Show/Hide Menu
Hide/Show Apps
Logout
Türkçe
Türkçe
Search
Search
Login
Login
OpenMETU
OpenMETU
About
About
Open Science Policy
Open Science Policy
Open Access Guideline
Open Access Guideline
Postgraduate Thesis Guideline
Postgraduate Thesis Guideline
Communities & Collections
Communities & Collections
Help
Help
Frequently Asked Questions
Frequently Asked Questions
Guides
Guides
Thesis submission
Thesis submission
MS without thesis term project submission
MS without thesis term project submission
Publication submission with DOI
Publication submission with DOI
Publication submission
Publication submission
Supporting Information
Supporting Information
General Information
General Information
Copyright, Embargo and License
Copyright, Embargo and License
Contact us
Contact us
Performance prediction of nozzleless solid propellant rocket motors
Download
index.pdf
Date
2015
Author
Özer, Ali Can
Metadata
Show full item record
Item Usage Stats
682
views
809
downloads
Cite This
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 nozzleless solid propellant rocket motors. In order to predict performance and numerically simulate the flow field inside the motor, first internal ballistics of the motor is examined theoretically. Then, quasi one dimensional internal ballistics model is constructed and solved numerically through inside the motor. In order to predict burning rate, an erosive burning relation has been implemented into the numerical scheme. To verify the flow solver, results against the Sod shock tube problem is obtained. Grid resolution and time step size sensitivity study is made. The results of numerical internal ballistics simulations are compared with the experimental nozzleless motor firing results found in literature are simulated and compared. Simulations are conducted for both quasi steady and unsteady approach, and outcomes of two approaches are compared as well. Proposed numerical scheme is promising for predicting thrust and pressure histories of nozzleless solid propellant rocket motors. Also from the design point of view, parametric studies are conducted. Effect of grain geometry and propellant burning rate are studied.
Subject Keywords
Nozzles.
,
Propellants.
,
Solid propellants.
,
Rockets (Aeronautics).
URI
http://etd.lib.metu.edu.tr/upload/12619350/index.pdf
https://hdl.handle.net/11511/24937
Collections
Graduate School of Natural and Applied Sciences, Thesis
Suggestions
OpenMETU
Core
Application of the universal expression for erosive burning to Nozzleless solid propellant Rocket motors
Özer, Ali Can; Özyörük, Yusuf (2017-01-01)
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. The present approach includes performance prediction of nozzleless solid propellant rocket motors (SPRM). Quasi one dimensional internal ballistics model is constructed and solved numerically through inside the motor. To predict the burning rate, universal erosive burning rate relat...
Experimental analysis on the measurement of ballistic properties of solid propellants
Cuerdaneli, S.; Ak, M. A.; Ulaş, Abdullah (2007-06-16)
Ballistic properties of solid propellants play an important role in the performance of the solid propellant rocket motors. Therefore, ballistic properties of a likely propellant should be known and provided to the design engineers. In this study, a specific AP/HTPB composite solid propellant (SCP) was examined to obtain steady-state linear burning rates as a function of pressure and propellant initial temperature, temperature sensitivity, and pressure deflagration limit (PDL). In some tests micro-thermocoup...
Analysis of 3-d grain burnback of solid propellant rocket motors and verification with rocket motor tests
Püskülcü, Gökay; Ulaş, Abdullah; Department of Mechanical Engineering (2004)
Solid propellant rocket motors are the most widely used propulsion systems for military applications that require high thrust to weight ratio for relatively short time intervals. Very wide range of magnitude and duration of the thrust can be obtained from solid propellant rocket motors by making some small changes at the design of the rocket motor. The most effective of these design criteria is the geometry of the solid propellant grain. So the most important step in designing the solid propellant rocket mo...
Conceptual internal design and computational fluid dynamics analysis of a supersonic inlet
Alemdaroğlu, Mine; Özyörük, Yusuf; Department of Aerospace Engineering (2005)
In this thesis, the conceptual internal design of the air inlet of a supersonic, high altitude, solid propellant ramjet cruise missile is performed. Inviscid, compressible CFD analysis of the designed inlet is made in order to obtain qualitative and quantitative performance characteristics of the inlet at different operating conditions. The conceptual design of the inlet is realized by using analytical relations and equations, correlations derived from numerous available past experimental data and state-of-...
DYNAMIC MODELING AND CONTROL OF AN ELECTROMECHANICAL CONTROL ACTUATION SYSTEM
Yerlikaya, Umit; Balkan, Raif Tuna (2017-10-13)
Electromechanical actuators are widely used in miscellaneous applications in engineering such as aircrafts, missiles, etc. due to their momentary overdrive capability, long-term storability, and low quiescent power/low maintenance characteristics. This work focuses on electromechanical control actuation systems (CAS) that are composed of a brushless direct current motor, ball screw, and lever mechanism. In this type of CAS, nonlinearity and asymmetry occur due to the lever mechanism itself, saturation limit...
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
A. C. Özer, “Performance prediction of nozzleless solid propellant rocket motors,” M.S. - Master of Science, Middle East Technical University, 2015.