3 #include <simgear/misc/sg_path.hxx>
4 #include <simgear/debug/logstream.hxx>
5 #include <simgear/xml/easyxml.hxx>
6 #include <Main/globals.hxx>
7 #include <Main/fg_props.hxx>
8 #include <Scenery/scenery.hxx>
11 #include "Atmosphere.hpp"
13 #include "Airplane.hpp"
15 #include "Integrator.hpp"
18 #include "PropEngine.hpp"
19 #include "PistonEngine.hpp"
23 using namespace yasim;
25 static const float RAD2DEG = 180/3.14159265358979323846;
26 static const float RAD2RPM = 9.54929658551;
27 static const float M2FT = 3.2808399;
28 static const float FT2M = 0.3048;
29 static const float MPS2KTS = 3600.0/1852.0;
30 static const float CM2GALS = 264.172037284; // gallons/cubic meter
31 static const float KG2LBS = 2.20462262185;
32 static const float W2HP = 1.3416e-3;
34 void YASim::printDEBUG()
36 static int debugCount = 0;
42 // printf("N1 %5.1f N2 %5.1f FF %7.1f EPR %4.2f EGT %6.1f\n",
43 // fgGetFloat("/engines/engine[0]/n1"),
44 // fgGetFloat("/engines/engine[0]/n2"),
45 // fgGetFloat("/engines/engine[0]/fuel-flow-gph"),
46 // fgGetFloat("/engines/engine[0]/epr"),
47 // fgGetFloat("/engines/engine[0]/egt"));
49 // printf("gear: %f\n", fgGetFloat("/controls/gear-down"));
51 // printf("alpha %5.1f beta %5.1f\n", get_Alpha()*57.3, get_Beta()*57.3);
53 // printf("pilot: %f %f %f\n",
54 // fgGetDouble("/sim/view/pilot/x-offset-m"),
55 // fgGetDouble("/sim/view/pilot/y-offset-m"),
56 // fgGetDouble("/sim/view/pilot/z-offset-m"));
60 YASim::YASim(double dt)
67 _fdm->getAirplane()->getModel()->getIntegrator()->setInterval(_dt);
72 Airplane* a = _fdm->getAirplane();
74 float aoa = a->getCruiseAoA() * RAD2DEG;
75 float tail = -1 * a->getTailIncidence() * RAD2DEG;
76 float drag = 1000 * a->getDragCoefficient();
78 SG_LOG(SG_FLIGHT,SG_INFO,"YASim solution results:");
79 SG_LOG(SG_FLIGHT,SG_INFO," Iterations: "<<a->getSolutionIterations());
80 SG_LOG(SG_FLIGHT,SG_INFO,"Drag Coefficient: "<< drag);
81 SG_LOG(SG_FLIGHT,SG_INFO," Lift Ratio: "<<a->getLiftRatio());
82 SG_LOG(SG_FLIGHT,SG_INFO," Cruise AoA: "<< aoa);
83 SG_LOG(SG_FLIGHT,SG_INFO," Tail Incidence: "<< tail);
87 a->getModel()->getBody()->getCG(cg);
88 sprintf(buf, " CG: %.1f, %.1f, %.1f", cg[0], cg[1], cg[2]);
89 SG_LOG(SG_FLIGHT, SG_INFO, buf);
91 if(a->getFailureMsg()) {
92 SG_LOG(SG_FLIGHT, SG_ALERT, "YASim SOLUTION FAILURE:");
93 SG_LOG(SG_FLIGHT, SG_ALERT, a->getFailureMsg());
100 // Run the superclass bind to set up a bunch of property ties
103 // Now UNtie the ones that we are going to set ourselves.
