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flightgear/src/FDM/JSBSim/FGState.cpp
curt 6b2e17493e Syncing with most recent JSBSim.
2001-12-07 17:10:17 +00:00

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/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
Module: FGState.cpp
Author: Jon Berndt
Date started: 11/17/98
Called by: FGFDMExec and accessed by all models.
------------- 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
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.
FUNCTIONAL DESCRIPTION
--------------------------------------------------------------------------------
See header file.
HISTORY
--------------------------------------------------------------------------------
11/17/98 JSB Created
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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 _MSC_VER
#define snprintf _snprintf
#endif
#include "FGState.h"
static const char *IdSrc = "$Id$";
static const char *IdHdr = ID_STATE;
/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
MACROS
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
#define RegisterVariable(ID,DEF) coeffdef[#ID] = ID; paramdef[ID] = DEF
/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
CLASS IMPLEMENTATION
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
//
// 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 FGJSBBase.h. The ID is what must be used
// in any config file entry which references that item.
FGState::FGState(FGFDMExec* fdex)
{
FDMExec = fdex;
a = 1000.0;
sim_time = 0.0;
dt = 1.0/120.0;
ActiveEngine = -1;
Aircraft = FDMExec->GetAircraft();
Translation = FDMExec->GetTranslation();
Rotation = FDMExec->GetRotation();
Position = FDMExec->GetPosition();
FCS = FDMExec->GetFCS();
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_WINGAREA, " wing_area " );
RegisterVariable(FG_WINGSPAN, " wingspan " );
RegisterVariable(FG_CBAR, " cbar " );
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_PSI, " heading_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_BI2VEL, " BI2Vel " );
RegisterVariable(FG_CI2VEL, " CI2Vel " );
RegisterVariable(FG_ELEVATOR_POS, " elevator_pos " );
RegisterVariable(FG_AILERON_POS, " aileron_pos " );
RegisterVariable(FG_RUDDER_POS, " rudder_pos " );
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_SPDBRAKE_CMD, " speedbrake_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_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;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
FGState::~FGState()
{
if (debug_lvl & 2) cout << "Destroyed: FGState" << endl;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
double FGState::GetParameter(eParam val_idx) {
double scratch;
switch(val_idx) {
case FG_TIME:
return sim_time;
case FG_QBAR:
return Translation->Getqbar();
case FG_WINGAREA:
return Aircraft->GetWingArea();
case FG_WINGSPAN:
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->Getphi();
case FG_THT:
return Rotation->Gettht();
case FG_PSI:
return Rotation->Getpsi();
case FG_PITCHRATE:
return Rotation->GetPQR(eQ);
case FG_ROLLRATE:
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());
else
scratch = 0.0;
return scratch*scratch;
case FG_ELEVATOR_POS:
return FCS->GetDePos();
case FG_AILERON_POS:
return FCS->GetDaPos();
case FG_RUDDER_POS:
return FCS->GetDrPos();
case FG_SPDBRAKE_POS:
return FCS->GetDsbPos();
case FG_SPOILERS_POS:
