fly/flightgear
1
0
Fork 0
Code Activity
flightgear/src/FDM/JSBSim/FGAircraft.cpp
curt 94034c3081 Latest jsbsim updates.
2001-04-02 03:12:38 +00:00

747 lines
23 KiB
C++
Raw Blame History

/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
Module: FGAircraft.cpp
Author: Jon S. Berndt
Date started: 12/12/98
Purpose: Encapsulates an aircraft
Called by: FGFDMExec
------------- 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
--------------------------------------------------------------------------------
Models the aircraft reactions and forces. This class is instantiated by the
FGFDMExec class and scheduled as an FDM entry. LoadAircraft() is supplied with a
name of a valid, registered aircraft, and the data file is parsed.
HISTORY
--------------------------------------------------------------------------------
12/12/98 JSB Created
04/03/99 JSB Changed Aero() method to correct body axis force calculation
from wind vector. Fix provided by Tony Peden.
05/03/99 JSB Changed (for the better?) the way configurations are read in.
9/17/99 TP Combined force and moment functions. Added aero reference
point to config file. Added calculations for moments due to
difference in cg and aero reference point
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
COMMENTS, REFERENCES, and NOTES
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
[1] Cooke, Zyda, Pratt, and McGhee, "NPSNET: Flight Simulation Dynamic Modeling
Using Quaternions", Presence, Vol. 1, No. 4, pp. 404-420 Naval Postgraduate
School, January 1994
[2] D. M. Henderson, "Euler Angles, Quaternions, and Transformation Matrices",
JSC 12960, July 1977
[3] Richard E. McFarland, "A Standard Kinematic Model for Flight Simulation at
NASA-Ames", NASA CR-2497, January 1975
[4] Barnes W. McCormick, "Aerodynamics, Aeronautics, and Flight Mechanics",
Wiley & Sons, 1979 ISBN 0-471-03032-5
[5] Bernard Etkin, "Dynamics of Flight, Stability and Control", Wiley & Sons,
1982 ISBN 0-471-08936-2
The aerodynamic coefficients used in this model are:
Longitudinal
CL0 - Reference lift at zero alpha
CD0 - Reference drag at zero alpha
CDM - Drag due to Mach
CLa - Lift curve slope (w.r.t. alpha)
CDa - Drag curve slope (w.r.t. alpha)
CLq - Lift due to pitch rate
CLM - Lift due to Mach
CLadt - Lift due to alpha rate
Cmadt - Pitching Moment due to alpha rate
Cm0 - Reference Pitching moment at zero alpha
Cma - Pitching moment slope (w.r.t. alpha)
Cmq - Pitch damping (pitch moment due to pitch rate)
CmM - Pitch Moment due to Mach
Lateral
Cyb - Side force due to sideslip
Cyr - Side force due to yaw rate
Clb - Dihedral effect (roll moment due to sideslip)
Clp - Roll damping (roll moment due to roll rate)
Clr - Roll moment due to yaw rate
Cnb - Weathercocking stability (yaw moment due to sideslip)
Cnp - Rudder adverse yaw (yaw moment due to roll rate)
Cnr - Yaw damping (yaw moment due to yaw rate)
Control
CLDe - Lift due to elevator
CDDe - Drag due to elevator
CyDr - Side force due to rudder
CyDa - Side force due to aileron
CmDe - Pitch moment due to elevator
ClDa - Roll moment due to aileron
ClDr - Roll moment due to rudder
CnDr - Yaw moment due to rudder
CnDa - Yaw moment due to aileron
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
INCLUDES
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
#include <sys/stat.h>
#include <sys/types.h>
#ifdef FGFS
# ifndef __BORLANDC__
# include <simgear/compiler.h>
# endif
# ifdef FG_HAVE_STD_INCLUDES
# include <cmath>
# else
# include <math.h>
# endif
#else
# include <cmath>
#endif
#include "FGAircraft.h"
#include "FGTranslation.h"
#include "FGRotation.h"
#include "FGAtmosphere.h"
#include "FGState.h"
#include "FGFDMExec.h"
#include "FGFCS.h"
#include "FGPosition.h"
#include "FGAuxiliary.h"
#include "FGOutput.h"
/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
DEFINITIONS
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
