IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0478311
(2009-06-04)
|
등록번호 |
US-8177169
(2012-05-15)
|
우선권정보 |
ES-200900851 (2009-03-30) |
발명자
/ 주소 |
- Lobo Barros, Abel
- Lozano Garcia, Jose Luis
|
출원인 / 주소 |
|
대리인 / 주소 |
Oblon, Spivak, McClelland, Maier & Neustadt, L.L.P.
|
인용정보 |
피인용 횟수 :
4 인용 특허 :
6 |
초록
▼
Joining structure for aircraft fairing (7), said fairing (7) being arranged between the horizontal stabilizer and the vertical stabilizer or fuselage section (6) of the aircraft, the structure comprising fittings (2) in the shape of angle, the fittings in turn comprising a vertical surface and a hor
Joining structure for aircraft fairing (7), said fairing (7) being arranged between the horizontal stabilizer and the vertical stabilizer or fuselage section (6) of the aircraft, the structure comprising fittings (2) in the shape of angle, the fittings in turn comprising a vertical surface and a horizontal surface, the fittings (2) being joined via their vertical surface to the fairing (7) with removable fixing parts (12), the structure also comprising a deformable resilient element (13) between the fairing (7) and the vertical surface of the fitting (2), such that the resilient element (13) is able to compensate for the necessary deformation play and the manufacturing and assembly tolerances of the fittings (2), the fairing (7), the horizontal stabilizer and the vertical stabilizer or fuselage section (6) with different torques for tightening of the above parts.
대표청구항
▼
1. A joining structure for a fairing of an aircraft, said fairing being arranged between a horizontal stabilizer and a vertical stabilizer or fuselage section of said aircraft, said structure comprising; a fitting that is in the shape of an angle, said fitting including a vertical surface and a hori
1. A joining structure for a fairing of an aircraft, said fairing being arranged between a horizontal stabilizer and a vertical stabilizer or fuselage section of said aircraft, said structure comprising; a fitting that is in the shape of an angle, said fitting including a vertical surface and a horizontal surface, the fitting being joined via the vertical surface to the fairing by removable fixing parts; anda resilient element that is deformable and is located between the fairing and the vertical surface of the fitting, said resilient element being configured to compensate for manufacturing and assembly tolerances of the fitting, the fairing, the horizontal stabilizer, and the vertical stabilizer or fuselage section, by the resilient element being expandable or contractible in thickness from deformation of the resilient element to adjust a spacing between the fairing and the vertical surface of the fitting, the deformation resulting from torques that tighten the fitting, the fairing, the horizontal stabilizer, and the vertical stabilizer or fuselage section. 2. The joining structure for the fairing according to claim 1, wherein the joining structure is adjustable between a top part and a bottom part of the fairing, by amplifying differences in the deformation of the resilient element during securing of the resilient element to the fitting in a sealing zone, thus reducing a diameter of the resilient element required and facilitating considerably joining of the fairing, the resilient element, and the fitting. 3. The joining structure for the fairing according to either of the preceding claims, wherein the resilient element retains its resilience, allowing it to be joined between the fairing and the fitting independently of the aircraft assembled. 4. The joining structure for the fairing according to either of claims 1 to 2, wherein the resilient element is hardened after a suitable curing process, once assembly of said resilient element between the fairing and the fitting has been performed. 5. The joining structure for the fairing according to claim 1, wherein a joint between the fitting and a skin of the horizontal stabilizer is secured by blind rivets which transmit shearing loads from the fairing to said skin. 6. The joining structure for the fairing according to claim 1, wherein a joint between the fitting and a skin of the horizontal stabilizer is secured by stud pins where there is suitable internal accessibility to the skin of the horizontal stabilizer, in a fuel tank. 7. The joining structure for the fairing according to claim 1, wherein the fitting forms a right angle between the vertical surface and the horizontal surface. 8. The joining structure for the fairing according to claim 1, wherein the resilient element deforms so that a surface of the resilient element that is adjacent to the fairing forms an oblique angle relative to at least one of the vertical surface and the horizontal surface. 9. The joining structure for the fairing according to claim 1, wherein the resilient element deforms so that the spacing between the fairing and the vertical surface of the fitting is greater at a top part of the vertical surface of the fitting than at a bottom part of the vertical surface of the fitting. 10. The joining structure for the fairing according to claim 1, wherein the resilient element deforms so that the spacing between the fairing and the vertical surface of the fitting is greater at a bottom part of the vertical surface of the fitting than at a top part of the vertical surface of the fitting. 11. A joining structure for a fairing of an aircraft, said fairing being arranged between a horizontal stabilizer and a vertical stabilizer or fuselage section of said aircraft, said structure comprising: means for fitting, said fitting means being in the shape of an angle and including a vertical surface and a horizontal surface, the fitting means being joined via the vertical surface to the fairing by removable fixing parts; andmeans for deforming, said deforming means being resilient and being located between the fairing and the vertical surface of the fitting means, and said deforming means being configured to compensate for manufacturing and assembly tolerances of the fitting means, the fairing, the horizontal stabilizer, and the vertical stabilizer or fuselage section, by the deforming means being expandable or contractible in thickness from deformation of the deforming means to adjust a spacing between the fairing and the vertical surface of the fitting, the deformation resulting from torques that tighten the fitting means, the fairing, the horizontal stabilizer, and the vertical stabilizer or fuselage section.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.