[특허]Method and apparatus for pressure adaptive morphing structure

University of Kansas

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Method and apparatus for pressure adaptive morphing structure

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-003/46 B64C-003/44 B64C-003/52 F01B-019/00
미국특허분류(USC)	244/219; 244/099.8; 244/123.11; 244/126.6; 244/201; 244/214; 244/215
출원번호	US-0843255 (2010-07-26)
등록번호	US-8366057 (2013-02-05)
발명자 / 주소	Vos, Roelof Barrett, Ronald M.
출원인 / 주소	University of Kansas
인용정보	피인용 횟수 : 7 인용 특허 : 8

초록
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A method and apparatus for an adaptive aerostructure is presented that relies on certified aerospace materials and can therefore be applied in conventional passenger aircraft. This structure consists of a honeycomb material which cells extend over a significant length perpendicular to the plane of the cells. Each of the cells contains an inelastic pouch (or bladder) that forms a circular tube when the cell forms a perfect hexagon. By changing the cell differential pressure (CDP) the stiffness of the honeycomb can be altered. Using an external force or the elastic force within the honeycomb material, the honeycomb can be deformed such that the cells deviate from their perfect-hexagonal shape. It can be shown that by increasing the CDP, the structure eventually returns to a perfect hexagon. By doing so, a fully embedded pneumatic actuator is created that can perform work and substitute conventional low-bandwidth flight control actuators. It is shown that two approaches can be taken to regulate the stiffness of this embedded actuator.

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1. An adaptive morphing airfoil-structure comprising: an airfoil-structure having spaced apart first and second outer skins having disposed there between a stacked grid of elongated tubular cells each having cell walls with a substantially hexagonal cross-section thereby forming a honeycomb structure and where each of said elongated tubular cells extend perpendicular to a cross-sectional plane of the cells from a first end to a distal end, and where the first end and the distal end are sealed off forming a pressurized cell;where said cell walls having a material structure that radially deforms along the cross-sectional plane of the substantially hexagonal cross-section responsive to changes in ambient pressure; andwhere said first and second outer skins having a material structure to morph responsive to deformation of said cell walls. 2. The adaptive morphing airfoil-structure as recited in claim 1, where the airfoil-structure is a propeller blade. 3. The adaptive morphing airfoil-structure as recited in claim 1, where the airfoil-structure is an aero control structure of an aircraft and where said cell walls deform responsive to an ambient pressure-altitude cycle that the aircraft control structure encounters during flight. 4. The adaptive morphing airfoil-structure as recited in claim 3, where the aero control structure is one of the structures selected from a group of structures consisting of a wing section structure, a flap structure, a nose structure, a tail structure, an elevator structure, an engine inlet structure, an engine outlet nozzle structure and a stabilizer structure. 5. The adaptive morphing airfoil-structure as recited in claim 1, further comprising: a plurality of bladders where each is disposed inside the interior of the cell walls of one of the cells and communicably linked to a controlled compressed air source adapted to change relative pressure of the bladder to thereby change cell differential pressure for effecting cell deformation. 6. The adaptive morphing airfoil-structure as recited in claim 5, where the plurality of bladders are integrally interconnected and controlled. 7. The adaptive morphing airfoil-structure as recited in claim 5, where the airfoil-structure is an aero control structure of an aircraft and where said cell walls deform responsive to an ambient pressure-altitude cycle that the aircraft control structure encounters during flight. 8. The adaptive morphing airfoil-structure as recited in claim 7, where the aero control structure is one of the structures selected from a group structures consisting of a wing section structure, a flap structure, a nose structure, a tail structure, and a stabilizer structure. 9. An adaptive morphing airfoil-structure comprising: a stacked grid of elongated tubular cells each having cell walls with a substantially hexagonal cross-section thereby forming a honeycomb structure and where each extend perpendicular to a cross-sectional plane of the cells from a first end to a distal end, and where the first end and the distal end are sealed off forming a pressurized cell;said honeycomb structure bounded on one side by fixed outer boundary skin and on an opposing side by a free boundary area;where said cell walls having a material structure that radially deforms along the cross-sectional plane from the substantially hexagonal cross-section responsive to changes in ambient pressure; andwhere said fixed outer boundary skin having a material structure to morph responsive to deformation of said cell walls. 10. The adaptive morphing airfoil-structure as recited in claim 9, where the airfoil-structure is an aero control structure of an aircraft and where said cell walls deform responsive to an ambient pressure-altitude cycle that the aircraft control structure encounters during flight. 11. The adaptive morphing airfoil-structure as recited in claim 10, where the aero control structure is one of the structures selected from a group of structures consisting of a wing section structure, a flap structure, a nose structure, a tail structure, and a stabilizer structure. 12. The adaptive morphing airfoil-structure as recited in claim 10, where the cells that border the free boundary have an immediately adjacent sidewall pair and an opposing immediately adjacent sidewall pair where each of the immediately adjacent sidewall pairs form substantially flat opposing sidewalls in the immediately adjacent sidewall pairs' default state when the cell differential pressure is substantially zero such that the fixed outer boundary skin has a curvature. 13. A method for adaptively morphing an airfoil-structure comprising the steps of: providing an airfoil-structure having proximately spaced apart first and second outer skins having disposed there between a stacked grid of elongated tubular cells each having cell walls with a substantially hexagonal cross-section thereby forming a honeycomb structure and where each extend perpendicular to a cross-sectional plane of the cells from a first end to a distal end;sealing and pressurizing each cell; andwhere said cell walls having a material structure that radially deforms along the cross-sectional plane from the substantially hexagonal cross-section responsive to changes in ambient pressure, where said first and second outer skins having a material structure to morph responsive to deformation of said cell walls. 14. The method for adaptively morphing an airfoil-structure as recited in claim 13, further comprising the steps of: controlling the relative pressure within a plurality of bladders where each bladder is disposed inside the interior of the walls of one of the cells by communicably linking the bladders to a controlled compressed air source adapted to change relative pressure of the bladder to thereby change cell differential pressure for effecting cell deformation. 15. The method for adaptively morphing an airfoil-structure as recited in claim 14, further comprising the steps of: communicably interlinking the plurality bladders and integrally controlling the relative pressures of the bladders. 16. The method for adaptively morphing an airfoil-structure as recited in claim 15, further comprising the steps of: providing a line of cells that have an immediately adjacent sidewall pair and an opposing immediately adjacent sidewall pair where each of the immediately adjacent sidewall pairs form substantially flat opposing sidewalls in there default state when the cell differential pressure is substantially zero such that the first and second skins have a curvature. 17. The method for adaptively morphing an airfoil-structure as recited in claim 16, further comprising the steps of: transitioning the cell differential pressure to a value substantially above zero thereby reducing the curvature. 18. The method for adaptively morphing an airfoil-structure as recited in claim 17, where the airfoil-structure is a propeller blade. 19. The method for adaptively morphing an airfoil-structure as recited in claim 18, where the airfoil-structure is an aero control structure which is one of the structures selected from a group of structures consisting of a wing section structure, a flap structure, a nose structure, a tail structure, an elevator structure, an engine inlet structure, an engine outlet nozzle structure and a stabilizer structure. 20. The method for adaptively morphing an airfoil-structure as recited in claim 19, where controlling the relative pressure within a plurality of bladders is manually controlled.

이 특허에 인용된 특허 (8)

이 특허를 인용한 특허 피인용횟수: 7

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Method and apparatus for pressure adaptive morphing structure

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Method and apparatus for pressure adaptive morphing structure

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