WO2022183659A1 - Circuit de commutation, son procédé de commande et aéronef - Google Patents

Circuit de commutation, son procédé de commande et aéronef Download PDF

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Publication number
WO2022183659A1
WO2022183659A1 PCT/CN2021/106103 CN2021106103W WO2022183659A1 WO 2022183659 A1 WO2022183659 A1 WO 2022183659A1 CN 2021106103 W CN2021106103 W CN 2021106103W WO 2022183659 A1 WO2022183659 A1 WO 2022183659A1
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WIPO (PCT)
Prior art keywords
switch
aircraft
circuit
electrically connected
flight
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PCT/CN2021/106103
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English (en)
Chinese (zh)
Inventor
赵德力
全洪飞
张书存
周双久
李�杰
Original Assignee
广东汇天航空航天科技有限公司
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Priority claimed from CN202120456044.0U external-priority patent/CN214751375U/zh
Priority claimed from CN202110232158.1A external-priority patent/CN112904706A/zh
Application filed by 广东汇天航空航天科技有限公司 filed Critical 广东汇天航空航天科技有限公司
Publication of WO2022183659A1 publication Critical patent/WO2022183659A1/fr

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    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B9/00—Safety arrangements
    • G05B9/02—Safety arrangements electric
    • G05B9/03—Safety arrangements electric with multiple-channel loop, i.e. redundant control systems

Definitions

  • the present invention relates to the technical field of integrated circuits, and more particularly, to a switch circuit, a method for controlling the switch circuit, and an aircraft.
  • the current aircraft are basically powered by electricity. If the aircraft is powered off when it is working in the air, the consequences will be disastrous. However, the current aircraft cannot guarantee that the aircraft will not be powered off when it is in flight, resulting in There are safety hazards when the aircraft is working.
  • the present invention proposes a switch circuit, a method for controlling the switch circuit, and an aircraft to solve or partially solve the above problems.
  • an embodiment of the present invention provides a switch circuit, which is applied to an aircraft, and the switch circuit includes a flight state detection circuit, a power switch, a safety switch, and a switch control circuit.
  • the flight state detection circuit is used to detect whether the aircraft is in flight state
  • the power switch is electrically connected to the power supply of the aircraft
  • the safety switch is electrically connected to the power supply of the aircraft and the load of the aircraft, respectively
  • the switch control circuit is respectively connected to the flight state detection circuit, the power switch and the The safety switch is electrically connected for keeping the safety switch closed when the aircraft is in a flying state, so that when the aircraft is in a flying state, the power supply and the load are always connected.
  • an embodiment of the present invention provides a switch circuit control method.
  • the switch circuit control method is applied to the switch circuit of the first aspect.
  • the switch circuit control method includes: a flight state detection circuit detects whether the aircraft is in a flight state; a switch control circuit When the aircraft is in flight state, keep the safety switch closed, so that when the aircraft is in flight state, the power supply is connected to the load.
  • an embodiment of the present invention provides an aircraft, where the aircraft includes a memory and a processor, where the processor is configured to execute the method of the first aspect.
  • the switch circuit, the switch circuit control method and the aircraft provided by the embodiments of the present invention are composed of a flight state detection circuit, a power switch, a safety switch and a switch control circuit, wherein the flight state detection circuit is used to detect whether the aircraft is in a flight state , the power switch is electrically connected to the power supply of the aircraft; the safety switch is electrically connected to the power supply of the aircraft and the load of the aircraft; the switch control circuit is electrically connected to the flight state detection circuit, the power switch and the safety switch, respectively, for when the aircraft is in the flight state, Keep the safety switch closed, so that when the aircraft is in flight, the power supply and the load are always connected, so as to ensure that the power supply can always supply power to the load when the aircraft is in flight, avoiding the situation of load power failure, and effectively improving the aircraft's working time. security.
  • FIG. 1 shows a schematic structural diagram of a switch circuit provided according to an embodiment of the present invention.
  • FIG. 2 shows a schematic structural diagram of a switch circuit provided according to another embodiment of the present invention.
  • FIG. 3 shows a schematic structural diagram of a switch control circuit provided according to an embodiment of the present invention.
  • FIG. 4 shows a schematic structural diagram of a switch control circuit provided according to another embodiment of the present invention.
  • FIG. 5 shows a schematic structural diagram of a switch control circuit provided according to yet another embodiment of the present invention.
  • Fig. 6 shows a schematic structural diagram of a switch control circuit provided according to still another embodiment of the present invention.
  • FIG. 7 shows a flowchart of a method for controlling a switch circuit according to an embodiment of the present invention.
  • FIG. 8 shows a flowchart of the method S120 in the switch circuit control method provided in FIG. 7 according to the present invention.
