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CelestLab >> Trajectory and maneuvers > CL_ex_kepler

CL_ex_kepler

Keplerian orbit propagation

Calling Sequence

[kep_t2]=CL_ex_kepler(t1,kep_t1,t2 [,mu])

Description

Parameters

t1:

Initial time [days] (1xP)

kep_t1:

Keplerian elements at time t1 [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).

mu :

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

kep_t2:

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

Authors

Bibliography

See also

Examples

// Example 1 :
t1 = 21482.125 // initial time (days, origin = 1950.0)
kep_t1 = [ 24464560; 0.7311; 0.122138; 3.10686; 1.00681; 0.048363 ]
T = CL_kp_params('per', kep_t1(1,:)) // orbital period in seconds
t2 = t1 + (0:1/4:1)*T/86400 // final times (days, origin = 1950.0)
kep_t2 = CL_ex_kepler(t1, kep_t1, t2)

// Example 2 :
t1 = 0.  // initial time (arbitrary origin)
kep_t1 = [ 7.e6, 0.,  %pi/2,  0., %pi, 0.; ..
8.e6, 0.1, %pi/2,  0., %pi, 0.  ]'
t2 = 1. // final time : 1 day later
kep_t2 = CL_ex_kepler(t1, kep_t1, t2)
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