One-key power supply starting device for unmanned aerial vehicle and control method of one-key power supply starting device

Abstract

The invention relates to the technical field of starting switches, in particular to a one-key power supply starting device for an unmanned aerial vehicle and a control method of the one-key power supply starting device, the device comprises a non-travel switch, a control mainboard, an anti-sparking module and an avionics control circuit, and a self-checking and starting function is triggered through short-press and long-press operations. The control mainboard is integrated with a main control chip and is matched with three paths of high-side control circuits to realize time-sharing power management; the anti-sparking module suppresses surge current through a pre-charging resistor series connection and MOS tube delay conduction strategy, and contact sparking is avoided. The voltage reduction circuit adopts a wide voltage input LDO chip to provide multi-stage voltage stabilization output. According to the invention, the operation steps are simplified, the hardware cost is reduced by more than 40%, the problems of operation redundancy, potential safety hazards and poor environmental adaptability in the prior art are effectively solved, and the method is suitable for high-reliability power supply control requirements of industrial-grade unmanned aerial vehicles.

Description

TECHNICAL FIELD

[0001] The application relates to the technical field of starting switch, in particular to a one-key power supply starting device for a UAV and a control method thereof. BACKGROUND

[0002] With the rapid development of UAV technology, its application in the fields of agricultural plant protection, logistics transportation, aerial photography, etc. is becoming more and more widespread. The power management and starting control of the on-board equipment of the UAV as one of the core subsystems directly affect the performance of the whole machine in terms of reliability, operation convenience and environmental adaptability. At present, the following technical solutions are mainly used in the industry to realize the on-off control of the UAV:

[0003] Key type mechanical switch: the circuit is turned on and off by triggering a mechanical structure through a physical key. This solution is widely used for mode switching function of consumer-grade UAVs, but has the limitations of relying on manual intervention for operation, being unable to adapt to remote control scenarios, and frequent mechanical contact leading to component wear.

[0004] Toggle type mechanical switch: a toggle lever type structure is used to control the power on and off, which is commonly used in industrial-grade UAVs (such as agricultural plant protection models). Although it has the advantage of fast operation, the switch is large in size and difficult to meet the design requirements of small UAVs, and is prone to accidental power failure due to false touch in a vibrating environment.

[0005] Battery communication switch: send instructions to the battery through UART serial port to realize on-off (such as DJI TB series battery). This solution relies on the built-in communication module of the battery, which limits compatibility and increases additional hardware cost, making it difficult to promote on general UAV platforms.

[0006] Touch screen gesture control: use touch screen to recognize gestures such as sliding and long pressing to generate control instructions. Although it improves the interaction experience, it requires a high-cost touch display screen, and the recognition success rate is significantly reduced in strong light and humid environments, restricting its application in outdoor scenarios.

[0007] Touch sensing interaction: use pressure or slip sensors integrated into the body to sense user operations. Although this solution does not require an external switch, it requires customized modification of the UAV structure, and the sensor wiring and anti-interference design are difficult and the maintenance cost is high.

[0008] The above solutions generally have the following problems: operation redundancy: mechanical switches require multiple physical operations and cannot implement a "self-checking-starting" integrated process; hardware limitations: dedicated communication modules or sensors increase design complexity and cost; poor environmental adaptability: mechanical components are easily affected by dust and humid environments, and touch solutions are not stable in harsh conditions; safety hazards: direct connection of high-current power supply can generate electric sparks, especially in flammable environments.

[0009] Therefore, there is an urgent need for a high-integration, simple operation and high-security unmanned aerial vehicle starting control scheme to overcome the comprehensive defects of the prior art. SUMMARY

[0010] To solve the above technical problems, the application discloses a one-key power supply starting device for an unmanned aerial vehicle and a control method thereof to solve the above technical problems.

[0011] The application discloses a one-key power supply starting device for an unmanned aerial vehicle, characterized in that the device comprises:

[0012] A travel switch is used for receiving user operation and generating a trigger signal;

[0013] A control mainboard is connected with the travel switch and comprises a control circuit module, a voltage reduction circuit module, a 3-way control circuit module and a clock circuit module, wherein the control circuit module is used for generating a self-checking control signal or a starting control signal according to the time length of the trigger signal;

[0014] A fire prevention module is integrated on the control mainboard and comprises a pre-charge circuit, a MOS control switch and a timer, wherein the pre-charge circuit limits starting current by delay conduction;

[0015] An avionics control circuit is connected with a power battery and an unmanned aerial vehicle flight control terminal and realizes power on-off control through the MOS control switch.