  • FIG. 9 shows a flowchart of a method for controlling a switch circuit according to another embodiment of the present invention.
  • FIG. 10 shows a functional block diagram of a high-switch circuit control device provided by an embodiment of the present invention.
  • FIG. 11 shows a structural block diagram of an aircraft provided by an embodiment of the present invention.
  • FIG. 12 shows a storage medium for storing or carrying a program code for implementing a switching circuit control method according to an embodiment of the present invention according to an embodiment of the present invention.
  • aircraft technology has been widely used in various fields, such as unmanned aerial vehicles used for aerial photography in daily life, aircraft used for sowing seeds from the air in the agricultural field, Human aircraft, etc.
  • Most of these various aircrafts are driven by electricity, which means that the stable power supply of the power supply is the guarantee for the normal operation of the aircraft. If the aircraft is powered off in the air, it will directly crash. It may cause serious safety accident.
  • a switch circuit, a switch circuit control method, and an aircraft in the embodiments of the present invention are proposed.
  • the power supply of the aircraft and the load of the aircraft can be kept in constant communication, thereby ensuring that when the aircraft is in the flight state, The power supply can always supply power to the load, avoiding the situation of load power failure, and effectively improving the safety of the aircraft during operation.
  • FIG. 1 shows a schematic structural diagram of a switch circuit provided by an embodiment of the present invention.
  • the switch circuit 100 can be applied to an aircraft, which includes but is not limited to a multi-rotor aircraft, a jet aircraft, and the like.
  • the switch circuit 100 may include: a flight state detection circuit 110, a power switch 120, a safety switch 130, and a switch control circuit 140, wherein: the flight state detection circuit 110 is used to detect whether the aircraft is in a flight state; the power switch 120 and the aircraft's The power supply 210 is electrically connected; the safety switch 130 is electrically connected to the power supply 210 of the aircraft and the load 220 of the aircraft; the switch control circuit 140 is electrically connected to the flight state detection circuit 110 , the power switch 120 and the safety switch 130 respectively, and is used when the aircraft When in the flying state, keep the safety switch 130 closed, so that when the aircraft is in the flying state, the power supply 210 and the load 220 are always connected.
  • the flight state detection circuit 110 is used to detect whether the aircraft is in a flight state
  • the power supply 210 is electrically connected
  • the safety switch 130 is electrically connected to the power supply 210 of the aircraft and the load 220 of the aircraft
  • the switch control circuit 140 is electrical
  • the power supply 210 of the aircraft may be installed on the aircraft; it may not be installed on the aircraft. When the power supply 210 is not installed on the aircraft, the power supply 210 is connected to the aircraft through a line. Alternatively, the power source 210 of the aircraft may be a battery pack. The power supply 210 of the aircraft is mainly used to supply power to the load 220 of the aircraft, provide the flight power of the aircraft, and make various functions of the aircraft work normally.
  • the load 220 of the aircraft may be a power unit of the aircraft. Taking a multi-rotor aircraft as an example, the load 220 may be a motor of the multi-rotor aircraft. devices, communication devices, etc.
  • the switch control circuit 140 can also be used to control the opening and closing of the safety switch 130 according to the state of the power switch 120 when the aircraft is not in flight, so as to disconnect or connect the power supply 210 and the load 220 of the aircraft.
  • the switch 120 and the safety switch 130 of the aircraft are both turned off. At this time, there is no communication between the power supply 210 and the load 220 of the aircraft, and the aircraft is not working and is located on the ground. Not in flight either.
  • the power switch 120 When the aircraft receives the turn-on command, the power switch 120 is closed. If the power switch 120 is closed and the flight state detection circuit 110 detects that the aircraft is not in the flight state, the switch control circuit 140 controls the safety switch 130 to close. At this time, the power supply 210 of the aircraft can communicate with the load 220 of the aircraft through the closed safety switch 130 , the aircraft starts to work.
  • the switch control circuit 140 keeps the safety switch 130 closed, so that when the aircraft is in the flight state, the power supply 210 is always connected to the load 220. At this time, no matter whether the power switch 120 is in the closed state or the open state, it will not affect the working state of the safety switch 130, and the safety switch 130 will always be in the closed state, so as to prevent the user from accidentally touching the aircraft when the aircraft is in the flying state. Turning off the power switch 120 results in a situation in which the aircraft is powered off.
  • the flight state detection circuit 110 detects that the aircraft is not in the flight state, and the switch control circuit 140 can restore the function of the power switch 120. At this time, if the power switch 120 is disconnected, the switch control circuit 140 Then, the safety switch 130 is controlled to be turned off, thereby disconnecting the communication between the power source 210 and the load 220, and the aircraft stops working.
