Airplane anti-icing and de-icing control power distribution device

Abstract

The invention belongs to the electrical field, relates to an anti-icing and de-icing control power distribution device suitable for the leading edge of an aircraft wing and an air inlet lip, and can generate an anti-icing and de-icing working time sequence according to information such as the environment condition of an aircraft, the icing state and an anti-icing and de-icing system working instruction when the aircraft is in an icing meteorological condition. And the deicing heating power supply is provided for the electric heating assembly according to the deicing work time sequence. The device adopts a distributed control architecture, has three control redundancies, and has the characteristics of active fault tolerance, system reconstruction and autonomous optimization of a control strategy. The device is composed of an interface unit, a control unit, a power unit and a shell assembly.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of electricity, and particularly relates to an aircraft anti-icing control power distribution device, which has the functions of anti-icing control and anti-icing power distribution, and has the functions of semi-supervised learning control law training and active tolerance control, is suitable for AC and DC anti-icing power supply systems, is suitable for anti-icing of the wing leading edge or the inlet lip, and can work in both anti-icing mode and deicing mode. BACKGROUND

[0002] An aircraft may encounter icing weather within a certain flight envelope, and icing of the wing may change the aerodynamic shape of the wing, resulting in a decrease in lift. Icing of the inlet lip may cause a decrease in engine thrust, and the falling ice may damage the engine blades, which may seriously threaten the flight safety of the aircraft. With the development of unmanned aerial vehicles and low-altitude economy, the flight performance of the aircraft in icing environments should be paid more attention to. In order to ensure the safety and airworthiness of the aircraft, the aircraft is equipped with an anti-icing system to ensure that the wing leading edge icing can be effectively removed and the inlet lip can be prevented from icing, so as to reduce or eliminate the influence of the icing environment on the flight safety of the aircraft.

[0003] The current anti-icing system of the aircraft mainly consists of an anti-icing controller and an anti-icing power distributor. The controller is used to realize communication, generate deicing control law, and send control instructions to the anti-icing power distributor. The anti-icing power distributor distributes the anti-icing heating power to the electric heating components. The anti-icing system composed of multiple products has large space and weight, requires much maintenance work, and cannot improve the system reliability. The cooperation ability between the devices is weak. At the same time, the existing anti-icing system relies more on the operation of the pilot, and cannot work efficiently, reliably and adaptively according to the environmental conditions. In the case of failure, the system enters a degraded working state, and cannot be reconstructed to maximize the anti-icing performance of the system. SUMMARY

[0004] The present application provides an aircraft anti-icing control power distribution device, which has the functions of anti-icing control and anti-icing power distribution, and has the functions of semi-supervised learning control law training and active tolerance control, can work in both anti-icing mode and deicing mode, and can reduce the volume and weight of the anti-icing system product and reduce the energy consumption of the system in the automatic working state.

[0005] The technical solution of the present application is as follows: An aircraft anti-icing control power distribution device, comprising an interface unit, a control unit and four power units integrated in a housing unit. The interface unit transmits the 28V power supply and external bus signals inputted from outside to the control unit; transmits the anti-icing power supply inputted from outside to the power unit, and transmits the power signal outputted from the power unit to the external electric heating assembly; and transmits the internal bus signals and power signals between the control unit and the power unit, so as to achieve the purposes of modularization, standardization and leadless design. The control unit obtains instructions and environmental information through the external bus signals, calculates the anti-icing control law, and sends the control instructions to the power unit through the internal bus. The power unit receives the control instructions sent by the control unit, and performs the corresponding power distribution work; during the work, the working state is monitored, and the working state is fed back to the control unit through the internal bus and the interface unit, so as to realize the decoupling of the control law calculation and the power distribution execution.

[0006] Further, the control unit comprises three independent control channels, each of which has a processor; the power supply circuit, clock circuit and communication circuit of each processor are independent of each other, and can form three control redundancies to realize the reconstruction of the control channel when the control channel fails.

[0007] Further, each power unit comprises a microprocessor, a clock circuit, a voltage stabilizing circuit and a power circuit.

