jsbsim/FGAuxiliary_8cpp_source.html

/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%


 Module:       FGAuxiliary.cpp

 Author:       Tony Peden, Jon Berndt

 Date started: 01/26/99

 Purpose:      Calculates additional parameters needed by the visual system, etc.

 Called by:    FGFDMExec


 ------------- Copyright (C) 1999  Jon S. Berndt (jon@jsbsim.org) -------------


 This program is free software; you can redistribute it and/or modify it under

 the terms of the GNU Lesser 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 Lesser General Public License for more

 details.


 You should have received a copy of the GNU Lesser 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 Lesser 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.


REFERENCES

  Anderson, John D. "Introduction to Flight", 3rd Edition, McGraw-Hill, 1989

                    pgs. 112-126

HISTORY

--------------------------------------------------------------------------------

01/26/99   JSB   Created


%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

INCLUDES

%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/


#include <iostream>


#include "FGAuxiliary.h"

#include "initialization/FGInitialCondition.h"

#include "FGFDMExec.h"

#include "input_output/FGPropertyManager.h"

#include "FGInertial.h"

#include "FGAtmosphere.h"

#include "input_output/FGLog.h"


using namespace std;


namespace JSBSim {


/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

CLASS IMPLEMENTATION

%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/


FGAuxiliary::FGAuxiliary(FGFDMExec* fdmex) : FGModel(fdmex)

{

  Name = "FGAuxiliary";

  pt = FGAtmosphere::StdDaySLpressure;     // ISA SL pressure

  tat = FGAtmosphere::StdDaySLtemperature; // ISA SL temperature

  tatc = RankineToCelsius(tat);


  vcas = veas = 0.0;

  qbar = qbarUW = qbarUV = 0.0;

  Mach = MachU = 0.0;

  alpha = beta = 0.0;

  adot = bdot = 0.0;

  gamma = Vt = Vground = 0.0;

  psigt = 0.0;

  hoverbmac = hoverbcg = 0.0;

  Re = 0.0;

  Nx = Ny = Nz = 0.0;


  vPilotAccel.InitMatrix();

  vPilotAccelN.InitMatrix();

  vAeroUVW.InitMatrix();

  vAeroPQR.InitMatrix();

  vMachUVW.InitMatrix();

  vEulerRates.InitMatrix();

  vNEUFromStart.InitMatrix();

  NEUCalcValid = false;


  bind();


  Debug(0);

}


//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%


bool FGAuxiliary::InitModel(void)

{

  if (!FGModel::InitModel()) return false;


  pt = in.Pressure;

  tat = in.Temperature;

  tatc = RankineToCelsius(tat);


  vcas = veas = 0.0;

  qbar = qbarUW = qbarUV = 0.0;

  Mach = MachU = 0.0;

  alpha = beta = 0.0;

  adot = bdot = 0.0;

  gamma = Vt = Vground = 0.0;

  psigt = 0.0;

  hoverbmac = hoverbcg = 0.0;

  Re = 0.0;

  Nz = Ny = 0.0;


  vPilotAccel.InitMatrix();

  vPilotAccelN.InitMatrix();

  vAeroUVW.InitMatrix();

  vAeroPQR.InitMatrix();

  vMachUVW.InitMatrix();

  vEulerRates.InitMatrix();

  vNEUFromStart.InitMatrix();

  NEUCalcValid = false;


  return true;

}


//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%


void FGAuxiliary::SetInitialState(const FGInitialCondition* ic)

{

  NEUStartLocation = ic->GetPosition();

  NEUStartLocation.SetPositionGeodetic(NEUStartLocation.GetLongitude(), NEUStartLocation.GetGeodLatitudeRad(), 0.0);

}


//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%


FGAuxiliary::~FGAuxiliary()

{

  Debug(1);

}


//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%


bool FGAuxiliary::Run(bool Holding)

{

  if (FGModel::Run(Holding)) return true; // return true if error returned from base class

  if (Holding) return false;


  // Rotation


  vEulerRates(eTht) = in.vPQR(eQ)*in.CosPhi - in.vPQR(eR)*in.SinPhi;

  if (in.CosTht != 0.0) {

    vEulerRates(ePsi) = (in.vPQR(eQ)*in.SinPhi + in.vPQR(eR)*in.CosPhi)/in.CosTht;

    vEulerRates(ePhi) = in.vPQR(eP) + vEulerRates(ePsi)*in.SinTht;

