UA86958C2 - Liquid rocket engine with regulated thrust vector - Google Patents

Liquid rocket engine with regulated thrust vector

Info

Publication number
UA86958C2
UA86958C2 UAA200607625A UAA200607625A UA86958C2 UA 86958 C2 UA86958 C2 UA 86958C2 UA A200607625 A UAA200607625 A UA A200607625A UA A200607625 A UAA200607625 A UA A200607625A UA 86958 C2 UA86958 C2 UA 86958C2
Authority
UA
Ukraine
Prior art keywords
nozzle
injection
unit
thrust vector
collector
Prior art date
Application number
UAA200607625A
Other languages
Russian (ru)
Ukrainian (uk)
Inventor
Николай Дмитриевич Коваленко
Геннадий Афанасьевич Стрельников
Галина Николаевна Коваленко
Александр Владимирович Хоменко
Тит Александрович Коваленко
Наталья Петровна Сироткина
Original Assignee
Институт Технической Механики Нану И Нкау
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 Институт Технической Механики Нану И Нкау filed Critical Институт Технической Механики Нану И Нкау
Priority to UAA200607625A priority Critical patent/UA86958C2/en
Publication of UA86958C2 publication Critical patent/UA86958C2/en

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  • Jet Pumps And Other Pumps (AREA)

Abstract

A liquid rocket engine with controlled thrust vector has a combustion chamber with nozzle, turbo-pump system for supply of fuel components to the combustion chamber, turbine exhaust collector of which is connected to circular collector of unit for exhaust gas injection to supersonic section of the nozzle. Upstream of circular slot of unit for exhaust gas injection in each one fourth section of the nozzle units for fuel component injection are installed, those are connected to fuel high-pressure line of engine placed downstream of outlet collector of cooling section of the chamber and connected to drives controlled by the system for engine thrust vector control. Each injection unit has either centrifugal, or jet injection nozzles provided in the wall of the nozzle or in movable two-position solid interceptor in the part that is introduced to supersonic flow of the nozzle, at that at inlet to each injection unit a generator of pressure pulses of liquid fuel component supplied to nozzle is installed.
UAA200607625A 2006-07-07 2006-07-07 Liquid rocket engine with regulated thrust vector UA86958C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
UAA200607625A UA86958C2 (en) 2006-07-07 2006-07-07 Liquid rocket engine with regulated thrust vector

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
UAA200607625A UA86958C2 (en) 2006-07-07 2006-07-07 Liquid rocket engine with regulated thrust vector

Publications (1)

Publication Number Publication Date
UA86958C2 true UA86958C2 (en) 2009-06-10

Family

ID=50631594

Family Applications (1)

Application Number Title Priority Date Filing Date
UAA200607625A UA86958C2 (en) 2006-07-07 2006-07-07 Liquid rocket engine with regulated thrust vector

Country Status (1)

Country Link
UA (1) UA86958C2 (en)

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