Aircraft capable of hovering and method for transporting a load suspended from such aircraft

An aircraft (1) configured to be able to hover, the aircraft comprising:

• a fuselage (2);
• and
• a support element (55) adapted to support a load (51), made of elastically deformable material and constrained to said fuselage (2);
• said support element (55) being movable in at least one operating position in which it is arranged at least partially outside said fuselage (2) and supports said load (51);
• said support element (55) being a rope (55) comprising first ends (56, 57) opposite to each other and connected one (56) to a first connector (53) connected to said fuselage (2) and the other one (57) to a second connector (54) connected to said load (51), so as to maintain said load (51) at a fixed distance from said fuselage (2) when said rope (55) is arranged in the operating position;
• said aircraft (1) further comprising a sock (60) surrounding said support element (55), when said support element (55) is arranged, in use, in said operating position;
• characterized in that said sock (60) comprises, in turn, second ends (61, 62) opposite to each other and connected one (61) to said first connector (53) and the other one (62) to said second connector (54) independently of the respective said first ends (56, 57) of said support element (55);
• said sock (60) being configured to contain the elastic return of said support element (55), in case said support element (55) arranged, in use, in at least one said operating position is sheared off;
• said sock (60) having a first length greater than a second breaking length of said support element (55) in the presence of a load parallel to a first extension axis (C) of said support element (55) in said operating position, so that when said support element (55) in use breaks, said load (51) remains suspended form said sock (60) which is still, in use, loose and intact;
• said second breaking length being the maximum breaking length reached, in use, by said support element (55) under the action of said load (51);
• wherein said sock (60) has a preferential breaking section at one of its ends (61) arranged on the side of said fuselage (2) and opposite to said load (51).