4 #include <Main/fg_props.hxx>
7 #include "SimpleJet.hpp"
9 #include "Atmosphere.hpp"
10 #include "PropEngine.hpp"
11 #include "Propeller.hpp"
12 #include "PistonEngine.hpp"
14 #include "Rotorpart.hpp"
15 #include "Rotorblade.hpp"
21 // Some conversion factors
22 static const float KTS2MPS = 0.514444444444;
23 static const float FT2M = 0.3048;
24 static const float DEG2RAD = 0.0174532925199;
25 static const float RPM2RAD = 0.10471975512;
26 static const float LBS2N = 4.44822;
27 static const float LBS2KG = 0.45359237;
28 static const float KG2LBS = 2.2046225;
29 static const float CM2GALS = 264.172037284;
30 static const float HP2W = 745.700;
31 static const float INHG2PA = 3386.389;
32 static const float K2DEGF = 1.8;
33 static const float K2DEGFOFFSET = -459.4;
34 static const float CIN2CM = 1.6387064e-5;
35 static const float YASIM_PI = 3.14159265358979323846;
37 // Stubs, so that this can be compiled without the FlightGear
38 // binary. What's the best way to handle this?
40 // float fgGetFloat(char* name, float def) { return 0; }
41 // void fgSetFloat(char* name, float val) {}
47 // Map /controls/flight/elevator to the approach elevator control. This
48 // should probably be settable, but there are very few aircraft
49 // who trim their approaches using things other than elevator.
50 _airplane.setElevatorControl(parseAxis("/controls/flight/elevator-trim"));
52 // FIXME: read seed from somewhere?
54 _turb = new Turbulence(10, seed);
60 for(i=0; i<_axes.size(); i++) {
61 AxisRec* a = (AxisRec*)_axes.get(i);
65 for(i=0; i<_thrusters.size(); i++) {
66 EngRec* er = (EngRec*)_thrusters.get(i);
71 for(i=0; i<_weights.size(); i++) {
72 WeightRec* wr = (WeightRec*)_weights.get(i);
76 for(i=0; i<_controlProps.size(); i++)
77 delete (PropOut*)_controlProps.get(i);
80 void FGFDM::iterate(float dt)
83 _airplane.iterate(dt);
85 if(fgGetBool("/sim/freeze/fuel") != true)
86 _airplane.consumeFuel(dt);
88 setOutputProperties();
91 Airplane* FGFDM::getAirplane()
98 // Allows the user to start with something other than full fuel
99 _airplane.setFuelFraction(fgGetFloat("/sim/fuel-fraction", 1));
101 // This has a nasty habit of being false at startup. That's not
103 fgSetBool("/controls/gear/gear-down", true);
105 _airplane.getModel()->setTurbulence(_turb);
108 // Not the worlds safest parser. But it's short & sweet.
