/*******************************************************************************
-
+
Module: FGAuxiliary.cpp
Author: Jon Berndt
Date started: 01/26/99
Purpose: Calculates additional parameters needed by the visual system, etc.
Called by: FGSimExec
-
+
------------- Copyright (C) 1999 Jon S. Berndt (jsb@hal-pc.org) -------------
-
+
This program is free software; you can redistribute it and/or modify it under
the terms of the GNU General Public License as published by the Free Software
Foundation; either version 2 of the License, or (at your option) any later
version.
-
+
This program is distributed in the hope that it will be useful, but WITHOUT
ANY WARRANTY; without even the implied warranty of MERCHANTABILITY or FITNESS
FOR A PARTICULAR PURPOSE. See the GNU General Public License for more
details.
-
+
You should have received a copy of the GNU General Public License along with
this program; if not, write to the Free Software Foundation, Inc., 59 Temple
Place - Suite 330, Boston, MA 02111-1307, USA.
-
+
Further information about the GNU General Public License can also be found on
the world wide web at http://www.gnu.org.
-
+
FUNCTIONAL DESCRIPTION
--------------------------------------------------------------------------------
-This class calculates various auxiliary parameters, mostly used by the visual
-system
-
+This class calculates various auxiliary parameters.
+
+REFERENCES
+ Anderson, John D. "Introduction to Flight", 3rd Edition, McGraw-Hill, 1989
+ pgs. 112-126
HISTORY
--------------------------------------------------------------------------------
01/26/99 JSB Created
-
+
********************************************************************************
INCLUDES
*******************************************************************************/
#include "FGAircraft.h"
#include "FGPosition.h"
#include "FGOutput.h"
+#include "FGMatrix.h"
+
+static const char *IdSrc = "$Header$";
+static const char *IdHdr = ID_AUXILIARY;
/*******************************************************************************
************************************ CODE **************************************
*******************************************************************************/
-FGAuxiliary::FGAuxiliary(FGFDMExec* fdmex) : FGModel(fdmex)
-{
+FGAuxiliary::FGAuxiliary(FGFDMExec* fdmex) : FGModel(fdmex) {
Name = "FGAuxiliary";
+ vcas = veas = mach = qbar = pt = 0;
+ psl = rhosl = 1;
+ earthPosAngle = 0.0;
}
-FGAuxiliary::~FGAuxiliary()
-{
-}
+FGAuxiliary::~FGAuxiliary() {}
+
-bool FGAuxiliary::Run()
-{
+bool FGAuxiliary::Run() {
+ float A,B,D;
+
if (!FGModel::Run()) {
+ GetState();
+ if(mach < 1) //calculate total pressure assuming isentropic flow
+ pt=p*pow((1 + 0.2*mach*mach),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);
+
+ // 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;
+ 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);
+
+ vPilotAccel = Translation->GetUVWdot() + Aircraft->GetXYZep() * Rotation->GetPQRdot();
+
+
+
+ earthPosAngle += State->Getdt()*OMEGA_EARTH;
+
} else {
}
+
+
return false;
}
+void FGAuxiliary::GetState(void) {
+ qbar = Translation->Getqbar();
+ mach = Translation->GetMach();
+ p = Atmosphere->GetPressure();
+ rhosl = Atmosphere->GetDensitySL();
+ psl = Atmosphere->GetPressureSL();
+
+}