# Polar Equation of a Conic Section

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MichaelBartmess.Polar Equation of a Conic Section
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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