109 void FGFDM::startElement(const char* name, const XMLAttributes &atts)
111 XMLAttributes* a = (XMLAttributes*)&atts;
115 if(eq(name, "airplane")) {
116 _airplane.setWeight(attrf(a, "mass") * LBS2KG);
117 } else if(eq(name, "approach")) {
118 float spd = attrf(a, "speed") * KTS2MPS;
119 float alt = attrf(a, "alt", 0) * FT2M;
120 float aoa = attrf(a, "aoa", 0) * DEG2RAD;
121 _airplane.setApproach(spd, alt, aoa, attrf(a, "fuel", 0.2));
123 } else if(eq(name, "cruise")) {
124 float spd = attrf(a, "speed") * KTS2MPS;
125 float alt = attrf(a, "alt") * FT2M;
126 _airplane.setCruise(spd, alt, attrf(a, "fuel", 0.5));
128 } else if(eq(name, "solve-weight")) {
129 int idx = attri(a, "idx");
130 float wgt = attrf(a, "weight") * LBS2KG;
131 _airplane.addSolutionWeight(!_cruiseCurr, idx, wgt);
132 } else if(eq(name, "cockpit")) {
133 v[0] = attrf(a, "x");
134 v[1] = attrf(a, "y");
135 v[2] = attrf(a, "z");
136 _airplane.setPilotPos(v);
137 } else if(eq(name, "rotor")) {
138 _airplane.addRotor(parseRotor(a, name));
139 } else if(eq(name, "wing")) {
140 _airplane.setWing(parseWing(a, name));
141 } else if(eq(name, "hstab")) {
142 _airplane.setTail(parseWing(a, name));
143 } else if(eq(name, "vstab") || eq(name, "mstab")) {
144 _airplane.addVStab(parseWing(a, name));
145 } else if(eq(name, "propeller")) {
147 } else if(eq(name, "thruster")) {
148 SimpleJet* j = new SimpleJet();
150 v[0] = attrf(a, "x"); v[1] = attrf(a, "y"); v[2] = attrf(a, "z");
152 _airplane.addThruster(j, 0, v);
153 v[0] = attrf(a, "vx"); v[1] = attrf(a, "vy"); v[2] = attrf(a, "vz");
155 j->setThrust(attrf(a, "thrust") * LBS2N);
156 } else if(eq(name, "jet")) {
159 v[0] = attrf(a, "x");
160 v[1] = attrf(a, "y");
161 v[2] = attrf(a, "z");
162 float mass = attrf(a, "mass") * LBS2KG;
163 j->setMaxThrust(attrf(a, "thrust") * LBS2N,
164 attrf(a, "afterburner", 0) * LBS2N);
165 j->setVectorAngle(attrf(a, "rotate", 0) * DEG2RAD);
166 j->setReverseThrust(attrf(a, "reverse", 0.2));
168 float n1min = attrf(a, "n1-idle", 55);
169 float n1max = attrf(a, "n1-max", 102);
170 float n2min = attrf(a, "n2-idle", 73);
171 float n2max = attrf(a, "n2-max", 103);
172 j->setRPMs(n1min, n1max, n2min, n2max);
174 j->setTSFC(attrf(a, "tsfc", 0.8));
175 if(a->hasAttribute("egt")) j->setEGT(attrf(a, "egt"));
176 if(a->hasAttribute("epr")) j->setEPR(attrf(a, "epr"));
177 if(a->hasAttribute("exhaust-speed"))
178 j->setVMax(attrf(a, "exhaust-speed") * KTS2MPS);
181 _airplane.addThruster(j, mass, v);
182 sprintf(buf, "/engines/engine[%d]", _nextEngine++);
183 EngRec* er = new EngRec();
185 er->prefix = dup(buf);
187 } else if(eq(name, "gear")) {
188 Gear* g = new Gear();
190 v[0] = attrf(a, "x");
191 v[1] = attrf(a, "y");
192 v[2] = attrf(a, "z");
196 v[2] = attrf(a, "compression", 1);
197 g->setCompression(v);
198 g->setBrake(attrf(a, "skid", 0));
199 g->setStaticFriction(attrf(a, "sfric", 0.8));
