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

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Description

Predicts a future position and velocity by evaluating the HCW equations using the specified primary satellite mean motion, relative state vector of the secondary satellite in units of km and km/s, and time interval deltaT. This overload assumes the Earth is the central body. The inputOutputSystem argument specifies the coordinate system of both the input and output relative states. The HCW equations of motion will be propagated using the Cartesian relative state vector. The output state will be returned in units of km and km/s

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(	Array relativeSecondaryState,
	Variable primaryMeanMotion,
	Variable deltaT,
	Variable inputOutputSystem)

Arguments

relativeSecondaryState
Description:	Array containing the relative state of the Secondary, in relation to the Primary.
Required Size:	6

primaryMeanMotion
Description:	The mean motion of the Primary to which the state will be evaluated.
Units:	rad/s
Valid Range:	primaryMeanMotion ≥ 0

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
1	VNB
2	LVLH
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(myArray2, myVariable1, myVariable2, myVariable3);