delete (Surface*)_surfs.get(i);
for(i=0; i<_contacts.size(); i++)
delete[] (float*)_contacts.get(i);
+ for(i=0; i<_solveWeights.size(); i++)
+ delete[] (SolveWeight*)_solveWeights.get(i);
}
void Airplane::iterate(float dt)
// The gear might have moved. Change their aerodynamics.
updateGearState();
- _model.iterate(dt);
+ _model.iterate();
}
-void Airplane::consumeFuel(float dt)
+void Airplane::calcFuelWeights()
{
- // This is a really simple implementation that assumes all engines
- // draw equally from all tanks in proportion to the amount of fuel
- // stored there. Needs to be fixed, but that has to wait for a
- // decision as to what the property interface will look like.
- int i, outOfFuel = 0;
- float fuelFlow = 0, totalFuel = 0.00001; // <-- overflow protection
- for(i=0; i<_thrusters.size(); i++)
- fuelFlow += ((ThrustRec*)_thrusters.get(i))->thruster->getFuelFlow();
- for(i=0; i<_tanks.size(); i++)
- totalFuel += ((Tank*)_tanks.get(i))->fill;
- for(i=0; i<_tanks.size(); i++) {
- Tank* t = (Tank*)_tanks.get(i);
- t->fill -= dt * fuelFlow * (t->fill/totalFuel);
- if(t->fill <= 0) {
- t->fill = 0;
- outOfFuel = 1;
- }
- }
- if(outOfFuel)
- for(int i=0; i<_thrusters.size(); i++)
- ((ThrustRec*)_thrusters.get(i))->thruster->setFuelState(false);
-
- // Set the tank masses on the RigidBody
- for(i=0; i<_tanks.size(); i++) {
+ for(int i=0; i<_tanks.size(); i++) {
Tank* t = (Tank*)_tanks.get(i);
_model.getBody()->setMass(t->handle, t->fill);
}
}
}
-void Airplane::setApproach(float speed, float altitude)
-{
- // The zero AoA will become a calculated stall AoA in compile()
- setApproach(speed, altitude, 0);
-}
-
-void Airplane::setApproach(float speed, float altitude, float aoa)
+void Airplane::setApproach(float speed, float altitude, float aoa, float fuel)
{
_approachSpeed = speed;
_approachP = Atmosphere::getStdPressure(altitude);
_approachT = Atmosphere::getStdTemperature(altitude);
_approachAoA = aoa;
+ _approachFuel = fuel;
}
-void Airplane::setCruise(float speed, float altitude)
+void Airplane::setCruise(float speed, float altitude, float fuel)
{
_cruiseSpeed = speed;
_cruiseP = Atmosphere::getStdPressure(altitude);
_cruiseT = Atmosphere::getStdTemperature(altitude);
_cruiseAoA = 0;
_tailIncidence = 0;
+ _cruiseFuel = fuel;
}
void Airplane::setElevatorControl(int control)
_cruiseControls.add(c);
}
+void Airplane::addSolutionWeight(bool approach, int idx, float wgt)
+{
+ SolveWeight* w = new SolveWeight();
+ w->approach = approach;
+ w->idx = idx;
+ w->wgt = wgt;
+ _solveWeights.add(w);
+}
+
int Airplane::numTanks()
{
return _tanks.size();
return ((Tank*)_tanks.get(tank))->fill;
}
+float Airplane::setFuel(int tank, float fuel)
+{
+ ((Tank*)_tanks.get(tank))->fill = fuel;
+}
+
float Airplane::getFuelDensity(int tank)
{
return ((Tank*)_tanks.get(tank))->density;
return wgt;
}
-float Airplane::compileRotor(Rotor* w)
+float Airplane::compileRotor(Rotor* r)
{
- /* todo contact points
- // The tip of the wing is a contact point
- float tip[3];
- w->getTip(tip);
- addContactPoint(tip);
- if(w->isMirrored()) {
- tip[1] *= -1;
- addContactPoint(tip);
- }
- */
-
- // Make sure it's initialized. The surfaces will pop out with
- // total drag coefficients equal to their areas, which is what we
- // want.
- w->compile();
- _model.addRotor(w);
+ // Todo: add rotor to model!!!
+ // Todo: calc and add mass!!!
+ r->compile();
+ _model.addRotor(r);
float wgt = 0;
int i;
- /* Todo: add rotor to model!!!
- Todo: calc and add mass!!!
