1 #include "Atmosphere.hpp"
3 #include "PistonEngine.hpp"
6 const static float HP2W = 745.7f;
7 const static float CIN2CM = 1.6387064e-5f;
8 const static float RPM2RADPS = 0.1047198f;
10 PistonEngine::PistonEngine(float power, float speed)
17 // Presume a BSFC (in lb/hour per HP) of 0.45. In SI that becomes
18 // (2.2 lb/kg, 745.7 W/hp, 3600 sec/hour) 7.62e-08 kg/Ws.
19 _f0 = power * 7.62e-08f;
24 // We must be at sea level under standard conditions
25 _rho0 = Atmosphere::getStdDensity(0);
27 // Further presume that takeoff is (duh) full throttle and
28 // peak-power, that means that by our efficiency function, we are
29 // at 11/8 of "ideal" fuel flow.
30 float realFlow = _f0 * (11.0f/8.0f);
31 _mixCoeff = realFlow * 1.1f / _omega0;
34 _maxMP = 1e6; // No waste gate on non-turbo engines.
36 // Guess at reasonable values for these guys. Displacements run
37 // at about 2 cubic inches per horsepower or so, at least for
38 // non-turbocharged engines.
40 _displacement = power * (2*CIN2CM/HP2W);
43 void PistonEngine::setTurboParams(float turbo, float maxMP)
48 // This changes the "sea level" manifold air density
49 float P0 = Atmosphere::getStdPressure(0);
50 float P = P0 * (1 + _boost * (_turbo - 1));
51 if(P > _maxMP) P = _maxMP;
52 float T = Atmosphere::getStdTemperature(0) * Math::pow(P/P0, 2./7.);
53 _rho0 = P / (287.1f * T);
56 void PistonEngine::setDisplacement(float d)
61 void PistonEngine::setCompression(float c)
66 float PistonEngine::getMaxPower()
71 void PistonEngine::setThrottle(float t)
76 void PistonEngine::setRunning(bool r)
81 void PistonEngine::setStarter(bool s)
86 void PistonEngine::setMagnetos(int m)
91 void PistonEngine::setMixture(float m)
96 void PistonEngine::setBoost(float boost)
101 bool PistonEngine::isRunning()
106 bool PistonEngine::isCranking()
111 float PistonEngine::getTorque()
116 float PistonEngine::getFuelFlow()
121 float PistonEngine::getMP()
126 float PistonEngine::getEGT()
131 void PistonEngine::calc(float pressure, float temp, float speed)
133 if(_magnetos == 0 || speed < 200*RPM2RADPS)
135 else if(_fuel == false)
140 // Calculate manifold pressure as ambient pressure modified for
141 // turbocharging and reduced by the throttle setting. According
142 // to Dave Luff, minimum throttle at sea level corresponds to 6"
143 // manifold pressure. Assume that this means that minimum MP is
144 // always 20% of ambient pressure. (But that's too much idle
145 // power, so use 10% instead!) But we need to produce _zero_
146 // thrust at that setting, so hold onto the "output" value
148 _mp = pressure * (1 + _boost*(_turbo-1)); // turbocharger
149 float mp = _mp * (0.1f + 0.9f * _throttle); // throttle
151 if(mp > _maxMP) mp = _maxMP; // wastegate
153 // Air entering the manifold does so rapidly, and thus the
154 // pressure change can be assumed to be adiabatic. Calculate a
155 // temperature change, and use that to get the density.
156 float T = temp * Math::pow(mp/pressure, 2.0/7.0);
157 float rho = mp / (287.1f * T);
159 // The actual fuel flow is determined only by engine RPM and the
160 // mixture setting. Not all of this will burn with the same
162 _fuelFlow = _mixture * speed * _mixCoeff;
163 if(_fuel == false) _fuelFlow = 0;
165 // How much fuel could be burned with ideal (i.e. uncorrected!)
167 float burnable = _f0 * (rho/_rho0) * (speed/_omega0);
169 // Calculate the fuel that actually burns to produce work. The
170 // idea is that less than 5/8 of ideal, we get complete
171 // combustion. We use up all the oxygen at 1 3/8 of ideal (that
172 // is, you need to waste fuel to use all your O2). In between,
173 // interpolate. This vaguely matches a curve I copied out of a
174 // book for a single engine. Shrug.
176 float r = _fuelFlow/burnable;
177 if (burnable == 0) burned = 0;
178 else if(r < .625) burned = _fuelFlow;
179 else if(r > 1.375) burned = burnable;
181 burned = _fuelFlow + (burnable-_fuelFlow)*(r-0.625f)*(4.0f/3.0f);
183 // Correct for engine control state
189 // And finally the power is just the reference power scaled by the
190 // amount of fuel burned, and torque is that divided by RPM.
191 float power = _power0 * burned/_f0;
192 _torque = power/speed;
194 // Figure that the starter motor produces 20% of the engine's
196 if(_cranking && !_running)
197 _torque += 0.20f * _power0/_omega0;
199 // Also, add a negative torque of 10% of cruise, to represent
200 // internal friction. Propeller aerodynamic friction is too low
201 // at low RPMs to provide a good deceleration. Interpolate it
202 // away as we approach cruise RPMs, though, to prevent interaction
203 // with the power computations. Ugly.
204 if(speed > 0 && speed < _omega0)
205 _torque -= 0.05f * (_power0/_omega0) * (1 - speed/_omega0);
207 // Now EGT. This one gets a little goofy. We can calculate the
208 // work done by an isentropically expanding exhaust gas as the
209 // mass of the gas times the specific heat times the change in
210 // temperature. The mass is just the engine displacement times
211 // the manifold density, plus the mass of the fuel, which we know.
212 // The change in temperature can be calculated adiabatically as a
213 // function of the exhaust gas temperature and the compression
214 // ratio (which we know). So just rearrange the equation to get
215 // EGT as a function of engine power. Cool. I'm using a value of
216 // 1300 J/(kg*K) for the exhaust gas specific heat. I found this
217 // on a web page somewhere; no idea if it's accurate. Also,
218 // remember that four stroke engines do one combustion cycle every
219 // TWO revolutions, so the displacement per revolution is half of
220 // what we'd expect. And diddle the work done by the gas a bit to
221 // account for non-thermodynamic losses like internal friction;
224 float massFlow = _fuelFlow + (rho * 0.5f * _displacement * speed);
225 float specHeat = 1300;
226 float corr = 1.0f/(Math::pow(_compression, 0.4f) - 1.0f);
227 _egt = corr * (power * 1.1f) / (massFlow * specHeat);
228 if(_egt < temp) _egt = temp;
231 }; // namespace yasim