[0016] Optionally, the VSS pin and the VDD pin of the main control chip in the control circuit module are connected through a 100nF capacitor, the BOOT0 pin is connected to the ground through a 10kΩ pull-down resistor, and a short-circuit cap is connected with the VCC to realize a burning mode.

[0017] Optionally, the 3-way control circuit module comprises:

[0018] A 24V on-off control circuit is realized by using a PMOS tube to realize high-side control;

[0019] A contactor control circuit is connected with the pre-charge circuit in parallel;

[0020] The pre-charge circuit is connected with the positive pole of the power battery at the input end and connected with the load through a pre-charge resistor at the output end;

[0021] The control pins of the 3-way control circuit are connected with the PA5, PA4 and PA3 pins of the main control chip, respectively.

[0022] Optionally, in the pre-charge circuit, the gate of the PMOS tube is connected with an NMOS tube through a voltage stabilizing diode, the source of the NMOS tube is connected to the ground, and the gate is connected with the PA3 pin of the main control chip through a 10kΩ pull-down resistor.

[0023] Optionally, the voltage reduction circuit module comprises a first stage voltage reduction circuit and a second stage voltage reduction circuit, the first stage voltage reduction circuit converts circuit voltage from 12V to 5V, and the second stage voltage reduction circuit converts circuit voltage from 5V to 3.3V.

[0024] Optionally, the first stage voltage reduction circuit is a 4.5V-28V wide voltage input, and the output voltage is adjusted according to the voltage dividing resistors R18, R20 and R23; the output end of the second stage voltage reduction circuit is configured with 100nF and 10uF filter capacitors.

[0025] Optionally, the power-on control timing of the anti-arcing module is as follows: after closing the pre-charge MOS, delaying for 2 seconds, closing the avionics control MOS, delaying for 500ms, closing the contactor control circuit, and after 1 second, opening the pre-charge MOS; the power-off timing is as follows: after opening the contactor control MOS, delaying for 500ms, opening the avionics control MOS, and delaying for 2 seconds to discharge.

[0026] Optionally, a state indicating lamp is further included, a control pin of the state indicating lamp is connected to a PA2 pin of a master control chip through a 2.2kΩ current limiting resistor, and the state indicating lamp is used for indicating the power-on / power-off state of the system.

[0027] The application discloses a control method of a one-key power supply starting device for a UAV.

[0028] The power-on process is as follows:

[0029] S1. Short press a travel-free switch to trigger a self-check signal and start a long press detection window;

[0030] S2. After detecting a long press operation in the 2-second window, sequentially close a pre-charge MOS, an avionics control MOS and a contactor control MOS, and delay to open the pre-charge MOS;

[0031] The power-off process is as follows:

[0032] S3. Short press a travel-free switch to trigger a self-check signal and start a long press detection window;

[0033] S4. After detecting a long press operation in the 2-second window, sequentially open a contactor control MOS and an avionics control MOS, and delay to discharge.

[0034] Optionally, the determination threshold of the long press operation is 2 seconds, and in the power-off state, the system capacitor discharge delay is 2 seconds.

[0035] Compared with the prior art, the technical scheme provided by the application application embodiment has the following advantages:

