CL_man_incRaanCirc — Inclination and RAAN maneuver for circular orbits
[dv,arg_lat]=CL_man_incRaanCirc(sma,inci,raani,incf,raanf,[mu])
dv is the velocity increment required given in spherical coordinates in the QSW frame : first parameter lambda is the in plane component (pi ~= towards planet and pi/2 = along velocity) second parameter phi is the out of plane component, positive towards the kinetic moment, third parameter is the norm
arg_lat is the argument of latitude of the maneuver.
semi-major axis of orbit [m] (1xN)
inclination of initial orbit [rad] (1xN)
right ascension of ascending node of initial orbit [rad] (1xN)
inclination of final orbit [rad] (1xN)
right ascension of ascending node of final orbit [rad] (1xN)
(optionnal) gravitational constant. [m^3/s^2] (default value is %CL_mu)
velocity increment in spherical coordinates in the QSW frame [lambda;phi;|dv|] [rad,rad,m/s] (3xN)
argument of latitude of the maneuver [rad] (1xN)