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. If the specified body is a member of the Earth-Moon system, the counterpart not specified will also be considered in shadow evaluation.
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.
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 millisecond timing precision mode. Millisecond timing precision mode is deprecated and will be removed in a future release. We recommend that you migrate your Mission Plans to nanosecond timing precision mode.
Click here to see the documentation for this object in nanosecond timing precision mode.
Overload List
Signatures |
Return Value |
Description |
Determines the entry time, exit time, and duration of a Spacecraft's pass through the shadow of the spacecraft's central body. |
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Spacecraft.PenumbralShadowTimes(CelestialObject celestialObject) |
Determines the entry time, exit time, and duration of a Spacecraft's pass through the shadow of the central body specified by celestialObject. |
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Spacecraft.PenumbralShadowTimes(Array EventTime, Array EventType) |
Determines the entry time, exit time, and duration of a Spacecraft's pass through the shadow of the spacecraft's central body. |
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Spacecraft.PenumbralShadowTimes(CelestialObject celestialObject, Array EventTime, Array EventType) |
Determines the entry time, exit time, and duration of a Spacecraft's pass through the shadow of the central body specified by celestialObject. |
See also
Coverage and Contact Analysis Guide