WO2017128052A1

WO2017128052A1 - Unmanned aerial vehicle and electrical motor control chip and electronic governor thereof

Info

Publication number: WO2017128052A1
Application number: PCT/CN2016/072219
Authority: WO
Inventors: 蓝求; 周长兴
Original assignee: 深圳市大疆创新科技有限公司
Priority date: 2016-01-26
Filing date: 2016-01-26
Publication date: 2017-08-03
Also published as: CN107078677A

Abstract

An unmanned aerial vehicle and an electrical motor control chip and an electronic governor thereof. The electrical motor control chip comprises: an encapsulation case (11), an analogue peripheral circuit (21) encapsulated in the encapsulation case (11), an analogue-to-digital conversion circuit (22), a micro-control unit (23), an MOSFET driving circuit (24) and a multi-mode power management circuit (25). By integrating the analogue peripheral circuit (21), the analogue-to-digital conversion circuit (22), the micro-control unit (23), the MOSFET driving circuit (24) and the multi-mode power management circuit (25) into a chip, the problem that a connection relationship between chips is unstable, caused by many solder joints when a plurality of chips are interconnected, can be avoided.

Description

Unmanned aerial vehicle and its motor control chip, electronic governor

Technical field

The invention relates to a control element of an unmanned aerial vehicle, in particular to a motor control chip, an electronic governor and an aircraft of an unmanned aerial vehicle.

Background technique

With the rapid development of electronic technology and communication technology, more and more aircraft, robots, and the like are being manufactured. The electronic governor is the component of the motor used to drive the aircraft, while the chip for motor control is an important core component of the electronic governor.

In the prior art, for each rotor in the aircraft, a control chip for controlling the rotational speed of the motor, a voltage management chip for supplying power to the control chip, and a MOSFET driving chip for supplying a driving signal to the motor are disposed on the connection with the rotor. In the lumen of the arm. The control chip is connected to the voltage management chip. Further, the voltage management chip is also connected to the MOSFET driving chip. However, the connection relationship between the control chip, the voltage management chip, and the MOSFET driving chip causes the connection line between the chips to be complicated. There are many solder joints, which tends to cause unstable connection between the chips, which affects the normal use of the aircraft.

Summary of the invention

In view of the above-mentioned deficiencies in the prior art, the present invention provides a connection between the control chip, the voltage management chip, and the MOSFET driver chip in the prior art, which results in a complicated connection line between the chips and more solder joints. It is easy to cause the connection relationship between the chips to be unstable, thereby affecting the problem of normal use of the aircraft.

A first aspect of the invention provides a motor control chip comprising:

a package shell having a plurality of pins, the plurality of pins including a power pin and a signal output pin, and a plurality of analog signal input pins;

An analog peripheral circuit, an analog-to-digital conversion circuit, a micro control unit MCU, a MOSFET driving circuit, and a multi-mode power management circuit encapsulated in the package;

The analog peripheral circuit is configured to collect a motor running signal;

The input end of the multi-mode power management circuit is electrically connected to the power pin, and the multi-mode power management circuit is further electrically connected to an analog peripheral circuit, an analog-to-digital conversion circuit, a micro control unit MCU, and a MOSFET driving circuit. connection;

The analog peripheral circuit is electrically connected to the analog-to-digital conversion circuit, the analog-to-digital conversion circuit is electrically connected to the micro control unit MCU, and the micro control unit MCU is electrically connected to an input end of the MOSFET driving circuit;

An output end of the MOSFET driving circuit is electrically connected to the analog signal output pin for outputting a driving signal to the MOSFET circuit;

The analog peripheral circuit is electrically connected to one of the analog signal input pins for receiving an analog signal external to the control chip.

A second aspect of the present invention provides an electronic governor comprising: a motor control chip of an aircraft and a MOSFET circuit;

Wherein the MOSFET circuit is connected between the motor control chip and the motor;

The motor control chip of the aircraft includes: a package shell, the package shell is provided with a plurality of pins, and the plurality of pins comprise a power pin and a signal output pin and a plurality of analog signal input pins;

The analog peripheral circuit is configured to collect a motor running signal;

An output end of the MOSFET driving circuit is electrically connected to the analog signal output pin for outputting a driving signal to the MOSFET circuit; the analog peripheral circuit is electrically connected to one of the analog signal input pins for receiving The analog signal external to the control chip.

A third aspect of the present invention provides an unmanned aerial vehicle comprising: an electronic governor and a motor coupled to the electronic governor, the electronic governor comprising: a motor control chip of the aircraft and MOSFET circuit

The analog peripheral circuit is configured to collect a motor running signal;

The unmanned aerial vehicle of the invention and the motor control chip and the electronic governor thereof are integrated in the motor control chip, the analog peripheral circuit, the analog-to-digital conversion circuit, the micro control unit MCU, the MOSFET drive circuit and the multi-mode power management circuit In the chip, compared with the plurality of chips of the prior art, the circuit is simplified, and the problem that the plurality of chips in the prior art are connected to each other when the electrodes are connected to each other is avoided, thereby causing unstable connection relationship between the chips.

A fourth aspect of the present invention provides a motor control chip for an aircraft, the circuit of the internal control package of the motor control chip comprising:

An analog peripheral circuit for collecting motor operating signals;

An analog to digital conversion circuit for converting an analog signal to a digital signal;

a MOSFET driving circuit for driving the MOSFET circuit;

a multi-mode power management circuit for outputting multiple voltages;

a micro control unit MCU communicably connected to the multi-mode power management circuit, the analog-to-digital conversion circuit, and the MOSFET driving circuit;

Wherein the multi-mode power management circuit supplies power to the analog peripheral circuit, the analog-to-digital conversion circuit, the MOSFET driving circuit, and the micro control unit MCU, and the micro control unit MCU passes the multi-mode The power management circuit controls the order in which the analog peripheral circuit, the analog to digital conversion circuit, and the MOSFET driving circuit supply power.

A fifth aspect of the invention provides an electronic governor comprising: a motor control chip of an aircraft and a MOSFET circuit;

The circuit encapsulated in the motor control chip includes:

An analog peripheral circuit for collecting motor operating signals;

a MOSFET driving circuit for driving the MOSFET circuit;

a multi-mode power management circuit for outputting multiple voltages;

A sixth aspect of the present invention provides an unmanned aerial vehicle comprising: an electronic governor and a motor coupled to the electronic governor, the electronic governor comprising: a motor control chip of the aircraft and a MOSFET circuit;

The package circuit inside the motor control chip of the aircraft includes:

An analog peripheral circuit for collecting motor operating signals;

a MOSFET driving circuit for driving the MOSFET circuit;

a multi-mode power management circuit for outputting multiple voltages;

Wherein the multi-mode power management circuit supplies power to the analog peripheral circuit, the analog-to-digital conversion circuit, the MOSFET driving circuit, and the micro control unit MCU, and the micro control The unit MCU controls the order of power supply of the analog peripheral circuit, the analog-to-digital conversion circuit, and the MOSFET driving circuit through the multi-mode power management circuit.

DRAWINGS

1 is a schematic structural diagram of a motor control chip of an aircraft according to Embodiment 1 of the present invention;

2 is a schematic structural diagram of a motor control chip of an aircraft according to Embodiment 2 of the present invention;

3 is a schematic structural diagram of a differential amplifier and a mosfet circuit according to Embodiment 3 of the present invention;

4 is a schematic structural diagram of a motor control chip of an aircraft according to Embodiment 4 of the present invention;

5 is a schematic structural diagram of a motor control chip of an aircraft according to Embodiment 5 of the present invention;

6 is a schematic structural diagram of a motor control chip of an aircraft according to Embodiment 6 of the present invention;

7 is a schematic structural diagram of a motor control chip of an aircraft according to Embodiment 7 of the present invention;

8 is a schematic structural diagram of a motor control chip of an aircraft according to Embodiment 8 of the present invention;

9 is a schematic structural diagram of a motor control chip of an aircraft according to Embodiment 9 of the present invention;

FIG. 10 is a schematic structural diagram of a motor control chip of an aircraft according to Embodiment 10 of the present invention.

Reference mark:

11-package; 21- analog peripheral circuit;

22-Analog-to-digital conversion circuit; 23-micro control unit;

24-MOSFET drive circuit; 25-multi-mode power management circuit;

31-power pin; 32-signal output pin;

211-differential amplifier; 212-three-way comparator;

33- analog signal input pin; 331- analog signal input pin;

34-internal reference voltage pin; 332-analog signal input pin;

333-analog signal input pin; 26-pulse width modulation generator;

241-voltage amplifying circuit; 27-temperature sensing circuit;

322-upper bridge gate driver bootstrap source input pin; 325-upper bridge gate drive source pin;

323-upper bridge gate drive pin; 324-bridge gate drive pin;

251-Switch circuit controller.

detailed description

Some embodiments of the present invention are described in detail below with reference to the accompanying drawings. The features of the embodiments and examples described below can be combined with each other without conflict.

Embodiment 1

The present embodiment provides a motor control chip of an aircraft. FIG. 1 is a schematic structural diagram of a motor control chip of an aircraft according to Embodiment 1 of the present invention. As shown in FIG. 1 , the motor control chip of the aircraft includes:

The package housing 11, the analog peripheral circuit 21 encapsulated in the package housing 11, the analog to digital converter (ADC) 22, the micro control unit MCU23 (Microcontroller Unit, MCU for short, MOSFET (Metal) An Oxide-Semiconductor Field-Effect Transistor (referred to as MOSFET) drive circuit 24 and a multi-mode power management circuit 25.

Specifically, the package housing 11 is provided with a plurality of pins, wherein the plurality of pins include a power pin 31 and a signal output pin 32 and a plurality of analog signal input pins 33. It should be noted that only two analog signal input pins 33 are schematically shown in FIG. 1, but the number and setting positions of the analog signal input pins 33 are not limited thereto.

The analog peripheral circuit 21 is electrically connected to one of the analog signal input pins, for example, can be electrically connected to the analog signal input pin 33 for receiving an analog signal external to the control chip. Specifically, the analog peripheral circuit 21 is configured to collect a motor operation signal. Specifically, for example, the motor operation signal may include one or more signals of a motor speed signal, a motor steering signal, and the like.

The output signal of the analog peripheral circuit 21 is an analog signal, the analog peripheral circuit 21 is electrically connected to the analog-to-digital conversion circuit ADC22, and the analog-to-digital conversion circuit ADC22 can convert the analog signal output from the analog peripheral circuit 21 into a digital signal.

