# include <simgear/compiler.h>
# include <math.h>
#else
-# include <cmath>
+# if defined(sgi) && !defined(__GNUC__)
+# include <math.h>
+# else
+# include <cmath>
+# endif
#endif
-#ifndef M_PI
-# include <simgear/constants.h>
-# define M_PI SG_PI
+#ifdef _MSC_VER
+#define snprintf _snprintf
#endif
#include "FGState.h"
static const char *IdSrc = "$Id$";
static const char *IdHdr = ID_STATE;
-extern short debug_lvl;
-
/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
MACROS
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
//
// For every term registered here there must be a corresponding handler in
// GetParameter() below that retrieves that parameter. Also, there must be an
-// entry in the enum eParam definition in FGDefs.h. The ID is what must be used
+// entry in the enum eParam definition in FGJSBBase.h. The ID is what must be used
// in any config file entry which references that item.
-FGState::FGState(FGFDMExec* fdex) : mTb2l(3,3),
- mTl2b(3,3),
- mTs2b(3,3),
- vQtrn(4),
- vlastQdot(4),
- vQdot(4),
- vTmp(4),
- vEuler(3)
+FGState::FGState(FGFDMExec* fdex)
{
FDMExec = fdex;
Output = FDMExec->GetOutput();
Atmosphere = FDMExec->GetAtmosphere();
Aerodynamics = FDMExec->GetAerodynamics();
+ GroundReactions = FDMExec->GetGroundReactions();
+ Propulsion = FDMExec->GetPropulsion();
RegisterVariable(FG_TIME, " time " );
RegisterVariable(FG_QBAR, " qbar " );
RegisterVariable(FG_ALPHA, " alpha " );
RegisterVariable(FG_ALPHADOT, " alphadot " );
RegisterVariable(FG_BETA, " beta " );
+ RegisterVariable(FG_ABETA, " |beta| " );
RegisterVariable(FG_BETADOT, " betadot " );
RegisterVariable(FG_PHI, " roll_angle " );
RegisterVariable(FG_THT, " pitch_angle " );
RegisterVariable(FG_PITCHRATE, " pitch_rate " );
RegisterVariable(FG_ROLLRATE, " roll_rate " );
RegisterVariable(FG_YAWRATE, " yaw_rate " );
+ RegisterVariable(FG_AEROQ, " aero_pitch_rate ");
+ RegisterVariable(FG_AEROP, " aero_roll_rate " );
+ RegisterVariable(FG_AEROR, " aero_yaw_rate " );
RegisterVariable(FG_CL_SQRD, " Clift_sqrd " );
RegisterVariable(FG_MACH, " mach " );
RegisterVariable(FG_ALTITUDE, " altitude " );
RegisterVariable(FG_SPDBRAKE_POS, " speedbrake_pos " );
RegisterVariable(FG_SPOILERS_POS, " spoiler_pos " );
RegisterVariable(FG_FLAPS_POS, " flaps_pos " );
+ RegisterVariable(FG_GEAR_POS, " gear_pos " );
RegisterVariable(FG_ELEVATOR_CMD, " elevator_cmd " );
RegisterVariable(FG_AILERON_CMD, " aileron_cmd " );
RegisterVariable(FG_RUDDER_CMD, " rudder_cmd " );
RegisterVariable(FG_SPOILERS_CMD, " spoiler_cmd " );
RegisterVariable(FG_FLAPS_CMD, " flaps_cmd " );
RegisterVariable(FG_THROTTLE_CMD, " throttle_cmd " );
+ RegisterVariable(FG_GEAR_CMD, " gear_cmd " );
RegisterVariable(FG_THROTTLE_POS, " throttle_pos " );
+ RegisterVariable(FG_MIXTURE_CMD, " mixture_cmd " );
+ RegisterVariable(FG_MIXTURE_POS, " mixture_pos " );
+ RegisterVariable(FG_MAGNETO_CMD, " magneto_cmd " );
+ RegisterVariable(FG_STARTER_CMD, " starter_cmd " );
RegisterVariable(FG_ACTIVE_ENGINE, " active_engine " );
RegisterVariable(FG_HOVERB, " height/span " );
