Eccentricity: Difference between revisions

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For the love of God, keep wtrinig these articles.

For elliptic orbits, eccentricity can be calculated from distance at periapsis and apoapsis:

e = \frac{d_{a} - d_{p}}{d_{a} + d_{p}}

= 1 - \frac{2}{(d_{a} / d_{p}) + 1}

where:

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 {{wikipedia}}
-==Definition==
+For the love of God, keep wtrinig these articles.
-Any orbit in planetary dynamics can be assumed to be of conic cross-section shape. The '''eccentricity''' of this conic section, the orbit's eccentricity, is an important parameter of the orbit that defines its absolute shape. Eccentricity may be interpreted as a measure of how much this shape deviates from a circle.
-Eccentricity (<math>e\,\!</math>) is strictly defined for all circular, elliptic, parabolic and hyperbolic orbits and may take following values:<ref>[http://en.wikipedia.org/w/index.php?title=Orbital_eccentricity Wikipedia article on eccentricity.]</ref>
-*for circular orbits: <math>e=0\,\!</math>,
-*for elliptic orbits: <math>0<e<1\,\!</math>,
-*for parabolic orbits: <math>e=1\,\!</math>,
-*for hyperbolic orbits: <math>e>1\,\!</math>.
 ==Calculation==