WO2017128113A1 - 电源控制电路、电子调速器、无人飞行器及控制方法 - Google Patents

电源控制电路、电子调速器、无人飞行器及控制方法 Download PDF

Info

Publication number
WO2017128113A1
WO2017128113A1 PCT/CN2016/072362 CN2016072362W WO2017128113A1 WO 2017128113 A1 WO2017128113 A1 WO 2017128113A1 CN 2016072362 W CN2016072362 W CN 2016072362W WO 2017128113 A1 WO2017128113 A1 WO 2017128113A1
Authority
WO
WIPO (PCT)
Prior art keywords
circuit
control circuit
resistor
capacitor
power
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/CN2016/072362
Other languages
English (en)
French (fr)
Inventor
倪锦云
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
SZ DJI Technology Co Ltd
Original Assignee
SZ DJI Technology Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by SZ DJI Technology Co Ltd filed Critical SZ DJI Technology Co Ltd
Priority to CN201680002467.7A priority Critical patent/CN107078640B/zh
Priority to PCT/CN2016/072362 priority patent/WO2017128113A1/zh
Publication of WO2017128113A1 publication Critical patent/WO2017128113A1/zh
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Images

Classifications

    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
    • H02M3/00—Conversion of DC power input into DC power output
    • H02M3/02—Conversion of DC power input into DC power output without intermediate conversion into AC
    • H02M3/04—Conversion of DC power input into DC power output without intermediate conversion into AC by static converters
    • H02M3/10—Conversion of DC power input into DC power output without intermediate conversion into AC by static converters using discharge tubes with control electrode or semiconductor devices with control electrode
    • H02M3/145—Conversion of DC power input into DC power output without intermediate conversion into AC by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal
    • H02M3/155—Conversion of DC power input into DC power output without intermediate conversion into AC by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only
    • H02M3/156—Conversion of DC power input into DC power output without intermediate conversion into AC by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only with automatic control of output voltage or current, e.g. switching regulators
    • H02M3/158—Conversion of DC power input into DC power output without intermediate conversion into AC by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only with automatic control of output voltage or current, e.g. switching regulators including plural semiconductor devices as final control devices for a single load
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02H—EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS
    • H02H9/00—Emergency protective circuit arrangements for limiting excess current or voltage without disconnection
    • H02H9/02—Emergency protective circuit arrangements for limiting excess current or voltage without disconnection responsive to excess current
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to a power control circuit, an electronic governor, an unmanned aerial vehicle and a control method thereof, in particular to a power control circuit capable of being used for power-on and anti-sparking, and belongs to the technical field of aircraft.
  • the electronic governor is one of the most important components in the aircraft, used to drive the rotation of the motor in the aircraft to achieve the start and stop of the aircraft and speed regulation.
  • the electronic governor of the drone is used to drive the brushless motor by converting the DC voltage of the replaceable battery into an AC voltage.
  • the current during the conversion is large, and a large capacitor must be used to ensure the instantaneous energy supply.
  • the ESC is installed on the UAV, it is equivalent to a plurality of large capacitors in parallel. From the perspective of the total power supply plug, the capacitive load is large. In the process of battery replacement, the battery plug is often charged. When directly inserted into the battery compartment of the drone, the hot plug process will occur. When the power plug is plugged in, the plug touches a large spark, which reduces the life and performance of the plug.
  • preventing sparking during hot plugging is generally performed by first connecting a resistor to pre-charge a large capacitor for supplying a large current to the motor in the unmanned aerial vehicle, and then manually controlling the auxiliary switch.
  • the capacitor is connected in series to both ends of the power supply to prevent sparking.
  • the object of the present invention is to provide a power control circuit, an electronic governor, an unmanned aerial vehicle and a control method for solving the technical problem that the anti-sparking operation in the hot plugging process of the UAV battery in the prior art requires complicated operation.
  • the present invention provides the following technical solutions:
  • a power supply control circuit for an unmanned aerial vehicle including: a capacitive load Circuit, switching circuit and delay control circuit;
  • the input end of the capacitive load circuit is electrically connected to the positive pole of the power source
  • the switching circuit is connected in series between an output end of the load circuit and a power ground;
  • the power supply positive pole and the power ground are respectively connected between the input end and the output end of the delay control circuit, and the control end of the delay control circuit is electrically connected to the switch circuit;
  • the delay control circuit is configured to control the switch circuit to switch from a high impedance output state to a low impedance output state after the power-on time exceeds a preset time when the power source positive pole and the power source ground are in a power-on state.
  • an electronic governor including a motor drive circuit and a power control circuit, wherein the power control circuit is electrically connected to the motor drive circuit for supplying power to the motor drive circuit, and the power control circuit Including: capacitive load circuit switching circuit and delay control circuit;
  • the input end of the capacitive load circuit is electrically connected to the positive pole of the power source
  • the switching circuit is connected in series between an output end of the load circuit and a power ground;
  • the power supply positive pole and the power ground are respectively connected between the input end and the output end of the delay control circuit, and the control end of the delay control circuit is electrically connected to the switch circuit;
  • the delay control circuit is configured to control the switch circuit to switch from a high impedance output state to a low impedance output state after the power-on time exceeds a preset time when the power source positive pole and the power source ground are in a power-on state.
  • an unmanned aerial vehicle comprising: an electric motor and an electronic governor for providing flight power;
  • the electronic governor is electrically connected to the motor for controlling an operating state of the motor
  • the electronic governor includes: a motor drive circuit and a power control circuit;
  • the power control circuit is electrically connected to the motor driving circuit for supplying power to the motor driving circuit;
  • the power control circuit includes: a capacitive load circuit switch circuit and a delay control circuit;
  • the input end of the capacitive load circuit is electrically connected to the positive pole of the power source
  • the switching circuit is connected in series between an output end of the load circuit and a power ground;
  • the power supply positive pole and the power ground are respectively connected between the input end and the output end of the delay control circuit, and the control end of the delay control circuit is electrically connected to the switch circuit;
  • the delay control circuit is configured to control the switch circuit to switch from a high impedance output state to a low impedance output state after the power-on time exceeds a preset time when the power source positive pole and the power source ground are in a power-on state.
  • a control method of a power output circuit including a capacitive load circuit for providing a large current output to an unmanned aircraft motor, the power output circuit further comprising: a switch circuit, the switch The circuit is connected in series between the capacitive load circuit and the power ground;
  • a method of controlling the switching circuit includes:
  • the switching circuit is controlled to switch from a high impedance output state to a low impedance output state after a power-on time between the power source positive pole and the power source ground exceeds a preset time.
  • the power supply control circuit, the electronic governor, the unmanned aerial vehicle and the control method provided by the invention control the high-impedance output of the switching circuit after the power-on time between the positive pole and the power ground exceeds the preset time by the delay control circuit
  • the state switches to a low-impedance output state, which reduces the manual operation of the main power supply, enabling automatic control of spark-proof and high-current output.
  • FIG. 1 is a schematic diagram of a power supply control circuit according to Embodiment 1 of the present invention.
  • FIG. 2a is a schematic diagram of a power control circuit according to Embodiment 2 of the present invention.
  • FIG. 2b is a schematic diagram of another power control circuit according to Embodiment 2 of the present invention.
  • FIG. 3 is a schematic diagram of a power supply control circuit according to Embodiment 3 of the present invention.
  • FIG. 4 is a schematic diagram of a power supply control circuit according to Embodiment 4 of the present invention.
  • FIG. 5 is a schematic diagram of a power supply control circuit according to Embodiment 5 of the present invention.
  • FIG. 6a is a schematic diagram of a power control circuit according to Embodiment 6 of the present invention.
  • FIG. 6b is a schematic diagram of another power supply control circuit according to Embodiment 6 of the present invention.
  • FIG. 7a is a schematic diagram of a power control circuit according to Embodiment 7 of the present invention.
  • FIG. 7b is a schematic diagram of another power control circuit according to Embodiment 7 of the present invention.
  • Embodiment 8 is a schematic diagram of a power supply control circuit according to Embodiment 8 of the present invention.
  • FIG. 9 is a schematic diagram of a power supply control circuit according to Embodiment 9 of the present invention.
  • FIG. 10 is a schematic structural diagram of an electronic governor according to Embodiment 10 of the present invention.
  • FIG. 11 is a schematic flow chart of a control method of a power output circuit according to Embodiment 28 of the present invention.
  • Embodiment 1 of the present invention provides a power supply control circuit 1 for an unmanned aerial vehicle.
  • FIG. 1 is a schematic diagram of a power supply control circuit according to Embodiment 1.
  • the power control circuit 1 of the embodiment is used to prevent the unmanned aerial vehicle power supply from being hot-swapped Electric sparks.
  • the power control circuit 1 includes a capacitive load circuit 11, a switch circuit 12, and a delay control circuit 13.
  • the capacitive load circuit 11 and the switch circuit 12 are connected in series between the positive pole 14 of the power source and the power ground 15, that is, the input end of the capacitive load circuit 11 is connected to the positive pole 14 of the power supply, and the output end thereof is connected to the input end of the switch circuit 12, and the switch circuit 12 is connected.
  • the output is connected to the power ground 15.
  • the input end of the delay control circuit 13 is electrically connected to the positive pole 14 of the power supply, the output end thereof is connected to the power supply ground 15, and the control end thereof is electrically connected to the switch circuit 12 for controlling the operating state of the switch circuit 12.
  • the delay control circuit 13 controls the switch circuit 12 to switch the switch circuit 12 from the high-impedance output state to the power-on time after the power-on time exceeds the preset time. Low impedance output state.
  • the capacitive load circuit 11 is primarily used to provide a large current output to the motor of the unmanned aerial vehicle.
  • the capacitive load circuit 11 may be composed of a large capacitor, or may be composed of a plurality of parallel capacitors, or may be composed of a capacitor and other electronic components connected in series and in parallel.
  • the specific form of the capacitive load circuit 11 is not limited in this embodiment, and those skilled in the art can select according to actual needs.
  • the switching circuit 12 can be formed by a single crystal switching transistor, such as a bidirectional switching transistor.
  • the switch circuit 12 can also be composed of a circuit breaker and a resistor connected in parallel, or a circuit breaker and an inductor connected in parallel.
  • the switch circuit 12 can also be a CMOS (Complementary Metal Oxide Semiconductor), a complementary metal oxide semiconductor, an amplifier component of voltage control, and a basic unit constituting a CMOS digital integrated circuit. It should be clear to those skilled in the art that as long as the switch circuit 12 can be controlled by the delay control circuit 13 to change the impedance of its output, that is, it can be controlled by the delay control circuit 13 to switch from the high impedance output to the low impedance output. .
  • CMOS Complementary Metal Oxide Semiconductor
  • the specific form of the switch circuit 12 is not specifically limited in this embodiment, and those skilled in the art can specifically set as needed.
  • the high impedance means that the charging current of the capacitive load circuit 11 can be greatly reduced to satisfy the impedance for preventing the generation of the sparking function
  • the low impedance means that the impedance of the capacitive connecting circuit is small.
  • the charging current of the capacitive load circuit 11 when the power is dynamically supplied to the motor is not affected.
  • the high impedance can be the resistance or the impedance of the switching element when it is open or closed
  • the low impedance is the impedance of the guiding line or the impedance of the switching element when it is closed or turned on.
  • the delay control circuit 13 is not specifically limited in this embodiment, and may be connected in series. a timer between the positive pole 14 of the power source and the power ground 15 and whose control terminal is electrically connected to the switch circuit 12, the timer is activated when the power is turned on and is controlled until a predetermined time, that is, after the power-on time exceeds the preset time The switching circuit 12 is switched from a high impedance output state to a low impedance output state.
  • the delay control circuit 13 can also be implemented by a timing control chip or control software.
  • the working principle of the power control circuit 1 of the present embodiment is: when the power plug of the battery of the unmanned aerial vehicle is inserted into the power jack of the electronic governor, that is, when the positive and negative poles of the battery are connected to the input interface of the power control circuit 1
  • the voltage difference is input between the power source positive electrode 14 of the power supply control circuit 1 and the power source ground 15, and the capacitance in the capacitance load circuit 11 is charged by the high impedance output from the switch circuit 12. Since there is a high impedance output of the switching circuit 12, the charging current of the capacitor in the capacitive load circuit 11 is small, and no spark is generated at the power plug of the battery to prevent the electric sparking phenomenon.
  • the input and output terminals connected to the power supply positive electrode 14 and the power supply ground 15 respectively detect the differential pressure, and the power supply positive electrode 14 and the power supply ground 15 are in a power-on state.
  • the control terminal controls the switch circuit 12 to switch from the high impedance output state to the low impedance output state to prepare the capacitive load circuit 11 to output a large current to the motor.
  • the capacitive load circuit 11 can provide a large current output thereof, and after the output, the capacitive load circuit 11 can be quickly charged by the low impedance outputted by the switching circuit 12.
  • the dynamic charging and discharging efficiency of the capacitive load circuit 11 is improved.
  • the power supply control circuit 1 of the present embodiment controls the switch circuit 12 to switch from the high-impedance output state to the low-impedance output state after the power supply positive electrode 14 and the power supply ground 15 are powered on by the delay control circuit 13 for a predetermined time, thereby eliminating the need to manually
  • the main power supply and the large capacitor connection simplify the anti-ignition operation of the unmanned aerial vehicle battery during hot plugging, and realize the automatic control of the anti-spark.
  • the power control circuit 1 of the embodiment greatly reduces the current peak at the moment of power-on when the power plug is plugged in, reduces and eliminates the spark generated by the plug contact moment, and effectively prolongs the life of the power connector.
  • the power control circuit 1 of the present embodiment is very simple and easy to be integrated on hardware such as an electronic governor; it is very suitable for the smart battery to reduce the spark of the plug during hot plugging. At the same time, it can greatly reduce the current stress when the battery is powered on, and protect the battery. Suitable for application on high power drones.
  • Embodiment 2 of the present invention provides a power supply control circuit for an unmanned aerial vehicle.
  • FIG. 2 is a schematic diagram of a power control circuit according to Embodiment 2;
  • FIG. 2b is a schematic diagram of another power control circuit according to Embodiment 2.
  • This embodiment is based on the solution provided in Embodiment 1, and the switch circuit 12 is provided to include a MOS transistor 121 (metal-semiconductor-semiconductor field effect transistor).
  • MOS transistor 121 metal-semiconductor-semiconductor field effect transistor
  • the gate (G) of the MOS transistor 121 is electrically connected to the control terminal of the delay control circuit 13, and the drain (D) thereof is electrically connected to the output terminal of the capacitive load circuit 11 to have its source ( S) is electrically connected to the power ground 15 for turning on and off the MOS transistor 121 according to the voltage change of the gate.
  • the turn-on and turn-off of the MOS transistor 121 can be easily realized by controlling the voltage of the gate (G) by the delay control circuit 13. Switching between them to output high impedance or low impedance to the switching circuit 12. Moreover, the switch circuit 12 thus provided has a simple structure and a more stable performance.
  • the MOS transistor 121 is in an off state. Therefore, the switching circuit 12 outputs a high impedance, so that the charging current of the capacitive load circuit 11 is reduced to avoid generation. Instantaneous inrush current to prevent sparking at the joint.
  • the delay control circuit 13 increases the voltage of the gate (G) of the MOS transistor 121 to the turn-on voltage through the control terminal, for example, to 2.5V, thereby turning on the MOS transistor 121. Since the impedance when the MOS transistor 121 is turned on is small, the switching transistor circuit can output a low impedance after the MOS transistor 121 is turned on.
  • the turn-on voltage of the MOS transistor 121 is only an exemplary turn-on voltage of the embodiment. In actual settings, different MOS transistor 121 turn-on voltages may be selected according to circuit requirements.
  • raising the gate (G) voltage of the MOS transistor 121 to the turn-on voltage may be completed instantaneously or by a period of time.
  • the timer (G) is turned on immediately by the timer when the timing exceeds the preset time, or the voltage of the gate (G) is slowly increased over a period of time by the control chip and the control software until the preset is exceeded.
  • the turn-on voltage is reached after time.
  • a first resistor 123 connected in parallel with the MOS transistor 121 may be disposed in the switching circuit 12 for protecting the MOS transistor 121.
  • the first resistor 123 will function as a shunt, thereby avoiding excessive charging current at the time of power-on and thereby puncturing the MOS transistor. 121.
  • the switching circuit 12 may be connected in series with the capacitive load circuit 11 in a branch and in parallel with the delay control circuit 13, that is, the switching circuit 12 is disposed in the branch of the capacitive load circuit 11.
  • the turning on and off of the MOS transistor 121 does not affect the output of the power supply to the UAV motor.
  • the switch circuit 12 can also connect the branch formed by the parallel connection of the capacitive load circuit 11 and the delay control circuit 13 in series with the switch circuit 12, that is, the switch circuit 12 is connected in series in the trunk circuit.
  • the time during which the power supply control circuit 1 outputs to the UAV motor can be controlled by the turning on and off of the MOS transistor 121.
  • the effect of anti-sparking can be improved, and the voltage overshoot spike at the time of power-on can be eliminated, so that the overshoot spike is not output to the motor.
  • the power supply control circuit 1 of the present embodiment can make the structure of the switch circuit 12 simpler by providing the MOS transistor 121, and can also control the MOS transistor 121 from the off state to the time when the on-voltage is supplied to the gate (G). The time of the on state is easier and more convenient to control. Moreover, the parallel connection of the first resistor 123 for the MOS transistor 121 can protect the MOS transistor 121 and improve the stability of the entire power supply control circuit 1.
  • Embodiment 3 of the present invention provides a power supply control circuit for an unmanned aerial vehicle.
  • 3 is a schematic diagram of a power supply control circuit provided in Embodiment 3.
  • the switch circuit 12 is configured to include a relay 125 and a second resistor 127.
  • the control terminal of the delay control circuit 13 is electrically connected to the relay 125 for controlling the opening and closing state of the open end of the relay 125 to switch the switching circuit from the high impedance output state to the low impedance output state.
  • the delay control circuit 13 and the capacitive load circuit 11 are connected in parallel between the power source positive electrode 14 and the power source ground 15. That is, the input end of the delay control circuit 13 is connected to the positive pole 14 of the power supply, and the output end thereof is connected to the power supply ground 15; the input end of the capacitive load circuit 11 is also connected to the positive pole 14 of the power supply, and the input thereof is The outlet is also connected to the power ground 15. And the control end of the delay control circuit 13 is electrically connected to the input end of the relay 125, and the output end of the relay 125 is connected to the power supply ground 15. The switch of the relay 125 is connected in parallel with the second resistor 127, and the two ends thereof are respectively connected to the output end of the delay control circuit 13 and the output end of the capacitive load circuit 11.
  • the switch of the relay 125 is turned off.
  • the second resistor 127 serves as a high-impedance output of the switch circuit 12, thereby reducing the current charged by the capacitive load circuit 11 at the time of power-on, eliminating the instantaneous peak value of the capacitive load circuit 11 when charging, thereby preventing the power plug from being sparked.
  • the control terminal of the delay control circuit 13 turns on the relay 125.
  • the second resistor 127 When the relay 125 is turned on, the second resistor 127 is short-circuited by the relay 125, and the output end of the capacitive load circuit 11 is directly connected to the power ground 15 through the relay 125, that is, the capacitive load circuit 11 is dynamic through the low impedance outputted by the switch circuit 12. Charging, thereby shortening the time of dynamic charging, and improving the efficiency of outputting a large current by the capacitive load circuit 11.
  • the power supply control circuit 1 of the embodiment realizes the switching of the high-impedance output and the low-impedance output of the switch circuit 12 by setting the parallel relay 125 and the second resistor 127, which is convenient, simple, and easy to realize automatic anti-sparking during power-on. control. It is also possible to control the time at which the power control circuit 1 outputs to the unmanned aerial vehicle motor. And for higher voltages, the effect of anti-sparking can be improved, and the voltage overshoot spike at the time of power-on can be eliminated, so that the overshoot spike is not output to the motor.
  • Embodiment 4 of the present invention provides a power supply control circuit for an unmanned aerial vehicle.
  • 4 is a schematic diagram of a power supply control circuit provided in Embodiment 4.
  • the delay control circuit 13 is configured to include a first capacitor 1311 and a pull-up resistor 1313.
  • the first capacitor 1311 and the pull-up resistor 1313 are connected in series between the power source positive electrode 14 and the power source ground 15 and in parallel with the capacitive load circuit 11; and the anode of the first capacitor 1311 is electrically connected to the switch circuit 12.
  • the pull-up resistor 1313 may be directly connected in series to the positive pole 14 of the power supply, or may be indirectly connected in series with the positive pole 14 of the power supply.
  • the pull up resistor 1313 can be in series with the system power supply of the UAV that is divided by the power supply positive terminal 14.
  • the first capacitor 1311 is also charged by the pull-up resistor 1313 while the capacitive load circuit 11 is being charged. As the first capacitor 1311 is charged, the voltage across it is also gradually increased, thereby controlling the operating state of the switching circuit 12 by the voltage change between the positive and negative terminals of the first capacitor 1311.
  • the voltage between the positive electrode and the negative electrode of the first capacitor 1311 also increases with time. And rising, that is, the voltage between the input terminal and the output terminal of the relay 125 electrically connected to the two poles of the first capacitor 1311 increases as the power-on time increases.
  • the relay 125 is closed, and the output impedance of the switch circuit 12 is switched from high impedance to low impedance. .
  • the voltage between the input terminal and the output terminal of the load capacitor circuit gradually decreases as the capacitor in the load capacitor circuit discharges.
  • the first capacitor 1311 starts to discharge, and the voltage between the positive electrode and the negative terminal of the first capacitor 1311 also decreases, and the relay 125 inputs The voltage between the terminal and the output also decreases.
  • the relay 125 is turned off and the output impedance of the switching circuit 12 is switched from a low impedance to a high impedance.
  • the anode of the first capacitor 1311 when the anode of the first capacitor 1311 is electrically connected to the gate (G) of the MOS transistor 121, as the power-on time increases, the voltage between the anode and the cathode of the first capacitor 1311 also increases with time.
  • the rise that is, the voltage of the gate (G) of the MOS transistor 121 electrically connected to the positive electrode of the first capacitor 1311 also increases as the power-on time increases.
  • the MOS transistor 121 After the power-on time exceeds the preset time, after the voltage of the gate (G) of the MOS transistor 121 exceeds the turn-on voltage, the MOS transistor 121 is turned on, and the output impedance of the switch circuit 12 is switched from high impedance to low impedance. .
  • the voltage between the input terminal and the output terminal of the load capacitor circuit gradually decreases as the capacitor in the load capacitor circuit discharges.
