Description
Converts the position or velocity components of from3or6Vector from the fromAttitude reference system to the toAttitude reference system, using referenceSpacecraft as the reference Spacecraft.
This overload allows you to specify whether to perform a position vector conversion or velocity vector conversion using the conversionType argument. Note that the BCS and Geodetic frames are not supported for velocity vector conversions.
Timing Precision Mode
This page describes functionality in nanosecond timing precision mode.
Function Signature
Arguments
fromAttitude


Description:

Attitude system of input state.

Valid Values:

Value

Label

0

ICRF

1

Spacecraft's current velocitynormalbinormal (VNB) reference system

2

Spacecraft's current local vertical and local horizontal (LVLH) reference system

3

Spacecraft's body coordinate system (BCS)

4

Spacecraft's current geodetic system

5

Spacecraft's current UVW reference system

6

Spacecraft's current RIC reference system


toAttitude


Description:

Attitude system of output state.

Valid Values:

Value

Label

0

ICRF

1

Spacecraft's current velocitynormalbinormal (VNB) reference system

2

Spacecraft's current local vertical  local horizontal (LVLH) reference system

3

Spacecraft's body coordinate system (BCS)

4

Spacecraft's current geodetic system

5

Spacecraft's current UVW reference system

6

Spacecraft's current RIC reference system


referenceSpacecraft


Description:

The Spacecraft object to which the attitude frames are referenced.

from3or6Vector


Description:

A three or sixelement array containing the relative position and velocity vectors relative to the origin in the input attitude system. A threeelement array is for position conversions, a sixelement array is required for velocity conversions.

Required Size:

At least 3

conversionType


Description:

Type of conversion to perform.

Valid Values:

Value

Label

0

Position vector conversion

1

Velocity vector conversion


Return Value
Type:

Array of number (size = 3)

Returns a threeelement array containing the converted vector in the output attitude system.
Syntax
myArray1 = AttitudeConvert(myVariable1, myVariable2, mySpacecraft1, myArray2, myVariable3);

See also
AttitudeConvert
Attitude Reference Frames
