yodaUtility/sgp4/cEci.cpp

//
// cEci.cpp
//
// Copyright (c) 2002-2003 Michael F. Henry
//
#include "stdafx.h"

#include "cEci.h"
#include "globals.h"

//////////////////////////////////////////////////////////////////////
// cEci Class
//////////////////////////////////////////////////////////////////////
cEci::cEci(const cVector &pos, 
           const cVector &vel, 
           const cJulian &date,
           bool  IsAeUnits /* = true */)
{
   m_pos      = pos;
   m_vel      = vel;
   m_date     = date;
   m_VecUnits = (IsAeUnits ? UNITS_AE : UNITS_NONE);
}

//////////////////////////////////////////////////////////////////////
// cEci(cCoordGeo&, cJulian&)
// Calculate the ECI coordinates of the location "geo" at time "date".
// Assumes geo coordinates are km-based.
// Assumes the earth is an oblate spheroid as defined in WGS '72.
// Reference: The 1992 Astronomical Almanac, page K11
// Reference: www.celestrak.com (Dr. TS Kelso)
cEci::cEci(const cCoordGeo &geo, const cJulian &date)
{
   m_VecUnits = UNITS_KM;

   double mfactor = TWOPI * (OMEGA_E / SEC_PER_DAY);
   double lat = geo.m_Lat;
   double lon = geo.m_Lon;
   double alt = geo.m_Alt;

   // Calculate Local Mean Sidereal Time (theta)
   double theta = date.toLMST(lon);
   double c = 1.0 / sqrt(1.0 + F * (F - 2.0) * sqr(sin(lat)));
   double s = sqr(1.0 - F) * c;
   double achcp = (XKMPER_WGS72 * c + alt) * cos(lat);

   m_date = date;

   m_pos.m_x = achcp * cos(theta);               // km
   m_pos.m_y = achcp * sin(theta);               // km
   m_pos.m_z = (XKMPER_WGS72 * s + alt) * sin(lat);   // km
   m_pos.m_w = sqrt(sqr(m_pos.m_x) + 
                    sqr(m_pos.m_y) + 
                    sqr(m_pos.m_z));            // range, km

   m_vel.m_x = -mfactor * m_pos.m_y;            // km / sec
   m_vel.m_y =  mfactor * m_pos.m_x;
   m_vel.m_z = 0.0;
   m_vel.m_w = sqrt(sqr(m_vel.m_x) +            // range rate km/sec^2
                    sqr(m_vel.m_y));
}

//////////////////////////////////////////////////////////////////////////////
// toGeo()
// Return the corresponding geodetic position (based on the current ECI
// coordinates/Julian date).
// Assumes the earth is an oblate spheroid as defined in WGS '72.
// Side effects: Converts the position and velocity vectors to km-based units.
// Reference: The 1992 Astronomical Almanac, page K12. 
// Reference: www.celestrak.com (Dr. TS Kelso)
cCoordGeo cEci::toGeo()
{
   ae2km(); // Vectors must be in kilometer-based units

   double theta = AcTan(m_pos.m_y, m_pos.m_x);
   double lon   = fmod(theta - m_date.toGMST(), TWOPI);
   
   if (lon < 0.0) 
      lon += TWOPI;  // "wrap" negative modulo

   double r   = sqrt(sqr(m_pos.m_x) + sqr(m_pos.m_y));
   double e2  = F * (2.0 - F);
   double lat = AcTan(m_pos.m_z, r);

   const double delta = 1.0e-07;
   double phi;
   double c;

   do   
   {
      phi = lat;
      c   = 1.0 / sqrt(1.0 - e2 * sqr(sin(phi)));
      lat = AcTan(m_pos.m_z + XKMPER_WGS72 * c * e2 * sin(phi), r);
   }
   while (fabs(lat - phi) > delta);
   
   double alt = r / cos(lat) - XKMPER_WGS72 * c;

