Spherical bearing centrifugal force retention link

1. A rotor blade assembly, comprising:

a hub rotatable about a rotational axis;

a rotor blade extending radially from the hub along a pitch axis and having a rotor blade pitch range; and

a centrifugal force (CF) link having an inboard spherical bearing attached to the hub and an outboard spherical bearing attached to the rotor blade and a torsional moment of the CF link is constant throughout the rotor blade pitch range.

2. The rotor blade assembly of claim 1 , wherein the CF link comprises a beam between the inboard spherical bearing and the outboard spherical bearing.

3. The rotor blade assembly of claim 1 , wherein the rotor blade pitch range is between 70 and 85 degrees.

4. The rotor blade assembly of claim 1 , wherein the rotor blade pitch range is 50 to 85 degrees.

5. The rotor blade assembly of claim 1 , wherein the inboard spherical bearing and the outboard spherical bearing react a centrifugal force radially.

6. The rotor blade assembly of claim 1 , further comprising a blade grip having an inboard end connected to the outboard spherical bearing and a first blade grip portion rotationally coupled to the hub outboard of the inboard end.

7. The rotor blade assembly of claim 6 , wherein the inboard spherical bearing and the outboard spherical bearing react a centrifugal force radially.

8. The rotor blade assembly of claim 7 , wherein the rotor blade pitch range is 50 to 85 degrees.

9. The rotor blade assembly of claim 7 , wherein the rotor blade pitch range is between 70 and 85 degrees.

10. A rotorcraft, comprising:

a rotor comprising a hub rotatable about a rotational axis;

a rotor blade extending radially from the hub along a pitch axis and having a rotor blade pitch range; and

a centrifugal force (CF) link having an inboard spherical bearing attached to the hub and an outboard spherical bearing attached to the rotor blade, wherein the inboard spherical bearing and the outboard spherical bearing react centrifugal force radially, and a torsional moment of the CF link is constant throughout the rotor blade pitch range.

11. The rotorcraft of claim 10 , wherein the rotor is located in a duct.

12. The rotorcraft of claim 10 , wherein the rotor is an anti-torque rotor.

13. The rotorcraft of claim 10 , wherein the rotor blade pitch range is between 70 and 85 degrees.

14. The rotorcraft of claim 10 , wherein the rotor is a ducted anti-torque rotor; and

the rotor blade pitch range is between 70 and 85 degrees.

15. The rotorcraft of claim 10 , wherein the rotor blade pitch range is between 50 to 85 degrees.

16. A ducted fan, comprising:

a duct having a central axis;

a rotor assembly located in the duct, the rotor assembly comprising:

a hub rotatable about a rotational axis coaxial with the central axis;

a rotor blade extending radially from the hub along a pitch axis and having a rotor blade pitch range; and

a centrifugal force (CF) link having an inboard spherical bearing attached to the hub and an outboard spherical bearing attached to the rotor blade, wherein the inboard spherical bearing and the outboard spherical bearing react centrifugal force radially, and a torsional moment of the CF link is constant throughout the rotor blade pitch range.

17. The ducted fan of claim 16 , further comprising a blade grip having an inboard end connected to the outboard spherical bearing and a first blade grip portion rotationally coupled to the hub outboard of the inboard end.

18. The ducted fan of claim 16 , wherein the rotor blade pitch range is between 70 and 85 degrees.

19. The ducted fan of claim 18 , further comprising a blade grip having an inboard end connected to the outboard spherical bearing and a first blade grip portion rotationally coupled to the hub outboard of the inboard end.

20. The ducted fan of claim 16 , wherein the rotor blade pitch range is between 50 to 85 degrees.