GLOBAL DATA
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
static const char *IdSrc = "$Id$";
static const char *IdHdr = ID_AIRCRAFT;
extern char highint[5];
extern char halfint[5];
extern char normint[6];
extern char reset[5];
extern char underon[5];
extern char underoff[6];
extern char fgblue[6];
extern char fgcyan[6];
extern char fgred[6];
extern char fggreen[6];
extern char fgdef[6];
extern short debug_lvl;
/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
CLASS IMPLEMENTATION
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
FGAircraft::FGAircraft(FGFDMExec* fdmex) : FGModel(fdmex),
vMoments(3),
vForces(3),
vFs(3),
vXYZrp(3),
vbaseXYZcg(3),
vXYZcg(3),
vXYZep(3),
vEuler(3)
{
Name = "FGAircraft";
AxisIdx["DRAG"] = 0;
AxisIdx["SIDE"] = 1;
AxisIdx["LIFT"] = 2;
AxisIdx["ROLL"] = 3;
AxisIdx["PITCH"] = 4;
AxisIdx["YAW"] = 5;
Coeff = new CoeffArray[6];
GearUp = false;
alphaclmin = alphaclmax = 0;
if (debug_lvl & 2) cout << "Instantiated: " << Name << endl;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
FGAircraft::~FGAircraft() {
unsigned int i,j;
for (i=0; i<6; i++) {
for (j=0; j<Coeff[i].size(); j++) {
delete Coeff[i][j];
}
}
delete[] Coeff;
if (debug_lvl & 2) cout << "Destroyed: FGAircraft" << endl;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
bool FGAircraft::LoadAircraft(string aircraft_path, string engine_path, string fname) {
string path;
string filename;
string aircraftCfgFileName;
string token;
AircraftPath = aircraft_path;
EnginePath = engine_path;
# ifndef macintosh
aircraftCfgFileName = AircraftPath + "/" + fname + "/" + fname + ".xml";
# else
aircraftCfgFileName = AircraftPath + ";" + fname + ";" + fname + ".xml";
# endif
FGConfigFile AC_cfg(aircraftCfgFileName);
if (!AC_cfg.IsOpen()) return false;
ReadPrologue(&AC_cfg);
while ((AC_cfg.GetNextConfigLine() != string("EOF")) &&
(token = AC_cfg.GetValue()) != string("/FDM_CONFIG")) {
if (token == "METRICS") {
cout << fgcyan << "\n Reading Metrics" << fgdef << endl;
ReadMetrics(&AC_cfg);
} else if (token == "AERODYNAMICS") {
cout << fgcyan << "\n Reading Aerodynamics" << fgdef << endl;
ReadAerodynamics(&AC_cfg);
} else if (token == "UNDERCARRIAGE") {
cout << fgcyan << "\n Reading Landing Gear" << fgdef << endl;
ReadUndercarriage(&AC_cfg);
} else if (token == "PROPULSION") {
cout << fgcyan << "\n Reading Propulsion" << fgdef << endl;
ReadPropulsion(&AC_cfg);
} else if (token == "FLIGHT_CONTROL") {
cout << fgcyan << "\n Reading Flight Control" << fgdef << endl;
ReadFlightControls(&AC_cfg);
} else if (token == "OUTPUT") {
cout << fgcyan << "\n Reading Output directives" << fgdef << endl;
ReadOutput(&AC_cfg);
}
}
return true;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
bool FGAircraft::Run(void) {
if (!FGModel::Run()) { // if false then execute this Run()
GetState();
for (int i = 1; i <= 3; i++) vForces(i) = vMoments(i) = 0.0;
MassChange();
FMProp();
FMAero();
FMGear();
FMMass();
nlf = 0;
if (fabs(Position->GetGamma()) < 1.57) {
nlf = vFs(eZ)/(Weight*cos(Position->GetGamma()));
}
} else { // skip Run() execution this time
}
return false;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGAircraft::MassChange() {
static FGColumnVector vXYZtank(3);
float Tw;
float IXXt, IYYt, IZZt, IXZt;
// unsigned int t;
// unsigned int axis_ctr;
/*
for (axis_ctr=1; axis_ctr<=3; axis_ctr++) vXYZtank(axis_ctr) = 0.0;
// UPDATE TANK CONTENTS
//
// For each engine, cycle through the tanks and draw an equal amount of
// fuel (or oxidizer) from each active tank. The needed amount of fuel is
// determined by the engine in the FGEngine class. If more fuel is needed
// than is available in the tank, then that amount is considered a shortage,
// and will be drawn from the next tank. If the engine cannot be fed what it
// needs, it will be considered to be starved, and will shut down.
