RU2001103139A - METAL CONSTRUCTION ELEMENT OF THE COVERING - Google Patents

METAL CONSTRUCTION ELEMENT OF THE COVERING

Info

Publication number
RU2001103139A
RU2001103139A RU2001103139/28A RU2001103139A RU2001103139A RU 2001103139 A RU2001103139 A RU 2001103139A RU 2001103139/28 A RU2001103139/28 A RU 2001103139/28A RU 2001103139 A RU2001103139 A RU 2001103139A RU 2001103139 A RU2001103139 A RU 2001103139A
Authority
RU
Russia
Prior art keywords
joint
structural element
profile
casing
thickness
Prior art date
Application number
RU2001103139/28A
Other languages
Russian (ru)
Other versions
RU2249538C2 (en
Inventor
Франк ПАЛЬМ
Original Assignee
Еадс Дойчланд Гмбх
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from DE19924909A external-priority patent/DE19924909C1/en
Application filed by Еадс Дойчланд Гмбх filed Critical Еадс Дойчланд Гмбх
Publication of RU2001103139A publication Critical patent/RU2001103139A/en
Application granted granted Critical
Publication of RU2249538C2 publication Critical patent/RU2249538C2/en

Links

Claims (10)

1. Металлический конструктивный элемент обшивки, состоящий из металлического листа обшивки и профильных элементов жесткости, отличающийся тем, что указанные профильные элементы (2) жесткости имеют в зоне основания утолщение (4) определенной толщины (f), которое уменьшается в сторону места (3) стыка или соединения до определенной толщины (а) в этом месте стыка или соединения, при этом отношение толщины (f) основания профильного элемента (2) жесткости к толщине (а) в месте стыка или соединения больше или равно 2.1. The metal structural element of the casing, consisting of a metal sheet of the casing and profile stiffeners, characterized in that the said profile elements (2) of stiffness have a thickening (4) of a certain thickness (f) in the base zone, which decreases towards the site (3) the joint or joint to a certain thickness (a) at this point of the joint or joint, the ratio of the thickness (f) of the base of the profile element (2) stiffness to the thickness (a) at the joint or joint is greater than or equal to 2. 2. Конструктивный элемент обшивки по п. 1, отличающийся тем, что толщина (а) в месте стыка или соединения меньше или равна толщине (s) профильного элемента (2) жесткости без утолщения. 2. The structural element of the casing according to claim 1, characterized in that the thickness (a) at the junction or joint is less than or equal to the thickness (s) of the stiffening profile element (2) without thickening. 3. Конструктивный элемент обшивки по п. 1 или 2, отличающийся тем, что жесткость профильного элемента жесткости в зоне места (3) стыка или соединения уменьшена за счет наличия одной либо двух расположенных с противоположных сторон выемок (6). 3. The structural element of the casing according to claim 1 or 2, characterized in that the stiffness of the profile stiffener in the area of the place (3) of the joint or joint is reduced due to the presence of one or two recesses located on opposite sides (6). 4. Конструктивный элемент обшивки по п. 1 или 2, отличающийся тем, что в профильном элементе (2) жесткости в зоне места (3) стыка или соединения выполнена канавка, сформированная уплотнением материала валками или роликами. 4. The structural element of the casing according to claim 1 or 2, characterized in that in the profile element (2) of the stiffness in the area of the place (3) of the joint or connection, a groove is formed formed by sealing the material with rollers or rollers. 5. Конструктивный элемент обшивки по любому из пп. 1-4, отличающийся тем, что отношение толщины (f) основания профильного элемента жесткости к толщине (t) листа обшивки больше или равно 2. 5. The structural element of the casing according to any one of paragraphs. 1-4, characterized in that the ratio of the thickness (f) of the base of the profile stiffener to the thickness (t) of the sheathing sheet is greater than or equal to 2. 6. Конструктивный элемент обшивки по любому из пп. 1-5, отличающийся тем, что профильные элементы (2) жесткости приварены к листу (1) обшивки. 6. The structural element of the casing according to any one of paragraphs. 1-5, characterized in that the profile elements (2) of rigidity are welded to the sheathing sheet (1). 7. Конструктивный элемент обшивки по любому из пп. 1-5, отличающийся тем, что он выполнен в виде прессованного профиля (7). 7. The structural element of the casing according to any one of paragraphs. 1-5, characterized in that it is made in the form of a pressed profile (7). 8. Конструктивный элемент обшивки по любому из пп. 1-5, отличающийся тем, что он изготовлен фрезерованием из цельной заготовки с получением цельной детали, состоящей из листа (1) обшивки и профильных элементов (2) жесткости. 8. The structural element of the casing according to any one of paragraphs. 1-5, characterized in that it is made by milling from a solid billet with obtaining a solid part consisting of a sheet (1) sheathing and profile elements (2) stiffness. 9. Конструктивный элемент обшивки по любому из пп. 6-8, отличающийся тем, что он составлен из нескольких, имеющих меньшие размеры сварных конструктивных элементов обшивки, прессованных профилей (7) или фрезерованных конструктивных элементов обшивки, соединенных вместе стыковой сваркой или клепкой с получением конструктивного элемента обшивки больших размеров. 9. The structural element of the casing according to any one of paragraphs. 6-8, characterized in that it is composed of several smaller sizes of welded structural elements of the casing, extruded profiles (7) or milled structural elements of the casing, joined together by butt welding or riveting to obtain a structural element of the casing of large sizes. 10. Конструктивный элемент обшивки по любому из пп. 1-9, отличающийся тем, что он предназначен для применения в конструкции фюзеляжа самолета и изготовлен из авиационного алюминиевого сплава, а профильные элементы (2) жесткости в качестве стрингеров соединены с листом (1) обшивки. 10. The structural element of the casing according to any one of paragraphs. 1-9, characterized in that it is intended for use in the design of the fuselage of the aircraft and is made of an aircraft aluminum alloy, and the profile elements (2) of rigidity as stringers are connected to the skin sheet (1).
RU2001103139/11A 1999-05-31 2000-05-03 Metal structural member of skin RU2249538C2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19924909A DE19924909C1 (en) 1999-05-31 1999-05-31 Metallic shell structural part for aircraft fuselage comprises main plate and stiffening profiles which in foot area have a thickened formation with a specific profile foot thickness
DE19924909.1 1999-05-31

