#include <Main/fg_props.hxx>
+#include "Math.hpp"
#include "Jet.hpp"
+#include "SimpleJet.hpp"
#include "Gear.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"
#include "FGFDM.hpp"
+
namespace yasim {
// Some conversion factors
static const float RPM2RAD = 0.10471975512;
static const float LBS2N = 4.44822;
static const float LBS2KG = 0.45359237;
+static const float KG2LBS = 2.2046225;
static const float CM2GALS = 264.172037284;
static const float HP2W = 745.700;
static const float INHG2PA = 3386.389;
+static const float K2DEGF = 1.8;
+static const float K2DEGFOFFSET = -459.4;
+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()
{
_nextEngine = 0;
+
+ // Map /controls/flight/elevator to the approach elevator control. 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()
delete[] a->name;
delete a;
}
- for(i=0; i<_pistons.size(); i++) {
- EngRec* er = (EngRec*)_pistons.get(i);
- delete[] er->prefix;
- delete (PropEngine*)er->eng;
- delete er;
- }
- for(i=0; i<_jets.size(); i++) {
- EngRec* er = (EngRec*)_pistons.get(i);
+ for(i=0; i<_thrusters.size(); i++) {
+ EngRec* er = (EngRec*)_thrusters.get(i);
delete[] er->prefix;
- delete (Jet*)er->eng;
+ delete er->eng;
delete er;
}
for(i=0; i<_weights.size(); i++) {
delete[] wr->prop;
delete wr;
}
-
+ for(i=0; i<_controlProps.size(); i++)
+ delete (PropOut*)_controlProps.get(i);
}
void FGFDM::iterate(float dt)
{
getExternalInput(dt);
_airplane.iterate(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();
}
void FGFDM::init()
{
- // We don't want to use these ties (we set the values ourselves,
- // and this works only for the first piston engine anyway).
- fgUntie("/engines/engine[0]/rpm");
- fgUntie("/engines/engine[0]/egt-degf");
- fgUntie("/engines/engine[0]/cht-degf");
- fgUntie("/engines/engine[0]/oil-temperature-degf");
- fgUntie("/engines/engine[0]/mp-osi");
- fgUntie("/engines/engine[0]/fuel-flow-gph");
- fgUntie("/engines/engine[0]/running");
- fgUntie("/engines/engine[0]/cranking");
- fgUntie("/consumables/fuel/tank[0]/level-gal_us");
- fgUntie("/consumables/fuel/tank[1]/level-gal_us");
-
- // Set these to sane values. We don't support engine start yet.
- fgSetBool("/engines/engine[0]/running", true);
- fgSetBool("/engines/engine[0]/cranking", false);
-
// Allows the user to start with something other than full fuel
- _airplane.setFuelFraction(fgGetFloat("/yasim/fuel-fraction", 1));
+ _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-down", true);
+ 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");
v[2] = attrf(a, "z");
_airplane.setPilotPos(v);
+ } else if(eq(name, "rotor")) {
+ _airplane.addRotor(parseRotor(a, name));
} else if(eq(name, "wing")) {
_airplane.setWing(parseWing(a, name));
} else if(eq(name, "hstab")) {
_airplane.setTail(parseWing(a, name));
- } else if(eq(name, "vstab")) {
+ } 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")) {
+ SimpleJet* j = new SimpleJet();
+ _currObj = j;
+ v[0] = attrf(a, "x"); v[1] = attrf(a, "y"); v[2] = attrf(a, "z");
