Aircraft generating thrust in multiple directions

Patent metadata

Field	Value
Publication number	US-11312487-B2
Application number	US-202016840292-A
Country	US
Kind code	B2
Filing date	Apr 3, 2020
Priority date	Jul 1, 2016
Publication date	Apr 26, 2022
Grant date	Apr 26, 2022

Abstract

An aircraft has an airframe with first and second wings having first and second pylons extending therebetween. A distributed propulsion system attached to the airframe includes at least first, second, third and fourth propulsion assemblies that are independently controlled by a flight control system. A pod assembly is coupled to the airframe. In a VTOL flight mode, the first and second propulsion assemblies are forward of the pod assembly and the third and fourth propulsion assemblies are aft of the pod assembly. In a forward flight mode, the first and second propulsion assemblies are below the pod assembly and the third and fourth propulsion assemblies are above the pod assembly. In both the VTOL and forward flight modes, the first and fourth propulsion assemblies generate thrust having a first direction while the second and third propulsion assemblies generate thrust having a second direction that is different from the first direction.

First claim

What is claimed is:

1. An aircraft operable to transition between thrust-borne lift in a vertical takeoff and landing flight mode and wing-borne lift in a forward flight mode, the aircraft comprising:
an airframe including a first wing, a second wing, a first pylon extending between the first and second wings and a second pylon extending between the first and second wings;
a distributed propulsion system attached to the airframe including at least first, second, third and fourth propulsion assemblies;
a flight control system operably associated with the distributed propulsion system and operable to independently control each of the propulsion assemblies; and
a pod assembly coupled to the airframe;
wherein, the first propulsion assembly is symmetrically disposed relative to the fourth propulsion assembly and the second propulsion assembly is symmetrically disposed relative to the third propulsion assembly;
wherein, in the vertical takeoff and landing flight mode, the first and second propulsion assemblies are forward of the pod assembly and the third and fourth propulsion assemblies are aft of the pod assembly;
wherein, in the forward flight mode, the first and second propulsion assemblies are below the pod assembly and the third and fourth propulsion assemblies are above the pod assembly; and
wherein, in both the vertical takeoff and landing flight mode and the forward flight mode, the first and fourth propulsion assemblies are configured to generate thrust having a first direction while the second and third propulsion assemblies are configured to generate thrust having a second direction that is different from the first direction.

2. The aircraft as recited in claim 1 wherein, in the vertical takeoff and landing flight mode, the first wing is forward of the pod assembly, the second wing is aft of the pod assembly and the first and second pylons are lateral of the pod assembly.

3. The aircraft as recited in claim 1 wherein, in the forward flight mode, the first wing is below the pod assembly, the second wing is above the pod assembly and the first and second pylons are lateral of the pod assembly.

4. The aircraft as recited in claim 1 wherein, the first direction has a first component in a direction of flight of the aircraft and a second component in a first lateral direction; and
wherein the second direction has a first component in the direction of flight of the aircraft and a second component in a second lateral direction that is different from the first lateral direction.

5. The aircraft as recited in claim 4 wherein the first lateral direction is opposite the second lateral direction.

6. The aircraft as recited in claim 1 wherein the distributed propulsion system further comprises at least six propulsion assemblies including the first, second, third and fourth propulsion assemblies.

7. The aircraft as recited in claim 6 wherein, in both the vertical takeoff and landing flight mode and the forward flight mode, at least two of the propulsion assemblies are lateral of the pod assembly.

8. The aircraft as recited in claim 1 wherein the first wing has first and second ends and the second wing has first and second ends; and
wherein the first pylon extends between the first ends of the first and second wings and the second pylon extends between the second ends of the first and second wings forming a closed wing.

9. The aircraft as recited in claim 8 wherein the closed wing further comprises a polygonal-shaped closed wing.

10. The aircraft as recited in claim 8 wherein the closed wing further comprises a rectangular-shaped closed wing.

11. The aircraft as recited in claim 8 wherein the closed wing further comprises at least four sides.

12. The aircraft as recited in claim 1 wherein the first wing is generally parallel to the second wing and wherein the first pylon is generally parallel to the second pylon.

13. The aircraft as recited in claim 1 wherein each of the propulsion assemblies further comprises at least one electric motor.

14. The aircraft as recited in claim 1 wherein the first and second propulsion assemblies are coupled to the first wing and the third and fourth propulsion assemblies are coupled to the second wing.

15. The aircraft as recited in claim 1 wherein two of the first, second, third and fourth propulsion assemblies have rotors that rotate clockwise and two of the first, second, third and fourth propulsion assemblies have rotors that rotate counterclockwise.

16. The aircraft as recited in claim 1 wherein the pod assembly further comprises an unmanned pod assembly.

17. The aircraft as recited in claim 1 wherein the flight control system is configured for autonomous flight control.

18. The aircraft as recited in claim 1 wherein the flight control system is operable to independently control a rotor speed of each of the propulsion assemblies.

19. An aircraft operable to transition between thrust-borne lift in a vertical takeoff and landing flight mode and wing-borne lift in a forward flight mode, the aircraft comprising:
an airframe including a first wing, a second wing, a first pylon extending between the first and second wings and a second pylon extending between the first and second wings;
a distributed propulsion system attached to the airframe including at least first, second, third and fourth propulsion assemblies;
a flight control system operably associated with the distributed propulsion system and operable to independently control each of the propulsion assemblies; and
a pod assembly coupled to the airframe;
wherein, in the vertical takeoff and landing flight mode, the first and second propulsion assemblies are forward of the pod assembly and the third and fourth propulsion assemblies are aft of the pod assembly;
wherein, in the forward flight mode, the first and second propulsion assemblies are below the pod assembly and the third and fourth propulsion assemblies are above the pod assembly; and
wherein, in both the vertical takeoff and landing flight mode and the forward flight mode, the first and fourth propulsion assemblies are configured to generate thrust having a first direction while the second and third propulsion assemblies are configured to generate thrust having a second direction that is different from the first direction.

20. An aircraft operable to transition between thrust-borne lift in a vertical takeoff and landing flight mode and wing-borne lift in a forward flight mode, the aircraft comprising:
an airframe including a first wing, a second wing, a first pylon extending between the first and second wings and a second pylon extending between the first and second wings;
a distributed propulsion system attached to the airframe including at least first, second, third and fourth propulsion assemblies;
a flight control system operably associated with the distributed propulsion system and operable to independently control each of the propulsion assemblies; and
a pod assembly coupled to the airframe;
wherein, in the vertical takeoff and landing flight mode, the first and second propulsion assemblies are forward of the pod assembly and the third and fourth propulsion assemblies are aft of the pod assembly;
wherein, in the forward flight mode, the first and second propulsion assemblies are below the pod assembly and the third and fourth propulsion assemblies are above the pod assembly; and
wherein, in both the vertical takeoff and landing flight mode and the forward flight mode, the first and second propulsion assemblies are configured to generate t

Assignees

• Textron Innovations Inc

Inventors

• Mccullough John Richard
• Oldroyd Paul K

Classifications

• B64C39/02

  characterised by special use · CPC title

• B64D25/12

  Ejectable capsules · CPC title

• B64C29/0033 Primary

  the propellers being tiltable relative to the fuselage · CPC title

• B64D35/00

  Transmitting power from power plants to propellers or rotors; Arrangements of transmissions · CPC title

• B64D37/04

  Arrangement thereof in or on aircraft · CPC title