Flight apparatus with vertical take-off and landing, of a biplane type, having two main distinct parts which are articulated between them, a first distinct part consisting of a cockpit hinged to the second distinct part which is a wings assembly comprising two wings (a,b) in a biplane configuration and upright central vertical supports joining the wings (a,b); the cockpit being attached to the wings assembly by two hinges fixed in the upright central vertical supports and configured to permitthe the cockpit to rotate with respect of the wings assembly about a transversal hinge axis while limiting the arc of rotation of the cockpit wherein the wings (a, b) are provided with four propellers each one driven by an electric engine , two of them being disposed on the upper wing (a) and two on the lower wing (b), the four propellers forming thus a quadcopter layout; wherein batteries transmit the electric energy to the engines through speed regulators; wherein the entire operation of the apparatus is managed by means of a flight computer ; wherein the taking-off is executed with the wings (a,b) and the engines vertically oriented; wherein the flight apparatus is adapted to be supported on the ground by means of a landing gear fixed in the wing extremities; wherein the flight apparatus taking off as a quadcopter and the transition to the cruise flight is made by reducing the angle of incidence of the wings (a,b), which angle of incidence decreases naturally due to the increasing wings drag, concurrently with the increasing of the translation speed of the flight apparatus, in the meantime, the cockpit remaining in a vertical position due to its lower center of gravity and due to the hinges ; and wherein the landing is executed similarly to a quadcopter, slowing down the speed in order to lead the increasing the angle of incidence of the wings (a, b) until they naturally return to the vertical position required for landing, characterized in that the cockpit rotates inside of the central vertical supports through an open area of the lower wing (b), each propeller has a first duct provided on the inlet lip with an annular ejection slit , the batteries are placed under the pilot's seat and the flight computer is disposed in the central part of the upper wing (a). wherein the wings (a, b) are provided with four propellers each one driven by an electric engine , two of them being disposed on the upper wing (a) and two on the lower wing (b), the four propellers forming thus a quadcopter layout; wherein batteries transmit the electric energy to the engines through speed regulators; wherein the entire operation of the apparatus is managed by means of a flight computer ; wherein the taking-off is executed with the wings (a,b) and the engines vertically oriented; wherein the flight apparatus is adapted to be supported on the ground by means of a landing gear fixed in the wing extremities; wherein the flight apparatus taking off as a quadcopter and the transition to the cruise flight is made by reducing the angle of incidence of the wings (a,b), which angle of incidence decreases naturally due to the increasing wings drag, concurrently with the increasing of the translation speed of the flight apparatus, in the meantime, the cockpit remaining in a vertical position due to its lower center of gravity and due to the hinges ; and wherein the landing is executed similarly to a quadcopter, slowing down the speed in order to lead the increasing the angle of incidence of the wings (a, b) until they naturally return to the vertical position required for landing, characterized in that the cockpit rotates inside of the central vertical supports through an open area of the lower wing (b), each propeller has a first duct provided on the inlet lip with an annular ejection slit , the batteries are placed under the pilot's seat and the flight computer is disposed in the central part of the upper wing (a). <EOS>