Polar Equation of a Conic Section

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Equation / Last modified by Administrator on 2015/07/30 07:05
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ID
MichaelBartmess.Polar Equation of a Conic Section
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

PolarEquationofaConicSection-illustration.png