10609521019

Committed 29 Aug 2024 05:56AM UTC coverage: 12.113% (-0.03%) from 12.138%

Build # 10609521019

Build Type

Pull #3847

github

Committed by

alex-w

Commit Message

[SSE] Add info for total candidates for addiing...

Pull Request Pull Request #3847: Threaded planet computation (and a few more speedups)

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30 of 686 new or added lines in 51 files covered. (4.37%)

41 existing lines in 18 files now uncovered.

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0.0

/plugins/Satellites/src/gsatellite/gSatTEME.cpp

/***************************************************************************
 * Name: gSatTEME.cpp
 *
 * Description: gSatTEME class implementation.
 *              This class abstract all the SGP4 complexity. It uses the
 *              David. A. Vallado code for SGP4 Calculation.
 *
 * Reference:
 *              Revisiting Spacetrack Report #3 AIAA 2006-6753
 *              Vallado, David A., Paul Crawford, Richard Hujsak, and T.S.
 *              Kelso, "Revisiting Spacetrack Report #3,"
 *              presented at the AIAA/AAS Astrodynamics Specialist
 *              Conference, Keystone, CO, 2006 August 21-24.
 *              https://celestrak.org/publications/AIAA/2006-6753/
 ***************************************************************************/

/***************************************************************************
 *   Copyright (C) 2004 by J.L. Canales                                    *
 *   ph03696@homeserver                                                    *
 *                                                                         *
 *   This program is free software; you can redistribute it and/or modify  *
 *   it under the terms of the GNU General Public License as published by  *
 *   the Free Software Foundation; either version 2 of the License, or     *
 *   (at your option) any later version.                                   *
 *                                                                         *
 *   This program is distributed in the hope that it will be useful,       *
 *   but WITHOUT ANY WARRANTY; without even the implied warranty of        *
 *   MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE.  See the         *
 *   GNU General Public License for more details.                          *
 *                                                                         *
 *   You should have received a copy of the GNU General Public License     *
 *   along with this program; if not, write to the                         *
 *   Free Software Foundation, Inc.,                                       *
 *   51 Franklin Street, Suite 500, Boston, MA  02110-1335, USA.             *
 ***************************************************************************/

// GKepFile
#include "gSatTEME.hpp"
//#include <iostream>
//#include <iomanip>
#include <math.h>

#include "mathUtils.hpp"
#include "sgp4io.h"

#define CONSTANTS_SET wgs84
#define TYPERUN_SET   'c'
#define OPSMODE_SET   'i'
#define TYPEINPUT_SET 'm'

#define LATITUDE  0
#define LONGITUDE 1
#define ALTITUDE  2

// Constructors
gSatTEME::gSatTEME(const char *pstrName, char *pstrTleLine1, char *pstrTleLine2)
{
        double startmfe, stopmfe, deltamin; // dummies

        m_SatName = pstrName;

        //set gravitational constants
        getgravconst(CONSTANTS_SET, tumin, mu, radiusearthkm, xke, j2, j3, j4, j3oj2);

        //Parsing TLE_Files and sat variables setting
        twoline2rv(pstrTleLine1, pstrTleLine2, TYPERUN_SET, TYPEINPUT_SET, OPSMODE_SET, CONSTANTS_SET,
                   startmfe, stopmfe, deltamin, satrec);

        // call the propagator to get the initial state vector value
        sgp4(CONSTANTS_SET, satrec,  0.0, m_Position.v,  m_Vel.v);
}

void gSatTEME::setEpoch(gTime ai_time)
{
        gTime     kepEpoch(satrec.jdsatepoch);
        gTimeSpan tSince = ai_time - kepEpoch;

        double dtsince = tSince.getDblSeconds()/KSEC_PER_MIN;
        // call the propagator to get the initial state vector value
        sgp4(CONSTANTS_SET, satrec,  dtsince, m_Position.v,  m_Vel.v);

