/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-
+
Header: FGTrimAxis.cpp
Author: Tony Peden
Date started: 7/3/00
-
+
--------- Copyright (C) 1999 Anthony K. Peden (apeden@earthlink.net) ---------
-
+
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.
-
-
+
+
HISTORY
--------------------------------------------------------------------------------
7/3/00 TP Created
-
+
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
INCLUDES
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
+#ifdef _MSC_VER
+# pragma warning (disable : 4786)
+#endif
+
#include <string>
#include <stdlib.h>
#include "FGTrimAxis.h"
#include "FGAircraft.h"
#include "FGPropulsion.h"
+#include "FGAerodynamics.h"
+
+
+namespace JSBSim {
static const char *IdSrc = "$Id$";
static const char *IdHdr = ID_TRIMAXIS;
-extern short debug_lvl;
-
/*****************************************************************************/
FGTrimAxis::FGTrimAxis(FGFDMExec* fdex, FGInitialCondition* ic, State st,
fgic=ic;
state=st;
control=ctrl;
- solver_eps=tolerance;
max_iterations=10;
control_value=0;
its_to_stable_value=0;
state_convert=1.0;
control_convert=1.0;
state_value=0;
+ state_target=0;
+ switch(state) {
+ case tUdot: tolerance = DEFAULT_TOLERANCE; break;
+ case tVdot: tolerance = DEFAULT_TOLERANCE; break;
+ case tWdot: tolerance = DEFAULT_TOLERANCE; break;
+ case tQdot: tolerance = DEFAULT_TOLERANCE / 10; break;
+ case tPdot: tolerance = DEFAULT_TOLERANCE / 10; break;
+ case tRdot: tolerance = DEFAULT_TOLERANCE / 10; break;
+ case tHmgt: tolerance = 0.01; break;
+ case tNlf: state_target=1.0; tolerance = 1E-5; break;
+ case tAll: break;
+ }
+
+ solver_eps=tolerance;
switch(control) {
case tThrottle:
control_min=0;
control_value=0.5;
break;
case tBeta:
- control_min=-30*DEGTORAD;
- control_max=30*DEGTORAD;
- control_convert=RADTODEG;
+ control_min=-30*degtorad;
+ control_max=30*degtorad;
+ control_convert=radtodeg;
break;
case tAlpha:
- control_min=fdmex->GetAircraft()->GetAlphaCLMin();
- control_max=fdmex->GetAircraft()->GetAlphaCLMax();
+ control_min=fdmex->GetAerodynamics()->GetAlphaCLMin();
+ control_max=fdmex->GetAerodynamics()->GetAlphaCLMax();
if(control_max <= control_min) {
- control_max=20*DEGTORAD;
- control_min=-5*DEGTORAD;
+ control_max=20*degtorad;
+ control_min=-5*degtorad;
}
control_value= (control_min+control_max)/2;
- control_convert=RADTODEG;
+ control_convert=radtodeg;
solver_eps=tolerance/100;
break;
case tPitchTrim:
case tRudder:
control_min=-1;
control_max=1;
- state_convert=RADTODEG;
+ state_convert=radtodeg;
solver_eps=tolerance/100;
break;
case tAltAGL:
control_min=0;
control_max=30;
- control_value=fdmex->GetPosition()->GetDistanceAGL();
+ control_value=fdmex->GetPropagate()->GetDistanceAGL();
solver_eps=tolerance/100;
break;
case tTheta:
- control_min=fdmex->GetRotation()->Gettht() - 5*DEGTORAD;
- control_max=fdmex->GetRotation()->Gettht() + 5*DEGTORAD;
- state_convert=RADTODEG;
+ control_min=fdmex->GetPropagate()->GetEuler(eTht) - 5*degtorad;
