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17 package org.orekit.propagation.events;
18
19 import org.hipparchus.geometry.euclidean.threed.Vector3D;
20 import org.hipparchus.ode.events.Action;
21 import org.hipparchus.util.FastMath;
22 import org.junit.jupiter.api.AfterEach;
23 import org.junit.jupiter.api.Assertions;
24 import org.junit.jupiter.api.BeforeEach;
25 import org.junit.jupiter.api.Disabled;
26 import org.junit.jupiter.api.Test;
27 import org.orekit.Utils;
28 import org.orekit.bodies.BodyShape;
29 import org.orekit.bodies.GeodeticPoint;
30 import org.orekit.bodies.OneAxisEllipsoid;
31 import org.orekit.frames.Frame;
32 import org.orekit.frames.FramesFactory;
33 import org.orekit.frames.TopocentricFrame;
34 import org.orekit.models.AtmosphericRefractionModel;
35 import org.orekit.models.earth.EarthStandardAtmosphereRefraction;
36 import org.orekit.orbits.EquinoctialOrbit;
37 import org.orekit.orbits.KeplerianOrbit;
38 import org.orekit.orbits.Orbit;
39 import org.orekit.orbits.PositionAngleType;
40 import org.orekit.propagation.Propagator;
41 import org.orekit.propagation.SpacecraftState;
42 import org.orekit.propagation.analytical.EcksteinHechlerPropagator;
43 import org.orekit.propagation.analytical.KeplerianPropagator;
44 import org.orekit.propagation.analytical.tle.TLE;
45 import org.orekit.propagation.analytical.tle.TLEPropagator;
46 import org.orekit.propagation.events.EventsLogger.LoggedEvent;
47 import org.orekit.propagation.events.handlers.ContinueOnEvent;
48 import org.orekit.propagation.events.handlers.EventHandler;
49 import org.orekit.propagation.events.handlers.StopOnIncreasing;
50 import org.orekit.propagation.events.intervals.AdaptableInterval;
51 import org.orekit.propagation.events.intervals.ElevationDetectionAdaptableIntervalFactory;
52 import org.orekit.propagation.sampling.OrekitFixedStepHandler;
53 import org.orekit.time.AbsoluteDate;
54 import org.orekit.time.TimeScale;
55 import org.orekit.time.TimeScalesFactory;
56 import org.orekit.utils.Constants;
57 import org.orekit.utils.ElevationMask;
58 import org.orekit.utils.IERSConventions;
59 import org.orekit.utils.PVCoordinates;
60
61 import java.util.List;
62
63 public class ElevationDetectorTest {
64
65 private double mu;
66 private double ae;
67 private double c20;
68 private double c30;
69 private double c40;
70 private double c50;
71 private double c60;
72
73 @Test
74 public void testAgata() {
75
76 final TimeScale utc = TimeScalesFactory.getUTC();
77 final Vector3D position = new Vector3D(-6142438.668, 3492467.56, -25767.257);
78 final Vector3D velocity = new Vector3D(505.848, 942.781, 7435.922);
79 final AbsoluteDate date = new AbsoluteDate(2003, 9, 16, utc);
80 final Orbit orbit = new EquinoctialOrbit(new PVCoordinates(position, velocity),
81 FramesFactory.getEME2000(), date, mu);
82
83 Propagator propagator =
84 new EcksteinHechlerPropagator(orbit, ae, mu, c20, c30, c40, c50, c60);
85
86
87 double ae = 6378137.0;
88 double f = 1.0 / 298.257223563;
89 Frame itrf = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
90 BodyShape earth = new OneAxisEllipsoid(ae, f, itrf);
91 GeodeticPoint point = new GeodeticPoint(FastMath.toRadians(48.833),
92 FastMath.toRadians(2.333),
93 0.0);
94 TopocentricFrame topo = new TopocentricFrame(earth, point, "Gstation");
95 Checking checking = new Checking(topo);
96 ElevationDetector detector =
97 new ElevationDetector(topo).
