GB605642A - Improvements in control means for aircraft - Google Patents

Abstract

605,642. Aircraft control systems. ROBERT, R. A. Jan. 1, 1946, No. 112. Convention date, May 15, 1943. [Class 4] In an aircraft control system the rudder may, at the will of the pilot, be locked or be controlled by the same control means as the ailerons. The velocity ratio between the rudder and the aileron control means may be varied by the pilot. The movement of the aileron control member 1 is transmitted by chains and sprockets 2, 3, 4, 5, 6 to a shaft 8 on which is secured an arm 10 connected to the cables 11, 12 for controlling the ailerons 13. A lever 16 pivoted to a yoke 15 on the shaft 8 about a transverse axis C-C is connected by a link 17, to which it is universally jointed, to one arm 19 of a bell-crank 20 whose other arm 21 is connected to the cable 22 controlling the rudder 23. The connection 18 between the link 17 and the bell-crank 20 normally lies on the axis C-C so that the rudder is not affected by movement of the .lever 16 about the axis C-C when the control member 1 is in its central position as shown. The lever 16 is moved about the axis C-C by the piston 29 of a fluid-pressure cylinder 30 mounted on the shaft 8 and supplied with pressure fluid through a flexible conduit 34 from a cylinder 33 operated by a pedal 31<SP>1</SP>. When the pedal 31<SP>1</SP> is not depressed the universal joint between the lever 16 and the link 17 lies on the axis of the shaft 8 and the rudder is locked. When the pedal is depressed, the universal joint is displaced from the axis of the shaft 8 so that rotation of the shaft by the control member 1 causes motion of the rudder 23, the velocity ratio being determined by the extent of depression of the pedal 311.