  }


  // Combine the wind speed with aircraft speed to obtain wind relative speed

  vAeroPQR = in.vPQR - in.TurbPQR;

  vAeroUVW = in.vUVW - in.Tl2b * in.TotalWindNED;


  alpha = beta = adot = bdot = 0;

  double AeroU2 = vAeroUVW(eU)*vAeroUVW(eU);

  double AeroV2 = vAeroUVW(eV)*vAeroUVW(eV);

  double AeroW2 = vAeroUVW(eW)*vAeroUVW(eW);

  double mUW = AeroU2 + AeroW2;


  double Vt2 = mUW + AeroV2;

  Vt = sqrt(Vt2);


  if ( Vt > 0.001 ) {

    beta = atan2(vAeroUVW(eV), sqrt(mUW));


    if ( mUW >= 1E-6 ) {

      alpha = atan2(vAeroUVW(eW), vAeroUVW(eU));

      double Vtdot = (vAeroUVW(eU)*in.vUVWdot(eU) + vAeroUVW(eV)*in.vUVWdot(eV) + vAeroUVW(eW)*in.vUVWdot(eW))/Vt;

      adot = (vAeroUVW(eU)*in.vUVWdot(eW) - vAeroUVW(eW)*in.vUVWdot(eU))/mUW;

      bdot = (in.vUVWdot(eV)*Vt - vAeroUVW(eV)*Vtdot)/(Vt*sqrt(mUW));

    }

  }


  UpdateWindMatrices();


  Re = Vt * in.Wingchord / in.KinematicViscosity;


  double densityD2 = 0.5*in.Density;


  qbar = densityD2 * Vt2;

  qbarUW = densityD2 * (mUW);

  qbarUV = densityD2 * (AeroU2 + AeroV2);

  Mach = Vt / in.SoundSpeed;

  MachU = vMachUVW(eU) = vAeroUVW(eU) / in.SoundSpeed;

  vMachUVW(eV) = vAeroUVW(eV) / in.SoundSpeed;

  vMachUVW(eW) = vAeroUVW(eW) / in.SoundSpeed;


  Vground = sqrt( in.vVel(eNorth)*in.vVel(eNorth) + in.vVel(eEast)*in.vVel(eEast) );


  psigt = atan2(in.vVel(eEast), in.vVel(eNorth));

  if (psigt < 0.0) psigt += 2*M_PI;

  gamma = atan2(-in.vVel(eDown), Vground);


  tat = in.Temperature*(1 + 0.2*Mach*Mach); // Total Temperature, isentropic flow

  tatc = RankineToCelsius(tat);


  pt = PitotTotalPressure(Mach, in.Pressure);


  if (abs(Mach) > 0.0) {

    vcas = VcalibratedFromMach(Mach, in.Pressure);

    veas = sqrt(2 * qbar / FGAtmosphere::StdDaySLdensity);

  }

  else

    vcas = veas = 0.0;


  vPilotAccel.InitMatrix();

  vNcg = in.vBodyAccel/in.StandardGravity;

  // Nz is Acceleration in "g's", along normal axis (-Z body axis)

  Nz = -vNcg(eZ);

  Ny =  vNcg(eY);

  Nx =  vNcg(eX);

  vPilotAccel = in.vBodyAccel + in.vPQRidot * in.ToEyePt;

  vPilotAccel += in.vPQRi * (in.vPQRi * in.ToEyePt);


  vNwcg = mTb2w * vNcg;

  vNwcg(eZ) = 1.0 - vNwcg(eZ);


  vPilotAccelN = vPilotAccel / in.StandardGravity;


  // VRP computation

  vLocationVRP = in.vLocation.LocalToLocation( in.Tb2l * in.VRPBody );


  // Recompute some derived values now that we know the dependent parameters values ...

  hoverbcg = in.DistanceAGL / in.Wingspan;


  FGColumnVector3 vMac = in.Tb2l * in.RPBody;

  hoverbmac = (in.DistanceAGL - vMac(3)) / in.Wingspan;


  // New timestep so vNEUFromStart is no longer valid since we only calculate it on demand

  NEUCalcValid = false;


  return false;

