# US 11,897,601 B2 · Aircraft and methods of use for aerodynamic control with winglet surfaces > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,897,601 B2 - Document ID: US11897601B2 - Status: Granted - Kind: B2 - Application number: 17/672,860 - Filed: 2022-02-16 - Published: 2023-08-17 - Granted: 2024-02-13 - Earliest claimed: 2022-02-16 - Assignees: JetZero, Inc. - Applicants: JETZERO, Inc. - Inventors: Mark Allan Page; Blaine Knight Rawdon - Web page: https://patentgrep.com/patent/US11897601B2 ## CPC - B64C 23/076: {the wing tip airfoil devices comprising one or more separate moveable members thereon affecting the vortices, e.g. flaps} - B64C 9/06: with two or more independent movements - B64C 39/10: All-wing aircraft - B64D 27/14: within, or attached to, fuselages - B64C 13/24: Transmitting means - B64C 2039/105: {of blended wing body type} - Y02T 50/10: Drag reduction - B64C: AEROPLANES; HELICOPTERS - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract Aspects relate to aircraft and methods of use for aerodynamic control with winglet surfaces. In an aspect an exemplary aircraft includes a first wing having a first winglet at a distal end of the wing, wherein the first winglet comprises at least a first control surface at a first trailing edge of the first winglet and a second wing having a second winglet at a distal end of the wing, wherein the second winglet comprises at least a second control surface at a second trailing edge of the second winglet. ## Claims ### Claim 1 An aircraft for transonic flight comprising: a fuselage extending to a back portion lacking a vertical tailfin, wherein the back portion comprises a first main body control surface and a second main body control surface; a propulsor configured to generate thrust; a first substantially swept wing having a first winglet disposed beyond the back portion of the fuselage, the first winglet comprising a carbon-fiber composite with carbon fibers between 5-10 micrometers at a distal end of the wing, wherein the first winglet comprises at least a first control surface including a first trailing edge of the first winglet, wherein the fuselage and a leading edge of the first substantially swept wing creates a continuous curvilinear geometry; a second substantially swept wing having a second winglet disposed beyond the back portion of the fuselage, the second winglet comprising a carbon-fiber composite with carbon fibers between 5-10 micrometers at a distal end of the wing, wherein the second winglet comprises at least a second control surface including a second trailing edge of the second winglet, wherein the fuselage and a leading edge of the second substantially swept wing creates a continuous curvilinear geometry; wherein the at least a first control surface and the at least a second control surface are independently movable and the at least a first control surface and the at least a second control surface each comprise at least two control surface segments, wherein each of the at least two control surface segments are independently positioned; a first actuator configured to move the at least first control surface; and a second actuator configured to move the at least second control surface, wherein an actuator of the first actuator and second actuator comprises a pneumatic actuator. ### Claim 2 (depends on 1) The aircraft of claim 1, further comprising a blended wing body. ### Claim 3 (depends on 1) The aircraft of claim 1, wherein the at least a first control surface and the at least a second control surface each comprise a rudder. ### Claim 4 (depends on 1) The aircraft of claim 1, further comprising: at least a first actuator configured to move the at least a first control surface; at least a second actuator configured to move the at least a second control surface; and a controller configured to control each of the at least a first actuator and the at least a second actuator. ### Claim 5 (depends on 4) The aircraft of claim 4, wherein the controller is further configured to control each of the at least a first actuator and the at least a second actuator to reduce drag using the at least a first control surface and the at least a second control surface. ### Claim 6 (depends on 4) The aircraft of claim 4, wherein the controller is further configured to control one or more of the at least a first actuator and the at least a second actuator to introduce a yaw moment using one or more of the at least a first control surface and the at least a second control surface. ### Claim 7 (depends on 4) The aircraft of claim 4, wherein the controller is further configured to control one or more of the at least a first actuator and the at least a second actuator to introduce a side force using one or more of the at least a first control surface and the at least a second control surface. ### Claim 8 (depends on 4) The aircraft of claim 4, wherein the controller is further configured to control each of the at least a first actuator and the at least a second actuator