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testmat.m
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testmat.m
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% script testmat.m
%
% This script tests the SGP4 propagator.
% Author:
% Jeff Beck
% beckja@alumni.lehigh.edu
% Version Info:
% 1.0 (051019) - Initial version from Vallado C++ version.
% 1.0 (aug 14, 2006) - update for paper
% 2.0 (apr 2, 2007) - update for manual operations
% 3.0 (3 jul, 2008) - update for opsmode operation afspc or improved
% 3.1 (2 dec, 2008) - fix tsince/1440.0 in jd update
% sgp4fix consolidate call to getgravconst in sgp4init
% these are set in sgp4init
% global tumin mu radiusearthkm xke j2 j3 j4 j3oj2
directory = 'd:\codes\library\matlab\';
fprintf(1,'output directory set to: %s, change in testmat.m if needed \n', directory);
% global opsmode
% // ------------------------ implementation --------------------------
% add operation smode for afspc (a) or improved (i)
opsmode= input('input opsmode afspc (a), improved i ','s');
% //typerun = 'c' compare 1 year of full satcat data
% //typerun = 'v' verification run, requires modified elm file with
% //typerun = 'm' maunual operation- either mfe, epoch, or dayof yr
% // start stop and delta times
typerun = input('input type of run c, v, m: ','s');
if (typerun == 'm')
typeinput = input('input mfe, epoch (YMDHMS), or dayofyr approach, m,e,d: ','s');
else
typeinput = 'e';
end;
whichconst = input('input constants 721, (72), 84 ');
rad = 180.0 / pi;
% // ---------------- setup files for operation ------------------
% // input 2-line element set file
infilename = input('input elset filename: ','s');
infile = fopen(infilename, 'r');
if (infile == -1)
fprintf(1,'Failed to open file: %s\n', infilename);
return;
end
if (typerun == 'c')
outfile = fopen(strcat(directory,'tmatall.out'), 'wt');
else
if (typerun == 'v')
outfile = fopen(strcat(directory,'tmatver.out'), 'wt');
else
outfile = fopen(strcat(directory,'tmat.out'), 'wt');
end
end
if (outfile == -1)
fprintf(1,'Failed to open outfile in %s\n', directory);
return;
end
global idebug dbgfile
mu = 398600.8; % km3/s2, WGS072 value
% // ----------------- test simple propagation -------------------
while (~feof(infile))
longstr1 = fgets(infile, 130);
while ( (longstr1(1) == '#') && (feof(infile) == 0) )
longstr1 = fgets(infile, 130);
end
if (feof(infile) == 0)
longstr2 = fgets(infile, 130);
% sgp4fix additional parameters to store from the TLE
satrec.classification = 'U';
satrec.intldesg = ' ';
satrec.ephtype = 0;
satrec.elnum = 0;
satrec.revnum = 0;
if idebug
catno = strtrim(longstr1(3:7));
dbgfile = fopen(strcat('sgp4test.dbg.',catno), 'wt');
fprintf(dbgfile,'this is the debug output\n\n' );
end
% // convert the char string to sgp4 elements
% // includes initialization of sgp4
[startmfe, stopmfe, deltamin, satrec] = twoline2rv( ...
longstr1, longstr2, typerun, typeinput, opsmode, whichconst);
fprintf(outfile, '%d xx\n', satrec.satnum);
fprintf(1,' %d\n', satrec.satnum);
% // call the propagator to get the initial state vector value
[satrec, ro ,vo] = sgp4 (satrec, 0.0);
fprintf(outfile, ' %16.8f %16.8f %16.8f %16.8f %12.9f %12.9f %12.9f\n',...
satrec.t,ro(1),ro(2),ro(3),vo(1),vo(2),vo(3));
% fprintf(outfile, ' %16.7f %16.7f %16.7f %16.7f %12.8f %12.8f %12.8f\n',...
% satrec.t,ro(1),ro(2),ro(3),vo(1),vo(2),vo(3));
% fprintf(1, ' %16.8f %16.8f %16.8f %16.8f %12.9f %12.9f %12.9f\n',...
% satrec.t,ro(1),ro(2),ro(3),vo(1),vo(2),vo(3));
tsince = startmfe;
% // check so the first value isn't written twice
if ( abs(tsince) > 1.0e-8 )
tsince = tsince - deltamin;
end
% // loop to perform the propagation
while ((tsince < stopmfe) && (satrec.error == 0))
tsince = tsince + deltamin;
if(tsince > stopmfe)
tsince = stopmfe;
end
[satrec, ro, vo] = sgp4 (satrec, tsince);
if (satrec.error > 0)
fprintf(1,'# *** error: t:= %f *** code = %3i\n', tsince, satrec.error);
end
if (satrec.error == 0)
if ((typerun ~= 'v') && (typerun ~= 'c'))
jd = satrec.jdsatepoch;
jdfrac = satrec.jdsatepochf + tsince/1440.0;
if jdfrac < 0.0
jd = jd - 1.0;
jdfrac = jdfrac + 1.0;
end
[year,mon,day,hr,minute,sec] = invjday ( jd, jdfrac );
fprintf(outfile,...