  • the first capacitor 1311 starts to discharge, and the positive voltage of the first capacitor 1311 also decreases, and the gate of the MOS transistor 121 (G) The voltage is also reduced.
  • the MOS transistor 121 is turned off, and the output impedance of the switching circuit 12 is switched from the low impedance to the high resistance. anti.
  • the preset time when the switching circuit 12 is switched from the high-impedance output state to the low-impedance output state is the time during which the first capacitor 1311 is charged to the conduction voltage of the relay 125 or the MOS transistor 121, that is, the first capacitor. 1311 The time to charge to the preset voltage value.
  • different charging times of the first capacitor 1311 can be obtained, that is, different times when the control switch circuit 12 is switched from high impedance to low impedance, that is, pre- Set the time.
  • a third capacitor 1321 may be connected between the anode of the first capacitor 1311 and the output end of the capacitive load circuit 11 for reducing the conduction current of the MOS transistor 121.
  • Vgs refers to the voltage difference between the gate (G) and the source (S);
  • Vds refers to the voltage difference between the drain (D) and the source (S).
  • the third capacitor 1321 can also extend the discharge time of the first capacitor 1311, thereby increasing the turn-on time of the MOS transistor 121.
  • the first capacitor 1311 and the pull-up resistor 1313 connected in series between the power source positive electrode 14 and the power source ground 15 can control the switching circuit 12 in a very convenient manner by charging and discharging of the first capacitor 1311. Switching between high-impedance and low-impedance outputs automates the hot swapping of batteries.
  • the charging time of the first capacitor 1311 can be controlled by adjusting the parameters of the first resistor 123 and the first capacitor 1311, thereby controlling the switching circuit 12 to switch from the high-impedance output to the low-impedance output, thereby improving the capacitor at the time of power-on. The time during which the load circuit 11 is charged at a high impedance improves the effect of the power supply control circuit 1 against sparking.
  • Embodiment 5 of the present invention provides a power supply control circuit for an unmanned aerial vehicle.
  • FIG. 5 is a schematic diagram of a power supply control circuit according to Embodiment 5.
  • the pull-up resistor 1313 is connected in parallel with a diode 1331 for accelerating the discharge of the first capacitor 1311.
  • the anode of the diode 1331 is electrically connected to the anode of the first capacitor 1311, and the cathode and the pull-up of the diode 1331
  • the input of the resistor 1313 is electrically connected.
  • the first capacitor 1311 can be discharged through the diode 1331 to accelerate the discharge of the first capacitor 1311 to return to the initial state to be charged as soon as possible.
  • a third capacitor 1321 is connected between the anode of the first capacitor 1311 and the output end of the capacitive load circuit 11 for reducing the MOS.
  • the conduction current of the tube 121 For the principle and effect of the third capacitor 1321, refer to Embodiment 4.
  • the power supply connected to the pull-up resistor 1313 in FIG. 5 is divided by the power supply of the battery, that is, the power supply positive electrode 14 is divided, and the essence is that the pull-up resistor 1313 is indirectly connected to the power supply positive electrode 14.
  • the power supply control circuit 1 of the present embodiment accelerates the discharge of the first capacitor 1311 by connecting a diode 1331 in parallel with the pull-up resistor 1313, so that the circuit can quickly return to the initial state for the next access of the battery.
  • Embodiment 6 of the present invention provides a power supply control circuit for an unmanned aerial vehicle.
  • FIG. 6a is a schematic diagram of a power control circuit according to Embodiment 6.
  • FIG. 6b is a schematic diagram of a power control circuit according to Embodiment 6.
  • the first capacitor 1311 is connected in parallel with a third resistor 1333, and the third resistor 1333 is connected in series with the pull-up resistor 1313.
  • the third resistor 1333 is used for The pull resistor 1313 divides the power supply for protecting the switch circuit 12.
  • the power control circuit 1 of the embodiment when the power source positive electrode 14 and the power source ground 15 are in the power-on state, the power source is divided by the pull-up resistor 1313 and the third resistor 1333, and then the first capacitor 1311 is charged, thereby being protected.
  • a switching circuit 12 connected to the positive terminal of the first capacitor 1311.
  • the MOS transistor 121 when the MOS transistor 121 is connected to the positive electrode of the first capacitor 1311, since the Vgs of the MOS transistor 121 may be within 20V, and the voltage difference between the power source positive electrode 14 and the power source ground 15 may be higher than 20V, it may pass
  • the third resistor 1333 is connected to adjust the voltage of the gate (G) of the MOS transistor 121 such that the Vgs full voltage of the MOS transistor 121 approaches 12V, thereby protecting the MOS transistor 121. when However, based on the above principle, the third resistor 1333 can also protect the relay 125 or other switching components in the switch circuit 12.
  • the first capacitor 1311 When the power supply positive electrode 14 and the power supply ground 15 are in the power-off state, when the voltage of the input terminal and the output terminal of the load capacitance circuit is lowered to a preset voltage (for example, 6-7v), the first capacitor 1311 can be discharged through the third resistor 1333. Thereby, the discharge of the first capacitor 1311 is accelerated, so that it returns to the initial state to be charged as soon as possible.
  • a preset voltage for example, 6-7v
  • a third capacitor 1321 is connected between the anode of the first capacitor 1311 and the output end of the capacitive load circuit 11 for reducing the MOS.
  • the conduction current of the tube 121 For the principle and effect of the third capacitor 1321, refer to Embodiment 4.
  • the power supply control circuit 1 of the present embodiment protects the switching circuit 12 by adjusting a voltage dividing ratio of the pull-up resistor 1313 and the third resistor 1333 by connecting a pull-up resistor 1313 in series with a third resistor 1333 in parallel with the first capacitor 1311. .
  • the third resistor 1333 can also accelerate its discharge when the first capacitor 1311 is discharged, so that the circuit can quickly return to the initial state for the next access of the battery.
  • Embodiment 7 of the present invention provides a power supply control circuit 1 for an unmanned aerial vehicle.
  • FIG. 7a is a schematic diagram of a power control circuit according to Embodiment 7.
  • FIG. 7b is a schematic diagram of a power control circuit according to Embodiment 7.
  • the first capacitor 1311 is connected in parallel with a Zener diode 1335, and the Zener diode 1335 is connected in series with the pull-up resistor 1313 for parallel connection with the pull-up resistor 1313.
  • the voltage stabilizing circuit protects the switching circuit 12.
  • the Zener diode 1335 will always stabilize the voltage of the positive electrode of the first capacitor 1311 at the regulated value of the diode 1331, thereby protecting the switch circuit 12 connected to the positive terminal of the first capacitor 1311.
  • the Zener diode 1335 of FIG. 7 can control the Vgs of the MOS transistor 121 to be within 12 V, thereby protecting the Zener diode 1335 from being burned out.
  • the Zener diode 1335 can also protect the relay 125 or other transistor components in the switching circuit 12.
  • a third capacitor 1321 is connected between the anode of the first capacitor 1311 and the output terminal of the capacitive load circuit 11 for reducing the on current of the MOS transistor 121.
  • the third capacitor 1321 refers to Embodiment 4.
  • the switching circuit 12 can be protected by connecting a Zener diode 1335 in parallel with the first capacitor 1311 for the pull-up resistor 1313.
  • Embodiment 8 of the present invention provides a power supply control circuit for an unmanned aerial vehicle.
  • FIG. 8 is a schematic diagram of a power supply control circuit according to Embodiment 8.
  • a discharge control circuit for controlling discharge of the first capacitor 1311 after the voltage of the capacitive load circuit 11 is lower than a preset voltage is provided.
  • the discharge control circuit includes a first transistor 1351, a fourth resistor 1353, and a fifth resistor 1355.
  • the emitter of the first transistor 1351 is electrically connected to the anode of the first capacitor 1311, the collector of the first transistor 1351 is connected to the power ground 15, and the base of the first transistor 1351 passes through the fourth resistor 1353.
  • the power supply positive electrode 14 is electrically connected, and the base of the first transistor 1351 is also electrically connected to the power supply ground 15 through the fifth resistor 1355.
  • the switch circuit 12 switches from the high-impedance output to the low-impedance output to achieve a large current output to the motor of the capacitive load circuit 11 and in the switch circuit 12 Dynamic charging is achieved at low impedance, reducing the time for dynamic charging.
  • the power-on time is longer than the time when the first capacitor 1311 is charged to the ON voltage of the MOS transistor 121, and the high impedance of the switch circuit 12 is provided by the impedance when the MOS transistor 121 is turned off and the first resistor 123.
  • the low impedance is mainly provided by the impedance of the MOS transistor 121 itself after the MOS transistor 121 is turned on.
  • the battery is in an off state throughout the time when the battery is connected to the power supply control circuit 1.
  • a third capacitor 1321 is connected between the anode of the first capacitor 1311 and the output end of the capacitive load circuit 11 for reducing the MOS.
  • the conduction current of the tube 121 For the principle and effect of the third capacitor 1321, refer to Embodiment 4.
  • the power supply control circuit 1 of the present embodiment can delay the time during which the switching circuit 12 is switched from the low impedance output state to the high impedance output state by setting the discharge control circuit including the first transistor 1351, thereby increasing the discharge time of the capacitive load circuit 11.
  • Embodiment 9 of the present invention provides a power supply control circuit for an unmanned aerial vehicle.
  • FIG. 9 is a schematic diagram of a power supply control circuit according to Embodiment 9.
  • a discharge control circuit for controlling discharge of the first capacitor 1311 after the voltage of the capacitive load circuit 11 is lower than a preset voltage is provided.
  • the discharge control circuit includes a second transistor 1371, a third transistor 1373, a sixth resistor 1375, a seventh resistor 1376, and an eighth resistor 1377.
  • the emitter of the second transistor 1371 is electrically connected to the power ground 15, the base of the second transistor 1371 is electrically connected to the power source positive electrode 14 through the sixth resistor 1375, and the collector of the second transistor 1371 is first.
  • the positive electrode of the capacitor 1311 is electrically connected.
  • the collector of the third transistor 1373 is electrically connected to the base of the second transistor 1371, the emitter of the third transistor 1373 is electrically connected to the power supply ground 15, and the base of the third transistor 1373 is connected to the positive pole of the power supply. 14 electrical connections.
  • the seventh resistor 1376 and the eighth resistor 1377 are connected in series between the base of the second transistor 1371 and the power source positive electrode 14.
  • the switch circuit 12 switches from the high-impedance output to the low-impedance output to achieve a large current output to the motor of the capacitive load circuit 11 and in the switch circuit 12 Dynamic charging is achieved at low impedance, reducing the time for dynamic charging.
  • the power-on time is longer than the time when the first capacitor 1311 is charged to the ON voltage of the MOS transistor 121, and the high impedance of the switch circuit 12 is provided by the impedance when the MOS transistor 121 is turned off and the first resistor 123.
  • the low impedance is mainly provided by the impedance of the MOS transistor 121 itself after the MOS transistor 121 is turned on.
  • the base voltage of the third transistor 1373 is greater than the voltage of the emitter electrode, and the third diode 1331 is in an on state. Since the third transistor 1331 is in an on state, the second transistor 1371 has a base voltage lower than a voltage drop between the base and the emitter, thereby causing the second transistor 1371 to be in an off state.
  • the base voltage of the third transistor 1373 is lowered to be less than its base.
  • the voltage drop between the electrode and the emitter electrode is such that the third transistor 1373 is turned off.
  • the third transistor 1373 is turned off, the base voltage of the second transistor 1371 is higher than the emitter voltage, the second transistor 1371 is turned on, and the first capacitor 1311 is rapidly discharged.
  • the gate voltage of the MOS transistor 121 also rapidly drops below the on-voltage, the MOS transistor 121 is turned off, and the switching circuit 12 returns to the state of outputting a high impedance.
  • a second capacitor 1379 is provided for improving the detection capability of the third diode 1331 for the voltage drop at the input and output of the capacitive load circuit 11.
  • the second capacitor 1379 is connected in parallel with the eighth resistor 1377 and in series with the seventh resistor 1376.
  • the voltage between the input terminal and the output terminal of the capacitive load circuit 11 when the first capacitor 1311 is discharged can be controlled by controlling the sixth resistor 1375, the seventh resistor 1376, and the eighth resistor 1377.
  • the sixth resistor 1375, the seventh resistor 1376, the eighth resistor 1377, and the second capacitor 1379 can be controlled to control the first A capacitor 1311 discharges a voltage between the input terminal and the output terminal of the capacitive load circuit 11 to improve control accuracy.
  • a third capacitor 1321 is connected between the anode of the first capacitor 1311 and the output end of the capacitive load circuit 11 for reducing the MOS.
  • the conduction current of the tube 121 For the principle and effect of the third capacitor 1321, refer to Embodiment 4.
  • the power supply connected to the pull-up resistor 1313 in FIG. 9 is divided by the power supply of the battery, that is, the power supply positive electrode 14 is divided, and the pull-up resistor 1313 is indirectly connected to the power supply positive electrode 14 in essence.
  • the double triode composed of the second transistor 1371 and the third transistor 1373 serves as a discharge control circuit, and the control effect of discharging the first capacitor 1311 can be improved.
  • Embodiment 10 of the present invention provides an electronic governor.
  • FIG. 10 is a schematic structural view of an electronic governor according to Embodiment 10.
  • the electronic governor of this embodiment includes a motor drive circuit 2 and a power supply control circuit 1.
  • the power control circuit 1 is electrically connected to the motor drive circuit 2 for supplying power to the motor drive circuit 2.
  • the power control circuit 1 is configured to prevent an electric spark from being generated when the UAV power supply is hot swapped.
  • the power control circuit 1 includes a capacitive load circuit 11, a switch circuit 12, and a delay control circuit 13.
  • the capacitive load circuit 11 and the switch circuit 12 are connected in series between the positive pole 14 of the power source and the power ground 15, that is, the input end of the capacitive load circuit 11 is connected to the positive pole 14 of the power supply, and the output end thereof is connected to the input end of the switch circuit 12, and the switch circuit 12 is connected.
  • the output is connected to the power ground 15.
  • the input end of the delay control circuit 13 is electrically connected to the positive pole 14 of the power supply, the output end thereof is connected to the power supply ground 15, and the control end thereof is electrically connected to the switch circuit 12 for controlling the operating state of the switch circuit 12.
  • the delay control circuit 13 controls the switch circuit 12 to switch the switch circuit 12 from the high-impedance output state to the power-on time after the power-on time exceeds the preset time. Low impedance output state.
  • the capacitive load circuit 11 is primarily used to provide a large current output to the motor of the unmanned aerial vehicle.
  • the capacitive load circuit 11 may be composed of a large capacitor, or may be composed of a plurality of parallel capacitors, or may be composed of a capacitor and other electronic components connected in series and in parallel.
  • the specific form of the capacitive load circuit 11 is not limited in this embodiment, and those skilled in the art can select according to actual needs.
  • the switching circuit 12 can be formed by a single crystal switching transistor, such as a bidirectional switching transistor.
  • the switch circuit 12 can also be composed of a circuit breaker and a resistor connected in parallel, or a circuit breaker and an inductor connected in parallel.
  • the switch circuit 12 can also be a CMOS (Complementary Metal Oxide Semiconductor), a complementary metal oxide semiconductor, an amplifier component of voltage control, and a basic unit constituting a CMOS digital integrated circuit. It should be clear to those skilled in the art that as long as the switch circuit 12 can be controlled by the delay control circuit 13 to change the impedance of its output, that is, it can be controlled by the delay control circuit 13 to switch from the high impedance output to the low impedance output. .
  • CMOS Complementary Metal Oxide Semiconductor
  • the specific form of the switch circuit 12 is not specifically limited in this embodiment, and those skilled in the art can specifically set as needed.
  • the high impedance means that the charging current of the capacitive load circuit 11 can be greatly reduced to satisfy the impedance for preventing the generation of the sparking function
  • the low impedance means that the impedance of the capacitive connecting circuit is small.
  • the charging current of the capacitive load circuit 11 when the power is dynamically supplied to the motor is not affected.
  • the high impedance can be the resistance or the impedance of the switching element when it is open or closed
  • the low impedance is the impedance of the guiding line or the impedance of the switching element when it is closed or turned on.
  • the delay control circuit 13 is not specifically limited in this embodiment, and may be a timer connected in series between the power source positive electrode 14 and the power source ground 15 and whose control terminal is electrically connected to the switch circuit 12, the timer being on the power supply. The power-on time is started and the timer switch circuit 12 is switched from the high-impedance output state to the low-impedance output state after timing up to a predetermined time, that is, after the power-on exceeds the preset time.
  • the delay control circuit 13 can also be implemented by a timing control chip or control software.
  • the working principle of the power control circuit 1 is: when the power plug of the battery of the UAV is inserted into the power jack of the electronic governor, that is, the positive and negative poles of the battery are connected to the power control circuit 1
  • the interface When the interface is input, a voltage difference is input between the power source positive electrode 14 of the power supply control circuit 1 and the power source ground 15, and the capacitance in the capacitance load circuit 11 is charged by the high impedance output from the switch circuit 12. Since there is a high impedance output of the switching circuit 12, the capacitive load The charging current of the capacitor in the circuit 11 is small, and no spark is generated at the power plug of the battery to prevent electric sparking.
  • the input and output terminals connected to the power supply positive electrode 14 and the power supply ground 15 respectively detect the differential pressure, and the power supply positive electrode 14 and the power supply ground 15 are in a power-on state.
  • the control terminal controls the switch circuit 12 to switch from the high impedance output state to the low impedance output state to prepare the capacitive load circuit 11 to output a large current to the motor.
  • the capacitive load circuit 11 can provide a large current output for the motor drive circuit 2, and after the output, the capacitive load circuit 11 can be performed by the low impedance outputted by the switch circuit 12.
  • the charging is fast to reduce the dynamic charging time of the capacitive load circuit 11 during the normal operation of the UAV, thereby improving the dynamic charging and discharging efficiency of the capacitive load circuit 11.
  • control switch circuit 12 is switched from the high impedance output state to the low impedance output after the power supply positive electrode 14 and the power supply ground 15 are powered on for a predetermined time by the delay control circuit 13 in the power supply control circuit 1.
  • the state eliminates the need to manually connect the main power source and the large capacitor, which simplifies the operation of the anti-sparking when the UAV battery is hot-swapped, and realizes the automatic control of the anti-spark.
  • the electronic governor of the embodiment greatly reduces the current peak at the moment of power-on when the power plug is plugged, reduces and eliminates the spark generated by the plug contact moment, and effectively prolongs the life of the power connector.
  • the power control circuit 1 of the electronic governor of the embodiment is very simple and easy to be integrated in hardware such as an electronic governor; it is very suitable for the smart battery to reduce the spark of the plug during hot plugging. Moreover, it can greatly reduce the current stress when the battery is powered on, and protect the battery, which is very suitable for application on high-power UAVs.
  • Embodiment 11 of the present invention provides an electronic governor.
  • the present embodiment is based on the solution provided in Embodiment 10, and the switch circuit 12 is arranged to include a MOS transistor 121 (metal-oxid-semiconductor field). Effect transistor).
  • MOS transistor 121 metal-oxid-semiconductor field. Effect transistor
  • the gate (G) of the MOS transistor 121 is electrically connected to the control terminal of the delay control circuit 13, and the drain (D) thereof is electrically connected to the output terminal of the capacitive load circuit 11 to have its source ( S) is electrically connected to the power ground 15 for realizing the conduction of the MOS transistor 121 according to the voltage change of the gate cutoff.
  • the turn-on and turn-off of the MOS transistor 121 can be easily realized by controlling the voltage of the gate (G) by the delay control circuit 13. Switching between them to output high impedance or low impedance to the switching circuit 12. Moreover, the switch circuit 12 thus provided has a simple structure and a more stable performance.
  • the MOS transistor 121 is in an off state. Therefore, the switching circuit 12 outputs a high impedance, so that the charging current of the capacitive load circuit 11 is reduced to avoid generation. Instantaneous inrush current to prevent sparking at the joint.
  • the delay control circuit 13 increases the voltage of the gate (G) of the MOS transistor 121 to the turn-on voltage through the control terminal, for example, to 2.5V, thereby turning on the MOS transistor 121. Since the impedance when the MOS transistor 121 is turned on is small, the switching transistor circuit can output a low impedance after the MOS transistor 121 is turned on.
  • the turn-on voltage of the MOS transistor 121 is only an exemplary turn-on voltage of the embodiment. In actual settings, different MOS transistor 121 turn-on voltages may be selected according to circuit requirements.
  • raising the gate (G) voltage of the MOS transistor 121 to the turn-on voltage may be completed instantaneously or by a period of time.
  • the timer (G) is turned on immediately by the timer when the timing exceeds the preset time, or the voltage of the gate (G) is slowly increased over a period of time by the control chip and the control software until the preset is exceeded.
  • the turn-on voltage is reached after time.
  • a first resistor 123 connected in parallel with the MOS transistor 121 may be disposed in the switching circuit 12 for protecting the MOS transistor 121.
  • the first resistor 123 will function as a shunt to avoid excessive charging current at the time of power-on, thereby puncturing the MOS transistor 121. .
  • the switching circuit 12 may be connected in series with the capacitive load circuit 11 in a branch and in parallel with the delay control circuit 13, that is, the switching circuit 12 is disposed in the branch of the capacitive load circuit 11.
  • the turning on and off of the MOS transistor 121 does not affect the output of the power supply to the UAV motor.
  • the switch circuit 12 can also connect the branch formed by the parallel connection of the capacitive load circuit 11 and the delay control circuit 13 in series with the switch circuit 12, that is, the switch circuit 12 is connected in series in the trunk circuit. in.
  • the time during which the power supply control circuit 1 outputs to the UAV motor can be controlled by the turning on and off of the MOS transistor 121.
  • the effect of anti-sparking can be improved, and the voltage overshoot spike at the time of power-on can be eliminated, so that the overshoot spike is not output to the motor.
  • the power supply control circuit 1 in the electronic governor of the present embodiment can make the structure of the switch circuit 12 simpler by providing the MOS transistor 121, and can also control the MOS by providing a turn-on voltage for the gate (G).
  • the time from the off state to the on state of the tube 121 is easier and more convenient to control.
  • the parallel connection of the first resistor 123 for the MOS transistor 121 can protect the MOS transistor 121 and improve the stability of the entire power supply control circuit 1.
  • Embodiment 12 of the present invention provides an electronic governor.
  • the present embodiment is based on the solution provided in Embodiment 11, and the switch circuit 12 is configured to include a relay 125 and a second resistor 127.
  • the control terminal of the delay control circuit 13 is electrically connected to the relay 125 for controlling the opening and closing state of the open end of the relay 125 to switch the switching circuit from the high impedance output state to the low impedance output state.
  • the delay control circuit 13 and the capacitive load circuit 11 are connected in parallel between the power source positive electrode 14 and the power source ground 15. That is, the input end of the delay control circuit 13 is connected to the positive pole 14 of the power supply, and the output end thereof is connected to the power supply ground 15; the input end of the capacitive load circuit 11 is also connected to the positive pole 14 of the power supply, and the output end thereof is also connected to the power supply ground 15. And the control end of the delay control circuit 13 is electrically connected to the input end of the relay 125, and the output end of the relay 125 is connected to the power supply ground 15. The switch of the relay 125 is connected in parallel with the second resistor 127, and the two ends thereof are respectively connected to the output end of the delay control circuit 13 and the output end of the capacitive load circuit 11.
  • the switch of the relay 125 is turned off.
  • the second resistor 127 serves as a high-impedance output of the switch circuit 12, thereby reducing the current charged by the capacitive load circuit 11 at the time of power-on, eliminating the instantaneous peak value of the capacitive load circuit 11 when charging, thereby preventing the power plug from being sparked.
  • the control terminal of the delay control circuit 13 turns on the relay 125.
