Investigating the dominant factors regarding ignition transient in the design procedure of the nozzle of a pyrogen igniter

Download

index.pdf

Date

2019

Author

Yeşilyurt, Yavuz

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

171
views

167
downloads

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 becomes a very important design subject, because an extra element is added to the ignition train of the SRM system when a pyrogen igniter is used. In this thesis work, the nozzle design of pyrogen igniters is investigated and the most dominant factors that pressurize (therefore, accelerate ignition) the grand SRM propellant empty volume and shorten the ignition transient duration are determined by a design of experiment (DOE) procedure. The series of test case simulations is made by a “Fully Coupled Compressible Solver for Turbulent Perfect Gas Flows”, which is designed to solve closed volume problems like shock tube interactions, in a systematic and comparable manner. Before starting DOE procedure, the solver is validated by a test case having an exact solution. The importance and junction of parameters that should be considered in nozzle design of pyrogen igniters are discussed in the end of the thesis work.

Subject Keywords

Solid propellant rocket engines., Pyrogen, Igniter, Solid Propellant Rocket Motor, Propulsion Systems.

URI

http://etd.lib.metu.edu.tr/upload/12624324/index.pdf
https://hdl.handle.net/11511/44632

Collections

Graduate School of Natural and Applied Sciences, Thesis

Suggestions

OpenMETU
Core

Determining service life and ageing characteristics of composite solid propellants by their chemical properties Kösa, Yasemin; Üner, Deniz; Kesik Mancar, Melis; Department of Chemical Engineering (2022-2) Solid composite propellants are widely used in rocket systems due to their extended manageability and practicality. Service life determination issue of these energetic materials is an extremely important subject as performance and operation safety of rockets may greatly be affected by ageing of propellant. In the literature, service life determination of composite propellants is commonly based on mechanical properties such as stress and strain parameters. In this study, direct monitoring of chemical alterat...
Three-dimensional retarding walls and flow in their vicinity Toker, Kemal Atılgan; Aksel, Mehmet Haluk; Department of Mechanical Engineering (2004) 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 ...
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 ...
Development of an iterative method for liquid-propellant combustion chamber instability analysis Cengiz, Kenan; Özyörük, Yusuf; Department of Aerospace Engineering (2010) Controlling unsteady combustion induced gas flow fluctuations and the resultant motor vibrations is a very significant step in rocket motor design. It occurs when the unsteady heat release due to combustion happens to feed the acoustic oscillations of the closed duct forming a feed-back system. The resultant vibrations concerned may even lead to total failure of the rocket system unless analysed and tested thoroughly. This thesis aims developing a linear numerical analysis method for the growth rate of inst...
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...

Citation Formats

Y. Yeşilyurt, “Investigating the dominant factors regarding ignition transient in the design procedure of the nozzle of a pyrogen igniter,” Thesis (M.S.) -- Graduate School of Natural and Applied Sciences. Mechanical Engineering., Middle East Technical University, 2019.