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

Claim 6:
7. A co-axial rotary wing aircraft, comprising:
a first rotor hub configured to spin about a central axis in a first direction;
a first torsional pitch member extending away from the central axis and coupled to the first rotor hub at a first position such that the first torsional pitch member does not hinge about the first rotor hub, wherein the first 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 first blade coupled to the first rotor hub and associated with a first pitch angle;
a first torque tube coupled to the first torsional pitch member such that a portion of the first torque tube surrounds the first torsional pitch member;
a second rotor hub configured to spin about the central axis in a second direction that is opposite the first direction;
a second torsional pitch member extending away from the central axis and coupled to the second rotor hub at a second position such that the second torsional pitch member does not hinge about the second rotor hub;
a second blade coupled to the second rotor hub and associated with a second pitch angle; and
a second torque tube coupled to the second torsional pitch member such that a portion of the second torque tube surrounds the second torsional pitch member.