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KNZ_GeoTrackLab/headers/cal_mod.h
T
KenanZhu111 aba6c009ab SUPPORT: 
1. be able to calculate the sat pos of BDS & Galileo
2. be able to Single postiting by GPS & Galileo
2024-10-14 21:24:01 +08:00

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#ifndef _CAL_MOD_H_
#define _CAL_MOD_H_
#include<stdio.h>
#include<stdlib.h>
#include<Windows.h>
#include<math.h>
#include<time.h>
#include"public.h"
#include"2gpst.h"
#include"rahcal.h"
#include"xyz2blh.h"
#include"degRrad.h"
#include"deg2dms.h"
#include"blh2enu.h"
#include"type2code.h"
#include"select_epo.h"
/* -------------------- GPS Satellite position calculate -------------------- */
pos_ts gps_pos(int sPRN, int best_epoch, double GPSsec,
pnav_body nav_b, pobs_head obs_h, pos_ts pos_t)
{ double T_S = GPSsec - pos_t.delta_t;
double n_0 = sqrt(GM) / pow(nav_b[best_epoch].sqrtA,3);
double n = n_0 + nav_b[best_epoch].deltan;
double tk = T_S - nav_b[best_epoch].TOE;
if (tk > 32400)tk -= 604800;
else if (tk < -32400)tk += 604800;
double Ms = nav_b[best_epoch].M0 + n * tk;
double Es = Ms, E0;
do
{
E0 = Es;
Es = Ms + nav_b[best_epoch].e * sin(Es);
} while (fabs(Es - E0) > 1.0e-10);
double cosfs = (cos(Es) - nav_b[best_epoch].e) / (1 - nav_b[best_epoch].e * cos(Es));
double sinfs = (sqrt(1 - pow(nav_b[best_epoch].e, 2)) * sin(Es)) / (1 - nav_b[best_epoch].e * cos(Es));
double fs = atan2(sinfs, cosfs);
double u0 = fs + nav_b[best_epoch].omega;
double epsilon_u = nav_b[best_epoch].Cus * sin(2 * u0) + nav_b[best_epoch].Cuc * cos(2 * u0);
double epsilon_r = nav_b[best_epoch].Crs * sin(2 * u0) + nav_b[best_epoch].Crc * cos(2 * u0);
double epsilon_i = nav_b[best_epoch].Cis * sin(2 * u0) + nav_b[best_epoch].Cic * cos(2 * u0);
double u = u0 + epsilon_u;
double r = pow(nav_b[best_epoch].sqrtA, 2) * (1 - nav_b[best_epoch].e * cos(Es)) + epsilon_r;
double i = nav_b[best_epoch].i0 + epsilon_i + nav_b[best_epoch].IDOT * tk;
double x = r * cos(u);
double y = r * sin(u);
double l = nav_b[best_epoch].OMEGA + (nav_b[best_epoch].deltaomega - Earth_e) * tk - Earth_e * nav_b[best_epoch].TOE;
double X = x * cos(l) - y * cos(i) * sin(l);
double Y = x * sin(l) + y * cos(i) * cos(l);
double Z = y * sin(i);
pos_t.X = cos(Earth_e * pos_t.delta_t) * X + sin(Earth_e * pos_t.delta_t) * Y;
pos_t.Y = -sin(Earth_e * pos_t.delta_t) * X + cos(Earth_e * pos_t.delta_t) * Y;
pos_t.Z = Z;//Correction of earth rotation
double R = sqrt(pow(pos_t.X - obs_h->apX, 2) + pow(pos_t.Y - obs_h->apY, 2) + pow(pos_t.Z - obs_h->apZ, 2));
pos_t.deltat = pos_t.delta_t;
double rela = 2*sqrt(GM) * nav_b[best_epoch].e * nav_b[best_epoch].sqrtA * sin(Es)/pow(C_V,2);//Relativistic effect
pos_t.delta_clk = nav_b[best_epoch].sa0 + nav_b[best_epoch].sa1 * tk + nav_b[best_epoch].sa2 * pow(tk,2) - rela - nav_b[best_epoch].TGD;
pos_t.delta_t = R / C_V + pos_t.delta_clk;
