Patent ID: 11884387
Assignee: LOCKHEED MARTIN CORPORATION
Field: Transport (Mechanical engineering)
Classification: CPC B | IPC B

Claim 15:
16. A method of controlling a co-axial rotary wing aircraft, the method comprising:
controlling, by a pitch control member, a pitch input to a pitch horn, the pitch horn being coupled to a rotor assembly including:
a rotor hub configured to rotate about a center axis;
a blade defining a pitch angle and comprising:
a torsional pitch member coupled to the rotor hub, wherein the torsional pitch member includes a first curvilinear channel and a second curvilinear channel each having a front side and a back side, wherein the first curvilinear channel and the second curvilinear channel are disposed adjacent to each other, such that the back side of the first curvilinear channel faces the back side of the second curvilinear channel;
a torque tube coupled to the torsional pitch member, wherein the torsional pitch member extends away from the center axis through a portion of the torque tube; and

a blade spar coupled to the torque tube.