[0008] Further, the control unit and the power unit are provided with independent first internal communication circuits and second internal communication circuits. The two internal communication circuits are divided into two groups, and the first internal communication circuits of the processors of the three control channels and the microprocessors of the power units are interconnected, and the second internal communication circuits are interconnected, which are used to transmit the working state, the diagnosed fault information and the anti-icing work start / stop judgment results between each other, and form two internal communication bus redundancies.

[0009] Further, the three control channels of the control unit also perform bidirectional state indication between the processors, and transmit the state indication to the microprocessors of the power units, which are used to indicate the working state of the current processor when both the two internal bus communication circuits fail.

[0010] Further, the control channels on the control unit perform control redundancy reconstruction: when the three control channels are normal, the three control channels send control instructions to the power unit through the internal bus; When one control channel on the control unit fails and two control channels are normal, the control channel with the smaller preset ID number among the two normal control channels sends the control instructions to the power unit through the internal bus, and the processor with the larger preset ID number among the two normal control channels enters standby mode. When two control channels on the control unit are faulty and one control channel is normal, the normal control channel sends control instructions to the power unit through the internal bus.

[0011] Further, when both internal communication circuits are normal, the power unit uses the instructions of the first internal communication circuit; When only one internal communication circuit is normal, the power unit uses the instructions of the normal internal communication circuit; When both internal communication circuits are abnormal, the power unit continues to work according to the square wave hard-wire control signal of the control unit and outputs a square wave hard-wire indication signal to represent its working state; When both internal communication circuits are abnormal and the power unit cannot receive the square wave hard-wire indication signal sent by the control unit, the anti-icing control power distribution device should prohibit the anti-icing work.

[0012] Further, each control channel on the control unit has an independent storage circuit for storing the control instructions, environmental parameters and system working parameters of the anti-icing control power distribution device each time the anti-icing work is started / stopped, the control channel uses the stored parameters as training data for semi-supervised learning, and automatically executes the anti-icing work according to the training results through the environmental parameters to realize autonomous optimization of the anti-icing control law and reduce energy consumption.

[0013] Further, the number of independent power distribution channels on the power circuit of the power unit is even, and each power distribution channel has two redundant power distribution branches; there is a power switching switch between the two independent power distribution channels, and when the fault diagnosis result is a switch circuit fault, the power distribution channel is reconfigured through the switching switch to ensure that the power distribution channel still has two redundancies when a single branch fails.

[0014] Further, the microprocessor on the power unit distinguishes whether the fault occurs in the sensor or the heating circuit according to the fault characteristics, and if it occurs in the sensor, the fault is offset in the feedback result; if it occurs in the heating circuit, the heating circuit needs to be disconnected and the heating channel needs to be reconfigured.

[0015] Advantages This invention aims to propose an aircraft anti-icing and de-icing control and power distribution device based on the principle of electrothermal anti-icing and de-icing. It possesses anti-icing and de-icing control and power distribution capabilities, and features semi-supervised learning for control law training and active tolerance control. It is suitable for both AC and DC anti-icing and de-icing power supply systems, and applicable to anti-icing and de-icing at the wing leading edge or air intake lip. It can operate in both anti-icing and de-icing modes. Compared to traditional anti-icing and de-icing power distribution devices, it offers advantages such as high power supply reliability, low line loss, and strong maintainability. Compared to the traditional anti-icing and de-icing system architecture that consists of multiple devices including an anti-icing controller and anti-icing and de-icing power distribution unit, this invention integrates anti-icing and de-icing control with high-voltage, high-power power distribution functions into one unit. It features semi-supervised learning and active tolerance control, which helps reduce system weight, maintenance workload, and improve the integration, intelligence, and health management capabilities of the anti-icing and de-icing system.