200 g->setDynamicFriction(attrf(a, "dfric", 0.7));
201 g->setSpring(attrf(a, "spring", 1));
202 g->setDamping(attrf(a, "damp", 1));
203 _airplane.addGear(g);
204 } else if(eq(name, "fuselage")) {
206 v[0] = attrf(a, "ax");
207 v[1] = attrf(a, "ay");
208 v[2] = attrf(a, "az");
209 b[0] = attrf(a, "bx");
210 b[1] = attrf(a, "by");
211 b[2] = attrf(a, "bz");
212 float taper = attrf(a, "taper", 1);
213 float mid = attrf(a, "midpoint", 0.5);
214 _airplane.addFuselage(v, b, attrf(a, "width"), taper, mid);
215 } else if(eq(name, "tank")) {
216 v[0] = attrf(a, "x");
217 v[1] = attrf(a, "y");
218 v[2] = attrf(a, "z");
219 float density = 6.0; // gasoline, in lbs/gal
220 if(a->hasAttribute("jet")) density = 6.72;
221 density *= LBS2KG*CM2GALS;
222 _airplane.addTank(v, attrf(a, "capacity") * LBS2KG, density);
223 } else if(eq(name, "ballast")) {
224 v[0] = attrf(a, "x");
225 v[1] = attrf(a, "y");
226 v[2] = attrf(a, "z");
227 _airplane.addBallast(v, attrf(a, "mass") * LBS2KG);
228 } else if(eq(name, "weight")) {
230 } else if(eq(name, "stall")) {
231 Wing* w = (Wing*)_currObj;
232 w->setStall(attrf(a, "aoa") * DEG2RAD);
233 w->setStallWidth(attrf(a, "width", 2) * DEG2RAD);
234 w->setStallPeak(attrf(a, "peak", 1.5));
235 } else if(eq(name, "flap0")) {
236 ((Wing*)_currObj)->setFlap0(attrf(a, "start"), attrf(a, "end"),
237 attrf(a, "lift"), attrf(a, "drag"));
238 } else if(eq(name, "flap1")) {
239 ((Wing*)_currObj)->setFlap1(attrf(a, "start"), attrf(a, "end"),
240 attrf(a, "lift"), attrf(a, "drag"));
241 } else if(eq(name, "slat")) {
242 ((Wing*)_currObj)->setSlat(attrf(a, "start"), attrf(a, "end"),
243 attrf(a, "aoa"), attrf(a, "drag"));
244 } else if(eq(name, "spoiler")) {
245 ((Wing*)_currObj)->setSpoiler(attrf(a, "start"), attrf(a, "end"),
246 attrf(a, "lift"), attrf(a, "drag"));
247 /* } else if(eq(name, "collective")) {
248 ((Rotor*)_currObj)->setcollective(attrf(a, "min"), attrf(a, "max"));
249 } else if(eq(name, "cyclic")) {
250 ((Rotor*)_currObj)->setcyclic(attrf(a, "ail"), attrf(a, "ele"));
252 } else if(eq(name, "actionpt")) {
253 v[0] = attrf(a, "x");
254 v[1] = attrf(a, "y");
255 v[2] = attrf(a, "z");
256 ((Thruster*)_currObj)->setPosition(v);
257 } else if(eq(name, "dir")) {
258 v[0] = attrf(a, "x");
259 v[1] = attrf(a, "y");
260 v[2] = attrf(a, "z");
261 ((Thruster*)_currObj)->setDirection(v);
262 } else if(eq(name, "control-setting")) {
263 // A cruise or approach control setting
264 const char* axis = a->getValue("axis");
265 float value = attrf(a, "value", 0);
267 _airplane.addCruiseControl(parseAxis(axis), value);
269 _airplane.addApproachControl(parseAxis(axis), value);
270 } else if(eq(name, "control-input")) {
272 // A mapping of input property to a control
273 int axis = parseAxis(a->getValue("axis"));
274 int control = parseOutput(a->getValue("control"));
276 opt |= a->hasAttribute("split") ? ControlMap::OPT_SPLIT : 0;