98 withConstantElevation(FastMath.toRadians(5.0)).
99 withHandler(checking);
100 Assertions.assertNull(detector.getElevationMask());
101 Assertions.assertNull(detector.getRefractionModel());
102 Assertions.assertSame(topo, detector.getTopocentricFrame());
103 Assertions.assertEquals(FastMath.toRadians(5.0), detector.getMinElevation(), 1.0e-15);
104
105 AbsoluteDate startDate = new AbsoluteDate(2003, 9, 15, 12, 0, 0, utc);
106 propagator.resetInitialState(propagator.propagate(startDate));
107 propagator.addEventDetector(detector);
108 propagator.setStepHandler(10.0, checking);
109 propagator.propagate(startDate.shiftedBy(Constants.JULIAN_DAY));
110
111 }
112
113 private static class Checking implements EventHandler, OrekitFixedStepHandler {
114
115 private final TopocentricFrame topo;
116 private boolean visible;
117
118 public Checking(final TopocentricFrame topo) {
119 this.topo = topo;
120 this.visible = false;
121 }
122
123 public Action eventOccurred(SpacecraftState s, EventDetector detector, boolean increasing) {
124 visible = increasing;
125 return Action.CONTINUE;
126 }
127
128 public void handleStep(SpacecraftState currentState)
129 {
130 BodyShape shape = topo.getParentShape();
131 GeodeticPoint p =
132 shape.transform(currentState.getPosition(),
133 currentState.getFrame(), currentState.getDate());
134 Vector3D subSat = shape.transform(new GeodeticPoint(p.getLatitude(), p.getLongitude(), 0.0));
135 double range = topo.getTrackingCoordinates(subSat, shape.getBodyFrame(), currentState.getDate()).getRange();
136
137 if (visible) {
138 Assertions.assertTrue(range < 2.45e6);
139 } else {
140 Assertions.assertTrue(range > 2.02e6);
141 }
142 }
143
144 }
145
146 @Test
147 public void testEventForMask() {
148
149 final TimeScale utc = TimeScalesFactory.getUTC();
150 final Vector3D position = new Vector3D(-6142438.668, 3492467.56, -25767.257);
151 final Vector3D velocity = new Vector3D(505.848, 942.781, 7435.922);
152 final AbsoluteDate date = new AbsoluteDate(2003, 9, 16, utc);
153 final Orbit orbit = new EquinoctialOrbit(new PVCoordinates(position, velocity),
154 FramesFactory.getEME2000(), date, mu);
155
156 Propagator propagator =
157 new EcksteinHechlerPropagator(orbit, ae, mu, c20, c30, c40, c50, c60);
158
159
160 double ae = 6378137.0;
161 double f = 1.0 / 298.257223563;
162 Frame itrf = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
163 BodyShape earth = new OneAxisEllipsoid(ae, f, itrf);
164 GeodeticPoint point = new GeodeticPoint(FastMath.toRadians(48.833),
165 FastMath.toRadians(2.333),
166 0.0);
167 TopocentricFrame topo = new TopocentricFrame(earth, point, "Gstation");
168 double [][] maskValues = {{ FastMath.toRadians( 0), FastMath.toRadians(5)},
169 { FastMath.toRadians( 30), FastMath.toRadians(4)},
170 { FastMath.toRadians( 60), FastMath.toRadians(3)},
171 { FastMath.toRadians( 90), FastMath.toRadians(2)},
172 { FastMath.toRadians(120), FastMath.toRadians(3)},
173 { FastMath.toRadians(150), FastMath.toRadians(4)},
174 { FastMath.toRadians(180), FastMath.toRadians(5)},
175 { FastMath.toRadians(210), FastMath.toRadians(6)},
176 { FastMath.toRadians(240), FastMath.toRadians(5)},
177 { FastMath.toRadians(270), FastMath.toRadians(4)},
178 { FastMath.toRadians(300), FastMath.toRadians(3)},
179 { FastMath.toRadians(330), FastMath.toRadians(4)}};
180 ElevationMask mask = new ElevationMask(maskValues);
