Aircraft having a versatile propulsion system

Patent metadata

Field	Value
Publication number	US-10501193-B2
Application number	US-201715606242-A
Country	US
Kind code	B2
Filing date	May 26, 2017
Priority date	Jul 1, 2016
Publication date	Dec 10, 2019
Grant date	Dec 10, 2019

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.

First claim

What is claimed is:

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.

Assignees

• Textron Innovations Inc

Inventors

• Oldroyd Paul K
• Mccullough John Richard

Classifications

• B64U70/60

  Take-off or landing of UAVs from a runway using their own power · CPC title

• B64C11/46

  Arrangements of, or constructional features peculiar to, multiple propellers {(B64C11/306 takes precedence)} · CPC title

• B64C29/0033

  the propellers being tiltable relative to the fuselage · CPC title

• B64D27/06

  within, or attached to, wings · CPC title

• B64C2211/00

  Modular constructions of airplanes or helicopters · CPC title