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Optimisation of a Rocket Nozzle Side Load Reduction Device

Stark, Ralf and Génin, Ch. (2012) Optimisation of a Rocket Nozzle Side Load Reduction Device. In: Proceedings. 48th AIAA Joint Propulsion Conference, 30. Jul. - 1. Aug 2012, Atlanta, GA, USA.

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Abstract

The flow during transient startup and shutdown in all rocket engines operated on sea level under ambient conditions will separate inside the supersonic part of the nozzle. A separated nozzle flow is circumferential asymmetric distributed and induces high side loads. DLR carried out a cold flow subscale test campaign to study devices that can reduce the side loads during transient operation of a thrust optimised parabolic nozzle. A detailed parametrical study was performed and experimental data demonstrate the potential of the device to reduce the side loads.

Item URL in elib:https://elib.dlr.de/77680/
Document Type:Conference or Workshop Item (Speech, Paper)
Title:Optimisation of a Rocket Nozzle Side Load Reduction Device
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Stark, RalfRalf.Stark (at) dlr.dehttps://orcid.org/0000-0003-1923-1901
Génin, Ch.Chloe.Genin (at) dlr.deUNSPECIFIED
Date:2012
Journal or Publication Title:Proceedings
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Status:Published
Keywords:nozzle flow, side loads, flow separation
Event Title:48th AIAA Joint Propulsion Conference
Event Location:Atlanta, GA, USA
Event Type:international Conference
Event Dates:30. Jul. - 1. Aug 2012
Organizer:AIAA
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Transport
DLR - Research area:Raumfahrt
DLR - Program:R RP - Raumtransport
DLR - Research theme (Project):R - Antriebsystemtechnik - Schubkammertechnologie
Location: Lampoldshausen
Institutes and Institutions:Institute of Space Propulsion > Rocket Propulsion
Deposited By: Nürnberger-Genin, Chloe
Deposited On:08 Oct 2012 20:26
Last Modified:01 Dec 2018 19:48

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