#include <sstream>
#include <iomanip>
#include <cstdlib>
-#include <FGFDMExec.h>
+#include "FGFDMExec.h"
#include "FGAerodynamics.h"
-#include "FGPropagate.h"
-#include "FGAircraft.h"
-#include "FGAuxiliary.h"
-#include "FGMassBalance.h"
#include "input_output/FGPropertyManager.h"
using namespace std;
namespace JSBSim {
-static const char *IdSrc = "$Id: FGAerodynamics.cpp,v 1.37 2011/03/11 13:02:26 jberndt Exp $";
+static const char *IdSrc = "$Id: FGAerodynamics.cpp,v 1.45 2012/04/13 13:25:52 jberndt Exp $";
static const char *IdHdr = ID_AERODYNAMICS;
/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-bool FGAerodynamics::Run(void)
+bool FGAerodynamics::Run(bool Holding)
{
- if (FGModel::Run()) return true;
- if (FDMExec->Holding()) return false; // if paused don't execute
+ if (FGModel::Run(Holding)) return true;
+ if (Holding) return false; // if paused don't execute
unsigned int axis_ctr, ctr;
- const double alpha=FDMExec->GetAuxiliary()->Getalpha();
- const double twovel=2*FDMExec->GetAuxiliary()->GetVt();
- const double qbar = FDMExec->GetAuxiliary()->Getqbar();
- const double wingarea = FDMExec->GetAircraft()->GetWingArea(); // TODO: Make these constants constant!
- const double wingspan = FDMExec->GetAircraft()->GetWingSpan();
- const double wingchord = FDMExec->GetAircraft()->Getcbar();
- const double wingincidence = FDMExec->GetAircraft()->GetWingIncidence();
+ const double twovel=2*in.Vt;
+
RunPreFunctions();
// calculate some oft-used quantities for speed
if (twovel != 0) {
- bi2vel = wingspan / twovel;
- ci2vel = wingchord / twovel;
+ bi2vel = in.Wingspan / twovel;
+ ci2vel = in.Wingchord / twovel;
}
- alphaw = alpha + wingincidence;
- qbar_area = wingarea * qbar;
+ alphaw = in.Alpha + in.Wingincidence;
+ qbar_area = in.Wingarea * in.Qbar;
if (alphaclmax != 0) {
- if (alpha > 0.85*alphaclmax) {
- impending_stall = 10*(alpha/alphaclmax - 0.85);
+ if (in.Alpha > 0.85*alphaclmax) {
+ impending_stall = 10*(in.Alpha/alphaclmax - 0.85);
} else {
impending_stall = 0;
}
}
if (alphahystmax != 0.0 && alphahystmin != 0.0) {
- if (alpha > alphahystmax) {
+ if (in.Alpha > alphahystmax) {
stall_hyst = 1;
- } else if (alpha < alphahystmin) {
+ } else if (in.Alpha < alphahystmin) {
stall_hyst = 0;
}
}
switch (axisType) {
case atBodyXYZ: // Forces already in body axes; no manipulation needed
- vFw = GetTb2w()*vFnative;
+ vFw = in.Tb2w*vFnative;
vForces = vFnative;
break;
case atLiftDrag: // Copy forces into wind axes
vFw = vFnative;
vFw(eDrag)*=-1; vFw(eLift)*=-1;
- vForces = GetTw2b()*vFw;
+ vForces = in.Tw2b*vFw;
break;
case atAxialNormal: // Convert native forces into Axial|Normal|Side system
- vFw = GetTb2w()*vFnative;
+ vFw = in.Tb2w*vFnative;
vFnative(eX)*=-1; vFnative(eZ)*=-1;
vForces = vFnative;
break;
exit(-1);
}
- // Calculate aerodynamic reference point shift, if any
- if (AeroRPShift) vDeltaRP(eX) = AeroRPShift->GetValue()*wingchord*12.0;
-
// Calculate lift coefficient squared
- if ( qbar > 0) {
- clsq = vFw(eLift) / (wingarea*qbar);
+ if ( in.Qbar > 0) {
+ clsq = vFw(eLift) / (in.Wingarea*in.Qbar);
clsq *= clsq;
}
// Calculate lift Lift over Drag
if ( fabs(vFw(eDrag)) > 0.0) lod = fabs( vFw(eLift) / vFw(eDrag) );
- vDXYZcg = FDMExec->GetMassBalance()->StructuralToBody(FDMExec->GetAircraft()->GetXYZrp() + vDeltaRP);
+ // Calculate aerodynamic reference point shift, if any. The shift
+ // takes place in the structual axis. That is, if the shift is positive,
+ // it is towards the back (tail) of the vehicle. The AeroRPShift
+ // function should be non-dimensionalized by the wing chord. The
+ // calculated vDeltaRP will be in feet.
