Name

CL_gm_orbit2inertialSph — Spherical coordinates conversion from orbital frame to inertial frame

Calling Sequence

   [alpha2,delta2] = CL_gm_orbit2inertialSph(inc,raan,alpha1,delta1)
   
   

Description

  • This function takes as input right ascension and declination in the orbital frame (defined by orbit's ascending node and inclination) and converts them to an inertial frame. 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 orbital frame [rad] (1xN)

delta1:

declination in orbital frame [rad] (1xN)

alpha2:

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

delta2:

declination in inertial frame [rad] (1xN)

Authors

CNES - DCT/SB