An aircraft (10; 210; 310; 410; 510; 610) operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation, the aircraft (10; 210; 310; 410; 510; 610) comprising: an airframe (12; 212; 312; 412; 512; 612) having first (14; 214; 314; 414; 514; 614) and second (16; 216; 316; 416; 516; 616) wings in a staggerwing configuration with first (18; 218; 318; 418; 518; 618) and second (20; 220; 320; 420; 520; 620) swept pylons extending therebetween; a distributed thrust array attached to the airframe, the thrust array including a first plurality of propulsion assemblies (34a, 34b; 234a, 234b; 334a, 334b; 434a, 434b; 534a, 534b; 634a, 634b) coupled to the first wing (14; 214; 314; 414; 514; 614) and a second plurality of propulsion assemblies (34c, 34d; 234c, 234d; 334c, 334d; 434c, 434d; 534c, 534d; 634c, 634d) coupled to the second wing (16; 216; 316; 416; 516; 616), each of the propulsion assemblies (34a-d; 234a-d; 334a-d; 434a-d; 534a-d; 634a-d) including a tailboom (38a-d; 238a-d; 338a-d; 438a-d; 538a-d; 638a-d); a plurality of tail surfaces (40a, 40b; 240a, 240b; 340a, 340b; 440a, 440b; 540) each extending between the tailbooms (38a-d; 238a-d; 338a-d; 438a-d; 538a-d; 638a-d) of one of the propulsion assemblies of the first plurality of propulsion assemblies (34a, 34b; 234a, 234b; 334a, 334b; 434a, 434b; 534a, 534b; 634a, 634b) and one of the propulsion assemblies of the second plurality of propulsion assemblies (34c, 34d; 234c, 234d; 334c, 334d; 434c, 434d; 534c, 534d; 634c, 634d); and a flight control system coupled to the airframe (12; 212; 312; 412; 512; 612), the flight control system configured to independently control each of the propulsion assemblies (34a-d; 234a-d; 334a-d; 434a-d; 534a-d; 634a-d); wherein, the first plurality of propulsion assemblies (34a, 34b; 234a, 234b; 334a, 334b; 434a, 434b; 534a, 534b; 634a, 634b) is longitudinally offset relative to the second plurality of propulsion assemblies (34c, 34d; 234c, 234d; 334c, 334d; 434c, 434d; 534c, 534d; 634c, 634d) such that rotors of the first plurality of propulsion assemblies (34a, 34b; 234a, 234b; 334a, 334b; 434a, 434b; 534a, 534b; 634a, 634b) rotate in a different plane than rotors of the second plurality of propulsion assemblies (34c, 34d; 234c, 234d; 334c, 334d; 434c, 434d; 534c, 534d; 634c, 634d). an airframe (12; 212; 312; 412; 512; 612) having first (14; 214; 314; 414; 514; 614) and second (16; 216; 316; 416; 516; 616) wings in a staggerwing configuration with first (18; 218; 318; 418; 518; 618) and second (20; 220; 320; 420; 520; 620) swept pylons extending therebetween; a distributed thrust array attached to the airframe, the thrust array including a first plurality of propulsion assemblies (34a, 34b; 234a, 234b; 334a, 334b; 434a, 434b; 534a, 534b; 634a, 634b) coupled to the first wing (14; 214; 314; 414; 514; 614) and a second plurality of propulsion assemblies (34c, 34d; 234c, 234d; 334c, 334d; 434c, 434d; 534c, 534d; 634c, 634d) coupled to the second wing (16; 216; 316; 416; 516; 616), each of the propulsion assemblies (34a-d; 234a-d; 334a-d; 434a-d; 534a-d; 634a-d) including a tailboom (38a-d; 238a-d; 338a-d; 438a-d; 538a-d; 638a-d); a plurality of tail surfaces (40a, 40b; 240a, 240b; 340a, 340b; 440a, 440b; 540) each extending between the tailbooms (38a-d; 238a-d; 338a-d; 438a-d; 538a-d; 638a-d) of one of the propulsion assemblies of the first plurality of propulsion assemblies (34a, 34b; 234a, 234b; 334a, 334b; 434a, 434b; 534a, 534b; 634a, 634b) and one of the propulsion assemblies of the second plurality of propulsion assemblies (34c, 34d; 234c, 234d; 334c, 334d; 434c, 434d; 534c, 534d; 634c, 634d); and a flight control system coupled to the airframe (12; 212; 312; 412; 512; 612), the flight control system configured to independently control each of the propulsion assemblies (34a-d; 234a-d; 334a-d; 434a-d; 534a-d; 634a-d); wherein, the first plurality of propulsion assemblies (34a, 34b; 234a, 234b; 334a, 334b; 434a, 434b; 534a, 534b; 634a, 634b) is longitudinally offset relative to the second plurality of propulsion assemblies (34c, 34d; 234c, 234d; 334c, 334d; 434c, 434d; 534c, 534d; 634c, 634d) such that rotors of the first plurality of propulsion assemblies (34a, 34b; 234a, 234b; 334a, 334b; 434a, 434b; 534a, 534b; 634a, 634b) rotate in a different plane than rotors of the second plurality of propulsion assemblies (34c, 34d; 234c, 234d; 334c, 334d; 434c, 434d; 534c, 534d; 634c, 634d).