return pos_t;}
/* -------------------- GAL Satellite position calculate -------------------- */
pos_ts gal_pos(int sPRN, int best_epoch, double GALsec,
pnav_body nav_b, pobs_head obs_h, pos_ts pos_t)
{ double T_S = GALsec - pos_t.delta_t;
double n_0 = sqrt(GM) / pow(nav_b[best_epoch].sqrtA, 3);
double n = n_0 + nav_b[best_epoch].deltan;
double tk = T_S - nav_b[best_epoch].TOE;
if (tk > 32400)tk -= 604800;
else if (tk < -32400)tk += 604800;
double Ms = nav_b[best_epoch].M0 + n * tk;
double Es = Ms, E0;
do
{
E0 = Es;
Es = Ms + nav_b[best_epoch].e * sin(Es);
} while (fabs(Es - E0) > 1.0e-10);
double cosfs = (cos(Es) - nav_b[best_epoch].e) / (1 - nav_b[best_epoch].e * cos(Es));
double sinfs = (sqrt(1 - pow(nav_b[best_epoch].e, 2)) * sin(Es)) / (1 - nav_b[best_epoch].e * cos(Es));
double fs = atan2(sinfs, cosfs);
double u0 = fs + nav_b[best_epoch].omega;
double epsilon_u = nav_b[best_epoch].Cus * sin(2 * u0) + nav_b[best_epoch].Cuc * cos(2 * u0);
double epsilon_r = nav_b[best_epoch].Crs * sin(2 * u0) + nav_b[best_epoch].Crc * cos(2 * u0);
double epsilon_i = nav_b[best_epoch].Cis * sin(2 * u0) + nav_b[best_epoch].Cic * cos(2 * u0);
double u = u0 + epsilon_u;
double r = pow(nav_b[best_epoch].sqrtA, 2) * (1 - nav_b[best_epoch].e * cos(Es)) + epsilon_r;
double i = nav_b[best_epoch].i0 + epsilon_i + nav_b[best_epoch].IDOT * tk;
double x = r * cos(u);
double y = r * sin(u);
double l = nav_b[best_epoch].OMEGA + (nav_b[best_epoch].deltaomega - Earth_e) * tk - Earth_e * nav_b[best_epoch].TOE;
double X = x * cos(l) - y * cos(i) * sin(l);
double Y = x * sin(l) + y * cos(i) * cos(l);
double Z = y * sin(i);
pos_t.X = cos(Earth_e * pos_t.delta_t) * X + sin(Earth_e * pos_t.delta_t) * Y;
pos_t.Y = -sin(Earth_e * pos_t.delta_t) * X + cos(Earth_e * pos_t.delta_t) * Y;
pos_t.Z = Z;//Correction of earth rotation
double R = sqrt(pow(pos_t.X - obs_h->apX, 2) + pow(pos_t.Y - obs_h->apY, 2) + pow(pos_t.Z - obs_h->apZ, 2));
pos_t.deltat = pos_t.delta_t;
double rela = 2 * sqrt(GM) * nav_b[best_epoch].e * nav_b[best_epoch].sqrtA * sin(Es) / pow(C_V, 2);//Relativistic effect
pos_t.delta_clk = nav_b[best_epoch].sa0 + nav_b[best_epoch].sa1 * tk + nav_b[best_epoch].sa2 * pow(tk, 2) - rela - nav_b[best_epoch].BGDa;
pos_t.delta_t = R / C_V + pos_t.delta_clk;
return pos_t;}
/* -------------------- BDS Satellite position calculate -------------------- */
pos_ts bds_pos(int sPRN, int best_epoch, double BDSsec,
pnav_body nav_b, pobs_head obs_h, pos_ts pos_t)
{ double T_S = BDSsec - pos_t.delta_t;
double n_0 = sqrt(GM) / pow(nav_b[best_epoch].sqrtA, 3);
double n = n_0 + nav_b[best_epoch].deltan;
double tk = T_S - nav_b[best_epoch].TOE - 14;
if (tk > 32400)tk -= 604800;
else if (tk < -32400)tk += 604800;
double Ms = nav_b[best_epoch].M0 + n * tk;
double Es = Ms, E0;
do
{
E0 = Es;
Es = Ms + nav_b[best_epoch].e * sin(Es);
} while (fabs(Es - E0) > 1.0e-10);
