A helicopter anti-icing power distribution control system

Abstract

A helicopter anti-icing power distribution control system includes a power supply switching contactor, contactor A, contactor B, a logic control module, and a current / voltage detection module, where: The 28V DC on the aircraft is connected to a 28V to 5V power supply module with a power of 30W to supply power to the electrical heating rotor anti-icing power distribution architecture with the 28V DC on the aircraft; The 5V power supply module is connected to a multi-channel AD chip, an MSP430 single-chip microcomputer, an opto-isolation chip, a Darlington driver array, and a relay to supply power to the above-mentioned devices; The multi-channel AD chip is connected to the MSP430 single-chip microcomputer to send digital signals to the MSP430 single-chip microcomputer; The anti-icing controller is connected to the RS422 communication module, and the RS422 communication module is connected to the MSP430 single-chip microcomputer to send data to the MSP430 single-chip microcomputer through the RS422 communication module; The MSP430 single-chip microcomputer is connected to the RS422 communication module, and the RS422 communication module is connected to the anti-icing controller to send data to the anti-icing controller through the RS422 communication module; The MSP430 single-chip microcomputer is connected to the Darlington driver array, and the Darlington driver array is connected to the relay.

Description

Technical Field

[0001] The invention patent relates to a design of a power distribution control for an electrically heated rotor of a helicopter for anti-icing, and relates to a power distribution control system for anti-icing of a helicopter. Background Art

[0002] When a helicopter flies in an environment of -20°C to 0°C, water vapor or ice crystals in the air will condense into ice on the surface of the airframe or the rotor. If the ice cannot be removed in time, the vibration of the helicopter will increase, thereby threatening the flight safety of the helicopter.

[0003] Currently, the mainstream helicopters all use the form of electric heating for rotor anti-icing. However, there is currently no solution on how to ensure that the anti-icing system can obtain stable and reliable power supply. Summary of the Invention

[0004] The present application provides a power distribution control system for anti-icing of a helicopter, which ensures that the anti-icing system can obtain stable and reliable power supply and prevents the rotor anti-icing system from failing due to power system failures.

[0005] Technical solution: A helicopter anti-icing power distribution control system includes a power supply switching contactor, contactor A, contactor B, a logic control module, and a current / voltage detection module. Among them: The 28V DC on the aircraft is connected to a 30W 28V-to-5V power supply module to supply power to the electric heating rotor anti-icing power distribution architecture with 28V DC on the aircraft; The 5V power supply module is connected to a multi-channel AD chip, an MSP430 single-chip microcomputer, an opto-isolation chip, a Darlington drive array, and a relay to supply power to the above-mentioned devices; The multi-channel AD chip is connected to the MSP430 single-chip microcomputer and sends digital signals to the MSP430 single-chip microcomputer; The anti-icing controller is connected to the RS422 communication module, and the RS422 communication module is connected to the MSP430 single-chip microcomputer to send data to the MSP430 single-chip microcomputer through the RS422 communication module; The MSP430 single-chip microcomputer is connected to the RS422 communication module, and the RS422 communication module is connected to the anti-icing controller to send data to the anti-icing controller through the RS422 communication module; The MSP430 single-chip microcomputer is connected to the Darlington drive array, and the Darlington drive array is connected to the relay to control the relay through the Darlington drive array with control instructions; The relay is connected to the power supply switching contactor to control the power contactor to turn on or off with the control instructions received from the MSP430 single-chip microcomputer; The power supply switching contactor is connected to the 1# AC power supply system and the 3# AC power supply system to supply 115V three-phase alternating current of the 1# or 3# AC power supply system to contactor A; The power supply switching contactor is connected to contactor A to supply the received 115V three-phase alternating current to the main rotor heating component; The 2# AC power supply system is connected to contactor B to supply 115V three-phase alternating current of the 2# AC power supply system to the power supply switching contactor B; Contactor B is connected to the tail rotor blade heating component to supply the received 115V three-phase alternating current to the tail rotor heating component; The 1# AC power supply system is connected to the 2# AC power supply system, and the 1# and 2# AC power supply systems are backups for each other, that is, when a certain AC power supply system fails, the load powered by it is powered by another non-failed AC power supply system.