[0016] This invention aims to propose an integrated anti-icing and de-icing control and power distribution device for aircraft based on the principle of electrothermal anti-icing and de-icing. By adopting functional unit decomposition and electrical isolation measures, its insulation performance under high-voltage conditions is guaranteed. The control unit performs complex logic operations and system operation control, employing a triple-redundant control channel design to improve system reliability. The control channel has semi-supervised learning capabilities, autonomously optimizing the control law based on stored system operation data and environmental parameters from previous operations, achieving automatic anti-icing and de-icing operation. Simultaneously, adjusting the control law according to environmental parameters reduces power consumption during system operation. The power unit is the high-voltage power distribution actuator, containing internal software that can communicate with the control unit in real time, executing anti-icing and de-icing power distribution operations according to the control unit's instructions. It can monitor the power unit's operating status in real time, detecting and isolating faults based on the monitored data. Power distribution channel reconfiguration can be achieved through power switching switches between distribution channels, thus achieving active fault-tolerant control. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. The drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 This is a schematic diagram of the principle of an aircraft anti-icing and de-icing control power distribution device; Figure 2 This is a schematic diagram of its structure; Figure 3 This diagram illustrates the interconnection relationship and working principle between the control unit and the power unit. Figure 4 This is a schematic diagram of the power circuit of the power unit. Figure 5 Schematic diagram of semi-supervised learning process for control law of control unit; Figure 6 Schematic diagram of the fault-tolerant control process of the power unit control law. Detailed Implementation

[0019] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0020] The features and illustrative embodiments of various aspects of the present invention will now be described in detail. Numerous specific details are set forth in the following detailed description to provide a thorough understanding of the invention. However, it will be apparent to those skilled in the art that the invention may be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. The invention is by no means limited to any specific setups and methods set forth below, but covers any improvements, substitutions, and modifications to structures, methods, and devices without departing from the spirit of the invention. Well-known structures and techniques are not shown in the drawings and the following description to avoid unnecessarily obscuring the invention.

[0021] In the description of this invention, it should be noted that the directions or positional relationships indicated by terms such as "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer" are based on the directions or positional relationships shown in the accompanying drawings and are only for the convenience of describing and simplifying the invention, and should not be construed as limiting the invention. Furthermore, the use of ordinal numbers (e.g., "first and second," etc.) is for distinguishing objects and is not limited to this order, and should not be construed as indicating or implying relative importance.

[0022] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly, encompassing both direct connection and indirect connection via an intermediate medium. Those skilled in the art can understand the specific meaning of these terms in this invention based on the specific circumstances.

[0023] It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other, and the various embodiments can be referenced and cited in each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0024] The present invention will be further described in detail below with reference to the embodiments and accompanying drawings, but the embodiments of the present invention are not limited thereto.

[0025] 1.Reference Figure 1 An aircraft anti-icing and de-icing control and power distribution device based on the principle of electrothermal anti-icing is disclosed. It includes one interface unit 1, one control unit 2, and four power units 3 integrated within a housing unit 4. The four power units 3 are identical, differing only in the electric heating components they supply. The number of power units depends on the power and quantity of the electric heating components. The interface unit 1 serves as a motherboard, transmitting external and internal signals and providing electromagnetic compatibility, power supply compatibility, and lightning protection for the interface and power supply circuits. The control unit 2 and power units 3 are both board-like structures, electrically connected to the interface unit 1 via electrical connectors and fixed by the housing unit 4. The control unit 2 receives 28V power from the interface unit 1, converts it to internal DC power to supply power to the circuitry on the control unit, and then supplies power to the power units 3 via the interface unit 1. After receiving data from the host computer, the control unit 2 calculates the anti-icing and de-icing control law. The power units 3 receive control commands from the control unit 2 via the interface unit 1, obtain anti-icing and de-icing power from the interface unit 1, and control the electric heating components to energize and heat for de-icing according to the anti-icing and de-icing control law. When the input 28V power supply has two redundancies, the two redundancies of 28V power supply can be combined into one circuit through rectifier diodes, and then the power conversion is performed by control unit 2; when the input 28V power supply has three redundancies, the following can be adopted: ① Each 28V power supply supplies power to one control channel, and each control channel performs conversion separately; ② The three redundancies of 28V power supply can be combined into one circuit through rectifier diodes, and then the power conversion is performed by control unit 2.

