Helicopter rotor anti-icing and de-icing system current fault positioning method

Abstract

The invention belongs to the technical field of electronic circuits, and relates to a current fault positioning method for a helicopter rotor anti-icing and de-icing system. Due to the particularity that the main blade is long and large in deformation, no matter in an open circuit or a short circuit, a fault cannot be positioned in time when the main blade rotates through static measurement. According to the invention, if the current is zero all the time in the heating process, the fault is positioned to the anti-icing and deicing distribution box and the main paddle collector ring assembly; otherwise, the same partitions of all the paddles are heated in sequence, and the partition with the fault is judged according to whether the total current of the current sensor is abnormal or not; the main paddle distributor is controlled to heat all the paddles in sequence, and the paddles with faults are judged according to whether the total current of the current sensor is abnormal or not; if the total current during heating is higher than the rated current, determining that the anti-icing and de-icing heating assembly has a fault; if the total current during heating is lower than the rated current and the power switch monitoring circuit detects the peak voltage, determining that the anti-icing and de-icing heating assembly has a fault; and if the total current during heating is lower than the rated current and the power switch monitoring circuit does not detect the peak voltage, the main paddle distributor breaks down. Faults are accurately determined through comprehensive current monitoring and power switch output monitoring, the replacement and maintenance time of products is shortened, and the maintainability, testability and supportability of the products are improved.

Description

Technical Field

[0001] The invention belongs to the technical field of electronic circuits and relates to a method for locating current faults in a helicopter rotor anti-icing and deicing system. Background Art

[0002] The helicopter rotor anti-icing system includes the anti-icing controller, anti-icing distribution box, main rotor distributor, anti-icing heating assembly, and main rotor collector ring assembly. Current faults are generally divided into open circuit and short circuit. For the helicopter rotor anti-icing system, open circuit faults may occur in the main power distribution switch of the anti-icing distribution box, the main rotor collector ring assembly, the main rotor distributor, and the anti-icing heating assembly.

[0003] When an AC main heating circuit current fault occurs, fault location is extremely difficult. In most cases, the fault is located by replacing the anti-icing distribution box, anti-icing controller or main propeller distributor in sequence, and measuring the conductivity of the onboard cables between the devices when the helicopter is static.

[0004] However, for helicopters, due to the special characteristics of the main rotor blades, which are long and have large deformation, static measurement cannot locate the fault in time when the main rotor blades are rotating, whether it is an open circuit or a short circuit. Summary of the invention

[0005] The purpose of the present invention is to provide a method for locating current faults in a helicopter rotor anti-icing and de-icing system.

[0006] The technical solution of the present invention is: a method for locating current faults in a helicopter rotor anti-icing system, the helicopter rotor anti-icing system comprising an anti-icing controller, an anti-icing distribution box, a main rotor distributor, an anti-icing heating assembly and a main rotor collector ring assembly, wherein the anti-icing distribution box is provided with a current sensor, the main rotor distributor comprises a control circuit, a power switch and a power switch monitoring circuit connected in sequence, and the method comprises the following steps:

[0007] S1. The de-icing controller sends a control command to the de-icing distribution box and the main propeller distributor. If the current is always 0 during the heating process, the fault is located in the de-icing distribution box and the main propeller collector ring assembly; otherwise, proceed to the next step;

[0008] S2, controlling the main propeller distributor to heat the same partition of each blade in turn, and the anti-icing controller determines the partition where the fault occurs based on whether the total current of the current sensor is abnormal;

[0009] S3, controlling the main propeller distributor to heat all the propeller blades in sequence, and the anti-deicing controller determines the faulty propeller blade based on whether the total current of the current sensor is abnormal;

[0010] S4. If the total current during heating is higher than the rated current, it means that the anti-deicing heating component is faulty; if the total current during heating is lower than the rated current and the power switch monitoring circuit detects a spike voltage, it means that the anti-deicing heating component is faulty; if the total current during heating is lower than the rated current and the power switch monitoring circuit does not detect a spike voltage, it means that the main propeller distributor is faulty.

[0011] Advantageously, the anti-icing controller sends anti-icing control instructions to the anti-icing distribution box according to the climatic conditions to turn on the main distribution switch, sends anti-icing control instructions to the main propeller distributor to turn on each partition power switch according to a specific timing, and receives the total current signal transmitted by the anti-icing distribution box and the power switch monitoring information of the main propeller distributor.

[0012] Advantageously, the main propeller distributor receives the anti-icing control instruction from the anti-icing controller to turn on and off the power switches of each blade partition, and monitors and determines the peak voltage at the output end of the power switch.

[0013] Advantageously, the anti-icing heating component receives the zoned heating power transmitted by the main rotor distributor for heating to achieve anti-icing of the main rotor blades.