- */
- for(i=0; i<w->numRotorparts(); i++) {
- Rotorpart* s = (Rotorpart*)w->getRotorpart(i);
-
- //float td = s->getTotalDrag();
- //s->setTotalDrag(td);
+ for(i=0; i<r->numRotorparts(); i++) {
+ Rotorpart* s = (Rotorpart*)r->getRotorpart(i);
_model.addRotorpart(s);
-
float mass = s->getWeight();
mass = mass * Math::sqrt(mass);
s->getPosition(pos);
_model.getBody()->addMass(mass, pos);
wgt += mass;
-
}
- for(i=0; i<w->numRotorblades(); i++) {
- Rotorblade* s = (Rotorblade*)w->getRotorblade(i);
-
- //float td = s->getTotalDrag();
- //s->setTotalDrag(td);
-
- _model.addRotorblade(s);
+ for(i=0; i<r->numRotorblades(); i++) {
+ Rotorblade* b = (Rotorblade*)r->getRotorblade(i);
+ _model.addRotorblade(b);
- float mass = s->getWeight();
+ float mass = b->getWeight();
mass = mass * Math::sqrt(mass);
float pos[3];
- s->getPosition(pos);
+ b->getPosition(pos);
_model.getBody()->addMass(mass, pos);
wgt += mass;
-
}
-
return wgt;
}
if (_tail)
aeroWgt += compileWing(_tail);
int i;
- for(i=0; i<_vstabs.size(); i++) {
+ for(i=0; i<_vstabs.size(); i++)
aeroWgt += compileWing((Wing*)_vstabs.get(i));
- }
- for(i=0; i<_rotors.size(); i++) {
+ for(i=0; i<_rotors.size(); i++)
aeroWgt += compileRotor((Rotor*)_rotors.get(i));
- }
// The fuselage(s)
- for(i=0; i<_fuselages.size(); i++) {
+ for(i=0; i<_fuselages.size(); i++)
aeroWgt += compileFuselage((Fuselage*)_fuselages.get(i));
- }
// Count up the absolute weight we have
float nonAeroWgt = _ballast;
// Ground effect
float gepos[3];
- float gespan;
+ float gespan = 0;
if(_wing)
gespan = _wing->getGroundEffect(gepos);
- else
- gespan=0;
_model.setGroundEffect(gepos, gespan, 0.15f);
solveGear();
-
- solve();
+ if(_wing && _tail) solve();
+ else solveHelicopter();
// Do this after solveGear, because it creates "gear" objects that
// we don't want to affect.
_model.getThruster(i)->stabilize();
}
+void Airplane::setupWeights(bool isApproach)
+{
+ int i;
+ for(i=0; i<_weights.size(); i++)
+ setWeight(i, 0);
+ for(i=0; i<_solveWeights.size(); i++) {
+ SolveWeight* w = (SolveWeight*)_solveWeights.get(i);
+ if(w->approach == isApproach)
+ setWeight(w->idx, w->wgt);
+ }
+}
+
void Airplane::runCruise()
{
setupState(_cruiseAoA, _cruiseSpeed, &_cruiseState);
Math::mul3(-1, _cruiseState.v, wind);
Math::vmul33(_cruiseState.orient, wind, wind);
- // Cruise is by convention at 50% tank capacity
- setFuelFraction(0.5);
+ setFuelFraction(_cruiseFuel);
+ setupWeights(false);
// Set up the thruster parameters and iterate until the thrust
// stabilizes.
// Precompute thrust in the model, and calculate aerodynamic forces
_model.getBody()->recalc();
_model.getBody()->reset();
- _model.initIteration(.01);//hier parameter egal
+ _model.initIteration();
_model.calcForces(&_cruiseState);
}
Math::mul3(-1, _approachState.v, wind);
Math::vmul33(_approachState.orient, wind, wind);
- // Approach is by convention at 20% tank capacity
- setFuelFraction(0.2f);
+ setFuelFraction(_approachFuel);
+
+ setupWeights(true);
// Run the thrusters until they get to a stable setting. FIXME:
// this is lots of wasted work.
// Precompute thrust in the model, and calculate aerodynamic forces
_model.getBody()->recalc();
_model.getBody()->reset();
- _model.initIteration(.01);//hier parameter egal
+ _model.initIteration();
_model.calcForces(&_approachState);
}
float tmp[3];
_solutionIterations = 0;
_failureMsg = 0;
- if((_wing)&&(_tail))
- {
- while(1) {
-#if 0
- printf("%d %f %f %f %f %f\n", //DEBUG
- _solutionIterations,
- 1000*_dragFactor,
- _liftRatio,
- _cruiseAoA,
- _tailIncidence,
- _approachElevator.val);
-#endif
+ while(1) {
if(_solutionIterations++ > 10000) {
_failureMsg = "Solution failed to converge after 10000 iterations";
return;
_failureMsg = "Tail incidence > 10 degrees";
return;
}
- }
- else
- {
- applyDragFactor(Math::pow(15.7/1000, 1/SOLVE_TWEAK));
- applyLiftRatio(Math::pow(104, 1/SOLVE_TWEAK));
- setupState(0,0, &_cruiseState);
- _model.setState(&_cruiseState);
- _controls.reset();
- _model.getBody()->reset();
-
+}
- }
+void Airplane::solveHelicopter()
+{
+ _solutionIterations = 0;
+ _failureMsg = 0;
- return;
+ applyDragFactor(Math::pow(15.7/1000, 1/SOLVE_TWEAK));
+ applyLiftRatio(Math::pow(104, 1/SOLVE_TWEAK));
+ setupState(0,0, &_cruiseState);
+ _model.setState(&_cruiseState);
+ _controls.reset();
+ _model.getBody()->reset();
}
+
}; // namespace yasim
projects / flightgear.git / blobdiff