Aircraft capable of hovering and relative control method

Aircraft (1) capable of hovering comprising:

• a fuselage (2) elongated along a longitudinal axis (Y);
• at least one rotor (3a, 3b, 4) that is rotatable about an axis of rotation with respect to said fuselage (2);
• electrical drive means adapted to rotate said at least one rotor (3a, 3b, 4);
• batteries (9) adapted to power said electrical drive means;
• and
• a cooling system (10) of said batteries (9);
• said cooling system (10) comprising:
• a first opening (20) adapted to allow air to enter;
• a plurality of second openings (21) adapted to allow air to escape;
• a passage (22), which fluidly connects said first opening (20) with at least some of said second openings (21);
• said batteries (9) being placed within said passage (22) and fluidically interposed between said first opening (20) and at least some of said second openings (21);
• said cooling system (10) further comprising at least one fan (23) adapted to increase the kinetic energy of the air contained in said passage (22);
• said fan (23) being operated, in use, when the forward speed (v) of said aircraft (1) with respect to the ground is lower than a speed threshold value (v0) and/or when the temperature (T) of said batteries (9) exceeds a temperature threshold value (T0);
• wherein it comprises at least one container (41, 42, 43) defining an inner volume (50), inside which a plurality of said batteries (9) is contained;
• said batteries (9) inside said inner volume (50) defining a plurality of interstices (45) between one another and said container (41, 42, 43);
• characterized in that said passage (22) comprises at least one duct (30), which fluidly connects said first opening (20) to said at least one container (41, 42, 43);
• said passage (22) further comprising at least one auxiliary duct (34, 35);
• each said auxiliary duct (34, 35) comprising a first end (34a, 35a) and a second end (34b, 35b) that are opposite to each other;
• said first and second end (34a, 35a;
• 34b, 35b) being both directly facing said duct (30);
• each said fan (23) being arranged at a respective auxiliary duct (34, 35).

Method for controlling an aircraft (1) capable of hovering;

• said aircraft comprising:
• a fuselage (2) elongated along a longitudinal axis (Y);
• at least one rotor (3a, 3b, 4) that is rotatable about an axis of rotation with respect to said fuselage (2);
• electrical drive means adapted to rotate said at least one rotor (3a, 3b, 4);
• batteries (9) adapted to power said electrical drive means;
• and
• a cooling system (10) of said batteries (9);
• said cooling system (10) comprising:
• a first opening (20) adapted to allow air to enter;
• a plurality of second openings (21) adapted to allow air to escape;
• a passage (22), which places said first opening (20) in fluidic communication with at least some of said second openings (21);
• said batteries (9) being placed within said passage (22) and fluidically interposed between said first opening (20) and at least some of said second openings (21);
• said cooling system (10) further comprising at least one fan (23) adapted to increase the kinetic energy of the air contained in said passage (22);
• said aircraft (1) further comprising at least one container (41, 42, 43) defining an inner volume (50), inside which a plurality of said batteries (9) is contained;
• said batteries (9) inside said inner volume (50) defining a plurality of interstices (45) between one another and said container (41, 42, 43);
• said passage (22) comprising:
• a first duct (30), which extends starting from said first opening (20);
• at least one second duct (31, 32, 33), which branches off from said first duct (30) and fluidically connects said first duct (30) to the inner volume (50) of a respective said container (41, 42, 43);
• and
• said interstices (45);
• said method being characterized in that it comprises the step of operating said fan (23) when the forward speed (v) of said aircraft (1) with respect to the ground is lower than a speed threshold value (v0) and/or when the temperature (T) of said batteries (9) exceeds a temperature threshold value (T0).

Method for controlling an aircraft (1) capable of hovering;

• said aircraft comprising:
• a fuselage (2) elongated along a longitudinal axis (Y);
• at least one rotor (3a, 3b, 4) that is rotatable about an axis of rotation with respect to said fuselage (2);
• electrical drive means adapted to rotate said at least one rotor (3a, 3b, 4);
• batteries (9) adapted to power said electrical drive means;
• and
• a cooling system (10) of said batteries (9);
• said cooling system (10) comprising:
• a first opening (20) adapted to allow air to enter;
• a plurality of second openings (21) adapted to allow air to escape;
• a passage (22), which places said first opening (20) in fluidic communication with at least some of said second openings (21);
• said batteries (9) being placed within said passage (22) and fluidically interposed between said first opening (20) and at least some of said second openings (21);
• said cooling system (10) further comprising at least one fan (23) adapted to increase the kinetic energy of the air contained in said passage (22);
• said aircraft (1) further comprising at least one container (41, 42, 43) defining an inner volume (50), inside which a plurality of said batteries (9) is contained;
• said batteries (9) inside said inner volume (50) defining a plurality of interstices (45) between one another and said container (41, 42, 43);
• said passage (22) comprising at least one duct (30), which fluidly connects said first opening (20) to said at least one container (41, 42, 43);
• said passage (22) further comprises at least one auxiliary duct (34, 35);
• each said auxiliary duct (34, 35) comprising a first end (34a, 35a) and a second end (34b, 35b) that are opposite to each other;
• said first and second end (34a, 35a;
• 34b, 35b) being both directly facing said duct (30);
• each said fan (23) being arranged at a respective auxiliary duct (34, 35);
• said method being characterized in that it comprises the step i) of operating said fan (23) when the forward speed (v) of said aircraft (1) with respect to the ground is lower than a speed threshold value (v0) and/or when the temperature (T) of said batteries (9) exceeds a temperature threshold value (T0).