It's not a new idea; it's been previously referred to as a "compound helicopter" and the concept was extensively explored by Lockheed with the XH51A-compound* and subsequent AH56 Cheyenne programme*.
The general idea is to have the stub wings develop sufficient lift that in cruising flight the rotor runs at zero pitch to eliminate the advancing blade problem, while still acting as the primary pitch/roll control with cyclic pitch.
Bell did something similar with their experimental model 533, and MacDuck also did the McDonnell XV-1. Oh and of course there was the Fairey Rotordyne which went a stage further, being a compound helicopter that was also an autogyro depending on how fast it was flying at the time.
So the basic concept isn't novel - we have to assume that AIrbus have managed to find some extra novel features to justify the Patent.
PDR
* One of the Lockheed model 286s demonstrators they built to develop the rigid rotor concept for the Army Observation Helicopter competition, with a single stub wing carrying a 3,000lb thrust turbojet. It is alleged that it was so fast that the plexiglass canopy would squash inwards when flown "with gusto".
** The AH56 had a rigid rotor and two tail rotors - one tail rotor was coaxial with the tail boom and provided thrust. It had variable pitch and so could provide powerful deceleration as well as acceleration.