  • the second resistor 127 When the relay 125 is turned on, the second resistor 127 is short-circuited by the relay 125, and the output end of the capacitive load circuit 11 is directly connected to the power ground 15 through the relay 125, that is, the capacitive load circuit 11 is dynamic through the low impedance outputted by the switch circuit 12. Charging, thereby shortening the time of dynamic charging and improving the capacitive load circuit 11 output high current efficiency.
  • the power supply control circuit 1 in the electronic governor of the embodiment realizes switching of the high-impedance output and the low-impedance output of the switch circuit 12 by setting the parallel relay 125 and the second resistor 127, which is convenient, simple, and easy to implement power-on. Automatic control of anti-electric sparks. It is also possible to control the time at which the power control circuit 1 outputs to the unmanned aerial vehicle motor. And for higher voltages, the effect of anti-sparking can be improved, and the voltage overshoot spike at the time of power-on can be eliminated, so that the overshoot spike is not output to the motor.
  • Embodiment 13 of the present invention provides an electronic governor.
  • the delay control circuit 13 is configured to include a first capacitor 1311 and a pull-up resistor 1313 on the basis of the technical solutions provided in Embodiment 10, Embodiment 11, or Embodiment 12.
  • the first capacitor 1311 and the pull-up resistor 1313 are connected in series between the power source positive electrode 14 and the power source ground 15 and in parallel with the capacitive load circuit 11; and the anode of the first capacitor 1311 is electrically connected to the switch circuit 12.
  • the pull-up resistor 1313 may be directly connected in series to the positive pole 14 of the power supply, or may be indirectly connected in series with the positive pole 14 of the power supply.
  • the pull up resistor 1313 can be in series with the system power supply of the UAV that is divided by the power supply positive terminal 14.
  • the first capacitor 1311 is also charged by the pull-up resistor 1313 while the capacitive load circuit 11 is being charged. As the first capacitor 1311 is charged, the voltage across it is also gradually increased, thereby controlling the operating state of the switching circuit 12 by the voltage change between the positive and negative terminals of the first capacitor 1311.
  • the voltage between the positive electrode and the negative electrode of the first capacitor 1311 also increases with time. And rising, that is, the voltage between the input terminal and the output terminal of the relay 125 electrically connected to the two poles of the first capacitor 1311 increases as the power-on time increases.
  • the relay 125 is closed, and the output impedance of the switch circuit 12 is switched from high impedance to low impedance. .
  • the voltage between the input terminal and the output terminal of the load capacitor circuit gradually decreases as the capacitor in the load capacitor circuit discharges.
  • the first capacitor 1311 begins to discharge, and the voltage between the positive and negative terminals of the first capacitor 1311 also decreases, and the voltage value between the input terminal and the output terminal of the relay 125 also decreases.
  • the relay 125 is turned off and the output impedance of the switching circuit 12 is switched from a low impedance to a high impedance.
  • the anode of the first capacitor 1311 when the anode of the first capacitor 1311 is electrically connected to the gate (G) of the MOS transistor 121, as the power-on time increases, the voltage between the anode and the cathode of the first capacitor 1311 also increases with time.
  • the rise that is, the voltage of the gate (G) of the MOS transistor 121 electrically connected to the positive electrode of the first capacitor 1311 also increases as the power-on time increases.
  • the MOS transistor 121 After the power-on time exceeds the preset time, after the voltage of the gate (G) of the MOS transistor 121 exceeds the turn-on voltage, the MOS transistor 121 is turned on, and the output impedance of the switch circuit 12 is switched from high impedance to low impedance. .
  • the voltage between the input terminal and the output terminal of the load capacitor circuit gradually decreases as the capacitor in the load capacitor circuit discharges.
  • the first capacitor 1311 starts to discharge, and the positive voltage of the first capacitor 1311 also decreases, and the gate of the MOS transistor 121 (G) The voltage is also reduced.
  • the MOS transistor 121 is turned off, and the output impedance of the switching circuit 12 is switched from a low impedance to a high impedance.
  • the preset time when the switching circuit 12 is switched from the high-impedance output state to the low-impedance output state is the time during which the first capacitor 1311 is charged to the conduction voltage of the relay 125 or the MOS transistor 121, that is, the first capacitor. 1311 The time to charge to the preset voltage value.
  • different charging times of the first capacitor 1311 can be obtained, that is, different times when the control switch circuit 12 is switched from high impedance to low impedance, that is, pre- Set the time.
  • a third capacitor 1321 may be connected between the anode of the first capacitor 1311 and the output end of the capacitive load circuit 11 for reducing the conduction current of the MOS transistor 121.
  • Vgs refers to the gate
  • Vds refers to the voltage difference between the drain (D) and the source (S).
  • the third capacitor 1321 can also extend the discharge time of the first capacitor 1311, thereby increasing the turn-on time of the MOS transistor 121.
  • the power supply control circuit 1 in the electronic governor of the present embodiment can conveniently charge and discharge through the first capacitor 1311 through the first capacitor 1311 and the pull-up resistor 1313 connected in series between the power source positive electrode 14 and the power source ground 15.
  • the switching circuit 12 to switch between the high impedance output and the low impedance output, the automation of the battery hot plug is realized.
  • the charging time of the first capacitor 1311 can be controlled by adjusting the parameters of the first resistor 123 and the first capacitor 1311, thereby controlling the switching circuit 12 to switch from the high-impedance output to the low-impedance output, thereby improving the capacitor at the time of power-on.
  • the time during which the load circuit 11 is charged at a high impedance improves the effect of the power supply control circuit 1 against sparking.
  • Embodiment 14 of the present invention provides an electronic governor.
  • the pull-up resistor 1313 is connected in parallel with a diode 1331 for accelerating the discharge of the first capacitor 1311.
  • the anode of the diode 1331 is electrically connected to the anode of the first capacitor 1311, and the cathode of the diode 1331 is electrically connected to the input end of the pull-up resistor 1313.
  • the first capacitor 1311 it is possible to discharge through the diode 1331 to accelerate the discharge of the first capacitor 1311 to return it to the initial state to be charged as soon as possible.
  • a third capacitor 1321 is connected between the anode of the first capacitor 1311 and the output end of the capacitive load circuit 11 for reducing the MOS.
  • the conduction current of the tube 121 For the principle and effect of the third capacitor 1321, refer to Embodiment 4.
  • the power supply control circuit 1 in the electronic governor of the embodiment accelerates the discharge of the first capacitor 1311 by connecting a diode 1331 in parallel with the pull-up resistor 1313, so that the circuit can quickly return to the initial state for the next battery. Access.
  • Embodiment 15 of the present invention provides an electronic governor.
  • the first capacitor 1311 is connected in parallel with a third resistor 1333, and the third resistor 1333 is connected in series with the pull-up resistor 1313.
  • the third resistor 1333 is for dividing the power supply with the pull-up resistor 1313 for protecting the switch circuit 12.
  • the power control circuit 1 of the electronic governor of the embodiment when the power source positive electrode 14 and the power source ground 15 are in a power-on state, the power source is divided by the pull-up resistor 1313 and the third resistor 1333 and then applied to the first capacitor 1311. Charging, thereby protecting the switching circuit 12 connected to the positive terminal of the first capacitor 1311.
  • the MOS transistor 121 when the MOS transistor 121 is connected to the positive electrode of the first capacitor 1311, since the Vgs of the MOS transistor 121 may be within 20V, and the voltage difference between the power source positive electrode 14 and the power source ground 15 may be higher than 20V, it may pass
  • the third resistor 1333 is connected to adjust the voltage of the gate (G) of the MOS transistor 121 such that the Vgs full voltage of the MOS transistor 121 approaches 12V, thereby protecting the MOS transistor 121.
  • the third resistor 1333 can also protect the relay 125 or other switching components in the switch circuit 12.
  • the first capacitor 1311 When the power supply positive electrode 14 and the power supply ground 15 are in the power-off state, when the voltage of the input terminal and the output terminal of the load capacitance circuit is lowered to a preset voltage (for example, 6-7v), the first capacitor 1311 can be discharged through the third resistor 1333. Thereby, the discharge of the first capacitor 1311 is accelerated, so that it returns to the initial state to be charged as soon as possible.
  • a preset voltage for example, 6-7v
  • a third capacitor 1321 is connected between the anode of the first capacitor 1311 and the output end of the capacitive load circuit 11 for reducing the MOS.
  • the conduction current of the tube 121 For the principle and effect of the third capacitor 1321, refer to Embodiment 4.
  • the power supply control circuit 1 in the electronic governor of the embodiment can adjust the voltage division of the pull-up resistor 1313 and the third resistor 1333 by connecting a pull-up resistor 1313 in series with a third resistor 1333 in parallel with the first capacitor 1311.
  • the protection switch circuit 12 is compared.
  • the third resistor 1333 can also accelerate its discharge when the first capacitor 1311 is discharged, so that the circuit can quickly return to the initial state for the next access of the battery.
  • Embodiment 16 of the present invention provides an electronic governor.
  • this embodiment is the technical solution foundation provided in Embodiment 13.
  • the first capacitor 1311 is connected in parallel with a Zener diode 1335, and the Zener diode 1335 is connected in series with the pull-up resistor 1313 for forming a shunt regulator circuit with the pull-up resistor 1313, thereby protecting the switch circuit 12.
  • the Zener diode 1335 When the power control circuit 1 in the electronic governor of the embodiment is in operation, the Zener diode 1335 will always stabilize the voltage of the positive pole of the first capacitor 1311 at the voltage regulator value of the diode 1331, thereby protecting the positive pole of the first capacitor 1311.
  • Switch circuit 12 For example, when the MOS transistor 121 is connected to the positive terminal of the first capacitor 1311, the Zener diode 1335 of FIG. 7 can control the Vgs of the MOS transistor 121 to be within 12 V, thereby protecting the Zener diode 1335 from being burned out.
  • the Zener diode 1335 can also protect the relay 125 or other transistor components in the switching circuit 12.
  • a third capacitor 1321 is connected between the anode of the first capacitor 1311 and the output end of the capacitive load circuit 11 for reducing the MOS.
  • the conduction current of the tube 121 For the principle and effect of the third capacitor 1321, refer to Embodiment 4.
  • the switching circuit 12 can be protected by connecting a Zener diode 1335 in parallel with the first capacitor 1311 for the pull-up resistor 1313.
  • Embodiment 17 of the present invention provides an electronic governor.
  • a discharge control circuit for controlling discharge of the first capacitor 1311 after the voltage of the capacitive load circuit 11 is lower than a preset voltage is provided.
  • the discharge control circuit includes a first transistor 1351, a fourth resistor 1353, and a fifth resistor 1355.
  • the emitter of the first transistor 1351 is electrically connected to the anode of the first capacitor 1311, the collector of the first transistor 1351 is connected to the power ground 15, and the base of the first transistor 1351 passes through the fourth resistor 1353.
  • the power supply positive electrode 14 is electrically connected, and the base of the first transistor 1351 is also electrically connected to the power supply ground 15 through the fifth resistor 1355.
  • the switch circuit 12 switches from the high-impedance output to the low-impedance output to achieve a large current output to the motor of the capacitive load circuit 11 and in the switch circuit 12 Dynamic charging is achieved at low impedance, reducing the time for dynamic charging.
  • the power-on time is longer than the time when the first capacitor 1311 is charged to the ON voltage of the MOS transistor 121, and the high impedance of the switch circuit 12 is provided by the impedance when the MOS transistor 121 is turned off and the first resistor 123.
  • the low impedance is mainly provided by the impedance of the MOS transistor 121 itself after the MOS transistor 121 is turned on.
  • the voltage drop between the base voltage of the first transistor 1351 and the emitter electrode is smaller than the conduction voltage of the first transistor 1351, and therefore, the battery is connected.
  • the power supply control circuit 1 is in an off state for the entire time.
  • a third capacitor 1321 is connected between the anode of the first capacitor 1311 and the output end of the capacitive load circuit 11 for reducing the MOS.
  • the conduction current of the tube 121 For the principle and effect of the third capacitor 1321, refer to Embodiment 4.
  • the power supply control circuit 1 in the electronic governor of the present embodiment can delay the time when the switching circuit 12 is switched from the low impedance output state to the high impedance output state by setting the discharge control circuit including the triode, thereby increasing the discharge time of the capacitive load circuit 11. .
  • Embodiment 18 of the present invention provides an electronic governor.
  • a discharge control circuit for controlling discharge of the first capacitor 1311 after the voltage of the capacitive load circuit 11 is lower than a preset voltage is provided.
  • the discharge control circuit includes a second transistor 1371, a third transistor 1373, a sixth resistor 1375, a seventh resistor 1376, and an eighth resistor 1377.
  • the emitter of the second transistor 1371 is electrically connected to the power ground 15, the base of the second transistor 1371 is electrically connected to the power source positive electrode 14 through the sixth resistor 1375, and the collector of the second transistor 1371 is first.
  • the positive electrode of the capacitor 1311 is electrically connected.
  • the collector of the third transistor 1373 is electrically connected to the base of the second transistor 1371, the emitter of the third transistor 1373 is electrically connected to the power supply ground 15, and the base of the third transistor 1373 is connected to the positive pole of the power supply. 14 electrical connections.
  • the seventh resistor 1376 and the eighth resistor 1377 are connected in series between the base of the second transistor 1371 and the power source positive electrode 14.
  • the switch circuit 12 switches from the high-impedance output to the low-impedance output to achieve a large current output to the motor of the capacitive load circuit 11 and in the switch circuit 12 Dynamic charging is achieved at low impedance, reducing the time for dynamic charging.
  • the power-on time is longer than the time when the first capacitor 1311 is charged to the ON voltage of the MOS transistor 121, and the high impedance of the switch circuit 12 is provided by the impedance when the MOS transistor 121 is turned off and the first resistor 123.
  • the low impedance is mainly provided by the impedance of the MOS transistor 121 itself after the MOS transistor 121 is turned on.
  • the base voltage of the third transistor 1373 is greater than the voltage of the emitter electrode, and the third diode 1331 is in an on state. Since the third transistor 1331 is in an on state, the second transistor 1371 has a base voltage lower than a voltage drop between the base and the emitter, thereby causing the second transistor 1371 to be in an off state.
  • the base voltage of the third transistor 1373 is lowered to be less than its base.
  • the voltage drop between the electrode and the emitter electrode is such that the third transistor 1373 is turned off.
  • the base voltage of the second transistor 1371 is higher than the emitter electrode.
  • the voltage, the second transistor 1371 is turned on, and the first capacitor 1311 is rapidly discharged.
  • the gate voltage of the MOS transistor 121 also rapidly drops below the on-voltage, the MOS transistor 121 is turned off, and the switching circuit 12 returns to the state of outputting a high impedance.
  • a second capacitor 1379 is provided for improving the detection capability of the third diode 1331 for the voltage drop at the input and output of the capacitive load circuit 11.
  • the second capacitor 1379 is connected in parallel with the seventh resistor 1376 and in series with the sixth resistor 1375.
  • the voltage between the input terminal and the output terminal of the capacitive load circuit 11 when the first capacitor 1311 is discharged can be controlled by controlling the sixth resistor 1375, the seventh resistor 1376, and the eighth resistor 1377.
  • the input and output of the capacitive load circuit 11 when the first capacitor 1311 is discharged can be controlled by controlling the sixth resistor 1375, the seventh resistor 1376, the eighth resistor 1377, and the second capacitor 1379. The voltage between the ends to improve control accuracy.
  • a third capacitor 1321 is connected between the anode of the first capacitor 1311 and the output end of the capacitive load circuit 11 for reducing the MOS.
  • the conduction current of the tube 121 For the principle and effect of the third capacitor 1321, refer to Embodiment 4.
  • the double triode formed by the second triode 1371 and the third triode 1373 serves as a discharge control circuit, and the control effect on the discharge of the first capacitor 1311 can be improved.
  • Embodiment 19 of the present invention provides an unmanned aerial vehicle.
  • the unmanned aerial vehicle of this embodiment includes an electric motor and an electronic governor.
  • the electronic governor is electrically connected to the motor, the motor is used to provide flight power, and the electronic governor is used to control the working state of the motor.
  • the electronic governor includes a motor drive circuit 2 and a power control circuit 1.
  • the power control circuit 1 is electrically connected to the motor drive circuit 2 for supplying power to the motor drive circuit 2.
  • the power control circuit 1 is configured to prevent an electric spark from being generated when the UAV power supply is hot swapped.
  • the power control circuit 1 includes a capacitive load circuit 11 and a switch circuit 12 And a delay control circuit 13.
  • the capacitive load circuit 11 and the switch circuit 12 are connected in series between the positive pole 14 of the power source and the power ground 15, that is, the input end of the capacitive load circuit 11 is connected to the positive pole 14 of the power supply, and the output end thereof is connected to the input end of the switch circuit 12, and the switch circuit 12 is connected.
  • the output is connected to the power ground 15.
  • the input end of the delay control circuit 13 is electrically connected to the positive pole 14 of the power supply, the output end thereof is connected to the power supply ground 15, and the control end thereof is electrically connected to the switch circuit 12 for controlling the operating state of the switch circuit 12.
  • the delay control circuit 13 controls the switch circuit 12 to switch the switch circuit 12 from the high-impedance output state to the power-on time after the power-on time exceeds the preset time. Low impedance output state.
  • the capacitive load circuit 11 is primarily used to provide a large current output to the motor of the unmanned aerial vehicle.
  • the capacitive load circuit 11 may be composed of a large capacitor, or may be composed of a plurality of parallel capacitors, or may be composed of a capacitor and other electronic components connected in series and in parallel.
  • the specific form of the capacitive load circuit 11 is not limited in this embodiment, and those skilled in the art can select according to actual needs.
  • the switching circuit 12 can be formed by a single crystal switching transistor, such as a bidirectional switching transistor.
  • the switch circuit 12 can also be composed of a circuit breaker and a resistor connected in parallel, or a circuit breaker and an inductor connected in parallel.
  • the switch circuit 12 can also be a CMOS (Complementary Metal Oxide Semiconductor), a complementary metal oxide semiconductor, an amplifier component of voltage control, and a basic unit constituting a CMOS digital integrated circuit. It should be clear to those skilled in the art that as long as the switch circuit 12 can be controlled by the delay control circuit 13 to change the impedance of its output, that is, it can be controlled by the delay control circuit 13 to switch from the high impedance output to the low impedance output. .
  • CMOS Complementary Metal Oxide Semiconductor
  • the specific form of the switch circuit 12 is not specifically limited in this embodiment, and those skilled in the art can specifically set as needed.
  • the high impedance means that the charging current of the capacitive load circuit 11 can be greatly reduced to satisfy the impedance for preventing the generation of the sparking function
  • the low impedance means that the impedance of the capacitive connecting circuit is small.
  • the charging current of the capacitive load circuit 11 when the power is dynamically supplied to the motor is not affected.
  • the high impedance can be the resistance or the impedance of the switching element when it is open or closed
  • the low impedance is the impedance of the guiding line or the impedance of the switching element when it is closed or turned on.
  • the delay control circuit 13 is not specifically limited in this embodiment, and may be a timing connected in series between the positive pole 14 of the power source and the power ground 15 and whose control terminal is electrically connected to the switch circuit 12.
  • the timer is activated when the power is turned on and is timed to a predetermined time, that is, after the power is turned on for a preset time, the control switch circuit 12 is switched from the high impedance output state to the low impedance output state.
  • the delay control circuit 13 can also be implemented by a timing control chip or control software.
  • the working principle of the power control circuit 1 is: when the power plug of the battery of the UAV is inserted into the power jack of the electronic governor, that is, the positive and negative poles of the battery are connected to the power control circuit 1
  • the interface When the interface is input, a voltage difference is input between the power source positive electrode 14 of the power supply control circuit 1 and the power source ground 15, and the capacitance in the capacitance load circuit 11 is charged by the high impedance output from the switch circuit 12. Since there is a high impedance output of the switching circuit 12, the charging current of the capacitor in the capacitive load circuit 11 is small, and no spark is generated at the power plug of the battery to prevent the electric sparking phenomenon.
  • the input and output terminals connected to the power supply positive electrode 14 and the power supply ground 15 respectively detect the differential pressure, and the power supply positive electrode 14 and the power supply ground 15 are in a power-on state.
  • the control terminal controls the switch circuit 12 to switch from the high impedance output state to the low impedance output state to prepare the capacitive load circuit 11 to output a large current to the motor.
  • the capacitive load circuit 11 can provide a large current output for the motor drive circuit 2, and after the output, the capacitive load circuit 11 can be performed by the low impedance outputted by the switch circuit 12.
  • the charging is fast to reduce the dynamic charging time of the capacitive load circuit 11 during the normal operation of the UAV, thereby improving the dynamic charging and discharging efficiency of the capacitive load circuit 11.
  • control switch circuit 12 is switched from the high-impedance output state to the low-impedance output state after the power supply positive electrode 14 and the power supply ground 15 are powered on for a predetermined time by the delay control circuit 13 in the power supply control circuit 1. Therefore, it is no longer necessary to manually connect the main power source and the large capacitor, which simplifies the operation of the anti-sparking when the UAV battery is hot-swapped, and realizes the automatic control of the anti-spark.
  • the UAV of the embodiment greatly reduces the current peak at the moment of power-on when the power plug is plugged in, reduces and eliminates the spark generated when the plug contacts, and effectively extends the life of the power connector.
  • the power control circuit 1 of the UAV of the present embodiment is very simple and easy to be integrated on hardware such as an electronic governor; it is very suitable for the smart battery to reduce the spark of the plug during hot plugging. Moreover, it can greatly reduce the current stress when the battery is powered on, and protect the battery, which is very suitable for application on high-power UAVs.
  • Embodiment 20 of the present invention provides an unmanned aerial vehicle.
  • the present embodiment is based on the solution provided in Embodiment 10, and the switch circuit 12 is arranged to include a MOS transistor 121 (metal-oxid-semiconductor field). Effect transistor).
  • MOS transistor 121 metal-oxid-semiconductor field. Effect transistor
  • the gate (G) of the MOS transistor 121 is electrically connected to the control terminal of the delay control circuit 13, and the drain (D) thereof is electrically connected to the output terminal of the capacitive load circuit 11 to have its source ( S) is electrically connected to the power ground 15 for turning on and off the MOS transistor 121 according to the voltage change of the gate.
  • the turn-on and turn-off of the MOS transistor 121 can be easily realized by controlling the voltage of the gate (G) by the delay control circuit 13. Switching between them to output high impedance or low impedance to the switching circuit 12. Moreover, the switch circuit 12 thus provided has a simple structure and a more stable performance.
  • the MOS transistor 121 is in an off state. Therefore, the switching circuit 12 outputs a high impedance, so that the charging current of the capacitive load circuit 11 is reduced to avoid generation. Instantaneous inrush current to prevent sparking at the joint.
  • the delay control circuit 13 increases the voltage of the gate (G) of the MOS transistor 121 to the turn-on voltage through the control terminal, for example, to 2.5V, thereby turning on the MOS transistor 121. Since the impedance when the MOS transistor 121 is turned on is small, the switching transistor circuit can output a low impedance after the MOS transistor 121 is turned on.
  • the turn-on voltage of the MOS transistor 121 is only an exemplary turn-on voltage of the embodiment. In actual settings, different MOS transistor 121 turn-on voltages may be selected according to circuit requirements.
  • raising the gate (G) voltage of the MOS transistor 121 to the turn-on voltage may be completed instantaneously or by a period of time.
  • the timer (G) is turned on immediately by the timer when the timing exceeds the preset time, or the voltage of the gate (G) is slowly increased over a period of time by the control chip and the control software until the preset is exceeded.