Further, the analog-to-digital conversion circuit ADC22 is electrically connected to the micro control unit MCU23, and the analog-to-digital conversion circuit ADC22 transmits the converted digital signal to the micro control unit MCU23.

It should be noted that the analog-to-digital conversion circuit ADC22 is not limited to converting only the analog signal outputted by the analog peripheral circuit 21 into a digital signal, and may also convert the analog signal outputted by other circuits except the analog peripheral circuit 21 in the chip. For digital signals.

Further, in order to control the mosfet circuit (not shown) outside the chip to be turned on, the micro control unit MCU23 is electrically connected to the input end of the MOSFET drive circuit 24, and the micro control unit MCU23 outputs a control signal to cause the MOSFET drive circuit 24 to drive the mosfet circuit. Open. Wherein, the MOSFET driving circuit 24 can be used for connecting with the mosfet circuit for using the micro control unit MCU23 The output control signal is voltage amplified to drive the mosfet circuit to turn on.

The output of the MOSFET drive circuit 24 is electrically coupled to the signal output pin 32 for outputting a drive signal to the MOSFET circuit, wherein the MOSFET drive signal is used to drive the MOSFET circuit on or off, optionally, the MOSFET circuit One or more metal-oxide semiconductor field effect transistors are included.

When the motor control chip of the aircraft provided in this embodiment is in operation, the analog peripheral circuit 21 receives an analog signal external to the chip, and the specific analog signal may be an operation signal of the motor, for example, may be a motor speed signal, a motor steering One or more signals such as signals, the analog peripheral circuit 21 inputs the running analog signal of the motor to the analog-to-digital conversion circuit ADC 22. The analog-to-digital conversion circuit ADC 22 converts the running analog signal of the motor into an operating digital signal of the motor and outputs it to the micro control unit MCU23. The micro control unit MCU23 can judge the current running condition of the motor according to the running digital signal of the motor, and then output the control signal to control one or more of the rotation speed of the motor and the steering of the motor through the opening or closing of the mosfet circuit. Since the driving mosfet circuit requires a large instantaneous current, and the current of the control signal outputted by the micro control unit MCU23 is insufficient to drive the mosfet circuit, the micro control unit MCU23 outputs a control signal to the MOSFET driving circuit, and the current of the control signal is passed through the MOSFET driving circuit. Amplification is performed to drive the opening of the mosfet circuit.

Of course, the analog signal external to the chip received by the analog peripheral circuit 21 may not be the running signal of the motor, for example, one or more of a timing signal outputted by a crystal external to the chip and a temperature signal external to the chip. That is, the micro control unit MCU 23 may not control the mosfet circuit based on the signal transmitted from the analog peripheral circuit 21.

In addition, since the analog peripheral circuit 21, the analog-to-digital conversion circuit 22, the micro control unit MCU23, and the MOSFET drive circuit 24 require different voltages during normal operation, the multi-mode power management circuit 25 is an analog peripheral circuit 21, and a modulus. The conversion circuit 22, the micro control unit MCU 23, and the MOSFET drive circuit 24 supply power, and different voltages are provided according to the different requirements of the above circuits.

Specifically, the input end of the multi-mode power management circuit 25 is electrically connected to the power pin 31, and the multi-mode power management circuit 25 can pass through the power pin 31 and a power supply unit external to the chip, such as a battery or the like (not shown in the figure). )connection.

The multi-mode power management circuit 25 is also electrically connected to the analog peripheral circuit 21, the analog-to-digital conversion circuit 22, the micro control unit MCU23, and the MOSFET drive circuit 24, respectively, so as to be respectively to the analog peripheral circuit 21, the analog-to-digital conversion circuit 22, and the micro Control unit MCU23 and MOSFET drive Road 24 output voltage.

For example, multi-mode power management circuit 25 provides a 3.3V supply voltage for analog peripheral circuit 21, a 2.5V reference voltage for analog-to-digital conversion circuit ADC22, and a 1.8V core operating voltage for micro-control unit MCU 203. .

The motor control chip of the aircraft provided in this embodiment integrates the analog peripheral circuit 21, the analog-to-digital conversion circuit 22, the micro control unit MCU23, the MOSFET drive circuit 24 and the multi-mode power management circuit 25 in one chip, and the prior art Compared with the plurality of chips, the circuit is simplified, and the problem that the plurality of chips in the prior art are connected to each other when the electrodes are connected to each other is avoided, thereby causing unstable connection relationship between the chips. Since the integrated chip is mounted in the inner cavity of the aircraft connecting arm, the volume of the inner cavity of the connecting arm can be reduced when the aircraft is designed, thereby making the aircraft more compact and lightweight.

Embodiment 2

2 is a schematic structural diagram of a motor control chip of an aircraft according to Embodiment 2 of the present invention. As shown in FIG. 2, on the basis of the embodiment shown in FIG. 1, the analog peripheral circuit 21 can adopt different circuit structures to implement the same. Specific features. Figure 2 provides a possible structure of the analog peripheral circuit 21, but is not intended to be limiting.

The analog peripheral circuit 21 may include a differential amplifier 211 for collecting an operating current signal of the motor, wherein an input of the differential amplifier 211 is connected to one of the analog signal input pins 331 for receiving a voltage signal of the motor 5. The output of the differential amplifier 211 is electrically coupled to the analog to digital conversion circuit ADC22.

Optionally, the running current signal of the motor can be a motor speed signal and a turn signal.

An input terminal of the differential amplifier 211 is connected to one of the analog signal input pins 331 for receiving the voltage signal of the motor 5 through the analog signal input pin 331.

Specifically, the analog signal input pin 331 is connected to the motor 5 through the mosfet circuit 4, thereby receiving the voltage signal of the motor 5.

It should be noted that the analog signal input pin 331 in this embodiment may be the same pin or the analog pin input pin 33 in the first embodiment.

The other input terminal of the differential amplifier 211 is connected to an internal reference voltage, and the differential amplifier 211 acquires an analog differential signal of the voltage signal sent by the motor 5 and the internal reference voltage, and the analog difference is After the sub-signal is amplified and shaped, the amplified analog differential signal is sent to the analog-to-digital conversion circuit ADC22, so that the analog-to-digital conversion circuit ADC22 converts the analog differential signal into a digital signal.

The internal reference voltage is connected to the analog peripheral circuit 21 via the internal reference voltage pin 34. In the present embodiment, the internal reference voltage is connected to the differential amplifier 211 through the internal reference voltage pin 34.

Further, the analog-to-digital conversion circuit ADC 22 is electrically connected to the micro control unit MCU 23, and the analog-to-digital conversion circuit ADC22 transmits the converted digital signal to the micro control unit MCU23.

In addition, the differential amplifier 211 is also connected to a multi-mode power management circuit 25 for supplying power to the differential amplifier 211.

The motor control chip of the aircraft in this embodiment receives the voltage signal of the motor 5 by using the differential amplifier 211, and the differential amplifier 211 can suppress the common mode interference well, thereby ensuring the accuracy of the digital signal received by the final micro control unit MCU23. Sex.

Embodiment 3

FIG. 3 is a schematic structural diagram of a differential amplifier and a mosfet circuit according to Embodiment 3 of the present invention. On the basis of the embodiment shown in FIG. 2, it can be understood that the specific structure of the mosfet circuit needs to be compatible with the specific type of the motor 5. Taking FIG. 3 as an example, the motor 5 can be a three-phase motor. Correspondingly, the mosfet circuit includes three mosfet groups connected in series, and the three mosfet groups are respectively connected to the three-phase stator windings of the motor.

Further, one input terminal of the differential amplifier 211 is connected to one of the stator windings of the motor, and the other end of the differential amplifier 211 is connected to the internal reference voltage GND.

Optionally, the differential amplifier 211 collects a voltage signal of the motor through a sampling resistor 10 external to the motor control chip of the aircraft.

Optionally, the voltage signal of the motor can be the speed signal of the motor. Specifically, one end of the sampling resistor 10 is connected between the mosfet circuit 4 and one input terminal of the differential amplifier 211, and the other end of the sampling resistor 10 is connected between the internal reference voltage and the other input terminal of the differential amplifier 211.

Embodiment 4

4 is a schematic structural diagram of a motor control chip of an aircraft according to Embodiment 4 of the present invention, such as As shown in FIG. 4, on the basis of any of the first embodiment to the third embodiment, the analog peripheral circuit 21 can adopt different circuit configurations to realize its specific functions. FIG. 4 provides a possible structure of the analog peripheral circuit 21, but is not intended to be limiting.

The analog peripheral circuit 21 includes a three-way comparator 212 for collecting a commutation signal of the motor. The first input terminal of the three-way comparator 212 is connected to one of the analog signal input pins 332 for receiving the phase end of the motor. Voltage. The other input of the three-way comparator 212 is connected to an internal reference voltage, and the output of the three-way comparator 212 is connected to the micro control unit MCU 23.

It should be noted that the analog signal input pin 332 in this embodiment and the analog signal input pin 33 in the first embodiment may be the same pin or different pins, and the simulation in the second embodiment. The signal input pin 331 can also be the same pin or a different pin.

The three-way comparator 212 compares the difference between the internal reference voltage GND and the phase-end voltage of the motor with a preset threshold to detect a zero-crossing signal of the motor 5, that is, a commutation signal, which is a binary signal. Further, the three-way comparator 212 outputs the binary commutation signal to the micro control unit MCU23.

In addition, the three-way comparator 212 is also coupled to a multi-mode power management circuit 25 for powering the three-way comparator 212.

The motor control chip of the aircraft in this embodiment can accurately detect the commutation signal of the motor 5 through the three-way comparator 212.

Embodiment 5

Based on the above embodiment, FIG. 5 is a schematic structural diagram of a motor control chip of an aircraft according to Embodiment 5 of the present invention. As shown in FIG. 5, the analog peripheral circuit 21 includes a differential amplifier 211 and a three-way comparator 212. For details, the working principles of the differential amplifier 211 and the three-way comparator 212 can be referred to the foregoing embodiments, and details are not described herein again.

Embodiment 6

On the basis of any of the foregoing embodiments 1 to 5, FIG. 6 is a schematic structural diagram of a motor control chip of an aircraft according to Embodiment 6 of the present invention. As shown in FIG. 6, the motor control chip of the aircraft further includes: a Pulse Width Modulation (PWM) generator 26 encapsulated in the package 11 and an input terminal and a micro control unit of the PWM generator 26 The output of the MCU 23 is connected, and the output of the PWM generator 26 is connected to the MOSFET drive circuit 24, which is used to convert the control signal output from the micro control unit MCU23 into a PWM pulse signal.

