Vertical take-off and landing (VTOL) aircraft with rotor configurations tolerant to rotor failure
Vertical take-off and landing (VTOL) aircraft include a fuselage having a center of gravity (CG) and defining mutually orthogonal X-, Y- and Z-axes. An even number of positionally mirror imaged port and starboard side rotors are provided laterally of the fuselage in spaced relationship to a plane established by the XZ axes while an even number of fuselage rotors are positioned along an X-axis centerline of the fuselage. Improved stability during failure of an engine/motor/rotor is achieved by causing one-half of the side rotors to rotate in one direction about the Z-axis and a remaining one-half of the side rotors rotate in a counter direction relative thereto, while one-half of the fuselage rotors rotate in one direction about the Z-axis and a remaining one-half of the fuselage rotors rotated in a counter direction relative thereto.
1. A vertical take-off and landing (VTOL) aircraft comprising:
a fuselage which includes a cabin section, the fuselage having a center of gravity (CG) and defining mutually orthogonal X-, Y- and Z-axes passing through the CG, wherein the X-axis defines a longitudinal centerline roll axis of the fuselage, the Y-axis defines a pitch axis of the fuselage and the Z-axis defines a yaw axis of the fuselage;
rotorless port and starboard aerodynamic wings extending laterally outwardly from port and starboard sides of the fuselage, respectively;
port and starboard rotor pods positioned at terminal ends of the rotorless port and starboard aerodynamic wings, respectively, wherein the port and starboard rotor pods are respectively aligned with port and starboard lateral planes parallel to but spaced laterally from a central plane established by the XZ axes;
single port and starboard rotor columns each comprised of an even number of positionally mirror imaged ducted port and starboard side rotors positionally aligned within the port and starboard rotor pods such that the ducted port and starboard side rotors respectively forming each of the single port and starboard rotor columns is aligned with the respective port and starboard lateral planes so as to be parallel to but spaced laterally from the central plane established by the XZ axes;
an even number of fuselage rotors positioned along the longitudinal centerline roll axis of the fuselage aft of the fuselage CG, wherein a first one-half set of the fuselage rotors rotates in one direction about the Z-axis and a second one-half set of the fuselage rotors rotates in a direction about the Z-axis which is opposite to the first one-half set;
port and starboard propulsive rotors each providing thrust along the X-axis of the fuselage, wherein each of the port and starboard propulsive rotors are ducted and extend laterally outwardly from the fuselage at a position rearwardly midway between the even number of fuselage rotors aft the CG of the fuselage; and wherein
one-half of the side rotors rotate in one direction about an axis parallel to the Z-axis and a remaining one-half of the side rotors rotate in a counter direction relative thereto.
2. The VTOL aircraft according to claim 1 , further comprising ruddervators at an aft portion of the fuselage.
3. The VTOL aircraft according to claim 1 , wherein at least some of the even number of side rotors are positioned forward of the CG of the aircraft.