[0036] The application discloses a one-key power supply starting device for a UAV and a control method thereof. The application discloses a one-key power supply starting device for a UAV and a control method thereof.The application remarkably improves the intelligent level and safety of power supply management of the UAV through the cooperative design of the non-travel switch and the main control circuit, the pre-charging anti-arcing mechanism and the time-sharing control logic.The compound operation logic of short pressing triggering self-checking and long pressing starting integrates the traditional multi-step "self-checking-power supply-starting" process into a single key action, simplifies the user operation steps, reduces the risk of misoperation, shortens the starting response time to 3 seconds, and remarkably improves the operation efficiency.The pre-charging circuit uses the time-sharing conduction strategy of the series current-limiting resistor and the MOS tube, closes the main power supply path after the voltage of the power battery slowly rises to the rated value of the load capacitor, effectively suppresses the inrush current, avoids the arcing phenomenon of the contact, and is especially suitable for flammable and explosive or high-dust environments.The application adopts the general STM32 main control chip and the standardized MOS driving scheme, does not need to rely on special communication batteries or high-precision sensors, and reduces the hardware cost by about 40%.The modular design supports 12-24V wide voltage input, adapts to most UAV power systems, and remarkably improves the compatibility.The non-travel switch adopts the IP67 level waterproof packaging and the anti-misoperation structure design, the main control board reduces the electromagnetic interference through the double-layer PCB layout and the filtering circuit, ensures stable operation in the temperature range of-20 DEG C to 60 DEG C and the environment with humidity below 95%, and reduces the failure rate by more than 70% compared with the traditional mechanical switch.The double-signal checking mechanism (short pressing + long pressing combination triggering) based on the timer avoids accidental starting, the state indicating lamp is used for feeding back the system state in real time, the capacitor active discharge module is added in the power-off process, and the risk of circuit damage caused by residual charge is completely eliminated.The device realizes breakthroughs in the three dimensions of simplifying operation, strengthening safety and reducing cost through the above technical innovations, and provides bottom hardware guarantee for the reliable operation of the industrial UAV in complex working conditions. BRIEF DESCRIPTION OF DRAWINGS

[0037] The drawings incorporated into the specification and forming a part thereof illustrate embodiments in accordance with the present disclosure and, together with the description, serve to explain the principles of the disclosure.

[0038] In order to more clearly illustrate the technical solutions in the embodiments of the present disclosure or the prior art, brief introductions will be given to the drawings needed to be used in the embodiments or prior art descriptions. Obviously, for those skilled in the art, other drawings can also be obtained from these drawings without creative labor.

[0039] Figure 1 FIG. 1 is a structural schematic diagram of a one-key starting device for a UAV in the embodiments of the present disclosure;

[0040] Figure 2 FIG. 2 is a schematic diagram of a main control circuit in the embodiments of the present disclosure;

[0041] Figure 3A schematic diagram of a first voltage reduction circuit in an embodiment of the present disclosure is shown in the figure.

[0042] Figure 4 A schematic diagram of a second voltage reduction circuit in an embodiment of the present disclosure is shown in the figure.

[0043] Figure 5 A schematic diagram of a 24V on-off control circuit in an embodiment of the present disclosure is shown in the figure.

[0044] Figure 6 A schematic diagram of a contactor control circuit in an embodiment of the present disclosure is shown in the figure.

[0045] Figure 7 A schematic diagram of a pre-charge circuit in an embodiment of the present disclosure is shown in the figure.

[0046] Figure 8 A schematic diagram of a pre-charge resistor in an embodiment of the present disclosure is shown in the figure.

[0047] Figure 9 A schematic diagram of a clock circuit in an embodiment of the present disclosure is shown in the figure.

[0048] Figure 10 A flow chart of a control method of a one-key starting device of a UAV in an embodiment of the present disclosure is shown in the figure. DETAILED DESCRIPTION

[0049] In order to enable a person skilled in the art to more clearly understand the above-mentioned purposes, features and advantages of the present disclosure, the schemes of the present disclosure will be further described below. It should be noted that the embodiments of the present disclosure and the features in the embodiments can be combined with each other without conflict.

[0050] In the following description, many specific details are set forth in order to provide a thorough understanding of the present disclosure, but the present disclosure can also be implemented in other ways different from those described herein; obviously, the embodiments in the description are only some of the embodiments of the present disclosure, not all the embodiments.

[0051] In combination Figures 1-9 As shown in the figure, the present disclosure discloses a one-key power supply starting device for a UAV, which comprises:

[0052] A travel switch is used for receiving user operation and generating a trigger signal;

[0053] A control mainboard is connected with the travel switch and comprises a control circuit module, a voltage reduction circuit module, a 3-way control circuit module and a clock circuit module, wherein the control circuit module is used for generating a self-check control signal or a starting control signal according to the time length of the trigger signal;

[0054] A fire prevention module is integrated on the control mainboard and comprises a pre-charge circuit, a MOS control switch and a timer, wherein the pre-charge circuit limits starting current by delay conduction;

[0055] The avionics control circuit is connected with the power battery and the unmanned aerial vehicle flight control terminal, and realizes power on-off control through the MOS control switch.

