/*******************************************************************************
-
+
Module: FGAircraft.cpp
Author: Jon S. Berndt
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
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.
-
+
HISTORY
--------------------------------------------------------------------------------
12/12/98 JSB Created
04/03/99 JSB Changed Aero() method to correct body axis force calculation
from wind vector. Fix provided by Tony Peden.
05/03/99 JSB Changed (for the better?) the way configurations are read in.
-
+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
********************************************************************************
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/types.h>
#ifdef FGFS
-# ifndef __BORLANDC__
-# include <Include/compiler.h>
-# endif
+# ifndef __BORLANDC__
+# include <simgear/compiler.h>
+# endif
# ifdef FG_HAVE_STD_INCLUDES
# include <cmath>
# else
#include "FGAuxiliary.h"
#include "FGOutput.h"
+static const char *IdSrc = "$Header$";
+static const char *IdHdr = ID_AIRCRAFT;
+
/*******************************************************************************
************************************ CODE **************************************
*******************************************************************************/
-FGAircraft::FGAircraft(FGFDMExec* fdmex) : FGModel(fdmex)
+FGAircraft::FGAircraft(FGFDMExec* fdmex) : FGModel(fdmex),
+ vMoments(3),
+ vForces(3),
+ vFs(3),
+ vXYZrp(3),
+ vbaseXYZcg(3),
+ vXYZcg(3),
+ vXYZep(3),
+ vEuler(3)
+
{
- int i;
-
Name = "FGAircraft";
- for (i=0;i<6;i++) coeff_ctr[i] = 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;
-FGAircraft::~FGAircraft(void)
-{
+ numTanks = numEngines = numSelectedFuelTanks = numSelectedOxiTanks = 0;
}
-bool FGAircraft::LoadAircraft(string aircraft_path, string engine_path, string fname)
-{
- string path;
- string fullpath;
- string filename;
- string aircraftDef;
- string tag;
- string holding_string;
- char scratch[128];
- ifstream coeffInFile;
- streampos gpos;
- int axis;
- string axis_descript;
-
- axis = -1;
- aircraftDef = aircraft_path + "/" + fname + "/" + fname + ".cfg";
- ifstream aircraftfile(aircraftDef.c_str());
- cout << "Reading Aircraft Configuration File: " << aircraftDef << endl;
-
- numTanks = numEngines = 0;
- numSelectedOxiTanks = numSelectedFuelTanks = 0;
-
- while (!aircraftfile.fail()) {
- holding_string.erase();
- aircraftfile >> holding_string;
-#ifdef __BORLANDC__
- if (holding_string.compare(0, 2, "//") != 0) {
-#else
- if (holding_string.compare("//",0,2) != 0) {
-#endif
- if (holding_string == "AIRCRAFT") {
- cout << "Reading in Aircraft parameters ..." << endl;
- } else if (holding_string == "AERODYNAMICS") {
- cout << "Reading in Aerodynamic parameters ..." << endl;
- } else if (holding_string == "AC_NAME") {
- aircraftfile >> AircraftName; // String with no embedded spaces
- cout << "Aircraft Name: " << AircraftName << endl;
- } else if (holding_string == "AC_WINGAREA") {
- aircraftfile >> WingArea;
- cout << "Aircraft Wing Area: " << WingArea << endl;
- } else if (holding_string == "AC_WINGSPAN") {
- aircraftfile >> WingSpan;
- cout << "Aircraft WingSpan: " << WingSpan << endl;
- } else if (holding_string == "AC_CHORD") {
- aircraftfile >> cbar;
- cout << "Aircraft Chord: " << cbar << endl;
- } else if (holding_string == "AC_IXX") {
- aircraftfile >> Ixx;
- cout << "Aircraft Ixx: " << Ixx << endl;
- } else if (holding_string == "AC_IYY") {
- aircraftfile >> Iyy;
- cout << "Aircraft Iyy: " << Iyy << endl;
- } else if (holding_string == "AC_IZZ") {
- aircraftfile >> Izz;
- cout << "Aircraft Izz: " << Izz << endl;
- } else if (holding_string == "AC_IXZ") {
- aircraftfile >> Ixz;
- cout << "Aircraft Ixz: " << Ixz << endl;
- } else if (holding_string == "AC_EMPTYWT") {
- aircraftfile >> EmptyWeight;
- EmptyMass = EmptyWeight / GRAVITY;
- cout << "Aircraft Empty Weight: " << EmptyWeight << endl;
- } else if (holding_string == "AC_CGLOC") {
- aircraftfile >> Xcg >> Ycg >> Zcg;
- cout << "Aircraft C.G.: " << Xcg << " " << Ycg << " " << Zcg << endl;
- } else if (holding_string == "AC_EYEPTLOC") {
- aircraftfile >> Xep >> Yep >> Zep;
- cout << "Pilot Eyepoint: " << Xep << " " << Yep << " " << Zep << endl;
- } else if (holding_string == "AC_TANK") {
- Tank[numTanks] = new FGTank(aircraftfile);
- switch(Tank[numTanks]->GetType()) {
