Helicopter rotor anti-icing and de-icing system based on 270V direct-current power supply and control method

Abstract

The invention belongs to the technical field of rotor anti-icing and de-icing systems, and discloses a helicopter rotor anti-icing and de-icing system based on a 270V direct-current power supply and a control method, and the system comprises two icing detection sensors which are used for detecting icing signals; the icing signal processor is connected with the fly pipe computer, judges whether icing occurs or not according to the icing detection signal and transmits a result to the fly pipe computer; the flight pipe computer is connected with the atmospheric static temperature system and the man-machine interaction system, and the man-machine interaction system is used for displaying whether freezing occurs or not, receiving a control instruction of a pilot and transmitting the atmospheric static temperature and the control instruction to the anti-icing and deicing distribution box; the anti-icing and deicing distribution box is connected with the atmospheric temperature sensor, the 270 DC power supply and the main and tail rotor collector rings, the current temperature is determined according to the atmospheric temperature sensor and the atmospheric static temperature, and the deicing time is calculated according to the current temperature; and the main rotor heating assembly and the tail rotor heating assembly are respectively connected with the main rotor collector ring and the tail rotor collector ring and are used for heating and deicing by utilizing power supplies from the main rotor collector ring and the tail rotor collector ring.

Description

Technical Field

[0001] The invention belongs to the technical field of rotor anti-icing systems, and in particular relates to a helicopter rotor anti-icing system based on a 270V direct current power supply and a control method. Background Art

[0002] When a helicopter flies in an environment of -20℃ to 0℃, water vapor or ice crystals in the air will condense into ice on the surface of the fuselage or the rotor. If the ice is not removed in time, the vibration of the helicopter will increase, thus threatening the flight safety of the helicopter. At present, the power supply of the mainstream rotor anti-icing system in China is AC 400Hz / 115V, but this power supply type makes the control logic and power supply switching logic of the rotor anti-icing system extremely complex, and the weight of the rotor anti-icing system remains high. If DC 270V power supply is adopted, the power supply logic of the rotor anti-icing system can be simplified and the system weight can be reduced. Summary of the invention

[0003] Purpose of the invention: To propose a helicopter rotor anti-icing system and control method based on a 270V DC power supply. The biggest difference between this system and other helicopter rotor anti-icing system configurations is that this system is powered by a DC 270V power supply system. This configuration can simplify the power supply logic of the rotor anti-icing system and the power distribution logic of the blade heating assembly, while also reducing the system weight and streamlining the rotor anti-icing system architecture.

[0004] Technical Solution

[0005] A helicopter rotor anti-icing system based on a 270V DC power supply comprises: two icing detection sensors, both connected to an icing signal processor, for detecting icing signals;

[0006] An icing signal processor is connected to the flight tube computer, determines whether there is icing according to the detected icing signal, and transmits the result to the flight tube computer;

[0007] The flight control computer is connected to the atmospheric static temperature system and the human-computer interaction system. The human-computer interaction system is used to display whether there is icing, receive the pilot's control command, and transmit the atmospheric static temperature and control command to the anti-icing distribution box;

[0008] The anti-icing distribution box is connected to the atmospheric temperature sensor, 270 DC power supply and the main and tail rotor collector rings, determines the current temperature according to the atmospheric temperature sensor and the atmospheric static temperature, and calculates the deicing time according to the current temperature;

[0009] The main and tail rotor heating components are connected to the main and tail rotor collector rings, respectively, and use the power from the main and tail rotor collector rings to heat and de-ice.

[0010] Furthermore, the icing signal processor determines that the helicopter is in an icing environment when an icing signal appears in any one of the two icing detection sensors.

[0011] Furthermore, the flight tube computer receives two independent channels of atmospheric static temperature data from the atmospheric static temperature system;

[0012] The anti-icing distribution box votes out the current temperature data based on two independent atmospheric static temperature data and the data from the atmospheric temperature sensor.

[0013] Furthermore, the main rotor collector ring includes: a conductive ring and a brush, which converts the static 270V high voltage electricity into 270V high voltage electricity in a rotating state. The tail rotor collector ring is similar to the main rotor collector ring.

[0014] Further, the main propeller heating assembly includes six heating units;

[0015] The main rotor collector ring includes seven brushes. One end of each of the six heating units is connected to a brush and then to a conductive ring. The other ends of the six heating units are connected together to a brush and then to the conductive ring.

