Three-dimensional retarding walls and flow in their vicinity

Download
index.pdf
2004
Toker, Kemal Atılgan
Show full item record
137
views
118
downloads
The performance prediction of solid propellant rocket motor depends on the calculation of internal aerodynamics of the motor through its operational life. In order to obtain the control volume, in which the solutions will be carried out, a process called أgrain burnback calculationؤ is required. During the operation of the motor, as the interface between the solid and gas phases moves towards the solid propellant in a direction normal to the surface, the combustion products are generated and added into the control volume. This phenomenon requires handling of moving boundaries as the solution proceeds. In this thesis, Fast Marching Method is implemented to the problem of grain burnback. This method uses the upwinding nature of the propellant interface motion and solves the Eikonal type equations on a fixed three-dimensional tetrahedron mesh. The control volume is coupled to a one-dimensional and a three-dimensional Euler aerodynamic solver in order to obtain the performance of the engine. The speed by which the interface moves depends on the static pressure on the surface of the propellant and comes from the solver. Therefore an iterative method has been proposed between the interface capturing algorithms and the flow solver. Both of the calculation results, which are obtained from one-dimensional and three-dimensional solvers are compared with actual rocket firing data and validated.
Solid propellant rockets., Solid propellant.
http://etd.lib.metu.edu.tr/upload/12605668/index.pdf
https://hdl.handle.net/11511/15045
Graduate School of Natural and Applied Sciences, Thesis

Suggestions

3-D grain burnback analysis of solid propellant rocket motors: Part 2-modeling and simulations
Puskulcu, G.; Ulaş, Abdullah (2008-12-01)
Determination of the grain geometry is an important step in the design of solid propellant rocket motors. The performance prediction of the solid rocket motor can be achieved easily if the burnback steps of the grain are known. fit this study, grain burnback analysis for 3-D grain geometries wits investigated. The method used was solid modeling of the propellant grain for predefined intervals of burnback. In this method, the initial grain geometry was modeled parametrically using CAD software. For every bur...
Investigating the dominant factors regarding ignition transient in the design procedure of the nozzle of a pyrogen igniter
Yeşilyurt, Yavuz; Güvenç Yazıcıoğlu, Almıla; Department of Mechanical Engineering (2019)
In a standard solid rocket motor (SRM) system, the propellant of the SRM is generally ignited by a pyrotechnic device (which is much smaller in size compared to SRM itself). However, grand systems like solid propellant Space Propulsion Systems need more mass flow rate in a very short time duration to be ignited, which is not easy task for a pyrotechnic igniter. The solution for this issue is utilizing pyrogen igniter in the SRM system, which is both a small-scale SRM and an igniter. Here ignition transient ...
The Effects of geometric design parameters on the flow behavior of a dual pulse solid rocket motor during secondary firing
Ertuğrul, Suat Erdem; Kurtuluş, Dilek Funda; Ulaş, Abdullah; Department of Aerospace Engineering (2012)
The ability of a propulsion system is very crucial for the capability of a missile or a rocket system. Unlike liquid propellant rocket motors, the only control mechanism of the thrust value is the propellant geometry in solid propellant rocket motors. When the operation of solid propellant rocket motor has started, it cannot be stopped anymore. For this main reason the advance of dual pulse motor technology has started. The aim of this study is to investigate the geometrical effects of design parameters on ...
Ultrasonic measurement of solid propellant burning rates in closed bombs and subscale motors
Atak, Özen; Yamalı, Cemil; Department of Mechanical Engineering (2016)
In the scope of this thesis, applications of ultrasonic measurement method on closed bombs and test motors were investigated with various aluminized and nonaluminized propellants with the main target of evaluation of burning rates. Detailed comparison between conventional methods for solid propellant burning rate measurements such as strand burner, firing of subscale test motors and ultrasonic measurement was performed. Burning rate evaluation of eight propellant batches were determined by thirty three clos...
Ballistic design optimization of three-dimensional grains using genetic algorithms
Yücel, Osman; Aksel, Mehmet Haluk; Department of Mechanical Engineering (2012)
Within the scope of this thesis study, an optimization tool for the ballistic design of three-dimensional grains in solid propellant rocket motors is developed. The modeling of grain geometry and burnback analysis is performed analytically by using basic geometries like cylinder, cone, sphere, ellipsoid, prism and torus. For the internal ballistic analysis, a quasi-steady zero-dimensional flow solver is used. Genetic algorithms have been studied and implemented to the design process as an optimization algor...
Citation Formats
K. A. Toker, “Three-dimensional retarding walls and flow in their vicinity,” Ph.D. - Doctoral Program, Middle East Technical University, 2004.
METU IIS - Integrated Information Service open@metu.edu.tr