Date started: 12/12/98
Purpose: Encapsulates an aircraft
Called by: FGFDMExec
-
+
------------- Copyright (C) 1999 Jon S. Berndt (jsb@hal-pc.org) -------------
This program is free software; you can redistribute it and/or modify it under
FUNCTIONAL DESCRIPTION
--------------------------------------------------------------------------------
Models the aircraft reactions and forces. This class is instantiated by the
-FGFDMExec class and scheduled as an FDM entry. LoadAircraft() is supplied with a
-name of a valid, registered aircraft, and the data file is parsed.
+FGFDMExec class and scheduled as an FDM entry.
HISTORY
--------------------------------------------------------------------------------
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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 - 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
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
INCLUDES
# ifndef __BORLANDC__
# include <simgear/compiler.h>
# endif
-# ifdef FG_HAVE_STD_INCLUDES
+# ifdef SG_HAVE_STD_INCLUDES
# include <cmath>
# else
# include <math.h>
# endif
#else
-# include <cmath>
+# if defined (sgi) && !defined(__GNUC__)
+# include <math.h>
+# else
+# include <cmath>
+# endif
#endif
#include "FGAircraft.h"
+#include "FGMassBalance.h"
+#include "FGInertial.h"
+#include "FGGroundReactions.h"
+#include "FGAerodynamics.h"
#include "FGTranslation.h"
#include "FGRotation.h"
#include "FGAtmosphere.h"
#include "FGPosition.h"
#include "FGAuxiliary.h"
#include "FGOutput.h"
+#include "FGPropertyManager.h"
/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
DEFINITIONS
GLOBAL DATA
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
-static const char *IdSrc = "$Header$";
+static const char *IdSrc = "$Id$";
static const char *IdHdr = ID_AIRCRAFT;
/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
CLASS IMPLEMENTATION
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
-FGAircraft::FGAircraft(FGFDMExec* fdmex) : FGModel(fdmex),
- vMoments(3),
- vForces(3),
- vFs(3),
- vXYZrp(3),
- vbaseXYZcg(3),
- vXYZcg(3),
- vXYZep(3),
- vEuler(3)
-
+FGAircraft::FGAircraft(FGFDMExec* fdmex) : FGModel(fdmex)
{
Name = "FGAircraft";
+ HTailArea = VTailArea = 0.0;
+ HTailArm = VTailArm = 0.0;
+ lbarh = lbarv = 0.0;
+ vbarh = vbarv = 0.0;
- AxisIdx["DRAG"] = 0;
- AxisIdx["SIDE"] = 1;
- AxisIdx["LIFT"] = 2;
- AxisIdx["ROLL"] = 3;
- AxisIdx["PITCH"] = 4;
- AxisIdx["YAW"] = 5;
-
- Coeff = new CoeffArray[6];
-
- GearUp = false;
-
- alphaclmin = alphaclmax = 0;
-
- numTanks = numEngines = numSelectedFuelTanks = numSelectedOxiTanks = 0;
-}
-
-
-//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-
-
-FGAircraft::~FGAircraft(void) {
- unsigned int i,j;
+ bind();
- if (Engine != NULL) {
- for (i=0; i<numEngines; i++)
- delete Engine[i];
- }
- if (Tank != NULL) {
- for (i=0; i<numTanks; i++)
- delete Tank[i];
- }
- for (i=0; i<6; i++) {
- for (j=0; j<Coeff[i].size(); j++) {
- delete Coeff[i][j];
- }
- }
- delete[] Coeff;
+ Debug(0);
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-bool FGAircraft::LoadAircraft(string aircraft_path, string engine_path, string fname) {
- string path;
- string filename;
- string aircraftCfgFileName;
- string token;
-
- AircraftPath = aircraft_path;
- EnginePath = engine_path;
-
-# ifndef macintosh
- aircraftCfgFileName = AircraftPath + "/" + fname + "/" + fname + ".xml";
-# else
- aircraftCfgFileName = AircraftPath + ";" + fname + ";" + fname + ".xml";
-# endif
-
- FGConfigFile AC_cfg(aircraftCfgFileName);
- if (!AC_cfg.IsOpen()) return false;
-
- ReadPrologue(&AC_cfg);
-
- while ((AC_cfg.GetNextConfigLine() != "EOF") &&