104 fgUntie("/consumables/fuel/tank[0]/level-gal_us");
105 fgUntie("/consumables/fuel/tank[1]/level-gal_us");
108 for(int i=0; i<_fdm->getAirplane()->getModel()->numThrusters(); i++) {
109 sprintf(buf, "/engines/engine[%d]/fuel-flow-gph", i); fgUntie(buf);
110 sprintf(buf, "/engines/engine[%d]/rpm", i); fgUntie(buf);
111 sprintf(buf, "/engines/engine[%d]/mp-osi", i); fgUntie(buf);
112 sprintf(buf, "/engines/engine[%d]/egt-degf", i); fgUntie(buf);
119 Airplane* a = _fdm->getAirplane();
120 Model* m = a->getModel();
125 m->setCrashed(false);
127 // Build a filename and parse it
128 SGPath f(globals->get_fg_root());
129 f.append("Aircraft-yasim");
130 f.append(fgGetString("/sim/aero"));
132 readXML(f.str(), *_fdm);
134 // Compile it into a real airplane, and tell the user what they got
140 // Create some FG{Eng|Gear}Interface objects
142 for(i=0; i<a->numGear(); i++) {
143 Gear* g = a->getGear(i);
147 fgg.SetX(pos[0]); fgg.SetY(-pos[1]); fgg.SetZ(-pos[2]);
150 for(i=0; i<m->numThrusters(); i++) {
154 // Sanify the initial input conditions
156 sprintf(buf, "/controls/throttle[%d]", i); fgSetFloat(buf, 0);
157 sprintf(buf, "/controls/mixture[%d]", i); fgSetFloat(buf, 1);
158 sprintf(buf, "/controls/propeller-pitch[%d]", i); fgSetFloat(buf, 1);
159 sprintf(buf, "/controls/afterburner[%d]", i); fgSetFloat(buf, 0);
162 fgSetFloat("/controls/slats", 0);
163 fgSetFloat("/controls/spoilers", 0);
165 // Are we at ground level? If so, lift the plane up so the gear
167 if(get_Altitude() - get_Runway_altitude() < 50) {
168 float minGearZ = 1e18;
169 for(i=0; i<a->numGear(); i++) {
170 Gear* g = a->getGear(i);
173 if(pos[2] < minGearZ)
176 _set_Altitude(get_Runway_altitude() - minGearZ*M2FT);
179 // The pilot's eyepoint
181 a->getPilotPos(pilot);
182 fgSetFloat("/sim/view/pilot/x-offset-m", -pilot[0]);
183 fgSetFloat("/sim/view/pilot/y-offset-m", -pilot[1]);
184 fgSetFloat("/sim/view/pilot/z-offset-m", pilot[2]);
186 // Blank the state, and copy in ours
191 _fdm->getExternalInput();
192 _fdm->getAirplane()->stabilizeThrust();
197 void YASim::update(int iterations)
199 // If we're crashed, then we don't care
200 if(_fdm->getAirplane()->getModel()->isCrashed())
204 for(i=0; i<iterations; i++) {
213 void YASim::copyToYASim(bool copyState)
216 float lat = get_Latitude();
217 float lon = get_Longitude();
218 float alt = get_Altitude() * FT2M;
219 float roll = get_Phi();
220 float pitch = get_Theta();
221 float hdg = get_Psi();
225 wind[0] = get_V_north_airmass() * FT2M;
226 wind[1] = get_V_east_airmass() * FT2M;
227 wind[2] = get_V_down_airmass() * FT2M;
228 double ground = get_Runway_altitude() * FT2M;
230 // You'd this this would work, but it doesn't. These values are
231 // always zero. Use a "standard" pressure intstead.
233 // float pressure = get_Static_pressure();
234 // float temp = get_Static_temperature();
235 float pressure = Atmosphere::getStdPressure(alt);
236 float temp = Atmosphere::getStdTemperature(alt);
239 Model* model = _fdm->getAirplane()->getModel();
242 Glue::xyz2nedMat(lat, lon, xyz2ned);
245 Glue::geod2xyz(lat, lon, alt, s.pos);
248 Glue::euler2orient(roll, pitch, hdg, s.orient);
249 Math::mmul33(s.orient, xyz2ned, s.orient);
251 // Copy in the existing velocity for now...
252 Math::set3(model->getState()->v, s.v);
258 Math::tmul33(xyz2ned, wind, wind);
259 model->setWind(wind);
261 // ground. Calculate a cartesian coordinate for the ground under
262 // us, find the (geodetic) up vector normal to the ground, then
263 // use that to find the final (radius) term of the plane equation.
264 double xyz[3], gplane[3]; float up[3];
265 Glue::geod2xyz(lat, lon, ground, xyz);
266 Glue::geodUp(xyz, up); // FIXME, needless reverse computation...
268 for(i=0; i<3; i++) gplane[i] = up[i];
269 double rad = gplane[0]*xyz[0] + gplane[1]*xyz[1] + gplane[2]*xyz[2];
270 model->setGroundPlane(gplane, rad);
273 model->setAir(pressure, temp);
276 // All the settables:
278 // These are set below:
281 // _set_Accels_CG_Body
282 // _set_Accels_Pilot_Body
283 // _set_Accels_CG_Body_N
284 // _set_Velocities_Local
285 // _set_Velocities_Ground
286 // _set_Velocities_Wind_Body
291 // _set_V_ground_speed
293 // _set_V_calibrated_kts
301 // _set_Geodetic_Position
302 // _set_Runway_altitude
304 // Ignoring these, because they're unused:
305 // _set_Geocentric_Position
306 // _set_Geocentric_Rates
309 // _set_Earth_position_angle (WTF?)