RegisterVariable(FG_PITCH_TRIM_CMD, " pitch_trim_cmd " );
+ RegisterVariable(FG_YAW_TRIM_CMD, " yaw_trim_cmd " );
+ RegisterVariable(FG_ROLL_TRIM_CMD, " roll_trim_cmd " );
RegisterVariable(FG_LEFT_BRAKE_CMD, " left_brake_cmd " );
RegisterVariable(FG_RIGHT_BRAKE_CMD," right_brake_cmd ");
RegisterVariable(FG_CENTER_BRAKE_CMD," center_brake_cmd ");
+ RegisterVariable(FG_ALPHAH, " h-tail alpha " );
+ RegisterVariable(FG_ALPHAW, " wing alpha " );
+ RegisterVariable(FG_LBARH, " h-tail arm " );
+ RegisterVariable(FG_LBARV, " v-tail arm " );
+ RegisterVariable(FG_HTAILAREA, " h-tail area " );
+ RegisterVariable(FG_VTAILAREA, " v-tail area " );
+ RegisterVariable(FG_VBARH, " h-tail volume " );
+ RegisterVariable(FG_VBARV, " v-tail volume " );
RegisterVariable(FG_SET_LOGGING, " data_logging " );
- if (debug_lvl & 2) cout << "Instantiated: FGState" << endl;
+ Debug(0);
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
FGState::~FGState()
{
- if (debug_lvl & 2) cout << "Destroyed: FGState" << endl;
+ Debug(1);
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-float FGState::GetParameter(eParam val_idx) {
- float scratch;
+double FGState::GetParameter(eParam val_idx) {
+ double scratch;
switch(val_idx) {
case FG_TIME:
return Aircraft->GetWingSpan();
case FG_CBAR:
return Aircraft->Getcbar();
+ case FG_LBARH:
+ return Aircraft->Getlbarh();
+ case FG_LBARV:
+ return Aircraft->Getvbarh();
+ case FG_HTAILAREA:
+ return Aircraft->GetHTailArea();
+ case FG_VTAILAREA:
+ return Aircraft->GetVTailArea();
+ case FG_VBARH:
+ return Aircraft->Getvbarh();
+ case FG_VBARV:
+ return Aircraft->Getvbarv();
case FG_ALPHA:
return Translation->Getalpha();
+ case FG_ALPHAW:
+ return Translation->Getalpha() + Aircraft->GetWingIncidence();
case FG_ALPHADOT:
return Translation->Getadot();
case FG_BETA:
return Translation->Getbeta();
+ case FG_ABETA:
+ return fabs(Translation->Getbeta());
case FG_BETADOT:
return Translation->Getbdot();
case FG_PHI:
return Rotation->GetPQR(eP);
case FG_YAWRATE:
return Rotation->GetPQR(eR);
+ case FG_AEROP:
+ return Rotation->GetAeroPQR(eP);
+ case FG_AEROQ:
+ return Rotation->GetAeroPQR(eQ);
+ case FG_AEROR:
+ return Rotation->GetAeroPQR(eR);
case FG_CL_SQRD:
if (Translation->Getqbar() > 0.00)
scratch = Aerodynamics->GetvLastFs(eLift)/(Aircraft->GetWingArea()*Translation->Getqbar());
case FG_THROTTLE_POS:
if (ActiveEngine < 0) return FCS->GetThrottlePos(0);
else return FCS->GetThrottlePos(ActiveEngine);
+ case FG_MAGNETO_CMD:
+ if (ActiveEngine < 0) return Propulsion->GetEngine(0)->GetMagnetos();
+ else return Propulsion->GetEngine(ActiveEngine)->GetMagnetos();
+ case FG_STARTER_CMD:
+ if (ActiveEngine < 0) {
+ if (Propulsion->GetEngine(0)->GetStarter()) return 1.0;
+ else return 0.0;
+ } else {
+ if (Propulsion->GetEngine(ActiveEngine)->GetStarter()) return 1.0;
+ else return 0.0;
+ }
+ case FG_MIXTURE_CMD:
+ if (ActiveEngine < 0) return FCS->GetMixtureCmd(0);
+ else return FCS->GetMixtureCmd(ActiveEngine);
+ case FG_MIXTURE_POS:
+ if (ActiveEngine < 0) return FCS->GetMixturePos(0);
+ else return FCS->GetMixturePos(ActiveEngine);
