#include <Main/fg_props.hxx>
+#include "Math.hpp"
#include "Jet.hpp"
#include "SimpleJet.hpp"
#include "Gear.hpp"
#include "PropEngine.hpp"
#include "Propeller.hpp"
#include "PistonEngine.hpp"
+#include "TurbineEngine.hpp"
#include "Rotor.hpp"
#include "Rotorpart.hpp"
#include "Rotorblade.hpp"
static const float CIN2CM = 1.6387064e-5;
static const float YASIM_PI = 3.14159265358979323846;
+static const float NM2FTLB = (1/(LBS2N*FT2M));
+
// Stubs, so that this can be compiled without the FlightGear
// binary. What's the best way to handle this?
// should probably be settable, but there are very few aircraft
// who trim their approaches using things other than elevator.
_airplane.setElevatorControl(parseAxis("/controls/flight/elevator-trim"));
+
+ // FIXME: read seed from somewhere?
+ int seed = 0;
+ _turb = new Turbulence(10, seed);
}
FGFDM::~FGFDM()
getExternalInput(dt);
_airplane.iterate(dt);
- if(fgGetBool("/sim/freeze/fuel") != true)
- _airplane.consumeFuel(dt);
+ // Do fuel stuff (FIXME: should stash SGPropertyNode objects here)
+ char buf[256];
+ for(int i=0; i<_airplane.numThrusters(); i++) {
+ Thruster* t = _airplane.getThruster(i);
+
+ sprintf(buf, "/engines/engine[%d]/out-of-fuel", i);
+ t->setFuelState(!fgGetBool(buf));
+ sprintf(buf, "/engines/engine[%d]/fuel-consumed-lbs", i);
+ double consumed = fgGetDouble(buf) + dt * KG2LBS * t->getFuelFlow();
+ fgSetDouble(buf, consumed);
+ }
+ for(int i=0; i<_airplane.numTanks(); i++) {
+ sprintf(buf, "/consumables/fuel/tank[%d]/level-lbs", i);
+ _airplane.setFuel(i, LBS2KG * fgGetFloat(buf));
+ }
+ _airplane.calcFuelWeights();
+
setOutputProperties();
}
// Allows the user to start with something other than full fuel
_airplane.setFuelFraction(fgGetFloat("/sim/fuel-fraction", 1));
+ // Read out the resulting fuel state
+ char buf[256];
+ for(int i=0; i<_airplane.numTanks(); i++) {
+ sprintf(buf, "/consumables/fuel/tank[%d]/level-lbs", i);
+ fgSetDouble(buf, _airplane.getFuel(i) * KG2LBS);
+
+ double density = _airplane.getFuelDensity(i);
+ sprintf(buf, "/consumables/fuel/tank[%d]/density-ppg", i);
+ fgSetDouble(buf, density * (KG2LBS/CM2GALS));
+
+ sprintf(buf, "/consumables/fuel/tank[%d]/level-gal_us", i);
+ fgSetDouble(buf, _airplane.getFuel(i) * CM2GALS / density);
+
+ sprintf(buf, "/consumables/fuel/tank[%d]/capacity-gal_us", i);
+ fgSetDouble(buf, CM2GALS * _airplane.getTankCapacity(i)/density);
+ }
+
// This has a nasty habit of being false at startup. That's not
// good.
fgSetBool("/controls/gear/gear-down", true);
+
+ _airplane.getModel()->setTurbulence(_turb);
}
// Not the worlds safest parser. But it's short & sweet.