The micro control unit MCU23 controls the PWM generator 26 to generate PWM pulses with a fixed frequency, a high level, and a pulse width within a preset range. The larger the pulse width of the PWM wave, the higher the rotational speed of the motor can be controlled. Optionally, the preset range of the pulse width can be selected between 1ms and 2ms.

The motor control chip of the aircraft of the present embodiment generates a PWM pulse signal through the PWM generator 26, so that the rotational speed of the motor can be controlled.

Example 7

On the basis of the sixth embodiment, if the voltage intensity of the PWM signal generated by the PWM generator 26 is insufficient to drive the MOSFET circuit outside the chip, the voltage intensity of the PWM signal needs to be amplified.

7 is a schematic structural diagram of a motor control chip of an aircraft according to Embodiment 7 of the present invention. As shown in FIG. 7, the MOSFET driving circuit 24 in the motor control chip of the aircraft includes: a voltage amplifying circuit 241, and an input of the voltage amplifying circuit 241. The terminal is connected to the PWM generator 26, and the voltage amplifying circuit 241 is for amplifying the PWM signal output from the PWM generator 26, and the output terminal of the voltage amplifying circuit 241 is electrically connected to the signal output pin 321.

Since the types of MOSFETs in the MOSFET circuit outside the chip are different, for example, if the MOSFET is an N-type MOSFET, the voltage to turn on the MOSFET needs to be greater than 10V. If the P-type MOSFET can, the voltage to turn on the MOSFET is less than 10V. Therefore, the amplitude of the PWM signal amplified by the voltage amplifying circuit 241 can be specifically designed according to the MOSFET circuit outside the chip.

Example eight

8 is a schematic structural diagram of a motor control chip of an aircraft according to Embodiment 8 of the present invention. As shown in FIG. 8, the motor control chip of the aircraft of the present embodiment further includes The temperature sensing circuit 27 is for detecting the internal temperature of the chip, and the temperature sensing circuit 27 is connected to the multi-mode power management circuit 25 and the analog-to-digital conversion circuit 22, respectively.

Among them, the multi-mode power management circuit 25 supplies power to the temperature sensing circuit 27. The analog-to-digital conversion circuit 22 is configured to convert the analog temperature signal inside the chip collected by the temperature sensing circuit 27 into a digital signal and send it to the micro control unit MCU23.

When the micro control unit MCU23 determines that the chip temperature is too high according to the temperature signal sent by the temperature sensing circuit 27, the multi-mode power management circuit 25 can be controlled to cut off the power supply to the circuit unnecessary for the chip operation, thereby achieving the purpose of lowering the temperature. For example, a circuit that is not necessary for operation may be the analog peripheral circuit 21.

Alternatively, the temperature sensing circuit 27 may include a thermistor or a diode.

The motor control chip of the aircraft in this embodiment can measure the temperature inside the chip through the temperature sensing circuit 27, and can prevent the function abnormality caused by the overheating of the chip.

Example nine

9 is a schematic structural diagram of a motor control chip of an aircraft according to Embodiment 9 of the present invention. As shown in FIG. 9, the motor control chip of the aircraft of this embodiment is shown in FIG. The analog signal output pin 32 further includes: a MOSFET pin connected to the output of the MOSFET drive circuit 24, and the MOSFET pin includes: three upper gate driver bootstrap for receiving a voltage signal of the external bootstrap circuit A source input pin 322, three upper bridge gate drive pins 323 for outputting a drive signal, and three lower bridge gate drive pins 324, three upper bridges for receiving voltage signals of an external bootstrap circuit The gate drives the source pin 325.

It should be noted that, in FIG. 9, the bootstrap source input pin 322, the upper bridge gate drive pin 323, the lower bridge gate drive pin 324, and the upper bridge gate drive source pin 325 are only examples. Sexually draw one, but it does not mean that there is only one pin.

The upper bridge gate drive pin 323 is connected to the upper bridge gate of the mosfet circuit, and the lower bridge gate drive pin 324 is connected to the lower bridge gate of the mosfet circuit.

Example ten

10 is a schematic structural diagram of a motor control chip of an aircraft according to Embodiment 10 of the present invention. On the basis of any of the foregoing Embodiments 1 to 9, as shown in FIG. 10, in the motor control chip of the aircraft of the present embodiment, The multi-mode power management circuit 25 includes a switch circuit controller 251 for dropping out multiple voltages and in communication with the micro control unit MCU 23.

The power supply pin 31 includes a switching power supply controller power supply input pin 311, and the switch circuit controller 251 is electrically connected to the switching power supply controller power supply input pin 311.

The switch circuit controller 251 is connected to the analog peripheral circuit 21, the mode conversion circuit 22, and the micro control unit MCU23 and the MOSFET drive circuit 24, respectively. The micro control unit MCU23 controls the analog peripheral circuit 21 and the mode conversion circuit 22 MOSFET through the switch circuit controller 251. The driving circuit 24 is turned on and off, thereby controlling the power supply sequence of the analog peripheral circuit 21, the mode conversion circuit 22, and the MOSFET driving circuit 24, that is, the startup sequence, so that the mode conversion circuit 22 and the micro control unit MCU23 and the MOSFET driving circuit 24 can be avoided at the same time. The transient voltage or current caused by the startup is too large, resulting in chip failure.

Optionally, the switch circuit controller 251 may be multiple, and the analog peripheral circuit 21, the mode conversion circuit 22, and the micro control unit MCU23 and the MOSFET drive circuit 24 respectively have their corresponding switch circuit controllers 251.

In the motor control chip of the aircraft in this example, the micro control unit MCU23 controls the power supply sequence of the analog peripheral circuit 21, the mode conversion circuit 22, and the MOSFET drive circuit 24 through the switch circuit controller 251, that is, the startup sequence, thereby avoiding the mode conversion circuit. 22 and the micro-control unit MCU23, MOSFET drive circuit 24 simultaneously start the instantaneous voltage or current is too large, resulting in chip failure, to ensure system stability.

Embodiment 11

The embodiment provides an electronic governor including a motor control chip of the aircraft and a MOSFET circuit, wherein the MOSFET circuit is connected between the motor control chip and the motor.

As shown in FIG. 1 , the motor control chip of the aircraft includes: a package shell 11 , an analog peripheral circuit 21 encapsulated in the package shell 11 , an analog to digital converter (ADC) 22 , and a micro control The unit MCU 23 (Microcontroller Unit, MCU for short), the MOSFET (Metal-Oxide-Semiconductor Field-Effect Transistor, MOSFET) drive circuit 24, and the multi-mode power management circuit 25.

The analog peripheral circuit 21 is electrically connected to one of the analog signal input pins, for example, can be electrically connected to the analog signal input pin 33 for receiving an analog signal external to the control chip. Specifically, the analog peripheral circuit 21 is configured to collect a motor running signal. Specifically, the motor running signal may include one or more of a signal such as a motor speed signal and a motor steering signal.

Further, in order to control the mosfet circuit (not shown) outside the chip to be turned on, the micro control unit MCU23 is electrically connected to the input end of the MOSFET drive circuit 24, and the micro control unit MCU23 outputs a control signal to cause the MOSFET drive circuit 24 to drive the mosfet circuit. Open. The mosfet driving circuit 24 can be used for connecting with the mosfet circuit for voltage amplification of the control signal output by the micro control unit MCU23, thereby driving the mosfet circuit to be turned on.

The output of the MOSFET drive circuit 24 is electrically coupled to the signal output pin 32 for outputting a drive signal to the MOSFET circuit, wherein the MOSFET drive signal is used to drive the MOSFET circuit on or off, optionally, the MOSFET circuit A plurality of metal-oxide semiconductor field effect transistors are included.

When the motor control chip of the aircraft provided in this embodiment is in operation, the analog peripheral circuit 21 receives an analog signal external to the chip, and the specific analog signal may be an operation signal of the motor, for example, may be a motor speed signal, a motor steering One or more of the signals, the analog peripheral circuit 21 inputs the operational analog signal of the motor to the analog to digital conversion circuit ADC22. The analog-to-digital conversion circuit ADC22 converts the running analog signal of the motor into an operating digital signal of the motor and outputs it to the micro control unit MCU23. The micro control unit MCU23 can judge the current running condition of the motor according to the running digital signal of the motor, and then output the control signal to control one or more of the rotation speed of the motor and the steering of the motor through the opening or closing of the mosfet circuit. Since the driving mosfet circuit requires a large instantaneous current, the current of the control signal output by the micro control unit MCU23 is insufficient to drive the mosfet circuit, therefore, The micro control unit MCU23 outputs a control signal to the MOSFET drive circuit, and the current of the control signal is amplified by the MOSFET drive circuit to drive the opening of the mosfet circuit.

In addition, since the analog peripheral circuit 21, the analog-to-digital conversion circuit 22, the micro control unit MCU23, and the MOSFET drive circuit 24 require different voltages during normal operation, the multi-mode power management circuit 25 is an analog peripheral circuit 21, and a modulus. The conversion circuit 22, the micro control unit MCU 23, and the MOSFET drive circuit 24 are powered.

Specifically, the input end of the multi-mode power management circuit 25 is electrically connected to the power pin 31, and the multi-mode power management circuit 25 can be connected to a power supply unit external to the chip, such as a battery (not shown), through the power pin 31.

The multi-mode power management circuit 25 is also electrically connected to the analog peripheral circuit 21, the analog-to-digital conversion circuit 22, the micro control unit MCU23, and the MOSFET drive circuit 24, respectively, so as to be respectively to the analog peripheral circuit 21, the analog-to-digital conversion circuit 22, and the micro The control unit MCU 23 and the MOSFET drive circuit 24 output voltages.

For example, multi-mode power management circuit 25 provides a 3.3V supply voltage for analog peripheral circuit 21, a 2.5V reference voltage for analog-to-digital conversion circuit ADC22, and a 1.8V core operating voltage for micro-control unit MCU203.

In the electronic governor provided in this embodiment, the analog peripheral circuit 21, the analog-to-digital conversion circuit 22, the micro control unit MCU23, the MOSFET drive circuit 24, and the multi-mode power management circuit 25 are integrated in one chip, and the prior art Compared with the plurality of chips, the circuit is simplified, and the problem that the plurality of chips in the prior art are connected to each other when the electrodes are connected to each other is avoided, thereby causing unstable connection relationship between the chips. Moreover, since the integrated chip is employed, the volume and weight of the electronic governor are reduced. Since the electronic governor is mounted in the inner cavity of the aircraft connecting arm, the volume of the inner cavity of the connecting arm can be reduced when the aircraft is designed, thereby making the aircraft more compact and lightweight.

