#include <Main/fg_props.hxx>
+#include "Math.hpp"
#include "Jet.hpp"
#include "SimpleJet.hpp"
#include "Gear.hpp"
+#include "Hook.hpp"
+#include "Launchbar.hpp"
#include "Atmosphere.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?
FGFDM::FGFDM()
{
+ _vehicle_radius = 0.0f;
+
_nextEngine = 0;
// Map /controls/flight/elevator to the approach elevator control. This
}
for(i=0; i<_controlProps.size(); i++)
delete (PropOut*)_controlProps.get(i);
+ delete _turb;
}
void FGFDM::iterate(float dt)
t->setFuelState(!fgGetBool(buf));
sprintf(buf, "/engines/engine[%d]/fuel-consumed-lbs", i);
- double consumed = fgGetDouble(buf) + dt * t->getFuelFlow();
+ double consumed = fgGetDouble(buf) + dt * KG2LBS * t->getFuelFlow();
fgSetDouble(buf, consumed);
}
for(int i=0; i<_airplane.numTanks(); i++) {
}
_airplane.calcFuelWeights();
- setOutputProperties();
+ setOutputProperties(dt);
}
Airplane* FGFDM::getAirplane()
_airplane.setTail(parseWing(a, name));
} 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")) {
if(a->hasAttribute("epr")) j->setEPR(attrf(a, "epr"));
if(a->hasAttribute("exhaust-speed"))
j->setVMax(attrf(a, "exhaust-speed") * KTS2MPS);
+ if(a->hasAttribute("spool-time"))
+ j->setSpooling(attrf(a, "spool-time"));
j->setPosition(v);
_airplane.addThruster(j, mass, v);
v[1] = attrf(a, "y");
v[2] = attrf(a, "z");
g->setPosition(v);
- v[0] = 0;
- v[1] = 0;
- v[2] = attrf(a, "compression", 1);
+ float nrm = Math::mag3(v);
+ if (_vehicle_radius < nrm)
+ _vehicle_radius = nrm;
+ if(a->hasAttribute("upx")) {
+ v[0] = attrf(a, "upx");
+ v[1] = attrf(a, "upy");
+ v[2] = attrf(a, "upz");
+ Math::unit3(v, v);
+ } else {
+ v[0] = 0;
+ v[1] = 0;
+ v[2] = 1;
+ }
+ for(int i=0; i<3; i++)
+ v[i] *= attrf(a, "compression", 1);
g->setCompression(v);
g->setBrake(attrf(a, "skid", 0));
g->setStaticFriction(attrf(a, "sfric", 0.8));
g->setSpring(attrf(a, "spring", 1));
g->setDamping(attrf(a, "damp", 1));
_airplane.addGear(g);
+ } else if(eq(name, "hook")) {
+ Hook* h = new Hook();
+ _currObj = h;
+ v[0] = attrf(a, "x");
+ v[1] = attrf(a, "y");
+ v[2] = attrf(a, "z");
+ h->setPosition(v);
+ float length = attrf(a, "length", 1.0);
+ h->setLength(length);
+ float nrm = length+Math::mag3(v);
+ if (_vehicle_radius < nrm)
+ _vehicle_radius = nrm;
+ h->setDownAngle(attrf(a, "down-angle", 70) * DEG2RAD);
+ h->setUpAngle(attrf(a, "up-angle", 0) * DEG2RAD);
+ _airplane.addHook(h);
+ } else if(eq(name, "launchbar")) {
+ Launchbar* l = new Launchbar();
+ _currObj = l;
+ v[0] = attrf(a, "x");
+ v[1] = attrf(a, "y");
+ v[2] = attrf(a, "z");
+ l->setLaunchbarMount(v);
+ v[0] = attrf(a, "holdback-x", v[0]);
+ v[1] = attrf(a, "holdback-y", v[1]);
+ v[2] = attrf(a, "holdback-z", v[2]);
+ l->setHoldbackMount(v);
+ float length = attrf(a, "length", 1.0);
+ l->setLength(length);
+ l->setDownAngle(attrf(a, "down-angle", 45) * DEG2RAD);
+ l->setUpAngle(attrf(a, "up-angle", -45) * DEG2RAD);
+ l->setHoldbackLength(attrf(a, "holdback-length", 2.0));
+ _airplane.addLaunchbar(l);
} else if(eq(name, "fuselage")) {
float b[3];
v[0] = attrf(a, "ax");
}
}
-void FGFDM::setOutputProperties()
+// Linearly "seeks" a property by the specified fraction of the way to
+// the target value. Used to emulate "slowly changing" output values.