[0014] Advantageously, when one or more partition faults occur, the total current detected by the current sensor is between 0 and the rated current; when the anti-icing heating component is short-circuited, the total current detected by the current sensor exceeds the rated current.

[0015] Advantageously, when an AC voltage passes through the monitored circuit, the power switch monitoring circuit generates a high-level signal to determine that the power switch output of the circuit is normal, otherwise it is abnormal.

[0016] Advantageously, the power switch monitoring circuit collects the power switch self-test A and B signals drawn from the output end of the power switch of any group of one zone and converts them into high and low level signals through optical couplers. The signals are processed by the voltage comparator and input into the signal processing module for judgment, thereby determining whether the power switch is in an open circuit state.

[0017] Advantageously, the main rotor collector ring assembly transmits the control signal of the anti-icing controller and the power distribution power of the anti-icing distribution box to the main rotor distributor.

[0018] Beneficial effects of the present invention: The present invention accurately determines faults through comprehensive current monitoring and power switch output monitoring, reduces product replacement and repair time, and improves product maintainability, testability and security. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 The design principle diagram of the helicopter rotor anti-icing system of the present invention;

[0020] Figure 2This is a typical power switch monitoring circuit. DETAILED DESCRIPTION

[0021] The present invention is further described below in conjunction with the accompanying drawings:

[0022] like Figure 1 As shown, a helicopter rotor anti-icing system designed to implement the current fault locating method of the helicopter rotor anti-icing system of the present invention includes an anti-icing controller, an anti-icing distribution box, a main rotor distributor, an anti-icing heating assembly and a main rotor collector ring assembly (not shown).

[0023] The anti-icing controller sends anti-icing control instructions to the anti-icing distribution box according to the weather conditions to connect the main distribution switch, and sends anti-icing control instructions to the main propeller distributor to connect each partition power switch according to a specific timing, while receiving the total current monitoring signal transmitted by the anti-icing distribution box and the power switch monitoring information of the main propeller distributor.

[0024] The anti-icing distribution box is equipped with a current sensor. The anti-icing distribution box receives the anti-icing control command sent by the anti-icing controller to turn on and off the main distribution switch, monitor the total current through the current sensor and transmit it to the anti-icing controller. When the main distribution switch and the main propeller collector ring assembly of the anti-icing distribution box have a circuit breaker fault, the total current monitored by the current sensor is 0.

[0025] The main propeller distributor includes a control circuit, a power switch and a power switch monitoring circuit connected in sequence. The main propeller distributor receives the anti-icing control command from the anti-icing controller to turn on and off the power switch of each blade partition, and monitors and judges the peak voltage at the output end of the power switch.

[0026] The function of the anti-icing heating component is to receive the partitioned heating power transmitted by the main rotor distributor for heating to achieve anti-icing of the main rotor blades. Among them, a common helicopter has 5 main rotor blades, each of which is divided into 7 partitions, and the corresponding main rotor distributor power switches have a total of 5×7=35 groups. When one or more partition faults occur, the total current detected by the current sensor is between 0 and the rated current. When the anti-icing heating component is short-circuited, it is manifested as the current sensor detecting that the total current exceeds the rated current.

[0027] The function of the main propeller collector ring assembly is to transmit the control signal of the anti-icing controller and the distribution power of the anti-icing distribution box to the main propeller distributor.

[0028] like Figure 2 The power switch monitoring circuit shown can collect the power switch self-test A and B signals led out from the output end of the power switch of any group of one zone and convert them into high and low level signals through optical couplers. The signals are processed by the voltage comparator and input into the signal processing module for judgment, so as to determine whether the power switch is in the open circuit state.

[0029] In the method for locating the current fault of the helicopter rotor anti-icing system of this embodiment, the anti-icing controller sends a control command to the anti-icing distribution box and the main rotor distributor.

[0030] If the current is always 0 during the heating process, the fault can be located on the anti-icing distribution box and the main propeller collector ring assembly;

[0031] The main propeller distributor first heats all the blades sequentially according to the partitions in the normal mode (such as: Zone 1 → Zone 2 → Zone 3 → Zone 4 → ·). During heating, the anti-icing controller determines in which partition the fault occurs (assuming it is Zone 2) based on the total current monitoring information of the anti-icing distribution box. If the current is lower than the rated current when heating to a certain partition, it means that there is a circuit breaker fault in Zone 2; if the current is higher than the rated current when heating to a certain partition, it means that there is a short circuit fault in that partition.

[0032] The output control signal fixes the main propeller distributor in the abnormal current zone (i.e. zone 2), and then heats the individual blades in sequence (e.g. blade A → blade B → blade C → ·). During heating, the anti-icing controller determines which blade the fault occurs in (assuming it is blade B) based on the total current monitoring information of the anti-icing distribution box. That is, the current fault is located in zone 2 of blade B.

