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)

Authors

CNES - DCT/SB

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

See also

CL_stumpS, CL_stumpC