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// |
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// stdafx.h |
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// |
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#ifndef sgp4_h |
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#define sgp4_h |
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|
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#if !defined(__CINT__) || defined(__MAKECINT__) |
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|
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//#define WIN32_LEAN_AND_MEAN // Exclude rarely-used stuff from Windows headers |
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#include <stdio.h> |
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//#include <tchar.h> |
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#include <ctype.h> |
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#include <string> |
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#include <map> |
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#include <vector> |
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#include <algorithm> |
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#include <assert.h> |
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#include <time.h> |
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#include <math.h> |
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|
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using namespace std; |
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// |
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// globals.h |
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// |
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|
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const double PI = 3.141592653589793; |
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const double TWOPI = 2.0 * PI; |
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const double RADS_PER_DEG = PI / 180.0; |
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|
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const double GM = 398601.2; // Earth gravitational constant, km^3/sec^2 |
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const double GEOSYNC_ALT = 42241.892; // km |
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const double EARTH_DIA = 12800.0; // km |
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const double DAY_SIDERAL = (23 * 3600) + (56 * 60) + 4.09; // sec |
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const double DAY_24HR = (24 * 3600); // sec |
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|
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const double AE = 1.0; |
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const double AU = 149597870.0; // Astronomical unit (km) (IAU 76) |
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const double SR = 696000.0; // Solar radius (km) (IAU 76) |
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const double TWOTHRD = 2.0 / 3.0; |
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const double XKMPER_WGS72 = 6378.135; // Earth equatorial radius - km (WGS '72) |
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const double F = 1.0 / 298.26; // Earth flattening (WGS '72) |
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const double GE = 398600.8; // Earth gravitational constant (WGS '72) |
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const double J2 = 1.0826158E-3; // J2 harmonic (WGS '72) |
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const double J3 = -2.53881E-6; // J3 harmonic (WGS '72) |
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const double J4 = -1.65597E-6; // J4 harmonic (WGS '72) |
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const double CK2 = J2 / 2.0; |
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const double CK4 = -3.0 * J4 / 8.0; |
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const double XJ3 = J3; |
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const double E6A = 1.0e-06; |
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const double QO = AE + 120.0 / XKMPER_WGS72; |
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const double S = AE + 78.0 / XKMPER_WGS72; |
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const double HR_PER_DAY = 24.0; // Hours per day (solar) |
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const double MIN_PER_DAY = 1440.0; // Minutes per day (solar) |
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const double SEC_PER_DAY = 86400.0; // Seconds per day (solar) |
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const double OMEGA_E = 1.00273790934; // earth rotation per sideral day |
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const double XKE = sqrt(3600.0 * GE / //sqrt(ge) ER^3/min^2 |
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(XKMPER_WGS72 * XKMPER_WGS72 * XKMPER_WGS72)); |
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const double QOMS2T = pow((QO - S), 4); //(QO - S)^4 ER^4 |
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|
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// Utility functions |
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double sqr (const double x); |
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double Fmod2p(const double arg); |
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double AcTan (const double sinx, double cosx); |
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|