float Oshortage, Fshortage;
for (unsigned int e=0; e<numEngines; e++) {
Fshortage = Oshortage = 0.0;
for (t=0; t<numTanks; t++) {
switch(Engine[e]->GetType()) {
case FGEngine::etRocket:
switch(Tank[t]->GetType()) {
case FGTank::ttFUEL:
if (Tank[t]->GetSelected()) {
Fshortage = Tank[t]->Reduce((Engine[e]->CalcFuelNeed()/
numSelectedFuelTanks)*(dt*rate) + Fshortage);
}
break;
case FGTank::ttOXIDIZER:
if (Tank[t]->GetSelected()) {
Oshortage = Tank[t]->Reduce((Engine[e]->CalcOxidizerNeed()/
numSelectedOxiTanks)*(dt*rate) + Oshortage);
}
break;
}
break;
case FGEngine::etPiston:
case FGEngine::etTurboJet:
case FGEngine::etTurboProp:
if (Tank[t]->GetSelected()) {
Fshortage = Tank[t]->Reduce((Engine[e]->CalcFuelNeed()/
numSelectedFuelTanks)*(dt*rate) + Fshortage);
}
break;
}
}
if ((Fshortage <= 0.0) || (Oshortage <= 0.0)) Engine[e]->SetStarved();
else Engine[e]->SetStarved(false);
}
*/
Weight = EmptyWeight;
// for (t=0; t<numTanks; t++)
// Weight += Tank[t]->GetContents();
Mass = Weight / GRAVITY;
// Calculate new CG here.
Tw = 0;
// for (t=0; t<numTanks; t++) {
// vXYZtank(eX) += Tank[t]->GetX()*Tank[t]->GetContents();
// vXYZtank(eY) += Tank[t]->GetY()*Tank[t]->GetContents();
// vXYZtank(eZ) += Tank[t]->GetZ()*Tank[t]->GetContents();
//
// Tw += Tank[t]->GetContents();
// }
vXYZcg = (vXYZtank + EmptyWeight*vbaseXYZcg) / (Tw + EmptyWeight);
// Calculate new moments of inertia here
IXXt = IYYt = IZZt = IXZt = 0.0;
// for (t=0; t<numTanks; t++) {
// IXXt += ((Tank[t]->GetX()-vXYZcg(eX))/12.0)*((Tank[t]->GetX() - vXYZcg(eX))/12.0)*Tank[t]->GetContents()/GRAVITY;
// IYYt += ((Tank[t]->GetY()-vXYZcg(eY))/12.0)*((Tank[t]->GetY() - vXYZcg(eY))/12.0)*Tank[t]->GetContents()/GRAVITY;
// IZZt += ((Tank[t]->GetZ()-vXYZcg(eZ))/12.0)*((Tank[t]->GetZ() - vXYZcg(eZ))/12.0)*Tank[t]->GetContents()/GRAVITY;
// IXZt += ((Tank[t]->GetX()-vXYZcg(eX))/12.0)*((Tank[t]->GetZ() - vXYZcg(eZ))/12.0)*Tank[t]->GetContents()/GRAVITY;
// }
Ixx = baseIxx + IXXt;
Iyy = baseIyy + IYYt;
Izz = baseIzz + IZZt;
Ixz = baseIxz + IXZt;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGAircraft::FMAero(void) {
static FGColumnVector vDXYZcg(3);
static FGColumnVector vAeroBodyForces(3);
unsigned int axis_ctr,ctr;
for (axis_ctr=1; axis_ctr<=3; axis_ctr++) vFs(axis_ctr) = 0.0;
for (axis_ctr = 0; axis_ctr < 3; axis_ctr++) {
for (ctr=0; ctr < Coeff[axis_ctr].size(); ctr++) {
vFs(axis_ctr+1) += Coeff[axis_ctr][ctr]->TotalValue();
}
}
vAeroBodyForces = State->GetTs2b(alpha, beta)*vFs;
vForces += vAeroBodyForces;
// see http://home.earthlink.net/~apeden/jsbsim_moments_due_to_forces.txt
// for details on this
vDXYZcg(eX) = -(vXYZrp(eX) - vXYZcg(eX))/12.0; //cg and rp values are in inches
vDXYZcg(eY) = (vXYZrp(eY) - vXYZcg(eY))/12.0;
vDXYZcg(eZ) = -(vXYZrp(eZ) - vXYZcg(eZ))/12.0;
vMoments(eL) += vAeroBodyForces(eZ)*vDXYZcg(eY) - vAeroBodyForces(eY)*vDXYZcg(eZ); // rolling moment
vMoments(eM) += vAeroBodyForces(eX)*vDXYZcg(eZ) - vAeroBodyForces(eZ)*vDXYZcg(eX); // pitching moment
