Commit 17ff9647 authored by Luc Maisonobe's avatar Luc Maisonobe

Added test for inter satellites range measurements creation.

parent afc3a0b2
/* Copyright 2002-2018 CS Systèmes d'Information
* Licensed to CS Systèmes d'Information (CS) under one or more
* contributor license agreements. See the NOTICE file distributed with
* this work for additional information regarding copyright ownership.
* CS licenses this file to You under the Apache License, Version 2.0
* (the "License"); you may not use this file except in compliance with
* the License. You may obtain a copy of the License at
* Unless required by applicable law or agreed to in writing, software
* distributed under the License is distributed on an "AS IS" BASIS,
* See the License for the specific language governing permissions and
* limitations under the License.
package org.orekit.estimation.measurements.generation;
import java.util.SortedSet;
import org.hipparchus.linear.MatrixUtils;
import org.hipparchus.linear.RealMatrix;
import org.hipparchus.random.CorrelatedRandomVectorGenerator;
import org.hipparchus.random.GaussianRandomGenerator;
import org.hipparchus.random.RandomGenerator;
import org.hipparchus.random.Well19937a;
import org.hipparchus.util.FastMath;
import org.junit.Assert;
import org.junit.Before;
import org.junit.Test;
import org.orekit.estimation.Context;
import org.orekit.estimation.EstimationTestUtils;
import org.orekit.estimation.Force;
import org.orekit.estimation.measurements.InterSatellitesRange;
import org.orekit.estimation.measurements.ObservedMeasurement;
import org.orekit.estimation.measurements.modifiers.Bias;
import org.orekit.orbits.KeplerianOrbit;
import org.orekit.orbits.Orbit;
import org.orekit.orbits.OrbitType;
import org.orekit.orbits.PositionAngle;
import org.orekit.propagation.Propagator;
import org.orekit.propagation.SpacecraftState;
import org.orekit.propagation.analytical.KeplerianPropagator;
import org.orekit.propagation.conversion.NumericalPropagatorBuilder;
import org.orekit.time.AbsoluteDate;
import org.orekit.time.FixedStepSelector;
import org.orekit.time.TimeScalesFactory;
import org.orekit.utils.PVCoordinates;
public class InterSatellitesRangeBuilderTest {
private static final double SIGMA = 0.5;
private static final double BIAS = -0.01;
private MeasurementBuilder<InterSatellitesRange> getBuilder(final RandomGenerator random,
final int satellite1Index, final int satellite2Index) {
final RealMatrix covariance = MatrixUtils.createRealDiagonalMatrix(new double[] { SIGMA * SIGMA });
MeasurementBuilder<InterSatellitesRange> isrb =
new InterSatellitesRangeBuilder(random == null ? null : new CorrelatedRandomVectorGenerator(covariance,
new GaussianRandomGenerator(random)),
satellite1Index, satellite2Index,
true, SIGMA, 1.0);
isrb.addModifier(new Bias<>(new String[] { "bias" },
new double[] { BIAS },
new double[] { 1.0 },
new double[] { Double.NEGATIVE_INFINITY },
new double[] { Double.POSITIVE_INFINITY }));
return isrb;
public void testForward() {
doTest(0xc82a56322345dc25l, 0.0, 1.2, 2.8 * SIGMA);
public void testBackward() {
doTest(0x95c10149c4891232l, 0.0, -1.0, 2.6 * SIGMA);
private Propagator buildPropagator() {
return EstimationTestUtils.createPropagator(context.initialOrbit, propagatorBuilder);
private void doTest(long seed, double startPeriod, double endPeriod, double tolerance) {
Generator generator = new Generator();
int satellite1Index = generator.addPropagator(buildPropagator());
final Orbit o1 = context.initialOrbit;
// for the second satellite, we simply reverse velocity
final Orbit o2 = new KeplerianOrbit(new PVCoordinates(o1.getPVCoordinates().getPosition(),
o1.getFrame(), o1.getDate(), o1.getMu());
int satellite2Index = generator.addPropagator(new KeplerianPropagator(o2));
final double step = 60.0;
// beware that in order to avoid deadlocks, the slave PV coordinates provider
// in InterSatDirectViewDetector must be *different* from the second propagator
// added to generator above! The reason is the event detector will be bound
// to the first propagator, so it cannot also refer to the second one at the same time
// this is the reason why we create a *new* KeplerianPropagator below
generator.addScheduler(new EventBasedScheduler<>(getBuilder(new Well19937a(seed), satellite1Index, satellite2Index),
new FixedStepSelector(step, TimeScalesFactory.getUTC()),
new InterSatDirectViewDetector(, new KeplerianPropagator(o2)),
final double period = o1.getKeplerianPeriod();
AbsoluteDate t0 = o1.getDate().shiftedBy(startPeriod * period);
AbsoluteDate t1 = o1.getDate().shiftedBy(endPeriod * period);
SortedSet<ObservedMeasurement<?>> measurements = generator.generate(t0, t1);
// and yet another set of propagators for reference
Propagator propagator1 = buildPropagator();
Propagator propagator2 = new KeplerianPropagator(o2);
double maxError = 0;
AbsoluteDate previous = null;
AbsoluteDate tInf = t0.compareTo(t1) < 0 ? t0 : t1;
AbsoluteDate tSup = t0.compareTo(t1) < 0 ? t1 : t0;
for (ObservedMeasurement<?> measurement : measurements) {
AbsoluteDate date = measurement.getDate();
double[] m = measurement.getObservedValue();
Assert.assertTrue(date.compareTo(tInf) >= 0);
Assert.assertTrue(date.compareTo(tSup) <= 0);
if (previous != null) {
// measurements are always chronological, even with backward propagation,
// due to the SortedSet (which is intended for combining several
// measurements types with different builders and schedulers)
Assert.assertTrue(date.durationFrom(previous) >= 0.999999 * step);
previous = date;
double[] e = measurement.estimate(0, 0,
new SpacecraftState[] {
for (int i = 0; i < m.length; ++i) {
maxError = FastMath.max(maxError, FastMath.abs(e[i] - m[i]));
Assert.assertEquals(0.0, maxError, tolerance);
public void setUp() {
context = EstimationTestUtils.eccentricContext("regular-data:potential:tides");
propagatorBuilder = context.createBuilder(OrbitType.KEPLERIAN, PositionAngle.TRUE, true,
1.0e-6, 300.0, 0.001, Force.POTENTIAL,
Context context;
NumericalPropagatorBuilder propagatorBuilder;
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