/* Copyright 2002-2025 Joseph Reed
    * Licensed to CS GROUP (CS) under one or more
    * contributor license agreements.  See the NOTICE file distributed with
    * this work for additional information regarding copyright ownership.
    * Joseph Reed 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 static org.junit.jupiter.api.Assertions.assertEquals;
  
  import org.hipparchus.geometry.euclidean.threed.Vector3D;
  import org.hipparchus.ode.nonstiff.AdaptiveStepsizeIntegrator;
  import org.hipparchus.ode.nonstiff.DormandPrince853Integrator;
  import org.hipparchus.util.FastMath;
  import org.hipparchus.util.MathUtils;
  import org.junit.jupiter.api.BeforeEach;
  import org.junit.jupiter.api.Test;
  import org.orekit.Utils;
  import org.orekit.bodies.CelestialBodyFactory;
  import org.orekit.frames.FramesFactory;
  import org.orekit.orbits.EquinoctialOrbit;
  import org.orekit.orbits.Orbit;
  import org.orekit.propagation.Propagator;
  import org.orekit.propagation.SpacecraftState;
  import org.orekit.propagation.events.handlers.RecordAndContinue;
  import org.orekit.propagation.numerical.NumericalPropagator;
  import org.orekit.time.AbsoluteDate;
  import org.orekit.time.TimeScalesFactory;
  import org.orekit.utils.PVCoordinates;
  
  public class BetaAngleDetectorTest {
      private Propagator propagator;
      private AbsoluteDate date;
  
      @BeforeEach
      void setup() {
          Utils.setDataRoot("regular-data");
          final Vector3D position  = new Vector3D(-6142438.668, 3492467.560, -25767.25680);
          final Vector3D velocity  = new Vector3D(505.8479685, 942.7809215, 7435.922231);
          final AbsoluteDate iniDate = new AbsoluteDate(1969, 7, 28, 4, 0, 0.0, TimeScalesFactory.getTT());
          final Orbit orbit = new EquinoctialOrbit(new PVCoordinates(position,  velocity),
                                                      FramesFactory.getGCRF(), iniDate, 3.9860047e14);
          final SpacecraftState initialState = new SpacecraftState(orbit);
          double[] absTolerance = {
              0.001, 1.0e-9, 1.0e-9, 1.0e-6, 1.0e-6, 1.0e-6, 0.001
          };
          double[] relTolerance = {
              1.0e-7, 1.0e-4, 1.0e-4, 1.0e-7, 1.0e-7, 1.0e-7, 1.0e-7
          };
          AdaptiveStepsizeIntegrator integrator =
              new DormandPrince853Integrator(0.001, 1000, absTolerance, relTolerance);
          integrator.setInitialStepSize(60);
          propagator = new NumericalPropagator(integrator);
          ((NumericalPropagator) propagator).setInitialState(initialState);
          date = iniDate;
      }
  
      @Test
      void evaluate() {
          final BetaAngleDetector detector = new BetaAngleDetector(0);
          
          AbsoluteDate d = date;
          for (int i = 0; i < 50; i++) {
              final SpacecraftState state = propagator.propagate(d);
              final double g = detector.g(state);
              final double beta = BetaAngleDetector.calculateBetaAngle(
                      state, CelestialBodyFactory.getSun(), FramesFactory.getGCRF());
  
              final double expectedBeta = MathUtils.SEMI_PI - Vector3D.angle(
                      state.getPVCoordinates(FramesFactory.getGCRF()).getMomentum().normalize(),
                      CelestialBodyFactory.getSun().getPosition(state.getDate(), FramesFactory.getGCRF()).normalize());
              assertEquals(-beta, g, 1e-9);
              assertEquals(expectedBeta, beta, 1e-9);
  
              d = d.shiftedBy(86400);
          }
      }
  
      @Test
      void simpleStop() {
          final BetaAngleDetector detector = new BetaAngleDetector(0,
                  CelestialBodyFactory.getSun(),
                  FramesFactory.getGCRF());
          
          propagator.addEventDetector(detector);
          
          final SpacecraftState state = propagator.propagate(date, date.shiftedBy(30 * 86400));
          assertEquals(1883928.588393031, state.getDate().durationFrom(date), 1e-9);
  
         assertEquals(0, BetaAngleDetector.calculateBetaAngle(state, propagator), 1e-9);
     }
 
     @Test
     void record() {
         final RecordAndContinue handler = new RecordAndContinue();
         final BetaAngleDetector detector = new BetaAngleDetector(0,
                 CelestialBodyFactory.getMoon(),
                 FramesFactory.getGCRF())
             .withBetaThreshold(FastMath.toRadians(1))
             .withCelestialProvider(CelestialBodyFactory.getSun())
             .withInertialFrame(FramesFactory.getEME2000())
             .withHandler(handler);
         
         propagator.addEventDetector(detector);
         
         final SpacecraftState state = propagator.propagate(date, date.shiftedBy(30 * 86400));
         assertEquals(30 * 86400, state.getDate().durationFrom(date), 1e-9);
         assertEquals(1, handler.getEvents().size());
     }
 }