-/*******************************************************************************
-
+/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
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
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
-
-********************************************************************************
+ 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 <Include/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 **************************************
-*******************************************************************************/
-
-FGAircraft::FGAircraft(FGFDMExec* fdmex) : FGModel(fdmex)
+/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+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),
+ vXYZep(3),
+ vEuler(3),
+ vDXYZcg(3),
+ vAeroBodyForces(3)
{
- int i;
-
Name = "FGAircraft";
- for (i=0;i<6;i++) coeff_ctr[i] = 0;
+ GearUp = false;
+
+ 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 fullpath;
- string filename;
- string aircraftDef;
- string tag;
- string holding_string;
- char scratch[128];
- ifstream coeffInFile;
- streampos gpos;
- int axis;
- string axis_descript;
- bool readAeroRp=false;
-
- axis = -1;
- aircraftDef = aircraft_path + "/" + fname + "/" + fname + ".cfg";
- ifstream aircraftfile(aircraftDef.c_str());
- cout << "Reading Aircraft Configuration File: " << aircraftDef << endl;
- Output->SocketStatusOutput("Reading Aircraft Configuration File: " + aircraftDef);
-
- numTanks = numEngines = 0;
- numSelectedOxiTanks = numSelectedFuelTanks = 0;
-
- Xcg=Ycg=Zcg=0; //protection for no cg specified in file
-
- 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 == "CFG_VERSION") {
- aircraftfile >> CFGVersion;
- cout << "Config file version: " << CFGVersion << endl;
- if (CFGVersion < NEEDED_CFG_VERSION) {
- cout << endl << "YOU HAVE AN OLD CFG FILE FOR THIS AIRCRAFT."
- " RESULTS WILL BE UNPREDICTABLE !!" << endl << endl;
- }
- } else 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_AERORP") {
- aircraftfile >> Xrp >> Yrp >> Zrp;
- readAeroRp=true;
- cout << "Aerodynamic Reference Point: " << Xrp << " " << Yrp << " " << Zrp << 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_GEAR") {
-
- lGear.push_back(new FGLGear(aircraftfile));
-
- } 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 token;
+
+ ReadPrologue(AC_cfg);
+
+ while ((AC_cfg->GetNextConfigLine() != "EOF") &&
+ (token = AC_cfg->GetValue()) != "/FDM_CONFIG") {
+ if (token == "METRICS") {
+ if (debug_lvl > 0) cout << fgcyan << "\n Reading Metrics" << fgdef << endl;
+ ReadMetrics(AC_cfg);
+ } else if (token == "AERODYNAMICS") {
+ if (debug_lvl > 0) cout << fgcyan << "\n Reading Aerodynamics" << fgdef << endl;
+ ReadAerodynamics(AC_cfg);
+ } else if (token == "UNDERCARRIAGE") {
+ if (debug_lvl > 0) cout << fgcyan << "\n Reading Landing Gear" << fgdef << endl;
+ ReadUndercarriage(AC_cfg);
+ } else if (token == "PROPULSION") {
+ if (debug_lvl > 0) cout << fgcyan << "\n Reading Propulsion" << fgdef << endl;
+ ReadPropulsion(AC_cfg);
+ } else if (token == "FLIGHT_CONTROL") {
+ 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);
}
}
-
- if(!readAeroRp) {
- Xrp = Xcg;
- Yrp = Ycg;
- Zrp = Zcg;
- cout << "Aerodynamic reference point not found, set to empty weight cg location" << endl;
- }
-
- 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;
+ vForces.InitMatrix();
+ vMoments.InitMatrix();
- MassChange();
+ FMProp();
+ FMAero();
+ FMMass();
+ FMGear();
- FMProp(); FMAero(); FMGear(); FMMass();
-
- PutState();
+ return false;
} else { // skip Run() execution this time
+ return true;
}
- return false;
}
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGAircraft::MassChange()
+void FGAircraft::FMAero(void)
{
- float Xt, Xw, Yt, Yw, Zt, Zw, Tw;
- float IXXt, IYYt, IZZt, IXZt;
- int t;
-
- // 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;
- }
+ vForces += Aerodynamics->GetForces();
+ vMoments += Aerodynamics->GetMoments();
+}
+
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
+void FGAircraft::FMGear(void)
+{
+ if ( !GearUp ) {
+ vector <FGLGear>::iterator iGear = lGear.begin();
+ while (iGear != lGear.end()) {
+ vForces += iGear->Force();
+ vMoments += iGear->Moment();
+ iGear++;
}
- if ((Fshortage <= 0.0) || (Oshortage <= 0.0)) Engine[e]->SetStarved();
- else Engine[e]->SetStarved(false);
+ } else {
+ // Crash Routine
}
+}
+
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
+void FGAircraft::FMMass(void)
+{
+ vForces += Inertial->GetForces();
+}
- Weight = EmptyWeight;
- for (t=0; t<numTanks; t++)
- Weight += Tank[t]->GetContents();
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
- Mass = Weight / GRAVITY;
+void FGAircraft::FMProp(void)
+{
+ vForces += Propulsion->GetForces();
+ vMoments += Propulsion->GetMoments();
+}
- // Calculate new CG here.
