NOVELTY - The unmanned high altitude aircraft such as a stratosphere aircraft comprises a fuselage (10), wings (13, 14), control surfaces (13", 14", 20', 20", 21', 21"), and a drive device (15, 16, 17) that has a drive machine and a propeller (15', 16' 17'). Each of the wings has tubes and wing spars that extend in a direction perpendicular to a longitudinal axis of the fuselage and are surrounded by a skin that forms a wing covering and defines a cross-sectional contour of the wing, where the cross-sectional contour forms a laminar profile that generates a high lift at low flow resistance.    USE - The unmanned high altitude aircraft such as a stratosphere aircraft is useful as a relay station for a wireless signal transmission to replace communications satellites or to complement it with additional broadband data connections.    ADVANTAGE - The unmanned high altitude aircraft can be easily produced at low cost in an efficient manner.    DETAILED DESCRIPTION - The unmanned high altitude aircraft such as a stratosphere aircraft comprises a fuselage (10), wings (13, 14), control surfaces (13", 14", 20', 20", 21', 21"), and a drive device (15, 16, 17) that has a drive machine and a propeller (15', 16' 17'). Each of the wings has tubes and wing spars that extend in a direction perpendicular to a longitudinal axis of the fuselage and are surrounded by a skin that forms a wing covering and defines a cross-sectional contour of the wing, where the cross-sectional contour forms a laminar profile that generates a high lift at low flow resistance. One of the wings is provided with: a winglet that extends transverse to the longitudinal axis of the wing on its free end, which faces away from the fuselage; and a drive nacelle for receiving the drive device. The winglet is provided with a movable control surface that enables an aerodynamic side force to be generated to bring the aircraft into an oblique bank position. A part of hoses in the wings is fillable with hydrogen and oxygen. A volume ratio of the oxygen-scavenging hoses to the hydrogen-scavenging hoses is 1:2. The skin of the wing covering: is transparent on an upper side of the wing; and consists of a high-strength aramid film vaporized with aluminum. The upper side of the wing is provided with solar cells, which are arranged between the transparent skin and the hoses. The fuselage is provided with a bracing tower that extends upwardly and downwardly from the fuselage. Clamping devices clamp the free end of the wing, the drive nacelles against the fuselage and/or the bracing tower. The wing spars consist of two-membered, lattice tubular structure from a carbon fiber composite material. The propeller in the form of a helicopter rotor is provided with flapping hinges. The drive device comprises a hydrogen-oxygen combustion engine, and an electromotor supplied by a fuel cell. The fuselage at its rear portion is provided with elevators, which are completely movable. The fuselage in its rear portion is provided with a rudder that is completely movable. A landing gear is provided and arranged at the bracing tower, a rear end of the fuselage and/or an elevator unit. The unmanned high altitude aircraft further comprises: an electric drive machine; a photovoltaic power supply device that is configured for creating a driving power and is provided with a photovoltaic solar generator, which converts a solar radiation energy into an electrical energy; a water electrolysis apparatus that is configured for creating hydrogen and oxygen from water and is operated at a constant ground pressure to prevent contamination of gases by the diffusion of hydrogen; a water storage container, which is connected with the water electrolysis apparatus over a first water conduit; a hydrogen supply reservoir that is formed by a first hose and is connected with the water electrolysis apparatus via a first hydrogen line; an oxygen supply reservoir that is formed by a second hose and connected with the water electrolysis apparatus via a first oxygen line; a fuel cell, which operates at the constant ground pressure in a closed circuit so that the contaminations of combustible gases are mixed by air carbon dioxide that is connected with the hydrogen supply reservoir via a second hydrogen line, is connected with the oxygen supply reservoir via an second oxygen line and is connected with the water storage container via a second water conduit; a control device, which is electrically connected with the solar generator, the water electrolysis apparatus and the fuel cell; and an electrical energy storage such as an accumulator. The solar generator comprises a carrier element that is provided with copper-indium-gallium-selenide thin-film solar cells and is formed by a polyimide film. The solar cells are thin layer solar cells such as cadmium-telluride cells. The control device is configured so that it supplies, during the presence of electrical energy produced by the solar radiation energy form the solar generator, an electrical load connection of the power supply device. The fuel cell is activated to provide the electrical energy to the load connection. A part of the electrical energy produced by the solar generator is supplied to the water electrolysis apparatus, during the presence of the electrical energy produced by the solar radiation energy. The water from the water storage container is supplied to the water electrolysis apparatus so that the water electrolysis apparatus is activated to produce the water from hydrogen and oxygen, where the water is stored in a hydrogen reservoir and an oxygen reservoir. The part of the electrical energy produced by the solar generator and/or the solar cell is supplied to the energy storage. The solar generator is arranged within the skin of the wings. The skin of the wing covering is weatherproof such as rainproof so that the aircraft enables to fly in tropopause and troposphere. INDEPENDENT CLAIMS are included for:    (1) an aircraft association; and    (2) a method for operating the aircraft association.    DESCRIPTION OF DRAWING(S) - The figure shows a schematic rear view of a high altitude aircraft.    Fuselage (10)    Wings (13, 14)    Control surfaces (13", 14", 20', 20", 21', 21")    Drive device (15, 16, 17)    Propeller. (15', 16' 17')