  • the turn-on voltage is reached after time.
  • a first resistor 123 connected in parallel with the MOS transistor 121 may be disposed in the switching circuit 12 for protecting the MOS transistor 121.
  • the capacitive load circuit 11 when the power source positive electrode 14 and the power source ground 15 are powered on, the capacitive load circuit 11 During the charging process, the first resistor 123 will function as a shunt to avoid excessive charging current at the time of power-on to break through the MOS transistor 121.
  • the switching circuit 12 may be connected in series with the capacitive load circuit 11 in a branch and in parallel with the delay control circuit 13, that is, the switching circuit 12 is disposed in the branch of the capacitive load circuit 11.
  • the turning on and off of the MOS transistor 121 does not affect the output of the power supply to the UAV motor.
  • the switch circuit 12 can also connect the branch formed by the parallel connection of the capacitive load circuit 11 and the delay control circuit 13 in series with the switch circuit 12, that is, the switch circuit 12 is connected in series in the trunk circuit.
  • the time during which the power supply control circuit 1 outputs to the UAV motor can be controlled by the turning on and off of the MOS transistor 121.
  • the effect of anti-sparking can be improved, and the voltage overshoot spike at the time of power-on can be eliminated, so that the overshoot spike is not output to the motor.
  • the power supply control circuit 1 in the UAV of the present embodiment can make the structure of the switch circuit 12 simpler by providing the MOS transistor 121, and can also control the MOS transistor by providing a turn-on voltage for the gate (G). 121 The time from the off state to the on state is easier and more convenient to control. Moreover, the parallel connection of the first resistor 123 for the MOS transistor 121 can protect the MOS transistor 121 and improve the stability of the entire power supply control circuit 1.
  • Embodiment 21 of the present invention provides an unmanned aerial vehicle.
  • the present embodiment is based on the solution provided in Embodiment 11, and the switch circuit 12 is configured to include a relay 125 and a second resistor 127.
  • the control terminal of the delay control circuit 13 is electrically connected to the relay 125 for controlling the opening and closing state of the open end of the relay 125 to switch the switching circuit from the high impedance output state to the low impedance output state.
  • the delay control circuit 13 and the capacitive load circuit 11 are connected in parallel between the power source positive electrode 14 and the power source ground 15. That is, the input end of the delay control circuit 13 is connected to the positive pole 14 of the power supply, and the output end thereof is connected to the power supply ground 15; the input end of the capacitive load circuit 11 is also connected to the positive pole 14 of the power supply, and the output end thereof is also connected to the power supply ground 15. And the control end of the delay control circuit 13 is electrically connected to the input end of the relay 125, and the output end of the relay 125 is connected to the power supply ground 15. The switch of the relay 125 is connected in parallel with the second resistor 127, and the two ends thereof are respectively connected to the output end of the delay control circuit 13 and the output end of the capacitive load circuit 11.
  • the switch of the relay 125 is turned off.
  • the second resistor 127 serves as a high-impedance output of the switch circuit 12, thereby reducing the current charged by the capacitive load circuit 11 at the time of power-on, eliminating the instantaneous peak value of the capacitive load circuit 11 when charging, thereby preventing the power plug from being sparked.
  • the control terminal of the delay control circuit 13 turns on the relay 125.
  • the second resistor 127 When the relay 125 is turned on, the second resistor 127 is short-circuited by the relay 125, and the output end of the capacitive load circuit 11 is directly connected to the power ground 15 through the relay 125, that is, the capacitive load circuit 11 is dynamic through the low impedance outputted by the switch circuit 12. Charging, thereby shortening the time of dynamic charging, and improving the efficiency of outputting a large current by the capacitive load circuit 11.
  • the power supply control circuit 1 in the UAV of the present embodiment realizes switching of the high-impedance output and the low-impedance output of the switch circuit 12 by providing the parallel relay 125 and the second resistor 127, which is convenient, simple, and easy to implement when powering up. Automatic control of anti-sparking. It is also possible to control the time at which the power control circuit 1 outputs to the unmanned aerial vehicle motor. And for higher voltages, the effect of anti-sparking can be improved, and the voltage overshoot spike at the time of power-on can be eliminated, so that the overshoot spike is not output to the motor.
  • Embodiment 22 of the present invention provides an unmanned aerial vehicle.
  • the delay control circuit 13 is configured to include a first capacitor 1311 and a pull-up resistor 1313 on the basis of the technical solutions provided in Embodiment 19, Embodiment 20 or Embodiment 21.
  • the first capacitor 1311 and the pull-up resistor 1313 are connected in series between the power source positive electrode 14 and the power source ground 15 and in parallel with the capacitive load circuit 11; and the anode of the first capacitor 1311 is electrically connected to the switch circuit 12.
  • the pull-up resistor 1313 may be directly connected in series to the positive pole 14 of the power supply, or may be indirectly connected in series with the positive pole 14 of the power supply.
  • the pull up resistor 1313 can be in series with the system power supply of the UAV that is divided by the power supply positive terminal 14.
  • the first capacitor 1311 is also charged by the pull-up resistor 1313 while the capacitive load circuit 11 is being charged. As the first capacitor 1311 is charged, the voltage across it is also gradually increased, thereby controlling the operating state of the switching circuit 12 by the voltage change between the positive and negative terminals of the first capacitor 1311.
  • the voltage between the positive pole and the negative pole of the first capacitor 1311 also increases with time, that is, the relay 125 electrically connected to the two poles of the first capacitor 1311
  • the voltage between the input and output increases as the power-up time increases.
  • the relay 125 is closed, and the output impedance of the switch circuit 12 is switched from high impedance to low impedance. .
  • the voltage between the input terminal and the output terminal of the load capacitor circuit gradually decreases as the capacitor in the load capacitor circuit discharges.
  • the first capacitor 1311 starts to discharge, and the voltage between the positive electrode and the negative terminal of the first capacitor 1311 also decreases, and the relay 125 inputs The voltage between the terminal and the output also decreases.
  • the relay 125 is turned off and the output impedance of the switching circuit 12 is switched from a low impedance to a high impedance.
  • the anode of the first capacitor 1311 when the anode of the first capacitor 1311 is electrically connected to the gate (G) of the MOS transistor 121, as the power-on time increases, the voltage between the anode and the cathode of the first capacitor 1311 also increases with time.
  • the rise that is, the voltage of the gate (G) of the MOS transistor 121 electrically connected to the positive electrode of the first capacitor 1311 also increases as the power-on time increases.
  • the MOS transistor 121 After the power-on time exceeds the preset time, after the voltage of the gate (G) of the MOS transistor 121 exceeds the turn-on voltage, the MOS transistor 121 is turned on, and the output impedance of the switch circuit 12 is switched from high impedance to low impedance. .
  • the voltage between the input terminal and the output terminal of the load capacitor circuit gradually decreases as the capacitor in the load capacitor circuit discharges.
  • the first capacitor 1311 starts to discharge, and the positive voltage of the first capacitor 1311 also decreases, and the gate of the MOS transistor 121 (G) The voltage is also reduced.
  • the MOS transistor 121 is turned off, and the output impedance of the switching circuit 12 is switched from a low impedance to a high impedance.
  • the preset time when the switching circuit 12 is switched from the high-impedance output state to the low-impedance output state is the time during which the first capacitor 1311 is charged to the conduction voltage of the relay 125 or the MOS transistor 121, that is, the first capacitor. 1311 The time to charge to the preset voltage value. And, by controlling the parameters of the first capacitor 1311 and the pull-up resistor 1313, different firsts can be obtained.
  • the charging time of the capacitor 1311 that is, the time at which the different control switching circuit 12 is switched from high impedance to low impedance, that is, the preset time, is obtained.
  • a third capacitor 1321 may be connected between the anode of the first capacitor 1311 and the output end of the capacitive load circuit 11 for reducing the conduction current of the MOS transistor 121.
  • Vgs refers to the voltage difference between the gate (G) and the source (S);
  • Vds refers to the voltage difference between the drain (D) and the source (S).
  • the third capacitor 1321 can also extend the discharge time of the first capacitor 1311, thereby increasing the turn-on time of the MOS transistor 121.
  • the power supply control circuit 1 in the UAV of the present embodiment can pass the charging and discharging of the first capacitor 1311 very conveniently by the first capacitor 1311 and the pull-up resistor 1313 connected in series between the power source positive electrode 14 and the power source ground 15.
  • the control switch circuit 12 switches between a high impedance output and a low impedance output to automate the hot swapping of the battery.
  • the charging time of the first capacitor 1311 can be controlled by adjusting the parameters of the first resistor 123 and the first capacitor 1311, thereby controlling the switching circuit 12 to switch from the high-impedance output to the low-impedance output, thereby improving the capacitor at the time of power-on.
  • the time during which the load circuit 11 is charged at a high impedance improves the effect of the power supply control circuit 1 against sparking.
  • Embodiment 23 of the present invention provides an unmanned aerial vehicle.
  • the pull-up resistor 1313 is connected in parallel with a diode 1331 for accelerating the discharge of the first capacitor 1311.
  • the anode of the diode 1331 is electrically connected to the anode of the first capacitor 1311, and the cathode of the diode 1331 is electrically connected to the input end of the pull-up resistor 1313.
  • the first capacitor 1311 it is possible to discharge through the diode 1331 to accelerate the discharge of the first capacitor 1311 to return it to the initial state to be charged as soon as possible.
  • a third capacitor 1321 is connected between the anode of the first capacitor 1311 and the output end of the capacitive load circuit 11 for reducing the MOS.
  • the conduction current of the tube 121 For the operation principle and effect of the third capacitor 1321, refer to Embodiment 22.
  • the discharge of the first capacitor 1311 is accelerated by connecting a pull-up resistor 1313 in parallel with a diode 1331, so that the circuit can be quickly restored to the initial state for the next battery connection.
  • Embodiment 24 of the present invention provides an unmanned aerial vehicle.
  • the first capacitor 1311 is connected in parallel with a third resistor 1333, and the third resistor 1333 is connected in series with the pull-up resistor 1313.
  • the third resistor 1333 is for dividing the power supply with the pull-up resistor 1313 for protecting the switch circuit 12.
  • the power control circuit 1 of the UAV of the present embodiment when the power source positive electrode 14 and the power source ground 15 are in a power-on state, the power source is divided by the pull-up resistor 1313 and the third resistor 1333 to charge the first capacitor 1311.
  • the switching circuit 12 connected to the positive terminal of the first capacitor 1311 can be protected.
  • the MOS transistor 121 when the MOS transistor 121 is connected to the positive electrode of the first capacitor 1311, since the Vgs of the MOS transistor 121 may be within 20V, and the voltage difference between the power source positive electrode 14 and the power source ground 15 may be higher than 20V, it may pass
  • the third resistor 1333 is connected to adjust the voltage of the gate (G) of the MOS transistor 121 such that the Vgs full voltage of the MOS transistor 121 approaches 12V, thereby protecting the MOS transistor 121.
  • the third resistor 1333 can also protect the relay 125 or other switching components in the switch circuit 12.
  • the first capacitor 1311 When the power supply positive electrode 14 and the power supply ground 15 are in the power-off state, when the voltage of the input terminal and the output terminal of the load capacitance circuit is lowered to a preset voltage (for example, 6-7v), the first capacitor 1311 can be discharged through the third resistor 1333. Thereby, the discharge of the first capacitor 1311 is accelerated, so that it returns to the initial state to be charged as soon as possible.
  • a preset voltage for example, 6-7v
  • a third capacitor 1321 is connected between the anode of the first capacitor 1311 and the output end of the capacitive load circuit 11 for reducing the MOS.
  • the conduction current of the tube 121 For the operation principle and effect of the third capacitor 1321, refer to Embodiment 22.
  • the power supply control circuit 1 in the UAV of the present embodiment can adjust the voltage dividing ratio of the pull-up resistor 1313 and the third resistor 1333 by connecting a pull-up resistor 1313 in series with a third resistor 1333 in parallel with the first capacitor 1311. To protect the switch circuit 12. At the same time, the third resistor 1333 can also accelerate its discharge when the first capacitor 1311 is discharged, so that the circuit can quickly return to the initial state for the next access of the battery.
  • Embodiment 25 of the present invention provides an unmanned aerial vehicle.
  • the first capacitor 1311 is connected in parallel with a Zener diode 1335, and the Zener diode 1335 is connected in series with the pull-up resistor 1313.
  • the parallel regulator circuit is formed in parallel with the pull-up resistor 1313 to protect the switch circuit 12.
  • the Zener diode 1335 When the power control circuit 1 in the electronic governor of the embodiment is in operation, the Zener diode 1335 will always stabilize the voltage of the positive pole of the first capacitor 1311 at the voltage regulator value of the diode 1331, thereby protecting the positive pole of the first capacitor 1311.
  • Switch circuit 12 For example, when the MOS transistor 121 is connected to the positive terminal of the first capacitor 1311, the Zener diode 1335 of FIG. 7 can control the Vgs of the MOS transistor 121 to be within 12 V, thereby protecting the Zener diode 1335 from being burned out.
  • the Zener diode 1335 can also protect the relay 125 or other transistor components in the switching circuit 12.
  • a third capacitor 1321 is connected between the anode of the first capacitor 1311 and the output end of the capacitive load circuit 11 for reducing the MOS.
  • the conduction current of the tube 121 For the operation principle and effect of the third capacitor 1321, refer to Embodiment 22.
  • the switching circuit 12 can be protected by connecting a Zener diode 1335 in parallel with the first capacitor 1311 for the pull-up resistor 1313.
  • Embodiment 26 of the present invention provides an unmanned aerial vehicle.
  • this embodiment is based on the technical solution provided in Embodiment 22, and a discharge control circuit for controlling discharge of the first capacitor 1311 after the voltage of the capacitive load circuit 11 is lower than a preset voltage is provided.
  • the discharge control circuit includes a first transistor 1351, a fourth resistor 1353, and a fifth resistor 1355.
  • the emitter of the first transistor 1351 is electrically connected to the anode of the first capacitor 1311, the collector of the first transistor 1351 is connected to the power ground 15, and the base of the first transistor 1351 passes through the fourth resistor 1353.
  • the power supply positive electrode 14 is electrically connected, and the base of the first transistor 1351 is also electrically connected to the power supply ground 15 through the fifth resistor 1355.
  • the switch circuit 12 switches from the high-impedance output to the low-impedance output to achieve a large current output to the motor of the capacitive load circuit 11 and in the switch circuit 12 Dynamic charging is achieved at low impedance, reducing the time for dynamic charging.
  • the power-on time is longer than the time when the first capacitor 1311 is charged to the ON voltage of the MOS transistor 121, and the high impedance of the switch circuit 12 is provided by the impedance when the MOS transistor 121 is turned off and the first resistor 123.
  • the low impedance is mainly provided by the impedance of the MOS transistor 121 itself after the MOS transistor 121 is turned on.
  • the voltage drop between the base voltage of the first transistor 1351 and the emitter electrode is smaller than the conduction voltage of the first transistor 1351, and therefore, the battery is connected.
  • the power supply control circuit 1 is in an off state for the entire time.
  • a third capacitor 1321 is connected between the anode of the first capacitor 1311 and the output end of the capacitive load circuit 11 for reducing the MOS.
  • the conduction current of the tube 121 For the operation principle and effect of the third capacitor 1321, refer to Embodiment 22.
  • the power supply control circuit 1 in the UAV of the present embodiment can delay the time during which the switching circuit 12 is switched from the low impedance output state to the high impedance output state by setting the discharge control circuit including the triode, thereby increasing the discharge time of the capacitive load circuit 11.
  • Embodiment 27 of the present invention provides an unmanned aerial vehicle.
  • this embodiment is based on the technical solution provided in Embodiment 22, and a discharge control circuit for controlling discharge of the first capacitor 1311 after the voltage of the capacitive load circuit 11 is lower than a preset voltage is provided.
  • the discharge control circuit includes a second transistor 1371, a third transistor 1373, a sixth resistor 1375, a seventh resistor 1376, and an eighth resistor 1377.
  • the emitter of the second transistor 1371 is electrically connected to the power ground 15, the base of the second transistor 1371 is electrically connected to the power source positive electrode 14 through the sixth resistor 1375, and the collector of the second transistor 1371 is first.
  • the positive electrode of the capacitor 1311 is electrically connected.
  • the collector of the third transistor 1373 is electrically connected to the base of the second transistor 1371, the emitter of the third transistor 1373 is electrically connected to the power supply ground 15, and the base of the third transistor 1373 is connected to the positive pole of the power supply. 14 electrical connections.
  • the seventh resistor 1376 and the eighth resistor 1377 are connected in series between the base of the second transistor 1371 and the power source positive electrode 14.
  • the switch circuit 12 switches from the high-impedance output to the low-impedance output to achieve a large current output to the motor of the capacitive load circuit 11 and in the switch circuit 12 Dynamic charging is achieved at low impedance, reducing the time for dynamic charging.
  • the power-on time is longer than the time when the first capacitor 1311 is charged to the ON voltage of the MOS transistor 121, and the high impedance of the switch circuit 12 is provided by the impedance when the MOS transistor 121 is turned off and the first resistor 123.
  • the low impedance is mainly provided by the impedance of the MOS transistor 121 itself after the MOS transistor 121 is turned on.
  • the base voltage of the third transistor 1373 is greater than the voltage of the emitter electrode, and the third diode 1331 is in an on state. Since the third transistor 1331 is in an on state, the second transistor 1371 has a base voltage lower than a voltage drop between the base and the emitter, thereby causing the second transistor 1371 to be in an off state.
  • the base voltage of the third transistor 1373 is lowered to be less than its base.
  • the voltage drop between the electrode and the emitter electrode is such that the third transistor 1373 is turned off.
  • the third transistor 1373 is turned off, the base voltage of the second transistor 1371 is higher than the emitter voltage, the second transistor 1371 is turned on, and the first capacitor 1311 is rapidly discharged.
  • the gate voltage of the MOS transistor 121 also rapidly drops below the on-voltage, the MOS transistor 121 is turned off, and the switching circuit 12 returns to the state of outputting a high impedance.
  • a second capacitor 1379 is provided for improving the detection capability of the third diode 1331 for the voltage drop at the input and output of the capacitive load circuit 11.
  • the second capacitor 1379 is connected in parallel with the seventh resistor 1376 and in series with the sixth resistor 1375.
  • the voltage between the input terminal and the output terminal of the capacitive load circuit 11 when the first capacitor 1311 is discharged can be controlled by controlling the sixth resistor 1375, the seventh resistor 1376, and the eighth resistor 1377.
  • the input and output of the capacitive load circuit 11 when the first capacitor 1311 is discharged can be controlled by controlling the sixth resistor 1375, the seventh resistor 1376, the eighth resistor 1377, and the second capacitor 1379. The voltage between the ends to improve control accuracy.
  • a third capacitor 1321 is connected between the anode of the first capacitor 1311 and the output end of the capacitive load circuit 11 for reducing the MOS.
  • the conduction current of the tube 121 For the operation principle and effect of the third capacitor 1321, refer to Embodiment 22.
  • the double triode composed of the second triode 1371 and the third triode 1373 serves as a discharge control circuit, and the control effect on the discharge of the first capacitor 1311 can be improved.
  • Embodiment 28 of the present invention provides a control method of a power supply output circuit.
  • 11 is a schematic flow chart of a method for controlling a power output circuit according to Embodiment 28 of the present invention.
  • the control method of the present embodiment includes a capacitive load circuit 11 and a switching circuit 12 for providing a large current output to the unmanned aerial vehicle motor.
  • the switch circuit 12 is connected in series between the capacitive load circuit 11 and the power ground 15 .
  • the method for controlling the switch circuit 12 in the power output circuit control method of this embodiment includes:
  • the switch circuit 12 is controlled to switch from the high impedance output state to the low impedance output state after the power supply positive electrode 14 and the power supply ground 15 are powered on for more than a preset time.
  • the method of controlling the switching circuit 12 to switch from the high impedance output state to the low impedance output state can be implemented by software or hardware circuits, and chips.
  • the operating state of the switching circuit 12 can be controlled by controlling the turning on and off of the relay 125 in the switching circuit 12. It is also possible to control the switching circuit 12 by the MOS transistor 121 which may be included in the switching circuit 12 from the off state to the on state.
  • the control of time can be realized by a timer or a timing circuit and timing software.
  • the control MOS transistor 121 is switched from the off state to the on state after the preset time, thereby switching the switch circuit 12 from the high impedance output state to The purpose of the low impedance output state.
  • the method for controlling the switch circuit 12 further includes: controlling the discharge of the first capacitor 1311, and then controlling the switch circuit 12 to switch from a low impedance output state to a high impedance after the voltage of the capacitive load circuit 11 is lower than a preset voltage. Output status.
  • controlling the discharge of the first capacitor 1311 and controlling the switching circuit 12 to switch from the low impedance output state to the high impedance output state can be implemented by a chip.
  • the switch circuit 12 can be connected to a control chip, the first capacitor discharge is controlled by the voltage change of the capacitive load circuit 11 detected on the chip, and the switch circuit 12 is controlled after the voltage of the capacitive load circuit 11 is lower than the preset voltage. Switch from low impedance output state to high impedance output state.
  • the above control method can also be implemented by a circuit.
  • a sampling control circuit connected to the first capacitor 1311 is provided.
  • the sampling control circuit acquires the voltage of the capacitive load circuit 11 and decreases to a preset value
  • the first capacitor 1311 is controlled to discharge to control the working state of the switching circuit 12.
  • the discharge of the first capacitor 1311 and the switching circuit 12 can also be implemented by software. Control from low impedance output state to high impedance output state.
  • control method the principle, and the process of the control method in this embodiment are the same as the control method, the principle, and the operation process described in the foregoing embodiments, and those skilled in the art may refer to all the above embodiments. This will not be repeated here.
  • the control method of the power output circuit of the embodiment switches the high-impedance output state to the low-impedance output state after the power-on exceeds the preset time by the control switch circuit 12, so that the battery hot plugging process can be realized very conveniently and simply. Anti-sparking purposes, and no manual operation.
  • the related apparatus and method disclosed may be implemented in other manners.
  • the device embodiments described above are merely illustrative.
  • the division of the modules or units is only a logical function division.
  • there may be another division manner for example, multiple units or components may be used. Combinations can be integrated into another system, or some features can be ignored or not executed.
  • the mutual coupling or direct coupling or communication connection shown or discussed may be an indirect coupling or communication connection through some interface, device or unit, and may be in an electrical, mechanical or other form.
  • the units described as separate components may or may not be physically separated, and the components displayed as units may or may not be physical units, that is, may be located in one place, or may be distributed to multiple network units. Some or all of the units may be selected according to actual needs to achieve the purpose of the solution of the embodiment.
  • each functional unit in each embodiment of the present invention may be integrated into one processing unit, or each unit may exist physically separately, or two or more units may be integrated into one unit.
  • the above integrated unit can be implemented in the form of hardware or in the form of a software functional unit.
  • the integrated unit if implemented in the form of a software functional unit and sold or used as a standalone product, may be stored in a computer readable storage medium.
  • a computer readable storage medium comprising instructions for causing a computer processor to perform all or part of the steps of the methods described in various embodiments of the present invention.
  • the foregoing storage medium includes: a U disk, a removable hard disk, a read-only memory (ROM), a random access memory (RAM), a magnetic disk, or an optical disk, and the like, which can store program codes.