        m_SubPoint    = computeSubPoint( ai_time);
}

void gSatTEME::setMinSinceKepEpoch(double ai_minSinceKepEpoch)
{
        gTimeSpan tSince( ai_minSinceKepEpoch/KMIN_PER_DAY);
        gTime     Epoch(satrec.jdsatepoch);
        Epoch += tSince;
        // call the propagator to get the initial state vector value
        sgp4(CONSTANTS_SET, satrec,  ai_minSinceKepEpoch, m_Position.v,  m_Vel.v);

        m_SubPoint    = computeSubPoint( Epoch);
}

Vec3d gSatTEME::computeSubPoint(gTime ai_Time)
{
        Vec3d resultVector; // (0) Latitude, (1) Longitude, (2) altitude

        const double theta = atan2(m_Position[1], m_Position[0]); // radians
        resultVector[ LONGITUDE] = fmod((theta - ai_Time.toThetaGMST()), 2.*M_PI);  //radians


        const double r = std::sqrt(Sqr(m_Position[0]) + Sqr(m_Position[1]));
        const double e2 = __f*(2. - __f);
        resultVector[ LATITUDE] = atan2(m_Position[2],r); /*radians*/

        double phi, c;
        do
        {
                phi = resultVector[ LATITUDE];
                c = 1./std::sqrt(1. - e2*Sqr(sin(phi)));
                resultVector[ LATITUDE] = atan2(m_Position[2] + EARTH_RADIUS*c*e2*sin(phi),r);
        }
        while(fabs(resultVector[ LATITUDE] - phi) >= 1E-10);

        resultVector[ ALTITUDE] = r/cos(resultVector[ LATITUDE]) - EARTH_RADIUS*c;/*kilometers*/

        if(resultVector[ LATITUDE] > (M_PI/2.0)) resultVector[ LATITUDE] -= 2.*M_PI;

        resultVector[LATITUDE]  *= M_180_PI;
        resultVector[LONGITUDE] *= M_180_PI;
        if(resultVector[LONGITUDE] < -180.0) resultVector[LONGITUDE] += 360;
        else if(resultVector[LONGITUDE] > 180.0) resultVector[LONGITUDE] -= 360;

