Aircraft capable of hovering comprising: - a fuselage elongated along a longitudinal axis; - at least one rotor (3a, 3b, 4) that is rotatable about an axis of rotation with respect to said fuselage; - electrical drive means adapted to rotate said at least one rotor (3a, 3b, 4); - batteries adapted to power said electrical drive means; and - a cooling system of said batteries; said cooling system comprising: - a first opening adapted to allow air to enter; - a plurality of second openings adapted to allow air to escape; - a passage, which fluidly connects said first opening with at least some of said second openings; said batteries being placed within said passage and fluidically interposed between said first opening and at least some of said second openings; said cooling system further comprising at least one fan adapted to increase the kinetic energy of the air contained in said passage; said fan being operated, in use, when the forward speed (v) of said aircraft with respect to the ground is lower than a speed threshold value and/or when the temperature of said batteries exceeds a temperature threshold value; wherein it comprises at least one container (41, 42, 43) defining an inner volume, inside which a plurality of said batteries is contained; said batteries inside said inner volume defining a plurality of interstices between one another and said container (41, 42, 43); characterized in that said passage comprises: - a first duct, which extends starting from said first opening; - at least one second duct (31, 32, 33), which branches off from said first duct and fluidically connects said first duct to the inner volume of a respective said container (41, 42, 43); and - said interstices. - a fuselage elongated along a longitudinal axis; - at least one rotor (3a, 3b, 4) that is rotatable about an axis of rotation with respect to said fuselage; - electrical drive means adapted to rotate said at least one rotor (3a, 3b, 4); - batteries adapted to power said electrical drive means; and - a cooling system of said batteries; said cooling system comprising: - a first opening adapted to allow air to enter; - a plurality of second openings adapted to allow air to escape; - a passage, which fluidly connects said first opening with at least some of said second openings; - a first opening adapted to allow air to enter; - a plurality of second openings adapted to allow air to escape; - a passage, which fluidly connects said first opening with at least some of said second openings; said batteries being placed within said passage and fluidically interposed between said first opening and at least some of said second openings; said cooling system further comprising at least one fan adapted to increase the kinetic energy of the air contained in said passage; said fan being operated, in use, when the forward speed (v) of said aircraft with respect to the ground is lower than a speed threshold value and/or when the temperature of said batteries exceeds a temperature threshold value; wherein it comprises at least one container (41, 42, 43) defining an inner volume, inside which a plurality of said batteries is contained; said batteries inside said inner volume defining a plurality of interstices between one another and said container (41, 42, 43); characterized in that said passage comprises: - a first duct, which extends starting from said first opening; - at least one second duct (31, 32, 33), which branches off from said first duct and fluidically connects said first duct to the inner volume of a respective said container (41, 42, 43); and - said interstices. - a first duct, which extends starting from said first opening; - at least one second duct (31, 32, 33), which branches off from said first duct and fluidically connects said first duct to the inner volume of a respective said container (41, 42, 43); and - said interstices.