[0033] After locating the current fault to area 2 of blade B, if the current during heating is higher than the rated current, it can be determined that the anti-icing heating component is faulty; if the current during heating is lower than the rated current and the power switch monitoring circuit of the main propeller distributor detects a spike voltage, it can be determined that the heating component is faulty, otherwise it is a faulty main propeller distributor.

[0034] The peak voltage monitoring circuit can generate a high-level signal when an AC voltage passes through the monitored circuit. The main propeller distributor control circuit receives the high-level signal and can determine that the power switch output of the circuit is normal, otherwise it is abnormal.

[0035] like Figure 2 As shown, a typical power switch monitoring circuit can collect the power switch self-test A and B signals led out from the output end of the power switch of any group of one zone and convert them into high and low level signals through optical couplers. The signals are processed by the voltage comparator and input into the signal processing module for judgment, so as to determine whether the power switch is in the open circuit state.

[0036] Helicopter Rotor Anti-Ice System Blade Fault Determination is used in conjunction with the helicopter rotor anti-ice system.

Claims

1. A method for locating current faults in a helicopter rotor anti-icing system, characterized in that: The helicopter rotor anti-icing system comprises an anti-icing controller, an anti-icing distribution box, a main rotor distributor, an anti-icing heating assembly and a main rotor collector ring assembly, wherein the anti-icing distribution box is provided with a current sensor, and the main rotor distributor comprises a control circuit, a power switch and a power switch monitoring circuit connected in sequence, and the method comprises the following steps: S1. The de-icing controller sends a control command to the de-icing distribution box and the main propeller distributor. If the current is always 0 during the heating process, the fault is located in the de-icing distribution box and the main propeller collector ring assembly; otherwise, proceed to the next step; S2, controlling the main propeller distributor to heat the same partition of each blade in turn, and the anti-icing controller determines the partition where the fault occurs based on whether the total current of the current sensor is abnormal; S3, controlling the main propeller distributor to heat all the propeller blades in sequence, and the anti-deicing controller determines the faulty propeller blade based on whether the total current of the current sensor is abnormal; S4. If the total current during heating is higher than the rated current, it means that the anti-deicing heating component is faulty; if the total current during heating is lower than the rated current and the power switch monitoring circuit detects a spike voltage, it means that the anti-deicing heating component is faulty; if the total current during heating is lower than the rated current and the power switch monitoring circuit does not detect a spike voltage, it means that the main propeller distributor is faulty.

2. The method for locating current faults in a helicopter rotor anti-icing and de-icing system according to claim 1, characterized in that: The anti-icing controller sends anti-icing control instructions to the anti-icing distribution box according to the climate conditions to turn on the main distribution switch, sends anti-icing control instructions to the main propeller distributor to turn on each partition power switch according to a specific timing, and receives the total current signal transmitted by the anti-icing distribution box and the power switch monitoring information of the main propeller distributor.

3. The method for locating current faults in a helicopter rotor anti-icing and de-icing system according to claim 1, characterized in that: The main propeller distributor receives the anti-icing control command from the anti-icing controller to turn on and off the power switches of each blade partition, and monitors and judges the peak voltage at the output end of the power switch.

4. The method for locating current faults in a helicopter rotor anti-icing and de-icing system according to claim 1, characterized in that: The anti-icing heating component receives the partitioned heating power transmitted by the main propeller distributor to perform heating to achieve anti-icing of the main propeller blades.

5. The method for locating current faults in a helicopter rotor anti-icing and de-icing system according to claim 4, characterized in that: When one or more partition faults occur, the total current detected by the current sensor is between 0 and the rated current; when the anti-icing heating component is short-circuited, the current sensor detects that the total current exceeds the rated current.

6. The method for locating current faults in a helicopter rotor anti-icing and de-icing system according to claim 1, characterized in that: When an AC voltage passes through the monitored circuit, the power switch monitoring circuit generates a high-level signal to determine that the power switch output of the circuit is normal, otherwise it is abnormal.

7. The method for locating current faults in a helicopter rotor anti-icing and de-icing system according to claim 6, characterized in that: The power switch monitoring circuit collects the power switch self-test A and B signals led out from the output end of the power switch of any group of one zone and converts them into high and low level signals through optical couplers. The signals are processed by the voltage comparator and input into the signal processing module for judgment, so as to determine whether the power switch is in an open circuit state.

8. The method for locating current faults in a helicopter rotor anti-icing and de-icing system according to claim 1, characterized in that: The main rotor collector ring assembly transmits the control signal of the anti-icing controller and the distribution power of the anti-icing distribution box to the main rotor distributor.

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