/*
    * Licensed to the Hipparchus project under one or more
    * contributor license agreements.  See the NOTICE file distributed with
    * this work for additional information regarding copyright ownership.
    * The ASF 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
    *
    *      http://www.apache.org/licenses/LICENSE-2.0
   *
   * Unless required by applicable law or agreed to in writing, software
   * distributed under the License is distributed on an "AS IS" BASIS,
   * WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
   * See the License for the specific language governing permissions and
   * limitations under the License.
   */
  package org.orekit.propagation.events;
  
  import org.hipparchus.ode.ODEIntegrator;
  import org.hipparchus.ode.nonstiff.DormandPrince853Integrator;
  import org.orekit.bodies.CelestialBodyFactory;
  import org.orekit.orbits.OrbitType;
  import org.orekit.propagation.PropagationType;
  import org.orekit.propagation.Propagator;
  import org.orekit.propagation.SpacecraftState;
  import org.orekit.propagation.ToleranceProvider;
  import org.orekit.propagation.semianalytical.dsst.DSSTPropagator;
  import org.orekit.propagation.semianalytical.dsst.forces.DSSTThirdBody;
  import org.orekit.utils.Constants;
  
  /** Test events with the DSST Propagator.
  *
  * @author Evan Ward
  */
  public class CloseEventsDsstOsculatingTest extends CloseEventsAbstractTest {
  
      @Override
      public Propagator getPropagator(double stepSize) {
          double[][] tol = ToleranceProvider.getDefaultToleranceProvider(1).getTolerances(initialOrbit, OrbitType.EQUINOCTIAL);
          ODEIntegrator integrator = new DormandPrince853Integrator(stepSize, stepSize, tol[0], tol[1]);
          DSSTPropagator propagator = new DSSTPropagator(integrator, PropagationType.OSCULATING);
          propagator.setInitialState(new SpacecraftState(initialOrbit));
          double gm = Constants.EIGEN5C_EARTH_MU;
          propagator.addForceModel(new DSSTThirdBody(CelestialBodyFactory.getMoon(), gm));
          return propagator;
      }
  
  }