الفهرس 
Maneuvers calculations for satellite altitude control
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Abstract
The orbit transfer problems using impulsive thrusters have attracted researchers for a long time [3]. One of the objectives in these problems is to find the optimal fuel orbit transfer between two orbits, generally inclined eccentric orbits. The optimal two-impulse orbit transfer problem poses multiple local optima, and classical optimization methods find only local optimum solution. McCue [7] solved the problem of optimal two-impulse orbit transfer using a combination between numerical search and steepest descent optimization procedures. The transfer of satellites in too high orbits as geosynchronous one (geostationary), usually is achieved firstly by launching the satellite in Low Earth Orbit (LEO) (Parking orbit), then in elliptical transfer orbit and finally to the final orbit (Working orbit). The three steps process is known as Hohmann transfer. The Hohmann transfer which involves two circular orbits with different orbital inclinations is known as non{u2010}coplanar Hohmann transfer. If both orbital planes are aligned the Hohmann transfer is known as coplanar what is further considered in this paper. In terms of propellant consumptions the Hohmann transfer is the best known transfer to be applied when transferring between elliptical coplanar orbits. For transfer between elliptical coplanar orbits, the given information usually consists of the altitude of perigee and apogee of the initial and the altitude of perigee and apogee of the final orbits. The velocity to be applied into two orbit points in order to attain the dedicated final orbit is analyzed. The aim of this paper is compare between three types of coplanar impulsive transfer (two impulses, three impulses and one tangent burn) and conclude about the velocity changes for these types under relation between initial low Earth altitudes and final orbit. For the relation between initial orbit altitudes and final orbit altitude, the velocities to be applied in process of Hohmann transfer are simulated. from respective simulations, the velocity variations on dependence of this relation are derived. And the time of flight is considered too. The problem of spacecraft orbit transfer with minimum fuel consumption is considered, in terms of testing numerical solutions