Application of ultrasonic burning rate measurement method on closed bombs

Download
2013
Mumcu, Berkan
In this thesis study, detailed information about solid rocket motors and ultrasonic burning rate measurement method is given. An experimental setup is prepared for applying the ultrasonic burning rate measurement method. Before performing the burning tests, some pre-tests are performed for affirming the ultrasonic sensor and obtaining some experimental coefficients. Two different types of propellants, which do not include aluminum, are produced for the burning tests. The first type of the propellants has two different batches while the second type has one batch. Coupling materials, which are compatible with these propellants, are prepared. Uncertainty analysis is performed to get burning rate uncertainties of ultrasonic burning rate measurement method and test motor firing method. After that, burning rate measurement experiments are made by using ultrasonic burning rate measurement method. The results of these experiments are compared with each other and test motor firings. Finally, the applicability of the ultrasonic burning rate measurement method is discussed.

Suggestions

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...
Analysis of grain burnback and international flow in solid propellant rocket motors in 3-dimensions
Yıldırım, Cengizhan; Aksel, Mehmet Haluk; Department of Mechanical Engineering (2007)
In this thesis, Initial Value Problem of Level-set Method is applied to solid propellant combustion to find the grain burnback. For the performance prediction of the rocket motor, 0-D, 1-D or 3-D flow models are used depending on the type of thre grain configuration.
Service life assessment of solid rocket propellants considering random thermal and vibratory loads
Yılmaz, Okan; Özgen, Gökhan Osman; Kuran, Bayındır; Department of Mechanical Engineering (2012)
In this study, a detailed service life assessment procedure for solid propellant rockets under random environmental temperature and transportation loads is introduced. During storage and deployment of rocket motors, uncontrolled thermal environments and random vibratory loads due to transportation induce random stresses and strains in the propellant which provoke mechanical damage. In addition, structural capability degrades due to environmental conditions and induced stresses and strains as well as materia...
Experimental and numerical investigation of an augmented spark igniter and evaluation of igniter’s effective flame length as a performance parameter
Öz, Levent Çağatay; Ulaş, Abdullah; Department of Mechanical Engineering (2019)
In the scope of this thesis, the impact of operating conditions on the performance of an augmented spark igniter in means of effective length of the flame developed by the igniter and thermal energy output of it, by using numerical and experimental techniques, is examined. The igniter uses gaseous oxygen as oxidizer and gaseous hydrogen as fuel. Tests were carried out for 3 different oxygen mass flow rate to fuel mass flow rate ratios, and at each ratio with four different total mass flow rates. Experimenta...
Citation Formats
B. Mumcu, “Application of ultrasonic burning rate measurement method on closed bombs,” M.S. - Master of Science, Middle East Technical University, 2013.