HCW.InitialReferenceOrbit Property

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 ICRF. 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. 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.

Attributes

Syntax

See also

HCW Object