received by the International Bureau on 23 November 2020 (23.11.2020)

CLAIMS:

Although the subject matter has been described in language specific to structural features and/or methodological acts, it is to be understood that the subject matter defined in the appended claims is not necessarily limited to the specific features or acts described. Rather, the specific features and acts are disclosed as illustrative forms of implementing the claims. What is claimed is:

[Claim 1 ] A vertical take-off and landing aircraft including a fuselage, a flight computer, a control system, at least one pair of retractable wings (2,3) being retractable and extendable sideways with the axes of rotation of the retractable wings being virtually vertical, at least one actuator to extend and retract the wings, with said retractable wings being supported by at least one hinge (12,13) and said hinge being supported by the fuselage (1 ), characterized by including at least one wing having at least one trailing edge mounted control surface (TEMCS) (4,5) and at least one engine (14) being supported by a TEMCS (4,5) and being tilt-able together with said TEMCS thus creating vectored forces, said TEMCS (4,5) having rotational range of motion of at least 80 degrees to tilt said at least one engine fully upward in a virtually vertical position in order to create vertical lift for a hover mode and tilt said at least one engine forward in order to create thrust for a cruise mode and having bidirectional range of motion of at least 1 degree in both hover mode and cruise mode to create controlled vectored forces in both positions.

[Claim 2] The aircraft according to claim 1 wherein the type of actuator is one of hydraulic actuator, screw actuator, ball screw actuator and a rotary actuator. [Claim 3] The aircraft according to claim 1 wherein the retractable wings are one of rearward retracting and forward retracting wings.

[Claim 4] The aircraft according to claim 1 wherein the engine is one of electrically driven propeller, electrically driven ducted fan, motor driven ducted fan, jet engine, hydraulic motor driven propeller, hydraulic motor driven ducted fan, and an internal combustion engine driven propeller. [Claim 5] The aircraft according to claim 1 further comprising an onboard power generator.

[Claim 6] The aircraft according to claim 1 wherein at least one of said retractable wing hinges type is one of a pivot joint, a multi-linkage mechanism, a round rail, and a rising but hinge.

[Claim 7] The aircraft according to claim 1 wherein there is at least one uneven contact surface on the wing which at the end-stroke in one of the retracted or extended wing positions, said contact surface of the wing touches another matching uneven contact surface on one rigid body supported by the aircraft fuselage to create better support when said two uneven contact surfaces touch.

[Claim 8] The aircraft according to claim 1 wherein there is at least one mechanical link between a right retractable wing and a left retractable wing to guarantee synchronized extension and retraction of the wings.

[Claim 9] The aircraft according to claim 1 wherein the fuselage has a body lift design. [Claim 10] The aircraft according to claim 1 wherein at least one of the retractable wings and upward tilted engines may be used as a stairway for the pilot to reach the cockpit.

[Claim 1 1 ] The aircraft according to claim 1 wherein plurality of engines are supported by at least one TEMCS.

[Claim 12] The aircraft according to claim 1 wherein the hinge of at least one of said retractable wings is located one of below, above and at one side of the center line of the fuselage.

[Claim 13] The aircraft according to claim 1 further comprising at least one mechanical brake to lock at least one wing movement in at least one working position. [Claim 14] The aircraft according to claim 1 wherein at least one alighting element is connected to the trailing side of at least one of said tilt-able TEMCSs and rotates downward to a virtually vertical position toward the ground during take-off and landing as the engines tilt upward.

[Claim 15] An emergency landing means for a VTOL aircraft according to claim 1 including at least one wheel covered by an aerodynamic breakable cover which is broken upon touching ground in case of emergency landing during cruise mode allowing the covered wheel to revolve on ground.

[Claim 16] The emergency landing means of a VTOL according to claim 15 wherein the said breakable cover is designed to bear vertical loads thus being usable as landing gear for Vertical take-off and landing.

[Claim 17] The aircraft according to claim 1 wherein one pair of retractable wings are located closer to one end of the fuselage, said aircraft further comprising at least one pair of right and left tilt-able bodies located closer to the other end of the aircraft, each of said tilt-able bodies supporting at least one engine.

[Claim 18] The aircraft according to claim 17 further comprising at least one pair of right and left fixed airfoil shaped lift bodies extended from opposite sides of the fuselage wherein said tilt-able bodies of claim 17 are each a TEMCS of said lift bodies.

[Claim 19] A flight strategy for the aircraft according to claim 18 including:

The aircraft stability control in different hover modes is performed by the means of the thrust of individual engines and direction and amount of the vectored forces created by tilt-able engines and is performed by said flight computer while the direction of the flight and changes in flight modes is decided by one of a pilot and the flight computer as one of a fully autonomous and semi-autonomous operations;

during all the below mentioned hover modes, yaw is induced by at least one of mismatching the aerodynamic torque created by the engines, and by the moment created by vectored force of at least one tilting engine which the plane defining the locus of its tilting axis does not pass through the center of gravity of the aircraft;

The aircraft takes-off with the engines directed upward and said retractable wings retracted, the aircraft takes off similar to a conventional multi-rotor aircraft, with the additional flight dynamics control means of vectored forces created by tilt-able engines, flight direction is controlled in this mode by rolling the whole aircraft toward desired direction, and also by the means of tilting retracted wing engines by said engine supporting TEMCSs for transversal

25 flight direction control and tilting other said tilt-able engines for longitudinal flight direction control, as the aircraft reaches to a safe distance from the ground, wing extending transition phase is performed in the air while the flight computer continues to monitor the angle of the retractable wings, position of the engines and controls the lift created by each individual engine, when the wings become fully extended, the tilt-able engines vectored forces can only be effective in the longitudinal direction of the flight, forward flight is started by tilting at least one of the tilt-table engines forward while the flight computer maintains a positive angel of attack;

as the forward flight speed increases, the lift created by the wings also increases and allows further forward tilting of the engines, the flight computer continuously monitors the aerodynamic lift created by the wings and the lift and thrust created by the tilted engines and limits the tilt angle of the engines to guarantee the overall lift is enough to compensate weight, and continues this process until the engines become virtually parallel to the flight direction, and the aircraft enters a cruise mode;

as the aircraft reaches close to the destination, the speed is reduced while flight computer limits the minimum speed of the aircraft safely above the stall speed, transition to hover mode is performed preferably by the flight computer and starts by slightly tilting the engines upward by the means of said engine supporting TEMCSs, it increases the wings angle of attack and creates more lift both by the engines and wings which allows further reduction in the speed of the aircraft, the flight computer continues this process until the aircraft speed drops below stall speed and the aircraft weight is only carried by the vertical lift created by the engines which means the aircraft enters a hover mode with extended wings and control of the flight direction is done by rolling the whole aircraft in the desired direction and as the second means of direction control, longitudinal direction of flight is also controllable by tilting the tilt-able engines;

a reverse wing transition phase is performed by retracting the wings during which the flight computer performs a live time monitoring of the position of

26 the engines and controlling the aircraft stability by controlling the lift created by each engine individually and by the angle of tilt-able engines until the wings are retracted and the aircraft is ready to land;

landing is performed as the flight computer controls the aircraft direction of flight and stability by rolling the aircraft in desired direction similar to a conventional multi-rotor aircraft and also in both longitudinal and transversal directions by the means of tilt-able TEMCS supported engines.

[Claim 20] The aircraft according to claim 18 wherein a lift body located closer to the front of the aircraft and a lift body located closer to the rear of the aircraft are in different heights in order to avoid aerodynamic interference during cruise mode.

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