+ j->setPosition(v);
+ _airplane.addThruster(j, 0, v);
+ v[0] = attrf(a, "vx"); v[1] = attrf(a, "vy"); v[2] = attrf(a, "vz");
+ j->setDirection(v);
+ j->setThrust(attrf(a, "thrust") * LBS2N);
} else if(eq(name, "jet")) {
Jet* j = new Jet();
_currObj = j;
v[1] = attrf(a, "y");
v[2] = attrf(a, "z");
float mass = attrf(a, "mass") * LBS2KG;
- j->setDryThrust(attrf(a, "thrust") * LBS2N);
- j->setReheatThrust(attrf(a, "afterburner", 0) * LBS2N);
+ 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);
+ float n2min = attrf(a, "n2-idle", 73);
+ float n2max = attrf(a, "n2-max", 103);
+ j->setRPMs(n1min, n1max, n2min, n2max);
+
+ j->setTSFC(attrf(a, "tsfc", 0.8));
+ if(a->hasAttribute("egt")) j->setEGT(attrf(a, "egt"));
+ if(a->hasAttribute("epr")) j->setEPR(attrf(a, "epr"));
+ if(a->hasAttribute("exhaust-speed"))
+ j->setVMax(attrf(a, "exhaust-speed") * KTS2MPS);
+
j->setPosition(v);
_airplane.addThruster(j, mass, v);
sprintf(buf, "/engines/engine[%d]", _nextEngine++);
EngRec* er = new EngRec();
er->eng = j;
er->prefix = dup(buf);
- _jets.add(er);
+ _thrusters.add(er);
} else if(eq(name, "gear")) {
Gear* g = new Gear();
_currObj = g;
v[1] = 0;
v[2] = attrf(a, "compression", 1);
g->setCompression(v);
+ g->setBrake(attrf(a, "skid", 0));
g->setStaticFriction(attrf(a, "sfric", 0.8));
g->setDynamicFriction(attrf(a, "dfric", 0.7));
- float transitionTime = attrf(a, "retract-time", 0);
- _airplane.addGear(g, transitionTime);
+ g->setSpring(attrf(a, "spring", 1));
+ g->setDamping(attrf(a, "damp", 1));
+ _airplane.addGear(g);
} else if(eq(name, "fuselage")) {
float b[3];
v[0] = attrf(a, "ax");
b[0] = attrf(a, "bx");
b[1] = attrf(a, "by");
b[2] = attrf(a, "bz");
- _airplane.addFuselage(v, b, attrf(a, "width"));
+ float taper = attrf(a, "taper", 1);
+ float mid = attrf(a, "midpoint", 0.5);
+ _airplane.addFuselage(v, b, attrf(a, "width"), taper, mid);
} else if(eq(name, "tank")) {
v[0] = attrf(a, "x");
v[1] = attrf(a, "y");
v[2] = attrf(a, "z");
float density = 6.0; // gasoline, in lbs/gal
if(a->hasAttribute("jet")) density = 6.72;
- density *= LBS2KG/CM2GALS;
+ density *= LBS2KG*CM2GALS;
_airplane.addTank(v, attrf(a, "capacity") * LBS2KG, density);
} else if(eq(name, "ballast")) {
v[0] = attrf(a, "x");
} else if(eq(name, "spoiler")) {
((Wing*)_currObj)->setSpoiler(attrf(a, "start"), attrf(a, "end"),
attrf(a, "lift"), attrf(a, "drag"));
+ /* } else if(eq(name, "collective")) {
+ ((Rotor*)_currObj)->setcollective(attrf(a, "min"), attrf(a, "max"));
+ } else if(eq(name, "cyclic")) {
+ ((Rotor*)_currObj)->setcyclic(attrf(a, "ail"), attrf(a, "ele"));
+ */
} else if(eq(name, "actionpt")) {
v[0] = attrf(a, "x");
v[1] = attrf(a, "y");
v[1] = attrf(a, "y");
v[2] = attrf(a, "z");
((Thruster*)_currObj)->setDirection(v);
- } else if(eq(name, "control")) {
+ } else if(eq(name, "control-setting")) {
+ // A cruise or approach control setting
const char* axis = a->getValue("axis");
- if(a->hasAttribute("output")) {
- // assert: output type must match _currObj type!