- (token = AC_cfg.GetValue()) != "/FDM_CONFIG") {
- if (token == "METRICS") {
- cout << " Reading Metrics" << endl;
- ReadMetrics(&AC_cfg);
- } else if (token == "AERODYNAMICS") {
- cout << " Reading Aerodynamics" << endl;
- ReadAerodynamics(&AC_cfg);
- } else if (token == "UNDERCARRIAGE") {
- cout << " Reading Landing Gear" << endl;
- ReadUndercarriage(&AC_cfg);
- } else if (token == "PROPULSION") {
- cout << " Reading Propulsion" << endl;
- ReadPropulsion(&AC_cfg);
- } else if (token == "FLIGHT_CONTROL") {
- cout << " Reading Flight Control" << endl;
- ReadFlightControls(&AC_cfg);
- } else if (token == "OUTPUT") {
- ReadOutput(&AC_cfg);
- }
- }
-
- return true;
+FGAircraft::~FGAircraft()
+{
+ unbind();
+ Debug(1);
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-bool FGAircraft::Run(void) {
+bool FGAircraft::Run(void)
+{
if (!FGModel::Run()) { // if false then execute this Run()
- GetState();
-
- for (int i = 1; i <= 3; i++) vForces(i) = vMoments(i) = 0.0;
-
- MassChange();
- FMProp();
- FMAero();
- FMGear();
- FMMass();
+ vForces.InitMatrix();
+ vForces += Aerodynamics->GetForces();
+ vForces += Inertial->GetForces();
+ vForces += Propulsion->GetForces();
+ vForces += GroundReactions->GetForces();
+
+ vMoments.InitMatrix();
+ vMoments += Aerodynamics->GetMoments();
+ vMoments += Propulsion->GetMoments();
+ vMoments += GroundReactions->GetMoments();
+
+ vBodyAccel = vForces/MassBalance->GetMass();
+
+ vNcg = vBodyAccel/Inertial->gravity();
- nlf = 0;
- if (fabs(Position->GetGamma()) < 1.57) {
- nlf = vFs(eZ)/(Weight*cos(Position->GetGamma()));
- }
-
+ vNwcg = State->GetTb2s() * vNcg;
+ vNwcg(3) = -1*vNwcg(3) + 1;
+
+ return false;
} else { // skip Run() execution this time
- }
-
-
- return false;
-}
-
-//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-
-void FGAircraft::MassChange() {
- static FGColumnVector vXYZtank(3);
- float Tw;
- float IXXt, IYYt, IZZt, IXZt;
- unsigned int t;
- unsigned int axis_ctr;
-
- for (axis_ctr=1; axis_ctr<=3; axis_ctr++) vXYZtank(axis_ctr) = 0.0;
-
- // UPDATE TANK CONTENTS
- //
- // For each engine, cycle through the tanks and draw an equal amount of
- // fuel (or oxidizer) from each active tank. The needed amount of fuel is
- // determined by the engine in the FGEngine class. If more fuel is needed
- // than is available in the tank, then that amount is considered a shortage,
- // and will be drawn from the next tank. If the engine cannot be fed what it
- // needs, it will be considered to be starved, and will shut down.
-
- float Oshortage, Fshortage;
-
- for (unsigned int e=0; e<numEngines; e++) {
- Fshortage = Oshortage = 0.0;
- for (t=0; t<numTanks; t++) {
- switch(Engine[e]->GetType()) {
- case FGEngine::etRocket:
-
- switch(Tank[t]->GetType()) {
- case FGTank::ttFUEL:
- if (Tank[t]->GetSelected()) {
- Fshortage = Tank[t]->Reduce((Engine[e]->CalcFuelNeed()/
- numSelectedFuelTanks)*(dt*rate) + Fshortage);
- }
- break;
- case FGTank::ttOXIDIZER:
- if (Tank[t]->GetSelected()) {
- Oshortage = Tank[t]->Reduce((Engine[e]->CalcOxidizerNeed()/
- numSelectedOxiTanks)*(dt*rate) + Oshortage);
- }
- break;
- }
- break;
-
- case FGEngine::etPiston:
- case FGEngine::etTurboJet:
- case FGEngine::etTurboProp:
-
- if (Tank[t]->GetSelected()) {
- Fshortage = Tank[t]->Reduce((Engine[e]->CalcFuelNeed()/
- numSelectedFuelTanks)*(dt*rate) + Fshortage);
- }
- break;
- }
- }
- if ((Fshortage <= 0.0) || (Oshortage <= 0.0)) Engine[e]->SetStarved();
- else Engine[e]->SetStarved(false);
- }
-
- Weight = EmptyWeight;
- for (t=0; t<numTanks; t++)
- Weight += Tank[t]->GetContents();
-
- Mass = Weight / GRAVITY;
- // Calculate new CG here.
