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 analysis of the effects of atmospheric parameters on space launch center safety
Download
index.pdf
Date
2016
Author
Yaman, İbrahim
Metadata
Show full item record
Item Usage Stats
264
views
147
downloads
Cite This
This thesis study aims at the problem of space launch center safety which is dependent on launch vehicle conceptual design and atmospheric parameters. Selection of the concept at the initial step of the satellite launch vehicle affects the project cost and space launch center safety directly. It is also important to model properties of atmospheric conditions and conduct safety analysis. Successful mission for a launch vehicle depends on providing the total velocity requirement. In this study, launch vehicle performance that is necessary for a successful mission was modelled. Different launch vehicle configurations are compared using a parametric cost model and best alternative in terms of lifetime cost is selected to be used for the safety analysis of space launch center safety. Atmospheric parameters, variation of temperature and pressure with altitude and winds with their deviations are modelled. Drop points of launch vehicle fragments under different atmospheric conditions are analyzed. In addition, seasonal variations of safety distance requirements due to secondary effects such as temperature, pressure and toxic pollutants are calculated.
Subject Keywords
Launch vehicles (Astronautics).
,
Artificial satellites
,
Space shuttles
,
Space vehicles
URI
http://etd.lib.metu.edu.tr/upload/12619654/index.pdf
https://hdl.handle.net/11511/25376
Collections
Graduate School of Natural and Applied Sciences, Thesis
Suggestions
OpenMETU
Core
Progress in space weather modeling in an operational environment
Tsagouri, Ioanna; Belehaki, Anna; Bergeot, Nicolas; Cid, Consuelo; Delouille, Veronique; Egorova, Tatiana; Jakowski, Norbert; Kutiev, Ivan; Mikhailov, Andrei; Nunez, Marlon; Pietrella, Marco; Potapov, Alexander; Qahwaji, Rami; Tulunay, Yurdanur; Velinov, Peter; Viljanen, Ari (2013-01-01)
This paper aims at providing an overview of latest advances in space weather modeling in an operational environment in Europe, including both the introduction of new models and improvements to existing codes and algorithms that address the broad range of space weather's prediction requirements from the Sun to the Earth. For each case, we consider the model's input data, the output parameters, products or services, its operational status, and whether it is supported by validation results, in order to build a...
Orbit transfer optimization of a spacecraft with impulsive thrusts using genetic algorithm
Yılmaz, Ahmet; Özgören, Mustafa Kemal; Department of Mechanical Engineering (2012)
This thesis addresses the orbit transfer optimization problem of a spacecraft. The optimal orbit transfer is the process of altering the orbit of a spacecraft with minimum propellant consumption. The spacecrafts are needed to realize orbit transfer to reach, change or keep its orbit. The spacecraft may be a satellite or the last stage of a launch vehicle that is operated at the exo-atmospheric region. In this study, a genetic algorithm based orbit transfer method has been developed. The applicability of gen...
Autonomous spacecraft rendezvous and docking on safe trajectories
Büyükkoçak, Ali Tevfik; Tekinalp, Ozan; Department of Aerospace Engineering (2018)
In this thesis, rendezvous and docking operation of a pair of low earth orbit spacecraft is addressed. Two different sets of equations for the nonlinear orbital relative motion of spacecraft are derived and simulation codes for this motion are developed. First, Hill-Clohessy-Wiltshire (HCW) equations are used in chaser-target spacecraft configuration with Model Predictive Control (MPC) algorithm including some safety considerations such as debris avoidance, direction of approach constraint and slow impact r...
Passively Safe Relative Orbit Configurations over LongTime Intervals for Heterogeneously Distributed SpacecraftClusters
YAĞLIOĞLU, BURAK; Tekinalp, Ozan (2019-07-01)
The problem of relative orbit configurations over a long time intervalsincorporating realistic dynamics, platform differences and operational constraints for safety, station keeping and inter-spacecraft communicationsis addressed. Two different approaches are developed. In the first approach, relative mean orbital mean elements are found through minimizing deviations from reference mean orbit. In second one, relative configurations are found from a refere...
Linearization in satellite attitude control with modified Rodriguez parameters
Doruk, R. Özgür (2009-01-01)
Purpose - The purpose of this paper is to analyze the results of the Jacobian matrix linearization of the satellite attitude dynamics with modified Rodriguez parameters (MRP) as attitude representation.
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
İ. Yaman, “Numerical analysis of the effects of atmospheric parameters on space launch center safety,” M.S. - Master of Science, Middle East Technical University, 2016.
