%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
#include "FGAerodynamics.h"
+#include "FGFactorGroup.h"
+#include "FGCoefficient.h"
+#include "FGPropertyManager.h"
static const char *IdSrc = "$Id$";
static const char *IdHdr = ID_AERODYNAMICS;
-extern short debug_lvl;
+const unsigned NAxes=6;
+const char* AxisNames[] = { "drag", "side-force", "lift", "rolling-moment",
+ "pitching-moment","yawing-moment" };
/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
CLASS IMPLEMENTATION
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
-FGAerodynamics::FGAerodynamics(FGFDMExec* FDMExec) : FGModel(FDMExec),
- vMoments(3),
- vForces(3),
- vFs(3),
- vLastFs(3),
- vDXYZcg(3)
+FGAerodynamics::FGAerodynamics(FGFDMExec* FDMExec) : FGModel(FDMExec)
{
Name = "FGAerodynamics";
AxisIdx["YAW"] = 5;
Coeff = new CoeffArray[6];
-
- if (debug_lvl & 2) cout << "Instantiated: FGAerodynamics" << endl;
+
+ impending_stall = stall_hyst = 0.0;
+ alphaclmin = alphaclmax = 0.0;
+ alphahystmin = alphahystmax = 0.0;
+ clsq = lod = 0.0;
+ alphaw = 0.0;
+ bind();
+
+ Debug(0);
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
FGAerodynamics::~FGAerodynamics()
{
unsigned int i,j;
+
+ unbind();
+
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: FGAerodynamics" << endl;
+
+ Debug(1);
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
bool FGAerodynamics::Run(void)
{
- float alpha, beta;
unsigned int axis_ctr,ctr;
+ double alpha, twovel;
if (!FGModel::Run()) {
+ twovel = 2*Translation->GetVt();
+ if (twovel > 0) {
+ bi2vel = Aircraft->GetWingSpan() / twovel;
+ ci2vel = Aircraft->Getcbar() / twovel;
+ }
+
+ alphaw = Translation->Getalpha() + Aircraft->GetWingIncidence();
+
alpha = Translation->Getalpha();
- beta = Translation->Getbeta();
-
+
+ if (alphaclmax != 0) {
+ if (alpha > 0.85*alphaclmax) {
+ impending_stall = 10*(alpha/alphaclmax - 0.85);
+ } else {
+ impending_stall = 0;
+ }
+ }
+
+ if (alphahystmax != 0.0 && alphahystmin != 0.0) {
+ if (alpha > alphahystmax) {
+ stall_hyst = 1;
+ } else if (alpha < alphahystmin) {
+ stall_hyst = 0;
+ }
+ }
+
vLastFs = vFs;
vFs.InitMatrix();
}
}
- vForces = State->GetTs2b(alpha, beta)*vFs;
+ //correct signs of drag and lift to wind axes convention
+ //positive forward, right, down
+ if ( Translation->Getqbar() > 0) {
+ clsq = vFs(eLift) / (Aircraft->GetWingArea()*Translation->Getqbar());
+ clsq *= clsq;
+ }
+ if ( vFs(eDrag) > 0) {
+ lod = vFs(eLift) / vFs(eDrag);
+ }
+
+ //correct signs of drag and lift to wind axes convention
+ //positive forward, right, down
+ vFs(eDrag)*=-1; vFs(eLift)*=-1;
- // see http://home.earthlink.net/~apeden/jsbsim_moments_due_to_forces.txt
- // for details on this
+ vForces = State->GetTs2b()*vFs;
- vDXYZcg(eX) = -(Aircraft->GetXYZrp(eX) - MassBalance->GetXYZcg(eX))/12.0;
- vDXYZcg(eY) = (Aircraft->GetXYZrp(eY) - MassBalance->GetXYZcg(eY))/12.0;
- vDXYZcg(eZ) = -(Aircraft->GetXYZrp(eZ) - MassBalance->GetXYZcg(eZ))/12.0;
+ vDXYZcg(eX) = -(Aircraft->GetXYZrp(eX)
+ - MassBalance->GetXYZcg(eX))*inchtoft;
+ vDXYZcg(eY) = (Aircraft->GetXYZrp(eY)
+ - MassBalance->GetXYZcg(eY))*inchtoft;
+ vDXYZcg(eZ) = -(Aircraft->GetXYZrp(eZ)
+ - MassBalance->GetXYZcg(eZ))*inchtoft;
- vMoments(eL) = vForces(eZ)*vDXYZcg(eY) - vForces(eY)*vDXYZcg(eZ);
