X-Git-Url: https://git.mxchange.org/?a=blobdiff_plain;f=src%2FFDM%2FJSBSim%2FFGAuxiliary.cpp;h=09b2aefc74dc08993f3dc40adb88e43302d18545;hb=fbee3d10f0aafd4178fc1313edb8593c156b2874;hp=a4a430b90fde24fdd969f7632ed6709724329d04;hpb=815333af23c86aef9ea8ae2b19b3e9b5da3c2af3;p=flightgear.git

diff --git a/src/FDM/JSBSim/FGAuxiliary.cpp b/src/FDM/JSBSim/FGAuxiliary.cpp
index a4a430b90..09b2aefc7 100644
--- a/src/FDM/JSBSim/FGAuxiliary.cpp
+++ b/src/FDM/JSBSim/FGAuxiliary.cpp
@@ -47,14 +47,8 @@ INCLUDES
 #include "FGAtmosphere.h"
 #include "FGState.h"
 #include "FGFDMExec.h"
-#include "FGFCS.h"
 #include "FGAircraft.h"
-#include "FGPosition.h"
-#include "FGOutput.h"
 #include "FGInertial.h"
-#include "FGMatrix33.h"
-#include "FGColumnVector3.h"
-#include "FGColumnVector4.h"
 #include "FGPropertyManager.h"
 
 namespace JSBSim {
@@ -98,28 +92,33 @@ bool FGAuxiliary::Run()
   if (!FGModel::Run()) {
     GetState();
     
-    //caculate total temperature assuming isentropic flow
+    //calculate total temperature assuming isentropic flow
     tat=sat*(1 + 0.2*mach*mach);
+    tatc=RankineToCelsius(tat);
     
     if (mach < 1) {   //calculate total pressure assuming isentropic flow
-      pt=p*pow((1 + 0.2*mach*mach),3.5);
+      pt = p*pow((1 + 0.2*machU*machU),3.5);
     } else {
       // shock in front of pitot tube, we'll assume its normal and use
       // the Rayleigh Pitot Tube Formula, i.e. the ratio of total
       // pressure behind the shock to the static pressure in front
 
-      B = 5.76*mach*mach/(5.6*mach*mach - 0.8);
+      B = 5.76*machU*machU/(5.6*machU*machU - 0.8);
 
       // The denominator above is zero for Mach ~ 0.38, for which
       // we'll never be here, so we're safe
 
-      D = (2.8*mach*mach-0.4)*0.4167;
+      D = (2.8*machU*machU-0.4)*0.4167;
       pt = p*pow(B,3.5)*D;
     }
 
     A = pow(((pt-p)/psl+1),0.28571);
-    vcas = sqrt(7*psl/rhosl*(A-1));
-    veas = sqrt(2*qbar/rhosl);
+    if (machU > 0.0) {
+      vcas = sqrt(7*psl/rhosl*(A-1));
+      veas = sqrt(2*qbar/rhosl);
+    } else {
+      vcas = veas = 0.0;
+    }
 
     // Pilot sensed accelerations are calculated here. This is used
     // for the coordinated turn ball instrument. Motion base platforms sometimes
@@ -162,11 +161,10 @@ bool FGAuxiliary::Run()
     vPilotAccel.InitMatrix();   
     if ( Translation->GetVt() > 1 ) {
        vPilotAccel =  Aerodynamics->GetForces() 
-                  +  Propulsion->GetForces()
-                  +  GroundReactions->GetForces();
+                      +  Propulsion->GetForces()
+                      +  GroundReactions->GetForces();
        vPilotAccel /= MassBalance->GetMass();
-       vToEyePt = Aircraft->GetXYZep() - MassBalance->GetXYZcg();
-       vToEyePt *= inchtoft;
+       vToEyePt = MassBalance->StructuralToBody(Aircraft->GetXYZep());
        vPilotAccel += Rotation->GetPQRdot() * vToEyePt;
        vPilotAccel += Rotation->GetPQR() * (Rotation->GetPQR() * vToEyePt);
     } else {
@@ -174,8 +172,7 @@ bool FGAuxiliary::Run()
     }   
 
     vPilotAccelN = vPilotAccel/Inertial->gravity();
-      
-    
+
     earthPosAngle += State->Getdt()*Inertial->omega();
     return false;
   } else {
@@ -222,8 +219,12 @@ void FGAuxiliary::bind(void)
                        &FGAuxiliary::GetVequivalentFPS);
   PropertyManager->Tie("velocities/ve-kts", this,
                        &FGAuxiliary::GetVequivalentKTS);
+  PropertyManager->Tie("velocities/machU", this,
+                       &FGAuxiliary::GetMachU);
   PropertyManager->Tie("velocities/tat-r", this,
                        &FGAuxiliary::GetTotalTemperature);
+  PropertyManager->Tie("velocities/tat-c", this,
+                       &FGAuxiliary::GetTAT_C);
   PropertyManager->Tie("velocities/pt-lbs_sqft", this,
                        &FGAuxiliary::GetTotalPressure);
                      
@@ -257,6 +258,9 @@ void FGAuxiliary::unbind(void)
   PropertyManager->Untie("velocities/vc-kts");
   PropertyManager->Untie("velocities/ve-fps");
   PropertyManager->Untie("velocities/ve-kts");
+  PropertyManager->Untie("velocities/machU");
+  PropertyManager->Untie("velocities/tat-r");
+  PropertyManager->Untie("velocities/tat-c");
   PropertyManager->Untie("accelerations/a-pilot-x-ft_sec2");
   PropertyManager->Untie("accelerations/a-pilot-y-ft_sec2");
   PropertyManager->Untie("accelerations/a-pilot-z-ft_sec2");
@@ -275,6 +279,7 @@ void FGAuxiliary::GetState(void)
 {
   qbar = Translation->Getqbar();
   mach = Translation->GetMach();
+  machU= Translation->GetMachU();
   p = Atmosphere->GetPressure();
   rhosl = Atmosphere->GetDensitySL();
   psl = Atmosphere->GetPressureSL();