الفهرس 
Time of free-flight
The cases of small e and small jOnly 14 pages are availabe for public view
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Abstract
The ballistic missile problem is typically represented in astrodynamics as a simplified planar two-body problem with a non-rotating Earth. The missile is only guided during the relatively brief initial and final powered phases of flight while most of its course, the free flight part, is subsequently governed by the laws of orbital mechanics and ballistics. from this information we can usually determine the range of a projectile, the initial flight path angle, the orbit eccentricity and semi-major axis, and its true (eccentric) anomaly angles at launch and landing points. It is of interest to expand upon this basic model in order to add realism to the problem. Therefore the thesis is organized so as to include five chapters