- const char* output = a->getValue("output");
- int opt = 0;
- opt |= a->hasAttribute("split") ? ControlMap::OPT_SPLIT : 0;
- opt |= a->hasAttribute("invert") ? ControlMap::OPT_INVERT : 0;
- opt |= a->hasAttribute("square") ? ControlMap::OPT_SQUARE : 0;
- _airplane.getControlMap()->addMapping(parseAxis(axis),
- parseOutput(output),
- _currObj,
- opt);
+ float value = attrf(a, "value", 0);
+ if(_cruiseCurr)
+ _airplane.addCruiseControl(parseAxis(axis), value);
+ else
+ _airplane.addApproachControl(parseAxis(axis), value);
+ } else if(eq(name, "control-input")) {
+
+ // A mapping of input property to a control
+ int axis = parseAxis(a->getValue("axis"));
+ int control = parseOutput(a->getValue("control"));
+ int opt = 0;
+ opt |= a->hasAttribute("split") ? ControlMap::OPT_SPLIT : 0;
+ opt |= a->hasAttribute("invert") ? ControlMap::OPT_INVERT : 0;
+ opt |= a->hasAttribute("square") ? ControlMap::OPT_SQUARE : 0;
+
+ ControlMap* cm = _airplane.getControlMap();
+ if(a->hasAttribute("src0")) {
+ cm->addMapping(axis, control, _currObj, opt,
+ attrf(a, "src0"), attrf(a, "src1"),
+ attrf(a, "dst0"), attrf(a, "dst1"));
} else {
- // assert: must be under a "cruise" or "approach" tag
- float value = attrf(a, "value", 0);
- if(_cruiseCurr)
- _airplane.addCruiseControl(parseAxis(axis), value);
- else
- _airplane.addApproachControl(parseAxis(axis), value);
+ cm->addMapping(axis, control, _currObj, opt);
}
+ } else if(eq(name, "control-output")) {
+ // A property output for a control on the current object
+ ControlMap* cm = _airplane.getControlMap();
+ int type = parseOutput(a->getValue("control"));
+ int handle = cm->getOutputHandle(_currObj, type);
+
+ PropOut* p = new PropOut();
+ p->prop = fgGetNode(a->getValue("prop"), true);
+ p->handle = handle;
+ p->type = type;
+ p->left = !(a->hasAttribute("side") &&
+ eq("right", a->getValue("side")));
+ p->min = attrf(a, "min", cm->rangeMin(type));
+ p->max = attrf(a, "max", cm->rangeMax(type));
+ _controlProps.add(p);
+
+ } else if(eq(name, "control-speed")) {
+ ControlMap* cm = _airplane.getControlMap();
+ int type = parseOutput(a->getValue("control"));
+ int handle = cm->getOutputHandle(_currObj, type);
+ float time = attrf(a, "transition-time", 0);
+
+ cm->setTransitionTime(handle, time);
} else {
- *(int*)0=0; // unexpected tag, boom
+ SG_LOG(SG_FLIGHT,SG_ALERT,"Unexpected tag '"
+ << name << "' found in YASim aircraft description");
+ exit(1);
}
}
void FGFDM::getExternalInput(float dt)
{
+ 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();
float val = fgGetFloat(a->name, 0);
cm->setInput(a->handle, val);
}
- cm->applyControls();
+ cm->applyControls(dt);
// Weights
for(i=0; i<_weights.size(); i++) {
WeightRec* wr = (WeightRec*)_weights.get(i);
- _airplane.setWeight(wr->handle, fgGetFloat(wr->prop));
+ _airplane.setWeight(wr->handle, LBS2KG * fgGetFloat(wr->prop));
}
- // Gear state
- _airplane.setGearState(fgGetBool("/controls/gear-down"), dt);
+ for(i=0; i<_thrusters.size(); i++) {
+ EngRec* er = (EngRec*)_thrusters.get(i);
+ Thruster* t = er->eng;
+
+ if(t->getPropEngine()) {
+ PropEngine* p = t->getPropEngine();
+ sprintf(buf, "%s/rpm", er->prefix);
+ p->setOmega(fgGetFloat(buf, 500) * RPM2RAD);
+ }
+ }
}
void FGFDM::setOutputProperties()
{
- char buf[256];
+ // char buf[256];
int i;
- for(i=0; i<_airplane.numTanks(); i++) {
- sprintf(buf, "/consumables/fuel/tank[%d]/level-gal_us", i);
- fgSetFloat(buf,
