An unmanned aerial vehicle, UAV, comprising: - a fuselage, - at least one rotating shaft protruding from both sides of said fuselage, - at least one wing on either side of the fuselage positioned on said rotating shaft, and - at least one rotor propeller, comprising one or more rotor blades and a housing arranged on said rotating shaft on either side of said fuselage, wherein the UAV is configured to shift between: a first flight mode using rotatable wings in which each wing is arranged so as to rotate freely around the at least one rotating shaft, and the wing is oriented due to a direction and strength of crossover wind impinging against a surface area of the wing as well as a downstream flow generated by the rotor propeller arranged in hover mode and a second flight mode using fixed wings in which each wing remains in a predetermined fixed position by means of a wing-locking mechanism, and the rotor propeller facing forward, characterised in that the wings are each made up of front and rear detachable components (3a, 3b) mounted around said at least one rotating shaft, wherein said assembled wings include a cut-out portion allowing each rotor propeller housing to rotate freely in conjunction with the rotation of the at least one rotating shaft between said first and second flight modes. - a fuselage, - at least one rotating shaft protruding from both sides of said fuselage, - at least one wing on either side of the fuselage positioned on said rotating shaft, and - at least one rotor propeller, comprising one or more rotor blades and a housing arranged on said rotating shaft on either side of said fuselage, wherein the UAV is configured to shift between: a first flight mode using rotatable wings in which each wing is arranged so as to rotate freely around the at least one rotating shaft, and the wing is oriented due to a direction and strength of crossover wind impinging against a surface area of the wing as well as a downstream flow generated by the rotor propeller arranged in hover mode and a second flight mode using fixed wings in which each wing remains in a predetermined fixed position by means of a wing-locking mechanism, and the rotor propeller facing forward, characterised in that the wings are each made up of front and rear detachable components (3a, 3b) mounted around said at least one rotating shaft, wherein said assembled wings include a cut-out portion allowing each rotor propeller housing to rotate freely in conjunction with the rotation of the at least one rotating shaft between said first and second flight modes. a first flight mode using rotatable wings in which each wing is arranged so as to rotate freely around the at least one rotating shaft, and the wing is oriented due to a direction and strength of crossover wind impinging against a surface area of the wing as well as a downstream flow generated by the rotor propeller arranged in hover mode and a second flight mode using fixed wings in which each wing remains in a predetermined fixed position by means of a wing-locking mechanism, and the rotor propeller facing forward, characterised in that the wings are each made up of front and rear detachable components (3a, 3b) mounted around said at least one rotating shaft, wherein said assembled wings include a cut-out portion allowing each rotor propeller housing to rotate freely in conjunction with the rotation of the at least one rotating shaft between said first and second flight modes.