/* Copyright 2002-2024 Luc Maisonobe
    * 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.
    * 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
    *
    *   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.files.ccsds.ndm.adm.acm;
  
  import org.hipparchus.geometry.euclidean.threed.Vector3D;
  import org.hipparchus.linear.MatrixUtils;
  import org.hipparchus.linear.RealMatrix;
  import org.orekit.files.ccsds.definitions.FrameFacade;
  import org.orekit.files.ccsds.section.CommentsContainer;
  import org.orekit.time.AbsoluteDate;
  
  /** Spacecraft physical properties.
   * @author Luc Maisonobe
   * @since 12.0
   */
  public class AttitudePhysicalProperties extends CommentsContainer {
  
      /** Drag coefficient. */
      private double dragCoefficient;
  
      /** Total mass at T₀. */
      private double wetMass;
  
      /** Mass without propellant. */
      private double dryMass;
  
      /** Reference frame for center of pressure. */
      private FrameFacade centerOfPressureReferenceFrame;
  
      /** Location of center of pressure. */
      private Vector3D centerOfPressure;
  
      /** Reference frame for inertia. */
      private FrameFacade inertiaReferenceFrame;
  
      /** Inertia matrix. */
      private RealMatrix inertiaMatrix;
  
      /** Simple constructor.
       * @param epochT0 T0 epoch from file metadata
       */
      public AttitudePhysicalProperties(final AbsoluteDate epochT0) {
          dragCoefficient = Double.NaN;
          wetMass         = Double.NaN;
          dryMass         = Double.NaN;
          inertiaMatrix   = MatrixUtils.createRealMatrix(3, 3);
      }
  
      /** {@inheritDoc} */
      @Override
      public void validate(final double version) {
          super.validate(version);
          if (centerOfPressureReferenceFrame != null) {
              checkNotNull(centerOfPressure, AttitudePhysicalPropertiesKey.CP.name());
          }
      }
  
      /** Get the drag coefficient.
       * @return the drag coefficient
       */
      public double getDragCoefficient() {
          return dragCoefficient;
      }
  
      /** Set the the drag coefficient.
       * @param dragCoefficient the drag coefficient
       */
      public void setDragCoefficient(final double dragCoefficient) {
          refuseFurtherComments();
          this.dragCoefficient = dragCoefficient;
      }
  
      /** Get the total mass at T₀.
       * @return total mass at T₀
       */
      public double getWetMass() {
          return wetMass;
      }
  
      /** Set the total mass at T₀.
       * @param wetMass total mass at T₀
       */
      public void setWetMass(final double wetMass) {
          refuseFurtherComments();
         this.wetMass = wetMass;
     }
 
     /** Get the mass without propellant.
      * @return mass without propellant
      */
     public double getDryMass() {
         return dryMass;
     }
 
     /** Set the mass without propellant.
      * @param dryMass mass without propellant
      */
     public void setDryMass(final double dryMass) {
         refuseFurtherComments();
         this.dryMass = dryMass;
     }
 
     /** Get reference frame for center of pressure.
      * @return reference frame for center of pressure
      */
     public FrameFacade getCenterOfPressureReferenceFrame() {
         return centerOfPressureReferenceFrame;
     }
 
     /** Set reference frame for center of pressure.
      * @param centerOfPressureReferenceFrame reference frame for center of pressure
      */
     public void setCenterOfPressureReferenceFrame(final FrameFacade centerOfPressureReferenceFrame) {
         this.centerOfPressureReferenceFrame = centerOfPressureReferenceFrame;
     }
 
     /** Get the location of center of pressure.
      * @return location of center of pressure
      */
     public Vector3D getCenterOfPressure() {
         return centerOfPressure;
     }
 
     /** Set the location of center of pressure.
      * @param centerOfPressure location of center of pressure
      */
     public void setCenterOfPressure(final Vector3D centerOfPressure) {
         this.centerOfPressure = centerOfPressure;
     }
 
     /** Get reference frame for inertia.
      * @return reference frame for inertia
      */
     public FrameFacade getInertiaReferenceFrame() {
         return inertiaReferenceFrame;
     }
 
     /** Set reference frame for inertia.
      * @param inertiaReferenceFrame reference frame for inertia
      */
     public void setInertiaReferenceFrame(final FrameFacade inertiaReferenceFrame) {
         this.inertiaReferenceFrame = inertiaReferenceFrame;
     }
 
     /** Get the inertia matrix.
      * @return the inertia matrix
      */
     public RealMatrix getInertiaMatrix() {
         return inertiaMatrix;
     }
 
     /** Set an entry in the inertia matrix.
      * <p>
      * Both I(j, k) and I(k, j) are set.
      * </p>
      * @param j row index (must be between 0 and 3 (inclusive)
      * @param k column index (must be between 0 and 3 (inclusive)
      * @param entry value of the matrix entry
      */
     public void setInertiaMatrixEntry(final int j, final int k, final double entry) {
         refuseFurtherComments();
         inertiaMatrix.setEntry(j, k, entry);
         inertiaMatrix.setEntry(k, j, entry);
     }
 
 }