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CN-121984342-A - Reliable unmanned aerial vehicle system power supply control method

CN121984342ACN 121984342 ACN121984342 ACN 121984342ACN-121984342-A

Abstract

The invention discloses a reliable unmanned aerial vehicle system power supply control method. The method comprises the steps of responding to physical key triggering to generate a hardware triggering signal to start the system, outputting a software latching signal after the flight control main controller confirms that the hardware triggering signal is effective, combining the software latching signal and the system starting enabling signal through a diode or a logic circuit, setting a hardware forced shutdown circuit independent of the flight control main controller, directly cutting off a main power supply after the key is continuously triggered and overtime, and adopting a path management charging chip to realize intelligent power supply and charging management among an external power supply, a battery and the system. The invention realizes microampere standby power consumption, provides dual shutdown guarantee of software and hardware, supports intelligent charging in the machine, has anti-interference reliable starting-up capability, and improves the safety, reliability and user experience of the unmanned aerial vehicle system.

Inventors

  • XU XIANGHUA

Assignees

  • 江西联晟精密工业有限公司

Dates

Publication Date
20260505
Application Date
20260210

Claims (10)

  1. 1. A reliable unmanned aerial vehicle system power control method, comprising: generating a hardware trigger signal in response to the triggering of the physical key; switching on a main power supply of the unmanned aerial vehicle based on the hardware trigger signal, and starting a flight control main controller connected with the main power supply of the unmanned aerial vehicle; The flight control main controller outputs a software latch signal after confirming that the startup is effective, and carries out logic or synthesis on the hardware trigger signal and the software latch signal to generate and maintain a system startup enabling signal; Monitoring the triggering state of the physical key through a hardware forced shutdown circuit independent of the flight control main controller, and directly cutting off the main power supply of the unmanned aerial vehicle when the duration of the triggering state is monitored to exceed a first preset duration; The method comprises the steps that an external charging power supply, an unmanned aerial vehicle battery and a main power supply of the unmanned aerial vehicle are connected through a path management charging chip; the path management charging chip is configured to charge the unmanned aerial vehicle battery by the external charging power supply preferentially and cut off or isolate a power supply loop of the unmanned aerial vehicle main power supply when the external charging power supply is connected and the voltage of the unmanned aerial vehicle main power supply is lower than an internal switching threshold value.
  2. 2. The reliable unmanned aerial vehicle system power supply control method of claim 1, wherein the hardware forced shutdown circuit comprises an RC delay circuit composed of a resistor and a capacitor, and an electronic switching tube controlled by the RC delay circuit; When the continuous triggering time enables the RC delay circuit to reach a triggering threshold value, the electronic switching tube is controlled to act so as to change the controlled end potential of the main power switch module corresponding to the unmanned aerial vehicle main power supply.
  3. 3. The method of claim 2, wherein the hardware forced shutdown circuit further comprises a voltage comparator; The voltage of the capacitor in the RC delay circuit is connected to the first input end of the voltage comparator, and the second input end of the voltage comparator is connected to a reference voltage; when the voltage of the capacitor exceeds the reference voltage, the output state of the voltage comparator is reversed, so that the electronic switching tube is triggered to act.
  4. 4. A reliable unmanned aerial vehicle system power supply control method according to claim 3, wherein the reference voltage is generated by dividing a voltage-stabilized power supply by a first voltage dividing resistor and a second voltage dividing resistor, and an intermediate connection point of the first voltage dividing resistor and the second voltage dividing resistor provides the reference voltage to the second input terminal of the voltage comparator.
  5. 5. The method of claim 2, wherein the RC delay circuit further comprises a charging resistor, one end of the charging resistor is connected to the hardware trigger signal node or the trigger node of the physical key, the other end of the charging resistor is connected to the first end of the capacitor, and the second end of the capacitor is grounded.
  6. 6. The reliable unmanned aerial vehicle system power supply control method of claim 5, wherein the hardware forced shutdown circuit further comprises a bleeder resistor connected in parallel to two ends of the capacitor, and configured to provide a charge release path for the capacitor after triggering of the physical key is completed, so as to realize automatic reset of the RC delay circuit.
  7. 7. A reliable unmanned aerial vehicle system power control method according to claim 3, wherein the electronic switching tube is an N-channel MOSFET, the gate of which is controlled by the output of the voltage comparator or the output of the RC delay circuit, the source of which is grounded, and the drain of which is connected to the common node of the controlled end of the main power switching module and a pull-down resistor; And when the electronic switching tube is conducted, the controlled end potential of the main power switch module is pulled down to the reference ground level.
  8. 8. The method for controlling the power supply of the unmanned aerial vehicle system according to claim 1, wherein the logic or synthesis is realized by a diode or a logic circuit; The diode or logic circuit comprises a first diode and a second diode, wherein the anode of the first diode receives the hardware trigger signal, the anode of the second diode receives the software latch signal, and the cathodes of the first diode and the second diode are commonly connected to the system start-up enabling signal node.
  9. 9. The method of claim 1, wherein the step of the flight control master controller confirming that power-on is valid comprises: After the flight control main controller is started and completes basic initialization, reading the level state of an input pin connected with a system start-up enabling signal; if the level read for the first time is in an effective state, an internal timer is started to delay; reading the level of the input pin again after the delay is finished; If the first and second read averages are in the valid state, the startup is judged to be valid.
  10. 10. The method for controlling the power supply of the unmanned aerial vehicle system according to claim 1, the method is characterized by further comprising the step of software shutdown: And responding to any one of the received wireless shutdown instruction or the specific short pressing mode of the physical key, stopping outputting the software latch signal, so that the system startup enabling signal is disabled, and further controlling the main power switch module to turn off the main power supply of the unmanned aerial vehicle.

