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);
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);
128 } else if(eq(name, "cockpit")) {
129 v[0] = attrf(a, "x");
130 v[1] = attrf(a, "y");
131 v[2] = attrf(a, "z");
132 _airplane.setPilotPos(v);
133 } else if(eq(name, "rotor")) {
134 _airplane.addRotor(parseRotor(a, name));
135 } else if(eq(name, "wing")) {
136 _airplane.setWing(parseWing(a, name));
137 } else if(eq(name, "hstab")) {
138 _airplane.setTail(parseWing(a, name));
139 } else if(eq(name, "vstab") || eq(name, "mstab")) {
140 _airplane.addVStab(parseWing(a, name));
141 } else if(eq(name, "propeller")) {
143 } else if(eq(name, "thruster")) {
144 SimpleJet* j = new SimpleJet();
146 v[0] = attrf(a, "x"); v[1] = attrf(a, "y"); v[2] = attrf(a, "z");
148 _airplane.addThruster(j, 0, v);
149 v[0] = attrf(a, "vx"); v[1] = attrf(a, "vy"); v[2] = attrf(a, "vz");
151 j->setThrust(attrf(a, "thrust") * LBS2N);
152 } else if(eq(name, "jet")) {
155 v[0] = attrf(a, "x");
156 v[1] = attrf(a, "y");
157 v[2] = attrf(a, "z");
158 float mass = attrf(a, "mass") * LBS2KG;
159 j->setMaxThrust(attrf(a, "thrust") * LBS2N,
160 attrf(a, "afterburner", 0) * LBS2N);
161 j->setVectorAngle(attrf(a, "rotate", 0) * DEG2RAD);
163 float n1min = attrf(a, "n1-idle", 55);
164 float n1max = attrf(a, "n1-max", 102);
165 float n2min = attrf(a, "n2-idle", 73);
166 float n2max = attrf(a, "n2-max", 103);
167 j->setRPMs(n1min, n1max, n2min, n2max);
169 j->setTSFC(attrf(a, "tsfc", 0.8));
170 if(a->hasAttribute("egt")) j->setEGT(attrf(a, "egt"));
171 if(a->hasAttribute("epr")) j->setEPR(attrf(a, "epr"));
172 if(a->hasAttribute("exhaust-speed"))
173 j->setVMax(attrf(a, "exhaust-speed") * KTS2MPS);
176 _airplane.addThruster(j, mass, v);
177 sprintf(buf, "/engines/engine[%d]", _nextEngine++);
178 EngRec* er = new EngRec();
180 er->prefix = dup(buf);
182 } else if(eq(name, "gear")) {
183 Gear* g = new Gear();
185 v[0] = attrf(a, "x");
186 v[1] = attrf(a, "y");
187 v[2] = attrf(a, "z");
191 v[2] = attrf(a, "compression", 1);
192 g->setCompression(v);
193 g->setBrake(attrf(a, "skid", 0));
194 g->setStaticFriction(attrf(a, "sfric", 0.8));
195 g->setDynamicFriction(attrf(a, "dfric", 0.7));
196 g->setSpring(attrf(a, "spring", 1));
197 g->setDamping(attrf(a, "damp", 1));
198 _airplane.addGear(g);
199 } else if(eq(name, "fuselage")) {
201 v[0] = attrf(a, "ax");
202 v[1] = attrf(a, "ay");
203 v[2] = attrf(a, "az");
204 b[0] = attrf(a, "bx");
205 b[1] = attrf(a, "by");
206 b[2] = attrf(a, "bz");
207 float taper = attrf(a, "taper", 1);
208 float mid = attrf(a, "midpoint", 0.5);
209 _airplane.addFuselage(v, b, attrf(a, "width"), taper, mid);
210 } else if(eq(name, "tank")) {
211 v[0] = attrf(a, "x");
212 v[1] = attrf(a, "y");
213 v[2] = attrf(a, "z");
214 float density = 6.0; // gasoline, in lbs/gal
215 if(a->hasAttribute("jet")) density = 6.72;
216 density *= LBS2KG*CM2GALS;
217 _airplane.addTank(v, attrf(a, "capacity") * LBS2KG, density);
218 } else if(eq(name, "ballast")) {
219 v[0] = attrf(a, "x");
220 v[1] = attrf(a, "y");
221 v[2] = attrf(a, "z");
222 _airplane.addBallast(v, attrf(a, "mass") * LBS2KG);
223 } else if(eq(name, "weight")) {
