Universal unmanned aerial vehicle parachute opening control system and method and unmanned aerial vehicle

Abstract

The invention discloses a parachute opening control system and method of a universal unmanned aerial vehicle parachute and an unmanned aerial vehicle. The parachute opening control system of the universal unmanned aerial vehicle parachute comprises a microprocessor, and an air pressure sensor circuit, an IMU sensor circuit, a communication module, a parachute opening control circuit, a display circuit, a data storage circuit, a battery voltage acquisition circuit, a parachute bay state detection circuit, a power supply control circuit and an indicator lamp circuit which are connected with the microprocessor, the communication module comprises a first communication circuit, a second communication circuit and a third communication circuit and is used for communication between the parachute opening control system and the unmanned aerial vehicle, and the first communication circuit, the second communication circuit and the third communication circuit are preset communication circuits; the power supply control circuit comprises a first power supply input circuit and a second power supply input circuit, and the input ranges of the first power supply input circuit and the second power supply input circuit are preset. The corresponding system can be applied to unmanned aerial vehicles with different communication modes and different voltage power supplies.

Description

Technical Field

[0001] This invention relates to the field of drone safety and rescue technology, and in particular to a universal drone parachute deployment control system, method, and drone. Background Technology

[0002] With the widespread application of drones in logistics, surveying, agriculture, and other fields, their payload capacity and functional requirements are becoming increasingly diversified, ranging from micro-consumer drones to large industrial drones, with significant differences in power systems (such as battery voltage and capacity) and communication architectures. To ensure flight safety, parachute deployment control has become a crucial component.

[0003] However, current parachute deployment controls are usually designed for specific drones and have a fixed power input range. Therefore, it is more costly to deploy them for different drone models. At the same time, current parachute deployment control systems usually only support a single communication interface, while different drones have different communication interfaces. This means that when users change drone controllers, they need to adjust the corresponding parachute deployment control system, resulting in a waste of manpower and resources.

[0004] Therefore, existing technologies still need to be improved and developed. Summary of the Invention

[0005] The main objective of this invention is to provide a universal parachute deployment control system, method, and drone, aiming to solve the problems of existing parachute deployment controls, which are usually designed for specific drones and have a fixed power input range. Therefore, when adapting to different drone models, higher costs are required. At the same time, current parachute deployment control systems usually only support a single communication interface, while different drones have different communication interfaces. This requires users to adjust the corresponding parachute deployment control system when changing drone controllers, resulting in a waste of manpower and resources.

[0006] To achieve the above objectives, the present invention provides a universal UAV parachute deployment control system, which includes a microprocessor and a barometric pressure sensor circuit, an IMU sensor circuit, a communication module, a parachute deployment control circuit, a display circuit, a data storage circuit, a battery voltage acquisition circuit, a parachute compartment status detection circuit, a power control circuit, and an indicator light circuit connected to the microprocessor. The communication module includes a first communication circuit, a second communication circuit, and a third communication circuit, which are used for the parachute control system to communicate with the UAV. The first communication circuit, the second communication circuit, and the third communication circuit are pre-set communication circuits. The power control circuit includes a first power input circuit and a second power input circuit, and the input range of the first power input circuit and the second power input circuit is a preset range. The air pressure sensor circuit is used to acquire air pressure data and transmit it to the microprocessor; the IMU sensor circuit is used to acquire attitude data and transmit it to the microprocessor; the parachute deployment control circuit is used to receive the parachute deployment signal and correspondingly control the gas generator to launch the parachute; the data storage circuit is used to detect whether the storage device is inserted and to store the data of the parachute deployment control system in the storage device; the battery voltage acquisition circuit is used to detect whether the power supply is normal; the indicator light circuit is used to display the power status of the parachute deployment control system; the parachute compartment status detection circuit is used to detect the parachute compartment connection status and the parachute deployment status. The display circuit includes an LED and a buzzer, as well as the circuit structure corresponding to the LED and the buzzer, for displaying the status of the umbrella opening control system.

[0007] Optionally, the first communication circuit includes a CAN transceiver and two terminating resistors. The two differential signal lines of the CAN transceiver that communicate with the UAV are respectively connected in series with a terminating resistor, and a switch is connected in series between the two terminating resistors to control the activation of the terminating resistors.