Description

Reliable unmanned aerial vehicle system power supply control method Technical Field The invention belongs to the technical field of unmanned aerial vehicle power supply management and control systems, and relates to a reliable unmanned aerial vehicle system power supply control method. Background Currently, consumer and open source unmanned aerial vehicle systems commonly employ a simplified power tree architecture for power management. In such an architecture, the drone battery is directly connected to the flight control system, communication module, load device, etc. through a main switch. When the battery is connected to the machine body interface, the whole system is electrified, and the flight control main controller and each peripheral module immediately enter a working or standby state. This simplified power management approach suffers from several drawbacks, firstly, the system standby power consumption is too high. Because the whole system is electrified after the battery is connected, even when the unmanned aerial vehicle is idle and not flown, modules such as flight control, data transmission, image transmission and the like still need to maintain basic working current, and the basic working current can reach hundred milliamperes generally. This results in full-power batteries that can be fully depleted in tens to hundreds of hours, affecting the long-term standby state-keeping capability of the device, and exacerbating the unnecessary cycling of the battery, shortening its useful life. Second, the shutdown mode is unsafe and unreliable. Such systems lack controlled shutdown logic, and the only safe shutdown mode for the user is to physically unplug the battery. When an unmanned aerial vehicle system is abnormal, for example, a motor is blocked to cause high current or flight control software is dead, an electric arc is very easy to generate at an interface by hot-line plugging of a battery, and clear potential safety hazards exist. Meanwhile, in the case of complete failure of software, the system cannot realize autonomous or controlled power failure. Finally, the charging experience is poor. The user must take out the battery from the fuselage, uses independent special charger to charge, and complex operation, and frequent plug charging interface easily leads to mechanical wear and contact failure. Most of the prior art schemes focus on optimizing flight performance and endurance, fail to provide a system-level and user-friendly intelligent on-off management scheme, fail to fully consider ultimate hardware security guarantee under the extreme condition of software failure, and fail to realize a seamless and convenient in-machine charging function. Therefore, there is a need for a power control method of an unmanned aerial vehicle system with high reliability, high safety and good user experience, so as to systematically solve the above problems. Disclosure of Invention In order to solve the problems in the background technology, the invention provides a reliable unmanned aerial vehicle system power supply control method. In order to achieve the purpose, the technical scheme adopted by the invention is as follows, and the reliable unmanned aerial vehicle system power supply control method comprises the following steps: generating a hardware trigger signal in response to the triggering of the physical key; switching on a main power supply of the unmanned aerial vehicle based on the hardware trigger signal, and starting a flight control main controller connected with the main power supply of the unmanned aerial vehicle; the flight control main controller outputs a software latch signal after confirming that the startup is effective, and carries out logic OR synthesis on the hardware trigger signal and the software latch signal to generate and maintain a system startup enabling signal; Monitoring the triggering state of the physical key through a hardware forced shutdown circuit independent of the flight control main controller, and directly cutting off the main power supply of the unmanned aerial vehicle when the duration of the triggering state is monitored to exceed a first preset duration; The method comprises the steps that an external charging power supply, an unmanned aerial vehicle battery and a main power supply of the unmanned aerial vehicle are connected through a path management charging chip; the path management charging chip is configured to charge the unmanned aerial vehicle battery by the external charging power supply preferentially and cut off or isolate a power supply loop of the unmanned aerial vehicle main power supply when the external charging power supply is connected and the voltage of the unmanned aerial vehicle main power supply is lower than an internal switching threshold value. Specifically, the hardware forced shutdown circuit comprises an RC delay circuit formed by a resistor and a capacitor, and an electronic switching tube controlled by the RC delay circuit; When t