Aerodynamically efficient lightweight vertical take-off and landing aircraft with deployable rotors
An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements 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 may have deployment mechanisms which deploy electric motor driven propellers from a forward facing to a vertical orientation. The wing mounted rotor assemblies may have split nacelles, wherein a forward portion of the nacelle deploys along with the electric motor and the propeller.
1. An aerial vehicle adapted for vertical take-off and horizontal flight, said aerial vehicle comprising:
a main vehicle body;
a plurality of electric motors;
one or more electric power sources, said one or more electric power sources electrically coupled to said electric motors;
a right side wing, said right side wing comprising:
a plurality of nacelles, said nacelles comprising:
a motor cover; and
a rear nacelle portion, said rear nacelle portion structurally coupled to said right side wing;
a plurality of right wing rotor assemblies, each of said right wing rotor assemblies comprising one of said electric motors and a propeller and a spin axis, each of said 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, each of said deployment mechanisms enclosed within a nacelle, wherein said nacelle covers said deployment mechanism and an electric motor when in said forward facing horizontal flight configuration, and wherein said nacelle splits when deployed to the vertical take-off configuration such that said motor cover deploys with said electric motor and said propeller; and
a left side wing, said left side wing comprising:
a plurality of nacelles, said nacelles comprising:
a motor cover; and
a rear nacelle portion, said rear nacelle portion structurally coupled to said left side wing;
a plurality of left wing rotor assemblies, each of said left wing rotor assemblies comprising one of said electric motors and a propeller and a spin axis, each of said left wing rotor assemblies attached to said left side wing by a deployment mechanism adapted to deploy said left wing rotor assemblies from a forward facing horizontal flight configuration to a vertical take-off configuration, each of said deployment mechanisms enclosed within a nacelle, wherein said nacelle covers said deployment mechanism and an electric motor when in said forward facing horizontal flight configuration, and wherein said nacelle splits when deployed to the vertical take-off configuration such that said motor cover deploys with said electric motor and said propeller,
wherein said deployment mechanisms comprise:
an extendable linkage assembly, said extendable linkage assembly comprising a plurality of pivoting mounting points on a first end, said pivoting mounting points adapted to mount to fixed mounting points on an electric vertical take-off and landing aircraft; and
an outboard bracket, said outboard bracket comprising a central axis, said outboard bracket coupled to a second end of said extendable linkage,
wherein said extendable linkage is adapted to deploy said outboard bracket from a first position where said central axis of said outboard bracket is horizontal to a second position wherein said central axis of said outboard bracket is vertical, and wherein all of said outboard bracket is further forward from said plurality of main pivoting mounting points in said second position than in said first position, and wherein all of said outboard bracket is higher in said second position than in said first position.
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 1 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 the spin axis of said one or more right side wing rotor assemblies are forward of the leading edge of the wing in the vertical take-off position, and wherein the spin axis of said one or more left side wing rotor assemblies are forward of the leading edge of the wing in the vertical take-off position.
6. The aerial vehicle of claim 4 wherein the spin axis of said one or more right side wing rotor assemblies are forward of the leading edge of the wing in the vertical take-off position, and wherein the spin axis of said one or more left side wing rotor assemblies are forward of the leading edge of the wing in the vertical take-off position.
7. The aerial vehicle of claim 5 wherein an outside diameter of the propellers, when spinning, of said right side rotor assemblies are forward to the leading edge of the right side wing, and wherein the outside diameter of the spinning propellers blades of the propellers of said left side rotor assemblies are forward to the leading edge of the left side wing.
8. The aerial vehicle of claim 6 wherein an outside diameter of the propellers, when spinning, of said right side rotor assemblies are forward to the leading edge of the right side wing, and wherein the outside diameter of the spinning propellers blades of the propellers of said left side rotor assemblies are forward to the leading edge of the left side wing.
9. The aerial vehicle of claim 1 wherein said electric power sources are batteries.
10. The aerial vehicle of claim 7 wherein said electric power sources are batteries.
11. The aerial vehicle of claim 8 wherein said electric power sources are batteries.
12. The aerial vehicle of claim 1 wherein said extendable linkage assembly further comprises one or more multi-arm linkages.
13. The aerial vehicle of claim 12 wherein said extendable linkage assembly further comprises;
a first multi-arm linkage comprising a first end and a second end, said first multi-arm linkage comprising first pivoting mounting point at its first end, said second end of said first multi-arm linkage pivotally coupled to said outboard bracket;
a second multi-arm linkage comprising a first end and a second end, said second multi-arm linkage comprising second pivoting mounting point at its first end, said second end of said second multi-arm linkage pivotally coupled to said outboard bracket;
wherein said an arm of said first multi-arm linkage is pivotally coupled to an arm of said second multi-arm linkage.
14. The aerial vehicle of claim 11 wherein said extendable linkage assembly further comprises one or more multi-arm linkages.
15. The aerial vehicle of claim 14 wherein said extendable linkage assembly further comprises;
a first multi-arm linkage comprising a first end and a second end, said first multi-arm linkage comprising first pivoting mounting point at its first end, said second end of said first multi-arm linkage pivotally coupled to said outboard bracket;
a second multi-arm linkage comprising a first end and a second end, said second multi-arm linkage comprising second pivoting mounting point at its first end, said second end of said second multi-arm linkage pivotally coupled to said outboard bracket;
wherein said an arm of said first multi-arm linkage is pivotally coupled to an arm of said second multi-arm linkage.