[0026] 2.Reference Figure 3An aircraft anti-icing and de-icing control and power distribution device based on the principle of electrothermal de-icing is disclosed. The control unit 2 comprises three independent control channels, each with a processor. The power supply circuit, clock circuit, and communication circuit of each processor are independent of each other. The processors on the three channels can use processors of the same configuration, such as DSP, ARM, FPGA, or CPUs with integrated NPUs, or processors of different configurations can be used to create dissimilar redundancy. The power supply circuit uses an isolated DC-DC converter for power conversion, enabling the acquisition of multiple power signals. The clock circuit of the processor is provided by a quartz crystal oscillator. The three control channels on control unit 2 communicate with each other via redundant, independent bidirectional internal bus communication circuits. This allows them to exchange their own operating status, diagnosed fault information, and anti-icing / de-icing start / stop judgment results. The communication protocol can be selected from CAN bus, RS485 bus, or RS422 bus; in this embodiment, CAN bus is preferred for easier networking with power unit 3. The three control channels also provide bidirectional status indication between each other via internal hard-wired signals. This indicates the current processor's operating status when both redundant internal bus communication circuits fail. The status indication uses a continuous square wave signal with anti-false triggering and fault prevention features. When communication between channels is lost, if a square wave hard-wired indication signal from a different channel is received, it indicates that the control channel has only lost communication and is not out of control; the anti-icing control and distribution device can continue to operate. When communication between channels is lost, if a square wave hard-wired indication signal from a different channel is not received, it indicates that the control channel is out of control, and the anti-icing control and distribution device should disable anti-icing operation. Each control channel on control unit 2 has an independent Flash storage circuit for storing control commands, environmental parameters, and system operating parameters of the anti-icing control power distribution device each time it starts / stops anti-icing operation.

[0027] 3.Reference Figure 3 An aircraft anti-icing and de-icing control and power distribution device based on the principle of electrothermal anti-icing, wherein the control channels on the control unit 2 can be reconfigured for control redundancy: when all three control channels are normal, all three control channels send control commands to the power unit 3 through the internal bus; the power unit adopts a three-to-two mechanism to respond to the control commands of the control unit and perform power distribution work. If one control channel on control unit 2 fails and both control channels are functioning normally, the control channel with the smaller preset ID number among the two functioning channels sends a control command to power unit 3 via the internal bus. The processor with the larger preset ID number among the two functioning control channels then enters standby mode. If two control channels on control unit 2 fail and one control channel is functioning normally, the functioning control channel sends a control command to power unit 3 via the internal bus. Control channel status information is transmitted via the internal bus. The control channel ID number can be preset in two ways: ① Hardware preset, using high and low levels provided to the processor's I / O ports to form a binary code, which serves as the unit ID; ② Software preset, where the unit ID is written into the processor during software programming.

[0028] 4.Reference Figure 5 A semi-supervised learning process for an aircraft anti-icing control and power distribution device based on the principle of electrothermal anti-icing is described below: ① The control channel of control unit 2 uses the stored working parameters as training data to perform semi-supervised learning to obtain a classifier; ②Then, the classifier is iterated by learning from the unlabeled data pre-stored in the memory and some pre-labeled data is obtained; ③ Next, the stored working parameters and pre-labeled data are used as a test set for validation, and the classifier is iterated again; ④ If the result does not meet the requirements, repeat steps ② and ③, retrain using unlabeled data to obtain new pre-labeled data, and iterate the classifier; ⑤ If the requirements are met, the classifier obtained in the final iteration is the latest control law, which can be used to automatically perform anti-icing and de-icing work based on environmental parameters and system operating parameters.

[0029] 5.Reference Figure 4An aircraft anti-icing and de-icing control and power distribution device based on the principle of electrothermal anti-icing is disclosed. Its power unit 3 includes a microprocessor, clock circuit, internal communication circuit, voltage regulator circuit, and power circuit. The microprocessor in power unit 3 has lower computing power requirements than the control unit 2; therefore, a DSP or ARM processor can be used. A quartz crystal oscillator is used as the clock circuit to provide a clock signal to the microprocessor. The internal communication circuit uses a CAN bus circuit to communicate with the control unit 2. The internal communication circuit can use two independent circuits: ① The first group: the internal communication circuits 1-1, 2-1, and 3-1 of control unit 2 communicate with the internal communication circuit 1 of power unit 3 in a network; ② The second group: the internal communication circuits 1-2, 2-2, and 3-2 of control unit 2 communicate with the internal communication circuit 2 of power unit 3 in a network. Both circuits serve as backups. When both circuits are communicating normally, control unit 2 and power unit 3 prioritize and use internal communication circuit 1 to issue commands.

