Multi-bladed rotor system for rotorcraft
A rotor system for a rotorcraft includes a rotor having a plurality of pitch control links and a pair of rotor blades mechanically coupled with each of the plurality of pitch control links. A rotorcraft includes a power train, a mast extending from the power train, a rotor having a plurality of pitch control links, the rotor mechanically coupled with the mast, and a pair of rotor blades mechanically coupled with each of the plurality of pitch control links.
1. A rotor system for a rotorcraft, comprising:
a first pair of rotor blades, comprising:
a first rotor blade and a second rotor blade;
a first pitch control link operably associated with the first rotor blade;
a first coupling link coupled between the first rotor blade to the second rotor blade;
wherein actuation of the first pitch control link changes a first pitch setting associated with the first rotor blade and the second rotor blade;
a second pair of rotor blades, comprising:
a third rotor blade and a fourth rotor blade;
a second pitch control link operably associated with the third rotor blade;
a second coupling link coupled between the third rotor blade to the fourth rotor blade;
wherein actuation of the second pitch control link changes a second pitch setting associated with the third rotor blade and the fourth rotor blade;
wherein the first pitch setting is independently controlled by the first pitch control link, while the second pitch setting is independently controlled by the second pitch control link;
wherein the first, second, third, and fourth rotor blades are generally in the same plane.
2. The rotor system, according to claim 1 , further comprising:
a first pitch shaft mechanically coupled with the first pitch control link and the first rotor blade;
a second pitch shaft mechanically coupled with the second pitch control link and the third rotor blade.
3. The rotor system, according to claim 2 , wherein:
the first pitch shaft terminates in a lug at which the first rotor blade is attached; and
the second pitch shaft terminates in a lug at which the second rotor blade is attached.
4. The rotor system, according to claim 1 , wherein the first rotor blade is angularly spaced apart from the second rotor blade by an angle of about 20 degrees.
5. A rotorcraft, comprising:
a power train;
a mast extending from the power train;
a first pair of rotor blades, comprising:
a first rotor blade and a second rotor blade;
a first pitch control link operably associated with the first rotor blade;
a first coupling link coupled between the first rotor blade to the second rotor blade;
wherein actuation of the pitch control link changes a first pitch setting associated with the first rotor blade and the second rotor blade;
a second pair of rotor blades, comprising:
a third rotor blade and a fourth rotor blade;
a second pitch control link operably associated with the third rotor blade;
a second coupling link coupled between the third rotor blade to the fourth rotor blade;
wherein actuation of the second pitch control link changes a second pitch setting associated with the third rotor blade and the fourth rotor blade;
wherein the first pitch setting is independently controlled by the first pitch control link, while the second pitch setting is independently controlled by the second pitch control link;
wherein the first, second, third, and fourth rotor blades are generally in the same plane.
6. The rotorcraft, according to claim 5 , further comprising:
a first pitch shaft mechanically coupled with the first pitch control link and the first rotor blade;
a second pitch shaft mechanically coupled with the second pitch control link and the third rotor blade.
7. The rotorcraft, according to claim 6 , wherein:
the first pitch shaft terminates in a lug at which the first rotor blade is attached; and
the second pitch shaft terminates in a lug at which the second rotor blade is attached.
8. The rotorcraft, according to claim 5 , wherein the first rotor blade is angularly spaced apart from the second rotor blade by an angle of about 20 degrees.