[0008] Optionally, the second communication circuit receives flight control signals and microprocessor inputs with corresponding communication protocols, performs level conversion, inputs the converted flight control signals to the microprocessor, and transmits the converted microprocessor inputs to the UAV. The third communication circuit shapes the received signal with the corresponding communication protocol based on a Schmitt trigger to obtain a digital signal, and then inputs the digital signal into the microprocessor.

[0009] Optionally, the first power input circuit is connected to a fixed voltage power supply, and the second power input circuit is connected to a range voltage power supply. When the umbrella opening control system is connected to a range voltage power supply, the range voltage power supply is stepped down based on the step-down circuit of the second power input circuit to obtain a stepped-down voltage and realize power input.

[0010] Optionally, the parachute compartment status detection circuit is used to detect the parachute compartment connection status, including a first resistor and a second resistor connected in sequence, and a first capacitor connected in parallel with the second resistor. The second resistor is connected to the parachute opening control circuit. The parachute compartment status detection circuit also includes a parachute compartment circuit, which includes a third resistor and is connected to the parachute opening controller circuit. When the parachute compartment is connected to the parachute opening control system, the voltage on the capacitor side before and after the parachute compartment is connected is obtained. When the voltage after the parachute compartment is connected is half of that before the connection, the parachute compartment is successfully connected, and the corresponding information is input into the microprocessor.

[0011] Optionally, the parachute compartment status detection circuit is also used to detect the parachute opening status; When the parachute compartment status detection circuit receives the parachute opening command from the microprocessor, the parachute opening controller circuit outputs an activation current to detect the voltage on the capacitor side before and after receiving the parachute opening command. When the voltage after receiving the parachute opening command is twice that before receiving the parachute opening command, the parachute opening is successful, and the corresponding parachute opening status is input to the microprocessor. If the voltage after receiving the umbrella opening command is the same as before receiving the umbrella opening command, then the umbrella opening fails, and the corresponding umbrella opening status is input into the microprocessor.

[0012] Furthermore, to achieve the above objectives, the present invention also provides a universal UAV parachute deployment control method, wherein the universal UAV parachute deployment control method specifically includes: The communication method and power input range of the target UAV are obtained, and the communication circuit of the communication module and the power input circuit of the power control circuit in the parachute opening control system are selected according to the communication method and the power input range. The connection status of the parachute compartment is detected by the parachute compartment status detection circuit. The microprocessor acquires data transmitted by the barometric pressure sensor circuit and the IMU sensor circuit in real time. When the parachute opening conditions are met, the microprocessor controls and outputs a parachute opening signal to the parachute opening control circuit. The parachute opening control circuit outputs an activation current to control the parachute compartment to release the parachute.

[0013] Optionally, the step of acquiring the communication method and power input range of the target UAV, and selecting the communication circuit of the communication module and the power input circuit of the power control circuit in the parachute deployment control system based on the communication method and the power input range, specifically includes: Obtain the target drone's communication method and power input range; When the target drone's communication mode is the first communication mode, the first communication circuit is selected to communicate with the target drone; when the target drone's communication mode is the second communication mode, the second communication circuit is selected to communicate with the target drone; when the target drone's communication mode is the third communication mode, the third communication circuit is selected to communicate with the target drone. When the power input range of the target UAV is a fixed voltage power supply, the first power input circuit is selected for power control; when the power input range of the target UAV is a range voltage power supply, the second power input circuit is selected for power control.

[0014] In addition, to achieve the above objectives, the present invention also provides a drone, which includes the above-described general-purpose drone parachute deployment control system.

