Fix stall widths for the "auxilliary" (reverse flow) stalls so they

[flightgear.git] / src / FDM / JSBSim / FGInertial.cpp

diff --git a/src/FDM/JSBSim/FGInertial.cpp b/src/FDM/JSBSim/FGInertial.cpp
index 1475a6b93a3b416b6b1e9457c41880626b6ee4f3..d75854a51545298e37ee3df09306e79e2458e4dd 100644 (file)
--- a/src/FDM/JSBSim/FGInertial.cpp
+++ b/src/FDM/JSBSim/FGInertial.cpp
@@ -36,9 +36,12 @@ INCLUDES
 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
 
 #include "FGInertial.h"
-#include "FGPosition.h"
+#include "FGPropagate.h"
+#include "FGState.h"
 #include "FGMassBalance.h"
 
+namespace JSBSim {
+
 static const char *IdSrc = "$Id$";
 static const char *IdHdr = ID_INERTIAL;
 
@@ -51,16 +54,12 @@ FGInertial::FGInertial(FGFDMExec* fgex) : FGModel(fgex)
 {
   Name = "FGInertial";
 
-  vRadius.InitMatrix();
-  
   // Defaults
   RotationRate    = 0.00007272205217;
   GM              = 14.06252720E15;
   RadiusReference = 20925650.00;
   gAccelReference = GM/(RadiusReference*RadiusReference);
   gAccel          = GM/(RadiusReference*RadiusReference);
-  
-  bind();
 
   Debug(0);
 }
@@ -69,7 +68,6 @@ FGInertial::FGInertial(FGFDMExec* fgex) : FGModel(fgex)
 
 FGInertial::~FGInertial(void)
 {
-  unbind();
   Debug(1);
 }
 
@@ -77,45 +75,14 @@ FGInertial::~FGInertial(void)
 
 bool FGInertial::Run(void)
 {
-  double stht, ctht, sphi, cphi;
-
-  if (!FGModel::Run()) {
-
-    gAccel = GM / (Position->GetRadius()*Position->GetRadius());
-
-    stht = sin(Rotation->GetEuler(eTht));
-    ctht = cos(Rotation->GetEuler(eTht));
-    sphi = sin(Rotation->GetEuler(ePhi));
-    cphi = cos(Rotation->GetEuler(ePhi));
-
-    vGravity(eX) = vForces(eX) = -gravity()*stht;
-    vGravity(eY) = vForces(eY) =  gravity()*sphi*ctht;
-    vGravity(eZ) = vForces(eZ) =  gravity()*cphi*ctht;
-    
-    // The following equation for vOmegaLocal terms shows the angular velocity
-    // calculation _for_the_local_frame_ given the earth's rotation (first set)
-    // at the current latitude, and also the component due to the aircraft
-    // motion over the curved surface of the earth (second set).
-
-    vOmegaLocal(eX) = omega() * cos(Position->GetLatitude());
-    vOmegaLocal(eY) = 0.0;
-    vOmegaLocal(eZ) = omega() * -sin(Position->GetLatitude());
-
-    vOmegaLocal(eX) +=  Position->GetVe() / Position->GetRadius();
-    vOmegaLocal(eY) += -Position->GetVn() / Position->GetRadius();
-    vOmegaLocal(eZ) +=  0.00;
+  // Fast return if we have nothing to do ...
+  if (FGModel::Run()) return true;
 
-//    vForces = State->GetTl2b()*(-2.0*vOmegaLocal * Position->GetVel());
+  // Gravitation accel
+  double r = Propagate->GetRadius();
+  gAccel = GetGAccel(r);
 
-    vRadius(3) = Position->GetRadius();
-    vForces += State->GetTl2b()*(vOmegaLocal * (vOmegaLocal * vRadius));
-
-    vForces *= MassBalance->GetMass(); // IMPORTANT !!!!!!!!!!!!!!!!!!!!!!!!!!!!
-    
-    return false;
-  } else {
-    return true;
-  }
+  return false;
 }
 
 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
@@ -126,6 +93,7 @@ bool FGInertial::LoadInertial(FGConfigFile* AC_cfg)
 }
 
 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
 //    The bitmasked value choices are as follows:
 //    unset: In this case (the default) JSBSim would only print
 //       out the normally expected messages, essentially echoing
@@ -170,18 +138,4 @@ void FGInertial::Debug(int from)
     }
   }
 }
-
-void FGInertial::bind(void){
-  PropertyManager->Tie("forces/fbx-inertial-lbs", this,1,
-                       &FGInertial::GetForces);
-  PropertyManager->Tie("forces/fby-inertial-lbs", this,2,
-                       &FGInertial::GetForces);
-  PropertyManager->Tie("forces/fbz-inertial-lbs", this,3,
-                       &FGInertial::GetForces);
-}
-
-void FGInertial::unbind(void){
-  PropertyManager->Untie("forces/fbx-inertial-lbs");
-  PropertyManager->Untie("forces/fby-inertial-lbs");
-  PropertyManager->Untie("forces/fbz-inertial-lbs");
 }