   return cCoordGeo(lat, lon, alt); // radians, radians, kilometers
}

//////////////////////////////////////////////////////////////////////////////
// ae2km()
// Convert the position and velocity vector units from AE-based units
// to kilometer based units.
void cEci::ae2km()
{
   if (UnitsAreAe())
   {
      MulPos(XKMPER_WGS72 / AE);                       // km
      MulVel((XKMPER_WGS72 / AE) * (MIN_PER_DAY / 86400));  // km/sec
      m_VecUnits = UNITS_KM;
   }
}
1	//
2	// cEci.cpp
3	//
4	// Copyright (c) 2002-2003 Michael F. Henry
5	//
6	#include "stdafx.h"
7
8	#include "cEci.h"
9	#include "globals.h"
10
11	//////////////////////////////////////////////////////////////////////
12	// cEci Class
13	//////////////////////////////////////////////////////////////////////
14	cEci::cEci(const cVector &pos,
15	const cVector &vel,
16	const cJulian &date,
17	bool IsAeUnits /* = true */)
18	{
19	m_pos = pos;
20	m_vel = vel;
21	m_date = date;
22	m_VecUnits = (IsAeUnits ? UNITS_AE : UNITS_NONE);
23	}
24
25	//////////////////////////////////////////////////////////////////////
26	// cEci(cCoordGeo&, cJulian&)
27	// Calculate the ECI coordinates of the location "geo" at time "date".
28	// Assumes geo coordinates are km-based.
29	// Assumes the earth is an oblate spheroid as defined in WGS '72.
30	// Reference: The 1992 Astronomical Almanac, page K11
31	// Reference: www.celestrak.com (Dr. TS Kelso)
32	cEci::cEci(const cCoordGeo &geo, const cJulian &date)
33	{
34	m_VecUnits = UNITS_KM;
35
36	double mfactor = TWOPI * (OMEGA_E / SEC_PER_DAY);
37	double lat = geo.m_Lat;
38	double lon = geo.m_Lon;
39	double alt = geo.m_Alt;
40
41	// Calculate Local Mean Sidereal Time (theta)
42	double theta = date.toLMST(lon);
43	double c = 1.0 / sqrt(1.0 + F * (F - 2.0) * sqr(sin(lat)));
44	double s = sqr(1.0 - F) * c;
45	double achcp = (XKMPER_WGS72 * c + alt) * cos(lat);
46
47	m_date = date;
48
49	m_pos.m_x = achcp * cos(theta); // km
50	m_pos.m_y = achcp * sin(theta); // km
51	m_pos.m_z = (XKMPER_WGS72 * s + alt) * sin(lat); // km
52	m_pos.m_w = sqrt(sqr(m_pos.m_x) +
53	sqr(m_pos.m_y) +
54	sqr(m_pos.m_z)); // range, km
55
56	m_vel.m_x = -mfactor * m_pos.m_y; // km / sec
57	m_vel.m_y = mfactor * m_pos.m_x;
58	m_vel.m_z = 0.0;
59	m_vel.m_w = sqrt(sqr(m_vel.m_x) + // range rate km/sec^2
60	sqr(m_vel.m_y));
61	}
62
63	//////////////////////////////////////////////////////////////////////////////
64	// toGeo()
65	// Return the corresponding geodetic position (based on the current ECI
66	// coordinates/Julian date).
67	// Assumes the earth is an oblate spheroid as defined in WGS '72.
68	// Side effects: Converts the position and velocity vectors to km-based units.
69	// Reference: The 1992 Astronomical Almanac, page K12.
70	// Reference: www.celestrak.com (Dr. TS Kelso)
71	cCoordGeo cEci::toGeo()
72	{
73	ae2km(); // Vectors must be in kilometer-based units
74
75	double theta = AcTan(m_pos.m_y, m_pos.m_x);
76	double lon = fmod(theta - m_date.toGMST(), TWOPI);
77
78	if (lon < 0.0)
79	lon += TWOPI; // "wrap" negative modulo
80
81	double r = sqrt(sqr(m_pos.m_x) + sqr(m_pos.m_y));
82	double e2 = F * (2.0 - F);
83	double lat = AcTan(m_pos.m_z, r);
84
85	const double delta = 1.0e-07;
86	double phi;
87	double c;
88
89	do
90	{
91	phi = lat;
92	c = 1.0 / sqrt(1.0 - e2 * sqr(sin(phi)));
93	lat = AcTan(m_pos.m_z + XKMPER_WGS72 * c * e2 * sin(phi), r);
94	}
95	while (fabs(lat - phi) > delta);
96
97	double alt = r / cos(lat) - XKMPER_WGS72 * c;
98
99	return cCoordGeo(lat, lon, alt); // radians, radians, kilometers
100	}
101
102	//////////////////////////////////////////////////////////////////////////////
103	// ae2km()
104	// Convert the position and velocity vector units from AE-based units
105	// to kilometer based units.
106	void cEci::ae2km()
107	{
108	if (UnitsAreAe())
109	{
110	MulPos(XKMPER_WGS72 / AE); // km
111	MulVel((XKMPER_WGS72 / AE) * (MIN_PER_DAY / 86400)); // km/sec
112	m_VecUnits = UNITS_KM;
113	}
114	}