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CelestLab >> Trajectory and maneuvers > CL_man_inclination

CL_man_inclination

Delta V required to change the inclination

Calling Sequence

[dv,anv] = CL_man_inclination(ai,ei,inci,pomi,incf [,posman,mu])

Description

Parameters

ai :

Semi major axis [m] (1xN)

ei:

Eccentricity (1xN)

inci :

Initial inclination [rad] (1xN)

pomi:

Argument of periapsis [rad] (1xN)

incf :

Final inclination [rad] (1xN)

posman:

(optional) Flag specifying the position of maneuver (1->ascending node, -1->descending node, 0->minimal |dv|). Default is ascending node) (1xN)

mu :

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

dv :

velocity increment vector in spherical coordinates in the QSW frame [lambda;phi;|dv|] [rad,rad,m/s] (3xN)

anv:

true anomaly at maneuver position [rad] (1xN)

Authors

See also

Examples

ai = 7200.e3;
ei = 0.1;
inci = CL_deg2rad(65);
pomi = CL_deg2rad(110);
incf = CL_deg2rad(70);
[dv,anv] = CL_man_inclination(ai,ei,inci,pomi,incf,0)
// Check results :
anm = CL_kp_v2M(ei,anv);
kep = [ai ; ei ; inci ; pomi ; 0 ; anm];
kep1 = CL_man_applyDv(kep,dv)
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