}


//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%


double FGAuxiliary::PitotTotalPressure(double mach, double pressure) const

{

  constexpr double SHRatio = FGAtmosphere::SHRatio;

  constexpr double a = (SHRatio-1.0) / 2.0;

  constexpr double b = SHRatio / (SHRatio-1.0);

  constexpr double c = 2.0*b;

  constexpr double d = 1.0 / (SHRatio-1.0);

  const double coeff = pow(0.5*(SHRatio+1.0), b)

                     * pow((SHRatio+1.0)/(SHRatio-1.0), d);


  if (mach < 0) return pressure;

  if (mach < 1)    //calculate total pressure assuming isentropic flow

    return pressure*pow((1.0 + a*mach*mach), b);

  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 of the normal shock assumption

    // should not be a bad one -- most supersonic aircraft place the pitot probe

    // out front so that it is the forward most point on the aircraft.

    // The real shock would, of course, take on something like the shape of a

    // rounded-off cone but, here again, the assumption should be good since the

    // opening of the pitot probe is very small and, therefore, the effects of

    // the shock curvature should be small as well. AFAIK, this approach is

    // fairly well accepted within the aerospace community


    // The denominator below is zero for Mach ~ 0.38, for which

    // we'll never be here, so we're safe


    return pressure*coeff*pow(mach, c)/pow(c*mach*mach-1.0, d);

  }

}


//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%


// Based on the formulas in the US Air Force Aircraft Performance Flight Testing

// Manual (AFFTC-TIH-99-01). In particular sections 4.6 to 4.8.


double FGAuxiliary::MachFromImpactPressure(double qc, double pressure) const

{

  constexpr double SHRatio = FGAtmosphere::SHRatio;

  constexpr double a = 2.0/(SHRatio-1.0);

  constexpr double b = (SHRatio-1.0)/SHRatio;

  constexpr double c = 2.0/b;

  constexpr double d = 0.5*a;

  const double coeff = pow(0.5*(SHRatio+1.0), -0.25*c)

                     * pow(0.5*(SHRatio+1.0)/SHRatio, -0.5*d);


  double A = qc / pressure + 1;

  double M = sqrt(a*(pow(A, b) - 1.0));  // Equation (4.12)


  if (M > 1.0)

    for (unsigned int i = 0; i<10; i++)

      M = coeff*sqrt(A*pow(1 - 1.0 / (c*M*M), d));  // Equation (4.17)


  return M;

}


//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%


double FGAuxiliary::VcalibratedFromMach(double mach, double pressure) const

{

  double qc = PitotTotalPressure(mach, pressure) - pressure;

  return in.StdDaySLsoundspeed * MachFromImpactPressure(qc, FGAtmosphere::StdDaySLpressure);

}


//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%


double FGAuxiliary::MachFromVcalibrated(double vcas, double pressure) const

{

  constexpr double StdDaySLpressure = FGAtmosphere::StdDaySLpressure;

  double qc = PitotTotalPressure(vcas / in.StdDaySLsoundspeed, StdDaySLpressure) - StdDaySLpressure;

  return MachFromImpactPressure(qc, pressure);

}


//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

//

// 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)


void FGAuxiliary::UpdateWindMatrices(void)

{

  double ca, cb, sa, sb;


  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;


  mTb2w = mTw2b.Transposed();

}


//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%


double FGAuxiliary::GetNlf(void) const

{

  if (in.Mass != 0)

    return (in.vFw(3))/(in.Mass*slugtolb);

  else

    return 0.;

}


//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%


double FGAuxiliary::GetLongitudeRelativePosition(void) const

{

  return in.vLocation.GetDistanceTo(FDMExec->GetIC()->GetLongitudeRadIC(),

                                    in.vLocation.GetGeodLatitudeRad())*fttom;

}


//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%


double FGAuxiliary::GetLatitudeRelativePosition(void) const

{

  return in.vLocation.GetDistanceTo(in.vLocation.GetLongitude(),

                                    FDMExec->GetIC()->GetGeodLatitudeRadIC())*fttom;

}


//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%


double FGAuxiliary::GetDistanceRelativePosition(void) const

{

  auto ic = FDMExec->GetIC();

  return in.vLocation.GetDistanceTo(ic->GetLongitudeRadIC(),

                                    ic->GetGeodLatitudeRadIC())*fttom;

