An aircraft (10) operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft (10) includes an airframe (12) having first (14) and second (16) wings in a staggerwing configuration with first and second swept pylons (18, 20) extending therebetween. A distributed thrust array is attached to the airframe (12). The thrust array includes a first plurality of propulsion assemblies (34a, 34b) coupled to the first wing (14) and a second plurality of propulsion assemblies (34c, 34d) coupled to the second wing (16). A flight control system (30) is coupled to the airframe (12) and is configured to independently control each of the propulsion assemblies (34a, 34b, 34c, 34d). The first plurality of propulsion assemblies (34a, 34b) is longitudinally offset relative to the second plurality of propulsion assemblies (34c, 34d) such that rotors of the first plurality of propulsion assemblies (34a, 34b) rotate in a different plane than rotors of the second plurality of propulsion assemblies (34c, 34d).
CONVERTIBLE STAGGERWING AIRCRAFT HAVING OPTIMIZED HOVER POWER
SENKRECHTSTARTENDES UND -LANDENDES FLUGZEUG MIT GESTAFFELTEN FLÜGELN UND OPTIMIERTER SCHWEBELEISTUNG
AÉRONEF CONVERTIBLE À AILES DÉCALÉES PRÉSENTANT UNE PUISSANCE DE VOL STATIONNAIRE OPTIMISÉE
2023-08-09
Patent
Electronic Resource
English
Convertible Staggerwing Aircraft having Optimized Hover Power
European Patent Office | 2023
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