Name

CL_cw_twoImpulse — Two-impulse transfer

Calling Sequence

   [delta_vi,delta_vf]=CL_cw_twoImpulse(pv_ini,pv_fin,alt,t_transfer[,er[,mu]])
   
   

Description

  • Computes delta_v for a two_impulse transfer. This transfer is performed with a maneuver at the starting point (delta_vi at A) and a maneuver at the ending point (delta_vf at B).

    The local orbital reference frame tied to the target is the LVLH (See CL_fr_lvlhMat).

  • Last update : 20/10/2009

Parameters

pv_ini:

initial chaser position and velocity (A in the figure) in the target's LVLH frame [rx;ry;rz;vx;vy;vz]_ini (6x1) [m]

pv_fin:

final chaser position and velocity (B in the figure) in the target's LVLH frame [rx;ry;rz;vx;vy;vz]_fin (6x1) [m]

alt:

target's altitude [m]

t_transfer:

transfer time (time between the two maneuvers) [s]

er:

(optional) equatorial radius [m] (default is %CL_eqRad)

mu:

(optional) geocentric gravitational constant [m^3/s^2] (default value is %CL_mu)

delta_vi:

Delta_v of the first maneuver (dans quelles coordonnées/repere??) (3x1) [m/s]

delta_vf:

Delta_v of the second maneuver (dans quelles coordonnées/repere??) (3x1) [m/s]

Authors

CNES - DCT/SB

See also

CL_cw_Nmatrix, CL_cw_Mmatrix

Bibliography

1 Mecanique spatiale, CNES - Cepadues 1995, Tome II, 16.3

2 Orbital Mechanics for engineering students, H D Curtis, Chapter 7 (section 7.5)

Examples

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