Example twelve

On the basis of the embodiment shown in FIG. 1, the analog peripheral circuit 21 can adopt different circuit structures. To achieve its specific function. Figure 2 provides a possible structure of the analog peripheral circuit 21, but is not intended to be limiting. As shown in FIG. 2, in the electronic governor provided in this embodiment, the analog peripheral circuit 21 may include: a differential amplifier 211 for collecting an operating current signal of the motor, wherein an input terminal of the differential amplifier 211 is used for An analog signal input pin 331 is connected for receiving a voltage signal of the motor 5, and an output of the differential amplifier 211 is electrically connected to the analog-to-digital conversion circuit ADC22.

Specifically, an input terminal of the differential amplifier 211 is connected to one of the analog signal input pins 331 for receiving the voltage signal of the motor 5 through the analog signal input pin 331. Specifically, the analog signal input pin 331 passes through the mosfet circuit. 4 is connected to the motor 5 to receive the voltage signal of the motor 5.

It should be noted that the analog signal input pin 331 in this embodiment and the analog signal input pin 33 in the eleventh embodiment may be the same pin or different pins.

The other input end of the differential amplifier 211 is connected to an internal reference voltage, and the differential amplifier 211 acquires an analog differential signal between the voltage signal sent by the motor 5 and the internal reference voltage, and the amplified differential signal is amplified and shaped, and then amplified. The analog differential signal is sent to analog to digital conversion circuit ADC22 to cause analog to digital conversion circuit ADC22 to convert the analog differential signal to a digital signal.

In the electronic governor provided in this embodiment, by using the differential amplifier 211 to receive the voltage signal of the motor 5, the differential amplifier 211 can well suppress the common mode interference, thereby ensuring the accuracy of the digital signal received by the final micro control unit MCU23. Sex.

Example thirteen

As shown in FIG. 3, on the basis of the embodiment shown in FIG. 2, it can be understood that the specific structure of the mosfet circuit needs to be adapted to the specific type of the motor 5. Take Figure 3 as an example, where the motor 5 can The three-phase motor, correspondingly, the mosfet circuit comprises three mosfet groups connected in series, and the three mosfet groups are respectively connected to the three-phase stator windings of the motor.

Embodiment 14

As shown in FIG. 4, on the basis of any one of the eleventh to thirteenth embodiments, the analog peripheral circuit 21 can adopt different circuit structures to realize its specific functions. FIG. 4 provides a possible structure of the analog peripheral circuit 21, but is not intended to be limiting.

The analog peripheral circuit 21 includes a three-way comparator 212 for collecting a commutation signal of the motor. The first input terminal of the three-way comparator 212 is connected to one of the analog signal input pins 332 for receiving the phase end of the motor. The voltage, the other input of the three-way comparator 212 is connected to the internal reference voltage, and the output of the three-way comparator 212 is connected to the micro control unit MCU23.

It should be noted that the analog signal input pin 332 in this embodiment may be the same pin or the analog pin input pin 33 in the eleventh embodiment, and may be different pins. The analog signal input pin 331 can also be the same pin or a different pin.

In this embodiment, the commutation signal of the motor 5 can be accurately detected by the three-way comparator 212.

Example fifteen

Based on the above embodiment, as shown in FIG. 5, the analog peripheral circuit 21 includes a differential amplifier 211 and a three-way comparator 212. For details, the working principles of the differential amplifier 211 and the three-way comparator 212 can be referred to the foregoing embodiments, and details are not described herein again.

Example sixteen

On the basis of the above-mentioned Embodiment 11 to Embodiment 15, as shown in FIG. 6, in the electronic governor provided in this embodiment, the motor control chip of the aircraft further includes: pulse width modulation encapsulated in the package housing 11. A PWM (Pulse Width Modulation) PWM 26, an input of the PWM generator 26 is connected to an output of the micro control unit MCU23, an output of the PWM generator 26 is connected to the MOSFET drive circuit 24, and a PWM generator is used to The control signal output from the control unit MCU 23 is converted into a PWM pulse signal.

In the electronic governor provided in this embodiment, the motor control chip of the aircraft generates a PWM pulse signal through the PWM generator 26, so that the rotational speed of the motor can be controlled.

Example seventeen

On the basis of the sixteenth embodiment, if the voltage intensity of the PWM signal generated by the PWM generator 26 is insufficient to drive the MOSFET circuit outside the chip, it is necessary to amplify the voltage intensity of the PWM signal.

As shown in FIG. 7, the MOSFET driving circuit 24 in the motor control chip of the aircraft includes a voltage amplifying circuit 241, an input terminal of the voltage amplifying circuit 241 is connected to the PWM generator 26, and a voltage amplifying circuit 241 is used for the PWM generator 26. The output PWM signal is amplified, and the output of the voltage amplifying circuit 241 is electrically connected to the signal output pin 321.

Since the types of MOSFETs in the MOSFET circuit outside the chip are different, for example, if the MOSFET is an N-type MOSFET, the voltage to turn on the MOSFET needs to be greater than 10V. If the P-type MOSFET can, the voltage to turn on the MOSFET is less than 10V. Therefore, the amplitude of the PWM signal amplified by the voltage amplifying circuit 241 can be based on the MOSFET circuit outside the chip. Designed specifically.

Example 18

On the basis of any of the above-mentioned Embodiments 11 to 17, as shown in FIG. 8, the motor control chip of the aircraft of the present embodiment further includes: a temperature sensing circuit 27, and the temperature sensing circuit 27 is used. The internal temperature of the chip is detected, and the temperature sensing circuit 27 is connected to the multi-mode power management circuit 25 and the analog-to-digital conversion circuit 22, respectively.

In the electronic governor provided in this embodiment, the temperature inside the chip can be measured by the temperature sensing circuit 27 in the chip, and the function abnormality caused by the overheating of the chip can be prevented.

Example 19

On the basis of any of the above-mentioned Embodiments 11 to 18, as shown in FIG. 9, in the motor control chip of the aircraft of the electronic governor provided by the embodiment, the analog signal output pin 32 further includes : a MOSFET pin connected to the output of the MOSFET drive circuit 24, the MOSFET pin includes: three upper gate driver drivers for receiving the voltage signal of the external bootstrap circuit, a bootstrap source input pin 322, for output driving The three upper bridge gate drive pins 323 of the signal, and three lower bridge gate drive pins 324, three upper bridge gate drive source pins 325 for receiving the voltage signals of the external bootstrap circuit.

Wherein, the upper bridge gate drive pin 323 is connected to the upper bridge gate of the mosfet circuit, and the lower bridge gate Drive pin 324 is coupled to the lower bridge gate of the mosfet circuit.

Example twenty

As shown in FIG. 10, in the motor control chip of the aircraft of the electronic governor of the present embodiment, the multi-mode power management circuit 25 is included in the motor control chip of the aircraft of the electronic governor of the present embodiment. A switch circuit controller 251 that separates multiple voltages and is communicatively coupled to the micro control unit MCU23.

The switch circuit controller 251 is connected to the analog peripheral circuit 21, the mode conversion circuit 22, and the micro control unit MCU23 and the MOSFET drive circuit 24, respectively. The micro control unit MCU23 controls the analog peripheral circuit 21 and the mode conversion circuit 22 MOSFET through the switch circuit controller 251. The driving circuit 24 is turned on and off, thereby controlling the power supply sequence of the analog peripheral circuit 21, the mode conversion circuit 22, and the micro control unit MCU23 and the MOSFET driving circuit 24, that is, the startup sequence, so that the mode conversion circuit 22 and the micro control unit MCU23 can be avoided. The instantaneous voltage or current caused by the simultaneous startup of the MOSFET driving circuit 24 is too large, resulting in chip failure.

Embodiment 21

The embodiment provides an unmanned aerial vehicle (hereinafter referred to as an aircraft) comprising: an electronic governor and a motor connected to the electronic governor, the electronic governor comprising: a motor control chip of the aircraft and a MOSFET circuit The MOSFET circuit is connected between the motor control chip and the motor.

As shown in FIG. 1 , the motor control chip of the aircraft includes: a package shell 11 , an analog peripheral circuit 21 encapsulated in the package shell 11 , an analog-to-digital conversion circuit ADC 22 , a micro control unit MCU 23 , a MOSFET drive circuit 24 , and Multi-mode power management circuit 25.

The package body 11 is provided with a plurality of pins, wherein the plurality of pins include a power pin 31 and a signal output pin 32 and a plurality of analog signal input pins 33.

The analog peripheral circuit 21 is electrically connected to one of the analog signal input pins, for example, can be electrically connected to the analog signal input pin 33 for receiving an analog signal external to the control chip. Specifically, the analog peripheral circuit 21 is configured to collect a motor running signal.

The analog peripheral circuit 21 is electrically connected to the analog-to-digital conversion circuit ADC22, and the analog-to-digital conversion circuit ADC22 can convert the analog signal output from the analog peripheral circuit 21 into a digital signal.

The specific principles, implementations, and connection relationships of the motor control chip of the aircraft in this embodiment are the same as those in the first embodiment, and are not described herein again.

The unmanned aerial vehicle of the present embodiment integrates the analog peripheral circuit 21, the analog-to-digital conversion circuit 22, the micro control unit MCU23, the MOSFET drive circuit 24, and the multi-mode power management circuit 25 into one chip due to the adopted motor control chip of the aircraft. Compared with the plurality of chips of the prior art, the circuit is simplified, and the problem that the plurality of chips in the prior art are connected to each other when the electrodes are connected to each other is caused to be unstable, thereby causing unstable connection relationship between the chips. Moreover, due to the use of the integrated chip, the size and weight of the electronic governor are reduced. Since the electronic governor is mounted in the inner cavity of the aircraft connecting arm, the volume of the inner cavity of the connecting arm can be reduced when the aircraft is designed, thereby making the aircraft more compact and lightweight.

Example twenty two

As shown in FIG. 2, on the basis of the embodiment shown in FIG. 1, the analog peripheral circuit 21 can adopt different circuit configurations to achieve its specific functions. Figure 2 provides a possible structure of the analog peripheral circuit 21, but is not intended to be limiting. The analog peripheral circuit 21 may include a differential amplifier 211 for collecting an operating current signal of the motor, wherein an input of the differential amplifier 211 is connected to one of the analog signal input pins 331 for receiving a voltage signal of the motor 5. The output of the differential amplifier 211 is electrically coupled to the analog to digital conversion circuit ADC22.

