A convertible aircraft (100) comprising a fuselage body (10) extending according to a main longitudinal direction (L) of development and including a receiving housing (50a, 50b, 50c, 50d); a propulsion unit, connected to the fuselage body (10) and comprising first motor means (20) configured to supply a thrust parallel (H) to said longitudinal direction (L), second motor means (30a, 30b, 30c, 30d) configured to supply a thrust orthogonal (V) to said longitudinal direction (L), which second motor means (30a, 30b, 30c, 30d) are movable between an extracted configuration and a retracted configuration, the aircraft further comprising a wing folding system comprising opposed wings (41, 42) projecting from the fuselage body (10), which opposed wings (41, 42) being configured to be folded so as to define opposite terminal portions (41a, 42a) each intended to support the aircraft (100) on a landing and/or taking-off region, wherein the receiving housing (50a, 50b, 50c, 50d) of the fuselage body (10) and the second motor means (30a, 30b, 30c, 30d) are configured so that the receiving housing entirely encloses the second motor means (30a, 30b, 30c, 30d) inside it in said retracted configuration.
HYBRID UNMANNED AERIAL VEHICLE
HYBRIDES UNBEMANNTES LUFTFAHRZEUG
VÉHICULE AÉRIEN SANS PILOTE HYBRIDE
2023-02-15
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |