Flap control system of unmanned aerial vehicle

Abstract

The invention discloses a flap control system for an unmanned aerial vehicle. The flap control system comprises a bus power supply processing and current limiting unit, a control part power supply conversion top power unit, a driving part power supply conversion unit, a control unit, a system power supply acquisition and judgment unit, a signal input and output unit and a power control unit, according to the system, multiple paths of power sources input by the system are integrated, power distribution of the controller meets the power supply relation of the flap control device required by the system, power supply of a driving part and power supply of a control part are isolated, primary and secondary power source voltages and working currents of the system are collected and processed, monitoring is achieved, the reliability is high, power supply is stable, and the reliability is high. And a control instruction of an upper computer can be stably received, so that the steering engine is driven to perform closed-loop motion.

Description

Technical Field

[0001] This application relates to the field of UAV control technology, and particularly to a flap control system for unmanned aircraft. Background Art

[0002] The flap control system is an important component of an unmanned aircraft, used to control the takeoff and landing of the aircraft, and affects the overall performance of the aircraft. The control part of the flap control system is the core of the entire system. How to provide a highly reliable, stable power supply, and an unmanned aircraft flap control system that can stably receive control instructions from the upper computer and drive the servo to perform closed-loop motion is an urgent problem to be solved by those skilled in the art. Summary of the Invention

[0003] This application provides an unmanned aircraft flap control system, which is highly reliable, has a stable power supply, can stably receive control instructions from the upper computer, and thus drives the servo to perform closed-loop motion.

[0004] In view of this, this application provides an unmanned aircraft flap control system, including:

[0005] A bus power supply processing and current limiting unit 01, a control part power conversion top power unit 02, a drive part power conversion unit 03, a control unit 04, a system power supply acquisition and judgment unit 05, a signal input / output unit 06, and a power control unit 07;

[0006] The bus power supply processing and current limiting unit 01 integrates multiple power supply sources and provides a 28V power supply to the control part power conversion top power unit 02, the drive part power conversion unit 03, and the system power supply acquisition and judgment unit 05 respectively;

[0007] The control part power conversion top power unit 02 converts the 28V power supply into the power supply voltages required by the control unit 04 and the signal input / output unit 06, and is connected to the system power supply acquisition and judgment unit 05;

[0008] The drive part power conversion unit 03 converts the 28V power supply into the power supply voltage required by the power control unit 07, and is connected to the system power supply acquisition and judgment unit 05;

[0009] The system power supply acquisition and judgment unit 05 respectively collects and processes the primary and secondary power supply voltages and working currents in the bus power supply processing and current limiting unit 01, the control part power conversion top power unit 02, and the drive part power conversion unit 03, and transmits the acquisition results to the control unit 04;

[0010] The power control unit 07 controls the on / off of the three-phase windings of the motor according to the drive logic of the control unit 04;

[0011] The signal input / output unit 06 provides a communication interface, an analog input / output interface, and a discrete input / output interface for the control unit 04, and is communicatively connected to a host computer through the signal input / output unit 06.

[0012] Optionally, it further includes:

[0013] A drive part filtering unit 08;

[0014] The drive part filtering unit 08 is disposed between the bus power processing and current limiting unit 01 and the drive part power conversion unit 03.

[0015] Optionally, it further includes:

[0016] A control part filtering unit 09;

[0017] The control part filtering unit 09 is disposed between the bus power processing and current limiting unit 01 and the control part power conversion top power unit 02.

[0018] Optionally, the bus power processing and current limiting unit 01 includes a control power current limiting sub-unit and a power supply current limiting sub-unit;

[0019] The control power current limiting sub-unit includes a power supply switching module, a first resistor current limiting module, a first MOS transistor current limiting module, and a first MOS transistor control module;

[0020] The power supply current limiting sub-unit includes a second resistor current limiting module, a second MOS transistor current limiting module, and a second MOS transistor control module;

[0021] The input end of the power supply switching module is connected to two Vin power supplies, and the output end is sequentially connected to the first resistor current limiting module, the first MOS transistor current limiting module, and the first MOS transistor control module;

[0022] The input end of the second resistor current limiting module is connected to the VCC power supply, and the output end is sequentially connected to the second MOS transistor current limiting module and the second MOS transistor control module.

