The present aircraft comprises a pair of spaced apart and parallelly disposed fuselages, a pair of wings, each wing is attached to an outer portion to each fuselage, a pyramid structure adapted to connect the pair of fuselages and an articulated propulsion system having a thrust axis, wherein the articulated propulsion system is pivotably attached to the pyramid structure and configured for angle of rotation of from about 0 degrees corresponding to the thrust axis disposed substantially parallel but at an offset to a longitudinal axis of the aircraft to about 90 degrees corresponding to the thrust axis disposed substantially at right angle to the longitudinal axis. The thrust axis substantially intersects the center of gravity when the thrust axis is disposed substantially at right angle to the longitudinal axis and the thruster is capable of angle of rotation of about 0 degrees or 90 degrees during take-off or landing.
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