[0056] In an embodiment, the control mainboard adopts a double-layer PCB board with a size of 60 mm*50 mm*20 mm, and a control chip of STM32F103C8T6 of STMicroelectronics Company is adopted, which internally contains a step-down circuit and a 3-way MOS control circuit, and the chip has the characteristics of high performance and low power consumption, can stably run a control program, and realizes accurate control on the starting process of the unmanned aerial vehicle, effectively improving the reliability and stability of the starting of the unmanned aerial vehicle.

[0057] In an embodiment, the VSS pin and the VDD pin of the main control chip in the control circuit module are connected through a 100 nF capacitor, the BOOT0 pin is grounded through a 10 kΩ pull-down resistor, and is configured to be connected with the VCC through a short-circuit cap to realize a burning mode.

[0058] In a further embodiment, the main control circuit takes stm32f103c8t6 as the main control chip, and the required 3.3V power supply input is provided by two step-down circuits, the VSS pin and the VDD pin of the main control chip are connected through a 100 nf capacitor, the BOOT0 pin and the PB2 pin are pulled down through a 10KΩ resistor, the BOOT0 is connected with the VCC through a short-circuit cap, and only short-circuit is needed for burning during burning. The on-board touch key is of TS5220A type, the key detection pin is connected with the PB4 pin of the single-chip microcomputer, and the other pin of the key is grounded. The status indicator lamp control pin is connected with the PA2 pin of the single-chip microcomputer through a 2.2K current-limiting resistor, and the other end is grounded. The serial port printing PZ254V-11-04P pin is connected with the PA10 / PA9 pin of the single-chip microcomputer, and is used for printing log information. The crystal circuit is divided into an external clock crystal and an internal clock crystal circuit, the bit number X1 is a 32.768Hz crystal, which is filtered to ground through 22pF filter capacitors C5 and C6, the crystal is connected with the crystal 2 input / output pin of the single-chip microcomputer, the other way of the crystal is an 8MHz external crystal circuit, which is filtered to ground through 22pF filter capacitors C7 and C8, the crystal is connected with the crystal 1 input / output pin of the single-chip microcomputer, and a 1MΩ resistor is connected in parallel with the crystal 1 input / output pin. The VSS pin and the VDD pin of the main control chip are connected through a 100nF capacitor, which can effectively filter out power supply noise and improve the stability of chip power supply. The BOOT0 pin is grounded through a 10kΩ pull-down resistor, and is configured to be connected with the VCC through a short-circuit cap to realize a burning mode, such a design not only guarantees the stable state of the chip in normal operation, but also facilitates the burning and updating of the program, reduces the difficulty of maintenance and upgrading, and ensures that the system can adjust and optimize the control logic in time according to the actual demand.

[0059] In an embodiment, the contact key switch is made of waterproof material and is integrally formed, is installed on the mounting bracket, the mounting bracket is fixedly connected to the bottom of the head of the unmanned aerial vehicle, and the key terminal is connected with the main control key detection terminal. The contact key switch made of waterproof material and integrally formed is installed on the mounting bracket at the bottom of the head of the unmanned aerial vehicle, has good waterproof performance and mechanical stability, can adapt to the use of the unmanned aerial vehicle in different environments, such as under complex weather conditions such as humidity or rainy days, effectively prevents water from entering to cause short circuit or failure of the key, ensures accurate transmission of the starting signal, prolongs the service life of the key, and simultaneously, the installation position is convenient for the starting operation of the operator.

[0060] In an embodiment, the 3-way control circuit module comprises: a 24V on-off control circuit, a PMOS tube is used to realize high-side control; a contactor control circuit, which is connected in parallel with a pre-charge circuit; and the pre-charge circuit, the input end of which is connected with the positive pole of the power battery, and the output end of which is connected with the load through a pre-charge resistor; wherein the control pins of the 3-way control circuit are respectively connected with the PA5, PA4 and PA3 pins of the main control chip. The 24V on-off control circuit, the contactor control circuit and the pre-charge circuit all adopt high-side control mode, and the control pins of the 3-way control circuit are respectively connected with the specific pins of the main control chip, through which independent and accurate control of each circuit can be realized. In the control process, the characteristics of NMOS and PMOS tubes are used in combination with current-limiting protection resistors, voltage stabilizing diodes and other elements to ensure the stability and safety of the circuit in on-off control, avoid damage of the elements caused by current impact or voltage abnormality, and ensure the smooth progress of the starting process of the unmanned aerial vehicle. Meanwhile, the high-side control mode is helpful to reduce the ground interference and improve the anti-interference ability of the circuit.

