Exemplo n.º 1
0
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));

}
Exemplo n.º 2
0
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);
}