Aircraft with asymmetric rotors
In an embodiment, an aircraft includes an airframe and a first propulsion assembly coupled to the airframe. The first propulsion assembly includes a first rotor hub and a first plurality of rotor blades non-uniformly spaced about the first rotor hub and operable to rotate in a rotor plane with the first rotor hub. The aircraft also includes a second propulsion assembly coupled to the airframe. The second propulsion assembly includes a second rotor hub and a second plurality of rotor blades non-uniformly spaced about the second rotor hub and operable to rotate in a rotor plane with the second rotor hub.
1. An aircraft comprising:
an airframe having a plurality of wings and a plurality of vertical supports;
a removable pod positioned between the plurality of wings and the plurality of vertical supports;
vertical supports;
a first propulsion assembly coupled to the airframe, the first propulsion assembly comprising:
a first rotor hub; and
a first plurality of rotor blades non-uniformly spaced about the first rotor hub and operable to rotate in a rotor plane with the first rotor hub; and
a second propulsion assembly coupled to the airframe, the second propulsion assembly comprising:
a second rotor hub; and
a second plurality of rotor blades non-uniformly spaced about the second rotor hub and operable to rotate in a rotor plane with the second rotor hub;
wherein the non-uniform spacing of the first plurality of rotor blades about the first rotor hub and the non-uniform spacing of the second plurality of rotor blades about the second rotor hub are different from one another.
2. The aircraft of claim 1 , wherein the first plurality of rotor blades comprise:
a first rotor blade;
a second rotor blade that forms a first angle with the first rotor blade relative to the first rotor hub;
a third rotor blade that forms a second angle with the second rotor blade relative to the first rotor hub; and
a fourth rotor blade that forms a third angle with the third rotor blade relative to the first rotor hub and a fourth angle with the first rotor blade relative to the first rotor hub.
3. The aircraft of claim 2 , wherein the second angle is greater than the first angle.
4. The aircraft of claim 2 , wherein a sum of the first angle and the second angle equals approximately 180 degrees.
5. The aircraft of claim 2 , wherein:
the first angle and the third angle are approximately equal; and
the second angle and the fourth angle are approximately equal.
6. The aircraft of claim 2 , wherein:
the first angle is between approximately 55 degrees and approximately 70 degrees; and
the second angle is between approximately 110 degrees and approximately 125 degrees.
7. The aircraft of claim 2 , wherein the first angle is approximately 70 degrees and the second angle is approximately 110 degrees.
8. The aircraft of claim 1 , wherein the rotor plane of the first plurality of rotor blades and the rotor plane of the second plurality of rotor blades are different.
9. The aircraft of claim 1 , comprising:
a third propulsion assembly coupled to the airframe, the third propulsion assembly comprising:
a third rotor hub; and
a third plurality of rotor blades non-uniformly spaced about the third rotor hub and operable to rotate in a rotor plane with the third rotor hub; and
a fourth propulsion assembly coupled to the airframe, the fourth propulsion assembly comprising:
a fourth rotor hub; and
a fourth plurality of rotor blades non-uniformly spaced about the second rotor hub and operable to rotate in a rotor plane with the second rotor hub.
10. The aircraft of claim 1 , wherein the first plurality of rotor blades are arranged about the first rotor hub in a scissors configuration.