Eccentricity Vector

In astrodynamics the eccentricity vector of a conic section orbit is the vector pointing towards the periapsis and with length equal to the orbit's scalar eccentricity.

Calculation

The eccentricity vector \mathbf{e} \, can be calculated from the orbital state vectors \mathbf{v} \, and \mathbf{r} \, at any time (the result is constant):
\mathbf{e} = {1 \over {\mu}} \left (v^2 - {\mu \over {\mathbf{\left |r \right |}}}\right)
\mathbf{r} - (\mathbf{r} \cdot \mathbf{v} ) \mathbf{v} \right where: Alternatively it can also be computed from orbital angular momentum vector h:
\mathbf{e} = {\mathbf{v}\times\mathbf{h}\over{\mu}} - {\mathbf{r}\over{\left|\mathbf{r}\right|}}
where:

See also

 

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