Spacecraft.OrbitApogee Method



The OrbitApogee method is a conditional property that can be used with the Step command to advance the Spacecraft to apogee, the point in the orbit where the Spacecraft is at its furthest distance from a celestial body. FreeFlyer determines this condition by monitoring the dot product between the position and velocity vectors and identifying when this value passes from positive to negative. The celestial body to be used in the apoapsis calculation can be specified using a Variable, String, or CelestialObject. If a celestial body is not specified, the current Spacecraft Central Body will be used.


Note that as a general rule this method should only be used as a propagation stopping condition and should not be used as a means monitor whether or not a Spacecraft is at apogee at a particular epoch.


Timing Precision Mode

This page describes functionality in nanosecond timing precision mode.


Overload List







See also

Spacecraft Object

Spacecraft Propagation Guide

Coverage and Contact Analysis Guide