The specific principles, implementations, and connection relationships of the motor control chip of the aircraft in this embodiment are the same as those in the second embodiment, and are not described herein again.

In the aircraft in this embodiment, the motor control chip of the aircraft receives the voltage signal of the motor 5 by using the differential amplifier 211, and the differential amplifier 211 can suppress the common mode interference well, thereby ensuring the digital signal received by the final micro control unit MCU23. The accuracy.

Example twenty-three

As shown in FIG. 3, on the basis of the embodiment shown in FIG. 2, it can be understood that the specific structure of the mosfet circuit needs to be adapted to the specific type of the motor 5. Taking FIG. 3 as an example, the motor 5 can be a three-phase motor. Correspondingly, the mosfet circuit includes three mosfet groups connected in series, and the three mosfet groups are respectively connected to the three-phase stator windings of the motor.

Example twenty four

As shown in FIG. 4, on the basis of any one of Embodiment 21 to Embodiment 23, the analog peripheral circuit 21 includes: a three-way comparator 212 for collecting a commutation signal of the motor, and three The first input of the comparator 21 is connected to one of the analog signal input pins 332 for receiving the phase terminal voltage of the motor, and the other input of the three comparator 212 is connected to the internal reference voltage, and the three comparators The output of 212 is connected to the micro control unit MCU 23.

The specific principle, implementation, and connection relationship of the three-way comparator 212 of the motor control chip of the aircraft in this embodiment are the same as those in the fourth embodiment, and details are not described herein again.

In the aircraft in this embodiment, the three-way comparator 212 of the motor control chip of the aircraft can accurately detect the commutation signal of the motor 5.

Example twenty five

Example twenty six

On the basis of any one of Embodiments 21 to 25, as shown in FIG. 6, the motor control chip of the aircraft further includes: Pulse Width Modulation PWM (Pulse Width) encapsulated in the package 11 Modulation (referred to as PWM) generator 26, the input end of the PWM generator 26 is connected to the output end of the micro control unit MCU23, the output end of the PWM generator 26 is connected to the MOSFET drive circuit 24, and the PWM generator is used to output the micro control unit MCU23. The control signal is converted to a PWM pulse signal.

In the aircraft of this embodiment, the PWM generator 26 of the motor control chip generates a PWM pulse signal so that the rotational speed of the motor can be controlled.

Example twenty seven

On the basis of any one of the twenty-first embodiment to the twenty-sixth embodiment, if the voltage of the PWM signal generated by the PWM generator 26 is insufficient to drive the MOSFET circuit outside the chip, the voltage intensity of the PWM signal needs to be amplified. .

As shown in FIG. 7, the MOSFET driving circuit 24 in the motor control chip of the aircraft includes a voltage amplifying circuit 241, an input terminal of the voltage amplifying circuit 241 is connected to the PWM generator 26, and a voltage amplifying circuit 241 is used to output the PWM generator 26. The PWM signal is amplified, and the output of the voltage amplifying circuit 241 is electrically connected to the signal output pin 321.

The specific principle, the implementation manner, and the connection relationship of the PWM generator of the chip in the aircraft of the present embodiment are the same as those in the seventh embodiment, and details are not described herein again.

Example twenty eight

As shown in FIG. 8, on the basis of any one of the foregoing embodiments, the motor control chip further includes: a temperature sensing circuit 27, and a temperature sensing system. The circuit 27 is for detecting the internal temperature of the chip, and the temperature sensing circuit 27 is connected to the multi-mode power management circuit 25 and the analog-to-digital conversion circuit 22, respectively.

The specific principles, implementations, and connection relationships of the temperature sensing circuit 27 of the chip in the aircraft of the present embodiment are the same as those in the eighth embodiment, and are not described herein again.

Example twenty nine

In the motor control chip of the aircraft of the embodiment, the analog signal output pin 32 further includes: driving with the MOSFET, on the basis of any one of the above-mentioned embodiments 21 to 28 The output of circuit 24 is connected to a MOSFET pin. The MOSFET pin includes three upper gate driver drivers for receiving the voltage signal of the external bootstrap circuit, a bootstrap source input pin 322, and three for outputting the drive signal. The upper bridge gate drive pin 323, and the three lower bridge gate drive pins 324, three upper bridge gate drive source pins 325 for receiving the voltage signals of the external bootstrap circuit.

Example thirty

As shown in FIG. 10, in the aircraft of the present embodiment, the multi-mode power management circuit 25 of the motor control chip of the aircraft is included in the aircraft of the present embodiment, as shown in FIG. A switch circuit controller 251 that outputs a plurality of voltages and is communicatively coupled to the micro control unit MCU 23.

The specific principle, the implementation manner, and the connection relationship of the switch circuit controller 251 of the chip in the aircraft of the present embodiment are the same as those in the tenth embodiment, and details are not described herein again.

The micro control unit MCU23 controls the analog peripheral circuit 21 and the mode through the switch circuit controller 251. The power supply sequence of the conversion circuit 22 and the MOSFET drive circuit 24, that is, the startup sequence, can avoid the chip voltage failure caused by the excessive voltage or current caused by the mode conversion circuit 22 and the micro-control unit MCU23 and the MOSFET drive circuit 24 being simultaneously activated. Ensure the stability of the system.

Embodiment 31

This embodiment provides a motor control chip for an aircraft. In the prior art, the battery is usually connected to the control chip, the voltage management chip, the MOSFET driver chip, etc., and the battery is simultaneously supplied with the control chip, the voltage management chip, and the MOSFET driver chip. At the time of startup, the control chip, the voltage control chip, The MOSFET driver chip is activated at the same time, so the battery needs to provide a high instantaneous current, and the high instantaneous current is easy to cause the system to generate too high heat, and it is easy to cause breakdown failure of each chip.

As shown in FIG. 1 , the circuit of the motor control chip motor control chip of the aircraft includes: an analog peripheral circuit 21 for collecting motor operation signals, an analog-to-digital conversion circuit ADC22 for converting analog signals into digital signals, and a MOSFET driving circuit 24 for driving a MOSFET circuit, a multi-mode power management circuit 25 for outputting multiple voltages, and a micro control unit MCU23 communicably connected to the multi-mode power management circuit 25, the analog-to-digital conversion circuit 22, and the MOSFET driving circuit 24. .

The multi-mode power management circuit 25 supplies power to the analog peripheral circuit 21, the analog-to-digital conversion circuit 22, the MOSFET drive circuit 24, and the micro control unit MCU23, and the micro control unit MCU23 controls the analog peripheral circuit 21 through the multimode power management circuit 25. The order in which the analog-to-digital conversion circuit 22 and the MOSFET drive circuit 24 supply power.

The power supply sequence of the multi-mode power management circuit 25 for supplying power to the analog peripheral circuit 21, the analog-to-digital conversion circuit 22, the MOSFET drive circuit 24, and the micro control unit MCU23 can be changed according to actual needs, and is not limited herein.

The micro control unit MCU23 controls the power supply sequence of the analog peripheral circuit 21, the mode conversion circuit 22, and the MOSFET drive circuit 24 by controlling the on/off of the analog peripheral circuit 21 and the mode conversion circuit 22 MOSFET drive circuit 24, that is, the startup sequence, thereby The transient voltage or current caused by the simultaneous start of the mode conversion circuit 22 and the micro control unit MCU23 and the MOSFET drive circuit 24 is prevented, resulting in chip failure and ensuring system stability.

Example thirty-two

As shown in FIG. 2, on the basis of Embodiment 31, the analog peripheral circuit 21 can adopt different circuit structures to realize its specific functions. Figure 2 provides a possible structure of the analog peripheral circuit 21, but is not intended to be limiting.

The present embodiment provides an analog peripheral circuit 21 of a motor control chip of an aircraft, comprising: a differential amplifier 211 for collecting an operating current signal of the motor, wherein the differential amplifier 211 is configured to receive a voltage signal of the motor and convert the voltage signal The differential analog signal is output to the analog to digital conversion circuit ADC22.

The specific working principle, the implementation manner, and the connection relationship of the differential amplifier 211 in this embodiment are the same as those in the second embodiment, and are not described herein again.

Example thirty three

As shown in FIG. 3, on the basis of the embodiment shown in the thirty-second embodiment, it can be understood that the specific structure of the mosfet circuit needs to be adapted to the specific type of the motor 5. Taking FIG. 3 as an example, the motor 5 can be a three-phase motor. Correspondingly, the mosfet circuit includes three mosfet groups connected in series, and the three mosfet groups are respectively connected to the three-phase stator windings of the motor.

Embodiment thirty four

As shown in FIG. 4, on the basis of any one of Embodiment 31 to Embodiment 33, the analog peripheral circuit 21 can adopt different circuit structures to realize its specific functions. Figure 4 provides a simulation A possible structure of the peripheral circuit 21, but is not limited thereto.

The analog peripheral circuit 21 includes: a three-way comparator 212 for collecting a commutation signal of the motor, the three-way comparator 212 is for receiving the phase terminal voltage of the motor, and also receiving the internal reference voltage, according to the phase terminal voltage and the internal The reference voltage generates a comparison signal, and the three-way comparator 212 outputs the comparison signal to the micro control unit MCU23.

The three-way comparator 212 compares the difference between the internal reference voltage GND and the phase-end voltage of the motor with a preset threshold to generate a comparison signal, and according to the comparison signal, the zero-crossing signal of the motor 5, that is, the commutation signal, can be detected. The commutation signal is a binary signal. Further, the three-way comparator 212 outputs the binary commutation signal to the micro control unit MCU23.

The specific working principle, the implementation manner, and the connection relationship of the differential amplifier 211 in this embodiment are the same as those in the fourth embodiment, and details are not described herein again.

Example thirty-fifth

Example thirty-six

On the basis of any of the foregoing embodiments, the motor control chip of the aircraft of the present embodiment further includes:

The pulse width modulation PWM generator 26 has an input terminal connected to the output of the micro control unit MCU23, an output of the PWM generator 26 connected to the MOSFET drive circuit 24, and a PWM generator 26 for the micro control unit MCU23. The output control signal is converted to a PWM pulse signal.

In the motor control chip of the aircraft of this embodiment, the PWM generator 26 generates a PWM pulse. The signal thus controls the speed of the motor.

Example thirty seven

On the basis of the thirty-sixth embodiment, if the voltage intensity of the PWM signal generated by the PWM generator 26 is insufficient to drive the MOSFET circuit outside the chip, the voltage intensity of the PWM signal needs to be amplified.

