Method and apparatus for in-flight blade folding
A foldable rotor system for a rotorcraft, the foldable rotor system comprising a rotor assembly operably associated with a driveshaft, the driveshaft being operable associated with an engine, the rotor assembly comprising a rotor blade connected to a grip pin. A swashplate is operable associated with the grip pin in order selectively change a pitch of the rotor blade. A blade fold actuator is operably associated with the grip pin such that the blade fold actuator is configured to fold and unfold the rotor blade about a blade fold axis. During an airplane mode, the rotorcraft can stop and fold the rotor blades so that the rotorcraft relies upon thrust from the engine for propulsion. The rotor blades are folded in a spiral fold path so that the rotor blades remain substantially edgewise, or feathered, during the folding process. The spiral fold path minimizes the aerodynamic drag experienced by the rotor blades while being folded during flight of the rotorcraft.
1. A foldable rotor system for a rotorcraft, the foldable rotor system, comprising:
a rotor assembly comprising:
a rotor blade connected to a grip pin that is rotatable about a grip pin axis;
a swashplate operably associated with the grip pin to rotate the rotor blade about the grip pin axis;
a blade fold actuator operably associated with the rotor blade to rotate the rotor blade about a blade fold axis; and
an inflatable air bag configured to act as a buffer for the rotor blade when in a folded position;
wherein the grip pin axis intersects the blade fold axis.
2. The foldable rotor system according to claim 1 , wherein the blade fold actuator is configured to fold the rotor blade about the blade fold axis while the rotor blade simultaneously rotates about the grip pin axis.
3. The foldable rotor system according to claim 1 , wherein the swashplate is operably associated with the grip pin through a pitch link.
4. The foldable rotor system according to claim 1 , wherein the blade fold actuator is located within the grip pin.
5. The foldable rotor system according to claim 1 , wherein the rotor assembly is part of a nacelle, the nacelle being configured to rotate the rotor assembly between a helicopter mode and an airplane mode.
6. The foldable rotor system according to claim 1 , further comprising:
a computer for controlling the blade fold actuator.
7. The foldable rotor system according to claim 1 , further comprising:
a driveshaft operably connected to the rotor assembly; and
a rotor brake configured to selectively stop the driveshaft from rotating before the rotor blade rotates about the blade fold axis.
8. The foldable rotor system according to claim 1 , further comprising:
a driveshaft operably connected to the rotor assembly; and
a clutch configured to selectively control transmission of torque to the driveshaft.
9. A method of spirally folding rotor blades on a rotorcraft during flight, comprising:
disengaging power from an engine to a driveshaft via a clutch;
halting the rotation of the driveshaft and the rotor blades;
changing the pitch of the rotor blades such that a leading edge of each rotor blade is substantially edgewise into an airstream;
folding each of the rotor blades about a blade fold axis towards a downstream direction, while selectively rotating each of the rotor blades about a grip pin axis, until the rotor blades lie substantially parallel to the direction of the airstream; and
inflating an inflatable air bag so as to provide pressure against the rotor blades;
wherein the grip pin axis intersects the blade fold axis.
10. The method according to claim 9 , further comprising:
locking the plurality of rotor blades in a folded position.
11. The method according to claim 9 , wherein the rotor blades remain substantially edgewise during a first part of the folding.
12. The method according to claim 9 , wherein a rate of the folding each of the rotor blades is substantially linear, while a rate of rotating each of the rotor blades about the grip pin axis increases until the rotor blades lie substantially parallel to the direction of the airstream.
13. An aircraft, comprising:
a wing member attached to a fuselage;
nacelles rotatably coupled to the wing member, each nacelle being rotatable between an airplane mode and a helicopter mode;
a rotor assembly operably associated with each nacelle, the rotor assembly comprising:
a swashplate;
a grip pin rotatable about a grip pin axis by the swashplate;
a rotor blades connected to each grip pin; and
a blade fold actuator operably connected to each rotor blade for rotating the rotor blade about a blade fold axis;
wherein the grip pin axis intersects the blade fold axis; and
wherein operation of the swashplate and the blade fold actuator enables each rotor blade to follow a spiral fold path such that each rotor blade remains substantially edgewise through the spiral fold path so as to minimize aerodynamic drag upon each rotor blade; and
an inflatable air bag on each nacelle so as to provide pressure against each rotor blade when each rotor blade is in a folded position.
14. The aircraft according to claim 13 , wherein the foldable rotor system further comprises:
a mechanical lock configured to lock each rotor blade when each rotor blade is in a folded position.
15. The foldable rotor system according to claim 1 , wherein:
the rotor assembly is rotatable about a rotor mast axis; and
the grip pin axis intersects the blade fold axis and the rotor mast axis.
16. A rotor assembly comprising:
a rotor blade connected to a grip pin that is rotatable about a grip pin axis;
a swashplate operably associated with the grip pin to rotate the rotor blade about the grip pin axis;
a blade fold actuator operably associated with the rotor blade to rotate the rotor blade about a blade fold axis into a folded position; and
an inflatable air bag configured to act as a buffer for the rotor blade when in the folded position.