[특허]Aerodynamic flight control surface said of crocodile style for aircraft

Airbus Operations (S.A.S.)

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Aerodynamic flight control surface said of crocodile style for aircraft

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-009/00 B64C-003/50 B64C-009/32 B64C-005/10
미국특허분류(USC)	244/217; 244/099.14; 244/090R; 244/090A; 244/087; 244/213; 244/215; 244/216
출원번호	US-0941230 (2010-11-08)
등록번호	US-8613409 (2013-12-24)
우선권정보	FR-09 57947 (2009-11-10)
발명자 / 주소	Cazals, Olivier Druot, Thierry
출원인 / 주소	Airbus Operations (S.A.S.)
대리인 / 주소	Lerner, David, Littenberg, Krumholz & Mentlik, LLP
인용정보	피인용 횟수 : 1 인용 특허 : 8

초록
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A trailing edge aerodynamic airfoil of a load-bearing aerodynamic surface of an aircraft of the crocodile type has two airfoil flaps, with each flap being integral in a forward section with a rotational shaft that determines the axis of rotation of the airfoil flap. In a position called the zero setting, the airfoil flaps are essentially joined and form a rear section of the load-bearing surface, and each airfoil flap is movable in translation independently of the other airfoil flap, relative to the load-bearing surface, with each flap being entrained in rotation relative to the load-bearing surface around its axis of rotation by the motion in translation. The ends of the rotational shaft have extensions guided by runners fastened to these ends and acting conjointly with racks fastened to the load-bearing surface.

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1. An aerodynamic airfoil having a first, top airfoil flap and a second, bottom airfoil flap, the airfoil comprising: a first rotational shaft located in a forward section of the first airfoil flap and having a first axis of rotation;a second rotational shaft located in a forward section of the second airfoil flap and having a second axis of rotation;wherein the first and second axes of rotation of said first and second airfoil flaps are substantially parallel to one another,a first guide runner and a second guide runner fastened to the aerodynamic airfoil, for the first and second rotational shafts, respectively, wherein the first and second guide runners comprise a rack located on one of the top or bottom surfaces of the guide runners,a first rotational entrainment device and a second rotational entrainment device for said first and second rotational shafts, respectively, wherein the rotational entrainment device comprises a sprocket or a pinion,at least first and second linear drivers for driving the first and second airfoil flaps, respectively, in translation,wherein the at least first and second linear drivers and the first and second rotational entrainment devices are configured to move the first and second airfoil flaps, respectively, independently of one another, simultaneously in translation and in rotation about the respective axis of rotation of the respective rotational shaft; andwherein a translational movement of at least one of the first and second rotational shafts causes the teeth of the sprocket or pinion to engage with the teeth of the rack, which causes the respective flap to rotate about the respective axis of rotation of the respective rotational shaft. 2. The aerodynamic airfoil of claim 1, wherein the at least one extension of the corresponding rotational shaft is configured to act in conjunction with the corresponding guide runner to determine a trajectory of the corresponding airfoil flap during the simultaneous movement in translation and rotation. 3. The aerodynamic airfoil of claim 2, wherein a zero setting position of the airfoil flap corresponds to an intermediate position of the translation movement between a forward limit position and a rear limit position in the guide runner. 4. The aerodynamic airfoil of claim 2, wherein a zero setting position of the airfoil flap corresponds to a forward limit position in the guide runner. 5. The aerodynamic airfoil of claim 2, wherein a position of the airfoil flap set at an angle of rotation greater than or equal to 90 degrees relative to a zero setting position corresponds to a rear limit position in the guide runner. 6. The aerodynamic airfoil of claim 2, wherein the guide runner of the airfoil flap has a curved portion determining a non-rectilinear trajectory of the motion of translation of said airfoil flap. 7. The aerodynamic airfoil of claim 1, wherein the rotational entrainment device is configured to act in conjunction with the aerodynamic airfoil to set the corresponding airfoil flap toward an external face of said flap subjected to an aerodynamic flow when in flight, when the flap is simultaneously moved in translation and rotation. 8. The aerodynamic airfoil of claim 1, wherein the linear driver of each airfoil flap is configured to displace the airfoil flap in translation independently of the other flap. 9. The aerodynamic airfoil of claim 1, wherein the at least one driver comprises a driver shaft for applying forces substantially perpendicular to the corresponding axis of rotation of the airfoil flap, and wherein the driver shaft is hinged to the corresponding rotational shaft. 10. The aerodynamic airfoil of claim 1, wherein the rack is located toward an external face of the corresponding airfoil flap relative to the corresponding sprocket or pinion. 11. The aerodynamic airfoil of claim 1, wherein said aerodynamic airfoil is a trailing edge aileron of an airplane wing, or a directional airfoil of a vertical fin of an airplane. 12. An aircraft that has at least one aerodynamic airfoil, the aerodynamic airfoil comprising a first, top airfoil flap and a second, bottom airfoil flap,a first rotational shaft located in a forward section of the first airfoil flap and having a first axis of rotation;a second rotational shaft located in a forward section of the second airfoil flap and having a second axis of rotation;wherein the first and second axes of rotation of said first and second airfoil flaps are substantially parallel to one another,a first guide runner and a second guide runner fastened to the aerodynamic airfoil, for the first and second rotational shafts, respectively, wherein the first and second guide runners comprise a rack located on one of the top or bottom surfaces of the guide runners,a first rotational entrainment device and a second rotational entrainment device for said first and second rotational shafts, respectively, wherein the rotational entrainment device comprises a sprocket or a pinion,at least first and second linear drivers for driving the first and second airfoil flaps, respectively, in translation,wherein the at least first and second linear drivers and the first and second rotational entrainment devices are configured to move the first and second airfoil flaps, respectively, independently of one another, simultaneously in translation and in rotation about the respective axis of rotation of the respective rotational shaft; andwherein a translational movement of at least one of the first and second rotational shafts causes the teeth of the sprocket or pinion to engage with the teeth of the rack, which causes the respective flap to rotate about the respective axis of rotation of the respective rotational shaft.

이 특허에 인용된 특허 (8)

이 특허를 인용한 특허 피인용횟수: 1

Havar, Tamas; Perez-Sanchez, Juan; Ender, Tobias; Seack, Oliver. Lift flap bearing apparatus, lift flap assembly, airfoil and aircraft. USP2016099452823.

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Aerodynamic flight control surface said of crocodile style for aircraft

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Aerodynamic flight control surface said of crocodile style for aircraft

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이 특허에 인용된 특허 (8)

이 특허를 인용한 특허 피인용횟수: 1

IPC 상위 출원인

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IPC 상세정보(version : 201201)

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