- CM2GALS*_airplane.getFuel(i)/_airplane.getFuelDensity(i));
- }
- for(i=0; i<_pistons.size(); i++) {
- EngRec* er = (EngRec*)_pistons.get(i);
- PropEngine* p = (PropEngine*)er->eng;
+ float grossWgt = _airplane.getModel()->getBody()->getTotalMass() * KG2LBS;
+ fgSetFloat("/yasim/gross-weight-lbs", grossWgt);
- sprintf(buf, "%s/rpm", er->prefix);
- fgSetFloat(buf, p->getOmega() / RPM2RAD);
+ ControlMap* cm = _airplane.getControlMap();
+ for(i=0; i<_controlProps.size(); i++) {
+ PropOut* p = (PropOut*)_controlProps.get(i);
+ float val = (p->left
+ ? cm->getOutput(p->handle)
+ : cm->getOutputR(p->handle));
+ float rmin = cm->rangeMin(p->type);
+ float rmax = cm->rangeMax(p->type);
+ float frac = (val - rmin) / (rmax - rmin);
+ val = frac*(p->max - p->min) + p->min;
+ p->prop->setFloatValue(val);
+ }
- sprintf(buf, "%s/fuel-flow-gph", er->prefix);
- fgSetFloat(buf, p->getFuelFlow() * (3600*2.2/5)); // FIXME, wrong
+ for(i=0; i<_airplane.getNumRotors(); i++) {
+ Rotor*r=(Rotor*)_airplane.getRotor(i);
+ int j = 0;
+ float f;
+ char b[256];
+ while(j = r->getValueforFGSet(j, b, &f))
+ if(b[0]) fgSetFloat(b,f);
+
+ 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));
+ }
+ }
+ 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(i=0; i<_jets.size(); i++) {
- EngRec* er = (EngRec*)_jets.get(i);
- Jet* j = (Jet*)er->eng;
-
- sprintf(buf, "%s/fuel-flow-gph", er->prefix);
- fgSetFloat(buf, j->getFuelFlow() * (3600*2.2/6)); // FIXME, wrong
+ 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());
+
+ 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();
+ 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();
+ node->setFloatValue("n1", j->getN1());
+ node->setFloatValue("n2", j->getN2());
+ node->setFloatValue("epr", j->getEPR());
+ node->setFloatValue("egr-degf",
+ j->getEGT() * K2DEGF + K2DEGFOFFSET);
+ }
}
}
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);
+
+ // The 70% is a magic number that sorta kinda seems to match known
+ // throttle settings to approach speed.
+ w->setInducedDrag(0.7*attrf(a, "idrag", 1));
float effect = attrf(a, "effectiveness", 1);
w->setDragScale(w->getDragScale()*effect);
return w;
}
+Rotor* FGFDM::parseRotor(XMLAttributes* a, const char* type)
+{
+ Rotor* w = new Rotor();
+
+ // float defDihed = 0;
+
+ float pos[3];
+ pos[0] = attrf(a, "x");
+ pos[1] = attrf(a, "y");
+ pos[2] = attrf(a, "z");
+ w->setBase(pos);
+
+ float normal[3];
+ normal[0] = attrf(a, "nx");
+ normal[1] = attrf(a, "ny");
+ normal[2] = attrf(a, "nz");
+ w->setNormal(normal);
+
+ float forward[3];
+ forward[0] = attrf(a, "fx");
+ forward[1] = attrf(a, "fy");
+ 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));
+ w->setMinCyclicele(attrf(a, "mincyclicele", -4.94));
+ w->setMaxCollective(attrf(a, "maxcollective", 15.8));
+ w->setMinCollective(attrf(a, "mincollective", -0.2));
+ w->setDiameter(attrf(a, "diameter", 10.2));
+ w->setWeightPerBlade(attrf(a, "weightperblade", 44));
+ w->setNumberOfBlades(attrf(a, "numblades", 4));
+ w->setRelBladeCenter(attrf(a, "relbladecenter", 0.7));
+ w->setDynamic(attrf(a, "dynamic", 0.7));
+ w->setDelta3(attrf(a, "delta3", 0));
+ w->setDelta(attrf(a, "delta", 0));
+ w->setTranslift(attrf(a, "translift", 0.05));
+ w->setC2(attrf(a, "dragfactor", 1));
+ w->setStepspersecond(attrf(a, "stepspersecond", 120));
+ w->setRPM(attrf(a, "rpm", 424));
+ w->setRelLenHinge(attrf(a, "rellenflaphinge", 0.07));
+ w->setAlpha0((attrf(a, "flap0", -5))*YASIM_PI/180);
