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CL_man_incRaanCirc

Inclination and RAAN maneuver for circular orbits

Calling Sequence

[dv,arg_lat]=CL_man_incRaanCirc(sma,inci,raani,incf,raanf [,mu])

Description

Parameters

sma :

Semi-major axis [m] (1xN)

inci:

Initial inclination [rad] (1xN)

raani:

Initial right ascension of ascending node [rad] (1xN)

incf:

Final inclination [rad] (1xN)

raanf:

Final right ascension of ascending node [rad] (1xN)

mu :

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

dv :

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

arg_lat:

Argument of latitude of the maneuver [rad] (1xN)

Authors

Examples

sma = 7200.e3;
inci = CL_deg2rad(111);
raani = CL_deg2rad(12);
incf = CL_deg2rad(108);
raanf = CL_deg2rad(15);
[dv,arg_lat]=CL_man_incRaanCirc(sma,inci,raani,incf,raanf)
kep = [sma*ones(inci);zeros(inci);inci;zeros(inci);raani;arg_lat];
kep1 = CL_man_applyDv(kep,dv)
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