[0016] Furthermore, the heating time T of each of the six heating units of the main propeller heating assembly is on The formula is as follows:

[0017]

[0018] Where a and b are constants determined by ice wind tunnel test data, and OAT is the current temperature;

[0019] Calculate the switching time T of each of the six heating units of the main propeller heating assembly OFF The formula is as follows:

[0020] T OFF =c+OAT seconds

[0021] Where c is a constant determined from ice wind tunnel test data, and OAT is the current temperature.

[0022] Further, the tail rotor heating assembly includes two heating units;

[0023] The main propeller collector ring includes two brushes. One end of each of the two heating units is connected to a brush and then to a conductive ring. The other ends of the two heating units are connected to a brush and then to a conductive ring.

[0024] Furthermore, the heating time T of each of the six heating units of the main propeller heating assembly is on1 The formula is as follows:

[0025]

[0026] Where A and B are constants determined by ice wind tunnel test data, and OAT is the current ambient temperature;

[0027] Calculate the switching time T of each of the six heating units of the main propeller heating assembly OFF1 The formula is as follows:

[0028] T OFF1 =C+OAT seconds

[0029] Where C is a constant determined by ice wind tunnel test data, and OAT is the current ambient temperature.

[0030] A helicopter rotor anti-icing system control method based on a 270V DC power supply, the process is as follows:

[0031] Step 1: The pilot selects the rotor anti-icing working mode to automatic;

[0032] Step 2: The ice detection subsystem, atmospheric static temperature system, atmospheric temperature sensor and flight tube computer are working;

[0033] Step 3: The icing detection subsystem detects an icing signal and sends the icing signal to the human-computer interaction system for the pilot to view, and simultaneously sends an icing warning signal to the flight control computer;

[0034] Step 4: The flight control computer sends the control command of connecting the rotor anti-icing system and two-way atmospheric static temperature data to the anti-icing distribution box, and the anti-icing distribution box works;

[0035] Step 5: The anti-icing distribution box collects the atmospheric temperature sensor data, and simultaneously votes on the atmospheric temperature sensor and the two-way atmospheric static temperature to determine the current temperature;

[0036] Step 6: The anti-icing distribution box distributes the 270V power supply 1 to the 6 conductive rings and brushes of the main rotor collector ring through 6 IGBTs, and the main rotor collector ring supplies 270V to the main rotor heating assembly;

[0037] Step 7: The anti-icing distribution box distributes the 270V power supply 2 to the 2 conductive rings and brushes of the tail rotor collector ring through 2 IGBTs, and the tail rotor collector ring supplies 270V to the tail rotor heating assembly;

[0038] Step 8: When the main and tail rotor heating components are working, the anti-icing distribution box measures the current of the main and tail rotor heating components in real time, and determines whether the current is within the normal range. If it is within the normal range, the anti-icing distribution box sends the anti-icing working signal to the flight control computer, which then sends it to the human-computer interaction system.

[0039] Step 9: The pilot observes through the human-computer interaction system that the rotor anti-icing system is working.

[0040] A helicopter rotor anti-icing system control method based on a 270V DC power supply, the process is as follows:

[0041] Step 1: The pilot selects the rotor de-icing working mode as manual;

[0042] Step 2: The ice detection subsystem, atmospheric static temperature system, atmospheric temperature sensor and flight tube computer are working;

[0043] Step 3: The icing detection subsystem detects an icing signal and sends the icing signal to the human-computer interaction system for the pilot to view. The pilot sends a control command to turn on the rotor anti-icing system to the flight control computer through the human-computer interaction system.

[0044] Step 4: The flight control computer sends the control command of connecting the rotor anti-icing system and two-way atmospheric static temperature data to the anti-icing distribution box, and the anti-icing distribution box works;

[0045] Step 5: The anti-icing distribution box collects the atmospheric temperature sensor data, and simultaneously votes on the atmospheric temperature sensor and the two-way atmospheric static temperature to determine the current ambient temperature;

[0046] Step 6: The anti-icing distribution box distributes the 270V power supply 1 to the 6-way conductive ring and brushes of the main rotor collector ring through 6 IGBTs, and the main rotor collector ring supplies 270V to the main rotor heating assembly;

[0047] Step 7: The anti-icing distribution box distributes the 270V power supply 2 to the 2 conductive rings and brushes of the tail rotor collector ring through 2 I GBTs, and the tail rotor collector ring supplies 270V to the tail rotor heating assembly;

[0048] Step 8: When the main and tail rotor heating components are working, the anti-icing distribution box measures the current of the main and tail rotor heating components in real time, and determines whether the current is within the normal range. If it is within the normal range, the anti-icing distribution box sends the anti-icing working signal to the flight control computer, which then sends it to the human-computer interaction system.