181 ElevationDetector detector = new ElevationDetector(topo)
182 .withElevationMask(mask)
183 .withHandler(new StopOnIncreasing());
184 Assertions.assertSame(mask, detector.getElevationMask());
185
186 AbsoluteDate startDate = new AbsoluteDate(2003, 9, 15, 20, 0, 0, utc);
187 propagator.resetInitialState(propagator.propagate(startDate));
188 propagator.addEventDetector(detector);
189 final SpacecraftState fs = propagator.propagate(startDate.shiftedBy(Constants.JULIAN_DAY));
190 double elevation = topo.getTrackingCoordinates(fs.getPosition(), fs.getFrame(), fs.getDate()).getElevation();
191 Assertions.assertEquals(0.065, elevation, 2.0e-5);
192
193 }
194
195
196 @Test
197 public void testHorizon() {
198
199 final TimeScale utc = TimeScalesFactory.getUTC();
200 final Vector3D position = new Vector3D(-6142438.668, 3492467.56, -25767.257);
201 final Vector3D velocity = new Vector3D(505.848, 942.781, 7435.922);
202 final AbsoluteDate date = new AbsoluteDate(2003, 9, 16, utc);
203 final Orbit orbit = new EquinoctialOrbit(new PVCoordinates(position, velocity),
204 FramesFactory.getEME2000(), date, mu);
205
206 Propagator propagator =
207 new EcksteinHechlerPropagator(orbit, ae, mu, c20, c30, c40, c50, c60);
208
209
210 double ae = 6378137.0;
211 double f = 1.0 / 298.257223563;
212 Frame itrf = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
213 BodyShape earth = new OneAxisEllipsoid(ae, f, itrf);
214 GeodeticPoint point = new GeodeticPoint(FastMath.toRadians(48.833),
215 FastMath.toRadians(2.333),
216 0.0);
217 TopocentricFrame topo = new TopocentricFrame(earth, point, "Gstation");
218 AtmosphericRefractionModel refractionModel = new EarthStandardAtmosphereRefraction();
219 ElevationDetector detector = new ElevationDetector(topo)
220 .withRefraction(refractionModel)
221 .withHandler(new StopOnIncreasing());
222 Assertions.assertSame(refractionModel, detector.getRefractionModel());
223
224 AbsoluteDate startDate = new AbsoluteDate(2003, 9, 15, 20, 0, 0, utc);
225 propagator.resetInitialState(propagator.propagate(startDate));
226 propagator.addEventDetector(detector);
227 final SpacecraftState fs = propagator.propagate(startDate.shiftedBy(Constants.JULIAN_DAY));
228 double elevation = topo.getTrackingCoordinates(fs.getPosition(), fs.getFrame(), fs.getDate()).getElevation();
229 Assertions.assertEquals(FastMath.toRadians(-0.5746255623877098), elevation, 2.0e-5);
230
231 }
232
233
234 @Test
235 public void testIssue136() {
236
237
238 AbsoluteDate initialDate = new AbsoluteDate(2004, 1, 1, 23, 30, 00.000, TimeScalesFactory.getUTC());
239 Frame inertialFrame = FramesFactory.getEME2000();
240 Orbit initialOrbit = new KeplerianOrbit(6828137.005, 7.322641382145889e-10, 1.6967079057368113,
241 0.0, 1.658054062748353,
242 0.0001223149429077902, PositionAngleType.MEAN,
243 inertialFrame, initialDate, Constants.EIGEN5C_EARTH_MU);
244
245
246 Propagator kepler = new EcksteinHechlerPropagator(initialOrbit,
247 Constants.EGM96_EARTH_EQUATORIAL_RADIUS, Constants.EGM96_EARTH_MU,
248 Constants.EGM96_EARTH_C20, 0.0, 0.0, 0.0, 0.0);
249
250
251 double ae = 6378137.0;
252 double f = 1.0 / 298.257223563;
253 Frame itrf = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
254 BodyShape earth = new OneAxisEllipsoid(ae, f, itrf);
255
256
257 final double longitude = FastMath.toRadians(-147.5);
