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公开(公告)号：EP2485941A2
公开(公告)日：2012-08-15
申请号：EP10762689.7
申请日：2010-10-07
IPC分类号： B64C1/06
摘要： The invention relates to a pressure fuselage of an aircraft, said pressure fuselage being composed of several fuselage sections (1a-1f) in the longitudinal direction, wherein at least one tail-face pressure calotte (2) is provided for forming an inner pressurized area (3) of the aircraft. An annular frame section (5) is provided in order to fix said pressure calotte radially outward to at least one fuselage section (1a-1f). The frame section (5) has a U-shaped section segment on the pressure calotte side. The first arm (6) of the section segment on the end face thereof is rearwardly fixed to the pressure calotte (2) by connecting means (7), and the elongated second arm (8) of the section segment, said second arm extending radially outward, produces a connection to at least one fuselage section (1e, 1f) such that the connecting means (7) can be mounted entirely from the inner pressurized area of the aircraft.
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2.发明公开
公开(公告)号：EP2414229A1
公开(公告)日：2012-02-08
申请号：EP10704838.1
申请日：2010-02-23
CPC分类号： B64C1/40 , B64D2011/0046 , F16L55/033 , F16L59/027 , F16L59/147 , Y10T29/49826
摘要： The invention relates to an aircraft (100) comprising an insulation system (101) for thermal and acoustic insulation. Said insulation system (101) includes a cabin (102), an outer skin (103), a sound insulating unit (104), and a heat insulating unit (105). The sound insulating unit (104) is designed to acoustically insulate the aircraft (100). The heat insulating unit (105) is designed to thermally insulate the aircraft (100). The sound insulating unit (104) and the heat insulating unit (105) are arranged between the cabin (102) and the outer skin (103).
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4.发明公开
公开(公告)号：EP2398636A1
公开(公告)日：2011-12-28
申请号：EP10704817.5
申请日：2010-02-17
CPC分类号： B29C70/86 , B23K2201/04 , B29C65/56 , B29C66/54 , B29C66/543 , B29C66/721 , B29C66/7212 , B29C66/72141 , B29C66/742 , B29K2105/06 , B29K2305/00 , B29K2307/00 , B29L2031/3082 , B64C1/069 , B64C2001/0072 , Y02T50/43 , Y10T156/1043 , Y10T428/13 , B29K2307/04
摘要： In a method for manufacturing a shell, at least two shell sections are fabricated out of a composite fiber material, at least one compensation body of a plastically deformable material is secured to at least one limiting edge of at least one shell section, the shell sections are overlapped to form the shell, yielding flat seams between respectively adjacent shell sections. The at least one compensation body is arranged on at least one of the seams. In order to compensate for dimensional deviations in each overlap, the shape of the corresponding compensation bodies is changed, and the shells sections are joined together at the seams.
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公开(公告)号：EP2456671B1
公开(公告)日：2014-09-03
申请号：EP10735005.0
申请日：2010-07-22
IPC分类号： B64F5/00
CPC分类号： B64D9/00 , B64C1/20 , B64F5/50 , Y10T29/49826
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6.发明授权
公开(公告)号：EP2414229B1
公开(公告)日：2013-08-21
申请号：EP10704838.1
申请日：2010-02-23
CPC分类号： B64C1/40 , B64D2011/0046 , F16L55/033 , F16L59/027 , F16L59/147 , Y10T29/49826
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7.发明公开
公开(公告)号：EP2456671A2
公开(公告)日：2012-05-30
申请号：EP10735005.0
申请日：2010-07-22
IPC分类号： B64F5/00
CPC分类号： B64D9/00 , B64C1/20 , B64F5/50 , Y10T29/49826
摘要： The invention relates to a method for system installation in a fuselage (4), to a device (2) comprising a rail system (14) for carrying out said method, and to a freight loading system (50) that uses the rail system (14) as a guidance system for unit loads (52, 54).
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