Motive fairing assembly for use in rotorcrafts

1. A rotor assembly with a longitudinal length for use in a stop-fold aircraft comprising:

a rotor hub;

a spinner structure comprising a spinner opening;

a rotor blade received through the spinner opening, the rotor blade comprising a rotor root located proximate to the rotor hub, the rotor blade being movable between an extended position and a folded position; and

a fairing face that moves along and is disposed outside the rotor hub;

wherein moving the rotor blade from the extended position to the folded position does not increase a longitudinal overlap between the rotor blade and the spinner structure.

2. The rotor assembly according to claim 1 , wherein the fairing face is situated above the rotor blade and the spinner opening.

3. The rotor assembly according to claim 2 , wherein the fairing face has aerodynamically tailored geometry.

4. The rotor assembly according to claim 3 , wherein the fairing face further comprises a base with a u-shaped bottom that is designed to partially encompass the blade root.

5. The rotor assembly according to claim 4 , wherein an actuator assembly is used to selectively move the fairing face.

6. The rotor assembly according to claim 5 , wherein the fairing face is configured to move along the longitudinal length of the rotor assembly.

7. The rotor assembly according to claim 6 , wherein the fairing face is configured to move along a curved path.

8. The rotor assembly according to claim 7 , wherein the actuator assembly further comprises an actuator ring and a ball screw to selectively move the fairing face.

9. The rotor assembly according to claim 8 , wherein the fairing face comprises:

a roller protrusion; and

a roller attached to the roller protrusion; and

wherein the actuator assembly comprises:

a power source in mechanical communication with the ball screw;

a mechanical arm to couple the power source to the fairing face; and

a slider track placed along the longitudinal length of the rotor assembly along which the roller rolls.

10. The rotor assembly according to claim 9 , wherein the rotor assembly further comprises:

a plurality of rotor blades;

a plurality of spinner openings; and

a plurality of fairing faces; and

wherein the actuator assembly is configured to simultaneously move the plurality of fairing faces.

11. The rotor assembly according to claim 8 , wherein the actuator assembly comprises:

a power source in mechanical communication with the actuator ring and the ball screw; and

a four-bar linkage to couple the power source to the fairing face.

12. The rotor assembly according to claim 11 , wherein the rotor assembly further comprises:

a plurality of rotor blades;

a plurality of spinner openings; and

a plurality of fairing faces; and

wherein the actuator assembly is configured to simultaneously move the plurality of fairing faces.

13. The rotor assembly according to claim 7 , wherein the rotor assembly has a non-folded mode, wherein the rotor blade extends radially outward and can selectively flap and feather, and a folded mode, wherein the rotor blade is folded along the longitudinal length of the rotor assembly and are locked, thereby preventing flapping motion and feathering motion.

14. The rotor assembly according to claim 13 , wherein the fairing face is lowered proximate to the spinner opening in the folded mode.

15. A method of using a stop-fold aircraft pilot input system in mechanical and electronic communication with a rotor assembly comprising a spinner structure having a spinner opening, a rotor blade, a rotor hub and a fairing face that moves along and is disposed outside the rotor hub, wherein the fairing face is situated upstream relative to both the spinner opening and the rotor blade to move along the longitudinal length of the rotor assembly, wherein the rotor blade is movable between an extended position and a folded position and wherein moving the rotor blade from the extended position to the folded position does not increase a longitudinal overlap between the rotor blade and the spinner structure.

16. The method of claim 15 , wherein in response to a pilot input into the pilot input system the rotor blade is first folded laterally along the length of the rotor assembly and the fairing face is secondly moved closer to the spinner opening.

17. The method of claim 16 , wherein in response to a pilot input into the pilot input system the fairing face is first moved away from the spinner opening and the rotor blade is secondly unfolded to extend radially outward.

18. A stop-fold aircraft comprising:

a body;

a wing coupled to the body;

a power train coupled to at least one of the body or the wing and comprising a power source and a pylon assembly in mechanical communication with the power source;

a rotor assembly pivotally coupled to the wing in mechanical communication with the pylon assembly, the rotor assembly comprising:

a rotor hub in mechanical communication with the pylon assembly;

a spinner structure comprising a spinner opening;

a rotor blade received through the spinner opening in mechanical communication with the rotor hub and foldable laterally along the length of the pylon assembly, the rotor blade being movable between an extended position and a folded position; and

a fairing face that moves along and is disposed outside the rotor hub;

a fairing face that moves along and is disposed outside the rotor hub, the fairing face being situated upstream of the spinner opening and rotor blade, the fairing face being configured to move longitudinally along the length of the rotor assembly; and

an actuator assembly for selectively moving the fairing face;

wherein moving the rotor blade from the extended position to the folded position does not increase a longitudinal overlap between the rotor blade and the spinner structure.

19. The stop-fold aircraft according to claim 18 , wherein the rotor assembly further comprises:

a plurality of rotor blades;

a plurality of spinner openings; and

a plurality of fairing faces; and

wherein the actuator assembly is configured to simultaneously move the plurality of fairing faces.

20. The stop-fold aircraft according to claim 19 , further comprising:

a cockpit; and

a pilot input system in mechanical or electronic communication with the plurality of rotor blades and the plurality of fairing faces.