258 final double latitude = FastMath.toRadians(64);
259 final double altitude = 160;
260 final GeodeticPoint station1 = new GeodeticPoint(latitude, longitude, altitude);
261 final TopocentricFrame sta1Frame = new TopocentricFrame(earth, station1, "station1");
262
263
264 final double maxcheck = 120.0;
265 final double elevation = FastMath.toRadians(5.);
266 final double threshold = 10.0;
267 final EventDetector rawEvent = new ElevationDetector(maxcheck, threshold, sta1Frame)
268 .withConstantElevation(elevation)
269 .withHandler(new ContinueOnEvent());
270 final EventsLogger logger = new EventsLogger();
271 kepler.addEventDetector(logger.monitorDetector(rawEvent));
272
273
274 kepler.propagate(initialDate.shiftedBy(60*60*24.0*40));
275 int countIncreasing = 0;
276 int countDecreasing = 0;
277 for (LoggedEvent le : logger.getLoggedEvents()) {
278 if (le.isIncreasing()) {
279 ++countIncreasing;
280 } else {
281 ++countDecreasing;
282 }
283 }
284 Assertions.assertEquals(314, countIncreasing);
285 Assertions.assertEquals(314, countDecreasing);
286
287 }
288
289 @Test
290 public void testIssue110() {
291
292
293 final Frame eme2000Frame = FramesFactory.getEME2000();
294 final AbsoluteDate initDate = AbsoluteDate.J2000_EPOCH;
295 final double a = 7000000.0;
296 final Orbit initialOrbit = new KeplerianOrbit(a, 0.0,
297 FastMath.PI / 2.2, 0.0, FastMath.PI / 2., 0.0,
298 PositionAngleType.TRUE, eme2000Frame, initDate,
299 Constants.EGM96_EARTH_MU);
300 final KeplerianPropagator kProp = new KeplerianPropagator(initialOrbit);
301
302
303 final OneAxisEllipsoid earthShape = new OneAxisEllipsoid(
304 Constants.WGS84_EARTH_EQUATORIAL_RADIUS,
305 Constants.WGS84_EARTH_FLATTENING, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
306
307 final GeodeticPoint stat = new GeodeticPoint(FastMath.toRadians(35.),
308 FastMath.toRadians(149.8), 0.);
309 final TopocentricFrame station = new TopocentricFrame(earthShape, stat,
310 "GSTATION");
311
312
313
314 final double maxCheck = 600.;
315 final double threshold = 1.0e-3;
316 final EventDetector rawEvent = new ElevationDetector(maxCheck, threshold, station)
317 .withConstantElevation(FastMath.toRadians(5.0))
318 .withHandler(new ContinueOnEvent());
319 final EventsLogger logger = new EventsLogger();
320 kProp.addEventDetector(logger.monitorDetector(rawEvent));
321
322
323 final AbsoluteDate finalDate = initDate.shiftedBy(30 * 60.);
324
325 kProp.propagate(finalDate);
326 Assertions.assertEquals(2, logger.getLoggedEvents().size());
327 Assertions.assertTrue(logger.getLoggedEvents().get(0).isIncreasing());
328 Assertions.assertEquals(478.945, logger.getLoggedEvents().get(0).getState().getDate().durationFrom(initDate), 1.0e-3);
329 Assertions.assertFalse(logger.getLoggedEvents().get(1).isIncreasing());
330 Assertions.assertEquals(665.721, logger.getLoggedEvents().get(1).getState().getDate().durationFrom(initDate), 1.0e-3);
331
332 }
333
334 @Disabled
335 @Test
336 public void testPresTemp() {
337
338 final TimeScale utc = TimeScalesFactory.getUTC();
339 final Vector3D position = new Vector3D(-6142438.668, 3492467.56, -25767.257);
340 final Vector3D velocity = new Vector3D(505.848, 942.781, 7435.922);
341 final AbsoluteDate date = new AbsoluteDate(2003, 9, 16, utc);
342 final Orbit orbit = new EquinoctialOrbit(new PVCoordinates(position, velocity),
343 FramesFactory.getEME2000(), date, mu);
