SU1412193A1 - AIR-HEATED ANTI-FRONT SYSTEM OF AIRCRAFT - Google Patents

AIR-HEATED ANTI-FRONT SYSTEM OF AIRCRAFT

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Publication number
SU1412193A1
SU1412193A1 SU4037947/23A SU4037947A SU1412193A1 SU 1412193 A1 SU1412193 A1 SU 1412193A1 SU 4037947/23 A SU4037947/23 A SU 4037947/23A SU 4037947 A SU4037947 A SU 4037947A SU 1412193 A1 SU1412193 A1 SU 1412193A1
Authority
SU
USSR - Soviet Union
Prior art keywords
air
aircraft
cavity
source
inner shell
Prior art date
Application number
SU4037947/23A
Other languages
Russian (ru)
Inventor
Е.И. Васькович
О.Н. Кашелевский
Ю.А. Куранов
Original Assignee
Е.И. Васькович
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 Е.И. Васькович filed Critical Е.И. Васькович
Priority to SU4037947/23A priority Critical patent/SU1412193A1/en
Application granted granted Critical
Publication of SU1412193A1 publication Critical patent/SU1412193A1/en

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Abstract

1. Воздушно-тепловая противообледенительная система летательного аппарата, содержащая источник сжатого воздуха, соединенный трубопроводами подвода воздуха с полостью горячего воздуха, выполненной между обогреваемой обшивкой и внутренней оболочкой, отличающаяся тем, что, с целью повышения экономичности системы, источник сжатого воздуха выполнен в виде компрессора, установленного на валу маршевого двигателя, при этом вход компрессора соединен с холодной полостью, образованной внутренней оболочкой, в которой выполнены отверстия.2. Система по п.1, отличающаяся тем, что в горячей полости установлены продольные перегородки, образующие каналы.1. Air-thermal anti-icing system of the aircraft, containing a source of compressed air connected by pipelines for supplying air with a cavity of hot air, made between heated skin and the inner shell, characterized in that, in order to improve the efficiency of the system, the source of compressed air is designed as a compressor mounted on the main engine shaft, while the compressor inlet is connected to a cold cavity formed by the inner shell in which the holes are made. A system according to claim 1, characterized in that longitudinal partitions forming channels are installed in the hot cavity.

SU4037947/23A 1986-03-17 1986-03-17 AIR-HEATED ANTI-FRONT SYSTEM OF AIRCRAFT SU1412193A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SU4037947/23A SU1412193A1 (en) 1986-03-17 1986-03-17 AIR-HEATED ANTI-FRONT SYSTEM OF AIRCRAFT

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SU4037947/23A SU1412193A1 (en) 1986-03-17 1986-03-17 AIR-HEATED ANTI-FRONT SYSTEM OF AIRCRAFT

Publications (1)

Publication Number Publication Date
SU1412193A1 true SU1412193A1 (en) 2005-02-20

Family

ID=60535998

Family Applications (1)

Application Number Title Priority Date Filing Date
SU4037947/23A SU1412193A1 (en) 1986-03-17 1986-03-17 AIR-HEATED ANTI-FRONT SYSTEM OF AIRCRAFT

Country Status (1)

Country Link
SU (1) SU1412193A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2736706C2 (en) * 2016-05-02 2020-11-19 Зе Боинг Компани Systems and methods for preventing formation of ice on aircraft parts

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2736706C2 (en) * 2016-05-02 2020-11-19 Зе Боинг Компани Systems and methods for preventing formation of ice on aircraft parts

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