[0015] In this invention, the universal UAV parachute deployment control system includes a microprocessor, and connected to the microprocessor are a barometric pressure sensor circuit, an IMU sensor circuit, a communication module, a parachute deployment control circuit, a display circuit, a data storage circuit, a battery voltage acquisition circuit, a parachute compartment status detection circuit, a power control circuit, and an indicator light circuit. The communication module includes a first communication circuit, a second communication circuit, and a third communication circuit for communication between the parachute deployment control system and the UAV. These three communication circuits are pre-configured. The power control circuit includes a first power input circuit and a second power input circuit, with the input range of both circuits being pre-configured. The system comprises: a pressure sensor circuit for acquiring pressure data and transmitting it to the microprocessor; an IMU sensor circuit for acquiring attitude data and transmitting it to the microprocessor; a parachute deployment control circuit for receiving deployment signals and correspondingly controlling the gas generator to launch the parachute; a data storage circuit for detecting whether a storage device is inserted and storing the data of the parachute deployment control system in the storage device; a battery voltage acquisition circuit for detecting whether the power supply is normal; an indicator light circuit for displaying the power status of the parachute deployment control system; a parachute compartment status detection circuit for detecting the parachute compartment connection status and deployment status; and a display circuit including LEDs and a buzzer, as well as corresponding circuit structures for the LEDs and the buzzer, for displaying the status of the parachute deployment control system. This invention, through its communication module and power control circuit, enables corresponding communication and power supply for different drone models, eliminating the need for adjustments and modifications to the parachute deployment control system and reducing the waste of manpower and resources when configuring different types of drones. Furthermore, by incorporating a microprocessor, barometric pressure sensor circuit, IMU sensor circuit, parachute deployment control circuit, display circuit, data storage circuit, battery voltage acquisition circuit, parachute compartment status detection circuit, and indicator light circuit, the invention allows for comprehensive system testing before parachute use and automatic parachute deployment when required, thus facilitating accurate and convenient parachute deployment control. Attached Figure Description

[0016] Figure 1This is a structural diagram of a preferred embodiment of the universal UAV parachute deployment control system of the present invention; Figure 2 This is a schematic diagram of the first communication circuit in the universal UAV parachute deployment control system of the present invention; Figure 3 This is a schematic diagram of the second power input circuit in the universal UAV parachute deployment control system of the present invention. Figure 4 This is a schematic diagram of the parachute compartment status detection circuit in the universal UAV parachute opening control system of the present invention. Figure 5 This is a flowchart of a preferred embodiment of the universal UAV parachute deployment control method of the present invention. Detailed Implementation

[0017] To make the objectives, technical solutions, and advantages of this invention clearer and more explicit, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

[0018] With the widespread application of drones in logistics, surveying, agriculture, and other fields, their payload capacity and functional requirements are becoming increasingly diversified, ranging from micro-consumer drones to large industrial drones, with significant differences in power systems (such as battery voltage and capacity) and communication architectures. To ensure flight safety, parachute deployment control has become a critical component. However, current parachute deployment controls are typically designed for specific drones, with fixed power input ranges, such as supporting only 12V or 24V. Therefore, adapting to different drone models incurs higher costs. Furthermore, current parachute deployment control systems usually only support a single communication interface, such as CAN, PWM, or RS232. Since different drones have different communication interfaces, users must simultaneously adjust the corresponding parachute deployment control system, hardware, and software when changing drone controllers, resulting in insufficient flexibility and wasted human and material resources.

[0019] To address one or more of the above-mentioned problems, the universal UAV parachute deployment control system of this application includes a microprocessor, and connected to the microprocessor are a barometric pressure sensor circuit, an IMU sensor circuit, a communication module, a parachute deployment control circuit, a display circuit, a data storage circuit, a battery voltage acquisition circuit, a parachute compartment status detection circuit, a power control circuit, and an indicator light circuit. The communication module includes a first communication circuit, a second communication circuit, and a third communication circuit for communication between the parachute deployment control system and the UAV. The first, second, and third communication circuits are pre-configured communication circuits. The power control circuit includes a first power input circuit and a second power input circuit, the input range of which is... The system includes: a pre-set range; a barometric pressure sensor circuit for acquiring barometric pressure data and transmitting it to the microprocessor; an IMU sensor circuit for acquiring attitude data and transmitting it to the microprocessor; a parachute deployment control circuit for receiving deployment signals and correspondingly controlling the gas generator to launch the parachute; a data storage circuit for detecting whether a storage device is inserted and storing the data of the parachute deployment control system in the storage device; a battery voltage acquisition circuit for detecting whether the power supply is normal; an indicator light circuit for displaying the power status of the parachute deployment control system; a parachute compartment status detection circuit for detecting the parachute compartment connection status and deployment status; and a display circuit including LEDs and a buzzer, as well as corresponding circuit structures for the LEDs and the buzzer, for displaying the status of the parachute deployment control system.

