Patent ID: 11383830

Abstract:
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.