Purpose: Manage output of sim parameters to file or stdout
Called by: FGSimExec
- ------------- Copyright (C) 1999 Jon S. Berndt (jsb@hal-pc.org) -------------
+ ------------- 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
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
#include "FGOutput.h"
-#include "FGState.h"
#include "FGFDMExec.h"
#include "FGAtmosphere.h"
#include "FGFCS.h"
#include "FGAerodynamics.h"
#include "FGGroundReactions.h"
+#include "FGExternalReactions.h"
+#include "FGBuoyantForces.h"
#include "FGAircraft.h"
#include "FGMassBalance.h"
#include "FGPropagate.h"
#include "FGAuxiliary.h"
#include "FGInertial.h"
-#include "FGPropulsion.h" //access to FGEngine, FGTank
+#include "FGPropulsion.h"
+#include "models/propulsion/FGEngine.h"
+#include "models/propulsion/FGTank.h"
#include "models/propulsion/FGPiston.h"
-#include <fstream>
+#include <sstream>
#include <iomanip>
#include <cstring>
+#include <cstdlib>
#include "input_output/net_fdm.hxx"
+#include "input_output/FGfdmSocket.h"
#if defined(WIN32) && !defined(__CYGWIN__)
# include <windows.h>
static const int endianTest = 1;
#define isLittleEndian (*((char *) &endianTest ) != 0)
+using namespace std;
namespace JSBSim {
-static const char *IdSrc = "$Id$";
+static const char *IdSrc = "$Id: FGOutput.cpp,v 1.48 2010/04/12 12:25:19 jberndt Exp $";
static const char *IdHdr = ID_OUTPUT;
// (stolen from FGFS native_fdm.cxx)
sFirstPass = dFirstPass = true;
socket = 0;
flightGearSocket = 0;
+ runID_postfix = 0;
Type = otNone;
SubSystems = 0;
enabled = true;
+ StartNewFile = false;
delimeter = ", ";
- Filename = "";
+ BaseFilename = Filename = "";
DirectivesFile = "";
output_file_name = "";
{
if (!FGModel::InitModel()) return false;
+ if (Filename.size() > 0 && StartNewFile) {
+ ostringstream buf;
+ string::size_type dot = BaseFilename.find_last_of('.');
+ if (dot != string::npos) {
+ buf << BaseFilename.substr(0, dot) << '_' << runID_postfix++ << BaseFilename.substr(dot);
+ } else {
+ buf << BaseFilename << '_' << runID_postfix++;
+ }
+ Filename = buf.str();
+ datafile.close();
+ StartNewFile = false;
+ dFirstPass = true;
+ }
+
return true;
}
{
if (FGModel::Run()) return true;
- if (enabled && !State->IntegrationSuspended()&& !FDMExec->Holding()) {
+ if (enabled && !FDMExec->IntegrationSuspended()&& !FDMExec->Holding()) {
+ RunPreFunctions();
if (Type == otSocket) {
SocketOutput();
} else if (Type == otFlightGear) {
} else {
// Not a valid type of output
}
+ RunPostFunctions();
}
return false;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGOutput::SetType(string type)
+void FGOutput::SetType(const string& type)
{
if (type == "CSV") {
Type = otCSV;
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGOutput::DelimitedOutput(string fname)
+void FGOutput::DelimitedOutput(const string& fname)
{
streambuf* buffer;
string scratch = "";
if (fname == "COUT" || fname == "cout") {
buffer = cout.rdbuf();
} else {
- datafile.open(fname.c_str());
+ if (!datafile.is_open()) datafile.open(fname.c_str());
buffer = datafile.rdbuf();
}
if (SubSystems & ssRates) {
outstream << delimeter;
outstream << "P (deg/s)" + delimeter + "Q (deg/s)" + delimeter + "R (deg/s)" + delimeter;
- outstream << "P dot (deg/s^2)" + delimeter + "Q dot (deg/s^2)" + delimeter + "R dot (deg/s^2)";