[0020] The preferred embodiment of the present invention describes a universal UAV parachute deployment control system, such as... Figure 1 As shown, the universal UAV parachute deployment control system includes a microprocessor, as well as a barometric pressure sensor circuit, an IMU sensor circuit, a communication module, a parachute deployment control circuit, a display circuit, a data storage circuit, a battery voltage acquisition circuit, a parachute compartment status detection circuit, a power control circuit, and an indicator light circuit connected to the microprocessor. The communication module includes a first communication circuit, a second communication circuit, and a third communication circuit, which are used for the parachute control system to communicate with the UAV. The first communication circuit, the second communication circuit, and the third communication circuit are pre-set communication circuits. The power control circuit includes a first power input circuit and a second power input circuit, and the input range of the first power input circuit and the second power input circuit is a preset range. The air pressure sensor circuit is used to acquire air pressure data and transmit it to the microprocessor; the IMU sensor circuit is used to acquire attitude data and transmit it to the microprocessor; the parachute deployment control circuit is used to receive the parachute deployment signal and correspondingly control the gas generator to launch the parachute; the data storage circuit is used to detect whether the storage device is inserted and to store the data of the parachute deployment control system in the storage device; the battery voltage acquisition circuit is used to detect whether the power supply is normal; the indicator light circuit is used to display the power status of the parachute deployment control system; the parachute compartment status detection circuit is used to detect the parachute compartment connection status and the parachute deployment status. The display circuit includes an LED and a buzzer, as well as the circuit structure corresponding to the LED and the buzzer, for displaying the status of the umbrella opening control system.

[0021] Specifically, in this invention, such as Figure 1 As shown, the parachute opening control system includes a microprocessor, a barometric pressure sensor circuit, an IMU sensor circuit, a communication module, a parachute opening control circuit, a display circuit, a data storage circuit, a battery voltage acquisition circuit, a parachute compartment status detection circuit, a power control circuit, and an indicator light circuit. All other circuits and modules are connected to the microprocessor, which is the IMU microprocessor.

[0022] The gas sensor circuit, composed of a pneumatic sensor, transmits the acquired air pressure data to the microprocessor for altitude calculation. The IMU sensor circuit transmits the acquired attitude data, i.e., acceleration and angle data, to the microprocessor for UAV attitude calculation. In a real-time configuration of this invention, the air pressure data from the air pressure sensor circuit is transmitted to the microprocessor via an I2C bus. The IMU sensor circuit uses a six-axis IMU U8, and the corresponding attitude data from the IMU sensor circuit is transmitted to the microprocessor via an SPI bus.

[0023] The parachute deployment control circuit includes a solid-state relay. When a parachute deployment signal is received, the relay is activated by a high-level signal, releasing an activation current to the gas generator inside the parachute compartment, thus ejecting the parachute and completing the deployment. The display circuit, i.e. Figure 1 The external indicator light and buzzer control circuit includes a trigger, which controls the external LEDs and buzzer. Specifically, in order to better alert ground personnel to the status of the parachute control system, external LEDs and buzzers are installed on the drone. When the microprocessor sends a corresponding signal to the trigger of the display circuit, the trigger outputs a corresponding signal to control the external LEDs and buzzer.

[0024] Data storage circuit, i.e. Figure 1The microSD circuit is mainly used to detect whether the corresponding storage device is inserted and to store the data in the corresponding storage device. The parachute controller contains a TF card for storing UAV flight data and parachute status data. The TF card slot is connected to an ESD protection diode via the SDMMC bus (SDMMC0, SDMMC1, SDMMC2, SDMMC3, SDMMC1_CMD, SDMMC1_CK) before being connected to the MCU. This prevents damage to the MCU from electrostatic discharge / surge during TF card insertion and removal. In this invention, when a TF card is inserted, its status is checked; if the TF card is not connected, a high-level output is shown.

[0025] The battery voltage acquisition circuit is used to detect whether the power supply is normal. It includes two resistors connected in series and a capacitor connected in parallel with the resistor on the side away from the power supply. In actual operation, the voltage after the power supply is divided by the two resistors is acquired to detect the battery voltage.

[0026] The indicator light circuit is used to display the power status of the umbrella opening controller. When there is no input power, the light flashes, with a green light indicating normal power and a red light indicating low voltage. When there is input power, the light stays on, with a red light indicating charging and a green light indicating charging is complete.

