#include "PropEngine.hpp"
#include "Propeller.hpp"
#include "PistonEngine.hpp"
+#include "TurbineEngine.hpp"
#include "Rotor.hpp"
#include "Rotorpart.hpp"
#include "Rotorblade.hpp"
static const float CIN2CM = 1.6387064e-5;
static const float YASIM_PI = 3.14159265358979323846;
+static const float NM2FTLB = (1/(LBS2N*FT2M));
+
// Stubs, so that this can be compiled without the FlightGear
// binary. What's the best way to handle this?
_airplane.setTail(parseWing(a, name));
} else if(eq(name, "vstab") || eq(name, "mstab")) {
_airplane.addVStab(parseWing(a, name));
+ } else if(eq(name, "piston-engine")) {
+ parsePistonEngine(a);
+ } else if(eq(name, "turbine-engine")) {
+ parseTurbineEngine(a);
} else if(eq(name, "propeller")) {
parsePropeller(a);
} else if(eq(name, "thruster")) {
void FGFDM::setOutputProperties()
{
- char buf[256];
+ // char buf[256];
int i;
float grossWgt = _airplane.getModel()->getBody()->getTotalMass() * KG2LBS;
float lbs = Math::mag3(tmp) * (KG2LBS/9.8);
node->setFloatValue("prop-thrust", lbs); // Deprecated name
node->setFloatValue("thrust-lbs", lbs);
-
node->setFloatValue("fuel-flow-gph",
(t->getFuelFlow()/fuelDensity) * 3600 * CM2GALS);
if(t->getPropEngine()) {
PropEngine* p = t->getPropEngine();
node->setFloatValue("rpm", p->getOmega() * (1/RPM2RAD));
-
+ node->setFloatValue("torque-ftlb",
+ p->getEngine()->getTorque() * NM2FTLB);
+
if(p->getEngine()->isPistonEngine()) {
PistonEngine* pe = p->getEngine()->isPistonEngine();
node->setFloatValue("mp-osi", pe->getMP() * (1/INHG2PA));
node->setFloatValue("mp-inhg", pe->getMP() * (1/INHG2PA));
node->setFloatValue("egt-degf",
pe->getEGT() * K2DEGF + K2DEGFOFFSET);
-// } else if(p->isTurbineEngine()) {
-// TurbineEngine* te = p->isTurbineEngine();
+ } else if(p->getEngine()->isTurbineEngine()) {
+ TurbineEngine* te = p->getEngine()->isTurbineEngine();
+ node->setFloatValue("n2", te->getN2());
}
}
return w;
}
-void FGFDM::parsePropeller(XMLAttributes* a)
+void FGFDM::parsePistonEngine(XMLAttributes* a)
{
- float cg[3];
- cg[0] = attrf(a, "x");
- cg[1] = attrf(a, "y");
- cg[2] = attrf(a, "z");
- float mass = attrf(a, "mass") * LBS2KG;
- float moment = attrf(a, "moment");
- float radius = attrf(a, "radius");
- float speed = attrf(a, "cruise-speed") * KTS2MPS;
- float omega = attrf(a, "cruise-rpm") * RPM2RAD;
- float power = attrf(a, "cruise-power") * HP2W;
- float rho = Atmosphere::getStdDensity(attrf(a, "cruise-alt") * FT2M);
-
- // Hack, fix this pronto:
float engP = attrf(a, "eng-power") * HP2W;
float engS = attrf(a, "eng-rpm") * RPM2RAD;
- Propeller* prop = new Propeller(radius, speed, omega, rho, power);
PistonEngine* eng = new PistonEngine(engP, engS);
- PropEngine* thruster = new PropEngine(prop, eng, moment);
- _airplane.addThruster(thruster, mass, cg);
if(a->hasAttribute("displacement"))
eng->setDisplacement(attrf(a, "displacement") * CIN2CM);
eng->setTurboParams(mul, mp);
}
+ ((PropEngine*)_currObj)->setEngine(eng);
+}
+
+void FGFDM::parseTurbineEngine(XMLAttributes* a)
+{
+ float power = attrf(a, "eng-power") * HP2W;
+ float omega = attrf(a, "eng-rpm") * RPM2RAD;