[0006] Specifically, the power supply switching contactor, contactor A, contactor B, and the power supply system fault signal are all connected to the opto-isolation chip, and the opto-isolation chip is connected to the MSP430 single-chip microcomputer. The opto-isolation chip sends the working feedback signal of the power supply switching contactor, the working feedback signal of contactor A, the working feedback signal of contactor B, and the power supply system fault signal to the MSP430 single-chip microcomputer.

[0007] Specifically, the voltage division sampling circuit is connected to the blade heating component to collect the AC voltage of the main / tail rotor blade heating group. The voltage division sampling circuit is connected to the operational amplifier follower circuit to achieve high-impedance input and low-impedance output. The operational amplifier follower circuit is connected to the RMS sampling chip to convert the collected AC voltage into a DC voltage, and the DC voltage is sent to the multi-channel AD chip through the operational amplifier follower circuit.

[0008] Specifically, the Hall sensor is connected to the blade heating assembly to collect the current of the main / tail rotor blade heating assembly. The Hall sensor converts the collected current signal into a DC voltage and is connected to the operational amplifier follower circuit to send the DC voltage to the multi-channel AD chip through the operational amplifier follower circuit.

[0009] Specifically, under normal circumstances, the controller sends a check instruction to the logic control module. The logic control module controls the contactor to make the main rotor and tail rotor heating assemblies work, and evaluates whether the main rotor and tail rotor heating assemblies are in good condition based on the measured voltage and current data. If the heating assembly is in good condition, it is determined whether rotor anti-icing is required according to whether the helicopter is in an icing environment.

[0010] Specifically, when performing rotor anti-icing, the 1# power supply powers the main rotor heating assembly, and the 2# power supply powers the tail rotor heating assembly.

[0011] Specifically, when the 1# power supply system fails and the logic control module receives a power supply system fault signal, the logic control module controls the power supply switching contactor to make the 3# power supply system power the main rotor heating assembly.

[0012] Specifically, when the 2# power supply system fails, since the conversion of the helicopter power supply system is that the 1# power supply system supplies power to the load of the 2# power supply system, at this time, the logic control module controls the power supply switching contactor to make the 3# power supply system power the main rotor heating assembly, so as to realize that when a single power supply system fails, the rotor anti-icing system can still work normally.

[0013] In summary, the present application provides a helicopter anti-icing power distribution control system. For helicopters of dual-power or multi-power types, this architecture can realize the switching of the rotor anti-icing system between different power supply systems. At the same time, when a certain power supply system fails, this control architecture can ensure that the rotor anti-icing system can still work normally. At the same time, this architecture can detect the current and voltage of the main rotor and tail rotor heating power supply in real time, and then perform health management on the blade heating assembly, thereby improving the reliability, testability and robustness of the system. Brief Description of the Drawings

[0014] Figure 1 It is a schematic structural diagram of a helicopter anti-icing power distribution control system provided by the present application. Detailed Embodiment

[0015] The architecture described in this patent is based on a 115V three-phase AC power supply system, and the AC power supply system includes multiple sets of independent AC power supply systems. This patent design provides a power distribution control architecture for the electric heating anti-icing system. This architecture can realize heating for the main rotor and tail rotor while ensuring that the system can still guarantee the normal operation of the rotor anti-icing system in the case of a single power supply system failure. Electric heating rotor anti-icing power distribution control architecture

[0016] The following will be further described in detail with reference to the accompanying drawings.

