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).
Perturbed Orbits
Modeling,Simulation in Science(Birkhäuser)
01.01.2007
19 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
Interplanetary Trajectory , Target Planet , Atmospheric Drag , Planetary Oblateness , Interplanetary Mission Applications of Mathematics , Systems Theory, Control , Mathematical Modeling and Industrial Mathematics , Computational Intelligence , Automotive Engineering , Mathematical and Computational Engineering , Engineering
J2-PERTURBED LOW-ENERGY ORBITS AROUND ENCELADUS
TIBKAT | 2021
|Nonlinear uncertainty propagation for perturbed two-body orbits
Online Contents | 2014
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