225 } else if(eq(name, "stall")) {
226 Wing* w = (Wing*)_currObj;
227 w->setStall(attrf(a, "aoa") * DEG2RAD);
228 w->setStallWidth(attrf(a, "width", 2) * DEG2RAD);
229 w->setStallPeak(attrf(a, "peak", 1.5));
230 } else if(eq(name, "flap0")) {
231 ((Wing*)_currObj)->setFlap0(attrf(a, "start"), attrf(a, "end"),
232 attrf(a, "lift"), attrf(a, "drag"));
233 } else if(eq(name, "flap1")) {
234 ((Wing*)_currObj)->setFlap1(attrf(a, "start"), attrf(a, "end"),
235 attrf(a, "lift"), attrf(a, "drag"));
236 } else if(eq(name, "slat")) {
237 ((Wing*)_currObj)->setSlat(attrf(a, "start"), attrf(a, "end"),
238 attrf(a, "aoa"), attrf(a, "drag"));
239 } else if(eq(name, "spoiler")) {
240 ((Wing*)_currObj)->setSpoiler(attrf(a, "start"), attrf(a, "end"),
241 attrf(a, "lift"), attrf(a, "drag"));
242 /* } else if(eq(name, "collective")) {
243 ((Rotor*)_currObj)->setcollective(attrf(a, "min"), attrf(a, "max"));
244 } else if(eq(name, "cyclic")) {
245 ((Rotor*)_currObj)->setcyclic(attrf(a, "ail"), attrf(a, "ele"));
247 } else if(eq(name, "actionpt")) {
248 v[0] = attrf(a, "x");
249 v[1] = attrf(a, "y");
250 v[2] = attrf(a, "z");
251 ((Thruster*)_currObj)->setPosition(v);
252 } else if(eq(name, "dir")) {
253 v[0] = attrf(a, "x");
254 v[1] = attrf(a, "y");
255 v[2] = attrf(a, "z");
256 ((Thruster*)_currObj)->setDirection(v);
257 } else if(eq(name, "control-setting")) {
258 // A cruise or approach control setting
259 const char* axis = a->getValue("axis");
260 float value = attrf(a, "value", 0);
262 _airplane.addCruiseControl(parseAxis(axis), value);
264 _airplane.addApproachControl(parseAxis(axis), value);
265 } else if(eq(name, "control-input")) {
267 // A mapping of input property to a control
268 int axis = parseAxis(a->getValue("axis"));
269 int control = parseOutput(a->getValue("control"));
271 opt |= a->hasAttribute("split") ? ControlMap::OPT_SPLIT : 0;
272 opt |= a->hasAttribute("invert") ? ControlMap::OPT_INVERT : 0;
273 opt |= a->hasAttribute("square") ? ControlMap::OPT_SQUARE : 0;
275 ControlMap* cm = _airplane.getControlMap();
276 if(a->hasAttribute("src0")) {
277 cm->addMapping(axis, control, _currObj, opt,
278 attrf(a, "src0"), attrf(a, "src1"),
279 attrf(a, "dst0"), attrf(a, "dst1"));
281 cm->addMapping(axis, control, _currObj, opt);
283 } else if(eq(name, "control-output")) {
284 // A property output for a control on the current object
285 ControlMap* cm = _airplane.getControlMap();
286 int type = parseOutput(a->getValue("control"));
287 int handle = cm->getOutputHandle(_currObj, type);
289 PropOut* p = new PropOut();
290 p->prop = fgGetNode(a->getValue("prop"), true);
293 p->left = !(a->hasAttribute("side") &&
294 eq("right", a->getValue("side")));
295 p->min = attrf(a, "min", cm->rangeMin(type));
296 p->max = attrf(a, "max", cm->rangeMax(type));
297 _controlProps.add(p);
299 } else if(eq(name, "control-speed")) {
300 ControlMap* cm = _airplane.getControlMap();
301 int type = parseOutput(a->getValue("control"));
302 int handle = cm->getOutputHandle(_currObj, type);
303 float time = attrf(a, "transition-time", 0);
305 cm->setTransitionTime(handle, time);
307 SG_LOG(SG_FLIGHT,SG_ALERT,"Unexpected tag '"