[0030] Meanwhile, when communication between the two sets of internal communication circuits is abnormal, to prevent the control unit 2 from being unable to obtain the status information of the power unit 3, the control unit 2 uses a hard-wired control signal to send a control command to the power unit 3, and the power unit 3 uses a hard-wired indicator signal to indicate its current operating status. Both the hard-wired control and hard-wired indicator use continuous square wave signals with anti-false triggering and anti-fault properties as valid signals.

[0031] When communication between channels is lost, if control unit 2 can receive the square wave hard-wire indication signal sent by power unit 3, it indicates that power unit 3 has only lost communication and is not in a state of being out of control. Power unit 3 can continue to perform power distribution work according to the square wave hard-wire control signal of control unit 2. When communication between channels is lost, if control unit 2 cannot receive the square wave hard-wire indication signal sent by power unit 3, it indicates that power unit 3 is in a state of being out of control. The anti-icing control power distribution device should prohibit all anti-icing work.

[0032] 6.Reference Figure 4An aircraft anti-icing and de-icing control power distribution device based on the principle of electrothermal anti-icing is disclosed. Its power unit 3 has an even number of independent power distribution channels, with a switching switch between adjacent power distribution channels. When a fault is diagnosed in the switching circuit of power distribution output channel 1, the switching switch reconfigures the system, allowing the switching circuit of power distribution output channel 2 to simultaneously supply power to both power distribution output channels 1 and 2. At this time, the operating status of the electric heating component in power distribution output channel 1 is still monitored by the channel's own current detection circuit. For DC power supplies, MOSFETs or IGBTs can be used for the switching circuit and the power electronic devices of the switching switch. In the switching circuit, two power electronic devices must be connected with a common source (emitter) to prevent uncontrolled backflow of power. For AC power supplies, bidirectional thyristors or MOSFETs or IGBTs with common source (emitter) connections can be used for the switching circuit and the power electronic devices of the switching switch.

[0033] 7.Reference Figure 4 An aircraft anti-icing and de-icing control power distribution device based on the principle of electrothermal anti-icing is disclosed. Its power unit 3 can detect the current of the heating component by current detection and calculate the power density of the heating component. The power density of the heating component can be controlled by adjusting the duty cycle of the switching device in the switching circuit, thereby avoiding overheating damage caused by power fluctuations or resistance drift of the heating component leading to an increase in the power density of the heating component.

[0034] 8.Reference Figure 6 An aircraft anti-icing and de-icing control power distribution device based on the principle of electrothermal anti-icing, the fault-tolerant control steps of its power unit 3 are as follows: ① Collect current and power supply data, and filter the data; ② Construct a state observer to detect and diagnose system operation faults. The state observer here is constructed using sliding mode variable structure control to reduce the state observer's dependence on system parameters. ③ When the residual is lower than the preset evaluation index, there is no fault in the surface system and no fault diagnosis is required; otherwise, fault diagnosis is required based on the magnitude of the residual. ④ When the residual indicates that the sensor in the current acquisition circuit has failed, the fault parameters of the sensor are estimated by the equivalent control and the estimated value is used to participate in the control. In this case, the anti-icing and de-icing work can be carried out normally. ⑤ When the residual indicates that the switching circuit of the power distribution channel has failed, close the fault switch and use the power switching switch to reconstruct the power distribution channel. In this case, the anti-icing work can be carried out normally. ⑥ When the residual indicates that the heating component has failed, in this case, because the actuator sends a fault, the reconstruction cannot compensate for the fault. Therefore, the working of the faulty heating component should be stopped, and the anti-icing operation should be in a degraded operating state.

[0035] The above detailed embodiments are a description of the present invention. It should not be considered that the specific embodiments of the present invention are limited to these descriptions. For those skilled in the art, several simple deductions and substitutions can be made without departing from the concept of the present invention, and all of these should be considered to fall within the protection scope of the present invention.