[0061] In a further embodiment, the 24V on / off control circuit, contactor control circuit, and pre-charge circuit all employ high-side control. The three control pins are PA5, PA4, and PA3 pins of the microcontroller, each connected to the gate of a BSS123 NMOS transistor. A 10K resistor pulls down the NMOS gate and source. The inputs of the 24V on / off control circuit and the contactor control circuit are DC 24V power supplies. The shutdown control is achieved by a high-side PMOS transistor (AOD4185). The PMOS source is connected to the 24V input, and a BZT52C12 Zener diode protects the PMOS gate drive. R4, R5, R6, and R7 are connected between the PMOS and NMOS transistors for current limiting protection. The pre-charge circuit input is connected to the positive output of the power battery pack and the gate of the SQJ45LEP-T1_GE3. The gate of the PMOS drive terminal is connected to the negative terminal of the Zener diode, and current limiting protection is provided by a 10K resistor R8. It is connected to the NMOS terminal of the BSS123 model. The source of the NMOS is grounded, and its gate is connected to PA3 of the main controller through a 10K pull-down resistor. The drain of the PMOS is connected to the pre-charge resistor, and the other end of the pre-charge resistor R24 ​​is connected to the control load.

[0062] In one embodiment, in the pre-charging circuit, the gate of the PMOS transistor is connected to the NMOS transistor via a Zener diode. The source of the NMOS transistor is grounded, and its gate is connected to the PA3 pin of the main control chip via a 10kΩ pull-down resistor. This structure effectively protects the gate of the PMOS transistor from damage due to overvoltage, ensuring the stable operation of the pre-charging circuit. By connecting the pre-charging resistor to the positive terminal of the power battery and the load, pre-charging of the load is achieved, reducing the current surge during startup, protecting the power battery and circuit system, extending battery life, and improving the reliability and safety of the entire starting device.

[0063] In one embodiment, the step-down circuit module includes a first-stage step-down circuit and a second-stage step-down circuit. The first-stage step-down circuit converts the circuit voltage from 12V to 5V, and the second-stage step-down circuit converts the circuit voltage from 5V to 3.3V.

[0064] In one embodiment, the buck circuit module includes a first-stage buck circuit and a second-stage buck circuit. The first-stage buck circuit converts the circuit voltage from 12V to 5V, and the second-stage buck circuit converts the circuit voltage from 5V to 3.3V. The first-stage buck circuit has a wide input voltage range of 4.5V-28V, and the output voltage is adjusted according to the voltage divider resistors R18, R20, and R23. The output terminal of the second-stage buck circuit is equipped with 100nF and 10μF filter capacitors.

[0065] In further embodiments, the LDO chip used for 12V to 5V conversion is TPS54335ADDAR chip from TI. This chip has a wide input voltage range of 4.5V-28V, and the output voltage is calculated based on the voltage dividing resistors R18, R20, and R23. The SS54 diode is a reverse connection prevention diode. Both the capacitors and inductors are for filtering purposes. The AMS1117-3.3 chip is used for 5V to 3.3V conversion, with a 5V input and a 3.3V output. The 100nF and 10uF capacitors are used for filtering the 5V and 3.3V voltages to ground. R16 is a current limiting resistor for the power display LED, with the positive terminal connected to the current limiting resistor and the negative terminal connected to ground. The first stage of the voltage reduction circuit converts 12V to 5V, and the second stage further converts 5V to 3.3V. Through two-stage voltage reduction, more accurate voltage regulation and more stable voltage output can be achieved, meeting the different voltage requirements of different circuit modules. For example, a stable 3.3V supply is provided for the control chip to ensure its normal operation, while the 5V voltage can be used for the power supply of other auxiliary circuits or components. In addition, the use of wide input LDO chip can adapt to a wider range of input voltage fluctuations, enhancing the adaptability of the device to different power supply conditions, improving the stability and reliability of the system.

