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#include<iostream>
#include<fstream>
#include<sstream>
#include<string>
#include<iomanip>
#include<math.h>
#include<cmath>
using namespace std;
int main()
{
// Read in data.dat into a temporary vector
string line;
ifstream myfile;
int index = 0;
float a, temp[220];
myfile.open("data.dat");
if (!myfile)
cout << "Unable to open file!" << endl;
while (!myfile.eof())
{
while (getline(myfile, line))
{
istringstream iss(line);
iss >> skipws >> a;
temp[index] = a;
index++;
}
}
myfile.close();
// Assign values from temporary vector to actual variables
double pi = temp[0];
double c = temp[1];
double R = temp[2];
double s = temp[3];
double u[24][3]; // double indexed u vector
double v[24][3]; // double indexed v vector
double per[24][1]; // periodicity vector
double alt[24][1]; // altitude vector
double ph[24][1]; // phase vector
// Assign the values for the satellites into double indexed vectors u and v
// Read in satellite data using loops
int i = 4;
for (int j = 0; j < 24; j++)
{
for (int k = 0; k < 3; k++)
{
u[j][k] = temp[i];
i++;
}
for (int l = 0; l < 3; l++)
{
v[j][l] = temp[i];
i++;
}
for (int m = 0; m < 1; m++)
{
per[j][m] = temp[i];
i++;
}
for (int n = 0; n < 1; n++)
{
alt[j][n] = temp[i];
i++;
}
for (int p = 0; p < 1; p++)
{
ph[j][p] = temp[i];
i++;
}
}
//Now read in data output by vehicle
string vehicleInput;
ofstream outFile;
outFile.open("mySatellite.log");
int is = 0;
//while (getline(cin, vehicleInput))
//{
double tv, latd, latm, lats, NS, longd, longm, longs, EW, h;
//istringstream vehicleInfo(vehicleInput);
//vehicleInfo >> tv >> latd >> latm >> lats >> NS >> longd >> longm >> longs >> EW >> h;
tv = 12123.0;
latd = 40;
latm = 45;
lats = 55;
NS = 1;
longd = 111;
longm = 50;
longs = 58;
EW = -1;
h = 1372;
double latitude = 2.0 * pi * NS * (latd / 360.0 + latm / (360.0 * 60.0) + lats / (360.0 * 60.0 * 60.0));
double longitude = 2.0 * pi * EW * (longd / 360.0 + longm / (360.0 * 60.0) + longs / (360.0 * 60.0 * 60.0));
double tempx = (R + h)*cos(latitude)*cos(longitude);
double tempy = (R + h)*cos(latitude)*sin(longitude);
double tempz = (R + h)*sin(latitude);;
double alpha = (2.0 * pi*tv) / s;
// Multiply the vector x y z by the rotation matrix
// This is hard-coded in
double x = tempx*cos(alpha) - tempy*sin(alpha);
double y = tempx*sin(alpha) + tempy*cos(alpha);
double z = tempz;
double xv[3] = { x,y,z };
// Go through each satellite and calculate ts and xs
for (int is = 0; is<24; is++)
{
// Compute ts and xs
long double Initialxs[3];
for (int kk = 0; kk<3; kk++)
{
Initialxs[kk] = (R + h)*(u[is][kk] * cos(((2.0 * pi*tv) / (s / 2.0)) + ph[is][0]) + v[is][kk] * sin(((2.0 * pi*tv) / (s / 2.0)) + ph[is][0]));
}
long double told = tv;
long double tnew = tv - (sqrt((Initialxs[0] - xv[0])*(Initialxs[0] - xv[0]) + (Initialxs[1] - xv[1])*(Initialxs[1] - xv[1]) + (Initialxs[2] - xv[2])*(Initialxs[2] - xv[2]))) / c;
long double check = abs(tnew - told);
long double xs[3];
long double dummy;
do {
told = tnew;
for (int ii = 0; ii < 3; ii++)
{
xs[ii] = (R + h)*(u[is][ii] * cos(2 * pi*told / (s / 2) + ph[is][0]) + v[is][ii] * sin(2 * pi*told / (s / 2) + ph[is][0]));
}
dummy = (sqrt(pow((xs[0] - xv[0]), 2.0) + pow((xs[1] - xv[1]), 2.0) + pow((xs[2] - xv[2]), 2.0))) / c;
tnew = tv - (sqrt((xs[0] - xv[0])*(xs[0] - xv[0]) + (xs[1] - xv[1])*(xs[1] - xv[1]) + (xs[2] - xv[2])*(xs[2] - xv[2]))) / c;
check = abs(tnew - told);
cout << check << endl;
} while (check > (0.01 / c));
long double ts = tnew;
// Output all data to a file
outFile << is << " " << setprecision(20) << ts << " " << setprecision(20) << xs[0] << " " << setprecision(20) << xs[1] << " " << setprecision(20) << xs[2] << endl;
// Check to see if the satellite is above the horizon and if it is, output the data
double xvTs = x*xs[0] + y*xs[1] + z*xs[2];
double xvTxv = pow(x, 2) + pow(y, 2) + pow(z, 2);
if (xvTs>xvTxv)
{
// Output data
cout << is << " " << setprecision(20) << ts << " " << setprecision(20) << xs[0] << " " << setprecision(20) << xs[1] << " " << setprecision(20) << xs[2] << endl;
}
}
//}
system("pause");
return 0;
}
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