A man portable aircraft system comprising: a first wing having first and second pylon stations(14a, 14b) and a plurality of nacelle stations (14c, 14d, 14e, 14f); a second wing having first and second pylon stations (16a, 16b) and a plurality of nacelle stations (16c, 16d, 16e, 16f); a first pylon couplable between the first pylon stations (14a, 16a) of the first and second wings (14, 16), the first pylon having a payload station; a second pylon couplable between the second pylon stations (14b, 16b) of the first and second wings (14, 16), the second pylon having a payload station, the wings (14, 16) and the pylons operable to form an airframe; a plurality of propulsion assemblies (24, 26) each couplable to one of the nacelle stations of the first and second wings (14, 16), the propulsion assemblies (24, 26) operable to form a two-dimensional distributed thrust array; a flight control system couplable to the airframe and operable to independently control each of the propulsion assemblies (24, 26), the airframe, the propulsion assemblies (24, 26) and the flight control system operable to form an aircraft; a payload couplable between the payload stations (18b, 20b) of the first and second pylons (18, 20); and a man portable container operable to receive the wings (14,16), the pylons (18, 20), the propulsion assemblies (24, 26), the flight control system and the payload in a disassembled configuration; wherein, each nacelle station (14c, 14d, 14e, 14f, 16c, 16d, 16e, 16f) includes a pair of upper mechanical connections (16g, 16h), a lower mechanical connection and a central mechanical connection including an electrical connection disposed therebetween; wherein, each propulsion assembly (24, 26) includes a pair of upper mechanical connections (24i, 24j), a lower mechanical connection and a central mechanical connection including an electrical connection disposed therebetween; wherein, a coupling is formed between each respective propulsion assembly and nacelle station by inserting the pair of upper mechanical connections (24i, 24j) of the propulsion assembly (24, 26) into the pair of upper mechanical connections (16g, 16h) of the nacelle station (14c, 14d, 14e, 14f, 16c, 16d, 16e, 16f) then rotating the propulsion assembly (24, 26) relative to the nacelle station (14c, 14d, 14e, 14f, 16c, 16d, 16e, 16f) which provides self locating for the central mechanical connections including the electrical connections (16j, 241) and the lower mechanical connections (16i, 24k) of the propulsion assembly (24, 26) and nacelle station (14c, 14d, 14e, 14f, 16c, 16d, 16e, 16f); and wherein, in an assembled configuration, the aircraft is operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. a first wing having first and second pylon stations(14a, 14b) and a plurality of nacelle stations (14c, 14d, 14e, 14f); a second wing having first and second pylon stations (16a, 16b) and a plurality of nacelle stations (16c, 16d, 16e, 16f); a first pylon couplable between the first pylon stations (14a, 16a) of the first and second wings (14, 16), the first pylon having a payload station; a second pylon couplable between the second pylon stations (14b, 16b) of the first and second wings (14, 16), the second pylon having a payload station, the wings (14, 16) and the pylons operable to form an airframe; a plurality of propulsion assemblies (24, 26) each couplable to one of the nacelle stations of the first and second wings (14, 16), the propulsion assemblies (24, 26) operable to form a two-dimensional distributed thrust array; a flight control system couplable to the airframe and operable to independently control each of the propulsion assemblies (24, 26), the airframe, the propulsion assemblies (24, 26) and the flight control system operable to form an aircraft; a payload couplable between the payload stations (18b, 20b) of the first and second pylons (18, 20); and a man portable container operable to receive the wings (14,16), the pylons (18, 20), the propulsion assemblies (24, 26), the flight control system and the payload in a disassembled configuration; wherein, each nacelle station (14c, 14d, 14e, 14f, 16c, 16d, 16e, 16f) includes a pair of upper mechanical connections (16g, 16h), a lower mechanical connection and a central mechanical connection including an electrical connection disposed therebetween; wherein, each propulsion assembly (24, 26) includes a pair of upper mechanical connections (24i, 24j), a lower mechanical connection and a central mechanical connection including an electrical connection disposed therebetween; wherein, a coupling is formed between each respective propulsion assembly and nacelle station by inserting the pair of upper mechanical connections (24i, 24j) of the propulsion assembly (24, 26) into the pair of upper mechanical connections (16g, 16h) of the nacelle station (14c, 14d, 14e, 14f, 16c, 16d, 16e, 16f) then rotating the propulsion assembly (24, 26) relative to the nacelle station (14c, 14d, 14e, 14f, 16c, 16d, 16e, 16f) which provides self locating for the central mechanical connections including the electrical connections (16j, 241) and the lower mechanical connections (16i, 24k) of the propulsion assembly (24, 26) and nacelle station (14c, 14d, 14e, 14f, 16c, 16d, 16e, 16f); and wherein, in an assembled configuration, the aircraft is operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation.