-/*******************************************************************************
-
+/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
Module: FGAircraft.cpp
Author: Jon S. Berndt
Date started: 12/12/98
Called by: FGFDMExec
------------- Copyright (C) 1999 Jon S. Berndt (jsb@hal-pc.org) -------------
-
+
This program is free software; you can redistribute it and/or modify it under
the terms of the GNU General Public License as published by the Free Software
Foundation; either version 2 of the License, or (at your option) any later
version.
-
+
This program is distributed in the hope that it will be useful, but WITHOUT
ANY WARRANTY; without even the implied warranty of MERCHANTABILITY or FITNESS
FOR A PARTICULAR PURPOSE. See the GNU General Public License for more
details.
-
+
You should have received a copy of the GNU General Public License along with
this program; if not, write to the Free Software Foundation, Inc., 59 Temple
Place - Suite 330, Boston, MA 02111-1307, USA.
-
+
Further information about the GNU General Public License can also be found on
the world wide web at http://www.gnu.org.
-
+
FUNCTIONAL DESCRIPTION
--------------------------------------------------------------------------------
Models the aircraft reactions and forces. This class is instantiated by the
-FGFDMExec class and scheduled as an FDM entry. LoadAircraft() is supplied with a
-name of a valid, registered aircraft, and the data file is parsed.
-
+FGFDMExec class and scheduled as an FDM entry.
+
HISTORY
--------------------------------------------------------------------------------
12/12/98 JSB Created
9/17/99 TP Combined force and moment functions. Added aero reference
point to config file. Added calculations for moments due to
difference in cg and aero reference point
-
-********************************************************************************
+
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
COMMENTS, REFERENCES, and NOTES
-********************************************************************************
-[1] Cooke, Zyda, Pratt, and McGhee, "NPSNET: Flight Simulation Dynamic Modeling
- Using Quaternions", Presence, Vol. 1, No. 4, pp. 404-420 Naval Postgraduate
- School, January 1994
-[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 <simgear/compiler.h>
-# endif
-# ifdef FG_HAVE_STD_INCLUDES
+# ifndef __BORLANDC__
+# include <simgear/compiler.h>
+# endif
+# ifdef SG_HAVE_STD_INCLUDES
# include <cmath>
# else
# include <math.h>
# endif
#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 **************************************
-*******************************************************************************/
-
-FGAircraft::FGAircraft(FGFDMExec* fdmex) : FGModel(fdmex),
- vMoments(3),
- vForces(3),
- vXYZrp(3),
- vbaseXYZcg(3),
- vXYZcg(3),
- vXYZep(3),
- vEuler(3)
-{
- Name = "FGAircraft";
+namespace JSBSim {
- AxisIdx["LIFT"] = 0;
- AxisIdx["SIDE"] = 1;
- AxisIdx["DRAG"] = 2;
- AxisIdx["ROLL"] = 3;
- AxisIdx["PITCH"] = 4;
- AxisIdx["YAW"] = 5;
-
- numTanks = numEngines = numSelectedFuelTanks = numSelectedOxiTanks = 0;
-}
+/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+DEFINITIONS
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
+/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+GLOBAL DATA
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
-/******************************************************************************/
+static const char *IdSrc = "$Id$";
