Purebred and hybrid electric VTOL tilt rotor aircraft
First Claim
1. A vertical takeoff and landing (VTOL), electrically-powered, winged aircraft, comprising:
- first and second tiltable nacelles disposed on a left wing and a right wing of the aircraft, respectively, each of the first and second nacelles configured to tilt with respect to the left and right wing, respectively;
first and second sets of electric motors disposed in the respective first and second nacelles;
first and second rotors mounted on the first and second nacelles, respectively, the first and second electric rotors configured to collectively produce a thrust force counter to a weight of the aircraft;
at least one electrical energy store coupled simultaneously and separably to each motor of the first and second sets;
wherein the at least one electrical energy store is configured to provide sufficient energy such that the aircraft is capable of achieving hover-out-of-ground-effect (HOGE) for a period of at least four minutes while one of the motors of the left or right set is inoperative, and while the aircraft carries a payload of at least 300 pounds;
wherein the first rotor has a maximum tip speed of less than Mach 0.7 M at sea level in a standard atmosphere; and
wherein the aircraft lacks a cross shaft coupling the electric motor set or rotor of the first or second nacelle to the electric motor set or rotor of the other nacelle, wherein the aircraft lacks a shifting gearbox between each of the first and second electric motor sets and its respective rotor, and wherein the aircraft has a maximum disk loading of less than 15 lbs/sq ft.
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Accused Products
Abstract
Electrically powered Vertical Takeoff and Landing (VTOL) aircraft are presented. Contemplated VTOL aircraft can include one or more electrical energy stores capable of delivering electrical power to one or more electric motors disposed within one or more rotor housings, where the motors can drive the rotors. The VTOL aircraft can also include one or more sustainer energy/power sources (e.g., batteries, engines, generators, fuel-cells, semi-cells, etc.) capable of driving the motors should the energy stores fail or deplete. Various VTOL configurations are presented including an all-battery purebred design, a light hybrid design, and a heavy hybrid design. The contemplated configurations address safety, noise, and outwash concerns to allow such designs to operate in built-up areas while retaining competitive performance relative to existing aircraft.
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Citations
13 Claims
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1. A vertical takeoff and landing (VTOL), electrically-powered, winged aircraft, comprising:
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first and second tiltable nacelles disposed on a left wing and a right wing of the aircraft, respectively, each of the first and second nacelles configured to tilt with respect to the left and right wing, respectively; first and second sets of electric motors disposed in the respective first and second nacelles; first and second rotors mounted on the first and second nacelles, respectively, the first and second electric rotors configured to collectively produce a thrust force counter to a weight of the aircraft; at least one electrical energy store coupled simultaneously and separably to each motor of the first and second sets; wherein the at least one electrical energy store is configured to provide sufficient energy such that the aircraft is capable of achieving hover-out-of-ground-effect (HOGE) for a period of at least four minutes while one of the motors of the left or right set is inoperative, and while the aircraft carries a payload of at least 300 pounds; wherein the first rotor has a maximum tip speed of less than Mach 0.7 M at sea level in a standard atmosphere; and wherein the aircraft lacks a cross shaft coupling the electric motor set or rotor of the first or second nacelle to the electric motor set or rotor of the other nacelle, wherein the aircraft lacks a shifting gearbox between each of the first and second electric motor sets and its respective rotor, and wherein the aircraft has a maximum disk loading of less than 15 lbs/sq ft. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13)
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Specification