1 /*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
3 Module: FGAuxiliary.cpp
6 Purpose: Calculates additional parameters needed by the visual system, etc.
9 ------------- Copyright (C) 1999 Jon S. Berndt (jsb@hal-pc.org) -------------
11 This program is free software; you can redistribute it and/or modify it under
12 the terms of the GNU General Public License as published by the Free Software
13 Foundation; either version 2 of the License, or (at your option) any later
16 This program is distributed in the hope that it will be useful, but WITHOUT
17 ANY WARRANTY; without even the implied warranty of MERCHANTABILITY or FITNESS
18 FOR A PARTICULAR PURPOSE. See the GNU General Public License for more
21 You should have received a copy of the GNU General Public License along with
22 this program; if not, write to the Free Software Foundation, Inc., 59 Temple
23 Place - Suite 330, Boston, MA 02111-1307, USA.
25 Further information about the GNU General Public License can also be found on
26 the world wide web at http://www.gnu.org.
28 FUNCTIONAL DESCRIPTION
29 --------------------------------------------------------------------------------
30 This class calculates various auxiliary parameters.
33 Anderson, John D. "Introduction to Flight", 3rd Edition, McGraw-Hill, 1989
36 --------------------------------------------------------------------------------
39 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
41 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
43 #include "FGAuxiliary.h"
44 #include "FGTranslation.h"
45 #include "FGRotation.h"
46 #include "FGAtmosphere.h"
48 #include "FGFDMExec.h"
50 #include "FGAircraft.h"
51 #include "FGPosition.h"
55 static const char *IdSrc = "$Header$";
56 static const char *IdHdr = ID_AUXILIARY;
58 /*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
60 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
62 FGAuxiliary::FGAuxiliary(FGFDMExec* fdmex) : FGModel(fdmex) {
64 vcas = veas = mach = qbar = pt = 0;
70 FGAuxiliary::~FGAuxiliary() {}
74 bool FGAuxiliary::Run() {
77 if (!FGModel::Run()) {
79 if(mach < 1) //calculate total pressure assuming isentropic flow
80 pt=p*pow((1 + 0.2*mach*mach),3.5);
82 // shock in front of pitot tube, we'll assume its normal and use
83 // the Rayleigh Pitot Tube Formula, i.e. the ratio of total
84 // pressure behind the shock to the static pressure in front
86 B = 5.76*mach*mach/(5.6*mach*mach - 0.8);
88 // The denominator above is zero for Mach ~ 0.38, for which
89 // we'll never be here, so we're safe
91 D = (2.8*mach*mach-0.4)*0.4167;
95 A = pow(((pt-p)/psl+1),0.28571);
96 vcas = sqrt(7*psl/rhosl*(A-1));
97 veas = sqrt(2*qbar/rhosl);
99 vPilotAccel = Translation->GetUVWdot() + Aircraft->GetXYZep() * Rotation->GetPQRdot();
103 earthPosAngle += State->Getdt()*OMEGA_EARTH;
112 void FGAuxiliary::GetState(void) {
113 qbar = Translation->Getqbar();
114 mach = Translation->GetMach();
115 p = Atmosphere->GetPressure();
116 rhosl = Atmosphere->GetDensitySL();
117 psl = Atmosphere->GetPressureSL();