flightgear/JSBsim/FGAircraft.h

/*******************************************************************************

 Header:       FGAircraft.h
 Author:       Jon S. Berndt
 Date started: 12/12/98

 ------------- Copyright (C) 1999  Jon S. Berndt (jsb@hal-pc.org) -------------

 This program is free software; you can redistribute it and/or modify it under
 the terms of the GNU 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 General Public License for more
 details.

 You should have received a copy of the GNU 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 General Public License can also be found on
 the world wide web at http://www.gnu.org.

HISTORY
--------------------------------------------------------------------------------
12/12/98   JSB   Created

********************************************************************************
SENTRY
*******************************************************************************/

#ifndef FGAIRCRAFT_H
#define FGAIRCRAFT_H

/*******************************************************************************
COMMENTS, REFERENCES,  and NOTES
********************************************************************************
[1] Cooke, Zyda, Pratt, and McGhee, "NPSNET: Flight Simulation Dynamic Modeling
	 Using Quaternions", Presence, Vol. 1, No. 4, pp. 404-420  Naval Postgraduate
	 School, January 1994
[2] D. M. Henderson, "Euler Angles, Quaternions, and Transformation Matrices",
	 JSC 12960, July 1977
[3] Richard E. McFarland, "A Standard Kinematic Model for Flight Simulation at
	 NASA-Ames", NASA CR-2497, January 1975
[4] Barnes W. McCormick, "Aerodynamics, Aeronautics, and Flight Mechanics",
	 Wiley & Sons, 1979 ISBN 0-471-03032-5
[5] Bernard Etkin, "Dynamics of Flight, Stability and Control", Wiley & Sons,
	 1982 ISBN 0-471-08936-2

The aerodynamic coefficients used in this model are:

Longitudinal
  CL0 - Reference lift at zero alpha
  CD0 - Reference drag at zero alpha
  CDM - Drag due to Mach
  CLa - Lift curve slope (w.r.t. alpha)
  CDa - Drag curve slope (w.r.t. alpha)
  CLq - Lift due to pitch rate
  CLM - Lift due to Mach
  CLadt - Lift due to alpha rate

  Cmadt - Moment due to alpha rate
  Cm0 - Reference moment at zero alpha
  Cma - Pitching moment slope (w.r.t. alpha)
  Cmq - Pitch damping (pitch moment due to pitch rate)
  CmM - Moment due to Mach

Lateral
  Cyb - Side force due to sideslip
  Cyr - Side force due to yaw rate

  Clb - Dihedral effect (roll moment due to sideslip)
  Clp - Roll damping (roll moment due to roll rate)
  Clr - Roll moment due to yaw rate
  Cnb - Weathercocking stability (yaw moment due to sideslip)
  Cnp - Rudder adverse yaw (yaw moment due to roll rate)
  Cnr - Yaw damping (yaw moment due to yaw rate)

Control
  ClDe - Lift due to elevator
  CdDe - Drag due to elevator
  CyDr - Side force due to rudder
  CyDa - Side force due to aileron

  CmDe - Pitch moment due to elevator
  ClDa - Roll moment due to aileron
  ClDr - Roll moment due to rudder
  CnDr - Yaw moment due to rudder
  CnDa - Yaw moment due to aileron

********************************************************************************
INCLUDES
*******************************************************************************/

#include <stdio.h>
#include <fstream.h>

#include "FGModel.h"
#include "FGCoefficient.h"
#include "FGEngine.h"
#include "FGTank.h"

/*******************************************************************************
DEFINITIONS
*******************************************************************************/

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


class FGAircraft : public FGModel
{
public:
  FGAircraft(FGFDMExec*);
  ~FGAircraft(void);

  bool Run(void);

  bool LoadAircraft(char*);
  
  inline char* GetAircraftName(void) {return AircraftName;}

  inline void SetGearUp(bool tt) {GearUp = tt;}
  inline bool GetGearUp(void) {return GearUp;}
  inline float GetWingArea(void) {return WingArea;}
  inline float GetWingSpan(void) {return WingSpan;}
  inline float Getcbar(void) {return cbar;}
  inline FGEngine* GetEngine(int tt) {return Engine[tt];}
  inline FGTank* GetTank(int tt) {return Tank[tt];}
  inline float GetWeight(void) {return Weight;}
  inline float GetMass(void) {return Mass;}

  inline float GetL(void) {return Moments[0];}
  inline float GetM(void) {return Moments[1];}
  inline float GetN(void) {return Moments[2];}

  inline float GetFx(void) {return Forces[0];}
  inline float GetFy(void) {return Forces[1];}
  inline float GetFz(void) {return Forces[2];}

  inline float GetIxx(void) {return Ixx;}
  inline float GetIyy(void) {return Iyy;}
  inline float GetIzz(void) {return Izz;}
  inline float GetIxz(void) {return Ixz;}

private:
  void GetState(void);
  void PutState(void);

  void FAero(void);
  void FGear(void);
  void FMass(void);
  void FProp(void);

  void MAero(void);
  void MGear(void);
  void MMass(void);
  void MProp(void);

  void MassChange(void);

  float Moments[3];
  float Forces[3];

  char AircraftName[50];
  float Ixx, Iyy, Izz, Ixz, EmptyMass, Mass;
  float Xcg, Ycg, Zcg;
  float Xep, Yep, Zep;
  float rho, qbar, Vt;
  float alpha, beta;
  float WingArea, WingSpan, cbar;
  float phi, tht, psi;
  float Weight, EmptyWeight;
  float dt;

  int numTanks;
  int numEngines;
  int numSelectedOxiTanks;
  int numSelectedFuelTanks;
  FGTank* Tank[MAX_TANKS];
  FGEngine *Engine[MAX_ENGINES];

  FGCoefficient *Coeff[6][10];
  int coeff_ctr[6];

  bool GearUp;

  enum Param {LiftCoeff,
              DragCoeff,
              SideCoeff,
              RollCoeff,
              PitchCoeff,
              YawCoeff,
              numCoeffs};

  char* Axis[6];

protected:

};

/******************************************************************************/
#endif