Propeller for an aircraft

1. A propeller for an aircraft, wherein the propeller comprises at least two blades, arranged about a central hub, the central hub being coupled to at least one motor, driven by a power source,

wherein at least one blade of the at least two blades is attached to at least one sleeve member, configured for being in an outer sliding connection to a first cylindrical element of the hub,

wherein an inner surface of each of said at least one sleeve member comprises at least one projecting element, configured to be in a sliding connection with a corresponding at least one first recessed guide path, arranged in an outer surface of the first cylindrical element,

wherein each of said at least one first recessed guide path circles at least partly around the first cylindrical element from a first position to a second position,

wherein each of said at least one sleeve member positions its blade in an operational position when its at least one projecting element is positioned in its corresponding first position in its designated first recessed guide path of the first cylindrical element,

wherein each of said at least one sleeve member positions its blade in a storage position when its at least one projecting element is positioned in its corresponding second position in its designated first recessed guide path of the first cylindrical element,

wherein a rotation of the first cylindrical element moves each of said at least one sleeve member thereabout along their first recessed guide path,

wherein the hub is operated by a second cylindrical element, the second cylindrical element being coupled to the at least one motor,

wherein the second cylindrical element further comprises at least one third recessed guide path, arranged in an outer surface of the second cylindrical element,

wherein an inner surface of the first cylindrical element comprises at least one projecting element, configured to be in a sliding connection with the corresponding at least one third recessed guide path, arranged in the outer surface of the second cylindrical element, and

wherein a rotation of the second cylindrical element transfers said rotation and moves the first cylindrical element along a length of the at least one third recessed guide path.

2. The propeller according to claim 1 , wherein the storage positions of each of said at least one blade is/are aligned at the same angular position in a radial direction from the first cylindrical element.

3. The propeller according to claim 1 , wherein the at least one blade is fixedly attached to the first cylindrical element at the same angular position as a corresponding storage position thereof.

4. The propeller according to claim 1 , wherein a second recessed guide path having a second position being arranged lower at the first cylindrical element than the at least one first recessed guide path, has a longer path length between its first and second position, compared to the at least one first adjacent recessed guide path.

5. The propeller according to claim 4 , wherein the second recessed guide path having a second position being arranged lower at the first cylindrical element than the at least one first recessed guide path, has a lower accumulated/overall path angle between its first and second position, compared to the at least one first recessed guide path.

6. The propeller according to claim 1 , wherein each sleeve member comprises a first end section being flat, and second end section that comprises at least one high point and at least one low point, compared to an average of an height of the second end section, wherein the sleeve members are arranged on the first cylindrical element so that second end sections of adjacent sleeve members face each other.

7. The propeller according to claim 1 , wherein a rotation of the second cylindrical element in a direction corresponding to the propeller moving forward for generating thrust, biases at least one propeller blade to move from its storage position towards its operational position by means of rotation of its sleeve member about the first cylindrical element.

8. The propeller according to claim 1 , further comprising at least one locking mechanism, configured to selectively lock each sleeve member in the operational position of the blades.

9. The propeller according to claim 1 , wherein said propeller comprises two blades.

10. The propeller according to claim 1 , wherein said propeller comprises four blades.

11. Arrangement comprising a propeller according to claim 1 , wherein the arrangement further comprises a compartment configured to accommodate the propeller.

12. A propeller for an aircraft, wherein the propeller comprises at least two blades, arranged about a central hub, the central hub being coupled to at least one motor, driven by a power source,

wherein at least one blade is attached to at least one sleeve member, configured for being in an outer sliding connection to a first cylindrical element of the hub,

wherein an inner surface of each of said at least one sleeve member comprises at least one projecting element, configured to be in a sliding connection with a corresponding at least one first recessed guide path, arranged in an outer surface of the first cylindrical element,

wherein each of said at least one first recessed guide path circles at least partly around the first cylindrical element from a first position to a second position,

wherein each of said at least one sleeve member positions its blade in an operational position when its at least one projecting element is positioned in its corresponding first position in its designated first recessed guide path of the first cylindrical element,

wherein each of said at least one sleeve member positions its blade in a storage position when its at least one projecting element is positioned in its corresponding second position in its designated first recessed guide path of the first cylindrical element,

wherein a rotation of the first cylindrical element moves each of said at least one sleeve member thereabout along their first recessed guide path,

wherein the storage positions of each of said at least one blade is/are aligned at the same angular position in a radial direction from the first cylindrical element,

wherein a blade is fixedly attached to the first cylindrical element at the same angular position as a corresponding storage position thereof,

wherein the hub is operated by a second cylindrical element, the second cylindrical element being coupled to the at least one motor,

wherein the second cylindrical element further comprises at least one third recessed guide path, arranged in an outer surface of the second cylindrical element,

wherein an inner surface of the first cylindrical element comprises at least one projecting element, configured to be in a sliding connection with the corresponding at least one third recessed guide path, arranged in the outer surface of the second cylindrical element, and

wherein a rotation of the second cylindrical element transfers said rotation and moves the first cylindrical element along a length of the at least one third recessed guide path.