double cosfs = (cos(Es) - nav_b[best_epoch].e) / (1 - nav_b[best_epoch].e * cos(Es));
double sinfs = (sqrt(1 - pow(nav_b[best_epoch].e, 2)) * sin(Es)) / (1 - nav_b[best_epoch].e * cos(Es));
double fs = atan2(sinfs, cosfs);
double u0 = fs + nav_b[best_epoch].omega;
double epsilon_u = nav_b[best_epoch].Cus * sin(2 * u0) + nav_b[best_epoch].Cuc * cos(2 * u0);
double epsilon_r = nav_b[best_epoch].Crs * sin(2 * u0) + nav_b[best_epoch].Crc * cos(2 * u0);
double epsilon_i = nav_b[best_epoch].Cis * sin(2 * u0) + nav_b[best_epoch].Cic * cos(2 * u0);
double u = u0 + epsilon_u;
double r = pow(nav_b[best_epoch].sqrtA, 2) * (1 - nav_b[best_epoch].e * cos(Es)) + epsilon_r;
double i = nav_b[best_epoch].i0 + epsilon_i + nav_b[best_epoch].IDOT * tk;
double x = r * cos(u);
double y = r * sin(u);
double l, X, Y, Z;
if (sPRN > 5 && sPRN < 59) //BDS IGSO & MEO Satellites
{
l = nav_b[best_epoch].OMEGA + (nav_b[best_epoch].deltaomega - Earth_e) * tk - Earth_e * nav_b[best_epoch].TOE;
X = x * cos(l) - y * cos(i) * sin(l);
Y = x * sin(l) + y * cos(i) * cos(l);
Z = y * sin(i);}
else // BDS GEO Satellites
{
l = nav_b[best_epoch].OMEGA + nav_b[best_epoch].deltaomega * tk - Earth_e * nav_b[best_epoch].TOE;
X = x * cos(l) - y * cos(i) * sin(l);
Y = x * sin(l) + y * cos(i) * cos(l);
Z = y * sin(i);
double f = deg2rad(-5);
double p = Earth_e * tk;
X = X * cos(p) + Y * sin(p) * cos(f) + Z * sin(p) * sin(f);
Y = X * -sin(p) + Y * cos(p) * cos(f) + Z * cos(p) * sin(f);
Z = Y * -sin(f) + Z * cos(f);}
pos_t.X = cos(Earth_e * pos_t.delta_t) * X + sin(Earth_e * pos_t.delta_t) * Y;
pos_t.Y = -sin(Earth_e * pos_t.delta_t) * X + cos(Earth_e * pos_t.delta_t) * Y;
pos_t.Z = Z;//Correction of earth rotation
double rela = 2 * sqrt(GM) * nav_b[best_epoch].e * nav_b[best_epoch].sqrtA * sin(Es) / pow(C_V, 2);//Relativistic effect
pos_t.delta_clk = nav_b[best_epoch].sa0 + nav_b[best_epoch].sa1 * tk + nav_b[best_epoch].sa2 * pow(tk, 2) - rela;
double R = sqrt(pow(pos_t.X - obs_h->apX, 2) + pow(pos_t.Y - obs_h->apY, 2) + pow(pos_t.Z - obs_h->apZ, 2));
pos_t.deltat = pos_t.delta_t;
pos_t.delta_t = R / C_V + pos_t.delta_clk;
return pos_t;}
/* -------------------------------- Satellite position calculate & Output -------------------------------- */
void sat_pos_clac(FILE* result_file,HWND hwndPB,
pnav_body nav_b, pobs_epoch obs_e, pobs_body obs_b,pobs_head obs_h,
int o_epochnum, int satnum, int gnssdecode,
char res_file[MAX_PATH], char obs_file[MAX_PATH], char nav_file[MAX_PATH],
int ionoption, int trooption)
{
PBRANGE range;
SendMessage(hwndPB, PBM_SETRANGE, (WPARAM)FALSE, (LPARAM)(MAKELPARAM(0, 100)));
SendMessage(hwndPB, PBM_GETRANGE, (WPARAM)TRUE, (LPARAM)&range);
time_t gen_time;time(&gen_time);stations station = { 0 };xyz2blh tem2 = { 0 };
tem2 = XYZ2BLH(tem2, obs_h->apX, obs_h->apY, obs_h->apZ);
station.B = tem2.B;
station.L = tem2.L;
station.H = tem2.H;
