RelativeMotionUtilities.ComputeStateHCW(Spacecraft, Spacecraft, Variable, Variable) Method

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Description

Predicts the future position and velocity of the secondarySC by evaluating the HCW equations of motion using the specified primarySC and time interval deltaT. The HCW equations of motion will be propagated using the Cartesian relative state vector. The predicted relative state (position and velocity) will be returned in the specified outputSystem in units of km and km/s. Note that the epochs and central bodies of the secondarySC andprimarySC must match, and an error will be reported if they do not.

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.

Method Signature

RelativeMotionUtilities.ComputeStateHCW(	Spacecraft secondarySC,
	Spacecraft primarySC,
	Variable deltaT,
	Variable inputOutputSystem)

Arguments

secondarySC
Description:	The Spacecraft whose future state is to be predicted.

primarySC
Description:	The Spacecraft to which the relative state will be evaluated.

deltaT
Description:	The time interval at the end of which the state will be evaluated.
Units:	s

inputOutputSystem

Description:

The coordinate system of both the input and output relative states.

Valid Values:

Value	Label
0	ICRF
1	VNB
2	LVLH
5	UVW
6	RIC
7	LVC (Cylindrical)
8	RIC Cylindrical
9	RIC Spherical

Return Value

Type:

Array of number (size = 6)

Returns the predicted future position and velocity of a secondary Spacecraft.

Syntax

myArray1 = RelativeMotionUtilities.ComputeStateHCW(mySpacecraft1, mySpacecraft2, myVariable1, myVariable2);