/******************************************************************************* 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 # else # include # include # endif #else # include # include #endif #include "FGModel.h" #include "FGCoefficient.h" #include "FGEngine.h" #include "FGTank.h" #include "FGLGear.h" /******************************************************************************* DEFINITIONS *******************************************************************************/ using namespace std; /******************************************************************************* CLASS DECLARATION *******************************************************************************/ class FGAircraft : public FGModel { 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 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;} inline float GetXcg(void) {return Xcg;} inline int GetNumEngines(void) {return numEngines;} private: void GetState(void); void PutState(void); void FMAero(void); void FMGear(void); void FMMass(void); void FMProp(void); void MassChange(void); float Moments[3]; float Forces[3]; string AircraftName; float baseIxx, baseIyy, baseIzz, baseIxz, EmptyMass, Mass; float Ixx, Iyy, Izz, Ixz; float Xrp, Yrp, Zrp; float baseXcg, baseYcg, baseZcg; 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; float CFGVersion; 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}; string Axis[6]; vector lGear; protected: }; /******************************************************************************/ #endif