The disclosed embodiments describe cover detection systems, controllers, and aircraft. The aircraft includes the controller and parts of the cover detection systems. A cover detection system includes an engine, a first sensor, an engine cover assembly, and a controller. The engine has moving parts and defines a fluid opening. The fluid opening exposes the moving parts to an ambient environment. The first sensor component is located proximate to the engine. The engine cover assembly includes an engine cover and a second sensor. The engine cover is configured to cover the fluid opening. The second sensor component is attached to the engine cover and is configured to interact with the first sensor component. The controller is configured to determine whether the engine cover is installed on the engine based on an interaction between the first sensor component and the second sensor component.


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    Title :

    ENGINE INLET COVER DETECTION SYSTEM AND METHOD


    Contributors:

    Publication date :

    2019-10-03


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / G01V Geophysik , GEOPHYSICS / G06K Erkennen von Daten , RECOGNITION OF DATA



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