Tilting hexrotor aircraft

Patent metadata

Field	Value
Publication number	US-2025187729-A1
Application number	US-202519055990-A
Country	US
Kind code	A1
Filing date	Feb 18, 2025
Priority date	Mar 29, 2021
Publication date	Jun 12, 2025
Grant date	—

Abstract

One embodiment is an aircraft including a fuselage; a wing connected to the fuselage; first and second booms connected to the wing on opposite sides of the fuselage; first and second forward propulsion systems attached to forward ends of the first and second booms; first and second aft propulsion systems fixedly attached proximate aft ends of the first and second booms; and first and second wing-mounted propulsion systems connected to outboard ends of wings; wherein the first and second wing-mounted propulsion systems are tiltable between a first position when the aircraft is in a hover mode and a second position when the aircraft is in a cruise mode.

First claim

What is claimed is:

1 . An aircraft comprising:
a fuselage; a wing connected to the fuselage; a tail assembly at an aft end of the fuselage, the tail assembly comprising a pair of airfoils; a first boom connected to a first side of the wing; a second boom connected to a second, opposite side of the wing; exactly six propulsion systems comprising:
first and second forward propulsion systems attached to forward ends of the first and second booms;
first and second aft propulsion systems fixedly attached proximate aft ends of the first and second booms, wherein each of the first and second aft propulsion systems is attached to a surface of the respective one of the booms such that an axis of rotation of the aft propulsion system forms a non-zero angle outboard from a vertical axis;
a first wing-mounted propulsion system connected to a first side of the wing at a first outboard end of the wing; and
a second-wing mounted propulsion system connected to a second, opposite of the wing at a second outboard end of the wing; wherein the first and second wing-mounted propulsion systems are tiltable with the first outboard end of the wing and the second outboard end of the wing between a first position when the aircraft is in a hover mode and a second position when the aircraft is in a cruise mode; and wherein each of the propulsion systems includes a rotor assembly comprising a plurality of rotor blades.

2 . The aircraft of claim 1 , wherein the rotor assemblies of the first and second aft propulsion systems rotate when the aircraft is in the hover mode and cease to rotate when the aircraft is in the cruise mode.

3 . The aircraft of claim 1 , wherein the first and second forward propulsion systems are tiltably connected to forward ends of the first and second booms such that the first and second forward propulsion systems are tiltable between a first position when the aircraft is in the hover mode and a second position when the aircraft is in the cruise mode.

4 . The aircraft of claim 1 , wherein the first and second forward propulsion systems are fixedly attached to the forward ends of the first and second booms.

5 . The aircraft of claim 1 , wherein the airfoils extend from a top surface of the fuselage at an angle θ2 from one another, wherein θ2 is selected from the range consisting of 30 to 330 degrees.

6 . The aircraft of claim 1 , further comprising control surfaces on trailing edges of the airfoils.

7 . The aircraft of claim 6 , wherein each of the control surfaces comprises multiple independently controlled segments.

8 . The aircraft of claim 1 , wherein the propulsion systems collectively comprise a hexrotor arc when the aircraft is in the hover mode.

9 . An aircraft comprising:
a fuselage; a wing connected to the fuselage; a first boom connected to a first side of the wing;
a second boom connected to a second, opposite side of the wing;
no more than six propulsion systems, the no more than six propulsion systems comprising:
first and second forward propulsion systems attached to forward ends of the first and second booms;
first and second aft propulsion systems fixedly attached proximate aft ends of the first and second booms, wherein each of the first and second aft propulsion systems is attached to a surface of the respective one of the booms such that an axis of rotation of the aft propulsion system forms a non-zero angle outboard from a vertical axis;
a first wing-mounted propulsion system connected to a first side of the wing at a first outboard end of the wing; and
a second-wing mounted propulsion system connected to a second, opposite of the wing at a second outboard end of the wing; and

a tail assembly connected to an aft end of the fuselage, the tail assembly comprising a vertical stabilizer having a first end connected to the aft end of the fuselage and a second end connected to a horizontal stabilizer;
wherein the first and second wing-mounted propulsion systems are tiltable with the first outboard end of the wing and the second outboard end of the wing between a first position when the aircraft is in a hover mode and a second position when the aircraft is in a cruise mode; and
wherein each of the propulsion systems includes a rotor assembly comprising a plurality of rotor blades.

