%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
#include "FGAerodynamics.h"
+#include "FGPropagate.h"
+#include "FGAircraft.h"
+#include "FGState.h"
+#include "FGMassBalance.h"
#include "FGFactorGroup.h"
-#include "FGCoefficient.h"
#include "FGPropertyManager.h"
+namespace JSBSim {
+
static const char *IdSrc = "$Id$";
static const char *IdHdr = ID_AERODYNAMICS;
-const unsigned NAxes=6;
+const unsigned NAxes=6;
const char* AxisNames[] = { "drag", "side-force", "lift", "rolling-moment",
- "pitching-moment","yawing-moment" };
+ "pitching-moment","yawing-moment" };
/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
CLASS IMPLEMENTATION
AxisIdx["YAW"] = 5;
Coeff = new CoeffArray[6];
-
- clsq=lod=0;
-
+
+ impending_stall = stall_hyst = 0.0;
+ alphaclmin = alphaclmax = 0.0;
+ alphahystmin = alphahystmax = 0.0;
+ clsq = lod = 0.0;
+ alphaw = 0.0;
+ bi2vel = ci2vel = 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;
-
+
Debug(1);
}
bool FGAerodynamics::Run(void)
{
unsigned int axis_ctr,ctr;
+ double alpha, twovel;
if (!FGModel::Run()) {
+ twovel = 2*Auxiliary->GetVt();
+ if (twovel != 0) {
+ bi2vel = Aircraft->GetWingSpan() / twovel;
+ ci2vel = Aircraft->Getcbar() / twovel;
+ }
+
+ alphaw = Auxiliary->Getalpha() + Aircraft->GetWingIncidence();
+
+ alpha = Auxiliary->Getalpha();
+
+ 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();
for (axis_ctr = 0; axis_ctr < 3; axis_ctr++) {
for (ctr=0; ctr < Coeff[axis_ctr].size(); ctr++) {
- //Coeff[axis_ctr][ctr]->Run();
vFs(axis_ctr+1) += Coeff[axis_ctr][ctr]->TotalValue();
- //cout << Coeff[axis_ctr][ctr]->Getname() << "= "
- // << Coeff[axis_ctr][ctr]->TotalValue() << endl;
}
}
+
//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());
+ if ( Auxiliary->Getqbar() > 0) {
+ clsq = vFs(eLift) / (Aircraft->GetWingArea()*Auxiliary->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;
- //cout << "Aircraft::vFs: " << vFs << endl;
+
vForces = State->GetTs2b()*vFs;
- 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;
+ vDXYZcg = MassBalance->StructuralToBody(Aircraft->GetXYZrp());
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++) {
- //Coeff[axis_ctr+3][ctr]->Run();
vMoments(axis_ctr+1) += Coeff[axis_ctr+3][ctr]->TotalValue();
}
}
+
return false;
} else {
return true;
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")) {
- if( token == "COEFFICIENT" ) {
+ while ((parameter = AC_cfg->GetValue()) != string("/AXIS")) {
+ if ( parameter == "COEFFICIENT" ) {
ca.push_back( new FGCoefficient(FDMExec) );
ca.back()->Load(AC_cfg);
- } else if ( token == "GROUP" ) {
+ } 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;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-string FGAerodynamics::GetCoefficientStrings(void)
+string FGAerodynamics::GetCoefficientStrings(string delimeter)
{
string CoeffStrings = "";
bool firstime = true;
if (firstime) {
firstime = false;
} else {
- CoeffStrings += ", ";
+ CoeffStrings += delimeter;
}
- CoeffStrings += Coeff[axis][sd]->GetCoefficientStrings();
+ CoeffStrings += Coeff[axis][sd]->GetCoefficientName();
}
}
return CoeffStrings;
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-string FGAerodynamics::GetCoefficientValues(void)
+string FGAerodynamics::GetCoefficientValues(string delimeter)
{
string SDValues = "";
bool firstime = true;
if (firstime) {
firstime = false;
} else {
- SDValues += ", ";
+ SDValues += delimeter;
}
- SDValues += Coeff[axis][sd]->GetCoefficientValues();
+ SDValues += Coeff[axis][sd]->GetSDstring();
}
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGAerodynamics::bind(void){
-
+void FGAerodynamics::bind(void)
+{
+ typedef double (FGAerodynamics::*PMF)(int) const;
+
PropertyManager->Tie("forces/fbx-aero-lbs", this,1,
- &FGAerodynamics::GetForces);
+ (PMF)&FGAerodynamics::GetForces);
PropertyManager->Tie("forces/fby-aero-lbs", this,2,
- &FGAerodynamics::GetForces);
+ (PMF)&FGAerodynamics::GetForces);
PropertyManager->Tie("forces/fbz-aero-lbs", this,3,
- &FGAerodynamics::GetForces);
+ (PMF)&FGAerodynamics::GetForces);
PropertyManager->Tie("moments/l-aero-lbsft", this,1,
- &FGAerodynamics::GetMoments);
+ (PMF)&FGAerodynamics::GetMoments);
PropertyManager->Tie("moments/m-aero-lbsft", this,2,
- &FGAerodynamics::GetMoments);
+ (PMF)&FGAerodynamics::GetMoments);
PropertyManager->Tie("moments/n-aero-lbsft", this,3,
- &FGAerodynamics::GetMoments);
+ (PMF)&FGAerodynamics::GetMoments);
PropertyManager->Tie("forces/fwx-aero-lbs", this,1,
- &FGAerodynamics::GetvFs);
+ (PMF)&FGAerodynamics::GetvFs);
PropertyManager->Tie("forces/fwy-aero-lbs", this,2,
- &FGAerodynamics::GetvFs);
+ (PMF)&FGAerodynamics::GetvFs);
PropertyManager->Tie("forces/fwz-aero-lbs", this,3,
- &FGAerodynamics::GetvFs);
+ (PMF)&FGAerodynamics::GetvFs);
PropertyManager->Tie("forces/lod-norm", this,
&FGAerodynamics::GetLoD);
PropertyManager->Tie("aero/cl-squared-norm", this,
- &FGAerodynamics::GetClSquared);
+ &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) {
-
+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++) {
+ 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();
+ }
+ node = (FGPropertyManager*)node->getParent();
}
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGAerodynamics::unbind(void){
+void FGAerodynamics::unbind(void)
+{
unsigned i,j;
PropertyManager->Untie("forces/fbx-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");
-
- for( i=0; i<NAxes; i++ ) {
+ 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("aero/stall-hyst-norm");
+ PropertyManager->Untie("systems/stall-warn-norm");
+
+ for ( i=0; i<NAxes; i++ ) {
for ( j=0; j < Coeff[i].size(); j++ ) {
Coeff[i][j]->unbind();
-
+
}
}
}
}
}
+} // namespace JSBSim
projects / flightgear.git / blobdiff