Wing tilt actuation system for electric vertical take-off and landing (VTOL) aircraft

A vertical take-off and landing (VTOL) aircraft comprising:

• a fuselage;
• first and second forward wings mounted to opposing sides of the fuselage, each wing having a fixed leading edge and a trailing control surface which is pivotal about a generally horizontal pivot axis;
• the first and second forward wings each having a first electric motor having a first variable pitch propeller, a second electric motor having a second variable pitch propeller, the first and second motors being mounted to each wing, the first and second propellers being pivotal with a common trailing control surface between a first position in which each propeller has a generally vertical axis of rotation, and a second position in which each propeller has a generally horizontal axis of rotation, a control system for controlling rotation speed and/or blade pitch each variable pitch propeller;
• wherein the control system is configured to change the pitch of the first propeller relative to the second propeller of each wing to generate a turning moment to pivot the respective control surface about the pivot axis.