Aircraft having a versatile propulsion system

• US 10,501,193 B2
• Filed: 05/26/2017
• Issued: 12/10/2019
• Est. Priority Date: 07/01/2016
• Status: Active Grant

• Current Assignee: Textron Innovations Incorporated (Textron Inc)
• Original Assignee: Textron Innovations Incorporated (Textron Inc)
• Inventors: Oldroyd, Paul K., McCullough, John Richard
• Primary Examiner(s): Freeman, Joshua E
• Application Number:
  US15/606,242
• Publication Number:
  US 20180002026A1
• Time in Patent Office: 928 Days
• Field of Search: 244 124
• CPC Class Codes: B64C 11/46 Arrangements of, or constructional features peculiar to, multiple propellers B64C11/306 takes precedence
• CPC Class Codes: B64C 2211/00 Modular constructions of airplanes or helicopters
• 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: B64D 27/026 comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine Hybrid electric aircraft B64D27/33
• CPC Class Codes: B64D 27/06 within, or attached to, wings
• CPC Class Codes: B64D 27/12 within, or attached to, wings
• CPC Class Codes: B64D 27/24 using steam or spring force jet aircraft B64D27/16
• CPC Class Codes: B64D 27/40 Arrangements for mounting power plants in aircraft
• CPC Class Codes: B64D 31/00 Power plant control systems; Arrangement of power plant control systems in aircraft
• CPC Class Codes: B64D 35/08 characterised by the transmission being driven by a plurality of power plants
• CPC Class Codes: B64U 10/20 Vertical take-off and landing [VTOL] aircraft flying platforms B64U10/13; helicopters B64U10/17
• CPC Class Codes: B64U 20/40 Modular UAVs
• CPC Class Codes: B64U 2101/61 for transporting passengers
• CPC Class Codes: B64U 30/10 Wings
• CPC Class Codes: B64U 50/11 using internal combustion piston engines
• CPC Class Codes: B64U 50/19 using electrically powered motors
• CPC Class Codes: B64U 70/60 Take-off or landing of UAVs from a runway using their own power
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An aircraft having a vertical takeoff and landing fight mode and a forward flight mode. The aircraft includes an airframe and a versatile propulsion system attached to the airframe. The versatile propulsion system includes a plurality of propulsion assemblies. A flight control system is operable to independently control the propulsion assemblies. The propulsion assemblies are interchangeably attachable to the airframe such that the aircraft has a liquid fuel flight mode and an electric flight mode. In the liquid fuel flight mode, energy is provided to each of the propulsion assemblies from a liquid fuel. In the electric flight mode, energy is provided to each of the propulsion assemblies from an electric power source.

Claims

1. An aircraft having a vertical takeoff and landing fight mode and a forward flight mode, the aircraft comprising:

an airframe;

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

a flight control system operable to independently control the propulsion assemblies;

wherein, the propulsion assemblies are interchangeably attachable to the airframe such that the aircraft has a liquid fuel flight mode and an electric flight mode;

wherein, in the liquid fuel flight mode, energy is provided to each of the propulsion assemblies from a liquid fuel; and

wherein, in the electric flight mode, energy is provided to each of the propulsion assemblies from an electric power source.

2. The aircraft as recited in claim 1 wherein each of the propulsion assemblies further comprises:

a nacelle operable to be coupled to the airframe;

an engine disposed within the nacelle;

a rotor hub mechanically coupled to the engine and operable to rotate responsive to operation of the engine; and

a proprotor mechanically coupled to the rotor hub and operable to rotate therewith.

3. The aircraft as recited in claim 2 wherein each of the propulsion assemblies further comprises at least one liquid fuel tank disposed within the nacelle operable to contain the liquid fuel.

4. The aircraft as recited in claim 3 wherein each of the engines further comprises an internal combustion engine.

5. The aircraft as recited in claim 2 wherein each of the propulsion assemblies further comprises at least one battery disposed within the nacelle.

6. The aircraft as recited in claim 5 wherein each of the engines further comprises an electric motor.

7. The aircraft as recited in claim 1 further comprising a mixed flight mode wherein energy is provided to at least one of the propulsion assemblies from the liquid fuel and energy is provided to at least another of the propulsion assemblies from the electric power source.

8. The aircraft as recited in claim 1 further comprising a distributed power system.

9. The aircraft as recited in claim 1 further comprising a shared power system.

10. The aircraft as recited in claim 1 wherein each of the propulsion assemblies further comprises a line replaceable unit.

11. The aircraft as recited in claim 1 wherein each of the propulsion assemblies further comprises an electronics node in communication with the flight control system, each of the electronics nodes operable to control operations of the respective propulsion assembly.

12. The aircraft as recited in claim 1 wherein the flight control system further comprises at least one of a redundant flight control system and a triply redundant flight control system.

13. The aircraft as recited in claim 1 wherein the flight control system commands operation of the propulsion assemblies responsive to at least one of onboard pilot flight control, remote flight control, autonomous flight control and combinations thereof.

14. The aircraft as recited in claim 1 further comprising a pod assembly selectively attachable to the airframe.

15. The aircraft as recited in claim 1 further comprising a passenger pod assembly rotatably attachable to the airframe such that the passenger pod assembly remains in a generally horizontal attitude in the vertical takeoff and landing fight mode, the forward flight mode and transitions therebetween.

16. The aircraft as recited in claim 1 wherein the airframe further comprises first and second wings;

wherein, in the vertical takeoff and landing mode, the first wing is forward of the pod assembly and the second wing is aft of the pod assembly; and

wherein, in the forward flight mode, the first wing is below the pod assembly and the second wing is above the pod assembly.

17. The aircraft as recited in claim 1 wherein the airframe further comprises first and second wings;

wherein, in the vertical takeoff and landing mode, the first and second wings are above the pod assembly; and

wherein, in the forward flight mode, the first wing is below the pod assembly and the second wing is above the pod assembly.