  • the switch circuit 100 is composed of a flight state detection circuit 110, a power switch 120, a safety switch 130 and a switch control circuit 140, wherein the flight state detection circuit 110 is used to detect whether the aircraft is in a flight state, and the power supply
  • the switch 120 is electrically connected to the power supply 210 of the aircraft
  • the safety switch 130 is electrically connected to the power supply 210 of the aircraft and the load 220 of the aircraft
  • the switch control circuit 140 is electrically connected to the flight state detection circuit 110, the power switch 120 and the safety switch 130, respectively, for When the aircraft is in the flight state, keep the safety switch 130 closed, so that the power source 210 is connected to the load 220 when the aircraft is in the flight state.
  • the switch control circuit 140 can be used when the aircraft is not in the In the flight state, the state of the safety switch 130 is controlled according to the state of the power switch 120, so as to safely turn on and off the aircraft; it is also possible to keep the safety switch 130 closed when the aircraft is in the flight state, that is, the power switch 120 is closed.
  • the state does not affect the state of the safety switch 130, thereby avoiding the situation that the load 220 is powered off due to the user's mistaken touch on the power switch 120 when the aircraft is in flight, effectively improving the safety of the aircraft during operation.
  • the flight state detection circuit 110 may include: a ranging module 111 and a flight control module 112, wherein the ranging module 111 is used to detect the distance between the aircraft and the ground;
  • the distance module 111 is electrically connected to the switch control circuit 140 for determining whether the aircraft is in a flying state according to the distance between the aircraft and the ground, and generating different signals according to whether the aircraft is in a flying state, and outputting the signal to the switch control circuit 140 .
  • the ranging module may include one or more combinations of ranging sensors such as ultrasonic ranging sensors, infrared ranging sensors, laser ranging sensors, and lidar ranging sensors.
  • ranging sensors such as ultrasonic ranging sensors, infrared ranging sensors, laser ranging sensors, and lidar ranging sensors.
  • the ranging module can collect the distance between the aircraft and the ground in real time to obtain distance information.
  • the flight control module 112 receives the distance information, and determines whether the distance information exceeds the distance threshold. If the distance information exceeds the distance threshold, it is determined that the aircraft is in a flying state. If the distance does not exceed the distance threshold, it is determined that the aircraft is not in a flying state.
  • the flight control module 112 determines that the aircraft is in the flight state, it can output flight information (eg, a low level) that is used to indicate that the aircraft is in the flight state.
  • the switch control circuit 140 receives the flight information, it can adjust the Safety switch 130 controls.
  • the distance threshold can be used to determine whether the aircraft is in the air or on the ground or close to the ground. Generally, when the aircraft is in the air, it is in the flying state, and when it is on the ground or close to the ground, it is not in the flying state, so it can be effectively used. , Accurately determine whether the aircraft is in flight state. As an example, for example, if the distance threshold is 20 cm, if the distance information is 100 cm, it can be determined that the aircraft is in a flying state, and the flight control module 112 can output flight information. If the distance information is 10cm, it can be determined that the aircraft is not in a flying state.
  • the flight state detection circuit 110 is formed by the ranging module and the flight control module 112, so that whether the aircraft is in the flight state can be determined according to the distance between the aircraft and the ground collected by the ranging module 111, which improves the Accuracy and efficiency of flight status judgment.
  • the flight state detection circuit 110 may include a communication module and a flight control module 112 .
  • the communication module is used for receiving flight state control instructions for the aircraft; the flight control module 112 is electrically connected to the communication module and the switch control circuit 140 respectively, and is used to determine whether the aircraft is in flight state according to the flight state control instructions.
  • the communication module may include one or more combinations of communication modules such as a 4G communication module, a 5G communication module, and a Bluetooth communication module.
  • the flight state control command may be a control command for controlling the flight of the aircraft (eg, control commands for controlling the aircraft to ascend, descend, turn, accelerate, decelerate, etc.).
  • the user can send the flight state control command to the aircraft through the control terminal to make the aircraft enter the flight state. Therefore, if the flight control module receives the flight state control command through the communication module, the flight state control command can be combined with the flight state control command. Specify the flight state control command for matching. If it matches, it can be determined that the aircraft is in flight state.
  • the flight state control command when determining whether the flight state control command matches the designated flight state control command, it can be determined whether the flight state control command includes the designated flight state control command, and if so, then determine the flight state control command and the designated flight state control command. match.
  • the designated flight state control command includes a first control command and a second control command
  • the flight state control command received by the flight control module includes at least one of the first control command and the second control command
  • the specified flight state control instruction includes the first control instruction and the second control instruction
  • the flight state control instruction received by the flight control module includes the first control instruction and the second control instruction
  • the flight state can be determined.