308 << name << "' found in YASim aircraft description");
313 void FGFDM::getExternalInput(float dt)
317 _turb->setMagnitude(fgGetFloat("/environment/turbulence/magnitude-norm"));
318 _turb->update(dt, fgGetFloat("/environment/turbulence/rate-hz"));
321 ControlMap* cm = _airplane.getControlMap();
324 for(i=0; i<_axes.size(); i++) {
325 AxisRec* a = (AxisRec*)_axes.get(i);
326 float val = fgGetFloat(a->name, 0);
327 cm->setInput(a->handle, val);
329 cm->applyControls(dt);
332 for(i=0; i<_weights.size(); i++) {
333 WeightRec* wr = (WeightRec*)_weights.get(i);
334 _airplane.setWeight(wr->handle, LBS2KG * fgGetFloat(wr->prop));
337 for(i=0; i<_thrusters.size(); i++) {
338 EngRec* er = (EngRec*)_thrusters.get(i);
339 Thruster* t = er->eng;
341 if(t->getPropEngine()) {
342 PropEngine* p = t->getPropEngine();
343 sprintf(buf, "%s/rpm", er->prefix);
344 p->setOmega(fgGetFloat(buf) * RPM2RAD);
349 void FGFDM::setOutputProperties()
354 float grossWgt = _airplane.getModel()->getBody()->getTotalMass() * KG2LBS;
355 fgSetFloat("/yasim/gross-weight-lbs", grossWgt);
357 ControlMap* cm = _airplane.getControlMap();
358 for(i=0; i<_controlProps.size(); i++) {
359 PropOut* p = (PropOut*)_controlProps.get(i);
361 ? cm->getOutput(p->handle)
362 : cm->getOutputR(p->handle));
363 float rmin = cm->rangeMin(p->type);
364 float rmax = cm->rangeMax(p->type);
365 float frac = (val - rmin) / (rmax - rmin);
366 val = frac*(p->max - p->min) + p->min;
367 p->prop->setFloatValue(val);
370 float totalFuel = 0, totalCap = 0;
371 float fuelDensity = 720; // in kg/m^3, default to gasoline: ~6 lb/gal
372 for(i=0; i<_airplane.numTanks(); i++) {
373 fuelDensity = _airplane.getFuelDensity(i);
374 sprintf(buf, "/consumables/fuel/tank[%d]/level-gal_us", i);
375 fgSetFloat(buf, CM2GALS*_airplane.getFuel(i)/fuelDensity);
376 sprintf(buf, "/consumables/fuel/tank[%d]/level-lbs", i);
377 fgSetFloat(buf, KG2LBS*_airplane.getFuel(i));
378 totalFuel += _airplane.getFuel(i);
379 totalCap += _airplane.getTankCapacity(i);
382 fgSetFloat("/consumables/fuel/total-fuel-lbs", KG2LBS*totalFuel);
383 fgSetFloat("/consumables/fuel/total-fuel-gals",
384 CM2GALS*totalFuel/fuelDensity);
385 fgSetFloat("/consumables/fuel/total-fuel-norm", totalFuel/totalCap);
388 for(i=0; i<_airplane.getNumRotors(); i++) {
389 Rotor*r=(Rotor*)_airplane.getRotor(i);
393 while(j = r->getValueforFGSet(j, b, &f))
394 if(b[0]) fgSetFloat(b,f);
396 for(j=0; j < r->numRotorparts(); j++) {
397 Rotorpart* s = (Rotorpart*)r->getRotorpart(j);
401 b=s->getAlphaoutput(k);
402 if(b[0]) fgSetFloat(b, s->getAlpha(k));
405 for(j=0; j < r->numRotorblades(); j++) {
406 Rotorblade* s = (Rotorblade*)r->getRotorblade(j);
409 for (k=0; k<2; k++) {
410 b = s->getAlphaoutput(k);
411 if(b[0]) fgSetFloat(b, s->getAlpha(k));
416 for(i=0; i<_thrusters.size(); i++) {
417 EngRec* er = (EngRec*)_thrusters.get(i);
418 Thruster* t = er->eng;
420 sprintf(buf, "%s/fuel-flow-gph", er->prefix);
421 fgSetFloat(buf, (t->getFuelFlow()/fuelDensity) * 3600 * CM2GALS);
423 if(t->getPropEngine()) {
424 PropEngine* p = t->getPropEngine();
426 sprintf(buf, "%s/rpm", er->prefix);
427 fgSetFloat(buf, p->getOmega() / RPM2RAD);