Landscapes

  • Engineering & Computer Science (AREA)
  • Power Engineering (AREA)
  • Direct Current Feeding And Distribution (AREA)
  • Electronic Switches (AREA)

Abstract

一种电源控制电路，包括：电容负载电路（11）、开关电路（12）和延时控制电路（13）。电容负载电路（11）和延时控制电路（13）并联在电源正极（14）和电源地（15）之间，且开关电路（12）与电容负载电路（11）串联并与延时控制电路（13）的控制端电连接。延时控制电路（13）用于在电源正极（14）和电源地（15）之间上电时间超过预设时间后控制开关电路（12）由输出高阻抗切换为输出低阻抗。还提供一种电源输出电路的控制方法，包括：控制开关电路（12）在上电超出预设时间后由输出高阻抗切换为输出低阻抗。还提供一种采用上述电源控制电路或控制方法的电子调速器和无人飞行器。本发明的电源控制电路、电子调速器、无人飞行器及电源控制方法，可以简化无人飞行器电池热插拔中防电火花操作。

Description

电源控制电路、电子调速器、无人飞行器及控制方法 技术领域
本发明涉及一种电源控制电路、电子调速器、无人飞行器及控制方法，尤其涉及一种能够用于上电防打火的电源控制电路，属于飞行器技术领域。
背景技术
电子调速器是飞行器中最重要的部件之一，用于驱动飞行器中的电动机转动，以实现飞行器启停和调速等。无人机的电子调速器通过把可更换电池的直流电压转换为交流电压，用来驱动无刷电动机，转换过程中电流很大，必须要使用大电容来保证瞬时的能量供给。当电调安装在无人机上面之后，相当于多个大电容并联，从总的供电插头来看，容性负载很大。在电池更换的过程中往往会出现电池插头是带电的，直接插入无人机电池仓的时候，会出现热插拔过程。而当插入供电插头的瞬间，插头触碰会产生较大的电火花，从而降低插头的寿命和性能。
现有技术中，防止热插拔过程中产生电火花一般是通过先接入一个电阻为无人飞行器中为电动机提供大电流的大电容进行预充电，然后再通过手动控制辅助开关的方式将大电容串联到电源的两端，以起到防电火花目的。
但是，现有技术中的这种防止电火花的方式的需要手动操作，非常的繁琐。
发明内容
本发明的目的是提供一种电源控制电路、电子调速器、无人飞行器及控制方法，以解决现有技术中无人机电池热插拔过程中防电火花需要操作繁琐的技术问题。
为了实现上述目的，本发明提供了以下技术方案：
第一方面，提供一种无人飞行器的电源控制电路，包括：电容负载 电路、开关电路和延时控制电路；
所述电容负载电路的输入端与电源正极电连接；
所述开关电路串联在所述负载电路的输出端和电源地之间；
所述延时控制电路的输入端和输出端之间分别连接所述电源正极和电源地，所述延时控制电路的控制端与所述开关电路电连接；
所述延时控制电路用于在所述电源正极和电源地为上电状态时，控制所述开关电路在上电时间超过预设时间后由高阻抗输出状态切换至低阻抗输出状态。
第二方面，提供一种电子调速器，包括电机驱动电路和电源控制电路，所述电源控制电路与所述电机驱动电路电连接，用于给所述电机驱动电路供电，所述电源控制电路包括：电容负载电路开关电路和延时控制电路；
所述电容负载电路的输入端与电源正极电连接；
所述开关电路串联在所述负载电路的输出端和电源地之间；
所述延时控制电路的输入端和输出端之间分别连接所述电源正极和电源地，所述延时控制电路的控制端与所述开关电路电连接；
所述延时控制电路用于在所述电源正极和电源地为上电状态时，控制所述开关电路在上电时间超过预设时间后由高阻抗输出状态切换至低阻抗输出状态。
第三方面，提供一种无人飞行器，包括：电动机以及电子调速器，所述电动机用于提供飞行动力；
所述电子调速器与所述电动机电连接，用于控制所述电机的工作状态；
所述电子调速器包括：包括电机驱动电路和电源控制电路；
所述电源控制电路与所述电机驱动电路电连接，用于给所述电机驱动电路供电；
所述电源控制电路包括：电容负载电路开关电路和延时控制电路；
所述电容负载电路的输入端与电源正极电连接；
所述开关电路串联在所述负载电路的输出端和电源地之间；
所述延时控制电路的输入端和输出端之间分别连接所述电源正极和电源地，所述延时控制电路的控制端与所述开关电路电连接；
所述延时控制电路用于在所述电源正极和电源地为上电状态时，控制所述开关电路在上电时间超过预设时间后由高阻抗输出状态切换至低阻抗输出状态。
第四方面，提供一种电源输出电路的控制方法，所述电源输出电路包括用于为无人飞行器电动机提供大电流输出的电容负载电路，所述电源输出电路还包括：开关电路，所述开关电路串联在电容负载电路和电源地之间；
控制所述开关电路的方法包括：
控制所述开关电路在所述电源正极和电源地之间上电时间超过预设时间后由高阻抗输出状态切换至低阻抗输出状态。
本发明提供的电源控制电路、电子调速器、无人飞行器及控制方法，通过延时控制电路来控制开关电路的在电源正极和电源地之间上电时间超过预设时间后由高阻抗输出状态切换至低阻抗输出状态，从而减少了手动将主电源接入的操作，实现了防电火花和大电流输出的自动控制。
附图说明
图1为本发明实施例1提供的电源控制电路的示意图；
图2a为本发明实施例2提供的一种电源控制电路的示意图；
图2b为本发明实施例2提供的另一种电源控制电路的示意图；
图3为本发明实施例3提供的电源控制电路的示意图；
图4为本发明实施例4提供的电源控制电路的示意图；
图5为本发明实施例5提供的电源控制电路的示意图；
图6a为本发明实施例6提供的一种电源控制电路的示意图；
图6b为本发明实施例6提供的另一种电源控制电路的示意图；
图7a为本发明实施例7提供的一种电源控制电路的示意图；
图7b为本发明实施例7提供的另一种电源控制电路的示意图
图8为本发明实施例8提供的电源控制电路的示意图；
图9为本发明实施例9提供的电源控制电路的示意图；
图10为本发明实施例10提供的电子调速器结构示意图；
图11为本发明实施例28提供的电源输出电路的控制方法流程示意图。
图中：
1、电源控制电路；                                  11、电容负载电路；
12、开关电路；                                     121、MOS管；
123、第一电阻；                                    125、继电器；
127、第二电阻；                                    13、延时控制电路；
1311、第一电容；                                   1313、上拉电阻；
1321、第三电容；                                   1331、二极管；
1333、第三电阻；                                   1335、稳压二极管；
1351、第一三极管；                                 1353、第四电阻；
1355、第五电阻；                                   1371、第二三极管；
1373、第三三极管；                                 1375、第六电阻；
1376、第七电阻；                                   1377、第八电阻；
1379、第二电容；                                   14、电源正极；
15、电源地；                                       2、电机驱动电路。
具体实施方式
下面结合附图，对本发明的一些实施方式作详细说明。在不冲突的情况下，下述的实施例及实施例中的特征可以相互组合。
实施例1
本发明实施例1提供一种无人飞行器的电源控制电路1。   图1为本实施例1提供的电源控制电路的示意图。
本实施例的电源控制电路1，用于防止无人飞行器电源热插拔时产生 电火花。该电源控制电路1包括：电容负载电路11、开关电路12和延时控制电路13。其中，电容负载电路11和开关电路12串联在电源正极14和电源地15之间，也即电容负载电路11的输入端连接电源正极14，其输出端连接开关电路12的输入端，开关电路12的输出端则连接电源地15。延时控制电路13的输入端与电源正极14电连接，其输出端与电源地15连接，其控制端与开关电路12电连接，用于控制开关电路12的工作状态。其中，当电源正极14和电源地15的通电状态为上电状态时，延时控制电路13控制开关电路12在上电时间超过预设时间后将所述开关电路12由高阻抗输出状态切换至低阻抗输出状态。
具体来说，电容负载电路11，其主要用于为无人飞行器的电动机提供大电流输出。该电容负载电路11可以是由一个大电容构成，也可以是由多个并联电容构成，还可以是由电容和其他电子元件串并联组成。在本实施例中对所述电容负载电路11的具体形式不作限制，本领域技术人员可以根据实际需要进行选择。
开关电路12可以是由单一晶体开关管构成，比如，双向开关三极管。该开关电路12也可以是由并联的断路器和电阻，或者并联的断路器和电感组成。当然，该开关电路12还可以是CMOS(Complementary Metal Oxide Semiconductor)，互补金属氧化物半导体，电压控制的一种放大器件，是组成CMOS数字集成电路的基本单元)开关或者集成芯片。本领域技术人员应该明确只要开关电路12能够受延时控制电路13的控制从而改变其输出的阻抗即可，也即，可以受延时控制电路13控制由高阻抗输出切换至低阻抗输出即可。因此，为了行文更简洁，在本实施例中对开关电路12的具体形式不做具体限制，本领域技术人员可以根据需要具体设置。另外，需要说明的是，高阻抗是指能够将电容负载电路11的充电电流大幅度减小以满足防止产生电火花功能的阻抗，而低阻抗则是指接入电容负载电路的阻抗很小基本不影响电容负载电路11的在向电动机动态供电时的充电电流。举例来说，高阻抗可以是电阻或者是开关元件断路或截止时自身所具有的阻抗，低阻抗则是指导线的阻抗或者是开关元件闭合或导通时具有的阻抗。
延时控制电路13在本实施例中也不作具体的限制，其可以是串联在 电源正极14和电源地15之间并且其控制端与开关电路12电连接的计时器，该计时器在电源上电时启动并在计时到预定时间，也即上电时间超过预设时间之后控制开关电路12由高阻抗输出状态切换至低阻抗输出状态。当然，延时控制电路13也可以通过计时控制芯片或者控制软件来实现。
本实施例的电源控制电路1的工作原理是：当无人飞行器的电池的电源插头插入电子调速器的电源插孔时，也即电池的正极和负极接入电源控制电路1的输入接口时，电源控制电路1的电源正极14和电源地15之间输入压差，电容负载电路11中的电容通过开关电路12输出的高阻抗进行充电。由于，有开关电路12的高阻抗输出，所以，电容负载电路11中的电容充电电流很小，在电池的电源插头处不会出现电火花，防止了电打火现象。与此同时，延时控制电路13分别与电源正极14和电源地15连接的输入端和输出端检测出该压差，获取到电源正极14和电源地15之间处于上电状态，则在上电超过预设时间之后通过控制端控制开关电路12由高阻抗输出状态切换为低阻抗输出状态从而为电容负载电路11向电动机输出大电流做准备。这样，当电子调速器调速过程中需要大电流时，电容负载电路11可以为其提供大电流的输出，而在输出后电容负载电路11可以通过开关电路12输出的低阻抗进行快速充电，以降低无人飞行器正常工作过程时电容负载电路11的动态充电时间，从而提高电容负载电路11的动态充放电效率。
本实施例的电源控制电路1通过延时控制电路13在电源正极14和电源地15上电超过预设时间后控制开关电路12由高阻抗输出状态切换至低阻抗输出状态，从而无需再手动将主电源和大电容连接，简化了无人飞行器电池热插拔时防打火的操作，实现了防电火花的自动控制。
同时，本实施例的电源控制电路1大大减小了插上电源插头时上电瞬间的电流峰值，减小并消除了插头接触瞬间产生的电火花，有效延长了电源接头的寿命。
而且，本实施例的电源控制电路1非常简单，容易集成在电子调速器等硬件上；非常适宜于智能电池在热插拔时候减小插头的电火花。同时还可以大大减小电池上电时候的电流应力，起到保护电池的作用，非常 适合在大功率无人机上应用。
实施例2
本发明实施例2提供一种无人飞行器的电源控制电路。图2a为本实施例2提供的一种电源控制电路的示意图；图2b为本实施例2提供的另一种电源控制电路的示意图。
本实施例是在实施例1提供的方案的基础上，将该开关电路12设置为包括MOS管121(金属(metal)—氧化物(oxid)—半导体(semiconductor)场效应晶体管)。
具体而言，是将MOS管121的栅极(G)与延时控制电路13的控制端电连接，将其漏极(D)与电容负载电路11的输出端电连接，将其源极(S)与电源地15电连接，用于根据栅极的电压变化实现MOS管121的导通和截止。
由于MOS管121在截止时具有非常大的阻抗，而在导通时阻抗很小，通过延时控制电路13控制栅极(G)的电压就可以非常方便的实现MOS管121的导通和截止之间的切换，从而为开关电路12输出高阻抗或者低阻抗。并且，这样设置的开关电路12结构也很简单，性能更加稳定。
具体的，在工作时，当电源正极14和电源地15之间上电时，MOS管121处于截止状态，因此，开关电路12输出一个高阻抗，使得电容负载电路11的充电电流降低，避免产生瞬时涌流，从而防止接头处产生电火花。当上电超过预设时间后，延时控制电路13则通过控制端将MOS管121栅极(G)的电压提高到开启电压，比如，提高到2.5V，从而导通该MOS管121。由于MOS管121导通时的阻抗很小，因此在导通该MOS管121后可以使开关管电路输出一低阻抗。当然，上述MOS管121的导通电压仅是本实施例的示例性导通电压，在实际设置中可以根据电路需要选择不同的MOS管121导通电压。
同时，还需要说明的是，将MOS管121的栅极(G)电压提高到开启电压可以是瞬时完成或者通过一段时间来完成。例如，通过计时器在计时超过预设时间时立即为栅极(G)提供导通电压，或者，通过控制芯片和控制软件将栅极(G)的电压在一段时间内缓慢提高直到超过预设时间后达到导通电压。
进一步，还可以在开关电路12中设置一个与MOS管121并联的第一电阻123，用于保护MOS管121。
具体来说，当电源正极14和电源地15上电时，在电容负载电路11的充电过程中，第一电阻123将起到分流作用，从而避免上电时充电电流过大从而击穿MOS管121。
可选的，开关电路12可以与电容负载电路11串联在一个支路中并与延时控制电路13并联，也即，将开关电路12设置在电容负载电路11的支路中。这样，MOS管121的导通和截止不会对电源输出到无人飞行器电动机的输出产生影响。
可选的，开关电路12还可以将电容负载电路11和延时控制电路13并联形成的支路与开关电路12串联，也即，将开关电路12串联在干路中。这样，通过MOS管121的导通和截止可以控制电源控制电路1输出到无人飞行器电动机的时间。并且对于较高电压的场合，可以提高防电火花的效果，并消除上电时刻电压过冲尖峰，使过冲尖峰不会输出到电动机中。
本实施例的电源控制电路1，通过设置MOS管121的方式可以使开关电路12的结构更简单，而且也能够通过为栅极(G)提供导通电压的时间控制MOS管121由截止状态到导通状态的时间，控制起来更容易和方便。并且，为MOS管121并联第一电阻123可以保护MOS管121，提高整个电源控制电路1的稳定性。
实施例3
本发明实施例3提供一种无人飞行器的电源控制电路。图3为本实施例3提供的电源控制电路的示意图。
本实施例是在实施例1提供的方案的基础上，将该开关电路12设置为包括：继电器125和第二电阻127。其中，延时控制电路13的控制端与继电器125电连接，用于控制继电器125的开端的开闭状态以将开关电路由高阻抗输出状态切换至低阻抗输出状态。
具体的，延时控制电路13和电容负载电路11并联在电源正极14和电源地15之间。也即，延时控制电路13的输入端连接电源正极14，其输出端连接电源地15；电容负载电路11的输入端也连接电源正极14，其输 出端也连接电源地15。并且延时控制电路13的控制端与继电器125的输入端电连接，继电器125的输出端连接电源地15。继电器125的开关与第二电阻127并联，且其两端分别连接延时控制电路13的输出端和电容负载电路11的输出端。
具体的，在工作时，当电源正极14和电源地15之间上电时，继电器125的开关断开。此时，第二电阻127作为开关电路12的高阻抗输出，从而降低了上电时电容负载电路11充电的电流，消除了电容负载电路11充电时的瞬时峰值，进而避免电源插头出现电火花。在充电超过预设时间后，延时控制电路13的控制端将继电器125接通。当继电器125接通后，第二电阻127被继电器125短路，电容负载电路11的输出端通过继电器125与电源地15直接连接，也即，电容负载电路11通过开关电路12输出的低阻抗进行动态充电，从而缩短动态充电的时间，提高电容负载电路11输出大电流的效率。
本实施例的电源控制电路1，通过设置并联的继电器125和第二电阻127的方式实现开关电路12高阻抗输出和低阻抗输出的切换，方便，简单，易于实现上电时防电火花的自动控制。并且还可以控制电源控制电路1输出到无人飞行器电动机的时间。并且对于较高电压的场合，可以提高防电火花的效果，并消除上电时刻电压过冲尖峰，使过冲尖峰不会输出到电动机中。
实施例4
本发明实施例4提供一种无人飞行器的电源控制电路。图4为本实施例4提供的电源控制电路的示意图。
本实施例是在实施例1、实施例2或者实施例3提供的技术方案基础上，将延时控制电路13设置为包括：第一电容1311和上拉电阻1313。其中，第一电容1311和上拉电阻1313串联在电源正极14和电源地15之间并与电容负载电路11并联；且第一电容1311的正极与开关电路12电连接。
具体的，上拉电阻1313可以直接串联到电源正极14，也可以间接与电源正极14串联。例如，上拉电阻1313可以与由电源正极14分压而来的无人飞行器的系统电源串联。
在工作时，当电源正极14和电源地15上电时，在电容负载电路11充电的同时，第一电容1311也通过上拉电阻1313进行充电。随着第一电容1311的充电，其两端的电压也在逐渐升高，从而通过第一电容1311正极和负极之间的电压变化来控制开关电路12的工作状态。
例如，当第一电容1311的正极和负极分别与继电器125的输入端和输出端电连接时，随着上电时间的增加，第一电容1311的正极和负极间的电压也随着时间的增加而升高，也即，与第一电容1311两极电连接的继电器125的输入端和输出端之间的电压随着上电时间的增加而升高。当上电时间超过预设时间后，继电器125输入端和输出端之间的电压超过导通电压阈值时，继电器125随之被闭合，开关电路12的输出阻抗也就从高阻抗切换为低阻抗。而当第一电容1311的正极和负极之间进入下电状态时，随着负载电容电路中的电容放电，负载电容电路的输入端和输出端之间的电压逐渐降低。当负载电容电路的输入端和输出端之间的电压降低到低于预设电压后，第一电容1311开始放电，第一电容1311的正极和负极之间的电压也随之降低，继电器125输入端和输出端之间的电压值也随之降低。当继电器125输入端和输出端之间的电压值降低到导通阈值以下时，继电器125随之被断开，开关电路12的输出阻抗也就从低阻抗切换为高阻抗。
再例如，当第一电容1311的正极与MOS管121的栅极(G)电连接时，随着上电时间的增加，第一电容1311的正极和负极间的电压也随着时间的增加而升高，也即，与第一电容1311正极电连接的MOS管121的栅极(G)的电压也随着上电时间的增加而升高。当上电时间超过预设时间后，MOS管121的栅极(G)的电压超过导通电压后，MOS管121随即被导通，开关电路12的输出阻抗也就从高阻抗切换为低阻抗。而当第一电容1311的正极和负极之间进入下电状态时，随着负载电容电路中电容的放电，负载电容电路的输入端和输出端之间的电压逐渐降低。当负载电容电路的输入端和输出端之间的电压降低到低于预设电压后，第一电容1311开始放电，第一电容1311的正极电压也随之降低，MOS管121栅极(G)的电压也随之降低。当MOS管121栅极(G)的电压降低到导通电压以下时，MOS管121随之被截止，开关电路12的输出阻抗也就从低阻抗切换为高阻 抗。
从上述分析可以看出，开关电路12由高阻抗输出状态切换为低阻抗输出状态的预设时间为第一电容1311充电到继电器125或者MOS管121的导通电压的时间，也即第一电容1311充电到预设电压值的时间。并且，通过控制第一电容1311和上拉电阻1313的参数可以获得不同的第一电容1311充电时间，也即，获得不同的控制开关电路12由高阻抗切换到低阻抗的时间，也即，预设时间。
可选的，当开关电路12包括MOS管121时，可以在第一电容1311的正极和电容负载电路11的输出端之间连接有第三电容1321，用于减小MOS管121的导通电流。
具体的，当第三电容1321和MOS管121并联时，可以增加总的弥勒电容。在MOS管121开通的时候可以增加Vgs的弥勒平台时间，可以减缓Vds电压的下降速度，从而减小MOS管121的开通电流。其中，Vgs指栅极(G)和源极(S)之间的压差；Vds指漏极(D)和源极(S)之间的压差。
同时，当第一电容1311放电时，第三电容1321还可以延长第一电容1311放电时间，从而增加MOS管121的开通时间。
本实施例的电源控制电路1，通过串联在电源正极14和电源地15之间的第一电容1311和上拉电阻1313，可以非常方便的通过第一电容1311的充放电来控制开关电路12在高阻抗输出和低阻抗输出之间进行切换，实现了电池热插拔的自动化。而且，还可以通过调整第一电阻123和第一电容1311的参数来控制第一电容1311的充电时间，从而控制开关电路12由高阻抗输出切换为低阻抗输出的时间，进而提高上电时电容负载电路11在高阻抗下充电的时间以提高电源控制电路1防电火花的效果。
实施例5
本发明实施例5提供一种无人飞行器的电源控制电路。图5为本实施例5提供的电源控制电路的示意图。
本实施例是在实施例4提供的技术方案基础上，将上拉电阻1313与一个二极管1331并联，用于加速第一电容1311放电。其中，该二极管1331的正极与第一电容1311的正极电连接，该二极管1331的负极与上拉 电阻1313的输入端电连接。
具体的，本实施例的电源控制电路1在电源正极14和电源地15处于下电状态时，当负载电容电路的输入端和输出端的电压降低到预设电压(比如，6-7v)后，第一电容1311可以通过二极管1331放电，从而加速第一电容1311的放电，使其尽快回到待充电的初始状态。
需要说明的是，本实施例中也可以在开关电路12包括MOS管121时，在第一电容1311的正极和电容负载电路11的输出端之间连接有第三电容1321，用于减小MOS管121的导通电流。第三电容1321的作用原理及效果请参见实施例4。
图5中上拉电阻1313连接的电源是由电池的电源分压而来，也即，为电源正极14分压而来，其实质就是将上拉电阻1313与电源正极14间接连接。
本实施例的电源控制电路1，通过对上拉电阻1313并联一个二极管1331的方式来加快第一电容1311的放电，可以使电路快速回复初始状态，以备下一次电池的接入。
实施例6
本发明实施例6提供一种无人飞行器的电源控制电路。图6a为本实施例6提供的一种电源控制电路的示意图。图6b为本实施例6提供的一种电源控制电路的示意图。
本实施例是在实施例4提供的技术方案基础上，将第一电容1311与一第三电阻1333并联，且该第三电阻1333与上拉电阻1313串联，该第三电阻1333用于与上拉电阻1313对电源进行分压，用于保护开关电路12。
具体的，本实施例的电源控制电路1，当电源正极14和电源地15处于上电状态时，电源经上拉电阻1313和第三电阻1333分压后给第一电容1311充电，从而可以保护与第一电容1311正极连接的开关电路12。例如，当与第一电容1311正极连接的为MOS管121时，由于MOS管121的Vgs可能在20V以内，而电源正极14与电源地15之间的压差可能会比20V高，所以可以通过接入第三电阻1333，以调整MOS管121的栅极(G)的电压，使得MOS管121的Vgs充满电压接近12V，从而保护MOS管121。当 然，基于上述原理可知，第三电阻1333也可以保护开关电路12中的继电器125或者其他开关元件
当电源正极14和电源地15处于下电状态时，当负载电容电路的输入端和输出端的电压降低到预设电压(比如，6-7v)后，第一电容1311可以通过第三电阻1333放电，从而加速第一电容1311的放电，使其尽快回到待充电的初始状态。
需要说明的是，本实施例中也可以在开关电路12包括MOS管121时，在第一电容1311的正极和电容负载电路11的输出端之间连接有第三电容1321，用于减小MOS管121的导通电流。第三电容1321的作用原理及效果请参见实施例4。
本实施例的电源控制电路1，通过为上拉电阻1313串联一个与第一电容1311并联的第三电阻1333，可以通过调整上拉电阻1313和第三电阻1333的分压比以保护开关电路12。同时，第三电阻1333在第一电容1311放电时还可以加快其放电，以使电路快速回复初始状态，以备下一次电池的接入。
实施例7
本发明实施例7提供一种无人飞行器的电源控制电路1。图7a为本实施例7提供的一种电源控制电路的示意图。图7b为本实施例7提供的一种电源控制电路的示意图。
本实施例是在实施例4提供的技术方案基础上，将第一电容1311与一稳压二极管1335并联，且该稳压二极管1335与上拉电阻1313串联，用于与上拉电阻1313组成并联稳压电路，从而保护开关电路12。
本实施例的电源控制电路1在工作时，稳压二极管1335会始终将第一电容1311正极的电压稳定在二极管1331的稳压值，从而保护与第一电容1311正极连接的开关电路12。例如，当与第一电容1311正极连接的为MOS管121时，图7中的稳压二极管1335可以将MOS管121的Vgs控制在12V以内，从而保护稳压二极管1335不会被烧坏。当然，基于上述原理可知，稳压二极管1335也可以保护开关电路12中的继电器125或者其他晶体管元件。
需要说明的是，本实施例中也可以在开关电路12包括MOS管121时， 在第一电容1311的正极和电容负载电路11的输出端之间连接有第三电容1321，用于减小MOS管121的导通电流。第三电容1321的作用原理及效果请参见实施例4。
本实施例的电源控制电路1，通过为上拉电阻1313串联一个与第一电容1311并联的稳压二极管1335，可以保护开关电路12。
实施例8
本发明实施例8提供一种无人飞行器的电源控制电路。图8为本实施例8提供的电源控制电路的示意图。
本实施例是在实施例4提供的技术方案基础上，设置一个用于控制第一电容1311在电容负载电路11的电压低于预设电压后放电的放电控制电路。
具体的，该放电控制电路包括第一三极管1351、第四电阻1353和第五电阻1355。其中，第一三极管1351的发射极与第一电容1311的正极电连接，第一三极管1351的集电极与电源地15连接，第一三极管1351的基极通过第四电阻1353与电源正极14电连接，且第一三极管1351的基极还通过第五电阻1355与电源地15电连接。
在工作时，当电源正极14和电源地15之间为上电状态时，电容负载电路11通过开关电路12输出的高阻抗进行充电时，第一电容1311也通过上拉电阻1313开始充电。此时，由于开关电路12输出的高阻抗作用，电容负载电路11的充电电流很小，且消除了其充电瞬间的电流峰值，避免了电源接头出现电火花。
当上电时间超过第一电容1311充电到预设电压的时间时，开关电路12从高阻抗输出切换为低阻抗输出，以实现对电容负载电路11对电动机的大电流输出，并在开关电路12提供的低阻抗下实现动态充电，从而减少动态充电的时间。具体的，在图8中，上电时间为超过第一电容1311充电到MOS管121导通电压的时间，而开关电路12的高阻抗由MOS管121截止时的阻抗和第一电阻123来提供，低阻抗则主要由MOS管121导通后的MOS管121自身的阻抗来提供。
同时，在电池接入电源控制电路1的所有时间内，第一三极管1351的基极电压和射电极之间的压降小于第一三极管1351的导通电压，因 此，在电池接入电源控制电路1的整个时间内均处于截止状态。
当电源正极14和电源地15之间为下电状态时，当电容负载电路11输入端和输出端的电压降低到预设电压后，第一三极管1351的基极电压和射电极之间的压降升高到超过第一三极管1351的导通电压，第一三极管1351随即导通。第一电容1311通过第一三极管1351迅速放电。MOS管121的栅极电压也随之迅速降低到低于导通电压，MOS管121截止，开关电路12回到输出高阻抗的状态。
需要说明的是，本实施例中也可以在开关电路12包括MOS管121时，在第一电容1311的正极和电容负载电路11的输出端之间连接有第三电容1321，用于减小MOS管121的导通电流。第三电容1321的作用原理及效果请参见实施例4。