[0049] Step 9: The pilot observes through the human-computer interaction system that the rotor anti-icing system is working.

[0050] In summary, the beneficial effects of the present invention are as follows:

[0051] a) Compared with the rotor de-icing system powered by the traditional AC 115V power system, the system of this configuration is planned to reduce weight by 10kg;

[0052] b) Compared with the rotor anti-icing system powered by the traditional AC 115V AC power system, the power distribution control of the blade heating assembly under this configuration is simple and reliable, and the control rate does not need to be monitored in real time;

[0053] c) This architecture realizes the highly integrated functions of the rotor anti-icing system and the whole aircraft system;

[0054] d) It is possible to disconnect the blade heating power supply within 0.1ms, thereby realizing the short-circuit protection function of the blade heating component;

[0055] e) Realize the dual margin function of icing alarm. BRIEF DESCRIPTION OF THE DRAWINGS

[0056] Figure 1 This is the schematic diagram of the helicopter rotor anti-icing system based on a 270V DC power supply system.

[0057] Figure 2 This is the internal principle block diagram of the de-icing distribution box;

[0058] Figure 4 This is the schematic diagram of the short-circuit protection circuit;

[0059] Figure 3 This is a schematic diagram of the collector ring wiring. DETAILED DESCRIPTION

[0060] A helicopter rotor anti-icing system based on a 270V DC power supply includes an "ice detection sensor A", an "ice detection sensor B", an "icing signal processor", an "atmospheric temperature sensor", a "flight tube computer", an "anti-icing distribution box", a "main rotor collector ring", a "main rotor heating assembly", a "tail rotor collector ring" and a "tail rotor heating assembly". This configuration can achieve reliable and stable operation of the rotor anti-icing system under DC270V power supply. The principle block diagram of this configuration is as follows: Figure 1 shown.

[0061] Under normal circumstances, when the helicopter enters an icing environment, the icing signal is first detected by the icing detection sensor, which then sends the icing information to the icing signal processor. The icing signal processor confirms the icing information and sends the icing result to the flight control computer and the human-computer interaction system after confirmation. The pilot controls the human-computer interaction system to send a control command to turn on the rotor anti-icing system according to the icing status displayed on the human-computer interaction system. When the flight control computer receives the control command to turn on the rotor anti-icing system sent by the human-computer interaction system, it controls the anti-icing distribution box to supply DC 270V power to the main and tail rotor collector rings, which then transmit the power to the main and tail rotor heating components to realize the blade heating function.

[0062] Ice Detection Subsystem

[0063] Ice detection sensors A and B and the ice signal processor are used together to realize the ice detection function. When the ice signal processor determines that any ice detection sensor has an ice signal, it is considered that the helicopter is in an icing environment. When both ice detection sensors do not detect an ice signal, it is considered that the helicopter is not in an icing environment. The two ice detectors are used as backup for each other.

[0064] Atmospheric Temperature Subsystem

[0065] The rotor anti-icing system includes an atmospheric temperature sensor for detecting the atmospheric temperature of the helicopter's environment. At the same time, the rotor anti-icing system also receives two independent atmospheric static temperature data through the flight tube computer. The anti-icing distribution box determines an accurate atmospheric temperature through voting, and the atmospheric temperature is used as the input of the rotor anti-icing control rate.

[0066] Blade heating assembly subsystem

[0067] The blade heating assembly subsystem includes a main rotor heating assembly and a tail rotor heating assembly. The main rotor heating assembly is divided into 6 heating zones, and the tail rotor heating assembly is divided into 2 heating zones.

[0068] Power Delivery Subsystem

[0069] The power transmission subsystem includes the main rotor collector ring assembly and the tail rotor collector ring assembly. The collector ring assembly is mainly composed of a conductive ring and a brush, which can convert the static 270V high voltage electricity into a rotating 270V high voltage electricity. The connection relationship between the main rotor collector ring assembly and the tail rotor collector ring assembly and the blade heating assembly is detailed in Figure 3 The positive end of the DC270V power supply is connected to the positive ends of the six heating components, and the negative ends of the six heating components are connected together. The connection method of the tail rotor heating component is similar to that of the main blade heating component.