- vMoments(eM) = vForces(eX)*vDXYZcg(eZ) - vForces(eZ)*vDXYZcg(eX);
- vMoments(eN) = vForces(eY)*vDXYZcg(eX) - vForces(eX)*vDXYZcg(eY);
+ vMoments = vDXYZcg*vForces; // M = r X F
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();
}
}
+
return false;
} else {
return true;
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-bool FGAerodynamics::LoadAerodynamics(FGConfigFile* AC_cfg)
+bool FGAerodynamics::Load(FGConfigFile* AC_cfg)
{
- string token, axis;
+ string parameter, axis, scratch;
AC_cfg->GetNextConfigLine();
- while ((token = AC_cfg->GetValue()) != string("/AERODYNAMICS")) {
- if (token == "AXIS") {
+ while ((parameter = AC_cfg->GetValue()) != string("/AERODYNAMICS")) {
+ if (parameter == "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));
- if (debug_lvl > 0) DisplayCoeffFactors(ca.back()->Getmultipliers());
+ while ((parameter = AC_cfg->GetValue()) != string("/AXIS")) {
+ if ( parameter == "COEFFICIENT" ) {
+ ca.push_back( new FGCoefficient(FDMExec) );
+ ca.back()->Load(AC_cfg);
+ } else if ( parameter == "GROUP" ) {
+ ca.push_back( new FGFactorGroup(FDMExec) );
+ ca.back()->Load(AC_cfg);
+ }
}
Coeff[AxisIdx[axis]] = ca;
AC_cfg->GetNextConfigLine();
+ } else if (parameter == "AC_ALPHALIMITS") {
+ *AC_cfg >> scratch >> alphaclmin >> alphaclmax;
+ if (debug_lvl > 0) cout << " Maximum Alpha: " << alphaclmax
+ << " Minimum Alpha: " << alphaclmin
+ << endl;
+ } else if (parameter == "AC_HYSTLIMITS") {
+ *AC_cfg >> scratch >> alphahystmin >> alphahystmax;
+ if (debug_lvl > 0) cout << " Hysteresis Start: " << alphahystmax
+ << " Hysteresis End: " << alphahystmin
+ << endl;
}
}
+ bindModel();
+
return true;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGAerodynamics::DisplayCoeffFactors(vector <eParam> multipliers)
-{
- unsigned int i;
-
- cout << " Non-Dimensionalized by: ";
-
- for (i=0; i<multipliers.size();i++) cout << State->paramdef[multipliers[i]];
-
- cout << endl;
-}
-
-//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-
string FGAerodynamics::GetCoefficientStrings(void)
{
string CoeffStrings = "";
} else {
CoeffStrings += ", ";
}
- CoeffStrings += Coeff[axis][sd]->Getname();
+ CoeffStrings += Coeff[axis][sd]->GetCoefficientName();
}
}
-
return CoeffStrings;
}
string FGAerodynamics::GetCoefficientValues(void)
{
string SDValues = "";
- char buffer[10];
bool firstime = true;
for (unsigned int axis = 0; axis < 6; axis++) {
} else {
SDValues += ", ";
}
- sprintf(buffer, "%9.6f", Coeff[axis][sd]->GetSD());
- SDValues += string(buffer);
+ SDValues += Coeff[axis][sd]->GetSDstring();
}
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-float FGAerodynamics::GetNlf(void)
+void FGAerodynamics::bind(void)
{
- if (fabs(Position->GetGamma()) < 1.57) {
- return (vFs(eZ)/(MassBalance->GetWeight()*cos(Position->GetGamma())));
- } else {
- return 0.0;
+ typedef double (FGAerodynamics::*PMF)(int) const;
+
+ PropertyManager->Tie("forces/fbx-aero-lbs", this,1,
+ (PMF)&FGAerodynamics::GetForces);
+ PropertyManager->Tie("forces/fby-aero-lbs", this,2,
+ (PMF)&FGAerodynamics::GetForces);
+ PropertyManager->Tie("forces/fbz-aero-lbs", this,3,
+ (PMF)&FGAerodynamics::GetForces);
+ PropertyManager->Tie("moments/l-aero-lbsft", this,1,
+ (PMF)&FGAerodynamics::GetMoments);
