Inertial to "tnw" local orbital frame vector transformation
vect_tnw = CL_fr_inertial2tnw(pos_car,vel_car,vect_inertial)
Converts the coordinates of a vector from the inertial frame to the "tnw" local orbital frame.
The inertial frame is implictly the frame relative to which the satellite's position and velocity are defined. The "tnw" local frame is built using these position and velocity vectors.
See Local frames for more details on the definition of local frames.
satellite's position vector relative to the inertial frame [m] (3xN)
satellite's velocity vector relative to the inertial frame [m/s] (3xN)
cartesian coordinates in the inertial frame [m] (3xN)
cartesian coordinates in the "tnw" local orbital frame [m] (3xN)
1) Mecanique spatiale, CNES - Cepadues 1995, Tome I, section 10.2.2.3 (Definition du Repere orbital local)
2) CNES - MSLIB FORTRAN 90, Volume O (mo_geo_tnw)
CNES - DCT/SB