Unmanned Aircraft, Control Method, Associated Platform and High-Altitude Turbine

Unmanned aircraft according to one or more of the preceding claims, wherein at least part of said aircraft is coated with and/or made of a material that is visible to the infrared and/or reflecting the infrared and/or visible for or reflecting wavelengths greater than 600 nm, more preferably 700 nm and/or is characterized by night visibility, and wherein in particular the retaining cable (18) has infrared visibility and/or infrared reflection properties and/or visibility or reflection of wavelengths greater than 600 nm, more preferably 700 nm and/or is characterized by night visibility.

Unmanned aircraft according to one or more of the preceding claims, comprising a first operating, take-off and/or landing configuration, and a second operating configuration of translated flight, wherein in said first operating configuration, the propellers (51) of each of the motors (50) have an axis of rotation inclined with respect to the vertical axis, although close to being vertical and/or the longitudinal axis of said aircraft is close to being vertical, said aircraft being configured to take off against the wind and/or the first operating configuration is an operating configuration of windward take-off and/or landing, wherein the axis of rotation of the propellers is facing the direction of origin of the wind.

Aircraft according to one or more of the preceding claims, wherein the interconnection supports (13, 14) comprise a first and a second interconnection support (13, 14), and wherein said first interconnection support and/or said second interconnection support (13;

• 14) are rigid supports, optionally substantially wing shaped, and integrate movable surfaces (13t, 14t) comprising ailerons or rudders or flaps and/or wherein said first or second wing (11, 12) integrate movable surfaces, wherein said movable surfaces (13t;
• 14t) are configured to modify the flow produced by said motors (50) when activated.

Unmanned aircraft according to one or more of the preceding claims, further comprising at least one tie rod or connecting element (41) for said aerodynamic container (40), said tie rod or connecting element (41) comprising a first portion, optionally a first end fixed to at least one between said first wing (11), said second wing (12), or an interconnection support (13, 14) and a second portion, distinct from said first portion and/or from said first end, optionally a second end opposite to said first end, fixed to said aerodynamic container.

Aircraft according to one or more of the preceding claims, wherein said aerodynamic container (40) comprises a fixed central motor (50c), and wherein the central motor (50c) and/or said plurality of motors (50) comprise a plurality of electric motors whose rotor is fixed to a propeller (51), and wherein said at least one first and one second wing profile are positioned behind said propeller (51) with respect to a direction of advancement of said aircraft and/or wherein said propeller (51) is located at the front with respect to the leading edge of said first wing (11) and/or of said second wing (12).

Aircraft according to one or more of the preceding claims, wherein said first wing (11) and/or said second wing (12) comprise a first wing portion and a second overlapping wing portion, in particular overlapping along a direction substantially orthogonal to a direction of advancement and/or comprising at least one intrados or an extrados and wherein the overlap occurs along the direction substantially identified by an ideal line joining the intrados or extrados of the first wing portion with the intrados or extrados of the second wing portion;

• said first wing (11) and/or said second wing (12) each comprising a plurality of dividing walls, optionally equally spaced, interposed between said first and said second wing.

Aircraft according to one or more of the preceding claims, characterized in that it is a vertical take-off aircraft, and in that it comprises at least a first operating movement configuration substantially in vertical and/or hovering direction, in particular at take-off and/or at landing, and at least a second operating configuration of translated flight, wherein in said first operating configuration said direction of advancement is substantially vertical, and wherein in said second operating configuration the direction of advancement is substantially and/or comprises a longitudinal component.

Aircraft according to one or more of the preceding claims, wherein said first interconnection support and/or said second interconnection support (13;

• 14) integrate movable surfaces (13t, 14t) comprising ailerons or rudders or flaps and/or wherein said first or second wing (11, 12) integrate movable surfaces, wherein said movable surfaces (13t;
• 14t) are configured to modify the flow produced by said motors (50) when activated.