277 opt |= a->hasAttribute("invert") ? ControlMap::OPT_INVERT : 0;
278 opt |= a->hasAttribute("square") ? ControlMap::OPT_SQUARE : 0;
280 ControlMap* cm = _airplane.getControlMap();
281 if(a->hasAttribute("src0")) {
282 cm->addMapping(axis, control, _currObj, opt,
283 attrf(a, "src0"), attrf(a, "src1"),
284 attrf(a, "dst0"), attrf(a, "dst1"));
286 cm->addMapping(axis, control, _currObj, opt);
288 } else if(eq(name, "control-output")) {
289 // A property output for a control on the current object
290 ControlMap* cm = _airplane.getControlMap();
291 int type = parseOutput(a->getValue("control"));
292 int handle = cm->getOutputHandle(_currObj, type);
294 PropOut* p = new PropOut();
295 p->prop = fgGetNode(a->getValue("prop"), true);
298 p->left = !(a->hasAttribute("side") &&
299 eq("right", a->getValue("side")));
300 p->min = attrf(a, "min", cm->rangeMin(type));
301 p->max = attrf(a, "max", cm->rangeMax(type));
302 _controlProps.add(p);
304 } else if(eq(name, "control-speed")) {
305 ControlMap* cm = _airplane.getControlMap();
306 int type = parseOutput(a->getValue("control"));
307 int handle = cm->getOutputHandle(_currObj, type);
308 float time = attrf(a, "transition-time", 0);
310 cm->setTransitionTime(handle, time);
312 SG_LOG(SG_FLIGHT,SG_ALERT,"Unexpected tag '"
313 << name << "' found in YASim aircraft description");
318 void FGFDM::getExternalInput(float dt)
322 _turb->setMagnitude(fgGetFloat("/environment/turbulence/magnitude-norm"));
323 _turb->update(dt, fgGetFloat("/environment/turbulence/rate-hz"));
326 ControlMap* cm = _airplane.getControlMap();
329 for(i=0; i<_axes.size(); i++) {
330 AxisRec* a = (AxisRec*)_axes.get(i);
331 float val = fgGetFloat(a->name, 0);
332 cm->setInput(a->handle, val);
334 cm->applyControls(dt);
337 for(i=0; i<_weights.size(); i++) {
338 WeightRec* wr = (WeightRec*)_weights.get(i);
339 _airplane.setWeight(wr->handle, LBS2KG * fgGetFloat(wr->prop));
342 for(i=0; i<_thrusters.size(); i++) {
343 EngRec* er = (EngRec*)_thrusters.get(i);
344 Thruster* t = er->eng;
346 if(t->getPropEngine()) {
347 PropEngine* p = t->getPropEngine();
348 sprintf(buf, "%s/rpm", er->prefix);
349 p->setOmega(fgGetFloat(buf, 500) * RPM2RAD);
354 void FGFDM::setOutputProperties()
359 float grossWgt = _airplane.getModel()->getBody()->getTotalMass() * KG2LBS;
360 fgSetFloat("/yasim/gross-weight-lbs", grossWgt);
362 ControlMap* cm = _airplane.getControlMap();
363 for(i=0; i<_controlProps.size(); i++) {
364 PropOut* p = (PropOut*)_controlProps.get(i);
366 ? cm->getOutput(p->handle)
367 : cm->getOutputR(p->handle));
368 float rmin = cm->rangeMin(p->type);
369 float rmax = cm->rangeMax(p->type);
370 float frac = (val - rmin) / (rmax - rmin);
371 val = frac*(p->max - p->min) + p->min;
372 p->prop->setFloatValue(val);
375 float totalFuel = 0, totalCap = 0;
376 float fuelDensity = 720; // in kg/m^3, default to gasoline: ~6 lb/gal
