to the OPEN_EN pin of the DC-DC step-down chip, the anode of the second diode is connected to the PWR_EN pin of the microcontroller, and the cathode of the second diode is connected to the OPEN_EN pin of the DC-DC step-down chip.

[0035] For details, please refer to Figure 3 To enable the one-button power-on / off function of the switch control board, a switch control hardware circuit was built. The P1 interface is a push-button switch, Q1 is an NMOS transistor, POWER_INPUT is the battery voltage, KEY_ON is the microcontroller input pin, PWR_EN is the microcontroller output pin, configured as push-pull output, and OPEN_EN is the enable pin of the DC-DC step-down chip RY8411. The first diode D4 and the second diode D7 form an OR gate circuit. As long as either diode outputs a high level, OPEN_EN will output a high level, thereby enabling the step-down circuit to work and output the voltage required for the microcontroller to operate normally.

[0036] Specifically, when the button is pressed, the onboard battery voltage is output to the RY8411 enable pin through the first diode D4. At this time, the buck circuit starts working, outputting a corresponding 3.3V voltage to supply the microcontroller, powering on the microcontroller. The gate of NMOS transistor Q1 detects a high level. According to the high-level conduction characteristic of NMOS transistors, NMOS transistor Q1 is in the conducting state at this time, and the 3.3V voltage is grounded through NMOS transistor Q1. The microcontroller's KEY_ON pin detects a low level. When the KEY_ON pin is low, PWR_EN outputs a high level. At this time, the second diode D7 conducts, and the OPEN_EN pin outputs a high level. Even if the button is released, the first diode D4 turns off, and the buck circuit can still work normally, realizing the one-button power-on function. When the circuit is powered on, if the switch is pressed again, the microcontroller's input pin KEY_ON detects a low level, and the output pin PWR_EN outputs a low level. At this time, releasing the button turns off the circuit, realizing the power-off function.

[0037] See Figure 4 In the voltage drive circuit, since the input voltage is much higher than the microcontroller output voltage, the voltage drive circuit adopts a combination of NMOS and PMOS. The voltage drive circuit has three voltage output interfaces. When it is necessary to output voltage to external devices such as flight control computers, electronic speed controllers and smoke generators, a high level is output through the microcontroller's I / O port. After the NMOS is turned on, the gate voltage of the PMOS is pulled low, thereby turning on the PMOS and realizing the battery voltage output. Each power output interface can achieve a maximum current output of 30A.

[0038] To enable real-time monitoring of the onboard battery voltage during drone operations, a power detection circuit is designed. (See [reference needed]). Figure 5 If the onboard battery voltage is lower than the nominal voltage, it can promptly report this to the flight control computer, allowing the pilot more operational space. The I / O port and ADC are connected to the microcontroller pins. POWER_INPUT represents the battery voltage. When the microcontroller controls the I / O port to output a high level, based on the high-level conduction characteristic of NMOS transistors, both NMOS transistors are in the conducting state, allowing the microcontroller's ADC to acquire the voltage normally. When the microcontroller controls the I / O port to output a low level, both NMOS transistors are in the off state, and the ADC acquisition function is disabled. At this time, the leakage current is only 1uA, resulting in extremely low power consumption. To further reduce circuit power consumption, a fixed interval can be set to enable the circuit's voltage acquisition function.

[0039] When in use, the circuit board powers on when the button is pressed for less than 3 seconds. This paper directly sets the microcontroller to drive the MOSFET to open the interface voltage for the electronic speed controller and flight control computer when it powers on, thus powering these two devices. At the same time, the flight control computer can be controlled to send communication commands to the microcontroller minimum system at any time during the UAV's flight to open the voltage interface of the smoke generator, so that the smoke generator can work normally.

[0040] When the circuit board is powered on, the power measurement circuit starts working, collecting battery power data in real time and determining whether the voltage is lower than the battery's nominal voltage. If it is lower, the data is sent to the flight controller via serial port and then transmitted to the pilot via radio or data link, prompting the pilot to end the flight mission.

[0041] When the device is powered on, if the button is pressed for more than 3 seconds, the microcontroller will shut down the power chip enable pin, cut off the voltage output, and complete the power-off process.

