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US 12,545,444 B2Granted
Rotary wing vehicle
OwnerPaul E. Arlton, David J. Arltoninventors
Life of this patent
Estimating the term…
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.
Claims29
A rotary wing aircraft comprising
- a non-rotating structural airframe arranged to extend along a rotor axis of rotation and formed to include a first hollow channel arranged to lie in parallel relation to the rotor axis of rotation,
- a plurality of first variable pitch rotor blades supported for rotation about the rotor axis of rotation in a first rotor plane of rotation,
- a plurality of second variable pitch rotor blades supported for rotation about the rotor axis of rotation in a second rotor plane of rotation and the second rotor plane of rotation is spaced apart from the first rotor plane of rotation along the rotor axis of rotation,
- a first blade pitch controller located above the second rotor plane of rotation for controlling cyclic pitch and collective pitch of the first rotor blades,
- a second blade pitch controller located below the first rotor plane of rotation for controlling cyclic pitch and collective pitch of the second rotor blades,
- three first servo actuators supported by the non-rotating structural airframe above the second rotor plane of rotation and coupled to the first blade pitch controller for simultaneously varying the cyclic pitch and collective pitch of the first rotor blades, and
- three second servo actuators supported by the non-rotating structural airframe below the first rotor plane of rotation and coupled to the second blade pitch controller for simultaneously varying the cyclic pitch and collective pitch of the second rotor blades,
- wherein the first servo actuators are configured to operate independently from one another and the second servo actuators are configured to operate independently from one another.
5 more elements
A rotary wing aircraft comprising
- a plurality of first variable pitch rotor blades supported for rotation about a rotor axis of rotation in a first rotor plane of rotation,
- a plurality of second variable pitch rotor blades supported for rotation about the rotor axis of rotation in a second rotor plane of rotation and the second rotor plane of rotation is spaced apart from the first rotor plane of rotation along the rotor axis of rotation,
- a non-rotating structural airframe arranged to extend along the rotor axis of rotation between the first rotor plane of rotation and the second rotor plane of rotation,
- a first motor coupled to the non-rotating structural airframe to drive the first variable pitch rotor blades about the rotor axis of rotation,
- a second motor coupled to the non-rotating structural airframe to drive the second variable pitch rotor blades about the rotor axis of rotation,
- a first blade pitch controller supported by the non-rotating structural airframe and located above the second rotor plane of rotation for controlling cyclic pitch and collective pitch of the first rotor blades,
- a second blade pitch controller supported by the non-rotating structural airframe and located below the first rotor plane of rotation for controlling cyclic pitch and collective pitch of the second rotor blades,
- three first servo actuators supported by the non-rotating structural airframe above the second rotor plane of rotation and coupled to the first blade pitch controller for simultaneously varying the cyclic pitch and collective pitch of the first rotor blades, and
- three second servo actuators supported by the non-rotating structural airframe below the first rotor plane of rotation and coupled to the second blade pitch controller for simultaneously varying the cyclic pitch and collective pitch of the second rotor blades,
- wherein the first servo actuators are configured to operate independently from one another and the second servo actuators are configured to operate independently from one another.
7 more elements
A rotary wing aircraft comprising
- a non-rotating structural airframe arranged to extend along a rotor axis of rotation,
- a plurality of first variable pitch rotor blades supported by the non-rotating structural airframe for rotation about the rotor axis of rotation in a first rotor plane of rotation,
- a plurality of second variable pitch rotor blades supported by the non-rotating structural airframe for rotation about the rotor axis of rotation in a second rotor plane of rotation and the second rotor plane of rotation is spaced apart from the first rotor plane of rotation along the rotor axis of rotation,
- a first motor supported by the non-rotating structural airframe and adapted to drive the first variable pitch rotor blades about the rotor axis of rotation,
- a second motor supported by the non-rotating structural airframe and adapted to drive the second variable pitch rotor blades about the rotor axis of rotation,
- a first swashplate located above the second rotor plane of rotation for controlling a cyclic pitch and a collective pitch of the first rotor blades,
- a second swashplate located below the first rotor plane of rotation for controlling a cyclic pitch and a collective pitch of the second rotor blades,
- three first servo actuators supported by the non-rotating structural airframe above the second rotor plane of rotation and coupled to the first swashplate for simultaneously varying the cyclic pitch and collective pitch of the first rotor blades, and
- three second servo actuators supported by the non-rotating structural airframe below the first rotor plane of rotation and coupled to the second swashplate for simultaneously varying the cyclic pitch and collective pitch of the second rotor blades,
- wherein the first servo actuators are configured to operate independently from one another and the second servo actuators are configured to operate independently from one another.
7 more elements
Dependencies are inferred from the claim text.