Keplerian.h

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/* 
* \todo include conversion functions
*/

#ifndef __SSF_KEPLERIAN_H__
#define __SSF_KEPLERIAN_H__
#include "Matrix.h"
#include "OrbitStateRepresentation.h"
#include <string>
#include <stdlib.h>
#include <sstream>
using namespace std;

#define MU 1    // not a good value for MU.
#ifndef PI
#include <math.h>
#define PI M_PI
#endif
namespace O_SESSAME {

#define NUM_KEPLERIAN_ELEMENTS 6 
const int SEMIMAJOR_AXIS = VectorIndexBase + 0; 
const int ECCENTRICITY  = VectorIndexBase + 1; 
const int INCLINATION   = VectorIndexBase + 2; 
const int LONG_ASC_NODE = VectorIndexBase + 3; 
const int ARG_PERIGEE   = VectorIndexBase + 4; 
const int TRUE_ANOMALY  = VectorIndexBase + 5; 
typedef struct tleStruct {
        string  satName;                                
        int             satNumber;                              
        char    satClassification;              
        int             launchYear;                             
        int             launchNumber;                   
        string  launchPiece;                    
        int             epochYear;                              
        double  epochDay;                               
        double  meanmotion1stDeriv;             
        double  meanmotion2ndDeriv;             
        double  bstarDrag;                              
        int             ephemerisType;                  
        int             elementNumber;                  
        int             checksumLine1;                  
        double  meanAnomaly;                    
        double  eccentricAnomaly;               
        double  meanMotion;                             
        int             revolutionNumber;               
        int             checksumLine2;                  
};

                
                
class Keplerian : public OrbitStateRepresentation
{
public:
    
    virtual ~Keplerian();

        virtual Keplerian* NewPointer();

    virtual Keplerian* Clone();

        Keplerian();
    
    Keplerian(const Vector& _Elements);

    void SetPositionVelocity(const Vector& _Position, const Vector& _Velocity);

    void SetPositionVelocity(const Vector& _PositionVelocity);

        void SetPositionVelocity(const Vector& _Position, const Vector& _Velocity, const OrbitFrame& _OrbFrame);
    
    void SetPositionVelocity(const Vector& _PositionVelocity, const OrbitFrame& _OrbFrame);

    Vector GetPositionVelocity() const;

    Vector GetPositionVelocity(const OrbitFrame& _TargetOrbFrame) const;

    void GetPositionVelocity(Vector& _Position, Vector& _Velocity) const;
  
    void GetPositionVelocity(Vector& _Position, Vector& _Velocity, const OrbitFrame& _TargetOrbFrame) const;

        double GetEccentricAnomalyFromMeanAnomaly(const double& _MeanAnomaly);
        
        void GetTrueAnomalyFromEccentricAnomaly(const double& _EccentricAnomaly);
        
        tleStruct ReadTwoLineElementSet(const string& _TwoLineElementSet);



/* ********* KEPLERIAN SPECIFIC FUNCTIONS ********* */    

    inline double GetSemiParameter() const {return GetSemimajorAxis() * (1 - pow(GetEccentricity(),2));};

    inline double GetSemimajorAxis() const {return m_OrbitalElements(SEMIMAJOR_AXIS);};

    inline double GetEccentricity() const {return m_OrbitalElements(ECCENTRICITY);};

    inline double GetInclination() const {return m_OrbitalElements(INCLINATION);};

    inline double GetLongAscNode() const {return m_OrbitalElements(LONG_ASC_NODE);};

    inline double GetArgPerigee() const  {return m_OrbitalElements(ARG_PERIGEE);};

    inline double GetTrueAnomaly() const {return m_OrbitalElements(TRUE_ANOMALY);};

    inline double GetMeanMotion() const  {return sqrt(MU/pow(GetSemimajorAxis(),3));};

/* ********* ********* ******** ********* ********* */    
        
        
        
        
        
/* ********* DEPRECATED FUNCTIONS ********* */    

    virtual void SetState(const Vector& _Elements);

    virtual Vector GetState() const;
        
    virtual void GetState(Vector& _Elements) const;
        
/* ********* ********** ********* ********* */          

        

private:
    Vector m_OrbitalElements;

        tleStruct m_tleData;
};
} // close namespace O_SESSAME

#endif

// Do not change the comments below - they will be added automatically by CVS
/*****************************************************************************
*       $Log: Keplerian.h,v $
*       Revision 1.11  2003/05/23 19:28:14  simpliciter
*       Moved comments to implementation file, basic housekeeping.
*       
*       Revision 1.10  2003/05/20 20:49:42  simpliciter
*       Added new functions for parsing TLEs:
*         - GetEccentricAnomalyFromMeanAnomaly,
*         - GetTrueAnomalyFromEccentricAnomaly,
*         - ReadTwoLineElementSet.
*       
*       Revision 1.9  2003/05/13 18:47:56  nilspace
*       Fixed comments for better formatting.
*       
*       Revision 1.8  2003/05/05 20:46:38  nilspace
*       Added inertial Get/SetPositionVelocity to conform to new OrbitStateRepresentation abstract class.
*       
*       Revision 1.7  2003/05/02 16:16:46  nilspace
*       Documented the API.
*       
*       Revision 1.6  2003/04/29 18:48:30  nilspace
*       Added NewPointer and Clone functions to help in getting the correct memory allocation.
*       
*       Revision 1.5  2003/04/24 21:14:23  nilspace
*       const'd all Get() functions.
*       
*       Revision 1.4  2003/04/24 20:10:47  nilspace
*       const'd all Get() functions.
*       
*       Revision 1.3  2003/04/23 18:52:29  nilspace
*       Updated to call correct OrbitFrame::GetRotation calls.
*       Added temporary PI and MU values.
*       Added K_Vector Values.
*       
*       Revision 1.2  2003/04/22 18:06:08  nilspace
*       Added math for Matthew Berry.
*       
*       Revision 1.1  2003/04/08 22:47:35  nilspace
*       Initial Submission.
*
******************************************************************************/

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