Inclination + semi-major axis combined maneuvers (circular orbits)
[deltav, dv1, dv2, anv1, anv2] = CL_man_dvIncSmaCirc(ai, inci, af, incf [[, posman, icheck, vectorize, mu, res="d"]]) man = CL_man_dvIncSmaCirc(ai, inci, af, incf, [[, posman, icheck, vectorize, mu, res="s"]])
Computes the velocity increment needed to change both the inclination and the semi major axis of a circular orbit using two combined maneuvers.
Two maneuvers are performed at the ascending and the descending node in order to change both the semi major axis and the inclination while keeping the initial and final orbits circular.
The ratio of inclination change between the 1st and the 2nd maneuver is determined so that the total DV is minimum.
The output argument deltav is the sum of the norms of the velocity increments: (deltav = |dv1| + |dv2|).
Velocity increments are expressed in the "qsw" frame.
anv1 and anv2 are the true anomalies where the DV are performed. As the initial orbit is circular, anv1 is arbitrarily set to 0 or %pi, which is consistent with an implicit value of the argument of periapsis of 0.
The optional flag posman can be used to define the position of the 1st maneuver (maneuver at ascending node or descending node).
The optional flag icheck is used to enforce no checking on the final inclination value. If the targetted inclination is less than 0 or more than pi, the ascending node will rotate 180 degrees. If icheck is true, the right ascension of the ascending node is not changed by the maneuver.
The optional flag vectorize is used to manage vectorization. Setting it to true makes the computation run faster, but because of the method used, the results slightly depend on the vectorization index.
If the argument res is present and is equal to "s", all the output data are returned in a structure.
Notes:
- This function is not a particular case of CL_man_dvIncSma, as the latter does not preserve the eccentricity of the initial orbit.
- Because of the method use to efficiently compute the solutions, the accuracy of the results slightly depends on the index (in case of "vectorized" inputs and if the "vectorize" option is true).
- The implicit value of the argument of the periapsis is 0.
Initial semi major-axis [m] (1xN or 1x1)
Initial inclination [rad] (1xN or 1x1)
Final semi major-axis [m] (1xN or 1x1)
Final inclination [rad] (1xN or 1x1)
(optional) Flag specifying the position of the maneuver: 1 or "an" for ascending node, -1 or "dn" for descending node. Default is at the ascending node. (1xN or 1x1)
(optional, boolean) Flag specifying if incf must be checked in the standard range for inclination values ([0, pi]). Default is %t. (1x1)
(optional, boolean) Vectorization option. Default is %t (1x1)
(optional) Gravitational constant. Default is %CL_mu. [m^3/s^2]
(string, optional) Type of output: "d" or "s". Default is "d".
Sum of norms of velocity increments. [m/s] (1xN)
First velocity increment in cartesian coordnates in the "qsw" local orbital frame. [m/s] (3xN)
Second velocity increment in cartesian coordnates in the "qsw" local orbital frame. [m/s] (3xN)
True anomaly at the location of the first velocity increment (relative to the initial orbit). The implicit value of the argument of perigee is 0. [rad] (1xN)
True anomaly at the location of the second velocity increment (relative to the intermediate orbit). [rad] (1xN)
Structure containing all the output data. (1x1)
CNES - DSO/DV/IF