$LastChangedDate: 27-Juil-2011 $

# CL_fr_inertial2tnw

Inertial to TNW local orbital frame vector transformation

## Calling Sequence

       [vect_tnw] = CL_fr_inertial2tnw(pos_car,vel_car,vect_inertial)

## Description

- 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.

## 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_inertial:

  cartesian coordinates in the inertial frame [m] (3xN)

vect_tnw:

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

## Bibliography

- 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)

## Authors

- CNES - DCT/SB

## See also

- CL_fr_qsw2inertial

- CL_fr_qswMat

- CL_fr_tnwMat

- CL_fr_inertial2qsw

- CL_fr_tnw2inertial

## 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]];
    vect_inertial = [[1;0;0] , [1;1;1]];
    [vect_tnw] = CL_fr_inertial2tnw(pos_car,vel_car,vect_inertial)