fgauxiliary.h

来自「6 DOF Missle Simulation」· C头文件 代码 · 共 275 行

/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

 Header:       FGAuxiliary.h
 Author:       Jon Berndt
 Date started: 01/26/99

 ------------- Copyright (C) 1999  Jon S. Berndt ([e-mail]) -------------

 This program is free software; you can redistribute it and/or modify it under
 the terms of the GNU Lesser General Public License as published by the Free Software
 Foundation; either version 2 of the License, or (at your option) any later
 version.

 This program is distributed in the hope that it will be useful, but WITHOUT
 ANY WARRANTY; without even the implied warranty of MERCHANTABILITY or FITNESS
 FOR A PARTICULAR PURPOSE.  See the GNU Lesser General Public License for more
 details.

 You should have received a copy of the GNU Lesser General Public License along with
 this program; if not, write to the Free Software Foundation, Inc., 59 Temple
 Place - Suite 330, Boston, MA  02111-1307, USA.

 Further information about the GNU Lesser General Public License can also be found on
 the world wide web at http://www.gnu.org.

HISTORY
--------------------------------------------------------------------------------
11/22/98   JSB   Created
  1/1/00   TP    Added calcs and getters for VTAS, VCAS, VEAS, Vground, in knots

%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
SENTRY
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/

#ifndef FGAUXILIARY_H
#define FGAUXILIARY_H

/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
INCLUDES
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/

#include "FGModel.h"
#include <math/FGColumnVector3.h>
#include <math/FGLocation.h>
#include "FGPropagate.h"

/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
DEFINITIONS
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/

#define ID_AUXILIARY "$Id$"

/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
FORWARD DECLARATIONS
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/

namespace JSBSim {

/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
CLASS DOCUMENTATION
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/

/** Encapsulates various uncategorized scheduled functions.
    Pilot sensed accelerations are calculated here. This is used
    for the coordinated turn ball instrument. Motion base platforms sometimes
    use the derivative of pilot sensed accelerations as the driving parameter,
    rather than straight accelerations.

    The theory behind pilot-sensed calculations is presented:

    For purposes of discussion and calculation, assume for a minute that the
    pilot is in space and motionless in inertial space. She will feel
    no accelerations. If the aircraft begins to accelerate along any axis or
    axes (without rotating), the pilot will sense those accelerations. If
    any rotational moment is applied, the pilot will sense an acceleration
    due to that motion in the amount:

    [wdot X R]  +  [w X (w X R)]
    Term I          Term II

    where:

    wdot = omegadot, the rotational acceleration rate vector
    w    = omega, the rotational rate vector
    R    = the vector from the aircraft CG to the pilot eyepoint

    The sum total of these two terms plus the acceleration of the aircraft
    body axis gives the acceleration the pilot senses in inertial space.
    In the presence of a large body such as a planet, a gravity field also
    provides an accelerating attraction. This acceleration can be transformed
    from the reference frame of the planet so as to be expressed in the frame
    of reference of the aircraft. This gravity field accelerating attraction
    is felt by the pilot as a force on her tushie as she sits in her aircraft
    on the runway awaiting takeoff clearance.

    In JSBSim the acceleration of the body frame in inertial space is given
    by the F = ma relation. If the vForces vector is divided by the aircraft
    mass, the acceleration vector is calculated. The term wdot is equivalent
    to the JSBSim vPQRdot vector, and the w parameter is equivalent to vPQR.
    The radius R is calculated below in the vector vToEyePt.

    @author Tony Peden, Jon Berndt
    @version $Id$
*/

/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
CLASS DECLARATION
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/

class FGAuxiliary : public FGModel {
public:
  /** Constructor
      @param Executive a pointer to the parent executive object */
  FGAuxiliary(FGFDMExec* Executive);

  /// Destructor
  ~FGAuxiliary();

  bool InitModel(void);

  /** Runs the Auxiliary routines; called by the Executive
      @return false if no error */
  bool Run(void);

// GET functions

  // Atmospheric parameters GET functions
  /** Returns Calibrated airspeed in feet/second.*/
  double GetVcalibratedFPS(void) const { return vcas; }
  /** Returns Calibrated airspeed in knots.*/
  double GetVcalibratedKTS(void) const { return vcas*fpstokts; }
  /** Returns equivalent airspeed in feet/second. */
  double GetVequivalentFPS(void) const { return veas; }
  /** Returns equivalent airspeed in knots. */
  double GetVequivalentKTS(void) const { return veas*fpstokts; }

  /** Returns the total pressure.
      Total pressure is freestream total pressure for
      subsonic only. For supersonic it is the 1D total pressure
      behind a normal shock. */
  double GetTotalPressure(void) const { return pt; }