[0066] In an embodiment, the anti-sparking module includes a pre-charge circuit, a MOS control switch, and a timer detection, which are integrated on a control mainboard. The pre-charge circuit controls one end of the MOS to be connected with the anti-sparking resistor, and the other end to be connected with the positive pole of the power battery. The other end of the anti-sparking resistor is connected with the power device, and the negative pole of the power battery is connected with the negative pole of the power device, forming a complete anti-sparking circuit. The contactor control is connected in parallel between the pre-charge circuit and the anti-sparking resistor. The contactor control is directly controlled by the peripheral circuit of the main control chip, and the specific power-on and power-off control timing is realized by the single-chip microcomputer logic. The power-on control timing of the anti-sparking module is as follows: after closing the pre-charge MOS, delay for 2 seconds, close the avionics control MOS, delay for 500 ms, close the contactor control circuit, and after 1 second, open the pre-charge MOS. The power-off timing is as follows: after opening the contactor control MOS, delay for 500 ms, open the avionics control MOS, and delay for 2 seconds to discharge. The pre-charge circuit controls one end of the MOS to be connected with the anti-sparking resistor, and the other end to be connected with the positive pole of the power battery, forming a complete anti-sparking circuit. The contactor control is connected in parallel between the pre-charge circuit and the anti-sparking resistor. Such a design can effectively prevent the occurrence of sparking during the starting and stopping processes, and avoid safety hazards such as fire or electromagnetic interference caused by sparking. At the same time, through reasonable power-on and power-off control timing, i.e., sequentially closing the pre-charge MOS, the avionics control MOS, and the contactor control MOS during power-on, and delaying to open the pre-charge MOS; sequentially opening the contactor control MOS and the avionics control MOS during power-off, and delaying to discharge, the smooth transition of the entire starting and stopping process is ensured, the impact on the circuit and the battery is reduced, which is conducive to improving the safety and service life of the system.

[0067] In an embodiment, the device further includes a state indicating lamp, the control pin of which is connected with the PA2 pin of the main control chip through a 2.2kΩ current limiting resistor, for indicating the power-on / power-off state of the system. The control pin of the state indicating lamp is connected with the PA2 pin of the main control chip through a 2.2kΩ current limiting resistor, which can directly indicate the power-on / power-off state of the system, providing clear visual feedback for the operator, facilitating the operator to timely understand the running state of the device, improving the convenience and accuracy of operation, and also facilitating preliminary troubleshooting and judgment when a fault occurs.

[0068] In an embodiment, the avionics control circuit includes an avionics control power supply, the positive electrode of the avionics control MOS is connected to the positive electrode of the avionics battery, and the output end of the MOS is connected to the avionics equipment. The MOS is integrated in the peripheral circuit of the main control chip and is controlled by the button. The connector uses a foolproof plug, and the control mainboard and the flight control terminal of the unmanned aerial vehicle are independently connected by the connecting line. The positive electrode of the avionics control MOS is connected to the positive electrode of the avionics battery, and the output end is connected to the avionics equipment, realizing the power control of the avionics equipment. The connection is made by using the foolproof plug, effectively preventing the connection error, improving the reliability and safety of the connection. The electrical parameters refer to the Pixhawk series interface standard, have good universality and compatibility, can meet the needs of different unmanned aerial vehicle flight control terminals, support multiple connection modes, and provide convenience for subsequent upgrading and expansion of the unmanned aerial vehicle.

[0069] In an embodiment, the foolproof plug adopts a 4Pin foolproof plug design, specifically including: PIN1: VOUT (avionics output), PIN2: GND (ground), PIN3: START_SIG (start state feedback signal), and PIN4: NC or spare serial port (optionally used as UART_TX). This wiring mode supports general PWM signal input, IO level trigger detection, TTL serial communication and other connection modes, and the electrical parameters refer to the Pixhawk series interface standard, the VOUT output is stable at 5V or 12V (can be jumpered), the START_SIG output level is 3.3V logic high, and is compatible with STM32 or ATmega kernel flight control recognition level.

[0070] In combination with Figure 10 As shown in the figure, the application discloses a control method of a one-key starting switch device of an unmanned aerial vehicle, specifically including the following steps:

[0071] Power-on process:

[0072] S1. Short press the no-stroke switch to trigger a self-check signal and start a long press detection window;

[0073] S2. After detecting a long press operation in the 2-second window, sequentially close the pre-charging MOS, the avionics control MOS and the contactor control MOS, and delay to open the pre-charging MOS;

[0074] Power-off process:

[0075] S3. Short press the no-stroke switch to trigger a self-check signal and start a long press detection window;

[0076] S4. After detecting a long press operation in the 2-second window, sequentially open the contactor control MOS and the avionics control MOS, and delay to discharge.

