Method for assembling an aircraft aft portion
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-001/06
B64C-001/26
출원번호
US-0695731
(2015-04-24)
등록번호
US-9656736
(2017-05-23)
우선권정보
FR-14 53807 (2014-04-28)
발명자
/ 주소
Guillemaut, Julien
Martino Gonzalez, Esteban
Folch Cortes, Diego
Colmagro, Jerome
Blanc, Jonathan
출원인 / 주소
Airbus Operations (S.A.S.)
대리인 / 주소
Jenkins, Wilson, Taylor & Hunt, P.A.
인용정보
피인용 횟수 :
1인용 특허 :
8
초록▼
In the case of an aircraft aft portion equipped with an engine mounting structure passing across the fuselage, assembly of the aft portion presents problems caused by the moving of the box structure of the mounting structure through lateral openings in the fuselage. In order to overcome these proble
In the case of an aircraft aft portion equipped with an engine mounting structure passing across the fuselage, assembly of the aft portion presents problems caused by the moving of the box structure of the mounting structure through lateral openings in the fuselage. In order to overcome these problems, a method of assembling an aircraft aft portion is proposed, in which method the box structure of the engine mounting structure is inserted into the fuselage through a top opening extending from one side of the fuselage to the other across a vertical midplane of the fuselage such that the top opening opens to the top and to the sides of the fuselage.
대표청구항▼
1. A method for assembling an aircraft aft portion, the method comprising: assembling a fuselage outer skin and circumferential frames to form a fuselage of the aircraft aft portion, the fuselage having a top opening extending from one side of the fuselage to another side thereof across a vertical m
1. A method for assembling an aircraft aft portion, the method comprising: assembling a fuselage outer skin and circumferential frames to form a fuselage of the aircraft aft portion, the fuselage having a top opening extending from one side of the fuselage to another side thereof across a vertical midplane of the fuselage, so that the top opening opens towards a top and towards sides of the fuselage;assembling a box structure of a mounting structure provided with an attachment structure configured to attach aircraft engines to the mounting structure;inserting a middle portion of the box structure of the mounting structure into the top opening of the fuselage; andfixing the middle portion of the box structure to the fuselage. 2. The method according to claim 1, wherein the fuselage comprises a forward frame extending forward of the top opening in the fuselage and an aft frame extending aft of the top opening in the fuselage. 3. The method according to claim 2, comprising connecting the forward frame and the aft circumferential frame by at least one top cross beam extending above the middle portion of the box structure of the mounting structure. 4. The method according to claim 3, wherein a central top cross beam of the at least one top cross beam is centered in the vertical midplane of the aircraft aft portion, the method comprising fixing the central top cross beam to the box structure of the mounting structure. 5. The method according to claim 2, wherein the forward frame and the aft circumferential frame are joined together by two lateral cross beams extending respectively on each side of the fuselage, below the top opening in the fuselage. 6. The method according to claim 1, comprising, before inserting the box structure of the mounting structure into the top opening in the fuselage, assembling a top fairing with the middle portion of the box structure of the mounting structure so that the top fairing aerodynamically closes off a middle section of the top opening in the fuselage after the middle portion of the box structure has been fixed to the fuselage. 7. The method according to claim 6, wherein the top fairing is secured beforehand to a top aileron, the top aileron being positioned in such a way that, when the top fairing is assembled with the fuselage, the top aileron extends above the top fairing as a forward continuation of an empennage of the aircraft aft portion. 8. The method according to claim 1, comprising, after fixing the middle portion of the box section to the fuselage, mounting a top fairing on the fuselage, over a top of the middle portion of the box structure of the mounting structure, so that the top fairing aerodynamically closes off a middle section of the top opening in the fuselage. 9. The method according to claim 8, comprising mounting a top aileron on the top fairing as a forward continuation of an empennage of the aircraft aft portion. 10. The method according to claim 8, wherein the top fairing incorporates longitudinal stiffeners so that, during normal operation, the top fairing participates in the transfer of load between a portion of the fuselage that is situated aft of the top opening in the fuselage and a portion of the fuselage that is situated forward of the top opening in the fuselage. 11. The method according to claim 1, wherein the middle portion of the box structure of the mounting structure comprises an aerodynamic top skin delimiting the box structure, which is shaped to extend as a continuation of the outer skin of the fuselage after the middle portion of the box structure is inserted into the top opening in the fuselage. 12. The method according to claim 1, comprising moving the mounting structure in a vertical direction, resulting in the box structure of the mounting structure being inserted in the top opening in the fuselage. 13. The method according to claim 1, comprising fixing aircraft engines to the mounting structure before the box structure of the mounting structure is inserted into the top opening in the fuselage. 14. An aircraft aft portion comprising a fuselage, which comprises a fuselage outer skin, circumferential frames, and a top opening extending from one side to another of the fuselage across a vertical midplane thereof, such that the top opening opens towards a top and sides of the fuselage; and a mounting structure comprising a box structure and attachment structure configured to attach aircraft engines to the mounting structure, wherein the box structure comprises a middle portion housed in the top opening in the fuselage and fixed to the fuselage. 15. The aircraft aft portion according to claim 14, wherein the box structure comprises a top skin forming part of an outer fairing of the aircraft aft portion. 16. A method for assembling an aircraft aft portion, the method comprising: assembling a fuselage outer skin and circumferential frames to form a fuselage of the aircraft aft portion, the fuselage having a top opening, which extends across a continuous portion of outer top surface of the fuselage, from one side of the fuselage to another side thereof across a vertical midplane of the fuselage, so that the top opening opens towards a top and towards sides of the fuselage;assembling a box structure of a mounting structure provided with an attachment structure configured to attach aircraft engines to the mounting structure;inserting a middle portion of the box structure of the mounting structure into the top opening of the fuselage; andfixing the middle portion of the box structure to the fuselage.
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이 특허에 인용된 특허 (8)
Cazals, Olivier; Druot, Thierry, Aircraft with its fuselage suspended under the wing.
Clausen Charles C. (Seattle WA) Johnson Ronald C. (Fall City WA) Chee Wan T. (Bellevue WA) Schmidt Warren E. (Erie PA), Vibration isolating engine mount.
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