[0017] As Figure 1 shown, this application provides a helicopter anti-icing power distribution control system, including a power supply switching contactor, contactor A, contactor B, a logic control module, and a current / voltage detection module. Among them: The 28V DC on the aircraft is connected to a 30W 28V-to-5V power supply module to supply power to the electric heating rotor anti-icing power distribution architecture with the 28V DC on the aircraft; The 5V power supply module is connected to a multi-channel AD chip, an MSP430 single-chip microcomputer, an optocoupler isolation chip, a Darlington driver array, and a relay to supply power to the above devices; The multi-channel AD chip is connected to the MSP430 single-chip microcomputer to send digital signals to the MSP430 single-chip microcomputer; The anti-icing controller is connected to the RS422 communication module, and the RS422 communication module is connected to the MSP430 single-chip microcomputer to send data to the MSP430 single-chip microcomputer through the RS422 communication module; The MSP430 single-chip microcomputer is connected to the RS422 communication module, and the RS422 communication module is connected to the anti-icing controller to send data to the anti-icing controller through the RS422 communication module; The MSP430 single-chip microcomputer is connected to the Darlington driver array, and the Darlington driver array is connected to the relay to control the relay through the Darlington driver array with control instructions; The relay is connected to the power supply switching contactor to control the power contactor to turn on or off with the control instructions received from the MSP430 single-chip microcomputer; The power supply switching contactor is connected to the 1# AC power supply system and the 3# AC power supply system to supply the 115V three-phase AC power of the 1# or 3# AC power supply system to contactor A; The power supply switching contactor is connected to contactor A to supply the received 115V three-phase AC power to the main rotor heating component; The 2# AC power supply system is connected to contactor B to supply the 115V three-phase AC power of the 2# AC power supply system to the power supply switching contactor B; Contactor B is connected to the tail rotor blade heating component to supply the received 115V three-phase AC power to the tail rotor heating component; The 1# AC power supply system is connected to the 2# AC power supply system, and the 1# and 2# AC power supply systems are backup to each other, that is, when a certain AC power supply system fails, the other non-failed AC power supply system supplies power to the load powered by it.

[0018] Specifically, the power switch contactor, contactor A, contactor B, and the power system fault signal are all connected to the opto-isolation chip. The opto-isolation chip is connected to the MSP430 single-chip microcomputer. The opto-isolation chip sends the working feedback signal of the power switch contactor, the working feedback signal of contactor A, the working feedback signal of contactor B, and the power system fault signal to the MSP430 single-chip microcomputer;

[0019] Specifically, the voltage-dividing sampling circuit is connected to the blade heating component to collect the AC voltage of the main / tail blade heating group. The voltage-dividing sampling circuit is connected to the op-amp follower circuit to achieve high-impedance input and low-impedance output. The op-amp follower circuit is connected to the RMS sampling chip to convert the collected AC voltage into a DC voltage. Similarly, the DC voltage is sent to the multi-channel AD chip through the op-amp follower circuit;

[0020] Specifically, the Hall sensor is connected to the blade heating component to collect the current of the main / tail blade heating component. The Hall sensor converts the collected current signal into a DC voltage. The Hall sensor is connected to the op-amp follower circuit to send the DC voltage to the multi-channel AD chip through the op-amp follower circuit.

[0021] Specifically, under normal circumstances, the controller sends a check instruction to the logic control module. The logic control module controls the contactor to make the main and tail blade heating components work, and evaluates whether the main and tail blade heating components are in good condition through the measured voltage and current data. If the heating components are in good condition, it is judged whether rotor anti-icing is required according to whether the helicopter is in an icing environment.

[0022] Specifically, when performing rotor anti-icing, the 1# power supply powers the main blade heating component, and the 2# power supply powers the tail blade heating component.

[0023] Specifically, when the 1# power supply system fails and the logic control module receives the power system fault signal, the logic control module controls the power switch contactor to make the 3# power supply system power the main blade heating component;

[0024] Specifically, when the 2# power supply system fails, since the conversion of the helicopter power supply system is that the 1# power supply system powers the load of the 2# power supply system (that is, the 1# power supply system powers the tail blade heating component at this time), the logic control module controls the power switch contactor to make the 3# power supply system power the main blade heating component at this time, so as to realize that when a single power supply system fails, the rotor anti-icing system can still work normally.

