#include "FGPosition.h"
#include "FGAuxiliary.h"
#include "FGOutput.h"
-#include "FGDefs.h"
+#include "FGConfigFile.h"
-static const char *IdSrc = "$Header$";
+static const char *IdSrc = "$Id$";
static const char *IdHdr = ID_INITIALCONDITION;
+//******************************************************************************
-FGInitialCondition::FGInitialCondition(FGFDMExec *FDMExec) {
- vt=vc=ve=0;
+FGInitialCondition::FGInitialCondition(FGFDMExec *FDMExec)
+{
+ vt=vc=ve=vg=0;
mach=0;
alpha=beta=gamma=0;
theta=phi=psi=0;
altitude=hdot=0;
latitude=longitude=0;
- u=v=w=0;
+ u=v=w=0;
+ uw=vw=ww=0;
vnorth=veast=vdown=0;
+ wnorth=weast=wdown=0;
+ whead=wcross=0;
+ wdir=wmag=0;
lastSpeedSet=setvt;
- sea_level_radius = EARTHRAD;
- radius_to_vehicle = EARTHRAD;
+ lastWindSet=setwned;
+ sea_level_radius = FDMExec->GetInertial()->RefRadius();
+ radius_to_vehicle = FDMExec->GetInertial()->RefRadius();
terrain_altitude = 0;
+
+ salpha=sbeta=stheta=sphi=spsi=sgamma=0;
+ calpha=cbeta=ctheta=cphi=cpsi=cgamma=1;
+
if(FDMExec != NULL ) {
fdmex=FDMExec;
fdmex->GetPosition()->Seth(altitude);
cout << "FGInitialCondition: This class requires a pointer to a valid FGFDMExec object" << endl;
}
+ Debug(0);
}
+//******************************************************************************
-FGInitialCondition::~FGInitialCondition(void) {}
+FGInitialCondition::~FGInitialCondition()
+{
+ Debug(1);
+}
+//******************************************************************************
-void FGInitialCondition::SetVcalibratedKtsIC(float tt) {
+void FGInitialCondition::SetVcalibratedKtsIC(double tt) {
- if(getMachFromVcas(&mach,tt*jsbKTSTOFPS)) {
+ if(getMachFromVcas(&mach,tt*ktstofps)) {
//cout << "Mach: " << mach << endl;
lastSpeedSet=setvc;
- vc=tt*jsbKTSTOFPS;
+ vc=tt*ktstofps;
vt=mach*fdmex->GetAtmosphere()->GetSoundSpeed();
ve=vt*sqrt(fdmex->GetAtmosphere()->GetDensityRatio());
- //cout << "Vt: " << vt*jsbFPSTOKTS << " Vc: " << vc*jsbFPSTOKTS << endl;
+ //cout << "Vt: " << vt*fpstokts << " Vc: " << vc*fpstokts << endl;
}
else {
cout << "Failed to get Mach number for given Vc and altitude, Vc unchanged." << endl;
}
}
-void FGInitialCondition::SetVequivalentKtsIC(float tt) {
- ve=tt*jsbKTSTOFPS;
+//******************************************************************************
+
+void FGInitialCondition::SetVequivalentKtsIC(double tt) {
+ ve=tt*ktstofps;
lastSpeedSet=setve;
vt=ve*1/sqrt(fdmex->GetAtmosphere()->GetDensityRatio());
mach=vt/fdmex->GetAtmosphere()->GetSoundSpeed();
vc=calcVcas(mach);
}
-void FGInitialCondition::SetVtrueKtsIC(float tt) {
- vt=tt*jsbKTSTOFPS;
+//******************************************************************************
+
+void FGInitialCondition::SetVgroundFpsIC(double tt) {
+ double ua,va,wa;
+ double vxz;
+
+ vg=tt;
+ lastSpeedSet=setvg;
+ vnorth = vg*cos(psi); veast = vg*sin(psi); vdown = 0;
+ calcUVWfromNED();
+ ua = u + uw; va = v + vw; wa = w + ww;
+ vt = sqrt( ua*ua + va*va + wa*wa );
+ alpha = beta = 0;
+ vxz = sqrt( u*u + w*w );
+ if( w != 0 ) alpha = atan2( w, u );
+ if( vxz != 0 ) beta = atan2( v, vxz );
+ mach=vt/fdmex->GetAtmosphere()->GetSoundSpeed();
+ vc=calcVcas(mach);