+ if (AeroRPShift) vDeltaRP(eX) = AeroRPShift->GetValue()*in.Wingchord;
+
+ vDXYZcg(eX) = in.RPBody(eX) - vDeltaRP(eX); // vDeltaRP is given in the structural frame
+ vDXYZcg(eY) = in.RPBody(eY) + vDeltaRP(eY);
+ vDXYZcg(eZ) = in.RPBody(eZ) - vDeltaRP(eZ);
vMoments = vDXYZcg*vForces; // M = r X F
return false;
}
-//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-//
-// From Stevens and Lewis, "Aircraft Control and Simulation", 3rd Ed., the
-// transformation from body to wind axes is defined (where "a" is alpha and "B"
-// is beta):
-//
-// cos(a)*cos(B) sin(B) sin(a)*cos(B)
-// -cos(a)*sin(B) cos(B) -sin(a)*sin(B)
-// -sin(a) 0 cos(a)
-//
-// The transform from wind to body axes is then,
-//
-// cos(a)*cos(B) -cos(a)*sin(B) -sin(a)
-// sin(B) cos(B) 0
-// sin(a)*cos(B) -sin(a)*sin(B) cos(a)
-
-FGMatrix33& FGAerodynamics::GetTw2b(void)
-{
- double ca, cb, sa, sb;
-
- double alpha = FDMExec->GetAuxiliary()->Getalpha();
- double beta = FDMExec->GetAuxiliary()->Getbeta();
-
- ca = cos(alpha);
- sa = sin(alpha);
- cb = cos(beta);
- sb = sin(beta);
-
- mTw2b(1,1) = ca*cb;
- mTw2b(1,2) = -ca*sb;
- mTw2b(1,3) = -sa;
- mTw2b(2,1) = sb;
- mTw2b(2,2) = cb;
- mTw2b(2,3) = 0.0;
- mTw2b(3,1) = sa*cb;
- mTw2b(3,2) = -sa*sb;
- mTw2b(3,3) = ca;
-
- return mTw2b;
-}
-
-//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-
-FGMatrix33& FGAerodynamics::GetTb2w(void)
-{
- double alpha,beta;
- double ca, cb, sa, sb;
-
- alpha = FDMExec->GetAuxiliary()->Getalpha();
- beta = FDMExec->GetAuxiliary()->Getbeta();
-
- ca = cos(alpha);
- sa = sin(alpha);
- cb = cos(beta);
- sb = sin(beta);
-
- mTb2w(1,1) = ca*cb;
- mTb2w(1,2) = sb;
- mTb2w(1,3) = sa*cb;
- mTb2w(2,1) = -ca*sb;
- mTb2w(2,2) = cb;
- mTb2w(2,3) = -sa*sb;
- mTb2w(3,1) = -sa;
- mTb2w(3,2) = 0.0;
- mTb2w(3,3) = ca;
-
- return mTb2w;
-}
-
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
bool FGAerodynamics::Load(Element *element)
if (!fname.empty()) {
file = FDMExec->GetFullAircraftPath() + separator + fname;
document = LoadXMLDocument(file);
+ if (document == 0L) return false;
} else {
document = element;
}
AeroFunctionStrings += AeroFunctions[axis][sd]->GetName();
}
}
+
+ string FunctionStrings = FGModelFunctions::GetFunctionStrings(delimeter);
+
+ if (FunctionStrings.size() > 0) {
+ if (AeroFunctionStrings.size() > 0) {
+ AeroFunctionStrings += delimeter + FunctionStrings;
+ } else {
+ AeroFunctionStrings = FunctionStrings;
+ }
+ }
+
return AeroFunctionStrings;
}
for (unsigned int axis = 0; axis < 6; axis++) {
for (unsigned int sd = 0; sd < AeroFunctions[axis].size(); sd++) {
if (buf.tellp() > 0) buf << delimeter;
- buf << setw(9) << AeroFunctions[axis][sd]->GetValue();
+ buf << AeroFunctions[axis][sd]->GetValue();
+ }
+ }
+
+ string FunctionValues = FGModelFunctions::GetFunctionValues(delimeter);
+
+ if (FunctionValues.size() > 0) {
+ if (buf.str().size() > 0) {
+ buf << delimeter << FunctionValues;
+ } else {
+ buf << FunctionValues;
}
}
projects / flightgear.git / blobdiff