Aircraft generating a triaxial dynamic thrust matrix

• US 10,293,931 B2
• Filed: 08/31/2016
• Issued: 05/21/2019
• Est. Priority Date: 08/31/2016
• Status: Active Grant

• Current Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Original Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Inventors: Robertson, Daniel Bryan, Groninga, Kirk Landon
• Primary Examiner(s): Green, Richard R.
• Assistant Examiner(s): Frazier, Brady W
• Application Number:
  US15/253,449
• Publication Number:
  US 20180057160A1
• Time in Patent Office: 993 Days
• Field of Search: 244 124, 244 35 A
• CPC Class Codes: B64C 11/006 Paddle wheels
• CPC Class Codes: B64C 11/06 for variable-pitch blades
• CPC Class Codes: B64C 11/32 mechanical
• CPC Class Codes: B64C 19/00 Aircraft control not otherwise provided for
• CPC Class Codes: B64C 23/02 by means of rotating members of cylindrical or similar form
• CPC Class Codes: B64C 25/10 retractable, foldable, or the like
• CPC Class Codes: B64C 25/32 characterised by elements which contact the ground or similar surface arrester hooks B64C25/68
• CPC Class Codes: B64C 29/0033 the propellers being tiltable relative to the fuselage
• CPC Class Codes: B64C 29/02 having its flight directional axis vertical when grounded
• CPC Class Codes: B64C 3/16 Frontal aspect
• CPC Class Codes: B64C 39/005 about a horizontal transversal axis
• CPC Class Codes: B64C 39/006 about a vertical axis
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64C 39/12 Canard-type aircraft
• CPC Class Codes: B64C 5/02 Tailplanes
• CPC Class Codes: B64U 10/20 Vertical take-off and landing [VTOL] aircraft flying platforms B64U10/13; helicopters B64U10/17
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 30/10 Wings
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 50/14 ducted or shrouded
• CPC Class Codes: B64U 50/18 : Thrust vectoring
• CPC Class Codes: B64U 50/19 : using electrically powered motors
• CPC Class Codes: B64U 60/50 : with landing legs
• CPC Class Codes: Y02T 50/10 : Drag reduction

Abstract

A tri-wing aircraft includes a fuselage having a longitudinally extending fuselage axis. Three wings extend generally radially outwardly from the fuselage axis and are circumferentially distributed generally uniformly about the fuselage at approximately 120-degree intervals. The wings have airfoil cross-sections including first and second surfaces having chordwise channels therebetween. A distributed propulsion system includes a plurality of propulsion assemblies. Each propulsion assembly includes a variable thrust cross-flow fan disposed within one of the chordwise channels of one of the wings. At least two variable thrust cross-flow fans are disposed within the chordwise channels of each of the wings. A flight control system is operably associated with the distributed propulsion system such that the flight control system and the distributed propulsion system are operable to generate a triaxial dynamic thrust matrix.

Claims

1. An aircraft comprising:

a fuselage having a longitudinally extending fuselage axis;

three wings extending from and circumferentially distributed about the fuselage at approximately 120-degree intervals, each wing having an airfoil cross-section including first and second surfaces and having leading and trailing edges with a chordwise channel extending between the leading and trailing edges such that the leading edge forms a forward air intake of the chordwise channel and the trailing edge forms an aft air discharge of the chordwise channel;

a distributed propulsion system including a plurality of propulsion assemblies, each propulsion assembly including a propulsion unit disposed within one of the chordwise channels of one of the wings between the forward air intake and the aft air discharge; and

a flight control system operably associated with the distributed propulsion system.

2. The aircraft as recited in claim 1 wherein the at least three wings extend generally radially outwardly from the fuselage axis.