result_file = fopen(res_file, "w");
fclose(result_file);
result_file = fopen(res_file, "a+");
fprintf(result_file, "@ GENERATE PROGRAM : KNZ_Calculate v1.2.2\n");
fprintf(result_file, "@ GENERATE TYPE : Satellite Position\n");
fprintf(result_file, "@ GENERATE TIME : %s", ctime(&gen_time));
fprintf(result_file, "@ OBS FILE PATH : %s\n", obs_file);
fprintf(result_file, "@ NAV FILE PATH : %s\n", nav_file);
fprintf(result_file, "@ TIME OF FIRST OBS : %4d %02d %02d %02d %02d %07.4f\n"
, obs_h->f_y, obs_h->f_m, obs_h->f_d, obs_h->f_h, obs_h->f_min, obs_h->f_sec);
fprintf(result_file, "@ TIME OF LAST OBS : %4d %02d %02d %02d %02d %07.4f\n"
, obs_h->l_y, obs_h->l_m, obs_h->l_d, obs_h->l_h, obs_h->l_min, obs_h->l_sec);
fprintf(result_file, "@ APPROX POSITION XYZ: %13.04f%13.04f%13.04f\n@ APPROX POSITION BLH: %12.07f %12.07f %12.07f\n"
, obs_h->apX, obs_h->apY, obs_h->apZ
, station.B, station.L, station.H);
if (ionoption == 0) { fprintf(result_file, "@ IONOS OPT : NULL\n"); }
if (ionoption == 1) { fprintf(result_file, "@ IONOS OPT : DEFAULT\n"); }
if (trooption == 0) { fprintf(result_file, "@ TROPO OPT : NULL\n@\n\n"); }
if (trooption == 1) { fprintf(result_file, "@ TROPO OPT : DEFAULT\n@\n\n"); }
fclose(result_file);
//the beginning second of observation
double beginsec = Time2Weeksec(obs_h->f_y, obs_h->f_m, obs_h->f_d, obs_h->f_h, obs_h->f_min, obs_h->f_sec);
//the ending second of observation
double endinsec = Time2Weeksec(obs_h->l_y, obs_h->l_m, obs_h->l_d, obs_h->l_h, obs_h->l_min, obs_h->l_sec);
for (int i = 0; i < o_epochnum; i++)
{ int y = obs_e[i].y;
int m = obs_e[i].m;
int d = obs_e[i].d;
double h = obs_e[i].h;
int min = obs_e[i].min;
double sec = obs_e[i].sec;
xyz2blh tem1 = { 0 };
blh2enu tem3 = { 0 };
rahcal tem4 = { 0 };
deg2dms temb = { 0 };
deg2dms teml = { 0 };
blhs blh = { 0 };
enus enu = { 0 };
rahs rah = { 0 };
pos_ts pos_t = { 0 };
double Weeksec = Time2Weeksec(y, m, d, h, min, sec);
int epochcount = round((Weeksec - beginsec) / obs_h->interval) + 1;
result_file = fopen(res_file, "a+");
fprintf(result_file, "\n>%04d %04d %02d %02d %02d %02d %07.04f"
, epochcount, obs_e[i].y, obs_e[i].m, obs_e[i].d, obs_e[i].h, obs_e[i].min, obs_e[i].sec);
fclose(result_file);
if (gnssdecode % GPS == 0)//Be judged as GPS
{
for (int j = 0; j < obs_e[i].gps_num; j++)
{
int sPRN = obs_e[i].sPRN_GPS[j];
int best_epoch = select_epoch(Weeksec, sPRN, nav_b, satnum, GPS);
if (best_epoch == -1)//when the sPRN is not exist func will return -1
break;
double detat_toc = Weeksec - nav_b[best_epoch].TOE;
//Iterative approximate propagation time
pos_t.delta_t = (obs_b[i].obs_gps[j][Code2Type(C1C, obs_h->obstypenum_gps, obs_h->obscode_gps)] / C_V)
- station.delta_TR + nav_b[best_epoch].sa0 + nav_b[best_epoch].sa1 * detat_toc + nav_b[best_epoch].sa2 * pow(detat_toc, 2);
pos_t.deltat = 0.0;
while (fabs(pos_t.delta_t - pos_t.deltat) > 1.0e-9)
