Unmanned aerial vehicle with different flight modes

2:

• The unmanned aerial vehicle according to claim 1, wherein in the first flight mode the at least one wing on either side of the fuselage rotate independently from one another, around the at least one rotating shaft.

4:

• The unmanned aerial vehicle according to claim 1, wherein the at least one rotating shaft protruding from the fuselage has at least, one port rotating shaft, and one starboard rotating shaft, and said at least one port rotating shaft and said at least one starboard rotating shaft are independent from one another.

5:

• The unmanned aerial vehicle according to claim 4, wherein the at least one port rotating shaft and the at least one starboard rotating shaft are powered by:
• one actuator, or
• multiple independent actuators, wherein each independent actuator is associated with one rotating shaft.

6:

• The unmanned aerial vehicle according to claim 4, wherein the at least one port and the at least one starboard rotating shafts are arranged either co-aligned or non-aligned on either side of the fuselage, and are arranged on or proximal to the centre of gravity of the unmanned aerial vehicle.

7:

• The unmanned aerial vehicle according to claim 1, wherein the at least one rotating shafts are either co-aligned or non-aligned on either side of the fuselage, and are arranged on or proximal to the centre of gravity of the unmanned aerial vehicle.

8:

• The unmanned aerial vehicle according to claim 1, wherein said front and rear detachable components are assembled together by means of opposing rows of magnets arranged on opposite adjacent surfaces of the front and rear detachable components, wherein said opposing rows of magnets have opposing poles.

9:

• The unmanned aerial vehicle according to claim 1, wherein the rotor propellers on either side of the fuselage rotate independently from one another.

10:

• The unmanned aerial vehicle according to claim 1, wherein the rotor propellers rotate between 0° and 90° with regards to a plane defined by said predetermined position of each wing in the second flight mode.

11:

• The unmanned aerial vehicle according to claim 1, wherein the front detachable component defines a leading edge of each wing and the rear detachable component defines a trailing edge of each wing.

12:

• The unmanned aerial vehicle according to claim 11, wherein the detachable components are not proportional in size.

14:

• The unmanned aerial vehicle according to claim 9, wherein the rotor propellers rotate between 0° and 90° with regards to a plane defined by said predetermined position of each wing in the second flight mode.