-
- Tw = 0;
- for (t=0; t<numTanks; t++) {
- vXYZtank(eX) += Tank[t]->GetX()*Tank[t]->GetContents();
- vXYZtank(eY) += Tank[t]->GetY()*Tank[t]->GetContents();
- vXYZtank(eZ) += Tank[t]->GetZ()*Tank[t]->GetContents();
-
- Tw += Tank[t]->GetContents();
- }
-
- vXYZcg = (vXYZtank + EmptyWeight*vbaseXYZcg) / (Tw + EmptyWeight);
-
- // Calculate new moments of inertia here
-
- IXXt = IYYt = IZZt = IXZt = 0.0;
- for (t=0; t<numTanks; t++) {
- IXXt += ((Tank[t]->GetX()-vXYZcg(eX))/12.0)*((Tank[t]->GetX() - vXYZcg(eX))/12.0)*Tank[t]->GetContents()/GRAVITY;
- IYYt += ((Tank[t]->GetY()-vXYZcg(eY))/12.0)*((Tank[t]->GetY() - vXYZcg(eY))/12.0)*Tank[t]->GetContents()/GRAVITY;
- IZZt += ((Tank[t]->GetZ()-vXYZcg(eZ))/12.0)*((Tank[t]->GetZ() - vXYZcg(eZ))/12.0)*Tank[t]->GetContents()/GRAVITY;
- IXZt += ((Tank[t]->GetX()-vXYZcg(eX))/12.0)*((Tank[t]->GetZ() - vXYZcg(eZ))/12.0)*Tank[t]->GetContents()/GRAVITY;
- }
-
- Ixx = baseIxx + IXXt;
- Iyy = baseIyy + IYYt;
- Izz = baseIzz + IZZt;
- Ixz = baseIxz + IXZt;
-
-}
-
-//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-
-void FGAircraft::FMAero(void) {
- static FGColumnVector vDXYZcg(3);
- static FGColumnVector vAeroBodyForces(3);
- unsigned int axis_ctr,ctr;
-
- for (axis_ctr=1; axis_ctr<=3; axis_ctr++) vFs(axis_ctr) = 0.0;
-
- for (axis_ctr = 0; axis_ctr < 3; axis_ctr++) {
- for (ctr=0; ctr < Coeff[axis_ctr].size(); ctr++) {
- vFs(axis_ctr+1) += Coeff[axis_ctr][ctr]->TotalValue();
- }
- }
-
- vAeroBodyForces = State->GetTs2b(alpha, beta)*vFs;
- vForces += vAeroBodyForces;
-
- // The d*cg distances below, given in inches, are the distances FROM the c.g.
- // TO the reference point. Since the c.g. and ref point are given in inches in
- // the structural system (X positive rearwards) and the body coordinate system
- // is given with X positive out the nose, the dxcg and dzcg values are
- // *rotated* 180 degrees about the Y axis.
-
- vDXYZcg(eX) = -(vXYZrp(eX) - vXYZcg(eX))/12.0; //cg and rp values are in inches
- vDXYZcg(eY) = (vXYZrp(eY) - vXYZcg(eY))/12.0;
- vDXYZcg(eZ) = -(vXYZrp(eZ) - vXYZcg(eZ))/12.0;
-
- vMoments(eL) += vAeroBodyForces(eZ)*vDXYZcg(eY) - vAeroBodyForces(eY)*vDXYZcg(eZ); // rolling moment
- vMoments(eM) += vAeroBodyForces(eX)*vDXYZcg(eZ) - vAeroBodyForces(eZ)*vDXYZcg(eX); // pitching moment
- vMoments(eN) += vAeroBodyForces(eY)*vDXYZcg(eX) - vAeroBodyForces(eX)*vDXYZcg(eY); // yawing moment
-
- for (axis_ctr = 0; axis_ctr < 3; axis_ctr++) {
- for (ctr = 0; ctr < Coeff[axis_ctr+3].size(); ctr++) {
- vMoments(axis_ctr+1) += Coeff[axis_ctr+3][ctr]->TotalValue();
- }
+ return true;
}
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGAircraft::FMGear(void) {
-
- if ( !GearUp ) {
- vector <FGLGear>::iterator iGear = lGear.begin();
- while (iGear != lGear.end()) {
- vForces += iGear->Force();
- vMoments += iGear->Moment();
- iGear++;
- }
- } else {
- // Crash Routine
- }
-}
-
-//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-
-void FGAircraft::FMMass(void) {
- vForces(eX) += -GRAVITY*sin(vEuler(eTht)) * Mass;
- vForces(eY) += GRAVITY*sin(vEuler(ePhi))*cos(vEuler(eTht)) * Mass;
- vForces(eZ) += GRAVITY*cos(vEuler(ePhi))*cos(vEuler(eTht)) * Mass;