344
345 Propagator propagator =
346 new EcksteinHechlerPropagator(orbit, ae, mu, c20, c30, c40, c50, c60);
347
348
349 double ae = 6378137.0;
350 double f = 1.0 / 298.257223563;
351 Frame itrf = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
352 BodyShape earth = new OneAxisEllipsoid(ae, f, itrf);
353 GeodeticPoint point = new GeodeticPoint(FastMath.toRadians(48.833),
354 FastMath.toRadians(2.333),
355 0.0);
356 TopocentricFrame topo = new TopocentricFrame(earth, point, "Gstation");
357 EarthStandardAtmosphereRefraction refractionModel = new EarthStandardAtmosphereRefraction();
358 ElevationDetector detector = new ElevationDetector(topo)
359 .withRefraction(refractionModel)
360 .withHandler(new StopOnIncreasing());
361 refractionModel.setPressure(101325);
362 refractionModel.setTemperature(290);
363
364 AbsoluteDate startDate = new AbsoluteDate(2003, 9, 15, 20, 0, 0, utc);
365 propagator.resetInitialState(propagator.propagate(startDate));
366 propagator.addEventDetector(detector);
367 final SpacecraftState fs = propagator.propagate(startDate.shiftedBy(Constants.JULIAN_DAY));
368 double elevation = topo.getTrackingCoordinates(fs.getPosition(), fs.getFrame(), fs.getDate()).getElevation();
369 Assertions.assertEquals(FastMath.toRadians(1.7026104902251749), elevation, 2.0e-5);
370
371 }
372
373 @Test
374 public void testIssue203() {
375
376
377 AbsoluteDate initialDate = new AbsoluteDate("2012-01-26T07:00:00.000", TimeScalesFactory.getUTC());
378
379 Frame inertialFrame = FramesFactory.getEME2000();
380
381 Orbit initialOrbit = new KeplerianOrbit(6828137.5, 7.322641060181212E-8, 1.7082667003713938, 0.0, 1.658054062748353, 1.2231496082116026E-4, PositionAngleType.TRUE , inertialFrame, initialDate, Constants.WGS84_EARTH_MU);
382
383 Propagator propagator =
384 new EcksteinHechlerPropagator(initialOrbit,
385 Constants.EGM96_EARTH_EQUATORIAL_RADIUS,
386 Constants.EGM96_EARTH_MU,
387 Constants.EGM96_EARTH_C20,
388 Constants.EGM96_EARTH_C30,
389 Constants.EGM96_EARTH_C40,
390 Constants.EGM96_EARTH_C50,
391 Constants.EGM96_EARTH_C60);
392
393
394 Frame earthFrame = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
395 BodyShape earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS,
396 Constants.WGS84_EARTH_FLATTENING,
397 earthFrame);
398
399
400 final double longitude = FastMath.toRadians(21.0);
401 final double latitude = FastMath.toRadians(67.9);
402 final double altitude = 300.0;
403
404 final GeodeticPoint station1 = new GeodeticPoint(latitude, longitude, altitude);
405 final TopocentricFrame sta1Frame = new TopocentricFrame(earth, station1, "station1");
406
407 double [][] maskValues = {
408 {-0.017453292519943098, 0.006981317007977318}, {0.0, 0.006981317007977318},
409 {0.017453292519943295, 0.006981317007977318}, {0.03490658503988659, 0.010471975511965976},
410 {0.05235987755982989, 0.012217304763960306}, {0.06981317007977318, 0.010471975511965976},
411 {0.08726646259971647, 0.010471975511965976}, {0.10471975511965978, 0.012217304763960306},
412 {0.12217304763960307, 0.010471975511965976}, {0.13962634015954636, 0.008726646259971648},
413 {0.15707963267948966, 0.008726646259971648}, {0.17453292519943295, 0.006981317007977318},
414 {0.19198621771937624, 0.006981317007977318}, {0.20943951023931956, 0.006981317007977318},
415 {0.22689280275926285, 0.005235987755982988}, {0.24434609527920614, 0.005235987755982988},