[0070] Distribution subsystem

[0071] The distribution subsystem is composed of an anti-icing distribution box, which has the function of receiving and connecting the rotor anti-icing system command. When the pilot operates the human-computer interaction system to send the rotor anti-icing connection control command, the human-computer interaction system sends the rotor anti-icing system connection command to the flight tube computer. The flight tube computer sends the control command to connect the rotor anti-icing system to the anti-icing distribution box based on the icing warning information sent by the icing signal processor. At the same time, after receiving the control command to connect the rotor anti-icing system, the anti-icing distribution box generates a control rate based on the received atmospheric temperature data and the two-way atmospheric temperature data sent by the flight tube computer, and controls the connection and disconnection of the IGBT to realize the cyclic heating of the blades, thereby realizing the anti-icing of the blades.

[0072] The anti-icing distribution box sends the parameters and fault information of the rotor anti-icing system to the flight control computer in real time. The flight control computer will perform secondary processing on the received rotor anti-icing system data and send the system faults and system operation suggestions to the human-computer interaction system.

[0073] The internal principle diagram of the anti-icing distribution box is as follows: Figure 2 In order to realize the function of this configuration, the anti-icing distribution box should have communication function, heating component short-circuit protection function, I GBT module, data processing function, driving function and control command receiving function. The role of each function is as follows;

[0074] a) Communication function: used for communication between the anti-icing distribution box and the flight control computer;

[0075] b) Heating component short circuit protection function: when the blade heating component is short-circuited, it is used to heat the heating component for short-circuit protection;

[0076] c) Data processing function: collect and process the parameters of the drive function and IGBT module;

[0077] d) Control command receiving function: receiving control commands from the flight control computer;

[0078] e) Driving function: converting the control rate generated by the data processing function into driving instructions, thereby driving the IGBT module;

[0079] f) IGBT module: transmits the DC 270V on the machine to the blade heating component according to the instruction cycle sent by the drive function.

[0080] The logical relationship between the modules of the anti-icing distribution box is as follows:

[0081] The CAN bus communication module is used to realize the communication between the flight control computer and the anti-icing controller. The flight control computer sends the rotor anti-icing control instructions and atmospheric static temperature data to the anti-icing distribution box through the bus. The anti-icing distribution box sends the current information of each heating component and the fault information of the internal components of the anti-icing distribution box to the flight control computer through the CAN bus. The communication module transmits the control instructions to the processor, and the processor connects the IGBT module according to the control instructions. At the same time, the processor solves the control rate at the current temperature according to the received atmospheric static temperature data and the data collected by the temperature sensor. And the IGBT of the corresponding heating component is turned on or off according to the control rate.

[0082] The atmospheric temperature sensor uses a Pt100 platinum resistance temperature sensor to convert the temperature signal into a digital signal through the differential sampling and AD conversion circuit inside the anti-icing distribution box and transmit it to the processor. The processor votes on the temperature with the two atmospheric static temperatures sent by the flight tube computer. The average of the two temperatures with the smallest difference is taken as the current ambient temperature.

[0083] Under normal circumstances, the anti-icing distribution box mainly uses the control instructions of the CAN bus data. When the CAN bus communication fails, the anti-icing distribution box uses the ground-opening signal (discrete quantity) sent by the flight tube computer as the control instruction to implement a dual-redundancy design of the anti-icing control instructions. Ensure the reliability of the rotor anti-icing system. The discrete quantity control instruction is converted into a low-level voltage signal recognized by the processor through an optoelectronic coupling module. Based on the signal, the processor sends a high-level signal, which is used as the input of the drive circuit. The drive circuit uses a Darlington module drive circuit. This circuit can achieve the function of high-level signal power amplification. The amplified high level can drive the enable end of the IGBT, and the IGBT is turned on, thereby transmitting 270V+ to the conductive ring (see Figure 3 ), and finally to the positive end of the blade heating assembly. When the processor sends a low-level signal, the IGBT is disconnected, which stops the transmission of 270V+ to the conductive ring and the blade heating assembly stops working.

[0084] Design of short-circuit protection circuit: Since IGBT has the function of measuring current, different currents correspond to different voltages. The larger the current, the higher the voltage. The short-circuit protection circuit is mainly composed of a comparator (see Figure 4 ), the voltage value output by the IGBT to represent the current value is compared with the voltage value of the comparator "-", and the voltage value corresponding to the maximum current of the blade heating component when it is working is used as the "-" of the comparison circuit. When the current output by the IGBT is greater than the maximum value of the working current of the heating component, the short-circuit protection circuit outputs a low level to the enable terminal of the IBGT, and then the IGBT is disconnected, finally realizing the short-circuit protection of the heating component.

