HCW.InitialReferenceOrbit Property

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Description

The reference orbit is the orbit of the "primary" or "chief" satellite used when propagating the Spacecraft using the HCW (Hills-Clohessy-Wiltshire) equations of relative motion. The reference orbit is specified in Keplerian elements (A, E, I, RAAN, W, TA) with respect to the MJ2000 Earth Equator frame. This is set using the SetReferenceOrbit() method. The reference orbit will be propagated with a two body (Keplerian) propagator when the Spacecraft is stepped. The initial reference orbit state corresponds to the InitialReferenceOrbitEpoch property. The updated reference orbit corresponding to the Spacecraft object's current epoch can be queried using CurrentReferenceOrbit.

 

Timing Precision Mode

This page describes functionality in millisecond timing precision mode.

Click here to see the documentation for this object in nanosecond timing precision mode.

 

Attributes

Type:

Array of number (size = 6)

Access:

read

 

Syntax

myVariable1 = myHCW1.InitialReferenceOrbit[0];

 

See also

HCW Object