RU93056603A - VENE FROM THERMOPLASTIC COMPOSITE MATERIAL, IN PARTICULAR FOR THE HELICOPTER TAIL OF SCREW, AND METHOD FOR ITS MANUFACTURE - Google Patents

VENE FROM THERMOPLASTIC COMPOSITE MATERIAL, IN PARTICULAR FOR THE HELICOPTER TAIL OF SCREW, AND METHOD FOR ITS MANUFACTURE

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Publication number
RU93056603A
RU93056603A RU93056603/11A RU93056603A RU93056603A RU 93056603 A RU93056603 A RU 93056603A RU 93056603/11 A RU93056603/11 A RU 93056603/11A RU 93056603 A RU93056603 A RU 93056603A RU 93056603 A RU93056603 A RU 93056603A
Authority
RU
Russia
Prior art keywords
composite material
shell
thermoplastic composite
blade
spar
Prior art date
Application number
RU93056603/11A
Other languages
Russian (ru)
Other versions
RU2113379C1 (en
Inventor
Антуан Обрий Жак
Луи Коффий Рене
Original Assignee
Эрокоптер Франс
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 FR9215608A external-priority patent/FR2699499B1/en
Application filed by Эрокоптер Франс filed Critical Эрокоптер Франс
Publication of RU93056603A publication Critical patent/RU93056603A/en
Application granted granted Critical
Publication of RU2113379C1 publication Critical patent/RU2113379C1/en

Links

Claims (1)

Лопасть содержит нижнюю и верхнюю части ее оболочки, передний и задний элементы заполнения этой оболочки и лонжерон из композиционного материала, состоящего из одной и той же матрицы, термопластичной и представляющей собой синтетическую смолу РЕЕК, армированной предпочтительно угольными волокнами. Лонжерон продолжается за пределами оболочки крепежной частью лопасти, жестко соединенной с петлеобразной или слоистой крепежной деталью, служащей для соединения с втулкой винта и выполненной из того же термопластичного композиционного материала. Способ заключается в том, что осуществляют сборку предварительно изготовленных в виде элементарных деталей: лонжерона и нижней и верхней частей оболочки лопасти с помощью литья под давлением сжиженного термопластичного композиционного материала с короткими армирующими волокнами, используемого для формирования элементов заполнения оболочки лопасти.The blade contains the lower and upper parts of its shell, the front and rear filling elements of this shell and the spar of a composite material consisting of the same matrix, thermoplastic and representing a synthetic resin REEK, preferably reinforced with carbon fibers. The spar extends beyond the envelope by the fastening part of the blade rigidly connected to a loop-shaped or laminated fastener serving to connect to the screw hub and made of the same thermoplastic composite material. The method consists in assembling prefabricated in the form of elementary parts: the spar and the lower and upper parts of the blade shell by injection molding a liquefied thermoplastic composite material with short reinforcing fibers used to form the filling elements of the blade shell.
RU93056603A 1992-12-23 1993-12-22 Blade made from thermoplastic composite material for helicopter tail rotor and method of manufacture of such blade RU2113379C1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9215608A FR2699499B1 (en) 1992-12-23 1992-12-23 Blade of thermoplastic composite, in particular for a faired tail rotor of a helicopter, and its manufacturing process with injection step.
FR9215608 1992-12-23

Publications (2)

Publication Number Publication Date
RU93056603A true RU93056603A (en) 1996-10-20
RU2113379C1 RU2113379C1 (en) 1998-06-20

Family

ID=9437030

Family Applications (1)

Application Number Title Priority Date Filing Date
RU93056603A RU2113379C1 (en) 1992-12-23 1993-12-22 Blade made from thermoplastic composite material for helicopter tail rotor and method of manufacture of such blade

Country Status (7)

Country Link
US (1) US5454693A (en)
EP (1) EP0604297B1 (en)
JP (1) JPH06219392A (en)
CA (1) CA2111887A1 (en)
DE (1) DE69303152T2 (en)
FR (1) FR2699499B1 (en)
RU (1) RU2113379C1 (en)

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KR20180031392A (en) * 2016-09-20 2018-03-28 다이텍연구원 Process Of Producing High―Tenacity Brading Tube Fraim Using Carbon Tow Fiber Prepreg
EP3406434A1 (en) 2017-05-22 2018-11-28 Ratier-Figeac SAS Composite blade and method of manufacture
EP3406424B1 (en) * 2017-05-22 2021-04-28 Ratier-Figeac SAS Aircraft blade and methods of forming and repairing an aircraft blade
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