-/*******************************************************************************
-
+/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
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
-[2] D. M. Henderson, "Euler Angles, Quaternions, and Transformation Matrices",
- JSC 12960, July 1977
-[3] Richard E. McFarland, "A Standard Kinematic Model for Flight Simulation at
- NASA-Ames", NASA CR-2497, January 1975
-[4] Barnes W. McCormick, "Aerodynamics, Aeronautics, and Flight Mechanics",
- Wiley & Sons, 1979 ISBN 0-471-03032-5
-[5] Bernard Etkin, "Dynamics of Flight, Stability and Control", Wiley & Sons,
- 1982 ISBN 0-471-08936-2
-
-The aerodynamic coefficients used in this model are:
-
-Longitudinal
- CL0 - Reference lift at zero alpha
- CD0 - Reference drag at zero alpha
- CDM - Drag due to Mach
- CLa - Lift curve slope (w.r.t. alpha)
- CDa - Drag curve slope (w.r.t. alpha)
- CLq - Lift due to pitch rate
- CLM - Lift due to Mach
- CLadt - Lift due to alpha rate
-
- Cmadt - Pitching Moment due to alpha rate
- Cm0 - Reference Pitching moment at zero alpha
- Cma - Pitching moment slope (w.r.t. alpha)
- Cmq - Pitch damping (pitch moment due to pitch rate)
- CmM - Pitch Moment due to Mach
-
-Lateral
- Cyb - Side force due to sideslip
- Cyr - Side force due to yaw rate
-
- Clb - Dihedral effect (roll moment due to sideslip)
- Clp - Roll damping (roll moment due to roll rate)
- Clr - Roll moment due to yaw rate
- Cnb - Weathercocking stability (yaw moment due to sideslip)
- Cnp - Rudder adverse yaw (yaw moment due to roll rate)
- Cnr - Yaw damping (yaw moment due to yaw rate)
-
-Control
- CLDe - Lift due to elevator
- CDDe - Drag due to elevator
- CyDr - Side force due to rudder
- CyDa - Side force due to aileron
-
- CmDe - Pitch moment due to elevator
- ClDa - Roll moment due to aileron
- ClDr - Roll moment due to rudder
- CnDr - Yaw moment due to rudder
- CnDa - Yaw moment due to aileron
-
-********************************************************************************
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
INCLUDES
-*******************************************************************************/
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
#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
#else
-# include <cmath>
+# if defined (sgi) && !defined(__GNUC__)
+# include <math.h>
+# else
+# include <cmath>
+# endif
#endif
#include "FGAircraft.h"
+#include "FGMassBalance.h"
+#include "FGInertial.h"
+#include "FGGroundReactions.h"
+#include "FGAerodynamics.h"
#include "FGTranslation.h"
#include "FGRotation.h"
#include "FGAtmosphere.h"
#include "FGPosition.h"
#include "FGAuxiliary.h"
#include "FGOutput.h"
+#include "FGPropertyManager.h"
-/*******************************************************************************
-************************************ CODE **************************************
-*******************************************************************************/
+/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+DEFINITIONS
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
-FGAircraft::FGAircraft(FGFDMExec* fdmex) : FGModel(fdmex)
-{
- int i;
+/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+GLOBAL DATA
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
- Name = "FGAircraft";
+static const char *IdSrc = "$Id$";
+static const char *IdHdr = ID_AIRCRAFT;
- for (i=0;i<6;i++) coeff_ctr[i] = 0;
-}
+/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+CLASS IMPLEMENTATION
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
-
-FGAircraft::~FGAircraft(void)
-{
-}
-
-bool FGAircraft::LoadAircraft(string aircraft_path, string engine_path, string fname)
+FGAircraft::FGAircraft(FGFDMExec* fdmex) : FGModel(fdmex)
{
- 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;
- Output->SocketStatusOutput("Reading Aircraft Configuration File: " + aircraftDef);
-
- 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 == "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;
- 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") {
+ Name = "FGAircraft";
+ HTailArea = VTailArea = 0.0;
+ HTailArm = VTailArm = 0.0;
+ lbarh = lbarv = 0.0;
+ vbarh = vbarv = 0.0;
- axis_descript = " Yaw Coefficients ...";
- axis = YawCoeff;
+ bind();
- }
+ Debug(0);
+}
- 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);
- }
- }
- cout << "End of Configuration File Parsing." << endl;
-
- return true;
+FGAircraft::~FGAircraft()
+{
+ unbind();
+ Debug(1);
}
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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;
-
- MassChange();
-
- FMProp(); FMAero(); FMGear(); FMMass();
-
- PutState();
+ vForces.InitMatrix();
+ vForces += Aerodynamics->GetForces();
+ vForces += Inertial->GetForces();
+ vForces += Propulsion->GetForces();
+ vForces += GroundReactions->GetForces();
+
+ vMoments.InitMatrix();
+ vMoments += Aerodynamics->GetMoments();
+ vMoments += Propulsion->GetMoments();
+ vMoments += GroundReactions->GetMoments();
+
+ vBodyAccel = vForces/MassBalance->GetMass();
+
+ vNcg = vBodyAccel/Inertial->gravity();
+
+ vNwcg = State->GetTb2s() * vNcg;
+ vNwcg(3) = -1*vNwcg(3) + 1;
+
+ return false;
} else { // skip Run() execution this time
+ return true;
}
- return false;
}
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGAircraft::MassChange()
+float FGAircraft::GetNlf(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;
- }
- }
- 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.
