206 lines
6.1 KiB
C++
206 lines
6.1 KiB
C++
/*******************************************************************************
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Header: FGAircraft.h
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Author: Jon S. Berndt
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Date started: 12/12/98
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------------- Copyright (C) 1999 Jon S. Berndt (jsb@hal-pc.org) -------------
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This program is free software; you can redistribute it and/or modify it under
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the terms of the GNU General Public License as published by the Free Software
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Foundation; either version 2 of the License, or (at your option) any later
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version.
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This program is distributed in the hope that it will be useful, but WITHOUT
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ANY WARRANTY; without even the implied warranty of MERCHANTABILITY or FITNESS
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FOR A PARTICULAR PURPOSE. See the GNU General Public License for more
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details.
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You should have received a copy of the GNU General Public License along with
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this program; if not, write to the Free Software Foundation, Inc., 59 Temple
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Place - Suite 330, Boston, MA 02111-1307, USA.
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Further information about the GNU General Public License can also be found on
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the world wide web at http://www.gnu.org.
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HISTORY
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--------------------------------------------------------------------------------
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12/12/98 JSB Created
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********************************************************************************
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SENTRY
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*******************************************************************************/
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#ifndef FGAIRCRAFT_H
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#define FGAIRCRAFT_H
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/*******************************************************************************
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COMMENTS, REFERENCES, and NOTES
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********************************************************************************
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[1] Cooke, Zyda, Pratt, and McGhee, "NPSNET: Flight Simulation Dynamic Modeling
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Using Quaternions", Presence, Vol. 1, No. 4, pp. 404-420 Naval Postgraduate
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School, January 1994
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[2] D. M. Henderson, "Euler Angles, Quaternions, and Transformation Matrices",
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JSC 12960, July 1977
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[3] Richard E. McFarland, "A Standard Kinematic Model for Flight Simulation at
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NASA-Ames", NASA CR-2497, January 1975
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[4] Barnes W. McCormick, "Aerodynamics, Aeronautics, and Flight Mechanics",
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Wiley & Sons, 1979 ISBN 0-471-03032-5
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[5] Bernard Etkin, "Dynamics of Flight, Stability and Control", Wiley & Sons,
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1982 ISBN 0-471-08936-2
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The aerodynamic coefficients used in this model are:
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Longitudinal
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CL0 - Reference lift at zero alpha
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CD0 - Reference drag at zero alpha
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CDM - Drag due to Mach
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CLa - Lift curve slope (w.r.t. alpha)
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CDa - Drag curve slope (w.r.t. alpha)
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CLq - Lift due to pitch rate
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CLM - Lift due to Mach
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CLadt - Lift due to alpha rate
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Cmadt - Moment due to alpha rate
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Cm0 - Reference moment at zero alpha
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Cma - Pitching moment slope (w.r.t. alpha)
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Cmq - Pitch damping (pitch moment due to pitch rate)
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CmM - Moment due to Mach
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Lateral
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Cyb - Side force due to sideslip
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Cyr - Side force due to yaw rate
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Clb - Dihedral effect (roll moment due to sideslip)
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Clp - Roll damping (roll moment due to roll rate)
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Clr - Roll moment due to yaw rate
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Cnb - Weathercocking stability (yaw moment due to sideslip)
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Cnp - Rudder adverse yaw (yaw moment due to roll rate)
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Cnr - Yaw damping (yaw moment due to yaw rate)
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Control
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ClDe - Lift due to elevator
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CdDe - Drag due to elevator
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CyDr - Side force due to rudder
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CyDa - Side force due to aileron
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CmDe - Pitch moment due to elevator
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ClDa - Roll moment due to aileron
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ClDr - Roll moment due to rudder
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CnDr - Yaw moment due to rudder
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CnDa - Yaw moment due to aileron
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********************************************************************************
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INCLUDES
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*******************************************************************************/
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#include <stdio.h>
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#include <fstream.h>
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#include "FGModel.h"
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#include "FGCoefficient.h"
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#include "FGEngine.h"
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#include "FGTank.h"
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/*******************************************************************************
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DEFINITIONS
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*******************************************************************************/
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/*******************************************************************************
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CLASS DECLARATION
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*******************************************************************************/
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class FGAircraft : public FGModel
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{
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public:
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FGAircraft(FGFDMExec*);
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~FGAircraft(void);
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bool Run(void);
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bool LoadAircraft(char*);
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inline char* GetAircraftName(void) {return AircraftName;}
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inline void SetGearUp(bool tt) {GearUp = tt;}
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inline bool GetGearUp(void) {return GearUp;}
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inline float GetWingArea(void) {return WingArea;}
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inline float GetWingSpan(void) {return WingSpan;}
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inline float Getcbar(void) {return cbar;}
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inline FGEngine* GetEngine(int tt) {return Engine[tt];}
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inline FGTank* GetTank(int tt) {return Tank[tt];}
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inline float GetWeight(void) {return Weight;}
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inline float GetMass(void) {return Mass;}
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inline float GetL(void) {return Moments[0];}
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inline float GetM(void) {return Moments[1];}
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inline float GetN(void) {return Moments[2];}
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inline float GetFx(void) {return Forces[0];}
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inline float GetFy(void) {return Forces[1];}
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inline float GetFz(void) {return Forces[2];}
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inline float GetIxx(void) {return Ixx;}
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inline float GetIyy(void) {return Iyy;}
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inline float GetIzz(void) {return Izz;}
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inline float GetIxz(void) {return Ixz;}
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private:
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void GetState(void);
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void PutState(void);
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void FAero(void);
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void FGear(void);
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void FMass(void);
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void FProp(void);
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void MAero(void);
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void MGear(void);
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void MMass(void);
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void MProp(void);
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void MassChange(void);
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float Moments[3];
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float Forces[3];
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char AircraftName[50];
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float Ixx, Iyy, Izz, Ixz, EmptyMass, Mass;
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float Xcg, Ycg, Zcg;
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float Xep, Yep, Zep;
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float rho, qbar, Vt;
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float alpha, beta;
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float WingArea, WingSpan, cbar;
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float phi, tht, psi;
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float Weight, EmptyWeight;
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float dt;
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int numTanks;
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int numEngines;
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int numSelectedOxiTanks;
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int numSelectedFuelTanks;
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FGTank* Tank[MAX_TANKS];
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FGEngine *Engine[MAX_ENGINES];
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FGCoefficient *Coeff[6][10];
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int coeff_ctr[6];
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bool GearUp;
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enum Param {LiftCoeff,
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DragCoeff,
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SideCoeff,
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RollCoeff,
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PitchCoeff,
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YawCoeff,
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numCoeffs};
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char* Axis[6];
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protected:
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};
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/******************************************************************************/
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#endif
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