-}
-
-//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-
-void FGAircraft::FMProp(void) {
- for (unsigned int i=0;i<numEngines;i++) {
-
- // Changes required here for new engine placement parameters (i.e. location and direction)
-
- vForces(eX) += Engine[i]->CalcThrust();
- }
-
-}
-
-//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-
-void FGAircraft::GetState(void) {
- dt = State->Getdt();
-
- alpha = Translation->Getalpha();
- beta = Translation->Getbeta();
- vEuler = Rotation->GetEuler();
+float FGAircraft::GetNlf(void)
+{
+ return -1*Aerodynamics->GetvFs(3)/MassBalance->GetWeight();
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGAircraft::ReadMetrics(FGConfigFile* AC_cfg) {
+bool FGAircraft::Load(FGConfigFile* AC_cfg)
+{
string token = "";
string parameter;
+ double EW, bixx, biyy, bizz, bixy, bixz;
+ double pmWt, pmX, pmY, pmZ;
+ FGColumnVector3 vbaseXYZcg;
AC_cfg->GetNextConfigLine();
- while ((token = AC_cfg->GetValue()) != "/METRICS") {
+ while ((token = AC_cfg->GetValue()) != string("/METRICS")) {
*AC_cfg >> parameter;
if (parameter == "AC_WINGAREA") {
- *AC_cfg >> WingArea;
- cout << " WingArea: " << WingArea << endl;
+ *AC_cfg >> WingArea;
+ if (debug_lvl > 0) cout << " WingArea: " << WingArea << endl;
} else if (parameter == "AC_WINGSPAN") {
- *AC_cfg >> WingSpan;
- cout << " WingSpan: " << WingSpan << endl;
+ *AC_cfg >> WingSpan;
+ if (debug_lvl > 0) cout << " WingSpan: " << WingSpan << endl;
+ } else if (parameter == "AC_WINGINCIDENCE") {
+ *AC_cfg >> WingIncidence;
+ if (debug_lvl > 0) cout << " Chord: " << cbar << endl;
} else if (parameter == "AC_CHORD") {
- *AC_cfg >> cbar;
- cout << " Chord: " << cbar << endl;
+ *AC_cfg >> cbar;
+ if (debug_lvl > 0) cout << " Chord: " << cbar << endl;
+ } else if (parameter == "AC_HTAILAREA") {
+ *AC_cfg >> HTailArea;
+ if (debug_lvl > 0) cout << " H. Tail Area: " << HTailArea << endl;
+ } else if (parameter == "AC_HTAILARM") {
+ *AC_cfg >> HTailArm;
+ if (debug_lvl > 0) cout << " H. Tail Arm: " << HTailArm << endl;
+ } else if (parameter == "AC_VTAILAREA") {
+ *AC_cfg >> VTailArea;
+ if (debug_lvl > 0) cout << " V. Tail Area: " << VTailArea << endl;
+ } else if (parameter == "AC_VTAILARM") {
+ *AC_cfg >> VTailArm;
+ if (debug_lvl > 0) cout << " V. Tail Arm: " << VTailArm << endl;
} else if (parameter == "AC_IXX") {
- *AC_cfg >> baseIxx;
- cout << " baseIxx: " << baseIxx << endl;
+ *AC_cfg >> bixx;
+ if (debug_lvl > 0) cout << " baseIxx: " << bixx << endl;
+ MassBalance->SetBaseIxx(bixx);
} else if (parameter == "AC_IYY") {
- *AC_cfg >> baseIyy;
- cout << " baseIyy: " << baseIyy << endl;
- } else if (parameter == "AC_IZZ") {
- *AC_cfg >> baseIzz;
- cout << " baseIzz: " << baseIzz << endl;
- } else if (parameter == "AC_IXZ") {
- *AC_cfg >> baseIxz;
- cout << " baseIxz: " << baseIxz << endl;
+ *AC_cfg >> biyy;
+ if (debug_lvl > 0) cout << " baseIyy: " << biyy << endl;
+ MassBalance->SetBaseIyy(biyy);
+ } else if (parameter == "AC_IZZ") {
+ *AC_cfg >> bizz;
+ if (debug_lvl > 0) cout << " baseIzz: " << bizz << endl;
+ MassBalance->SetBaseIzz(bizz);
+ } else if (parameter == "AC_IXY") {
