OrbitalElementsStateInit.h

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/*
Orbital elements model header file
 
Author: Alex Reynolds
*/
/*
Metadata for MS GUI:
imdata = {"displayname" : "Orbital Elements Initializer",
          "exclude" : False,
          "category" : "Initial States"
}
aliases = {"mu" : "GM",
           "pos__inertial" : "Position",
           "vel__inertial" : "Velocity",
           "a" : "Semimajor Axis",
           "e" : "Eccentricity",
           "i" : "Inclination",
           "RAAN" : "RAAN",
           "w" : "Arg. of Periapsis",
           "f" : "True Anomaly"
}
*/
 
#ifndef MODELS_STATES_ORBITAL_ELEMENTS_STATE_INIT_H
#define MODELS_STATES_ORBITAL_ELEMENTS_STATE_INIT_H
 
#include "simulation/Model.h"
#include "frames/Frame.h"
#include "frames/frameutils.h"
#include "constants/planetdefaults.h"
#include "constants/unitutils.h"
 
namespace warptwin {

    MODEL(OrbitalElementsStateInit)
    public:
        // Model params
        //         NAME                     TYPE                    DEFAULT VALUE
        START_PARAMS
            SIGNAL(mu,                      double,                 warpos::earth_wgs84.mu)
            SIGNAL(a,                       double,                 6878140.0)
            SIGNAL(e,                       double,                 1e-10)
            SIGNAL(i,                       double,                 45.0*warpos::DEGREES_TO_RADIANS)
            SIGNAL(RAAN,                    double,                 0.0)
            SIGNAL(w,                       double,                 0.0)
            SIGNAL(f,                       double,                 0.0)
        END_PARAMS
 
        // Model inputs
        //         NAME                     TYPE                    DEFAULT VALUE
        START_INPUTS
 
        END_INPUTS
 
        // Model outputs
        //         NAME                     TYPE                    DEFAULT VALUE
        START_OUTPUTS
            SIGNAL(pos__inertial,           CartesianVector3,      CartesianVector3({0.0,0.0,0.0}))
            SIGNAL(vel__inertial,           CartesianVector3,      CartesianVector3({0.0,0.0,0.0}))
        END_OUTPUTS
 
    protected:
        int16 start() override;
 
        // Temporary vector to hold orbital elements input
        CartesianVector6 _orbital_elements; 
 
        // Temporary vectors to hold position/velocity output
        CartesianVector3 _pos;
        CartesianVector3 _vel;
    };
 
}
 
#endif