{
pos_t = gps_pos(sPRN, best_epoch, Weeksec, nav_b, obs_h, pos_t);
}
tem1 = XYZ2BLH(tem1, pos_t.X, pos_t.Y, pos_t.Z);
blh.B = rad2deg(tem1.B);
blh.L = rad2deg(tem1.L);
blh.H = tem1.H;
double deltax = pos_t.X - obs_h->apX;
double deltay = pos_t.Y - obs_h->apY;
double deltaz = pos_t.Z - obs_h->apZ;
tem3 = BLH2ENU(tem3, station.B, station.L, deltax, deltay, deltaz);
enu.E = tem3.E;
enu.N = tem3.N;
enu.U = tem3.U;
//Satellite altitude Angle calculation
tem4 = RAHCAL(tem4, enu.E, enu.N, enu.U);
rah.R = tem4.R;
rah.A = rad2deg(tem4.A);
rah.H = rad2deg(tem4.H);
if (blh.H < 0 || rah.H < 10 || nav_b[best_epoch].sHEA != 0)
{
continue;
}
else
{
temb = DEG2DMS(temb, blh.B);
blh.B_d = temb.D;
blh.B_m = temb.M;
blh.B_s = temb.S;
teml = DEG2DMS(teml, blh.L);
blh.L_d = teml.D;
blh.L_m = teml.M;
blh.L_s = teml.S;
result_file = fopen(res_file, "a+");
fprintf(result_file, "\nG %02d| %15.05f %15.05f %15.05f %15.05f %15.05f %15.05f %16.13f"
, sPRN, pos_t.X, pos_t.Y, pos_t.Z
, obs_b[i].obs_gps[j][Code2Type(C1C, obs_h->obstypenum_gps, obs_h->obscode_gps)]
, obs_b[i].obs_gps[j][Code2Type(C2L, obs_h->obstypenum_gps, obs_h->obscode_gps)]
, rah.H, pos_t.delta_clk);//GPS satellite
fclose(result_file);
}
}
}
if (gnssdecode % BDS == 0)//Be judged as BeiDou
{
for (int j = 0; j < obs_e[i].bds_num; j++)
{
int sPRN = obs_e[i].sPRN_BDS[j];
int best_epoch = select_epoch(Weeksec, sPRN, nav_b, satnum, BDS);
if (best_epoch == -1)//when the sPRN is not exist func will return -1
break;
double detat_toc = Weeksec - nav_b[best_epoch].TOE - 14;//BDST - GPST = 14s
//Iterative approximate propagation time
pos_t.delta_t = (obs_b[i].obs_bds[j][Code2Type(C2I, obs_h->obstypenum_bds, obs_h->obscode_bds)] / C_V)
- station.delta_TR + nav_b[best_epoch].sa0 + nav_b[best_epoch].sa1 * detat_toc + nav_b[best_epoch].sa2 * pow(detat_toc, 2);
pos_t.deltat = 0.0;
while (fabs(pos_t.delta_t - pos_t.deltat) > 1.0e-9)
{
pos_t = bds_pos(sPRN, best_epoch, Weeksec, nav_b, obs_h, pos_t);
}
tem1 = XYZ2BLH(tem1, pos_t.X, pos_t.Y, pos_t.Z);
blh.B = rad2deg(tem1.B);
blh.L = rad2deg(tem1.L);
blh.H = tem1.H;
double deltax = pos_t.X - obs_h->apX;
double deltay = pos_t.Y - obs_h->apY;
double deltaz = pos_t.Z - obs_h->apZ;
tem3 = BLH2ENU(tem3, station.B, station.L, deltax, deltay, deltaz);
enu.E = tem3.E;
enu.N = tem3.N;
enu.U = tem3.U;
//Satellite altitude Angle calculation
tem4 = RAHCAL(tem4, enu.E, enu.N, enu.U);
rah.R = tem4.R;
rah.A = rad2deg(tem4.A);
rah.H = rad2deg(tem4.H);
if (blh.H < 0 || rah.H < 10 || nav_b[best_epoch].sHEA != 0){
continue;
}
else{
temb = DEG2DMS(temb, blh.B);
blh.B_d = temb.D;
blh.B_m = temb.M;
blh.B_s = temb.S;
teml = DEG2DMS(teml, blh.L);
blh.L_d = teml.D;
blh.L_m = teml.M;
blh.L_s = teml.S;
result_file = fopen(res_file, "a+");
if (sPRN >= 19) {
fprintf(result_file, "\nCC%02d| %15.05f %15.05f %15.05f %15.05f %15.05f %15.05f %16.13f"
