초록 ▼

A helicopter fuselage is coupled to a pylon to permit fore/aft pivotal movement of the fuselage relative to the pylon with resilient means connected between the pylon and fuselage to oppose and limit such pivotal movement. Structure is then provided to decouple the rotor control linkages to permit l

A helicopter fuselage is coupled to a pylon to permit fore/aft pivotal movement of the fuselage relative to the pylon with resilient means connected between the pylon and fuselage to oppose and limit such pivotal movement. Structure is then provided to decouple the rotor control linkages to permit limited fore/aft rotation of the fuselage relative to the pylon upon change of location of the center of gravity without introducing control motion in the control linkages. The control linkages include control tubes extending longitudinally of the fuselage from a pilot input location. Bell cranks are connected to the control tubes and are coupled as to control the pitch of rotor blades. Structure connecting the fuselage and each bell crank alters the pivot points of the bell cranks relative to the fuselage. The positions of the bell crank pivot points depend upon rotation of the fuselage relative to the pylon.

대표청구항 ▼

In a helicopter where a powered pylon drives a main rotor to support a fuselage in response to movement of input control elements, the combination comprising: a. means to pivotally mount said fuselage to said pylon on a lateral axis for fore/aft rotation of said fuselage relative to said pylon, b. r

In a helicopter where a powered pylon drives a main rotor to support a fuselage in response to movement of input control elements, the combination comprising: a. means to pivotally mount said fuselage to said pylon on a lateral axis for fore/aft rotation of said fuselage relative to said pylon, b. resilient means connected between said pylon and said fuselage to oppose said rotation, and c. control linkage structure between said control elements and main rotor for isolating said control elements of said main rotor from the effect of said rotation in which said control linkage structure includes control tubes extending longitudinally of said fuselage from said input control elements, bell cranks connected to said control tubes and connected in turn by control tube structures connected to control the pitch of blades on said rotor, and mixing levers, one interposed between said fuselage and each of said bell cranks for altering the pivot points of said bell cranks relative to said fuselage, and means to control the positions of said pivot points in response to the rotation of said fuselage relative to said pylon by connecting isolation control tubes one to each control for the pitch of said rotor blades and to one of said mixing lever pivot points.