SU614609A1 - METHOD OF MANUFACTURING WAFER PANELS OF AIRCRAFT - Google Patents

METHOD OF MANUFACTURING WAFER PANELS OF AIRCRAFT

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Publication number
SU614609A1
SU614609A1 SU2408390/23A SU2408390A SU614609A1 SU 614609 A1 SU614609 A1 SU 614609A1 SU 2408390/23 A SU2408390/23 A SU 2408390/23A SU 2408390 A SU2408390 A SU 2408390A SU 614609 A1 SU614609 A1 SU 614609A1
Authority
SU
USSR - Soviet Union
Prior art keywords
aircraft
ribs
longitudinal
manufacturing wafer
manufacturing
Prior art date
Application number
SU2408390/23A
Other languages
Russian (ru)
Inventor
К.А. Курьянский
Л.Р. Бальшин
А.А. Веселов
Original Assignee
РљСѓСЂСЊСЏРЅСЃРєРёР№ Рљ.Рђ.
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
Application filed by РљСѓСЂСЊСЏРЅСЃРєРёР№ Рљ.Рђ. filed Critical РљСѓСЂСЊСЏРЅСЃРєРёР№ Рљ.Рђ.
Priority to SU2408390/23A priority Critical patent/SU614609A1/en
Application granted granted Critical
Publication of SU614609A1 publication Critical patent/SU614609A1/en

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Abstract

Способ изготовления вафельных панелей летательного аппарата, включающий фрезерование панели с образованием продольных и поперечных ребер, отличающийся тем, что, с целью снижения трудоемкости изготовления и увеличения коэффициента использования материала, в нем после образования продольных ребер выполнение поперечных ребер осуществляют путем установки вкладышей между продольными ребрами, с последующим соединением их с продольными ребрами и панелью сквозным проплавлением, после чего вкладыши фрезеруют с двух сторон до расчетной толщины.A method of manufacturing wafer panels of the aircraft, including milling the panel with the formation of longitudinal and transverse ribs, characterized in that, in order to reduce the complexity of manufacturing and increase the utilization rate of the material, after the formation of longitudinal ribs, the transverse ribs are made by installing liners between the longitudinal ribs, with their subsequent connection with longitudinal ribs and panel through penetration, after which the liners are milled from two sides to the calculated thickness ins.

SU2408390/23A 1976-10-04 1976-10-04 METHOD OF MANUFACTURING WAFER PANELS OF AIRCRAFT SU614609A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SU2408390/23A SU614609A1 (en) 1976-10-04 1976-10-04 METHOD OF MANUFACTURING WAFER PANELS OF AIRCRAFT

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SU2408390/23A SU614609A1 (en) 1976-10-04 1976-10-04 METHOD OF MANUFACTURING WAFER PANELS OF AIRCRAFT

Publications (1)

Publication Number Publication Date
SU614609A1 true SU614609A1 (en) 2005-03-20

Family

ID=60522335

Family Applications (1)

Application Number Title Priority Date Filing Date
SU2408390/23A SU614609A1 (en) 1976-10-04 1976-10-04 METHOD OF MANUFACTURING WAFER PANELS OF AIRCRAFT

Country Status (1)

Country Link
SU (1) SU614609A1 (en)

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