+ control_max=fdmex->GetPropagate()->GetEuler(eTht) + 5*degtorad;
+ state_convert=radtodeg;
break;
case tPhi:
- control_min=fdmex->GetRotation()->Getphi() - 30*DEGTORAD;
- control_max=fdmex->GetRotation()->Getphi() + 30*DEGTORAD;
- state_convert=RADTODEG;
- control_convert=RADTODEG;
+ control_min=fdmex->GetPropagate()->GetEuler(ePhi) - 30*degtorad;
+ control_max=fdmex->GetPropagate()->GetEuler(ePhi) + 30*degtorad;
+ state_convert=radtodeg;
+ control_convert=radtodeg;
break;
case tGamma:
solver_eps=tolerance/100;
- control_min=-80*DEGTORAD;
- control_max=80*DEGTORAD;
- control_convert=RADTODEG;
+ control_min=-80*degtorad;
+ control_max=80*degtorad;
+ control_convert=radtodeg;
break;
case tHeading:
- control_min=fdmex->GetRotation()->Getpsi() - 30*DEGTORAD;
- control_max=fdmex->GetRotation()->Getpsi() + 30*DEGTORAD;
- state_convert=RADTODEG;
+ control_min=fdmex->GetPropagate()->GetEuler(ePsi) - 30*degtorad;
+ control_max=fdmex->GetPropagate()->GetEuler(ePsi) + 30*degtorad;
+ state_convert=radtodeg;
break;
}
-
- switch(state) {
- case tUdot: tolerance = DEFAULT_TOLERANCE; break;
- case tVdot: tolerance = DEFAULT_TOLERANCE; break;
- case tWdot: tolerance = DEFAULT_TOLERANCE; break;
- case tQdot: tolerance = DEFAULT_TOLERANCE / 10; break;
- case tPdot: tolerance = DEFAULT_TOLERANCE / 10; break;
- case tRdot: tolerance = DEFAULT_TOLERANCE / 10; break;
- case tHmgt: tolerance = 0.01; break;
- }
-
- if (debug_lvl & 2) cout << "Instantiated: FGTrimAxis" << endl;
+
+
+ Debug(0);
}
/*****************************************************************************/
-FGTrimAxis::~FGTrimAxis()
+FGTrimAxis::~FGTrimAxis(void)
{
- if (debug_lvl & 2) cout << "Destroyed: FGTrimAxis" << endl;
+ Debug(1);
}
/*****************************************************************************/
void FGTrimAxis::getState(void) {
switch(state) {
- case tUdot: state_value=fdmex->GetTranslation()->GetUVWdot(1); break;
- case tVdot: state_value=fdmex->GetTranslation()->GetUVWdot(2); break;
- case tWdot: state_value=fdmex->GetTranslation()->GetUVWdot(3); break;
- case tQdot: state_value=fdmex->GetRotation()->GetPQRdot(2);break;
- case tPdot: state_value=fdmex->GetRotation()->GetPQRdot(1); break;
- case tRdot: state_value=fdmex->GetRotation()->GetPQRdot(3); break;
- case tHmgt: state_value=computeHmgt(); break;
+ case tUdot: state_value=fdmex->GetPropagate()->GetUVWdot(1)-state_target; break;
+ case tVdot: state_value=fdmex->GetPropagate()->GetUVWdot(2)-state_target; break;
+ case tWdot: state_value=fdmex->GetPropagate()->GetUVWdot(3)-state_target; break;
+ case tQdot: state_value=fdmex->GetPropagate()->GetPQRdot(2)-state_target;break;
+ case tPdot: state_value=fdmex->GetPropagate()->GetPQRdot(1)-state_target; break;
+ case tRdot: state_value=fdmex->GetPropagate()->GetPQRdot(3)-state_target; break;
+ case tHmgt: state_value=computeHmgt()-state_target; break;
+ case tNlf: state_value=fdmex->GetAircraft()->GetNlf()-state_target; break;
+ case tAll: break;
}
}
void FGTrimAxis::getControl(void) {
switch(control) {
