# US 11,897,610 B2 · Quiet aerial vehicle > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,897,610 B2 - Document ID: US11897610B2 - Status: Granted - Kind: B2 - Application number: 17/320,357 - Filed: 2021-05-14 - Published: 2022-11-03 - Granted: 2024-02-13 - Earliest claimed: 2020-09-04 - Assignees: The Boeing Company - Applicants: The Boeing Company - Inventors: Keith A. Etling; Hilary G. Knight - Web page: https://patentgrep.com/patent/US11897610B2 ## CPC - B64C 39/12: Canard-type aircraft - B64C 1/0009: {Aerodynamic aspects} - B64C 1/16: specially adapted for mounting power plant - B64D 33/02: of combustion air intakes - B64D 33/06: {Silencing exhaust or propulsion jets} - B64U 10/25: Fixed-wing aircraft (VTOL aircraft B64U10/20) - B64U 20/20: for noise reduction - B64C 2001/0045: {Fuselages characterised by special shapes} - B64D 2033/0206: {comprising noise reduction means, e.g. acoustic liners} - B64U 2101/31: for surveillance - 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 - B64U: UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR ## Abstract An aerial vehicle including a main body having a leading edge. An inlet is recessed aft from the leading edge. Forward protrusions extend from the main body on opposite sides of the inlet. An outlet nozzle is proximate to an aft end. The inlet is in fluid communication with the outlet nozzle. Wings extend from the main body. ## Claims ### Claim 1 An aerial vehicle comprising: a main body having a leading edge, an inlet recessed aft from the leading edge; forward protrusions extending from the main body on opposite sides of the inlet; an outlet nozzle proximate to an aft end of the main body, wherein the inlet is in fluid communication with the outlet nozzle; wings extending from the aft end of the main body; and canards extending from a fore end of the main body. ### Claim 2 (depends on 1) The aerial vehicle of claim 1, wherein the aerial vehicle is an unmanned aerial vehicle (UAV). ### Claim 3 (depends on 1) The aerial vehicle of claim 1, wherein the main body comprises a base having a flat forward upper surface. ### Claim 4 (depends on 1) The aerial vehicle of claim 1, wherein at least portions of the canards extend to a plane that is aft of the inlet. ### Claim 5 (depends on 1) The aerial vehicle of claim 1, wherein at least one of the forward protrusions extends either above or below a height of the inlet. ### Claim 6 (depends on 1) The aerial vehicle of claim 1, wherein the forward protrusions form an entrance to the inlet, wherein the entrance is configured to direct airflow into the inlet. ### Claim 7 (depends on 1) The aerial vehicle of claim 1, wherein the inlet has a width and a height, wherein an aspect ratio is defined as a ratio of the width to the height, and wherein the aspect ratio is between 3 and 7. ### Claim 8 (depends on 7) The aerial vehicle of claim 7, wherein the aspect ratio is between 4.9 and 5.1. ### Claim 9 (depends on 1) The aerial vehicle of claim 1, wherein the inlet is recessed from the leading edge a distance that is between 1 to 5 times a height of the inlet. ### Claim 10 (depends on 9) The aerial vehicle of claim 9, wherein the distance is between 2.9 and 3.0 times the height of the inlet. ### Claim 11 (depends on 1) The aerial vehicle of claim 1, further comprising: an inlet duct within the main body, wherein the inlet provides an opening into the inlet duct; a propulsor within the main body and in fluid communication with the inlet duct; and an outlet duct within the main body and in fluid communication with the propulsor, wherein the outlet duct includes the outlet nozzle. ### Claim 12 A method of forming an aerial vehicle, the method comprising: recessing an inlet aft from a leading edge of a main body; extending forward protrusions from the main body on opposite sides of the inlet; extending canards from a fore end of the main body; fluidly coupling an outlet nozzle proximate to an aft end of the main body to the inlet; and extending wings from the aft end of the main body. ### Claim 13 (depends on 12) The method of claim 12, wherein at least portions of the canards extend to a plane that is aft of the inlet. ### Claim 14 (depends on 12) The method of claim 12, wherein at least one of the forward protrusions extends either above or below a height of the inlet, wherein the forward protrusions form an entrance to the inlet, and wherein the entrance is configured to direct airflow into the inlet. ### Claim 15 (depends on 12) The method of claim 12, wherein the inlet has a width and a height, wherein an aspect ratio is defined as a ratio of the width to the height, and wherein the aspect ratio is between 3 and 7. ### Claim 16 (depends on 12) The method of claim 12, wherein the inlet is recessed from the leading edge a distance that is between 1 to 5 times a height of the inlet. ### Claim 17 An unmanned aerial vehicle (UAV) comprising: a main body having a leading edge, wherein the main body comprises a base having a flat forward upper surface; an inlet recessed aft from the leading edge a distance that is between 1 to 5 times a height of the inlet, wherein an aspect ratio is defined as a ratio of a width to the height of the inlet, and wherein the aspect ratio is between 3 and 7; forward protrusions extending from the main body on opposite sides of the inlet, wherein at least one of the forward protrusions extends either above or below the height of the inlet, and wherein the forward protrusions form an entrance to the inlet; an outlet nozzle proximate to an aft end of the main body, wherein the inlet is in fluid communication with the outlet nozzle; wings extending from the aft end of the main body; and canards extending from a fore end of the main body, wherein at least portions of the canards extend to a plane that is aft of the inlet. ### Claim 18 An aerial vehicle comprising: a main body having a leading edge, an inlet recessed aft from the leading edge; forward protrusions extending from the main body on opposite sides of the inlet, wherein at least one of the forward protrusions extends either above or below a height of the inlet; an outlet nozzle proximate to an aft end of the main body, wherein the inlet is in fluid communication with the outlet nozzle; and wings extending from the main body. ### Claim 19 An aerial vehicle comprising: a main body having a leading edge, an inlet recessed aft from the leading edge; forward protrusions extending from the main body on opposite sides of the inlet, wherein the forward protrusions form an entrance to the inlet, and wherein the entrance is configured to direct airflow into the inlet; an outlet nozzle proximate to an aft end of the main body, wherein the inlet is in fluid communication with the outlet nozzle; and wings extending from the main body. ### Claim 20 An aerial vehicle comprising: a main body having a leading edge, an inlet recessed aft from the leading edge, wherein the inlet is recessed from the leading edge a distance that is between 1 to 5 times a height of the inlet; forward protrusions extending from the main body on opposite sides of the inlet; an outlet nozzle proximate to an aft end of the main body, wherein the inlet is in fluid communication with the outlet nozzle; and wings extending from the main body. ### Claim 21 (depends on 20) The aerial vehicle of claim 20, wherein the distance is between 2.9 and 3.0 times the height of the inlet.