Publications (2)

Publication Number Publication Date
RU2001103139A true RU2001103139A (en) 2003-04-10
RU2249538C2 RU2249538C2 (en) 2005-04-10

Family

ID=7909773

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2001103139/11A RU2249538C2 (en) 1999-05-31 2000-05-03 Metal structural member of skin

Country Status (9)

Country Link
US (1) US6543721B2 (en)
EP (1) EP1100636B1 (en)
JP (1) JP2003500278A (en)
CN (1) CN1188242C (en)
CA (1) CA2336074A1 (en)
DE (2) DE19924909C1 (en)
ES (1) ES2198316T3 (en)
RU (1) RU2249538C2 (en)
WO (1) WO2000072990A1 (en)

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DE50102291D1 (en) 2001-12-27 2004-06-17 Airbus Gmbh Metallic structural component for an aircraft
US6814331B2 (en) * 2002-05-10 2004-11-09 Goodrich Hella Aerospace Lighting Systems Gmbh Device for removably fastening a first part to a second part mountable in an aircraft
DE10301445B4 (en) 2003-01-16 2005-11-17 Airbus Deutschland Gmbh Lightweight structural component, in particular for aircraft and method for its production
ATE406998T1 (en) * 2003-07-08 2008-09-15 Airbus Gmbh LIGHTWEIGHT STRUCTURE
DE10331990A1 (en) * 2003-07-14 2005-02-24 Eads Deutschland Gmbh Welded aluminum structural component with metallic induced cracking
FR2863185B1 (en) * 2003-12-04 2007-02-09 Airbus France DEVICE FOR EQUIPPING A HOLE IN A PANEL AND PANEL THUS EQUIPPED
EP1666354B1 (en) 2004-12-01 2010-09-29 Airbus Operations GmbH Structural component, process for manufacturing a structural component and use of a structural component for an aircraft skin
DE102006026167B3 (en) 2006-06-06 2007-12-13 Airbus Deutschland Gmbh Lightweight structural panel
GB0616324D0 (en) * 2006-08-16 2006-09-27 Airbus Uk Ltd A cover panel for an aircraft wing and a method of forming thereof
US9016551B2 (en) 2006-11-02 2015-04-28 The Boeing Company Method and apparatus to construct metal securement member for an aircraft
GB0621952D0 (en) * 2006-11-03 2006-12-13 Airbus Uk Ltd A stringer for an aircraft wing and a method of reinforcing thereof
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US8100316B2 (en) * 2008-05-29 2012-01-24 Airbus Operations Gmbh Method for joining aircraft fuselage elements by friction stir welding (fsw)
DE102009007730B4 (en) 2009-02-05 2017-12-14 Mbda Deutschland Gmbh structural component
ES2387854B1 (en) * 2010-04-30 2013-11-07 Airbus Operations, S.L. INTERNAL AIRCRAFT STRUCTURE IN COMPOSITE MATERIAL.
US8752795B2 (en) * 2010-11-23 2014-06-17 John Ralph Stewart, III Inlet nose cowl with a locally thickened fastening portion to enable an uninterrupted airflow surface
FR2973773B1 (en) * 2011-04-05 2013-11-29 Airbus Operations Sas METHOD FOR SLOWING THE PROPAGATION OF CRACKS IN A SECURE STRUCTURE AND A HIGHLY SECURE FRAME, ESPECIALLY A FUSELAGE
CN109454331B (en) * 2018-11-30 2020-08-04 上海航天精密机械研究所 Double-side laser welding equipment suitable for manufacturing rocket T-shaped structure wall plate
CN115156849B (en) * 2022-07-07 2023-06-27 沈阳飞机工业(集团)有限公司 Integrated manufacturing method of aircraft metal skin and mouth frame structure

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