  • the control command matches the specified flight state control command.
  • control terminal may be a remote controller of an aircraft, a smart phone, or a personal computer (eg, a tablet computer, a notebook computer), or the like.
  • the flight status detection circuit 110 may have both a ranging module 111 and a communication module. If the flight control module 112 does not receive a flight status control command through the communication module, the distance measurement module 111 obtains the distance between the aircraft and the ground. distance, and determine whether the aircraft is in flight state according to the distance. Thus, it is more accurate and flexible to judge whether the aircraft is in flight state.
  • the flight status detection circuit is formed by the communication module and the flight control module.
  • the flight state control command it can be quickly and effectively judged whether the aircraft is in the flight state according to the flight state control command.
  • the flight state detection circuit 110 may include an acceleration sensor and a flight control module 112, and the flight control module 112 is electrically connected to the acceleration sensor and the switch control circuit 140, respectively.
  • the acceleration sensor can collect the acceleration information of the aircraft in real time. After receiving the acceleration information, the flight control module 112 can obtain the acceleration change of the aircraft in a specified direction (such as above the aircraft) according to the acceleration information. If the acceleration If the variation is greater than the acceleration variation threshold, it can be determined that the aircraft is in a flying state.
  • the specified direction may be one direction or multiple directions, which is not limited here.
  • the flight state detection circuit 110 is formed by the acceleration sensor and the flight control module 112, When the flight control module 112 receives the acceleration information of the aircraft through the acceleration sensor, it can accurately and effectively determine whether the aircraft is in a flying state according to the acceleration information of the aircraft.
  • the flight state detection circuit 110 may also be composed of a speed sensor and a flight control module 112, and the flight control module 112 may be electrically connected to the speed sensor and the switch control circuit 140, respectively.
  • the flight control module 112 can collect the speed of the aircraft in a specified direction through a speed sensor, and if the speed in the specified direction is not 0, it can be determined that the aircraft is in a flying state.
  • the switch circuit 100 further includes:
  • the resistance circuit 150 the first end of the resistance circuit 150 is electrically connected to the power supply 210 and the first end of the safety switch 130 respectively, the second end of the resistance circuit 150 is respectively electrically connected to the first end of the power switch 120 and the switch control circuit 140,
  • the second end of the safety switch 130 is electrically connected to the load 220 , the second end of the power switch 120 is grounded, and the first end of the power switch 120 is electrically connected to the power source 210 and the power switch 120 respectively.
  • the resistor circuit 150 may include one or more resistors, and when the resistor circuit 150 includes multiple resistors, the multiple resistors may be connected in series or/and in parallel to form a resistor circuit with a specified resistance value.
  • the switch control circuit 140 may be a logic gate circuit, and the logic gate circuit may determine the output level signal according to the input level signal.
  • the switch circuit 140 includes a first input terminal, a second input terminal and an output terminal; the first input terminal is electrically connected to the first terminal of the power switch 120; the second input terminal is connected to the flight state detection circuit 110 is electrically connected; the output terminal is electrically connected to the safety switch 130, the output terminal outputs a high level when the first input terminal is at a high level, and when the second input terminal is at a high level, so that the safety switch is turned off open, and when the second input terminal is at a low level, output a low level to close the safety switch.
  • the state and output signal relationship among the power switch 120 , the flight control module 112 , the switch control circuit 140 and the safety switch 130 in the switch circuit 100 may be as shown in Table 1:
  • the switch control circuit 140 can have two inputs, one input from the power switch 120 (hereinafter referred to as the first input), and the other input from the flight control module 112 (hereinafter referred to as the second input).
  • the flight control module 112 can output different level signals according to whether the aircraft is in a flying state. As shown in FIG. 2 , when the safety switch 130 is closed, the current of the power supply 210 flows to the ground through the resistance circuit, which is equivalent to the first input being low level. At this time, if the aircraft is not in the flying state, the output of the flight control module 112 is high. level, that is, the second input is a high level, the switch control circuit 140 can output a low level, so that the safety switch 130 is closed, and the power supply 210 can supply power to the load 220, thereby making the aircraft work and enter the flying state.
  • the flight control module 112 When the aircraft enters the flight state, the flight control module 112 outputs a low level. At this time, no matter whether the power switch 120 is open or closed, the switch control circuit 140 will only output a low level to keep the safety switch 130 closed and the aircraft is in In the flight state, the power source 210 can supply power to the load 220 . This can avoid the situation that the user accidentally touches the power switch 120 after the aircraft takes off and the power source 210 is turned off.
