CL_man_dvIncRaanCirc

Description

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

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

  pso is the argument of latitude of the maneuver.

  If the argument res is present and is equal to "s", all the output data are returned in a structure.

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.

res :

(string, optional) Type of output: "d" or "s" for . Default is "d".

deltav :

Norm of velocity increment. [m/s] (1xN)

dv :

Velocity increment (in cartesian coordinates) in the "qsw" local frame [m/s] (3xN)

pso :

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

man :

Structure containing all the output data.

Authors

• CNES - DCT/SB

See also

• CL_man_dvInc

Examples

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