Multimodal Unmanned Aerial Systems Having Tiltable Wings

Patent metadata

Field	Value
Publication number	US-2020324885-A1
Application number	US-201916383884-A
Country	US
Kind code	A1
Filing date	Apr 15, 2019
Priority date	Apr 15, 2019
Publication date	Oct 15, 2020
Grant date	—

Abstract

A multimodal unmanned aerial system includes a fuselage forming a payload bay, a control wing forward of the fuselage including a first plurality of propulsion assemblies and a primary wing aft of the fuselage including a second plurality of propulsion assemblies. The primary wing has a greater wingspan than the control wing. The multimodal unmanned aerial system includes linkages rotatably coupling the fuselage to the control wing and the primary wing. The fuselage, the control wing and the primary wing are configured to synchronously rotate between a vertical takeoff and landing flight mode and a forward flight mode. The fuselage, the control wing and the primary wing are substantially vertical in the vertical takeoff and landing flight mode and substantially horizontal in the forward flight mode.

First claim

What is claimed is:

1 . A multimodal unmanned aerial system comprising:
a fuselage forming a payload bay; a control wing forward of the fuselage including a first plurality of propulsion assemblies; a primary wing aft of the fuselage including a second plurality of propulsion assemblies, the primary wing having a greater wingspan than the control wing; and a plurality of linkages rotatably coupling the fuselage to the control wing and the primary wing; wherein, the fuselage, the control wing and the primary wing are configured to synchronously rotate between a vertical takeoff and landing flight mode and a forward flight mode, the fuselage, the control wing and the primary wing substantially vertical in the vertical takeoff and landing flight mode and substantially horizontal in the forward flight mode.

2 . The multimodal unmanned aerial system as recited in claim 1 wherein the fuselage includes an underside facing the control wing and a topside facing the primary wing in the vertical takeoff and landing flight mode.

3 . The multimodal unmanned aerial system as recited in claim 1 wherein the fuselage further comprises a conversion motor configured to rotate at least one of the plurality of linkages to transition the fuselage, the control wing and the primary wing between the vertical takeoff and landing flight mode and the forward flight mode.

4 . The multimodal unmanned aerial system as recited in claim 1 wherein the fuselage further comprises a battery configured to power the propulsion assemblies.

5 . The multimodal unmanned aerial system as recited in claim 1 wherein the control wing and the primary wing each further comprise a plurality of movable control surfaces.

6 . The multimodal unmanned aerial system as recited in claim 1 wherein aft edges of the fuselage, the control wing and the primary wing include a plurality of landing members.

7 . The multimodal unmanned aerial system as recited in claim 1 wherein the control wing and the primary wing are forwardly and aftwardly tiltable in the vertical takeoff and landing flight mode to permit thrust vectoring.

8 . The multimodal unmanned aerial system as recited in claim 1 wherein the control wing further comprises an anhedral wing and the primary wing further comprises a dihedral wing in the forward flight mode.

9 . The multimodal unmanned aerial system as recited in claim 1 wherein the control wing and the primary wing further comprise straight wings.

10 . The multimodal unmanned aerial system as recited in claim 1 wherein the primary wing is positioned higher than the control wing in the forward flight mode.

11 . The multimodal unmanned aerial system as recited in claim 1 wherein the fuselage, the control wing and the primary wing are rotatable in a range of motion of at least 90 degrees.

12 . The multimodal unmanned aerial system as recited in claim 1 wherein the fuselage, the control wing and the primary wing are rotatable in a range of motion of approximately 180 degrees.

13 . The multimodal unmanned aerial system as recited in claim 1 wherein the fuselage, the control wing and the primary wing transition between the vertical takeoff and landing flight mode and the forward flight mode using a differential thrust between the first plurality of propulsion assemblies on the control wing and the second plurality of propulsion assemblies on the primary wing.

14 . The multimodal unmanned aerial system as recited in claim 1 wherein the fuselage, the control wing and the primary wing are further configured to synchronously rotate into an aftward flight mode, the control wing trailing the primary wing in the aftward flight mode.

15 . The multimodal unmanned aerial system as recited in claim 14 wherein the fuselage, the control wing and the primary wing are substantially horizontal in the aftward flight mode.

16 . The multimodal unmanned aerial system as recited in claim 1 wherein the plurality of linkages further comprise an upper linkage and a lower linkage, the upper and lower linkages substantially parallel in both the vertical takeoff and landing flight mode and the forward flight mode.

17 . The multimodal unmanned aerial system as recited in claim 1 wherein the plurality of linkages further comprise an upper linkage and a lower linkage, the upper and lower linkages substantially horizontal in both the vertical takeoff and landing flight mode and the forward flight mode.

18 . The multimodal unmanned aerial system as recited in claim 1 wherein the plurality of linkages further comprise a plurality of upper linkages and a plurality of lower linkages rotatably coupled to lateral sides of the fuselage.

19 . The multimodal unmanned aerial system as recited in claim 1 further comprising a releasable payload receivable in the payload bay.

20 . A rotorcraft comprising:
a fuselage forming a payload bay; a control wing forward of the fuselage including a first plurality of proprotor assemblies; a primary wing aft of the fuselage including a second plurality of proprotor assemblies, the primary wing having a greater wingspan than the control wing; and a plurality of linkages rotatably coupling the fuselage to the control wing and the primary wing; wherein the fuselage, the control wing and the primary wing are rotatable in a range of motion of approximately 180 degrees; and wherein, the fuselage, the control wing and the primary wing are configured to synchronously rotate between a vertical takeoff and landing flight mode, a forward flight mode and an aftward flight mode, the fuselage, the control wing and the primary wing substantially vertical in the vertical takeoff and landing flight mode and substantially horizontal in the forward flight mode and the aftward flight mode.

Assignees

• Bell Textron Inc

Inventors

• Bernard Guy

Classifications

• B64U2201/104

  using satellite radio beacon positioning systems, e.g. GPS · CPC title

• B64U30/12

  Variable or detachable wings, e.g. wings with adjustable sweep · CPC title

• B64U30/297

  Tilting rotors · CPC title

• B64U40/10

  for adjusting control surfaces or rotors · CPC title

• B64U50/19

  using electrically powered motors · CPC title