LOW-NOISE ROTOR CONFIGURATIONS
In an embodiment, an aircraft includes a fuselage and a first support boom extending from the fuselage and having a first boom thickness. The aircraft also includes a first propulsion assembly coupled to the first support boom. The first propulsion assembly includes a first rotor hub and first rotor blades extending from the first rotor hub and operable to rotate in a first rotor plane with the first rotor hub. The aircraft also includes a first separation between the first rotor plane and the first support boom of not less than approximately 1.5 times the first boom thickness.
1 . An aircraft comprising:
a fuselage;
a first support boom extending from the fuselage;
a first propulsion assembly coupled to the first support boom, the first propulsion assembly comprising:
a first rotor hub;
first rotor blades extending from the first rotor hub and operable to rotate in a first rotor plane with the first rotor hub;
a second rotor hub;
second rotor blades extending from the second rotor hub and operable to rotate in a second rotor plane with the second rotor hub;
a first separation between the first rotor plane and the first support boom, the first separation having a first separation distance; and
a second separation between the first support boom and the second rotor plane, the second separation having a second separation distance, wherein the first separation distance and the second separation distance are unequal.
2 . The aircraft of claim 1 , wherein the second separation distance is greater than the first separation distance.
3 . The aircraft of claim 1 , wherein the first separation distance is not less than approximately 1.5 times a thickness of the first support boom.
4 . The aircraft of claim 1 , wherein the first separation distance is approximately 1.5 times a thickness of the first support boom.
5 . The aircraft of claim 1 , wherein the first separation distance is approximately 1.5 to 2.7 times a thickness of the first support boom.
6 . The aircraft of claim 5 , wherein the second separation distance is greater than the first separation distance.
7 . The aircraft of claim 1 , wherein the first separation distance is approximately 2 times a thickness of the first support boom.
8 . The aircraft of claim 1 , wherein the first separation distance is approximately 2.7 times a thickness of the first support boom.
9 . The aircraft of claim 1 , wherein the first rotor plane is substantially parallel to the second rotor plane.
10 . The aircraft of claim 1 , wherein the first support boom is coupled to the first propulsion assembly at a point between the first rotor hub and the second rotor hub.
11 . The aircraft of claim 1 , comprising:
a second support boom extending from the fuselage;
a second propulsion assembly coupled to the second support boom;
a third support boom extending from the fuselage;
a third propulsion assembly coupled to the third support boom;
a fourth support boom extending from the fuselage; and
a fourth propulsion assembly coupled to the fourth support boom.
12 . The aircraft of claim 1 , wherein the first rotor blades and the second rotor blades are operable to counterrotate.
13 . The aircraft of claim 1 , wherein the first rotor blades and the second rotor blades are operable to co-rotate.
14 . An aircraft comprising:
a fuselage;
a first support boom extending from the fuselage and having a first boom thickness;
a first propulsion assembly coupled to the first support boom, the first propulsion assembly comprising:
a first rotor hub; and
first rotor blades extending from the first rotor hub and operable to rotate in a first rotor plane with the first rotor hub; and
a first separation between the first rotor plane and the first support boom of not less than approximately 1.5 times the first boom thickness.
15 . The aircraft of claim 14 , wherein the first separation is approximately 1.5 times a thickness of the first support boom.
16 . The aircraft of claim 14 , wherein the first separation is approximately 1.5 to 2.7 times a thickness of the first support boom.
17 . The aircraft of claim 14 , wherein the first separation is approximately 2 times a thickness of the first support boom.
18 . The aircraft of claim 14 , wherein the first separation is approximately 2.7 times a thickness of the first support boom.
19 . The aircraft of claim 14 , comprising:
a second support boom extending from the fuselage and having a second boom thickness;
a second propulsion assembly coupled to the second support boom, the second propulsion assembly comprising:
a second rotor hub; and
second rotor blades extending from the second rotor hub and operable to rotate in a second rotor plane with the second rotor hub; and
a second separation between the second rotor plane and the second support boom of not less than approximately 1.5 times the second boom thickness.
20 . The aircraft of claim 19 , comprising:
a third support boom extending from the fuselage and having a third boom thickness;
a fourth support boom extending from the fuselage and having a fourth boom thickness;
a third propulsion assembly coupled to the third support boom, the third propulsion assembly comprising:
a third rotor hub; and
third rotor blades extending from the third rotor hub and operable to rotate in a third rotor plane with the third rotor hub; and
a fourth propulsion assembly coupled to the fourth support boom, the fourth propulsion assembly comprising:
a fourth rotor hub; and
fourth rotor blades extending from the fourth rotor hub and operable to rotate in a fourth rotor plane with the fourth rotor hub;
a third separation between the third rotor plane and the thiol support boom of not less than approximately 1.5 times the third boom thickness; and
a fourth separation between the fourth rotor plane and the fourth support boom of not less than approximately 1.5 times the fourth boom thickness.