[0027] Furthermore, in this invention, the communication module is used for communication between the parachute deployment control system and the drone. In one embodiment of this invention, the communication module includes three communication circuits, each suitable for a different communication method. The communication method of each communication circuit can be set according to user requirements. In one embodiment of this invention, the first communication circuit uses the CAN communication protocol, the second communication circuit uses the RS232 communication protocol, and the third communication circuit uses the PWM communication protocol.

[0028] Furthermore, the first communication circuit includes a CAN transceiver and two terminating resistors. The two differential signal lines of the CAN transceiver that communicate with the UAV are respectively connected in series with a terminating resistor, and a switch is connected in series between the two terminating resistors to control the activation of the terminating resistors.

[0029] Specifically, such as Figure 2The diagram shows a schematic of the first communication circuit in one embodiment of the present invention. The first communication circuit consists of a CAN transceiver U4. CAN_TXD and CAN_RXD are connected to the microprocessor. CAN_H and CAN_L communicate with the external drone. A 60.4Ω terminating resistor (R10, R11) is connected in series with the CAN_H / CAN_L lines to suppress signal reflection. A switch K1 is also connected in series, allowing manual selection to enable or disable the terminating resistor. The drone's parachute deployment signal is transmitted via CAN signals and then converted to TTL level by the CAN transceiver before being input to the microprocessor for analysis.

[0030] Furthermore, the second communication circuit receives flight control signals and microprocessor inputs with corresponding communication protocols, performs level conversion, inputs the converted flight control signals to the microprocessor, and transmits the converted microprocessor inputs to the UAV. The third communication circuit shapes the received signal with the corresponding communication protocol based on a Schmitt trigger to obtain a digital signal, and then inputs the digital signal into the microprocessor.

[0031] Specifically, in one embodiment of the present invention, the second communication circuit communicates via the RS232 communication protocol and is composed of an RS232 chip. The second communication circuit receives flight control RS23 signals sent by the UAV, converts them to TTL level through the RS232 chip, and sends them to the microprocessor. When the second communication circuit receives a signal sent by the microprocessor through the serial communication transmitter, it converts it to RS232 level and forwards it to the UAV.

[0032] The third communication circuit uses the PWM communication protocol and includes a Schmitt trigger. The externally received signal is input into the Schmitt trigger, shaped accordingly, and a clean digital signal is obtained and input into the microprocessor.

[0033] Furthermore, the first power input circuit is connected to a fixed voltage power supply, and the second power input circuit is connected to a range voltage power supply. When the umbrella opening control system is connected to a range voltage power supply, the range voltage power supply is stepped down based on the step-down circuit of the second power input circuit to obtain a stepped-down voltage and realize power input.

[0034] Specifically, in this invention, the first power input circuit is connected to a fixed voltage power supply, specifically implemented through a power conversion device, such as a Type-C converter. In this invention, the first power input circuit is a 5V Type-C connection, and the second power input circuit is the drone battery input. Since the drone battery input voltage range is relatively wide, it is often necessary to modify the hardware structure to handle different input voltages for different drone batteries. In this invention, such as... Figure 3 As shown, for power inputs of different voltages, this invention uses a DC-DC converter, i.e., U2, to step down the voltage to 5V. Figure 3 In the diagram, C1, C2, C3, C4, C5, C6, C7, and C8 are capacitors, D1, D2, and D3 are diodes, R4, R5, and R6 are resistors, and L1 is an inductor.

[0035] Furthermore, the power control system of the present invention also includes a power multiplexer. In one embodiment of the present invention, when both the TYPE-C and the drone battery are connected, the power multiplexer prioritizes using the TYPE-C for power input. The power multiplexer can switch the power supply. When the TYPE-C is used to connect to the parachute controller for debugging or data reading, the drone battery input is cut off to avoid power loss of the drone battery.

[0036] Furthermore, the power control system of the present invention also includes a power management chip. Furthermore, the parachute compartment status detection circuit is used to detect the parachute compartment connection status, including a first resistor and a second resistor connected in sequence, and a first capacitor connected in parallel with the second resistor. The second resistor is connected to the parachute opening control circuit. The parachute compartment status detection circuit also includes a parachute compartment circuit, which includes a third resistor and is connected to the parachute opening controller circuit. When the parachute compartment is connected to the parachute opening control system, the voltage on the capacitor side before and after the parachute compartment is connected is obtained. When the voltage after the parachute compartment is connected is half of that before the connection, the parachute compartment is successfully connected, and the corresponding information is input into the microprocessor.