+static const char *IdHdr = ID_AIRCRAFT;
+/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+CLASS IMPLEMENTATION
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
-FGAircraft::~FGAircraft(void)
+FGAircraft::FGAircraft(FGFDMExec* fdmex) : FGModel(fdmex)
{
+ Name = "FGAircraft";
+ WingSpan = 0.0;
+ HTailArea = VTailArea = 0.0;
+ HTailArm = VTailArm = 0.0;
+ lbarh = lbarv = 0.0;
+ vbarh = vbarv = 0.0;
+ WingIncidence = 0.0;
+
+ bind();
+
+ Debug(0);
}
-/******************************************************************************/
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-bool FGAircraft::LoadAircraft(string aircraft_path, string engine_path, string fname)
+FGAircraft::~FGAircraft()
{
- string path;
- string filename;
- string aircraftCfgFileName;
- string token;
-
- AircraftPath = aircraft_path;
- EnginePath = engine_path;
-
- aircraftCfgFileName = AircraftPath + "/" + fname + "/" + fname + ".cfg";
-
- FGConfigFile AC_cfg(aircraftCfgFileName);
-
- ReadPrologue(&AC_cfg);
-
- 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);
- }
- }
-
- return true;
+ unbind();
+ Debug(1);
}
-/******************************************************************************/
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
bool FGAircraft::Run(void)
{
if (!FGModel::Run()) { // if false then execute this Run()
- GetState();
-
- for (int i = 1; i <= 3; i++) vForces(i) = vMoments(i) = 0.0;
-
- MassChange();
-
- FMProp();
- FMAero();
- FMGear();
- FMMass();
+ 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 false;
-}
-
-/******************************************************************************/
-
-void FGAircraft::MassChange()
-{
- static FGColumnVector vXYZtank(3);
- float Tw;
- float IXXt, IYYt, IZZt, IXZt;
- int t;
- unsigned int axis_ctr;
-
- for (axis_ctr=1; axis_ctr<=3; axis_ctr++) vXYZtank(axis_ctr) = 0.0;
-
- // UPDATE TANK CONTENTS
- //
- // For each engine, cycle through the tanks and draw an equal amount of
- // fuel (or oxidizer) from each active tank. The needed amount of fuel is
- // determined by the engine in the FGEngine class. If more fuel is needed
- // than is available in the tank, then that amount is considered a shortage,
- // and will be drawn from the next tank. If the engine cannot be fed what it
- // needs, it will be considered to be starved, and will shut down.
-
- float Oshortage, Fshortage;
-
- for (int e=0; e<numEngines; e++) {
- Fshortage = Oshortage = 0.0;
- for (t=0; t<numTanks; t++) {
- switch(Engine[e]->GetType()) {
- case FGEngine::etRocket:
-
- switch(Tank[t]->GetType()) {
- case FGTank::ttFUEL:
- if (Tank[t]->GetSelected()) {
- Fshortage = Tank[t]->Reduce((Engine[e]->CalcFuelNeed()/
- numSelectedFuelTanks)*(dt*rate) + Fshortage);
- }
- break;
- case FGTank::ttOXIDIZER:
- if (Tank[t]->GetSelected()) {
- Oshortage = Tank[t]->Reduce((Engine[e]->CalcOxidizerNeed()/
- numSelectedOxiTanks)*(dt*rate) + Oshortage);
- }
- break;
- }
- break;
-
- case FGEngine::etPiston:
- case FGEngine::etTurboJet:
- case FGEngine::etTurboProp:
-
- if (Tank[t]->GetSelected()) {
- Fshortage = Tank[t]->Reduce((Engine[e]->CalcFuelNeed()/
- numSelectedFuelTanks)*(dt*rate) + Fshortage);
- }
- break;
- }
- }
- if ((Fshortage <= 0.0) || (Oshortage <= 0.0)) Engine[e]->SetStarved();
- else Engine[e]->SetStarved(false);
- }
-
- Weight = EmptyWeight;
- for (t=0; t<numTanks; t++)
- Weight += Tank[t]->GetContents();
-
- Mass = Weight / GRAVITY;
- // Calculate new CG here.