+ *AC_cfg >> bixy;
+ if (debug_lvl > 0) cout << " baseIxy: " << bixy << endl;
+ MassBalance->SetBaseIxy(bixy);
+ } else if (parameter == "AC_IXZ") {
+ *AC_cfg >> bixz;
+ if (debug_lvl > 0) cout << " baseIxz: " << bixz << endl;
+ MassBalance->SetBaseIxz(bixz);
} else if (parameter == "AC_EMPTYWT") {
- *AC_cfg >> EmptyWeight;
- cout << " EmptyWeight: " << EmptyWeight << endl;
+ *AC_cfg >> EW;
+ MassBalance->SetEmptyWeight(EW);
+ if (debug_lvl > 0) cout << " EmptyWeight: " << EW << endl;
} else if (parameter == "AC_CGLOC") {
- *AC_cfg >> vbaseXYZcg(eX) >> vbaseXYZcg(eY) >> vbaseXYZcg(eZ);
- cout << " CG (x, y, z): " << vbaseXYZcg << endl;
+ *AC_cfg >> vbaseXYZcg(eX) >> vbaseXYZcg(eY) >> vbaseXYZcg(eZ);
+ MassBalance->SetBaseCG(vbaseXYZcg);
+ if (debug_lvl > 0) cout << " CG (x, y, z): " << vbaseXYZcg << endl;
} else if (parameter == "AC_EYEPTLOC") {
- *AC_cfg >> vXYZep(eX) >> vXYZep(eY) >> vXYZep(eZ);
- cout << " Eyepoint (x, y, z): " << vXYZep << endl;
+ *AC_cfg >> vXYZep(eX) >> vXYZep(eY) >> vXYZep(eZ);
+ if (debug_lvl > 0) cout << " Eyepoint (x, y, z): " << vXYZep << endl;
} else if (parameter == "AC_AERORP") {
- *AC_cfg >> vXYZrp(eX) >> vXYZrp(eY) >> vXYZrp(eZ);
- cout << " Ref Pt (x, y, z): " << vXYZrp << endl;
- } else if (parameter == "AC_ALPHALIMITS") {
- *AC_cfg >> alphaclmin >> alphaclmax;
- cout << " Maximum Alpha: " << alphaclmax
- << " Minimum Alpha: " << alphaclmin
- << endl;
- }
- }
-}
-
-//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-
-void FGAircraft::ReadPropulsion(FGConfigFile* AC_cfg) {
- string token;
- string engine_name;
- string parameter;
-
- AC_cfg->GetNextConfigLine();
-
- while ((token = AC_cfg->GetValue()) != "/PROPULSION") {
- *AC_cfg >> parameter;
-
- if (parameter == "AC_ENGINE") {
-
- *AC_cfg >> engine_name;
- Engine[numEngines] = new FGEngine(FDMExec, EnginePath, engine_name, numEngines);
- numEngines++;
-
- } else if (parameter == "AC_TANK") {
-
- Tank[numTanks] = new FGTank(AC_cfg);
- switch(Tank[numTanks]->GetType()) {
- case FGTank::ttFUEL:
- numSelectedFuelTanks++;
- break;
- case FGTank::ttOXIDIZER:
- numSelectedOxiTanks++;
- break;
- }
- numTanks++;
+ *AC_cfg >> vXYZrp(eX) >> vXYZrp(eY) >> vXYZrp(eZ);
+ if (debug_lvl > 0) cout << " Ref Pt (x, y, z): " << vXYZrp << endl;
+ } else if (parameter == "AC_POINTMASS") {
+ *AC_cfg >> pmWt >> pmX >> pmY >> pmZ;
+ MassBalance->AddPointMass(pmWt, pmX, pmY, pmZ);
+ if (debug_lvl > 0) cout << " Point Mass Object: " << pmWt << " lbs. at "
+ << "X, Y, Z (in.): " << pmX << " " << pmY << " " << pmZ
+ << endl;
}
}
-}
-
-//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-
-void FGAircraft::ReadFlightControls(FGConfigFile* AC_cfg) {
- string token;
-
- FCS->LoadFCS(AC_cfg);
-}
-
-//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-
-void FGAircraft::ReadAerodynamics(FGConfigFile* AC_cfg) {
- string token, axis;
-
- AC_cfg->GetNextConfigLine();
- while ((token = AC_cfg->GetValue()) != "/AERODYNAMICS") {
- if (token == "AXIS") {
- CoeffArray ca;
- axis = AC_cfg->GetValue("NAME");
- AC_cfg->GetNextConfigLine();
- while ((token = AC_cfg->GetValue()) != "/AXIS") {