[0085] The tail rotor heating operation, short-circuit protection, and control rate generation are similar to those of the main rotor blade heating assembly. Once the de-icing distribution box receives the control command, the main rotor heating circuit and the tail rotor instant heating circuit are connected at the same time. However, the control rate of the main rotor de-icing and the control rate of the tail rotor anti-icing are inconsistent, resulting in inconsistent IGBT on-off cycles.

[0086] Rotor anti-icing control rate

[0087] The heating component is controlled by a periodic heating method. For helicopters with multiple main blades, the heating component is set up in zones, that is, each main blade contains 6 zones, each zone is arranged along the blade chord length, and from the upper edge to the lower edge of the blade, there are 1-2-3-4-5-6 zones in sequence. The negative ends of all heating components are connected through negative lines pre-buried inside the blades. For multiple tail blades, the heating component is also set up in zones. Similar to the main blades, the zones are also distributed along the blade chord length, with the upper part of the blade being zone 1 and the lower part being zone 2. According to historical experience and test data, the heating sequence of the main blade heating component for one cycle is determined to be 3→2→4→1→5→6, that is, the leading edge of the blade is heated first. The tail blade is heated in a heating cycle in the order of 2→1→2, that is, the lower part of the blade is heated for a longer time. When switching between heating zones, heating needs to be stopped. The blade heating algorithm is as follows:

[0088] Main propeller heating algorithm: heating time T for each zone on

[0089]

[0090] Where a and b are constants determined by ice wind tunnel test data, and OAT is the current ambient temperature.

[0091] The switching time of each heating zone is T OFF

[0092] T OFF =c+OAT seconds T OFF =c+OAT seconds

[0093] Where c is a constant determined from the ice wind tunnel test data, and OAT is the current ambient temperature.

[0094] Tail rotor heating algorithm, heating time T for each heating zone on1

[0095]

[0096] Where A and B are constants determined by ice wind tunnel test data, and OAT is the current ambient temperature. Assuming the current ambient temperature is -10℃, coefficient A is 3, and coefficient B is 10, then T ON1 =10+3×0.5=11.5S.

[0097] The switching time of each heating zone is T OFF1

[0098] T OFF1 =C+OAT seconds

[0099] Where C is a constant determined by the ice wind tunnel test data, and OAT is the current ambient temperature. Assuming the current ambient temperature is -10°C and the coefficient C is 20, then T OFF1 =50-10=40S.

[0100] Therefore, the main propeller heating cycle is: zone 3 heats for 11.5 seconds and disconnects for 40 seconds → zone 2 heats for 11.5 seconds and disconnects for 40 seconds → zone 4 heats for 11.5 seconds and disconnects for 40 seconds → zone 1 heats for 11.5 seconds and disconnects for 40 seconds → zone 5 heats for 11.5 seconds and disconnects for 40 seconds → zone 6 heats for 11.5 seconds and disconnects for 40 seconds.

[0101] System control method:

[0102] 1) Automatic control of the system under normal working conditions

[0103] Step 1: The pilot selects the rotor anti-icing working mode to automatic;

[0104] Step 2: The electric equipment such as the ice detection subsystem, atmospheric static temperature system, atmospheric temperature sensor and flight tube computer are working;

[0105] Step 3: The icing detection subsystem detects an icing signal and sends the icing signal to the human-computer interaction system for the pilot to view, and simultaneously sends an icing warning signal to the flight control computer;

[0106] Step 4: The flight control computer sends the control command of connecting the rotor anti-icing system and two-way atmospheric static temperature data to the anti-icing distribution box, and the anti-icing distribution box works;

[0107] Step 5: The anti-icing distribution box collects the atmospheric temperature sensor data, and simultaneously votes on the atmospheric temperature sensor and the two-way atmospheric static temperature to determine the current ambient temperature;

[0108] Step 6: The anti-icing distribution box distributes the 270V power supply 1 to the 6-way conductive ring and brushes of the main rotor collector ring through 6 IGBTs, and the main rotor collector ring supplies 270V to the main rotor heating assembly;

[0109] Step 7: The anti-icing distribution box distributes the 270V power supply 2 to the 2 conductive rings and brushes of the tail rotor collector ring through 2 I GBTs, and the tail rotor collector ring supplies 270V to the tail rotor heating assembly;

[0110] Step 8: When the main and tail rotor heating components are working, the anti-icing distribution box measures the current of the main and tail rotor heating components in real time, and determines whether the current is within the normal range. If it is within the normal range, the anti-icing distribution box sends the anti-icing working signal to the flight control computer, which then sends it to the human-computer interaction system.

