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CelestLab >> Trajectory and maneuvers > CL_man_lambert

CL_man_lambert

Lambert's problem

Calling Sequence

[v1,v2] = CL_man_lambert(pos1,pos2,delta_t,direction [,mu])

Description

Parameters

pos1 :

Initial position vector [m] (3xN)

pos2 :

Final position vector [m] (3xN)

delta_t :

Time of flight from r1 to r2 [s] (1xN or 1x1)

direction :

(optional) 'pro' if the transfer orbit is prograde, 'retro' if the transfer orbit is retrograde (default is 'pro')

mu :

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

v1 :

Initial velocity vector [m/s] (3xN)

v2 :

Final velocity vector [m/s] (3xN)

Authors

Bibliography

See also

Examples

r1 = [5000.e3 ; 10000.e3 ;2100.e3];
r2 = [-14600.e3 ; 2500.e3 ;7000.e3];
dt = 3600; //one hour
// direction = 'pro' by default
[v1, v2] = CL_man_lambert([r1 r1],[r2 r2],[dt dt]);
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