Aircraft having a Fault Tolerant Distributed Propulsion System

• US 20180002027A1
• Filed: 07/01/2016
• Published: 01/04/2018
• Est. Priority Date: 07/01/2016
• Status: Active Grant

• Current Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Original Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Inventors: McCullough, John Richard, Oldroyd, Paul K.
• Granted Patent: US 10,232,950 B2
• Time in Patent Office: Days
• CPC Class Codes: B64C 2211/00 Modular constructions of airplanes or helicopters
• CPC Class Codes: B64C 29/0075 the motors being tiltable relative to the fuselage
• CPC Class Codes: B64C 29/02 having its flight directional axis vertical when grounded
• CPC Class Codes: B64D 1/22 Taking-up articles from earth's surface
• CPC Class Codes: B64D 17/02 Canopy arrangement or construction
• CPC Class Codes: B64D 17/80 in association with aircraft, e.g. for braking thereof
• CPC Class Codes: B64D 25/12 Ejectable capsules
• CPC Class Codes: B64D 31/10 for preventing asymmetric thrust
• CPC Class Codes: B64U 10/16 with five or more distinct rotor axes, e.g. octocopters
• CPC Class Codes: B64U 2101/18 for dropping bombs; for firing ammunition
• CPC Class Codes: B64U 2101/31 for surveillance
• CPC Class Codes: B64U 2101/40 for agriculture or forestry operations
• CPC Class Codes: B64U 2101/61 for transporting passengers
• CPC Class Codes: B64U 2101/64 for parcel delivery or retrieval
• CPC Class Codes: B64U 30/293 Foldable or collapsible rotors or rotor supports
• CPC Class Codes: B64U 30/297 Tilting rotors
• CPC Class Codes: B64U 60/40 foldable or retractable

Abstract

In some embodiment, an aircraft includes a flying frame having an airframe, a distributed propulsion system attached to the airframe, the distributed propulsion system including a plurality of propulsion assemblies and a flight control system operably associated with the distributed propulsion system. The flying frame has a vertical takeoff and landing mode and a forward flight mode. The flight control system is operable to independently control the propulsion assemblies. The flight control system is also operable to detect faults in individual propulsion assemblies and to perform corrective action responsive to detected faults at a distributed propulsion system level.

Claims

1. An aircraft comprising:

a flying frame including an airframe;

a distributed propulsion system attached to the airframe, the distributed propulsion system including a plurality of propulsion assemblies; and

a flight control system operably associated with the distributed propulsion system, wherein, the flying frame has a vertical takeoff and landing mode and a forward flight mode;

wherein, the flight control system is operable to independently control the propulsion assemblies; and

wherein, the flight control system is operable to detect faults in individual propulsion assemblies and to perform corrective action responsive to detected faults at a distributed propulsion system level.

2. The aircraft as recited in claim 1 wherein the flight control system further comprises a redundant flight control system.

3. The aircraft as recited in claim 1 wherein the flight control system further comprises a triply redundant flight control system.

4. The aircraft as recited in claim 1 wherein, responsive to a fault detected in a first propulsion assembly, the flight control system shuts down the first propulsion assembly.

5. The aircraft as recited in claim 1 wherein, responsive to a fault detected in a first propulsion assembly, the flight control system shuts down the first propulsion assembly and shuts down a second propulsion assembly.

6. The aircraft as recited in claim 5 wherein the second propulsion assembly is symmetrically disposed on the airframe relative to the first propulsion assembly.

7. The aircraft as recited in claim 1 wherein, responsive to a fault detected in a first propulsion assembly, the flight control system adjusts collective pitch of at least a second propulsion assembly.

8. The aircraft as recited in claim 1 wherein, responsive to a fault detected in a first propulsion assembly, the flight control system adjusts cyclic pitch of at least a second propulsion assembly.

9. The aircraft as recited in claim 1 wherein, responsive to a fault detected in a first propulsion assembly, the flight control system adjusts rotor speed of at least a second propulsion assembly.

10. The aircraft as recited in claim 1 wherein, responsive to a fault detected in a first propulsion assembly, the flight control system adjusts a thrust vector of at least a second propulsion assembly.

11. The aircraft as recited in claim 1 wherein, responsive to a fault detected in a first propulsion assembly, the flight control system turns on at least a second propulsion assembly.

12. The aircraft as recited in claim 1 wherein, responsive to a fault detected in a first propulsion assembly, the flight control system turns on a plurality of second propulsion assemblies.

13. The aircraft as recited in claim 1 wherein, responsive to a fault detected in a first propulsion assembly, the flight control system shuts down the first propulsion assembly, shuts down a symmetrically disposed second propulsion assembly and turns on a plurality of third propulsion assemblies.

14. The aircraft as recited in claim 1 wherein, responsive to a fault detected in a first propulsion assembly, the flight control system commands the distributed propulsion system to return the aircraft to a predetermined location.

15. The aircraft as recited in claim 1 wherein, responsive to a fault detected in a first propulsion assembly, the flight control system commands the distributed propulsion system to perform an emergency landing.

16. The aircraft as recited in claim 1 wherein, responsive to a fault detected in a first propulsion assembly, the flight control system commands the distributed propulsion system to continue a current mission.

17. The aircraft as recited in claim 1 wherein, responsive to a fault detected in a first propulsion assembly, the flight control system initiates a pod assembly jettison sequence.

18. The aircraft as recited in claim 17 wherein, responsive to the pod assembly being jettisoned, the flight control system commands the distributed propulsion system to land the aircraft proximate to the pod assembly.

19. The aircraft as recited in claim 17 wherein, responsive to the pod assembly being jettisoned, the flight control system commands the distributed propulsion system to perform an emergency landing remote from the pod assembly.

20. An aircraft comprising:

a flying frame including an airframe;

a distributed propulsion system attached to the airframe, the distributed propulsion system including a plurality of propulsion assemblies;

a triply redundant flight control system operably associated with the distributed propulsion system; and

a passenger pod assembly selectively attachable to the flying frame, wherein, the flying frame has a vertical takeoff and landing mode and a forward flight mode;

wherein, the flight control system is operable to independently control the propulsion assemblies; and

wherein, the flight control system is operable to detect faults in individual propulsion assemblies and to perform corrective action responsive to detected faults at a distributed propulsion system level.