310 // _set_Gamma_vert_rad
312 // _set_T_Local_to_Body
314 // _set_Sea_Level_Radius
316 // Externally set via the weather code:
317 // _set_Velocities_Local_Airmass
319 // _set_Static_pressure
320 // _set_Static_temperature
321 void YASim::copyFromYASim()
323 Airplane* airplane = _fdm->getAirplane();
324 Model* model = airplane->getModel();
325 State* s = model->getState();
328 double lat, lon, alt;
329 Glue::xyz2geod(s->pos, &lat, &lon, &alt);
330 _set_Geodetic_Position(lat, lon, alt*M2FT);
333 //_set_Geocentric_Position(Glue::geod2geocLat(lat), lon, alt*M2FT);
335 _set_Altitude_AGL(model->getAGL() * M2FT);
337 // useful conversion matrix
339 Glue::xyz2nedMat(lat, lon, xyz2ned);
343 Math::vmul33(xyz2ned, s->v, v);
344 _set_Velocities_Local(M2FT*v[0], M2FT*v[1], M2FT*v[2]);
345 _set_V_ground_speed(Math::sqrt(M2FT*v[0]*M2FT*v[0] +
346 M2FT*v[1]*M2FT*v[1]));
347 _set_Climb_Rate(-M2FT*v[2]);
349 // The HUD uses this, but inverts down (?!)
350 _set_Velocities_Ground(M2FT*v[0], M2FT*v[1], -M2FT*v[2]);
352 // _set_Geocentric_Rates(M2FT*v[0], M2FT*v[1], M2FT*v[2]); // UNUSED
354 Math::vmul33(s->orient, s->v, v);
355 _set_Velocities_Wind_Body(v[0]*M2FT, -v[1]*M2FT, -v[2]*M2FT);
356 _set_V_rel_wind(Math::mag3(v)*M2FT); // units?
358 // These don't work, use a dummy based on altitude
359 // float P = get_Static_pressure();
360 // float T = get_Static_temperature();
361 float P = Atmosphere::getStdPressure(alt);
362 float T = Atmosphere::getStdTemperature(alt);
363 _set_V_equiv_kts(Atmosphere::calcVEAS(v[0], P, T)*MPS2KTS);
364 _set_V_calibrated_kts(Atmosphere::calcVCAS(v[0], P, T)*MPS2KTS);
365 _set_Mach_number(Atmosphere::calcMach(v[0], T));
368 Math::vmul33(xyz2ned, s->acc, v);
369 _set_Accels_Local(M2FT*v[0], M2FT*v[1], M2FT*v[2]);
371 Math::vmul33(s->orient, s->acc, v);
372 _set_Accels_Body(M2FT*v[0], -M2FT*v[1], -M2FT*v[2]);
373 _set_Accels_CG_Body(M2FT*v[0], -M2FT*v[1], -M2FT*v[2]);
375 _fdm->getAirplane()->getPilotAccel(v);
376 _set_Accels_Pilot_Body(M2FT*v[0], -M2FT*v[1], -M2FT*v[2]);
378 // The one appears (!) to want inverted pilot acceleration
379 // numbers, in G's...
380 Math::mul3(1.0/9.8, v, v);
381 _set_Accels_CG_Body_N(v[0], -v[1], -v[2]);
385 Glue::calcAlphaBeta(s, &alpha, &beta);
390 Math::trans33(xyz2ned, tmp);
391 Math::mmul33(s->orient, tmp, tmp);
392 float roll, pitch, hdg;
393 Glue::orient2euler(tmp, &roll, &pitch, &hdg);
394 _set_Euler_Angles(roll, pitch, hdg);
397 Math::vmul33(s->orient, s->rot, v);
398 _set_Omega_Body(v[0], -v[1], -v[2]);
400 Glue::calcEulerRates(s, &roll, &pitch, &hdg);
401 _set_Euler_Rates(roll, pitch, hdg);
403 // Fill out our engine and gear objects
405 for(i=0; i<get_num_gear(); i++) {
406 FGGearInterface* fgg = get_gear_unit(i);
407 Gear* g = airplane->getGear(i);
408 if(g->getBrake() != 0)
410 if(g->getCompressFraction() != 0)
414 fgg->SetPosition(g->getExtension());
417 for(i=0; i<get_num_engines(); i++) {
418 FGEngInterface* fge = get_engine(i);
419 Thruster* t = model->getThruster(i);
421 fge->set_Running_Flag(true);
422 fge->set_Cranking_Flag(false);
424 // Note: assumes all tanks have the same fuel density!
425 fge->set_Fuel_Flow(CM2GALS * t->getFuelFlow()
426 / airplane->getFuelDensity(0));
430 fge->set_prop_thrust(Math::mag3(tmp) * KG2LBS / 9.8);
432 PropEngine* pe = t->getPropEngine();
434 fge->set_RPM(pe->getOmega() * RAD2RPM);
437 float power = Math::mag3(tmp) * pe->getOmega();
438 float maxPower = pe->getPistonEngine()->getMaxPower();
440 fge->set_MaxHP(maxPower * W2HP);
441 fge->set_Percentage_Power(100 * power/maxPower);