+ outstream << "P dot (deg/s^2)" + delimeter + "Q dot (deg/s^2)" + delimeter + "R dot (deg/s^2)" + delimeter;
+ outstream << "P_{inertial} (deg/s)" + delimeter + "Q_{inertial} (deg/s)" + delimeter + "R_{inertial} (deg/s)";
}
if (SubSystems & ssVelocities) {
outstream << delimeter;
outstream << "q bar (psf)" + delimeter;
+ outstream << "Reynolds Number" + delimeter;
outstream << "V_{Total} (ft/s)" + delimeter;
outstream << "V_{Inertial} (ft/s)" + delimeter;
outstream << "UBody" + delimeter + "VBody" + delimeter + "WBody" + delimeter;
outstream << "Aero V_{X Body} (ft/s)" + delimeter + "Aero V_{Y Body} (ft/s)" + delimeter + "Aero V_{Z Body} (ft/s)" + delimeter;
+ outstream << "V_{X_{inertial}} (ft/s)" + delimeter + "V_{Y_{inertial}} (ft/s)" + delimeter + "V_{Z_{inertial}} (ft/s)" + delimeter;
outstream << "V_{North} (ft/s)" + delimeter + "V_{East} (ft/s)" + delimeter + "V_{Down} (ft/s)";
}
if (SubSystems & ssForces) {
outstream << delimeter;
outstream << "F_{Drag} (lbs)" + delimeter + "F_{Side} (lbs)" + delimeter + "F_{Lift} (lbs)" + delimeter;
outstream << "L/D" + delimeter;
- outstream << "F_X (lbs)" + delimeter + "F_Y (lbs)" + delimeter + "F_Z (lbs)";
+ outstream << "F_{Aero x} (lbs)" + delimeter + "F_{Aero y} (lbs)" + delimeter + "F_{Aero z} (lbs)" + delimeter;
+ outstream << "F_{Prop x} (lbs)" + delimeter + "F_{Prop y} (lbs)" + delimeter + "F_{Prop z} (lbs)" + delimeter;
+ outstream << "F_{Gear x} (lbs)" + delimeter + "F_{Gear y} (lbs)" + delimeter + "F_{Gear z} (lbs)" + delimeter;
+ outstream << "F_{Ext x} (lbs)" + delimeter + "F_{Ext y} (lbs)" + delimeter + "F_{Ext z} (lbs)" + delimeter;
+ outstream << "F_{Buoyant x} (lbs)" + delimeter + "F_{Buoyant y} (lbs)" + delimeter + "F_{Buoyant z} (lbs)" + delimeter;
+ outstream << "F_{Total x} (lbs)" + delimeter + "F_{Total y} (lbs)" + delimeter + "F_{Total z} (lbs)";
}
if (SubSystems & ssMoments) {
outstream << delimeter;
- outstream << "L (ft-lbs)" + delimeter + "M (ft-lbs)" + delimeter + "N (ft-lbs)";
+ outstream << "L_{Aero} (ft-lbs)" + delimeter + "M_{Aero} ( ft-lbs)" + delimeter + "N_{Aero} (ft-lbs)" + delimeter;
+ outstream << "L_{Prop} (ft-lbs)" + delimeter + "M_{Prop} (ft-lbs)" + delimeter + "N_{Prop} (ft-lbs)" + delimeter;
+ outstream << "L_{Gear} (ft-lbs)" + delimeter + "M_{Gear} (ft-lbs)" + delimeter + "N_{Gear} (ft-lbs)" + delimeter;
+ outstream << "L_{ext} (ft-lbs)" + delimeter + "M_{ext} (ft-lbs)" + delimeter + "N_{ext} (ft-lbs)" + delimeter;
+ outstream << "L_{Buoyant} (ft-lbs)" + delimeter + "M_{Buoyant} (ft-lbs)" + delimeter + "N_{Buoyant} (ft-lbs)" + delimeter;
+ outstream << "L_{Total} (ft-lbs)" + delimeter + "M_{Total} (ft-lbs)" + delimeter + "N_{Total} (ft-lbs)";
}
if (SubSystems & ssAtmosphere) {
outstream << delimeter;
outstream << "Rho (slugs/ft^3)" + delimeter;
+ outstream << "Absolute Viscosity" + delimeter;
+ outstream << "Kinematic Viscosity" + delimeter;
+ outstream << "Temperature (R)" + delimeter;
outstream << "P_{SL} (psf)" + delimeter;
outstream << "P_{Ambient} (psf)" + delimeter;
outstream << "Turbulence Magnitude (ft/sec)" + delimeter;
}
if (SubSystems & ssMassProps) {
outstream << delimeter;
- outstream << "I_xx" + delimeter;
- outstream << "I_xy" + delimeter;
- outstream << "I_xz" + delimeter;
- outstream << "I_yx" + delimeter;
- outstream << "I_yy" + delimeter;
- outstream << "I_yz" + delimeter;
