CL_man_incRaanCirc

Description

• This function is deprecated.

  Replacement function: CL_man_dvIncRaanCirc

• Computes the dv needed for an inclination and RAAN change for a circular orbit.

  dv is the velocity increment vector (in spherical coordinates) in the "qsw" local orbital frame.

  pso is the argument of latitude of the maneuver.

Parameters

sma :

Semi-major axis [m] (1xN or 1x1)

inci :

Initial inclination [rad] (1xN or 1x1)

raani :

Initial right ascension of ascending node [rad] (1xN or 1x1)

incf :

Final inclination [rad] (1xN or 1x1)

raanf :

Final right ascension of ascending node [rad] (1xN or 1x1)

posman:

(optional) Flag specifying the position of the maneuver: 1 or "n" -> northern hemisphere, -1 or "s" -> southern hemisphere. Default is in the northern hemisphere. (1xN or 1x1)

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)

pso :

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

Authors

• CNES - DCT/SB

Examples

sma = 7200.e3; inci = 1; raani = 2; incf = 1.1; raanf = 1.9; [dv,pso]=CL_man_incRaanCirc(sma,inci,raani,incf,raanf) kep = [sma;0;inci;0;raani;pso]; kep1 = CL_man_applyDv(kep,dv)