[0111] Step 9: The pilot observes through the human-computer interaction system that the rotor anti-icing system is working.

[0112] 2) Manual control of the system under normal working conditions

[0113] Step 1: The pilot selects the rotor de-icing working mode as manual;

[0114] Step 2: The electric equipment such as the ice detection subsystem, atmospheric static temperature system, atmospheric temperature sensor and flight tube computer are working;

[0115] Step 3: The icing detection subsystem detects an icing signal and sends the icing signal to the human-computer interaction system for the pilot to view. The pilot sends a control command to turn on the rotor anti-icing system to the flight control computer through the human-computer interaction system.

[0116] Step 4: The flight control computer sends the control command of connecting the rotor anti-icing system and two-way atmospheric static temperature data to the anti-icing distribution box, and the anti-icing distribution box works;

[0117] Step 5: The anti-icing distribution box collects the atmospheric temperature sensor data, and simultaneously votes on the atmospheric temperature sensor and the two-way atmospheric static temperature to determine the current ambient temperature;

[0118] Step 6: The anti-icing distribution box distributes the 270V power supply 1 to the 6-way conductive ring and brushes of the main rotor collector ring through 6 IGBTs, and the main rotor collector ring supplies 270V to the main rotor heating assembly;

[0119] Step 7: The anti-icing distribution box distributes the 270V power supply 2 to the 2 conductive rings and brushes of the tail rotor collector ring through 2 I GBTs, and the tail rotor collector ring supplies 270V to the tail rotor heating assembly;

[0120] Step 8: When the main and tail rotor heating components are working, the anti-icing distribution box measures the current of the main and tail rotor heating components in real time, and determines whether the current is within the normal range. If it is within the normal range, the anti-icing distribution box sends the anti-icing working signal to the flight control computer, which then sends it to the human-computer interaction system.

[0121] Step 9: The pilot observes through the human-computer interaction system that the rotor anti-icing system is working.

[0122] 3) Rotor anti-icing system maintenance self-check

[0123] Step 1: The pilot selects the rotor anti-icing working mode as self-check;

[0124] Step 2: The ice signal processor sends a self-test command to the two ice detectors and waits for the self-test result of the ice detector system;

[0125] Step 3: The flight control computer verifies whether the two atmospheric static temperature data are between -55 and 70°C, and reports the two atmospheric static temperatures to the human-computer interaction system for maintenance personnel to check whether they are similar to the actual body temperature, and then determine whether the two atmospheric temperature signals are accurate;

[0126] Step 4: The anti-icing distribution box checks whether the temperature of the atmospheric temperature sensor is between -55 and 70°C, and reports the temperature data of the atmospheric temperature sensor to the human-computer interaction system for maintenance personnel to check whether it is similar to the actual body temperature, and then determine whether the atmospheric temperature sensor measurement value is accurate;

[0127] Step 5: Perform maintenance BIT on the deicing distribution box to check whether the internal components are working properly; at the same time, the deicing distribution box distributes 270V power supply 1 to 6 conductive rings and brushes of the main rotor collector ring through 6 IGBTs, and the main rotor collector ring supplies 270V to the main rotor heating assembly, and the deicing distribution box distributes 270V power supply 2 to 2 conductive rings and brushes of the tail rotor collector ring through 2 IGBTs, and the tail rotor collector ring supplies 270V to the tail rotor heating assembly;

[0128] Step 6: The anti-icing distribution box measures the operating current of the main rotor heating assembly and the tail rotor heating assembly, and determines whether the current is within the normal range;

[0129] Step 7: If all the above self-checks are within the normal range, the flight control computer reports the system self-check results to the pilot through the human-computer interaction system.

