134 lines
3.2 KiB
C++
134 lines
3.2 KiB
C++
#include "Julian.h"
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#include "Tle.h"
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#include "SGDP4.h"
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#include "Globals.h"
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#include "Observer.h"
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#include "Coord.h"
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#include <list>
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#include <string>
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#include <iomanip>
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void FindSatellite(const Julian& time_start, const Julian& time_end) {
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/*
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* half a second
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*/
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static const double delta = 1.0 / (60.0 * 60.0 * 24.0 * 2.0);
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//while (fabs(time_end - time_start) > delta) {
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//}
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}
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void GeneratePassList(const CoordGeodetic& geo, const SGDP4& model, const Julian& date) {
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Observer obs(geo);
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Eci eci;
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model.FindPosition(eci, date);
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CoordTopographic topo = obs.GetLookAngle(eci);
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/*
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* set start and end date
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*/
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Julian time0 = date;
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Julian time1 = date;
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time1.AddDay(10.0);
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/*
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* step throw period with 1 minute increments
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*/
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for (Julian jd = date; jd <= time1; jd.AddMin(1.0)) {
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}
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}
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int main() {
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Tle tle = Tle("UK-DMC 2 ",
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"1 35683U 09041C 11089.11558659 .00000272 00000-0 54146-4 0 8712",
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"2 35683 98.0762 348.1067 0001434 99.8921 260.2456 14.69414094 89293");
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CoordGeodetic geo(Globals::Deg2Rad(51.360242), Globals::Deg2Rad(0.101473), 0.07);
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SGDP4 sgp4_model;
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sgp4_model.SetTle(tle);
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Julian date;
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GeneratePassList(geo, sgp4_model, date);
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return 0;
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}
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#if 0
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http://olifantasia.com/projects/gnuradio/mdvh/weather_sat/weather_sat_scripts_without_capture_files_2010061701/decoding/poes-weather-hrpt-decoder/hrpt-decoder-1.0.0.2/satellite/predict/
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xmnpda = 1440.0
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/* same formulas, but the one from predict is nicer */
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//sat->footprint = 2.0 * xkmper * acos (xkmper/sat->pos.w);
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sat->footprint = 12756.33 * acos (xkmper / (xkmper+sat->alt));
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age = sat->jul_utc - sat->jul_epoch;
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sat->orbit = (long) floor((sat->tle.xno * xmnpda/twopi +
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age * sat->tle.bstar * ae) * age +
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sat->tle.xmo/twopi) + sat->tle.revnum - 1;
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bool TSat::IsGeostationary(void)
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{
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/* This function returns a 1 if the satellite
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appears to be in a geostationary orbit
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Circular orbit at an altitude of 35 800 km over the equator.
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A satellite moving with the Earth's rotation in a geostationary
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orbit has a period of 23 hours, 56 minutes and 4 seconds.
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*/
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double sma, aalt;
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if(meanmo == 0.0)
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return true;
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sma = 331.25*exp(log(1440.0/meanmo)*(2.0/3.0));
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aalt = sma*(1.0+eccn)-xkmper;
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if(fabs(meanmo-omega_E) < 0.0005 || // allmost same speed as earth
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aalt > 35000) // altitude is over 35000 km
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return true;
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else
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return false;
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}
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// latitude in radians
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bool TSat::DoesRise(double lat)
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{
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/* This function returns a true if the satellite can ever rise
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above the horizon of the ground station.
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*/
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double lin, sma, apogee;
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bool rc = false;
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if(meanmo == 0.0)
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return rc;
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else {
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lin = incl;
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if(lin >= 90.0)
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lin=180.0-lin;
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sma = 331.25*exp(log(1440.0/meanmo)*(2.0/3.0));
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apogee = sma*(1.0+eccn)-xkmper;
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if((acos2(xkmper/(apogee+xkmper))+lin*deg2rad) > fabs(lat))
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rc = true;
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else
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rc = false;
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}
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return rc;
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}
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#endif
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