[0077] The power-on process is triggered by a short press of the non-stroke switch, and after detecting a long press operation within a 2-second window, the pre-charge MOS, the avionics control MOS, and the contactor control MOS are sequentially closed, and the pre-charge MOS is opened after a delay. This control method can achieve a fast and stable power-on process, ensuring that each system of the unmanned aerial vehicle can be gradually powered on according to the preset timing sequence when starting, avoiding failures caused by current impact or improper starting sequence, and improving the success rate of starting and the reliability of the system. The power-down process is triggered by a short press of the non-stroke switch, and after detecting a long press operation within a 2-second window, the contactor control MOS and the avionics control MOS are sequentially opened, and the discharge is delayed, realizing a safe and complete power-down process, ensuring that the unmanned aerial vehicle can be fully discharged after power-off, avoiding harm to equipment and personnel caused by residual charge, and also protecting the battery and circuit system, prolonging the service life of the equipment.

[0078] In further embodiments, the power-on process comprises the following steps:

[0079] The operator short presses the non-stroke switch, and the control chip records the trigger time. When the trigger time is less than 1 second, a self-check control signal is generated, the short press is effective, and long press detection is started;

[0080] The single-chip microcomputer timer detects the start of the 2-second timing of the short press, and detects the low-level of the key to determine whether the key is pressed again. When the key is pressed, the second key timing is started, and whether the key pressing time is greater than the judgment long press key time of 2 seconds is recorded;

[0081] The single-chip microcomputer determines that the long press key is pressed, i.e., the system detects a short press long press in the power-off state, and the system starts the power-on process;

[0082] When the system detects a long press short press in the power-off state, the control mainboard circuit LED lamp is always on, the pre-charge MOS is closed, and the timing of 2 seconds is started. After 2 seconds, the avionics control MOS is closed, and then the contactor control circuit is closed after a delay of 500 ms. The pre-charge MOS is opened after a delay of 1 second. The power-on process is completed.

[0083] In further embodiments, the power-down process comprises the following steps:

[0084] The operator short presses the non-stroke switch, and the control chip records the trigger time. When the trigger time is less than 1 second, a self-check control signal is generated, the short press is effective, and long press detection is started;

[0085] The single-chip microcomputer timer detects the start of the 2-second timing of the short press, and detects the low-level of the key to determine whether the key is pressed again. When the key is pressed, the second key timing is started, and whether the key pressing time is greater than the judgment long press key time of 2 seconds is recorded;

[0086] The single-chip microcomputer judges that the long-press key is pressed, that is, the system detects the short press and the long press in the power-on state, and the system starts the power-on process;

[0087] When the system detects the long press and the short press in the power-on state, the control mainboard circuit extinguishes the LED lamp, disconnects the contactor control MOS, delays for 500 ms, disconnects the navigation and control MOS, and delays for 2 seconds to discharge the system capacitor, and completes the power-off process.

[0088] In an embodiment, the judgment threshold of the long-press operation is 2 seconds, and in the power-off state, the system capacitor discharge delay is 2 seconds.

[0089] In a specific embodiment, the control process is measured on an industrial unmanned aerial vehicle (model E300), and the test process is as follows:

[0090] Power-on test: short press (0.5 seconds) → LED flashes once → enters long press detection; continuously press for 2.5 seconds → LED always on → pre-charge start (2 seconds) → main power on → flight control system starts successfully, total time 3.5 seconds.

[0091] Power-off test: short press → LED flashes → long press for 2 seconds → LED is extinguished → contactor is disconnected (0.5 seconds) → navigation and control is disconnected → after 2 seconds, the residual voltage of the capacitor measured by the multimeter is <0.3V.

[0092] Anti-interference test: fast release (1 second press + 0.5 second release + 1 second press) within the long press window period, the system does not trigger by mistake, and the validity of the double signal verification is verified.

[0093] The specific implementation manner and principle are the same as those of the above-described embodiment, and the same or similar technical effects can be brought, which will not be described here one by one. For details, refer to the description of the above cover airtightness detection tool embodiment.

[0094] In the description of the embodiments of the present disclosure, it should be understood that the orientations or positional relationships indicated by the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "height", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the embodiments of the present disclosure and simplifying the description, and therefore cannot be understood as indicating or implying that the structures or devices indicated must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the embodiments of the present disclosure.

