Abstract: The present invention relates to a vertical take-off and landing module (200) for a fixed-wing aircraft (110), which includes at least one vertically-acting propulsion unit (240), actuator means (245) and support means (230), so as to be adapted to be operatively connected to said aircraft (110). The actuator means (245) can move the propulsion unit (240) from the inside of the module (200) towards the outside, and vice versa, so that the propulsion unit (240) is adapted to generate a substantially vertical propulsive force during the aircraft take-off and landing phases.

Abstract: The present invention relates to a vertical take-off and landing module (200) for a fixed-wing aircraft (110), which includes at least one vertically-acting propulsion unit (240), actuator means (245) and support means (230), so as to be adapted to be operatively connected to said aircraft (110). The actuator means (245) can move the propulsion unit (240) from the inside of the module (200) towards the outside, and vice versa, so that the propulsion unit (240) is adapted to generate a substantially vertical propulsive force during the aircraft take-off and landing phases.

Abstract: A computer implemented method for estimating angles of attack and/or an angle of sideslip of a flying body includes the steps of: providing data or measurements representative of a time derivative of a module of a speed of the flying body with respect to an air; providing data or measurements representative of corresponding projections of coordinate accelerations on a Cartesian reference frame fixed to the flying body; and calculating the angles of attack and/or the sideslip on a basis of an mathematical relationship of the angles of attack and the sideslip with the coordinate accelerations and the time derivative of the module of the speed of the flying body with respect to the air.