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double rad2deg(const double); |
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double deg2rad(const double); |
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// |
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// coord.h |
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// |
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// Copyright 2002-2003 Michael F. Henry |
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// |
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////////////////////////////////////////////////////////////////////// |
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// Geocentric coordinates. |
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class cCoordGeo |
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{ |
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public: |
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cCoordGeo(); |
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cCoordGeo(double lat, double lon, double alt) : |
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m_Lat(lat), m_Lon(lon), m_Alt(alt) {} |
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virtual ~cCoordGeo() {}; |
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|
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double m_Lat; // Latitude, radians (negative south) |
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double m_Lon; // Longitude, radians (negative west) |
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double m_Alt; // Altitude, km (above mean sea level) |
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}; |
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|
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////////////////////////////////////////////////////////////////////// |
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// Topocentric-Horizon coordinates. |
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class cCoordTopo |
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{ |
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public: |
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cCoordTopo(); |
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cCoordTopo(double az, double el, double rng, double rate) : |
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m_Az(az), m_El(el), m_Range(rng), m_RangeRate(rate) {} |
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virtual ~cCoordTopo() {}; |
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|
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double m_Az; // Azimuth, radians |
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double m_El; // Elevation, radians |
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double m_Range; // Range, kilometers |
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double m_RangeRate; // Range rate of change, km/sec |
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// Negative value means "towards observer" |
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}; |
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|
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// cVector.h: interface for the cVector class. |
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// |
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// Copyright 2003 (c) Michael F. Henry |
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// |
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////////////////////////////////////////////////////////////////////// |
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|
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class cVector |
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{ |
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public: |
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cVector(double x = 0.0, double y = 0.0, double z = 0.0, double w = 0.0) : |
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m_x(x), m_y(y), m_z(z), m_w(w) {} |
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virtual ~cVector() {}; |
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|
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void Sub(const cVector&); // subtraction |
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void Mul(double factor); // multiply each component by 'factor' |
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|
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double Angle(const cVector&) const; // angle between two vectors |
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double Magnitude() const; // vector magnitude |
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double Dot(const cVector& vec) const; // dot product |
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|
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// protected: |
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double m_x; |
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double m_y; |
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double m_z; |
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double m_w; |
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}; |
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// |
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// cTle.h |
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// |
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// This class will accept a single set of two-line elements and then allow |
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// a client to request specific fields, such as epoch, mean motion, |
