Eccentricty using `r_a`

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Equation / Last modified by Administrator on 2015/08/11 07:07
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MichaelBartmess.Eccentricty using `r_a`
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This equation produces the eccentricity,e , with inputs being the apogee radius, `r_a`, and the semi-major axis, a.

Eccentrictyusingra-illustration.png

Notes

The orbits and trajectories that can be characterized by eccentricity are:

elliptical:

circular: e = 1

parabolic trajectory

hyperbolic trajectory

  


 0 < e < 1

e = 1

e = 1

e> 1