430 if(t->getPistonEngine()) {
431 PistonEngine* p = t->getPistonEngine();
433 sprintf(buf, "%s/mp-osi", er->prefix);
434 fgSetFloat(buf, p->getMP() * (1/INHG2PA));
436 sprintf(buf, "%s/egt-degf", er->prefix);
437 fgSetFloat(buf, p->getEGT() * K2DEGF + K2DEGFOFFSET);
441 Jet* j = t->getJet();
443 sprintf(buf, "%s/n1", er->prefix);
444 fgSetFloat(buf, j->getN1());
446 sprintf(buf, "%s/n2", er->prefix);
447 fgSetFloat(buf, j->getN2());
449 sprintf(buf, "%s/epr", er->prefix);
450 fgSetFloat(buf, j->getEPR());
452 sprintf(buf, "%s/egt-degf", er->prefix);
453 fgSetFloat(buf, j->getEGT() * K2DEGF + K2DEGFOFFSET);
458 Wing* FGFDM::parseWing(XMLAttributes* a, const char* type)
460 Wing* w = new Wing();
463 if(eq(type, "vstab"))
469 pos[0] = attrf(a, "x");
470 pos[1] = attrf(a, "y");
471 pos[2] = attrf(a, "z");
474 w->setLength(attrf(a, "length"));
475 w->setChord(attrf(a, "chord"));
476 w->setSweep(attrf(a, "sweep", 0) * DEG2RAD);
477 w->setTaper(attrf(a, "taper", 1));
478 w->setDihedral(attrf(a, "dihedral", defDihed) * DEG2RAD);
479 w->setCamber(attrf(a, "camber", 0));
480 w->setIncidence(attrf(a, "incidence", 0) * DEG2RAD);
481 w->setTwist(attrf(a, "twist", 0) * DEG2RAD);
483 // The 70% is a magic number that sorta kinda seems to match known
484 // throttle settings to approach speed.
485 w->setInducedDrag(0.7*attrf(a, "idrag", 1));
487 float effect = attrf(a, "effectiveness", 1);
488 w->setDragScale(w->getDragScale()*effect);
494 Rotor* FGFDM::parseRotor(XMLAttributes* a, const char* type)
496 Rotor* w = new Rotor();
501 pos[0] = attrf(a, "x");
502 pos[1] = attrf(a, "y");
503 pos[2] = attrf(a, "z");
507 normal[0] = attrf(a, "nx");
508 normal[1] = attrf(a, "ny");
509 normal[2] = attrf(a, "nz");
510 w->setNormal(normal);
513 forward[0] = attrf(a, "fx");
514 forward[1] = attrf(a, "fy");
515 forward[2] = attrf(a, "fz");
516 w->setForward(forward);
518 w->setMaxCyclicail(attrf(a, "maxcyclicail", 7.6));
519 w->setMaxCyclicele(attrf(a, "maxcyclicele", 4.94));
520 w->setMinCyclicail(attrf(a, "mincyclicail", -7.6));
521 w->setMinCyclicele(attrf(a, "mincyclicele", -4.94));
522 w->setMaxCollective(attrf(a, "maxcollective", 15.8));
523 w->setMinCollective(attrf(a, "mincollective", -0.2));
524 w->setDiameter(attrf(a, "diameter", 10.2));
525 w->setWeightPerBlade(attrf(a, "weightperblade", 44));
526 w->setNumberOfBlades(attrf(a, "numblades", 4));
527 w->setRelBladeCenter(attrf(a, "relbladecenter", 0.7));
528 w->setDynamic(attrf(a, "dynamic", 0.7));
529 w->setDelta3(attrf(a, "delta3", 0));
530 w->setDelta(attrf(a, "delta", 0));
531 w->setTranslift(attrf(a, "translift", 0.05));
532 w->setC2(attrf(a, "dragfactor", 1));
533 w->setStepspersecond(attrf(a, "stepspersecond", 120));
534 w->setRPM(attrf(a, "rpm", 424));
535 w->setRelLenHinge(attrf(a, "rellenflaphinge", 0.07));
536 w->setAlpha0((attrf(a, "flap0", -5))*YASIM_PI/180);
537 w->setAlphamin((attrf(a, "flapmin", -15))/180*YASIM_PI);
538 w->setAlphamax((attrf(a, "flapmax", 15))*YASIM_PI/180);
539 w->setAlpha0factor(attrf(a, "flap0factor", 1));
540 w->setTeeterdamp(attrf(a,"teeterdamp",.0001));
541 w->setMaxteeterdamp(attrf(a,"maxteeterdamp",1000));
542 w->setRelLenTeeterHinge(attrf(a,"rellenteeterhinge",0.01));