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// etc., from the set. |
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// |
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// Copyright 1996-2003 Michael F. Henry |
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// |
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///////////////////////////////////////////////////////////////////////////// |
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class cTle |
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{ |
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public: |
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cTle(string&, string&, string&); |
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cTle(const cTle &tle); |
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~cTle(); |
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|
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enum eTleLine |
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{ |
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LINE_ZERO, |
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LINE_ONE, |
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LINE_TWO |
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}; |
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|
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enum eField |
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{ |
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FLD_FIRST, |
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FLD_NORADNUM = FLD_FIRST, |
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FLD_INTLDESC, |
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FLD_SET, // TLE set number |
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FLD_EPOCHYEAR, // Epoch: Last two digits of year |
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FLD_EPOCHDAY, // Epoch: Fractional Julian Day of year |
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FLD_ORBITNUM, // Orbit at epoch |
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FLD_I, // Inclination |
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FLD_RAAN, // R.A. ascending node |
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FLD_E, // Eccentricity |
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FLD_ARGPER, // Argument of perigee |
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FLD_M, // Mean anomaly |
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FLD_MMOTION, // Mean motion |
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FLD_MMOTIONDT, // First time derivative of mean motion |
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FLD_MMOTIONDT2,// Second time derivative of mean motion |
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FLD_BSTAR, // BSTAR Drag |
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FLD_LAST // MUST be last |
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}; |
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|
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enum eUnits |
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{ |
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U_FIRST, |
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U_RAD = U_FIRST, // radians |
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U_DEG, // degrees |
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U_NATIVE, // TLE format native units (no conversion) |
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U_LAST // MUST be last |
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}; |
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|
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void Initialize(); |
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|
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static int CheckSum(const string&); |
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static bool IsValidLine(string&, eTleLine); |
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static string ExpToDecimal(const string&); |
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|
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static void TrimLeft(string&); |
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static void TrimRight(string&); |
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|
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double getField(eField fld, // which field to retrieve |
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eUnits unit = U_NATIVE, // return units in rad, deg etc. |
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string *pstr = NULL, // return ptr for str value |
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bool bStrUnits = false) // 'true': append units to str val |
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const; |
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string getName() const { return m_strName; } |
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string getLine1() const { return m_strLine1;} |
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string getLine2() const { return m_strLine2;} |
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|
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protected: |
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static double ConvertUnits(double val, eField fld, eUnits units); |
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|
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private: |
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string getUnits(eField) const; |