13. The propeller according to claim 12 , wherein a second recessed guide path having a second position being arranged lower at the first cylindrical element than the at least one first recessed guide path, has a longer path length between its first and second position, compared to the at least one first adjacent recessed guide path.

14. An aircraft, comprising at least one wing, wherein the aircraft comprises at least one propeller, wherein the propeller comprises at least two blades, arranged about a central hub, the central hub being coupled to at least one motor, driven by a power source,

wherein at least one blade is attached to at least one sleeve member, configured for being in an outer sliding connection to a first cylindrical element of the hub,

wherein an inner surface of each of said at least one sleeve member comprises at least one projecting element, configured to be in a sliding connection with a corresponding at least one first recessed guide path, arranged in an outer surface of the first cylindrical element,

wherein each of said at least one first recessed guide path circles at least partly around the first cylindrical element from a first position to a second position,

wherein each of said at least one sleeve member positions its blade in an operational position when its at least one projecting element is positioned in its corresponding first position in its designated first recessed guide path of the first cylindrical element,

wherein each of said at least one sleeve member positions its blade in a storage position when its at least one projecting element is positioned in its corresponding second position in its designated first recessed guide path of the first cylindrical element,

wherein a rotation of the first cylindrical element moves each of said at least one sleeve member thereabout along their first recessed guide path,

wherein the hub is operated by a second cylindrical element, the second cylindrical element being coupled to the at least one motor,

wherein the second cylindrical element further comprises at least one third recessed guide path, arranged in an outer surface of the second cylindrical element,

wherein an inner surface of the first cylindrical element comprises at least one projecting element, configured to be in a sliding connection with the corresponding at least one third recessed guide path, arranged in the outer surface of the second cylindrical element, and

wherein a rotation of the second cylindrical element transfers said rotation and moves the first cylindrical element along a length of the at least one third recessed guide path.

15. The aircraft according to claim 14 , wherein the aircraft comprises a compartment for accommodation of the at least one propeller.

16. An aircraft, comprising at least one wing, wherein the aircraft comprises at least one propeller, wherein the propeller comprises at least two blades, arranged about a central hub, the central hub being coupled to at least one motor, driven by a power source,

wherein at least one blade is attached to at least one sleeve member, configured for being in an outer sliding connection to a first cylindrical element of the hub,

wherein an inner surface of each of said at least one sleeve member comprises at least one projecting element, configured to be in a sliding connection with a corresponding at least one first recessed guide path, arranged in an outer surface of the first cylindrical element,

wherein each of said at least one first recessed guide path circles at least partly around the first cylindrical element from a first position to a second position,

wherein each of said at least one sleeve member positions its blade in an operational position when its at least one projecting element is positioned in its corresponding first position in its designated first recessed guide path of the first cylindrical element,

wherein each of said at least one sleeve member positions its blade in a storage position when its at least one projecting element is positioned in its corresponding second position in its designated first recessed guide path of the first cylindrical element,

wherein a rotation of the first cylindrical element moves each of said at least one sleeve member thereabout along their first recessed guide path,

wherein the storage positions of each of said at least one blade is/are aligned at the same angular position in a radial direction from the first cylindrical element,

wherein a blade is fixedly attached to the first cylindrical element at the same angular position as a corresponding storage position thereof,

wherein the hub is operated by a second cylindrical element, the second cylindrical element being coupled to the at least one motor,

wherein the second cylindrical element further comprises at least one third recessed guide path, arranged in an outer surface of the second cylindrical element,

wherein an inner surface of the first cylindrical element comprises at least one projecting element, configured to be in a sliding connection with the corresponding at least one third recessed guide path, arranged in the outer surface of the second cylindrical element, and

wherein a rotation of the second cylindrical element transfers said rotation and moves the first cylindrical element along a length of the at least one third recessed guide path..

17. An aircraft according to claim 16 , wherein a second recessed guide path having a second position being arranged lower at the first cylindrical element than the at least one first recessed guide path, has a longer path length between its first and second position, compared to the at least one first adjacent recessed guide path.