CL_cw_twoImpulse — Two-impulse transfer
[delta_vi,delta_vf]=CL_cw_twoImpulse(pv_ini,pv_fin,alt,t_transfer[,er[,mu]])
The local orbital reference frame tied to the target is the LVLH (See CL_fr_lvlhMat).
initial chaser position and velocity (A in the figure) in the target's LVLH frame [rx;ry;rz;vx;vy;vz]_ini (6x1) [m]
final chaser position and velocity (B in the figure) in the target's LVLH frame [rx;ry;rz;vx;vy;vz]_fin (6x1) [m]
target's altitude [m]
transfer time (time between the two maneuvers) [s]
(optional) equatorial radius [m] (default is %CL_eqRad)
(optional) geocentric gravitational constant [m^3/s^2] (default value is %CL_mu)
Delta_v of the first maneuver (dans quelles coordonnées/repere??) (3x1) [m/s]
Delta_v of the second maneuver (dans quelles coordonnées/repere??) (3x1) [m/s]
1 Mecanique spatiale, CNES - Cepadues 1995, Tome II, 16.3
2 Orbital Mechanics for engineering students, H D Curtis, Chapter 7 (section 7.5)
pv_ini=[-30000,0,6000,10.18,0,0]' pv_fin=[-15860,0,0,0,0,0]' alt=450000; omega=CL_kp_params('mm',%CL_eqRad+alt); periode=2*%pi/omega; t_transfer=periode/2; [delta_vi,delta_vf]=CL_cw_twoImpulse(pv_ini,pv_fin,alt,t_transfer) //see 'CelestLab> Demos> RELATIVE MOTION> CW_propagation' for more examples