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double getFieldNumeric(eField) const; |
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|
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// Satellite name and two data lines |
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string m_strName; |
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string m_strLine1; |
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string m_strLine2; |
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|
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// Converted fields, in atof()-readable form |
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string m_Field[FLD_LAST]; |
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|
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// Cache of field values in "double" format |
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typedef int FldKey; |
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FldKey Key(eUnits u, eField f) const { return (u * 100) + f; } |
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mutable map<FldKey, double> m_mapCache; |
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}; |
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|
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/////////////////////////////////////////////////////////////////////////// |
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// |
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// TLE data format |
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// |
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// [Reference: T.S. Kelso] |
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// |
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// Two line element data consists of three lines in the following format: |
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// |
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// AAAAAAAAAAAAAAAAAAAAAA |
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// 1 NNNNNU NNNNNAAA NNNNN.NNNNNNNN +.NNNNNNNN +NNNNN-N +NNNNN-N N NNNNN |
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// 2 NNNNN NNN.NNNN NNN.NNNN NNNNNNN NNN.NNNN NNN.NNNN NN.NNNNNNNNNNNNNN |
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// |
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// Line 0 is a twenty-two-character name. |
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// |
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// Lines 1 and 2 are the standard Two-Line Orbital Element Set Format identical |
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// to that used by NORAD and NASA. The format description is: |
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// |
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// Line 1 |
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// Column Description |
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// 01-01 Line Number of Element Data |
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// 03-07 Satellite Number |
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// 10-11 International Designator (Last two digits of launch year) |
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// 12-14 International Designator (Launch number of the year) |
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// 15-17 International Designator (Piece of launch) |
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// 19-20 Epoch Year (Last two digits of year) |
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// 21-32 Epoch (Julian Day and fractional portion of the day) |
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// 34-43 First Time Derivative of the Mean Motion |
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// or Ballistic Coefficient (Depending on ephemeris type) |
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// 45-52 Second Time Derivative of Mean Motion (decimal point assumed; |
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// blank if N/A) |
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// 54-61 BSTAR drag term if GP4 general perturbation theory was used. |
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// Otherwise, radiation pressure coefficient. (Decimal point assumed) |
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// 63-63 Ephemeris type |
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// 65-68 Element number |
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// 69-69 Check Sum (Modulo 10) |
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// (Letters, blanks, periods, plus signs = 0; minus signs = 1) |
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// |
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// Line 2 |
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// Column Description |
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// 01-01 Line Number of Element Data |
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// 03-07 Satellite Number |
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// 09-16 Inclination [Degrees] |
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// 18-25 Right Ascension of the Ascending Node [Degrees] |
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// 27-33 Eccentricity (decimal point assumed) |
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// 35-42 Argument of Perigee [Degrees] |
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// 44-51 Mean Anomaly [Degrees] |
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// 53-63 Mean Motion [Revs per day] |
