Convertible rotor aircraft
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.
1. 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.
2. 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.
3. The convertible rotor aircraft according to claim 2 , wherein the at least one rotor comprises two rotors.
4. The convertible rotor aircraft according to claim 3 , wherein the two rotors are located on opposite sides of the longitudinal axis of the aircraft.
5. The convertible rotor aircraft according to claim 4 , wherein the two rotors are configured as intermeshing rotors in a synchropter arrangement.
6. The convertible rotor aircraft according to claim 2 , wherein in the folded state, the rotor is positioned to be apposed to a surface of a body of the aircraft.
7. The convertible rotor aircraft according to claim 2 , wherein in the folded state, the rotor is positioned so that a longitudinal axis of a mast of the rotor is substantially parallel to a lateral axis of the aircraft.
8. The convertible rotor aircraft according to claim 2 , wherein, in the folded state, the rotor is positioned so that at least a portion of a major surface of the at least one blade of each rotor is substantially flush against a portion of the aircraft body.
9. The convertible rotor aircraft according to claim 2 , wherein an arrangement of a rotor hub to a respective rotor mast in unchanged between the folded state and the deployed state.
10. The convertible rotor aircraft in accordance with claim 2 , comprising at least one tiltable proprotor assembly comprising a proprotor that is tiltable to change the axis of rotation of the proprotor between a substantially horizontal orientation to provide forward thrust and a substantially vertical orientation to provide lift.
11. The convertible rotor aircraft in accordance with claim 2 , comprising a propeller system to provide forward thrust.
12. The convertible rotor aircraft in accordance with claim 2 , comprising a jet propulsion system to provide forward thrust.
13. The convertible rotor aircraft in accordance with claim 2 comprising a blade holder operable to substantially immobilize the at least one blade when the rotor is in a folded state.
14. The convertible rotor aircraft in accordance with claim 13 , wherein the blade holder comprises a structure operable to close around a portion of the at least one blade.
15. The convertible rotor aircraft in accordance with claim 13 , wherein the blade holder comprises an electromagnet placed underneath a surface of the aircraft body designated to receive the at least one blade.
16. 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.