+ float alt = attrf(a, "alt") * FT2M;
+ float flatRating = attrf(a, "flat-rating") * HP2W;
+ TurbineEngine* eng = new TurbineEngine(power, omega, alt, flatRating);
+
+ if(a->hasAttribute("n2-low-idle"))
+ eng->setN2Range(attrf(a, "n2-low-idle"), attrf(a, "n2-high-idle"),
+ attrf(a, "n2-max"));
+
+ // Nasty units conversion: lbs/hr per hp -> kg/s per watt
+ if(a->hasAttribute("bsfc"))
+ eng->setFuelConsumption(attrf(a, "bsfc") * (LBS2KG/(3600*HP2W)));
+
+ ((PropEngine*)_currObj)->setEngine(eng);
+}
+
+void FGFDM::parsePropeller(XMLAttributes* a)
+{
+ // Legacy Handling for the old engines syntax:
+ PistonEngine* eng = 0;
+ if(a->hasAttribute("eng-power")) {
+ SG_LOG(SG_FLIGHT,SG_ALERT, "WARNING: "
+ << "Legacy engine definition in YASim configuration file. "
+ << "Please fix.");
+ float engP = attrf(a, "eng-power") * HP2W;
+ float engS = attrf(a, "eng-rpm") * RPM2RAD;
+ eng = new PistonEngine(engP, engS);
+ if(a->hasAttribute("displacement"))
+ eng->setDisplacement(attrf(a, "displacement") * CIN2CM);
+ if(a->hasAttribute("compression"))
+ eng->setCompression(attrf(a, "compression"));
+ if(a->hasAttribute("turbo-mul")) {
+ float mul = attrf(a, "turbo-mul");
+ float mp = attrf(a, "wastegate-mp", 1e6) * INHG2PA;
+ eng->setTurboParams(mul, mp);
+ }
+ }
+
+ // Now parse the actual propeller definition:
+ float cg[3];
+ cg[0] = attrf(a, "x");
+ cg[1] = attrf(a, "y");
+ cg[2] = attrf(a, "z");
+ float mass = attrf(a, "mass") * LBS2KG;
+ float moment = attrf(a, "moment");
+ float radius = attrf(a, "radius");
+ float speed = attrf(a, "cruise-speed") * KTS2MPS;
+ float omega = attrf(a, "cruise-rpm") * RPM2RAD;
+ float power = attrf(a, "cruise-power") * HP2W;
+ float rho = Atmosphere::getStdDensity(attrf(a, "cruise-alt") * FT2M);
+
+ Propeller* prop = new Propeller(radius, speed, omega, rho, power);
+ PropEngine* thruster = new PropEngine(prop, eng, moment);
+ _airplane.addThruster(thruster, mass, cg);
+
if(a->hasAttribute("takeoff-power")) {
float power0 = attrf(a, "takeoff-power") * HP2W;
float omega0 = attrf(a, "takeoff-rpm") * RPM2RAD;
// Not there, make a new one.
AxisRec* a = new AxisRec();
a->name = dup(name);
+ fgGetNode( a->name, true ); // make sure the property name exists
a->handle = _airplane.getControlMap()->newInput();
_axes.add(a);
return a->handle;
{
if(eq(name, "THROTTLE")) return ControlMap::THROTTLE;
if(eq(name, "MIXTURE")) return ControlMap::MIXTURE;
+ if(eq(name, "CONDLEVER")) return ControlMap::CONDLEVER;
if(eq(name, "STARTER")) return ControlMap::STARTER;
if(eq(name, "MAGNETOS")) return ControlMap::MAGNETOS;
if(eq(name, "ADVANCE")) return ControlMap::ADVANCE;
if(eq(name, "SPOILER")) return ControlMap::SPOILER;
if(eq(name, "CASTERING")) return ControlMap::CASTERING;
if(eq(name, "PROPPITCH")) return ControlMap::PROPPITCH;
+ if(eq(name, "PROPFEATHER")) return ControlMap::PROPFEATHER;
if(eq(name, "COLLECTIVE")) return ControlMap::COLLECTIVE;
if(eq(name, "CYCLICAIL")) return ControlMap::CYCLICAIL;
if(eq(name, "CYCLICELE")) return ControlMap::CYCLICELE;
projects / flightgear.git / blobdiff