JP2022105979A5 - - Google Patents

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Publication number
JP2022105979A5
JP2022105979A5 JP2021174539A JP2021174539A JP2022105979A5 JP 2022105979 A5 JP2022105979 A5 JP 2022105979A5 JP 2021174539 A JP2021174539 A JP 2021174539A JP 2021174539 A JP2021174539 A JP 2021174539A JP 2022105979 A5 JP2022105979 A5 JP 2022105979A5
Authority
JP
Japan
Prior art keywords
composite
sacrificial member
layup
spar
skin panel
Prior art date
Legal status (The legal status 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 status listed.)
Granted
Application number
JP2021174539A
Other languages
English (en)
Japanese (ja)
Other versions
JP7783717B2 (ja
JP2022105979A (ja
Filing date
Publication date
Application filed filed Critical
Publication of JP2022105979A publication Critical patent/JP2022105979A/ja
Publication of JP2022105979A5 publication Critical patent/JP2022105979A5/ja
Application granted granted Critical
Publication of JP7783717B2 publication Critical patent/JP7783717B2/ja
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

JP2021174539A 2021-01-05 2021-10-26 一体化された犠牲表面を備えた複合スパー Active JP7783717B2 (ja)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US202163134071P 2021-01-05 2021-01-05
US63/134,071 2021-01-05

Publications (3)

Publication Number Publication Date
JP2022105979A JP2022105979A (ja) 2022-07-15
JP2022105979A5 true JP2022105979A5 (enExample) 2025-10-20
JP7783717B2 JP7783717B2 (ja) 2025-12-10

Family

ID=82219926

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2021174539A Active JP7783717B2 (ja) 2021-01-05 2021-10-26 一体化された犠牲表面を備えた複合スパー

Country Status (2)

Country Link
US (1) US11981426B2 (enExample)
JP (1) JP7783717B2 (enExample)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2617556A (en) * 2022-04-08 2023-10-18 Airbus Operations Ltd Wing-box structure

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB9024387D0 (en) * 1990-11-09 1991-01-02 British Aerospace Carbon fibre composite wing manufacture
JP2000043796A (ja) 1998-07-30 2000-02-15 Japan Aircraft Development Corp 複合材の翼形構造およびその成形方法
JP5476916B2 (ja) 2009-10-16 2014-04-23 東レ株式会社 繊維強化プラスチックの製造方法
US9731453B2 (en) 2015-03-04 2017-08-15 The Boeing Company Co-curing process for the joining of composite structures
US20170274577A1 (en) 2016-03-24 2017-09-28 The Boeing Company Composite structures with stiffeners and method of making the same
US10220935B2 (en) 2016-09-13 2019-03-05 The Boeing Company Open-channel stiffener
US11247409B2 (en) 2017-03-16 2022-02-15 The Boeing Company Methods of co-bonding a first thermoset composite and a second thermoset composite to define a cured composite part
US10875625B2 (en) 2017-08-23 2020-12-29 The Boeing Company Co-cured spar and stringer center wing box
DE102017222897A1 (de) 2017-12-15 2019-06-19 MTU Aero Engines AG Faserverbund-Bauteilanordnung, Faserverbund-Bauteilsystem und Verfahren zum Herstellen eines Faserverbund-Bauteilsystems
US10974465B2 (en) 2018-06-20 2021-04-13 The Boeing Company Method and system for generating a layup plan for forming a composite laminate
GB2575280A (en) 2018-07-04 2020-01-08 Airbus Operations Ltd A Connector
RU2749432C1 (ru) * 2020-01-10 2021-06-10 Акционерное общество "АэроКомпозит" Способ модульной сборки стыковой нервюры самолета для соединения консолей крыла с центропланом и устройство для осуществления способа
US11673644B2 (en) * 2021-01-05 2023-06-13 The Boeing Company Composite spars with integrated sacrificial surfaces

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