Vertical takeoff and landing aircraft having a forward thrust propulsor

A hybrid-electric propulsion system for an aircraft comprising:

• a power source comprising a combustion engine and an electric generator;
• a plurality of vertical thrust electric fans configured to be integrated into a wing of the aircraft in an orientation to generate thrust along a vertical direction of the aircraft, the plurality of vertical thrust electric fans driven by the power source;
• a forward thrust propulsor selectively coupled to the combustion engine through a coupling unit, wherein the coupling unit is configured to disengage the forward thrust propulsor from the combustion engine when a variable geometry portion of the wing is moved from a position in which one or more of the plurality of vertical thrust electric fans are covered to a position in which one or more of the plurality of vertical thrust electric fans are exposed;
• and
• a speed change mechanism positioned rearwardly of an aft end of the combustion engine and between the combustion engine and the coupling unit.

An aircraft defining a vertical direction and a transverse direction, the aircraft comprising:

• a fuselage;
• a wing coupled to, and extending from, the fuselage;
• and
• a hybrid-electric propulsion system, the hybrid-electric propulsion system comprising:
• a power source comprising a combustion engine and an electric generator;
• a plurality of vertical thrust electric fans integrated into the wing and oriented to generate thrust along the vertical direction, the plurality of vertical thrust electric fans arranged along a length of the wing and driven by the power source;
• a forward thrust propulsor coupled to the combustion engine, wherein the forward thrust propulsor is configured as a variable pitch propulsor;
• and
• a drive motor coupled with the forward thrust propulsor, the drive motor positioned rearwardly of an aft end of the combustion engine and configured to selectively rotate the forward thrust propulsor, wherein an aft output shaft of the combustion engine is generally axially aligned with a fan axis of the forward thrust propulsor.