Description
Converts the position and velocity specified by fromVector from the fromSystem coordinate system to a velocity in the toSystem coordinate system, referencing the coordinate systems to the specified epoch.
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.
Function Signature
Arguments
fromSystem
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Description:
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Coordinate system of input velocity.
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Valid Values:
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Value
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Label
|
1
|
ICRF
|
2
|
Mean of J2000 Earth Ecliptic
|
3
|
True of Date Earth Equator
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4
|
Earth Fixed
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5
|
Local Coordinates - Longitude
|
6
|
True Equator Mean Equinox
|
7
|
Local Coordinates - Longitude/Latitude
|
8
|
Mean of Date Earth Equator
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9
|
Mean of 1950 Earth Equator
|
10
|
Moon Fixed (Principle Axis Rotating)
|
11
|
TIRF
|
12
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Moon Principle Axis - Inertial at J2000
|
13
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Moon Principle Axis - Inertial at Epoch
|
14
|
Moon Mean Earth - Rotating
|
15
|
Moon Mean Earth - Inertial at J2000
|
16
|
Moon Mean Earth - Inertial at Epoch
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17
|
Mean of J2000 Earth Equator
|
18
|
CIRF
|
19
|
Specify any CelestialObject.ReferenceFrameId
|
|
toSystem
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|
Description:
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Coordinate system of output velocity.
|
Valid Values:
|
Value
|
Label
|
1
|
ICRF
|
2
|
Mean of J2000 Earth Ecliptic
|
3
|
True of Date Earth Equator
|
4
|
Earth Fixed
|
5
|
Local Coordinates - Longitude
|
6
|
True Equator Mean Equinox
|
7
|
Local Coordinates - Longitude/Latitude
|
8
|
Mean of Date Earth Equator
|
9
|
Mean of 1950 Earth Equator
|
10
|
Moon Fixed (Principle Axis Rotating)
|
11
|
TIRF
|
12
|
Moon Principle Axis - Inertial at J2000
|
13
|
Moon Principle Axis - Inertial at Epoch
|
14
|
Moon Mean Earth - Rotating
|
15
|
Moon Mean Earth - Inertial at J2000
|
16
|
Moon Mean Earth - Inertial at Epoch
|
17
|
Mean of J2000 Earth Equator
|
18
|
CIRF
|
19
|
Specify any CelestialObject.ReferenceFrameId
|
|
epoch
|
|
Description:
|
The TAI epoch of the input and/or output velocity in modified Julian date format. If both the input and output coordinate systems are referenced to an epoch, both will be defined using this epoch.
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fromVector
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Description:
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A six-element array containing the position and velocity in the input coordinate system.
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Required Size:
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At least 6
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frameEpoch
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Description:
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When the 'fromSystem' or 'toSystem' is Body Inertial Equatorial at Epoch, this argument defines the epoch at which the coordinate system will be evaluated. If both the input and output coordinate systems are referenced to the epoch, both will be evaluated at the same epoch.
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Return Value
Type:
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Array of number (size = 3)
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Units:
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km/s
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Returns a three-element array containing the velocity in the output coordinate system.
Syntax
myArray1 = VelocityConvert(myVariable1, myVariable2, myVariable3, myArray2, myVariable4);
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See also
VelocityConvert
Orbit Reference Frames
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