CL_ex_kepler

Description

• Propagates orbital elements considering the central force only.

  The jacobian of the transformation (i.e. the transition matrix) is also optionally computed.

• The type of orbital elements is the following:

  

• Notes:

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

  - This function works for any type of orbit and any type of orbital elements ("kep", "cir", "cireq" or "equin").

Parameters

t1:

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

kep_t1:

Orbital elements at time t1 (6x1 or 6xN).

t2:

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

mu :

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

kep_t2:

Orbital elements propagated to time t2. (6xN)

jac:

Transition matrix = d(kep_t2)/d(kep_t1) (6x6xN)

Authors

• CNES - DCT/SB

Bibliography

• 1) Mecanique spatiale, CNES - Cepadues 1995, Tome I

See also

• CL_ex_secularJ2

Examples

// Example 1 : t1 = 20000 // initial time (days) kep_t1 = [ 10000.e3; 0.7; 0; 0; 0; 0] T = CL_kp_params('per', kep_t1(1,:)) // orbital period (s) t2 = t1 + (1:5) * (T/2) / 86400 // final times (days) 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; 0; 0 ], .. [8.e6; 0.1; %pi/2; 0; 0; 0 ] ] t2 = [1,2] // final times (1 or 2 days later) kep_t2 = CL_ex_kepler(t1, kep_t1, t2)