Name
CL_man_lambert — Lambert's problem
Calling Sequence
[v1,v2] = CL_man_lambert(R1,R2,dt,sense [,mu])
Description
-
Given the position vectors r1 and r2, the time of flight dt between them,
and the sens of the orbit sense, CL_man_lambert(r1,r2,dt,sense) computes the velocity vectors v1 and v2.
- Last update : 12/02/2007
Parameters
- R1 :
initial position vector [m] (3xN)
- R2 :
final position vector [m] (3xN)
- dt :
time between r1 and r2 [s] (1xN)
- sense :
'pro' if the orbit is prograde, 'retro' if the orbit is retrograde (1xN)
- mu :
(optional) gravitational parameter (default is %CL_mu) [m^3/s^2]
- v1 :
initial velocity vector [m/s] (3xN)
- v2 :
final velocity vector [m/s] (3xN)
Bibliography
1 Orbital Mechanics for Engineering Students, H D Curtis, Chapter 5, section 5.3 and Appendix D, section D.11 (algorithm 5.2)
2 Modern astrodynamics Fundamentals and perturbation methods, V Bond and M Allman, Chapter 6.2