本实施例的电源控制电路1，通过设置包括第一三极管1351的放电控制电路，可以延迟开关电路12由低阻抗输出状态切换至高阻抗输出状态的时间，提高电容负载电路11的放电时间。
实施例9
本发明实施例9提供一种无人飞行器的电源控制电路。图9为本实施例9提供的电源控制电路的示意图。
本实施例是在实施例4提供的技术方案基础上，设置一个用于控制第一电容1311在电容负载电路11的电压低于预设电压后放电的放电控制电路。
具体的，该放电控制电路包括：第二三极管1371、第三三极管1373、第六电阻1375、第七电阻1376和第八电阻1377。
该第二三极管1371的发射极与电源地15电连接，第二三极管1371的基极通过第六电阻1375与电源正极14电连接，第二三极管1371的集电极与第一电容1311的正极电连接。
第三三极管1373的集电极与第二三极管1371的基极电连接，第三三极管1373的发射极与电源地15电连接，第三三极管1373的基极与电源正极14电连接。
第七电阻1376和第八电阻1377串联在第二三极管1371的基极和电源正极14之间。
在工作时，当电源正极14和电源地15之间为上电状态时，电容负载电路11通过开关电路12输出的高阻抗进行充电时，第一电容1311也通过上拉电阻1313开始充电。此时，由于开关电路12输出的高阻抗作用，电容负载电路11的充电电流很小，且消除了其充电瞬间的电流峰值，避免了电源接头出现电火花。
当上电时间超过第一电容1311充电到预设电压的时间时，开关电路12从高阻抗输出切换为低阻抗输出，以实现对电容负载电路11对电动机的大电流输出，并在开关电路12提供的低阻抗下实现动态充电，从而减少动态充电的时间。具体的，在图9中，上电时间为超过第一电容1311充电到MOS管121导通电压的时间，而开关电路12的高阻抗由MOS管121截止时的阻抗和第一电阻123来提供，低阻抗则主要由MOS管121导通后的MOS管121自身的阻抗来提供。
同时，在电池接入电源控制电路1的所有时间内，第三三极管1373的基极电压大于射电极的电压，第三二极管1331处于导通状态。第二三极管1371由于第三二极管1331处于导通状态，因此，其基极电压小于基极和射电极之间的压降，从而使得第二三极管1371处于截止状态。
当电源正极14和电源地15之间为下电状态时，当电容负载电路11输入端和输出端的电压降低到预设电压后，第三三极管1373的基极电压降低到小于其基极和射电极之间的压降，从而第三三极管1373截止。此时，由于第三三极管1373截止，第二三极管1371的基极电压高于射电极电压，第二三极管1371导通，第一电容1311迅速放电。MOS管121的栅极电压也随之迅速降低到低于导通电压，MOS管121截止，开关电路12回到输出高阻抗的状态。
进一步，设置一个第二电容1379，用于提高第三二极管1331对于电容负载电路11输入端和输出端压降的检测能力。该第二电容1379与第八电阻1377并联，且与第七电阻1376串联。
另外，在本实施例中可以通过控制第六电阻1375、第七电阻1376和第八电阻1377来控制第一电容1311放电时电容负载电路11的输入端和输出端之间的电压。当然，当设置有第二电容1379时，可以通过控制第六电阻1375、第七电阻1376、第八电阻1377和第二电容1379来控制第 一电容1311放电时电容负载电路11的输入端和输出端之间的电压，以提高控制精度。
需要说明的是，本实施例中也可以在开关电路12包括MOS管121时，在第一电容1311的正极和电容负载电路11的输出端之间连接有第三电容1321，用于减小MOS管121的导通电流。第三电容1321的作用原理及效果请参见实施例4。
另外，图9中上拉电阻1313连接的电源是由电池的电源分压而来，也即，为电源正极14分压而来，其实质就是将上拉电阻1313与电源正极14间接连接。
本实施例的电源控制电路1，通过第二三极管1371和第三三极管1373组成的双三极管作为放电控制电路，可以提高对第一电容1311放电的控制效果。
实施例10
本发明实施例10提供一种电子调速器。图10为本实施例10提供的电子调速器结构示意图。
本实施例的电子调速器包括：电机驱动电路2和电源控制电路1。其中，电源控制电路1与电机驱动电路2电连接，用于给电机驱动电路2供电。
请参照附图1，该电源控制电路1，用于防止无人飞行器电源热插拔时产生电火花。所述电源控制电路1包括：电容负载电路11、开关电路12和延时控制电路13。其中，电容负载电路11和开关电路12串联在电源正极14和电源地15之间，也即电容负载电路11的输入端连接电源正极14，其输出端连接开关电路12的输入端，开关电路12的输出端则连接电源地15。延时控制电路13的输入端与电源正极14电连接，其输出端与电源地15连接，其控制端与开关电路12电连接，用于控制开关电路12的工作状态。其中，当电源正极14和电源地15的通电状态为上电状态时，延时控制电路13控制开关电路12在上电时间超过预设时间后将所述开关电路12由高阻抗输出状态切换至低阻抗输出状态。
具体来说，电容负载电路11，其主要用于为无人飞行器的电动机提供大电流输出。该电容负载电路11可以是由一个大电容构成，也可以是由多个并联电容构成，还可以是由电容和其他电子元件串并联组成。在本实施例中对所述电容负载电路11的具体形式不作限制，本领域技术人员可以根据实际需要进行选择。
开关电路12可以是由单一晶体开关管构成，比如，双向开关三极管。该开关电路12也可以是由并联的断路器和电阻，或者并联的断路器和电感组成。当然，该开关电路12还可以是CMOS(Complementary Metal Oxide Semiconductor)，互补金属氧化物半导体，电压控制的一种放大器件，是组成CMOS数字集成电路的基本单元)开关或者集成芯片。本领域技术人员应该明确只要开关电路12能够受延时控制电路13的控制从而改变其输出的阻抗即可，也即，可以受延时控制电路13控制由高阻抗输出切换至低阻抗输出即可。因此，为了行文更简洁，在本实施例中对开关电路12的具体形式不做具体限制，本领域技术人员可以根据需要具体设置。另外，需要说明的是，高阻抗是指能够将电容负载电路11的充电电流大幅度减小以满足防止产生电火花功能的阻抗，而低阻抗则是指接入电容负载电路的阻抗很小基本不影响电容负载电路11的在向电动机动态供电时的充电电流。举例来说，高阻抗可以是电阻或者是开关元件断路或截止时自身所具有的阻抗，低阻抗则是指导线的阻抗或者是开关元件闭合或导通时具有的阻抗。
延时控制电路13在本实施例中也不作具体的限制，其可以是串联在电源正极14和电源地15之间并且其控制端与开关电路12电连接的计时器，该计时器在电源上电时启动并在计时到预定时间，也即上电超过预设时间之后控制开关电路12由高阻抗输出状态切换至低阻抗输出状态。当然，延时控制电路13也可以通过计时控制芯片或者控制软件来实现。
在本实施例中，该电源控制电路1的工作原理是：当无人飞行器的电池的电源插头插入电子调速器的电源插孔时，也即电池的正极和负极接入电源控制电路1的输入接口时，电源控制电路1的电源正极14和电源地15之间输入压差，电容负载电路11中的电容通过开关电路12输出的高阻抗进行充电。由于，有开关电路12的高阻抗输出，所以，电容负载 电路11中的电容充电电流很小，在电池的电源插头处不会出现电火花，防止了电打火现象。与此同时，延时控制电路13分别与电源正极14和电源地15连接的输入端和输出端检测出该压差，获取到电源正极14和电源地15之间处于上电状态，则在上电超过预设时间之后通过控制端控制开关电路12由高阻抗输出状态切换为低阻抗输出状态从而为电容负载电路11向电动机输出大电流做准备。这样，当电子调速器调速过程中需要大电流时，电容负载电路11可以为电机驱动电路2提供大电流的输出，而在输出后电容负载电路11可以通过开关电路12输出的低阻抗进行快速充电，以降低无人飞行器正常工作过程时电容负载电路11的动态充电时间，从而提高电容负载电路11的动态充放电效率。
本实施例的电子调速器，通过电源控制电路1中的延时控制电路13在电源正极14和电源地15上电超过预设时间后控制开关电路12由高阻抗输出状态切换至低阻抗输出状态，从而无需再手动将主电源和大电容连接，简化了无人飞行器电池热插拔时防打火的操作，实现了防电火花的自动控制。
本实施例的电子调速器大大减小了插上电源插头时上电瞬间的电流峰值，减小并消除了插头接触瞬间产生的电火花，有效延长了电源接头的寿命。
同时，本实施例的电子调速器的电源控制电路1非常简单，容易集成在电子调速器等硬件上；非常适宜于智能电池在热插拔时候减小插头的电火花。而且，还可以大大减小电池上电时候的电流应力，起到保护电池的作用，非常适合在大功率无人机上应用。
实施例11
本发明实施例11提供一种电子调速器。
请参阅图2a和2b，本实施例是在实施例10提供的方案的基础上，将该开关电路12设置为包括MOS管121(金属(metal)—氧化物(oxid)—半导体(semiconductor)场效应晶体管)。
具体而言，是将MOS管121的栅极(G)与延时控制电路13的控制端电连接，将其漏极(D)与电容负载电路11的输出端电连接，将其源极(S)与电源地15电连接，用于根据栅极的电压变化实现MOS管121的导通和 截止。
由于MOS管121在截止时具有非常大的阻抗，而在导通时阻抗很小，通过延时控制电路13控制栅极(G)的电压就可以非常方便的实现MOS管121的导通和截止之间的切换，从而为开关电路12输出高阻抗或者低阻抗。并且，这样设置的开关电路12结构也很简单，性能更加稳定。
具体的，在工作时，当电源正极14和电源地15之间上电时，MOS管121处于截止状态，因此，开关电路12输出一个高阻抗，使得电容负载电路11的充电电流降低，避免产生瞬时涌流，从而防止接头处产生电火花。当上电超过预设时间后，延时控制电路13则通过控制端将MOS管121栅极(G)的电压提高到开启电压，比如，提高到2.5V，从而导通该MOS管121。由于MOS管121导通时的阻抗很小，因此在导通该MOS管121后可以使开关管电路输出一低阻抗。当然，上述MOS管121的导通电压仅是本实施例的示例性导通电压，在实际设置中可以根据电路需要选择不同的MOS管121导通电压。
同时，还需要说明的是，将MOS管121的栅极(G)电压提高到开启电压可以是瞬时完成或者通过一段时间来完成。例如，通过计时器在计时超过预设时间时立即为栅极(G)提供导通电压，或者，通过控制芯片和控制软件将栅极(G)的电压在一段时间内缓慢提高直到超过预设时间后达到导通电压。
进一步，还可以在开关电路12中设置一个与MOS管121并联的第一电阻123，用于保护MOS管121。
具体的，当电源正极14和电源地15上电时，在电容负载电路11的充电过程中，第一电阻123将起到分流作用，从而避免上电时充电电流过大从而击穿MOS管121。
可选的，开关电路12可以与电容负载电路11串联在一个支路中并与延时控制电路13并联，也即，将开关电路12设置在电容负载电路11的支路中。这样，MOS管121的导通和截止不会对电源输出到无人飞行器电动机的输出产生影响。
可选的，开关电路12还可以将电容负载电路11和延时控制电路13并联形成的支路与开关电路12串联，也即，将开关电路12串联在干路 中。这样，通过MOS管121的导通和截止可以控制电源控制电路1输出到无人飞行器电动机的时间。并且对于较高电压的场合，可以提高防电火花的效果，并消除上电时刻电压过冲尖峰，使过冲尖峰不会输出到电动机中。
本实施例的电子调速器中的电源控制电路1，通过设置MOS管121的方式可以使开关电路12的结构更简单，而且也能够通过为栅极(G)提供导通电压的时间控制MOS管121由截止状态到导通状态的时间，控制起来更容易和方便。并且，为MOS管121并联第一电阻123可以保护MOS管121，提高整个电源控制电路1的稳定性。
实施例12
本发明实施例12提供一种电子调速器。
请参阅图3a和3b，本实施例是在实施例11提供的方案的基础上，将该开关电路12设置为包括：继电器125和第二电阻127。其中，延时控制电路13的控制端与继电器125电连接，用于控制继电器125的开端的开闭状态以将开关电路由高阻抗输出状态切换至低阻抗输出状态。
具体的，延时控制电路13和电容负载电路11并联在电源正极14和电源地15之间。也即，延时控制电路13的输入端连接电源正极14，其输出端连接电源地15；电容负载电路11的输入端也连接电源正极14，其输出端也连接电源地15。并且延时控制电路13的控制端与继电器125的输入端电连接，继电器125的输出端连接电源地15。继电器125的开关与第二电阻127并联，且其两端分别连接延时控制电路13的输出端和电容负载电路11的输出端。
具体的，在工作时，当电源正极14和电源地15之间上电时，继电器125的开关断开。此时，第二电阻127作为开关电路12的高阻抗输出，从而降低了上电时电容负载电路11充电的电流，消除了电容负载电路11充电时的瞬时峰值，进而避免电源插头出现电火花。在充电超过预设时间后，延时控制电路13的控制端将继电器125接通。当继电器125接通后，第二电阻127被继电器125短路，电容负载电路11的输出端通过继电器125与电源地15直接连接，也即，电容负载电路11通过开关电路12输出的低阻抗进行动态充电，从而缩短动态充电的时间，提高电容负载电路 11输出大电流的效率。
本实施例的电子调速器中的电源控制电路1，通过设置并联的继电器125和第二电阻127的方式实现开关电路12高阻抗输出和低阻抗输出的切换，方便，简单，易于实现上电时防电火花的自动控制。并且还可以控制电源控制电路1输出到无人飞行器电动机的时间。并且对于较高电压的场合，可以提高防电火花的效果，并消除上电时刻电压过冲尖峰，使过冲尖峰不会输出到电动机中。
实施例13
本发明实施例13提供一种电子调速器。
请参阅图4，本实施例是在实施例10、实施例11或者实施例12提供的技术方案基础上，将延时控制电路13设置为包括：第一电容1311和上拉电阻1313。其中，第一电容1311和上拉电阻1313串联在电源正极14和电源地15之间并与电容负载电路11并联；且第一电容1311的正极与开关电路12电连接。
具体的，上拉电阻1313可以直接串联到电源正极14，也可以间接与电源正极14串联。例如，上拉电阻1313可以与由电源正极14分压而来的无人飞行器的系统电源串联。
在工作时，当电源正极14和电源地15上电时，在电容负载电路11充电的同时，第一电容1311也通过上拉电阻1313进行充电。随着第一电容1311的充电，其两端的电压也在逐渐升高，从而通过第一电容1311正极和负极之间的电压变化来控制开关电路12的工作状态。
例如，当第一电容1311的正极和负极分别与继电器125的输入端和输出端电连接时，随着上电时间的增加，第一电容1311的正极和负极间的电压也随着时间的增加而升高，也即，与第一电容1311两极电连接的继电器125的输入端和输出端之间的电压随着上电时间的增加而升高。当上电时间超过预设时间后，继电器125输入端和输出端之间的电压超过导通电压阈值时，继电器125随之被闭合，开关电路12的输出阻抗也就从高阻抗切换为低阻抗。而当第一电容1311的正极和负极之间进入下电状态时，随着负载电容电路中的电容放电，负载电容电路的输入端和输出端之间的电压逐渐降低。当负载电容电路的输入端和输出端之间的电压 降低到低于预设电压后，第一电容1311开始放电，第一电容1311的正极和负极之间的电压也随之降低，继电器125输入端和输出端之间的电压值也随之降低。当继电器125输入端和输出端之间的电压值降低到导通阈值以下时，继电器125随之被断开，开关电路12的输出阻抗也就从低阻抗切换为高阻抗。
再例如，当第一电容1311的正极与MOS管121的栅极(G)电连接时，随着上电时间的增加，第一电容1311的正极和负极间的电压也随着时间的增加而升高，也即，与第一电容1311正极电连接的MOS管121的栅极(G)的电压也随着上电时间的增加而升高。当上电时间超过预设时间后，MOS管121的栅极(G)的电压超过导通电压后，MOS管121随即被导通，开关电路12的输出阻抗也就从高阻抗切换为低阻抗。而当第一电容1311的正极和负极之间进入下电状态时，随着负载电容电路中电容的放电，负载电容电路的输入端和输出端之间的电压逐渐降低。当负载电容电路的输入端和输出端之间的电压降低到低于预设电压后，第一电容1311开始放电，第一电容1311的正极电压也随之降低，MOS管121栅极(G)的电压也随之降低。当MOS管121栅极(G)的电压降低到导通电压以下时，MOS管121随之被截止，开关电路12的输出阻抗也就从低阻抗切换为高阻抗。
从上述分析可以看出，开关电路12由高阻抗输出状态切换为低阻抗输出状态的预设时间为第一电容1311充电到继电器125或者MOS管121的导通电压的时间，也即第一电容1311充电到预设电压值的时间。并且，通过控制第一电容1311和上拉电阻1313的参数可以获得不同的第一电容1311充电时间，也即，获得不同的控制开关电路12由高阻抗切换到低阻抗的时间，也即，预设时间。
可选的，当开关电路12包括MOS管121时，可以在第一电容1311的正极和电容负载电路11的输出端之间连接有第三电容1321，用于减小MOS管121的导通电流。
具体的，当第三电容1321和MOS管121并联时，可以增加总的弥勒电容。在MOS管121开通的时候可以增加Vgs的弥勒平台时间，可以减缓Vds电压的下降速度，从而减小MOS管121的开通电流。其中，Vgs指栅 极(G)和源极(S)之间的压差；Vds指漏极(D)和源极(S)之间的压差。
同时，当第一电容1311放电时，第三电容1321还可以延长第一电容1311放电时间，从而增加MOS管121的开通时间。
本实施例的电子调速器中的电源控制电路1，通过串联在电源正极14和电源地15之间的第一电容1311和上拉电阻1313，可以非常方便的通过第一电容1311的充放电来控制开关电路12在高阻抗输出和低阻抗输出之间进行切换，实现了电池热插拔的自动化。而且，还可以通过调整第一电阻123和第一电容1311的参数来控制第一电容1311的充电时间，从而控制开关电路12由高阻抗输出切换为低阻抗输出的时间，进而提高上电时电容负载电路11在高阻抗下充电的时间以提高电源控制电路1防电火花的效果。
实施例14
本发明实施例14提供一种电子调速器。
请参阅图5，本实施例是在实施例13提供的技术方案基础上，将上拉电阻1313与一个二极管1331并联，用于加速第一电容1311放电。其中，该二极管1331的正极与第一电容1311的正极电连接，该二极管1331的负极与上拉电阻1313的输入端电连接。
具体的，电源控制电路1在电源正极14和电源地15处于下电状态时，当负载电容电路的输入端和输出端的电压降低到预设电压(比如，6-7v)后，第一电容1311可以通过二极管1331放电，从而加速第一电容1311的放电，使其尽快回到待充电的初始状态。
需要说明的是，本实施例中也可以在开关电路12包括MOS管121时，在第一电容1311的正极和电容负载电路11的输出端之间连接有第三电容1321，用于减小MOS管121的导通电流。第三电容1321的作用原理及效果请参见实施例4。
本实施例的电子调速器中的电源控制电路1，通过对上拉电阻1313并联一个二极管1331的方式来加快第一电容1311的放电，可以使电路快速回复初始状态，以备下一次电池的接入。
实施例15
本发明实施例15提供一种电子调速器。
请参阅图6a和图6b，本实施例是在实施例13提供的技术方案基础上，将第一电容1311与一第三电阻1333并联，且该第三电阻1333与上拉电阻1313串联，该第三电阻1333用于与上拉电阻1313对电源进行分压，用于保护开关电路12。
具体的，本实施例电子调速器中的电源控制电路1，当电源正极14和电源地15处于上电状态时，电源经上拉电阻1313和第三电阻1333分压后给第一电容1311充电，从而可以保护与第一电容1311正极连接的开关电路12。例如，当与第一电容1311正极连接的为MOS管121时，由于MOS管121的Vgs可能在20V以内，而电源正极14与电源地15之间的压差可能会比20V高，所以可以通过接入第三电阻1333，以调整MOS管121的栅极(G)的电压，使得MOS管121的Vgs充满电压接近12V，从而保护MOS管121。当然，基于上述原理可知，第三电阻1333也可以保护开关电路12中的继电器125或者其他开关元件
当电源正极14和电源地15处于下电状态时，当负载电容电路的输入端和输出端的电压降低到预设电压(比如，6-7v)后，第一电容1311可以通过第三电阻1333放电，从而加速第一电容1311的放电，使其尽快回到待充电的初始状态。
需要说明的是，本实施例中也可以在开关电路12包括MOS管121时，在第一电容1311的正极和电容负载电路11的输出端之间连接有第三电容1321，用于减小MOS管121的导通电流。第三电容1321的作用原理及效果请参见实施例4。
本实施例的电子调速器中的电源控制电路1，通过为上拉电阻1313串联一个与第一电容1311并联的第三电阻1333，可以通过调整上拉电阻1313和第三电阻1333的分压比以保护开关电路12。同时，第三电阻1333在第一电容1311放电时还可以加快其放电，以使电路快速回复初始状态，以备下一次电池的接入。
实施例16
本发明实施例16提供一种电子调速器。
请参阅图7a和图7b，本实施例是在实施例13提供的技术方案基础 上，将第一电容1311与一稳压二极管1335并联，且该稳压二极管1335与上拉电阻1313串联，用于与上拉电阻1313组成并联稳压电路，从而保护开关电路12。
本实施例的电子调速器中的电源控制电路1在工作时，稳压二极管1335会始终将第一电容1311正极的电压稳定在二极管1331的稳压值，从而保护与第一电容1311正极连接的开关电路12。例如，当与第一电容1311正极连接的为MOS管121时，图7中的稳压二极管1335可以将MOS管121的Vgs控制在12V以内，从而保护稳压二极管1335不会被烧坏。当然，基于上述原理可知，稳压二极管1335也可以保护开关电路12中的继电器125或者其他晶体管元件。
需要说明的是，本实施例中也可以在开关电路12包括MOS管121时，在第一电容1311的正极和电容负载电路11的输出端之间连接有第三电容1321，用于减小MOS管121的导通电流。第三电容1321的作用原理及效果请参见实施例4。
本实施例的电子调速器中的电源控制电路1，通过为上拉电阻1313串联一个与第一电容1311并联的稳压二极管1335，可以保护开关电路12。
实施例17
本发明实施例17提供一种电子调速器。
请参阅图8，本实施例是在实施例13提供的技术方案基础上，设置一个用于控制第一电容1311在电容负载电路11的电压低于预设电压后放电的放电控制电路。
具体的，该放电控制电路包括第一三极管1351、第四电阻1353和第五电阻1355。其中，第一三极管1351的发射极与第一电容1311的正极电连接，第一三极管1351的集电极与电源地15连接，第一三极管1351的基极通过第四电阻1353与电源正极14电连接，且第一三极管1351的基极还通过第五电阻1355与电源地15电连接。
在工作时，当电源正极14和电源地15之间为上电状态时，电容负载电路11通过开关电路12输出的高阻抗进行充电时，第一电容1311也通过上拉电阻1313开始充电。此时，由于开关电路12输出的高阻抗作用， 电容负载电路11的充电电流很小，且消除了其充电瞬间的电流峰值，避免了电源接头出现电火花。
当上电时间超过第一电容1311充电到预设电压的时间时，开关电路12从高阻抗输出切换为低阻抗输出，以实现对电容负载电路11对电动机的大电流输出，并在开关电路12提供的低阻抗下实现动态充电，从而减少动态充电的时间。具体的，在图8中，上电时间为超过第一电容1311充电到MOS管121导通电压的时间，而开关电路12的高阻抗由MOS管121截止时的阻抗和第一电阻123来提供，低阻抗则主要由MOS管121导通后的MOS管121自身的阻抗来提供。
同时，在电池接入电源控制电路1的所有时间内，第一三极管1351的基极电压和射电极之间的压降小于第一三极管1351的导通电压，因此，在电池接入电源控制电路1的整个时间内均处于截止状态。
当电源正极14和电源地15之间为下电状态时，当电容负载电路11输入端和输出端的电压降低到预设电压后，第一三极管1351的基极电压和射电极之间的压降升高到超过第一三极管1351的导通电压，第一三极管1351随即导通。第一电容1311通过第一三极管1351迅速放电。MOS管121的栅极电压也随之迅速降低到低于导通电压，MOS管121截止，开关电路12回到输出高阻抗的状态。
需要说明的是，本实施例中也可以在开关电路12包括MOS管121时，在第一电容1311的正极和电容负载电路11的输出端之间连接有第三电容1321，用于减小MOS管121的导通电流。第三电容1321的作用原理及效果请参见实施例4。
本实施例的电子调速器中的电源控制电路1，通过设置包括三极管的放电控制电路，可以延迟开关电路12由低阻抗输出状态切换至高阻抗输出状态的时间，提高电容负载电路11的放电时间。
实施例18
本发明实施例18提供一种电子调速器。
请参阅图9，本实施例是在实施例13提供的技术方案基础上，设置一个用于控制第一电容1311在电容负载电路11的电压低于预设电压后放电的放电控制电路。
具体的，该放电控制电路包括：第二三极管1371、第三三极管1373、第六电阻1375、第七电阻1376和第八电阻1377。
该第二三极管1371的发射极与电源地15电连接，第二三极管1371的基极通过第六电阻1375与电源正极14电连接，第二三极管1371的集电极与第一电容1311的正极电连接。
第三三极管1373的集电极与第二三极管1371的基极电连接，第三三极管1373的发射极与电源地15电连接，第三三极管1373的基极与电源正极14电连接。
第七电阻1376和第八电阻1377串联在第二三极管1371的基极和电源正极14之间。
在工作时，当电源正极14和电源地15之间为上电状态时，电容负载电路11通过开关电路12输出的高阻抗进行充电时，第一电容1311也通过上拉电阻1313开始充电。此时，由于开关电路12输出的高阻抗作用，电容负载电路11的充电电流很小，且消除了其充电瞬间的电流峰值，避免了电源接头出现电火花。
当上电时间超过第一电容1311充电到预设电压的时间时，开关电路12从高阻抗输出切换为低阻抗输出，以实现对电容负载电路11对电动机的大电流输出，并在开关电路12提供的低阻抗下实现动态充电，从而减少动态充电的时间。具体的，在图8中，上电时间为超过第一电容1311充电到MOS管121导通电压的时间，而开关电路12的高阻抗由MOS管121截止时的阻抗和第一电阻123来提供，低阻抗则主要由MOS管121导通后的MOS管121自身的阻抗来提供。
同时，在电池接入电源控制电路1的所有时间内，第三三极管1373的基极电压大于射电极的电压，第三二极管1331处于导通状态。第二三极管1371由于第三二极管1331处于导通状态，因此，其基极电压小于基极和射电极之间的压降，从而使得第二三极管1371处于截止状态。
当电源正极14和电源地15之间为下电状态时，当电容负载电路11输入端和输出端的电压降低到预设电压后，第三三极管1373的基极电压降低到小于其基极和射电极之间的压降，从而第三三极管1373截止。此时，由于第三三极管1373截止，第二三极管1371的基极电压高于射电极 电压，第二三极管1371导通，第一电容1311迅速放电。MOS管121的栅极电压也随之迅速降低到低于导通电压，MOS管121截止，开关电路12回到输出高阻抗的状态。
进一步，设置一个第二电容1379，用于提高第三二极管1331对于电容负载电路11输入端和输出端压降的检测能力。该第二电容1379与第七电阻1376并联，且与第六电阻1375串联。
另外，在本实施例中可以通过控制第六电阻1375、第七电阻1376和第八电阻1377来控制第一电容1311放电时电容负载电路11的输入端和输出端之间的电压。当然，当设置有第二电容1379时，可以通过控制第六电阻1375、第七电阻1376、第八电阻1377和第二电容1379来控制第一电容1311放电时电容负载电路11的输入端和输出端之间的电压，以提高控制精度。
需要说明的是，本实施例中也可以在开关电路12包括MOS管121时，在第一电容1311的正极和电容负载电路11的输出端之间连接有第三电容1321，用于减小MOS管121的导通电流。第三电容1321的作用原理及效果请参见实施例4。
本实施例的电子调速器中的电源控制电路1，通过第二三极管1371和第三三极管1373组成的双三极管作为放电控制电路，可以提高对第一电容1311放电的控制效果。
实施例19
本发明实施例19提供一种无人飞行器。
本实施例的无人飞行器包括：电动机以及电子调速器。其中，电子调速器与电动机电连接，电动机用于提供飞行动力；电子调速器用于控制电动机的工作状态。
所述电子调速器包括：电机驱动电路2和电源控制电路1。其中，电源控制电路1与电机驱动电路2电连接，用于给电机驱动电路2供电。