[0025] The power distribution architecture for electro-heated rotor anti-icing is powered by two power sources, namely the 28V DC power on the aircraft and the 115V / 400Hz AC power of No. 1 - 3 on the aircraft. At the same time, the logic control module mainly communicates with the anti-icing controller through the RS422 bus, sending the status of each unit of the anti-icing power distribution architecture and the voltage and current of the blade heating components to the anti-icing controller. The 28V DC power on the aircraft powers the MSP430 single-chip microcomputer, multi-channel AD chip, Darlington driver array, opto-isolation chip, RS422 communication chip, and relay through a 30W 28V to 5V power module. The 1# and 3# AC power supplies respectively power the power switch contactors, the 2# AC power supply powers Contactor B, then Contactor A powers the main rotor heating component, and Contactor B powers the tail rotor heating component. The 1# and 2# AC power supplies are backup to each other. The MSP430 single-chip microcomputer controls the Darlington driver array and then controls the relay, and then controls the power conversion contactor and Contactor A through the relay, so as to realize the switching of the 1# and 3# AC power supplies and achieve the dual-redundancy 115V power supply for the main rotor heating component. Similarly, the MSP430 single-chip microcomputer controls the Darlington driver array and then controls the relay, and then controls Contactor B through the relay, so as to realize the 115V power supply for the tail rotor heating component. The dual-redundancy power supply for the tail rotor is realized through the mutual backup of the power system. At the same time, the above-mentioned contactors all feedback the contactor action signals to the MSP430 single-chip microcomputer through the opto-isolation chip. The voltage of the blade heating component passes through the voltage division and sampling circuit, then through the operational amplifier follower, and then through the RMS sampling chip to convert the AC voltage into a DC voltage, and then through the operational amplifier follower circuit, and finally through the multi-channel AD chip to convert the 115V voltage analog quantity into a digital quantity, and finally send the digital signal to the single-chip microcomputer. The single-chip microcomputer sends the voltage value of the blade heating component to the anti-icing controller through the RS422 communication module; the current of the blade heating group passes through the Hall sensor to convert the current value into a voltage value, and then through the operational amplifier follower circuit to convert the DC voltage into a digital signal through the AD chip and send it to the single-chip microcomputer, and finally the single-chip microcomputer sends the current value of the blade heating component to the anti-icing controller through the RS422 communication module. Because the electric power required for electro-heated rotor anti-icing is relatively large, when the power system fails, the anti-icing system needs to automatically unload the blade heating components.

[0026] In summary, the key technologies of this application are mainly as follows:

[0027] a) Through experimental verification, power distribution for the heating components of the main rotor and tail rotor can be achieved in an icing environment;

[0028] b) Through simulation and experimental verification, power supply to the heating components of the main rotor and tail rotor can still be achieved when a single power system fails;

[0029] c) The logic control module is used to switch the power supply of the anti-icing system between different power systems when the power system fails;

[0030] d) The logic control module is used to control the power supply of the main rotor heating component and the tail rotor heating component;

[0031] e) The data measured by the voltage and current detection module is sent to the logic control module for calculation, and then the logic control module sends the data to the anti-icing controller. The anti-icing controller uses an expert algorithm to monitor the health of the heating components of the main rotor blade and the tail rotor.

[0032] In summary, the technical effects of this application are as follows:

[0033] Compared with the current power distribution control architecture for electrically heated rotor anti-icing, the system described in this patent has the following advantages:

[0034] a) The added power supply selection function can flexibly select the power supply according to the power system failure, without being limited to a single-channel conversion;

[0035] b) When the power system fails, the anti-icing system can still work, improving the reliability of the anti-icing power distribution system.

[0036] c) By measuring the voltage / current of the blade, the health monitoring of the blade heating component can be realized, improving the testability of the system.

[0037] The principle and implementation method of the patent are described in the text. It should be noted that without departing from the principle of the present invention, several improvements and modifications can be made to it, but these improvements and modifications also fall within the protection scope of the patent claims.

