-/*******************************************************************************
-
+/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
Module: FGAircraft.cpp
Author: Jon S. Berndt
Date started: 12/12/98
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
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.
-
+
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
--------------------------------------------------------------------------------
12/12/98 JSB Created
9/17/99 TP Combined force and moment functions. Added aero reference
point to config file. Added calculations for moments due to
difference in cg and aero reference point
-
-********************************************************************************
+
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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
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
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
-*******************************************************************************/
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
#include <sys/stat.h>
#include <sys/types.h>
#ifdef FGFS
-# ifndef __BORLANDC__
-# include <simgear/compiler.h>
-# endif
-# ifdef FG_HAVE_STD_INCLUDES
+# ifndef __BORLANDC__
+# include <simgear/compiler.h>
+# endif
+# ifdef SG_HAVE_STD_INCLUDES
# include <cmath>
# else
# include <math.h>
#endif
#include "FGAircraft.h"
+#include "FGMassBalance.h"
+#include "FGInertial.h"
+#include "FGAerodynamics.h"
#include "FGTranslation.h"
#include "FGRotation.h"
#include "FGAtmosphere.h"
#include "FGAuxiliary.h"
#include "FGOutput.h"
-/*******************************************************************************
-************************************ CODE **************************************
-*******************************************************************************/
+/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+DEFINITIONS
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
+
+/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+GLOBAL DATA
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
+
+static const char *IdSrc = "$Id$";
+static const char *IdHdr = ID_AIRCRAFT;
+
+extern char highint[5];
+extern char halfint[5];
+extern char normint[6];
+extern char reset[5];
+extern char underon[5];
+extern char underoff[6];
+extern char fgblue[6];
+extern char fgcyan[6];
+extern char fgred[6];
+extern char fggreen[6];
+extern char fgdef[6];
+
+extern short debug_lvl;
+
+/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+CLASS IMPLEMENTATION
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
FGAircraft::FGAircraft(FGFDMExec* fdmex) : FGModel(fdmex),
- vMoments(3),
- vForces(3),
- vXYZrp(3),
- vbaseXYZcg(3),
- vXYZcg(3),
- vXYZep(3),
- vEuler(3)
+ vMoments(3),
+ vForces(3),
+ vXYZrp(3),
+ vXYZep(3),
+ vEuler(3),
+ vDXYZcg(3),
+ vAeroBodyForces(3)
{
Name = "FGAircraft";
- AxisIdx["LIFT"] = 0;
- AxisIdx["SIDE"] = 1;
- AxisIdx["DRAG"] = 2;
- AxisIdx["ROLL"] = 3;
- AxisIdx["PITCH"] = 4;
- AxisIdx["YAW"] = 5;
+ GearUp = false;
- numTanks = numEngines = numSelectedFuelTanks = numSelectedOxiTanks = 0;
+ alphaclmin = alphaclmax = 0;
+
+ if (debug_lvl & 2) cout << "Instantiated: " << Name << endl;
}
-/******************************************************************************/
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-FGAircraft::~FGAircraft(void)
+FGAircraft::~FGAircraft()
{
+ if (debug_lvl & 2) cout << "Destroyed: FGAircraft" << endl;
}
-/******************************************************************************/
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-bool FGAircraft::LoadAircraft(string aircraft_path, string engine_path, string fname)
+bool FGAircraft::Load(FGConfigFile* AC_cfg)
{
- string path;
- string filename;
- string aircraftCfgFileName;
string token;
- AircraftPath = aircraft_path;
- EnginePath = engine_path;
-
- aircraftCfgFileName = AircraftPath + "/" + fname + "/" + fname + ".cfg";
-
- FGConfigFile AC_cfg(aircraftCfgFileName);
-
- ReadPrologue(&AC_cfg);
+ ReadPrologue(AC_cfg);
- while ((AC_cfg.GetNextConfigLine() != "EOF") &&
