-/*******************************************************************************
-
+/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
Module: FGState.cpp
Author: Jon Berndt
Date started: 11/17/98
--------------------------------------------------------------------------------
11/17/98 JSB Created
-********************************************************************************
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
INCLUDES
-*******************************************************************************/
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
#ifdef FGFS
-# include <Include/compiler.h>
-# ifdef FG_HAVE_STD_INCLUDES
-# include <cmath>
-# else
+# include <simgear/compiler.h>
+# include <math.h>
+#else
+# if defined(sgi) && !defined(__GNUC__)
# include <math.h>
+# else
+# include <cmath>
# endif
-#else
-# include <cmath>
+#endif
+
+#ifdef _WIN32
+//#define snprintf _snprintf
#endif
#include "FGState.h"
-#include "FGFDMExec.h"
-#include "FGAtmosphere.h"
-#include "FGFCS.h"
-#include "FGAircraft.h"
-#include "FGTranslation.h"
-#include "FGRotation.h"
-#include "FGPosition.h"
-#include "FGAuxiliary.h"
-#include "FGOutput.h"
-/*******************************************************************************
-************************************ CODE **************************************
-*******************************************************************************/
+namespace JSBSim {
+static const char *IdSrc = "$Id$";
+static const char *IdHdr = ID_STATE;
+
+/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+MACROS
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
+
+/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+CLASS IMPLEMENTATION
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
FGState::FGState(FGFDMExec* fdex)
{
FDMExec = fdex;
- Vt = 0.0;
- latitude = longitude = 0.0;
- adot = bdot = 0.0;
- h = 0.0;
- a = 1000.0;
- qbar = 0.0;
- sim_time = dt = 0.1;
+ sim_time = 0.0;
+ dt = 1.0/120.0;
+
+ Aircraft = FDMExec->GetAircraft();
+ Propagate = FDMExec->GetPropagate();
+ Auxiliary = FDMExec->GetAuxiliary();
+ FCS = FDMExec->GetFCS();
+ Output = FDMExec->GetOutput();
+ Atmosphere = FDMExec->GetAtmosphere();
+ Aerodynamics = FDMExec->GetAerodynamics();
+ GroundReactions = FDMExec->GetGroundReactions();
+ Propulsion = FDMExec->GetPropulsion();
+ PropertyManager = FDMExec->GetPropertyManager();
+
+ bind();
+
+ Debug(0);
}
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-FGState::~FGState(void)
+FGState::~FGState()
{
+ unbind();
+ Debug(1);
}
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-bool FGState::Reset(string path, string fname)
+void FGState::Initialize(FGInitialCondition *FGIC)
{
- string resetDef;
- float U, V, W;
- float phi, tht, psi;
- float alpha, beta, gamma;
- float Q0, Q1, Q2, Q3;
- float T[4][4];
-
- resetDef = path + "/" + FDMExec->GetAircraft()->GetAircraftName() + "/" + fname;
-
- ifstream resetfile(resetDef.c_str());
-
- if (resetfile) {
- resetfile >> U;
- resetfile >> V;
- resetfile >> W;
- resetfile >> latitude;
