An aircraft having a vertical takeoff and landing fight mode and a forward flight mode, the aircraft comprising: an airframe including a plurality of stanchions, each of the stanchions including a flange and an interface panel with at least one power socket, at least one data or communication socket and at least one fluid socket; a versatile propulsion system attached to the airframe, the versatile propulsion system including a plurality of propulsion assemblies (26a, 26b, 26c, 26d), each propulsion assembly being one of a liquid fuel powered propulsion assembly or an electric powered propulsion assembly; and a flight control system operable to independently control each of the propulsion assemblies (26a, 26b, 26c, 26d); wherein, each of the propulsion assemblies includes a flange that matches the flanges of each of the stanchions such that the propulsion assemblies are interchangeably attachable to any one of the stanchions to create a mechanical connection therebetween, and an interface panel with at least one data or communication cable operable to couple with the at least one data or communication socket to establish data communication between the airframe and the propulsion assembly and at least one of: a power cable operable to couple with the at least one power socket to established electrical connections between airframe and propulsion assembly; and a fluid cable operable to couple with the at least one fluid socket to establish fluid communication between the airframe and the propulsion assembly, such that the aircraft is operable to transition between a liquid fuel flight mode and an electric flight mode; wherein, in the liquid fuel flight mode energy is provided to each of the propulsion assemblies from a liquid fuel; and wherein, in the electric flight mode energy is provided to each of the propulsion assemblies from an electric power source. an airframe including a plurality of stanchions, each of the stanchions including a flange and an interface panel with at least one power socket, at least one data or communication socket and at least one fluid socket; a versatile propulsion system attached to the airframe, the versatile propulsion system including a plurality of propulsion assemblies (26a, 26b, 26c, 26d), each propulsion assembly being one of a liquid fuel powered propulsion assembly or an electric powered propulsion assembly; and a flight control system operable to independently control each of the propulsion assemblies (26a, 26b, 26c, 26d); wherein, each of the propulsion assemblies includes a flange that matches the flanges of each of the stanchions such that the propulsion assemblies are interchangeably attachable to any one of the stanchions to create a mechanical connection therebetween, and an interface panel with at least one data or communication cable operable to couple with the at least one data or communication socket to establish data communication between the airframe and the propulsion assembly and at least one of: a power cable operable to couple with the at least one power socket to established electrical connections between airframe and propulsion assembly; and a fluid cable operable to couple with the at least one fluid socket to establish fluid communication between the airframe and the propulsion assembly, such that the aircraft is operable to transition between a liquid fuel flight mode and an electric flight mode; wherein, in the liquid fuel flight mode energy is provided to each of the propulsion assemblies from a liquid fuel; and wherein, in the electric flight mode energy is provided to each of the propulsion assemblies from an electric power source. a power cable operable to couple with the at least one power socket to established electrical connections between airframe and propulsion assembly; and a fluid cable operable to couple with the at least one fluid socket to establish fluid communication between the airframe and the propulsion assembly, such that the aircraft is operable to transition between a liquid fuel flight mode and an electric flight mode; wherein, in the liquid fuel flight mode energy is provided to each of the propulsion assemblies from a liquid fuel; and wherein, in the electric flight mode energy is provided to each of the propulsion assemblies from an electric power source.