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
Numerical simulation of two-dimensional collisionless plasma flows under the effect of electrostatic forces via particle in cell method
Download
index.pdf
Date
2013
Author
Tümüklü, Özgür
Metadata
Show full item record
Item Usage Stats
235
views
136
downloads
Cite This
Taking its name from its ability to generate thrust via electricity, the concept of electric propulsion has important space mission applications like station keeping for satellites and deep space probe. However, contamination of plumes in electric propulsion systems with ion beam could hinder communication, and effective neutralization is essential to clear away this predicament. Today, computer simulation is regarded as a powerful tool to investigate plasma behavior in the plumes of electric propulsion devices. The aim of this thesis is to write a generic simulation code named as SIMPFORT which studies two-dimensional, collisonless plasma flows under the effect of electrostatic forces using the Particle in Cell (PIC) method. The conservation of mass, momentum and energy are checked. In this thesis, the flows with negligible forces from magnetic fields are investigated and electrostatic Poisson’s equation is solved in both rectangular and non-rectangular domains. Successive Over Relaxation (SOR) method is implemented in the solution of the Poisson’s equation. SIMPFORT can handle plasma problems using either an accurate full kinetic particle model or an approximate hybrid model which combines kinetic and continuum (fluid) models. In the full kinetic model, both ions and electrons are simulated as particles, but in the hybrid model only ions are simulated as particles while electrons are modeled as fluid using the Boltzmann relation. In the full kinetic model the Poisson’s equation is linear, on the other hand, in the hybrid model it becomes nonlinear due to the effect of the Boltzmann relation. In this thesis, two generic test problems are solved and the results are compared with a demo version of a commercial full kinetic code named VORPAL. The present full kinetic model results compare favorably with those of VORPAL for both test problems. On the other hand, the hybrid model results show some deviations in one of the test problems.
Subject Keywords
Electric propulsion.
,
Plumes (Fluid dynamics).
,
Ion bombardment.
,
Plasma simulation.
URI
http://etd.lib.metu.edu.tr/upload/12616026/index.pdf
https://hdl.handle.net/11511/22706
Collections
Graduate School of Natural and Applied Sciences, Thesis
Suggestions
OpenMETU
Core
Comparison of Outer Rotor Radial Flux and Axial Flux PM Motors for CMG Application
Ertan, Hulusi Bülent (2014-09-05)
Control moment gyroscopes (CMG) are used in modern satellite applications for attitude control of satellites. The volume and mass of the instruments is very important in such applications. In this context, integrating the mass of the CMG, on the stator of the motor, promises to save space and mass. Radial-flux outer-rotor motor is a promising configuration in that respect. In this paper, using such a PM motor is considered for control moment gyroscope applications. The design of the motor must be made such ...
Orbit Control of an Earth Orbiting Solar Sail Satellite
Polat, Halis Can; Tekinalp, Ozan (2022-09-01)
A concept for the utilization of solar sail satellite's propellant-free thrust capability at Low earth orbit (LEO) is proposed and its orbit control strategy is analyzed. Thrust vector control of the sail's normal direction is used to harvest the solar radiation pressure for generating the necessary acceleration to change the orbital elements. The required control vector direction is determined with two approaches. The first approach is realized by approximating the Gaussian Variational Equations at the emp...
Passive flow control in liquid-propellant rocket engines with cavitating venturi
Ulaş, Abdullah (Elsevier BV, 2006-04-01)
In a companion liquid rocket engine development project, due to the overall weight constraint of the propulsion system, a cavitating venturi is selected to control the liquid fuel and liquid oxidizer mass flow rates. Two cavitating venturis, one for the fuel and the other for the oxidizer, are designed to deliver the desired mass flow rates for a specified operating inlet pressure, temperature, and inlet cross-sectional area. The converging and diverging angles of the venturis are selected from the literatu...
Solar Sail Application with a Proposed Low Earth Orbit Mission Concept
Polat, Halis Can; Tekinalp, Ozan (2019-01-01)
Solar Sail applications utilizing the advantages of propellant-free and theoretically infinite specific impulse are widely investigated, especially for interplanetary/interstellar and near-Earth asteroid missions and non-Keplerian orbit designs. However, applications regarding to the Low Earth Orbit (LEO), specifically below 700 km, are rarely studied as aerodynamic drag is dominant. This study is aimed to harvest the LEO mission advantages by proposing an elliptical orbit design and control via continuous ...
ATTITUDE CONTROL OF AN EARTH ORBITING SOLAR SAIL SATELLITE TO PROGRESSIVELY CHANGE THE SELECTED ORBITAL ELEMENT
Atas, Omer; Tekinalp, Ozan (2015-01-15)
Solar sailing where the radiation pressure from Sun is utilized to propel the spacecraft is examined in the context of orbital maneuvers. In this vein a locally optimal steering law to progressively change the selected orbital elements, without considering others, of an Earth centered Keplerian orbit of a cubesat satellite with solar sail is addressed. The proper attitude maneuver mechanization is proposed to harvest highest solar radiation force in the desired direction for such Earth orbiting satellites. ...
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
Ö. Tümüklü, “Numerical simulation of two-dimensional collisionless plasma flows under the effect of electrostatic forces via particle in cell method,” M.S. - Master of Science, Middle East Technical University, 2013.