- ca.push_back(new FGCoefficient(FDMExec, AC_cfg));
- DisplayCoeffFactors(ca.back()->Getmultipliers());
- }
- Coeff[AxisIdx[axis]]=ca;
- AC_cfg->GetNextConfigLine();
- }
- }
-}
-
-//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-
-void FGAircraft::ReadUndercarriage(FGConfigFile* AC_cfg) {
- string token;
-
- AC_cfg->GetNextConfigLine();
-
- while ((token = AC_cfg->GetValue()) != "/UNDERCARRIAGE") {
- lGear.push_back(FGLGear(AC_cfg, FDMExec));
- }
-}
-
-//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-
-void FGAircraft::ReadOutput(FGConfigFile* AC_cfg) {
- string token, parameter;
- int OutRate = 0;
- int subsystems = 0;
-
- token = AC_cfg->GetValue("NAME");
- Output->SetFilename(token);
- token = AC_cfg->GetValue("TYPE");
- Output->SetType(token);
- AC_cfg->GetNextConfigLine();
-
- while ((token = AC_cfg->GetValue()) != "/OUTPUT") {
- *AC_cfg >> parameter;
- if (parameter == "RATE_IN_HZ") *AC_cfg >> OutRate;
- if (parameter == "SIMULATION") {
- *AC_cfg >> parameter;
- if (parameter == "ON") subsystems += ssSimulation;
- }
- if (parameter == "AEROSURFACES") {
- *AC_cfg >> parameter;
- if (parameter == "ON") subsystems += ssAerosurfaces;
+ // calculate some derived parameters
+ if (cbar != 0.0) {
+ lbarh = HTailArm/cbar;
+ lbarv = VTailArm/cbar;
+ if (WingArea != 0.0) {
+ vbarh = HTailArm*HTailArea / (cbar*WingArea);
+ vbarv = VTailArm*VTailArea / (cbar*WingArea);
}
- if (parameter == "RATES") {
- *AC_cfg >> parameter;
- if (parameter == "ON") subsystems += ssRates;
- }
- if (parameter == "VELOCITIES") {
- *AC_cfg >> parameter;
- if (parameter == "ON") subsystems += ssVelocities;
- }
- if (parameter == "FORCES") {
- *AC_cfg >> parameter;
- if (parameter == "ON") subsystems += ssForces;
- }
- if (parameter == "MOMENTS") {
- *AC_cfg >> parameter;
- if (parameter == "ON") subsystems += ssMoments;
- }
- if (parameter == "ATMOSPHERE") {
- *AC_cfg >> parameter;
- if (parameter == "ON") subsystems += ssAtmosphere;
- }
- if (parameter == "MASSPROPS") {
- *AC_cfg >> parameter;
- if (parameter == "ON") subsystems += ssMassProps;
- }
- if (parameter == "POSITION") {
- *AC_cfg >> parameter;
- if (parameter == "ON") subsystems += ssPosition;
- }
- if (parameter == "COEFFICIENTS") {
- *AC_cfg >> parameter;
- if (parameter == "ON") subsystems += ssCoefficients;
- }
- if (parameter == "GROUND_REACTIONS") {
- *AC_cfg >> parameter;
- if (parameter == "ON") subsystems += ssGroundReactions;
- }
- }
-
- Output->SetSubsystems(subsystems);
-
- OutRate = OutRate>120?120:(OutRate<0?0:OutRate);
- Output->SetRate( (int)(0.5 + 1.0/(State->Getdt()*OutRate)) );
+ }
+ return true;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGAircraft::ReadPrologue(FGConfigFile* AC_cfg) {
- string token = AC_cfg->GetValue();
- string scratch;
- AircraftName = AC_cfg->GetValue("NAME");
- cout << "Reading Aircraft Configuration File: " << AircraftName << endl;
- scratch=AC_cfg->GetValue("VERSION").c_str();
-
- CFGVersion = AC_cfg->GetValue("VERSION");
- cout << " Version: " << CFGVersion << endl;
- if (CFGVersion != NEEDED_CFG_VERSION) {
- cout << endl << "YOU HAVE AN INCOMPATIBLE CFG FILE FOR THIS AIRCRAFT."