vMoments(eN) += vAeroBodyForces(eY)*vDXYZcg(eX) - vAeroBodyForces(eX)*vDXYZcg(eY); // yawing moment
for (axis_ctr = 0; axis_ctr < 3; axis_ctr++) {
for (ctr = 0; ctr < Coeff[axis_ctr+3].size(); ctr++) {
vMoments(axis_ctr+1) += Coeff[axis_ctr+3][ctr]->TotalValue();
}
}
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGAircraft::FMGear(void) {
if ( !GearUp ) {
vector <FGLGear>::iterator iGear = lGear.begin();
while (iGear != lGear.end()) {
vForces += iGear->Force();
vMoments += iGear->Moment();
iGear++;
}
} else {
// Crash Routine
}
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGAircraft::FMMass(void) {
vForces(eX) += -GRAVITY*sin(vEuler(eTht)) * Mass;
vForces(eY) += GRAVITY*sin(vEuler(ePhi))*cos(vEuler(eTht)) * Mass;
vForces(eZ) += GRAVITY*cos(vEuler(ePhi))*cos(vEuler(eTht)) * Mass;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGAircraft::FMProp(void) {
vForces += Propulsion->GetForces();
vMoments += Propulsion->GetMoments();
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGAircraft::GetState(void) {
dt = State->Getdt();
alpha = Translation->Getalpha();
beta = Translation->Getbeta();
vEuler = Rotation->GetEuler();
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGAircraft::ReadMetrics(FGConfigFile* AC_cfg) {
string token = "";
string parameter;
AC_cfg->GetNextConfigLine();
while ((token = AC_cfg->GetValue()) != string("/METRICS")) {
*AC_cfg >> parameter;
if (parameter == string("AC_WINGAREA")) {
*AC_cfg >> WingArea;
cout << " WingArea: " << WingArea << endl;
} else if (parameter == "AC_WINGSPAN") {
*AC_cfg >> WingSpan;
cout << " WingSpan: " << WingSpan << endl;
} else if (parameter == "AC_CHORD") {
*AC_cfg >> cbar;
cout << " Chord: " << cbar << endl;
} else if (parameter == "AC_IXX") {
*AC_cfg >> baseIxx;
cout << " baseIxx: " << baseIxx << endl;
} else if (parameter == "AC_IYY") {
*AC_cfg >> baseIyy;
cout << " baseIyy: " << baseIyy << endl;
} else if (parameter == "AC_IZZ") {
*AC_cfg >> baseIzz;
cout << " baseIzz: " << baseIzz << endl;
} else if (parameter == "AC_IXZ") {
*AC_cfg >> baseIxz;
cout << " baseIxz: " << baseIxz << endl;
} else if (parameter == "AC_EMPTYWT") {
*AC_cfg >> EmptyWeight;
cout << " EmptyWeight: " << EmptyWeight << endl;
} else if (parameter == "AC_CGLOC") {
*AC_cfg >> vbaseXYZcg(eX) >> vbaseXYZcg(eY) >> vbaseXYZcg(eZ);
cout << " CG (x, y, z): " << vbaseXYZcg << endl;
} else if (parameter == "AC_EYEPTLOC") {
*AC_cfg >> vXYZep(eX) >> vXYZep(eY) >> vXYZep(eZ);
cout << " Eyepoint (x, y, z): " << vXYZep << endl;
} else if (parameter == "AC_AERORP") {
*AC_cfg >> vXYZrp(eX) >> vXYZrp(eY) >> vXYZrp(eZ);
cout << " Ref Pt (x, y, z): " << vXYZrp << endl;
} else if (parameter == "AC_ALPHALIMITS") {
*AC_cfg >> alphaclmin >> alphaclmax;
cout << " Maximum Alpha: " << alphaclmax
<< " Minimum Alpha: " << alphaclmin
<< endl;
}
}
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGAircraft::ReadPropulsion(FGConfigFile* AC_cfg) {
if (!Propulsion->LoadPropulsion(AC_cfg)) {
cerr << "Propulsion not successfully loaded" << endl;
}