case FG_HOVERB:
- return Position->GetHOverB();
+ return Position->GetHOverBMAC();
case FG_PITCH_TRIM_CMD:
return FCS->GetPitchTrimCmd();
+ case FG_YAW_TRIM_CMD:
+ return FCS->GetYawTrimCmd();
+ case FG_ROLL_TRIM_CMD:
+ return FCS->GetRollTrimCmd();
+ case FG_GEAR_CMD:
+ return FCS->GetGearCmd();
+ case FG_GEAR_POS:
+ return FCS->GetGearPos();
default:
- cerr << "FGState::GetParameter() - No handler for parameter " << val_idx << endl;
+ cerr << "FGState::GetParameter() - No handler for parameter " << paramdef[val_idx] << endl;
return 0.0;
}
return 0;
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-float FGState::GetParameter(string val_string) {
+double FGState::GetParameter(string val_string) {
return GetParameter(coeffdef[val_string]);
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-eParam FGState::GetParameterIndex(string val_string) {
+eParam FGState::GetParameterIndex(string val_string)
+{
return coeffdef[val_string];
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGState::SetParameter(eParam val_idx, float val) {
+void FGState::SetParameter(eParam val_idx, double val)
+{
+ unsigned i;
+
switch(val_idx) {
case FG_ELEVATOR_POS:
FCS->SetDePos(val);
FCS->SetDfPos(val);
break;
case FG_THROTTLE_POS:
- FCS->SetThrottlePos(ActiveEngine,val);
+ if (ActiveEngine == -1) {
+ for (i=0; i<Propulsion->GetNumEngines(); i++) {
+ FCS->SetThrottlePos(i,val);
+ }
+ } else {
+ FCS->SetThrottlePos(ActiveEngine,val);
+ }
+ break;
+ case FG_MIXTURE_POS:
+ if (ActiveEngine == -1) {
+ for (i=0; i<Propulsion->GetNumEngines(); i++) {
+ FCS->SetMixturePos(i,val);
+ }
+ } else {
+ FCS->SetMixturePos(ActiveEngine,val);
+ }
break;
case FG_ELEVATOR_CMD:
FCS->SetDfCmd(val);
break;
case FG_THROTTLE_CMD:
- FCS->SetThrottleCmd(ActiveEngine,val);
+ if (ActiveEngine == -1) {
+ for (i=0; i<Propulsion->GetNumEngines(); i++) {
+ FCS->SetThrottleCmd(i,val);
+ }
+ } else {
+ FCS->SetThrottleCmd(ActiveEngine,val);
+ }
+ break;
+ case FG_MIXTURE_CMD:
+ if (ActiveEngine == -1) {
+ for (i=0; i<Propulsion->GetNumEngines(); i++) {
+ FCS->SetMixtureCmd(i,val);
+ }
+ } else {
+ FCS->SetMixtureCmd(ActiveEngine,val);
+ }
+ break;
+ case FG_MAGNETO_CMD:
+ if (ActiveEngine == -1) {
+ for (i=0; i<Propulsion->GetNumEngines(); i++) {
+ Propulsion->GetEngine(i)->SetMagnetos((int)val);
+ }
+ } else {
+ Propulsion->GetEngine(ActiveEngine)->SetMagnetos((int)val);
+ }
+ break;
+ case FG_STARTER_CMD:
+ if (ActiveEngine == -1) {
+ for (i=0; i<Propulsion->GetNumEngines(); i++) {
+ if (val < 0.001)
+ Propulsion->GetEngine(i)->SetStarter(false);
+ else if (val >= 0.001)
+ Propulsion->GetEngine(i)->SetStarter(true);
+ }
+ } else {
+ Propulsion->GetEngine(ActiveEngine)->SetStarter(true);
+ }
break;
-
case FG_ACTIVE_ENGINE:
ActiveEngine = (int)val;
break;
case FG_RIGHT_BRAKE_CMD:
FCS->SetRBrake(val);
break;
-
+ case FG_GEAR_CMD:
+ FCS->SetGearCmd(val);
+ break;
+ case FG_GEAR_POS:
+ FCS->SetGearPos(val);
+ break;
case FG_SET_LOGGING:
if (val < -0.01) Output->Disable();
else if (val > 0.01) Output->Enable();
// Reset: Assume all angles READ FROM FILE IN DEGREES !!