return FCS->GetDspPos();
case FG_FLAPS_POS:
return FCS->GetDfPos();
case FG_ELEVATOR_CMD:
return FCS->GetDeCmd();
case FG_AILERON_CMD:
return FCS->GetDaCmd();
case FG_RUDDER_CMD:
return FCS->GetDrCmd();
case FG_SPDBRAKE_CMD:
return FCS->GetDsbCmd();
case FG_SPOILERS_CMD:
return FCS->GetDspCmd();
case FG_FLAPS_CMD:
return FCS->GetDfCmd();
case FG_MACH:
return Translation->GetMach();
case FG_ALTITUDE:
return Position->Geth();
case FG_BI2VEL:
if(Translation->GetVt() > 0)
return Aircraft->GetWingSpan()/(2.0 * Translation->GetVt());
else
return 0;
case FG_CI2VEL:
if(Translation->GetVt() > 0)
return Aircraft->Getcbar()/(2.0 * Translation->GetVt());
else
return 0;
case FG_THROTTLE_CMD:
if (ActiveEngine < 0) return FCS->GetThrottleCmd(0);
else return FCS->GetThrottleCmd(ActiveEngine);
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->GetHOverBMAC();
case FG_PITCH_TRIM_CMD:
return FCS->GetPitchTrimCmd();
case FG_GEAR_CMD:
return FCS->GetGearCmd();
case FG_GEAR_POS:
return FCS->GetGearPos();
default:
cerr << "FGState::GetParameter() - No handler for parameter " << paramdef[val_idx] << endl;
return 0.0;
}
return 0;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
double FGState::GetParameter(string val_string) {
return GetParameter(coeffdef[val_string]);
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
eParam FGState::GetParameterIndex(string val_string)
{
return coeffdef[val_string];
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGState::SetParameter(eParam val_idx, double val)
{
int i;
switch(val_idx) {
case FG_ELEVATOR_POS:
FCS->SetDePos(val);
break;
case FG_AILERON_POS:
FCS->SetDaPos(val);
break;
case FG_RUDDER_POS:
FCS->SetDrPos(val);
break;
case FG_SPDBRAKE_POS:
FCS->SetDsbPos(val);
break;
case FG_SPOILERS_POS:
FCS->SetDspPos(val);
break;
case FG_FLAPS_POS:
FCS->SetDfPos(val);
break;
case FG_THROTTLE_POS:
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->SetDeCmd(val);
break;
case FG_AILERON_CMD:
FCS->SetDaCmd(val);
break;
case FG_RUDDER_CMD:
FCS->SetDrCmd(val);
break;
case FG_SPDBRAKE_CMD:
FCS->SetDsbCmd(val);
break;
case FG_SPOILERS_CMD:
FCS->SetDspCmd(val);
break;
case FG_FLAPS_CMD:
FCS->SetDfCmd(val);
break;
case FG_THROTTLE_CMD:
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_LEFT_BRAKE_CMD:
FCS->SetLBrake(val);
break;
case FG_CENTER_BRAKE_CMD:
FCS->SetCBrake(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();
else Output->Toggle();
break;
default:
cerr << "Parameter '" << val_idx << "' (" << paramdef[val_idx] << ") not handled" << endl;
}
}
//***************************************************************************
//
// Reset: Assume all angles READ FROM FILE IN DEGREES !!
//
bool FGState::Reset(string path, string acname, string fname)
{
string resetDef;
string token="";
double U, V, W;
double phi, tht, psi;
double latitude, longitude, h;
double wdir, wmag, wnorth, weast;
# 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;
}
resetfile.GetNextConfigLine();
resetfile >> token;
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(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);
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 (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;
Translation->SetAB(alpha, beta);
Vt = sqrt(U*U + V*V + W*W);
Translation->SetVt(Vt);
Translation->SetMach(Vt/Atmosphere->GetSoundSpeed());
qbar = 0.5*(U*U + V*V + W*W)*Atmosphere->GetDensity();