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGAircraft::ReadFlightControls(FGConfigFile* AC_cfg) {
if (!FCS->LoadFCS(AC_cfg)) {
cerr << "Flight Controls not successfully loaded" << endl;
}
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGAircraft::ReadAerodynamics(FGConfigFile* AC_cfg) {
string token, axis;
AC_cfg->GetNextConfigLine();
while ((token = AC_cfg->GetValue()) != string("/AERODYNAMICS")) {
if (token == "AXIS") {
CoeffArray ca;
axis = AC_cfg->GetValue("NAME");
AC_cfg->GetNextConfigLine();
while ((token = AC_cfg->GetValue()) != string("/AXIS")) {
ca.push_back(new FGCoefficient(FDMExec, AC_cfg));
DisplayCoeffFactors(ca.back()->Getmultipliers());
}
Coeff[AxisIdx[axis]]=ca;
AC_cfg->GetNextConfigLine();
}
}
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGAircraft::ReadUndercarriage(FGConfigFile* AC_cfg) {
string token;
AC_cfg->GetNextConfigLine();
while ((token = AC_cfg->GetValue()) != string("/UNDERCARRIAGE")) {
lGear.push_back(FGLGear(AC_cfg, FDMExec));
}
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGAircraft::ReadOutput(FGConfigFile* AC_cfg) {
string token, parameter;
int OutRate = 0;
int subsystems = 0;
token = AC_cfg->GetValue("NAME");
Output->SetFilename(token);
token = AC_cfg->GetValue("TYPE");
Output->SetType(token);
AC_cfg->GetNextConfigLine();
while ((token = AC_cfg->GetValue()) != string("/OUTPUT")) {
*AC_cfg >> parameter;
if (parameter == "RATE_IN_HZ") *AC_cfg >> OutRate;
if (parameter == "SIMULATION") {
*AC_cfg >> parameter;
if (parameter == "ON") subsystems += ssSimulation;
}
if (parameter == "AEROSURFACES") {
*AC_cfg >> parameter;
if (parameter == "ON") subsystems += ssAerosurfaces;
}
if (parameter == "RATES") {
*AC_cfg >> parameter;
if (parameter == "ON") subsystems += ssRates;
}
if (parameter == "VELOCITIES") {
*AC_cfg >> parameter;
if (parameter == "ON") subsystems += ssVelocities;
}
if (parameter == "FORCES") {
*AC_cfg >> parameter;
if (parameter == "ON") subsystems += ssForces;
}
if (parameter == "MOMENTS") {
*AC_cfg >> parameter;
if (parameter == "ON") subsystems += ssMoments;
}
if (parameter == "ATMOSPHERE") {
*AC_cfg >> parameter;
if (parameter == "ON") subsystems += ssAtmosphere;
}
if (parameter == "MASSPROPS") {
*AC_cfg >> parameter;
if (parameter == "ON") subsystems += ssMassProps;
}
if (parameter == "POSITION") {
*AC_cfg >> parameter;
if (parameter == "ON") subsystems += ssPosition;
}
if (parameter == "COEFFICIENTS") {
*AC_cfg >> parameter;
if (parameter == "ON") subsystems += ssCoefficients;
}
if (parameter == "GROUND_REACTIONS") {
*AC_cfg >> parameter;
if (parameter == "ON") subsystems += ssGroundReactions;
}
if (parameter == "FCS") {
*AC_cfg >> parameter;
if (parameter == "ON") subsystems += ssFCS;
}
}
Output->SetSubsystems(subsystems);
OutRate = OutRate>120?120:(OutRate<0?0:OutRate);
Output->SetRate( (int)(0.5 + 1.0/(State->Getdt()*OutRate)) );
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGAircraft::ReadPrologue(FGConfigFile* AC_cfg) {
string token = AC_cfg->GetValue();
string scratch;
AircraftName = AC_cfg->GetValue("NAME");