}


//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%


const FGColumnVector3& FGAuxiliary::GetNEUPositionFromStart() const

{

  if (!NEUCalcValid) {

    // Position tracking in local frame with local frame origin at lat, lon of initial condition

    // and at 0 altitude relative to the reference ellipsoid. Position is NEU (North, East, UP) in feet.

    vNEUFromStart = NEUStartLocation.LocationToLocal(in.vLocation);

    vNEUFromStart(3) *= -1.0;  // Flip sign for Up, so + for altitude above reference ellipsoid

    NEUCalcValid = true;

  }


  return vNEUFromStart;

}


//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%


void FGAuxiliary::bind(void)

{

  PropertyManager->Tie("propulsion/tat-r", this, &FGAuxiliary::GetTotalTemperature);

  PropertyManager->Tie("propulsion/tat-c", this, &FGAuxiliary::GetTAT_C);

  PropertyManager->Tie("propulsion/pt-lbs_sqft", this, &FGAuxiliary::GetTotalPressure);

  PropertyManager->Tie("velocities/vc-fps", this, &FGAuxiliary::GetVcalibratedFPS);

  PropertyManager->Tie("velocities/vc-kts", this, &FGAuxiliary::GetVcalibratedKTS);

  PropertyManager->Tie("velocities/ve-fps", this, &FGAuxiliary::GetVequivalentFPS);

  PropertyManager->Tie("velocities/ve-kts", this, &FGAuxiliary::GetVequivalentKTS);

  PropertyManager->Tie("velocities/vtrue-fps", this, &FGAuxiliary::GetVtrueFPS);

  PropertyManager->Tie("velocities/vtrue-kts", this, &FGAuxiliary::GetVtrueKTS);

  PropertyManager->Tie("velocities/machU", this, &FGAuxiliary::GetMachU);

  PropertyManager->Tie("velocities/p-aero-rad_sec", this, eX, &FGAuxiliary::GetAeroPQR);

  PropertyManager->Tie("velocities/q-aero-rad_sec", this, eY, &FGAuxiliary::GetAeroPQR);

  PropertyManager->Tie("velocities/r-aero-rad_sec", this, eZ, &FGAuxiliary::GetAeroPQR);

  PropertyManager->Tie("velocities/phidot-rad_sec", this, ePhi, &FGAuxiliary::GetEulerRates);

  PropertyManager->Tie("velocities/thetadot-rad_sec", this, eTht, &FGAuxiliary::GetEulerRates);

  PropertyManager->Tie("velocities/psidot-rad_sec", this, ePsi, &FGAuxiliary::GetEulerRates);

  PropertyManager->Tie("velocities/u-aero-fps", this, eU, &FGAuxiliary::GetAeroUVW);

  PropertyManager->Tie("velocities/v-aero-fps", this, eV, &FGAuxiliary::GetAeroUVW);

  PropertyManager->Tie("velocities/w-aero-fps", this, eW, &FGAuxiliary::GetAeroUVW);

  PropertyManager->Tie("velocities/vt-fps", this, &FGAuxiliary::GetVt);

  PropertyManager->Tie("velocities/mach", this, &FGAuxiliary::GetMach);

  PropertyManager->Tie("velocities/vg-fps", this, &FGAuxiliary::GetVground);

  PropertyManager->Tie("accelerations/a-pilot-x-ft_sec2", this, eX, &FGAuxiliary::GetPilotAccel);

  PropertyManager->Tie("accelerations/a-pilot-y-ft_sec2", this, eY, &FGAuxiliary::GetPilotAccel);

  PropertyManager->Tie("accelerations/a-pilot-z-ft_sec2", this, eZ, &FGAuxiliary::GetPilotAccel);

  PropertyManager->Tie("accelerations/n-pilot-x-norm", this, eX, &FGAuxiliary::GetNpilot);

  PropertyManager->Tie("accelerations/n-pilot-y-norm", this, eY, &FGAuxiliary::GetNpilot);

  PropertyManager->Tie("accelerations/n-pilot-z-norm", this, eZ, &FGAuxiliary::GetNpilot);

  PropertyManager->Tie("accelerations/Nx", this, &FGAuxiliary::GetNx);

  PropertyManager->Tie("accelerations/Ny", this, &FGAuxiliary::GetNy);