3. The aircraft as recited in claim 1 wherein the propulsion units further comprise cross-flow fans.

4. The aircraft as recited in claim 1 wherein the propulsion units further comprise variable thrust cross-flow fans.

5. The aircraft as recited in claim 4 wherein each of the variable thrust cross-flow fans further comprises:

a cross-flow fan assembly having a longitudinal axis and including first and second driver plates having a plurality of blades rotatably mounted therebetween, the plurality of blades disposed radially outwardly from the longitudinal axis such that the plurality of blades have a generally circular path of travel when the cross-flow fan assembly rotates about the longitudinal axis, the plurality of blades moveable between a plurality of pitch angle configurations; and

a control assembly coupled to the plurality of blades, the control assembly operable to change the pitch angle configuration of the plurality of blades to generate variable thrust.

6. The aircraft as recited in claim 1 wherein the propulsion units further comprise electrically powered propulsion units.

7. The aircraft as recited in claim 1 wherein the distributed propulsion system further comprises at least two propulsion units disposed within the chordwise channels of each wing.

8. The aircraft as recited in claim 1 wherein the flight control system and the distributed propulsion system are operable to generate a dynamic thrust matrix.

9. The aircraft as recited in claim 8 wherein the dynamic thrust matrix further comprise a triaxial dynamic thrust matrix.

10. The aircraft as recited in claim 8 wherein the dynamic thrust matrix further comprises a thrust magnitude and a thrust vector of each propulsion unit.

11. The aircraft as recited in claim 8 wherein adjustments to the dynamic thrust matrix are operable to transition the aircraft between a vertical takeoff and landing mode and a forward flight mode.

12. The aircraft as recited in claim 8 wherein adjustments to the dynamic thrust matrix are operable to maintain the aircraft in a stable hover and to perform lateral transitions in vertical takeoff and landing mode.

13. The aircraft as recited in claim 8 wherein adjustments to the dynamic thrust matrix are operable to provide roll control during forward flight.

14. The aircraft as recited in claim 8 wherein adjustments to the dynamic thrust matrix are operable to enhance aircraft endurance during forward flight.

15. A tri-wing aircraft comprising:

a fuselage having a longitudinally extending fuselage axis;

three wings extended generally radially outwardly from the fuselage axis and circumferentially distributed generally uniformly about the fuselage at approximately 120-degree intervals, each wing having an airfoil cross-section including first and second surfaces and having leading and trailing edges with a chordwise channel extending between the leading and trailing edges such that the leading edge forms a forward air intake of the chordwise channel and the trailing edge forms an aft air discharge of the chordwise channel;

a distributed propulsion system including a plurality of propulsion assemblies, each propulsion assembly including a variable thrust cross-flow fan disposed within one of the chordwise channels of one of the wings between the forward air intake and the aft air discharge with at least two variable thrust cross-flow fans disposed within the chordwise channels of each of the wings; and

a flight control system operably associated with the distributed propulsion system such that the flight control system and the distributed propulsion system are operable to generate a triaxial dynamic thrust matrix.

16. The aircraft as recited in claim 15 wherein each of the variable thrust cross-flow fans further comprises:

a cross-flow fan assembly having a longitudinal axis and including first and second driver plates having a plurality of blades rotatably mounted therebetween, the plurality of blades disposed radially outwardly from the longitudinal axis such that the plurality of blades have a generally circular path of travel when the cross-flow fan assembly rotates about the longitudinal axis, the plurality of blades moveable between a plurality of pitch angle configurations; and

a control assembly coupled to the plurality of blades, the control assembly operable to change the pitch angle configuration of the plurality of blades to generate variable thrust.

17. The aircraft as recited in claim 15 wherein the variable thrust cross-flow fans of the distributed propulsion system further comprise electrically powered variable thrust cross-flow fans.

18. The aircraft as recited in claim 15 wherein the triaxial dynamic thrust matrix further comprises a thrust magnitude and a thrust vector of each propulsion assembly.

19. The aircraft as recited in claim 15 wherein adjustments to the triaxial dynamic thrust matrix are operable to transition the aircraft between a vertical takeoff and landing mode and a forward flight mode, maintain the aircraft in a stable hover, perform lateral transitions in vertical takeoff and landing mode, provide roll control during forward flight and enhance aircraft endurance during forward flight.