elib
DLR-Header
DLR-Logo -> http://www.dlr.de
DLR Portal Home | Imprint | Privacy Policy | Contact | Deutsch
Fontsize: [-] Text [+]

Combustion modeling in solid rocket motor plumes

Ecker, Tobias and Karl, Sebastian and Hannemann, Klaus (2019) Combustion modeling in solid rocket motor plumes. In: 8th European Conference for Aeronautics and Space Sciences 2019. 8th European Conference for Aeronautics and Space Sciences 2019, 1 - 4 Juli, 2019, Madrid, Spanien.

[img] PDF - Registered users only until 31 December 2021
4MB

Official URL: http://www.eucass2019.eu/

Abstract

Plumes emanating from solid rocket motors (SRM) exhibit flow statistics strongly influenced by complex hydrogen/oxygen/chlorine chemistry. These after burning reactions within the plume have a significant impact onto the infrared (IR) irradiance signature, as well as on the chemical erosion of any active or passive mechanical steering system exposed to the reactive motor plume. As SRM combustion chambers operate at oxidizer-fuel ratios considerably less than stoichiometric, afterburning within the plume shear layer occurs. Asides from the intermediate thermochemical loads of the plume on the launch vehicle, the resulting plume exhaust gases of Ammonium perchlorate (AP) based SRM may also have an impact on ozone layer depletion1,2 in the atmosphere and the biosphere of the launch site.3 Within this study we provide an overview on the currently available combustion mechanism and evaluate their applicability to SRM plume modeling. For a preliminary evaluation, the performance of the considered mechanisms is evaluated using a constant volume reactor. Based on the results an improved 28 reaction skeletal kinetic model is proposed and validated against detailed mechanisms in constant volume reactor test cases and a counter-flowing diffusion flame. Subsequently, selected mechanisms are applied in Reynolds-averaged Navier-Stokes CFD calculations of a small scale AP/HTPB SRM plume test case. From the evaluation of the plume thermochemistry it can be shown that the proposed model offers improved performance at lower computational costs. The results of this study offer a relevant evaluation of the performance of current SRM finite rate chemistry models and their impact on flowfield characteristics and are helpful for future scale-resolved simulations of multispecies, reactive solid-rocket motor plumes.

Item URL in elib:https://elib.dlr.de/126478/
Document Type:Conference or Workshop Item (Speech)
Title:Combustion modeling in solid rocket motor plumes
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Ecker, TobiasTobias.Ecker (at) dlr.dehttps://orcid.org/0000-0001-7134-1185
Karl, SebastianSebastian.Karl (at) dlr.deUNSPECIFIED
Hannemann, Klausklaus.hannemann (at) dlr.deUNSPECIFIED
Date:July 2019
Journal or Publication Title:8th European Conference for Aeronautics and Space Sciences 2019
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Status:Published
Keywords:solid rocket combustion, SRM, plume
Event Title:8th European Conference for Aeronautics and Space Sciences 2019
Event Location:Madrid, Spanien
Event Type:international Conference
Event Dates:1 - 4 Juli, 2019
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):Project ATEK, R - Raumfahrzeugsysteme - Numerische Verfahren und Simulation
Location: Göttingen
Institutes and Institutions:Institute for Aerodynamics and Flow Technology > Spacecraft, GO
Deposited By: Ecker, Tobias
Deposited On:18 Jul 2019 16:01
Last Modified:18 Jul 2019 16:01

Repository Staff Only: item control page

Browse
Search
Help & Contact
Information
electronic library is running on EPrints 3.3.12
Copyright © 2008-2017 German Aerospace Center (DLR). All rights reserved.