//
-bool FGState::Reset(string path, string acname, string fname) {
+bool FGState::Reset(string path, string acname, string fname)
+{
string resetDef;
- float U, V, W;
- float phi, tht, psi;
- float latitude, longitude, h;
-
- resetDef = path + "/" + acname + "/" + fname + ".xml";
-
-#if defined ( sgi ) && !defined( __GNUC__ )
- ifstream resetfile(resetDef.c_str(), ios::in );
-#else
- ifstream resetfile(resetDef.c_str(), ios::in | ios::binary );
-#endif
+ string token="";
- if (resetfile) {
- resetfile >> U;
- resetfile >> V;
- resetfile >> W;
- resetfile >> latitude;
- resetfile >> longitude;
- resetfile >> phi;
- resetfile >> tht;
- resetfile >> psi;
- resetfile >> h;
- resetfile.close();
-
- Position->SetLatitude(latitude*DEGTORAD);
- Position->SetLongitude(longitude*DEGTORAD);
- Position->Seth(h);
-
- Initialize(U, V, W, phi*DEGTORAD, tht*DEGTORAD, psi*DEGTORAD,
- latitude*DEGTORAD, longitude*DEGTORAD, h);
+ double U, V, W;
+ double phi, tht, psi;
+ double latitude, longitude, h;
+ double wdir, wmag, wnorth, weast;
- return true;
- } else {
- cerr << "Unable to load reset file " << fname << endl;
+# ifndef macintosh
+ resetDef = path + "/" + acname + "/" + fname + ".xml";
+# else
+ resetDef = path + ";" + acname + ";" + fname + ".xml";
+# endif
+
+ FGConfigFile resetfile(resetDef);
+ if (!resetfile.IsOpen()) 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;
+ } else {
+ resetfile.GetNextConfigLine();
+ resetfile >> token;
+ cout << "Resetting using: " << token << endl << endl;
}
+
+ while (token != string("/initialize") && token != string("EOF")) {
+ if (token == "UBODY") resetfile >> U;
+ if (token == "VBODY") resetfile >> V;
+ if (token == "WBODY") resetfile >> W;
+ if (token == "LATITUDE") resetfile >> latitude;
+ if (token == "LONGITUDE") resetfile >> longitude;
+ if (token == "PHI") resetfile >> phi;
+ if (token == "THETA") resetfile >> tht;
+ if (token == "PSI") resetfile >> psi;
+ if (token == "ALTITUDE") resetfile >> h;
+ if (token == "WINDDIR") resetfile >> wdir;
+ if (token == "VWIND") resetfile >> wmag;
+
+ resetfile >> token;
+ }
+
+
+ Position->SetLatitude(latitude*degtorad);
+ Position->SetLongitude(longitude*degtorad);
+ Position->Seth(h);
+
+ wnorth = wmag*ktstofps*cos(wdir*degtorad);
+ weast = wmag*ktstofps*sin(wdir*degtorad);
+
+ Initialize(U, V, W, phi*degtorad, tht*degtorad, psi*degtorad,
+ latitude*degtorad, longitude*degtorad, h, wnorth, weast, 0.0);
+
+ return true;
}
//***************************************************************************
// Initialize: Assume all angles GIVEN IN RADIANS !!