case tThrottle: control_value=fdmex->GetFCS()->GetThrottleCmd(0); break;
- case tBeta: control_value=fdmex->GetTranslation()->Getalpha(); break;
- case tAlpha: control_value=fdmex->GetTranslation()->Getbeta(); break;
+ case tBeta: control_value=fdmex->GetAuxiliary()->Getalpha(); break;
+ case tAlpha: control_value=fdmex->GetAuxiliary()->Getbeta(); break;
case tPitchTrim: control_value=fdmex->GetFCS() -> GetPitchTrimCmd(); break;
case tElevator: control_value=fdmex->GetFCS() -> GetDeCmd(); break;
case tRollTrim:
case tAileron: control_value=fdmex->GetFCS() -> GetDaCmd(); break;
case tYawTrim:
case tRudder: control_value=fdmex->GetFCS() -> GetDrCmd(); break;
- case tAltAGL: control_value=fdmex->GetPosition()->GetDistanceAGL();break;
- case tTheta: control_value=fdmex->GetRotation()->Gettht(); break;
- case tPhi: control_value=fdmex->GetRotation()->Getphi(); break;
- case tGamma: control_value=fdmex->GetPosition()->GetGamma();break;
- case tHeading: control_value=fdmex->GetRotation()->Getpsi(); break;
+ case tAltAGL: control_value=fdmex->GetPropagate()->GetDistanceAGL();break;
+ case tTheta: control_value=fdmex->GetPropagate()->GetEuler(eTht); break;
+ case tPhi: control_value=fdmex->GetPropagate()->GetEuler(ePhi); break;
+ case tGamma: control_value=fdmex->GetAuxiliary()->GetGamma();break;
+ case tHeading: control_value=fdmex->GetPropagate()->GetEuler(ePsi); break;
}
}
/*****************************************************************************/
-float FGTrimAxis::computeHmgt(void) {
- float diff;
-
- diff = fdmex->GetRotation()->Getpsi() -
- fdmex->GetPosition()->GetGroundTrack();
-
+double FGTrimAxis::computeHmgt(void) {
+ double diff;
+
+ diff = fdmex->GetPropagate()->GetEuler(ePsi) -
+ fdmex->GetAuxiliary()->GetGroundTrack();
+
if( diff < -M_PI ) {
return (diff + 2*M_PI);
} else if( diff > M_PI ) {
}
}
-
+
/*****************************************************************************/
}
-
+
/*****************************************************************************/
// the aircraft center of rotation is no longer the cg once the gear
-// contact the ground so the altitude needs to be changed when pitch
-// and roll angle are adjusted. Instead of attempting to calculate the
+// contact the ground so the altitude needs to be changed when pitch
+// and roll angle are adjusted. Instead of attempting to calculate the
// new center of rotation, pick a gear unit as a reference and use its
// location vector to calculate the new height change. i.e. new altitude =
-// earth z component of that vector (which is in body axes )
-void FGTrimAxis::SetThetaOnGround(float ff) {
+// earth z component of that vector (which is in body axes )
+void FGTrimAxis::SetThetaOnGround(double ff) {
int center,i,ref;
// favor an off-center unit so that the same one can be used for both
- // pitch and roll. An on-center unit is used (for pitch)if that's all
+ // pitch and roll. An on-center unit is used (for pitch)if that's all
// that's in contact with the ground.