- resetfile >> longitude;
- resetfile >> phi;
- resetfile >> tht;
- resetfile >> psi;
- resetfile >> h;
- resetfile.close();
-
-// Change all angular measurements from degrees (as in config file) to radians
-
- gamma = 0.0;
- if (W != 0.0)
- alpha = U*U > 0.0 ? atan2(W, U) : 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;
- else
- beta = 0.0;
-
- latitude *= M_PI / 180.0;
- longitude *= M_PI / 180.0;
- phi *= M_PI / 180.0;
- tht *= M_PI / 180.0;
- psi *= M_PI / 180.0;
-
- FDMExec->GetTranslation()->SetUVW(U, V, W);
- FDMExec->GetRotation()->SetEuler(phi, tht, psi);
- FDMExec->GetTranslation()->SetABG(alpha, beta, gamma);
-
- Vt = sqrt(U*U + V*V + W*W);
- qbar = 0.5*(U*U + V*V + W*W)*FDMExec->GetAtmosphere()->CalcRho(h);
-
- Q0 = sin(psi*0.5)*sin(tht*0.5)*sin(phi*0.5) + cos(psi*0.5)*cos(tht*0.5)*cos(phi*0.5);
- Q1 = -sin(psi*0.5)*sin(tht*0.5)*cos(phi*0.5) + cos(psi*0.5)*cos(tht*0.5)*sin(phi*0.5);
- Q2 = sin(psi*0.5)*cos(tht*0.5)*sin(phi*0.5) + cos(psi*0.5)*sin(tht*0.5)*cos(phi*0.5);
- Q3 = sin(psi*0.5)*cos(tht*0.5)*cos(phi*0.5) - cos(psi*0.5)*sin(tht*0.5)*sin(phi*0.5);
-
- FDMExec->GetRotation()->SetQ0123(Q0, Q1, Q2, Q3);
-
- T[1][1] = Q0*Q0 + Q1*Q1 - Q2*Q2 - Q3*Q3;
- T[1][2] = 2*(Q1*Q2 + Q0*Q3);
- T[1][3] = 2*(Q1*Q3 - Q0*Q2);
- T[2][1] = 2*(Q1*Q2 - Q0*Q3);
- T[2][2] = Q0*Q0 - Q1*Q1 + Q2*Q2 - Q3*Q3;
- T[2][3] = 2*(Q2*Q3 + Q0*Q1);
- T[3][1] = 2*(Q1*Q3 + Q0*Q2);
- T[3][2] = 2*(Q2*Q3 - Q0*Q1);
- T[3][3] = Q0*Q0 - Q1*Q1 - Q2*Q2 + Q3*Q3;
-
- FDMExec->GetPosition()->SetT(T[1][1], T[1][2], T[1][3],
- T[2][1], T[2][2], T[2][3],
- T[3][1], T[3][2], T[3][3]);
-
- return true;
- } else {
- cerr << "Unable to load reset file " << fname << endl;
- return false;
- }
+ sim_time = 0.0;
+
+ Propagate->SetInitialState( FGIC );
+
+ Atmosphere->Run();
+ Atmosphere->SetWindNED( FGIC->GetWindNFpsIC(),
+ FGIC->GetWindEFpsIC(),
+ FGIC->GetWindDFpsIC() );
+
+ FGColumnVector3 vAeroUVW;
+ vAeroUVW = Propagate->GetUVW() + Propagate->GetTl2b()*Atmosphere->GetWindNED();
+
+ double alpha, beta;
+ if (vAeroUVW(eW) != 0.0)
+ alpha = vAeroUVW(eU)*vAeroUVW(eU) > 0.0 ? atan2(vAeroUVW(eW), vAeroUVW(eU)) : 0.0;
+ else
+ alpha = 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;
+
+ Auxiliary->SetAB(alpha, beta);
+
+ double Vt = vAeroUVW.Magnitude();
+ Auxiliary->SetVt(Vt);
+
+ Auxiliary->SetMach(Vt/Atmosphere->GetSoundSpeed());
+
+ double qbar = 0.5*Vt*Vt*Atmosphere->GetDensity();
+ Auxiliary->Setqbar(qbar);
}
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-bool FGState::StoreData(string fname)
+FGMatrix33& FGState::GetTs2b(void)
{
- ofstream datafile(fname.c_str());
-
- if (datafile) {
- datafile << FDMExec->GetTranslation()->GetU();
- datafile << FDMExec->GetTranslation()->GetV();
- datafile << FDMExec->GetTranslation()->GetW();
- datafile << latitude;
- datafile << longitude;
- datafile << FDMExec->GetRotation()->Getphi();
- datafile << FDMExec->GetRotation()->Gettht();
- datafile << FDMExec->GetRotation()->Getpsi();
- datafile << h;
- datafile.close();
- return true;
- } else {
- cerr << "Could not open dump file " << fname << endl;