Claims

1. An aircraft anti-icing and de-icing control power distribution device, characterized in that, This includes an interface unit, a control unit, and four power units integrated into the housing unit; The interface unit transmits the externally input 28V power supply and external bus signals to the control unit; transmits the externally input anti-icing power supply to the power unit, and transmits the power unit's output power signal to the external electric heating component; and transmits the internal bus signals and power signals between the control unit and the power unit. The control unit obtains instructions and environmental information through external bus signals, calculates the anti-icing and de-icing control law, and sends control instructions to the power unit through the internal bus. The power unit receives control commands sent by the control unit and performs corresponding power distribution work. During operation, it monitors the power distribution status and feeds back the status to the control unit via the interface unit through the internal bus.

2. The aircraft anti-icing and de-icing control power distribution device according to claim 1, characterized in that, The control unit contains three independent control channels, each with a processor; the power supply circuit, clock circuit, and communication circuit of each processor are all independent of each other.

3. The aircraft anti-icing and de-icing control power distribution device according to claim 2, characterized in that, Each power unit includes a microprocessor, clock circuit, voltage regulator circuit, and power circuit.

4. The aircraft anti-icing and de-icing control power distribution device according to claim 3, characterized in that, The control unit is equipped with an independent first internal communication circuit and a first internal communication circuit; Two internal communication circuits connect the processors of the three control channels to each other in pairs, and also connect to the microprocessor of the power unit, for transmitting their own working status, diagnostic fault information, and the start / stop judgment results of anti-icing and de-icing work.

5. The aircraft anti-icing and de-icing control power distribution device according to claim 4, characterized in that, The three control channels of the control unit also provide bidirectional status indication between the two processors via internal hardwire signals, and transmit the status indication to the microprocessor of the power unit. This is used to indicate the current working status of the processor when both redundant internal bus communication circuits fail.

6. The aircraft anti-icing and de-icing control power distribution device according to claim 4, characterized in that, The control channels on the control unit undergo control redundancy reconfiguration: when all three control channels are normal, all three control channels send control commands to the power unit via the internal bus; If one control channel on the control unit fails and both control channels are normal, the control channel with the smaller preset ID number among the two normal control channels will send control commands to the power unit through the internal bus, and the processor with the larger preset ID number among the two normal control channels will enter standby mode. Two control channels on the control unit are faulty. When one control channel is normal, the normal control channel sends control commands to the power unit through the internal bus.

7. The aircraft anti-icing and de-icing control power distribution device according to claim 5, characterized in that, When all internal communication circuits are functioning normally, the power unit uses the instructions from the first internal communication circuit. When only one internal communication circuit is functioning normally, the power unit uses the instructions of the functioning internal communication circuit. When both internal communication circuits malfunction, the power unit continues to operate according to the square wave hard-wired indication signal. When both internal communication circuits are malfunctioning and the power unit cannot receive the square wave hard-wired indication signal sent by the control unit, the anti-icing control power distribution device should prohibit anti-icing operation.

8. The aircraft anti-icing and de-icing control power distribution device according to claim 7, characterized in that, Each control channel on the control unit has an independent storage circuit for storing the control commands, environmental parameters, and system operating parameters of the anti-icing control power distribution device each time it starts / stops anti-icing operation. The control channel uses the stored parameters as training data for semi-supervised learning and automatically executes anti-icing operation based on the training results and environmental parameters.

9. The aircraft anti-icing and de-icing control power distribution device according to claim 3, characterized in that, The number of independent power distribution channels on the power circuit of the power unit is even, and each power distribution channel has two redundant power distribution branches; there is a power switching switch between two independent power distribution channels. When the fault diagnosis result is a fault in the switching circuit, the power distribution channel is reconstructed through the switching switch.

10. The aircraft anti-icing and de-icing control power distribution device according to claim 9, characterized in that, The microprocessor on the power unit distinguishes whether the fault occurs in the sensor or the heating circuit based on the fault characteristics. If the fault occurs in the sensor, the fault is canceled in the feedback result. If the problem occurs in the heating circuit, the heating circuit must be disconnected and the heating channel reconstructed.

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