A rotor for use on an aircraft has a plurality (N) of rotor blades mounted on a plurality (N) of concentric masts. Each of the rotor blades has a rounded leading edge and a tapered trailing edge. The plurality (N) of concentric masts each operably mount one of the plurality of rotor blades at N diff
A rotor for use on an aircraft has a plurality (N) of rotor blades mounted on a plurality (N) of concentric masts. Each of the rotor blades has a rounded leading edge and a tapered trailing edge. The plurality (N) of concentric masts each operably mount one of the plurality of rotor blades at N different elevations. A locking element selectively locks or unlocks the concentric masts together in a plane of rotation, enabling the angle between any two rotor blades to be variable from 0-360 degrees during flight. A feathering hinge is operably attached to each blade for changing the pitch of each blade with respect to the plane of rotation as controlled by a pitch control mechanism.
대표청구항▼
1. A rotor comprising: two rotor blades, each having a rounded leading edge and a tapered trailing edge to reduce drag and improve lift efficiency;two concentric masts, each for operably mounting one of the plurality of rotor blades at two different elevations substantially parallel to a plane of ro
1. A rotor comprising: two rotor blades, each having a rounded leading edge and a tapered trailing edge to reduce drag and improve lift efficiency;two concentric masts, each for operably mounting one of the plurality of rotor blades at two different elevations substantially parallel to a plane of rotation;a locking element for selectively locking and unlocking the concentric masts such that an angle between any two rotor blades may be variable within the plane of rotation during flight when the locking element is unlocked;a feathering hinge attached to each blade for changing the pitch of each blade with respect to the plane of rotation; anda pitch control mechanism operably attached to the feathering hinges of the blades for controlling the pitches of the blades collectively. 2. The rotor as recited in claim 1, further comprising a rotor enclosure adapted to be pivotally mounted on an aircraft, the lower parts of concentric masts being operably mounted within the rotor enclosure. 3. The rotor as recited in claim 1, wherein the locking element enables the angle between any two rotor blades to be variable between 0-360 degrees within the plane of rotation during flight. 4. An aircraft capable of flying in both rotary wing mode and fixed wing mode, the aircraft comprising: a fuselage having right and left sides;two fixed wings extending from the left and right sides of the fuselage;two rotor enclosures mounted on or adjacent to the fuselage and/or the two fixed wings; anda pair of rotors, each of the rotors being operably mounted on one of the rotor enclosures, each of the rotors comprising: two rotor blades, each having a rounded leading edge and a tapered trailing edge to reduce drag and improve lift efficiency;two concentric masts, each for operably mounting one of the plurality of rotor blades at two different elevations;a locking element for selectively locking or unlocking the concentric masts together, enabling the angle between any two rotor blades to be variable from 0-360 degrees during flight when the locking element is unlocked;a feathering hinge attached to each blade for changing the pitch of each blade with respect to the plane of rotation; anda pitch control mechanism operably attached to the feathering hinges of the blades for controlling the pitches of the blades collectively. 5. The aircraft of claim 4, further comprising: wherein the aircraft may fly in the fixed wing mode in which the rotor blades are stopped in the plane of rotation and the angles between the rotor blades of each rotor are reduced in the plane of rotation so that the rotor blades may be configured and positioned in any of the following manners: a) all rotor blades of each rotor function as fixed wings in blade advancing regions; b) some of the rotor blades functions as fixed wings and the rest of rotor blades are positioned at the trailing positions; and c) all of the rotor blades of each rotor are positioned at the trailing position; andwherein the aircraft may fly in the rotary wing mode in which the rotor blades of each rotor are substantially evenly spaced in the plane of rotation so that when the rotor blades are rotated they provide lift to enable the aircraft to fly vertically, hover, and fly translationally at relatively low speeds. 6. The aircraft of claim 4, wherein, when the aircraft transitions in flight from rotary wing mode to fixed wing mode, the aircraft enters an intermediate flight regime during which the main fixed wings provides lift to the aircraft, thereby enabling the rotors to be free of lift requirement in order that the rotor blades may be stopped, and positioned into their fixed wing configuration. 7. The aircraft as recited in claim 6, wherein substantially all of the aerodynamic lift for the aircraft during said intermediate flight regime is provided by lifting surfaces other than the rotors. 8. The aircraft as recited in claim 4, further comprising at least one jet engine operably mounted on the aircraft for horizontal propulsion of the aircraft; and a transmission for operably connecting the at least one jet engine with the pair of rotors for turning the rotor blades. 9. An aircraft capable of flying in both rotary wing mode and fixed wing mode, the aircraft comprising: a fuselage having a top, right and left sides, and a longitudinal axis;two fixed wings extending from the left and right sides of the fuselage; anda pair of counter rotating rotors mounted on the top of the fuselage laterally transverse to the longitudinal axis of the fuselage, each of the rotors comprising: a pair of rotor blades, each having a rounded leading edge and a tapered trailing edge to reduce drag and improve lift efficiency;a pair of concentric masts, each for operably mounting one of the plurality of rotor blades;a locking element for selectively locking or unlocking the concentric masts together in a plane of rotation, enabling the angle between the two rotor blades to be variable during flight when the locking element is unlocked;a feathering hinge attached to each blade for changing the pitch of each blade with respect to the plane of rotation; anda pitch control mechanism operably attached to the feathering hinges of the blades for controlling the pitches of the blades collectively,whereby the counter rotating rotors are operably mounted such that the rotors intermesh with each other in the rotary wing mode. 10. The aircraft of claim 9, further comprising: wherein the aircraft may fly in the fixed wing mode in which the rotor blades of each rotor are stopped in the plane of rotation and the angles between the blades of each rotor are reduced to 90 degrees in the plane of rotation of each rotor so that the rotor blades may be configured and positioned such that all four rotor blades function as fixed wings in blade advancing regions, with two blades at 45 degrees forward swept and two blades at 45 degrees aft swept; andwherein the aircraft may fly in the rotary wing mode in which the two rotor blades of each rotor are spaced at 180 degrees in the plane of rotation of each rotor so that when the rotor blades are rotated they provide lift to enable the aircraft to fly vertically, hover, and fly translationally at relatively low speeds.
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이 특허에 인용된 특허 (8)
Rutherford John W. (Scottsdale AZ) O\Rourke Matthew (Newport News VA) McDonnell William R. (St. Louis MO) Smith Brian T. (Everett WA), Canard rotor/wing.
Vetter, Eugene H; Vetter, James W; Vetter, Paul A, Devices and methods for in flight transition VTOL/fixed wing hybrid aircraft structures and flight modes.
Sada-Salinas, Jaime G.; Arellano-Escarpita, David Alejandro, Modular nacelles to provide vertical takeoff and landing (VTOL) capabilities to fixed wing aerial vehicles, and associated systems and methods.
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