[0023] Optionally, the control part power conversion top power unit 02 specifically includes:

[0024] A first isolated DC / DC circuit, a second isolated DC / DC circuit, a first top power circuit, a second top power circuit, a third isolated DC / DC circuit, a first LDO circuit, and a first non-isolated conversion circuit;

[0025] The first isolated DC / DC circuit converts a 28V power supply into a 12V power supply voltage;

[0026] The second isolated DC / DC circuit converts the 12V power supply voltage into a 5V power supply voltage;

[0027] A first top power circuit is provided between the first isolated DC / DC circuit and the second isolated DC / DC circuit, and the first top power circuit provides a 12V top power supply voltage;

[0028] The second isolated DC / DC circuit converts the 5V power supply voltage into a 3.3V power supply voltage through the first LDO circuit, and converts the 5V power supply voltage into a 5V power supply voltage for the communication interface through a third isolated DC / DC circuit;

[0029] A second top power circuit is provided at the rear stage of the second isolated DC / DC circuit, and the second top power circuit provides a 5V top power supply voltage;

[0030] The first non-isolated conversion circuit converts the 28V power supply into 12V direct current.

[0031] Optionally, the drive part power conversion unit 03 specifically includes:

[0032] A second non-isolated conversion circuit and a second LDO circuit;

[0033] The second non-isolated conversion circuit converts the 28V power supply into 15V direct current;

[0034] The second LDO circuit converts the 15V direct current into 5V direct current.

[0035] Optionally, the system power supply acquisition and judgment unit 05 specifically includes:

[0036] A primary power supply voltage monitoring unit, a working current acquisition unit, and a secondary power conversion unit;

[0037] The primary power supply voltage monitoring unit specifically includes: a bus power supply voltage monitoring sub-unit, a drive power supply voltage monitoring sub-unit, and a control power supply voltage monitoring sub-unit;

[0038] The bus power supply voltage monitoring sub-unit acquires the 28V power supply and inputs it to the control power supply voltage monitoring sub-unit;

[0039] The drive power supply voltage monitoring sub-unit acquires the 15V and 5V power supply voltages and inputs them to the control unit 04;

[0040] The control power supply voltage monitoring sub-unit acquires the 12V power supply voltage, the 28V first sampling component input by the bus power supply voltage monitoring sub-unit, and the 28V second sampling component, and inputs them to the control unit 04;

[0041] The working current acquisition unit respectively acquires the power circuit current and the control circuit current, and inputs them to the control unit 04;

[0042] The secondary power conversion unit respectively acquires the 12V and 5V power supply voltages, and converts them into secondary power and inputs them to the control unit 04.

[0043] Optionally, the power control unit 07 specifically includes a MOS bridge arm circuit, a MOS drive circuit, and a drive signal isolation circuit.

[0044] Optionally, a position sensor is further included;

[0045] The position sensor acquires the motor rotor position signal and inputs it to the signal input / output unit 06.

[0046] Optionally, the bus power supply processing and current limiting unit 01, the control part power conversion and boosting unit 02, the drive part power conversion unit 03, the control unit 04, the system power supply acquisition and judgment unit 05, the signal input / output unit 06, and the power control unit 07 constitute a first redundant control board;

[0047] The unmanned aircraft flap control system further includes a second redundant control board identical to the first redundant control board;

[0048] The first redundant control board and the second redundant control board are communicatively connected through the signal input / output unit 06.

