Examples
tle = CL_tle_new(); // cjd in TREF, mean Keplerian elements relative to ECI cjd = 18000; mean_kep = [7200.e3; 0.1; 1; 0; 0; 0]; tle = CL_tle_setElem(tle, "kep", cjd, mean_kep) // Check results [mean_kep2, cjd2] = CL_tle_getElem(tle, "kep") |  |  |
Sets TLE orbital state
[tle] = CL_tle_setElem(tle, type_oe, cjd, mean_oe [, frame, ut1_tref, tt_tref])
Modifies the mean orbital elements in a TLE structure.
The input orbital elements can be given in various forms: Keplerian elements, position and velocity... and in any frame.
In a standard situation, the orbital elements are converted from the specified reference frame to TEME. The epoch is converted from the TREF time scale to UTC. Note that if the frame is not a true equator frame, the transformation may not as accurate as should be as the frame transformation arguments that can be provided are limited to ut1_tref and tt_tref.
It is also possible to give frame a special value: "native". It means that the input reference frame AND time scale are those natively used for TLEs: TEME and UTC repectively. No conversion is performed.
TLE structure (size N)
(string) Type of output orbital elements: "kep", "cir", "cireq", "equin" or "pv" (1x1)
TLE epoch (modified julian date from 1950.0, TREF time scale except if frame == "native") (1xN or 1x1)
Mean orbital elements (of type given by "type_oe") relative to the specified frame [m, m/s, rad] (6xN)
(string, optional) Output frame, see above for details. Default is "ECI".
(optional) UT1-TREF [seconds]. Default is %CL_UT1_TREF (1xN or 1x1)
(optional) TT-TREF [seconds]. Default is %CL_TT_TREF (1xN or 1x1)
CNES - DCT/SB/MS
tle = CL_tle_new(); // cjd in TREF, mean Keplerian elements relative to ECI cjd = 18000; mean_kep = [7200.e3; 0.1; 1; 0; 0; 0]; tle = CL_tle_setElem(tle, "kep", cjd, mean_kep) // Check results [mean_kep2, cjd2] = CL_tle_getElem(tle, "kep") | | |