An aircraft (200, 300, 400) having a distributed propulsion system comprising: a fuselage (205, 305, 405); one or more support structures (210a-210c, 215, 310a-310c, 315, 410a-410c, 415) connected to the fuselage (205, 305, 405), the one or more support structures (210a-210c, 215, 310a-310c, 315, 410a-410c, 415) comprising a ring wing (215, 315, 415) and spokes (210a-210c, 310a-310c, 410a-410c); one or more engines or motors disposed within or attached to the one or more support structures (210a-210c, 215, 310a-310c, 315, 410a-410c, 415) or the fuselage (205, 305, 405); wherein the distributed propulsion system comprises two or more propellers (220a-220l, 320a-320l, 420a-420l), wherein the propellers (220a-220l, 320a-320l, 420a-420l) are symmetrically distributed in an array along the ring wing (215, 315, 415) with respect to a center of gravity of the aircraft and operably connected to the one or more engines or motors; wherein each propeller has a rotation direction (225a-2251, 325a-325l, 425a-4251) within a tilted plane of rotation (235a-235l, 335a-335l, 435a-435l) and a rotational axis (240a-240l, 340a-340l, 440a-440l); wherein the two or more propellers (220a-220l, 320a-320l, 420a-420l) are configured in pairs, each pair of propellers comprising a first propeller (220a-220f, 320a-320f, 420a-420f) creating a first thrust having a first horizontal force vector (230a-230f, 330a-330f, 430a-430f) and a second propeller (220g-220l, 320g-320l, 420g-420l) creating a second thrust having a second horizontal force vector (230g-230l, 330g-330l, 430g-430l), and wherein a summation of the first and second horizontal force vectors is substantially zero when the first thrust is substantially equal to the second thrust, wherein the rotational axes of the first and second propellers in each pair of propellers are substantially coplanar with respect to a vertical axis (245, 345, 445) disposed between the respective pair of propellers, and the vertical axis (245, 345, 445) extends through a center (250, 350) of the ring wing (215, 315, 415); and wherein a movement of the aircraft is controlled by selectively increasing or decreasing a thrust of at least one of the propellers. a fuselage (205, 305, 405); one or more support structures (210a-210c, 215, 310a-310c, 315, 410a-410c, 415) connected to the fuselage (205, 305, 405), the one or more support structures (210a-210c, 215, 310a-310c, 315, 410a-410c, 415) comprising a ring wing (215, 315, 415) and spokes (210a-210c, 310a-310c, 410a-410c); one or more engines or motors disposed within or attached to the one or more support structures (210a-210c, 215, 310a-310c, 315, 410a-410c, 415) or the fuselage (205, 305, 405); wherein the distributed propulsion system comprises two or more propellers (220a-220l, 320a-320l, 420a-420l), wherein the propellers (220a-220l, 320a-320l, 420a-420l) are symmetrically distributed in an array along the ring wing (215, 315, 415) with respect to a center of gravity of the aircraft and operably connected to the one or more engines or motors; wherein each propeller has a rotation direction (225a-2251, 325a-325l, 425a-4251) within a tilted plane of rotation (235a-235l, 335a-335l, 435a-435l) and a rotational axis (240a-240l, 340a-340l, 440a-440l); wherein the two or more propellers (220a-220l, 320a-320l, 420a-420l) are configured in pairs, each pair of propellers comprising a first propeller (220a-220f, 320a-320f, 420a-420f) creating a first thrust having a first horizontal force vector (230a-230f, 330a-330f, 430a-430f) and a second propeller (220g-220l, 320g-320l, 420g-420l) creating a second thrust having a second horizontal force vector (230g-230l, 330g-330l, 430g-430l), and wherein a summation of the first and second horizontal force vectors is substantially zero when the first thrust is substantially equal to the second thrust, wherein the rotational axes of the first and second propellers in each pair of propellers are substantially coplanar with respect to a vertical axis (245, 345, 445) disposed between the respective pair of propellers, and the vertical axis (245, 345, 445) extends through a center (250, 350) of the ring wing (215, 315, 415); and wherein a movement of the aircraft is controlled by selectively increasing or decreasing a thrust of at least one of the propellers.