+ ve=vt*sqrt(fdmex->GetAtmosphere()->GetDensityRatio());
+}
+
+//******************************************************************************
+
+void FGInitialCondition::SetVtrueFpsIC(double tt) {
+ vt=tt;
lastSpeedSet=setvt;
mach=vt/fdmex->GetAtmosphere()->GetSoundSpeed();
vc=calcVcas(mach);
ve=vt*sqrt(fdmex->GetAtmosphere()->GetDensityRatio());
}
-void FGInitialCondition::SetMachIC(float tt) {
+//******************************************************************************
+
+void FGInitialCondition::SetMachIC(double tt) {
mach=tt;
lastSpeedSet=setmach;
vt=mach*fdmex->GetAtmosphere()->GetSoundSpeed();
vc=calcVcas(mach);
ve=vt*sqrt(fdmex->GetAtmosphere()->GetDensityRatio());
- //cout << "Vt: " << vt*jsbFPSTOKTS << " Vc: " << vc*jsbFPSTOKTS << endl;
+ //cout << "Vt: " << vt*fpstokts << " Vc: " << vc*fpstokts << endl;
}
-void FGInitialCondition::SetClimbRateFpmIC(float tt) {
+//******************************************************************************
+
+void FGInitialCondition::SetClimbRateFpmIC(double tt) {
SetClimbRateFpsIC(tt/60.0);
}
-void FGInitialCondition::SetClimbRateFpsIC(float tt) {
+//******************************************************************************
+
+void FGInitialCondition::SetClimbRateFpsIC(double tt) {
if(vt > 0.1) {
hdot=tt;
gamma=asin(hdot/vt);
+ sgamma=sin(gamma); cgamma=cos(gamma);
}
}
-void FGInitialCondition::SetFlightPathAngleRadIC(float tt) {
+//******************************************************************************
+
+void FGInitialCondition::SetFlightPathAngleRadIC(double tt) {
gamma=tt;
+ sgamma=sin(gamma); cgamma=cos(gamma);
getTheta();
- hdot=vt*sin(tt);
+ hdot=vt*sgamma;
}
+//******************************************************************************
+
+void FGInitialCondition::SetAlphaRadIC(double tt) {
+ alpha=tt;
+ salpha=sin(alpha); calpha=cos(alpha);
+ getTheta();
+}
-void FGInitialCondition::SetUBodyFpsIC(float tt) {
+//******************************************************************************
+
+void FGInitialCondition::SetPitchAngleRadIC(double tt) {
+ theta=tt;
+ stheta=sin(theta); ctheta=cos(theta);
+ getAlpha();
+}
+
+//******************************************************************************
+
+void FGInitialCondition::SetBetaRadIC(double tt) {
+ beta=tt;
+ sbeta=sin(beta); cbeta=cos(beta);
+ getTheta();
+
+}
+
+//******************************************************************************
+
+void FGInitialCondition::SetRollAngleRadIC(double tt) {
+ phi=tt;
+ sphi=sin(phi); cphi=cos(phi);
+ getTheta();
+}
+
+//******************************************************************************
+
+void FGInitialCondition::SetTrueHeadingRadIC(double tt) {
+ psi=tt;
+ spsi=sin(psi); cpsi=cos(psi);
+ calcWindUVW();
+}
+
+//******************************************************************************
+
+void FGInitialCondition::SetUBodyFpsIC(double tt) {
u=tt;
- vt=sqrt(u*u+v*v+w*w);
+ vt=sqrt(u*u + v*v + w*w);
lastSpeedSet=setuvw;
}
-
-void FGInitialCondition::SetVBodyFpsIC(float tt) {
+//******************************************************************************
+
+void FGInitialCondition::SetVBodyFpsIC(double tt) {
v=tt;
- vt=sqrt(u*u+v*v+w*w);