  PropertyManager->Tie("accelerations/Nz", this, &FGAuxiliary::GetNz);

  PropertyManager->Tie("forces/load-factor", this, &FGAuxiliary::GetNlf);

  PropertyManager->Tie("aero/alpha-rad", this, &FGAuxiliary::Getalpha);

  PropertyManager->Tie("aero/beta-rad", this, &FGAuxiliary::Getbeta);

  PropertyManager->Tie("aero/mag-beta-rad", this, &FGAuxiliary::GetMagBeta);

  PropertyManager->Tie("aero/alpha-deg", this, inDegrees, &FGAuxiliary::Getalpha);

  PropertyManager->Tie("aero/beta-deg", this, inDegrees, &FGAuxiliary::Getbeta);

  PropertyManager->Tie("aero/mag-beta-deg", this, inDegrees, &FGAuxiliary::GetMagBeta);

  PropertyManager->Tie("aero/Re", this, &FGAuxiliary::GetReynoldsNumber);

  PropertyManager->Tie("aero/qbar-psf", this, &FGAuxiliary::Getqbar);

  PropertyManager->Tie("aero/qbarUW-psf", this, &FGAuxiliary::GetqbarUW);

  PropertyManager->Tie("aero/qbarUV-psf", this, &FGAuxiliary::GetqbarUV);

  PropertyManager->Tie("aero/alphadot-rad_sec", this, &FGAuxiliary::Getadot);

  PropertyManager->Tie("aero/betadot-rad_sec", this, &FGAuxiliary::Getbdot);

  PropertyManager->Tie("aero/alphadot-deg_sec", this, inDegrees, &FGAuxiliary::Getadot);

  PropertyManager->Tie("aero/betadot-deg_sec", this, inDegrees, &FGAuxiliary::Getbdot);

  PropertyManager->Tie("aero/h_b-cg-ft", this, &FGAuxiliary::GetHOverBCG);

  PropertyManager->Tie("aero/h_b-mac-ft", this, &FGAuxiliary::GetHOverBMAC);

  PropertyManager->Tie("flight-path/gamma-rad", this, &FGAuxiliary::GetGamma);

  PropertyManager->Tie("flight-path/gamma-deg", this, inDegrees, &FGAuxiliary::GetGamma);

  PropertyManager->Tie("flight-path/psi-gt-rad", this, &FGAuxiliary::GetGroundTrack);


  PropertyManager->Tie("position/distance-from-start-lon-mt", this, &FGAuxiliary::GetLongitudeRelativePosition);

  PropertyManager->Tie("position/distance-from-start-lat-mt", this, &FGAuxiliary::GetLatitudeRelativePosition);

  PropertyManager->Tie("position/distance-from-start-mag-mt", this, &FGAuxiliary::GetDistanceRelativePosition);

  PropertyManager->Tie("position/vrp-gc-latitude_deg", &vLocationVRP, &FGLocation::GetLatitudeDeg);

  PropertyManager->Tie("position/vrp-longitude_deg", &vLocationVRP, &FGLocation::GetLongitudeDeg);

  PropertyManager->Tie("position/vrp-radius-ft", &vLocationVRP, &FGLocation::GetRadius);


  PropertyManager->Tie("position/from-start-neu-n-ft", this, eX, &FGAuxiliary::GetNEUPositionFromStart);

  PropertyManager->Tie("position/from-start-neu-e-ft", this, eY, &FGAuxiliary::GetNEUPositionFromStart);

  PropertyManager->Tie("position/from-start-neu-u-ft", this, eZ, &FGAuxiliary::GetNEUPositionFromStart);

}


//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%


double FGAuxiliary::BadUnits(void) const

{

  FGLogging log(LogLevel::ERROR);

  log << "Bad units" << endl;

  return 0.0;

}


//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

//    The bitmasked value choices are as follows:

//    unset: In this case (the default) JSBSim would only print

//       out the normally expected messages, essentially echoing

//       the config files as they are read. If the environment

//       variable is not set, debug_lvl is set to 1 internally

//    0: This requests JSBSim not to output any messages

//       whatsoever.

