Spacecraft.GetHyperbolicExcessVelocityVector(Variable) Method

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Description

Returns the X, Y, Z unit vector of the Spacecraft's outbound hyperbolic excess velocity vector (V_inf) referenced to the chosen coordinate frame. This value is only valid for hyperbolic cases (e > 1), it is invalid for elliptical orbits (e < 1) and will report an error. The reference frame will be evaluated at the Spacecraft's epoch.

 

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.

 

Method Signature

Spacecraft.GetHyperbolicExcessVelocityVector(

Variable referenceFrame)

 

 

Arguments

referenceFrame


Description:

The reference frame in which the vector will be evaluated.

Valid Values:

Value

Label

0

Mean of J2000 Earth Equator

1

Mean of J2000 Earth Ecliptic

 

 

 

 

Return Value

Type:

Array of number (size = 3)

 

 

Returns the hyperbolic excess velocity vector.

 

Syntax

myArray1 = mySpacecraft1.GetHyperbolicExcessVelocityVector(myVariable1);

 

 

See also

Spacecraft Object

Spacecraft Propagation Guide

Coverage and Contact Analysis Guide