An aerial vehicle adapted for vertical take-off and horizontal flight, said aerial vehicle (200, 300) comprising: a main vehicle body (201, 301); one or more electric batteries; a right side wing (203, 303), said right side wing (203, 303) attached to a right side of said main vehicle body (201, 301), said right side wing (203, 303) comprising a plurality of right wing rotor assemblies (206, 306) attached to said right side wing (203, 303) by a deployment mechanism adapted to deploy said right wing rotor assemblies (206, 306) from a forward facing horizontal flight configuration to a vertical take-off configuration, each of said right wing rotor assemblies (206, 306) comprising a rotor and an electric motor, wherein the centers of mass of said right side wing rotor assemblies (206, 306) are forward of the leading edge of said right side wing 203, 303), and wherein said one or more right side wing rotor assemblies (206, 306) protrude forward of a leading edge of said right side wing (203, 303); a left side wing (202, 302), said left side wing (202, 302) attached to a left side of said main vehicle body, said left side wing (202, 302) comprising a plurality of left wing rotor assemblies (206, 306) attached to said second left side wing (202, 302) by a deployment mechanism adapted to deploy said rotor assemblies (206, 306) from a forward facing horizontal flight configuration to a vertical take-off configuration, each of said left wing rotor assemblies (206, 306) comprising a rotor and an electric motor, wherein the centers of mass of said left side wing rotor assemblies (206, 306) are forward of the leading edges of said left side wing (202, 302), and wherein said one or more left side wing rotor assemblies (206, 306) protrude forward of a leading edge of said left side wing (202, 302); wherein said right side wing (203, 303) and said left side wing (202, 302) are forward swept wings; one or more right side rear rotor assemblies (205, 305), said right side rear rotor assemblies (205, 305) attached to the rear of said vehicle body (201, 301) by a deployment mechanism adapted to deploy said right rear rotor assemblies (205, 305) from a forward facing horizontal flight configuration along the right side of said vehicle body (201, 301) to a vertical take-off configuration, said right rear rotor assemblies (205, 305) comprising an electric motor; and one or more left side rear rotor assemblies (205, 305), said left side rear rotor assemblies (205, 305) attached to the rear of said vehicle body (201, 301) by a deployment mechanism adapted to deploy said left rear rotor assemblies (205, 305) from a forward facing horizontal flight configuration along the left side of said vehicle body (201, 301) to a vertical take-off configuration, said left rear rotor assemblies (205, 305) comprising an electric motor. a main vehicle body (201, 301); one or more electric batteries; a right side wing (203, 303), said right side wing (203, 303) attached to a right side of said main vehicle body (201, 301), said right side wing (203, 303) comprising a plurality of right wing rotor assemblies (206, 306) attached to said right side wing (203, 303) by a deployment mechanism adapted to deploy said right wing rotor assemblies (206, 306) from a forward facing horizontal flight configuration to a vertical take-off configuration, each of said right wing rotor assemblies (206, 306) comprising a rotor and an electric motor, wherein the centers of mass of said right side wing rotor assemblies (206, 306) are forward of the leading edge of said right side wing 203, 303), and wherein said one or more right side wing rotor assemblies (206, 306) protrude forward of a leading edge of said right side wing (203, 303); a left side wing (202, 302), said left side wing (202, 302) attached to a left side of said main vehicle body, said left side wing (202, 302) comprising a plurality of left wing rotor assemblies (206, 306) attached to said second left side wing (202, 302) by a deployment mechanism adapted to deploy said rotor assemblies (206, 306) from a forward facing horizontal flight configuration to a vertical take-off configuration, each of said left wing rotor assemblies (206, 306) comprising a rotor and an electric motor, wherein the centers of mass of said left side wing rotor assemblies (206, 306) are forward of the leading edges of said left side wing (202, 302), and wherein said one or more left side wing rotor assemblies (206, 306) protrude forward of a leading edge of said left side wing (202, 302); wherein said right side wing (203, 303) and said left side wing (202, 302) are forward swept wings; one or more right side rear rotor assemblies (205, 305), said right side rear rotor assemblies (205, 305) attached to the rear of said vehicle body (201, 301) by a deployment mechanism adapted to deploy said right rear rotor assemblies (205, 305) from a forward facing horizontal flight configuration along the right side of said vehicle body (201, 301) to a vertical take-off configuration, said right rear rotor assemblies (205, 305) comprising an electric motor; and one or more left side rear rotor assemblies (205, 305), said left side rear rotor assemblies (205, 305) attached to the rear of said vehicle body (201, 301) by a deployment mechanism adapted to deploy said left rear rotor assemblies (205, 305) from a forward facing horizontal flight configuration along the left side of said vehicle body (201, 301) to a vertical take-off configuration, said left rear rotor assemblies (205, 305) comprising an electric motor.