float spd = attrf(a, "speed") * KTS2MPS;
float alt = attrf(a, "alt", 0) * FT2M;
float aoa = attrf(a, "aoa", 0) * DEG2RAD;
- _airplane.setApproach(spd, alt, aoa);
+ _airplane.setApproach(spd, alt, aoa, attrf(a, "fuel", 0.2));
_cruiseCurr = false;
} else if(eq(name, "cruise")) {
float spd = attrf(a, "speed") * KTS2MPS;
float alt = attrf(a, "alt") * FT2M;
- _airplane.setCruise(spd, alt);
+ _airplane.setCruise(spd, alt, attrf(a, "fuel", 0.5));
_cruiseCurr = true;
+ } else if(eq(name, "solve-weight")) {
+ int idx = attri(a, "idx");
+ float wgt = attrf(a, "weight") * LBS2KG;
+ _airplane.addSolutionWeight(!_cruiseCurr, idx, wgt);
} else if(eq(name, "cockpit")) {
v[0] = attrf(a, "x");
v[1] = attrf(a, "y");
_airplane.setWing(parseWing(a, name));
} else if(eq(name, "hstab")) {
_airplane.setTail(parseWing(a, name));
- } else if(eq(name, "vstab")) {
- _airplane.addVStab(parseWing(a, name));
- } else if(eq(name, "mstab")) {
+ } else if(eq(name, "vstab") || eq(name, "mstab")) {
_airplane.addVStab(parseWing(a, name));
+ } else if(eq(name, "piston-engine")) {
+ parsePistonEngine(a);
+ } else if(eq(name, "turbine-engine")) {
+ parseTurbineEngine(a);
} else if(eq(name, "propeller")) {
parsePropeller(a);
} else if(eq(name, "thruster")) {
j->setMaxThrust(attrf(a, "thrust") * LBS2N,
attrf(a, "afterburner", 0) * LBS2N);
j->setVectorAngle(attrf(a, "rotate", 0) * DEG2RAD);
+ j->setReverseThrust(attrf(a, "reverse", 0.2));
float n1min = attrf(a, "n1-idle", 55);
float n1max = attrf(a, "n1-max", 102);
{
char buf[256];
+ _turb->setMagnitude(fgGetFloat("/environment/turbulence/magnitude-norm"));
+ _turb->update(dt, fgGetFloat("/environment/turbulence/rate-hz"));
+
// The control axes
ControlMap* cm = _airplane.getControlMap();
cm->reset();
if(t->getPropEngine()) {
PropEngine* p = t->getPropEngine();
sprintf(buf, "%s/rpm", er->prefix);
- p->setOmega(fgGetFloat(buf) * RPM2RAD);
+ p->setOmega(fgGetFloat(buf, 500) * RPM2RAD);
}
}
}
void FGFDM::setOutputProperties()
{
- char buf[256];
+ // char buf[256];
int i;
float grossWgt = _airplane.getModel()->getBody()->getTotalMass() * KG2LBS;
p->prop->setFloatValue(val);
}
- float totalFuel = 0, totalCap = 0;
- float fuelDensity = 720; // in kg/m^3, default to gasoline: ~6 lb/gal
- for(i=0; i<_airplane.numTanks(); i++) {
- fuelDensity = _airplane.getFuelDensity(i);
- sprintf(buf, "/consumables/fuel/tank[%d]/level-gal_us", i);
- fgSetFloat(buf, CM2GALS*_airplane.getFuel(i)/fuelDensity);
- sprintf(buf, "/consumables/fuel/tank[%d]/level-lbs", i);
- fgSetFloat(buf, KG2LBS*_airplane.getFuel(i));
- totalFuel += _airplane.getFuel(i);
- totalCap += _airplane.getTankCapacity(i);
- }
- if(totalCap != 0) {
- fgSetFloat("/consumables/fuel/total-fuel-lbs", KG2LBS*totalFuel);
- fgSetFloat("/consumables/fuel/total-fuel-gals",
- CM2GALS*totalFuel/fuelDensity);
- fgSetFloat("/consumables/fuel/total-fuel-norm", totalFuel/totalCap);
- }
-
for(i=0; i<_airplane.getNumRotors(); i++) {
Rotor*r=(Rotor*)_airplane.getRotor(i);
- int j=0;
+ int j = 0;
float f;
char b[256];
- while(j=r->getValueforFGSet(j,b,&f))
- {
- if (b[0])
- {
- fgSetFloat(b,f);
- }
- }
+ while(j = r->getValueforFGSet(j, b, &f))
+ if(b[0]) fgSetFloat(b,f);
- for(j=0; j<r->numRotorparts(); j++) {