请参照图1，该电源控制电路1，用于防止无人飞行器电源热插拔时产生电火花。所述电源控制电路1包括：电容负载电路11、开关电路12 和延时控制电路13。其中，电容负载电路11和开关电路12串联在电源正极14和电源地15之间，也即电容负载电路11的输入端连接电源正极14，其输出端连接开关电路12的输入端，开关电路12的输出端则连接电源地15。延时控制电路13的输入端与电源正极14电连接，其输出端与电源地15连接，其控制端与开关电路12电连接，用于控制开关电路12的工作状态。其中，当电源正极14和电源地15的通电状态为上电状态时，延时控制电路13控制开关电路12在上电时间超过预设时间后将所述开关电路12由高阻抗输出状态切换至低阻抗输出状态。
具体来说，电容负载电路11，其主要用于为无人飞行器的电动机提供大电流输出。该电容负载电路11可以是由一个大电容构成，也可以是由多个并联电容构成，还可以是由电容和其他电子元件串并联组成。在本实施例中对所述电容负载电路11的具体形式不作限制，本领域技术人员可以根据实际需要进行选择。
开关电路12可以是由单一晶体开关管构成，比如，双向开关三极管。该开关电路12也可以是由并联的断路器和电阻，或者并联的断路器和电感组成。当然，该开关电路12还可以是CMOS(Complementary Metal Oxide Semiconductor)，互补金属氧化物半导体，电压控制的一种放大器件，是组成CMOS数字集成电路的基本单元)开关或者集成芯片。本领域技术人员应该明确只要开关电路12能够受延时控制电路13的控制从而改变其输出的阻抗即可，也即，可以受延时控制电路13控制由高阻抗输出切换至低阻抗输出即可。因此，为了行文更简洁，在本实施例中对开关电路12的具体形式不做具体限制，本领域技术人员可以根据需要具体设置。另外，需要说明的是，高阻抗是指能够将电容负载电路11的充电电流大幅度减小以满足防止产生电火花功能的阻抗，而低阻抗则是指接入电容负载电路的阻抗很小基本不影响电容负载电路11的在向电动机动态供电时的充电电流。举例来说，高阻抗可以是电阻或者是开关元件断路或截止时自身所具有的阻抗，低阻抗则是指导线的阻抗或者是开关元件闭合或导通时具有的阻抗。
延时控制电路13在本实施例中也不作具体的限制，其可以是串联在电源正极14和电源地15之间并且其控制端与开关电路12电连接的计时 器，该计时器在电源上电时启动并在计时到预定时间，也即上电超过预设时间之后控制开关电路12由高阻抗输出状态切换至低阻抗输出状态。当然，延时控制电路13也可以通过计时控制芯片或者控制软件来实现。
在本实施例中，该电源控制电路1的工作原理是：当无人飞行器的电池的电源插头插入电子调速器的电源插孔时，也即电池的正极和负极接入电源控制电路1的输入接口时，电源控制电路1的电源正极14和电源地15之间输入压差，电容负载电路11中的电容通过开关电路12输出的高阻抗进行充电。由于，有开关电路12的高阻抗输出，所以，电容负载电路11中的电容充电电流很小，在电池的电源插头处不会出现电火花，防止了电打火现象。与此同时，延时控制电路13分别与电源正极14和电源地15连接的输入端和输出端检测出该压差，获取到电源正极14和电源地15之间处于上电状态，则在上电超过预设时间之后通过控制端控制开关电路12由高阻抗输出状态切换为低阻抗输出状态从而为电容负载电路11向电动机输出大电流做准备。这样，当电子调速器调速过程中需要大电流时，电容负载电路11可以为电机驱动电路2提供大电流的输出，而在输出后电容负载电路11可以通过开关电路12输出的低阻抗进行快速充电，以降低无人飞行器正常工作过程时电容负载电路11的动态充电时间，从而提高电容负载电路11的动态充放电效率。
本实施例的无人飞行器，通过电源控制电路1中的延时控制电路13在电源正极14和电源地15上电超过预设时间后控制开关电路12由高阻抗输出状态切换至低阻抗输出状态，从而无需再手动将主电源和大电容连接，简化了无人飞行器电池热插拔时防打火的操作，实现了防电火花的自动控制。
本实施例的无人飞行器大大减小了插上电源插头时上电瞬间的电流峰值，减小并消除了插头接触瞬间产生的电火花，有效延长了电源接头的寿命。
同时，本实施例的无人飞行器的电源控制电路1非常简单，容易集成在电子调速器等硬件上；非常适宜于智能电池在热插拔时候减小插头的电火花。而且还可以大大减小电池上电时候的电流应力，起到保护电池的作用，非常适合在大功率无人机上应用。
实施例20
本发明实施例20提供一种无人飞行器。
请参阅图2a和2b，本实施例是在实施例10提供的方案的基础上，将该开关电路12设置为包括MOS管121(金属(metal)—氧化物(oxid)—半导体(semiconductor)场效应晶体管)。
具体而言，是将MOS管121的栅极(G)与延时控制电路13的控制端电连接，将其漏极(D)与电容负载电路11的输出端电连接，将其源极(S)与电源地15电连接，用于根据栅极的电压变化实现MOS管121的导通和截止。
由于MOS管121在截止时具有非常大的阻抗，而在导通时阻抗很小，通过延时控制电路13控制栅极(G)的电压就可以非常方便的实现MOS管121的导通和截止之间的切换，从而为开关电路12输出高阻抗或者低阻抗。并且，这样设置的开关电路12结构也很简单，性能更加稳定。
具体的，在工作时，当电源正极14和电源地15之间上电时，MOS管121处于截止状态，因此，开关电路12输出一个高阻抗，使得电容负载电路11的充电电流降低，避免产生瞬时涌流，从而防止接头处产生电火花。当上电超过预设时间后，延时控制电路13则通过控制端将MOS管121栅极(G)的电压提高到开启电压，比如，提高到2.5V，从而导通该MOS管121。由于MOS管121导通时的阻抗很小，因此在导通该MOS管121后可以使开关管电路输出一低阻抗。当然，上述MOS管121的导通电压仅是本实施例的示例性导通电压，在实际设置中可以根据电路需要选择不同的MOS管121导通电压。
同时，还需要说明的是，将MOS管121的栅极(G)电压提高到开启电压可以是瞬时完成或者通过一段时间来完成。例如，通过计时器在计时超过预设时间时立即为栅极(G)提供导通电压，或者，通过控制芯片和控制软件将栅极(G)的电压在一段时间内缓慢提高直到超过预设时间后达到导通电压。
进一步，还可以在开关电路12中设置一个与MOS管121并联的第一电阻123，用于保护MOS管121。
具体的，当电源正极14和电源地15上电时，在电容负载电路11的 充电过程中，第一电阻123将起到分流作用，从而避免上电时充电电流过大从而击穿MOS管121。
可选的，开关电路12可以与电容负载电路11串联在一个支路中并与延时控制电路13并联，也即，将开关电路12设置在电容负载电路11的支路中。这样，MOS管121的导通和截止不会对电源输出到无人飞行器电动机的输出产生影响。
可选的，开关电路12还可以将电容负载电路11和延时控制电路13并联形成的支路与开关电路12串联，也即，将开关电路12串联在干路中。这样，通过MOS管121的导通和截止可以控制电源控制电路1输出到无人飞行器电动机的时间。并且对于较高电压的场合，可以提高防电火花的效果，并消除上电时刻电压过冲尖峰，使过冲尖峰不会输出到电动机中。
本实施例的无人飞行器中的电源控制电路1，通过设置MOS管121的方式可以使开关电路12的结构更简单，而且也能够通过为栅极(G)提供导通电压的时间控制MOS管121由截止状态到导通状态的时间，控制起来更容易和方便。并且，为MOS管121并联第一电阻123可以保护MOS管121，提高整个电源控制电路1的稳定性。
实施例21
本发明实施例21提供一种无人飞行器。
请参阅图3a和3b，本实施例是在实施例11提供的方案的基础上，将该开关电路12设置为包括：继电器125和第二电阻127。其中，延时控制电路13的控制端与继电器125电连接，用于控制继电器125的开端的开闭状态以将开关电路由高阻抗输出状态切换至低阻抗输出状态。
具体的，延时控制电路13和电容负载电路11并联在电源正极14和电源地15之间。也即，延时控制电路13的输入端连接电源正极14，其输出端连接电源地15；电容负载电路11的输入端也连接电源正极14，其输出端也连接电源地15。并且延时控制电路13的控制端与继电器125的输入端电连接，继电器125的输出端连接电源地15。继电器125的开关与第二电阻127并联，且其两端分别连接延时控制电路13的输出端和电容负载电路11的输出端。
具体的，在工作时，当电源正极14和电源地15之间上电时，继电器125的开关断开。此时，第二电阻127作为开关电路12的高阻抗输出，从而降低了上电时电容负载电路11充电的电流，消除了电容负载电路11充电时的瞬时峰值，进而避免电源插头出现电火花。在充电超过预设时间后，延时控制电路13的控制端将继电器125接通。当继电器125接通后，第二电阻127被继电器125短路，电容负载电路11的输出端通过继电器125与电源地15直接连接，也即，电容负载电路11通过开关电路12输出的低阻抗进行动态充电，从而缩短动态充电的时间，提高电容负载电路11输出大电流的效率。
本实施例的无人飞行器中的电源控制电路1，通过设置并联的继电器125和第二电阻127的方式实现开关电路12高阻抗输出和低阻抗输出的切换，方便，简单，易于实现上电时防电火花的自动控制。并且还可以控制电源控制电路1输出到无人飞行器电动机的时间。并且对于较高电压的场合，可以提高防电火花的效果，并消除上电时刻电压过冲尖峰，使过冲尖峰不会输出到电动机中。
实施例22
本发明实施例22提供一种无人飞行器。
请参阅图4，本实施例是在实施例19、实施例20或者实施例21提供的技术方案基础上，将延时控制电路13设置为包括：第一电容1311和上拉电阻1313。其中，第一电容1311和上拉电阻1313串联在电源正极14和电源地15之间并与电容负载电路11并联；且第一电容1311的正极与开关电路12电连接。
具体的，上拉电阻1313可以直接串联到电源正极14，也可以间接与电源正极14串联。例如，上拉电阻1313可以与由电源正极14分压而来的无人飞行器的系统电源串联。
在工作时，当电源正极14和电源地15上电时，在电容负载电路11充电的同时，第一电容1311也通过上拉电阻1313进行充电。随着第一电容1311的充电，其两端的电压也在逐渐升高，从而通过第一电容1311正极和负极之间的电压变化来控制开关电路12的工作状态。
例如，当第一电容1311的正极和负极分别与继电器125的输入端和 输出端电连接时，随着上电时间的增加，第一电容1311的正极和负极间的电压也随着时间的增加而升高，也即，与第一电容1311两极电连接的继电器125的输入端和输出端之间的电压随着上电时间的增加而升高。当上电时间超过预设时间后，继电器125输入端和输出端之间的电压超过导通电压阈值时，继电器125随之被闭合，开关电路12的输出阻抗也就从高阻抗切换为低阻抗。而当第一电容1311的正极和负极之间进入下电状态时，随着负载电容电路中的电容放电，负载电容电路的输入端和输出端之间的电压逐渐降低。当负载电容电路的输入端和输出端之间的电压降低到低于预设电压后，第一电容1311开始放电，第一电容1311的正极和负极之间的电压也随之降低，继电器125输入端和输出端之间的电压值也随之降低。当继电器125输入端和输出端之间的电压值降低到导通阈值以下时，继电器125随之被断开，开关电路12的输出阻抗也就从低阻抗切换为高阻抗。
再例如，当第一电容1311的正极与MOS管121的栅极(G)电连接时，随着上电时间的增加，第一电容1311的正极和负极间的电压也随着时间的增加而升高，也即，与第一电容1311正极电连接的MOS管121的栅极(G)的电压也随着上电时间的增加而升高。当上电时间超过预设时间后，MOS管121的栅极(G)的电压超过导通电压后，MOS管121随即被导通，开关电路12的输出阻抗也就从高阻抗切换为低阻抗。而当第一电容1311的正极和负极之间进入下电状态时，随着负载电容电路中电容的放电，负载电容电路的输入端和输出端之间的电压逐渐降低。当负载电容电路的输入端和输出端之间的电压降低到低于预设电压后，第一电容1311开始放电，第一电容1311的正极电压也随之降低，MOS管121栅极(G)的电压也随之降低。当MOS管121栅极(G)的电压降低到导通电压以下时，MOS管121随之被截止，开关电路12的输出阻抗也就从低阻抗切换为高阻抗。
从上述分析可以看出，开关电路12由高阻抗输出状态切换为低阻抗输出状态的预设时间为第一电容1311充电到继电器125或者MOS管121的导通电压的时间，也即第一电容1311充电到预设电压值的时间。并且，通过控制第一电容1311和上拉电阻1313的参数可以获得不同的第一 电容1311充电时间，也即，获得不同的控制开关电路12由高阻抗切换到低阻抗的时间，也即，预设时间。
可选的，当开关电路12包括MOS管121时，可以在第一电容1311的正极和电容负载电路11的输出端之间连接有第三电容1321，用于减小MOS管121的导通电流。
具体的，当第三电容1321和MOS管121并联时，可以增加总的弥勒电容。在MOS管121开通的时候可以增加Vgs的弥勒平台时间，可以减缓Vds电压的下降速度，从而减小MOS管121的开通电流。其中，Vgs指栅极(G)和源极(S)之间的压差；Vds指漏极(D)和源极(S)之间的压差。
同时，当第一电容1311放电时，第三电容1321还可以延长第一电容1311放电时间，从而增加MOS管121的开通时间。
本实施例的无人飞行器中的电源控制电路1，通过串联在电源正极14和电源地15之间的第一电容1311和上拉电阻1313，可以非常方便的通过第一电容1311的充放电来控制开关电路12在高阻抗输出和低阻抗输出之间进行切换，实现了电池热插拔的自动化。而且，还可以通过调整第一电阻123和第一电容1311的参数来控制第一电容1311的充电时间，从而控制开关电路12由高阻抗输出切换为低阻抗输出的时间，进而提高上电时电容负载电路11在高阻抗下充电的时间以提高电源控制电路1防电火花的效果。
实施例23
本发明实施例23提供一种无人飞行器。
请参阅图5，本实施例是在实施例22提供的技术方案基础上，将上拉电阻1313与一个二极管1331并联，用于加速第一电容1311放电。其中，该二极管1331的正极与第一电容1311的正极电连接，该二极管1331的负极与上拉电阻1313的输入端电连接。
具体的，电源控制电路1在电源正极14和电源地15处于下电状态时，当负载电容电路的输入端和输出端的电压降低到预设电压(比如，6-7v)后，第一电容1311可以通过二极管1331放电，从而加速第一电容1311的放电，使其尽快回到待充电的初始状态。
需要说明的是，本实施例中也可以在开关电路12包括MOS管121时，在第一电容1311的正极和电容负载电路11的输出端之间连接有第三电容1321，用于减小MOS管121的导通电流。第三电容1321的作用原理及效果请参见实施例22。
本实施例的无人飞行器中的电源控制电路1，通过对上拉电阻1313并联一个二极管1331的方式来加快第一电容1311的放电，可以使电路快速回复初始状态，以备下一次电池的接入。
实施例24
本发明实施例24提供一种无人飞行器。
请参阅图6a和图6b，本实施例是在实施例23提供的技术方案基础上，将第一电容1311与一第三电阻1333并联，且该第三电阻1333与上拉电阻1313串联，该第三电阻1333用于与上拉电阻1313对电源进行分压，用于保护开关电路12。
具体的，本实施例无人飞行器中的电源控制电路1，当电源正极14和电源地15处于上电状态时，电源经上拉电阻1313和第三电阻1333分压后给第一电容1311充电，从而可以保护与第一电容1311正极连接的开关电路12。例如，当与第一电容1311正极连接的为MOS管121时，由于MOS管121的Vgs可能在20V以内，而电源正极14与电源地15之间的压差可能会比20V高，所以可以通过接入第三电阻1333，以调整MOS管121的栅极(G)的电压，使得MOS管121的Vgs充满电压接近12V，从而保护MOS管121。当然，基于上述原理可知，第三电阻1333也可以保护开关电路12中的继电器125或者其他开关元件
当电源正极14和电源地15处于下电状态时，当负载电容电路的输入端和输出端的电压降低到预设电压(比如，6-7v)后，第一电容1311可以通过第三电阻1333放电，从而加速第一电容1311的放电，使其尽快回到待充电的初始状态。
需要说明的是，本实施例中也可以在开关电路12包括MOS管121时，在第一电容1311的正极和电容负载电路11的输出端之间连接有第三电容1321，用于减小MOS管121的导通电流。第三电容1321的作用原理及效果请参见实施例22。
本实施例的无人飞行器中的电源控制电路1，通过为上拉电阻1313串联一个与第一电容1311并联的第三电阻1333，可以通过调整上拉电阻1313和第三电阻1333的分压比以保护开关电路12。同时，第三电阻1333在第一电容1311放电时还可以加快其放电，以使电路快速回复初始状态，以备下一次电池的接入。
实施例25
本发明实施例25提供一种无人飞行器。
请参阅图7a和图7b，本实施例是在实施例23提供的技术方案基础上，将第一电容1311与一稳压二极管1335并联，且该稳压二极管1335与上拉电阻1313串联，用于与上拉电阻1313组成并联稳压电路，从而保护开关电路12。
本实施例的电子调速器中的电源控制电路1在工作时，稳压二极管1335会始终将第一电容1311正极的电压稳定在二极管1331的稳压值，从而保护与第一电容1311正极连接的开关电路12。例如，当与第一电容1311正极连接的为MOS管121时，图7中的稳压二极管1335可以将MOS管121的Vgs控制在12V以内，从而保护稳压二极管1335不会被烧坏。当然，基于上述原理可知，稳压二极管1335也可以保护开关电路12中的继电器125或者其他晶体管元件。
需要说明的是，本实施例中也可以在开关电路12包括MOS管121时，在第一电容1311的正极和电容负载电路11的输出端之间连接有第三电容1321，用于减小MOS管121的导通电流。第三电容1321的作用原理及效果请参见实施例22。
本实施例的无人飞行器中的电源控制电路1，通过为上拉电阻1313串联一个与第一电容1311并联的稳压二极管1335，可以保护开关电路12。
实施例26
本发明实施例26提供一种无人飞行器。
请参阅图8，本实施例是在实施例22提供的技术方案基础上，设置一个用于控制第一电容1311在电容负载电路11的电压低于预设电压后放电的放电控制电路。
具体的，该放电控制电路包括第一三极管1351、第四电阻1353和第五电阻1355。其中，第一三极管1351的发射极与第一电容1311的正极电连接，第一三极管1351的集电极与电源地15连接，第一三极管1351的基极通过第四电阻1353与电源正极14电连接，且第一三极管1351的基极还通过第五电阻1355与电源地15电连接。
在工作时，当电源正极14和电源地15之间为上电状态时，电容负载电路11通过开关电路12输出的高阻抗进行充电时，第一电容1311也通过上拉电阻1313开始充电。此时，由于开关电路12输出的高阻抗作用，电容负载电路11的充电电流很小，且消除了其充电瞬间的电流峰值，避免了电源接头出现电火花。
当上电时间超过第一电容1311充电到预设电压的时间时，开关电路12从高阻抗输出切换为低阻抗输出，以实现对电容负载电路11对电动机的大电流输出，并在开关电路12提供的低阻抗下实现动态充电，从而减少动态充电的时间。具体的，在图8中，上电时间为超过第一电容1311充电到MOS管121导通电压的时间，而开关电路12的高阻抗由MOS管121截止时的阻抗和第一电阻123来提供，低阻抗则主要由MOS管121导通后的MOS管121自身的阻抗来提供。
同时，在电池接入电源控制电路1的所有时间内，第一三极管1351的基极电压和射电极之间的压降小于第一三极管1351的导通电压，因此，在电池接入电源控制电路1的整个时间内均处于截止状态。
当电源正极14和电源地15之间为下电状态时，当电容负载电路11输入端和输出端的电压降低到预设电压后，第一三极管1351的基极电压和射电极之间的压降升高到超过第一三极管1351的导通电压，第一三极管1351随即导通。第一电容1311通过第一三极管1351迅速放电。MOS管121的栅极电压也随之迅速降低到低于导通电压，MOS管121截止，开关电路12回到输出高阻抗的状态。
需要说明的是，本实施例中也可以在开关电路12包括MOS管121时，在第一电容1311的正极和电容负载电路11的输出端之间连接有第三电容1321，用于减小MOS管121的导通电流。第三电容1321的作用原理及效果请参见实施例22。
本实施例的无人飞行器中的电源控制电路1，通过设置包括三极管的放电控制电路，可以延迟开关电路12由低阻抗输出状态切换至高阻抗输出状态的时间，提高电容负载电路11的放电时间。
实施例27
本发明实施例27提供一种无人飞行器。
请参阅图9，本实施例是在实施例22提供的技术方案基础上，设置一个用于控制第一电容1311在电容负载电路11的电压低于预设电压后放电的放电控制电路。
具体的，该放电控制电路包括：第二三极管1371、第三三极管1373、第六电阻1375、第七电阻1376和第八电阻1377。
该第二三极管1371的发射极与电源地15电连接，第二三极管1371的基极通过第六电阻1375与电源正极14电连接，第二三极管1371的集电极与第一电容1311的正极电连接。
第三三极管1373的集电极与第二三极管1371的基极电连接，第三三极管1373的发射极与电源地15电连接，第三三极管1373的基极与电源正极14电连接。
第七电阻1376和第八电阻1377串联在第二三极管1371的基极和电源正极14之间。
在工作时，当电源正极14和电源地15之间为上电状态时，电容负载电路11通过开关电路12输出的高阻抗进行充电时，第一电容1311也通过上拉电阻1313开始充电。此时，由于开关电路12输出的高阻抗作用，电容负载电路11的充电电流很小，且消除了其充电瞬间的电流峰值，避免了电源接头出现电火花。
当上电时间超过第一电容1311充电到预设电压的时间时，开关电路12从高阻抗输出切换为低阻抗输出，以实现对电容负载电路11对电动机的大电流输出，并在开关电路12提供的低阻抗下实现动态充电，从而减少动态充电的时间。具体的，在图8中，上电时间为超过第一电容1311充电到MOS管121导通电压的时间，而开关电路12的高阻抗由MOS管121截止时的阻抗和第一电阻123来提供，低阻抗则主要由MOS管121导通后的MOS管121自身的阻抗来提供。
同时，在电池接入电源控制电路1的所有时间内，第三三极管1373的基极电压大于射电极的电压，第三二极管1331处于导通状态。第二三极管1371由于第三二极管1331处于导通状态，因此，其基极电压小于基极和射电极之间的压降，从而使得第二三极管1371处于截止状态。
当电源正极14和电源地15之间为下电状态时，当电容负载电路11输入端和输出端的电压降低到预设电压后，第三三极管1373的基极电压降低到小于其基极和射电极之间的压降，从而第三三极管1373截止。此时，由于第三三极管1373截止，第二三极管1371的基极电压高于射电极电压，第二三极管1371导通，第一电容1311迅速放电。MOS管121的栅极电压也随之迅速降低到低于导通电压，MOS管121截止，开关电路12回到输出高阻抗的状态。
进一步，设置一个第二电容1379，用于提高第三二极管1331对于电容负载电路11输入端和输出端压降的检测能力。该第二电容1379与第七电阻1376并联，且与第六电阻1375串联。
另外，在本实施例中可以通过控制第六电阻1375、第七电阻1376和第八电阻1377来控制第一电容1311放电时电容负载电路11的输入端和输出端之间的电压。当然，当设置有第二电容1379时，可以通过控制第六电阻1375、第七电阻1376、第八电阻1377和第二电容1379来控制第一电容1311放电时电容负载电路11的输入端和输出端之间的电压，以提高控制精度。
需要说明的是，本实施例中也可以在开关电路12包括MOS管121时，在第一电容1311的正极和电容负载电路11的输出端之间连接有第三电容1321，用于减小MOS管121的导通电流。第三电容1321的作用原理及效果请参见实施例22。
本实施例的无人飞行器中的电源控制电路1，通过第二三极管1371和第三三极管1373组成的双三极管作为放电控制电路，可以提高对第一电容1311放电的控制效果。
实施例28
本发明实施例28提供一种电源输出电路的控制方法。图11为本发明实施例28提供的电源输出电路的控制方法的流程示意图。
本实施例的控制方法，包括用于为无人飞行器电动机提供大电流输出的电容负载电路11和开关电路12。其中，开关电路12串联在电容负载电路11和电源地15之间。本实施例的电源输出电路控制方法中控制所述开关电路12的方法包括：
控制所述开关电路12在所述电源正极14和电源地15之间上电超过预设时间后由高阻抗输出状态切换至低阻抗输出状态。
具体的，控制开关电路12由高阻抗输出状态切换至低阻抗输出状态的方法可以通过软件或者硬件电路，以及芯片来实现。
例如，可以是通过控制开关电路12中的继电器125开关的接通与断开来对开关电路12的工作状态进行控制。也可以是通过开关电路12中可能包括的MOS管121从截止状态到导通状态的来对开关电路12进行控制。当然，对于时间的控制可以通过计时器或者计时电路、计时软件来实现。
具体的，可以通过控制与MOS管121的栅极连接的第一电容1311充电来实现在预设时间后控制MOS管121从截止状态到导通状态从而实现开关电路12由高阻抗输出状态切换至低阻抗输出状态的目的。
进一步，控制所述开关电路12的方法还包括：控制第一电容1311放电，然后控制所述开关电路12在所述电容负载电路11的电压低于预设电压后由低阻抗输出状态切换至高阻抗输出状态。
具体的，控制第一电容1311放电以及控制所述开关电路12由低阻抗输出状态切换至高阻抗输出状态都可以通过芯片来实现。例如，可以将开关电路12与一控制芯片连接，通过芯片上检测到的电容负载电路11的电压变化控制第一电容放电，并控制开关电路12在电容负载电路11的电压低于预设电压后由低阻抗输出状态切换至高阻抗输出状态。当然，上述控制方式也可以通过电路来实现。比如，设置一个与第一电容1311连接的取样控制电路，当取样控制电路获取到电容负载电路11的电压降低到预设值时就控制第一电容1311放电来实现对开关电路12工作状态的控制。当然，还可以通过软件来实现对第一电容1311放电以及开关电路12 由低阻抗输出状态切换至高阻抗输出状态的控制。
另外，需要说明的是，本实施例中控制方法的具体控制方法、原理及其过程与上述实施例所描述的控制方法、原理和操作过程相同，本领域技术人员可以参阅以上所有实施例，在此不再赘述。
本实施例的电源输出电路的控制方法，通过控制开关电路12在上电超过预设时间之后由高阻抗输出状态切换至低阻抗输出状态，从而可以非常方便简单的实现电池热插拔过程中的防电火花目的，而且无需手工操作。
以上各个实施例中的技术方案、技术特征在与本相冲突的情况下均可以单独，或者进行组合，只要未超出本领域技术人员的认知范围，均属于本申请保护范围内的等同实施例。
在本发明所提供的几个实施例中，应该理解到，所揭露的相关装置和方法，可以通过其它的方式实现。例如，以上所描述的装置实施例仅仅是示意性的，例如，所述模块或单元的划分，仅仅为一种逻辑功能划分，实际实现时可以有另外的划分方式，例如多个单元或组件可以结合或者可以集成到另一个系统，或一些特征可以忽略，或不执行。另一点，所显示或讨论的相互之间的耦合或直接耦合或通信连接可以是通过一些接口，装置或单元的间接耦合或通信连接，可以是电性，机械或其它的形式。
所述作为分离部件说明的单元可以是或者也可以不是物理上分开的，作为单元显示的部件可以是或者也可以不是物理单元，即可以位于一个地方，或者也可以分布到多个网络单元上。可以根据实际的需要选择其中的部分或者全部单元来实现本实施例方案的目的。
另外，在本发明各个实施例中的各功能单元可以集成在一个处理单元中，也可以是各个单元单独物理存在，也可以两个或两个以上单元集成在一个单元中。上述集成的单元既可以采用硬件的形式实现，也可以采用软件功能单元的形式实现。
所述集成的单元如果以软件功能单元的形式实现并作为独立的产品销售或使用时，可以存储在一个计算机可读取存储介质中。基于这样的理解，本发明的技术方案本质上或者说对现有技术做出贡献的部分或者该技术方案的 全部或部分可以以软件产品的形式体现出来，该计算机软件产品存储在一个存储介质中，包括若干指令用以使得计算机处理器(processor)执行本发明各个实施例所述方法的全部或部分步骤。而前述的存储介质包括：U盘、移动硬盘、只读存储器(ROM，Read-Only Memory)、随机存取存储器(RAM，Random Access Memory)、磁盘或者光盘等各种可以存储程序代码的介质。
以上所述仅为本发明的实施例，并非因此限制本发明的专利范围，凡是利用本发明说明书及附图内容所作的等效结构或等效流程变换，或直接或间接运用在其他相关的技术领域，均同理包括在本发明的专利保护范围内。
最后应说明的是：以上各实施例仅用以说明本发明的技术方案，而非对其限制；尽管参照前述各实施例对本发明进行了详细的说明，本领域的普通技术人员应当理解：其依然可以对前述各实施例所记载的技术方案进行修改，或者对其中部分或者全部技术特征进行等同替换；而这些修改或者替换，并不使相应技术方案的本质脱离本发明各实施例技术方案的范围。

