int main(int argc, char* argv[])
{
// Test SGP4
string str1 = "SGP4 Test";
string str2 = "1 88888U 80275.98708465 .00073094 13844-3 66816-4 0 8";
string str3 = "2 88888 72.8435 115.9689 0086731 52.6988 110.5714 16.05824518 105";
cTle tle1(str1, str2, str3);
PrintPosVel(tle1);
printf("\n");
// Test SDP4
str1 = "SDP4 Test";
str2 = "1 11801U 80230.29629788 .01431103 00000-0 14311-1 8";
str3 = "2 11801 46.7916 230.4354 7318036 47.4722 10.4117 2.28537848 6";
cTle tleSDP4(str1, str2, str3);
PrintPosVel(tleSDP4);
printf("\nExample output:\n");
// Example: Define a location on the earth, then determine the look-angle
// to the SDP4 satellite defined above.
// Create an orbit object using the SDP4 TLE object.
cOrbit orbitSDP4(tleSDP4);
// Create an ECI object to hold the location of the satellite
cEci eciSDP4;
// Get the location of the satellite from the Orbit object. The
// earth-centered inertial information is placed into eciSDP4.
// Here we ask for the location of the satellite 90 minutes after
// the TLE epoch.
orbitSDP4.getPosition(90.0, &eciSDP4);
// Now create a site object. Site objects represent a location on the
// surface of the earth. Here we arbitrarily select a point on the
// equator.
cSite siteEquator(0.0, -100.0, 0); // 0.00 N, 100.00 W, 0 km altitude
// Now get the "look angle" from the site to the satellite.
// Note that the ECI object "eciSDP4" contains a time associated
// with the coordinates it contains; this is the time at which
// the look angle is valid.
cCoordTopo topoLook = siteEquator.getLookAngle(eciSDP4);
// Print out the results. Note that the Azimuth and Elevation are
// stored in the cCoordTopo object as radians. Here we convert
// to degrees using rad2deg()
printf("AZ: %.3f EL: %.3f\n",
rad2deg(topoLook.m_Az),
rad2deg(topoLook.m_El));
}
void CSatNote::ListInitial(TLE tle)
{
if(m_satInfo.GetSelCount()!=0)
{
m_satInfo.ResetContent();
}
cTle tle1(tle.name,tle.line1,tle.line2);//采用SDP模型计算
cOrbit orbit(tle1);
///////////////////////////////////////////////////////
string syear= tle.line1.substr(9,2);
char *cyear = (char *)syear.c_str();
int year=atoi(cyear);
if(year>57) //判断具体年份
year+=1900;
else
year+=2000;
//////////////////////////////////////
double p_motion =orbit.mnMotion()*2*PI/(24*3600);//平均角速度
double a =pow(GM/(p_motion*p_motion),1/3.0);//长半径
///////////////////////////////////////////
CString str1,str2,str3,str4,str5,str6,str7,str8,str9;
CString str11,str22,str33,str44,str55,str66,str77,str88,str99;//字符相加不能以常字符开始
str11="发射年份: ";
str22="升交点赤经:";
str33="轨道倾角: ";
str44="长半轴: ";
str55="偏心率: ";
str66="近地点角距:";
str77="平近点角: ";
str88="周期: ";
str99="近地点距离:";
str1.Format("%d",year);
str1=str11+str1;
str2.Format("%.4lf",orbit.RAAN()*180/PI);
str2=str22+str2+"度";
str3.Format("%.4lf",orbit.Inclination()*180/PI);
str3=str33+str3+"度";
str4.Format("%.4lf",a);
str4=str44+str4+"km";
str5.Format("%.7lf",orbit.Eccentricity());
str5=str55+str5;
str6.Format("%.4lf",orbit.ArgPerigee()*180/PI);
str6=str66+str6+"度";
str7.Format("%.4lf",orbit.mnAnomaly()*180/PI);
str7=str77+str7+"度";
str8.Format("%.4lf",orbit.Period()/(60*60*24.0));
str8=str88+str8+"天";
str9.Format("%.4lf",orbit.Perigee());
str9=str99+str9+"km";
m_satInfo.AddString(str1);
m_satInfo.AddString(str2);
m_satInfo.AddString(str3);
m_satInfo.AddString(str4);
m_satInfo.AddString(str5);
m_satInfo.AddString(str6);
m_satInfo.AddString(str7);
m_satInfo.AddString(str8);
m_satInfo.AddString(str9);
}