- " RESULTS WILL BE UNPREDICTABLE !!" << endl;
- cout << "Current version needed is: " << NEEDED_CFG_VERSION << endl;
- cout << " You have version: " << CFGVersion << endl << endl;
- //exit(-1);
- }
-
-
+void FGAircraft::bind(void)
+{
+ typedef double (FGAircraft::*PMF)(int) const;
+ PropertyManager->Tie("metrics/Sw-sqft", this,
+ &FGAircraft::GetWingArea);
+ PropertyManager->Tie("metrics/bw-ft", this,
+ &FGAircraft::GetWingSpan);
+ PropertyManager->Tie("metrics/cbarw-ft", this,
+ &FGAircraft::Getcbar);
+ PropertyManager->Tie("metrics/iw-deg", this,
+ &FGAircraft::GetWingIncidence);
+ PropertyManager->Tie("metrics/Sh-sqft", this,
+ &FGAircraft::GetHTailArea);
+ PropertyManager->Tie("metrics/lh-ft", this,
+ &FGAircraft::GetHTailArm);
+ PropertyManager->Tie("metrics/Sv-sqft", this,
+ &FGAircraft::GetVTailArea);
+ PropertyManager->Tie("metrics/lv-ft", this,
+ &FGAircraft::GetVTailArm);
+ PropertyManager->Tie("metrics/lh-norm", this,
+ &FGAircraft::Getlbarh);
+ PropertyManager->Tie("metrics/lv-norm", this,
+ &FGAircraft::Getlbarv);
+ PropertyManager->Tie("metrics/vbarh-norm", this,
+ &FGAircraft::Getvbarh);
+ PropertyManager->Tie("metrics/vbarv-norm", this,
+ &FGAircraft::Getvbarv);
+ PropertyManager->Tie("moments/l-total-lbsft", this,1,
+ (PMF)&FGAircraft::GetMoments);
+ PropertyManager->Tie("moments/m-total-lbsft", this,2,
+ (PMF)&FGAircraft::GetMoments);
+ PropertyManager->Tie("moments/n-total-lbsft", this,3,
+ (PMF)&FGAircraft::GetMoments);
+ PropertyManager->Tie("forces/fbx-total-lbs", this,1,
+ (PMF)&FGAircraft::GetForces);
+ PropertyManager->Tie("forces/fby-total-lbs", this,2,
+ (PMF)&FGAircraft::GetForces);
+ PropertyManager->Tie("forces/fbz-total-lbs", this,3,
+ (PMF)&FGAircraft::GetForces);
+ PropertyManager->Tie("metrics/aero-rp-x-ft", this,1,
+ (PMF)&FGAircraft::GetXYZrp);
+ PropertyManager->Tie("metrics/aero-rp-y-ft", this,2,
+ (PMF)&FGAircraft::GetXYZrp);
+ PropertyManager->Tie("metrics/aero-rp-z-ft", this,3,
+ (PMF)&FGAircraft::GetXYZrp);
+ PropertyManager->Tie("metrics/eyepoint-x-ft", this,1,
+ (PMF)&FGAircraft::GetXYZep);
+ PropertyManager->Tie("metrics/eyepoint-y-ft", this,2,
+ (PMF)&FGAircraft::GetXYZep);
+ PropertyManager->Tie("metrics/eyepoint-z-ft", this,3,
+ (PMF)&FGAircraft::GetXYZep);
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGAircraft::DisplayCoeffFactors(vector <eParam> multipliers) {
- cout << " Non-Dimensionalized by: ";
-
- for (unsigned int i=0; i<multipliers.size();i++)
- cout << State->paramdef[multipliers[i]];
-
- cout << endl;
+void FGAircraft::unbind(void)
+{
+ PropertyManager->Untie("metrics/Sw-sqft");
+ PropertyManager->Untie("metrics/bw-ft");
+ PropertyManager->Untie("metrics/cbarw-ft");
+ PropertyManager->Untie("metrics/iw-deg");
+ PropertyManager->Untie("metrics/Sh-sqft");
+ PropertyManager->Untie("metrics/lh-ft");
+ PropertyManager->Untie("metrics/Sv-sqft");
+ PropertyManager->Untie("metrics/lv-ft");
+ PropertyManager->Untie("metrics/lh-norm");
+ PropertyManager->Untie("metrics/lv-norm");
+ PropertyManager->Untie("metrics/vbarh-norm");
+ PropertyManager->Untie("metrics/vbarv-norm");
+ PropertyManager->Untie("moments/l-total-lbsft");
+ PropertyManager->Untie("moments/m-total-lbsft");
+ PropertyManager->Untie("moments/n-total-lbsft");
+ PropertyManager->Untie("forces/fbx-total-lbs");
+ PropertyManager->Untie("forces/fby-total-lbs");
+ PropertyManager->Untie("forces/fbz-total-lbs");
+ PropertyManager->Untie("metrics/aero-rp-x-ft");
+ PropertyManager->Untie("metrics/aero-rp-y-ft");
+ PropertyManager->Untie("metrics/aero-rp-z-ft");
+ PropertyManager->Untie("metrics/eyepoint-x-ft");
+ PropertyManager->Untie("metrics/eyepoint-y-ft");
+ PropertyManager->Untie("metrics/eyepoint-z-ft");
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+// The bitmasked value choices are as follows:
+// unset: In this case (the default) JSBSim would only print
+// out the normally expected messages, essentially echoing
+// the config files as they are read. If the environment
+// variable is not set, debug_lvl is set to 1 internally
+// 0: This requests JSBSim not to output any messages
+// whatsoever.