10 . The aircraft of claim 9 , wherein the first and second wing-mounted propulsion systems are tiltable between a first position when the aircraft is in a hover mode and a second position when the aircraft is in a cruise mode.

11 . The aircraft of claim 9 , wherein the tail assembly comprises a T-tail.

12 . The aircraft of claim 9 , further comprising control surfaces on trailing edges of the vertical stabilizer and the horizontal stabilizer.

13 . The aircraft of claim 9 , wherein the rotor assemblies of the first and second aft propulsion systems rotate when the aircraft is in the hover mode and cease to rotate when the aircraft is in the cruise mode.

14 . The aircraft of claim 9 , wherein the first and second forward propulsion systems are tiltably connected to forward ends of the first and second booms such that the first and second forward propulsion systems are tiltable between a first position when the aircraft is in the hover mode and a second position when the aircraft is in the cruise mode.

15 . The aircraft of claim 9 , wherein the first and second forward propulsion systems are fixedly attached to the forward ends of the first and second booms.

16 . An electric vertical takeoff and landing aircraft (eVTOL) selectively convertible between a hover mode and a cruise mode, the eVTOL comprising:
a fuselage; a wing connected to the fuselage; a first boom connected to a first side of the wing; a second boom connected to a second, opposite side of the wing; exactly six propulsion systems, the six propulsion systems comprising:
first and second forward propulsion systems attached to forward ends of the first and second booms;
first and second aft propulsion systems fixedly attached proximate aft ends of the first and second booms, wherein each of the first and second aft propulsion systems is attached to a surface of the respective one of the booms such that an axis of rotation of the aft propulsion system forms a non-zero angle outboard from a vertical axis;
a first wing-mounted propulsion system connected to a first side of the wing at a first outboard end of the wing; and
a second-wing mounted propulsion system connected to a second, opposite of the wing at a second outboard end of the wing;
wherein each of the first and second wing-mounted propulsion systems includes a pylon for housing a drive system; and
a tail assembly on an aft end of the fuselage, the tail assembly comprising at least one of a T-tail and a V-tail; wherein each of the pylons is tiltable relative to the wing between a first position when the eVTOL is in a hover mode and a second position when the eVTOL is in a cruise mode; and wherein each of the propulsion systems includes a rotor assembly comprising a plurality of rotor blades.

17 . The eVTOL of claim 16 , wherein the tail assembly comprises a pair of airfoils each connected at one end to the aft end of the fuselage and wherein at least one of the airfoils extends from a top surface of the fuselage at an angle θ1 from vertical, wherein θ1 is less than 180 degrees.

18 . The eVTOL of claim 16 , wherein the tail assembly comprises a vertical stabilizer and a horizontal stabilizer and wherein a first end of the vertical stabilizer is connected to the aft en

Assignees

• Textron Innovations Inc

Inventors

• Ross Brent C
• Groninga Kirk L
• Ivans Steven R
• Schafer Steven R
• Passe Brad Joseph
• Carlson Nicholas Ralph
• Campbell Kip Gregory
• Regnier Bradley Paul
• Hagerott Steven G

Classifications

• B64D27/31

  within, or attached to, wings · CPC title

• B64D27/33

  Hybrid electric aircraft · CPC title

• B64C29/00

  Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft (rotorcraft B64C27/00) · CPC title

• B64C9/20

  by multiple flaps · CPC title

• B64C29/0033 Primary

  the propellers being tiltable relative to the fuselage · CPC title