US2017166305A1PendingUtilityA1
Rotary wing vehicle
Individually held — no corporate assignee on recordPriority: Apr 14, 2004Filed: Jun 7, 2016Published: Jun 15, 2017
Est. expiryApr 14, 2024(expired)· nominal 20-yr term from priority
B64U 80/84B64U 2201/10B64U 80/60B64U 2201/20B64U 70/20B64U 80/70B64C 27/605B64C 2027/8236B64C 27/10B64C 27/14B64C 39/024B64U 30/16B64U 30/21B64U 50/19B64U 50/13B64U 10/13B64C 7/00B64C 2027/8281
48
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Claims
Abstract
A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.
Claims
exact text as granted — not AI-modified1 . A rotary wing aircraft comprising a first variable pitch rotor blade supported for rotation about a common rotor axis of rotation in a first rotor plane of rotation, a second variable pitch rotor blade supported for rotation about the common rotor axis of rotation in a second rotor plane of rotation, a first blade pitch controller located between the first rotor plane of rotation and the second rotor plane of rotation and configured to control a pitch of the first rotor blade, a second blade pitch controller located between the first rotor plane of rotation and the second rotor plane of rotation and configured to control a pitch of the second rotor blades, and a first pitch control linkage having a first end coupled to the first blade pitch controller and a second end coupled to the second blade pitch controller so that displacement of the first pitch control linkage operates both the first blade pitch controller and second blade pitch controller at the same time.
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