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/****************************************/
/* driver.c */
/* */
/* origional satellite epherimus driver */
/****************************************/
/***** description
*
* $Id: driver.c,v 1.6 1993/05/12 18:58:51 craig Exp $
*
*/
/***** modification history
*
* translated by f2c (version of 12 March 1993 7:07:21).
*
* $Log: driver.c,v $
* Revision 1.6 1993/05/12 18:58:51 craig
* Changed the orbit calculation section to use the new satreduce
* subroutine and the new do_orbit routine.
*
* Revision 1.5 1993/04/30 18:31:36 craig
* Moved the rdelement () routine to rsat.c.
*
* Revision 1.4 1993/04/28 17:15:14 craig
* changed printed time to UT.
*
* Revision 1.3 1993/04/27 17:09:50 craig
* This version of the driver returns the Topocentric coords and the
* velocity of the satellite along with the Topocentric coords of the
* sun.
*
* Revision 1.2 1993/04/26 19:27:16 craig
* first working version that was integrated with the almanac software.
*
* Revision 1.1 1993/04/02 18:02:04 craig
* Initial revision
*
*
*/
/***** include files *****/
#include <string.h>
#include <math.h>
#include "satellite.h"
#include "satproto.h"
#include "aaproto.h"
/***** global variables *****/
FILE *elefile;
struct star fstar;
struct ELEMENT element;
/* from cnstinit.c */
extern int prtflg;
extern FILE *outfile;
extern double JD;
extern double UT;
extern struct PCONSTANTS pcnsts;
extern struct MCONSTANTS mcnsts;
/************************************************/
/* DRIVER 3 NOV 80 */
/* */
/* WGS-72 PHYSICAL AND GEOPOTENTIAL CONSTANTS */
/* CK2= .5*J2*AE**2 CK4=-.375*J4*AE**4 */
/************************************************/
int main (void)
{
/***** Local variables *****/
int iept, iflag, ideep;
char fname[32];
double delo, delt, del1, temp;
double a1, xnodp, ao;
double oalt, oaz, ora, odec;
double nalt, naz, nra, ndec;
double N, D, x;
double JDTIME, JDSTART, JDSTOP;
/***** initialize constants *****/
prtflg = 0;
cnstinit ();
if (kinit () == -1)
{
fprintf (stderr, "Unable to find a ./.site.ini or a ");
fprintf (stderr, "~/.site.ini site initialization file.\n");
exit (-1);
}
/***** initialize inputs *****/
iept = 2;
strcpy (fname, "ntest.tle");
delt = 5.;
outfile = stdout;
/***** select ephemeris type and output times *****/
getint ("Ephemeris type: [1-5] ", &iept);
getstring ("Element file name: ", fname, 32);
/*** open the element file ***/
elefile = fopen (fname, "r");
if (elefile == NULL)
{
fprintf (stderr, "Error in opening element file: %s\n", fname);
return (-1);
}
/* read the element file */
if (rdelement () != 0)
{
fprintf (stderr, "read element bombed \n");
exit (-1);
}
printf ("Output file name: ( stdout ) ? ");
if (strlen (gets (fname)))
{
/*** open the output file ***/
outfile = fopen (fname, "w");
if (outfile == NULL)
{
fprintf (stderr, "Error in opening output file: %s\n",
fname);
exit (-1);
}
}
/* printf ("\n ephemeris epoch %.7f\n\n", element.epoch); */
printf ("\nEnter start time: \n\n");
JDSTART = getdate ();
JDSTART += gethms ();
update (stdout);
/* printf ("\n Julian day %.7f\n\n", JD); */
printf ("\nEnter end time: \n\n");
JDSTOP = getdate ();
JDSTOP += gethms ();
getdouble ("\nTime increment: (minutes) ", &delt);
ideep = 0;
/***** INPUT CHECK FOR PERIOD VS EPHEMERIS SELECTED *****/
/***** PERIOD GE 225 MINUTES IS DEEP SPACE *****/
a1 = pow (pcnsts.xke / element.xno, mcnsts.tothrd);
temp = pcnsts.ck2 * 1.5 *
(cos (element.xincl) * cos (element.xincl) * 3. - 1.) /
pow (1. - element.eo * element.eo, 1.5);
del1 = temp / (a1 * a1);
ao = a1 * (1. - del1 * (mcnsts.tothrd * .5 + del1 *
(del1 * 134. / 81. + 1.)));
delo = temp / (ao * ao);
xnodp = element.xno / (delo + 1.);
if (mcnsts.twopi / xnodp / pcnsts.xmnpda >= .15625)
{
ideep = 1;
}
iflag = 1;
if (ideep == 1 && (iept == 1 || iept == 2 || iept == 4))
{
fprintf (stderr, "A deep space ephemeris should be used.\n");
exit (-1);
}
if (ideep == 0 && (iept == 3 || iept == 5))
{
fprintf (stderr, "A near earth ephemeris should be used.\n");
exit (-1);
}
/***** do the ephemeris *****/
JDTIME = JDSTART;
while (JDTIME <= JDSTOP)
{
/* update the time */
JD = JDTIME;
do_orbit (iflag, iept);
satreduce (&oalt, &oaz, &ora, &odec);
if (oalt > 0.)
{
/* find the rate at which ra and dec are changing */
JD = JDTIME + delt / pcnsts.xmnpda;
do_orbit (iflag, iept);
satreduce (&nalt, &naz, &nra, &ndec);
JD = JDTIME;
update (outfile);
x = mcnsts.ra2de / delt;
N = nra - ora;
if (N > mcnsts.pi)
{
N -= mcnsts.twopi;
}
else if ( N < -mcnsts.pi)
{
N += mcnsts.twopi;
}
N = x * N;
D = x * (ndec - odec);
fprintf (outfile, "\n");
jtocal (outfile, UT);
fprintf (outfile, "\t%s Position: \n", element.name);
fprintf (outfile,
"\t\tAltitude %.3f deg Azimuth %.3f deg\n", oalt, oaz);
fprintf (outfile, "\t\tR.A.");
hms (outfile, ora);
fprintf (outfile, " Dec.");
dms (outfile, odec);
fprintf (outfile, "\n");
fprintf (outfile,
"\t\tdRA/dt %.2f deg/min, dDec/dt %.2f deg/min\n", N, D );
fprintf (outfile, "\n");
}
JDTIME += delt / pcnsts.xmnpda;
}
if (strlen (fname))
{
/*** close the output file ***/
fclose (outfile);
}
/*** close the element file ***/
fclose (elefile);
exit (0);
}
These are the contents of the former NiCE NeXT User Group NeXTSTEP/OpenStep software archive, currently hosted by Netfuture.ch.