HCW.SetReferenceOrbit(Array, TimeSpan) Method

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Description

Sets the reference orbit of the HCW propagator using the specified Keplerian orbital elements (A, E, I, RAAN, W, TA) with respect to the ICRF. The reference orbit will be propagated with a two body (Keplerian) propagator when this Spacecraft is stepped. The epoch argument is optional; in the event that an epoch is not provided, the referenceOrbit will use the calling Spacecraft's epoch.

Timing Precision Mode

This page describes functionality in nanosecond timing precision mode.

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

Method Signature

HCW.SetReferenceOrbit(	Array referenceOrbit,
	TimeSpan referenceEpoch)

Arguments

referenceOrbit
Description:	The Array containing the reference orbit's Keplerian Elements (A, E, I, RAAN, W, TA).
Required Size:	6

referenceEpoch
Description:	The Epoch used to define the reference orbit. This argument is optional: in the event that this argument is not defined, the reference state will use the epoch of the Spacecraft to be propagated.

Syntax

myHCW1.SetReferenceOrbit(myArray1, myTimeSpan1);