AIRCRAFT VARIABLE MANUAL CONTROL (VERSIONS) Russian patent published in 2014 - IPC B64C13/04 

FIELD: aircraft engineering.

SUBSTANCE: proposed system consists of control components, controlled components and articulation there between. Note here that control mechanism comprises lengthwise shaft with horizontal transverse yoke and cantilever perpendicular lever. L-like lever is secured at said yoke with control lever at vertical end and with lengthwise horizontal lever with ball joint at opposite end coupled by link with two ball joints with vertical swing lever. Openings for connection of pitch and roll control links are arranged at vertical swing lever and cantilever link. Control mechanism can comprises lengthwise spider with cantilever vertical lever with yoke with control lever secured at transverse studs of the letter and with lever having ball hinge at its end. Besides, control component can be jointed with controlled element via one or two springs arranged nearby control or controlled component, or nearby linkage elements. Aircraft control lever is secured at ball or universal joint. Lower extension of said lever cruciform cantilever lever with multiple holes made at their ribs for connected of pitch and roll control links or their springs. In using the control column its post is secured at flange joint to swing in lengthwise plane while control column is secured at the post and coupled by parallelogram mechanism with said cruciform cantilever lever to swing in traverse plane. Control mechanism can comprises dampers arranged between control component and controlled component, or between controlled component and springs.

EFFECT: aircraft control performances similar to those of another aircraft, adjustment to various control versions.

7 cl, 4 dwg