i=0; ref=-1; center=-1;
- while( (ref < 0) && (i < fdmex->GetAircraft()->GetNumGearUnits()) ) {
- if(fdmex->GetAircraft()->GetGearUnit(i)->GetWOW()) {
- if(fabs(fdmex->GetAircraft()->GetGearUnit(i)->GetBodyLocation(2)) > 0.01)
+ while( (ref < 0) && (i < fdmex->GetGroundReactions()->GetNumGearUnits()) ) {
+ if(fdmex->GetGroundReactions()->GetGearUnit(i)->GetWOW()) {
+ if(fabs(fdmex->GetGroundReactions()->GetGearUnit(i)->GetBodyLocation(2)) > 0.01)
ref=i;
else
center=i;
- }
- i++;
+ }
+ i++;
}
if((ref < 0) && (center >= 0)) {
ref=center;
}
cout << "SetThetaOnGround ref gear: " << ref << endl;
if(ref >= 0) {
- float sp=fdmex->GetRotation()->GetSinphi();
- float cp=fdmex->GetRotation()->GetCosphi();
- float lx=fdmex->GetAircraft()->GetGearUnit(ref)->GetBodyLocation(1);
- float ly=fdmex->GetAircraft()->GetGearUnit(ref)->GetBodyLocation(2);
- float lz=fdmex->GetAircraft()->GetGearUnit(ref)->GetBodyLocation(3);
- float hagl = -1*lx*sin(ff) +
+ double sp = fdmex->GetPropagate()->GetSinEuler(ePhi);
+ double cp = fdmex->GetPropagate()->GetCosEuler(ePhi);
+ double lx = fdmex->GetGroundReactions()->GetGearUnit(ref)->GetBodyLocation(1);
+ double ly = fdmex->GetGroundReactions()->GetGearUnit(ref)->GetBodyLocation(2);
+ double lz = fdmex->GetGroundReactions()->GetGearUnit(ref)->GetBodyLocation(3);
+ double hagl = -1*lx*sin(ff) +
ly*sp*cos(ff) +
lz*cp*cos(ff);
-
+
fgic->SetAltitudeAGLFtIC(hagl);
cout << "SetThetaOnGround new alt: " << hagl << endl;
- }
- fgic->SetPitchAngleRadIC(ff);
- cout << "SetThetaOnGround new theta: " << ff << endl;
-}
+ }
+ fgic->SetPitchAngleRadIC(ff);
+ cout << "SetThetaOnGround new theta: " << ff << endl;
+}
/*****************************************************************************/
bool FGTrimAxis::initTheta(void) {
- int i,N,iAft, iForward;
- float zAft,zForward,zDiff,theta;
- bool level;
- float saveAlt;
-
+ int i,N;
+ int iForward = 0;
+ int iAft = 1;
+ double zAft,zForward,zDiff,theta;
+ double xAft,xForward,xDiff;
+ bool level;
+ double saveAlt;
+
saveAlt=fgic->GetAltitudeAGLFtIC();
fgic->SetAltitudeAGLFtIC(100);
-
-
- N=fdmex->GetAircraft()->GetNumGearUnits();
-
+
+
+ N=fdmex->GetGroundReactions()->GetNumGearUnits();
+
//find the first wheel unit forward of the cg
//the list is short so a simple linear search is fine
for( i=0; i<N; i++ ) {
- if(fdmex->GetAircraft()->GetGearUnit(i)->GetBodyLocation(1) > 0 ) {
+ if(fdmex->GetGroundReactions()->GetGearUnit(i)->GetBodyLocation(1) > 0 ) {
iForward=i;
break;
}
}
//now find the first wheel unit aft of the cg
for( i=0; i<N; i++ ) {
- if(fdmex->GetAircraft()->GetGearUnit(i)->GetBodyLocation(1) < 0 ) {
+ if(fdmex->GetGroundReactions()->GetGearUnit(i)->GetBodyLocation(1) < 0 ) {
iAft=i;
break;
}
}
-
+
// now adjust theta till the wheels are the same distance from the ground
- zAft=fdmex->GetAircraft()->GetGearUnit(1)->GetLocalGear(3);
- zForward=fdmex->GetAircraft()->GetGearUnit(0)->GetLocalGear(3);
+ xAft=fdmex->GetGroundReactions()->GetGearUnit(iAft)->GetBodyLocation(1);
+ xForward=fdmex->GetGroundReactions()->GetGearUnit(iForward)->GetBodyLocation(1);