  • the switch control circuit 140 includes: a first diode V1 , a second diode V2 and a first resistor R1 , wherein: the first diode V1 The negative electrode is electrically connected to the first end of the power switch 120; the negative electrode of the second diode V2 is electrically connected to the flight state detection circuit 110; the first end of the first resistor R1 is electrically connected to the circuit power supply VCC, and the first end of the first resistor R1 is electrically connected to the circuit power VCC.
  • the two terminals are respectively electrically connected to the anode of the first diode V1 , the anode of the second diode V2 and the safety switch 130 , wherein the circuit power supply VCC is used to supply power to the switch control circuit 140 .
  • the first resistor R1 may be 10K ⁇ .
  • the cathode of the first diode V1 is the first input terminal IN1
  • the cathode of the second diode V2 is the first input terminal IN2
  • the anode of the first diode V1 and the second diode V2 The junction of the positive electrode of the first resistor R1 and the second end of the first resistor R1 leads to the output end OUT.
  • Table 1 When the first input terminal IN1 is at a low level and the second input terminal IN2 is at a high level, the output terminal OUT is at a low level.
  • the output terminal OUT is at a high level.
  • the output terminal OUT is at a low level.
  • the switch control circuit 140 includes: a first Schottky diode V3 , a second Schottky diode V4 and a second resistor R2 , wherein: the first Schottky diode V3 The cathode of the diode V3 is electrically connected to the first end of the power switch 120; the cathode of the second Schottky diode V4 is electrically connected to the flight state detection circuit 110; the first end of the second resistor R2 is electrically connected to the circuit power supply VCC, the second The second end of the resistor R2 is respectively electrically connected to the anode of the first Schottky diode V3 , the anode of the second Schottky diode V4 and the safety switch 130 , wherein the circuit power VCC is used to supply power to the switch control circuit 140 .
  • the second resistor R2 may be 10K ⁇ .
  • the first Schottky diode V3 The cathode of the diode V3 is electrically
  • the cathode of the first Schottky diode V3 is the first input terminal IN1
  • the cathode of the second Schottky diode V4 is the first input terminal IN2
  • the anode of the first Schottky diode V3 the cathode of the second Schottky diode V3
  • the junction of the anode of the Turkey diode V4 and the second end of the second resistor R2 leads to the output end DT_Ctrl.
  • Table 1 When the first input terminal IN1 is at a low level and the second input terminal IN2 is at a high level, the output terminal DT_Ctrl is at a low level.
  • the output terminal DT_Ctrl When the first input terminal IN1 is at a high level and the second input terminal IN2 is at a high level, the output terminal DT_Ctrl is at a high level. When the second input terminal IN2 is at a low level, the output terminal DT_Ctrl is at a low level.
  • the switch control circuit 140 includes: a first MOS transistor V5, a second MOS transistor V6 and a third resistor R3, a first MOS transistor V5 and a second MOS transistor V6 All are P-type MOS transistors, wherein: the gate of the first MOS transistor V5 is electrically connected to the first end of the power switch 120, the drain of the first MOS transistor V5 is grounded; the gate of the second MOS transistor V6 is connected to the flight state detection The circuit 110 is electrically connected, and the drain of the second MOS transistor V6 is grounded; the first end of the third resistor R3 is electrically connected to the circuit power supply VCC, and the second end of the third resistor R3 is respectively connected to the source of the first MOS transistor V5, the second end of the third resistor R3 The source of the MOS transistor V6 is electrically connected to the safety switch 130 , wherein the circuit power supply VCC is used to supply power to the switch control circuit 140 .
  • the third resistor R3 is P-type MOS transistors, wherein
  • the gate of the first MOS transistor V5 is the first input terminal IN1
  • the gate of the second MOS transistor V6 is the second input terminal IN2
  • the second terminal of the third resistor R3 and the source of the first MOS transistor V5
  • the junction of the sources of the second MOS transistor V6 leads to the output terminal OUT.
  • Table 1 When the first input terminal IN1 is at a low level and the second input terminal IN2 is at a high level, the output terminal OUT is at a low level. When the first input terminal IN1 is at a high level and the second input terminal IN2 is at a high level, the output terminal OUT is at a high level. When the second input terminal IN2 is at a low level, the output terminal OUT is at a low level.
  • the switch control circuit 140 includes: a chip U6, the chip U6 may specifically include MC14081BDG, and the first input end of the chip U6, that is, the pin IN1A, can be connected with the power switch
  • the first terminal of 120 is electrically connected to the second input terminal of the chip U6, that is, the pin IN2A can be electrically connected to the flight state detection circuit 110, and specifically can be electrically connected to the output terminal of the flight control module 112, and the output terminal of the chip U6 can be electrically connected.
