Engine comprising a movable aerodynamic component

1. A vertical take-off and landing aircraft, comprising an aircraft component and a plurality of engine arrangements mounted adjacent to one another to the aircraft component such as to form a row, wherein each of the plurality of engine arrangements comprises at least one electric engine, and is pivotable with respect to the aircraft component independently from any of the other engine arrangements of the plurality of engine arrangements, wherein each engine arrangement is configured to be movable with respect to the aircraft component of the aircraft between a hover position for take-off and landing, and a cruise position for forward flight, wherein:

each of the engines comprises an aerodynamic component having at least one aerodynamic element movable between a first position and a second position, the aerodynamic element defining an aerodynamic surface in contact with an airstream passing through the engine, wherein each of the engines comprise a transmission having a first end connected to the aerodynamic component and a second end adapted to be connected to the aircraft component, wherein the transmission is adapted to translate a movement of the engine with respect to the aircraft component into a movement of the at least one aerodynamic element,

wherein each engine is configured to set the aerodynamic element to the first position when the engine arrangement assumes the hover position, and to set the aerodynamic element to the second position when the engine arrangement assumes the cruise position,

wherein the at least one aerodynamic element comprises a first aerodynamic element and a second aerodynamic element, wherein the first and second aerodynamic elements are connected to one another by a link mechanism comprising a linkage and/or a slotted cam, such that movement of the first aerodynamic element drives movement of the second aerodynamic element,

wherein the linkage is a hinge fixed with the first aerodynamic element and the second aerodynamic element, and

wherein the transmission is configured to just drive the first aerodynamic element, while the second aerodynamic element is configured to be driven by the first aerodynamic element through the link mechanism.

2. The vertical take-off and landing aircraft according to claim 1 , wherein the aircraft component is an airfoil or a fuselage of the aircraft, or a component fixed to an airfoil or a fuselage of the aircraft.

3. The vertical take-off and landing aircraft according to claim 1 , wherein the range of movement of each engine arrangement with respect to the aircraft component between hover position and cruise position comprises an idle range, wherein movement of each engine arrangement within the idle range is not transformed to a movement of the aerodynamic element.

4. The vertical take-off and landing aircraft according to claim 1 , wherein the transmission comprises linkage means, said linkage means comprising a rod and/or a cam mechanism.

5. The vertical take-off and landing aircraft of claim 4 , wherein the cam mechanism comprises a slotted cam.

6. The vertical take-off and landing aircraft according to claim 1 , wherein the aerodynamic element is biased towards the first position or towards the second position.

7. The vertical take-off and landing aircraft according to claim 1 , wherein movement of the aerodynamic element is controlled based on movement of the engine with respect to the aircraft component.

8. The vertical take-off and landing aircraft of claim 1 , wherein the plurality of engine arrangements comprises more than five engine arrangements.

9. The vertical take-off and landing aircraft of claim 1 , wherein the plurality of engine arrangements comprises more than ten engine arrangements.