A vertical take-off and landing (VTOL) aircraft , wherein the aircraft comprises: an airframe having at least one or at least a pair of wing/s extending along a transverse axis, the wing/s being operatively attached to a fuselage having leading and trailing ends (14.1, 14.2) extending between a longitudinal axis (A) of the aircraft , and a suitable empennage located adjacent the trailing end (14.2) of the fuselage or a suitable canard located adjacent the leading end (14.1) of the fuselage ; an array of electric rotors mounted to the airframe operatively to provide stability and/or vertical lift to the aircraft , wherein the electric rotors are fixedly mounted to the airframe and are driven by one or more suitable electric motor/s; a front rotor pivotably mounted to the leading end (14.1) of the fuselage , wherein the front rotor is displaceable about an axis parallel to the transverse axis between a lift position in which the front rotor is oriented to provide vertical lift to the aircraft for vertical flight, and a propulsion position in which the front rotor is oriented to provide forward thrust to the aircraft for horizontal flight; and a rear rotor pivotably mounted to the trailing end (14.2) of the fuselage , wherein the rear rotor is displaceable about an axis parallel to the transverse axis between a lift position in which the rear rotor is oriented to provide vertical lift to the aircraft for vertical flight, and a propulsion position in which the rear rotor is oriented to provide forward thrust to the aircraft for horizontal flight, wherein one or both of the front and rear rotors are driven by one or more suitable internal combustion engine/s, and wherein the front and rear rotors provide a majority, or all, of the vertical lift to the aircraft during vertical flight with the front and rear rotors in the lift position. an airframe having at least one or at least a pair of wing/s extending along a transverse axis, the wing/s being operatively attached to a fuselage having leading and trailing ends (14.1, 14.2) extending between a longitudinal axis (A) of the aircraft , and a suitable empennage located adjacent the trailing end (14.2) of the fuselage or a suitable canard located adjacent the leading end (14.1) of the fuselage ; an array of electric rotors mounted to the airframe operatively to provide stability and/or vertical lift to the aircraft , wherein the electric rotors are fixedly mounted to the airframe and are driven by one or more suitable electric motor/s; a front rotor pivotably mounted to the leading end (14.1) of the fuselage , wherein the front rotor is displaceable about an axis parallel to the transverse axis between a lift position in which the front rotor is oriented to provide vertical lift to the aircraft for vertical flight, and a propulsion position in which the front rotor is oriented to provide forward thrust to the aircraft for horizontal flight; and a rear rotor pivotably mounted to the trailing end (14.2) of the fuselage , wherein the rear rotor is displaceable about an axis parallel to the transverse axis between a lift position in which the rear rotor is oriented to provide vertical lift to the aircraft for vertical flight, and a propulsion position in which the rear rotor is oriented to provide forward thrust to the aircraft for horizontal flight, wherein one or both of the front and rear rotors are driven by one or more suitable internal combustion engine/s, and wherein the front and rear rotors provide a majority, or all, of the vertical lift to the aircraft during vertical flight with the front and rear rotors in the lift position. <EOS>