Lambert's problem
[v1,v2] = CL_man_lambert(pos1,pos2,delta_t,direction [,mu])
Computes the velocity vectors v1 and v2, given the position vectors r1 and r2, the time of flight delta_t, and the direction of motion direction.
Initial position vector [m] (3xN)
Final position vector [m] (3xN)
Time of flight from r1 to r2 [s] (1xN or 1x1)
(optional) 'pro' if the transfer orbit is prograde, 'retro' if the transfer orbit is retrograde (default is 'pro')
(optional) Gravitational constant (default is %CL_mu) [m^3/s^2]
Initial velocity vector [m/s] (3xN)
Final velocity vector [m/s] (3xN)
CNES - DCT/SB
1) Orbital Mechanics for Engineering Students, H D Curtis, Section 5.3 and Appendix D.11 (algorithm 5.2)
2) Modern astrodynamics Fundamentals and perturbation methods, V Bond and M Allman, Chapter 6.2