  • the terminal, that is, the pin OUTA may be electrically connected with the safety switch 130 .
  • the chip U6 can realize the signal processing shown in Table 1.
  • the switch control circuit 140 can also be other logic gate circuits, and the logic gate circuit can realize the signal processing shown in Table 1.
  • the specific circuit structure This is not limited.
  • the switch circuit 100 may further include a failure feedback circuit, which may be used to determine whether the power switch 120 can work normally when the aircraft is in flight, and the failure feedback circuit may be connected to the power switch 120 and the power switch 120. between the switch control circuit 140 .
  • the failure feedback circuit can detect whether there is current between the power switch 120 and the switch control circuit 140. If the power switch 120 is closed , the failure feedback circuit detects that there is no current between the power switch 120 and the switch control circuit 140, and determines that the power switch 120 fails, and if there is current, determines that the power switch 120 is normal.
  • failure feedback circuit detects the current between the power switch 120 and the switch control circuit 140 when the power switch 120 is switched off, it is determined that the power switch 120 fails.
  • the failure feedback circuit can feed back failure information to the user's terminal device to remind the user that the power switch 120 fails.
  • the failure feedback circuit may include a processing device, a current detection device, and a communication device
  • the current detection device may be connected between the power switch 120 and the switch control circuit 140
  • the processing device may be electrically connected to the current detection device and the communication device, respectively
  • the processing device detects that there is no current through the current detection device and the communication device receives the closing instruction from the user, it generates failure information, and sends the failure information to the user's terminal equipment through the communication device.
  • the processing device detects that there is current through the current detection device and the communication device receives the closing command from the user, it generates normal reminder information, and sends the normal reminder information to the user's terminal equipment through the communication device to remind the user of the power The switch works fine.
  • the switch circuit of this embodiment will temporarily turn off the function of the power switch when the aircraft is in flight, the user cannot easily know whether the power switch is abnormal.
  • the switch circuit can also include a failure feedback circuit, which can be used to judge whether the power switch of the aircraft can work normally when the aircraft is in flight, so as to timely remind the user whether the power switch fails to ensure that the user can safely Control the aircraft.
  • FIG. 7 shows a switch circuit control method provided by an embodiment of the present invention. The method can be applied to the switch circuit of the above-mentioned embodiment, and the switch circuit control method may include:
  • the flight state detection circuit detects whether the aircraft is in a flight state.
  • the flight state detection circuit may include a ranging module for acquiring distance information between the aircraft and the ground, and a flight control module for receiving the distance information, the flight control module may determine whether the distance information exceeds a distance threshold , if it exceeds, it can be determined that the aircraft is in the flying state, if not, it can be determined that the aircraft is not in the flying state.
  • the switch control circuit keeps the safety switch closed when the aircraft is in the flight state, so that when the aircraft enters the flight state, the power supply and the load are always connected.
  • S120 may include the following steps:
  • the switch control circuit controls the opening and closing of the safety switch according to the state of the power switch, so as to disconnect or connect the aircraft power supply with the load.
  • the switch control circuit keeps the safety switch closed when the aircraft is in a flying state, so that when the aircraft is in a flying state, the power supply is connected to the load.
  • the user can turn on or turn off the aircraft through the power switch only when the aircraft is not in the flying state (equivalent to when the aircraft is on the ground).
  • the load and power supply are guaranteed by closing the safety switch.
  • the connectivity between them can ensure that the aircraft can take off and land safely and will not be powered off when in the air.
  • FIG. 9 shows a switch circuit control method provided by an embodiment of the present invention.
  • the method can be applied to the switch circuit of the above-mentioned embodiment, and is specifically applied to the switch control circuit of the switch circuit.
  • the switch circuit control method can be include:
  • S210 Acquire the flight state information collected by the flight state detection circuit and the working state of the power switch.
  • the flight state information may include first flight information for indicating that the aircraft is in a flight state and second flight information for indicating that the aircraft is not in a flight state.
  • the working state of the power switch may include an open state and a closed state.
  • the switch control circuit When the switch control circuit receives the second flight information and the power switch is in a closed state, it can generate a first control command and send the first control command to the safety switch to instruct the safety switch to close.
  • the switch control circuit When the switch control circuit receives the first flight information, it can generate a second control command, and send the second control command to the safety switch to instruct the safety switch to remain closed.
  • FIG. 10 shows a switch circuit control apparatus 400 provided by an embodiment of the present invention, which is applied to the switch circuit of the above-mentioned embodiment, and is specifically applied to a switch control circuit.
  • the switch circuit control apparatus 400 includes: an information acquisition module 410, The first control module 420 and the second control circuit 430 . in:
  • the information acquisition module 410 is used for acquiring the flight state information collected by the flight state detection circuit and the working state of the power switch.