+ for(j=0; j < r->numRotorparts(); j++) {
Rotorpart* s = (Rotorpart*)r->getRotorpart(j);
char *b;
int k;
- for (k=0;k<2;k++)
- {
- b=s->getAlphaoutput(k);
- if (b[0])
- {
- fgSetFloat(b,s->getAlpha(k));
- //printf("setting [%s]\n",b);
- }
+ for(k=0; k<2; k++) {
+ b=s->getAlphaoutput(k);
+ if(b[0]) fgSetFloat(b, s->getAlpha(k));
}
}
- for(j=0; j<r->numRotorblades(); j++) {
+ for(j=0; j < r->numRotorblades(); j++) {
Rotorblade* s = (Rotorblade*)r->getRotorblade(j);
char *b;
int k;
- for (k=0;k<2;k++)
- {
- b=s->getAlphaoutput(k);
- if (b[0])
- {
- fgSetFloat(b,s->getAlpha(k));
- }
+ for (k=0; k<2; k++) {
+ b = s->getAlphaoutput(k);
+ if(b[0]) fgSetFloat(b, s->getAlpha(k));
}
}
- }
-
+ }
+ float fuelDensity = _airplane.getFuelDensity(0); // HACK
for(i=0; i<_thrusters.size(); i++) {
EngRec* er = (EngRec*)_thrusters.get(i);
Thruster* t = er->eng;
+ SGPropertyNode * node = fgGetNode("engines/engine", i, true);
+
+ // Set: running, cranking, prop-thrust, max-hp, power-pct
+ node->setBoolValue("running", t->isRunning());
+ node->setBoolValue("cranking", t->isCranking());
- sprintf(buf, "%s/fuel-flow-gph", er->prefix);
- fgSetFloat(buf, (t->getFuelFlow()/fuelDensity) * 3600 * CM2GALS);
+ float tmp[3];
+ t->getThrust(tmp);
+ float lbs = Math::mag3(tmp) * (KG2LBS/9.8);
+ node->setFloatValue("prop-thrust", lbs); // Deprecated name
+ node->setFloatValue("thrust-lbs", lbs);
+ node->setFloatValue("fuel-flow-gph",
+ (t->getFuelFlow()/fuelDensity) * 3600 * CM2GALS);
if(t->getPropEngine()) {
PropEngine* p = t->getPropEngine();
-
- sprintf(buf, "%s/rpm", er->prefix);
- fgSetFloat(buf, p->getOmega() / RPM2RAD);
- }
-
- if(t->getPistonEngine()) {
- PistonEngine* p = t->getPistonEngine();
-
- sprintf(buf, "%s/mp-osi", er->prefix);
- fgSetFloat(buf, p->getMP() * (1/INHG2PA));
-
- sprintf(buf, "%s/egt-degf", er->prefix);
- fgSetFloat(buf, p->getEGT() * K2DEGF + K2DEGFOFFSET);
+ node->setFloatValue("rpm", p->getOmega() * (1/RPM2RAD));
+ node->setFloatValue("torque-ftlb",
+ p->getEngine()->getTorque() * NM2FTLB);
+
+ if(p->getEngine()->isPistonEngine()) {
+ PistonEngine* pe = p->getEngine()->isPistonEngine();
+ node->setFloatValue("mp-osi", pe->getMP() * (1/INHG2PA));
+ node->setFloatValue("mp-inhg", pe->getMP() * (1/INHG2PA));
+ node->setFloatValue("egt-degf",
+ pe->getEGT() * K2DEGF + K2DEGFOFFSET);
+ } else if(p->getEngine()->isTurbineEngine()) {
+ TurbineEngine* te = p->getEngine()->isTurbineEngine();
+ node->setFloatValue("n2", te->getN2());
+ }
}
if(t->getJet()) {
Jet* j = t->getJet();
-
- sprintf(buf, "%s/n1", er->prefix);
- fgSetFloat(buf, j->getN1());
-
- sprintf(buf, "%s/n2", er->prefix);
- fgSetFloat(buf, j->getN2());
-
- sprintf(buf, "%s/epr", er->prefix);
- fgSetFloat(buf, j->getEPR());
-
- sprintf(buf, "%s/egt-degf", er->prefix);
- fgSetFloat(buf, j->getEGT() * K2DEGF + K2DEGFOFFSET);
+ node->setFloatValue("n1", j->getN1());
+ node->setFloatValue("n2", j->getN2());
+ node->setFloatValue("epr", j->getEPR());
+ node->setFloatValue("egr-degf",
+ j->getEGT() * K2DEGF + K2DEGFOFFSET);
}
}
}
_currObj = w;
return w;
}
+
Rotor* FGFDM::parseRotor(XMLAttributes* a, const char* type)
{
Rotor* w = new Rotor();
- float defDihed = 0;
+ // float defDihed = 0;
float pos[3];
