Engine comprising a movable aerodynamic component

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.