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Abstract

  • 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).

Keywords

Atmospheric Drag Interplanetary Mission Interplanetary Trajectory Planetary Oblateness Target Planet 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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Copyright information

© Birkhäuser Boston 2007

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