Granted Patent B2

US 9,056,674 · App. 13/283,461 · Granted Jun 16, 2015

Inventor: Robert Owen White (Orillia Ontario, CA)

Assignee: GROEN BROTHERS AVIATION, INC.

B64C27/473Y10T29/49318B64C11/06B64C11/24B64C11/20B64C15/14B64C27/22B64C27/82B64C2027/8245B64C27/18B64C27/26

Abstract

Claims (63)

1. A rotorcraft rotor comprising:

a hub configured to rotationally mount to a mast of a rotorcraft; and

a plurality of rotor blades, each rotor blade comprising

rotatably mounted to the hub;

leading edge fairing being mounted to the blade spar such that the leading edge fairing extends along a major portion of the blade spar;

a trailing edge fairing mounted to the blade spar such that the trailing edge fairing extends along a major portion of the blade spar and is located opposite the leading edge fairing secured to the blade spar and such that the blade spar, leading edge fairing, and trailing edge fairing form an airfoil contour along the length of the leading edge fairing;

at least one line formed to do at least one of extending between the leading edge fairing and the blade spar and extending between the trailing edge fairing and the blade spar; and

one or more detachable fairings, each of the detachable fairings being selectively securable to the blade spar and one of the leading and trailing edge fairings being flush with one of the leading and trailing edge fairings such that the blade spar and one or more detachable fairings form an airfoil contour;

wherein each rotor blade further comprises

the blade spar comprising a proximal end and a distal end, the blade spar pivotably secured to the hub at the proximal end; and

each of the one or more detachable fairings extending between a distal end of one of the leading and trailing edge fairings and the distal end of the blade spar.

2. The rotorcraft of claim 1 , wherein each rotor blade further comprises:

a tip jet attachment fitting secured to the distal end of the blade spar, the tip jet attachment fitting adapted to mount a tip jet to the blade spar; and

each of the one or more detachable fairings selectively securable to the tip jet attachment fitting.

3. The rotorcraft of claim 2 , wherein each rotor blade further comprises the one or more detachable fairings and the tip jet attachment fitting forming an airfoil contour.

4. The rotor craft of claim 1 , wherein each rotor blade further comprises:

at least one of the leading and trailing edge fairings comprising a tapered portion extending proximally from the distal end thereof; and

the one or more detachable fairings comprising a tapered portion shaped to mate with the tapered portion of at least one of the leading and trailing edge fairings.

5. The rotorcraft of claim 1 , wherein each rotor blade further comprises:

each of the one or more detachable fairings being positioned between a proximal end of one of the leading and trailing edge fairings and the proximal end of the blade spar.

6. The rotorcraft of claim 5 , wherein each rotor blade further comprises:

at least one of the leading and trailing edge fairings comprising a tapered portion extending distally from the proximal end thereof; and

the one or more detachable fairings comprising a tapered portion shaped to mate with the tapered portion of at least one of the leading and trailing edge fairings.

7. The rotorcraft of claim 5 , wherein each rotor blade further comprises:

a mounting structure secured to the blade spar; and

the one or more detachable fairings secure to the blade spar by means of the mounting structure.

8. The rotorcraft of claim 7 , wherein each rotor blade further comprises:

the mounting structure comprising an upper plate and a lower plate; and

the one or more detachable fairings securing to both the upper plate and lower plate, such that the one or more detachable fairings and the upper and lower plates form an airfoil contour.

9. The rotorcraft of claim 8 , further comprising:

a hub shroud positioned around the hub, the hub shroud including a spherical surface having a plurality spar apertures formed therein;

each blade spar further extending through each spar aperture, respectively;

each mounting structure further including a spherical seat interfacing with the spherical surface; and

proximal ends of each detachable fairing further securing to each spherical seat.

10. The rotorcraft of claim 9 , wherein each spherical seat defines at least one line aperture and each line extends through each ene line aperture, respectively.

11. The rotorcraft of claim 8 , wherein each rotor blade further comprises:

at least one actuator secured to at least one of the upper and lower plates;

at least one control cable coupled to the actuator and extending between one of the leading and trailing edge fairings and the blade spar.

12. The rotorcraft of claim 11 , wherein each rotor blade further comprises the control cable being intersected by a neutral bending plane of the combined blade spar and leading and trailing edge fairings.

13. The rotorcraft of claim 8 , wherein each rotor blade further comprises:

the blade spar comprising an upper registration surface and a lower registration surface; and

the upper and lower plates each including a mating surface, the mating surface of the upper plate engaging the upper registration surface and the mating surface of the lower plate engaging the lower registration surface.

14. The rotorcraft of claim 13 , wherein each rotor blade further comprises the upper and lower registration surfaces comprising surfaces extending radially outward from a center of the blade spar.

15. The rotorcraft of claim 14 , wherein each rotor blade further comprises:

the blade spar defining a longitudinal direction extending between the proximal and distal ends; and

the upper and lower registration surfaces extending both perpendicular and parallel to the longitudinal direction.

16. A method for servicing a rotor blade comprising:

removing a detachable portion of one of a leading edge fairing and a trailing edge fairing from a rotor blade, the rotor blade including:

a blade spar adapted to rotatably mount to a hub of a rotorcraft, the leading and trailing edge fairings being mounted to the blade spar; and

control lines extending between the blade spar and at least one of the leading and trailing edge fairings;

servicing one or more of the control lines; and

reattaching the portion of the one of the trailing edge fairing and the leading edge fairing.

17. The method of claim 16 , wherein:

the blade spar comprises a proximal end and a distal end;

the leading and trailing edge fairings further comprise a major portion secured to the blade spar and extending along a major portion of the longitudinal extent thereof; and

the detachable portion extends between a distal end of the major portion of one of the leading and trailing edge fairings and the distal end of the blade spar.

18. The method of claim 17 , wherein:

the blade further comprises a tip jet attachment fitting secured to the distal end of the blade spar, the tip jet attachment fitting adapted to mount a tip jet to the blade spar; and

removing the detachable portion of one of the leading edge fairing and trailing edge fairing further comprises releasing fasteners securing the detachable portion to the tip jet attachment fitting.

19. The method of claim 16 , wherein:

the blade spar comprises a proximal end and a distal end;

the leading and trailing edge fairings further comprise a major portion secured to the blade spar and extending along a major portion of the longitudinal extent thereof; and

the detachable portion extends proximally from the proximal end of the major portion of one of the leading and trailing edge fairings toward the proximal end of the blade spar.

Assignments (12)

Continuity (2)