[0130] 4) Rotor anti-icing system maintenance fault work

[0131] ① If an ice detector fails, the rotor anti-icing system will automatically isolate the fault: the ice signal processor will no longer collect data from the ice detector and report the ice detector failure, and the operation of the rotor anti-icing system will not be affected;

[0132] ② If both ice detectors fail, the rotor anti-icing system will be automatically isolated, and the ice signal processor will no longer collect data from the ice detector and report the ice detection. The rotor anti-icing system cannot work automatically, and the pilot needs to send a forced connection command to the rotor anti-icing system through the human-computer interaction system;

[0133] ③ The flight control computer determines that one of the two atmospheric static temperature signals is out of the normal range (between -55 and 70°C), and the flight control computer automatically isolates the fault signal and sends a certain atmospheric temperature fault to the anti-icing distribution box. At this time, the anti-icing distribution box changes the electrical temperature judgment criterion and gives priority to the temperature signal measured by the atmospheric temperature sensor. When the temperature signal of the atmospheric temperature sensor is out of the normal range, the anti-icing distribution box uses the intact atmospheric static temperature data;

[0134] ④ If there is an abnormality in both the atmospheric static temperature and the measurement value of one temperature sensor, the anti-icing distribution box uses the intact atmospheric temperature signal;

[0135] ⑤ If the atmospheric temperatures of the three routes are all out of the normal range, the anti-icing distribution box will send the rotor anti-icing failure information to the pilot through the flight control computer and the human-computer interaction system, indicating that the rotor anti-icing system cannot work, and automatically complete the fault isolation, and the system stops working;

[0136] ⑥ If the anti-icing distribution box fails, the flight control computer will send the rotor anti-icing failure information to the pilot through the human-computer interaction system, indicating that the rotor anti-icing system cannot work, and automatically complete the fault isolation, and the rotor anti-icing system will stop working;

[0137] ⑦ If the main rotor collector ring and tail rotor collector ring fail, the anti-icing distribution box will send the rotor anti-icing failure information to the pilot through the flight tube computer and the human-computer interaction system, indicating that the rotor anti-icing system cannot work, and automatically complete the fault isolation, and the rotor anti-icing system will stop working;

[0138] ⑧ If the blade heating assembly fails, the anti-icing distribution box will send the rotor anti-icing failure information to the pilot through the flight control computer and the human-computer interaction system, indicating that the rotor anti-icing system cannot work, and automatically complete the fault isolation, and the rotor anti-icing system stops working;

[0139] ⑨ If 270V power supply 1 fails, the anti-icing distribution box supplies 270V power supply 3 to the main propeller collector ring;

[0140] ⑩ If 270V power supply 2 fails, the anti-icing distribution box will supply 270V power supply 1 to the tail rotor collector ring and 270V power supply 3 to the main rotor collector ring.

Claims

1. A helicopter rotor anti-icing system based on a 270V DC power supply, characterized in that: The system includes: Two ice detection sensors are connected to the ice signal processor and are used to detect ice signals; An icing signal processor is connected to the flight tube computer, determines whether there is icing according to the detected icing signal, and transmits the result to the flight tube computer; The flight control computer is connected to the atmospheric static temperature system and the human-computer interaction system. The human-computer interaction system is used to display whether there is icing, receive the pilot's control command, and transmit the atmospheric static temperature and control command to the anti-icing distribution box; The anti-icing distribution box is connected to the atmospheric temperature sensor, 270 DC power supply and the main and tail rotor collector rings, determines the current temperature according to the atmospheric temperature sensor and the atmospheric static temperature, and calculates the deicing time according to the current temperature; The main and tail rotor heating components are connected to the main and tail rotor collector rings, respectively, and use the power from the main and tail rotor collector rings to heat and de-ice.

2. The system according to claim 1, characterized in that: When an icing signal appears in any of the two icing detection sensors, the icing signal processor determines that the helicopter is in an icing environment.

3. The system according to claim 2, characterized in that: The flight tube computer receives two independent channels of atmospheric static temperature data from the atmospheric static temperature system; The anti-icing distribution box votes out the current temperature data based on two independent atmospheric static temperature data and the data from the atmospheric temperature sensor.

4. The system according to claim 3, characterized in that: The main rotor collector ring includes: a conductive ring and a brush, which converts static 270V high voltage electricity into 270V high voltage electricity in a rotating state. The tail rotor collector ring is similar to the main rotor collector ring.

5. The system according to claim 4, characterized in that: The main propeller heating assembly includes six heating units; The main rotor collector ring includes seven brushes. One end of each of the six heating units is connected to a brush and then to a conductive ring. The other ends of the six heating units are connected together to a brush and then to the conductive ring.

