X-Git-Url: https://git.mxchange.org/?a=blobdiff_plain;f=src%2FFDM%2FJSBSim%2Fmodels%2FFGAerodynamics.cpp;h=ed1d639fce787d7fdc4a93f61ff00e41c7026342;hb=024ef128e3395e8c0e32b360abe19b4d345e4f80;hp=0a384447dbac79df5bfb7f3ea98861bab9753be2;hpb=f2a817d1370cde5a94474344a65bacb2f7845352;p=flightgear.git diff --git a/src/FDM/JSBSim/models/FGAerodynamics.cpp b/src/FDM/JSBSim/models/FGAerodynamics.cpp index 0a384447d..ed1d639fc 100644 --- a/src/FDM/JSBSim/models/FGAerodynamics.cpp +++ b/src/FDM/JSBSim/models/FGAerodynamics.cpp @@ -40,19 +40,15 @@ INCLUDES #include #include #include -#include +#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 1.34 2010/10/15 11:32:41 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; /*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% @@ -80,7 +76,7 @@ FGAerodynamics::FGAerodynamics(FGFDMExec* FDMExec) : FGModel(FDMExec) axisType = atNone; - Coeff = new CoeffArray[6]; + AeroFunctions = new AeroFunctionArray[6]; impending_stall = stall_hyst = 0.0; alphaclmin = alphaclmax = 0.0; @@ -103,10 +99,10 @@ FGAerodynamics::~FGAerodynamics() unsigned int i,j; for (i=0; i<6; i++) - for (j=0; jHolding()) 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; } } @@ -173,8 +168,8 @@ bool FGAerodynamics::Run(void) 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(); } } @@ -184,16 +179,16 @@ bool FGAerodynamics::Run(void) 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; @@ -203,25 +198,31 @@ bool FGAerodynamics::Run(void) 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(); } } @@ -230,75 +231,6 @@ bool FGAerodynamics::Run(void) 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) @@ -314,6 +246,7 @@ bool FGAerodynamics::Load(Element *element) if (!fname.empty()) { file = FDMExec->GetFullAircraftPath() + separator + fname; document = LoadXMLDocument(file); + if (document == 0L) return false; } else { document = element; } @@ -345,7 +278,7 @@ bool FGAerodynamics::Load(Element *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) { @@ -359,7 +292,7 @@ bool FGAerodynamics::Load(Element *element) } function_element = axis_element->FindNextElement("function"); } - Coeff[AxisIdx[axis]] = ca; + AeroFunctions[AxisIdx[axis]] = ca; axis_element = document->FindNextElement("axis"); } @@ -384,23 +317,28 @@ void FGAerodynamics::DetermineAxisSystem() 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" @@ -418,35 +356,56 @@ void FGAerodynamics::DetermineAxisSystem() //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% -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; } }