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CelestLab >> Coordinates and frames > CL_fr_locOrbMat

CL_fr_locOrbMat

Inertial frame to custom local orbital frame transformation matrix

Calling Sequence

[M] = CL_fr_locOrbMat(pos_car,vel_car,frame_name)

Description

Parameters

pos_car:

satellite's position vector relative to the inertial frame [m] (3xN)

vel_car:

satellite's velocity vector relative to the inertial frame [m/s] (3xN)

frame_name:

(string) name of local frame

M :

inertial to local orbital frame transformation matrix (3x3xN)

Authors

See also

Examples

pos_car = [[3500.e3;2500.e3;5800.e3] , [4500.e3;2100.e3;6800.e3]];
vel_car = [[1.e3;3.e3;7.e3] , [2.e3;3.e3;6.e3]];

// Example 1: Standard 'qsw' local frame:
[M] = CL_fr_locOrbMat(pos_car,vel_car,"qsw")
// is equivalent to:
[M] = CL_fr_qswMat(pos_car,vel_car)

// Example 2: 'lvlh': is the same as (s, -w, -q):
[M] = CL_fr_locOrbMat(pos_car,vel_car,"sWQ")
// is equivalent to:
[M] = CL_fr_lvlhMat(pos_car,vel_car)
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