الفهرس 
The eulerian parametersOnly 14 pages are availabe for public view
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Abstract
This work is concerned with the study of the Earth’s gravitational field and drageffects on the motion of an artificial sat-ellite using Euler parameters. We used the Earth’s gravitational field as Earth’s drag has two forms of air density. Also, we formulated our problem for the following three cases: 1- without atmospheric drag, 2- with atmospheric drag & without rotating atmosphere, and 3- with atmospheric drag & with rotating atmosphere. For the previous cases, we gave some numerical examples for different heights (200, 250 and 300 Krn). This thesis is divided into the following four Chapters: In Chapter I, we gave a genera1 review of the previous researches in this field especially the Euler parameters which is the subject of our thesis, and in Chapter 11, we explained the connections between orbit dynamics and rigid body dynamic (Euler parameters), while in chapter 111, we formulated our problem for the previous cases, which were considered as before, with using Euler parameters. Lastly, in Chapter IV our problem was programmed and applied with the fixed step size, fourth-order Rung-Kutta meth~d~togethewri th the basic equations for converting the position and velocity vector to the orbital elements of any conic motion especially semi-major axis. Also, a discussion of the numerical results and check relation were included in this Chapter.