+ vt=sqrt(u*u + v*v + w*w);
lastSpeedSet=setuvw;
}
-void FGInitialCondition::SetWBodyFpsIC(float tt) {
+//******************************************************************************
+
+void FGInitialCondition::SetWBodyFpsIC(double tt) {
w=tt;
- vt=sqrt(u*u+v*v+w*w);
+ vt=sqrt( u*u + v*v + w*w );
lastSpeedSet=setuvw;
}
+//******************************************************************************
+
+double FGInitialCondition::GetUBodyFpsIC(void) {
+ if(lastSpeedSet == setvg )
+ return u;
+ else
+ return vt*calpha*cbeta - uw;
+}
+
+//******************************************************************************
+
+double FGInitialCondition::GetVBodyFpsIC(void) {
+ if( lastSpeedSet == setvg )
+ return v;
+ else {
+ return vt*sbeta - vw;
+ }
+}
+
+//******************************************************************************
+
+double FGInitialCondition::GetWBodyFpsIC(void) {
+ if( lastSpeedSet == setvg )
+ return w;
+ else
+ return vt*salpha*cbeta -ww;
+}
+
+//******************************************************************************
+
+void FGInitialCondition::SetWindNEDFpsIC(double wN, double wE, double wD ) {
+ wnorth = wN; weast = wE; wdown = wD;
+ lastWindSet = setwned;
+ calcWindUVW();
+ if(lastSpeedSet == setvg)
+ SetVgroundFpsIC(vg);
+}
+
+//******************************************************************************
+
+// positive from left
+void FGInitialCondition::SetHeadWindKtsIC(double head){
+ whead=head*ktstofps;
+ lastWindSet=setwhc;
+ calcWindUVW();
+ if(lastSpeedSet == setvg)
+ SetVgroundFpsIC(vg);
+
+}
+
+//******************************************************************************
+
+void FGInitialCondition::SetCrossWindKtsIC(double cross){
+ wcross=cross*ktstofps;
+ lastWindSet=setwhc;
+ calcWindUVW();
+ if(lastSpeedSet == setvg)
+ SetVgroundFpsIC(vg);
+
+}
+
+//******************************************************************************
+
+void FGInitialCondition::SetWindDownKtsIC(double wD) {
+ wdown=wD;
+ calcWindUVW();
+ if(lastSpeedSet == setvg)
+ SetVgroundFpsIC(vg);
+}
+
+//******************************************************************************
+
+void FGInitialCondition::SetWindMagKtsIC(double mag) {
+ wmag=mag*ktstofps;
+ lastWindSet=setwmd;
+ calcWindUVW();
+ if(lastSpeedSet == setvg)
+ SetVgroundFpsIC(vg);
+}
+
+//******************************************************************************
+
+void FGInitialCondition::SetWindDirDegIC(double dir) {
+ wdir=dir*degtorad;
+ lastWindSet=setwmd;
+ calcWindUVW();
+ if(lastSpeedSet == setvg)
+ SetVgroundFpsIC(vg);
+}
+
+
+//******************************************************************************
+
+void FGInitialCondition::calcWindUVW(void) {
+
+ switch(lastWindSet) {
+ case setwmd:
+ wnorth=wmag*cos(wdir);
+ weast=wmag*sin(wdir);
+ break;
+ case setwhc:
+ wnorth=whead*cos(psi) + wcross*cos(psi+M_PI/2);
+ weast=whead*sin(psi) + wcross*sin(psi+M_PI/2);
+ break;
+ case setwned:
+ break;
+ }
+ uw=wnorth*ctheta*cpsi +
+ weast*ctheta*spsi -
+ wdown*stheta;
+ vw=wnorth*( sphi*stheta*cpsi - cphi*spsi ) +
+ weast*( sphi*stheta*spsi + cphi*cpsi ) +
+ wdown*sphi*ctheta;
+ ww=wnorth*(cphi*stheta*cpsi + sphi*spsi) +
