The invention relates to a sensing orifice (1) for an aircraft (100), an aircraft (100) with such a sensing orifice (1) and a method for assembling a sensing orifice (1) for an aircraft (100). The aircraft (100) may be an airplane, a helicopter, a UAV, a drone or similar. The static sensing orifice (1) comprises a passage (11) through an outer skin (22) of an aircraft (100) and a moisture protection body (12). The passage (11) is designed to connect with a pressure line (13) in the interior of the aircraft (100). The moisture protection body (12) is gas-permeable and water-impermeable, and the moisture protection body (12) is disposed such that the passage (11) is gas-permeably and water-impermeably sealed. The method for assembling a static sensing orifice (1) for an aircraft (100), comprises the following steps: Providing a passage (11) through an outer skin (22) of an aircraft (100) for connecting to a pressure line (13) in the interior of the aircraft (100), Providing a gas-permeable and water-impermeable moisture protection body (12), and gas-permeable and water-impermeable sealing of the passage (11) by means of the moisture protection body (12).


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    Titel :

    SENSING ORIFICE FOR AN AIRCRAFT


    Weitere Titelangaben:

    ORIFICE DE DETECTION POUR UN AERONEF


    Beteiligte:
    HEUER THOMAS (Autor:in) / ALTMANN HORST (Autor:in)

    Erscheinungsdatum :

    2016-01-11


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    G01L Messen von Kraft, mechanischer Spannung, Drehmoment, Arbeit, mechanischer Leistung, mechanischem Wirkungsgrad oder des Drucks von Fluiden , MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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