+ w->setAlphamin((attrf(a, "flapmin", -15))/180*YASIM_PI);
+ w->setAlphamax((attrf(a, "flapmax", 15))*YASIM_PI/180);
+ w->setAlpha0factor(attrf(a, "flap0factor", 1));
+ w->setTeeterdamp(attrf(a,"teeterdamp",.0001));
+ w->setMaxteeterdamp(attrf(a,"maxteeterdamp",1000));
+ w->setRelLenTeeterHinge(attrf(a,"rellenteeterhinge",0.01));
+ void setAlphamin(float f);
+ void setAlphamax(float f);
+ void setAlpha0factor(float f);
+
+ if(attrb(a,"ccw"))
+ w->setCcw(1);
+
+ if(a->hasAttribute("name"))
+ w->setName(a->getValue("name") );
+ if(a->hasAttribute("alphaout0"))
+ w->setAlphaoutput(0,a->getValue("alphaout0") );
+ if(a->hasAttribute("alphaout1")) w->setAlphaoutput(1,a->getValue("alphaout1") );
+ if(a->hasAttribute("alphaout2")) w->setAlphaoutput(2,a->getValue("alphaout2") );
+ if(a->hasAttribute("alphaout3")) w->setAlphaoutput(3,a->getValue("alphaout3") );
+ if(a->hasAttribute("coneout")) w->setAlphaoutput(4,a->getValue("coneout") );
+ if(a->hasAttribute("yawout")) w->setAlphaoutput(5,a->getValue("yawout") );
+ if(a->hasAttribute("rollout")) w->setAlphaoutput(6,a->getValue("rollout") );
+
+ w->setPitchA(attrf(a, "pitch_a", 10));
+ w->setPitchB(attrf(a, "pitch_b", 10));
+ w->setForceAtPitchA(attrf(a, "forceatpitch_a", 3000));
+ w->setPowerAtPitch0(attrf(a, "poweratpitch_0", 300));
+ w->setPowerAtPitchB(attrf(a, "poweratpitch_b", 3000));
+ if(attrb(a,"notorque"))
+ w->setNotorque(1);
+ 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);
+
+ 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("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;
thruster->setVariableProp(min, max);
}
+ if(a->hasAttribute("manual-pitch")) {
+ prop->setManualPitch();
+ }
+
+ thruster->setGearRatio(attrf(a, "gear-ratio", 1));
+
char buf[64];
sprintf(buf, "/engines/engine[%d]", _nextEngine++);
EngRec* er = new EngRec();
er->eng = thruster;
er->prefix = dup(buf);
- _pistons.add(er);
+ _thrusters.add(er);
_currObj = thruster;
}
// 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, "REHEAT")) return ControlMap::REHEAT;
+ if(eq(name, "BOOST")) return ControlMap::BOOST;
+ if(eq(name, "VECTOR")) return ControlMap::VECTOR;
if(eq(name, "PROP")) return ControlMap::PROP;
if(eq(name, "BRAKE")) return ControlMap::BRAKE;
if(eq(name, "STEER")) return ControlMap::STEER;
if(eq(name, "FLAP1")) return ControlMap::FLAP1;
if(eq(name, "SLAT")) return ControlMap::SLAT;
if(eq(name, "SPOILER")) return ControlMap::SPOILER;
- // error here...
- return -1;
+ 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);
+
}
void FGFDM::parseWeight(XMLAttributes* a)
bool FGFDM::eq(const char* a, const char* b)
{
// Figure it out for yourself. :)
- while(*a && *b && *a++ == *b++);
+ while(*a && *b && *a == *b) { a++; b++; }
return !(*a || *b);
}
int FGFDM::attri(XMLAttributes* atts, char* attr)
{
- if(!atts->hasAttribute(attr)) *(int*)0=0; // boom
+ if(!atts->hasAttribute(attr)) {
+ SG_LOG(SG_FLIGHT,SG_ALERT,"Missing '" << attr <<
+ "' in YASim aircraft description");
+ exit(1);
+ }
return attri(atts, attr, 0);
}
float FGFDM::attrf(XMLAttributes* atts, char* attr)
{
- if(!atts->hasAttribute(attr)) *(int*)0=0; // boom
+ if(!atts->hasAttribute(attr)) {
+ SG_LOG(SG_FLIGHT,SG_ALERT,"Missing '" << attr <<
+ "' in YASim aircraft description");
+ exit(1);
+ }
return attrf(atts, attr, 0);
}
else return (float)atof(val);
}
+// 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;
+
+ 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