-
- 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();
-
- Tw += Tank[t]->GetContents();
- }
-
- Xcg = (Xt + EmptyWeight*baseXcg) / (Tw + EmptyWeight);
- Ycg = (Yt + EmptyWeight*baseYcg) / (Tw + EmptyWeight);
- Zcg = (Zt + EmptyWeight*baseZcg) / (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;
- }
-
- Ixx = baseIxx + IXXt;
- Iyy = baseIyy + IYYt;
- Izz = baseIzz + IZZt;
- Ixz = baseIxz + IXZt;
-
+ return -1*Aerodynamics->GetvFs(3)/MassBalance->GetWeight();
}
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGAircraft::FMAero(void)
+bool FGAircraft::Load(FGConfigFile* AC_cfg)
{
- float F[3];
- float Fxaero,Fyaero,Fzaero;
- float dxcg,dycg,dzcg;
- 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();
-
- Fxaero = - F[DragCoeff]*cos(alpha)*cos(beta)
- - F[SideCoeff]*cos(alpha)*sin(beta)
- + F[LiftCoeff]*sin(alpha);
- Fyaero = F[DragCoeff]*sin(beta)
- + F[SideCoeff]*cos(beta);
- Fzaero = - F[DragCoeff]*sin(alpha)*cos(beta)
- - F[SideCoeff]*sin(alpha)*sin(beta)
- - F[LiftCoeff]*cos(alpha);
-
- 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);
-
- // 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] += Fzaero*dycg - Fyaero*dzcg; //rolling moment
- Moments[1] += Fxaero*dzcg - Fzaero*dxcg; //pitching moment
- Moments[2] += -Fxaero*dycg + Fyaero*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();
+ string token = "";
+ string parameter;
+ double EW, bixx, biyy, bizz, bixy, bixz;
+ double pmWt, pmX, pmY, pmZ;
+ FGColumnVector3 vbaseXYZcg;
+
+ AC_cfg->GetNextConfigLine();
+
+ while ((token = AC_cfg->GetValue()) != string("/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_WINGINCIDENCE") {
+ *AC_cfg >> WingIncidence;
+ if (debug_lvl > 0) cout << " Chord: " << cbar << endl;
+ } else if (parameter == "AC_CHORD") {
+ *AC_cfg >> cbar;
+ if (debug_lvl > 0) cout << " Chord: " << cbar << endl;
+ } else if (parameter == "AC_HTAILAREA") {
+ *AC_cfg >> HTailArea;
+ if (debug_lvl > 0) cout << " H. Tail Area: " << HTailArea << endl;
+ } else if (parameter == "AC_HTAILARM") {
+ *AC_cfg >> HTailArm;
+ if (debug_lvl > 0) cout << " H. Tail Arm: " << HTailArm << endl;
+ } else if (parameter == "AC_VTAILAREA") {
+ *AC_cfg >> VTailArea;
+ if (debug_lvl > 0) cout << " V. Tail Area: " << VTailArea << endl;
+ } else if (parameter == "AC_VTAILARM") {
+ *AC_cfg >> VTailArm;
+ if (debug_lvl > 0) cout << " V. Tail Arm: " << VTailArm << endl;
+ } else if (parameter == "AC_IXX") {
+ *AC_cfg >> 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_IXY") {
+ *AC_cfg >> bixy;
+ if (debug_lvl > 0) cout << " baseIxy: " << bixy << endl;
+ MassBalance->SetBaseIxy(bixy);
+ } else if (parameter == "AC_IXZ") {
+ *AC_cfg >> bixz;
+ if (debug_lvl > 0) cout << " baseIxz: " << bixz << endl;
+ MassBalance->SetBaseIxz(bixz);
+ } else if (parameter == "AC_EMPTYWT") {
+ *AC_cfg >> 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_POINTMASS") {
+ *AC_cfg >> pmWt >> pmX >> pmY >> pmZ;
+ MassBalance->AddPointMass(pmWt, pmX, pmY, pmZ);
+ if (debug_lvl > 0) cout << " Point Mass Object: " << pmWt << " lbs. at "
+ << "X, Y, Z (in.): " << pmX << " " << pmY << " " << pmZ
+ << endl;
}
}
-}
-
-
-void FGAircraft::FMGear(void)
-{
- if (GearUp) {
- // crash routine
- } else {
- for (int i=0;i<lGear.size();i++) {
- // lGear[i].
