Convertible rotor aircraft
AssigneeYoav Netzer
InventorYoav Netzer
Life of this patent
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Abstract
A convertible rotor aircraft (CRA) able to convert between airplane and helicopter flight modes during flight, comprising: at least one tillable proprotor assembly (TPA) comprising a proprotor that is tiltable to change the axis of rotation of the proprotor between a substantially horizontal airplane mode and a substantially vertical helicopter mode; and a main rotor system for providing lift during helicopter mode comprising at least one rotor, which produces airflow that flows through at least a portion the proprotor blades of the at least one TPA.
Claims16
A convertible rotor aircraft (CRA) able to convert between airplane and helicopter flight modes during flight, comprising:
- a rotor system for providing lift during helicopter mode comprising two intermeshing rotors in a synchropter arrangement on opposite sides of a longitudinal axis of the CRA, each rotor being pivotable around an axis that is substantially parallel to a longitudinal axis of the CRA and into a folded state.
A convertible rotor aircraft able to convert between airplane and helicopter flight modes during flight, comprising:
- at least one rotor comprising at least one rotor blade that is rotatable to provide lift to an aircraft, wherein:
- the at least one rotor is pivotable around an axis that is substantially parallel to a longitudinal axis of the aircraft to transition between a folded state in which the at least one rotor blade of the at least one rotor lies substantially along the longitudinal axis of the aircraft and a deployed state in which the at least one blade is rotatable to provide lift to the aircraft;
- and
- the at least one rotor is controlled to be in the folded state during the airplane flight mode and the deployed state during the helicopter flight mode.
A rotor system for providing lift to an aircraft, the rotor system comprising:
- two rotors on opposite sides of a longitudinal axis of the aircraft, each rotor comprising at least one rotor blade, wherein each rotor of the two rotors are respectively pivotable around an axis that is substantially parallel to a longitudinal axis of the aircraft so that the two rotors can transition between a folded state in which the at least one rotor blade of each rotor respectively lies substantially parallel to the longitudinal axis and a deployed state in which the two rotors are configured as intermeshing rotors in a synchropter arrangement and the at least one blade of each of the two rotors are rotatable to provide lift to the aircraft.
Dependencies are inferred from the claim text.