+ weast*(cphi*stheta*spsi - sphi*cpsi) +
+ wdown*cphi*ctheta;
+
+
+ /* cout << "FGInitialCondition::calcWindUVW: wnorth, weast, wdown "
+ << wnorth << ", " << weast << ", " << wdown << endl;
+ cout << "FGInitialCondition::calcWindUVW: theta, phi, psi "
+ << theta << ", " << phi << ", " << psi << endl;
+ cout << "FGInitialCondition::calcWindUVW: uw, vw, ww "
+ << uw << ", " << vw << ", " << ww << endl; */
+
+}
+
+//******************************************************************************
-void FGInitialCondition::SetAltitudeFtIC(float tt) {
+void FGInitialCondition::SetAltitudeFtIC(double tt) {
altitude=tt;
fdmex->GetPosition()->Seth(altitude);
fdmex->GetAtmosphere()->Run();
-
//lets try to make sure the user gets what they intended
switch(lastSpeedSet) {
case setned:
case setuvw:
case setvt:
- SetVtrueKtsIC(vt*jsbFPSTOKTS);
+ SetVtrueKtsIC(vt*fpstokts);
break;
case setvc:
- SetVcalibratedKtsIC(vc*jsbFPSTOKTS);
+ SetVcalibratedKtsIC(vc*fpstokts);
break;
case setve:
- SetVequivalentKtsIC(ve*jsbFPSTOKTS);
+ SetVequivalentKtsIC(ve*fpstokts);
break;
case setmach:
SetMachIC(mach);
break;
+ case setvg:
+ SetVgroundFpsIC(vg);
+ break;
}
}
-void FGInitialCondition::SetAltitudeAGLFtIC(float tt) {
+//******************************************************************************
+
+void FGInitialCondition::SetAltitudeAGLFtIC(double tt) {
fdmex->GetPosition()->SetDistanceAGL(tt);
altitude=fdmex->GetPosition()->Geth();
SetAltitudeFtIC(altitude);
-}
+}
+
+//******************************************************************************
+
void FGInitialCondition::SetSeaLevelRadiusFtIC(double tt) {
sea_level_radius = tt;
}
-
+
+//******************************************************************************
+
void FGInitialCondition::SetTerrainAltitudeFtIC(double tt) {
terrain_altitude=tt;
- fdmex->GetPosition()->SetDistanceAGL(altitude-terrain_altitude);
- fdmex->GetPosition()->SetRunwayRadius(sea_level_radius + terrain_altitude);
-}
+}
+
+//******************************************************************************
void FGInitialCondition::calcUVWfromNED(void) {
- u=vnorth*cos(theta)*cos(psi) +
- veast*cos(theta)*sin(psi) -
- vdown*sin(theta);
- v=vnorth*(sin(phi)*sin(theta)*cos(psi) - cos(phi)*sin(psi)) +
- veast*(sin(phi)*sin(theta)*sin(psi) + cos(phi)*cos(psi)) +
- vdown*sin(phi)*cos(theta);
- w=vnorth*(cos(phi)*sin(theta)*cos(psi) + sin(phi)*sin(psi)) +
- veast*(cos(phi)*sin(theta)*sin(psi) - sin(phi)*cos(psi)) +
- vdown*cos(phi)*cos(theta);
-}
-
-void FGInitialCondition::SetVnorthFpsIC(float tt) {
+ u=vnorth*ctheta*cpsi +
+ veast*ctheta*spsi -
+ vdown*stheta;
+ v=vnorth*( sphi*stheta*cpsi - cphi*spsi ) +
+ veast*( sphi*stheta*spsi + cphi*cpsi ) +
+ vdown*sphi*ctheta;
+ w=vnorth*( cphi*stheta*cpsi + sphi*spsi ) +
+ veast*( cphi*stheta*spsi - sphi*cpsi ) +
+ vdown*cphi*ctheta;
+}
+
+//******************************************************************************
+
+void FGInitialCondition::SetVnorthFpsIC(double tt) {
vnorth=tt;
calcUVWfromNED();
vt=sqrt(u*u + v*v + w*w);
lastSpeedSet=setned;
-}
-
-void FGInitialCondition::SetVeastFpsIC(float tt) {
+}
+
+//******************************************************************************
