NOMINAL BALLISTIC MISSILE ASCENT OPTIMIZATION WITH THERMAL INVESTAGATION

Abstract

Ballistic Missile Trajectory is one of the big issues to simulate and also to be optimized. The main objective of this paper is to find a method to obtain the Nominal trajectory for the ballistic missile through finding out the optimal parameters for each ballistic trajectory phases. To define the problem; the paper will list all governing equations and describe the parameters of input and output for each phase of the trajectory. Then, a method to reduce the number of input parameters will be discussed. We study each parameter effect to get the most optimal trajectory for the missile. At the final, optimal flight will be discussed in details. Although, we investigate the thermal effect for entry point from space into the earth atmosphere