Numerical analysis of the effects of atmospheric parameters on space launch center safety

Yaman, İbrahim
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.


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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...
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...
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...
Experimental and computational evaluation of transient behavior of a typical satellite monopropellant propulsion system
Çilli Tarçın, Ayşegül; Aksel, Mehmet Haluk; Ak, Mehmet Ali; Department of Mechanical Engineering (2014)
In this study, a typical satellite monopropellant propulsion system is numerically modeled by using a commercial software and analyses are conducted regarding the priming operation of satellite propulsion system. Analyses are performed for different tank pressures, downstream line pressures, distance between the tank and orifice, distance between the orifice and latch valve, distance between the latch valve and exit valve, orifice diameter and pipe diameters. Moreover, a test setup is constructed and tests ...
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...
Citation Formats
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.