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Polar Equation of a Conic Section

Last modified by

MichaelBartmess

on

Jul 24, 2020, 6:28:07 PM

Created by

MichaelBartmess

on

May 24, 2014, 5:07:13 AM

$r = ( "a" * (1 - 1 ^2)) / (1 + 1 * cos( nu ))$

$"Semi-major Axis"$

$"Eccentricity"$

$"True Anomaly"$

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UUID

444768c1-e301-11e3-b7aa-bc764e2038f2

This equation computes the magnitude of the position vector for a satellite in terms of the satellite's location in its orbit. This equation is based on the two-body equation of motion for the satellite orbiting the Earth.

The inputs are:

a - the semi-major axis of the ellipse
e - the eccentricity of the orbit
nu - the polar angle or true anomaly

/attachments/444768c1-e301-11e3-b7aa-bc764e2038f2/PolarEquationofaConicSection-illustration.png

This equation, Polar Equation of a Conic Section, is used in 1 page

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