CL_ex_secularJ2 — Secular J2 effects orbit propagation
[kep_t2] = CL_ex_secularJ2(t1, kep_t1, t2[,er[,mu[,j2]]]))
date(s) in CNES julian days of keplerian orbital elements : Same date for all keplerian elements : (1x1) or different date for each keplerian element (1xN)
keplerian orbital elements (6xN or 6x1)
dates in CNES julian days (1x1 or 1xM)
extrapolated keplerian orbital elements (6 x max(N,M))
(optional) equatorial radius [m] (default is %CL_eqRad)
(optional) geocentric gravitational constant [m^3/s^2] (default value is %CL_mu)
(optional) zonal coefficient (second zonal harmonic) (default is %CL_j2)
Secular J2 effects consist of a drift on periapsis argument, right ascension of ascending node and mean anomaly. See CL_op_driftJ2 for more details.
// J2 secular extrapolation of one satellite at several dates : dga = 7070 * 1000; ecc = 0.001; inc = CL_deg2rad(98); pom = CL_deg2rad(90); gom = 0; anm = 0; t1 = 21915; t2 = t1:0.1:t1+1; kep_t1=[dga;ecc;inc;pom;gom;anm]; [kep_t2] = CL_ex_secularJ2(t1, kep_t1, t2); // J2 secular extrapolation of 2 satellites at one date: t2 = t1+1; t1=[t1,t1+0.5]; kep_t1=[kep_t1,[dga+100*1000;ecc+0.1;inc;pom;gom;anm]]; [kep_t2] = CL_ex_secularJ2(t1, kep_t1, t2);