+// 1: This value explicity requests the normal JSBSim
+// startup messages
+// 2: This value asks for a message to be printed out when
+// a class is instantiated
+// 4: When this value is set, a message is displayed when a
+// FGModel object executes its Run() method
+// 8: When this value is set, various runtime state variables
+// are printed out periodically
+// 16: When set various parameters are sanity checked and
+// a message is printed out when they go out of bounds
+
+void FGAircraft::Debug(int from)
+{
+ if (debug_lvl <= 0) return;
-string FGAircraft::GetCoefficientStrings(void) {
- string CoeffStrings = "";
- bool firstime = true;
-
- for (unsigned int axis = 0; axis < 6; axis++) {
- for (unsigned int sd = 0; sd < Coeff[axis].size(); sd++) {
- if (firstime) {
- firstime = false;
- } else {
- CoeffStrings += ", ";
- }
- CoeffStrings += Coeff[axis][sd]->Getname();
+ if (debug_lvl & 1) { // Standard console startup message output
+ if (from == 0) { // Constructor
}
}
-
- return CoeffStrings;
-}
-
-//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-
-string FGAircraft::GetCoefficientValues(void) {
- string SDValues = "";
- char buffer[10];
- bool firstime = true;
-
- for (unsigned int axis = 0; axis < 6; axis++) {
- for (unsigned int sd = 0; sd < Coeff[axis].size(); sd++) {
- if (firstime) {
- firstime = false;
- } else {
- SDValues += ", ";
- }
- sprintf(buffer, "%9.6f", Coeff[axis][sd]->GetSD());
- SDValues += string(buffer);
- }
+ if (debug_lvl & 2 ) { // Instantiation/Destruction notification
+ if (from == 0) cout << "Instantiated: FGAircraft" << endl;
+ if (from == 1) cout << "Destroyed: FGAircraft" << endl;
}
-
- return SDValues;
- ;
-}
-
-//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-
-string FGAircraft::GetGroundReactionStrings(void) {
- string GroundReactionStrings = "";
- bool firstime = true;
-
- for (unsigned int i=0;i<lGear.size();i++) {
- if (!firstime) GroundReactionStrings += ", ";
- GroundReactionStrings += (lGear[i].GetName() + "_WOW, ");
- GroundReactionStrings += (lGear[i].GetName() + "_compressLength, ");
- GroundReactionStrings += (lGear[i].GetName() + "_compressSpeed, ");
- GroundReactionStrings += (lGear[i].GetName() + "_Force");
-
- firstime = false;
+ if (debug_lvl & 4 ) { // Run() method entry print for FGModel-derived objects
}
-
- return GroundReactionStrings;
-}
-
-//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-
-string FGAircraft::GetGroundReactionValues(void) {
- char buff[20];
- string GroundReactionValues = "";
-
- bool firstime = true;
-
- for (unsigned int i=0;i<lGear.size();i++) {
- if (!firstime) GroundReactionValues += ", ";
- GroundReactionValues += string( lGear[i].GetWOW()?"1":"0" ) + ", ";
- GroundReactionValues += (string(gcvt(lGear[i].GetCompLen(), 5, buff)) + ", ");
- GroundReactionValues += (string(gcvt(lGear[i].GetCompVel(), 6, buff)) + ", ");
- GroundReactionValues += (string(gcvt(lGear[i].GetCompForce(), 10, buff)));
-
- firstime = false;
+ if (debug_lvl & 8 ) { // Runtime state variables
+ }
+ if (debug_lvl & 16) { // Sanity checking
+ }
+ if (debug_lvl & 64) {
+ if (from == 0) { // Constructor
+ cout << IdSrc << endl;
+ cout << IdHdr << endl;
+ }
}
-
- return GroundReactionValues;
}
projects / flightgear.git / blobdiff