To model the effects of orbital perturbations caused by gravitational asymmetry due to oblateness and presence of a third body.
To present a simple atmospheric model for predicting the life of a satellite in a low orbit.
To introduce the concept of sphere of influence and the patched conic approach for the design and analysis of lunar and interplanetary missions.
To solve the perturbed two-body problem using numerical integration (Cowell’s and Encke’s methods).
KeywordsAtmospheric Drag Interplanetary Mission Interplanetary Trajectory Planetary Oblateness Target Planet
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