yodaUtility/sgp4/cNoradBase.h

//
// cNoradBase.h
//
// This class provides a base class for the NORAD SGP4/SDP4
// orbit models.
//
// Copyright (c) 2003 Michael F. Henry
//
#pragma once

//////////////////////////////////////////////////////////////////////////////

class cEci;
class cOrbit;

//////////////////////////////////////////////////////////////////////////////

class cNoradBase
{
public:
   cNoradBase(const cOrbit&);
   ~cNoradBase(void);

   virtual bool getPosition(double tsince, cEci &eci) = 0;

protected:
   cNoradBase& operator=(const cNoradBase&);

   void Initialize();
   bool FinalPosition(double  incl, double omega,  double     e,   
                      double     a, double    xl,  double xnode, 
                      double    xn, double tsince, cEci &eci);

   const cOrbit &m_Orbit;

   // Orbital parameter variables which need only be calculated one
   // time for a given orbit (ECI position time-independent).
   double m_satInc;  // inclination
   double m_satEcc;  // eccentricity

   double m_cosio;   double m_theta2;  double m_x3thm1;  double m_eosq;  
   double m_betao2;  double m_betao;   double m_aodp;    double m_xnodp;
   double m_s4;      double m_qoms24;  double m_perigee; double m_tsi;
   double m_eta;     double m_etasq;   double m_eeta;    double m_coef;
   double m_coef1;   double m_c1;      double m_c2;      double m_c3;
   double m_c4;      double m_sinio;   double m_a3ovk2;  double m_x1mth2;
   double m_xmdot;   double m_omgdot;  double m_xhdot1;  double m_xnodot;
   double m_xnodcf;  double m_t2cof;   double m_xlcof;   double m_aycof;
   double m_x7thm1;
};
1	//
2	// cNoradBase.h
3	//
4	// This class provides a base class for the NORAD SGP4/SDP4
5	// orbit models.
6	//
7	// Copyright (c) 2003 Michael F. Henry
8	//
9	#pragma once
10
11	//////////////////////////////////////////////////////////////////////////////
12
13	class cEci;
14	class cOrbit;
15
16	//////////////////////////////////////////////////////////////////////////////
17
18	class cNoradBase
19	{
20	public:
21	cNoradBase(const cOrbit&);
22	~cNoradBase(void);
23
24	virtual bool getPosition(double tsince, cEci &eci) = 0;
25
26	protected:
27	cNoradBase& operator=(const cNoradBase&);
28
29	void Initialize();
30	bool FinalPosition(double incl, double omega, double e,
31	double a, double xl, double xnode,
32	double xn, double tsince, cEci &eci);
33
34	const cOrbit &m_Orbit;
35
36	// Orbital parameter variables which need only be calculated one
37	// time for a given orbit (ECI position time-independent).
38	double m_satInc; // inclination
39	double m_satEcc; // eccentricity
40
41	double m_cosio; double m_theta2; double m_x3thm1; double m_eosq;
42	double m_betao2; double m_betao; double m_aodp; double m_xnodp;
43	double m_s4; double m_qoms24; double m_perigee; double m_tsi;
44	double m_eta; double m_etasq; double m_eeta; double m_coef;
45	double m_coef1; double m_c1; double m_c2; double m_c3;
46	double m_c4; double m_sinio; double m_a3ovk2; double m_x1mth2;
47	double m_xmdot; double m_omgdot; double m_xhdot1; double m_xnodot;
48	double m_xnodcf; double m_t2cof; double m_xlcof; double m_aycof;
49	double m_x7thm1;
50	};