- (token = AC_cfg.GetValue()) != "/FDM_CONFIG")
- {
+ while ((AC_cfg->GetNextConfigLine() != "EOF") &&
+ (token = AC_cfg->GetValue()) != "/FDM_CONFIG") {
if (token == "METRICS") {
- cout << " Reading Metrics" << endl;
- ReadMetrics(&AC_cfg);
+ if (debug_lvl > 0) cout << fgcyan << "\n Reading Metrics" << fgdef << endl;
+ ReadMetrics(AC_cfg);
} else if (token == "AERODYNAMICS") {
- cout << " Reading Aerodynamics" << endl;
- ReadAerodynamics(&AC_cfg);
+ if (debug_lvl > 0) cout << fgcyan << "\n Reading Aerodynamics" << fgdef << endl;
+ ReadAerodynamics(AC_cfg);
} else if (token == "UNDERCARRIAGE") {
- cout << " Reading Landing Gear" << endl;
- ReadUndercarriage(&AC_cfg);
+ if (debug_lvl > 0) cout << fgcyan << "\n Reading Landing Gear" << fgdef << endl;
+ ReadUndercarriage(AC_cfg);
} else if (token == "PROPULSION") {
- cout << " Reading Propulsion" << endl;
- ReadPropulsion(&AC_cfg);
+ if (debug_lvl > 0) cout << fgcyan << "\n Reading Propulsion" << fgdef << endl;
+ ReadPropulsion(AC_cfg);
} else if (token == "FLIGHT_CONTROL") {
- cout << " Reading Flight Control" << endl;
- ReadFlightControls(&AC_cfg);
+ if (debug_lvl > 0) cout << fgcyan << "\n Reading Flight Control" << fgdef << endl;
+ ReadFlightControls(AC_cfg);
+ } else if (token == "OUTPUT") {
+ if (debug_lvl > 0) cout << fgcyan << "\n Reading Output directives" << fgdef << endl;
+ ReadOutput(AC_cfg);
}
}
return true;
}
-/******************************************************************************/
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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();
+ vForces.InitMatrix();
+ vMoments.InitMatrix();
FMProp();
FMAero();
- FMGear();
FMMass();
- } else { // skip Run() execution this time
- }
- return false;
-}
-
-/******************************************************************************/
-
-void FGAircraft::MassChange()
-{
- static FGColumnVector vXYZtank(3);
- float Tw;
- float IXXt, IYYt, IZZt, IXZt;
- 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 (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
+ FMGear();
- 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;
+ return false;
+ } else { // skip Run() execution this time
+ return true;
}
-
- Ixx = baseIxx + IXXt;
- Iyy = baseIyy + IYYt;
- Izz = baseIzz + IZZt;
- Ixz = baseIxz + IXZt;
-
}
-/******************************************************************************/
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGAircraft::FMAero(void)
{
- static FGColumnVector vFs(3);
- static FGColumnVector vDXYZcg(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();
- }
- }
-
- vForces += State->GetTs2b(alpha, beta)*vFs;
-
- // 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) += vForces(eZ)*vDXYZcg(eY) - vForces(eY)*vDXYZcg(eZ); // rolling moment
- vMoments(eM) += vForces(eX)*vDXYZcg(eZ) - vForces(eZ)*vDXYZcg(eX); // pitching moment
- vMoments(eN) += vForces(eX)*vDXYZcg(eY) - vForces(eY)*vDXYZcg(eX); // 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();
- }
- }
+ vForces += Aerodynamics->GetForces();
+ vMoments += Aerodynamics->GetMoments();
}
-/******************************************************************************/
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGAircraft::FMGear(void)
{
- if (GearUp) {
- // crash routine
- } else {
- for (unsigned int i=0;i<lGear.size();i++) {
- // lGear[i].
+ 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;
+ vForces += Inertial->GetForces();
}
-/******************************************************************************/
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGAircraft::FMProp(void)
{
- for (int i=0;i<numEngines;i++) {
- vForces(eX) += Engine[i]->CalcThrust();
- }
+ vForces += Propulsion->GetForces();
+ vMoments += Propulsion->GetMoments();
}
-/******************************************************************************/
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGAircraft::GetState(void)
{
vEuler = Rotation->GetEuler();
}
-/******************************************************************************/
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGAircraft::ReadMetrics(FGConfigFile* AC_cfg)
