Drone comprising a supporting structure, at least three lift and propulsion rotors and a control system for providing at least one electrical energy supply of at least three electric motors which rotate said at least three rotors, respectively, about rotational axes arranged substantially vertically and allow a vertical thrust to be generated, said at least three rotors being longitudinally and transversely spaced from one another, said drone comprising: • a wing comprising two half-wings which are symmetrical with respect to an anteroposterior symmetry plane P of said drone and intended at least for increasing the lift of said drone, each of said two half-wings comprising at least one movable portion (31, 41, 51, 61, 71) suitable for moving relative to said supporting structure of said drone according to a first degree of rotational freedom about a first rotational axis R which is parallel to a longitudinal direction X of said drone, each movable portion (31, 41, 51, 61, 71) being suitable for moving between a folded position in which a free end (111, 121, 131) of each movable portion (31, 41, 51, 61, 71) forms a landing gear of said drone and an unfolded position in which each movable portion (31, 41, 51, 61, 71) increases the lift of said drone, said at least one movable portion (31, 41, 51, 61, 71) being suitable for moving relative to said supporting structure of said drone, according to a second degree of rotational freedom about a second rotational axis R' which is substantially parallel to a transverse direction Y of said drone, when said movable portion (31, 41, 51, 61, 71) of said two half-wings is in the unfolded position, • two first electric actuators (25, 26) for moving each movable portion (31, 41, 51, 61, 71) of each of said two half-wings, respectively, said control system providing at least one electrical energy supply of said two first electric actuators (25, 26), such that each actuator moves the movable portion (31, 41, 51, 61, 71) of said two half-wings between said folded position and said unfolded position and/or conversely between said unfolded position and said folded position, characterised in that each of said at least one movable portion (31, 41, 51, 61, 71) comprises: • a spar (36, 46, 56, 66, 76) having a proximal end (33, 43, 53, 63, 73) at which at least two first bearings (34, 44, 54, 64, 74) for forming a pivot connection to said supporting structure of said drone about said first rotational axis R are arranged, and a distal end (35, 45, 55, 65, 75) which is opposite said proximal end (33, 43, 53, 63, 73), • at least one profiled element (37, 47, 57, 67, 77) which aerodynamically covers said spar (36, 46, 56, 66, 76), • at least two second bearings (38, 48, 58, 68, 78) for aerodynamically forming a pivot connection between said spar (36, 46, 56, 66, 76) and said profiled element (37, 47, 57, 67, 77) about said second rotational axis R'. • a wing comprising two half-wings which are symmetrical with respect to an anteroposterior symmetry plane P of said drone and intended at least for increasing the lift of said drone, each of said two half-wings comprising at least one movable portion (31, 41, 51, 61, 71) suitable for moving relative to said supporting structure of said drone according to a first degree of rotational freedom about a first rotational axis R which is parallel to a longitudinal direction X of said drone, each movable portion (31, 41, 51, 61, 71) being suitable for moving between a folded position in which a free end (111, 121, 131) of each movable portion (31, 41, 51, 61, 71) forms a landing gear of said drone and an unfolded position in which each movable portion (31, 41, 51, 61, 71) increases the lift of said drone, said at least one movable portion (31, 41, 51, 61, 71) being suitable for moving relative to said supporting structure of said drone, according to a second degree of rotational freedom about a second rotational axis R' which is substantially parallel to a transverse direction Y of said drone, when said movable portion (31, 41, 51, 61, 71) of said two half-wings is in the unfolded position, • two first electric actuators (25, 26) for moving each movable portion (31, 41, 51, 61, 71) of each of said two half-wings, respectively, • a spar (36, 46, 56, 66, 76) having a proximal end (33, 43, 53, 63, 73) at which at least two first bearings (34, 44, 54, 64, 74) for forming a pivot connection to said supporting structure of said drone about said first rotational axis R are arranged, and a distal end (35, 45, 55, 65, 75) which is opposite said proximal end (33, 43, 53, 63, 73), • at least one profiled element (37, 47, 57, 67, 77) which aerodynamically covers said spar (36, 46, 56, 66, 76), • at least two second bearings (38, 48, 58, 68, 78) for aerodynamically forming a pivot connection between said spar (36, 46, 56, 66, 76) and said profiled element (37, 47, 57, 67, 77) about said second rotational axis R'.