Helicopter main blade heating assembly fault detection method and device

Through the coordinated work of the rotor anti-icing controller and the distribution device, the rapid positioning and detection of the failure of the helicopter's main blade heating component is achieved, solving the problem that the existing system cannot specifically locate the fault and dynamic detection, and improving flight safety.

CN119689109APending Publication Date: 2025-03-25WUHAN AVIATION INSTR
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Patent Information

Application Number
CN202411779994.1
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2024-12-05
Publication Date
2025-03-25

AI Technical Summary

Technical Problem

The existing rotor anti-icing system cannot specifically locate the faulty main blade heating component, and cannot dynamically detect the main blade heating component, affecting the safety of helicopter flight.

Method used

Through the maintenance self-test function of the rotor anti-icing controller, combined with the anti-icing distribution box and the main paddle distribution device, the fault detection of the main blade heating component is completed. The specific steps include controlling the rotor anti-icing controller to enter the maintenance self-test mode, the rotor anti-icing controller controls the distribution box to provide power for the distribution device, the distribution device enters the "maintenance self-test" working mode, and heating it in sequence according to the "heating zone inspection timing" and "pad blade inspection timing", and determining whether there are any faults in each heating partition and blade heating components.

Benefits of technology

It realizes rapid positioning of the faults of the main blade heating component, meets various usage environments such as static detection and dynamic detection, reduces troubleshooting time, and improves helicopter flight safety.

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Abstract

The invention belongs to the field of airplane anti-icing and deicing systems, and particularly relates to a helicopter main blade heating assembly fault detection method and device. The method comprises the following steps: step 1, controlling the rotor wing anti-icing and deicing controller to enter a maintenance self-inspection mode; 2, the rotor wing anti-icing and de-icing controller controls a power distribution box to provide power for a power distributor; 3, the rotor wing anti-icing and de-icing controller controls the power distributor to enter a maintenance self-checking working mode; 4, the rotor wing anti-icing and deicing controller controls a power distributor to sequentially heat the N heating subareas according to the heating area inspection time sequence, whether a heating assembly of each heating subarea breaks down or not is judged, if yes, the next step is executed, and if not, inspection is reported to be normal; 5, the rotor wing anti-icing and de-icing controller controls a power distributor to sequentially heat the M blades of the fault partition according to the blade inspection time sequence; and judging whether each blade heating assembly has a fault or not, and reporting the fault condition.
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