pos[0] = attrf(a, "x");
forward[2] = attrf(a, "fz");
w->setForward(forward);
-
-
w->setMaxCyclicail(attrf(a, "maxcyclicail", 7.6));
w->setMaxCyclicele(attrf(a, "maxcyclicele", 4.94));
w->setMinCyclicail(attrf(a, "mincyclicail", -7.6));
void setAlphamax(float f);
void setAlpha0factor(float f);
- if(attristrue(a,"ccw"))
+ if(attrb(a,"ccw"))
w->setCcw(1);
if(a->hasAttribute("name"))
w->setForceAtPitchA(attrf(a, "forceatpitch_a", 3000));
w->setPowerAtPitch0(attrf(a, "poweratpitch_0", 300));
w->setPowerAtPitchB(attrf(a, "poweratpitch_b", 3000));
- if(attristrue(a,"notorque"))
+ if(attrb(a,"notorque"))
w->setNotorque(1);
- if(attristrue(a,"simblades"))
+ if(attrb(a,"simblades"))
w->setSimBlades(1);
+ _currObj = w;
+ return w;
+}
+void FGFDM::parsePistonEngine(XMLAttributes* a)
+{
+ float engP = attrf(a, "eng-power") * HP2W;
+ float engS = attrf(a, "eng-rpm") * RPM2RAD;
+ PistonEngine* eng = new PistonEngine(engP, engS);
+ if(a->hasAttribute("displacement"))
+ eng->setDisplacement(attrf(a, "displacement") * CIN2CM);
- _currObj = w;
- return w;
+ if(a->hasAttribute("compression"))
+ eng->setCompression(attrf(a, "compression"));
+
+ if(a->hasAttribute("turbo-mul")) {
+ float mul = attrf(a, "turbo-mul");
+ float mp = attrf(a, "wastegate-mp", 1e6) * INHG2PA;
+ eng->setTurboParams(mul, mp);
+ }
+
+ ((PropEngine*)_currObj)->setEngine(eng);
+}
+
+void FGFDM::parseTurbineEngine(XMLAttributes* a)
+{
+ float power = attrf(a, "eng-power") * HP2W;
+ float omega = attrf(a, "eng-rpm") * RPM2RAD;
+ float alt = attrf(a, "alt") * FT2M;
+ float flatRating = attrf(a, "flat-rating") * HP2W;
+ TurbineEngine* eng = new TurbineEngine(power, omega, alt, flatRating);
+
+ if(a->hasAttribute("n2-low-idle"))
+ eng->setN2Range(attrf(a, "n2-low-idle"), attrf(a, "n2-high-idle"),
+ attrf(a, "n2-max"));
+
+ // Nasty units conversion: lbs/hr per hp -> kg/s per watt
+ if(a->hasAttribute("bsfc"))
+ eng->setFuelConsumption(attrf(a, "bsfc") * (LBS2KG/(3600*HP2W)));
+
+ ((PropEngine*)_currObj)->setEngine(eng);
}
void FGFDM::parsePropeller(XMLAttributes* a)
{
+ // Legacy Handling for the old engines syntax:
+ PistonEngine* eng = 0;
+ if(a->hasAttribute("eng-power")) {
+ SG_LOG(SG_FLIGHT,SG_ALERT, "WARNING: "
+ << "Legacy engine definition in YASim configuration file. "
+ << "Please fix.");
+ float engP = attrf(a, "eng-power") * HP2W;
+ float engS = attrf(a, "eng-rpm") * RPM2RAD;
+ eng = new PistonEngine(engP, engS);
+ if(a->hasAttribute("displacement"))
+ eng->setDisplacement(attrf(a, "displacement") * CIN2CM);
+ if(a->hasAttribute("compression"))
+ eng->setCompression(attrf(a, "compression"));
+ if(a->hasAttribute("turbo-mul")) {
+ float mul = attrf(a, "turbo-mul");
+ float mp = attrf(a, "wastegate-mp", 1e6) * INHG2PA;
+ eng->setTurboParams(mul, mp);
+ }
+ }
+
+ // Now parse the actual propeller definition:
float cg[3];
cg[0] = attrf(a, "x");
cg[1] = attrf(a, "y");
float power = attrf(a, "cruise-power") * HP2W;
float rho = Atmosphere::getStdDensity(attrf(a, "cruise-alt") * FT2M);
- // Hack, fix this pronto:
- float engP = attrf(a, "eng-power") * HP2W;
- float engS = attrf(a, "eng-rpm") * RPM2RAD;
-
Propeller* prop = new Propeller(radius, speed, omega, rho, power);
- PistonEngine* eng = new PistonEngine(engP, engS);
