CL_fr_tnwMat

Description

• Computes the frame transformation matrix M from the inertial reference frame to the "tnw" local orbital frame.

  The inertial frame is implicitly 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.

  By convention, M multiplied by coordinates relative to the inertial frame yields coordinates relative to the "tnw" frame.

• See Local frames for more details on the definition of local frames.

Parameters

pos_car:

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

vel_car:

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

M :

inertial frame to "tnw" local frame transformation matrix (3x3xN)

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_def_tnw)

Authors

• CNES - DCT/SB

See also

• CL_fr_qsw2inertial

• CL_fr_inertial2qsw

• CL_fr_qswMat

• CL_fr_inertial2tnw

• CL_fr_tnw2inertial

Examples

// Inertial to "tnw" : 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]]; M = CL_fr_tnwMat(pos_car, vel_car) pos_tnw = M * pos_car;