As shown in FIG. 7, the MOSFET driving circuit 24 in the motor control chip of the aircraft includes a voltage amplifying circuit 241, an input terminal of the voltage amplifying circuit 241 is connected to the PWM generator 26, and a voltage amplifying circuit 241 is used to output the PWM generator 26. The PWM signal is amplified.

The specific principle and implementation manner of the PWM generator of the motor control chip of the aircraft of the present embodiment are the same as those of the seventh embodiment, and details are not described herein again.

Example thirty eight

On the basis of any of the embodiments 31 to 37, as shown in FIG. 8, the motor control chip of the aircraft of the present embodiment further includes: a temperature sensing circuit 27, and the temperature sensing circuit 27 The temperature sensing circuit 27 is connected to the multi-mode power management circuit 25 and the analog-to-digital conversion circuit 22, respectively, for detecting the internal temperature of the chip.

The specific principle and implementation manner of the temperature sensing circuit 27 of the chip of the aircraft of the present embodiment are the same as those of the eighth embodiment, and details are not described herein again.

The motor control chip in this embodiment can measure the temperature inside the chip through the temperature sensing circuit 27, and can prevent the function abnormality caused by the overheating of the chip.

Example thirty nine

On the basis of any one of the foregoing embodiment 31 to the thirty-eighth embodiment, as shown in FIG. 10, the multi-mode power management circuit of the motor control chip of the aircraft of the embodiment includes: A switch circuit controller 251 that is voltage-connected and communicatively coupled to the MCU 23.

The specific principle and implementation manner of the switch circuit controller 251 of the chip in the aircraft of the present embodiment are the same as those in the tenth embodiment, and details are not described herein again.

The micro control unit MCU23 controls the power supply sequence of the analog peripheral circuit 21, the mode conversion circuit 22, and the MOSFET drive circuit 24 through the switch circuit controller 251, that is, the startup sequence, thereby The transient voltage or current caused by the simultaneous start of the mode conversion circuit 22 and the micro control unit MCU23 and the MOSFET drive circuit 24 is prevented, resulting in chip failure and ensuring system stability.

Example forty

As shown in FIG. 1, the motor control chip of the aircraft includes: an analog peripheral circuit 21 for collecting motor operation signals, an analog-to-digital conversion circuit ADC22 for converting analog signals into digital signals, and a MOSFET drive circuit for driving the MOSFET circuit. 24. A multi-mode power management circuit 25 for outputting multiple voltages, a micro control unit MCU23 communicably coupled to the multi-mode power management circuit 25, the analog-to-digital conversion circuit 22, and the MOSFET drive circuit 24.

Example 41

On the basis of the forty-seventh embodiment, as shown in FIG. 2, the analog peripheral circuit 21 of the electronic governor provided in this embodiment includes: a differential amplifier 211 for collecting an operating current signal of the motor, wherein the differential amplifier 211 It is used to receive the voltage signal of the motor and convert the voltage signal into a differential analog signal output to the analog to digital conversion circuit ADC22.

The specific working principle, implementation manner and connection relationship of the differential amplifier 211 in this embodiment The same as the second embodiment, and details are not described herein again.

Example forty two

Based on the embodiments of the forty-first embodiment and the forty-second embodiment, it can be understood that the specific structure of the mosfet circuit needs to be adapted to the specific type of the motor 5. As shown in FIG. 3, as shown in FIG. 3, the motor 5 can be a three-phase motor. Correspondingly, the mosfet circuit includes three mosfet groups connected in series, and the three mosfet groups are respectively connected to the three-phase stator windings of the motor.

Example forty three

As shown in FIG. 4, on the basis of any one of Embodiment 40 to Embodiment 42, the analog peripheral circuit 21 can adopt different circuit structures to realize its specific functions. FIG. 4 provides a possible structure of the analog peripheral circuit 21, but is not intended to be limiting.

The three-way comparator 212 compares the difference between the internal reference voltage GND and the phase-end voltage of the motor with a preset threshold to generate a comparison signal, and according to the comparison signal, the zero-crossing signal of the motor 5, that is, the commutation signal, can be detected. The commutation signal is a binary signal. Further, the three-way comparator 212 will The binary commutation signal is output to the micro control unit MCU23.

The motor control chip of the aircraft of the electronic governor in this embodiment can accurately detect the commutation signal of the motor 5 through the three-way comparator 212.

Embodiment 44

Example forty five

On the basis of any of the above embodiments to the forty-fourth embodiment, as shown in FIG. 6, the motor control chip of the aircraft of the electronic governor of the embodiment further includes:

In the motor control chip of the aircraft of the electronic governor of the present embodiment, the PWM pulse signal is generated by the PWM generator 26, so that the rotational speed of the motor can be controlled.

Example forty six

On the basis of the forty-fifth embodiment, if the voltage intensity of the PWM signal generated by the PWM generator 26 is insufficient to drive the MOSFET circuit outside the chip, the voltage intensity of the PWM signal needs to be amplified.

As shown in FIG. 7, the MOSFET driving circuit 24 in the motor control chip of the aircraft includes a voltage amplifying circuit 241, and an input end of the voltage amplifying circuit 241 is connected to the PWM generator 26, and is electrically connected. The voltage amplifying circuit 241 is for amplifying the PWM signal output from the PWM generator 26.

The specific principle and implementation manner of the PWM generator of the motor control chip in the electronic governor of the embodiment are the same as those in the seventh embodiment, and are not described herein again.

Example forty seven

On the basis of any of the above embodiments to the forty-sixth embodiment, as shown in FIG. 8, the motor control chip of the aircraft of the electronic governor of the embodiment further includes: a temperature sensing circuit 27, and a temperature. The sensing circuit 27 is for detecting the internal temperature of the chip, and the temperature sensing circuit 27 is connected to the multi-mode power management circuit 25 and the analog-to-digital conversion circuit 22, respectively.

The specific principle and implementation manner of the temperature sensing circuit 27 of the chip of the aircraft are the same as those in the eighth embodiment, and details are not described herein again.

In the electronic governor of the embodiment, the motor control chip can measure the temperature inside the chip through the temperature sensing circuit 27, and can prevent the function abnormality caused by the overheating of the chip.

Example forty eight

On the basis of any of the above embodiments to the forty-seventh embodiment, as shown in FIG. 10, the multi-mode power management circuit of the motor control chip of the aircraft of the present embodiment includes: for dividing the multi-channel voltage And a switch circuit controller 251 that is communicatively coupled to the MCU 23.

The specific principle and implementation manner of the switch circuit controller 251 are the same as those in the tenth embodiment, and details are not described herein again.

The micro control unit MCU23 controls the power supply sequence of the analog peripheral circuit 21, the mode conversion circuit 22, and the MOSFET drive circuit 24, that is, the startup sequence, by the switch circuit controller 251, so that the mode conversion circuit 22 and the micro control unit MCU23 and the MOSFET drive circuit can be avoided. 24 The instantaneous voltage or current caused by simultaneous startup is too large, resulting in chip failure and ensuring system stability.

Example forty-nine

The embodiment provides an unmanned aerial vehicle (hereinafter referred to as an aircraft) comprising: an electronic governor and a motor connected to the electronic governor, the electronic governor comprising: a motor control chip of the aircraft and a MOSFET circuit Wherein the MOSFET circuit is connected between the motor control chip and the motor.

Specifically, as shown in FIG. 1 , the motor control chip of the aircraft includes: an analog peripheral circuit 21 for collecting motor operation signals, an analog-to-digital conversion circuit ADC22 for converting analog signals into digital signals, and a circuit for driving the MOSFET. The MOSFET drive circuit 24, a multi-mode power supply management circuit 25 for outputting multiple voltages, and a micro control unit MCU23 communicably connected to the multi-mode power supply management circuit 25, the analog-to-digital conversion circuit 22, and the MOSFET drive circuit 24.

In the unmanned aerial vehicle provided in this embodiment, the micro control unit MCU23 controls the analog peripheral circuit 21, the mode conversion circuit 22, and the MOSFET drive circuit 24 to control the analog peripheral circuit 21, the mode conversion circuit 22, and the MOSFET drive circuit 24. The power supply sequence, that is, the startup sequence, can avoid the transient voltage or current caused by the mode switching circuit 22 and the micro-control unit MCU23 and the MOSFET driving circuit 24 being simultaneously activated, resulting in chip failure and ensuring the stability of the unmanned aerial vehicle.

Example fifty

Based on the forty-ninth embodiment, the analog peripheral circuit 21 can adopt different circuit configurations to achieve its specific functions. Figure 2 provides a possible structure of the analog peripheral circuit 21, but is not intended to be limiting.

As shown in FIG. 2, in the unmanned aerial vehicle provided in this embodiment, the analog peripheral circuit 21 of the motor control chip of the aircraft includes: a differential amplifier 211 for collecting an operating current signal of the motor, wherein the differential amplifier 211 is configured to receive The voltage signal of the motor is converted into a differential analog signal and output to the analog to digital conversion circuit ADC22.

In the aircraft in this embodiment, the motor control chip of the aircraft adopts a differential amplifier 211. Receiving the voltage signal of the motor 5, the differential amplifier 211 can well suppress the common mode interference, and thus the accuracy of the digital signal received by the final micro control unit MCU23 can be ensured.

Embodiment 51

Example fifty-two

As shown in FIG. 4, on the basis of any of the forty-ninth to fifty-second embodiments, the analog peripheral circuit 21 can adopt different circuit configurations to achieve its specific functions. FIG. 4 provides a possible structure of the analog peripheral circuit 21, but is not intended to be limiting.

The specific working principle, implementation manner and connection relationship of the differential amplifier 211 in this embodiment The same as the fourth embodiment, and details are not described herein again.

In the unmanned aerial vehicle of the embodiment, the motor control chip of the aircraft can accurately detect the commutation signal of the motor 5 through the three-way comparator 212.

Example fifty three

Embodiment fifty four

In the unmanned aerial vehicle of the embodiment, the motor control chip of the aircraft further includes:

In the unmanned aerial vehicle of the embodiment, the motor control chip of the aircraft generates a PWM pulse signal through the PWM generator 26, so that the rotational speed of the motor can be controlled.

Embodiment fifty four

On the basis of the fifty-third embodiment, if the voltage intensity of the PWM signal generated by the PWM generator 26 is insufficient to drive the MOSFET circuit outside the chip, the voltage intensity of the PWM signal needs to be amplified.

In the unmanned aerial vehicle of this embodiment, the specific principle and implementation manner of the PWM generator of the motor control chip are the same as those in the seventh embodiment, and details are not described herein again.