Translation->Setqbar(qbar);
vLocalVelNED = mTb2l*vUVW;
Position->SetvVel(vLocalVelNED);
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGState::Initialize(FGInitialCondition *FGIC) {
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();
U = FGIC->GetUBodyFpsIC();
V = FGIC->GetVBodyFpsIC();
W = FGIC->GetWBodyFpsIC();
tht = FGIC->GetThetaRadIC();
phi = FGIC->GetPhiRadIC();
psi = FGIC->GetPsiRadIC();
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);
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
bool FGState::StoreData(string fname) {
ofstream datafile(fname.c_str());
if (datafile) {
datafile << Translation->GetUVW(eU);
datafile << Translation->GetUVW(eV);
datafile << Translation->GetUVW(eW);
datafile << Position->GetLatitude();
datafile << Position->GetLongitude();
datafile << Rotation->GetEuler(ePhi);
datafile << Rotation->GetEuler(eTht);
datafile << Rotation->GetEuler(ePsi);
datafile << Position->Geth();
datafile.close();
return true;
} else {
cerr << "Could not open dump file " << fname << endl;
return false;
}
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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;
phid2 = phi/2.0;
Sthtd2 = sin(thtd2);
Spsid2 = sin(psid2);
Sphid2 = sin(phid2);
Cthtd2 = cos(thtd2);
Cpsid2 = cos(psid2);
Cphid2 = cos(phid2);
Cphid2Cthtd2 = Cphid2*Cthtd2;
Cphid2Sthtd2 = Cphid2*Sthtd2;
Sphid2Sthtd2 = Sphid2*Sthtd2;
Sphid2Cthtd2 = Sphid2*Cthtd2;
vQtrn(1) = Cphid2Cthtd2*Cpsid2 + Sphid2Sthtd2*Spsid2;
vQtrn(2) = Sphid2Cthtd2*Cpsid2 - Cphid2Sthtd2*Spsid2;
vQtrn(3) = Cphid2Sthtd2*Cpsid2 + Sphid2Cthtd2*Spsid2;
vQtrn(4) = Cphid2Cthtd2*Spsid2 - Sphid2Sthtd2*Cpsid2;
CalcMatrices();
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGState::CalcMatrices(void) {
double Q0Q0, Q1Q1, Q2Q2, Q3Q3;
double Q0Q1, Q0Q2, Q0Q3, Q1Q2;
double Q1Q3, Q2Q3;
Q0Q0 = vQtrn(1)*vQtrn(1);
Q1Q1 = vQtrn(2)*vQtrn(2);
Q2Q2 = vQtrn(3)*vQtrn(3);
Q3Q3 = vQtrn(4)*vQtrn(4);
Q0Q1 = vQtrn(1)*vQtrn(2);
Q0Q2 = vQtrn(1)*vQtrn(3);
Q0Q3 = vQtrn(1)*vQtrn(4);
Q1Q2 = vQtrn(2)*vQtrn(3);
Q1Q3 = vQtrn(2)*vQtrn(4);
Q2Q3 = vQtrn(3)*vQtrn(4);
mTl2b(1,1) = Q0Q0 + Q1Q1 - Q2Q2 - Q3Q3;
mTl2b(1,2) = 2*(Q1Q2 + Q0Q3);
mTl2b(1,3) = 2*(Q1Q3 - Q0Q2);
mTl2b(2,1) = 2*(Q1Q2 - Q0Q3);
mTl2b(2,2) = Q0Q0 - Q1Q1 + Q2Q2 - Q3Q3;
mTl2b(2,3) = 2*(Q2Q3 + Q0Q1);
mTl2b(3,1) = 2*(Q1Q3 + Q0Q2);
mTl2b(3,2) = 2*(Q2Q3 - Q0Q1);
mTl2b(3,3) = Q0Q0 - Q1Q1 - Q2Q2 + Q3Q3;
mTb2l = mTl2b;
mTb2l.T();
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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));
vQdot(4) = 0.5*(vQtrn(1)*vPQR(eR) + vQtrn(2)*vPQR(eQ) - vQtrn(3)*vPQR(eP));
vQtrn += 0.5*dt*rate*(vlastQdot + vQdot);
vQtrn.Normalize();
vlastQdot = vQdot;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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;
vEuler(ePhi) = atan2(mTl2b(2,3), mTl2b(3,3));
vEuler(eTht) = asin(-mTl2b(1,3));
vEuler(ePsi) = atan2(mTl2b(1,2), mTl2b(1,1));
if (vEuler(ePsi) < 0.0) vEuler(ePsi) += 2*M_PI;
return vEuler;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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(1,2) = -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 = 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;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGState::Debug(void)
{
//TODO: Add your source code here
}
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