Lyddane orbit propagation analytical model
[mean_kep_t2,osc_kep_t2] = CL_ex_lyddane(t1,mean_kep_t1,t2 [,er,mu,zonals])
Computes the mean orbital elements mean_kep_t2 and the osculating elements osc_kep_t2 at time t2 given the mean elements mean_kep_t1 at time t1.
Zonals coefficients up to J5 are taken into account.
The function works in the following cases:
- 1 initial time and 1 set of initial orbital elements, and N final times.
- N (or 1) initial times and N sets of initial orbital elements, and N (or 1) final times.
The orbital elements are the following:
Warnings :
- This function does not work for inclinations close to the critical inclinations (63.43494882 deg and 116.5650512 deg)
- This function does not work for eccentricities higher than 0.9
Initial time [days] (1xN ot 1x1)
Mean Keplerian elements at time t1 [sma;ecc;inc;pom;raan;anm] (6xN or 6x1).
Final time [days] (1xN or 1x1).
(optional) Equatorial radius [m] (default is %CL_eqRad)
(optional) Gravitational constant [m^3/s^2] (default value is %CL_mu)
(optional) Vector of zonal coefficients J1 to Jn (troncated to J5) to be used (default is %CL_j1jn(1:5)) (Nz x 1)
Mean Keplerian elements at t2 [sma;ecc;inc;pom;raan;anm] (6xN)
Osculating Keplerian elements at t2 [sma;ecc;inc;pom;raan;anm] (6xN)
CNES - DCT/SB
1) CNES - MSLIB FORTRAN 90, Volume E (me_lyddane)