CL_cw_contPropa — Continuous thrust trajectory
[rel_dates,rel_pos_vel]=CL_cw_contPropa(rel_date_ini,rel_pos_vel_ini,gama_diff,alt,rel_date_end,delta_t,[ballistic_coef_chaser,ballistic_coef_target,er,mu])
initial date in seconds [seconds] (1x1)
initial position and velocity of chaser in target's LVLH frame [rx;ry;rz;vx;vy;vz] [m;m/s] (6x1)
continuous thrust differential acceleration [ax, ay, az] [m/s**2] (3xM)
altitude of target [m]
relative end date in seconds [seconds] (1x1)
(optional) time step [s] (default is 100)
(optional) Ballistic coefficient of chaser : S*cx/m S=equivalent drag surface, cx = drag coefficient, m = mass [m^2/kg] (default is 0)
(optional) Ballistic coefficient of target : S*cx/m S=equivalent drag surface, cx = drag coefficient, m = mass [m^2/kg] (default is 0)
(optional) equatorial radius [m] (default is %CL_eqRad)
(optional) geocentric gravitational constant [m^3/s^2] (default value is %CL_mu)
dates in seconds [seconds] (1xN)
positions and velocities of chaser in target's LVLH frame at corresponding dates [rx;ry;rz;vx;vy;vz] (6xN)
rel_date_ini = 11550.677; rel_pos_vel_ini = [-249.99355; 0. ; 0.0000435 ; -0.0000003 ; 0. ; 0.0000003]; gama_diff = [0. ; 0. ; 0.0003238]; alt = 450.e3; ballistic_coef_chaser = 100 * 1 / 20.e3; ballistic_coef_target = 200 * 1 / 400.e3; rel_date_end = 4*3600; // 4 hours of ballistic propagation delta_t = 100; // 100 seconds time step [rel_dates,rel_pos_vel] = CL_cw_contPropa(rel_date_ini,rel_pos_vel_ini,gama_diff,alt,rel_date_end,delta_t,ballistic_coef_chaser,ballistic_coef_target) //see 'CelestLab> Demos> RELATIVE MOTION> CW_propagation' for more examples