Name

CL_gm_inertial2orbitSph — Spherical coordinates conversion from inertial frame to orbital frame

Calling Sequence

   [alpha2,delta2] = CL_gm_inertial2orbitSph(inc,raan,alpha1,delta1)
   
   

Description

  • This function takes as input right ascension and declination in an inertial frame and converts them to the orbital frame (defined by orbit's ascending node and inclination). Orbital frame is defined as follows:

    axe X: towards node

    axe Z: orbit's kinetic moment vector

    axe Y assures orthonormal direct frame

  • Last update : 3/3/2008

Parameters

inc:

orbit's inclination [rad] (1xN)

raan:

ascending node [rad] (1xN)

alpha1:

right ascension in inertial frame [rad] (1xN)

delta1:

declination in inertial frame [rad] (1xN)

alpha2:

right ascension in orbital frame [rad] (1xN)

delta2:

declination in orbital frame [rad] (1xN)

Authors

CNES - DCT/SB