377 for(i=0; i<_airplane.numTanks(); i++) {
378 fuelDensity = _airplane.getFuelDensity(i);
379 sprintf(buf, "/consumables/fuel/tank[%d]/level-gal_us", i);
380 fgSetFloat(buf, CM2GALS*_airplane.getFuel(i)/fuelDensity);
381 sprintf(buf, "/consumables/fuel/tank[%d]/level-lbs", i);
382 fgSetFloat(buf, KG2LBS*_airplane.getFuel(i));
383 totalFuel += _airplane.getFuel(i);
384 totalCap += _airplane.getTankCapacity(i);
387 fgSetFloat("/consumables/fuel/total-fuel-lbs", KG2LBS*totalFuel);
388 fgSetFloat("/consumables/fuel/total-fuel-gals",
389 CM2GALS*totalFuel/fuelDensity);
390 fgSetFloat("/consumables/fuel/total-fuel-norm", totalFuel/totalCap);
393 for(i=0; i<_airplane.getNumRotors(); i++) {
394 Rotor*r=(Rotor*)_airplane.getRotor(i);
398 while(j = r->getValueforFGSet(j, b, &f))
399 if(b[0]) fgSetFloat(b,f);
401 for(j=0; j < r->numRotorparts(); j++) {
402 Rotorpart* s = (Rotorpart*)r->getRotorpart(j);
406 b=s->getAlphaoutput(k);
407 if(b[0]) fgSetFloat(b, s->getAlpha(k));
410 for(j=0; j < r->numRotorblades(); j++) {
411 Rotorblade* s = (Rotorblade*)r->getRotorblade(j);
414 for (k=0; k<2; k++) {
415 b = s->getAlphaoutput(k);
416 if(b[0]) fgSetFloat(b, s->getAlpha(k));
421 for(i=0; i<_thrusters.size(); i++) {
422 EngRec* er = (EngRec*)_thrusters.get(i);
423 Thruster* t = er->eng;
425 sprintf(buf, "%s/fuel-flow-gph", er->prefix);
426 fgSetFloat(buf, (t->getFuelFlow()/fuelDensity) * 3600 * CM2GALS);
428 if(t->getPropEngine()) {
429 PropEngine* p = t->getPropEngine();
431 sprintf(buf, "%s/rpm", er->prefix);
432 fgSetFloat(buf, p->getOmega() / RPM2RAD);
435 if(t->getPistonEngine()) {
436 PistonEngine* p = t->getPistonEngine();
438 sprintf(buf, "%s/mp-osi", er->prefix);
439 fgSetFloat(buf, p->getMP() * (1/INHG2PA));
441 sprintf(buf, "%s/egt-degf", er->prefix);
442 fgSetFloat(buf, p->getEGT() * K2DEGF + K2DEGFOFFSET);
446 Jet* j = t->getJet();
448 sprintf(buf, "%s/n1", er->prefix);
449 fgSetFloat(buf, j->getN1());
451 sprintf(buf, "%s/n2", er->prefix);
452 fgSetFloat(buf, j->getN2());
454 sprintf(buf, "%s/epr", er->prefix);
455 fgSetFloat(buf, j->getEPR());
457 sprintf(buf, "%s/egt-degf", er->prefix);
458 fgSetFloat(buf, j->getEGT() * K2DEGF + K2DEGFOFFSET);
463 Wing* FGFDM::parseWing(XMLAttributes* a, const char* type)
465 Wing* w = new Wing();
468 if(eq(type, "vstab"))
474 pos[0] = attrf(a, "x");
475 pos[1] = attrf(a, "y");
476 pos[2] = attrf(a, "z");
479 w->setLength(attrf(a, "length"));
480 w->setChord(attrf(a, "chord"));
481 w->setSweep(attrf(a, "sweep", 0) * DEG2RAD);
482 w->setTaper(attrf(a, "taper", 1));
483 w->setDihedral(attrf(a, "dihedral", defDihed) * DEG2RAD);
484 w->setCamber(attrf(a, "camber", 0));
485 w->setIncidence(attrf(a, "incidence", 0) * DEG2RAD);
486 w->setTwist(attrf(a, "twist", 0) * DEG2RAD);
488 // The 70% is a magic number that sorta kinda seems to match known
489 // throttle settings to approach speed.
