CL_ex_lyddaneMan — Lydanne orbit extrapolation analytic model with maneuvers
[osc_t2[,osc_man]] = CL_ex_lyddaneMan(t1,mean_t1,t2[,tman[,dvman,[,er[,mu[,zonals]]]])
Zonals coefficients up to J5 are taken into account
tman is a 1xN matrix defining the dates of N maneuvers. dvman is a 3xN matrix defining the delta_v of N maneuvers. Each column contains [delta_vx;delta_vy;delta_vz] with delta_v defined in qsw local frame (see CL_fr_qswMat). Input osculatory parameters osc_t1 should be given in J2000 frame (see CL_fr_ter2J2000Mat) and keplerian parameters (as in CL_ex_meanLyddane or CL_ex_lyddane)
osc_t2 contains extrapolated parameters at dates t2 (impulsive maneuvers applied). osc_man contains extrapolated parameters at maneuver dates.
- This function does not work for inclinations close (0.0022918 deg) to the critical inclinations (63.43494882 deg and 116.5650512 deg)
- This function does not work for eccentricities higher than 0.9
CNES julian date of initial parameter (1xN)
keplerian osculatory parameters at date t1 [sma,ecc,inc,pom,gom,anm]' (6xN)
extrapolation dates (in CNES julian days) (1xM)
(optional)dates (CNES julian day) of manoeuvres [t] [cjd] (1xN)
(optional)delta_v of manoeuvres in qsw local frame [dvx;dvy;dvz] [m/s] (3xN)
(optional) equatorial radius [m] (default is %CL_eqRad)
(optional) geocentric gravitational constant [m^3/s^2] (default value is %CL_mu)
(optional) vector of zonals coefficients J1 to Jn (troncated to J5) to be used (default is %CL_j1jn(1:5)) (1 x N)
keplerian osculatory parameters at date t2 [sma,ecc,inc,pom,gom,anm]' (6xM)
keplerian mean_loc parameters at dates of maneuvers [sma,ecc,inc,pom,gom,anm]' (6xN)