[0037] Specifically, in this invention, the parachute compartment status detection circuit is used to detect the parachute compartment connection status, such as... Figure 4As shown, R24 is the third resistor, i.e., the internal resistance of the gas generator; the first resistor R21 and the second resistor R22 are resistors with the same resistance value; C27 is the first capacitor; OUT is the output terminal of the umbrella controller's output current; VCC_3V0 is the power input; and AD0 is the location where the voltage is sampled on the side of capacitor C27. When the umbrella compartment is not connected, OUT is in an open circuit state, and the MCU samples the voltage at AD0 as the first voltage; when the umbrella compartment is connected, VCC_3V0 is divided by R21 and R22 and R24 inside the umbrella compartment, where the resistance values ​​of R21 and R22 are equal, and the voltage at AD0 sampled by the MCU is half of the first voltage.

[0038] Furthermore, the parachute compartment status detection circuit is also used to detect the parachute opening status; When the parachute compartment status detection circuit receives the parachute opening command from the microprocessor, the parachute opening controller circuit outputs an activation current to detect the voltage on the capacitor side before and after receiving the parachute opening command. When the voltage after receiving the parachute opening command is twice that before receiving the parachute opening command, the parachute opening is successful, and the corresponding parachute opening status is input to the microprocessor. If the voltage after receiving the umbrella opening command is the same as before receiving the umbrella opening command, then the umbrella opening fails, and the corresponding umbrella opening status is input into the microprocessor.

[0039] Specifically, in this invention, the parachute compartment status detection circuit is also used to detect the parachute opening status. Specifically, in this invention, when the microprocessor sends the parachute opening command, the parachute opening controller circuit OUT outputs an activation current, then the bridge wire of the gas generator inside the parachute compartment is disconnected, and OUT is in an open circuit state. At this time, the voltage at AD0 is sampled again. Since OUT is in an open circuit state, the voltage at AD0 is pulled up by R21 and restored to the voltage before the parachute compartment is connected, which is twice the voltage after the parachute compartment is connected, indicating that the parachute opening is successful.

[0040] After the microprocessor sends the umbrella opening command, the umbrella opening controller circuit OUT outputs the activation current. If the bridge wire in the gas generator is not disconnected, the voltage at AD0 is divided by VCC_3V0 through R21 and R22 and R24 in the umbrella compartment. The resistance values ​​of R21 and R22 are equal. The voltage at AD0 collected by the MCU does not change, which is half of the voltage at AD0 when the umbrella compartment is not connected. This indicates that the umbrella opening has failed.

[0041] The universal UAV parachute deployment control system of this invention includes a microprocessor, and connected to the microprocessor are a barometric pressure sensor circuit, an IMU sensor circuit, a communication module, a parachute deployment control circuit, a display circuit, a data storage circuit, a battery voltage acquisition circuit, a parachute compartment status detection circuit, a power control circuit, and an indicator light circuit. The communication module includes a first communication circuit, a second communication circuit, and a third communication circuit for communication between the parachute deployment control system and the UAV. These three communication circuits are pre-configured. The power control circuit includes a first power input circuit and a second power input circuit, with input ranges for both circuits being pre-configured. The air pressure sensor circuit is used to acquire air pressure data and transmit it to the microprocessor; the IMU sensor circuit is used to acquire attitude data and transmit it to the microprocessor; the parachute deployment control circuit is used to receive the parachute deployment signal and correspondingly control the gas generator to launch the parachute; the data storage circuit is used to detect whether the storage device is inserted and to store the data of the parachute deployment control system in the storage device; the battery voltage acquisition circuit is used to detect whether the power supply is normal; the indicator light circuit is used to display the power status of the parachute deployment control system; the parachute compartment status detection circuit is used to detect the parachute compartment connection status and the parachute deployment status; the display circuit includes LEDs and a buzzer, as well as the circuit structure corresponding to the LEDs and the buzzer, for displaying the status of the parachute deployment control system. This invention, through its communication module and power control circuit, enables corresponding communication and power supply for different drone models, eliminating the need for adjustments and modifications to the parachute deployment control system and reducing the waste of manpower and resources when configuring different types of drones. Furthermore, by incorporating a microprocessor, barometric pressure sensor circuit, IMU sensor circuit, parachute deployment control circuit, display circuit, data storage circuit, battery voltage acquisition circuit, parachute compartment status detection circuit, and indicator light circuit, the invention allows for comprehensive system testing before parachute use and automatic parachute deployment when required, thus facilitating accurate and convenient parachute deployment control.