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// 64-68 Revolution number at epoch [Revs] |
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// 69-69 Check Sum (Modulo 10) |
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// |
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// All other columns are blank or fixed. |
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// |
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// Example: |
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// |
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// NOAA 6 |
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// 1 11416U 86 50.28438588 0.00000140 67960-4 0 5293 |
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// 2 11416 98.5105 69.3305 0012788 63.2828 296.9658 14.24899292346978 |
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|
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// |
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// cJulian.h |
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// |
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// Copyright (c) 2003 Michael F. Henry |
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// |
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// |
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// See note in cJulian.cpp for information on this class and the epoch dates |
| 288 |
// |
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const double EPOCH_JAN1_00H_1900 = 2415019.5; // Jan 1.0 1900 = Jan 1 1900 00h UTC |
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const double EPOCH_JAN1_12H_1900 = 2415020.0; // Jan 1.5 1900 = Jan 1 1900 12h UTC |
| 291 |
const double EPOCH_JAN1_12H_2000 = 2451545.0; // Jan 1.5 2000 = Jan 1 2000 12h UTC |
| 292 |
|
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////////////////////////////////////////////////////////////////////////////// |
| 294 |
class cJulian |
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{ |
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public: |
| 297 |
cJulian() { Initialize(2000, 1); } |
| 298 |
explicit cJulian(time_t t); // Create from time_t |
| 299 |
explicit cJulian(int year, double day); // Create from year, day of year |
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explicit cJulian(int year, // i.e., 2004 |
| 301 |
int mon, // 1..12 |
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int day, // 1..31 |
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int hour, // 0..23 |
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int min, // 0..59 |
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double sec = 0.0); // 0..(59.999999...) |
| 306 |
~cJulian() {}; |
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|
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double toGMST() const; // Greenwich Mean Sidereal Time |
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double toLMST(double lon) const; // Local Mean Sideral Time |
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time_t toTime() const; // To time_t type - avoid using |
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|
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double FromJan1_00h_1900() const { return m_Date - EPOCH_JAN1_00H_1900; } |
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double FromJan1_12h_1900() const { return m_Date - EPOCH_JAN1_12H_1900; } |
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double FromJan1_12h_2000() const { return m_Date - EPOCH_JAN1_12H_2000; } |
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|
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void getComponent(int *pYear, int *pMon = NULL, double *pDOM = NULL) const; |
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double getDate() const { return m_Date; } |
| 318 |
|
| 319 |
void addDay (double day) { m_Date += day; } |
| 320 |
void addHour(double hr ) { m_Date += (hr / HR_PER_DAY ); } |
| 321 |
void addMin (double min) { m_Date += (min / MIN_PER_DAY); } |
| 322 |
void addSec (double sec) { m_Date += (sec / SEC_PER_DAY); } |
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|
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double spanDay (const cJulian& b) const { return m_Date - b.m_Date; } |
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double spanHour(const cJulian& b) const { return spanDay(b) * HR_PER_DAY; } |
| 326 |
double spanMin (const cJulian& b) const { return spanDay(b) * MIN_PER_DAY; } |
| 327 |
double spanSec (const cJulian& b) const { return spanDay(b) * SEC_PER_DAY; } |
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|
| 329 |
static bool IsLeapYear(int y) |
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{ return (y % 4 == 0 && y % 100 != 0) || (y % 400 == 0); } |
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|
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protected: |
| 333 |
void Initialize(int year, double day); |
| 334 |
|
| 335 |
double m_Date; // Julian date |
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}; |
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// |
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// cEci.h |
| 339 |
// |
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// Copyright (c) 2003 Michael F. Henry |
| 341 |
// |
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////////////////////////////////////////////////////////////////////// |
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// class cEci |
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// Encapsulates an Earth-Centered Inertial position, velocity, and time. |
| 345 |
class cEci |
