# US 11,111,010 B2 · Multimodal unmanned aerial systems having tiltable wings > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,111,010 B2 - Document ID: US11111010B2 - Status: Granted - Kind: B2 - Application number: 16/383,884 - Filed: 2019-04-15 - Published: 2020-10-15 - Granted: 2021-09-07 - Earliest claimed: 2019-04-15 - Assignees: Textron Innovations Inc. - Applicants: Textron Innovations Inc. - Inventors: Guy Bernard - Web page: https://patentgrep.com/patent/US11111010B2 ## CPC - B64C 27/26: characterised by provision of fixed wings - B64C 39/12: Canard-type aircraft - B64C 29/02: having its flight directional axis vertical when grounded - B64U 10/20: Vertical take-off and landing [VTOL] aircraft (flying platforms B64U10/13; helicopters B64U10/17) - B64U 30/12: Variable or detachable wings, e.g. wings with adjustable sweep - B64U 30/297: Tilting rotors - B64U 40/10: for adjusting control surfaces or rotors - B64U 20/30: for safety, e.g. with frangible components (rotor guards B64U30/299) - B64U 50/19: using electrically powered motors - B64U 2201/104: using satellite radio beacon positioning systems, e.g. GPS - B64C: AEROPLANES; HELICOPTERS - B64U: UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR ## 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. ## Claims ### Claim 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; and wherein, the fuselage, the control wing and the primary wing are configured to synchronously rotate into an aftward flight mode, the control wing trailing the primary wing in the aftward flight mode. ### Claim 2 (depends on 1) 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. ### Claim 3 (depends on 1) 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. ### Claim 4 (depends on 1) The multimodal unmanned aerial system as recited in claim 1 wherein the fuselage further comprises a battery configured to power the propulsion assemblies. ### Claim 5 (depends on 1) 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. ### Claim 6 (depends on 1) 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. ### Claim 7 (depends on 1) 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. ### Claim 8 (depends on 1) 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. ### Claim 9 (depends on 1) The multimodal unmanned aerial system as recited in claim 1 wherein the control wing and the primary wing further comprise straight wings. ### Claim 10 (depends on 1) 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. ### Claim 11 (depends on 1) 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. ### Claim 12 (depends on 1) 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. ### Claim 13 (depends on 1) 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. ### Claim 14 (depends on 1) The multimodal unmanned aerial system as recited in claim 1 wherein the fuselage, the control wing and the primary wing are substantially horizontal in the aftward flight mode. ### Claim 15 (depends on 1) 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. ### Claim 16 (depends on 1) 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. ### Claim 17 (depends on 1) 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. ### Claim 18 (depends on 1) The multimodal unmanned aerial system as recited in claim 1 further comprising a releasable payload receivable in the payload bay. ### Claim 19 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, the control wing trailing the primary wing in the aftward flight mode.