- case FGTank::ttFUEL:
- numSelectedFuelTanks++;
- cout << "Reading in Fuel Tank #" << numSelectedFuelTanks << " parameters ..." << endl;
- break;
- case FGTank::ttOXIDIZER:
- numSelectedOxiTanks++;
- cout << "Reading in Oxidizer Tank #" << numSelectedOxiTanks << " parameters ..." << endl;
- break;
- }
- numTanks++;
-
- } else if (holding_string == "AC_ENGINE") {
-
- aircraftfile >> tag;
- cout << "Reading in " << tag << " Engine parameters ..." << endl;
- Engine[numEngines] = new FGEngine(FDMExec, engine_path, tag, numEngines);
- numEngines++;
-
- } else if (holding_string == "}") {
-
- } else if (holding_string == "{") {
- } else if (holding_string == "LIFT") {
+/******************************************************************************/
- axis_descript = " Lift Coefficients ...";
- axis = LiftCoeff;
-
- } else if (holding_string == "DRAG") {
- axis_descript = " Drag Coefficients ...";
- axis = DragCoeff;
+FGAircraft::~FGAircraft(void) {
+ unsigned int i,j;
- } else if (holding_string == "SIDE") {
-
- axis_descript = " Side Coefficients ...";
- axis = SideCoeff;
-
- } else if (holding_string == "ROLL") {
-
- axis_descript = " Roll Coefficients ...";
- axis = RollCoeff;
-
- } else if (holding_string == "PITCH") {
+ 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;
+}
- axis_descript = " Pitch Coefficients ...";
- axis = PitchCoeff;
+/******************************************************************************/
- } else if (holding_string == "YAW") {
+bool FGAircraft::LoadAircraft(string aircraft_path, string engine_path, string fname) {
+ string path;
+ string filename;
+ string aircraftCfgFileName;
+ string token;
- axis_descript = " Yaw Coefficients ...";
- axis = YawCoeff;
+ AircraftPath = aircraft_path;
+ EnginePath = engine_path;
- }
+# ifndef macintosh
+ aircraftCfgFileName = AircraftPath + "/" + fname + "/" + fname + ".xml";
+# else
+ aircraftCfgFileName = AircraftPath + ";" + fname + ";" + fname + ".xml";
+# endif
- if (axis >= 0) {
- cout << axis_descript << endl;
- aircraftfile >> tag;
- gpos = aircraftfile.tellg();
- aircraftfile >> tag;
- if (tag != "}" ) {
- while (tag != "}") {
- aircraftfile.seekg(gpos);
- Coeff[axis][coeff_ctr[axis]] = new FGCoefficient(FDMExec, aircraftfile);
- coeff_ctr[axis]++;
- aircraftfile >> tag;
- gpos = aircraftfile.tellg();
- aircraftfile >> tag;
- }
- } else {
- cout << " None found ..." << endl;
- }
- }
- axis = -1;
-
- } else {
- aircraftfile.getline(scratch, 127);
+ 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);
}
}
- cout << "End of Configuration File Parsing." << endl;
return true;
}
+/******************************************************************************/
-bool FGAircraft::Run(void)
-{
+bool FGAircraft::Run(void) {
if (!FGModel::Run()) { // if false then execute this Run()
GetState();
- for (int i = 0; i < 3; i++) Forces[i] = Moments[i] = 0.0;
+ for (int i = 1; i <= 3; i++) vForces(i) = vMoments(i) = 0.0;
MassChange();
-
- FProp(); FAero(); FGear(); FMass();
- MProp(); MAero(); MGear(); MMass();
-
- PutState();
+ FMProp();
+ FMAero();
+ FMGear();
+ FMMass();
+
+ nlf = 0;
+ if (fabs(Position->GetGamma()) < 1.57) {
+ nlf = vFs(eZ)/(Weight*cos(Position->GetGamma()));
+ }
+
} 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;
-void FGAircraft::MassChange()
-{
// UPDATE TANK CONTENTS
//
// For each engine, cycle through the tanks and draw an equal amount of
float Oshortage, Fshortage;
- for (int e=0; e<numEngines; e++) {
+ for (unsigned int e=0; e<numEngines; e++) {
Fshortage = Oshortage = 0.0;
- for (int t=0; t<numTanks; t++) {
+ for (t=0; t<numTanks; t++) {
switch(Engine[e]->GetType()) {
case FGEngine::etRocket:
case FGTank::ttFUEL:
if (Tank[t]->GetSelected()) {
Fshortage = Tank[t]->Reduce((Engine[e]->CalcFuelNeed()/
- numSelectedFuelTanks)*(dt*rate) + Fshortage);
+ numSelectedFuelTanks)*(dt*rate) + Fshortage);
}
break;
case FGTank::ttOXIDIZER:
if (Tank[t]->GetSelected()) {
Oshortage = Tank[t]->Reduce((Engine[e]->CalcOxidizerNeed()/
- numSelectedOxiTanks)*(dt*rate) + Oshortage);
+ numSelectedOxiTanks)*(dt*rate) + Oshortage);
}
break;
}
if (Tank[t]->GetSelected()) {
Fshortage = Tank[t]->Reduce((Engine[e]->CalcFuelNeed()/
- numSelectedFuelTanks)*(dt*rate) + Fshortage);
+ numSelectedFuelTanks)*(dt*rate) + Fshortage);
}
break;
}
}
Weight = EmptyWeight;
- for (int t=0; t<numTanks; t++)
