CL_fr_tnwMat — Local orbital frame (t,n,w) definition in an inertial frame
[M] = CL_fr_tnwMat(pos_car,vel_car)
origin: center of gravity of satellite
t: unit vector in the direction of satellite's velocity
w: unit vector of the kinetic moment of the osculating orbit
n: unit vector chosen so TNW is a direct orthonormal frame
To convert a vector pos_tnw to pos_car, you can use the (hyper)matrix M' : pos_car = M'*pos_tnw;
For big hypermatrixes, it is faster to use the functions CL_fr_inertial2tnw and CL_fr_tnw2inertial
satellite's cartesien position in a geocentric inertiel frame [m] (3xN)
satellite's cartesien velocity in a geocentric inertiel frame [m/s] (3xN)
frame transfer matrix from an inertial frame to the TNW local frame (3x3xN)
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_def_tnw)