//    1: This value explicity requests the normal JSBSim

//       startup messages

//    2: This value asks for a message to be printed out when

//       a class is instantiated

//    4: When this value is set, a message is displayed when a

//       FGModel object executes its Run() method

//    8: When this value is set, various runtime state variables

//       are printed out periodically

//    16: When set various parameters are sanity checked and

//       a message is printed out when they go out of bounds


void FGAuxiliary::Debug(int from)

{

  if (debug_lvl <= 0) return;


  if (debug_lvl & 1) { // Standard console startup message output

    if (from == 0) { // Constructor


    }

  }

  if (debug_lvl & 2 ) { // Instantiation/Destruction notification

    FGLogging log(LogLevel::DEBUG);

    if (from == 0) log << "Instantiated: FGAuxiliary" << endl;

    if (from == 1) log << "Destroyed:    FGAuxiliary" << endl;

  }

  if (debug_lvl & 4 ) { // Run() method entry print for FGModel-derived objects

  }

  if (debug_lvl & 8 ) { // Runtime state variables

  }

  if (debug_lvl & 16) { // Sanity checking

    FGLogging log(LogLevel::DEBUG);

    if (Mach > 100 || Mach < 0.00)

      log << "FGPropagate::Mach is out of bounds: " << Mach << endl;

    if (qbar > 1e6 || qbar < 0.00)

      log << "FGPropagate::qbar is out of bounds: " << qbar << endl;

  }

  if (debug_lvl & 64) {

    if (from == 0) { // Constructor

    }

  }

}


} // namespace JSBSim

JSBSim::FGAuxiliary::PitotTotalPressure
double PitotTotalPressure(double mach, double pressure) const
Compute the total pressure in front of the Pitot tube.
Definition FGAuxiliary.cpp:244

JSBSim::FGAuxiliary::VcalibratedFromMach
double VcalibratedFromMach(double mach, double pressure) const
Calculate the calibrated airspeed from the Mach number.
Definition FGAuxiliary.cpp:303

JSBSim::FGAuxiliary::GetVtrueFPS
double GetVtrueFPS() const
Returns the true airspeed in feet per second.
Definition FGAuxiliary.h:170

JSBSim::FGAuxiliary::GetVcalibratedFPS
double GetVcalibratedFPS(void) const
Returns Calibrated airspeed in feet/second.
Definition FGAuxiliary.h:162

JSBSim::FGAuxiliary::GetVground
double GetVground(void) const
Gets the ground speed in feet per second.
Definition FGAuxiliary.h:247

JSBSim::FGAuxiliary::GetVcalibratedKTS
double GetVcalibratedKTS(void) const
Returns Calibrated airspeed in knots.
Definition FGAuxiliary.h:164

JSBSim::FGAuxiliary::GetMach
double GetMach(void) const
Gets the Mach number.
Definition FGAuxiliary.h:250

JSBSim::FGAuxiliary::GetTotalPressure
double GetTotalPressure(void) const
Returns the total pressure.
Definition FGAuxiliary.h:178

JSBSim::FGAuxiliary::GetVtrueKTS
double GetVtrueKTS() const
Returns the true airspeed in knots.
Definition FGAuxiliary.h:172

JSBSim::FGAuxiliary::GetNz
double GetNz(void) const
The vertical acceleration in g's of the aircraft center of gravity.
Definition FGAuxiliary.h:262

JSBSim::FGAuxiliary::GetVequivalentFPS
double GetVequivalentFPS(void) const
Returns equivalent airspeed in feet/second.
Definition FGAuxiliary.h:166

JSBSim::FGAuxiliary::GetMachU
double GetMachU(void) const
The mach number calculated using the vehicle X axis velocity.
Definition FGAuxiliary.h:253

JSBSim::FGAuxiliary::Run
bool Run(bool Holding) override
Runs the Auxiliary routines; called by the Executive Can pass in a value indicating if the executive ...
Definition FGAuxiliary.cpp:144

JSBSim::FGAuxiliary::GetTotalTemperature
double GetTotalTemperature(void) const
Returns the total temperature.
Definition FGAuxiliary.h:188

JSBSim::FGAuxiliary::GetVt
double GetVt(void) const
Gets the magnitude of total vehicle velocity including wind effects in feet per second.
Definition FGAuxiliary.h:241

JSBSim::FGAuxiliary::GetNy
double GetNy(void) const
The lateral acceleration in g's of the aircraft center of gravity.
Definition FGAuxiliary.h:259