{
string token = "";
string parameter;
+ float EW, bixx, biyy, bizz, bixz, biyz;
+ FGColumnVector vbaseXYZcg(3);
AC_cfg->GetNextConfigLine();
while ((token = AC_cfg->GetValue()) != "/METRICS") {
*AC_cfg >> parameter;
- if (parameter == "AC_WINGAREA") *AC_cfg >> WingArea;
- else if (parameter == "AC_WINGSPAN") *AC_cfg >> WingSpan;
- else if (parameter == "AC_CHORD") *AC_cfg >> cbar;
- else if (parameter == "AC_IXX") *AC_cfg >> baseIxx;
- else if (parameter == "AC_IYY") *AC_cfg >> baseIyy;
- else if (parameter == "AC_IZZ") *AC_cfg >> baseIzz;
- else if (parameter == "AC_IXZ") *AC_cfg >> baseIxz;
- else if (parameter == "AC_EMPTYWT") *AC_cfg >> EmptyWeight;
- else if (parameter == "AC_CGLOC") *AC_cfg >> vbaseXYZcg(eX) >> vbaseXYZcg(eY) >> vbaseXYZcg(eZ);
- else if (parameter == "AC_EYEPTLOC") *AC_cfg >> vXYZep(eX) >> vXYZep(eY) >> vXYZep(eZ);
- else if (parameter == "AC_AERORP") *AC_cfg >> vXYZrp(eX) >> vXYZrp(eY) >> vXYZrp(eZ);
+ if (parameter == "AC_WINGAREA") {
+ *AC_cfg >> WingArea;
+ if (debug_lvl > 0) cout << " WingArea: " << WingArea << endl;
+ } else if (parameter == "AC_WINGSPAN") {
+ *AC_cfg >> WingSpan;
+ if (debug_lvl > 0) cout << " WingSpan: " << WingSpan << endl;
+ } else if (parameter == "AC_CHORD") {
+ *AC_cfg >> cbar;
+ if (debug_lvl > 0) cout << " Chord: " << cbar << endl;
+ } else if (parameter == "AC_IXX") {
+ *AC_cfg >> bixx;
+ if (debug_lvl > 0) cout << " baseIxx: " << bixx << endl;
+ MassBalance->SetBaseIxx(bixx);
+ } else if (parameter == "AC_IYY") {
+ *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_IXZ") {
+ *AC_cfg >> bixz;
+ if (debug_lvl > 0) cout << " baseIxz: " << bixz << endl;
+ MassBalance->SetBaseIxz(bixz);
+ } else if (parameter == "AC_IYZ") {
+ *AC_cfg >> biyz;
+ if (debug_lvl > 0) cout << " baseIyz: " << biyz << endl;
+ MassBalance->SetBaseIyz(biyz);
+ } else if (parameter == "AC_EMPTYWT") {
+ *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);
+ 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);
+ if (debug_lvl > 0) cout << " Eyepoint (x, y, z): " << vXYZep << endl;
+ } else if (parameter == "AC_AERORP") {
+ *AC_cfg >> vXYZrp(eX) >> vXYZrp(eY) >> vXYZrp(eZ);
+ if (debug_lvl > 0) cout << " Ref Pt (x, y, z): " << vXYZrp << endl;
+ } else if (parameter == "AC_ALPHALIMITS") {
+ *AC_cfg >> alphaclmin >> alphaclmax;
+ if (debug_lvl > 0) 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++;
+void FGAircraft::ReadPropulsion(FGConfigFile* AC_cfg) {
+ if (!Propulsion->Load(AC_cfg)) {
+ cerr << "Propulsion not successfully loaded" << endl;
+ }
+}
- } 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++;
- }
+void FGAircraft::ReadFlightControls(FGConfigFile* AC_cfg) {
+ if (!FCS->Load(AC_cfg)) {
+ cerr << "Flight Controls not successfully loaded" << endl;
}
}
-/******************************************************************************/
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGAircraft::ReadFlightControls(FGConfigFile* AC_cfg)
+void FGAircraft::ReadAerodynamics(FGConfigFile* AC_cfg)
{
- string token;
+ if (!Aerodynamics->Load(AC_cfg)) {
+ cerr << "Aerodynamics not successfully loaded" << endl;
+ }
- FCS->LoadFCS(AC_cfg);
}
-/******************************************************************************/
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGAircraft::ReadAerodynamics(FGConfigFile* AC_cfg)
-{
- string token, axis;
+void FGAircraft::ReadUndercarriage(FGConfigFile* AC_cfg) {
+ string token;
AC_cfg->GetNextConfigLine();
- Coeff.push_back(*(new CoeffArray()));
- Coeff.push_back(*(new CoeffArray()));
- Coeff.push_back(*(new CoeffArray()));
- Coeff.push_back(*(new CoeffArray()));
- Coeff.push_back(*(new CoeffArray()));
- Coeff.push_back(*(new CoeffArray()));
-
- while ((token = AC_cfg->GetValue()) != "/AERODYNAMICS") {
- if (token == "AXIS") {
- axis = AC_cfg->GetValue("NAME");
- AC_cfg->GetNextConfigLine();
- while ((token = AC_cfg->GetValue()) != "/AXIS") {
- Coeff[AxisIdx[axis]].push_back(*(new FGCoefficient(FDMExec, AC_cfg)));
- DisplayCoeffFactors(Coeff[AxisIdx[axis]].back().Getmultipliers());
- }
- AC_cfg->GetNextConfigLine();
