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Eccentricty using `r_a`

Last modified by
on
Jul 24, 2020, 6:28:07 PM
Created by
on
May 25, 2014, 5:36:31 AM
`e = ( r_a / "a" ) - 1`
`"Radius of Apogee"`
`"Semi-major Axis""`
Tags
Orbital Mechanics eccentricity
UUID
869e1afc-e3ce-11e3-b7aa-bc764e2038f2

This equation produces the eccentricity,e , with inputs being the apogee radius, `r_a`, and the semi-major axis, a.

/attachments/869e1afc-e3ce-11e3-b7aa-bc764e2038f2/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

  

This equation, Eccentricty using `r_a`, is used in 1 page
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