+static void moveprop(SGPropertyNode* node, const char* prop,
+ float target, float frac)
{
- char buf[256];
+ float val = node->getFloatValue(prop);
+ if(frac > 1) frac = 1;
+ if(frac < 0) frac = 0;
+ val += (target - val) * frac;
+ node->setFloatValue(prop, val);
+}
+
+void FGFDM::setOutputProperties(float dt)
+{
+ // char buf[256];
int i;
float grossWgt = _airplane.getModel()->getBody()->getTotalMass() * KG2LBS;
for(i=0; i<_thrusters.size(); i++) {
EngRec* er = (EngRec*)_thrusters.get(i);
Thruster* t = er->eng;
+ SGPropertyNode * node = fgGetNode("engines/engine", i, true);
- sprintf(buf, "%s/fuel-flow-gph", er->prefix);
- fgSetFloat(buf, (t->getFuelFlow()/fuelDensity) * 3600 * CM2GALS);
+ // Set: running, cranking, prop-thrust, max-hp, power-pct
+ node->setBoolValue("running", t->isRunning());
+ node->setBoolValue("cranking", t->isCranking());
+
+ 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);
+ node->setFloatValue("oil-temperature-degf",
+ pe->getOilTemp() * K2DEGF + K2DEGFOFFSET);
+ node->setFloatValue("boost-gauge-inhg",
+ pe->getBoost() * (1/INHG2PA));
+ } 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("egt-degf",
+ j->getEGT() * K2DEGF + K2DEGFOFFSET);
+
+ // These are "unmodeled" values that are still needed for
+ // many cockpits. Tie them all to the N1 speed, but
+ // normalize the numbers to the range [0:1] so the
+ // cockpit code can scale them to the right values.
+ float pnorm = j->getPerfNorm();
+ moveprop(node, "oilp-norm", pnorm, dt/3); // 3s seek time
+ moveprop(node, "oilt-norm", pnorm, dt/30); // 30s
+ moveprop(node, "itt-norm", pnorm, dt/1); // 1s
}
}
}
w->setTaper(attrf(a, "taper", 1));
w->setDihedral(attrf(a, "dihedral", defDihed) * DEG2RAD);
w->setCamber(attrf(a, "camber", 0));
- w->setIncidence(attrf(a, "incidence", 0) * DEG2RAD);
- w->setTwist(attrf(a, "twist", 0) * DEG2RAD);
+
+ // These come in with positive indicating positive AoA, but the
+ // internals expect a rotation about the left-pointing Y axis, so
+ // invert the sign.
+ w->setIncidence(attrf(a, "incidence", 0) * DEG2RAD * -1);
+ w->setTwist(attrf(a, "twist", 0) * DEG2RAD * -1);
// The 70% is a magic number that sorta kinda seems to match known
// throttle settings to approach speed.
{
Rotor* w = new Rotor();
- float defDihed = 0;
+ // float defDihed = 0;
float pos[3];
pos[0] = attrf(a, "x");
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);
+
+ 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);
+ eng->setTurboLag(attrf(a, "turbo-lag", 2));
+ }
+
+ if(a->hasAttribute("supercharger"))
+ eng->setSupercharger(attrb(a, "supercharger"));
+
+ ((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);
- }
+ // Set the stops (fine = minimum pitch, coarse = maximum pitch)
+ float fine_stop = attrf(a, "fine-stop", 0.25f);
+ float coarse_stop = attrf(a, "coarse-stop", 4.0f);
+ prop->setStops(fine_stop, coarse_stop);
if(a->hasAttribute("takeoff-power")) {
float power0 = attrf(a, "takeoff-power") * HP2W;
thruster->setVariableProp(min, max);
}
+ if(attrb(a, "contra"))
+ thruster->setContraPair(true);
+
if(a->hasAttribute("manual-pitch")) {
prop->setManualPitch();
}
// 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, "BRAKE")) return ControlMap::BRAKE;
if(eq(name, "STEER")) return ControlMap::STEER;
if(eq(name, "EXTEND")) return ControlMap::EXTEND;
+ if(eq(name, "HEXTEND")) return ControlMap::HEXTEND;
+ if(eq(name, "LEXTEND")) return ControlMap::LEXTEND;
if(eq(name, "INCIDENCE")) return ControlMap::INCIDENCE;
if(eq(name, "FLAP0")) return ControlMap::FLAP0;
if(eq(name, "FLAP1")) return ControlMap::FLAP1;
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;
+ if(eq(name, "WASTEGATE")) return ControlMap::WASTEGATE;
SG_LOG(SG_FLIGHT,SG_ALERT,"Unrecognized control type '"
<< name << "' in YASim aircraft description.");
exit(1);
projects / flightgear.git / blobdiff