Eckstein Hechler orbit propagation analytical model
[mean_cir_t2,osc_cir_t2] = CL_ex_eckHech(t1,mean_cir_t1,t2 [,er,mu,zonals])
Computes the mean orbital elements mean_cir_t2 and the osculating orbital elements osc_cir_t2 at time t2 given the mean orbital elements mean_cir_t1 at time t1.
Zonals coefficients up to J6 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 nominally works for eccentricities smaller than 5.e-3
- This function works but with a lesser accuracy for eccentricities between 5.e-3 and 0.1
- This function does not work for eccentricities greater than 0.1
Initial time [days] (1xN or 1x1)
Circular adapted mean orbital elements at time t1 [sma;ex;ey;inc;raan;pom+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 J6) to be used (default is %CL_j1jn(1:6)) (Nz x 1)
Circular adapted mean orbital elements at t2 [sma;ex;ey;inc;raan;pom+anm] (6xN)
Circular adapted osculating orbital elements at t2 [sma;ex;ey;inc;raan;pom+anm] (6xN)
CNES - DCT/SB
1) CNES - MSLIB FORTRAN 90, Volume E (me_eck_hech)