AIRCRAFT FRONT SUPPORT WHEEL TURN CONTROL SYSTEM

摘要

FIELD: aeronautical engineering; aircraft front landing gear wheel turn hydraulic control systems. SUBSTANCE: control system consists of mechanical control linkage and electrohydraulic power control loop; mechanical linkage is provided with three-articulation lever 3 and additional rod 4. On end articulation 7 of three-articulation lever 3 is fitted on bracket securing setter 5 and second end articulation 9 is engageable with cam 10 secured on same bracket 8. Rod 2 of mechanical linkage is connected with intermediate articulation 11 of lever 3 and rod connects second end articulation 9 with carrier 6 of setter 5. Passed through axles of articulations 7 and 9 are rods and 13 between which spring device 14 is fitted. During displacement of pedals 1, carrier 6 performs motion determined by profile of cam 10 which is selected through calculations or graphically depending on required characteristics of control system. EFFECT: easy and facilitated change of aircraft controllability characteristics at any stage of operation. 2 cl, 1 dwg