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{ |
| 347 |
public: |
| 348 |
cEci() { m_VecUnits = UNITS_NONE; } |
| 349 |
cEci(const cCoordGeo &geo, const cJulian &cJulian); |
| 350 |
cEci(const cVector &pos, const cVector &vel, |
| 351 |
const cJulian &date, bool IsAeUnits = true); |
| 352 |
virtual ~cEci() {}; |
| 353 |
|
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cCoordGeo toGeo(); |
| 355 |
|
| 356 |
cVector getPos() const { return m_pos; } |
| 357 |
cVector getVel() const { return m_vel; } |
| 358 |
cJulian getDate() const { return m_date; } |
| 359 |
|
| 360 |
void setUnitsAe() { m_VecUnits = UNITS_AE; } |
| 361 |
void setUnitsKm() { m_VecUnits = UNITS_KM; } |
| 362 |
bool UnitsAreAe() const { return m_VecUnits == UNITS_AE; } |
| 363 |
bool UnitsAreKm() const { return m_VecUnits == UNITS_KM; } |
| 364 |
void ae2km(); // Convert position, velocity vector units from AE to km |
| 365 |
|
| 366 |
protected: |
| 367 |
void MulPos(double factor) { m_pos.Mul(factor); } |
| 368 |
void MulVel(double factor) { m_vel.Mul(factor); } |
| 369 |
|
| 370 |
enum VecUnits |
| 371 |
{ |
| 372 |
UNITS_NONE, // not initialized |
| 373 |
UNITS_AE, |
| 374 |
UNITS_KM, |
| 375 |
}; |
| 376 |
|
| 377 |
cVector m_pos; |
| 378 |
cVector m_vel; |
| 379 |
cJulian m_date; |
| 380 |
VecUnits m_VecUnits; |
| 381 |
}; |
| 382 |
// |
| 383 |
// cNoradBase.h |
| 384 |
// |
| 385 |
// This class provides a base class for the NORAD SGP4/SDP4 |
| 386 |
// orbit models. |
| 387 |
// |
| 388 |
// Copyright (c) 2003 Michael F. Henry |
| 389 |
// |
| 390 |
#pragma once |
| 391 |
|
| 392 |
////////////////////////////////////////////////////////////////////////////// |
| 393 |
|
| 394 |
class cEci; |
| 395 |
class cOrbit; |
| 396 |
|
| 397 |
////////////////////////////////////////////////////////////////////////////// |
| 398 |
|
| 399 |
class cNoradBase |
| 400 |
{ |
| 401 |
public: |
| 402 |
cNoradBase(const cOrbit&); |
| 403 |
virtual ~cNoradBase() {}; |
| 404 |
|
| 405 |
virtual bool getPosition(double tsince, cEci &eci) = 0; |
| 406 |
|
| 407 |
protected: |
| 408 |
cNoradBase& operator=(const cNoradBase&); |
| 409 |
|
| 410 |
void Initialize(); |
| 411 |
bool FinalPosition(double incl, double omega, double e, |
| 412 |
double a, double xl, double xnode, |
| 413 |
double xn, double tsince, cEci &eci); |
| 414 |
|
| 415 |
const cOrbit &m_Orbit; |
| 416 |
|
| 417 |
// Orbital parameter variables which need only be calculated one |
| 418 |
// time for a given orbit (ECI position time-independent). |
| 419 |
double m_satInc; // inclination |
| 420 |
double m_satEcc; // eccentricity |
| 421 |
|
| 422 |
double m_cosio; double m_theta2; double m_x3thm1; double m_eosq; |
| 423 |
double m_betao2; double m_betao; double m_aodp; double m_xnodp; |
| 424 |
double m_s4; double m_qoms24; double m_perigee; double m_tsi; |
| 425 |
double m_eta; double m_etasq; double m_eeta; double m_coef; |
| 426 |
double m_coef1; double m_c1; double m_c2; double m_c3; |
| 427 |
double m_c4; double m_sinio; double m_a3ovk2; double m_x1mth2; |
| 428 |
double m_xmdot; double m_omgdot; double m_xhdot1; double m_xnodot; |
| 429 |
double m_xnodcf; double m_t2cof; double m_xlcof; double m_aycof; |
| 430 |
double m_x7thm1; |
| 431 |
}; |
| 432 |
// |
| 433 |
// cOrbit.h |
| 434 |
// |
| 435 |
// This is the header file for the class cOrbit. This class accepts a |
| 436 |
// single satellite's NORAD two-line element set and provides information |
| 437 |
// regarding the satellite's orbit such as period, axis length, |
| 438 |
// ECI coordinates/velocity, etc., using the SGP4/SDP4 orbital models. |
| 439 |
// |
| 440 |
// Copyright (c) 2002-2003 Michael F. Henry |
| 441 |
// |
| 442 |
#pragma once |
| 443 |
|
| 444 |
#include "math.h" |
| 445 |
|
| 446 |
using namespace std; |
| 447 |
////////////////////////////////////////////////////////////////////////////// |
| 448 |
|
| 449 |
class cVector; |
| 450 |
class cGeoCoord; |
| 451 |
class cEci; |
| 452 |
|
| 453 |
////////////////////////////////////////////////////////////////////////////// |
| 454 |
class cOrbit |
| 455 |
{ |
| 456 |
public: |
| 457 |
cOrbit(const cTle &tle); |
| 458 |
virtual ~cOrbit(); |
| 459 |
|
| 460 |
// Return satellite ECI data at given minutes since element's epoch. |
| 461 |
bool getPosition(double tsince, cEci *pEci) const; |
| 462 |
|
| 463 |
double Inclination() const { return radGet(cTle::FLD_I); } |
| 464 |
double Eccentricity() const { return m_tle.getField(cTle::FLD_E); } |
| 465 |
double RAAN() const { return radGet(cTle::FLD_RAAN); } |
| 466 |
double ArgPerigee() const { return radGet(cTle::FLD_ARGPER); } |
| 467 |
double BStar() const { return m_tle.getField(cTle::FLD_BSTAR) / AE;} |
| 468 |
double Drag() const { return m_tle.getField(cTle::FLD_MMOTIONDT); } |
| 469 |
double mnMotion() const { return m_tle.getField(cTle::FLD_MMOTION); } |
| 470 |
double mnAnomaly() const { return radGet(cTle::FLD_M); } |
| 471 |
double mnAnomaly(cJulian t) const; // mean anomaly (in radians) at time t |
| 472 |
|
| 473 |
cJulian Epoch() const { return m_jdEpoch; } |
| 474 |
|
| 475 |
double TPlusEpoch(const cJulian &t) const; // time span [t - epoch] in secs |
| 476 |
|
| 477 |
string SatName(bool fAppendId = false) const; |
| 478 |
|
| 479 |
// "Recovered" from the input elements |
| 480 |
double SemiMajor() const { return m_aeAxisSemiMajorRec; } |
| 481 |
double SemiMinor() const { return m_aeAxisSemiMinorRec; } |
| 482 |
double mnMotionRec() const { return m_mnMotionRec; } // mn motion, rads/min |
| 483 |
double Major() const { return 2.0 * SemiMajor(); } // major axis in AE |
| 484 |
double Minor() const { return 2.0 * SemiMinor(); } // minor axis in AE |