490 w->setInducedDrag(0.7*attrf(a, "idrag", 1));
492 float effect = attrf(a, "effectiveness", 1);
493 w->setDragScale(w->getDragScale()*effect);
499 Rotor* FGFDM::parseRotor(XMLAttributes* a, const char* type)
501 Rotor* w = new Rotor();
506 pos[0] = attrf(a, "x");
507 pos[1] = attrf(a, "y");
508 pos[2] = attrf(a, "z");
512 normal[0] = attrf(a, "nx");
513 normal[1] = attrf(a, "ny");
514 normal[2] = attrf(a, "nz");
515 w->setNormal(normal);
518 forward[0] = attrf(a, "fx");
519 forward[1] = attrf(a, "fy");
520 forward[2] = attrf(a, "fz");
521 w->setForward(forward);
523 w->setMaxCyclicail(attrf(a, "maxcyclicail", 7.6));
524 w->setMaxCyclicele(attrf(a, "maxcyclicele", 4.94));
525 w->setMinCyclicail(attrf(a, "mincyclicail", -7.6));
526 w->setMinCyclicele(attrf(a, "mincyclicele", -4.94));
527 w->setMaxCollective(attrf(a, "maxcollective", 15.8));
528 w->setMinCollective(attrf(a, "mincollective", -0.2));
529 w->setDiameter(attrf(a, "diameter", 10.2));
530 w->setWeightPerBlade(attrf(a, "weightperblade", 44));
531 w->setNumberOfBlades(attrf(a, "numblades", 4));
532 w->setRelBladeCenter(attrf(a, "relbladecenter", 0.7));
533 w->setDynamic(attrf(a, "dynamic", 0.7));
534 w->setDelta3(attrf(a, "delta3", 0));
535 w->setDelta(attrf(a, "delta", 0));
536 w->setTranslift(attrf(a, "translift", 0.05));
537 w->setC2(attrf(a, "dragfactor", 1));
538 w->setStepspersecond(attrf(a, "stepspersecond", 120));
539 w->setRPM(attrf(a, "rpm", 424));
540 w->setRelLenHinge(attrf(a, "rellenflaphinge", 0.07));
541 w->setAlpha0((attrf(a, "flap0", -5))*YASIM_PI/180);
542 w->setAlphamin((attrf(a, "flapmin", -15))/180*YASIM_PI);
543 w->setAlphamax((attrf(a, "flapmax", 15))*YASIM_PI/180);
544 w->setAlpha0factor(attrf(a, "flap0factor", 1));
545 w->setTeeterdamp(attrf(a,"teeterdamp",.0001));
546 w->setMaxteeterdamp(attrf(a,"maxteeterdamp",1000));
547 w->setRelLenTeeterHinge(attrf(a,"rellenteeterhinge",0.01));
548 void setAlphamin(float f);
549 void setAlphamax(float f);
550 void setAlpha0factor(float f);
555 if(a->hasAttribute("name"))
556 w->setName(a->getValue("name") );
557 if(a->hasAttribute("alphaout0"))
558 w->setAlphaoutput(0,a->getValue("alphaout0") );
559 if(a->hasAttribute("alphaout1")) w->setAlphaoutput(1,a->getValue("alphaout1") );
560 if(a->hasAttribute("alphaout2")) w->setAlphaoutput(2,a->getValue("alphaout2") );
561 if(a->hasAttribute("alphaout3")) w->setAlphaoutput(3,a->getValue("alphaout3") );
562 if(a->hasAttribute("coneout")) w->setAlphaoutput(4,a->getValue("coneout") );
563 if(a->hasAttribute("yawout")) w->setAlphaoutput(5,a->getValue("yawout") );