-
- Tw = 0;
- for (t=0; t<numTanks; t++) {
- vXYZtank(eX) += Tank[t]->GetX()*Tank[t]->GetContents();
- vXYZtank(eY) += Tank[t]->GetY()*Tank[t]->GetContents();
- vXYZtank(eZ) += Tank[t]->GetZ()*Tank[t]->GetContents();
-
- Tw += Tank[t]->GetContents();
- }
-
- vXYZcg = (vXYZtank + EmptyWeight*vbaseXYZcg) / (Tw + EmptyWeight);
-
- // Calculate new moments of inertia here
-
- 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::FMAero(void)
-{
- static FGColumnVector vFs(3);
- static FGColumnVector vDXYZcg(3);
- unsigned int axis_ctr,ctr;
-
- for (axis_ctr=1; axis_ctr<=3; axis_ctr++) vFs(axis_ctr) = 0.0;
-
- for (axis_ctr = 0; axis_ctr < 3; axis_ctr++) {
- for (ctr=0; ctr < Coeff[axis_ctr].size(); ctr++) {
- vFs(axis_ctr+1) += Coeff[axis_ctr][ctr].TotalValue();
- }
- }
-
- vForces += State->GetTs2b(alpha, beta)*vFs;
-
- // The d*cg distances below, given in inches, are the distances FROM the c.g.
- // TO the reference point. Since the c.g. and ref point are given in inches in
- // the structural system (X positive rearwards) and the body coordinate system
- // is given with X positive out the nose, the dxcg and dzcg values are
- // *rotated* 180 degrees about the Y axis.
-
- vDXYZcg(eX) = -(vXYZrp(eX) - vXYZcg(eX))/12.0; //cg and rp values are in inches
- vDXYZcg(eY) = (vXYZrp(eY) - vXYZcg(eY))/12.0;
- vDXYZcg(eZ) = -(vXYZrp(eZ) - vXYZcg(eZ))/12.0;
-
- vMoments(eL) += vForces(eZ)*vDXYZcg(eY) - vForces(eY)*vDXYZcg(eZ); // rolling moment
- vMoments(eM) += vForces(eX)*vDXYZcg(eZ) - vForces(eZ)*vDXYZcg(eX); // pitching moment
- vMoments(eN) += vForces(eX)*vDXYZcg(eY) - vForces(eY)*vDXYZcg(eX); // yawing moment
-
- for (axis_ctr = 0; axis_ctr < 3; axis_ctr++) {
- for (ctr = 0; ctr < Coeff[axis_ctr+3].size(); ctr++) {
- vMoments(axis_ctr+1) += Coeff[axis_ctr+3][ctr].TotalValue();
- }
- }
-}
-
-/******************************************************************************/
-
-void FGAircraft::FMGear(void)
-{
- if (GearUp) {
- // crash routine
- } else {
- for (unsigned int i=0;i<lGear.size();i++) {
- // lGear[i].
- }
+ return true;
}
}
-/******************************************************************************/
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGAircraft::FMMass(void)
+float FGAircraft::GetNlf(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;
+ return -1*Aerodynamics->GetvFs(3)/MassBalance->GetWeight();
}
-/******************************************************************************/
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGAircraft::FMProp(void)
-{
- for (int i=0;i<numEngines;i++) {
- vForces(eX) += Engine[i]->CalcThrust();
- }
-}
-
-/******************************************************************************/
-
-void FGAircraft::GetState(void)
-{
- dt = State->Getdt();
-
- alpha = Translation->Getalpha();
- beta = Translation->Getbeta();
- vEuler = Rotation->GetEuler();
-}
-
-/******************************************************************************/
-
-void FGAircraft::ReadMetrics(FGConfigFile* AC_cfg)
+bool FGAircraft::Load(FGConfigFile* AC_cfg)
{
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()) != "/METRICS") {
+ while ((token = AC_cfg->GetValue()) != string("/METRICS")) {
*AC_cfg >> parameter;
- if (parameter == "AC_WINGAREA") *AC_cfg >> WingArea;
- else if (parameter == "AC_WINGSPAN") *AC_cfg >> WingSpan;
- else if (parameter == "AC_CHORD") *AC_cfg >> cbar;
- else if (parameter == "AC_IXX") *AC_cfg >> baseIxx;
- else if (parameter == "AC_IYY") *AC_cfg >> baseIyy;
- else if (parameter == "AC_IZZ") *AC_cfg >> baseIzz;
