Spacecraft.PenumbralShadowTimes Method

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Description

Determines the entry time, exit time, and duration of a Spacecraft's pass through the shadow of a central body. Events are reported for penumbral shadow condition geometries only.

 

The shadow times are determined using a conical shadow. The three regions of the Spacecraft's central body's shadow, the umbra, penumbra, and annular, are shown in the diagram below. Events are reported for prenumbral shadow conditions only.

 

The three regions of the Spacecraft's central body's shadow.

The three regions of the Spacecraft's central body's shadow.

 

 

Note: This method uses a spherical model for the occulting body. Use the options available in the VisibilityCalculator to exercise more control over the analysis.

 

Timing Precision Mode

This page describes functionality in nanosecond timing precision mode.

 

Overload List

Signatures

Spacecraft.PenumbralShadowTimes()

Spacecraft.PenumbralShadowTimes(CelestialObject)

Spacecraft.PenumbralShadowTimes(TimeSpanArray, Array)

Spacecraft.PenumbralShadowTimes(CelestialObject, TimeSpanArray, Array)

 

See also

Spacecraft Object

Spacecraft Propagation Guide

Coverage and Contact Analysis Guide