- outstream << "I_zx" + delimeter;
- outstream << "I_zy" + delimeter;
- outstream << "I_zz" + delimeter;
+ outstream << "I_{xx}" + delimeter;
+ outstream << "I_{xy}" + delimeter;
+ outstream << "I_{xz}" + delimeter;
+ outstream << "I_{yx}" + delimeter;
+ outstream << "I_{yy}" + delimeter;
+ outstream << "I_{yz}" + delimeter;
+ outstream << "I_{zx}" + delimeter;
+ outstream << "I_{zy}" + delimeter;
+ outstream << "I_{zz}" + delimeter;
outstream << "Mass" + delimeter;
- outstream << "X_cg" + delimeter + "Y_cg" + delimeter + "Z_cg";
+ outstream << "X_{cg}" + delimeter + "Y_{cg}" + delimeter + "Z_{cg}";
}
if (SubSystems & ssPropagate) {
outstream << delimeter;
- outstream << "Altitude (ft)" + delimeter;
+ outstream << "Altitude ASL (ft)" + delimeter;
+ outstream << "Altitude AGL (ft)" + delimeter;
outstream << "Phi (deg)" + delimeter + "Theta (deg)" + delimeter + "Psi (deg)" + delimeter;
outstream << "Alpha (deg)" + delimeter;
outstream << "Beta (deg)" + delimeter;
outstream << "Latitude (deg)" + delimeter;
outstream << "Longitude (deg)" + delimeter;
- outstream << "ECEF X (ft)" + delimeter + "ECEF Y (ft)" + delimeter + "ECEF Z (ft)" + delimeter;
- outstream << "EPA (deg)" + delimeter;
+ outstream << "X_{ECI} (ft)" + delimeter + "Y_{ECI} (ft)" + delimeter + "Z_{ECI} (ft)" + delimeter;
+ outstream << "X_{ECEF} (ft)" + delimeter + "Y_{ECEF} (ft)" + delimeter + "Z_{ECEF} (ft)" + delimeter;
+ outstream << "Earth Position Angle (deg)" + delimeter;
outstream << "Distance AGL (ft)" + delimeter;
- outstream << "Runway Radius (ft)";
+ outstream << "Terrain Elevation (ft)";
}
if (SubSystems & ssCoefficients) {
scratch = Aerodynamics->GetCoefficientStrings(delimeter);
dFirstPass = false;
}
- outstream << State->Getsim_time();
+ outstream << FDMExec->GetSimTime();
if (SubSystems & ssSimulation) {
}
if (SubSystems & ssAerosurfaces) {
if (SubSystems & ssRates) {
outstream << delimeter;
outstream << (radtodeg*Propagate->GetPQR()).Dump(delimeter) << delimeter;
- outstream << (radtodeg*Propagate->GetPQRdot()).Dump(delimeter);
+ outstream << (radtodeg*Propagate->GetPQRdot()).Dump(delimeter) << delimeter;
+ outstream << (radtodeg*Propagate->GetPQRi()).Dump(delimeter);
}
if (SubSystems & ssVelocities) {
outstream << delimeter;
outstream << Auxiliary->Getqbar() << delimeter;
+ outstream << Auxiliary->GetReynoldsNumber() << delimeter;
outstream << setprecision(12) << Auxiliary->GetVt() << delimeter;
outstream << Propagate->GetInertialVelocityMagnitude() << delimeter;
outstream << setprecision(12) << Propagate->GetUVW().Dump(delimeter) << delimeter;
outstream << Auxiliary->GetAeroUVW().Dump(delimeter) << delimeter;
+ outstream << Propagate->GetInertialVelocity().Dump(delimeter) << delimeter;
outstream << Propagate->GetVel().Dump(delimeter);
+ outstream.precision(10);
}
if (SubSystems & ssForces) {
outstream << delimeter;
- outstream << Aerodynamics->GetvFw() << delimeter;
+ outstream << Aerodynamics->GetvFw().Dump(delimeter) << delimeter;
outstream << Aerodynamics->GetLoD() << delimeter;
+ outstream << Aerodynamics->GetForces().Dump(delimeter) << delimeter;
+ outstream << Propulsion->GetForces().Dump(delimeter) << delimeter;
+ outstream << GroundReactions->GetForces().Dump(delimeter) << delimeter;
+ outstream << ExternalReactions->GetForces().Dump(delimeter) << delimeter;
