GB435888A - Automatic aero-dynamic stabiliser for aeroplanes - Google Patents

Abstract

435,888. Controlling aircraft automatically. BEMBERG, O. E., 28, Rue Emile Menier, Paris. Aug. 21, 1934, Nos. 24147 and 24148. Convention dates, Oct. 12, 1933 and July 4, 1934. Addition to 422,493. [Class 4] The single stabilizing device mounted in a ball or universal joint on a lever connected through links to the member controlling the lateral stability of the aeroplane, as described in the parent Specification, is replaced by two similar devices, one on each side of the longitudinal axis of the aeroplane, connected at the ball joints to bent levers such that for one direction of tilting the control is mainly effected by one of the devices, whilst the other device chiefly restores stability when the aeroplane is tilted in the other direction. When the plane is tilted so that the wind vane g<2> moves downwardly the arm carrying the vane tends to a vertical position and moves towards a position in which it would be perpendicular to its arm i<2> and exerts leverage at the pivot i<4>. At the same time the upward movement of the vane g<1> tends to bring its arm into alignment with the arm i<1>, thus exerting relatively little effect at the pivot i<3>. The rotation of the lever i2 rotates a lever j<4> secured to a shaft j<6> carrying an arm J<8> which through a link [2 moves the control arm M to restore the lateral stability of the aeroplane. In a modification each wind vane gl, g<2>, is replaced by a dihedral plane D carried by a bar d pivoted on a spherical or ball member c.