+ xDiff = xForward - xAft;
+ zAft=fdmex->GetGroundReactions()->GetGearUnit(iAft)->GetLocalGear(3);
+ zForward=fdmex->GetGroundReactions()->GetGearUnit(iForward)->GetLocalGear(3);
zDiff = zForward - zAft;
level=false;
- theta=fgic->GetPitchAngleDegIC();
+ theta=fgic->GetPitchAngleDegIC();
while(!level && (i < 100)) {
- theta+=2.0*zDiff;
- fgic->SetPitchAngleDegIC(theta);
- fdmex->RunIC(fgic);
- zAft=fdmex->GetAircraft()->GetGearUnit(1)->GetLocalGear(3);
- zForward=fdmex->GetAircraft()->GetGearUnit(0)->GetLocalGear(3);
- zDiff = zForward - zAft;
- //cout << endl << theta << " " << zDiff << endl;
- //cout << "0: " << fdmex->GetAircraft()->GetGearUnit(0)->GetLocalGear() << endl;
- //cout << "1: " << fdmex->GetAircraft()->GetGearUnit(1)->GetLocalGear() << endl;
-
- if(fabs(zDiff ) < 0.1)
- level=true;
- i++;
- }
+ theta+=radtodeg*atan(zDiff/xDiff);
+ fgic->SetPitchAngleDegIC(theta);
+ fdmex->RunIC();
+ zAft=fdmex->GetGroundReactions()->GetGearUnit(iAft)->GetLocalGear(3);
+ zForward=fdmex->GetGroundReactions()->GetGearUnit(iForward)->GetLocalGear(3);
+ zDiff = zForward - zAft;
+ //cout << endl << theta << " " << zDiff << endl;
+ //cout << "0: " << fdmex->GetGroundReactions()->GetGearUnit(0)->GetLocalGear() << endl;
+ //cout << "1: " << fdmex->GetGroundReactions()->GetGearUnit(1)->GetLocalGear() << endl;
+ if(fabs(zDiff ) < 0.1)
+ level=true;
+ i++;
+ }
//cout << i << endl;
- cout << " Initial Theta: " << fdmex->GetRotation()->Gettht()*RADTODEG << endl;
- control_min=(theta+5)*DEGTORAD;
- control_max=(theta-5)*DEGTORAD;
+ if (debug_lvl > 0) {
+ cout << " Initial Theta: " << fdmex->GetPropagate()->GetEuler(eTht)*radtodeg << endl;
+ cout << " Used gear unit " << iAft << " as aft and " << iForward << " as forward" << endl;
+ }
+ control_min=(theta+5)*degtorad;
+ control_max=(theta-5)*degtorad;
fgic->SetAltitudeAGLFtIC(saveAlt);
- if(i < 100)
+ if(i < 100)
return true;
else
- return false;
-}
+ return false;
+}
/*****************************************************************************/
-void FGTrimAxis::SetPhiOnGround(float ff) {
+void FGTrimAxis::SetPhiOnGround(double ff) {
int i,ref;
i=0; ref=-1;
- //must have an off-center unit here
- while( (ref < 0) && (i < fdmex->GetAircraft()->GetNumGearUnits()) ) {
- if( (fdmex->GetAircraft()->GetGearUnit(i)->GetWOW()) &&
- (fabs(fdmex->GetAircraft()->GetGearUnit(i)->GetBodyLocation(2)) > 0.01))
+ //must have an off-center unit here
+ while ( (ref < 0) && (i < fdmex->GetGroundReactions()->GetNumGearUnits()) ) {
+ if ( (fdmex->GetGroundReactions()->GetGearUnit(i)->GetWOW()) &&
+ (fabs(fdmex->GetGroundReactions()->GetGearUnit(i)->GetBodyLocation(2)) > 0.01))
ref=i;
- i++;
+ i++;
}
- if(ref >= 0) {
- float st=fdmex->GetRotation()->GetSintht();
- float ct=fdmex->GetRotation()->GetCostht();
- float lx=fdmex->GetAircraft()->GetGearUnit(ref)->GetBodyLocation(1);
- float ly=fdmex->GetAircraft()->GetGearUnit(ref)->GetBodyLocation(2);
- float lz=fdmex->GetAircraft()->GetGearUnit(ref)->GetBodyLocation(3);
- float hagl = -1*lx*st +