+ outstream << BuoyantForces->GetForces().Dump(delimeter) << delimeter;
outstream << Aircraft->GetForces().Dump(delimeter);
}
if (SubSystems & ssMoments) {
outstream << delimeter;
+ outstream << Aerodynamics->GetMoments().Dump(delimeter) << delimeter;
+ outstream << Propulsion->GetMoments().Dump(delimeter) << delimeter;
+ outstream << GroundReactions->GetMoments().Dump(delimeter) << delimeter;
+ outstream << ExternalReactions->GetMoments().Dump(delimeter) << delimeter;
+ outstream << BuoyantForces->GetMoments().Dump(delimeter) << delimeter;
outstream << Aircraft->GetMoments().Dump(delimeter);
}
if (SubSystems & ssAtmosphere) {
outstream << delimeter;
outstream << Atmosphere->GetDensity() << delimeter;
+ outstream << Atmosphere->GetAbsoluteViscosity() << delimeter;
+ outstream << Atmosphere->GetKinematicViscosity() << delimeter;
+ outstream << Atmosphere->GetTemperature() << delimeter;
outstream << Atmosphere->GetPressureSL() << delimeter;
outstream << Atmosphere->GetPressure() << delimeter;
outstream << Atmosphere->GetTurbMagnitude() << delimeter;
outstream << Atmosphere->GetTurbDirection().Dump(delimeter) << delimeter;
- outstream << Atmosphere->GetWindNED().Dump(delimeter);
+ outstream << Atmosphere->GetTotalWindNED().Dump(delimeter);
}
if (SubSystems & ssMassProps) {
outstream << delimeter;
- outstream << MassBalance->GetJ() << delimeter;
+ outstream << MassBalance->GetJ().Dump(delimeter) << delimeter;
outstream << MassBalance->GetMass() << delimeter;
- outstream << MassBalance->GetXYZcg();
+ outstream << MassBalance->GetXYZcg().Dump(delimeter);
}
if (SubSystems & ssPropagate) {
+ outstream.precision(14);
outstream << delimeter;
- outstream << Propagate->Geth() << delimeter;
+ outstream << Propagate->GetAltitudeASL() << delimeter;
+ outstream << Propagate->GetDistanceAGL() << delimeter;
outstream << (radtodeg*Propagate->GetEuler()).Dump(delimeter) << delimeter;
outstream << Auxiliary->Getalpha(inDegrees) << delimeter;
outstream << Auxiliary->Getbeta(inDegrees) << delimeter;
outstream << Propagate->GetLocation().GetLatitudeDeg() << delimeter;
outstream << Propagate->GetLocation().GetLongitudeDeg() << delimeter;
+ outstream.precision(18);
+ outstream << ((FGColumnVector3)Propagate->GetInertialPosition()).Dump(delimeter) << delimeter;
outstream << ((FGColumnVector3)Propagate->GetLocation()).Dump(delimeter) << delimeter;
+ outstream.precision(14);
outstream << Inertial->GetEarthPositionAngleDeg() << delimeter;
outstream << Propagate->GetDistanceAGL() << delimeter;
- outstream << Propagate->GetRunwayRadius();
+ outstream << Propagate->GetTerrainElevation();
+ outstream.precision(10);
}
if (SubSystems & ssCoefficients) {
scratch = Aerodynamics->GetCoefficientValues(delimeter);
outstream << Propulsion->GetPropulsionValues(delimeter);
}
+ outstream.precision(18);
for (unsigned int i=0;i<OutputProperties.size();i++) {
outstream << delimeter << OutputProperties[i]->getDoubleValue();
}
+ outstream.precision(10);
outstream << endl;
outstream.flush();
// Positions
net->longitude = Propagate->GetLocation().GetLongitude(); // geodetic (radians)
net->latitude = Propagate->GetLocation().GetLatitude(); // geodetic (radians)
- net->altitude = Propagate->Geth()*0.3048; // altitude, above sea level (meters)
+ net->altitude = Propagate->GetAltitudeASL()*0.3048; // altitude, above sea level (meters)