+
+void FGInitialCondition::SetVeastFpsIC(double tt) {
veast=tt;
calcUVWfromNED();
vt=sqrt(u*u + v*v + w*w);
lastSpeedSet=setned;
-}
+}
+
+//******************************************************************************
-void FGInitialCondition::SetVdownFpsIC(float tt) {
+void FGInitialCondition::SetVdownFpsIC(double tt) {
vdown=tt;
calcUVWfromNED();
vt=sqrt(u*u + v*v + w*w);
SetClimbRateFpsIC(-1*vdown);
lastSpeedSet=setned;
-}
+}
+
+//******************************************************************************
+
+bool FGInitialCondition::getMachFromVcas(double *Mach,double vcas) {
-bool FGInitialCondition::getMachFromVcas(float *Mach,float vcas) {
-
bool result=false;
- float guess=1.5;
+ double guess=1.5;
xlo=xhi=0;
xmin=0;xmax=50;
sfunc=&FGInitialCondition::calcVcas;
if(findInterval(vcas,guess)) {
if(solve(&mach,vcas))
result=true;
- }
+ }
return result;
}
+//******************************************************************************
+
bool FGInitialCondition::getAlpha(void) {
bool result=false;
- float guess=theta-gamma;
+ double guess=theta-gamma;
xlo=xhi=0;
xmin=fdmex->GetAircraft()->GetAlphaCLMin();
xmax=fdmex->GetAircraft()->GetAlphaCLMax();
if(findInterval(0,guess)){
if(solve(&alpha,0)){
result=true;
+ salpha=sin(alpha);
+ calpha=cos(alpha);
}
}
+ calcWindUVW();
return result;
-}
-
+}
+
+//******************************************************************************
+
bool FGInitialCondition::getTheta(void) {
bool result=false;
- float guess=alpha+gamma;
+ double guess=alpha+gamma;
xlo=xhi=0;
xmin=-89;xmax=89;
sfunc=&FGInitialCondition::GammaEqOfTheta;
if(findInterval(0,guess)){
if(solve(&theta,0)){
result=true;
+ stheta=sin(theta);
+ ctheta=cos(theta);
}
}
+ calcWindUVW();
return result;
-}
-
+}
+//******************************************************************************
-float FGInitialCondition::GammaEqOfTheta(float Theta) {
- float a,b,c;
-
- a=cos(alpha)*cos(beta)*sin(Theta);
- b=sin(beta)*sin(phi);
- c=sin(alpha)*cos(beta)*cos(phi);
- return sin(gamma)-a+(b+c)*cos(Theta);
+double FGInitialCondition::GammaEqOfTheta(double Theta) {
+ double a,b,c;
+ double sTheta,cTheta;
+
+ //theta=Theta; stheta=sin(theta); ctheta=cos(theta);
+ sTheta=sin(Theta); cTheta=cos(Theta);
+ calcWindUVW();
+ a=wdown + vt*calpha*cbeta + uw;
+ b=vt*sphi*sbeta + vw*sphi;
+ c=vt*cphi*salpha*cbeta + ww*cphi;
+ return vt*sgamma - ( a*sTheta - (b+c)*cTheta);
}
-float FGInitialCondition::GammaEqOfAlpha(float Alpha) {
- float a,b,c;
-
- a=cos(Alpha)*cos(beta)*sin(theta);
- b=sin(beta)*sin(phi);
- c=sin(Alpha)*cos(beta)*cos(phi);
- return sin(gamma)-a+(b+c)*cos(theta);
+//******************************************************************************
+
+double FGInitialCondition::GammaEqOfAlpha(double Alpha) {
+ double a,b,c;
+ double sAlpha,cAlpha;
+
+ sAlpha=sin(Alpha); cAlpha=cos(Alpha);
+ a=wdown + vt*cAlpha*cbeta + uw;
+ b=vt*sphi*sbeta + vw*sphi;
+ c=vt*cphi*sAlpha*cbeta + ww*cphi;
+
+ return vt*sgamma - ( a*stheta - (b+c)*ctheta );
}
-
-float FGInitialCondition::calcVcas(float Mach) {
+//******************************************************************************
+
+double FGInitialCondition::calcVcas(double Mach) {