564 if(a->hasAttribute("rollout")) w->setAlphaoutput(6,a->getValue("rollout") );
566 w->setPitchA(attrf(a, "pitch_a", 10));
567 w->setPitchB(attrf(a, "pitch_b", 10));
568 w->setForceAtPitchA(attrf(a, "forceatpitch_a", 3000));
569 w->setPowerAtPitch0(attrf(a, "poweratpitch_0", 300));
570 w->setPowerAtPitchB(attrf(a, "poweratpitch_b", 3000));
571 if(attrb(a,"notorque"))
573 if(attrb(a,"simblades"))
580 void FGFDM::parsePropeller(XMLAttributes* a)
583 cg[0] = attrf(a, "x");
584 cg[1] = attrf(a, "y");
585 cg[2] = attrf(a, "z");
586 float mass = attrf(a, "mass") * LBS2KG;
587 float moment = attrf(a, "moment");
588 float radius = attrf(a, "radius");
589 float speed = attrf(a, "cruise-speed") * KTS2MPS;
590 float omega = attrf(a, "cruise-rpm") * RPM2RAD;
591 float power = attrf(a, "cruise-power") * HP2W;
592 float rho = Atmosphere::getStdDensity(attrf(a, "cruise-alt") * FT2M);
594 // Hack, fix this pronto:
595 float engP = attrf(a, "eng-power") * HP2W;
596 float engS = attrf(a, "eng-rpm") * RPM2RAD;
598 Propeller* prop = new Propeller(radius, speed, omega, rho, power);
599 PistonEngine* eng = new PistonEngine(engP, engS);
600 PropEngine* thruster = new PropEngine(prop, eng, moment);
601 _airplane.addThruster(thruster, mass, cg);
603 if(a->hasAttribute("displacement"))
604 eng->setDisplacement(attrf(a, "displacement") * CIN2CM);
606 if(a->hasAttribute("compression"))
607 eng->setCompression(attrf(a, "compression"));
609 if(a->hasAttribute("turbo-mul")) {
610 float mul = attrf(a, "turbo-mul");
611 float mp = attrf(a, "wastegate-mp", 1e6) * INHG2PA;
612 eng->setTurboParams(mul, mp);
615 if(a->hasAttribute("takeoff-power")) {
616 float power0 = attrf(a, "takeoff-power") * HP2W;
617 float omega0 = attrf(a, "takeoff-rpm") * RPM2RAD;
618 prop->setTakeoff(omega0, power0);
621 if(a->hasAttribute("max-rpm")) {
622 float max = attrf(a, "max-rpm") * RPM2RAD;
623 float min = attrf(a, "min-rpm") * RPM2RAD;
624 thruster->setVariableProp(min, max);
627 if(a->hasAttribute("manual-pitch")) {
628 prop->setManualPitch();
631 thruster->setGearRatio(attrf(a, "gear-ratio", 1));
634 sprintf(buf, "/engines/engine[%d]", _nextEngine++);
635 EngRec* er = new EngRec();
637 er->prefix = dup(buf);
643 // Turns a string axis name into an integer for use by the
644 // ControlMap. Creates a new axis if this one hasn't been defined
646 int FGFDM::parseAxis(const char* name)
649 for(i=0; i<_axes.size(); i++) {
650 AxisRec* a = (AxisRec*)_axes.get(i);
651 if(eq(a->name, name))
655 // Not there, make a new one.