416 {0.2617993877991494, 0.003490658503988659}, {0.2792526803190927, 0.003490658503988659},
417 {0.29670597283903605, 0.0017453292519943296}, {0.3141592653589793, 0.003490658503988659},
418 {0.33161255787892263, 0.0017453292519943296}, {0.3490658503988659, 0.0},
419 {0.3665191429188092, 0.012217304763960306}, {0.3839724354387525, 0.012217304763960306},
420 {0.4014257279586958, 0.0}, {0.4188790204786391, 0.010471975511965976},
421 {0.4363323129985824, 0.029670597283903602}, {0.4537856055185257, 0.029670597283903602},
422 {0.47123889803846897, 0.017453292519943295}, {0.4886921905584123, 0.0},
423 {0.5061454830783556, 0.029670597283903602}, {0.5235987755982988, 0.015707963267948967},
424 {0.5410520681182421, 0.005235987755982988}, {0.5585053606381855, 0.024434609527920613},
425 {0.5759586531581288, 0.041887902047863905}, {0.5934119456780721, 0.06283185307179587},
426 {0.6108652381980153, 0.05235987755982989}, {0.6283185307179586, 0.05759586531581287},
427 {0.6457718232379019, 0.061086523819801536}, {0.6632251157578453, 0.05759586531581287},
428 {0.6806784082777885, 0.04363323129985824}, {0.6981317007977318, 0.059341194567807204},
429 {0.7155849933176751, 0.07504915783575616}, {0.7330382858376184, 0.08726646259971647},
430 {0.7504915783575618, 0.08726646259971647}, {0.767944870877505, 0.07330382858376185},
431 {0.7853981633974483, 0.07853981633974483}, {0.8028514559173916, 0.09075712110370514},
432 {0.8203047484373349, 0.0942477796076938}, {0.8377580409572782, 0.11519173063162574},
433 {0.8552113334772214, 0.11519173063162574}, {0.8726646259971648, 0.12566370614359174},
434 {0.8901179185171081, 0.12566370614359174}, {0.9075712110370514, 0.10122909661567112},
435 {0.9250245035569946, 0.11868238913561441}, {0.9424777960769379, 0.11868238913561441},
436 {0.9599310885968813, 0.11868238913561441}, {0.9773843811168246, 0.10821041362364843},
437 {0.9948376736367679, 0.12217304763960307}, {1.0122909661567112, 0.12740903539558607},
438 {1.0297442586766545, 0.11344640137963143}, {1.0471975511965976, 0.11344640137963143},
439 {1.064650843716541, 0.06632251157578452}, {1.0821041362364843, 0.12391837689159739},
440 {1.0995574287564276, 0.12391837689159739}, {1.117010721276371, 0.10995574287564276},
441 {1.1344640137963142, 0.09250245035569947}, {1.1519173063162575, 0.12740903539558607},
442 {1.1693705988362009, 0.1308996938995747}, {1.1868238913561442, 0.1117010721276371},
443 {1.2042771838760873, 0.1117010721276371}, {1.2217304763960306, 0.0942477796076938},
444 {1.239183768915974, 0.10821041362364843}, {1.2566370614359172, 0.09599310885968812},
445 {1.2740903539558606, 0.09948376736367678}, {1.2915436464758039, 0.09773843811168245},
446 {1.3089969389957472, 0.08726646259971647}, {1.3264502315156905, 0.09250245035569947},
447 {1.3439035240356338, 0.10122909661567112}, {1.361356816555577, 0.09250245035569947},
448 {1.3788101090755203, 0.08552113334772216}, {1.3962634015954636, 0.08726646259971647},
449 {1.413716694115407, 0.08028514559173916}, {1.4311699866353502, 0.05759586531581287},
450 {1.4486232791552935, 0.054105206811824215}, {1.4660765716752369, 0.06632251157578452},
451 {1.4835298641951802, 0.08028514559173916}, {1.5009831567151235, 0.061086523819801536},
452 {1.5184364492350666, 0.048869219055841226}, {1.53588974175501, 0.0715584993317675},