Example fifty five

On the basis of any of the foregoing embodiments of the forty-ninth embodiment to the fifty-fourth embodiment, as shown in FIG. 8, the motor control chip of the unmanned aerial vehicle of the embodiment further includes: a temperature sensing circuit 27, and temperature sensing. The circuit 27 is for detecting the internal temperature of the chip, and the temperature sensing circuit 27 is connected to the multi-mode power management circuit 25 and the analog-to-digital conversion circuit 22, respectively.

In the unmanned aerial vehicle of the embodiment, the motor control chip can measure the temperature inside the chip through the temperature sensing circuit 27, and can prevent the function abnormality caused by the overheating of the chip.

Example fifty six

On the basis of any of the foregoing embodiments of the forty-ninth embodiment to the fifty-fifth embodiment, as shown in FIG. 10, in the unmanned aerial vehicle of the embodiment, the multi-mode power management circuit of the motor control chip includes: A switch circuit controller 251 that outputs a plurality of voltages and is communicatively coupled to the MCU 23.

In the several embodiments provided by the present invention, it should be understood that the related apparatus and method disclosed may be implemented in other manners. For example, the device embodiments described above are merely illustrative. For example, the division of the modules or units is only a logical function division. In actual implementation, 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. In addition, 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 unit described as a separate component may or may not be physically separated, and the component displayed as a unit may or may not be a physical unit, that is, may be located in one place. Or it can be distributed to multiple network elements. Some or all of the units may be selected according to actual needs to achieve the purpose of the solution of the embodiment.

In addition, 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. Based on such understanding, the technical solution of the present invention, which is essential or contributes to the prior art, or all or part of the technical solution, may be embodied in the form of a software product stored in a storage medium. A number of instructions are included to cause 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.

The above is only the embodiment of the present invention, and is not intended to limit the scope of the invention, and the equivalent structure or equivalent process transformation of the present invention and the contents of the drawings may be directly or indirectly applied to other related technologies. The fields are all included in the scope of patent protection of the present invention.

Finally, it should be noted that the above embodiments are merely illustrative of the technical solutions of the present invention, and are not intended to be limiting; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art will understand that The technical solutions described in the foregoing embodiments may be modified, or some or all of the technical features may be equivalently replaced; and the modifications or substitutions do not deviate from the technical solutions of the embodiments of the present invention. range.

Claims

A motor control chip for an aircraft, comprising:

a package shell having a plurality of pins, the plurality of pins including a power pin and a signal output pin, and a plurality of analog signal input pins;

An analog peripheral circuit, an analog-to-digital conversion circuit, a micro control unit MCU, a MOSFET driving circuit, and a multi-mode power management circuit encapsulated in the package;

The analog peripheral circuit is configured to collect a motor running signal;

The input end of the multi-mode power management circuit is electrically connected to the power pin, and the multi-mode power management circuit is further electrically connected to an analog peripheral circuit, an analog-to-digital conversion circuit, a micro control unit MCU, and a MOSFET driving circuit. connection;

The analog peripheral circuit is electrically connected to the analog-to-digital conversion circuit, the analog-to-digital conversion circuit is electrically connected to the micro control unit MCU, and the micro control unit MCU is electrically connected to an input end of the MOSFET driving circuit;

An output end of the MOSFET driving circuit is electrically connected to the analog signal output pin for outputting a driving signal to the MOSFET circuit;

The analog peripheral circuit is electrically connected to one of the analog signal input pins for receiving an analog signal external to the control chip.
The motor control chip for an aircraft according to claim 1, wherein said analog peripheral circuit comprises:

a differential amplifier for collecting an operating current signal of the motor;

The input end of the differential amplifier is connected to one of the analog signal input pins for receiving a voltage signal of the motor, and the output of the differential amplifier is electrically connected to the analog-to-digital conversion circuit ADC.
The motor control chip of the aircraft according to claim 1, wherein the analog peripheral circuit further comprises:

a three-way comparator for collecting a commutation signal of the motor, the first input end of the three-way comparator being connected to one of the analog signal input pins for receiving a phase terminal voltage of the motor, the three-way The other input of the comparator is connected to an internal reference voltage, the output of which is connected to the micro control unit MCU.
The motor control chip of the aircraft according to claim 1, further comprising: a pulse width modulation PWM generator encapsulated in the package housing, an input end of the PWM generator is connected to an output end of the micro control unit MCU, and an output end is connected to the MOSFET driving circuit, and the PWM generator is used The control signal output by the micro control unit MCU is converted into a PWM pulse signal.
The motor control chip of an aircraft according to claim 4, wherein the MOSFET driving circuit comprises:

a voltage amplifying circuit, an input end of the voltage amplifying circuit is connected to the PWM generator, the voltage amplifying circuit is configured to amplify a PWM signal output by the PWM generator, an output end of the voltage amplifying circuit and the The analog signal output pin is electrically connected.
The motor control chip of the aircraft according to claim 1, further comprising:

The temperature sensing circuit is used to detect the internal temperature of the chip, and the temperature sensing circuit is respectively connected to the multi-mode power management circuit and the analog-to-digital conversion circuit.
The motor control chip of an aircraft according to claim 1, wherein the analog signal output pin further comprises: a MOSFET pin connected to an output end of the MOSFET driving circuit, the MOSFET pin comprising:

Three upper bridge gate driver bootstrap source input pins for receiving a voltage signal of an external bootstrap circuit;

Three upper bridge gate drive pins for outputting a drive signal, and three lower bridge gate drive pins;

Three upper bridge gate drive source pins for receiving the voltage signal of the external bootstrap circuit.
The motor control chip of an aircraft according to claim 1, wherein said multi-mode power management circuit comprises a switch circuit controller for dividing a plurality of voltages and communicating with said MCU;

The power pin includes a switching power supply controller power input pin, and the switch circuit controller is electrically connected to the switching power supply controller power input pin.
An electronic governor, comprising: a motor control chip of an aircraft and a MOSFET circuit;

Wherein the MOSFET circuit is connected between the motor control chip and the motor;

The motor control chip of the aircraft includes: a package shell, and the package shell is provided with a plurality of pins, The plurality of pins include a power pin and a signal output pin, and a plurality of analog signal input pins;

An analog peripheral circuit, an analog-to-digital conversion circuit, a micro control unit MCU, a MOSFET driving circuit, and a multi-mode power management circuit encapsulated in the package;

The analog peripheral circuit is configured to collect a motor running signal;

The input end of the multi-mode power management circuit is electrically connected to the power pin, and the multi-mode power management circuit is further electrically connected to an analog peripheral circuit, an analog-to-digital conversion circuit, a micro control unit MCU, and a MOSFET driving circuit. connection;

The analog peripheral circuit is electrically connected to the analog-to-digital conversion circuit, the analog-to-digital conversion circuit is electrically connected to the micro control unit MCU, and the micro control unit MCU is electrically connected to an input end of the MOSFET driving circuit;

An output end of the MOSFET driving circuit is electrically connected to the analog signal output pin for outputting a driving signal to the MOSFET circuit; the analog peripheral circuit is electrically connected to one of the analog signal input pins for receiving The analog signal external to the control chip.
The electronic governor according to claim 9, wherein said analog peripheral circuit comprises: said differential amplifier for collecting an operating current signal of the motor;

The input end of the differential amplifier is connected to one of the analog signal input pins for receiving a voltage signal of a sampling resistor, and an output of the differential amplifier is electrically connected to the analog-to-digital conversion circuit ADC.
The electronic governor according to claim 9, wherein the analog peripheral circuit further comprises:

a three-way comparator for collecting a commutation signal of the motor, the first input end of the three-way comparator being connected to one of the analog signal input pins for receiving a phase terminal voltage of the motor, the three-way The other input of the comparator is connected to an internal reference voltage, the output of which is connected to the micro control unit MCU.
The electronic governor according to claim 9, wherein the motor control chip of the aircraft further comprises:

a pulse width modulation PWM generator encapsulated in the package housing, an input end of the PWM generator is connected to an output end of the micro control unit MCU, and an output end is connected to the MOSFET driving circuit, and the PWM generator is used The control signal output by the micro control unit MCU is converted into a PWM pulse signal.
The electronic governor of claim 12 wherein said MOSFET drive circuit comprises:

a voltage amplifying circuit, an input end of the voltage amplifying circuit is connected to the PWM generator, the voltage amplifying circuit is configured to amplify a PWM signal output by the PWM generator, an output end of the voltage amplifying circuit and the The analog signal output pin is electrically connected.
The electronic governor according to claim 9, wherein the motor control chip of the aircraft further comprises: a temperature sensing circuit encapsulated in the package, the temperature sensing circuit for detecting the internal temperature of the chip, The temperature sensing circuit is respectively connected to the multi-mode power management circuit and the analog to digital conversion circuit.
The electronic governor according to claim 9, wherein the analog signal output pin further comprises: a MOSFET pin connected to an output end of the MOSFET driving circuit, the MOSFET pin comprising:

Three upper bridge gate driver bootstrap source input pins for receiving a voltage signal of an external bootstrap circuit connected to an output terminal of the MOSFET driving circuit, and three upper bridge gate driving leads for outputting a driving signal The pin and the three lower bridge gate drive pins;

Three upper bridge gate drive source pins for receiving the voltage signal of the external bootstrap circuit.
The electronic governor according to claim 9, wherein said multi-mode power management circuit comprises a switch circuit controller for dividing a plurality of voltages and communicating with said MCU;

The power pin includes a switching power supply controller power input pin, and the switch circuit controller is electrically connected to the switching power supply controller power input pin.
An unmanned aerial vehicle, comprising: an electronic governor and a motor connected to the electronic governor, the electronic governor comprising: a motor control chip of the aircraft and a MOSFET circuit;

Wherein the MOSFET circuit is connected between the motor control chip and the motor;

The motor control chip of the aircraft includes: a package shell, the package shell is provided with a plurality of pins, and the plurality of pins comprise a power pin and a signal output pin and a plurality of analog signal input pins;

An analog peripheral circuit, an analog-to-digital conversion circuit, a micro control unit MCU, a MOSFET driving circuit, and a multi-mode power management circuit encapsulated in the package;

The analog peripheral circuit is configured to collect a motor running signal;

The input end of the multi-mode power management circuit is electrically connected to the power pin, and the multi-mode power management circuit is further electrically connected to an analog peripheral circuit, an analog-to-digital conversion circuit, a micro control unit MCU, and a MOSFET driving circuit. connection;