net->agl = (float)(Propagate->GetDistanceAGL()*0.3048); // altitude, above ground level (meters)
net->phi = (float)(Propagate->GetEuler(ePhi)); // roll (radians)
}
socket->Clear();
- socket->Append(State->Getsim_time());
+ socket->Append(FDMExec->GetSimTime());
if (SubSystems & ssAerosurfaces) {
socket->Append(FCS->GetDaCmd());
socket->Append(Atmosphere->GetPressure());
socket->Append(Atmosphere->GetTurbMagnitude());
socket->Append(Atmosphere->GetTurbDirection().Dump(","));
- socket->Append(Atmosphere->GetWindNED().Dump(","));
+ socket->Append(Atmosphere->GetTotalWindNED().Dump(","));
}
if (SubSystems & ssMassProps) {
socket->Append(MassBalance->GetJ()(1,1));
socket->Append(MassBalance->GetXYZcg()(eZ));
}
if (SubSystems & ssPropagate) {
- socket->Append(Propagate->Geth());
+ socket->Append(Propagate->GetAltitudeASL());
socket->Append(radtodeg*Propagate->GetEuler(ePhi));
socket->Append(radtodeg*Propagate->GetEuler(eTht));
socket->Append(radtodeg*Propagate->GetEuler(ePsi));
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGOutput::SocketStatusOutput(string out_str)
+void FGOutput::SocketStatusOutput(const string& out_str)
{
string asciiData;
Element *property_element;
string separator = "/";
-# ifdef macintosh
- separator = ";";
-# endif
if (!DirectivesFile.empty()) { // A directives filename from the command line overrides
output_file_name = DirectivesFile; // one found in the config file.
document = LoadXMLDocument(output_file_name);
} else if (!element->GetAttributeValue("file").empty()) {
- output_file_name = element->GetAttributeValue("file");
+ output_file_name = FDMExec->GetRootDir() + element->GetAttributeValue("file");
document = LoadXMLDocument(output_file_name);
} else {
document = element;
}
- name = document->GetAttributeValue("name");
+ if (!document) return false;
+
+ name = FDMExec->GetRootDir() + document->GetAttributeValue("name");
type = document->GetAttributeValue("type");
SetType(type);
if (!document->GetAttributeValue("port").empty() && type == string("SOCKET")) {
else
flightGearSocket = new FGfdmSocket(name, port, FGfdmSocket::ptTCP); // create tcp socket (default)
} else {
- Filename = name;
+ BaseFilename = Filename = name;
}
if (!document->GetAttributeValue("rate").empty()) {
OutRate = (int)document->GetAttributeValueAsNumber("rate");
property_element = document->FindNextElement("property");
}
- OutRate = OutRate>1000?1000:(OutRate<0?0:OutRate);
- rate = (int)(0.5 + 1.0/(State->Getdt()*OutRate));
+ SetRate(OutRate);
Debug(2);
return true;
}
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
+void FGOutput::SetRate(int rtHz)
+{
+ rtHz = rtHz>1000?1000:(rtHz<0?0:rtHz);
+ if (rtHz > 0) {
+ rate = (int)(0.5 + 1.0/(FDMExec->GetDeltaT()*rtHz));
+ Enable();
+ } else {
+ rate = 1;
+ Disable();
+ }
+}
+
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
// The bitmasked value choices are as follows:
// unset: In this case (the default) JSBSim would only print
}
switch (Type) {
case otCSV:
- cout << scratch << " in CSV format output at rate " << 1/(State->Getdt()*rate) << " Hz" << endl;
+ cout << scratch << " in CSV format output at rate " << 1/(FDMExec->GetDeltaT()*rate) << " Hz" << endl;
break;
case otNone:
+ default:
cout << " No log output" << endl;
break;
}
projects / flightgear.git / blobdiff