Accession Number : AD0164088
Title : Helicopter Cyclic and Collective Pitch Mechanism.
Descriptive Note : Patent,
Corporate Author : DEPARTMENT OF THE NAVY WASHINGTON D C
Personal Author(s) : Scheibe,Harold R. ; Blankenship,John E.
Report Date : 24 OCT 1972
Pagination or Media Count : 6
Abstract : The patent relates to an apparatus for changing both the cyclic and collective pitch of each blade of a rigid rotor helicopter with a single differential gear mechanism. To change the collective pitch, a spider element is moved up or down which simultaneously actuates the differential gear mechanism for each blade in order to change its pitch collectively. To change the cyclic pitch, a seesaw type linkage is actuated and applies a torque to the swash plate and control gyro of the helicopter. The control gyro supports lateral arms and the applied torque changes their plane of rotation. Linkages connected between each of the control arms and differential gear mechanisms react to this change in the plane of rotation and actuate the appropriate differential gear mechanisms to cyclically change the pitch of the blades.
Descriptors : (*Actuators, *Patents), (*Helicopter rotors, Control systems), Gears, Differentials(Mechanical), Gyro stabilizers, Helicopters
Subject Categories : Helicopters
Distribution Statement : APPROVED FOR PUBLIC RELEASE