Thermal radiation from solid propellant rocket motor plume

Download

index.pdf

Date

2015

Author

Özen, Güzide

Metadata

Show full item record

Item Usage Stats

550
views

246
downloads

Radiation emitted from rocket plumes plays a significant role in quantifying infrared (IR) radiative signature which is essential for identification and tracking of rockets. Prediction of plume radiation necessitates simultaneous solution of conservation equations for mass, momentum, energy, chemical species and radiant energy to provide input data for the radiation code. This is carried out by a Computational Fluid Dynamics (CFD) solver. As CFD solvers are CPU time expensive, an accurate and CPU efficient solution method of radiative transfer equation (RTE) and a less accurate but CPU efficient radiative property estimation technique are usually employed in these solvers. However, radiation code for prediction of plume radiation necessitates an accurate and CPU efficient solution method of RTE as well as a highly accurate wavelength dependent radiative property estimation technique. Therefore, predictive accuracy and CPU efficiency of RTE solvers and radiative property estimation techniques were first evaluated by applying the code to different 3-D enclosures containing non-grey, absorbing-emitting-scattering media and benchmarking their predictions against reference solutions and measurements. Comparisons reveal that as RTE solver Discrete Ordinates Method (DOM) for both CFD solver and radiation code and as radiative property estimation techniques Spectral Line-based Weighted Sum of Grey Gases (SLW) and Statistical Narrow-Band Correlated-k (SNBCK) for CFD solver and radiation code, respectively, satisfy the requirements. This was followed by running the CFD solver, ANSYS FLUENT v.15.0 with and without radiation in order to see the effect of radiation on the input data provided to the radiation code. CFD solver without radiation was found to be accurate and CPU efficient. Radiation code based on DOM with SNBCK for gas and Mie Theory for particles was developed to predict plume radiation for non-aluminized and aluminized propellants. For non-aluminized propellant, the prediction accuracy and computational efficiency of radiation code was tested by comparing its predictions with measurements available in the literature. Predictions were found to be in good agreement with measured data. Predictions of spectral radiant intensity under aluminized propellant case were found to be higher than those of non-aluminized propellant due to the use of higher temperature profiles and radiative properties of particles under aluminized propellant case.

Subject Keywords

Propellants., Solid propellants., Plumes (Fluid Dynamics)., Computational fluid Dynamics.

URI

http://etd.lib.metu.edu.tr/upload/12619117/index.pdf
https://hdl.handle.net/11511/24817

Collections

Graduate School of Natural and Applied Sciences, Thesis

Suggestions

OpenMETU
Core

Static aeroelastic modeling and parametric study of stacking sequence for laminated composite missile fins Aslan, Göktuğ Murat; Kurtuluş, Dilek Funda; Department of Aerospace Engineering (2018) In this thesis, a surface-to-surface missile model with laminated composite fins is examined with respect to one-way static aeroelastic response under constant supersonic flight conditions. Two different modified double wedge fins or control surfaces using for control actuation system of a missile are investigated and compared in terms of aerodynamic and linear structural characteristics in order to minimize tip deflection. A serial set of steady-state supersonic Computational Fluid Dynamics (CFD) analyses ...
Use of artificial neural network in rotorcraft cooling system Akin, Altug; Kahveci, Harika Senem (2019-07-01) In this study, an Artificial Neural Network (ANN) is used to determine the surface temperatures of the avionics equipment located in an avionics bay of a rotorcraft. The bay is cooled via a system of a fan that supplies ambient air to the interior of the bay and an exhaust. A Feedforward Multi-Layer ANN is used with the input parameters of the fan and exhaust locations and the air mass flow rate of the fan. For training of the network, the results obtained by a large number of Computational Fluid Dynamics (...
Improving flow structure and natural convection within fin spacings of plate fin heat sinks Özet, Mehmet Erdem; Tarı, İlker; Department of Mechanical Engineering (2015) The main objectives of this thesis are to numerically investigate the previously observed recirculation zones and longitudinal vortices that occur in low fin height plate finned horizontal heat sinks and to improve the flow structures and heat transfer in these zones using various approaches with the help of simulations performed using commercially available CFD software. The approaches used for improvements are replacing the outer most fins with higher ones, introducing gaps on the length of the fins in va...
Performance prediction of nozzleless solid propellant rocket motors Özer, Ali Can; Özyörük, Yusuf; Department of Aerospace Engineering (2015) Integral rocket ramjet (IRR) type propulsion systems have many advantages over conventional solid rocket motors when used in tactical missile systems. Nozzleless boosters are one of the applicable concept choices for the system [1]. During the design and development phase of solid propellant rocket motors, simulation and prediction of behavior of a given motor by numerical tools is important in terms of decreasing the development duration and costs. The present approach includes performance prediction of no...
Thermal Infrared Hyperspectral Dimension Reduction Experiment Results For Global And Local Information Based Linear Discriminant Analysis Sakarya, Ufuk (2015-05-19) Thermal infrared hyperspectral image processing has become an important research topic in remote sensing. One of the research topics in thermal infrared hyperspectral image classification is dimension reduction. In this paper, thermal infrared hyperspectral dimension reduction experiment results for global and local information based linear discriminant analysis is presented. Advantages of the use of not only global pattern information, but also local pattern information are tested in thermal infrared hyper...

Citation Formats

G. Özen, “Thermal radiation from solid propellant rocket motor plume,” Ph.D. - Doctoral Program, Middle East Technical University, 2015.