  /** Returns the total temperature.
    The total temperature ("tat", isentropic flow) is calculated:
    @code
    tat = sat*(1 + 0.2*Mach*Mach)
    @endcode
    (where "sat" is standard temperature) */

  double GetTotalTemperature(void) const { return tat; }
  double GetTAT_C(void) const { return tatc; }

  double GetPilotAccel(int idx)  const { return vPilotAccel(idx);  }
  double GetNpilot(int idx)      const { return vPilotAccelN(idx); }
  double GetAeroPQR(int axis)    const { return vAeroPQR(axis);    }
  double GetEulerRates(int axis) const { return vEulerRates(axis); }

  const FGColumnVector3& GetPilotAccel (void) const { return vPilotAccel;  }
  const FGColumnVector3& GetNpilot     (void) const { return vPilotAccelN; }
  const FGColumnVector3& GetAeroPQR    (void) const { return vAeroPQR;     }
  const FGColumnVector3& GetEulerRates (void) const { return vEulerRates;  }
  const FGColumnVector3& GetAeroUVW    (void) const { return vAeroUVW;     }
  const FGLocation&      GetLocationVRP(void) const { return vLocationVRP; }

  double GethVRP(void) const { return vLocationVRP.GetRadius() - Propagate->GetSeaLevelRadius(); }
  double GetAeroUVW (int idx) const { return vAeroUVW(idx); }
  double Getalpha   (void) const { return alpha;      }
  double Getbeta    (void) const { return beta;       }
  double Getadot    (void) const { return adot;       }
  double Getbdot    (void) const { return bdot;       }
  double GetMagBeta (void) const { return fabs(beta); }

  double Getalpha   (int unit) const { if (unit == inDegrees) return alpha*radtodeg;
                                       else cerr << "Bad units" << endl; return 0.0;}
  double Getbeta    (int unit) const { if (unit == inDegrees) return beta*radtodeg;
                                       else cerr << "Bad units" << endl; return 0.0;}
  double Getadot    (int unit) const { if (unit == inDegrees) return adot*radtodeg;
                                       else cerr << "Bad units" << endl; return 0.0;}
  double Getbdot    (int unit) const { if (unit == inDegrees) return bdot*radtodeg;
                                       else cerr << "Bad units" << endl; return 0.0;}
  double GetMagBeta (int unit) const { if (unit == inDegrees) return fabs(beta)*radtodeg;
                                       else cerr << "Bad units" << endl; return 0.0;}

  double Getqbar    (void) const { return qbar;       }
  double GetqbarUW  (void) const { return qbarUW;     }
  double GetqbarUV  (void) const { return qbarUV;     }
  double GetVt      (void) const { return Vt;         }
  double GetVground (void) const { return Vground;    }
  double GetMach    (void) const { return Mach;       }
  double GetMachU   (void) const { return MachU;      }
  double GetNz      (void) const { return Nz;         }

  double GetHOverBCG(void) const { return hoverbcg; }
  double GetHOverBMAC(void) const { return hoverbmac; }

  double GetGamma(void)              const { return gamma;         }
  double GetGroundTrack(void)        const { return psigt;         }

  double GetHeadWind(void) const;
  double GetCrossWind(void) const;

// SET functions

  void SetAeroUVW(FGColumnVector3 tt) { vAeroUVW = tt; }

  void Setalpha  (double tt) { alpha = tt;  }
  void Setbeta   (double tt) { beta  = tt;  }
  void Setqbar   (double tt) { qbar = tt;   }
  void SetqbarUW (double tt) { qbarUW = tt; }
  void SetqbarUV (double tt) { qbarUV = tt; }
  void SetVt     (double tt) { Vt = tt;     }
  void SetMach   (double tt) { Mach=tt;     }
  void Setadot   (double tt) { adot = tt;   }
  void Setbdot   (double tt) { bdot = tt;   }

  void SetAB    (double t1, double t2) { alpha=t1; beta=t2; }
  void SetGamma (double tt)            { gamma = tt;        }

// Time routines, SET and GET functions, used by FGMSIS atmosphere

  void SetDayOfYear    (int doy)    { day_of_year = doy;    }
  void SetSecondsInDay (double sid) { seconds_in_day = sid; }

  int    GetDayOfYear    (void) const { return day_of_year;    }
  double GetSecondsInDay (void) const { return seconds_in_day; }

  double GetLongitudeRelativePosition (void) const { return lon_relative_position; }
  double GetLatitudeRelativePosition  (void) const { return lat_relative_position; }
  double GetDistanceRelativePosition  (void) const { return relative_position; }

  void SetAeroPQR(FGColumnVector3 tt) { vAeroPQR = tt; }

private:
  double vcas, veas;
  double rhosl, rho, p, psl, pt, tat, sat, tatc; // Don't add a getter for pt!

  FGColumnVector3 vPilotAccel;
  FGColumnVector3 vPilotAccelN;
  FGColumnVector3 vToEyePt;
  FGColumnVector3 vAeroPQR;
  FGColumnVector3 vAeroUVW;
  FGColumnVector3 vEuler;
  FGColumnVector3 vEulerRates;
  FGColumnVector3 vMachUVW;
  FGColumnVector3 vAircraftAccel;
  FGLocation vLocationVRP;

  double Vt, Vground, Mach, MachU;
  double qbar, qbarUW, qbarUV;
  double alpha, beta;
  double adot,bdot;
  double psigt, gamma;
  double Nz;
  double seconds_in_day;  // seconds since current GMT day began
  int    day_of_year;     // GMT day, 1 .. 366

  double hoverbcg, hoverbmac;

  // helper data, calculation of distance from initial position

  double lon_relative_position;
  double lat_relative_position;
  double relative_position;

  void CalculateRelativePosition(void);

  void bind(void);
  void Debug(int from);
};

} // namespace JSBSim

//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
#endif