Eccentricty $| | \to e | |$ $||vece||$

Last modified by

on

Jul 24, 2020, 6:28:07 PM

Created by

on

May 25, 2014, 5:05:12 AM

e = | | \to e [\to r, \to v] | |

$e = ||vece"" [vecr, vecv]||$

x-component of the velocity vector

$"x-component of the velocity vector"$

y-component of the velocity vector

$"y-component of the velocity vector"$

z-component of the velocity vector

$"z-component of the velocity vector"$

x-component of the orbit radius vector

$"x-component of the orbit radius vector"$

y-component of the orbit radius vector

$"y-component of the orbit radius vector"$

y-component of the orbit radius vector

$"y-component of the orbit radius vector"$

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

This equation, Eccentricty

| | \to e | |

$||vece||$ , references 2 pages

Equations and Data Items

• Earth Gravitational Constant (

μ

$mu$ ) :

m^{3}

$m^3$ /

{sec}^{2}

$sec^2$ by MichaelBartmess

• V3 - Vector Norm by MichaelBartmess

This equation, Eccentricty

| | \to e | |

$||vece||$ , is used in 1 page

Calculators

• Orbitology Calculator by MichaelBartmess

Equations and Data Items

Collections

Comments
Attachments
Stats

No comments

Eccentrictyvece-illustration.png

Last 12 Months

This site uses cookies to give you the best, most relevant experience. By continuing to browse the site you are agreeing to our use of cookies.

Eccentricty ||→e||||→e||||vece||

Notes

Datasets

Equations and Data Items

Calculators

Equations and Data Items

Collections

Eccentricty $| | \to e | |$ $||vece||$