Aircraft with Independently Controllable Propulsion Assemblies

Patent metadata

Field	Value
Publication number	US-2018002012-A1
Application number	US-201615200182-A
Country	US
Kind code	A1
Filing date	Jul 1, 2016
Priority date	Jul 1, 2016
Publication date	Jan 4, 2018
Grant date	—

Abstract

In some embodiments, an aircraft includes a flying frame having an airframe, a distributed propulsion system attached to the airframe, a flight control system operably associated with the distributed propulsion system and a pod assembly selectively attachable to the flying frame. The distributed propulsion system includes a plurality of propulsion assemblies that are independently controlled by the flight control system, thereby enabling the flying frame to have a vertical takeoff and landing mode and a forward flight mode.

First claim

What is claimed is:

1 . An aircraft comprising:
a flying frame including an airframe having first and second wing members with pylons extending therebetween; a distributed propulsion system attached to the airframe, the distributed propulsion system including a plurality of propulsion assemblies; a flight control system operably associated with the distributed propulsion system and operable to independently control the propulsion assemblies; and a pod assembly selectively attachable to the flying frame, wherein, the flying frame has a vertical takeoff and landing mode and a forward flight mode.

2 . The aircraft as recited in claim 1 wherein, in the vertical takeoff and landing mode, the distributed propulsion system is generally above the pod assembly and wherein, in the forward flight mode, the distributed propulsion system is generally forward of the pod assembly.

3 . The aircraft as recited in claim 1 wherein the propulsion assemblies are attached to the airframe in a mid wing configuration.

4 . The aircraft as recited in claim 1 wherein the propulsion assemblies are attached to the airframe in a high wing configuration.

5 . The aircraft as recited in claim 1 wherein, in the vertical takeoff and landing mode, the first wing member is forward of the pod assembly and the second wing member is aft of the pod assembly and wherein, in the forward flight mode, the first wing member is below the pod assembly and the second wing member is above the pod assembly.

6 . The aircraft as recited in claim 1 wherein the plurality of propulsion assemblies further comprises a plurality of first propulsion assemblies having proprotors that rotate clockwise and a plurality of second propulsion assemblies having proprotors that rotate counterclockwise.

7 . The aircraft as recited in claim 1 wherein the plurality of propulsion assemblies further comprises a plurality of first propulsion assemblies utilized in the forward flight mode and a plurality of second propulsion assemblies operable to be shut down in the forward flight mode.

8 . The aircraft as recited in claim 7 wherein the plurality of first propulsion assemblies further comprises outboard propulsion assemblies and the plurality of second propulsion assemblies further comprises inboard propulsion assemblies.

9 . The aircraft as recited in claim 7 wherein the plurality of second propulsion assemblies further comprise proprotors having folding blades that are operable for passive folding in the forward flight mode.

10 . The aircraft as recited in claim 7 wherein the plurality of second propulsion assemblies further comprise proprotors having blades that are operable to be feathered and locked to prevent rotation in the forward flight mode.

11 . The aircraft as recited in claim 7 wherein the plurality of second propulsion assemblies further comprise proprotors having blades that are operable to be feathered and allowed to windmill in the forward flight mode.

12 . The aircraft as recited in claim 1 wherein the plurality of propulsion assemblies further comprises a plurality of thrust vectoring propulsion assemblies.

13 . The aircraft as recited in claim 12 wherein the thrust vectoring propulsion assemblies further comprise outboard propulsion assemblies.

14 . The aircraft as recited in claim 1 wherein the distributed propulsion system further comprises a distributed fuel system.

15 . The aircraft as recited in claim 1 wherein each of the plurality of propulsion assemblies further comprise a nacelle, an engine, a drive system, a rotor hub, a proprotor and an electronics node.

16 . A method of operating an aircraft comprising:
providing a flying frame including an airframe, a distributed propulsion system attached to the airframe and a flight control system operably associated with the distributed propulsion system; selectively attaching the flying frame to a pod assembly; independently controlling a plurality of propulsion assemblies of the distributed propulsion system with the flight control system; lifting the pod assembly into the air in a vertical takeoff and landing mode of the aircraft; transitioning the aircraft between the vertical takeoff and landing mode and a forward flight mode; and transporting the pod assembly in the forward flight mode of the aircraft.

17 . The method as recited in claim 16 wherein independently controlling the plurality of propulsion assemblies of the distributed propulsion system with the flight control system further comprises independently controlling rotational velocity of proprotors of the propulsion assemblies.

18 . The method as recited in claim 16 wherein independently controlling the plurality of propulsion assemblies of the distributed propulsion system with the flight control system further comprises independently controlling collective pitch of proprotors of the propulsion assemblies.

19 . The method as recited in claim 16 wherein independently controlling the plurality of propulsion assemblies of the distributed propulsion system with the flight control system further comprises independently controlling thrust vectors of the propulsion assemblies.

20 . The method as recited in claim 16 wherein independently controlling the plurality of propulsion assemblies of the distributed propulsion system with the flight control system further comprises operating a plurality of first propulsion assemblies of the distributed propulsion system in the forward flight mode and shutting down a plurality of second propulsion assemblies of the distributed propulsion system in the forward flight mode.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Mccullough John Richard
• Oldroyd Paul K

Classifications

• B64U2201/10

  autonomous, i.e. by navigating independently from ground or air stations, e.g. by using inertial navigation systems [INS] · CPC title

• B64C11/46

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

• B64C25/10

  retractable, foldable, or the like · CPC title

• B64C11/28

  Collapsible or foldable blades · CPC title

• B64C29/0033 Primary

  the propellers being tiltable relative to the fuselage · CPC title