fly/flightgear
1
0
Fork 0
Code Activity
flightgear/src/FDM/JSBSim/FGAircraft.h
curt 6a98486375 JSBSim updates. 
Updates to put more internal JSBSim values on the "bus".
2000-07-25 21:41:59 +00:00

245 lines
7.9 KiB
C++
Raw Blame History

/*******************************************************************************
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 <simgear/compiler.h>
# ifdef FG_HAVE_STD_INCLUDES
# include <vector>
# include <map>
# else
# include <vector.h>
# include <map.h>
# endif
#else
# include <vector>
# include <map>
#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 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; }
string GetCoefficientStrings(void);
string GetCoefficientValues(void);
string GetGroundReactionStrings(void);
string GetGroundReactionValues(void);
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];
FGEngine *Engine[MAX_ENGINES];
typedef map<string,int> AxisIndex;
AxisIndex AxisIdx;
typedef vector<FGCoefficient> CoeffArray;
typedef vector<CoeffArray> CoeffVector;
CoeffVector Coeff;
void DisplayCoeffFactors(int multipliers);
bool GearUp;
string Axis[6];
vector <FGLGear*> 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
View git blame Copy permalink