WsfParabolicMover.hpp

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// ****************************************************************************
// CUI
//
// The Advanced Framework for Simulation, Integration, and Modeling (AFSIM)
//
// Copyright 2003-2015 The Boeing Company. All rights reserved.
//
// The use, dissemination or disclosure of data in this file is subject to
// limitation or restriction. See accompanying README and LICENSE for details.
// ****************************************************************************
 
#ifndef WSFPARABOLICMOVER_HPP
#define WSFPARABOLICMOVER_HPP
 
#include "wsf_mil_export.h"
 
#include "WsfMover.hpp"

 
class WSF_MIL_EXPORT WsfParabolicMover : public WsfMover
{
public:
   static WsfStringId TypeId();
 
   WsfParabolicMover(WsfScenario& aScenario);
   ~WsfParabolicMover() override;
   WsfParabolicMover& operator=(const WsfParabolicMover&) = delete;
 
   WsfMover* Clone() const override;
 
   bool Initialize(double aSimTime) override;
   bool ProcessInput(UtInput& aInput) override;
   void Update(double aSimTime) override;
 
   WsfSpatialDomain GetSpatialDomain() const override { return WSF_SPATIAL_DOMAIN_AIR; }
 
   bool SetBallistic();
   bool SetCurrentTarget();
   bool SetImpactTOFAndLLA(double aTOF, double aLat, double aLon, double aAlt);
   bool SetImpactTOFAndLL(double aTOF, double aLat, double aLon);
 
protected:
   enum TrajectoryType
   {
      cUNDETERMINED,
      cSIMPLE_GRAVITY,
      cLLA_IMPACT,
      cCURRENT_TARGET
   };
 
   WsfParabolicMover(const WsfParabolicMover& aSrc);
 
   void InitShot(double aSimTime);
   void ToWCSLocation(double aFinalWCSLocation[]);
   void SetAccelerations();
 
private:
   double         mLastUpdate;
   double         mPlannedFlightTime;
   double         mPlannedFinalLatDeg;
   double         mPlannedFinalLonDeg;
   double         mPlannedFinalAlt;
   double         mGreatCircleDist;
   double         mStraightLineDist;
   double         mGroundSpeed; // Constant ONLY in the case of a cSIMPLE_GRAVITY trajectory
   double         mHeadingDeg;  // Constant ONLY in the case of a cSIMPLE_GRAVITY trajectory
   double         mStartFlightTime;
   double         mAccelNED[3];      // Always assumed constant, for all trajectory types (simplification)
   double         mCurVelNED[3];     // Initialized at launch, and varies during trajectory.
   double         mTotalDeltaNED[3]; // NED vector from launch point to desired impact point
   bool           mInitialized;
   bool           mInFlight;
   TrajectoryType mTrajType;
};
 
#endif