Claims (50)

  1. 一种无人飞行器的电源控制电路，其特征在于，包括：电容负载电路、开关电路和延时控制电路；
    所述电容负载电路的输入端与电源正极电连接；
    所述开关电路串联在所述电容负载电路的输出端和电源地之间；
    所述延时控制电路的输入端和输出端之间分别连接所述电源正极和电源地，所述延时控制电路的控制端与所述开关电路电连接；
    所述延时控制电路用于在所述电源正极和电源地为上电状态时，控制所述开关电路在上电时间超过预设时间后由高阻抗输出状态切换至低阻抗输出状态。
  2. 根据权利要求1所述的电源控制电路，其特征在于，所述开关电路包括：MOS管，所述MOS管的栅极与所述延时控制电路的控制端电连接，所述MOS管的漏极与所述电容负载电路的输出端电连接，所述MOS管的源极与所述电源地电连接；所述开关电路由高阻抗输出状态切换至低阻抗输出状态为所述MOS管由截止状态切换至导通状态。
  3. 根据权利要求2所述的电源控制电路，其特征在于，所述开关电路还包括与所述MOS管并联的第一电阻。
  4. 根据权利要求1所述的电源控制电路，其特征在于，所述开关电路包括：并联的继电器和第二电阻，所述延时控制电路的控制端与所述继电器电连接，所述开关电路由高阻抗输出状态切换至低阻抗输出状态为所述继电器由断开状态切换至接通状态。
  5. 根据权利要求1所述的电源控制电路，其特征在于，所述延时控制电路包括：第一电容和上拉电阻；
    所述第一电容和上拉电阻串联在电源正极和电源地之间并与所述电容负载电路并联；
    所述第一电容的正极与所述开关电路电连接；
    所述预设时间为所述第一电容充电到预设电压值的时间。
  6. 根据权利要求5所述的电源控制电路，其特征在于，所述延时控制电路还包括：二极管，所述二极管与所述上拉电阻并联，且所述二极管的正极与所述第一电容的正极电连接，所述二极管的负极与所述上拉电阻的输入端电连接。
  7. 根据权利要求5所述的电源控制电路，其特征在于，所述延时控制电路还包括：第三电阻，所述第三电阻与所述第一电容并联，且该第三电阻与所述上拉电阻串联。
  8. 根据权利要求5所述的电源控制电路，其特征在于，所述延时控制电路还包括：稳压二极管，所述稳压二极管与所述第一电容并联，且所述稳压二极管与所述上拉电阻串联。
  9. 根据权利要求5所述的电源控制电路，其特征在于，所述延时控制电路还包括：放电控制电路；
    所述放电控制电路的输入端与所述电源正极电连接，所述放电控制电路的输出端与所述电源地电连接，所述放电控制电路的控制端与所述第一电容正极电连接；
    所述放电控制电路用于在所述电源正极和电源地之间为下电状态时，控制所述第一电容在所述电容负载电路的电压低于预设电压后放电。
  10. 根据权利要求9所述的电源控制电路，其特征在于，所述放电控制电路包括：第一三极管、第四电阻和第五电阻；
    所述第一三极管的发射极与所述第一电容的正极电连接，所述第一三极管的集电极与所述电源地连接，所述第一三极管的基极通过第四电阻与电源正极电连接，且所述第一三极管的基极还通过第五电阻与电源地电连接。
  11. 根据权利要求9所述的电源控制电路，其特征在于，所述放电控制电路包括：第二三极管、第三三极管、第六电阻、第七电阻和第八电阻；
    所述第二三极管的发射极与所述电源地电连接，所述第二三极管的基极通过所述第六电阻与所述电源正极电连接，所述第二三极管的集电极与所述第一电容的正极电连接；
    所述第三三极管的集电极与所述第二三极管的基极电连接，所述第三三 极管的发射极与所述电源地电连接，所述第三三极管的基极与电源正极电连接；
    所述第七电阻和第八电阻串联在所述第二三极管的基极和电源正极之间。
  12. 根据权利要求11所述的电源控制电路，其特征在于，所述放电控制电路还包括：第二电容，所述第二电容与所述第八电阻并联且与所述第七电阻串联。
  13. 根据权利要求5-12任一项所述的电源控制电路，其特征在于，所述第一电容的正极和所述电容负载电路的输出端之间连接有第三电容。
  14. 根据权利要求1-12任一项所述的电源控制电路，其特征在于，所述电容负载电路与开关电路所构成的串联支路与所述延时控制电路并联。
  15. 根据权利要求1-12任一项所述的电源控制电路，其特征在于，所述电容负载电路和所述延时控制电路所构成的并联支路与所述开关电路串联。
  16. 一种电子调速器，包括电机驱动电路和电源控制电路，所述电源控制电路与所述电机驱动电路电连接，用于给所述电机驱动电路供电，其特征在于，所述电源控制电路包括：电容负载电路、开关电路和延时控制电路；
    所述电容负载电路的输入端与电源正极电连接；
    所述开关电路串联在所述电容负载电路的输出端和电源地之间；
    所述延时控制电路的输入端和输出端之间分别连接所述电源正极和电源地，所述延时控制电路的控制端与所述开关电路电连接；
    所述延时控制电路用于在所述电源正极和电源地为上电状态时，控制所述开关电路在上电时间超过预设时间后由高阻抗输出状态切换至低阻抗输出状态。
  17. 根据权利要求16所述的电子调速器，其特征在于，所述开关电路包括：MOS管，所述MOS管的栅极与所述延时控制电路的控制端电连接， 所述MOS管的漏极与所述电容负载电路的输出端电连接，所述MOS管的源极与所述电源地电连接；所述开关电路由高阻抗输出状态切换至低阻抗输出状态为所述MOS管由截止状态切换至导通状态。
  18. 根据权利要求17所述的电子调速器，其特征在于，所述开关电路还包括与所述MOS管并联的第一电阻。
  19. 根据权利要求16所述的电子调速器，其特征在于，所述开关电路包括：并联的继电器和第二电阻，所述延时控制电路的控制端与所述继电器电连接，所述开关电路由高阻抗输出状态切换至低阻抗输出状态为所述继电器由断开状态切换至接通状态。
  20. 根据权利要求16所述的电子调速器，其特征在于，所述延时控制电路包括：第一电容和上拉电阻；
    所述第一电容和上拉电阻串联在电源正极和电源地之间并与所述电容负载电路并联；
    所述第一电容的正极与所述开关电路电连接；
    所述预设时间为所述第一电容充电到预设电压值的时间。
  21. 根据权利要求20所述的电子调速器，其特征在于，所述延时控制电路还包括：二极管，所述二极管与所述上拉电阻并联，且所述二极管的正极与所述第一电容的正极电连接，所述二极管的负极与所述上拉电阻的输入端电连接。
  22. 根据权利要求20所述的电子调速器，其特征在于，所述延时控制电路还包括：第三电阻，所述第三电阻与所述第一电容并联，且该第三电阻与所述上拉电阻串联。
  23. 根据权利要求20所述的电子调速器，其特征在于，所述延时控制电路还包括：稳压二极管，所述稳压二极管与所述第一电容并联，且所述稳压二极管与所述上拉电阻串联。
  24. 根据权利要求20所述的电子调速器，其特征在于，所述延时控制电路还包括：放电控制电路；
    所述放电控制电路的输入端与所述电源正极电连接，所述放电控制电路 的输出端与所述电源地电连接，所述放电控制电路的控制端与所述第一电容正极电连接；
    所述放电控制电路用于在所述电源正极和电源地之间为下电状态时，控制所述第一电容在所述电容负载电路的电压低于预设电压后放电。
  25. 根据权利要求24所述的电子调速器，其特征在于，所述放电控制电路包括：第一三极管、第四电阻和第五电阻；
    所述第一三极管的发射极与所述第一电容的正极电连接，所述第一三极管的集电极与所述电源地连接，所述第一三极管的基极通过第四电阻与电源正极电连接，且所述第一三极管的基极还通过第五电阻与电源地电连接。
  26. 根据权利要求24所述的电子调速器，其特征在于，所述放电控制电路包括：第二三极管、第三三极管、第六电阻、第七电阻和第八电阻；
    所述第二三极管的发射极与所述电源地电连接，所述第二三极管的基极通过所述第六电阻与所述电源正极电连接，所述第二三极管的集电极与所述第一电容的正极电连接；
    所述第三三极管的集电极与所述第二三极管的基极电连接，所述第三三极管的发射极与所述电源地电连接，所述第三三极管的基极与电源正极电连接；
    所述第七电阻和第八电阻串联在所述第二三极管的基极和电源正极之间。
  27. 根据权利要求26所述的电子调速器，其特征在于，所述放电控制电路还包括：第二电容，所述第二电容与所述第七电阻并联且与所述第六电阻串联。
  28. 根据权利要求20-27任一项所述的电子调速器，其特征在于，所述第一电容的正极和所述电容负载电路的输出端之间连接有第三电容。
  29. 根据权利要求16-27任一项所述的电子调速器，其特征在于，所述电容负载电路与开关电路所构成的串联支路与所述延时控制电路并联。
  30. 根据权利要求16-27任一项所述的电子调速器，其特征在于，所述电容负载电路和所述延时控制电路所构成的并联支路与所述开关电路串联。
  31. 一种无人飞行器，包括：电动机以及电子调速器，所述电动机用于提供飞行动力；
    所述电子调速器与所述电动机电连接，用于控制所述电动机的工作状态；
    所述电子调速器包括：包括电机驱动电路和电源控制电路；
    所述电源控制电路与所述电机驱动电路电连接，用于给所述电机驱动电路供电；
    其特征在于，所述电源控制电路包括：电容负载电路、开关电路和延时控制电路；
    所述电容负载电路的输入端与电源正极电连接；
    所述开关电路串联在所述电容负载电路的输出端和电源地之间；
    所述延时控制电路的输入端和输出端之间分别连接所述电源正极和电源地，所述延时控制电路的控制端与所述开关电路电连接；
    所述延时控制电路用于在所述电源正极和电源地为上电状态时，控制所述开关电路在上电时间超过预设时间后由高阻抗输出状态切换至低阻抗输出状态。
  32. 根据权利要求31所述的无人飞行器，其特征在于，所述开关电路包括：MOS管，所述MOS管的栅极与所述延时控制电路的控制端电连接，所述MOS管的漏极与所述电容负载电路的输出端电连接，所述MOS管的源极与所述电源地电连接；所述开关电路由高阻抗输出状态切换至低阻抗输出状态为所述MOS管由截止状态切换至导通状态。
  33. 根据权利要求32所述的无人飞行器，其特征在于，所述开关电路还包括与所述MOS管并联的第一电阻。
  34. 根据权利要求31所述的无人飞行器，其特征在于，所述开关电路包括：并联的继电器和第二电阻，所述延时控制电路的控制端与所述继电器 电连接，所述开关电路由高阻抗输出状态切换至低阻抗输出状态为所述继电器由断开状态切换至接通状态。
  35. 根据权利要求31所述的无人飞行器，其特征在于，所述延时控制电路包括：第一电容和上拉电阻；
    所述第一电容和上拉电阻串联在电源正极和电源地之间并与所述电容负载电路并联；
    所述第一电容的正极与所述开关电路电连接；
    所述预设时间为所述第一电容充电到预设电压值的时间。
  36. 根据权利要求35所述的无人飞行器，其特征在于，所述延时控制电路还包括：二极管，所述二极管与所述上拉电阻并联，且所述二极管的正极与所述第一电容的正极电连接，所述二极管的负极与所述上拉电阻的输入端电连接。
  37. 根据权利要求35所述的无人飞行器，其特征在于，所述延时控制电路还包括：第三电阻，所述第三电阻与所述第一电容并联，且该第三电阻与所述上拉电阻串联。
  38. 根据权利要求35所述的无人飞行器，其特征在于，所述延时控制电路还包括：稳压二极管，所述稳压二极管与所述第一电容并联，且所述稳压二极管与所述上拉电阻串联。
  39. 根据权利要求35所述的无人飞行器，其特征在于，所述延时控制电路还包括：放电控制电路；
    所述放电控制电路的输入端与所述电源正极电连接，所述放电控制电路的输出端与所述电源地电连接，所述放电控制电路的控制端与所述第一电容正极电连接；
    所述放电控制电路用于在所述电源正极和电源地之间为下电状态时，控制所述第一电容在所述电容负载电路的电压低于预设电压后放电。
  40. 根据权利要求39所述的无人飞行器，其特征在于，所述放电控制电路包括：第一三极管、第四电阻和第五电阻；
    所述第一三极管的发射极与所述第一电容的正极电连接，所述第一三极管的集电极与所述电源地连接，所述第一三极管的基极通过第四电阻与电源正极电连接，且所述第一三极管的基极还通过第五电阻与电源地电连接。
  41. 根据权利要求39所述的无人飞行器，其特征在于，所述放电控制电路包括：第二三极管、第三三极管、第六电阻、第七电阻和第八电阻；
    所述第二三极管的发射极与所述电源地电连接，所述第二三极管的基极通过所述第六电阻与所述电源正极电连接，所述第二三极管的集电极与所述第一电容的正极电连接；
    所述第三三极管的集电极与所述第二三极管的基极电连接，所述第三三极管的发射极与所述电源地电连接，所述第三三极管的基极与电源正极电连接；
    所述第七电阻和第八电阻串联在所述第二三极管的基极和电源正极之间。
  42. 根据权利要求41所述的无人飞行器，其特征在于，所述放电控制电路还包括：第二电容，所述第二电容与所述第七电阻并联且与所述第六电阻串联。
  43. 根据权利要求35-42任一项所述的无人飞行器，其特征在于，所述第一电容的正极和所述电容负载电路的输出端之间连接有第三电容。
  44. 根据权利要求31-42任一项所述的无人飞行器，其特征在于，所述电容负载电路与开关电路所构成的串联支路与所述延时控制电路并联。
  45. 根据权利要求31-42任一项所述的无人飞行器，其特征在于，所述电容负载电路和所述延时控制电路所构成的并联支路与所述开关电路串联。
  46. 一种电源输出电路的控制方法，所述电源输出电路包括用于为无人飞行器电动机提供大电流输出的电容负载电路，其特征在于，所述电源输出电路还包括：开关电路，所述开关电路串联在电容负载电路和电源地之间；
    控制所述开关电路的方法包括：
    控制所述开关电路在所述电源正极和电源地之间上电时间超过预设时间后由高阻抗输出状态切换至低阻抗输出状态。
  47. 根据权利要求46的控制方法，其特征在于，所述开关电路包括MOS管和与MOS管栅极连接的第一电容，所述控制所述开关电路由高阻抗输出状态切换至低阻抗输出状态，具体包括：
    控制与所述MOS管的栅极连接的第一电容充电。
  48. 根据权利要求47的控制方法，其特征在于，所述控制所述开关电路由高阻抗输出状态切换至低阻抗输出状态，具体还包括：
    控制所述MOS管从截至状态到导通状态。
  49. 根据权利要求48的控制方法，其特征在于，还包括：
    控制所述第一电容放电。
  50. 根据权利要求49的控制方法，其特征在于，还包括：
    控制所述开关电路在所述电容负载电路的电压低于预设电压后由低阻抗输出状态切换至高阻抗输出状态。
PCT/CN2016/072362 2016-01-27 2016-01-27 电源控制电路、电子调速器、无人飞行器及控制方法 Ceased WO2017128113A1 (zh)

Priority Applications (2)

Application Number Priority Date Filing Date Title
CN201680002467.7A CN107078640B (zh) 2016-01-27 2016-01-27 电源控制电路、电子调速器、无人飞行器及控制方法
PCT/CN2016/072362 WO2017128113A1 (zh) 2016-01-27 2016-01-27 电源控制电路、电子调速器、无人飞行器及控制方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/CN2016/072362 WO2017128113A1 (zh) 2016-01-27 2016-01-27 电源控制电路、电子调速器、无人飞行器及控制方法

Publications (1)

Publication Number Publication Date
WO2017128113A1 true WO2017128113A1 (zh) 2017-08-03

Family

ID=59396902

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2016/072362 Ceased WO2017128113A1 (zh) 2016-01-27 2016-01-27 电源控制电路、电子调速器、无人飞行器及控制方法

Country Status (2)

Country Link
CN (1) CN107078640B (zh)
WO (1) WO2017128113A1 (zh)

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107889319A (zh) * 2017-12-14 2018-04-06 李顺华 一种镇流式led灯的驱动电源的过流保护电路
CN109164746A (zh) * 2018-11-14 2019-01-08 上海英恒电子有限公司 一种下电时序控制电路及电源电路
CN109378811A (zh) * 2018-12-05 2019-02-22 杭州士腾科技有限公司 基于大电容的防打火控制器
CN109450652A (zh) * 2018-11-26 2019-03-08 珠海世讯科技有限公司 一种knx总线供电电路
CN110635533A (zh) * 2019-10-07 2019-12-31 深圳市金威源科技股份有限公司 一种带防反接功能的串并联切换电路
CN111897389A (zh) * 2020-08-25 2020-11-06 特变电工西安柔性输配电有限公司 一种基于三极管串联的线性稳压电路
CN114211991A (zh) * 2021-12-15 2022-03-22 沃飞长空科技(成都)有限公司 用于无线充电无人机的控制单元、无人机及控制方法
CN114368485A (zh) * 2022-03-18 2022-04-19 珠海奕博科技有限公司 一种微型无人机控制电路
CN115378336A (zh) * 2022-08-25 2022-11-22 湘潭大学 基于场效应管导通电阻采样电路的电机控制装置及方法
CN115378251A (zh) * 2022-08-30 2022-11-22 东风电驱动系统有限公司 一种直流电源控制电路及装置
CN116243215A (zh) * 2022-12-21 2023-06-09 深圳市乐目通讯有限公司 一种电器插接防火花检测方法、装置、系统及存储介质
CN116634087A (zh) * 2023-05-10 2023-08-22 深圳市中科创激光技术有限公司 一种hdmi接口电路
CN116927978A (zh) * 2023-07-19 2023-10-24 东方空间技术(山东)有限公司 一种火箭发动机安全机构的控制系统及方法
CN117543753A (zh) * 2023-10-27 2024-02-09 深圳壹磁智控有限公司 一种上电防打火及放电电路
US12597766B2 (en) * 2022-11-03 2026-04-07 Jiangsu Dongcheng Tools Technology Co., Ltd Anti-sparking method for power tool, and control device, and computer-readable storage medium

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109672230A (zh) * 2017-10-16 2019-04-23 北京易驾卓阳科技有限公司 一种无人机启动防火花电路
CN108377144A (zh) * 2018-01-26 2018-08-07 江苏银河同智新能源科技有限公司 多功能延时导通装置及具有其的延迟电路和电池预充系统
CN108725783A (zh) * 2018-06-11 2018-11-02 中国水利水电科学研究院 一种简易的轻小型电动无人机动力电池防打火电路
CN108767837B (zh) * 2018-08-20 2023-10-13 深圳市格瑞普智能电子有限公司 电源连接方法及电源接头防打火电路及带该电路的电源
CN109672434A (zh) * 2018-12-24 2019-04-23 优数通（北京）科技有限公司 一种汽车电子控制器电源电压延迟开启保护电路
CN111196155A (zh) * 2020-02-21 2020-05-26 江苏兆能电子有限公司 一种车载dc-dc电源下电延时线路
CN111564829A (zh) * 2020-05-29 2020-08-21 深圳市康贝电子有限公司 一种过载保护电路和用电系统
CN114079370A (zh) * 2020-08-17 2022-02-22 维谛公司 一种输出热插拔电路
CN114567231B (zh) * 2020-11-27 2025-06-13 威刚科技股份有限公司 马达驱动系统
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
CN113410098B (zh) * 2021-06-30 2022-07-19 中车株洲电力机车研究所有限公司 一种继电器的安全驱动电路
CN113676034A (zh) * 2021-09-17 2021-11-19 苏州世纪芯晨电子科技有限公司 一种防过冲电路
CN114710034A (zh) * 2022-05-06 2022-07-05 深圳综合粒子设施研究院 双向阻抗电路、阻抗器件及电子设备
CN115513930B (zh) * 2022-10-27 2025-01-10 北京瀚海科技有限公司 一种风机用上电保护电路
CN119045632B (zh) * 2024-07-12 2025-08-19 北京鲲鹏凌昊智能技术有限公司 热插拔控制电路、供电控制电路及热插拔控制方法
CN118970620B (zh) * 2024-07-25 2025-10-03 武汉北极芯微电子有限公司 激光器的驱动电路、驱动方法及激光测距装置

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090027822A1 (en) * 2007-07-26 2009-01-29 Darwish Mohamed N Transient blocking unit having a fab-adjustable threshold current
GB2454362A (en) * 2007-11-01 2009-05-06 Boeing Co Programmable high-resolution phase delay
CN202026081U (zh) * 2011-02-25 2011-11-02 深圳雅图数字视频技术有限公司 消火花电路
CN104167622A (zh) * 2013-07-02 2014-11-26 世派电子株式会社 具有供电延时电路的充电系统
CN104494834A (zh) * 2014-11-05 2015-04-08 新誉集团有限公司 无人机混合动力系统与飞控系统的控制方法
CN104875897A (zh) * 2015-05-29 2015-09-02 珠海市双捷科技有限公司 大功率新能源无人机动力系统
CN204925686U (zh) * 2015-08-25 2015-12-30 飞瑞航空科技（江苏）有限公司 一种无人直升机飞行控制集控盒

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101453117B (zh) * 2007-12-05 2010-12-29 中国科学院空间科学与应用研究中心 一种适用于航天器供配电系统的开机浪涌电流抑制装置
CN102195271B (zh) * 2010-03-10 2016-01-20 深圳市朗科科技股份有限公司 用于降低电子设备启动电流的装置
JP2015056949A (ja) * 2013-09-11 2015-03-23 株式会社デンソー 昇圧電源装置
CN203645069U (zh) * 2013-12-05 2014-06-11 东莞市前锋电子有限公司 一种防止电源插头产生电火花的电路
CN205544915U (zh) * 2016-01-27 2016-08-31 深圳市大疆创新科技有限公司 电源控制电路、电子调速器及无人飞行器

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090027822A1 (en) * 2007-07-26 2009-01-29 Darwish Mohamed N Transient blocking unit having a fab-adjustable threshold current
GB2454362A (en) * 2007-11-01 2009-05-06 Boeing Co Programmable high-resolution phase delay
CN202026081U (zh) * 2011-02-25 2011-11-02 深圳雅图数字视频技术有限公司 消火花电路
CN104167622A (zh) * 2013-07-02 2014-11-26 世派电子株式会社 具有供电延时电路的充电系统
CN104494834A (zh) * 2014-11-05 2015-04-08 新誉集团有限公司 无人机混合动力系统与飞控系统的控制方法
CN104875897A (zh) * 2015-05-29 2015-09-02 珠海市双捷科技有限公司 大功率新能源无人机动力系统
CN204925686U (zh) * 2015-08-25 2015-12-30 飞瑞航空科技（江苏）有限公司 一种无人直升机飞行控制集控盒

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107889319A (zh) * 2017-12-14 2018-04-06 李顺华 一种镇流式led灯的驱动电源的过流保护电路
CN109164746A (zh) * 2018-11-14 2019-01-08 上海英恒电子有限公司 一种下电时序控制电路及电源电路
CN109450652A (zh) * 2018-11-26 2019-03-08 珠海世讯科技有限公司 一种knx总线供电电路
CN109378811A (zh) * 2018-12-05 2019-02-22 杭州士腾科技有限公司 基于大电容的防打火控制器
CN110635533A (zh) * 2019-10-07 2019-12-31 深圳市金威源科技股份有限公司 一种带防反接功能的串并联切换电路
CN111897389A (zh) * 2020-08-25 2020-11-06 特变电工西安柔性输配电有限公司 一种基于三极管串联的线性稳压电路
CN114211991B (zh) * 2021-12-15 2023-08-04 四川傲势科技有限公司 用于无线充电无人机的控制单元、无人机及控制方法
CN114211991A (zh) * 2021-12-15 2022-03-22 沃飞长空科技(成都)有限公司 用于无线充电无人机的控制单元、无人机及控制方法
CN114368485A (zh) * 2022-03-18 2022-04-19 珠海奕博科技有限公司 一种微型无人机控制电路
CN114368485B (zh) * 2022-03-18 2022-06-17 珠海奕博科技有限公司 一种微型无人机控制电路
CN115378336A (zh) * 2022-08-25 2022-11-22 湘潭大学 基于场效应管导通电阻采样电路的电机控制装置及方法
CN115378251A (zh) * 2022-08-30 2022-11-22 东风电驱动系统有限公司 一种直流电源控制电路及装置
US12597766B2 (en) * 2022-11-03 2026-04-07 Jiangsu Dongcheng Tools Technology Co., Ltd Anti-sparking method for power tool, and control device, and computer-readable storage medium
CN116243215A (zh) * 2022-12-21 2023-06-09 深圳市乐目通讯有限公司 一种电器插接防火花检测方法、装置、系统及存储介质
CN116634087A (zh) * 2023-05-10 2023-08-22 深圳市中科创激光技术有限公司 一种hdmi接口电路
CN116927978A (zh) * 2023-07-19 2023-10-24 东方空间技术(山东)有限公司 一种火箭发动机安全机构的控制系统及方法
CN116927978B (zh) * 2023-07-19 2024-02-13 东方空间技术(山东)有限公司 一种火箭发动机安全机构的控制系统及方法
CN117543753A (zh) * 2023-10-27 2024-02-09 深圳壹磁智控有限公司 一种上电防打火及放电电路

Also Published As

Publication number Publication date
CN107078640B (zh) 2018-12-07
CN107078640A (zh) 2017-08-18

Similar Documents

Publication Publication Date Title
WO2017128113A1 (zh) 电源控制电路、电子调速器、无人飞行器及控制方法
CN205544915U (zh) 电源控制电路、电子调速器及无人飞行器
CN110880737B (zh) 一种充电芯片及其过压保护电路和便携式电子设备
CN113690966B (zh) 开关电路、电池管理系统、电池包、用电设备及控制方法
CN105553246B (zh) 上下电驱动电路及其控制方法
CN105322522A (zh) 直流电源的浪涌电流抑制方法及电路
CN101505055A (zh) 有源浪涌电流控制电路
CN110581541A (zh) 一种隔离控制的浪涌电流抑制电路
CN206542179U (zh) 一种负载过流过压保护电路
CN204992556U (zh) 一种可快速关断的电压电流浪涌抑制电路
CN108711842B (zh) 放电装置
CN107565528A (zh) 一种抑制浪涌电流的电路结构
CN104753329A (zh) 一种大功率开关电源软启动电路
CN113541454A (zh) 开关电源控制电路、开关电源的控制方法及装置
CN108512191B (zh) 浪涌保护电路、电子设备及电路的浪涌防护方法
CN215268059U (zh) 一种小型化的开关机及浪涌电流保护电路
CN103683881B (zh) 加快电源下电速度的电路
CN107959324B (zh) 航天器电源系统储能电池放电开关电路
CN110855170A (zh) 光伏逆变器及电容放电电路
CN109155626B (zh) 供电控制装置
CN103972859A (zh) 过压保护电路
CN210380344U (zh) 供电电路以及智能照明装置
CN214101179U (zh) 一种降低开机浪涌功率管损耗的控制开关
CN211557136U (zh) 恒流放电电路及保护装置
CN116979493A (zh) 用于设备的浪涌抑制电路

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 16887000

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 16887000

Country of ref document: EP

Kind code of ref document: A1