JSBSim::FGAuxiliary::GetNx
double GetNx(void) const
The longitudinal acceleration in g's of the aircraft center of gravity.
Definition FGAuxiliary.h:256

JSBSim::FGAuxiliary::~FGAuxiliary
~FGAuxiliary()
Destructor.
Definition FGAuxiliary.cpp:137

JSBSim::FGAuxiliary::MachFromVcalibrated
double MachFromVcalibrated(double vcas, double pressure) const
Calculate the Mach number from the calibrated airspeed.Based on the formulas in the US Air Force Airc...
Definition FGAuxiliary.cpp:311

JSBSim::FGAuxiliary::MachFromImpactPressure
double MachFromImpactPressure(double qc, double p) const
Compute the Mach number from the differential pressure (qc) and the static pressure.
Definition FGAuxiliary.cpp:281

JSBSim::FGAuxiliary::FGAuxiliary
FGAuxiliary(FGFDMExec *Executive)
Constructor.
Definition FGAuxiliary.cpp:62

JSBSim::FGAuxiliary::GetVequivalentKTS
double GetVequivalentKTS(void) const
Returns equivalent airspeed in knots.
Definition FGAuxiliary.h:168

JSBSim::FGColumnVector3
This class implements a 3 element column vector.
Definition FGColumnVector3.h:66

JSBSim::FGFDMExec
Encapsulates the JSBSim simulation executive.
Definition FGFDMExec.h:185

JSBSim::FGFDMExec::GetIC
std::shared_ptr< FGInitialCondition > GetIC(void) const
Returns a pointer to the FGInitialCondition object.
Definition FGFDMExec.h:390

JSBSim::FGJSBBase::slugtolb
static constexpr double slugtolb
Note that definition of lbtoslug by the inverse of slugtolb and not to a different constant you can a...
Definition FGJSBBase.h:314

JSBSim::FGJSBBase::RankineToCelsius
static constexpr double RankineToCelsius(double rankine)
Converts from degrees Rankine to degrees Celsius.
Definition FGJSBBase.h:200

JSBSim::FGLocation::GetGeodLatitudeRad
double GetGeodLatitudeRad(void) const
Get the GEODETIC latitude in radians.
Definition FGLocation.h:258

JSBSim::FGLocation::GetLongitude
double GetLongitude() const
Get the longitude.
Definition FGLocation.h:234

JSBSim::FGLocation::GetRadius
double GetRadius() const
Get the distance from the center of the earth in feet.
Definition FGLocation.h:291

JSBSim::FGLocation::LocationToLocal
FGColumnVector3 LocationToLocal(const FGColumnVector3 &ecvec) const
Conversion from a location in the earth centered and fixed frame to local horizontal frame coordinate...
Definition FGLocation.h:336

JSBSim::FGLocation::LocalToLocation
FGLocation LocalToLocation(const FGColumnVector3 &lvec) const
Conversion from Local frame coordinates to a location in the earth centered and fixed frame.
Definition FGLocation.h:326

JSBSim::FGLocation::GetLatitudeDeg
double GetLatitudeDeg() const
Get the GEOCENTRIC latitude in degrees.
Definition FGLocation.h:267

JSBSim::FGLocation::GetLongitudeDeg
double GetLongitudeDeg() const
Get the longitude.
Definition FGLocation.h:240

JSBSim::FGLocation::SetPositionGeodetic
void SetPositionGeodetic(double lon, double lat, double height)
Sets the longitude, latitude and the distance above the reference spheroid.
Definition FGLocation.cpp:243

JSBSim::FGLocation::GetDistanceTo
double GetDistanceTo(double target_longitude, double target_latitude) const
Get the geodetic distance between the current location and a given location.
Definition FGLocation.cpp:377

JSBSim::FGMatrix33::Transposed
FGMatrix33 Transposed(void) const
Transposed matrix.
Definition FGMatrix33.h:221

JSBSim::FGModel
Base class for all scheduled JSBSim models.
Definition FGModel.h:70

JSBSim::FGModel::Run
virtual bool Run(bool Holding)
Runs the model; called by the Executive.
Definition FGModel.cpp:90

JSBSim
Main namespace for the JSBSim Flight Dynamics Model.
Definition FGFDMExec.cpp:71