Attitude control of v. t. o. l. aircraft

摘要

994,127. Jet propulsion plant. DORNIER-WERKE G.m.b.H. Oct. 25, 1963 [Nov. 3, 1962], No. 42148/63. Heading F1J. [Also in Divisions B7 and F2] A control system for an aircraft jet lifting engine has two control paths, one giving a fine control and one giving coarse control, the latter only operating outside a particular range of movement of the control stick. As shown, a control stick 8 operates an engine control 7 through a lever 3 one end of which is fixed to a coil spring 9, and is sensibly fixed thereby in the fine control regime, the control movement being transmitted along a rod 4. The limits of the fine control regime are defined by a piston 10 engaging the adjustable ends 18, 19 of a cylinder 1. Further movement of the stick 8 then causes the lever 3 to pivot about 13, against the spring 9, and the control movement is transmitted along rod 17. A control rod 2SP1/SP leads through a similar linkwork to a lifting engine on the other side of the aircraft centre line. In a modification (Fig. 2, not shown) the lever arm 5 is extended beyond joint 16 and engages a stop which prevents an increase in engine power beyond the maximum, and the rod 17 includes a spring link which allows movement of the joint 11 when this stop is engaged.