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	kusanagi	1.1	//
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			};