CL_ex_eckHech

Description

• This function is deprecated.

  Replacement function: CL_ex_propagate

• Propagates orbital elements using Eckstein-Hechler analytical model.

  The original algorithm has been modified so that the perigee of a frozen orbit remains perfectly constant over time. This resulted in a change of the mean eccentricity vector (x component) of about 4.e-7, which is small compared to the model's accuracy.

• Notes:

  - There can be 1 or N initial times, and 1 or N final times.

  - The input argument "zonals" is deprecated as of CelestLab v3.0.0. It has been replaced by "j1jn".

• See Propagation models for more details.

Parameters

t1:

Initial time [days] (1x1 or 1xN)

mean_cir_t1:

Mean orbital elements at time t1 (6x1 or 6xN).

t2:

Final time [days] (1xN or 1x1).

er:

(optional) Equatorial radius [m]. Default is %CL_eqRad

mu:

(optional) Gravitational constant [m^3/s^2]. Default is %CL_mu

j1jn:

(optional) Vector of zonal harmonics. Default is %CL_j1jn (Nz x 1)

mean_cir_t2:

Mean orbital elements at t2 (6xN)

osc_cir_t2:

Osculating orbital elements at t2 (6xN)

Authors

• CNES - DCT/SB

See also

• CL_ex_meanEckHech

Examples

// Example 1: one orbit, several final time instants: t1 = 12584; mean_cir_t1 = [7.e6; 0; 1.e-3; 1; 0.1; 0.2]; t2 = 12587:1:12590 [mean_cir_t2,osc_cir_t2] = CL_ex_eckHech(t1,mean_cir_t1,t2) // Example 2: one orbit, several final time instants: t1 = 12584; mean_cir_t1 = [7.e6; 0; 1.e-3; 0.1; 0.2; 0.3] * [1,1]; t2 = [12587, 12588]; [mean_cir_t2,osc_cir_t2] = CL_ex_eckHech(t1,mean_cir_t1,t2)