------------- 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
+ the terms of the GNU Lesser 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
+ FOR A PARTICULAR PURPOSE. See the GNU Lesser General Public License for more
details.
- You should have received a copy of the GNU General Public License along with
+ You should have received a copy of the GNU Lesser 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
+ Further information about the GNU Lesser General Public License can also be found on
the world wide web at http://www.gnu.org.
FUNCTIONAL DESCRIPTION
INCLUDES
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
-#ifdef FGFS
-# include <simgear/compiler.h>
-# include <math.h>
-#else
-# if defined(sgi) && !defined(__GNUC__)
-# include <math.h>
-# else
-# include <cmath>
-# endif
-#endif
-
-#ifdef _WIN32
-//#define snprintf _snprintf
-#endif
+#include <cmath>
#include "FGState.h"
Propagate = FDMExec->GetPropagate();
Auxiliary = FDMExec->GetAuxiliary();
FCS = FDMExec->GetFCS();
- Output = FDMExec->GetOutput();
Atmosphere = FDMExec->GetAtmosphere();
Aerodynamics = FDMExec->GetAerodynamics();
GroundReactions = FDMExec->GetGroundReactions();
FGState::~FGState()
{
- unbind();
Debug(1);
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-FGMatrix33& FGState::GetTs2b(void)
-{
- 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;
-}
-
-//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-
-FGMatrix33& FGState::GetTb2s(void)
-{
- float alpha,beta;
- float 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);
-}
-
-//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-
-void FGState::unbind(void)
-{
- PropertyManager->Untie("sim-time-sec");
+ PropertyManager->Tie("sim-time-sec", this, &FGState::Getsim_time);
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
projects / flightgear.git / blobdiff