        return resultVector;
}

1	/***************************************************************************
2	* Name: gSatTEME.cpp
3	*
4	* Description: gSatTEME class implementation.
5	* This class abstract all the SGP4 complexity. It uses the
6	* David. A. Vallado code for SGP4 Calculation.
7	*
8	* Reference:
9	* Revisiting Spacetrack Report #3 AIAA 2006-6753
10	* Vallado, David A., Paul Crawford, Richard Hujsak, and T.S.
11	* Kelso, "Revisiting Spacetrack Report #3,"
12	* presented at the AIAA/AAS Astrodynamics Specialist
13	* Conference, Keystone, CO, 2006 August 21-24.
14	* https://celestrak.org/publications/AIAA/2006-6753/
15	***************************************************************************/
16
17	/***************************************************************************
18	* Copyright (C) 2004 by J.L. Canales *
19	* ph03696@homeserver *
20	* *
21	* This program is free software; you can redistribute it and/or modify *
22	* it under the terms of the GNU General Public License as published by *
23	* the Free Software Foundation; either version 2 of the License, or *
24	* (at your option) any later version. *
25	* *
26	* This program is distributed in the hope that it will be useful, *
27	* but WITHOUT ANY WARRANTY; without even the implied warranty of *
28	* MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the *
29	* GNU General Public License for more details. *
30	* *
31	* You should have received a copy of the GNU General Public License *
32	* along with this program; if not, write to the *
33	* Free Software Foundation, Inc., *
34	* 51 Franklin Street, Suite 500, Boston, MA 02110-1335, USA. *
35	***************************************************************************/
36
37	// GKepFile
38	#include "gSatTEME.hpp"
39	//#include <iostream>
40	//#include <iomanip>
41	#include <math.h>
42
43	#include "mathUtils.hpp"
44	#include "sgp4io.h"
45
46	#define CONSTANTS_SET wgs84
47	#define TYPERUN_SET 'c'
48	#define OPSMODE_SET 'i'
49	#define TYPEINPUT_SET 'm'
50
51	#define LATITUDE 0
52	#define LONGITUDE 1
53	#define ALTITUDE 2
54
55	// Constructors
56	gSatTEME::gSatTEME(const char pstrName, char pstrTleLine1, char *pstrTleLine2)	×
57	{
58	double startmfe, stopmfe, deltamin; // dummies
59
60	m_SatName = pstrName;	×
61
62	//set gravitational constants
63	getgravconst(CONSTANTS_SET, tumin, mu, radiusearthkm, xke, j2, j3, j4, j3oj2);	×
64
65	//Parsing TLE_Files and sat variables setting
66	twoline2rv(pstrTleLine1, pstrTleLine2, TYPERUN_SET, TYPEINPUT_SET, OPSMODE_SET, CONSTANTS_SET,	×
67	startmfe, stopmfe, deltamin, satrec);	×
68
69	// call the propagator to get the initial state vector value
70	sgp4(CONSTANTS_SET, satrec, 0.0, m_Position.v, m_Vel.v);	×
71	}	×
72
73	void gSatTEME::setEpoch(gTime ai_time)	×
74	{
75	gTime kepEpoch(satrec.jdsatepoch);	×
76	gTimeSpan tSince = ai_time - kepEpoch;	×
77
78	double dtsince = tSince.getDblSeconds()/KSEC_PER_MIN;	×
79	// call the propagator to get the initial state vector value
80	sgp4(CONSTANTS_SET, satrec, dtsince, m_Position.v, m_Vel.v);	×
81
82	m_SubPoint = computeSubPoint( ai_time);	×
83	}	×
84
85	void gSatTEME::setMinSinceKepEpoch(double ai_minSinceKepEpoch)	×
86	{
87	gTimeSpan tSince( ai_minSinceKepEpoch/KMIN_PER_DAY);	×
88	gTime Epoch(satrec.jdsatepoch);	×
89	Epoch += tSince;	×
90	// call the propagator to get the initial state vector value
91	sgp4(CONSTANTS_SET, satrec, ai_minSinceKepEpoch, m_Position.v, m_Vel.v);	×
92
93	m_SubPoint = computeSubPoint( Epoch);	×
94	}	×
95
96	Vec3d gSatTEME::computeSubPoint(gTime ai_Time)	×
97	{
98	Vec3d resultVector; // (0) Latitude, (1) Longitude, (2) altitude	×
99
NEW 100	const double theta = atan2(m_Position[1], m_Position[0]); // radians	×
101	resultVector[ LONGITUDE] = fmod((theta - ai_Time.toThetaGMST()), 2.*M_PI); //radians	×
102
103
NEW 104	const double r = std::sqrt(Sqr(m_Position[0]) + Sqr(m_Position[1]));	×
NEW 105	const double e2 = __f*(2. - __f);	×
UNCOV 106	resultVector[ LATITUDE] = atan2(m_Position[2],r); /radians/	×
107
108	double phi, c;
109	do
110	{
111	phi = resultVector[ LATITUDE];	×
112	c = 1./std::sqrt(1. - e2*Sqr(sin(phi)));	×
113	resultVector[ LATITUDE] = atan2(m_Position[2] + EARTH_RADIUSce2*sin(phi),r);	×
114	}
115	while(fabs(resultVector[ LATITUDE] - phi) >= 1E-10);	×
116
117	resultVector[ ALTITUDE] = r/cos(resultVector[ LATITUDE]) - EARTH_RADIUSc;/kilometers*/	×
118
119	if(resultVector[ LATITUDE] > (M_PI/2.0)) resultVector[ LATITUDE] -= 2.*M_PI;	×
120
121	resultVector[LATITUDE] *= M_180_PI;	×
122	resultVector[LONGITUDE] *= M_180_PI;	×
123	if(resultVector[LONGITUDE] < -180.0) resultVector[LONGITUDE] += 360;	×
124	else if(resultVector[LONGITUDE] > 180.0) resultVector[LONGITUDE] -= 360;	×
125
126	return resultVector;	×
127	}

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