+ if (ref >= 0) {
+ double st = fdmex->GetPropagate()->GetSinEuler(eTht);
+ double ct = fdmex->GetPropagate()->GetCosEuler(eTht);
+ double lx = fdmex->GetGroundReactions()->GetGearUnit(ref)->GetBodyLocation(1);
+ double ly = fdmex->GetGroundReactions()->GetGearUnit(ref)->GetBodyLocation(2);
+ double lz = fdmex->GetGroundReactions()->GetGearUnit(ref)->GetBodyLocation(3);
+ double hagl = -1*lx*st +
ly*sin(ff)*ct +
lz*cos(ff)*ct;
-
+
fgic->SetAltitudeAGLFtIC(hagl);
- }
+ }
fgic->SetRollAngleRadIC(ff);
-
-}
+
+}
/*****************************************************************************/
void FGTrimAxis::Run(void) {
- float last_state_value;
+ double last_state_value;
int i;
setControl();
//cout << "FGTrimAxis::Run: " << control_value << endl;
while(!stable) {
i++;
last_state_value=state_value;
- fdmex->RunIC(fgic);
+ fdmex->RunIC();
getState();
if(i > 1) {
if((fabs(last_state_value - state_value) < tolerance) || (i >= 100) )
/*****************************************************************************/
void FGTrimAxis::setThrottlesPct(void) {
- float tMin,tMax;
+ double tMin,tMax;
for(unsigned i=0;i<fdmex->GetPropulsion()->GetNumEngines();i++) {
tMin=fdmex->GetPropulsion()->GetEngine(i)->GetThrottleMin();
tMax=fdmex->GetPropulsion()->GetEngine(i)->GetThrottleMax();
//cout << "setThrottlespct: " << i << ", " << control_min << ", " << control_max << ", " << control_value;
- fdmex -> GetFCS() -> SetThrottleCmd(i,tMin+control_value*(tMax-tMin));
+ fdmex->GetFCS()->SetThrottleCmd(i,tMin+control_value*(tMax-tMin));
+ //cout << "setThrottlespct: " << fdmex->GetFCS()->GetThrottleCmd(i) << endl;
+ fdmex->RunIC(); //apply throttle change
+ fdmex->GetPropulsion()->GetSteadyState();
}
}
/*****************************************************************************/
void FGTrimAxis::AxisReport(void) {
-
+
char out[80];
- sprintf(out," %20s: %6.2f %5s: %9.2e Tolerance: %3.0e\n",
+
+ sprintf(out," %20s: %6.2f %5s: %9.2e Tolerance: %3.0e",
GetControlName().c_str(), GetControl()*control_convert,
- GetStateName().c_str(), GetState(), GetTolerance());
+ GetStateName().c_str(), GetState()+state_target, GetTolerance());
cout << out;
+ if( fabs(GetState()+state_target) < fabs(GetTolerance()) )
+ cout << " Passed" << endl;
+ else
+ cout << " Failed" << endl;
}
/*****************************************************************************/
-float FGTrimAxis::GetAvgStability( void ) {
+double FGTrimAxis::GetAvgStability( void ) {
if(total_iterations > 0) {
- return float(total_stability_iterations)/float(total_iterations);
+ return double(total_stability_iterations)/double(total_iterations);
}
return 0;
}
/*****************************************************************************/
-
-void FGTrimAxis::Debug(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 FGTrimAxis::Debug(int from)
{
-}
+ if (debug_lvl <= 0) return;
+ 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: FGTrimAxis" << endl;
+ if (from == 1) cout << "Destroyed: FGTrimAxis" << 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;
+ }
+ }
+}
+}