FIELD: aeronautical engineering.
SUBSTANCE: proposed manual control system includes two detachable manual control units 1 connected with disconnection mechanism 2 fitted with disconnection lever 20 and disconnection mechanism control device. Fitted between manual control units 1 on horizontal axle is control panel 10 which may be swung through angle of 900. Disconnection mechanism control device is made in form of cable run whose one end is connected with stick 12 located on control panel and other end with disconnection mechanism lever through bearing roller 14 mounted on control panel and two auxiliary rollers 16 and 18 mounted on members of aircraft primary structure. Axis of bearing roller is shifted relative to horizontal axis of turn of control panel for lowering the bearing roller to avoid winding of cable of bearing and auxiliary rollers when cable is hauled-in at swinging the control panel.
EFFECT: extended functional capabilities.
5 dwg
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