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Eccentricty using `r_p`

Last modified by
on
Jul 24, 2020, 6:28:07 PM
Created by
on
May 25, 2014, 5:18:30 AM
`e = 1- ( r_p / "a" )`
`"Radius of Perigee"`
`"Semi-major Axis""`
Tags
Orbital Mechanics eccentricity
UUID
0298604d-e3cc-11e3-b7aa-bc764e2038f2

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

/attachments/0298604d-e3cc-11e3-b7aa-bc764e2038f2/Eccentrictyusingrp-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_p`, is used in 1 page
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