CL_man_inclination — Delta V for an inclination maneuver
[dv,anv] = CL_man_inclination(ai,ei,inci,pomi,incf[,posman[,mu]])
Output dv is the velocity increment given in spheric coordinates in 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
anv is the true anomaly of maneuver execution point in radians.
Optional flag posman can be used to define maneuver execution point (1->ascending node, -1->descending node, 0->point of optimal cost)
initial orbit semi major axis [m] (1xN)
initial orbit eccentricity (1xN)
initial orbit inclination [rad] (1xN)
initial orbit argument of periapsis [rad] (1xN)
final orbit desired inclination [rad] (1xN)
(optional) flag to indicate maneuver execution point (1->ascending node, -1->descending node, 0->point of optimal cost, default is ascending node) (1xN)
(optional) geocentric gravitational constant. [m^3/s^2] (default value is %CL_mu)
velocity impulsion required in spheric coordinates in QSW frame [lambda;phi;|dv|] [rad,rad,m/s] (3xN)
true anomaly of maneuver execution point [rad] (1xN)