453 {1.5533430342749532, 0.07504915783575616}, {1.5707963267948966, 0.05235987755982989},
454 {1.5882496193148399, 0.05235987755982989}, {1.6057029118347832, 0.06981317007977318},
455 {1.6231562043547265, 0.054105206811824215}, {1.6406094968746698, 0.0645771823237902},
456 {1.6580627893946132, 0.059341194567807204}, {1.6755160819145565, 0.029670597283903602},
457 {1.6929693744344996, 0.03316125578789226}, {1.710422666954443, 0.059341194567807204},
458 {1.7278759594743862, 0.0645771823237902}, {1.7453292519943295, 0.06283185307179587},
459 {1.7627825445142729, 0.061086523819801536}, {1.7802358370342162, 0.06806784082777885},
460 {1.7976891295541595, 0.06632251157578452}, {1.8151424220741028, 0.059341194567807204},
461 {1.8325957145940461, 0.05759586531581287}, {1.8500490071139892, 0.05759586531581287},
462 {1.8675022996339325, 0.0471238898038469}, {1.8849555921538759, 0.059341194567807204},
463 {1.9024088846738192, 0.05061454830783556}, {1.9198621771937625, 0.05061454830783556},
464 {1.9373154697137058, 0.024434609527920613}, {1.9547687622336491, 0.027925268031909273},
465 {1.9722220547535925, 0.041887902047863905}, {1.9896753472735358, 0.024434609527920613},
466 {2.007128639793479, 0.029670597283903602}, {2.0245819323134224, 0.03316125578789226},
467 {2.0420352248333655, 0.03665191429188092}, {2.059488517353309, 0.04537856055185257},
468 {2.076941809873252, 0.041887902047863905}, {2.0943951023931953, 0.05759586531581287},
469 {2.111848394913139, 0.06283185307179587}, {2.129301687433082, 0.06806784082777885},
470 {2.1467549799530254, 0.05759586531581287}, {2.1642082724729685, 0.059341194567807204},
471 {2.181661564992912, 0.06806784082777885}, {2.199114857512855, 0.06283185307179587},
472 {2.2165681500327987, 0.054105206811824215}, {2.234021442552742, 0.05235987755982989},
473 {2.251474735072685, 0.059341194567807204}, {2.2689280275926285, 0.07330382858376185},
474 {2.2863813201125716, 0.06283185307179587}, {2.303834612632515, 0.05235987755982989},
475 {2.321287905152458, 0.061086523819801536}, {2.3387411976724017, 0.048869219055841226},
476 {2.356194490192345, 0.06632251157578452}, {2.3736477827122884, 0.05061454830783556},
477 {2.3911010752322315, 0.07679448708775051}, {2.4085543677521746, 0.06283185307179587},
478 {2.426007660272118, 0.05585053606381855}, {2.443460952792061, 0.061086523819801536},
479 {2.4609142453120048, 0.06806784082777885}, {2.478367537831948, 0.0645771823237902},
480 {2.4958208303518914, 0.06283185307179587}, {2.5132741228718345, 0.06283185307179587},
481 {2.530727415391778, 0.0645771823237902}, {2.548180707911721, 0.07504915783575616},
482 {2.5656340004316642, 0.0715584993317675}, {2.5830872929516078, 0.0645771823237902},
483 {2.600540585471551, 0.059341194567807204}, {2.6179938779914944, 0.06283185307179587},
484 {2.6354471705114375, 0.06632251157578452}, {2.652900463031381, 0.06283185307179587},
485 {2.670353755551324, 0.06632251157578452}, {2.6878070480712677, 0.0645771823237902}};
486 ElevationMask mask = new ElevationMask(maskValues);
487
488
489 final AbsoluteDate start = new AbsoluteDate("2012-02-10T22:00:00.000", TimeScalesFactory.getUTC());
490 final AbsoluteDate end = initialDate.shiftedBy(1000 * Constants.JULIAN_DAY);
491
492
493 final double maxcheck = 60.0;
494 final double threshold = 2.0;
495 final EventDetector sta1Visi =
496 new ElevationDetector(maxcheck, threshold, sta1Frame).