Claims

1. A helicopter anti-icing power distribution control system, characterized in that, It includes a power supply switching contactor, contactor A, contactor B, a logic control module, and a current / voltage detection module, where: The 28V DC on the aircraft is connected to a 30W 28V-to-5V power supply module to supply power to the electrical heating rotor anti-icing power distribution architecture with 28V DC on the aircraft; the 5V power supply module is connected to a multi-channel AD chip, an MSP430 single-chip microcomputer, an optocoupler isolation chip, a Darlington driver array, and a relay to supply power to the above-mentioned devices; the multi-channel AD chip is connected to the MSP430 single-chip microcomputer to send digital signals to the MSP430 single-chip microcomputer; the anti-icing controller is connected to an RS422 communication module, and the RS422 communication module is connected to the MSP430 single-chip microcomputer to send data to the MSP430 single-chip microcomputer through the RS422 communication module; the MSP430 single-chip microcomputer is connected to the RS422 communication module, and the RS422 communication module is connected to the anti-icing controller to send data to the anti-icing controller through the RS422 communication module; the MSP430 single-chip microcomputer is connected to the Darlington driver array, and the Darlington driver array is connected to the relay to control the relay through the Darlington driver array with control instructions; the relay is connected to the power supply switching contactor to control the power contactor to turn on or off according to the control instructions of the MSP430 single-chip microcomputer received; the power supply switching contactor is connected to the 1# AC power supply system and the 3# AC power supply system to supply 115V three-phase alternating current of the 1# or 3# AC power supply system to contactor A; the power supply switching contactor is connected to contactor A to supply the received 115V three-phase alternating current to the main rotor heating component; the 2# AC power supply system is connected to contactor B to supply 115V three-phase alternating current of the 2# AC power supply system to the power supply switching contactor B; contactor B is connected to the tail rotor blade heating component to supply the received 115V three-phase alternating current to the tail rotor heating component; the 1# AC power supply system is connected to the 2# AC power supply system, and the 1# and 2# AC power supply systems are backup to each other, that is, when a certain AC power supply system fails, the load powered by it is powered by another non-failed AC power supply system.

2. The helicopter anti-icing power distribution control system according to claim 1, characterized in that The power supply switching contactor, contactor A, contactor B, and the power supply system fault signal are all connected to the optocoupler isolation chip, and the optocoupler isolation chip is connected to the MSP430 single-chip microcomputer. The optocoupler isolation chip sends the working feedback signal of the power supply switching contactor, the working feedback signal of contactor A, the working feedback signal of contactor B, and the power supply system fault signal to the MSP430 single-chip microcomputer.

3. The helicopter anti-icing power distribution control system according to claim 1, characterized in that, The voltage-dividing sampling circuit is connected to the blade heating component to collect the AC voltage of the main / tail rotor blade heating group. The voltage-dividing sampling circuit is connected to the operational amplifier follower circuit to achieve high-impedance input and low-impedance output. The operational amplifier follower circuit is connected to the RMS sampling chip to convert the collected AC voltage into a DC voltage, and the DC voltage is sent to the multi-channel AD chip through the operational amplifier follower circuit.

4. The helicopter anti-icing power distribution control system according to claim 1, wherein The Hall sensor is connected to the blade heating component to collect the current of the main / tail rotor blade heating component. The Hall sensor converts the collected current signal into a DC voltage. The Hall sensor is connected to the operational amplifier follower circuit to send the DC voltage to the multi-channel AD chip through the operational amplifier follower circuit.

5. The helicopter anti-icing power distribution control system according to claim 1, wherein Under normal circumstances, the controller sends a check instruction to the logic control module. The logic control module controls the contactor to make the main rotor and tail rotor heating components work, and evaluates whether the main rotor and tail rotor heating components are in good condition through the measured voltage and current data; if the heating components are in good condition, it is judged whether rotor anti-icing is required according to whether the helicopter is in an icing environment.

6. The helicopter anti-icing power distribution control system according to claim 1, characterized in that When performing rotor anti-icing, the 1# power supply powers the main rotor heating component, and the 2# power supply powers the tail rotor heating component.

7. The helicopter anti-icing power distribution control system according to claim 1, characterized in that, When the 1# power supply system fails and the logic control module receives a power supply system fault signal, the logic control module controls the power supply switching contactor to make the 3# power supply system power the main rotor heating component.

8. The helicopter anti-icing power distribution control system according to claim 1, characterized in that, When the 2# power supply system fails, since the conversion of the helicopter power supply system is that the 1# power supply system powers the load of the 2# power supply system, at this time the logic control module controls the power supply switching contactor to make the 3# power supply system power the main rotor heating component, so as to realize that when a single power supply system fails, the rotor anti-icing system can still work normally.

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