, sPRN, pos_t.X, pos_t.Y, pos_t.Z
, obs_b[i].obs_bds[j][Code2Type(C2I, obs_h->obstypenum_bds, obs_h->obscode_bds)]
, obs_b[i].obs_bds[j][Code2Type(C7I, obs_h->obstypenum_bds, obs_h->obscode_bds)]
, rah.H, pos_t.delta_clk);//BDS-3 satellite
}
else {
fprintf(result_file, "\nCB%02d| %15.05f %15.05f %15.05f %15.05f %15.05f %15.05f %16.13f"
, sPRN, pos_t.X, pos_t.Y, pos_t.Z
, obs_b[i].obs_bds[j][Code2Type(C2I, obs_h->obstypenum_bds, obs_h->obscode_bds)]
, obs_b[i].obs_bds[j][Code2Type(C7I, obs_h->obstypenum_bds, obs_h->obscode_bds)]
, rah.H, pos_t.delta_clk);//BDS-2 satellite
}
fclose(result_file);
}
}
}
if (gnssdecode % GAL == 0)//Be judged as Galileo
{
for (int j = 0; j < obs_e[i].gal_num; j++)
{
int sPRN = obs_e[i].sPRN_GAL[j];
int best_epoch = select_epoch(Weeksec, sPRN, nav_b, satnum, GAL);
if (best_epoch == -1)//when the sPRN is not exist func will return -1
break;
double detat_toc = Weeksec - nav_b[best_epoch].TOE;
//Iterative approximate propagation time
pos_t.delta_t = (obs_b[i].obs_gal[j][Code2Type(C1C, obs_h->obstypenum_gal, obs_h->obscode_gal)] / C_V)
- station.delta_TR + nav_b[best_epoch].sa0 + nav_b[best_epoch].sa1 * detat_toc + nav_b[best_epoch].sa2 * pow(detat_toc, 2);
pos_t.deltat = 0.0;
while (fabs(pos_t.delta_t - pos_t.deltat) > 1.0e-9)
{
pos_t = gal_pos(sPRN, best_epoch, Weeksec, nav_b, obs_h, pos_t);
}
tem1 = XYZ2BLH(tem1, pos_t.X, pos_t.Y, pos_t.Z);
blh.B = rad2deg(tem1.B);
blh.L = rad2deg(tem1.L);
blh.H = tem1.H;
double deltax = pos_t.X - obs_h->apX;
double deltay = pos_t.Y - obs_h->apY;
double deltaz = pos_t.Z - obs_h->apZ;
tem3 = BLH2ENU(tem3, station.B, station.L, deltax, deltay, deltaz);
enu.E = tem3.E;
enu.N = tem3.N;
enu.U = tem3.U;
//Satellite altitude Angle calculation
tem4 = RAHCAL(tem4, enu.E, enu.N, enu.U);
rah.R = tem4.R;
rah.A = rad2deg(tem4.A);
rah.H = rad2deg(tem4.H);
if (blh.H < 0 || rah.H < 10 || nav_b[best_epoch].sHEA != 0)
{ continue;}
else
{
temb = DEG2DMS(temb, blh.B);
blh.B_d = temb.D;
blh.B_m = temb.M;
blh.B_s = temb.S;
teml = DEG2DMS(teml, blh.L);
blh.L_d = teml.D;
blh.L_m = teml.M;
blh.L_s = teml.S;
result_file = fopen(res_file, "a+");
fprintf(result_file, "\nE %02d| %15.05f %15.05f %15.05f %15.05f %15.05f %15.05f %16.13f"
, sPRN, pos_t.X, pos_t.Y, pos_t.Z
, obs_b[i].obs_gal[j][Code2Type(C1C, obs_h->obstypenum_gps, obs_h->obscode_gps)]
, obs_b[i].obs_gal[j][Code2Type(C6C, obs_h->obstypenum_gps, obs_h->obscode_gps)]
, rah.H, pos_t.delta_clk);//Galileo satellite
fclose(result_file);
}
}
}
result_file = fopen(res_file, "a+");
fprintf(result_file, "\n");
fclose(result_file);
SendMessage(hwndPB, PBM_SETPOS, (WPARAM)((int)(i * 100 / o_epochnum)), (LPARAM)0);
}
result_file = fopen(res_file, "a+");
fprintf(result_file, "\nEND");
fclose(result_file);
SendMessage(hwndPB, PBM_SETPOS, (WPARAM)range.iHigh, (LPARAM)0);
}
#endif
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