[0049] It can be seen from the above technical solutions that the embodiments of the present application have the following advantages:

[0050] In the present application, an unmanned aircraft flap control system is provided, including: a bus power supply processing and current limiting unit, a control part power conversion and boosting unit, a drive part power conversion unit, a control unit, a system power supply acquisition and judgment unit, a signal input / output unit, and a power control unit; realizing the integration of multiple power supplies input by the system, enabling the power distribution of the controller to meet the power supply relationship of the flap control device required by the system, while isolating the power supply of the drive part and the control part, and collecting, processing, and monitoring the primary and secondary power supply voltages and working currents of the system, with high reliability, stable power supply, and being able to stably receive the control instructions of the upper computer, thereby driving the servo to perform closed-loop motion. Description of the Drawings

[0051] Figure 1 It is a schematic structural diagram of an unmanned aircraft flap control system in an embodiment of the present application;

[0052] Figure 2 It is a circuit schematic diagram of the bus power supply processing and current limiting unit;

[0053] Figure 3 It is a framework diagram for controlling the sub-power conversion top power unit and the driving part power conversion unit;

[0054] Figure 4 It is a circuit schematic diagram of the driving part power conversion unit;

[0055] Figure 5 It is a circuit schematic diagram of the system power acquisition and judgment unit;

[0056] Figure 6 It is a circuit schematic diagram of the power control unit. Specific implementation manners

[0057] In order to enable those skilled in the art to better understand the solution of this application, the technical solutions in the embodiments of this application will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of this application. Obviously, the described embodiments are only a part of the embodiments of this application, rather than all the embodiments. Based on the embodiments in this application, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of this application.

[0058] For ease of understanding, please refer to Figure 1 , Figure 1 It is a structural schematic diagram of a flap control system for an unmanned aircraft in an embodiment of this application. As Figure 1 shown, specifically:

[0059] Bus power supply processing and current limiting unit 01, control part power conversion top power unit 02, driving part power conversion unit 03, control unit 04, system power acquisition and judgment unit 05, signal input / output unit 06, and power control unit 07;

[0060] The bus power supply processing and current limiting unit 01 integrates multiple power supply sources and provides a 28V power supply to the control part power conversion top power unit 02, the driving part power conversion unit 03, and the system power acquisition and judgment unit 05 respectively;

[0061] The control part power conversion top power unit 02 converts the 28V power supply into the power supply voltages required by the control unit 04 and the signal input / output unit 06, and is connected to the system power acquisition and judgment unit 05;

[0062] The driving part power conversion unit 03 converts the 28V power supply into the power supply voltage required by the power control unit 07, and is connected to the system power acquisition and judgment unit 05;

[0063] The system power acquisition and judgment unit 05 respectively acquires and processes the primary and secondary power voltages and operating currents in the bus power processing and current limiting unit 01, the control part power conversion and boosting unit 02, and the drive part power conversion unit 03, and transmits the acquisition results to the control unit 04;

[0064] The power control unit 07 controls the on and off of the three-phase windings of the motor according to the drive logic of the control unit 04;

[0065] The signal input / output unit 06 provides a communication interface, an analog input / output interface, and a discrete input / output interface for the control unit 04, and is communicatively connected to the host computer through the signal input / output unit 06.

[0066] Furthermore, it also includes:

[0067] The drive part filtering unit 08;

[0068] The drive part filtering unit 08 is arranged between the bus power processing and current limiting unit 01 and the drive part power conversion unit 03.

[0069] Furthermore, it also includes:

[0070] The control part filtering unit 09;

[0071] The control part filtering unit 09 is arranged between the bus power processing and current limiting unit 01 and the control part power conversion and boosting unit 02.

[0072] It should be noted that the functions of the drive part filtering unit 08 and the control part filtering unit 09 are to filter the corresponding parts of the control unit, so that the product can meet the requirements related to system electromagnetic compatibility. This part of the circuit is mainly composed of filtering devices such as inductors, capacitors, and magnetic beads, and needs to be customized according to the actual situation of the product.

[0073] Furthermore, as Figure 2 shown, Figure 2 is the circuit schematic diagram of the bus power processing and current limiting unit. The bus power processing and current limiting unit 01 includes a control power current limiting sub-unit and a power supply current limiting sub-unit;

[0074] The control power current limiting sub-unit includes a power supply switching module, a first resistor current limiting module, a first MOS transistor current limiting module, and a first MOS transistor control module;

[0075] The power supply current limiting sub-unit includes a second resistor current limiting module, a second MOS transistor current limiting module, and a second MOS transistor control module;

[0076] The input end of the power supply switching module is connected to two Vin power supplies, and the output end is sequentially connected to the first resistor current limiting module, the first MOS tube current limiting module, and the first MOS tube control module;

[0077] The input end of the second resistor current limiting module is connected to the VCC power supply, and the output end is sequentially connected to the second MOS tube current limiting module and the second MOS tube control module.