543 void setAlphamin(float f);
544 void setAlphamax(float f);
545 void setAlpha0factor(float f);
550 if(a->hasAttribute("name"))
551 w->setName(a->getValue("name") );
552 if(a->hasAttribute("alphaout0"))
553 w->setAlphaoutput(0,a->getValue("alphaout0") );
554 if(a->hasAttribute("alphaout1")) w->setAlphaoutput(1,a->getValue("alphaout1") );
555 if(a->hasAttribute("alphaout2")) w->setAlphaoutput(2,a->getValue("alphaout2") );
556 if(a->hasAttribute("alphaout3")) w->setAlphaoutput(3,a->getValue("alphaout3") );
557 if(a->hasAttribute("coneout")) w->setAlphaoutput(4,a->getValue("coneout") );
558 if(a->hasAttribute("yawout")) w->setAlphaoutput(5,a->getValue("yawout") );
559 if(a->hasAttribute("rollout")) w->setAlphaoutput(6,a->getValue("rollout") );
561 w->setPitchA(attrf(a, "pitch_a", 10));
562 w->setPitchB(attrf(a, "pitch_b", 10));
563 w->setForceAtPitchA(attrf(a, "forceatpitch_a", 3000));
564 w->setPowerAtPitch0(attrf(a, "poweratpitch_0", 300));
565 w->setPowerAtPitchB(attrf(a, "poweratpitch_b", 3000));
566 if(attrb(a,"notorque"))
568 if(attrb(a,"simblades"))
575 void FGFDM::parsePropeller(XMLAttributes* a)
578 cg[0] = attrf(a, "x");
579 cg[1] = attrf(a, "y");
580 cg[2] = attrf(a, "z");
581 float mass = attrf(a, "mass") * LBS2KG;
582 float moment = attrf(a, "moment");
583 float radius = attrf(a, "radius");
584 float speed = attrf(a, "cruise-speed") * KTS2MPS;
585 float omega = attrf(a, "cruise-rpm") * RPM2RAD;
586 float power = attrf(a, "cruise-power") * HP2W;
587 float rho = Atmosphere::getStdDensity(attrf(a, "cruise-alt") * FT2M);
589 // Hack, fix this pronto:
590 float engP = attrf(a, "eng-power") * HP2W;
591 float engS = attrf(a, "eng-rpm") * RPM2RAD;
593 Propeller* prop = new Propeller(radius, speed, omega, rho, power);
594 PistonEngine* eng = new PistonEngine(engP, engS);
595 PropEngine* thruster = new PropEngine(prop, eng, moment);
596 _airplane.addThruster(thruster, mass, cg);
598 if(a->hasAttribute("displacement"))
599 eng->setDisplacement(attrf(a, "displacement") * CIN2CM);
601 if(a->hasAttribute("compression"))
602 eng->setCompression(attrf(a, "compression"));
604 if(a->hasAttribute("turbo-mul")) {
605 float mul = attrf(a, "turbo-mul");
606 float mp = attrf(a, "wastegate-mp", 1e6) * INHG2PA;
607 eng->setTurboParams(mul, mp);
610 if(a->hasAttribute("takeoff-power")) {
611 float power0 = attrf(a, "takeoff-power") * HP2W;
612 float omega0 = attrf(a, "takeoff-rpm") * RPM2RAD;
613 prop->setTakeoff(omega0, power0);
616 if(a->hasAttribute("max-rpm")) {
617 float max = attrf(a, "max-rpm") * RPM2RAD;
618 float min = attrf(a, "min-rpm") * RPM2RAD;
619 thruster->setVariableProp(min, max);
622 if(a->hasAttribute("manual-pitch")) {
623 prop->setManualPitch();
627 sprintf(buf, "/engines/engine[%d]", _nextEngine++);
628 EngRec* er = new EngRec();
630 er->prefix = dup(buf);
636 // Turns a string axis name into an integer for use by the
637 // ControlMap. Creates a new axis if this one hasn't been defined
639 int FGFDM::parseAxis(const char* name)
642 for(i=0; i<_axes.size(); i++) {
643 AxisRec* a = (AxisRec*)_axes.get(i);
644 if(eq(a->name, name))
648 // Not there, make a new one.