- return false;
- }
+ double ca, cb, sa, sb;
+
+ double alpha = Auxiliary->Getalpha();
+ double beta = Auxiliary->Getbeta();
+
+ ca = cos(alpha);
+ sa = sin(alpha);
+ cb = cos(beta);
+ sb = sin(beta);
+
+ mTs2b(1,1) = ca*cb;
+ mTs2b(1,2) = -ca*sb;
+ mTs2b(1,3) = -sa;
+ mTs2b(2,1) = sb;
+ mTs2b(2,2) = cb;
+ mTs2b(2,3) = 0.0;
+ mTs2b(3,1) = sa*cb;
+ mTs2b(3,2) = -sa*sb;
+ mTs2b(3,3) = ca;
+
+ return mTs2b;
}
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-bool FGState::DumpData(string fname)
+FGMatrix33& FGState::GetTb2s(void)
{
- ofstream datafile(fname.c_str());
-
- if (datafile) {
- datafile << "U: " << FDMExec->GetTranslation()->GetU() << endl;
- datafile << "V: " << FDMExec->GetTranslation()->GetV() << endl;
- datafile << "W: " << FDMExec->GetTranslation()->GetW() << endl;
- datafile << "P: " << FDMExec->GetRotation()->GetP() << endl;
- datafile << "Q: " << FDMExec->GetRotation()->GetQ() << endl;
- datafile << "R: " << FDMExec->GetRotation()->GetR() << endl;
- datafile << "L: " << FDMExec->GetAircraft()->GetL() << endl;
- datafile << "M: " << FDMExec->GetAircraft()->GetM() << endl;
- datafile << "N: " << FDMExec->GetAircraft()->GetN() << endl;
- datafile << "latitude: " << latitude << endl;
- datafile << "longitude: " << longitude << endl;
- datafile << "alpha: " << FDMExec->GetTranslation()->Getalpha() << endl;
- datafile << "beta: " << FDMExec->GetTranslation()->Getbeta() << endl;
- datafile << "gamma: " << FDMExec->GetTranslation()->Getgamma() << endl;
- datafile << "phi: " << FDMExec->GetRotation()->Getphi() << endl;
- datafile << "tht: " << FDMExec->GetRotation()->Gettht() << endl;
- datafile << "psi: " << FDMExec->GetRotation()->Getpsi() << endl;
- datafile << "Pdot: " << FDMExec->GetRotation()->GetPdot() << endl;
- datafile << "Qdot: " << FDMExec->GetRotation()->GetQdot() << endl;
- datafile << "Rdot: " << FDMExec->GetRotation()->GetRdot() << endl;
- datafile << "h: " << h << endl;
- datafile << "a: " << a << endl;
- datafile << "rho: " << FDMExec->GetAtmosphere()->Getrho() << endl;
- datafile << "qbar: " << qbar << endl;
- datafile << "sim_time: " << sim_time << endl;
- datafile << "dt: " << dt << endl;
- datafile << "m: " << FDMExec->GetAircraft()->GetMass() << endl;
- datafile.close();
- return true;
- } else {
- return false;
- }
+ double alpha,beta;
+ double ca, cb, sa, sb;
+
+ alpha = Auxiliary->Getalpha();
+ beta = Auxiliary->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)
+{
+#if 0
+#if !defined(__BORLANDCPP__)
+ 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",
+ Auxiliary->GetVcalibratedKTS(),
+ Auxiliary->GetMach() );
+ cout << out;
+ snprintf(out,80, " Altitude: %7.0f ft. AGL Altitude: %7.0f ft.\n",
+ Propagate->Geth(),
+ Propagate->GetDistanceAGL() );
+ cout << out;
+ snprintf(out,80, " Angle of Attack: %6.2f deg Pitch Angle: %6.2f deg\n",
+ Auxiliary->Getalpha()*radtodeg,
+ Propagate->Gettht()*radtodeg );
+ cout << out;
+ snprintf(out,80, " Flight Path Angle: %6.2f deg Climb Rate: %5.0f ft/min\n",
+ Auxiliary->GetGamma()*radtodeg,
+ Propagate->Gethdot()*60 );
