Improvements in or relating to aircraft control systems

Abstract

Abstract 482,080. Aircraft controlling and alighting gear. MERCIER, P. E. May 13, 1937, Nos. 13570 and 13571. Convention dates, June 11, 1936 and June 18, 1936. [Class 4] An aircraft control-system includes fins, movable or provided with movable flaps, mounted perpendicularly to the transverse and longitudinal axes of the aircraft and arranged substantially at the centre of gravity of the aircraft and vertical tail surfaces similar to the fins and arranged at the extremities of the aircraft elevators. As shown, a fin 1 is provided with a flap 2 movable about the axis t, t<1>, the fin 3 is movable about the axis y, y<1> and the tail-surfaces 4 are provided with surfaces movable about the axis s, s<1>. The deflection of the flap 2 may be less than that of the fin 3 and may be in the opposite direction. The surfaces are controlled, to move in opposite directions, from a handwheel 31, Fig. 5, axial movement of which through a member 16 actuates the elevator and rotation of which, through pulleys 32, 37 and cables connected to bars 11, 36, actuates the flap 2 and fin 3. A clutch 19 facilitates disconnection of the elevator control and the desired ratio of control movement may be obtained by choice of the diameter of the pulleys and the length of the bars. The surfaces are moved in the same sense by movement of one or other of pedals 13, 13<1> which through gearing 57, 12, 57<1> are caused to move in opposite directions and over which the cables are led. In order to improve control during taxying the alighting includes a fixed rear-wheel 6 located between the centre of gravity of the aircraft and the vertical rudder system, and wheels 7, 8 located forward of the centre of gravity and pivoted about vertical or inclined axes which meet the ground in front of the points of contact of the wheels. The orientation of the wheels 7, 8 may be controlled manually.

Inventors

No inventors recorded.

Bibliographic Details