RU2003120996A - GAS STEERING ROCKET ENGINE - Google Patents

GAS STEERING ROCKET ENGINE

Info

Publication number
RU2003120996A
RU2003120996A RU2003120996/06A RU2003120996A RU2003120996A RU 2003120996 A RU2003120996 A RU 2003120996A RU 2003120996/06 A RU2003120996/06 A RU 2003120996/06A RU 2003120996 A RU2003120996 A RU 2003120996A RU 2003120996 A RU2003120996 A RU 2003120996A
Authority
RU
Russia
Prior art keywords
protrusion
plate
rocket engine
connection
gas steering
Prior art date
Application number
RU2003120996/06A
Other languages
Russian (ru)
Other versions
RU2251013C2 (en
Inventor
Юрий Иванович Кустов (RU)
Юрий Иванович Кустов
Владимир Игнатьевич Зарицкий (RU)
Владимир Игнатьевич Зарицкий
Юрий Леонидович Макаревич (RU)
Юрий Леонидович Макаревич
Original Assignee
Открытое акционерное общество Научно-производственное объединение "Искра" (RU)
Открытое акционерное общество Научно-производственное объединение "Искра"
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 Открытое акционерное общество Научно-производственное объединение "Искра" (RU), Открытое акционерное общество Научно-производственное объединение "Искра" filed Critical Открытое акционерное общество Научно-производственное объединение "Искра" (RU)
Priority to RU2003120996/06A priority Critical patent/RU2251013C2/en
Publication of RU2003120996A publication Critical patent/RU2003120996A/en
Application granted granted Critical
Publication of RU2251013C2 publication Critical patent/RU2251013C2/en

Links

Landscapes

  • Shaping Metal By Deep-Drawing, Or The Like (AREA)
  • Connection Of Plates (AREA)

Claims (1)

Газовый руль ракетного двигателя, содержащий перо, тарель с цилиндрическим выступом, вал, хвостовик которого с помощью кольцевой выточки через посредство разжимного кольца насажен на выступ тарели, элементы фиксации полученного соединения, отличающийся тем, что тарель и перо выполнены из отдельных деталей, связанных между собой шлицевым соединением, причем паз соединения выполнен в тарели вдоль ее диаметра, пересекает выступ и имеет ступенчатый профиль, более широкая часть которого находится в области выступа, а выступ выполнен на пере по профилю паза.The gas rudder of a rocket engine containing a pen, a plate with a cylindrical protrusion, a shaft, the shank of which, with the help of an annular recess through the expansion ring, is mounted on the plate protrusion, fixing elements of the obtained connection, characterized in that the plate and the pen are made of separate parts interconnected splined connection, and the connection groove is made in the plate along its diameter, crosses the protrusion and has a stepped profile, the wider part of which is in the region of the protrusion, and the protrusion is made on the along the groove profile.
RU2003120996/06A 2003-07-08 2003-07-08 Rocket engine jet vane RU2251013C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2003120996/06A RU2251013C2 (en) 2003-07-08 2003-07-08 Rocket engine jet vane

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2003120996/06A RU2251013C2 (en) 2003-07-08 2003-07-08 Rocket engine jet vane

Publications (2)

Publication Number Publication Date
RU2003120996A true RU2003120996A (en) 2005-01-10
RU2251013C2 RU2251013C2 (en) 2005-04-27

Family

ID=34881587

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2003120996/06A RU2251013C2 (en) 2003-07-08 2003-07-08 Rocket engine jet vane

Country Status (1)

Country Link
RU (1) RU2251013C2 (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2579294C1 (en) * 2015-06-16 2016-04-10 Акционерное общество "Конструкторское бюро химавтоматики" Liquid rocket engine with baffle at nozzle section
RU2631370C1 (en) * 2016-05-04 2017-09-21 Акционерное общество "Конструкторское бюро химавтоматики" Liquid rocket engine with deflector sectors at the nozzle exit
CN111946461A (en) * 2020-07-27 2020-11-17 山东鑫聚龙动力科技集团有限公司 Wing shaft for aerospace engine and manufacturing process thereof

Also Published As

Publication number Publication date
RU2251013C2 (en) 2005-04-27

Similar Documents

Publication Publication Date Title
CY1109193T1 (en) ROTATED LOCK HEAD
RU2007128095A (en) TORQUE RIGID STATOR ASSEMBLY FOR AIRCRAFT ENGINE
BR0115563A (en) Bearing for fixing a steering axle
RU2004101283A (en) FASTENING ELEMENT FOR HEAT-INSULATING GLASS PACKAGE
US4004499A (en) Bolt-on piston assembly
RU2003120996A (en) GAS STEERING ROCKET ENGINE
KR920006621A (en) Arrangement of blade rings in steam turbine
RU2006140355A (en) BIKALIBLE ROCKET
RU2001116832A (en) NOZZLE
RU2000112276A (en) GAS TURBINE ENGINE
KR101255864B1 (en) Viscose damper comprising a sheet metal housing
RU2001121406A (en) GAS STEERING ROCKET ENGINE
WO2004079212A3 (en) Combined radial and axial bearing
DE60219270D1 (en) Sound-absorbing starting flywheel
RU2001112236A (en) GAS TURBINE ENGINE
RU2002120689A (en) COMBINED DISCONNECTING CHARGE
RU2002113620A (en) COMBAT PART
SU1691610A1 (en) Sliding contact bearing
DE10344404A1 (en) Hydraulic support element for valve gear of internal combustion engine has housing torsionally fixed in relation to cylinder head holder, with radial passage positioned at highest point of housing's circumferential section
RU2000116336A (en) BEARING ASSEMBLY
RU2003104040A (en) TURBINE OF A GAS-TURBINE ENGINE
KR930021996A (en) Camshaft
RU2001110901A (en) LOW-THROUGH LIQUID ROCKET ENGINE
RU2002131694A (en) SOLID FUEL ROCKET ENGINE
RU2003125302A (en) SUBMARINE BODY PRELIMINARY STRESSED BY CONSTANT FORCE

Legal Events

Date Code Title Description
MM4A The patent is invalid due to non-payment of fees

Effective date: 20120709