  • the first control module 420 is configured to control the safety switch to be closed if it is determined according to the flight state information that the aircraft is not in the flight state and the power switch is in the closed state.
  • the second control circuit 430 is configured to control the safety switch to close if it is determined according to the flight state information that the aircraft is in a flight state.
  • the coupling or direct coupling or communication connection between the modules shown or discussed may be through some interfaces, and the indirect coupling or communication connection of devices or modules may be electrical, mechanical or otherwise.
  • each functional module in each embodiment of the present invention may be integrated into one processing module, or each module may exist physically alone, or two or more modules may be integrated into one module.
  • the above-mentioned integrated modules can be implemented in the form of hardware, and can also be implemented in the form of software function modules.
  • FIG. 11 shows a structural block diagram of an aircraft provided by an embodiment of the present invention.
  • the aircraft 500 may be the aircraft 500 capable of running the program in the aforementioned embodiments.
  • Aircraft 500 in the present invention may include one or more of the following components: processor 510, memory 520, and one or more programs, wherein one or more programs may be stored in memory 520 and configured to be executed by one or more programs.
  • the processors 510 execute, and one or more programs are configured to execute the methods described in the foregoing method embodiments.
  • Processor 510 may include one or more processing cores.
  • the processor 510 uses various interfaces and lines to connect various parts of the entire aircraft 500, and executes the aircraft by running or executing the instructions, programs, code sets or instruction sets stored in the memory 520, and calling the data stored in the memory 520. 500 of various functions and processing data.
  • the processor 510 may adopt at least one of a digital signal processing (Digital Signal Processing, DSP), a Field-Programmable Gate Array (Field-Programmable Gate Array, FPGA), and a Programmable Logic Array (Programmable Logic Array, PLA).
  • DSP Digital Signal Processing
  • FPGA Field-Programmable Gate Array
  • PLA Programmable Logic Array
  • the processor 510 may integrate one or a combination of a central processing unit 510 (Central Processing Unit, CPU), a graphics processor 510 (Graphics Processing Unit, GPU), a modem, and the like.
  • CPU Central Processing Unit
  • GPU Graphics Processing Unit
  • the CPU mainly handles the operating system, user interface and application programs, etc.
  • the GPU is used for rendering and drawing of the display content
  • the modem is used to handle wireless communication. It can be understood that, the above-mentioned modem may not be integrated into the processor 510, and is implemented by a communication chip alone.
  • the processor 510 may be equivalent to the switch control circuit in FIG. 1 .
  • the memory 520 may include random access memory (Random Access Memory, RAM), or may include read-only memory (Read-Only Memory). Memory 520 may be used to store instructions, programs, codes, sets of codes, or sets of instructions.
  • the memory 520 may include a stored program area and a stored data area, wherein the stored program area may store instructions for implementing an operating system, instructions for implementing at least one function, instructions for implementing the above method embodiments, and the like.
  • the storage data area can also store data (such as positioning information, working state parameters, and driving record data) created by the aircraft in use.
  • the aircraft may also include:
  • the flight state detection circuit 530 is electrically connected to the processor 510 for detecting whether the aircraft is in a flight state.
  • a safety switch 540 is electrically connected to the processor 510, and the safety switch 540 can turn on the power supply of the aircraft and the load 220 when it is closed, and de-energize the load 220 of the aircraft when it is turned off.
  • FIG. 12 shows a structural block diagram of a computer-readable storage medium provided by an embodiment of the present invention.
  • the computer-readable medium 600 stores program codes 610, and the program codes 610 can be invoked by the processor to execute the methods described in the above method embodiments.
  • the computer-readable storage medium 600 may be an electronic memory such as flash memory, EEPROM (Electrically Erasable Programmable Read Only Memory), EPROM, hard disk, or ROM.
  • the computer-readable storage medium includes a non-transitory computer-readable storage medium.
  • a computer-readable storage medium has storage space for program code to perform any of the method steps in the above-described methods. These program codes can be read from or written to one or more computer program products.
  • the program code may, for example, be compressed in a suitable form.
  • the switch circuit, the switch circuit control method, and the aircraft provided by the embodiments of the present invention are composed of a flight state detection circuit, a power switch, a safety switch, and a switch control circuit, wherein: the flight state detection circuit is used to detect Whether the aircraft is in flight state, the power switch is electrically connected to the power supply of the aircraft; the safety switch is electrically connected to the power supply of the aircraft and the load of the aircraft; the switch control circuit is electrically connected to the flight state detection circuit, the power switch and the safety switch respectively, and is used when the aircraft When in flight, keep the safety switch closed, so that when the aircraft is in flight, the power supply is connected to the load.
