SatOrbitPropagator.hpp

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#pragma ident "$Id: SatOrbitPropagator.hpp 2457 2010-08-18 14:20:12Z coandrei $"

#ifndef GPSTK_SAT_ORBIT_PROPAGATOR_HPP
#define GPSTK_SAT_ORBIT_PROPAGATOR_HPP


//============================================================================
//
//  This file is part of GPSTk, the GPS Toolkit.
//
//  The GPSTk is free software; you can redistribute it and/or modify
//  it under the terms of the GNU Lesser General Public License as published
//  by the Free Software Foundation; either version 2.1 of the License, or
//  any later version.
//
//  The GPSTk is distributed in the hope that it will be useful,
//  but WITHOUT ANY WARRANTY; without even the implied warranty of
//  MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE.  See the
//  GNU Lesser General Public License for more details.
//
//  You should have received a copy of the GNU Lesser General Public
//  License along with GPSTk; if not, write to the Free Software Foundation,
//  Inc., 59 Temple Place, Suite 330, Boston, MA  02111-1307  USA
//
//  Wei Yan - Chinese Academy of Sciences . 2009, 2010
//
//============================================================================

#include <iostream>
#include <string>

#include "Integrator.hpp"
#include "RungeKuttaFehlberg.hpp"
#include "SatOrbit.hpp"


namespace gpstk
{

   class SatOrbitPropagator
   {
   public:

      SatOrbitPropagator();

      virtual ~SatOrbitPropagator();

      /* set force model setting
      */
      //void setForceModel(ForceModelSetting& fms);
   

      SatOrbitPropagator& setIntegrator(Integrator* pIntg)
      { pIntegrator = pIntg; return (*this); }


      SatOrbitPropagator& setDefaultIntegrator()
      { pIntegrator = &rkfIntegrator; return (*this); }

      SatOrbitPropagator& setOrbit(SatOrbit* porbit)
      { pOrbit = porbit; return (*this); }
      

      SatOrbitPropagator& setDefaultOrbit()
      { pOrbit = &defaultOrbit; return (*this); }


      SatOrbitPropagator& setStepSize(double step_size = 10.0)
      { pIntegrator->setStepSize(step_size); return (*this); }

      SatOrbitPropagator& setInitState(UTCTime utc0, Vector<double> rv0);
      

      virtual bool integrateTo(double tf);


      Vector<double> rvState(bool bJ2k = true);

      Matrix<double> transitionMatrix()
      { return phiMatrix; }

      Matrix<double> sensitivityMatrix()
      { return sMatrix; }

      UTCTime getCurTime()
      { UTCTime utc = pOrbit->getRefEpoch(); utc += curT; return utc;}

      Vector<double> getCurState()
      { return curState;}

      int getNP()
      { return (curState.size() - 42) / 6; }

      SatOrbit* getSatOrbitPointer()
      { return pOrbit; }

      void writeToFile(ostream& s);

      /*
      * try to integrate ephemeris and print it to a file
      * just for compare it with stk8.1
      * 
      * yanwei,Sep 19 th,2009
      */
      //void makeSatEph(OrbitSetting& os,string fileName);
      //void makeRefSatEph(OrbitSetting& os,string fileName);

      /* For Testing and Debuging...
      */
      void test();

   protected:

      virtual Vector<double> integrateTo(double t, Vector<double> y, double tf);

      /* set initial state of the the integrator
      *
      *  v      3
      * dr_dr0    3*3
      * dr_dv0   3*3
      * dr_dp0   3*np
      * dv_dr0   3*3
      * dv_dv0   3*3
      * dv_dp0   3*np
      */
      void setState(Vector<double> state);

      void setRefEpoch(UTCTime utc)
      { pOrbit->setRefEpoch(utc); }

      void updateMatrix();

      Integrator*   pIntegrator;

      SatOrbit*   pOrbit;

   private:

      RungeKuttaFehlberg rkfIntegrator;

      SatOrbit   defaultOrbit;
            
      double curT;         

         // r        3
         // v        3
         // dr_dr0   3*3
         // dr_dv0   3*3
         // dr_dp0   3*np
         // dv_dr0   3*3
         // dv_dv0   3*3
         // dv_dp0   3*np
      Vector<double> curState;         // 42+6*np
      
      Vector<double>   rvVector;      // 6

      Matrix<double> phiMatrix;      // 6*6
      
      Matrix<double> sMatrix;         // 6*np
      

      std::set<ForceModel::ForceModelType> setFMT;

   }; // End of class 'SatOrbitPropagator'
   

   ostream& operator<<(ostream& s, SatOrbitPropagator& op);

      // @}

} // end namespace 'gpstk'


#endif   // GPSTK_SAT_ORBIT_PROPAGATOR_HPP

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