/******************************************************************************* 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 *******************************************************************************/ /* The aerodynamic coefficients used in this model typically 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 - Pitching Moment due to alpha rate Cm0 - Reference Pitching moment at zero alpha Cma - Pitching moment slope (w.r.t. alpha) Cmq - Pitch damping (pitch moment due to pitch rate) CmM - Pitch 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 [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 */ /******************************************************************************* INCLUDES *******************************************************************************/ #ifdef FGFS # include # ifdef FG_HAVE_STD_INCLUDES # include # include # include # else # include # include # include # endif #else # include # include # include #endif #include "FGModel.h" #include "FGCoefficient.h" #include "FGEngine.h" #include "FGTank.h" #include "FGLGear.h" #include "FGConfigFile.h" #include "FGMatrix.h" /******************************************************************************* DEFINITIONS *******************************************************************************/ /******************************************************************************* CLASS DECLARATION *******************************************************************************/ class FGAircraft : public FGModel { enum {eL=1, eM, eN}; enum {eX=1, eY, eZ}; enum {eP=1, eQ, eR}; enum {ePhi=1, eTht, ePsi}; public: FGAircraft(FGFDMExec*); ~FGAircraft(void); bool Run(void); bool LoadAircraft(string, string, string); inline string GetAircraftName(void) { return AircraftName; } inline void SetGearUp(bool tt) { GearUp = tt; } inline bool GetGearUp(void) { return GearUp; } inline int GetNumGearUnits(void) { return lGear.size(); } inline FGLGear* GetGearUnit(int ii) { return lGear[ii]; } 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 FGColumnVector GetMoments(void) { return vMoments; } inline FGColumnVector GetForces(void) { return vForces; } inline FGColumnVector GetvFs(void) { return vFs; } inline float GetIxx(void) { return Ixx; } inline float GetIyy(void) { return Iyy; } inline float GetIzz(void) { return Izz; } inline float GetIxz(void) { return Ixz; } inline unsigned int GetNumEngines(void) { return numEngines; } inline FGColumnVector GetXYZcg(void) { return vXYZcg; } inline FGColumnVector GetXYZrp(void) { return vXYZrp; } inline FGColumnVector GetXYZep(void) { return vXYZep; } inline float GetNlf(void) { return nlf; } inline float GetAlphaCLMax(void) { return alphaclmax; } inline float GetAlphaCLMin(void) { return alphaclmin; } inline void SetAlphaCLMax(float tt) { alphaclmax=tt; } inline void SetAlphaCLMin(float tt) { alphaclmin=tt; } inline FGCoefficient* GetCoeff(int axis, int idx) { return Coeff[axis][idx]; } string GetCoefficientStrings(void); string GetCoefficientValues(void); string GetGroundReactionStrings(void); string GetGroundReactionValues(void); vector ::iterator iGear; enum { ssSimulation = 1, ssAerosurfaces = 2, ssRates = 4, ssVelocities = 8, ssForces = 16, ssMoments = 32, ssAtmosphere = 64, ssMassProps = 128, ssCoefficients = 256, ssPosition = 512, ssGroundReactions = 1024 } subsystems; private: void GetState(void); void FMAero(void); void FMGear(void); void FMMass(void); void FMProp(void); void MassChange(void); FGColumnVector vMoments; FGColumnVector vForces; FGColumnVector vFs; FGColumnVector vXYZrp; FGColumnVector vbaseXYZcg; FGColumnVector vXYZcg; FGColumnVector vXYZep; FGColumnVector vEuler; float baseIxx, baseIyy, baseIzz, baseIxz, EmptyMass, Mass; float Ixx, Iyy, Izz, Ixz; float alpha, beta; float WingArea, WingSpan, cbar; float Weight, EmptyWeight; float nlf,alphaclmax,alphaclmin; float dt; string CFGVersion; string AircraftName; unsigned int numTanks; unsigned int numEngines; unsigned int numSelectedOxiTanks; unsigned int numSelectedFuelTanks; FGTank* Tank[MAX_TANKS]; // need to make a vector FGEngine *Engine[MAX_ENGINES]; // need to make a vector typedef map AxisIndex; AxisIndex AxisIdx; typedef vector CoeffArray; CoeffArray* Coeff; void DisplayCoeffFactors(vector multipliers); bool GearUp; string Axis[6]; vector lGear; string AircraftPath; string EnginePath; void ReadMetrics(FGConfigFile*); void ReadPropulsion(FGConfigFile*); void ReadFlightControls(FGConfigFile*); void ReadAerodynamics(FGConfigFile*); void ReadUndercarriage(FGConfigFile*); void ReadPrologue(FGConfigFile*); void ReadOutput(FGConfigFile*); }; /******************************************************************************/ #endif