+ 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();
-void FGAircraft::FAero(void)
-{
- float F[3];
-
- F[0] = F[1] = F[2] = 0.0;
-
- for (int axis_ctr = 0; axis_ctr < 3; axis_ctr++)
- for (int ctr=0; ctr < coeff_ctr[axis_ctr]; ctr++)
- F[axis_ctr] += Coeff[axis_ctr][ctr]->TotalValue();
-
- Forces[0] += - F[DragCoeff]*cos(alpha)*cos(beta)
- - F[SideCoeff]*cos(alpha)*sin(beta)
- + F[LiftCoeff]*sin(alpha);
- Forces[1] += F[DragCoeff]*sin(beta)
- + F[SideCoeff]*cos(beta);
- Forces[2] += - F[DragCoeff]*sin(alpha)*cos(beta)
- - F[SideCoeff]*sin(alpha)*sin(beta)
- - F[LiftCoeff]*cos(alpha);
-}
+ Tw += Tank[t]->GetContents();
+ }
+ vXYZcg = (vXYZtank + EmptyWeight*vbaseXYZcg) / (Tw + EmptyWeight);
-void FGAircraft::FGear(void)
-{
- if (GearUp) {
- // crash routine
- } else {
-
+ // 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::FMass(void)
-{
- Forces[0] += -GRAVITY*sin(tht) * Mass;
- Forces[1] += GRAVITY*sin(phi)*cos(tht) * Mass;
- Forces[2] += GRAVITY*cos(phi)*cos(tht) * Mass;
}
+/******************************************************************************/
-void FGAircraft::FProp(void)
-{
- for (int i=0;i<numEngines;i++) {
- Forces[0] += Engine[i]->CalcThrust();
+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;
-void FGAircraft::MAero(void)
-{
- int axis_ctr, ctr;
-
+ // 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_ctr[axis_ctr+3]; ctr++) {
- Moments[axis_ctr] += Coeff[axis_ctr+3][ctr]->TotalValue();
+ for (ctr = 0; ctr < Coeff[axis_ctr+3].size(); ctr++) {
+ vMoments(axis_ctr+1) += Coeff[axis_ctr+3][ctr]->TotalValue();
}
}
}
+/******************************************************************************/
-void FGAircraft::MGear(void)
-{
- if (GearUp) {
+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::MMass(void)
-{
+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::MProp(void)
-{
+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)
-{
+void FGAircraft::GetState(void) {
dt = State->Getdt();
alpha = Translation->Getalpha();
beta = Translation->Getbeta();
- phi = Rotation->Getphi();
- tht = Rotation->Gettht();
- psi = Rotation->Getpsi();
+ vEuler = Rotation->GetEuler();
}
+/******************************************************************************/
+
+void FGAircraft::ReadMetrics(FGConfigFile* AC_cfg) {
+ string token = "";
+ string parameter;
+
+ AC_cfg->GetNextConfigLine();
+
+ while ((token = AC_cfg->GetValue()) != "/METRICS") {
+ *AC_cfg >> parameter;
+ if (parameter == "AC_WINGAREA") {
+ *AC_cfg >> WingArea;
+ cout << " WingArea: " << WingArea << endl;
+ } else if (parameter == "AC_WINGSPAN") {
+ *AC_cfg >> WingSpan;
+ cout << " WingSpan: " << WingSpan << endl;
+ } else if (parameter == "AC_CHORD") {
+ *AC_cfg >> cbar;
+ cout << " Chord: " << cbar << endl;
+ } else if (parameter == "AC_IXX") {
+ *AC_cfg >> baseIxx;
+ cout << " baseIxx: " << baseIxx << endl;
+ } 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;
+ } else if (parameter == "AC_EMPTYWT") {
+ *AC_cfg >> EmptyWeight;
+ cout << " EmptyWeight: " << EmptyWeight << endl;
+ } else if (parameter == "AC_CGLOC") {
+ *AC_cfg >> vbaseXYZcg(eX) >> vbaseXYZcg(eY) >> vbaseXYZcg(eZ);
+ 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;
+ } 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::PutState(void)
-{
+/******************************************************************************/
+
+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++;
+ }
+ }
+}
+
+/******************************************************************************/
+
+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;
+ }
+ 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)) );
+}
+
+/******************************************************************************/
+
+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::DisplayCoeffFactors(vector <eParam> multipliers) {
+ cout << " Non-Dimensionalized by: ";
+
+ for (unsigned int i=0; i<multipliers.size();i++)
+ cout << State->paramdef[multipliers[i]];
+
+ cout << endl;
+}
+
+/******************************************************************************/
+
+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();
+ }
+ }
+
+ 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);
+ }
+ }
+
+ 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;
+ }
+
+ 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;
}
projects / flightgear.git / blobdiff