| 485 |
double Perigee() const { return m_kmPerigeeRec; } // perigee in km |
| 486 |
double Apogee() const { return m_kmApogeeRec; } // apogee in km |
| 487 |
double Period() const; // period in seconds |
| 488 |
|
| 489 |
protected: |
| 490 |
double radGet(cTle::eField fld) const |
| 491 |
{ return m_tle.getField(fld, cTle::U_RAD); } |
| 492 |
|
| 493 |
double degGet(cTle::eField fld) const |
| 494 |
{ return m_tle.getField(fld, cTle::U_DEG); } |
| 495 |
|
| 496 |
private: |
| 497 |
cTle m_tle; |
| 498 |
cJulian m_jdEpoch; |
| 499 |
cNoradBase *m_pNoradModel; |
| 500 |
|
| 501 |
// Caching variables; note units are not necessarily the same as tle units |
| 502 |
mutable double m_secPeriod; |
| 503 |
|
| 504 |
// Caching variables recovered from the input TLE elements |
| 505 |
double m_aeAxisSemiMinorRec; // semi-minor axis, in AE units |
| 506 |
double m_aeAxisSemiMajorRec; // semi-major axis, in AE units |
| 507 |
double m_mnMotionRec; // radians per minute |
| 508 |
double m_kmPerigeeRec; // perigee, in km |
| 509 |
double m_kmApogeeRec; // apogee, in km |
| 510 |
}; |
| 511 |
|
| 512 |
// |
| 513 |
// cNoradSGP4.h |
| 514 |
// |
| 515 |
// This class implements the NORAD Simple General Perturbation 4 orbit |
| 516 |
// model. This model provides the ECI coordiantes/velocity of satellites |
| 517 |
// with orbit periods less than 225 minutes. |
| 518 |
// |
| 519 |
// Copyright (c) 2003 Michael F. Henry |
| 520 |
// |
| 521 |
#pragma once |
| 522 |
|
| 523 |
class cOrbit; |
| 524 |
|
| 525 |
////////////////////////////////////////////////////////////////////////////// |
| 526 |
class cNoradSGP4 : public cNoradBase |
| 527 |
{ |
| 528 |
public: |
| 529 |
cNoradSGP4(const cOrbit &orbit); |
| 530 |
virtual ~cNoradSGP4() {}; |
| 531 |
|
| 532 |
virtual bool getPosition(double tsince, cEci &eci); |
| 533 |
|
| 534 |
protected: |
| 535 |
double m_c5; |
| 536 |
double m_omgcof; |
| 537 |
double m_xmcof; |
| 538 |
double m_delmo; |
| 539 |
double m_sinmo; |
| 540 |
}; |
| 541 |
|
| 542 |
// |
| 543 |
// cNoradSDP4.h |
| 544 |
// |
| 545 |
// This class implements the NORAD Simple Deep Perturbation 4 orbit |
| 546 |
// model. This model provides the ECI coordinates/velocity of satellites |
| 547 |
// with periods >= 225 minutes. |
| 548 |
// |
| 549 |
// Copyright (c) 2003 Michael F. Henry |
| 550 |
// |
| 551 |
#pragma once |
| 552 |
|
| 553 |
class cOrbit; |
| 554 |
|
| 555 |
////////////////////////////////////////////////////////////////////////////// |
| 556 |
class cNoradSDP4 : public cNoradBase |
| 557 |
{ |
| 558 |
public: |
| 559 |
cNoradSDP4(const cOrbit &orbit); |
| 560 |
virtual ~cNoradSDP4() {}; |
| 561 |
|
| 562 |
virtual bool getPosition(double tsince, cEci &eci); |
| 563 |
|
| 564 |
protected: |
| 565 |
bool DeepInit(double *eosq, double *sinio, double *cosio, double *m_betao, |
| 566 |
double *m_aodp, double *m_theta2, double *m_sing, double *m_cosg, |
| 567 |
double *m_betao2,double *xmdot, double *omgdot, double *xnodott); |
| 568 |
|
| 569 |
bool DeepSecular(double *xmdf, double *omgadf,double *xnode, double *emm, |
| 570 |
double *xincc, double *xnn, double *tsince); |
| 571 |
bool DeepCalcDotTerms (double *pxndot, double *pxnddt, double *pxldot); |
| 572 |
void DeepCalcIntegrator(double *pxndot, double *pxnddt, double *pxldot, |
| 573 |
const double &delt); |
| 574 |
bool DeepPeriodics(double *e, double *xincc, double *omgadf, |
| 575 |
double *xnode, double *xmam); |
| 576 |
double m_sing; |
| 577 |
double m_cosg; |
| 578 |
|
| 579 |
// Deep Initialization |
| 580 |
double eqsq; double siniq; double cosiq; double rteqsq; double ao; |
| 581 |
double cosq2; double sinomo; double cosomo; double bsq; double xlldot; |
| 582 |
double omgdt; double xnodot; |
| 583 |
|
| 584 |
// Deep Secular, Periodic |
| 585 |
double xll; double omgasm; double xnodes; double _em; |
| 586 |
double xinc; double xn; double t; |
| 587 |
|
| 588 |
// Variables shared by "Deep" routines |
| 589 |
double dp_e3; double dp_ee2; double dp_savtsn; double dp_se2; |
| 590 |
double dp_se3; double dp_sgh2; double dp_sgh3; double dp_sgh4; |
| 591 |
double dp_sghs; double dp_sh2; double dp_sh3; double dp_si2; |
| 592 |
double dp_si3; double dp_sl2; double dp_sl3; double dp_sl4; |
| 593 |
double dp_xgh2; double dp_xgh3; double dp_xgh4; double dp_xh2; |
| 594 |
double dp_xh3; double dp_xi2; double dp_xi3; double dp_xl2; |
| 595 |
double dp_xl3; double dp_xl4; double dp_xqncl; double dp_zmol; |
| 596 |
double dp_zmos; |
| 597 |
|
| 598 |
double dp_atime; double dp_d2201; double dp_d2211; double dp_d3210; |
| 599 |
double dp_d3222; double dp_d4410; double dp_d4422; double dp_d5220; |
| 600 |
double dp_d5232; double dp_d5421; double dp_d5433; double dp_del1; |
| 601 |
double dp_del2; double dp_del3; double dp_fasx2; double dp_fasx4; |
| 602 |
double dp_fasx6; double dp_omegaq; double dp_sse; double dp_ssg; |
| 603 |
double dp_ssh; double dp_ssi; double dp_ssl; double dp_step2; |
| 604 |
double dp_stepn; double dp_stepp; double dp_thgr; double dp_xfact; |
| 605 |
double dp_xlamo; double dp_xli; double dp_xni; |
| 606 |
|
| 607 |
bool dp_iresfl; |
| 608 |
bool dp_isynfl; |
| 609 |
|
| 610 |
// DeepInit vars that change with epoch |
| 611 |
double dpi_c; double dpi_ctem; double dpi_day; double dpi_gam; |
| 612 |
double dpi_stem; double dpi_xnodce; double dpi_zcosgl; double dpi_zcoshl; |
| 613 |
double dpi_zcosil; double dpi_zsingl; double dpi_zsinhl; double dpi_zsinil; |
| 614 |
double dpi_zx; double dpi_zy; |
| 615 |
|
| 616 |
}; |
| 617 |
|
| 618 |
#endif |
| 619 |
#endif |
| 620 |
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