According to an embodiment of the present invention, a double actuator for an aircraft comprises: a first motor assembly; a second motor assembly; and a multiple planetary reducer assembly. In a method for fault diagnosis of a double actuator for an aircraft, a first motor and a second motor are determined to be malfunctioning when a condition that a normal current value during no-load of a BLDC motor is greater than a driving current of the first motor and a driving current of the second motor is not satisfied after determining the multiple planetary reducer assembly or a first clutch and a second clutch to be malfunctioning.

    본 발명의 실시예에 따른 항공기용 이중화 구동기의 고장진단 방법은 복합유성감속기조립체의 고장 또는 제1 클러치와 제2 클러치 모두 고장으로 판단하고 제1 모터의 구동전류와 제2 모터의 구동전류보다 BLDC모터의 무부하 시 정상 전류값이 큰 조건을 만족하지 않으면 제1 모터와 제2 모터의 고장으로 판단하는 것을 특징으로 한다.


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    Title :

    FAULT DIAGNOSING METHOD OF DOUBLE ACTUATOR FOR AIRCRAFT


    Additional title:

    항공기용 이중화 구동기의 고장진단 방법


    Contributors:

    Publication date :

    2018-03-15


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Korean


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64C AEROPLANES , Flugzeuge / G01R Messen elektrischer Größen , MEASURING ELECTRIC VARIABLES



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