+ PropertyManager->Tie("moments/m-aero-lbsft", this,2,
+ (PMF)&FGAerodynamics::GetMoments);
+ PropertyManager->Tie("moments/n-aero-lbsft", this,3,
+ (PMF)&FGAerodynamics::GetMoments);
+ PropertyManager->Tie("forces/fwx-aero-lbs", this,1,
+ (PMF)&FGAerodynamics::GetvFs);
+ PropertyManager->Tie("forces/fwy-aero-lbs", this,2,
+ (PMF)&FGAerodynamics::GetvFs);
+ PropertyManager->Tie("forces/fwz-aero-lbs", this,3,
+ (PMF)&FGAerodynamics::GetvFs);
+ PropertyManager->Tie("forces/lod-norm", this,
+ &FGAerodynamics::GetLoD);
+ PropertyManager->Tie("aero/cl-squared-norm", this,
+ &FGAerodynamics::GetClSquared);
+ PropertyManager->Tie("aero/alpha-max-deg", this,
+ &FGAerodynamics::GetAlphaCLMax,
+ &FGAerodynamics::SetAlphaCLMax,
+ true);
+ PropertyManager->Tie("aero/alpha-min-deg", this,
+ &FGAerodynamics::GetAlphaCLMin,
+ &FGAerodynamics::SetAlphaCLMin,
+ true);
+ PropertyManager->Tie("aero/bi2vel", this,
+ &FGAerodynamics::GetBI2Vel);
+ PropertyManager->Tie("aero/ci2vel", this,
+ &FGAerodynamics::GetCI2Vel);
+ PropertyManager->Tie("aero/alpha-wing-rad", this,
+ &FGAerodynamics::GetAlphaW);
+ PropertyManager->Tie("systems/stall-warn-norm", this,
+ &FGAerodynamics::GetStallWarn);
+ PropertyManager->Tie("aero/stall-hyst-norm", this,
+ &FGAerodynamics::GetHysteresisParm);
+}
+
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
+void FGAerodynamics::bindModel(void)
+{
+ unsigned i,j;
+ FGPropertyManager* node;
+ string axis_node_name;
+ node = PropertyManager->GetNode("aero/buildup",true);
+ for (i=0;i<NAxes;i++) {
+ node = node->GetNode( string(AxisNames[i]),true );
+ for (j=0; j < Coeff[i].size(); j++) {
+ Coeff[i][j]->bind(node);
+ }
+ node = (FGPropertyManager*)node->getParent();
}
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-float FGAerodynamics::GetLoD(void)
+void FGAerodynamics::unbind(void)
{
- float LoD;
-
- if (vFs(1) != 0.00) return vFs(3)/vFs(1);
- else return 0.00;
+ unsigned i,j;
+
+ PropertyManager->Untie("forces/fbx-aero-lbs");
+ PropertyManager->Untie("forces/fby-aero-lbs");
+ PropertyManager->Untie("forces/fbz-aero-lbs");
+ PropertyManager->Untie("moments/l-aero-lbsft");
+ PropertyManager->Untie("moments/m-aero-lbsft");
+ PropertyManager->Untie("moments/n-aero-lbsft");
+ PropertyManager->Untie("forces/fwx-aero-lbs");
+ PropertyManager->Untie("forces/fwy-aero-lbs");
+ PropertyManager->Untie("forces/fwz-aero-lbs");
+ PropertyManager->Untie("forces/lod-norm");
+ PropertyManager->Untie("aero/cl-squared-norm");
+ PropertyManager->Untie("aero/alpha-max-deg");
+ PropertyManager->Untie("aero/alpha-min-deg");
+ PropertyManager->Untie("aero/bi2vel");
+ PropertyManager->Untie("aero/ci2vel");
+ PropertyManager->Untie("aero/alpha-wing-rad");
+ PropertyManager->Untie("systems/stall-warn-norm");
+
+ for ( i=0; i<NAxes; i++ ) {
+ for ( j=0; j < Coeff[i].size(); j++ ) {
+ Coeff[i][j]->unbind();
+
+ }
+ }
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-
-void FGAerodynamics::Debug(void)
+// 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 FGAerodynamics::Debug(int from)
{
- //TODO: Add your source code here
+ 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: FGAerodynamics" << endl;
+ if (from == 1) cout << "Destroyed: FGAerodynamics" << 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