CL_man_sma — Delta V for an orbit shape modification (semi major axis)
[dv,anv] = CL_man_sma(ai,ei,af[,posman[,mu]])
Output dv is the impulsion required 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.
initial orbit semi major axis [m] (1xN)
initial orbit eccentricity (1xN)
semi major axis of desired orbit [m] (1xN)
(optional) flag to indicate maneuver execution point (0->periapsis, 1->apoapsis; default is 0) (1xN)
(optionnal) geocentric gravitational constant. [m^3/s^2] (default value is %CL_mu)
delta_v required in spheric coordinates in QSW frame [lambda;phi;|dv|] [rad,rad,m/s] (3xN)
true anomaly of maneuver execution point [rad] (1xN)