[특허]Aerodynamic profile with a reversibly deformable contour for aircraft, in particular for rotary wing aircraft

Aircus Helicopters Deutschland GmbH

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특허 상세정보

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Aerodynamic profile with a reversibly deformable contour for aircraft, in particular for rotary wing aircraft

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-003/44
미국특허분류(USC)	244/219;
출원번호	US-0472770 (2009-05-27)
등록번호	US-8770523 (2014-07-08)
우선권정보	DE-10 2008 025 414 (2008-05-27)
발명자 / 주소	Pfaller, Rupert
출원인 / 주소	Aircus Helicopters Deutschland GmbH
대리인 / 주소	Brooks Kushman P.C.
인용정보	피인용 횟수 : 0 인용 특허 : 8

초록

An aerodynamic profile (10) for aircraft, in particular for rotary wing aircraft, which profile (10) includes a cover skin (14, 15) on the pressure side and on the suction side, with a profile contour that is controllably formable in the rear profile region (13) by actuators (30), wherein each cover skin (14, 15) is designed as a non-shear-resistant sandwich that includes a film or foil (21, 22) which is connected to a non-shear-resistant core (20), wherein the cover skins (14, 15) are held in their profile shape by flexible webs (17).

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1. An aerodynamic profile for aircraft rotor blade, the aerodynamic profile comprising: a rotor blade contour being reversible deformable wherein the contour is defined by a rear hollow profile region extending from a front solid profile region, the rear hollow profile region having bottom and top cover skins that extend from the front solid profile region and close off the rear hollow profile by providing a sealed coating on a pressure side and on a suction side of the rotor blade respectively, the bottom cover skin and the top cover skin merging in a trailing edge of the rear hollow profile region;an elastic core disposed along an inwards-facing surface of each of the bottom and top cover skins;at least one piezo-actuator connected to the rear hollow profile region by effective connections attached to the bottom cover skin and the top cover skin for controllably setting the position of the rear hollow profile region relative to the front solid profile region; andat least one layer design of fiber reinforced material to which at least one of the effective connections is attached, each layer design of fiber reinforced material having at least one targeted bending line of the cover skins formed adjacent the trailing edge, the targeted bending line defined by at least one of an interruption and an undulation or strand of the layer design of fiber reinforced material,wherein the rear hollow profile region is elastically deformable at the targeted bending lines which form reversal points upon actuation of the actuator as an integral Flettner flap being reversibly deformable to define the contour of the rear hollow profile region in an s-shaped manner. 2. The aerodynamic profile according to claim 1, wherein the elastic core of the hollow profile includes a plurality of flexible webs that are arranged between the cover skins. 3. The aerodynamic profile according to claim 2 wherein the elastic core is enclosed by at least one of a film or a foil opposite the cover skins. 4. The aerodynamic profile according to claim 3, wherein the flexible webs are connected to the film or foil of the cover skins by way of fanned-open faces that form foot points that serve as web feet. 5. The aerodynamic profile according to claim 3, wherein the flexible webs are connected to the film or foil and the cover skin by way of elastic joints. 6. The aerodynamic profile according to claim 1, wherein the elastic core is plate-shaped extending parallel along the cover skins. 7. The aerodynamic profile according to claim 1, wherein the elastic core includes interruptions. 8. The aerodynamic profile according to claim 1, the elastic core includes an elastic roll web including a plurality of webs that are flexibly arranged between the cover skins. 9. The aerodynamic profile according to claim 2, wherein the at least one piezoelectric actuator has a first portion arranged in the solid profile region of the aerodynamic profile and a second portion extending into the hollow profile region and connecting the piezoelectric actuator to the elastic core, wherein actuation of the piezoelectric actuator thereby deforms the rear profile region. 10. The aerodynamic profile according to claim 1, wherein both the pressure-side cover skin and on the suction-side cover skin are reversibly deformable in the s-shape manner. 