A method of calculating and displaying the true airspeed of a rotorcraft. At least one omnidirectional airspeed sensor is installed at the top of a tail fin of the rotorcraft. The true airspeed of the rotorcraft flying at speeds that are lower than or equal to at least one airspeed threshold of the rotorcraft is calculated by correcting the measurements supplied by the airspeed sensor installed at the top of the tail fin as a function of the effects produced by the air stream generated by rotation of the main rotor of the rotorcraft on the characteristics of the speed of the air stream measured by the tail fin airspeed sensor. For this purpose, a correction rule calibrated in test flight is advantageously applied to correct the measurements supplied by the airspeed sensor installed at the top of the tail fin.


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    Title :

    GIRAVION ÉQUIPÉ D'UN ANÉMOMÈTRE PLACÉ AU SOMMET D'UNE DÉRIVE ARRIÈRE DU GIRAVION


    Additional title:

    ROTORCRAFT PROVIDED WITH AN ANEMOMETER LOCATED AT THE TOP OF A REAR STABILISER OF THE ROTORCRAFT
    DREHFLÜGER MIT EINEM AN DER SPITZE EINER HECKFLOSSE ANGEBRACHTEN ANEMOMETER


    Contributors:

    Publication date :

    2018-11-21


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    French


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / G01P MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION OR SHOCK , Messen der Linear- oder Winkelgeschwindigkeit, der Beschleunigung, der Verzögerung oder des Stoßes