Changes to the measurement generation script

src/main/java/fr/cs/examples/estimation/MeasurementsGeneration.java

@@ -111,6 +111,16 @@ public class MeasurementsGeneration {
 
             DataProvidersManager manager = DataProvidersManager.getInstance();
             manager.addProvider(new DirectoryCrawler(orekitData));
+            /*
+            // beware TLE model is not suitable for propagation more than a few days
+            // we have to select the correct TLE for the dates we will generate measurements
+            final TLE tle20190611 = new TLE("1 42778U 17036P   19162.69113096  .00000749  00000-0  35781-4 0  9997",
+                    "2 42778  97.3549 220.5119 0010756 245.3704 114.6412 15.21997549109170");
+            final TLE tle20190612 = new TLE("1 42778U 17036P   19163.74305518  .00000728  00000-0  34875-4 0  9996",
+                    "2 42778  97.3548 221.5408 0010807 241.2329 118.7822 15.21999132109334");
+            final TLE tle20190617 = new TLE("1 42778U 17036P   19168.73968312  .00000624  00000-0  30313-4 0  9995",
+                    "2 42778  97.3544 226.4276 0011195 221.3881 138.6508 15.22005879110094");
+            */
 
 
 
@@ -137,6 +147,7 @@ public class MeasurementsGeneration {
             final double       duration     = Constants.JULIAN_DAY;  // Sets the duration to be the length of a Julian day
 
 
+            //*
             // atmosphere model for drag
             MarshallSolarActivityFutureEstimation msafe =
                     new MarshallSolarActivityFutureEstimation(MarshallSolarActivityFutureEstimation.DEFAULT_SUPPORTED_NAMES,
@@ -144,8 +155,6 @@ public class MeasurementsGeneration {
             manager.feed(msafe.getSupportedNames(), msafe);
             Atmosphere atmosphere = new DTM2000(msafe, CelestialBodyFactory.getSun(), earth);
 
-
-
             // this orbit is a dummy one, close to the first results from orbit determination from Max Valier satellite
             final NormalizedSphericalHarmonicsProvider gravity = GravityFieldFactory.getNormalizedProvider(12, 12);
             final AbsoluteDate             tOrb      = new AbsoluteDate("2019-06-11T16:35:29.149", utc);
@@ -169,7 +178,7 @@ public class MeasurementsGeneration {
             propagator.addForceModel(new ThirdBodyAttraction(CelestialBodyFactory.getMoon()));
             propagator.addForceModel(new DragForce(atmosphere, new IsotropicDrag(cd, area)));
 
-
+            //*/
 
             // set up some correction models
             // coefficients files for Vienna Model 3 can be found at
@@ -186,6 +195,7 @@ public class MeasurementsGeneration {
 
             // set up measurements generation, with realistic models
             final Generator            generator    = new Generator();
+            //final ObservableSatellite  os           = generator.addPropagator(TLEPropagator.selectExtrapolator(tle20190611));
             final ObservableSatellite  os           = generator.addPropagator(propagator);
 
             /*
@@ -222,7 +232,6 @@ public class MeasurementsGeneration {
             generator.addScheduler(scheduler);
 
             // generate measurements
-            System.out.println("Line 223");
             final SortedSet<ObservedMeasurement<?>> measurements = generator.generate(t0, t0.shiftedBy(duration));
             System.out.println("generated " + measurements.size() + " measurements");
             System.out.println("first measurement at " + measurements.first().getDate());