[0042] Furthermore, such as Figure 5 As shown, based on the above-mentioned universal UAV parachute deployment control method, the present invention also provides a corresponding universal UAV parachute deployment control method, wherein the universal UAV parachute deployment control method includes: Step S10: Obtain the communication method and power input range of the target UAV; and select the communication circuit of the communication module and the power input circuit of the power control circuit in the parachute opening control system according to the communication method and the power input range. Step S20: Detect the connection status of the parachute compartment according to the parachute compartment status detection circuit; Step S30: Real-time acquisition of data transmitted by the barometric pressure sensor circuit and the IMU sensor circuit. When the parachute opening conditions are met, the microprocessor controls and outputs a parachute opening signal to the parachute opening control circuit. The parachute opening control circuit outputs an activation current to control the parachute compartment to release the parachute.

[0043] Specifically, in this invention, after the parachute control system is connected to the target UAV, the corresponding communication circuit and power input circuit are obtained according to the communication method and power input range of the target UAV. The communication method includes a first communication method, a second communication method, and a third communication method, and the power input range includes a fixed voltage power supply and a range voltage power supply.

[0044] Furthermore, the step of acquiring the communication method and power input range of the target UAV, and selecting the communication circuit of the communication module and the power input circuit of the power control circuit in the parachute deployment control system based on the communication method and the power input range, specifically includes: Obtain the target drone's communication method and power input range; When the target drone's communication mode is the first communication mode, the first communication circuit is selected to communicate with the target drone; when the target drone's communication mode is the second communication mode, the second communication circuit is selected to communicate with the target drone; when the target drone's communication mode is the third communication mode, the third communication circuit is selected to communicate with the target drone. When the power input range of the target UAV is a fixed voltage power supply, the first power input circuit is selected for power control; when the power input range of the target UAV is a range voltage power supply, the second power input circuit is selected for power control.

[0045] Furthermore, based on the above-mentioned universal UAV parachute deployment control system and method, the present invention also provides a UAV, which includes a universal UAV parachute deployment control system.

[0046] It should be noted that, in this document, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or terminal 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 terminal. Unless otherwise specified, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or terminal that includes that element.

[0047] Of course, those skilled in the art will understand that all or part of the processes in the above embodiments can be implemented by a computer program instructing related hardware (such as a processor, controller, etc.). The program can be stored in a computer-readable storage medium, and when executed, it can include the processes described in the above method embodiments. The computer-readable storage medium can be a memory, magnetic disk, optical disk, etc.

[0048] It should be understood that the application of the present invention is not limited to the examples above. Those skilled in the art can make improvements or modifications based on the above description, and all such improvements and modifications should fall within the protection scope of the appended claims.

Claims

1. A universal unmanned aerial vehicle (UAV) parachute deployment control system, characterized in that, The universal UAV parachute deployment control system includes a microprocessor, as well as a barometric pressure sensor circuit, an IMU sensor circuit, a communication module, a parachute deployment control circuit, a display circuit, a data storage circuit, a battery voltage acquisition circuit, a parachute compartment status detection circuit, a power control circuit, and an indicator light circuit connected to the microprocessor. The communication module includes a first communication circuit, a second communication circuit, and a third communication circuit, which are used for the parachute control system to communicate with the UAV. The first communication circuit, the second communication circuit, and the third communication circuit are pre-set communication circuits. The power control circuit includes a first power input circuit and a second power input circuit, and the input range of the first power input circuit and the second power input circuit is a preset range. The air pressure sensor circuit is used to acquire air pressure data and transmit it to the microprocessor; the IMU sensor circuit is used to acquire attitude data and transmit it to the microprocessor; the parachute deployment control circuit is used to receive the parachute deployment signal and correspondingly control the gas generator to launch the parachute; the data storage circuit is used to detect whether the storage device is inserted and to store the data of the parachute deployment control system in the storage device; the battery voltage acquisition circuit is used to detect whether the power supply is normal; the indicator light circuit is used to display the power status of the parachute deployment control system; the parachute compartment status detection circuit is used to detect the parachute compartment connection status and the parachute deployment status. The display circuit includes an LED and a buzzer, as well as the circuit structure corresponding to the LED and the buzzer, for displaying the status of the umbrella opening control system.

