A leveraged pitch link designed to reduce the effects of vibration and shock from the rotary-wing aircraft main rotor blades and to reduce the energy required by utilizing leverage. Consequently, the leveraged pitch links improve the operating comfort and efficiency The objective of the invention is to provide a rotary-wing aircraft with improved flight characteristics that reduce vibration and reduce repairs and maintenance. The invention accomplishes these objectives by utilizing leverage to reduce the amount of energy required for cyclic and collective pitch control and by utilizing shock and vibration dampening connectors.
ROTARY-WING AIRCRAFT LEVERAGED PITCH LINK
LIAISON DE PAS MOYENNE D'AERONEF A VOILURE TOURNANTE
2016-06-22
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
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