[0078] It should be noted that the main function of the bus power supply processing and current limiting unit 01 is to integrate the two power supplies input by the system, so that the controller power distribution meets the power supply relationship of the flap control system required by the system. At the same time, the overcurrent situation is controlled by placing current control devices.

[0079] In the bus power supply processing and current limiting unit 01, diodes are used to connect multiple power supplies to achieve mutual switching and backup of different power supplies. The one-way conduction of the diodes can achieve reverse connection protection of the power supply and prevent the reverse voltage of the motor from returning to the bus, causing system power fluctuations.

[0080] D2 and D8 are transient voltage suppression diodes, which are used to suppress transient high voltage in the circuit and protect the circuit.

[0081] The current limiting function of the power supply is realized by Q1 and Q2 and the parallel resistors. When the control unit detects high voltage, the control devices U1 and U2 turn off the corresponding MOS tube Q1 or Q2. At this time, the current is provided by the parallel resistors to achieve current limiting power supply. When the overcurrent phenomenon disappears and the control unit returns to normal, Q1 or Q2 is turned on again to resume power supply.

[0082] Furthermore, as Figure 3 shown, Figure 3 is the framework diagram of the control sub-power conversion top power unit and the drive part power conversion unit. Among them, the control part power conversion top power unit 02 specifically includes:

[0083] The first isolated DC / DC circuit, the second isolated DC / DC circuit, the first top power circuit, the second top power circuit, the third isolated DC / DC circuit, the first LDO circuit, and the first non-isolated conversion circuit;

[0084] The first isolated DC / DC circuit converts the 28V power supply into a 12V power supply voltage;

[0085] The second isolated DC / DC circuit converts the 12V power supply voltage into a 5V power supply voltage;

[0086] A first top power circuit is arranged between the first isolated DC / DC circuit and the second isolated DC / DC circuit, and the first top power circuit provides a 12V top power supply voltage;

[0087] The second isolated DC / DC circuit converts the 5V power supply voltage to 3.3V power supply voltage through the first LDO circuit, and converts the 5V power supply voltage to the 5V power supply voltage of the communication interface through the third isolated DC / DC circuit;

[0088] A second top power circuit is provided in the latter stage of the second isolated DC / DC circuit, and the second top power circuit provides a 5V top power supply voltage;

[0089] The first non-isolated conversion circuit converts the 28V power supply into 12V DC power.

[0090] Furthermore, the power conversion unit 03 of the drive part specifically includes:

[0091] A second non-isolated conversion circuit and a second LDO circuit;

[0092] The second non-isolated conversion circuit converts the 28V power supply into 15V DC power;

[0093] The second LDO circuit converts 15V DC power into 5V DC power.

[0094] It should be noted that to improve the anti-interference ability of the product, the controller power supply is designed in a way that isolates the power and the control ground. Therefore, the power conversion top power unit includes two parts: the power conversion top power unit 02 of the control part and the power conversion unit 03 of the drive part.

[0095] Among them, the function of the power conversion top power unit 02 of the control part is to convert the input power into the power required by the system, and at the same time provide a top power of not less than 5ms when the system loses power. According to the product function analysis, the power supplies mainly needed inside are VDDA_12V, VDD_5V, 422_5V, and VDD_3.3V. When designing this unit, a standard power module is selected to transform the 28V input power supply. To achieve the isolation between the control ground and the power ground, the scheme adopted in the design of this part is to convert the 28V power supply of the system into VDDA_12V through an isolated DCDC device to achieve the first isolation of the power supply, and then use an isolated DCDC to convert this power supply into isolated VDD_5V, 422_5V, and VDD_3.3V. Through this method, the effective isolation of the power supply system can be achieved.