+ cout << out;
+ snprintf(out,80, " Normal Load Factor: %4.2f g's Pitch Rate: %5.2f deg/s\n",
+ Aircraft->GetNlf(),
+ Propagate->GetPQR(2)*radtodeg );
+ cout << out;
+ snprintf(out,80, " Heading: %3.0f deg true Sideslip: %5.2f deg Yaw Rate: %5.2f deg/s\n",
+ Propagate->Getpsi()*radtodeg,
+ Auxiliary->Getbeta()*radtodeg,
+ Propagate->GetPQR(3)*radtodeg );
+ cout << out;
+ snprintf(out,80, " Bank Angle: %5.2f deg Roll Rate: %5.2f deg/s\n",
+ Propagate->Getphi()*radtodeg,
+ Propagate->GetPQR(1)*radtodeg );
+ cout << out;
+ snprintf(out,80, " Elevator: %5.2f deg Left Aileron: %5.2f deg Rudder: %5.2f deg\n",
+ FCS->GetDePos(ofRad)*radtodeg,
+ FCS->GetDaLPos(ofRad)*radtodeg,
+ FCS->GetDrPos(ofRad)*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",
+ Auxiliary->GetHeadWind()*fpstokts,
+ Auxiliary->GetCrossWind()*fpstokts );
+ cout << out;
+
+ snprintf(out,80, " Ground Speed: %4.0f knots , Ground Track: %3.0f deg true\n",
+ Auxiliary->GetVground()*fpstokts,
+ Auxiliary->GetGroundTrack()*radtodeg );
+ cout << out;
+#endif
+#endif
+}
+
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
+void FGState::bind(void)
+{
+ PropertyManager->Tie("sim-time-sec",this,
+ &FGState::Getsim_time);
}
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-bool FGState::DisplayData(void)
+void FGState::unbind(void)
{
- cout << "U: " << FDMExec->GetTranslation()->GetU() << endl;
- cout << "V: " << FDMExec->GetTranslation()->GetV() << endl;
- cout << "W: " << FDMExec->GetTranslation()->GetW() << endl;
- cout << "P: " << FDMExec->GetRotation()->GetP() << endl;
- cout << "Q: " << FDMExec->GetRotation()->GetQ() << endl;
- cout << "R: " << FDMExec->GetRotation()->GetR() << endl;
- cout << "L: " << FDMExec->GetAircraft()->GetL() << endl;
- cout << "M: " << FDMExec->GetAircraft()->GetM() << endl;
- cout << "N: " << FDMExec->GetAircraft()->GetN() << endl;
- cout << "Vt: " << Vt << endl;
- cout << "latitude: " << latitude << endl;
- cout << "longitude: " << longitude << endl;
- cout << "alpha: " << FDMExec->GetTranslation()->Getalpha() << endl;
- cout << "beta: " << FDMExec->GetTranslation()->Getbeta() << endl;
- cout << "gamma: " << FDMExec->GetTranslation()->Getgamma() << endl;
- cout << "phi: " << FDMExec->GetRotation()->Getphi() << endl;
- cout << "tht: " << FDMExec->GetRotation()->Gettht() << endl;
- cout << "psi: " << FDMExec->GetRotation()->Getpsi() << endl;
- cout << "Pdot: " << FDMExec->GetRotation()->GetPdot() << endl;
- cout << "Qdot: " << FDMExec->GetRotation()->GetQdot() << endl;
- cout << "Rdot: " << FDMExec->GetRotation()->GetRdot() << endl;
- cout << "h: " << h << endl;
- cout << "a: " << a << endl;
- cout << "rho: " << FDMExec->GetAtmosphere()->Getrho() << endl;
- cout << "qbar: " << qbar << endl;
- cout << "sim_time: " << sim_time << endl;
- cout << "dt: " << dt << endl;
- cout << "m: " << FDMExec->GetAircraft()->GetMass() << endl;
-
- return true;
+ PropertyManager->Untie("sim-time-sec");
+}
+
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+// 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