<< CL_fr_ter2topoN Coordinates and frames CL_fr_tnwMat >>

CelestLab >> Coordinates and frames > CL_fr_tnw2inertial

CL_fr_tnw2inertial

TNW Local orbital frame to inertial frame vector transformation

Calling Sequence

[vect_inertial] = CL_fr_tnw2inertial(pos_car,vel_car,vect_tnw)

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)

vect_tnw:

cartesian coordinates in the TNW local orbital frame (3xN)

vect_inertial:

cartesian coordinates in the inertial frame (3xN)

Bibliography

Authors

See also

Examples

// Example 1
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]];
vect_tnw = [[1;0;0] , [1;1;1]];
[vect_inertial] = CL_fr_inertial2tnw(pos_car,vel_car,vect_tnw)
<< CL_fr_ter2topoN Coordinates and frames CL_fr_tnwMat >>