Aerodynamically efficient lightweight vertical take-off and landing aircraft with pivoting rotors and stowing rotor blades
An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements and a set of tail mounted rotors for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle uses different configurations of its wing mounted rotors and propellers to reduce drag in all flight modes.
1. An aerial vehicle adapted for vertical take-off and horizontal flight, said aerial vehicle comprising:
a main vehicle body;
one or more electric power sources, said one or more electric power sources coupled to electric motors;
a right side wing, said right side wing comprising a plurality of right wing rotor assemblies attached to said right side wing by a deployment mechanism adapted to deploy said right wing rotor assemblies from a forward facing horizontal flight configuration to a vertical take-off configuration, said deployment mechanisms enclosed within a rotor mounting nacelle, wherein said rotor mounting nacelle covers said deployment mechanism and an electric motor when in said forward facing horizontal flight configuration, each of said right wing rotor assemblies comprising an electric motor, said electric motors electrically coupled to said one or more electric power sources;
a left side wing, said left side wing comprising a plurality of left wing rotor assemblies attached to said second left side wing by a deployment mechanism adapted to deploy said rotor assemblies from a forward facing horizontal flight configuration to a vertical take-off configuration, said deployment mechanisms enclosed within a rotor mounting nacelle, wherein said rotor mounting nacelle covers said deployment mechanism and an electric motor when in said forward facing horizontal flight configuration, each of said left wing rotor assemblies comprising an electric motor, said electric motors electrically coupled to said one or more electric power sources;
one or more right side rear rotor assemblies, said right side rear rotor assemblies attached to the rear of said vehicle body by a deployment mechanism adapted to deploy said right rear rotor assemblies from a forward facing horizontal flight configuration along the right side of said vehicle body to a vertical take-off configuration, said deployment mechanisms enclosed within a rotor mounting nacelle, wherein said rotor mounting nacelle covers said deployment mechanism and an electric motor when in said forward facing horizontal flight configuration, said right rear rotor assemblies comprising an electric motor, said electric motors electrically coupled to said one or more electric power sources; and
one or more left side rear rotor assemblies, said left side rear rotor assemblies attached to the rear of said vehicle body by a deployment mechanism adapted to deploy said left rear rotor assemblies from a forward facing horizontal flight configuration along the left side of said vehicle body to a vertical take-off configuration, said deployment mechanisms enclosed within a rotor mounting nacelle, wherein said rotor mounting nacelle covers said deployment mechanism and an electric motor when in said forward facing horizontal flight configuration, said left rear rotor assemblies comprising an electric motor, said electric motors electrically coupled to said one or more electric power sources.
2. The aerial vehicle of claim 1 wherein said right side wing and said left side wing are partially forward swept wings.
3. The aerial vehicle of claim 1 wherein said right side wing and said left side wing are forward swept wings.
4. The aerial vehicle of claim 3 wherein the centers of mass of said right side wing rotor assemblies are forward of the leading edge of said right side wing, and the centers of mass of said left side wing rotor assemblies are forward of the leading edges of said left side wing.
5. The aerial vehicle of claim 1 wherein said right side wing rotor assemblies and said left side wing rotor assemblies comprise propeller blades, said propeller blades adapted to pivot from a deployed configuration to a stowed configuration.
6. The aerial vehicle of claim 5 wherein stowed propeller blades reside in recesses on the outside of a rotor mounting nacelle.
7. The aerial vehicle of claim 2 wherein said right side wing rotor assemblies and said left side wing rotor assemblies comprise propeller blades, said propeller blades adapted to pivot from a deployed configuration to a stowed configuration.
8. The aerial vehicle of claim 7 wherein stowed propeller blades reside in recesses on the outside of a rotor mounting nacelle.