Lambert's problem using Clohessy-Whiltshire model (including constant acceleration)
[v1, v2] = CL_cw_lambert(p1, p2, delta_t, alt [[, acc, er, mu]])
Computes the initial and final velocities of a transfer knowing the initial and final positions.
The reference frame used is the target's LVLH local frame (origin = target).
The reference altitude alt is the altitude of the target = semi major axis of target's (circular) orbit minus equatorial radius.
acc is the differential inertial acceleration (corresponding to a physical force) with components in the reference frame.
Initial (relative) position vector, components in reference frame [m] (3xN or 3x1)
Final (relative) position vector, components in reference frame [m] (3xN or 3x1)
Transfer time [s] (1xN or 1x1)
Reference altitude (= altitude of target) [m] (1x1)
(optional) Differential acceleration, components in reference frame (m/s^2). Default is []. (3xN or 3x1 or [])
(optional) Equatorial radius. Default: %CL_eqRad. [m] (1x1)
(optional) Gravitational constant. Default: %CL_mu. [m^3/s^2] (1x1)
Initial (relative) velocity vector in reference frame [m/s] (3xN)
Final (relative) velocity vector in reference frame [m/s] (3xN)
CNES - DCT/SB
1) Mecanique spatiale, CNES - Cepadues 1995, Tome II, 16.3
2) Orbital Mechanics for engineering students, H D Curtis, Chapter 7 (section 7.5)