RU2001114577A - ROCKET NOZZLE CIRCUIT FOR CONTROL OF FLOW SEPARATION AND DECREASE OF LATERAL LOAD - Google Patents

ROCKET NOZZLE CIRCUIT FOR CONTROL OF FLOW SEPARATION AND DECREASE OF LATERAL LOAD

Info

Publication number
RU2001114577A
RU2001114577A RU2001114577/06A RU2001114577A RU2001114577A RU 2001114577 A RU2001114577 A RU 2001114577A RU 2001114577/06 A RU2001114577/06 A RU 2001114577/06A RU 2001114577 A RU2001114577 A RU 2001114577A RU 2001114577 A RU2001114577 A RU 2001114577A
Authority
RU
Russia
Prior art keywords
profile
rocket nozzle
decrease
derivative
control
Prior art date
Application number
RU2001114577/06A
Other languages
Russian (ru)
Other versions
RU2209333C2 (en
Inventor
Ян ХАГГАНДЕР
Ян МАТТССОН
Матс ОЛОФССОН
Йон АНГГАРД
Original Assignee
Вольво Аэро Корпорейшн
Filing date
Publication date
Application filed by Вольво Аэро Корпорейшн filed Critical Вольво Аэро Корпорейшн
Priority claimed from PCT/SE1998/002222 external-priority patent/WO2000034641A1/en
Publication of RU2001114577A publication Critical patent/RU2001114577A/en
Application granted granted Critical
Publication of RU2209333C2 publication Critical patent/RU2209333C2/en

Links

Claims (2)

1. Полнопоточное ракетное сопло, профиль которого в продольном сечении, по существу, соответствует параболе, отличающееся тем, что, начиная от точки, соответствующей коэффициенту расширения, равному 50%, параболический контур сопла в направлении от его критического сечения (горловины) преобразуется в (1) строго конический профиль с углом при вершине между 15o и 25o, (2) криволинейный профиль с небольшой выгнутостью наружу, т. е. профиль, характеризующийся положительной второй производной радиуса r, или (3) криволинейный профиль с небольшой вогнутостью внутрь, т. е. профиль, характеризующийся отрицательной второй производной радиуса r, но лежащий снаружи параболического контура, причем в последнем варианте третья производная r постоянно равна нулю.1. A full-flow rocket nozzle, the profile of which in longitudinal section essentially corresponds to a parabola, characterized in that, starting from a point corresponding to an expansion coefficient of 50%, the parabolic contour of the nozzle in the direction from its critical section (neck) is converted to ( 1) strictly conical profile with an apex angle of between 15 o and 25 o, (2) a curved profile with a small, outwardly convex, ie. e. profile characterized by a positive second derivative of the radius r, or (3) a curved profile with a slight concave Stu inward m. e. profile characterized by a negative second derivative of the radius r, but a parabolic contour lying outside, in the latter embodiment, the third derivative constant r is zero. 2. Полнопоточное ракетное сопло по п. 1, отличающееся тем, что в переходной зоне от параболического контура в контуре предусмотрен скачок, выбранный в интервале от 0 до 6o.2. Full-flow rocket nozzle according to claim 1, characterized in that in the transition zone from the parabolic contour in the contour there is a jump selected in the range from 0 to 6 o .
RU2001114577/06A 1998-12-04 1998-12-04 Conour of rocket nozzle to control division of flow and reduct side load RU2209333C2 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/SE1998/002222 WO2000034641A1 (en) 1998-12-04 1998-12-04 Rocket nozzle contour for flow separation control and side load reduction

Publications (2)

Publication Number Publication Date
RU2001114577A true RU2001114577A (en) 2003-02-20
RU2209333C2 RU2209333C2 (en) 2003-07-27

Family

ID=20411802

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2001114577/06A RU2209333C2 (en) 1998-12-04 1998-12-04 Conour of rocket nozzle to control division of flow and reduct side load

Country Status (7)

Country Link
US (1) US6574964B1 (en)
EP (1) EP1135588A1 (en)
JP (1) JP2002531766A (en)
CN (1) CN1322275A (en)
RU (1) RU2209333C2 (en)
UA (1) UA46175C2 (en)
WO (1) WO2000034641A1 (en)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2882401B1 (en) * 2005-02-22 2007-05-11 Agence Spatiale Europeenne DEVICE AND METHOD FOR REDUCING NON-STATIONARY SIDE FORCES ACTING ON A TUYERE OF A FUSEE ENGINE
US20080264372A1 (en) * 2007-03-19 2008-10-30 Sisk David B Two-stage ignition system
DE102010042890B4 (en) 2010-10-25 2020-07-30 Deutsches Zentrum für Luft- und Raumfahrt e.V. Engine device for a missile, test bench or launch pad for a missile and method for reducing a side load in an engine device
AT511466B1 (en) 2011-08-03 2012-12-15 Hoerbiger Kompressortech Hold FLUID MIXER
US9009966B2 (en) * 2013-03-15 2015-04-21 Northrop Gurmman Systems Corporation Internal/external single expansion ramp nozzle with integrated third stream
RU2531161C1 (en) * 2013-04-24 2014-10-20 Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") Axisymmetric nozzle of rocket engine
RU2552020C2 (en) * 2013-09-23 2015-06-10 Государственный научный центр Российской Федерации-федеральное государственное унитарное предприятие "Исследовательский Центр имени М.В. Келдыша" Rocket engine nozzle
DE102015011958B4 (en) 2015-09-18 2024-02-01 Arianegroup Gmbh Thruster
KR20200114123A (en) 2019-03-27 2020-10-07 엘지전자 주식회사 An air conditioning apparatus

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US3352495A (en) * 1965-01-29 1967-11-14 Thiokol Chemical Corp Nozzle construction
US3394549A (en) 1965-07-06 1968-07-30 North American Rockwell Step nozzle
FR2602275B1 (en) * 1986-08-04 1990-08-10 Onera (Off Nat Aerospatiale) IMPROVEMENTS ON PROPELLER NOZZLES FOR REDUCING SIDE EFFORT
FR2618488B1 (en) 1987-07-20 1989-12-15 Europ Propulsion DIVERGENT WITH BREAKING GALBE FOR NOZZLE OF MOTOR-ROCKET
US6324833B1 (en) * 1990-04-24 2001-12-04 Cordant Technologies, Inc. Reinforced composite articles and method of making same
FR2705739B1 (en) 1993-05-28 1995-08-18 Europ Propulsion Rocket engine nozzle with selectively reduced outlet section.
FR2705737B1 (en) 1993-05-28 1995-08-18 Europ Propulsion Scalloped rocket engine nozzle.
WO1997029277A1 (en) * 1996-02-12 1997-08-14 Volvo Aero Corporation Rocket engine nozzle
NL1004193C2 (en) 1996-04-01 1997-10-02 Sjoerd Meijer Method for processing metal sheet.
DE69621638T2 (en) * 1996-09-23 2002-11-07 Volvo Aero Corp., Trollhaettan TEMPERATURE CONTROLLED ROCKET NOZZLE
DE19755732C2 (en) 1997-12-15 2000-01-13 Waeschle Gmbh Process for the production of granules from polymeric materials

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