' %16.8f %16.8f %16.8f %16.8f %12.9f %12.9f %12.9f %5i%3i%3i %2i:%2i:%9.6f %16.8f%16.8f%16.8%12.9f%12.9f%12.9f \r\n',...
tsince,ro(1),ro(2),ro(3),vo(1),vo(2),vo(3),year,mon,day,hr,minute,sec );
else
jd = satrec.jdsatepoch;
jdfrac = satrec.jdsatepochf + tsince/1440.0;
if jdfrac < 0.0
jd = jd - 1.0;
jdfrac = jdfrac + 1.0;
end
[year,mon,day,hr,minute,sec] = invjday ( jd, jdfrac );
fprintf(outfile, ' %16.8f %16.8f %16.8f %16.8f %12.8f %12.8f %12.8f',...
tsince,ro(1),ro(2),ro(3),vo(1),vo(2),vo(3));
% fprintf(1, ' %16.8f %16.8f %16.8f %16.8f %12.9f %12.9f %12.9f \n',...
% tsince,ro(1),ro(2),ro(3),vo(1),vo(2),vo(3));
[p,a,ecc,incl,node,argp,nu,m,arglat,truelon,lonper ] = rv2coe (ro,vo);
fprintf(outfile, ' %14.6f %8.6f %10.5f %10.5f %10.5f %10.5f %10.5f %5i%3i%3i %2i:%2i:%9.6f \n',...
a, ecc, incl*rad, node*rad, argp*rad, nu*rad, m*rad,year,mon,day,hr,minute,sec );
end
end % if satrec.error == 0
end % while propagating the orbit
if (idebug && (dbgfile ~= -1))
fclose(dbgfile);
end
end % if not eof
end % while through the input file
fclose(infile);
fclose(outfile);
clear all; % clear out the variables to test direct approach
% sgp4fix demonstrate method of running SGP4 directly from orbital element values
%1 08195U 75081A 06176.33215444 .00000099 00000-0 11873-3 0 813
%2 08195 64.1586 279.0717 6877146 264.7651 20.2257 2.00491383225656
deg2rad = pi / 180.0; % 0.0174532925199433
xpdotp = 1440.0 / (2.0 *pi); % 229.1831180523293
whichconst = 72;
opsmode = 'a';
satrec.satnum = 8195;
satrec.jdsatepoch = 2453911.0;
satrec.jdsatepochf = 0.8321544402;
satrec.no_kozai = 2.00491383;
satrec.ecco = 0.6877146;
satrec.inclo = 64.1586;
satrec.nodeo = 279.0717;
satrec.argpo = 264.7651 ;
satrec.mo = 20.2257;
satrec.nddot = 0.00000e0;
satrec.bstar = 0.11873e-3;
satrec.ndot = 0.00000099;
satrec.elnum = 813;
satrec.revnum = 22565;
satrec.classification = 'U';
satrec.intldesg = '75081A';
satrec.ephtype = 0;
% convert units and initialize
satrec.no_kozai = satrec.no_kozai / xpdotp; %* rad/min
satrec.ndot = satrec.ndot / (xpdotp*1440.0); %* ? * minperday
satrec.nddot = satrec.nddot / (xpdotp*1440.0*1440);
satrec.inclo = satrec.inclo * deg2rad;
satrec.nodeo = satrec.nodeo * deg2rad;
satrec.argpo = satrec.argpo * deg2rad;
satrec.mo = satrec.mo * deg2rad;
% set start/stop times for propagation
startmfe = 0.0;
stopmfe = 2880.0;
deltamin = 120.0;
[satrec] = sgp4init( whichconst, opsmode, satrec, satrec.jdsatepoch+satrec.jdsatepochf-2433281.5, satrec.bstar, ...
satrec.ndot, satrec.nddot, satrec.ecco, satrec.argpo, satrec.inclo, satrec.mo, satrec.no_kozai, ...
satrec.nodeo);
tsince = startmfe;
while ((tsince < stopmfe) && (satrec.error == 0))
tsince = tsince + deltamin;
if (tsince > stopmfe)
tsince = stopmfe;
end
[satrec, ro, vo] = sgp4 (satrec, tsince);
jd = satrec.jdsatepoch;
jdfrac = satrec.jdsatepochf + tsince/1440.0;
if jdfrac < 0.0
jd = jd - 1.0;
jdfrac = jdfrac + 1.0;
end
[year,mon,day,hr,minute,sec] = invjday ( jd,jdfrac );
fprintf( 1,' %16.8f %16.8f %16.8f %16.8f %12.9f %12.9f %12.9f \n',...
tsince,ro(1),ro(2),ro(3),vo(1),vo(2),vo(3));
end % while propagating the orbit