Dual blade fold bolts and inboard centrifugal bearing in a folding rotor blade assembly
A folding rotor blade assembly for a tiltrotor aircraft comprising a rotor blade pivotally connected to a yoke with dual concentric blade bolts having a common central axis providing a pivotal axis inboard of an outboard shear bearing. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.
1. A folding rotor blade assembly for a tiltrotor aircraft, comprising:
a drive mast connected to a hub spring assembly;
a yoke connected to the hub spring assembly;
an inboard bearing assembly connected to the yoke;
an outboard bearing assembly connected to the yoke opposite the hub spring assembly;
a grip connected to the inboard bearing assembly and connected to the outboard bearing assembly;
a blade fold support connected to the grip and abutting the outboard bearing assembly; and
a rotor blade connected to the blade fold support at a pivotal connection positioned inboard of the outboard bearing assembly.
2. The folding rotor blade assembly of claim 1 , wherein the outboard bearing assembly further comprises an outboard shear bearing.
3. The folding rotor blade assembly of claim 1 , wherein the inboard bearing assembly further comprises an inboard shear bearing and an inboard centrifugal force (“CF”) bearing.
4. The folding rotor blade assembly of claim 1 , wherein the outboard bearing assembly further comprises:
an outboard beam connected to the grip and connected to an outboard shear bearing; and
a spindle connected to the outboard shear bearing and connected to a tip of the yoke.
5. The folding rotor blade assembly of claim 1 , wherein the inboard bearing assembly further comprises:
an inboard beam connected to the grip and connected to an inboard centrifugal force (“CF”) bearing;
a clamp plate connected to the yoke and connected to an inboard shear bearing; and
the inboard shear bearing connected to the inboard centrifugal force (“CF”) bearing.
6. The folding rotor blade assembly of claim 1 , further comprising a lock mechanism connected to the blade fold support and releasably engaged with the rotor blade.
7. The folding rotor blade assembly of claim 6 , wherein the rotor blade is releasably engaged with the lock mechanism by a blade tang.
8. The folding rotor blade assembly of claim 1 , further comprising a pair of axially aligned blade fold bolts at the pivotal connection providing a pivot axis of the rotor blade relative to the blade fold support.
9. The folding rotor blade assembly of claim 1 , wherein the blade fold support further comprises:
a first stanchion extending through the grip to the outboard bearing assembly at the pivotal connection; and
a second stanchion extending through the grip to the outboard bearing assembly preventing rotation of the blade fold support relative to the grip.
10. A folding rotor blade assembly, comprising:
a yoke connected to an axially aligned with a hub spring assembly;
an inboard clamp, housing an inboard shear bearing, connected to the yoke proximate the hub spring assembly;
an inboard beam, housing an inboard centrifugal force (“CF”) bearing, connected to the yoke wherein the inboard shear bearing is connected to the inboard CF bearing;
a spindle connected to a tip of the yoke and connected to an outboard shear bearing;
an outboard beam connected to a grip and the outboard shear bearing;
a blade fold support connected to the grip and the outboard beam; and
a rotor blade connected to the blade fold support at a pivotal connection positioned inboard of the outboard shear bearing.
11. The folding rotor blade assembly of claim 10 , further comprising a lock mechanism connected to the blade fold support and releasably engaged with the rotor blade.
12. The folding rotor blade assembly of claim 11 , wherein the rotor blade is releasably engaged with the lock mechanism by a blade tang.
13. The folding rotor blade assembly of claim 10 , further comprising axially aligned blade fold bolts at the pivotal connection providing a pivot axis of the rotor blade relative to the blade fold support.
14. The folding rotor blade assembly of claim 13 , wherein the rotor blade includes a central force path positioned on the pivot axis.
15. The folding rotor blade assembly of claim 10 , wherein the blade fold support further comprises:
a first stanchion extending through the grip to the outboard beam at the pivotal connection; and
a second stanchion extending through the grip to the outboard beam.
16. A method comprising:
pitching a rotor blade of a rotor blade assembly comprising an inboard bearing assembly connected to a yoke and a grip, an outboard bearing assembly connected to the yoke and the grip, a blade support connected to the grip and the outboard bearing assembly, and a rotor blade connected to the blade support at a lockable connection and at a pivotable connection with axially aligned blade bolts providing a pivot axis inboard of the outboard bearing assembly;
unlocking the lockable connection; and
rotating the rotor blade about the pivot axis.
17. The method of claim 16 , wherein the inboard bearing assembly further comprises an inboard shear bearing and an inboard centrifugal force (“CF”) bearing.
18. The method of claim 16 , wherein the outboard bearing assembly further comprises an outboard shear bearing.
19. The method of claim 16 , wherein the rotor blade assembly is connected to a nacelle pivotally mounted to a wing.
20. The method of claim 16 , wherein the rotor blade assembly is mounted to a wing and the wing is mounted to a fuselage.