[0095] It should be noted that, in this document, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0096] The above description is merely a specific embodiment of this disclosure, enabling those skilled in the art to understand or implement it. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of this disclosure. Therefore, this disclosure is not to be limited to the embodiments described herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A one-key power supply starting device for a UAV, characterized in that, The device comprises: a travel-free switch for receiving user operation and generating a trigger signal; a control mainboard connected with the travel-free switch, comprising a control circuit module, a step-down circuit module, a 3-way control circuit module and a clock circuit module, the control circuit module being used for generating a self-check control signal or a start control signal according to the length of the trigger signal; a spark-proof module integrated on the control mainboard, comprising a pre-charge circuit, a MOS control switch and a timer, the pre-charge circuit limiting start current by delay conduction; an avionics control circuit connected with a power battery and a UAV flight control terminal, realizing power on-off control through the MOS control switch.

2. The one-button power supply start device for a drone according to claim 1, characterized in that, The VSS pin and the VDD pin of the main control chip in the control circuit module are connected through a 100nF capacitor, the BOOT0 pin is connected to ground through a 10kΩ pull-down resistor, and a short-circuit cap is connected to VCC to realize the burning mode.

3. The one-key power supply starting device for the unmanned aerial vehicle according to claim 1, characterized in that, The 3-way control circuit module comprises: a 24V on-off control circuit using a PMOS tube to realize high-side control; a contactor control circuit connected in parallel with the pre-charge circuit; a pre-charge circuit with the input end connected to the positive pole of the power battery and the output end connected to the load through a pre-charge resistor; wherein the control pins of the 3-way control circuit are connected to the PA5, PA4 and PA3 pins of the main control chip respectively.

4. The one-key power supply starting device for the unmanned aerial vehicle according to claim 1, characterized in that, In the pre-charge circuit, the gate of the PMOS tube is connected to the NMOS tube through a voltage stabilizing diode, the source of the NMOS tube is connected to ground, and the gate is connected to the PA3 pin of the main control chip through a 10kΩ pull-down resistor.

5. The one-key power supply starting device for the unmanned aerial vehicle according to claim 1, characterized in that, The step-down circuit module comprises a first-stage step-down circuit and a second-stage step-down circuit, the first-stage step-down circuit converts circuit voltage from 12V to 5V, and the second-stage step-down circuit converts circuit voltage from 5V to 3.3V.

6. The one-key power supply starting device for the unmanned aerial vehicle according to claim 5, characterized in that, The first-stage step-down circuit is a 4.5V-28V wide voltage input, and the output voltage is adjusted according to the dividing resistors R18, R20 and R23; the output end of the second-stage step-down circuit is configured with 100nF and 10μF filter capacitors.

7. The one-key power supply starting device for the unmanned aerial vehicle according to claim 1, characterized in that, The power-on control sequence of the spark-proof module is: closing the pre-charge MOS, delaying for 2 seconds, closing the avionics control MOS, delaying for 500ms, closing the contactor control circuit, and disconnecting the pre-charge MOS after 1 second; the power-off sequence is: disconnecting the contactor control MOS, delaying for 500ms, disconnecting the avionics control MOS, and discharging after delaying for 2 seconds.

8. The one-key power supply starting device for the unmanned aerial vehicle according to claim 1, characterized in that, It also comprises a state indicating lamp, the control pin of which is connected to the PA2 pin of the main control chip through a 2.2kΩ current-limiting resistor, and is used for indicating the power-on / power-off state of the system.

9. A control method of a one-key power supply starting device for a UAV, characterized in that, Specifically comprising the following steps: power-on process: S1. Short press the travel-free switch to trigger a self-check signal and start a long press detection window; S2. After detecting a long press operation within the 2-second window, sequentially close the pre-charge MOS, the avionics control MOS and the contactor control MOS, and disconnect the pre-charge MOS after delaying; power-off process: S3. Short press the travel-free switch to trigger a self-check signal and start a long press detection window; S4. After detecting a long press operation within the 2-second window, sequentially disconnect the contactor control MOS and the avionics control MOS, and discharge after delaying.

10. The unmanned aerial vehicle motor performance testing method of claim 9, wherein, The determination threshold of the long press operation is 2 seconds, and the system capacitor discharge delay time in the power-off state is 2 seconds.

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