//
-void FGState::Initialize(float U, float V, float W,
- float phi, float tht, float psi,
- float Latitude, float Longitude, float H) {
- FGColumnVector vUVW(3);
- FGColumnVector vLocalVelNED(3);
- FGColumnVector vLocalEuler(3);
- float alpha, beta;
- float qbar, Vt;
+void FGState::Initialize(double U, double V, double W,
+ double phi, double tht, double psi,
+ double Latitude, double Longitude, double H,
+ double wnorth, double weast, double wdown)
+{
+ double alpha, beta;
+ double qbar, Vt;
+ FGColumnVector3 vAeroUVW;
Position->SetLatitude(Latitude);
Position->SetLongitude(Longitude);
Position->Seth(H);
Atmosphere->Run();
+
+ vLocalEuler << phi << tht << psi;
+ Rotation->SetEuler(vLocalEuler);
- if (W != 0.0)
- alpha = U*U > 0.0 ? atan2(W, U) : 0.0;
+ InitMatrices(phi, tht, psi);
+
+ vUVW << U << V << W;
+ Translation->SetUVW(vUVW);
+
+ Atmosphere->SetWindNED(wnorth, weast, wdown);
+
+ vAeroUVW = vUVW + mTl2b*Atmosphere->GetWindNED();
+
+ if (vAeroUVW(eW) != 0.0)
+ alpha = vAeroUVW(eU)*vAeroUVW(eU) > 0.0 ? atan2(vAeroUVW(eW), vAeroUVW(eU)) : 0.0;
else
alpha = 0.0;
- if (V != 0.0)
- beta = U*U+W*W > 0.0 ? atan2(V, (fabs(U)/U)*sqrt(U*U + W*W)) : 0.0;
+ if (vAeroUVW(eV) != 0.0)
+ beta = vAeroUVW(eU)*vAeroUVW(eU)+vAeroUVW(eW)*vAeroUVW(eW) > 0.0 ? atan2(vAeroUVW(eV), (fabs(vAeroUVW(eU))/vAeroUVW(eU))*sqrt(vAeroUVW(eU)*vAeroUVW(eU) + vAeroUVW(eW)*vAeroUVW(eW))) : 0.0;
else
beta = 0.0;
- vUVW << U << V << W;
- Translation->SetUVW(vUVW);
-
- vLocalEuler << phi << tht << psi;
- Rotation->SetEuler(vLocalEuler);
-
Translation->SetAB(alpha, beta);
Vt = sqrt(U*U + V*V + W*W);
qbar = 0.5*(U*U + V*V + W*W)*Atmosphere->GetDensity();
Translation->Setqbar(qbar);
- InitMatrices(phi, tht, psi);
-
vLocalVelNED = mTb2l*vUVW;
Position->SetvVel(vLocalVelNED);
}
void FGState::Initialize(FGInitialCondition *FGIC) {
- float tht,psi,phi;
- float U, V, W, h;
- float latitude, longitude;
-
+ double tht,psi,phi;
+ double U, V, W, h;
+ double latitude, longitude;
+ double wnorth,weast, wdown;
+
latitude = FGIC->GetLatitudeRadIC();
longitude = FGIC->GetLongitudeRadIC();
h = FGIC->GetAltitudeFtIC();
tht = FGIC->GetThetaRadIC();
phi = FGIC->GetPhiRadIC();
psi = FGIC->GetPsiRadIC();
-
- Initialize(U, V, W, phi, tht, psi, latitude, longitude, h);
+ wnorth = FGIC->GetWindNFpsIC();
+ weast = FGIC->GetWindEFpsIC();
+ wdown = FGIC->GetWindDFpsIC();
Position->SetSeaLevelRadius( FGIC->GetSeaLevelRadiusFtIC() );
Position->SetRunwayRadius( FGIC->GetSeaLevelRadiusFtIC() +
FGIC->GetTerrainAltitudeFtIC() );
+ // need to fix the wind speed args, here.
