CL_op_repeat2smaInc — Repeat orbit parameters (N,P,Q) to semi major axis and inclination
[sma,inc] = CL_op_repeat2smaInc(N,P,Q,ecc,sso,[incInput],[er,[mu,[j2,[om_earth,[om_sun]]]]])
Values of N (1 x No)
Values of P (1 x No)
Values of Q (1 x No)
eccentricity (1 x No)
1 = search for sun synchronous orbits, 0 = orbits have a given inclination (1 x No)
(mandatory in case sso=0, optional otherwise) given inclinations (rad) (1 x No)
(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)
(optional) angular rotation speed of the Earth (default is om_earth) (1 x 1)
(optional) mean apparent revolution speed of the Sun around the Earth (default is %CL_omSun) (1 x 1)
semi majors axis of orbits (m) (1 x No)
inclinations of orbits (rad) (1 x No)
An orbit is considered phased if after an even number of planet revolutions (with respect to orbit's node), the satellite has done an even number of orbits(exactly N+P*Q) and is back on the same ground tracks
N+P/Q is the fractionary number of orbits per orbital day
An orbital day is defined as the time between 2 consecutive crossings of a same meridian by the orbit ascending node direction. For a sun synchronous orbit, an orbital day is a solar day.
If sso = 1 then the function computes sun synchronous orbits (incInput is omitted)
If sso = 0 then the function uses incInput as inclinations for the orbits