PropEngine* thruster = new PropEngine(prop, eng, moment);
_airplane.addThruster(thruster, mass, cg);
- if(a->hasAttribute("displacement"))
- eng->setDisplacement(attrf(a, "displacement") * CIN2CM);
-
- if(a->hasAttribute("compression"))
- eng->setCompression(attrf(a, "compression"));
-
- if(a->hasAttribute("turbo-mul")) {
- float mul = attrf(a, "turbo-mul");
- float mp = attrf(a, "wastegate-mp", 1e6) * INHG2PA;
- eng->setTurboParams(mul, mp);
- }
-
if(a->hasAttribute("takeoff-power")) {
float power0 = attrf(a, "takeoff-power") * HP2W;
float omega0 = attrf(a, "takeoff-rpm") * RPM2RAD;
prop->setManualPitch();
}
+ thruster->setGearRatio(attrf(a, "gear-ratio", 1));
+
char buf[64];
sprintf(buf, "/engines/engine[%d]", _nextEngine++);
EngRec* er = new EngRec();
// Not there, make a new one.
AxisRec* a = new AxisRec();
a->name = dup(name);
+ fgGetNode( a->name, true ); // make sure the property name exists
a->handle = _airplane.getControlMap()->newInput();
_axes.add(a);
return a->handle;
{
if(eq(name, "THROTTLE")) return ControlMap::THROTTLE;
if(eq(name, "MIXTURE")) return ControlMap::MIXTURE;
+ if(eq(name, "CONDLEVER")) return ControlMap::CONDLEVER;
if(eq(name, "STARTER")) return ControlMap::STARTER;
if(eq(name, "MAGNETOS")) return ControlMap::MAGNETOS;
if(eq(name, "ADVANCE")) return ControlMap::ADVANCE;
if(eq(name, "SPOILER")) return ControlMap::SPOILER;
if(eq(name, "CASTERING")) return ControlMap::CASTERING;
if(eq(name, "PROPPITCH")) return ControlMap::PROPPITCH;
+ if(eq(name, "PROPFEATHER")) return ControlMap::PROPFEATHER;
if(eq(name, "COLLECTIVE")) return ControlMap::COLLECTIVE;
if(eq(name, "CYCLICAIL")) return ControlMap::CYCLICAIL;
if(eq(name, "CYCLICELE")) return ControlMap::CYCLICELE;
if(eq(name, "ROTORENGINEON")) return ControlMap::ROTORENGINEON;
+ if(eq(name, "REVERSE_THRUST")) return ControlMap::REVERSE_THRUST;
SG_LOG(SG_FLIGHT,SG_ALERT,"Unrecognized control type '"
<< name << "' in YASim aircraft description.");
exit(1);
else return (float)atof(val);
}
-bool FGFDM::attristrue(XMLAttributes* atts, char* attr)
+// ACK: the dreaded ambiguous string boolean. Remind me to shoot Maik
+// when I have a chance. :). Unless you have a parser that can check
+// symbol constants (we don't), this kind of coding is just a Bad
+// Idea. This implementation, for example, silently returns a boolean
+// falsehood for values of "1", "yes", "True", and "TRUE". Which is
+// especially annoying preexisting boolean attributes in the same
+// parser want to see "1" and will choke on a "true"...
+//
+// Unfortunately, this usage creeped into existing configuration files
+// while I wasn't active, and it's going to be hard to remove. Issue
+// a warning to nag people into changing their ways for now...
+bool FGFDM::attrb(XMLAttributes* atts, char* attr)
{
const char* val = atts->getValue(attr);
if(val == 0) return false;
- else return eq(val,"true");
+
+ if(eq(val,"true")) {
+ SG_LOG(SG_FLIGHT, SG_ALERT, "Warning: " <<
+ "deprecated 'true' boolean in YASim configuration file. " <<
+ "Use numeric booleans (attribute=\"1\") instead");
+ return true;
+ }
+ return attri(atts, attr, 0) ? true : false;
}
}; // namespace yasim
projects / flightgear.git / blobdiff