6. The system according to claim 5, characterized in that: The heating time T of each of the six heating units of the main propeller heating assembly on The formula is as follows: Where a and b are constants determined by ice wind tunnel test data, and OAT is the current temperature; Calculate the switching time T of each of the six heating units of the main propeller heating assembly OFF The formula is as follows: T OFF =c+OAT seconds Where c is a constant determined from ice wind tunnel test data, and OAT is the current temperature.

7. The system according to claim 4, characterized in that: The tail rotor heating assembly includes two heating units; The main propeller collector ring includes two brushes. One end of each of the two heating units is connected to a brush and then to a conductive ring. The other ends of the two heating units are connected to a brush and then to a conductive ring.

8. The system according to claim 7, characterized in that: The heating time T of each of the six heating units of the main propeller heating assembly on1 The formula is as follows: Where A and B are constants determined by ice wind tunnel test data, and OAT is the current ambient temperature; Calculate the switching time T of each of the six heating units of the main propeller heating assembly OFF1 The formula is as follows: T OFF1 =C+OAT seconds Where C is a constant determined by ice wind tunnel test data, and OAT is the current ambient temperature.

9. A method for controlling a helicopter rotor anti-icing system based on a 270V DC power supply, used to control any of the above-mentioned systems, characterized in that: The process is as follows: Step 1: The pilot selects the rotor anti-icing working mode to automatic; Step 2: The ice detection subsystem, atmospheric static temperature system, atmospheric temperature sensor and flight tube computer are working; Step 3: The icing detection subsystem detects an icing signal and sends the icing signal to the human-computer interaction system for the pilot to view, and simultaneously sends an icing warning signal to the flight control computer; Step 4: The flight control computer sends the control command of connecting the rotor anti-icing system and two-way atmospheric static temperature data to the anti-icing distribution box, and the anti-icing distribution box works; Step 5: The anti-icing distribution box collects the atmospheric temperature sensor data, and simultaneously votes on the atmospheric temperature sensor and the two-way atmospheric static temperature to determine the current temperature; Step 6: The anti-icing distribution box distributes the 270V power supply 1 to the 6 conductive rings and brushes of the main rotor collector ring through 6 IGBTs, and the main rotor collector ring supplies 270V to the main rotor heating assembly; Step 7: The anti-icing distribution box distributes the 270V power supply 2 to the 2 conductive rings and brushes of the tail rotor collector ring through the 2 IGBTs, and the tail rotor collector ring supplies 270V to the tail rotor heating assembly; Step 8: When the main and tail rotor heating components are working, the anti-icing distribution box measures the current of the main and tail rotor heating components in real time, and determines whether the current is within the normal range. If it is within the normal range, the anti-icing distribution box sends the anti-icing working signal to the flight control computer, which then sends it to the human-computer interaction system. Step 9: The pilot observes through the human-computer interaction system that the rotor anti-ice system is working.

10. The method according to claim 9, characterized in that: Step 1: The pilot selects the rotor de-icing working mode as manual; Step 2: The ice detection subsystem, atmospheric static temperature system, atmospheric temperature sensor and flight tube computer are working; Step 3: The icing detection subsystem detects an icing signal and sends the icing signal to the human-computer interaction system for the pilot to view. The pilot sends a control command to turn on the rotor anti-icing system to the flight control computer through the human-computer interaction system. Step 4: The flight control computer sends the control command of connecting the rotor anti-icing system and two-way atmospheric static temperature data to the anti-icing distribution box, and the anti-icing distribution box works; Step 5: The anti-icing distribution box collects the atmospheric temperature sensor data, and simultaneously votes on the atmospheric temperature sensor and the two-way atmospheric static temperature to determine the current ambient temperature; Step 6: The anti-icing distribution box distributes the 270V power supply 1 to the 6 conductive rings and brushes of the main rotor collector ring through 6 IGBTs, and the main rotor collector ring supplies 270V to the main rotor heating assembly; Step 7: The anti-icing distribution box distributes the 270V power supply 2 to the 2 conductive rings and brushes of the tail rotor collector ring through the 2 IGBTs, and the tail rotor collector ring supplies 270V to the tail rotor heating assembly; Step 8: When the main and tail rotor heating components are working, the anti-icing distribution box measures the current of the main and tail rotor heating components in real time, and determines whether the current is within the normal range. If it is within the normal range, the anti-icing distribution box sends the anti-icing working signal to the flight control computer, which then sends it to the human-computer interaction system. Step 9: The pilot observes through the human-computer interaction system that the rotor anti-ice system is working.

Images