An aircraft capable of vertical take-off and landing, stationary flight and forward flight, comprising: a closed wing, a fuselage at least partially disposed within a perimeter of the closed wing, and three or more spokes coupling the closed wing to the fuselage; and a distributed propulsion system, comprising: a plurality of variable displacement hydraulic motors (132, 26a-26f) disposed within or attached to the closed wing, fuselage or spokes in a distributed configuration; a constant pitch propeller (120, 28a-28f) proximate to a leading edge of the closed wing or the three or more spokes, and operably connected to each of the variable displacement hydraulic motors (132, 26a-26f) to provide lift whenever the aircraft is in vertical take-off and landing and stationary flight and thrust whenever the aircraft is in forward flight; a source of hydraulic power disposed within or attached to the closed wing, fuselage or spokes and coupled to each of the plurality of variable displacement hydraulic motors (132, 26a-26f), wherein the source of hydraulic power provides sufficient energy density for the aircraft to attain and maintain operations of the aircraft; a plurality of controllers (24a-24f), each controller (24a-24f) coupled to the source of hydraulic power, and to one of the variable displacement hydraulic motors (26a-26f) via a mechanical shaft (19a-19f) to independently control a speed and a torque of the variable displacement hydraulic motors (26a-26f) by changing a displacement of the variable displacement hydraulic motors (26a-26f); and one or more processors communicably coupled to each controller (24a-24f) that control an operation, the speed and the torque of the plurality of variable displacement hydraulic motors (26a-26f) via the controllers (24a-24f) such that a pitch, roll and yaw moment of the aircraft is controlled via differential and vectoring thrust without rotor cyclic and collective controls. a closed wing, a fuselage at least partially disposed within a perimeter of the closed wing, and three or more spokes coupling the closed wing to the fuselage; and a distributed propulsion system, comprising: a plurality of variable displacement hydraulic motors (132, 26a-26f) disposed within or attached to the closed wing, fuselage or spokes in a distributed configuration; a constant pitch propeller (120, 28a-28f) proximate to a leading edge of the closed wing or the three or more spokes, and operably connected to each of the variable displacement hydraulic motors (132, 26a-26f) to provide lift whenever the aircraft is in vertical take-off and landing and stationary flight and thrust whenever the aircraft is in forward flight; a source of hydraulic power disposed within or attached to the closed wing, fuselage or spokes and coupled to each of the plurality of variable displacement hydraulic motors (132, 26a-26f), wherein the source of hydraulic power provides sufficient energy density for the aircraft to attain and maintain operations of the aircraft; a plurality of controllers (24a-24f), each controller (24a-24f) coupled to the source of hydraulic power, and to one of the variable displacement hydraulic motors (26a-26f) via a mechanical shaft (19a-19f) to independently control a speed and a torque of the variable displacement hydraulic motors (26a-26f) by changing a displacement of the variable displacement hydraulic motors (26a-26f); and one or more processors communicably coupled to each controller (24a-24f) that control an operation, the speed and the torque of the plurality of variable displacement hydraulic motors (26a-26f) via the controllers (24a-24f) such that a pitch, roll and yaw moment of the aircraft is controlled via differential and vectoring thrust without rotor cyclic and collective controls. a plurality of variable displacement hydraulic motors (132, 26a-26f) disposed within or attached to the closed wing, fuselage or spokes in a distributed configuration; a constant pitch propeller (120, 28a-28f) proximate to a leading edge of the closed wing or the three or more spokes, and operably connected to each of the variable displacement hydraulic motors (132, 26a-26f) to provide lift whenever the aircraft is in vertical take-off and landing and stationary flight and thrust whenever the aircraft is in forward flight; a source of hydraulic power disposed within or attached to the closed wing, fuselage or spokes and coupled to each of the plurality of variable displacement hydraulic motors (132, 26a-26f), wherein the source of hydraulic power provides sufficient energy density for the aircraft to attain and maintain operations of the aircraft; a plurality of controllers (24a-24f), each controller (24a-24f) coupled to the source of hydraulic power, and to one of the variable displacement hydraulic motors (26a-26f) via a mechanical shaft (19a-19f) to independently control a speed and a torque of the variable displacement hydraulic motors (26a-26f) by changing a displacement of the variable displacement hydraulic motors (26a-26f); and one or more processors communicably coupled to each controller (24a-24f) that control an operation, the speed and the torque of the plurality of variable displacement hydraulic motors (26a-26f) via the controllers (24a-24f) such that a pitch, roll and yaw moment of the aircraft is controlled via differential and vectoring thrust without rotor cyclic and collective controls.