to adjust wing bending using the at least a first control surface and the at least a second control surface. ### Claim 9 (depends on 4) The aircraft of claim 4, wherein the controller is further configured to control each of the at least a first actuator and the at least a second actuator to increase drag using the at least a first control surface and the at least a second control surface. ### Claim 10 (depends on 9) The aircraft of claim 9, wherein: the at least a first control surface and the at least a second control surface each comprise at least two control surface segments; and the controller is further configured to increase drag by moving the at least two control surface segments in opposite directions. ### Claim 11 A method of using an aircraft for transonic flight comprising a fuselage extending to a back portion lacking a vertical tailfin, wherein the back portion comprises a first main body control surface and a second main body control surface; a propulsor configured to generate thrust; a first substantially swept wing having a first winglet extending beyond the back portion of the fuselage, the first winglet comprising a carbon-fiber composite with carbon fibers between 5-10 micrometers at a distal end of the wing, wherein the first winglet comprises at least a first control surface including a first trailing edge of the first winglet, wherein the fuselage and a leading edge of the first substantially swept wing creates a continuous curvilinear geometry and a second substantially swept wing having a second winglet extending beyond the back portion of the fuselage, the second winglet comprising a carbon-fiber composite with carbon fibers between 5-10 micrometers at a distal end of the wing, wherein the second winglet comprises at least a second control surface including a second trailing edge of the second winglet, wherein the fuselage and a leading edge of the second substantially swept wing creates a continuous curvilinear geometry, wherein the at least a first control surface and the at least a second control surface are independently movable and the at least a first control surface and the at least a second control surface each comprise at least two control surface segments, wherein each of the at least two control surface segments are independently positioned, the method comprising: driving, by a controller incorporated in the aircraft, at least a first actuator to move the at least a first control surface; driving, by the controller, at least a second actuator to move the at least a second control surface; and wherein an actuator of the at least first actuator and the at least second actuator comprises a pneumatic actuator. ### Claim 12 (depends on 11) The method of claim 11, wherein driving the at least a first actuator and the at least a second actuator further comprises driving each of the at least a first actuator and the at least a second actuator to reduce drag. ### Claim 13 (depends on 11) The method of claim 11, further comprising driving, using the controller, one or more of the at least a first actuator and the at least a second actuator to move one or more of the at least a first control surface and the at least a second control surface to introduce a yaw moment. ### Claim 14 (depends on 11) The method of claim 11, further comprising driving, using the controller, one or more of the at least a first actuator and the at least a second actuator to move one or more of the at least a first control surface and the at least a second control surface to introduce a side force. ### Claim 15 (depends on 11) The method of claim 11, further comprising driving, using the controller, the at least a first actuator and the at least a second actuator to move the at least a first control surface and the at least a second control surface to increase drag. ### Claim 16 (depends on 11) The method of claim 11, further comprising driving, using the controller, the at least a first actuator and the at least a second actuator to move the at least a first control surface and the at least a second control surface to adjust wing bending. ### Claim 17 (depends on 11) The method of claim 11, further comprising, driving, using the controller, the at least a first actuator and the at least a second actuator to move the at least a first control surface and the at least a second control surface to increase drag. ### Claim 18 (depends on 17) The method of claim 17, wherein the method further comprises driving, by the controller, at least one of the at least a first actuator and the at least a second actuator to move the at least two control surface segments in opposite directions and increase drag. ### Claim 19 (depends on 1) The aircraft of claim 1, wherein the fuselage comprises a nose portion, wherein the nose portion comprises a cockpit. ### Claim 20 (depends on 19) The aircraft of claim 19, wherein the nose portion of the fuselage and a leading edge of a substantially swept wing creates a continuous curvilinear geometry.