+
+ // calculate some derived parameters
+ if (cbar != 0.0) {
+ lbarh = HTailArm/cbar;
+ lbarv = VTailArm/cbar;
+ if (WingArea != 0.0) {
+ vbarh = HTailArm*HTailArea / (cbar*WingArea);
+ vbarv = VTailArm*VTailArea / (cbar*WingArea);
}
- }
+ }
+ return true;
}
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGAircraft::FMMass(void)
+void FGAircraft::bind(void)
{
- Forces[0] += -GRAVITY*sin(tht) * Mass;
- Forces[1] += GRAVITY*sin(phi)*cos(tht) * Mass;
- Forces[2] += GRAVITY*cos(phi)*cos(tht) * Mass;
+ typedef double (FGAircraft::*PMF)(int) const;
+ PropertyManager->Tie("metrics/Sw-sqft", this,
+ &FGAircraft::GetWingArea);
+ PropertyManager->Tie("metrics/bw-ft", this,
+ &FGAircraft::GetWingSpan);
+ PropertyManager->Tie("metrics/cbarw-ft", this,
+ &FGAircraft::Getcbar);
+ PropertyManager->Tie("metrics/iw-deg", this,
+ &FGAircraft::GetWingIncidence);
+ PropertyManager->Tie("metrics/Sh-sqft", this,
+ &FGAircraft::GetHTailArea);
+ PropertyManager->Tie("metrics/lh-ft", this,
+ &FGAircraft::GetHTailArm);
+ PropertyManager->Tie("metrics/Sv-sqft", this,
+ &FGAircraft::GetVTailArea);
+ PropertyManager->Tie("metrics/lv-ft", this,
+ &FGAircraft::GetVTailArm);
+ PropertyManager->Tie("metrics/lh-norm", this,
+ &FGAircraft::Getlbarh);
+ PropertyManager->Tie("metrics/lv-norm", this,
+ &FGAircraft::Getlbarv);
+ PropertyManager->Tie("metrics/vbarh-norm", this,
+ &FGAircraft::Getvbarh);
+ PropertyManager->Tie("metrics/vbarv-norm", this,
+ &FGAircraft::Getvbarv);
+ PropertyManager->Tie("moments/l-total-lbsft", this,1,
+ (PMF)&FGAircraft::GetMoments);
+ PropertyManager->Tie("moments/m-total-lbsft", this,2,
+ (PMF)&FGAircraft::GetMoments);
+ PropertyManager->Tie("moments/n-total-lbsft", this,3,
+ (PMF)&FGAircraft::GetMoments);
+ PropertyManager->Tie("forces/fbx-total-lbs", this,1,
+ (PMF)&FGAircraft::GetForces);
+ PropertyManager->Tie("forces/fby-total-lbs", this,2,
+ (PMF)&FGAircraft::GetForces);
+ PropertyManager->Tie("forces/fbz-total-lbs", this,3,
+ (PMF)&FGAircraft::GetForces);
+ PropertyManager->Tie("metrics/aero-rp-x-ft", this,1,
+ (PMF)&FGAircraft::GetXYZrp);
+ PropertyManager->Tie("metrics/aero-rp-y-ft", this,2,
+ (PMF)&FGAircraft::GetXYZrp);
+ PropertyManager->Tie("metrics/aero-rp-z-ft", this,3,
+ (PMF)&FGAircraft::GetXYZrp);
+ PropertyManager->Tie("metrics/eyepoint-x-ft", this,1,
+ (PMF)&FGAircraft::GetXYZep);
+ PropertyManager->Tie("metrics/eyepoint-y-ft", this,2,
+ (PMF)&FGAircraft::GetXYZep);
+ PropertyManager->Tie("metrics/eyepoint-z-ft", this,3,
+ (PMF)&FGAircraft::GetXYZep);
}
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGAircraft::FMProp(void)
+void FGAircraft::unbind(void)
{
- for (int i=0;i<numEngines;i++) {
- Forces[0] += Engine[i]->CalcThrust();
- }
+ PropertyManager->Untie("metrics/Sw-sqft");
+ PropertyManager->Untie("metrics/bw-ft");
+ PropertyManager->Untie("metrics/cbarw-ft");
