#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 = "$Id$";
+static const char *IdSrc = "$Id: FGAerodynamics.cpp,v 1.45 2012/04/13 13:25:52 jberndt Exp $";
static const char *IdHdr = ID_AERODYNAMICS;
/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
axisType = atNone;
- Coeff = new CoeffArray[6];
+ AeroFunctions = new AeroFunctionArray[6];
impending_stall = stall_hyst = 0.0;
alphaclmin = alphaclmax = 0.0;
unsigned int i,j;
for (i=0; i<6; i++)
- for (j=0; j<Coeff[i].size(); j++)
- delete Coeff[i][j];
+ for (j=0; j<AeroFunctions[i].size(); j++)
+ delete AeroFunctions[i][j];
- delete[] Coeff;
+ delete[] AeroFunctions;
delete AeroRPShift;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-bool FGAerodynamics::Run(void)
+bool FGAerodynamics::Run(bool Holding)
{
- unsigned int axis_ctr, ctr;
- double alpha, twovel;
- 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 twovel=2*in.Vt;
RunPreFunctions();
// calculate some oft-used quantities for speed
- twovel = 2*Auxiliary->GetVt();
if (twovel != 0) {
- bi2vel = Aircraft->GetWingSpan() / twovel;
- ci2vel = Aircraft->Getcbar() / twovel;
+ bi2vel = in.Wingspan / twovel;
+ ci2vel = in.Wingchord / twovel;
}
- alphaw = Auxiliary->Getalpha() + Aircraft->GetWingIncidence();
- alpha = Auxiliary->Getalpha();
- qbar_area = Aircraft->GetWingArea() * Auxiliary->Getqbar();
+ 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;
}
}
vFnative.InitMatrix();
for (axis_ctr = 0; axis_ctr < 3; axis_ctr++) {
- for (ctr=0; ctr < Coeff[axis_ctr].size(); ctr++) {
- vFnative(axis_ctr+1) += Coeff[axis_ctr][ctr]->GetValue();
+ for (ctr=0; ctr < AeroFunctions[axis_ctr].size(); ctr++) {
+ vFnative(axis_ctr+1) += AeroFunctions[axis_ctr][ctr]->GetValue();
}
}
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()*Aircraft->Getcbar()*12.0;
-
// Calculate lift coefficient squared
- if ( Auxiliary->Getqbar() > 0) {
- clsq = vFw(eLift) / (Aircraft->GetWingArea()*Auxiliary->Getqbar());
+ 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 = MassBalance->StructuralToBody(Aircraft->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
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]->GetValue();
+ for (ctr = 0; ctr < AeroFunctions[axis_ctr+3].size(); ctr++) {
+ vMoments(axis_ctr+1) += AeroFunctions[axis_ctr+3][ctr]->GetValue();
}
}
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 = Auxiliary->Getalpha();
- double beta = Auxiliary->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 = Auxiliary->Getalpha();
- beta = Auxiliary->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;
}
axis_element = document->FindElement("axis");
while (axis_element) {
- CoeffArray ca;
+ AeroFunctionArray ca;
axis = axis_element->GetAttributeValue("name");
function_element = axis_element->FindElement("function");
while (function_element) {
- ca.push_back( new FGFunction(PropertyManager, function_element) );
+ string current_func_name = function_element->GetAttributeValue("name");
+ try {
+ ca.push_back( new FGFunction(PropertyManager, function_element) );
+ } catch (string const str) {
+ cerr << endl << fgred << "Error loading aerodynamic function in "
+ << current_func_name << ":" << str << " Aborting." << reset << endl;
+ return false;
+ }
function_element = axis_element->FindNextElement("function");
}
- Coeff[AxisIdx[axis]] = ca;
+ AeroFunctions[AxisIdx[axis]] = ca;
axis_element = document->FindNextElement("axis");
}
- FGModel::PostLoad(document); // Perform base class Post-Load
+ PostLoad(document, PropertyManager); // Perform base class Post-Load
return true;
}
string axis;
while (axis_element) {
axis = axis_element->GetAttributeValue("name");
- if (axis == "LIFT" || axis == "DRAG" || axis == "SIDE") {
+ if (axis == "LIFT" || axis == "DRAG") {
if (axisType == atNone) axisType = atLiftDrag;
else if (axisType != atLiftDrag) {
cerr << endl << " Mixed aerodynamic axis systems have been used in the"
- << " aircraft config file." << endl;
+ << " aircraft config file. (LIFT DRAG)" << endl;
+ }
+ } else if (axis == "SIDE") {
+ if (axisType != atNone && axisType != atLiftDrag && axisType != atAxialNormal) {
+ cerr << endl << " Mixed aerodynamic axis systems have been used in the"
+ << " aircraft config file. (SIDE)" << endl;
}
} else if (axis == "AXIAL" || axis == "NORMAL") {
if (axisType == atNone) axisType = atAxialNormal;
else if (axisType != atAxialNormal) {
cerr << endl << " Mixed aerodynamic axis systems have been used in the"
- << " aircraft config file." << endl;
+ << " aircraft config file. (NORMAL AXIAL)" << endl;
}
} else if (axis == "X" || axis == "Y" || axis == "Z") {
if (axisType == atNone) axisType = atBodyXYZ;
else if (axisType != atBodyXYZ) {
cerr << endl << " Mixed aerodynamic axis systems have been used in the"
- << " aircraft config file." << endl;
+ << " aircraft config file. (XYZ)" << endl;
}
} else if (axis != "ROLL" && axis != "PITCH" && axis != "YAW") { // error
cerr << endl << " An unknown axis type, " << axis << " has been specified"
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-string FGAerodynamics::GetCoefficientStrings(const string& delimeter) const
+string FGAerodynamics::GetAeroFunctionStrings(const string& delimeter) const
{
- string CoeffStrings = "";
+ string AeroFunctionStrings = "";
bool firstime = true;
unsigned int axis, sd;
for (axis = 0; axis < 6; axis++) {
- for (sd = 0; sd < Coeff[axis].size(); sd++) {
+ for (sd = 0; sd < AeroFunctions[axis].size(); sd++) {
if (firstime) {
firstime = false;
} else {
- CoeffStrings += delimeter;
+ AeroFunctionStrings += delimeter;
}
- CoeffStrings += Coeff[axis][sd]->GetName();
+ 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 CoeffStrings;
+
+ return AeroFunctionStrings;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-string FGAerodynamics::GetCoefficientValues(const string& delimeter) const
+string FGAerodynamics::GetAeroFunctionValues(const string& delimeter) const
{
ostringstream buf;
for (unsigned int axis = 0; axis < 6; axis++) {
- for (unsigned int sd = 0; sd < Coeff[axis].size(); sd++) {
+ for (unsigned int sd = 0; sd < AeroFunctions[axis].size(); sd++) {
if (buf.tellp() > 0) buf << delimeter;
- buf << setw(9) << Coeff[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