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
- Xt = Yt = Zt = Tw = 0;
- Xw = Yw = Zw = 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();
+void FGAircraft::GetState(void)
+{
+ dt = State->Getdt();
- Tw += Tank[t]->GetContents();
- }
+ alpha = Translation->Getalpha();
+ beta = Translation->Getbeta();
+ vEuler = Rotation->GetEuler();
+}
- Xcg = (Xt + EmptyWeight*baseXcg) / (Tw + EmptyWeight);
- Ycg = (Yt + EmptyWeight*baseYcg) / (Tw + EmptyWeight);
- Zcg = (Zt + EmptyWeight*baseZcg) / (Tw + EmptyWeight);
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
- // Calculate new moments of inertia here
+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;
+ 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;
+ }
+ }
+}
- 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;
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
+void FGAircraft::ReadPropulsion(FGConfigFile* AC_cfg) {
+ if (!Propulsion->Load(AC_cfg)) {
+ cerr << "Propulsion not successfully loaded" << endl;
}
+}
- Ixx = baseIxx + IXXt;
- Iyy = baseIyy + IYYt;
- Izz = baseIzz + IZZt;
- Ixz = baseIxz + IXZt;
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+void FGAircraft::ReadFlightControls(FGConfigFile* AC_cfg) {
+ if (!FCS->Load(AC_cfg)) {
+ cerr << "Flight Controls not successfully loaded" << endl;
+ }
}
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGAircraft::FMAero(void)
+void FGAircraft::ReadAerodynamics(FGConfigFile* AC_cfg)
{
- float F[3];
- float dxcg,dycg,dzcg;
- float ca, cb, sa, sb;
- int axis_ctr,ctr;
- F[0] = F[1] = F[2] = 0.0;
-
- for (axis_ctr = 0; axis_ctr < 3; axis_ctr++) {
- for (ctr=0; ctr < coeff_ctr[axis_ctr]; ctr++) {
- F[axis_ctr] += Coeff[axis_ctr][ctr]->TotalValue();
- Coeff[axis_ctr][ctr]->DumpSD();
- }
+ if (!Aerodynamics->Load(AC_cfg)) {
+ cerr << "Aerodynamics not successfully loaded" << endl;
}
- ca = cos(alpha);
- sa = sin(alpha);
- cb = cos(beta);
- sb = sin(beta);
-
- Forces[0] += - F[DragCoeff]*ca*cb
- - F[SideCoeff]*ca*sb
- + F[LiftCoeff]*sa;
- Forces[1] += F[DragCoeff]*sb
- + F[SideCoeff]*cb;
- Forces[2] += - F[DragCoeff]*sa*cb
- - F[SideCoeff]*sa*sb
- - F[LiftCoeff]*ca;
-
- // 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.
-
- dxcg = -(Xrp - Xcg)/12; //cg and rp values are in inches
- dycg = (Yrp - Ycg)/12;
- dzcg = -(Zrp - Zcg)/12;
-
- Moments[0] += Forces[2]*dycg - Forces[1]*dzcg; //rolling moment
- Moments[1] += Forces[0]*dzcg - Forces[2]*dxcg; //pitching moment
- Moments[2] += -Forces[0]*dycg + Forces[1]*dxcg; //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();
- Coeff[axis_ctr+3][ctr]->DumpSD();
- }
- }
}
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGAircraft::FMGear(void)
-{
- if (GearUp) {
- // crash routine
- } else {
- for (int i=0;i<lGear.size();i++) {
- // lGear[i].
- }
+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;
+ }
+ 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);
-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;
+ 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");
+ 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::FMProp(void)
-{
- for (int i=0;i<numEngines;i++) {
- Forces[0] += Engine[i]->CalcThrust();
+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;
}
-void FGAircraft::GetState(void)
-{
- dt = State->Getdt();
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
- alpha = Translation->Getalpha();
- beta = Translation->Getbeta();
- phi = Rotation->Getphi();
- tht = Rotation->Gettht();
- psi = Rotation->Getpsi();
+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::PutState(void)
+void FGAircraft::Debug(void)
{
+ //TODO: Add your source code here
}
projects / flightgear.git / blobdiff