+ Initialize(U, V, W, phi, tht, psi, latitude, longitude, h, wnorth, weast, wdown);
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGState::InitMatrices(float phi, float tht, float psi) {
- float thtd2, psid2, phid2;
- float Sthtd2, Spsid2, Sphid2;
- float Cthtd2, Cpsid2, Cphid2;
- float Cphid2Cthtd2;
- float Cphid2Sthtd2;
- float Sphid2Sthtd2;
- float Sphid2Cthtd2;
+void FGState::InitMatrices(double phi, double tht, double psi) {
+ double thtd2, psid2, phid2;
+ double Sthtd2, Spsid2, Sphid2;
+ double Cthtd2, Cpsid2, Cphid2;
+ double Cphid2Cthtd2;
+ double Cphid2Sthtd2;
+ double Sphid2Sthtd2;
+ double Sphid2Cthtd2;
thtd2 = tht/2.0;
psid2 = psi/2.0;
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGState::CalcMatrices(void) {
- float Q0Q0, Q1Q1, Q2Q2, Q3Q3;
- float Q0Q1, Q0Q2, Q0Q3, Q1Q2;
- float Q1Q3, Q2Q3;
+ double Q0Q0, Q1Q1, Q2Q2, Q3Q3;
+ double Q0Q1, Q0Q2, Q0Q3, Q1Q2;
+ double Q1Q3, Q2Q3;
Q0Q0 = vQtrn(1)*vQtrn(1);
Q1Q1 = vQtrn(2)*vQtrn(2);
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGState::IntegrateQuat(FGColumnVector vPQR, int rate) {
+void FGState::IntegrateQuat(FGColumnVector3 vPQR, int rate) {
vQdot(1) = -0.5*(vQtrn(2)*vPQR(eP) + vQtrn(3)*vPQR(eQ) + vQtrn(4)*vPQR(eR));
vQdot(2) = 0.5*(vQtrn(1)*vPQR(eP) + vQtrn(3)*vPQR(eR) - vQtrn(4)*vPQR(eQ));
vQdot(3) = 0.5*(vQtrn(1)*vPQR(eQ) + vQtrn(4)*vPQR(eP) - vQtrn(2)*vPQR(eR));
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-FGColumnVector FGState::CalcEuler(void) {
+FGColumnVector3& FGState::CalcEuler(void) {
if (mTl2b(3,3) == 0.0) mTl2b(3,3) = 0.0000001;
if (mTl2b(1,1) == 0.0) mTl2b(1,1) = 0.0000001;
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-FGMatrix FGState::GetTs2b(float alpha, float beta) {
- float ca, cb, sa, sb;
+FGMatrix33& FGState::GetTs2b(void)
+{
+ double ca, cb, sa, sb;
+
+ double alpha = Translation->Getalpha();
+ double beta = Translation->Getbeta();
ca = cos(alpha);
sa = sin(alpha);
cb = cos(beta);
sb = sin(beta);
- mTs2b(1,1) = -ca*cb;
+ mTs2b(1,1) = ca*cb;
mTs2b(1,2) = -ca*sb;
- mTs2b(1,3) = sa;
- mTs2b(2,1) = -sb;
+ mTs2b(1,3) = -sa;
+ mTs2b(2,1) = sb;
mTs2b(2,2) = cb;
mTs2b(2,3) = 0.0;
- mTs2b(3,1) = -sa*cb;
+ mTs2b(3,1) = sa*cb;
mTs2b(3,2) = -sa*sb;
- mTs2b(3,3) = -ca;
+ mTs2b(3,3) = ca;
return mTs2b;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGState::Debug(void)
+FGMatrix33& FGState::GetTb2s(void)
{
- //TODO: Add your source code here
+ float alpha,beta;
+ float ca, cb, sa, sb;
+
+ alpha = Translation->Getalpha();
+ beta = Translation->Getbeta();
+
+ ca = cos(alpha);
+ sa = sin(alpha);
+ cb = cos(beta);
+ sb = sin(beta);
+
+ mTb2s(1,1) = ca*cb;
+ mTb2s(1,2) = sb;
+ mTb2s(1,3) = sa*cb;
+ mTb2s(2,1) = -ca*sb;
+ mTb2s(2,2) = cb;
+ mTb2s(2,3) = -sa*sb;
+ mTb2s(3,1) = -sa;
+ mTb2s(3,2) = 0.0;
+ mTb2s(3,3) = ca;
+
+ return mTb2s;