The analog peripheral circuit is electrically connected to the analog-to-digital conversion circuit, the analog-to-digital conversion circuit is electrically connected to the micro control unit MCU, and the micro control unit MCU is electrically connected to an input end of the MOSFET driving circuit;

An output end of the MOSFET driving circuit is electrically connected to the analog signal output pin for outputting a driving signal to the MOSFET circuit;

The analog peripheral circuit is electrically connected to one of the analog signal input pins for receiving an analog signal external to the control chip.
The UAV according to claim 17, wherein said analog peripheral circuit comprises: said differential amplifier for collecting an operating current signal of the motor;

The input end of the differential amplifier is connected to one of the analog signal input pins for receiving a voltage signal of a sampling resistor, and an output of the differential amplifier is electrically connected to the analog-to-digital conversion circuit ADC.
The UAV according to claim 17, wherein the analog peripheral circuit further comprises:

a three-way comparator for collecting a commutation signal of the motor, the first input end of the three-way comparator being connected to one of the analog signal input pins for receiving a phase terminal voltage of the motor, the three-way The other input of the comparator is connected to an internal reference voltage, the output of which is connected to the micro control unit MCU.
The UAV according to claim 17, wherein the motor control chip of the aircraft further comprises:

a pulse width modulation PWM generator encapsulated in the package housing, an input end of the PWM generator is connected to an output end of the micro control unit MCU, and an output end is connected to the MOSFET driving circuit, and the PWM generator is used The control signal output by the micro control unit MCU is converted into a PWM pulse signal.
The UAV according to claim 20, wherein said MOSFET drive circuit comprises:

a voltage amplifying circuit, wherein an input end of the voltage amplifying circuit is connected to the PWM generator, The voltage amplifying circuit is configured to amplify a PWM signal output by the PWM generator, and an output end of the voltage amplifying circuit is electrically connected to the analog signal output pin.
The UAV according to claim 15, wherein the motor control chip of the aircraft further comprises:

The temperature sensing circuit is used to detect the internal temperature of the chip, and the temperature sensing circuit is respectively connected to the multi-mode power management circuit and the analog-to-digital conversion circuit.
The UAV according to claim 15, wherein the analog signal output pin further comprises: a MOSFET pin connected to an output end of the MOSFET driving circuit, the MOSFET pin comprising: Three upper bridge gate driver bootstrap source input pins connected to the output of the MOSFET drive circuit for receiving the voltage signal of the external bootstrap circuit, three upper bridge gate drive pins for outputting the drive signal, And three lower bridge gate drive pins;

Three upper bridge gate drive source pins for receiving the voltage signal of the external bootstrap circuit.
The motor control chip of an aircraft according to claim 15, wherein said multi-mode power management circuit comprises:

a switch circuit controller for dividing a plurality of voltages and communicating with the MCU;

The power pin includes a switching power supply controller power input pin, and the switch circuit controller is electrically connected to the switching power supply controller power input pin.
A motor control chip for an aircraft, characterized in that the circuit of the internal control package of the motor control chip comprises:

An analog peripheral circuit for collecting motor operating signals;

An analog to digital conversion circuit for converting an analog signal to a digital signal;

a MOSFET driving circuit for driving the MOSFET circuit;

a multi-mode power management circuit for outputting multiple voltages;

a micro control unit MCU communicably connected to the multi-mode power management circuit, the analog-to-digital conversion circuit, and the MOSFET driving circuit;

Wherein the multi-mode power management circuit supplies power to the analog peripheral circuit, the analog-to-digital conversion circuit, the MOSFET driving circuit, and the micro control unit MCU, and the micro control unit MCU passes the multi-mode The power management circuit controls the order in which the analog peripheral circuit, the analog to digital conversion circuit, and the MOSFET driving circuit supply power.
The motor control chip for an aircraft according to claim 25, wherein said analog peripheral circuit comprises:

a differential amplifier for collecting an operating current signal of the motor;

The differential amplifier is configured to receive a voltage signal of the motor and convert the voltage signal into a differential analog signal output to the analog to digital conversion circuit ADC.
The motor control chip of an aircraft according to claim 25, wherein the analog peripheral circuit further comprises:

a three-way comparator for collecting a commutation signal of the motor, the three-way comparator for receiving a phase terminal voltage of the motor, and receiving an internal reference voltage, and generating a comparison according to the phase terminal voltage and the internal reference voltage a signal, the three comparators outputting the comparison signal to the micro control unit MCU.
The motor control chip for an aircraft according to claim 25, further comprising:

a pulse width modulation PWM generator, an input of the PWM generator being coupled to an output of the micro control unit MCU, an output coupled to the MOSFET drive circuit, the PWM generator for using the micro control unit MCU The output control signal is converted to a PWM pulse signal.
The motor control chip for an aircraft according to claim 28, wherein said MOSFET drive circuit comprises:

And a voltage amplifying circuit, wherein an input end of the voltage amplifying circuit is connected to the PWM generator, and the voltage amplifying circuit is configured to amplify a PWM signal output by the PWM generator.
The motor control chip for an aircraft according to claim 25, further comprising:

a temperature sensing circuit for detecting an internal temperature of the chip, wherein the temperature sensing circuit is respectively connected to the multi-mode power management circuit and the analog to digital conversion circuit.
The motor control chip of an aircraft according to claim 25, wherein said multi-mode power management circuit comprises:

A switching circuit controller for dividing a plurality of voltages and communicating with the MCU.
An electronic governor, comprising: a motor control chip of an aircraft and a MOSFET circuit;

The circuit encapsulated in the motor control chip includes:

An analog peripheral circuit for collecting motor operating signals;

An analog to digital conversion circuit for converting an analog signal to a digital signal;

a MOSFET driving circuit for driving the MOSFET circuit;

a multi-mode power management circuit for outputting multiple voltages;

a micro control unit MCU communicably connected to the multi-mode power management circuit, the analog-to-digital conversion circuit, and the MOSFET driving circuit;

Wherein the multi-mode power management circuit supplies power to the analog peripheral circuit, the analog-to-digital conversion circuit, the MOSFET driving circuit, and the micro control unit MCU, and the micro control unit MCU passes the multi-mode The power management circuit controls the order in which the analog peripheral circuit, the analog to digital conversion circuit, and the MOSFET driving circuit supply power.
The electronic governor of claim 32 wherein said analog peripheral circuitry comprises:

a differential amplifier for collecting an operating current signal of the motor;

The differential amplifier is configured to receive a voltage signal of the motor and convert the voltage signal into a differential analog signal output to the analog to digital conversion circuit ADC.
The electronic governor of claim 32, wherein the analog peripheral circuit further comprises:

a three-way comparator for collecting a commutation signal of the motor, the three-way comparator for receiving a phase terminal voltage of the motor, and receiving an internal reference voltage, and generating a comparison according to the phase terminal voltage and the internal reference voltage a signal, the three comparators outputting the comparison signal to the micro control unit MCU.
The electronic governor of claim 32, wherein the motor control chip of the aircraft further comprises:

a pulse width modulation PWM generator, an input of the PWM generator being coupled to an output of the micro control unit MCU, an output coupled to the MOSFET drive circuit, the PWM generator for using the micro control unit MCU The output control signal is converted to a PWM pulse signal.
The electronic governor of claim 35, wherein said MOSFET drive circuit comprises:

And a voltage amplifying circuit, wherein an input end of the voltage amplifying circuit is connected to the PWM generator, and the voltage amplifying circuit is configured to amplify a PWM signal output by the PWM generator.
The electronic governor of claim 32, wherein the motor control chip of the aircraft further comprises:

a temperature sensing circuit for detecting an internal temperature of the chip, wherein the temperature sensing circuit is respectively connected to the multi-mode power management circuit and the analog to digital conversion circuit.
The electronic governor of claim 32, wherein said multi-mode power management circuit comprises:

A switching circuit controller for dividing a plurality of voltages and communicating with the MCU.
An unmanned aerial vehicle, comprising: an electronic governor and a motor connected to the electronic governor, the electronic governor comprising: a motor control chip of the aircraft and a MOSFET circuit;

Wherein the MOSFET circuit is connected between the motor control chip and the motor;

The package circuit inside the motor control chip of the aircraft includes:

An analog peripheral circuit for collecting motor operating signals;

An analog to digital conversion circuit for converting an analog signal to a digital signal;

a MOSFET driving circuit for driving the MOSFET circuit;

a multi-mode power management circuit for outputting multiple voltages;

a micro control unit MCU communicably connected to the multi-mode power management circuit, the analog-to-digital conversion circuit, and the MOSFET driving circuit;

Wherein the multi-mode power management circuit supplies power to the analog peripheral circuit, the analog-to-digital conversion circuit, the MOSFET driving circuit, and the micro control unit MCU, and the micro control unit MCU passes the multi-mode The power management circuit controls the order in which the analog peripheral circuit, the analog to digital conversion circuit, and the MOSFET driving circuit supply power.
The UAV according to claim 39, wherein said analog peripheral circuit comprises:

a differential amplifier for collecting an operating current signal of the motor;

The differential amplifier is configured to receive a voltage signal of the motor and convert the voltage signal into a differential analog signal output to the analog to digital conversion circuit ADC.
The UAV according to claim 39, wherein the motor control chip of the aircraft further comprises:

a three-way comparator for collecting a commutation signal of a motor, the three-way comparator for receiving a motor The phase terminal voltage also receives an internal reference voltage, generates a comparison signal according to the phase terminal voltage and the internal reference voltage, and the three-way comparator outputs the comparison signal to the micro control unit MCU.
The UAV according to claim 39, wherein the motor control chip of the aircraft further comprises:

a pulse width modulation PWM generator, an input of the PWM generator being coupled to an output of the micro control unit MCU, an output coupled to the MOSFET drive circuit, the PWM generator for using the micro control unit MCU The output control signal is converted to a PWM pulse signal.
The UAV according to claim 42, wherein said MOSFET driving circuit comprises:

And a voltage amplifying circuit, wherein an input end of the voltage amplifying circuit is connected to the PWM generator, and the voltage amplifying circuit is configured to amplify a PWM signal output by the PWM generator.
The UAV according to claim 39, wherein the motor control chip of the aircraft further comprises:

a temperature sensing circuit for detecting an internal temperature of the chip, wherein the temperature sensing circuit is respectively connected to the multi-mode power management circuit and the analog to digital conversion circuit.
The UAV according to claim 39, wherein said multi-mode power management circuit includes a switch circuit controller for dividing a plurality of voltages and communicating with said MCU.