649 AxisRec* a = new AxisRec();
651 a->handle = _airplane.getControlMap()->newInput();
656 int FGFDM::parseOutput(const char* name)
658 if(eq(name, "THROTTLE")) return ControlMap::THROTTLE;
659 if(eq(name, "MIXTURE")) return ControlMap::MIXTURE;
660 if(eq(name, "STARTER")) return ControlMap::STARTER;
661 if(eq(name, "MAGNETOS")) return ControlMap::MAGNETOS;
662 if(eq(name, "ADVANCE")) return ControlMap::ADVANCE;
663 if(eq(name, "REHEAT")) return ControlMap::REHEAT;
664 if(eq(name, "BOOST")) return ControlMap::BOOST;
665 if(eq(name, "VECTOR")) return ControlMap::VECTOR;
666 if(eq(name, "PROP")) return ControlMap::PROP;
667 if(eq(name, "BRAKE")) return ControlMap::BRAKE;
668 if(eq(name, "STEER")) return ControlMap::STEER;
669 if(eq(name, "EXTEND")) return ControlMap::EXTEND;
670 if(eq(name, "INCIDENCE")) return ControlMap::INCIDENCE;
671 if(eq(name, "FLAP0")) return ControlMap::FLAP0;
672 if(eq(name, "FLAP1")) return ControlMap::FLAP1;
673 if(eq(name, "SLAT")) return ControlMap::SLAT;
674 if(eq(name, "SPOILER")) return ControlMap::SPOILER;
675 if(eq(name, "CASTERING")) return ControlMap::CASTERING;
676 if(eq(name, "PROPPITCH")) return ControlMap::PROPPITCH;
677 if(eq(name, "COLLECTIVE")) return ControlMap::COLLECTIVE;
678 if(eq(name, "CYCLICAIL")) return ControlMap::CYCLICAIL;
679 if(eq(name, "CYCLICELE")) return ControlMap::CYCLICELE;
680 if(eq(name, "ROTORENGINEON")) return ControlMap::ROTORENGINEON;
681 SG_LOG(SG_FLIGHT,SG_ALERT,"Unrecognized control type '"
682 << name << "' in YASim aircraft description.");
687 void FGFDM::parseWeight(XMLAttributes* a)
689 WeightRec* wr = new WeightRec();
692 v[0] = attrf(a, "x");
693 v[1] = attrf(a, "y");
694 v[2] = attrf(a, "z");
696 wr->prop = dup(a->getValue("mass-prop"));
697 wr->size = attrf(a, "size", 0);
698 wr->handle = _airplane.addWeight(v, wr->size);
703 bool FGFDM::eq(const char* a, const char* b)
705 // Figure it out for yourself. :)
706 while(*a && *b && *a == *b) { a++; b++; }
710 char* FGFDM::dup(const char* s)
714 char* s2 = new char[len+1];
716 while((*p++ = *s++));
721 int FGFDM::attri(XMLAttributes* atts, char* attr)
723 if(!atts->hasAttribute(attr)) {
724 SG_LOG(SG_FLIGHT,SG_ALERT,"Missing '" << attr <<
725 "' in YASim aircraft description");
728 return attri(atts, attr, 0);
731 int FGFDM::attri(XMLAttributes* atts, char* attr, int def)
733 const char* val = atts->getValue(attr);
734 if(val == 0) return def;
735 else return atol(val);
738 float FGFDM::attrf(XMLAttributes* atts, char* attr)
740 if(!atts->hasAttribute(attr)) {
741 SG_LOG(SG_FLIGHT,SG_ALERT,"Missing '" << attr <<
742 "' in YASim aircraft description");
745 return attrf(atts, attr, 0);
748 float FGFDM::attrf(XMLAttributes* atts, char* attr, float def)
750 const char* val = atts->getValue(attr);
751 if(val == 0) return def;
752 else return (float)atof(val);
755 // ACK: the dreaded ambiguous string boolean. Remind me to shoot Maik
756 // when I have a chance. :). Unless you have a parser that can check
757 // symbol constants (we don't), this kind of coding is just a Bad
758 // Idea. This implementation, for example, silently returns a boolean
759 // falsehood for values of "1", "yes", "True", and "TRUE". Which is
760 // especially annoying preexisting boolean attributes in the same
761 // parser want to see "1" and will choke on a "true"...
763 // Unfortunately, this usage creeped into existing configuration files
764 // while I wasn't active, and it's going to be hard to remove. Issue
765 // a warning to nag people into changing their ways for now...
766 bool FGFDM::attrb(XMLAttributes* atts, char* attr)
768 const char* val = atts->getValue(attr);
769 if(val == 0) return false;
772 SG_LOG(SG_FLIGHT, SG_ALERT, "Warning: " <<
773 "deprecated 'true' boolean in YASim configuration file. " <<
774 "Use numeric booleans (attribute=\"1\") instead");
777 return attri(atts, attr, 0) ? true : false;
780 }; // namespace yasim