- float p=fdmex->GetAtmosphere()->GetPressure();
- float psl=fdmex->GetAtmosphere()->GetPressureSL();
- float rhosl=fdmex->GetAtmosphere()->GetDensitySL();
- float pt,A,B,D,vcas;
+ double p=fdmex->GetAtmosphere()->GetPressure();
+ double psl=fdmex->GetAtmosphere()->GetPressureSL();
+ double rhosl=fdmex->GetAtmosphere()->GetDensitySL();
+ double pt,A,B,D,vcas;
if(Mach < 0) Mach=0;
if(Mach < 1) //calculate total pressure assuming isentropic flow
pt=p*pow((1 + 0.2*Mach*Mach),3.5);
A = pow(((pt-p)/psl+1),0.28571);
vcas = sqrt(7*psl/rhosl*(A-1));
- //cout << "calcVcas: vcas= " << vcas*jsbFPSTOKTS << " mach= " << Mach << " pressure: " << pt << endl;
+ //cout << "calcVcas: vcas= " << vcas*fpstokts << " mach= " << Mach << " pressure: " << pt << endl;
return vcas;
}
-bool FGInitialCondition::findInterval(float x,float guess) {
- //void find_interval(inter_params &ip,eqfunc f,float y,float constant, int &flag){
+//******************************************************************************
+
+bool FGInitialCondition::findInterval(double x,double guess) {
+ //void find_interval(inter_params &ip,eqfunc f,double y,double constant, int &flag){
int i=0;
bool found=false;
- float flo,fhi,fguess;
- float lo,hi,step;
+ double flo,fhi,fguess;
+ double lo,hi,step;
step=0.1;
fguess=(this->*sfunc)(guess)-x;
lo=hi=guess;
return found;
}
+//******************************************************************************
-
-
-bool FGInitialCondition::solve(float *y,float x) {
- float x1,x2,x3,f1,f2,f3,d,d0;
- float eps=1E-5;
- float const relax =0.9;
+bool FGInitialCondition::solve(double *y,double x)
+{
+ double x1,x2,x3,f1,f2,f3,d,d0;
+ double eps=1E-5;
+ double const relax =0.9;
int i;
bool success=false;
-
- //initializations
+
+ //initializations
d=1;
-
- x1=xlo;x3=xhi;
- f1=(this->*sfunc)(x1)-x;
- f3=(this->*sfunc)(x3)-x;
- d0=fabs(x3-x1);
-
- //iterations
- i=0;
- while ((fabs(d) > eps) && (i < 100)) {
- d=(x3-x1)/d0;
- x2=x1-d*d0*f1/(f3-f1);
-
- f2=(this->*sfunc)(x2)-x;
- //cout << "solve x1,x2,x3: " << x1 << "," << x2 << "," << x3 << endl;
- //cout << " " << f1 << "," << f2 << "," << f3 << endl;
-
- if(fabs(f2) <= 0.001) {
- x1=x3=x2;
- } else if(f1*f2 <= 0.0) {
- x3=x2;
- f3=f2;
- f1=relax*f1;
- } else if(f2*f3 <= 0) {
- x1=x2;
- f1=f2;
- f3=relax*f3;
- }
- //cout << i << endl;
- i++;
- }//end while
- if(i < 100) {
- success=true;
- *y=x2;
+ x2 = 0;
+ x1=xlo;x3=xhi;
+ f1=(this->*sfunc)(x1)-x;
+ f3=(this->*sfunc)(x3)-x;
+ d0=fabs(x3-x1);
+
+ //iterations
+ i=0;
+ while ((fabs(d) > eps) && (i < 100)) {
+ d=(x3-x1)/d0;
+ x2 = x1-d*d0*f1/(f3-f1);
+
+ f2=(this->*sfunc)(x2)-x;
+ //cout << "solve x1,x2,x3: " << x1 << "," << x2 << "," << x3 << endl;
+ //cout << " " << f1 << "," << f2 << "," << f3 << endl;
+
+ if(fabs(f2) <= 0.001) {
+ x1=x3=x2;
+ } else if(f1*f2 <= 0.0) {
+ x3=x2;
+ f3=f2;
+ f1=relax*f1;
+ } else if(f2*f3 <= 0) {
+ x1=x2;
+ f1=f2;
+ f3=relax*f3;
}
+ //cout << i << endl;
+ i++;
+ }//end while
+ if(i < 100) {
+ success=true;
+ *y=x2;
+ }
- //cout << "Success= " << success << " Vcas: " << vcas*jsbFPSTOKTS << " Mach: " << x2 << endl;
+ //cout << "Success= " << success << " Vcas: " << vcas*fpstokts << " Mach: " << x2 << endl;