}
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
+void FGState::ReportState(void) {
+ char out[80], flap[10], gear[12];
+
+ cout << endl << " JSBSim State" << endl;
+ snprintf(out,80," Weight: %7.0f lbs. CG: %5.1f, %5.1f, %5.1f inches\n",
+ FDMExec->GetMassBalance()->GetWeight(),
+ FDMExec->GetMassBalance()->GetXYZcg(1),
+ FDMExec->GetMassBalance()->GetXYZcg(2),
+ FDMExec->GetMassBalance()->GetXYZcg(3));
+ cout << out;
+ if( FCS->GetDfPos() <= 0.01)
+ snprintf(flap,10,"Up");
+ else
+ snprintf(flap,10,"%2.0f",FCS->GetDfPos());
+ if(FCS->GetGearPos() < 0.01)
+ snprintf(gear,12,"Up");
+ else if(FCS->GetGearPos() > 0.99)
+ snprintf(gear,12,"Down");
+ else
+ snprintf(gear,12,"In Transit");
+ snprintf(out,80, " Flaps: %3s Gear: %12s\n",flap,gear);
+ cout << out;
+ snprintf(out,80, " Speed: %4.0f KCAS Mach: %5.2f\n",
+ FDMExec->GetAuxiliary()->GetVcalibratedKTS(),
+ GetParameter(FG_MACH) );
+ cout << out;
+ snprintf(out,80, " Altitude: %7.0f ft. AGL Altitude: %7.0f ft.\n",
+ Position->Geth(),
+ Position->GetDistanceAGL() );
+ cout << out;
+ snprintf(out,80, " Angle of Attack: %6.2f deg Pitch Angle: %6.2f deg\n",
+ GetParameter(FG_ALPHA)*radtodeg,
+ Rotation->Gettht()*radtodeg );
+ cout << out;
+ snprintf(out,80, " Flight Path Angle: %6.2f deg Climb Rate: %5.0f ft/min\n",
+ Position->GetGamma()*radtodeg,
+ Position->Gethdot()*60 );
+ cout << out;
+ snprintf(out,80, " Normal Load Factor: %4.2f g's Pitch Rate: %5.2f deg/s\n",
+ Aircraft->GetNlf(),
+ GetParameter(FG_PITCHRATE)*radtodeg );
+ cout << out;
+ snprintf(out,80, " Heading: %3.0f deg true Sideslip: %5.2f deg\n",
+ Rotation->Getpsi()*radtodeg,
+ GetParameter(FG_BETA)*radtodeg );
+ cout << out;
+ snprintf(out,80, " Bank Angle: %5.2f deg\n",
+ Rotation->Getphi()*radtodeg );
+ cout << out;
+ snprintf(out,80, " Elevator: %5.2f deg Left Aileron: %5.2f deg Rudder: %5.2f deg\n",
+ GetParameter(FG_ELEVATOR_POS)*radtodeg,
+ GetParameter(FG_AILERON_POS)*radtodeg,
+ GetParameter(FG_RUDDER_POS)*radtodeg );
+ cout << out;
+ snprintf(out,80, " Throttle: %5.2f%c\n",
+ FCS->GetThrottlePos(0)*100,'%' );
+ cout << out;
+
+ snprintf(out,80, " Wind Components: %5.2f kts head wind, %5.2f kts cross wind\n",
+ FDMExec->GetAuxiliary()->GetHeadWind()*fpstokts,
+ FDMExec->GetAuxiliary()->GetCrossWind()*fpstokts );
+ cout << out;
+
+ snprintf(out,80, " Ground Speed: %4.0f knots , Ground Track: %3.0f deg true\n",
+ Position->GetVground()*fpstokts,
+ Position->GetGroundTrack()*radtodeg );
+ cout << out;
+
+}
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+// 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 FGState::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: FGState" << endl;
+ if (from == 1) cout << "Destroyed: FGState" << 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