[0096] The top power circuit in the unit is mainly implemented by placing large-capacity capacitors. According to the system block diagram, the parts of the control section that require top power are mainly the circuits after the VDDA_12V voltage. As long as this part of the circuit can work properly, the normal functions of the product can be ensured. Therefore, the top power part mainly considers this part. According to the circuit power consumption, it is estimated that the average working current of the control section is 0.2A. The minimum working voltage in the circuit is the 12V to 5V isolated DCDC module, and its lowest working voltage is 9V. According to the capacitance formula C = Q / U = I*t / U (where C is the capacitance, U is the voltage difference of 3V (15V - 12V), Q is the electric charge, I is the average working current of the product 0.2A, and t is the freewheeling time of 5ms), we can get C = 0.00033F = 330μf. Considering the power conversion efficiency of the power supply and the influence of the capacitance on the working voltage and temperature, 3 parallel-connected 25V 220μF tantalum capacitors TCN4227M025R0100 are selected as the support capacitors for the 12V control power supply bus to achieve the top power function when the control loop loses power for 5ms at 28V.

[0097] The core circuit of the product is the single-chip microcomputer and related logic processing parts. The voltage of this part is 3.3V. Therefore, 4 10V 470uF tantalum capacitors T495X477K010ATE100 are selected as the top power circuit for the core devices to achieve uninterrupted operation when the core devices are instantaneously powered off for 0.5ms.

[0098] As Figure 4 shown, Figure 4 is the circuit schematic diagram of the power conversion unit for the drive part. The grounds of the power part and the control part need to be isolated. In the motor drive, the control of the three-phase bridge arm needs to use the ground of the drive as the reference potential to be realized. Therefore, the main function of adding the connection to the power conversion unit of the drive part is to convert the 28V power supply of the system into +15V and +5V to supply power to the power drive unit separately to meet the requirements of electrical isolation. Since the power demand of this part of the power supply is relatively low and it needs to meet the 50V withstand voltage requirement.

[0099] Furthermore, as Figure 5 shown, Figure 5 is the circuit schematic diagram of the system power supply acquisition and judgment unit. The system power supply acquisition and judgment unit 05 specifically includes:

[0100] The primary power supply voltage monitoring unit, the working current acquisition unit, and the secondary power supply conversion unit;

[0101] The primary power supply voltage monitoring unit specifically includes: the bus power supply voltage monitoring sub-unit, the drive power supply voltage monitoring sub-unit, and the control power supply voltage monitoring sub-unit;

[0102] The bus power supply voltage monitoring sub-unit collects the 28V power supply and inputs it to the control power supply voltage monitoring sub-unit;

[0103] The driving power supply voltage monitoring sub-unit collects the 15V and 5V power supply voltages and inputs them to the control unit 04;

[0104] The control power supply voltage monitoring sub-unit collects the 12V power supply voltage, the 28V first sampling component input by the bus power supply voltage monitoring sub-unit, and the 28V second sampling component, and inputs them to the control unit 04;

[0105] The working current acquisition unit respectively collects the power loop current and the control loop current and inputs them to the control unit 04;

[0106] The secondary power conversion unit respectively collects the 12V and 5V power supply voltages and converts them into secondary power to input to the control unit 04.

[0107] It should be noted that the function of the system power supply acquisition and judgment unit is to collect and process the primary and secondary power supplies of the system, and transfer the collected results to the control unit to achieve the monitoring of relevant power supplies required by the protocol. This unit is mainly implemented based on Hall current, operational amplifiers, and comparators.

[0108] Furthermore, as Figure 6 shown, Figure 6 is the circuit schematic diagram of the power control unit. The power control unit 07 specifically includes a MOS bridge arm circuit, a MOS drive circuit, and a drive signal isolation circuit.

[0109] It should be noted that the function of the power control unit is to control the on and off of the three-phase windings of the motor according to the drive logic of the control unit to achieve the rotation control of the motor. This unit is mainly composed of a MOS bridge arm circuit, a MOS drive circuit, and a drive signal isolation circuit.

[0110] According to the motor power prediction, the working current of the MOS tube reaches 90A. The MOS tube model adopted in this design is HYG01510NS1TA, its rated voltage is 100V, and the continuous working current reaches 380A. To reduce the device temperature rise, the design adopts the output method of paralleling two MOS tubes to reduce the power consumption of a single tube.