+ PropertyManager->Untie("metrics/iw-deg");
+ PropertyManager->Untie("metrics/Sh-sqft");
+ PropertyManager->Untie("metrics/lh-ft");
+ PropertyManager->Untie("metrics/Sv-sqft");
+ PropertyManager->Untie("metrics/lv-ft");
+ PropertyManager->Untie("metrics/lh-norm");
+ PropertyManager->Untie("metrics/lv-norm");
+ PropertyManager->Untie("metrics/vbarh-norm");
+ PropertyManager->Untie("metrics/vbarv-norm");
+ PropertyManager->Untie("moments/l-total-lbsft");
+ PropertyManager->Untie("moments/m-total-lbsft");
+ PropertyManager->Untie("moments/n-total-lbsft");
+ PropertyManager->Untie("forces/fbx-total-lbs");
+ PropertyManager->Untie("forces/fby-total-lbs");
+ PropertyManager->Untie("forces/fbz-total-lbs");
+ PropertyManager->Untie("metrics/aero-rp-x-ft");
+ PropertyManager->Untie("metrics/aero-rp-y-ft");
+ PropertyManager->Untie("metrics/aero-rp-z-ft");
+ PropertyManager->Untie("metrics/eyepoint-x-ft");
+ PropertyManager->Untie("metrics/eyepoint-y-ft");
+ PropertyManager->Untie("metrics/eyepoint-z-ft");
}
-void FGAircraft::GetState(void)
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+// The bitmasked value choices are as follows:
+// unset: In this case (the default) JSBSim would only print
+// out the normally expected messages, essentially echoing
+// the config files as they are read. If the environment
+// variable is not set, debug_lvl is set to 1 internally
+// 0: This requests JSBSim not to output any messages
+// whatsoever.
+// 1: This value explicity requests the normal JSBSim
+// startup messages
+// 2: This value asks for a message to be printed out when
+// a class is instantiated
+// 4: When this value is set, a message is displayed when a
+// FGModel object executes its Run() method
+// 8: When this value is set, various runtime state variables
+// are printed out periodically
+// 16: When set various parameters are sanity checked and
+// a message is printed out when they go out of bounds
+
+void FGAircraft::Debug(int from)
{
- dt = State->Getdt();
-
- alpha = Translation->Getalpha();
- beta = Translation->Getbeta();
- phi = Rotation->Getphi();
- tht = Rotation->Gettht();
- psi = Rotation->Getpsi();
-}
-
+ if (debug_lvl <= 0) return;
-void FGAircraft::PutState(void)
-{
+ if (debug_lvl & 1) { // Standard console startup message output
+ if (from == 0) { // Constructor
+ }
+ }
+ if (debug_lvl & 2 ) { // Instantiation/Destruction notification
+ if (from == 0) cout << "Instantiated: FGAircraft" << endl;
+ if (from == 1) cout << "Destroyed: FGAircraft" << endl;
+ }
+ if (debug_lvl & 4 ) { // Run() method entry print for FGModel-derived objects
+ }
+ if (debug_lvl & 8 ) { // Runtime state variables
+ }
+ if (debug_lvl & 16) { // Sanity checking
+ }
+ if (debug_lvl & 64) {
+ if (from == 0) { // Constructor
+ cout << IdSrc << endl;
+ cout << IdHdr << endl;
+ }
+ }
}
projects / flightgear.git / blobdiff