656 AxisRec* a = new AxisRec();
658 a->handle = _airplane.getControlMap()->newInput();
663 int FGFDM::parseOutput(const char* name)
665 if(eq(name, "THROTTLE")) return ControlMap::THROTTLE;
666 if(eq(name, "MIXTURE")) return ControlMap::MIXTURE;
667 if(eq(name, "STARTER")) return ControlMap::STARTER;
668 if(eq(name, "MAGNETOS")) return ControlMap::MAGNETOS;
669 if(eq(name, "ADVANCE")) return ControlMap::ADVANCE;
670 if(eq(name, "REHEAT")) return ControlMap::REHEAT;
671 if(eq(name, "BOOST")) return ControlMap::BOOST;
672 if(eq(name, "VECTOR")) return ControlMap::VECTOR;
673 if(eq(name, "PROP")) return ControlMap::PROP;
674 if(eq(name, "BRAKE")) return ControlMap::BRAKE;
675 if(eq(name, "STEER")) return ControlMap::STEER;
676 if(eq(name, "EXTEND")) return ControlMap::EXTEND;
677 if(eq(name, "INCIDENCE")) return ControlMap::INCIDENCE;
678 if(eq(name, "FLAP0")) return ControlMap::FLAP0;
679 if(eq(name, "FLAP1")) return ControlMap::FLAP1;
680 if(eq(name, "SLAT")) return ControlMap::SLAT;
681 if(eq(name, "SPOILER")) return ControlMap::SPOILER;
682 if(eq(name, "CASTERING")) return ControlMap::CASTERING;
683 if(eq(name, "PROPPITCH")) return ControlMap::PROPPITCH;
684 if(eq(name, "COLLECTIVE")) return ControlMap::COLLECTIVE;
685 if(eq(name, "CYCLICAIL")) return ControlMap::CYCLICAIL;
686 if(eq(name, "CYCLICELE")) return ControlMap::CYCLICELE;
687 if(eq(name, "ROTORENGINEON")) return ControlMap::ROTORENGINEON;
688 if(eq(name, "REVERSE_THRUST")) return ControlMap::REVERSE_THRUST;
689 SG_LOG(SG_FLIGHT,SG_ALERT,"Unrecognized control type '"
690 << name << "' in YASim aircraft description.");
695 void FGFDM::parseWeight(XMLAttributes* a)
697 WeightRec* wr = new WeightRec();
700 v[0] = attrf(a, "x");
701 v[1] = attrf(a, "y");
702 v[2] = attrf(a, "z");
704 wr->prop = dup(a->getValue("mass-prop"));
705 wr->size = attrf(a, "size", 0);
706 wr->handle = _airplane.addWeight(v, wr->size);
711 bool FGFDM::eq(const char* a, const char* b)
713 // Figure it out for yourself. :)
714 while(*a && *b && *a == *b) { a++; b++; }
718 char* FGFDM::dup(const char* s)
722 char* s2 = new char[len+1];
724 while((*p++ = *s++));
729 int FGFDM::attri(XMLAttributes* atts, char* attr)
731 if(!atts->hasAttribute(attr)) {
732 SG_LOG(SG_FLIGHT,SG_ALERT,"Missing '" << attr <<
733 "' in YASim aircraft description");
736 return attri(atts, attr, 0);
739 int FGFDM::attri(XMLAttributes* atts, char* attr, int def)
741 const char* val = atts->getValue(attr);
742 if(val == 0) return def;
743 else return atol(val);
746 float FGFDM::attrf(XMLAttributes* atts, char* attr)
748 if(!atts->hasAttribute(attr)) {
749 SG_LOG(SG_FLIGHT,SG_ALERT,"Missing '" << attr <<
750 "' in YASim aircraft description");
753 return attrf(atts, attr, 0);
756 float FGFDM::attrf(XMLAttributes* atts, char* attr, float def)
758 const char* val = atts->getValue(attr);
759 if(val == 0) return def;
760 else return (float)atof(val);
763 // ACK: the dreaded ambiguous string boolean. Remind me to shoot Maik
764 // when I have a chance. :). Unless you have a parser that can check
765 // symbol constants (we don't), this kind of coding is just a Bad
766 // Idea. This implementation, for example, silently returns a boolean
767 // falsehood for values of "1", "yes", "True", and "TRUE". Which is
768 // especially annoying preexisting boolean attributes in the same
769 // parser want to see "1" and will choke on a "true"...
771 // Unfortunately, this usage creeped into existing configuration files
772 // while I wasn't active, and it's going to be hard to remove. Issue
773 // a warning to nag people into changing their ways for now...
774 bool FGFDM::attrb(XMLAttributes* atts, char* attr)
776 const char* val = atts->getValue(attr);
777 if(val == 0) return false;
780 SG_LOG(SG_FLIGHT, SG_ALERT, "Warning: " <<
781 "deprecated 'true' boolean in YASim configuration file. " <<
782 "Use numeric booleans (attribute=\"1\") instead");
785 return attri(atts, attr, 0) ? true : false;
788 }; // namespace yasim