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CL_ex_secularJ2

Secular J2 orbit propagation

Calling Sequence

[kep_t2] = CL_ex_secularJ2(t1,kep_t1,t2 [,er,mu,j2])

Description

Parameters

t1:

Initial time [days] (1xP)

kep_t1:

Keplerian orbital elements [sma;ecc;inc;pom;raan;anm] (6xP). P can be > 1 if there is only one final time (i.e. if N==1).

t2:

Final time [days] (1xN). N can be > 1 if there is only one set of orbital elements (i.e. if P==1).

kep_t2:

keplerian orbital elements at t2 [sma;ecc;inc;pom;raan;anm] (6 x max(P,N))

er:

(optional) Equatorial radius [m] (default is %CL_eqRad)

mu:

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

j2:

(optional) (Unnormalized) zonal coefficient (second zonal harmonic) (default is %CL_j2)

Authors

See also

Examples

// propagation of one satellite to several times:
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);

// propagation of 2 element sets to one final time:
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);
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