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
#ifdef FGFS
# ifndef __BORLANDC__
-# include <Include/compiler.h>
+# include <simgear/compiler.h>
# endif
# ifdef FG_HAVE_STD_INCLUDES
# include <cmath>
************************************ CODE **************************************
*******************************************************************************/
-FGAircraft::FGAircraft(FGFDMExec* fdmex) : FGModel(fdmex)
+FGAircraft::FGAircraft(FGFDMExec* fdmex) : FGModel(fdmex),
+ vMoments(3),
+ vForces(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["LIFT"] = 0;
+ AxisIdx["SIDE"] = 1;
+ AxisIdx["DRAG"] = 2;
+ AxisIdx["ROLL"] = 3;
+ AxisIdx["PITCH"] = 4;
+ AxisIdx["YAW"] = 5;
+
+ numTanks = numEngines = numSelectedFuelTanks = numSelectedOxiTanks = 0;
}
+/******************************************************************************/
+
+
FGAircraft::~FGAircraft(void)
{
}
+/******************************************************************************/
+
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;
-#if defined(__BORLANDC__) || defined(FG_HAVE_NATIVE_SGI_COMPILERS) || defined(_MSC_VER)
- 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 >> baseIxx;
- cout << "Aircraft Base Ixx: " << baseIxx << endl;
- } else if (holding_string == "AC_IYY") {
- aircraftfile >> baseIyy;
- cout << "Aircraft Base Iyy: " << baseIyy << endl;
- } else if (holding_string == "AC_IZZ") {
- aircraftfile >> baseIzz;
- cout << "Aircraft Base Izz: " << baseIzz << endl;
- } else if (holding_string == "AC_IXZ") {
- aircraftfile >> baseIxz;
- cout << "Aircraft Base Ixz: " << baseIxz << 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 >> baseXcg >> baseYcg >> baseZcg;
- cout << "Aircraft Base C.G.: " << baseXcg << " " << baseYcg << " " << baseZcg << 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;
-
- } 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") {
-
- axis_descript = " Pitch Coefficients ...";
- axis = PitchCoeff;
-
- } else if (holding_string == "YAW") {
-
- axis_descript = " Yaw Coefficients ...";
- axis = YawCoeff;
-
- }
-
- 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);
+ string aircraftCfgFileName;
+ string token;
+
+ AircraftPath = aircraft_path;
+ EnginePath = engine_path;
+
+ aircraftCfgFileName = AircraftPath + "/" + fname + "/" + fname + ".cfg";
+
+ FGConfigFile AC_cfg(aircraftCfgFileName);
+
+ 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);
}
}
- cout << "End of Configuration File Parsing." << endl;
return true;
}
+/******************************************************************************/
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();
} else { // skip Run() execution this time
}
return false;
}
+/******************************************************************************/
void FGAircraft::MassChange()
{
- float Xt, Xw, Yt, Yw, Zt, Zw, Tw;
+ 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
//
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 += Tank[t]->GetContents();
Mass = Weight / GRAVITY;
-
// Calculate new CG here.
- Xt = Yt = Zt = 0;
- Xw = Yw = Zw = 0;
+ Tw = 0;
for (t=0; t<numTanks; t++) {
- Xt += Tank[t]->GetX()*Tank[t]->GetContents();
- Yt += Tank[t]->GetY()*Tank[t]->GetContents();
- Zt += Tank[t]->GetZ()*Tank[t]->GetContents();
+ 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();
}
- Xcg = (Xt + EmptyWeight*baseXcg) / (Tw + EmptyWeight);
- Ycg = (Yt + EmptyWeight*baseYcg) / (Tw + EmptyWeight);
- Zcg = (Zt + EmptyWeight*baseZcg) / (Tw + EmptyWeight);
+ 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()-Xcg)/12.0)*((Tank[t]->GetX() - Xcg)/12.0)*Tank[t]->GetContents()/GRAVITY;
- IYYt += ((Tank[t]->GetY()-Ycg)/12.0)*((Tank[t]->GetY() - Ycg)/12.0)*Tank[t]->GetContents()/GRAVITY;
- IZZt += ((Tank[t]->GetZ()-Zcg)/12.0)*((Tank[t]->GetZ() - Zcg)/12.0)*Tank[t]->GetContents()/GRAVITY;
- IXZt += ((Tank[t]->GetX()-Xcg)/12.0)*((Tank[t]->GetZ() - Zcg)/12.0)*Tank[t]->GetContents()/GRAVITY;
+ 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;
}
+/******************************************************************************/
-void FGAircraft::FAero(void)
+void FGAircraft::FMAero(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);
+ 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();
+ }
+ }
}
+/******************************************************************************/
-void FGAircraft::FGear(void)
+void FGAircraft::FMGear(void)
{
if (GearUp) {
// crash routine
} else {
-
+ for (unsigned int i=0;i<lGear.size();i++) {
+ // lGear[i].
+ }
}
}
+/******************************************************************************/
-void FGAircraft::FMass(void)
+void FGAircraft::FMMass(void)
{
- Forces[0] += -GRAVITY*sin(tht) * Mass;
- Forces[1] += GRAVITY*sin(phi)*cos(tht) * Mass;
- Forces[2] += GRAVITY*cos(phi)*cos(tht) * Mass;
+ 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::FProp(void)
+void FGAircraft::FMProp(void)
{
for (int i=0;i<numEngines;i++) {
- Forces[0] += Engine[i]->CalcThrust();
+ vForces(eX) += Engine[i]->CalcThrust();
}
}
+/******************************************************************************/
-void FGAircraft::MAero(void)
+void FGAircraft::GetState(void)
{
- int axis_ctr, ctr;
-
- 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();
- }
+ dt = State->Getdt();
+
+ alpha = Translation->Getalpha();
+ beta = Translation->Getbeta();
+ 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;
+ 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);
}
}
+/******************************************************************************/
-void FGAircraft::MGear(void)
+void FGAircraft::ReadPropulsion(FGConfigFile* AC_cfg)
{
- if (GearUp) {
- } else {
+ 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::MMass(void)
+void FGAircraft::ReadFlightControls(FGConfigFile* AC_cfg)
{
+ string token;
+
+ FCS->LoadFCS(AC_cfg);
}
+/******************************************************************************/
-void FGAircraft::MProp(void)
+void FGAircraft::ReadAerodynamics(FGConfigFile* AC_cfg)
{
+ string token, axis;
+
+ 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();
+ }
+ }
}
+/******************************************************************************/
-void FGAircraft::GetState(void)
+void FGAircraft::ReadUndercarriage(FGConfigFile* AC_cfg)
{
- dt = State->Getdt();
+ string token;
- alpha = Translation->Getalpha();
- beta = Translation->Getbeta();
- phi = Rotation->Getphi();
- tht = Rotation->Gettht();
- psi = Rotation->Getpsi();
+ AC_cfg->GetNextConfigLine();
+
+ while ((token = AC_cfg->GetValue()) != "/UNDERCARRIAGE") {
+ lGear.push_back(new FGLGear(AC_cfg));
+ }
+}
+
+/******************************************************************************/
+
+void FGAircraft::ReadPrologue(FGConfigFile* AC_cfg)
+{
+ string token = AC_cfg->GetValue();
+
+ 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);
+ }
}
+/******************************************************************************/
-void FGAircraft::PutState(void)
+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;
}
+/******************************************************************************/
+
+
projects / flightgear.git / blobdiff