Payload dropping mechanism for unmanned aerial vehicle

1. An unmanned aerial vehicle having a dropping device for a first load and a second load, the dropping device comprising an actuation element which performs a first movement in order to drop the first load and which performs a second movement in order to drop the second load, the aerial vehicle having a first passage opening in a structural component, through which a projection of the first load can be led, and a second passage opening in the structural component, through which a projection of the second load can be led, and the dropping device comprising a first locking element which, in a connected state of the first load, engages into an opening of the first load, and a second locking element which, in a connected state of the second load, engages into an opening of the second load.

2. The aerial vehicle as claimed in claim 1 , wherein the first movement and the second movement of the actuation element have a corresponding movement direction.

3. The aerial vehicle as claimed in claim 1 , wherein the projection of the first load and the projection of the second load are oriented upward.

4. The aerial vehicle as claimed in claim 1 , wherein the projection of the first load and the first passage opening are adapted to one another such that a rotational movement of the first load about an axis of the first passage opening is prevented.

5. The aerial vehicle as claimed in claim 1 , wherein the engagement of the second locking element with the second load is more pronounced than the engagement of the first locking element with the first load.

6. The aerial vehicle as claimed in claim 1 , wherein the actuation element is connected to a drive motor which is designed to set the actuation element in rotation.

7. The aerial vehicle as claimed in claim 6 , wherein, for the first movement and the second movement of the actuation element, the drive motor is rotated in the same direction.

8. The aerial vehicle as claimed in claim 6 , wherein, for the first movement and the second movement of the actuation element, the drive motor is rotated through the same angle of rotation.

9. A method for dropping a first load and a second load from an unmanned aerial vehicle, wherein a projection of a first load is inserted into a first passage opening in a structural component of the aerial vehicle, in which method a projection of a second load is inserted into a second passage opening in the structural component of the aerial vehicle, in which method a first locking element, in a connected state of the first load, engages into an opening of the first load, in which method a second locking element, in a connected state of the second load, engages into an opening of the second load, and in which method an actuation element is set in motion in order to release the first locking element from the first load, and in which method, at a later point in time, the same actuation element is set in motion in order to release the second locking element from the second load.

10. An unmanned aerial vehicle having a dropping device for a first load and a second load, the dropping device comprising an actuation element which performs a first rotational movement to effect drop of the first load and which performs a second rotational movement to effect drop of the second load, the aerial vehicle having a shaped first passage opening in a structural component, through which a shaped projection of the first load is slip fit, and a shaped second passage opening in the structural component, through which a shaped projection of the second load is slip fit, and the dropping device comprising a first locking element which, in a connected state of the first load, engages into an opening of the first load to prevent dropping of the first load, and a second locking element which, in a connected state of the second load, engages into an opening of the second load to prevent dropping of the second load.

11. The aerial vehicle as claimed in claim 10 , wherein said first and second locking elements are elongated and disposed in a coplanar relationship with said actuation element.

12. The aerial vehicle as claimed in claim 11 , wherein said first and second locking elements each have a first end pivotally affixed to said actuation element.

13. The aerial vehicle as claimed in claim 12 , wherein said first and second locking elements each have an opposite end portion extending through an associated load projection bore to prevent dropping of the load.

14. The aerial vehicle as claimed in claim 13 , wherein said first and second locking elements are formed of resilient material.

15. The aerial vehicle as claimed in claim 13 , wherein said first and second locking elements are formed of resilient plastic material.

16. The aerial vehicle as claimed in claim 10 , wherein said actuation element is elongated and is configured for unirotational displacement about a central axis, and wherein said first and second locking elements each have a first end pivotally affixed to an opposed end of said actuation element, where upon rotation of said actuation element in one direction, each of the opposite end portions of said first and second locking elements converge and upon rotation of said actuation element in an opposite direction, each of the opposite end portions of said first and second locking elements diverge.

17. The aerial vehicle as claimed in claim 16 , wherein said activation element is substantially equally spaced between said loads and one of said locking elements is axially shorter than the other.

18. The aerial vehicle as claimed in claim 10 , wherein said structural component shaped passage openings are substantially rectangular.

19. The aerial vehicle as claimed in claim 10 , wherein said load shaped projections are substantially rectangular in cross section.