2. The universal UAV parachute deployment control system according to claim 1, characterized in that, The first communication circuit includes a CAN transceiver and two terminating resistors. The two differential signal lines of the CAN transceiver that communicate with the UAV are respectively connected in series with a terminating resistor, and a switch is connected in series between the two terminating resistors to control the activation of the terminating resistors.

3. The universal UAV parachute deployment control system according to claim 1, characterized in that, The second communication circuit receives flight control signals and microprocessor inputs with corresponding communication protocols, performs level conversion, inputs the converted flight control signals to the microprocessor, and transmits the converted microprocessor inputs to the UAV. The third communication circuit shapes the received signal with the corresponding communication protocol based on a Schmitt trigger to obtain a digital signal, and then inputs the digital signal into the microprocessor.

4. The universal UAV parachute deployment control system according to claim 1, characterized in that, The first power input circuit is connected to a fixed voltage power supply, and the second power input circuit is connected to a range voltage power supply. When the umbrella opening control system is connected to a range voltage power supply, the range voltage power supply is stepped down based on the step-down circuit of the second power input circuit to obtain a stepped-down voltage and realize power input.

5. The universal UAV parachute deployment control system according to claim 1, characterized in that, The parachute compartment status detection circuit is used to detect the parachute compartment connection status. It includes a first resistor and a second resistor connected in sequence, and a first capacitor is connected in parallel with the second resistor. The second resistor is connected to the parachute opening control circuit. The parachute compartment status detection circuit also includes a parachute compartment circuit, which includes a third resistor and is connected to the parachute opening controller circuit. When the parachute compartment is connected to the parachute opening control system, the voltage on the capacitor side before and after the parachute compartment is connected is obtained. When the voltage after the parachute compartment is connected is half of that before the connection, the parachute compartment is successfully connected, and the corresponding information is input into the microprocessor.

6. The universal UAV parachute deployment control system according to claim 5, characterized in that, The parachute compartment status detection circuit is also used to detect the parachute opening status; When the parachute compartment status detection circuit receives the parachute opening command from the microprocessor, the parachute opening controller circuit outputs an activation current to detect the voltage on the capacitor side before and after receiving the parachute opening command. When the voltage after receiving the parachute opening command is twice that before receiving the parachute opening command, the parachute opening is successful, and the corresponding parachute opening status is input to the microprocessor. If the voltage after receiving the umbrella opening command is the same as before receiving the umbrella opening command, then the umbrella opening fails, and the corresponding umbrella opening status is input into the microprocessor.

7. A parachute deployment control method for a general-purpose unmanned aerial vehicle (UAV) parachute according to any one of claims 1-6, characterized in that, The general-purpose UAV parachute deployment control method specifically includes: The communication method and power input range of the target UAV are obtained, and the communication circuit of the communication module and the power input circuit of the power control circuit in the parachute opening control system are selected according to the communication method and the power input range. The connection status of the parachute compartment is detected by the parachute compartment status detection circuit. The microprocessor acquires data transmitted by the barometric pressure sensor circuit and the IMU sensor circuit in real time. When the parachute opening conditions are met, the microprocessor controls and outputs a parachute opening signal to the parachute opening control circuit. The parachute opening control circuit outputs an activation current to control the parachute compartment to release the parachute.

8. The universal UAV parachute deployment control method according to claim 7, characterized in that, The step of acquiring the communication method and power input range of the target UAV, and selecting the communication circuit of the communication module and the power input circuit of the power control circuit in the parachute deployment control system based on the communication method and the power input range, specifically includes: Obtain the target drone's communication method and power input range; When the target drone's communication mode is the first communication mode, the first communication circuit is selected to communicate with the target drone; when the target drone's communication mode is the second communication mode, the second communication circuit is selected to communicate with the target drone; when the target drone's communication mode is the third communication mode, the third communication circuit is selected to communicate with the target drone. When the power input range of the target UAV is a fixed voltage power supply, the first power input circuit is selected for power control; when the power input range of the target UAV is a range voltage power supply, the second power input circuit is selected for power control.

9. A drone, characterized in that, The drone includes the universal drone parachute deployment control system as described in any one of claims 1-6.

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