cout << underon << "Reading Aircraft Configuration File" << underoff << ": "
<< highint << AircraftName << normint << endl;
scratch = AC_cfg->GetValue("VERSION").c_str();
CFGVersion = AC_cfg->GetValue("VERSION");
cout << " Version: " << highint << CFGVersion
<< normint << endl;
if (CFGVersion != string(NEEDED_CFG_VERSION)) {
cout << endl << fgred << "YOU HAVE AN INCOMPATIBLE CFG FILE FOR THIS AIRCRAFT."
" RESULTS WILL BE UNPREDICTABLE !!" << endl;
cout << "Current version needed is: " << NEEDED_CFG_VERSION << endl;
cout << " You have version: " << CFGVersion << endl << fgdef << endl;
//exit(-1);
}
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGAircraft::DisplayCoeffFactors(vector <eParam> multipliers) {
cout << " Non-Dimensionalized by: ";
for (unsigned int i=0; i<multipliers.size();i++)
cout << State->paramdef[multipliers[i]];
cout << endl;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
string FGAircraft::GetCoefficientStrings(void) {
string CoeffStrings = "";
bool firstime = true;
for (unsigned int axis = 0; axis < 6; axis++) {
for (unsigned int sd = 0; sd < Coeff[axis].size(); sd++) {
if (firstime) {
firstime = false;
} else {
CoeffStrings += ", ";
}
CoeffStrings += Coeff[axis][sd]->Getname();
}
}
return CoeffStrings;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
string FGAircraft::GetCoefficientValues(void) {
string SDValues = "";
char buffer[10];
bool firstime = true;
for (unsigned int axis = 0; axis < 6; axis++) {
for (unsigned int sd = 0; sd < Coeff[axis].size(); sd++) {
if (firstime) {
firstime = false;
} else {
SDValues += ", ";
}
sprintf(buffer, "%9.6f", Coeff[axis][sd]->GetSD());
SDValues += string(buffer);
}
}
return SDValues;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
string FGAircraft::GetGroundReactionStrings(void) {
string GroundReactionStrings = "";
bool firstime = true;
for (unsigned int i=0;i<lGear.size();i++) {
if (!firstime) GroundReactionStrings += ", ";
GroundReactionStrings += (lGear[i].GetName() + "_WOW, ");
GroundReactionStrings += (lGear[i].GetName() + "_compressLength, ");
GroundReactionStrings += (lGear[i].GetName() + "_compressSpeed, ");
GroundReactionStrings += (lGear[i].GetName() + "_Force");
firstime = false;
}
return GroundReactionStrings;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
string FGAircraft::GetGroundReactionValues(void) {
char buff[20];
string GroundReactionValues = "";
bool firstime = true;
for (unsigned int i=0;i<lGear.size();i++) {
if (!firstime) GroundReactionValues += ", ";
GroundReactionValues += string( lGear[i].GetWOW()?"1":"0" ) + ", ";
GroundReactionValues += (string(gcvt(lGear[i].GetCompLen(), 5, buff)) + ", ");
GroundReactionValues += (string(gcvt(lGear[i].GetCompVel(), 6, buff)) + ", ");
GroundReactionValues += (string(gcvt(lGear[i].GetCompForce(), 10, buff)));
firstime = false;
}
return GroundReactionValues;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGAircraft::Debug(void)
{
//TODO: Add your source code here
}
View git blame Copy permalink