A Launcher's calculation the area of stage decline for placing a satellite in to Leo orbit which will be created in Turkey

Space research has been accelerated in Turkey with a given priority to this area. Investments are made and still continue for satellite assembly , test platforms and launcher facilities. Until now satellites produced in Turkey are launched by several foreign countries. Although there is some research to develop Turkey's own launcher, no detailed investigations are made yet. In this study, necessary algorithm has been studied to place a satellite of 400 kg into an elliptical orbit in altitude of 350 km. Launchers of other countries are investigated and two stage launcher with a liquid-propellant is seemed suitable for this thesis. Launchers which start to move vertically, have to be put parallel to the ground when they were placed in orbit. In this case, Newton's second law is not enough to explain launcher's movement. When launchers starts to move, it's accelaration changes due to change in it's mass and drag force that depend on the ambient density. Also the maneuver of 900 means to interfere with launcher's direction of motion. Necessary angular trajectory corrections depend on total weight of the launcher and the payload and the angular inertia of the system. In this thesis, an altitude route and the necessary course corrections is determined by iterative approach to reach an orbit of 350 km with a launcher that has a two stage liquid propellant tank. As a result of the improved algorithm first stage that finishes it's fuel at 80 km should be separated from the launcher. It is also calculated that, first stage falls 175 km away from the launching point, if drag force is included in the calculations.