- else if (parameter == "AC_IXZ") *AC_cfg >> baseIxz;
- else if (parameter == "AC_EMPTYWT") *AC_cfg >> EmptyWeight;
- else if (parameter == "AC_CGLOC") *AC_cfg >> vbaseXYZcg(eX) >> vbaseXYZcg(eY) >> vbaseXYZcg(eZ);
- else if (parameter == "AC_EYEPTLOC") *AC_cfg >> vXYZep(eX) >> vXYZep(eY) >> vXYZep(eZ);
- else if (parameter == "AC_AERORP") *AC_cfg >> vXYZrp(eX) >> vXYZrp(eY) >> vXYZrp(eZ);
+ if (parameter == "AC_WINGAREA") {
+ *AC_cfg >> WingArea;
+ if (debug_lvl > 0) cout << " WingArea: " << WingArea << endl;
+ } else if (parameter == "AC_WINGSPAN") {
+ *AC_cfg >> WingSpan;
+ if (debug_lvl > 0) cout << " WingSpan: " << WingSpan << endl;
+ } else if (parameter == "AC_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_VRP") {
+ *AC_cfg >> vXYZvrp(eX) >> vXYZvrp(eY) >> vXYZvrp(eZ);
+ if (debug_lvl > 0) cout << " Visual Ref Pt (x, y, z): " << vXYZvrp << endl;
+ Position->SetVRP(vXYZvrp);
+ } 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;
+ }
}
+
+ // 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::ReadPropulsion(FGConfigFile* AC_cfg)
+void FGAircraft::bind(void)
{
- 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++;
- }
- }
+ 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);
+ PropertyManager->Tie("metrics/visualrefpoint-x-in", this,1,
+ (PMF)&FGAircraft::GetXYZvrp);
+ PropertyManager->Tie("metrics/visualrefpoint-y-in", this,2,
+ (PMF)&FGAircraft::GetXYZvrp);
+ PropertyManager->Tie("metrics/visualrefpoint-z-in", this,3,
+ (PMF)&FGAircraft::GetXYZvrp);
}
-/******************************************************************************/
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGAircraft::ReadFlightControls(FGConfigFile* AC_cfg)
+void FGAircraft::unbind(void)
{
- string token;
-
- FCS->LoadFCS(AC_cfg);
+ 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");
+ PropertyManager->Untie("metrics/visualrefpoint-x-in");
+ PropertyManager->Untie("metrics/visualrefpoint-y-in");
+ PropertyManager->Untie("metrics/visualrefpoint-z-in");
}
-/******************************************************************************/
-
-void FGAircraft::ReadAerodynamics(FGConfigFile* AC_cfg)
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+// 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)
{
- string token, axis;
-
- AC_cfg->GetNextConfigLine();
+ if (debug_lvl <= 0) return;
- 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();
+ if (debug_lvl & 1) { // Standard console startup message output
+ if (from == 0) { // Constructor
}
}
-}
-
-/******************************************************************************/
-
-void FGAircraft::ReadUndercarriage(FGConfigFile* AC_cfg)
-{
- string token;
-
- AC_cfg->GetNextConfigLine();
-
- while ((token = AC_cfg->GetValue()) != "/UNDERCARRIAGE") {
- lGear.push_back(new FGLGear(AC_cfg));
+ if (debug_lvl & 2 ) { // Instantiation/Destruction notification
+ if (from == 0) cout << "Instantiated: FGAircraft" << endl;
+ if (from == 1) cout << "Destroyed: FGAircraft" << endl;
}
-}
-
-/******************************************************************************/
-
-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);
+ 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;
+ }
}
}
-/******************************************************************************/
-
-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;
-}
-
-/******************************************************************************/
-
-
+} // namespace JSBSim
projects / flightgear.git / blobdiff