return success;
}
+
+//******************************************************************************
+
+double FGInitialCondition::GetWindDirDegIC(void) {
+ if(weast != 0.0)
+ return atan2(weast,wnorth)*radtodeg;
+ else if(wnorth > 0)
+ return 0.0;
+ else
+ return 180.0;
+}
+
+//******************************************************************************
+
+bool FGInitialCondition::Load(string acpath, string acname, string rstfile)
+{
+ string resetDef;
+ string token="";
+
+ double temp;
+
+# ifndef macintosh
+ resetDef = acpath + "/" + acname + "/" + rstfile + ".xml";
+# else
+ resetDef = acpath + ";" + acname + ";" + rstfile + ".xml";
+# endif
+
+ FGConfigFile resetfile(resetDef);
+ if (!resetfile.IsOpen()) {
+ cerr << "Failed to open reset file: " << resetDef << endl;
+ return false;
+ }
+
+ resetfile.GetNextConfigLine();
+ token = resetfile.GetValue();
+ if (token != string("initialize")) {
+ cerr << "The reset file " << resetDef
+ << " does not appear to be a reset file" << endl;
+ return false;
+ }
+
+ resetfile.GetNextConfigLine();
+ resetfile >> token;
+ while (token != string("/initialize") && token != string("EOF")) {
+ if (token == "UBODY" ) { resetfile >> temp; SetUBodyFpsIC(temp); }
+ if (token == "VBODY" ) { resetfile >> temp; SetVBodyFpsIC(temp); }
+ if (token == "WBODY" ) { resetfile >> temp; SetWBodyFpsIC(temp); }
+ if (token == "LATITUDE" ) { resetfile >> temp; SetLatitudeDegIC(temp); }
+ if (token == "LONGITUDE" ) { resetfile >> temp; SetLongitudeDegIC(temp); }
+ if (token == "PHI" ) { resetfile >> temp; SetRollAngleDegIC(temp); }
+ if (token == "THETA" ) { resetfile >> temp; SetPitchAngleDegIC(temp); }
+ if (token == "PSI" ) { resetfile >> temp; SetTrueHeadingDegIC(temp); }
+ if (token == "ALPHA" ) { resetfile >> temp; SetAlphaDegIC(temp); }
+ if (token == "BETA" ) { resetfile >> temp; SetBetaDegIC(temp); }
+ if (token == "GAMMA" ) { resetfile >> temp; SetFlightPathAngleDegIC(temp); }
+ if (token == "ROC" ) { resetfile >> temp; SetClimbRateFpmIC(temp); }
+ if (token == "ALTITUDE" ) { resetfile >> temp; SetAltitudeFtIC(temp); }
+ if (token == "WINDDIR" ) { resetfile >> temp; SetWindDirDegIC(temp); }
+ if (token == "VWIND" ) { resetfile >> temp; SetWindMagKtsIC(temp); }
+ if (token == "HWIND" ) { resetfile >> temp; SetHeadWindKtsIC(temp); }
+ if (token == "XWIND" ) { resetfile >> temp; SetCrossWindKtsIC(temp); }
+ if (token == "VC" ) { resetfile >> temp; SetVcalibratedKtsIC(temp); }
+ if (token == "MACH" ) { resetfile >> temp; SetMachIC(temp); }
+ if (token == "VGROUND" ) { resetfile >> temp; SetVgroundKtsIC(temp); }
+ resetfile >> token;
+ }
+
+ fdmex->RunIC(this);
+
+ return true;
+}
+
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+// 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 FGInitialCondition::Debug(int from)
+{
+ if (debug_lvl <= 0) return;
+
+ if (debug_lvl & 1) { // Standard console startup message output
+ }
+ if (debug_lvl & 2 ) { // Instantiation/Destruction notification
+ if (from == 0) cout << "Instantiated: FGInitialCondition" << endl;
+ if (from == 1) cout << "Destroyed: FGInitialCondition" << 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