Articulated electric propulsion system with fully stowing blades and lightweight vertical take-off and landing aircraft using same
An aerial vehicle adapted for vertical takeoff and landing using pivoting thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to takeoff with thrust units providing vertical thrust and then transitioning to a horizontal flight path. An aerial vehicle with pivoting thrust units with propellers, wherein some or all of the propellers are able to be stowed and fully nested during forward flight.
1. A vertical take-off and landing aircraft, said vertical take-off and landing aircraft comprising:
a left wing, said left wing comprising one or more propulsion assemblies; and
a right wing, said right wing comprising one or more propulsion assemblies, wherein said propulsion assemblies comprise:
a nacelle body, said nacelle body comprising a first principal axis along its center, and
a stowable propeller system, said stowable propeller system comprising:
a central hub, said central hub comprising a first rotation axis;
a drive motor, said drive motor rigidly coupled to said central hub;
a plurality of propeller blades, said plurality of propeller blades pivotally attached to said central hub, said propeller blades comprising blade tips at an end away from said central hub
wherein said blade tips of said blades when stowed in a direction substantially parallel to said first principal axis reside forward of the leading edge of said left wing and said right wing.
2. A vertical take-off and landing aircraft, said vertical take-off and landing aircraft comprising:
a left wing, said left wing comprising one or more propulsion assemblies; and
a right wing, said right wing comprising one or more propulsion assemblies, wherein said propulsion assemblies comprise:
a nacelle body, said nacelle body comprising recesses in its outer surface when said propeller blades are in a deployed position, and
a stowable propeller system, said stowable propeller system comprising:
a central hub, said central hub comprising a first rotation axis;
a drive motor, said drive motor rigidly coupled to said central hub;
a plurality of propeller blades, said plurality of propeller blades pivotally attached to said central hub, said propeller blades comprising blade tips at an end away from said central hub,
wherein said blade tips of said blades when stowed reside forward of the leading edge of said left wing and said right wing, and wherein said propeller blades are adapted to stow into said recesses in the outer surface of the nacelle body.
3. The vertical take-off and landing aircraft of claim 2 wherein said stowable propeller system further comprises a first rotation axis along its center, and wherein said propeller blades are adapted to pivot from a stowed position in the recesses of the nacelle body to a deployed position to a deployed position substantially perpendicular to said first rotation axis.
4. The vertical take-off and landing aircraft of claim 3 further comprising a rotary positional sensor adapted to sense the rotary position of said propeller blades relative to said nacelle body.
5. The vertical take-off and landing aircraft of claim 3 further comprising a stowing mechanism, said stowing mechanism adapted to stow said propeller blades into said recesses in the outer surface of the nacelle body.
6. The vertical take-off and landing aircraft of claim 4 further comprising a stowing mechanism, said stowing mechanism adapted to stow said propeller blades into said recesses in the outer surface of the nacelle body.
7. The vertical take-off and landing aircraft of claim 5 further comprising a spring system adapted to deploy the propeller blades from their stowed position.
8. The vertical take-off and landing aircraft of claim 6 further comprising a spring system adapted to deploy the propeller blades from their stowed position.
9. The vertical take-off and landing aircraft of claim 2 further comprising a rotor deployment mechanism, said rotor deployment mechanism coupled to said central hub on a first end, said rotor deployment mechanism coupled to mounting points within said nacelle body on a second end, wherein said rotor deployment mechanism is adapted to deploy said central hub and said drive motor.
10. The vertical take-off and landing aircraft of claim 9 wherein said nacelle body comprises a first principal axis along its center, and wherein said rotor deployment mechanism comprises one or more linkage assemblies adapted to deploy said central hub and said drive motor from a first position wherein said first rotation axis and said first principal axis are parallel to a second position wherein said first rotation axis and said first principal axis are substantially perpendicular.
11. The vertical take-off and landing aircraft of claim 7 further comprising a rotor deployment mechanism, said rotor deployment mechanism coupled to said central hub on a first end, said rotor deployment mechanism coupled to mounting points within said nacelle body on a second end, wherein said rotor deployment mechanism is adapted to deploy said central hub and said drive motor.
12. The vertical take-off and landing aircraft of claim 11 wherein said nacelle body comprises a first principal axis along its center, and wherein said rotor deployment mechanism comprises one or more linkage assemblies adapted to deploy said central hub and said drive motor from a first position wherein said first rotation axis and said first principal axis are parallel to a second position wherein said first rotation axis and said first principal axis are substantially perpendicular.