[0042] The above embodiments only illustrate one or more implementations of the present invention, and their descriptions are relatively specific and detailed, but they should not be construed as limiting the scope of the present invention. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these all fall within the protection scope of the present invention. Therefore, the protection scope of the present invention should be determined by the appended claims.

Claims

1. A power management system for a micro unmanned aerial vehicle (UAV), electrically connected to an onboard power supply and providing power to the flight control computer and electronic speed controller of the micro UAV, characterized in that, include: The microcontroller minimum system is used to control the on / off state of the circuit and communicate with the flight control computer. The step-down circuit is used to step down the output voltage of the airborne battery to power the minimum system of the microcontroller and to power the flight control computer and electronic speed controller via the voltage drive circuit. Voltage drive circuit, used to supply power to the flight control computer and electronic speed controller; The serial communication circuit is used to enable communication between the microcontroller minimum system and the flight control computer. A switching circuit is used to input key signals to the microcontroller minimum system. The power measurement circuit is used to collect onboard voltage data in real time. The charging circuit is used to charge the onboard battery.

2. The power management system for a micro unmanned aerial vehicle (UAV) according to claim 1, characterized in that, The input terminal of the step-down circuit is connected to the voltage output terminal of the airborne battery, and the output terminal of the step-down circuit is connected to the voltage input terminal of the voltage drive circuit and the voltage input terminal of the microcontroller minimum system.

3. The power management system for a micro unmanned aerial vehicle (UAV) according to claim 1, characterized in that, The input terminal of the power measurement circuit is electrically connected to the onboard battery, and the output terminal of the power measurement circuit is electrically connected to the microcontroller minimum system.

4. A power management system for a micro unmanned aerial vehicle (UAV) according to claim 1, characterized in that, The signal input terminal of the voltage drive circuit is connected to the minimum system of the microcontroller, and the voltage output terminal of the voltage drive circuit is connected to the voltage input terminal of the flight control computer and the voltage input terminal of the electronic speed controller, respectively.

5. A power management system for a micro unmanned aerial vehicle (UAV) according to claim 1, characterized in that, The serial communication circuit uses TTL signals to establish a communication connection between the flight control computer and the microcontroller minimum system, and is used for information transmission and control between the flight control computer and the microcontroller minimum system.

6. A power management system for a micro unmanned aerial vehicle (UAV) according to claim 1, characterized in that, The microcontroller minimum system uses HC32L130F8UA as the core processor.

7. A power management system for a micro unmanned aerial vehicle (UAV) according to any one of claims 1-6, characterized in that, The step-down circuit includes a step-down circuit and a secondary step-down circuit. The step-down circuit reduces the voltage at the output terminal of the onboard battery to 5V as the input voltage of the secondary step-down circuit, and the secondary step-down circuit reduces the 5V voltage to 3.3V as the input voltage of the microcontroller minimum system.

8. A power management system for a micro unmanned aerial vehicle (UAV) according to claim 7, characterized in that, The first-stage step-down circuit includes a DC-DC step-down chip, which outputs a voltage of up to 38V to power the flight control computer and electronic speed controller.

9. A power management system for a micro unmanned aerial vehicle (UAV) according to claim 8, characterized in that, The switching circuit includes a push-button switch and an NMOS transistor. The gate of the NMOS transistor is connected to the PWR_EN pin of the microcontroller in the minimum system of the microcontroller. The drain of the NMOS transistor is connected to the second pin of the push-button switch and to the KEY_ON pin of the microcontroller through the first diode. The first pin of the push-button switch is connected to the voltage output terminal of the airborne power supply.

10. A power management system for a micro unmanned aerial vehicle (UAV) according to claim 9, characterized in that, The switching circuit also includes an OR gate circuit composed of a first diode and a second diode. The anode of the first diode is connected to the second pin of the push-button switch, and the cathode of the first diode is connected to the OPEN_EN pin of the DC-DC step-down chip. The anode of the second diode is connected to the PWR_EN pin of the microcontroller, and the cathode of the second diode is connected to the OPEN_EN pin of the DC-DC step-down chip.

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