[0111] The MOS drive adopts EG3113. This device is a dedicated gate drive chip for MOS power devices. It realizes the drive of MOS devices with a high voltage side up to 600V through the bootstrap method and is widely used in motor drives.

[0112] The drive signal isolation circuit isolates and outputs the signal of the control unit to the drive unit through an optocoupler to achieve electrical isolation.

[0113] Furthermore, it also includes a position sensor;

[0114] The position sensor collects the motor rotor position signal and inputs it to the signal input / output unit 06.

[0115] Furthermore, the bus power supply processing and current limiting unit 01, the control part power conversion top power unit 02, the drive part power conversion unit 03, the control unit 04, the system power supply acquisition and judgment unit 05, the signal input / output unit 06, and the power control unit 07 constitute the first redundancy control board;

[0116] The unmanned aircraft flap control system further includes a second redundancy control board identical to the first redundancy control board;

[0117] The first redundancy control board and the second redundancy control board are communicatively connected through the signal input / output unit 06.

[0118] The embodiment of the present application provides an unmanned aircraft flap control system, including: a bus power supply processing and current limiting unit 01, a control part power conversion top power unit 02, a drive part power conversion unit 03, a control unit 04, a system power supply acquisition and judgment unit 05, a signal input / output unit 06, and a power control unit 07; it realizes the integration of multiple power supplies input by the system, enables the controller power distribution to meet the power supply relationship of the flap control device required by the system, isolates the power supply of the drive part and the control part at the same time, and collects and processes the primary and secondary power supply voltages and working currents of the system and realizes monitoring, with high reliability, stable power supply, and can stably receive the control instructions from the upper computer, so as to drive the servo to perform closed-loop motion.

[0119] As mentioned above, the above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit them; although the present application has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: they can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements on some of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present application.

Claims

1. An unmanned aircraft flap control system, characterized in that, It includes: A bus power supply processing and current limiting unit (01), a control part power supply conversion and overvoltage unit (02), a driving part power supply conversion unit (03), a control unit (04), a system power supply acquisition and judgment unit (05), a signal input / output unit (06), and a power control unit (07); The bus power supply processing and current limiting unit (01) integrates multiple power supply sources and provides a 28V power supply to the control part power supply conversion and overvoltage unit (02), the driving part power supply conversion unit (03), and the system power supply acquisition and judgment unit (05) respectively; The control part power supply conversion and overvoltage unit (02) converts the 28V power supply into the power supply voltages required by the control unit (04) and the signal input / output unit (06), and is connected to the system power supply acquisition and judgment unit (05); The driving part power supply conversion unit (03) converts the 28V power supply into the power supply voltage required by the power control unit (07), and is connected to the system power supply acquisition and judgment unit (05); The system power supply acquisition and judgment unit (05) respectively collects and processes the primary and secondary power supply voltages and working currents in the bus power supply processing and current limiting unit (01), the control part power supply conversion and overvoltage unit (02), and the driving part power supply conversion unit (03), and transfers the acquisition results to the control unit (04); The power control unit (07) controls the on / off of the three-phase windings of the motor according to the driving logic of the control unit (04); The signal input / output unit (06) provides a communication interface, an analog input / output interface, and a discrete input / output interface for the control unit (04), and is communicatively connected to the upper computer through the signal input / output unit (06).

2. The unmanned aircraft flap control system according to claim 1, wherein It further includes: A driving part filtering unit (08); The driving part filtering unit (08) is arranged between the bus power supply processing and current limiting unit (01) and the driving part power supply conversion unit (03).

3. The unmanned aircraft flap control system according to claim 2, wherein It further includes: A control part filtering unit (09); The control part filtering unit (09) is arranged between the bus power supply processing and current limiting unit (01) and the control part power supply conversion and overvoltage unit (02).