  • the switch control circuit can be used when the aircraft is not in flight state.
  • the state of the safety switch is controlled by the state of the power switch, so as to safely turn on and off the aircraft; it is also possible to keep the safety switch closed when the aircraft is in flight state, that is, the state of the power switch does not affect the state of the safety switch, thus avoiding the aircraft In the flight state, the load is powered off due to the user's mistaken touch on the power switch, which effectively improves the safety of the aircraft during operation.
  • the switch circuit of this embodiment can achieve the above effects by only introducing a safety switch and a switch control circuit on the basis of the circuit structure of the original aircraft, avoids excessive changes to the circuit structure of the aircraft, and is not only easy to install, but also low in cost , can be widely used.

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  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Automation & Control Theory (AREA)
  • Traffic Control Systems (AREA)

Abstract

La présente invention concerne un circuit de commutation, son procédé de commande et un aéronef qui relèvent du domaine technique des circuits intégrés. Le circuit de commutation (100) est constitué d'un circuit de détection d'état de vol (110), d'un commutateur de courant (120), d'un interrupteur de sécurité (130) et d'un circuit de commande de commutation (140). Le circuit de détection d'état de vol (110) est utilisé pour détecter si l'aéronef est dans un état de vol. Le commutateur de courant (120) est raccordé électriquement à une source de courant (210) de l'aéronef. L'interrupteur de sécurité (130) est raccordé électriquement respectivement à la source de courant (210) de l'aéronef et à une charge (220) de l'aéronef. Le circuit de commande de commutation (140) est raccordé électriquement respectivement au circuit de détection d'état de vol (110), au commutateur de courant (120) et à l'interrupteur de sécurité (130) de manière à maintenir l'interrupteur de sécurité (130) fermé lorsque l'aéronef est dans l'état de vol, de sorte que la source de courant (210) est toujours en communication avec la charge (220) lorsque l'aéronef est dans l'état de vol. De plus, il est garanti que la source de courant (210) peut toujours alimenter en courant la charge (220) lorsque l'aéronef est dans l'état de vol, ce qui évite la situation de désactivation de la charge (220) et, par conséquent, accroît efficacement la sécurité de l'aéronef en fonctionnement.
PCT/CN2021/106103 2021-03-02 2021-07-13 Circuit de commutation, son procédé de commande et aéronef WO2022183659A1 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
CN202120456044.0U CN214751375U (zh) 2021-03-02 2021-03-02 开关电路
CN202120456044.0 2021-03-02
CN202110232158.1 2021-03-02
CN202110232158.1A CN112904706A (zh) 2021-03-02 2021-03-02 开关电路、开关电路控制方法以及飞行器

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WO2022183659A1 true WO2022183659A1 (fr) 2022-09-09

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US9828107B1 (en) * 2014-08-25 2017-11-28 Stc.Unm Redundant component and intelligent computerized control system for multi-rotor VTOL aircraft
US20190086463A1 (en) * 2017-09-19 2019-03-21 Drone Racing League, Inc. Wireless power initiated aircraft test system
CN111258241A (zh) * 2018-12-03 2020-06-09 北京华航无线电测量研究所 一种用于航空器数据记录设备的无线传输开关机控制装置
CN111682644A (zh) * 2020-06-08 2020-09-18 朗星无人机系统有限公司 一种基于有人机无人化改装的电源管理系统
CN111886771A (zh) * 2019-03-28 2020-11-03 深圳市大疆创新科技有限公司 用于管理电力供应的方法、电路及装置
CN112904706A (zh) * 2021-03-02 2021-06-04 广东汇天航空航天科技有限公司 开关电路、开关电路控制方法以及飞行器

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Publication number Priority date Publication date Assignee Title
US9828107B1 (en) * 2014-08-25 2017-11-28 Stc.Unm Redundant component and intelligent computerized control system for multi-rotor VTOL aircraft
US20190086463A1 (en) * 2017-09-19 2019-03-21 Drone Racing League, Inc. Wireless power initiated aircraft test system
CN111258241A (zh) * 2018-12-03 2020-06-09 北京华航无线电测量研究所 一种用于航空器数据记录设备的无线传输开关机控制装置
CN111886771A (zh) * 2019-03-28 2020-11-03 深圳市大疆创新科技有限公司 用于管理电力供应的方法、电路及装置
CN111682644A (zh) * 2020-06-08 2020-09-18 朗星无人机系统有限公司 一种基于有人机无人化改装的电源管理系统
CN112904706A (zh) * 2021-03-02 2021-06-04 广东汇天航空航天科技有限公司 开关电路、开关电路控制方法以及飞行器

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