An automated flying transport vehicle comprising: an elongated body having an outer surface having a top portion, a bottom portion, a first and second side portion and a front portion and back portion, wherein the outer surface further defines an inner cavity; a slotted opening disposed through the first and second side portions and positioned within the body near an upper portion of the body; a fixed wing disposed within the slotted opening and configured to generate lift during flight; a plurality of side rotors each having a rotor housing and wherein each is disposed along each of the first and second side portions near the bottom portion of the body such that the majority of the body is disposed above the plurality of rotors and wherein each of the plurality of side rotors are connected to an elongated side shaft having a proximal end and a distal end wherein the proximal end is connected to the body and the distal end is connected to the rotor housing and wherein each of the plurality of side rotors is connected to a power system wherein the power system is disposed within the inner cavity; a first rear rotor positioned at the rear of the body, the first rear rotor having a rotor housing disposed at a predetermined distance from the back portion of the body and connected to an elongated support shaft having a first end and a second end wherein the first end is connected to the body and the second end is connected to the rotor housing, wherein the first rear rotor is connected to the power system and wherein the first rear rotor has a rotational axis that is parallel to a longitudinal axis of the body; a controller system disposed within the inner cavity and in electronic communication with the plurality of side rotors and the first rear rotor and configured to coordinate a rotational moment of each of the rotors thereby producing a corresponding thrust such that the transport vehicle further comprises a vertical motion and a horizontal motion, wherein the vertical motion is controlled by a vertical thrust generated by at least the plurality of side rotors; and wherein the horizontal motion is controlled by a thrust generated from the first rear rotor and the coordinated rotation of the plurality of side rotors, wherein the fixed wing further generates a lift force during the horizontal motion, and wherein the rear rotor is configured to provide enough thrust in conjunction with the lift force generated by the fixed wing, once operational, such that the power of the side rotors is reduced or eliminated during horizontal motion. an elongated body having an outer surface having a top portion, a bottom portion, a first and second side portion and a front portion and back portion, wherein the outer surface further defines an inner cavity; a slotted opening disposed through the first and second side portions and positioned within the body near an upper portion of the body; a fixed wing disposed within the slotted opening and configured to generate lift during flight; a plurality of side rotors each having a rotor housing and wherein each is disposed along each of the first and second side portions near the bottom portion of the body such that the majority of the body is disposed above the plurality of rotors and wherein each of the plurality of side rotors are connected to an elongated side shaft having a proximal end and a distal end wherein the proximal end is connected to the body and the distal end is connected to the rotor housing and wherein each of the plurality of side rotors is connected to a power system wherein the power system is disposed within the inner cavity; a first rear rotor positioned at the rear of the body, the first rear rotor having a rotor housing disposed at a predetermined distance from the back portion of the body and connected to an elongated support shaft having a first end and a second end wherein the first end is connected to the body and the second end is connected to the rotor housing, wherein the first rear rotor is connected to the power system and wherein the first rear rotor has a rotational axis that is parallel to a longitudinal axis of the body; a controller system disposed within the inner cavity and in electronic communication with the plurality of side rotors and the first rear rotor and configured to coordinate a rotational moment of each of the rotors thereby producing a corresponding thrust such that the transport vehicle further comprises a vertical motion and a horizontal motion, wherein the vertical motion is controlled by a vertical thrust generated by at least the plurality of side rotors; and wherein the horizontal motion is controlled by a thrust generated from the first rear rotor and the coordinated rotation of the plurality of side rotors, wherein the fixed wing further generates a lift force during the horizontal motion, and wherein the rear rotor is configured to provide enough thrust in conjunction with the lift force generated by the fixed wing, once operational, such that the power of the side rotors is reduced or eliminated during horizontal motion.