An aerial vehicle (200, 300) adapted for vertical take-off and horizontal flight, said aerial vehicle (200, 300) comprising: a main vehicle body (201, 301); a right side wing (203, 303), said right said wing (203, 303) attached to a right side of said main vehicle body (201, 301), said right side wing (203, 303) comprising a forward swept wing, one or more right side wing rotor assemblies (206, 306), wherein one or more right side wing rotor assemblies (206, 306) are attached to said right side wing (203, 303), and wherein said one or more right side wing rotor assemblies (206, 306) protrude forward of the leading edge of said right side wing (203, 303), 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), wherein said right side wing rotor assemblies (206, 306) are attached to said right wing (203, 303) by a deployment mechanism adapted to deploy said right side wing rotor assemblies from a forward facing horizontal flight configuration to a vertical take-off configuration; and a left side wing (202, 302), said left said wing (202, 302) attached to a left side of said main vehicle body (201, 301), said left side wing comprising a forward swept wing; one or more left side wing rotor assemblies (206, 306), wherein one or more left side wing rotor assemblies (206, 306) are attached to said left side wing (202, 302), and wherein said one or more left side wing rotor assemblies (206, 306) protrude forward of the leading edge of said left side wing (202, 302), 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), wherein said left side wing rotor assemblies (206, 306) are attached to said left wing (202, 302) by a deployment mechanism adapted to deploy said left wing rotor assemblies (206, 306) from a forward facing horizontal flight configuration to a vertical take-off configuration and said right and left side wing (203, 303; 202, 302) further comprising each a wing tip rotor unit adapted to rotate relative to the wing (302, 303) from a forward flight configuration to a VTOL configuration, wherein said wing tip rotor units comprising each a nacelle, and the wing tip rotor units are adapted to rotate relative to the wing such that the nacelle maintains its shape whether in a VTOL or a forward flight configuration, and wherein the wing tip rotor unit comprises a set of VTOL blades used for VTOL and transition modes, and further comprises a set of forward flight blades used for forward flight, with the VTOL blades stowed and nested. a main vehicle body (201, 301); a right side wing (203, 303), said right said wing (203, 303) attached to a right side of said main vehicle body (201, 301), said right side wing (203, 303) comprising a forward swept wing, one or more right side wing rotor assemblies (206, 306), wherein one or more right side wing rotor assemblies (206, 306) are attached to said right side wing (203, 303), and wherein said one or more right side wing rotor assemblies (206, 306) protrude forward of the leading edge of said right side wing (203, 303), 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), wherein said right side wing rotor assemblies (206, 306) are attached to said right wing (203, 303) by a deployment mechanism adapted to deploy said right side wing rotor assemblies from a forward facing horizontal flight configuration to a vertical take-off configuration; and a left side wing (202, 302), said left said wing (202, 302) attached to a left side of said main vehicle body (201, 301), said left side wing comprising a forward swept wing; one or more left side wing rotor assemblies (206, 306), wherein one or more left side wing rotor assemblies (206, 306) are attached to said left side wing (202, 302), and wherein said one or more left side wing rotor assemblies (206, 306) protrude forward of the leading edge of said left side wing (202, 302), 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), wherein said left side wing rotor assemblies (206, 306) are attached to said left wing (202, 302) by a deployment mechanism adapted to deploy said left wing rotor assemblies (206, 306) from a forward facing horizontal flight configuration to a vertical take-off configuration and said right and left side wing (203, 303; 202, 302) further comprising each a wing tip rotor unit adapted to rotate relative to the wing (302, 303) from a forward flight configuration to a VTOL configuration, wherein said wing tip rotor units comprising each a nacelle, and the wing tip rotor units are adapted to rotate relative to the wing such that the nacelle maintains its shape whether in a VTOL or a forward flight configuration, and wherein the wing tip rotor unit comprises a set of VTOL blades used for VTOL and transition modes, and further comprises a set of forward flight blades used for forward flight, with the VTOL blades stowed and nested.