497 withElevationMask(mask).
498 withHandler(new EventHandler() {
499
500 private int count = 6;
501 @Override
502 public Action eventOccurred(SpacecraftState s, EventDetector detector, boolean increasing) {
503 return (--count > 0) ? Action.CONTINUE : Action.STOP;
504 }
505
506 });
507
508
509 EventsLogger logger = new EventsLogger();
510 propagator.addEventDetector(logger.monitorDetector(sta1Visi));
511
512
513 propagator.propagate(start, end);
514
515 List<LoggedEvent> events = logger.getLoggedEvents();
516 Assertions.assertEquals(6, events.size());
517
518
519
520 AbsoluteDate d2 = events.get(2).getDate();
521 AbsoluteDate d3 = events.get(3).getDate();
522 Assertions.assertTrue(d3.durationFrom(d2) > 0.3 * threshold);
523 Assertions.assertTrue(d3.durationFrom(d2) < threshold);
524
525 }
526
527 @Test
528 public void testIssue1407() {
529 final TLE tle = new TLE("1 25544U 98067A 03042.38687590 .00035128 00000-0 41387-3 0 9990",
530 "2 25544 051.6337 292.0267 0005644 135.6869 224.5096 15.60691825241426");
531 final OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS,
532 Constants.WGS84_EARTH_FLATTENING,
533 FramesFactory.getITRF(IERSConventions.IERS_2010, true));
534 final TopocentricFrame topo = new TopocentricFrame(earth,
535 new GeodeticPoint(FastMath.toRadians(38.832772),
536 FastMath.toRadians(-104.74755),
537 1839.0),
538 "Colorado Springs");
539 final AdaptableInterval maxCheck = ElevationDetectionAdaptableIntervalFactory.
540 getAdaptableInterval(topo,
541 ElevationDetectionAdaptableIntervalFactory.DEFAULT_ELEVATION_SWITCH_INF,
542 ElevationDetectionAdaptableIntervalFactory.DEFAULT_ELEVATION_SWITCH_SUP,
543 60.0);
544 final ElevationDetector detector = new ElevationDetector(maxCheck, 1.0e-3, topo).
545 withConstantElevation(FastMath.toRadians(10.0)).
546 withHandler(new ContinueOnEvent());
547
548 final EventsLogger logger = new EventsLogger();
549 final Propagator propagator = TLEPropagator.selectExtrapolator(tle);
550 propagator.addEventDetector(logger.monitorDetector(detector));
551 propagator.propagate(tle.getDate().shiftedBy(Constants.JULIAN_DAY));
552 Assertions.assertEquals(8, logger.getLoggedEvents().size());
553
554 }
555
556 @BeforeEach
557 public void setUp() {
558 Utils.setDataRoot("regular-data");
559 mu = 3.9860047e14;
560 ae = 6.378137e6;
561 c20 = -1.08263e-3;
562 c30 = 2.54e-6;
563 c40 = 1.62e-6;
564 c50 = 2.3e-7;
565 c60 = -5.5e-7;
566 }
567
568 @AfterEach
569 public void tearDown() {
570 mu = Double.NaN;
571 ae = Double.NaN;
572 c20 = Double.NaN;
573 c30 = Double.NaN;
574 c40 = Double.NaN;
575 c50 = Double.NaN;
576 c60 = Double.NaN;
577 }
578
579 }
580