11. A rotary wing aircraft rotor blade with a contour that is reversibly deformable, the rotor blade comprising: a front solid profile region;a rear hollow profile region connected to and rearward of the front solid profile region, the rear profile region comprising: a first cover skin on a pressure side of the rear profile region;a second cover skin on a suction side of the rear profile region, wherein the first cover skin and the second cover skin merge at a trailing edge of the rotor blade; the first cover skin and the second cover skin closing off the rear hollow profile region by a sealed coating of the pressure side and of the suction side of the rotor blade;an elastic core layer disposed along an inwards-facing surface of each of the first cover skin and the second cover skin to form the rear hollow profile region therebetween;at least one layer design of fiber reinforced material having at least one targeted bending line of the cover skins formed adjacent the trailing edge, the targeted bending line defined by at least one of an interruption and an undulation or strand of the layer design of fiber reinforced material; andat least one piezoelectric actuator attached to the first and second cover skins at effective connections along the layer design of fiber reinforced material for controllably setting the position of the rear hollow profile region relative to the front solid profile region,wherein, the rear hollow profile region is elastically deformable at the targeted bending lines which form reversal points upon actuation of the at least one piezoelectric actuator as an integral Flettner flap being reversibly deformable to define the contour of the rear hollow profile region in an s-shaped manner. 12. The rotor blade according to claim 11, wherein the rear profile region comprises two reversal points such that the rear profile region is deformable to define a generally s-shaped profile. 13. The rotor blade according to claim 11, wherein the elastic core comprises a first elastic layer on the first cover skin and covered by a first foil and a second elastic layer on the second cover skin and covered by a second foil. 14. The rotor blade according to claim 11, wherein the at least one piezoelectric actuator has a first portion disposed in the solid profile region and a second portion extending into the hollow profile region and connecting the piezoelectric actuator to the elastic core layers, wherein actuation of the piezoelectric actuator thereby deforms the rear profile region. 15. The rotor blade according to claim 12, wherein both the pressure-side cover skin and on the suction-side cover skin are elastically deformable. 16. The rotor blade according to claim 12, wherein rear profile region is reversibly deformable in a first direction and a second direction being opposite the first direction. 17. An rotary wing aircraft rotor blade with a contour that is reversibly deformable, the rotor blade comprising: an aerodynamic profile defined by a first cover skin on a pressure side of the profile and a second cover skin on a suction side of the profile, the skins defining at least one hollow profile region therebetween, the first and second cover skins having an elastic layer extending along at least a portion of an inward-facing surface,at least one layer design of fiber reinforced material having at least one targeted bending line of the cover skins formed adjacent a trailing edge of the profile, the targeted bending line defined by at least one of an interruption and an undulation or strand of the layer design of fiber reinforced material; andat least one piezoelectric actuator attached to the first and second cover skins at effective connections along the layer design of fiber reinforced material for controllably setting the position of the hollow profile region,wherein the hollow profile region is elastically deformable at the targeted bending lines which form reversal points upon actuation of the at least one piezoelectric actuator as an integral Flettner flap being reversibly deformable, thereby elastically deforming the aerodynamic profile to define a generally s-shaped profile along to the hollow profile region. 18. The rotor blade according to claim 17, wherein the hollow profile region comprises at least two reversal points to promote formation of the generally s-shaped profile along the hollow profile region, wherein the reversal points are defined as interruptions in the elastic layers. 19. The rotor blade according to claim 18, further comprising least one interruption formed in the elastic layer extending along both the first and second cover skins to define the two reversal points such both the first cover skin and on the second cover skin are elastically deformable to define the generally s-shaped profile of the hollow profile region. 20. The rotor blade according to claim 18, wherein the hollow profile region defines a rear hollow profile region extending from a forward solid profile region of the rotor blade, the rotor blade further comprising: at least one piezoelectric actuator having a first portion disposed in the forward solid profile region and a second portion extending into the rear hollow profile region and connected with the cover skins,wherein, the rear hollow profile region is elastically deformable upon actuation of the at least one piezoelectric actuator.

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Aerodynamic profile with a reversibly deformable contour for aircraft, in particular for rotary wing aircraft

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Aerodynamic profile with a reversibly deformable contour for aircraft, in particular for rotary wing aircraft

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