[특허]Methods and apparatus for robust lift generation

The Boeing Company

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Methods and apparatus for robust lift generation

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-021/08 B64C-021/04 B64C-009/38
출원번호	US-0667043 (2015-03-24)
등록번호	US-9714082 (2017-07-25)
발명자 / 주소	Shmilovich, Arvin Yadlin, Yoram
출원인 / 주소	The Boeing Company
대리인 / 주소	Hanley, Flight & Zimmerman, LLC
인용정보	피인용 횟수 : 1 인용 특허 : 16

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Apparatus and methods for robust lift generation through flow separation suppression are disclosed. One example apparatus includes a cowling extending from a surface of a fluid dynamic body to provide an exhaust stream directed over the fluid dynamic body. The example apparatus also includes a fluid ejection slot proximate or on the fluid dynamic body, where the fluid ejection slot is to direct a compressed fluid along a surface of the fluid dynamic body. The example apparatus also includes rotatable vanes having blunt leading edges, where the vanes are ...

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1. An apparatus comprising: a cowling extending from a surface of a fluid dynamic body to provide an exhaust stream directed over the fluid dynamic body;a fluid ejection slot proximate or on the fluid dynamic body, the fluid ejection slot to direct a compressed fluid along a surface of the fluid dynamic body; androtatable vanes having blunt leading edges, the vanes proximate the fluid ejection slot to direct the compressed fluid to affect attachment of the exhaust stream to the fluid dynamic body to enhance lift, wherein the vanes are arranged in a pattern extending along a span-wise length of the fluid dynamic body, and wherein the vanes are to rotate about axes that are substantially perpendicular to the span-wise length to move a flow direction of the compressed fluid over the surface of the fluid dynamic body. 2. The apparatus as defined in claim 1, further comprising a controller to control the rotatable vanes and a flow of the compressed fluid through the fluid ejection slot. 3. The apparatus as defined in claim 2, wherein the controller controls the rotatable vanes and the flow based on operating conditions of an aircraft comprising the fluid dynamic body. 4. An apparatus comprising: a cowling extending from a surface of a fluid dynamic body to provide an exhaust stream directed over the fluid dynamic body;a fluid ejection slot proximate or on the fluid dynamic body, the fluid ejection slot to direct a compressed fluid along a surface of the fluid dynamic body; androtatable vanes having blunt leading edges, the vanes proximate the fluid ejection slot to direct the compressed fluid to affect attachment of the exhaust stream to the fluid dynamic body to enhance lift, wherein the rotatable vanes are arranged in an offset pattern to reduce flow blockage around the rotatable vanes. 5. The apparatus as defined in claim 4, wherein some of the rotatable vanes are rotated together. 6. The apparatus as defined in claim 1, wherein the rotatable vanes comprise a first distance from leading edges of the vanes to pivot points of the rotatable vanes and a second distance from the pivot points to trailing edges of the rotatable vanes, and wherein the second distance is greater than the first distance. 7. The apparatus as defined in claim 1, wherein the rotatable vanes comprise a narrowing trailing edge. 8. An apparatus comprising: a cowling extending from a fluid dynamic body to provide an exhaust stream directed over the fluid dynamic body;fluid ejection openings to direct a compressed fluid along a surface of the fluid dynamic body;a sleeve proximate the fluid ejection openings; andan actuator to move the sleeve in a periodic motion to cause the fluid to exit one or more of the fluid ejection openings at varying amounts to affect attachment of the exhaust stream to the fluid dynamic body to enhance lift. 9. The apparatus as defined in claim 8, wherein the sleeve comprises a cylinder, a rectangular block or a contoured block. 10. The apparatus as defined in claim 9, wherein the cylinder comprises a first cylinder and a second cylinder disposed within the first cylinder. 11. The apparatus as defined in claim 10, wherein the second cylinder receives the fluid and comprises a slot to allow the fluid received from a fluid source to flow through the slot toward one or more of the fluid ejection openings when the first cylinder is at one or more positions of the periodic motion. 12. The apparatus as defined in claim 8, wherein the fluid ejection openings comprise slots. 13. The apparatus as defined in claim 8, wherein the fluid comprises a pulsed compressible fluid. 14. The apparatus as defined in claim 8, wherein the actuator comprises a linear actuator. 15. A method comprising: providing an exhaust stream over a surface of a fluid dynamic body;directing a compressible fluid flow from fluid ejection openings to the surface;periodically varying amounts of the flows exiting the fluid ejection openings by varying a degree to which the openings are blocked to affect attachment of the exhaust stream to the fluid dynamic body to enhance lift; andcontrolling a period during which the flows exiting the openings is varied based on operating conditions of an aircraft. 16. A method comprising: providing an exhaust stream over a surface of a fluid dynamic body;directing a compressible fluid flow from fluid ejection openings to the surface;periodically varying amounts of the flows exiting the fluid ejection openings by varying a degree to which the openings are blocked to affect attachment of the exhaust stream to the fluid dynamic body to enhance lift, wherein the compressible fluid flow is pulsed. 17. A method comprising: providing an exhaust stream over a surface of a fluid dynamic body;directing a compressible fluid flow from fluid ejection openings to the surface; andperiodically varying amounts of the flows exiting the fluid ejection openings by varying a degree to which the openings are blocked to affect attachment of the exhaust stream to the fluid dynamic body to enhance lift, wherein periodically varying amounts of the flows exiting the openings comprises moving a cylinder relative to the openings in a periodic motion. 18. The method of claim 17, wherein the cylinder is moved in a periodic motion with a corresponding period, and wherein the period is varied. 19. The method of claim 18, wherein the periodic motion comprises a linear periodic motion. 20. The apparatus as defined in claim 1, wherein some of the rotatable vanes are rotated together.

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Evulet, Andrei. Fluidic propulsive system and thrust and lift generator for aerial vehicles. USP20190210207812.

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