4. The unmanned aircraft flap control system according to claim 1, characterized in that, The bus power supply processing and current limiting unit (01) includes a control power supply current limiting subunit and a power supply power current limiting subunit; The control power supply current limiting subunit includes a power supply switching module, a first resistor current limiting module, a first MOS transistor current limiting module, and a first MOS transistor control module; The power supply power current limiting subunit includes a second resistor current limiting module, a second MOS transistor current limiting module, and a second MOS transistor control module; The input end of the power supply switching module is connected to two Vin power supplies, and the output end is sequentially connected to the first resistor current limiting module, the first MOS transistor current limiting module, and the first MOS transistor control module; The input end of the second resistor current limiting module is connected to the VCC power supply, and the output end is sequentially connected to the second MOS transistor current limiting module and the second MOS transistor control module.

5. The unmanned aircraft flap control system according to claim 1, wherein The power conversion topping power supply unit (02) of the control part specifically includes: A first isolated DC / DC circuit, a second isolated DC / DC circuit, a first topping power supply circuit, a second topping power supply circuit, a third isolated DC / DC circuit, a first LDO circuit, and a first non-isolated conversion circuit; The first isolated DC / DC circuit converts the 28V power supply into a 12V power supply voltage; The second isolated DC / DC circuit converts the 12V power supply voltage into a 5V power supply voltage; A first topping power supply circuit is arranged between the first isolated DC / DC circuit and the second isolated DC / DC circuit, and the first topping power supply circuit provides a 12V topping power supply voltage; The second isolated DC / DC circuit converts the 5V power supply voltage into a 3.3V power supply voltage through the first LDO circuit, and converts the 5V power supply voltage into a 5V power supply voltage for the communication interface through the third isolated DC / DC circuit; A second topping power supply circuit is arranged at the rear stage of the second isolated DC / DC circuit, and the second topping power supply circuit provides a 5V topping power supply voltage; The first non-isolated conversion circuit converts the 28V power supply into 12V direct current.

6. The unmanned aircraft flap control system according to claim 1, characterized in that, The power conversion unit (03) of the drive part specifically includes: A second non-isolated conversion circuit and a second LDO circuit; The second non-isolated conversion circuit converts the 28V power supply into 15V direct current; The second LDO circuit converts the 15V direct current into 5V direct current.

7. The unmanned aircraft flap control system according to claim 1, wherein The system power supply acquisition and judgment unit (05) specifically includes: A primary power supply voltage monitoring unit, a working current acquisition unit, and a secondary power conversion unit; The primary power supply voltage monitoring unit specifically includes: a bus power supply voltage monitoring sub-unit, a drive power supply voltage monitoring sub-unit, and a control power supply voltage monitoring sub-unit; The bus power supply voltage monitoring sub-unit acquires the 28V power supply and inputs it to the control power supply voltage monitoring sub-unit; The drive power supply voltage monitoring sub-unit acquires the 15V and 5V power supply voltages and inputs them to the control unit (04); The control power supply voltage monitoring sub-unit acquires the 12V power supply voltage, the first 28V sampling component input by the bus power supply voltage monitoring sub-unit, and the second 28V sampling component, and inputs them to the control unit (04); The working current acquisition unit respectively acquires the power loop current and the control loop current and inputs them to the control unit (04); The secondary power conversion unit respectively acquires the 12V and 5V power supply voltages and converts them into secondary power and inputs them to the control unit (04).

8. The unmanned aircraft flap control system according to claim 1, wherein The power control unit (07) specifically includes a MOS bridge arm circuit, a MOS drive circuit, and a drive signal isolation circuit.

9. The unmanned aircraft flap control system according to claim 1, characterized in that A position sensor is also included; The position sensor acquires the motor rotor position signal and inputs it to the signal input and output unit (06).

10. The unmanned aircraft flap control system according to any one of claims 1 to 9, characterized in that, The bus power supply processing and current limiting unit (01), the control part power conversion top power unit (02), the drive part power conversion unit (03), the control unit (04), the system power supply acquisition and judgment unit (05), the signal input / output unit (06) and the power control unit (07) constitute the first redundancy control board; The unmanned aircraft flap control system further includes a second redundancy control board identical to the first redundancy control board; The first redundancy control board and the second redundancy control board are communicatively connected through the signal input / output unit (06).

Images