- }
+ while ((token = AC_cfg->GetValue()) != "/UNDERCARRIAGE") {
+ lGear.push_back(FGLGear(AC_cfg, FDMExec));
}
}
-/******************************************************************************/
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGAircraft::ReadUndercarriage(FGConfigFile* AC_cfg)
-{
- string token;
+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()) != "/UNDERCARRIAGE") {
- lGear.push_back(new FGLGear(AC_cfg));
+ 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;
+ }
+ 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;
+ }
+ if (parameter == "FCS") {
+ *AC_cfg >> parameter;
+ if (parameter == "ON") subsystems += ssFCS;
+ }
+ if (parameter == "PROPULSION") {
+ *AC_cfg >> parameter;
+ if (parameter == "ON") subsystems += ssPropulsion;
+ }
}
+
+ Output->SetSubsystems(subsystems);
+
+ OutRate = OutRate>120?120:(OutRate<0?0:OutRate);
+ Output->SetRate( (int)(0.5 + 1.0/(State->Getdt()*OutRate)) );
}
-/******************************************************************************/
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGAircraft::ReadPrologue(FGConfigFile* AC_cfg)
-{
+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;
- CFGVersion = strtod(AC_cfg->GetValue("VERSION").c_str(),NULL);
- cout << " Version: " << CFGVersion << endl;
-
- if (CFGVersion < NEEDED_CFG_VERSION) {
- cout << endl << "YOU HAVE AN OLD 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);
+ if (debug_lvl > 0) cout << underon << "Reading Aircraft Configuration File"
+ << underoff << ": " << highint << AircraftName << normint << endl;
+ scratch = AC_cfg->GetValue("VERSION").c_str();
+
+ CFGVersion = AC_cfg->GetValue("VERSION");
+
+ if (debug_lvl > 0)
+ cout << " Version: " << highint << CFGVersion
+ << normint << endl;
+ if (CFGVersion != NEEDED_CFG_VERSION) {
+ cerr << endl << fgred << "YOU HAVE AN INCOMPATIBLE CFG FILE FOR THIS AIRCRAFT."
+ " RESULTS WILL BE UNPREDICTABLE !!" << endl;
+ cerr << "Current version needed is: " << NEEDED_CFG_VERSION << endl;
+ cerr << " You have version: " << CFGVersion << endl << fgdef << endl;
}
}
-/******************************************************************************/
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGAircraft::DisplayCoeffFactors(int multipliers)
-{
- cout << " Non-Dimensionalized by: ";
-
- if (multipliers & FG_QBAR) cout << "qbar ";
- if (multipliers & FG_WINGAREA) cout << "S ";
- if (multipliers & FG_WINGSPAN) cout << "b ";
- if (multipliers & FG_CBAR) cout << "c ";
- if (multipliers & FG_ALPHA) cout << "alpha ";
- if (multipliers & FG_ALPHADOT) cout << "alphadot ";
- if (multipliers & FG_BETA) cout << "beta ";
- if (multipliers & FG_BETADOT) cout << "betadot ";
- if (multipliers & FG_PITCHRATE) cout << "q ";
- if (multipliers & FG_ROLLRATE) cout << "p ";
- if (multipliers & FG_YAWRATE) cout << "r ";
-
- if (multipliers & FG_ELEVATOR_CMD) cout << "De cmd ";
- if (multipliers & FG_AILERON_CMD) cout << "Da cmd ";
- if (multipliers & FG_RUDDER_CMD) cout << "Dr cmd ";
- if (multipliers & FG_FLAPS_CMD) cout << "Df cmd ";
- if (multipliers & FG_SPOILERS_CMD) cout << "Dsp cmd ";
- if (multipliers & FG_SPDBRAKE_CMD) cout << "Dsb cmd ";
-
- if (multipliers & FG_ELEVATOR_POS) cout << "De ";
- if (multipliers & FG_AILERON_POS) cout << "Da ";
- if (multipliers & FG_RUDDER_POS) cout << "Dr ";
- if (multipliers & FG_FLAPS_POS) cout << "Df ";
- if (multipliers & FG_SPOILERS_POS) cout << "Dsp ";
- if (multipliers & FG_SPDBRAKE_POS) cout << "Dsb ";
-
- if (multipliers & FG_MACH) cout << "Mach ";
- if (multipliers & FG_ALTITUDE) cout << "h ";
- if (multipliers & FG_BI2VEL) cout << "b /(2*Vt) ";
- if (multipliers & FG_CI2VEL) cout << "c /(2*Vt) ";
-
- cout << endl;
+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;
+ }
+
+ 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;
+ }
+
+ return GroundReactionValues;
}
-/******************************************************************************/
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+void FGAircraft::Debug(void)
+{
+ //TODO: Add your source code here
+}
projects / flightgear.git / blobdiff