This is achieved by the fact that the left-sided air pressure probes located in the front section of the fuselage, and those additionally installed in the tail section of the fuselage and at the left wingtip, are additionally provided with the horizontally located lateral openings for sensing left-sided lateral static air pressure; the right-sided air pressure probes located in the front section of the fuselage, and those additionally installed in the tail section of the fuselage and at the right wingtip, are additionally provided with the horizontally located lateral openings for sensing right-sided lateral static air pressure; and the air pressure probes additionally installed at the wingtips and in the tail section of the fuselage are provided by the vertically located openings for sensing static air pressure. When the roll angle of the aircraft changes, the vertical spatial movement of the static air pressure probes additionally installed at the wingtips causes the appearance of a difference in static pressure between such probes due to the difference in altitude of their relative positions. When the pitch angle of the aircraft changes, the vertical movement of the static air pressure probes additionally installed on the opposite sides of the fuselage causes the appearance of a difference of static air pressure between such probes due to the difference in altitude of their relative positions. In the process of yawing of the aircraft, the lateral static air pressure increases at the additionally installed lateral static air pressure probes located on the opposite sides of the fuselage in the direction of the yaw turn, and decreases at the probes located against the direction of the yaw turn. Under the wind effect, if the aircraft experiences a leftward or rightward lateral speed (in the absence of yawing), the lateral static air pressure increases at the additionally installed lateral static air pressure probes located in the wind plane, and decreases on the opposite sides.


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    Title :

    AEROMETRIC METHOD AND DEVICE (SYSTEM) FOR MEASURING AIRCRAFT SPATIAL POSITION, YAW AND LATERAL VELOCITY



    Publication date :

    2019-05-09


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    G01P MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION OR SHOCK , Messen der Linear- oder Winkelgeschwindigkeit, der Beschleunigung, der Verzögerung oder des Stoßes / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / G01C Messen von Entfernungen, Höhen, Neigungen oder Richtungen , MEASURING DISTANCES, LEVELS OR BEARINGS / G05D SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES , Systeme zum Steuern oder Regeln nichtelektrischer veränderlicher Größen