VTOL aircraft with tilting rotors and tilting ducted fans
An exemplary tiltrotor aircraft having a vertical takeoff and landing (VTOL) flight mode and a forward flight mode includes tiltable rotors located at forward boom ends, tiltable ducted fans located at wings aft of the forward boom ends, and aft rotors located on aft boom portions.
1. A tiltrotor aircraft having a vertical takeoff and landing (VTOL) flight mode and a forward flight mode, the tiltrotor aircraft comprising:
a fuselage;
a first wing extending laterally in a first direction from the fuselage and having a first wing tip distal from the fuselage;
a first tiltable ducted fan coupled to the first wing;
a second wing extending laterally in a second direction from the fuselage and having a second wing tip distal from the fuselage;
a second tiltable ducted fan coupled to the second wing;
a first boom coupled to the first wing, the first boom having a first forward boom end located forward of the first wing and a first boom aft end located aft of the first wing;
a first tiltable rotor coupled to the first forward boom end;
a first aft rotor coupled to a top side of an aft portion of the first boom between the first wing and the first boom aft end;
a second boom coupled to the second wing, the second boom having a second forward boom end located forward of the second wing and a second boom aft end located aft of the second wing;
a second tiltable rotor coupled to the second forward boom end; and
a second aft rotor coupled to a top side of an aft portion of the second boom between the second wing and the second boom aft end.
2. The tiltrotor aircraft of claim 1 , wherein the first boom is coupled to the first wing inboard of the first wing tip and the second boom is coupled to the second wing inboard of the second wing tip.
3. The tiltrotor aircraft of claim 1 , wherein the first tiltable ducted fan is positioned at the first wing tip and the second tiltable ducted fan is positioned at the second wing tip.
4. The tiltrotor aircraft of claim 1 , wherein:
the first boom is coupled to the first wing inboard of the first wing tip and the second boom is coupled to the second wing inboard of the second wing tip; and
the first tiltable ducted fan is positioned at the first wing tip and the second tiltable ducted fan is positioned at the second wing tip.
5. The tiltrotor aircraft of claim 1 , wherein the first and second aft rotors are canted relative to a vertical axis.
6. The tiltrotor aircraft of claim 1 , wherein:
the aft portion of the first boom proximate the first aft rotor has a low coefficient of drag profile; and
the aft portion of the second boom proximate the second aft rotor has a low coefficient of drag profile.
7. The tiltrotor aircraft of claim 6 , wherein a thrust vector of the first and second aft rotors is generally parallel to a chord line of the respective aft portions of the first and second booms.
8. The tiltrotor aircraft of claim 7 , wherein the chord line of the respective aft portions of the first and second booms are canted relative to a vertical axis.
9. The tiltrotor aircraft of claim 8 , wherein the chord line of the aft portion of the first boom and the chord line of the aft portion of the second boom are canted in opposite directions.
10. The tiltrotor aircraft of claim 1 , wherein:
the first boom is coupled to the first wing inboard of the first wing tip and the second boom is coupled to the second wing inboard of the second wing tip;
the first tiltable ducted fan is positioned at the first wing tip and the second tiltable ducted fan is positioned at the second wing tip; and
the first and second aft rotors are canted relative to a vertical axis.
11. The tiltrotor aircraft of claim 10 , wherein:
the aft portion of the first boom proximate the first aft rotor has a low coefficient of drag profile; and
the aft portion of the second boom proximate the second aft rotor has a low coefficient of drag profile.
12. The tiltrotor aircraft of claim 11 , wherein a thrust vector of the first and second aft rotors is generally parallel to a chord line of the respective aft portions of the first and second booms.
13. The tiltrotor aircraft of claim 12 , wherein the chord line of the aft portion of the first boom and the chord line of the aft portion of the second boom are canted in opposite directions.
14. A method of operating a tiltrotor aircraft having a vertical takeoff and landing (VTOL) flight mode and a forward flight mode, the method comprising:
operating the tiltrotor aircraft in flight, the tiltrotor aircraft comprising:
a first wing extending laterally in a first direction from a fuselage and having a first wing tip distal from the fuselage;
a first tiltable ducted fan coupled to the first wing at the first wing tip;
a second wing extending laterally in a second direction from the fuselage and having a second wing tip distal from the fuselage;
a second tiltable ducted fan coupled to the second wing at the second wing tip;
a first boom coupled to the first wing inboard of the first wing tip, the first boom having a first forward boom end located forward of the first wing and a first boom aft end located aft of the first wing;
a first tiltable rotor coupled to the first forward boom end;
a first aft rotor coupled to a top side of an aft portion of the first boom between the first wing and the first boom aft end;
a second boom coupled to the second wing inboard of the second wing tip, the second boom having a second forward boom end located forward of the second wing and a second boom aft end located aft of the second wing;
a second tiltable rotor coupled to the second forward boom end; and
a second aft rotor coupled to a top side of an aft portion of the second boom between the second wing and the second boom aft end; and
operating the tiltrotor aircraft in the VTOL flight mode, wherein the first and second tiltable rotors, the first and second tiltable ducted fans and the first and second aft rotors are rotating and the first and the second tiltable rotors and the first and second tiltable ducted fans are positioned in a generally horizontal plane.
15. The method of claim 14 , wherein the first and the second aft rotors are canted relative to a vertical axis.
16. The method of claim 15 , wherein:
the aft portion of the first boom proximate the first aft rotor has a low coefficient of drag profile; and
the aft portion of the second boom proximate the second aft rotor has a low coefficient of drag profile.
17. The method of claim 16 , wherein a thrust vector of the first and second aft rotors is generally parallel to a chord line of the respective aft portions of the first and second booms.
18. The method of claim 15 , comprising:
operating the tiltrotor aircraft in a forward flight mode; and
wherein the first and second tiltable rotors and the first and second tiltable ducted fans are rotating in a generally vertical plane and the first and second aft rotors are not rotating.
19. The method of claim 18 , wherein, in the forward flight mode, blades of the first and second aft rotors are locked in a stationary position generally parallel to the first and second booms.
20. The method of claim 18 , wherein:
the first and the second aft rotors are canted relative to a vertical axis;
the aft portion of the first boom proximate the first aft rotor has a low coefficient of drag profile;
the aft portion of the second boom proximate the second aft rotor has a low coefficient of drag profile; and
a thrust vector of the first and second aft rotors is generally parallel to a chord line of the respective aft portions of the first and second booms.