Contributed by Dave Luff:
Added fuel-flow and total fuel to the LaRCSim model. Its still a bit rough for now but it works, except the engine dosn't stop when fuel runs out at the moment since there's no refuelling capability in the sim just now. It takes about 4 gallons use before you see the fuel guages begin to drop since there's 28 gal per tank but the guages go to 26.
This commit is contained in:
curt
parent
d7ca2c7e7d
commit
5d423a94b0
7 changed files with 131 additions and 23 deletions
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@ -73,7 +73,10 @@
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// DCL 27/10/00 - Added first stab at cylinder head temperature model
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// See the comment block in the code for details
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//
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// DCL 02/11/00 - Modified EGT code to reduce values to those more representative of a sensor downstream
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// DCL 02/11/00 - Modified EGT code to reduce values to those more representative of a sensor downstream
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//
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// DCL 02/02/01 - Changed the prop model to one based on efficiency and co-efficient of power curves from McCormick instead of the
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// blade element method we were using previously. This works much better, and is similar to how Jon is doing it in JSBSim.
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//
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//////////////////////////////////////////////////////////////////////
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@ -97,8 +100,7 @@ float FGNewEngine::Lookup_Combustion_Efficiency(float thi_actual)
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float factor;
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int i;
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int j;
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j = NUM_ELEMENTS; //This must be equal to the number of elements in the lookup table arrays
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int j = NUM_ELEMENTS; //This must be equal to the number of elements in the lookup table arrays
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for(i=0;i<j;i++)
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{
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@ -224,6 +226,7 @@ void FGNewEngine::init(double dt) {
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Cp_air = 1005; // J/KgK
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Cp_fuel = 1700; // J/KgK
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calorific_value_fuel = 47.3e6; // W/Kg Note that this is only an approximate value
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rho_fuel = 800; // kg/m^3 - an estimate for now
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R_air = 287.3;
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// Control and environment inputs
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@ -260,7 +263,7 @@ void FGNewEngine::init(double dt) {
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Percentage_Power = 0;
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Manifold_Pressure = 29.00; // Inches
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RPM = 600;
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Fuel_Flow = 0; // lbs/hour
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Fuel_Flow_gals_hr = 0;
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Torque = 0;
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Torque_SI = 0;
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CHT = 298.0; //deg Kelvin
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@ -372,12 +375,14 @@ void FGNewEngine::update() {
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//calculate ideal engine volume inducted per second
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swept_volume = (displacement_SI * (RPM / 60)) / 2; //This equation is only valid for a four stroke engine
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//calculate volumetric efficiency - for now we will just use 0.8, but actually it is a function of engine speed and the exhaust to manifold pressure ratio
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//Note that this is cylinder vol eff - the throttle drop is already accounted for in the MAP calculation
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volumetric_efficiency = 0.8;
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//Now use volumetric efficiency to calculate actual air volume inducted per second
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v_dot_air = swept_volume * volumetric_efficiency;
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//Now calculate mass flow rate of air into engine
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m_dot_air = v_dot_air * rho_air_manifold;
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//cout << "air = " << m_dot_air;
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// cout << "rho air manifold " << rho_air_manifold << '\n';
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// cout << "Swept volume " << swept_volume << '\n';
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@ -385,13 +390,15 @@ void FGNewEngine::update() {
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//DCL - now calculate fuel flow into engine based on air flow and mixture lever position
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//assume lever runs from no flow at fully out to thi = 1.6 at fully in at sea level
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//***TODO*** - MUST try and get some real idea of the actual full rich sea level mixture - this is important !!!
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//also assume that the injector linkage is ideal - hence the set mixture is maintained at a given altitude throughout the speed and load range
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thi_sea_level = 1.6 * ( Mixture_Lever_Pos / 100.0 );
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equivalence_ratio = thi_sea_level * p_amb_sea_level / p_amb; //ie as we go higher the mixture gets richer for a given lever position
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m_dot_fuel = m_dot_air / 14.7 * equivalence_ratio;
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Fuel_Flow_gals_hr = (m_dot_fuel / rho_fuel) * 264.172 * 3600.0; // Note this assumes US gallons
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// cout << "fuel " << m_dot_fuel;
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// cout << " air " << m_dot_air << '\n';
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//cout << "fuel " << m_dot_fuel; << "kg/s " << Fuel_Flow_gals_hr << "gals/hr"
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//cout << " air " << m_dot_air << '\n';
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//***********************************************************************
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//Engine power and torque calculations
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@ -450,7 +457,7 @@ void FGNewEngine::update() {
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//***DCL - FIXME - this needs altering - for instance going richer than full power mixture decreases the %power but increases the fuel flow
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// Now Calculate Fuel Flow based on % Power Best Power Mixture
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Fuel_Flow = Percentage_Power * Max_Fuel_Flow / 100.0;
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// Fuel_Flow = Percentage_Power * Max_Fuel_Flow / 100.0;
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// cout << Fuel_Flow << " lbs/hr"<< endl;
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// Now Derate engine for the effects of Bad/Switched off magnetos
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@ -96,7 +96,7 @@ private:
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float Percentage_Power; // Power output as percentage of maximum power output
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float Manifold_Pressure; // Inches
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float RPM;
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float Fuel_Flow; // lbs/hour
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float Fuel_Flow_gals_hr; // gals/hour
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float Torque;
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float CHT; // Cylinder head temperature deg K
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float CHT_degF; // Ditto in deg Fahrenheit
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@ -128,6 +128,7 @@ private:
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float p_amb; // Pascals
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float T_amb; // deg Kelvin
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float calorific_value_fuel;
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float rho_fuel; // kg/m^3
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float thi_sea_level;
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float delta_T_exhaust;
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float displacement; // Engine displacement in cubic inches - to be read in from config file for each engine
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@ -232,6 +233,7 @@ public:
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inline float get_CHT() const { return CHT_degF; } // Note this returns CHT in Fahrenheit
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inline float get_prop_thrust_SI() const { return prop_thrust; }
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inline float get_prop_thrust_lbs() const { return (prop_thrust * 0.2248); }
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inline float get_fuel_flow_gals_hr() const { return (Fuel_Flow_gals_hr); }
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};
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@ -51,6 +51,10 @@ FGLaRCsim::FGLaRCsim( double dt ) {
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I_yy = 3.000000E+03;
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I_zz = 3.530000E+03;
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I_xz = 0.000000E+00;
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//current_aircraft.fdm_state->set_Tank1Fuel(15.0);
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//current_aircraft.fdm_state->set_Tank2Fuel(15.0);
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//Tank1Fuel = 15.0;
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//Tank2Fuel = 15.0;
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}
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FGLaRCsim::~FGLaRCsim(void) {
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@ -74,7 +78,13 @@ void FGLaRCsim::init() {
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// update the engines interface
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FGEngInterface e;
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add_engine( e );
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// Fill the fuel tanks
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// Hardwired to C172 full tanks for now - need to fix this sometime
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// Also note that this is the max quantity - the usable quantity
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// is slightly less
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set_Tank1Fuel(28.0);
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set_Tank2Fuel(28.0);
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// FG_LOG( FG_FLIGHT, FG_INFO, "FGLaRCsim::init()" );
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@ -134,6 +144,13 @@ bool FGLaRCsim::update( int multiloop ) {
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e->set_EGT( eng.get_EGT() );
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e->set_CHT( eng.get_CHT() );
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e->set_prop_thrust( eng.get_prop_thrust_SI() );
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e->set_Fuel_Flow( eng.get_fuel_flow_gals_hr() );
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//Assume we are using both tanks equally for now
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reduce_Tank1Fuel( (eng.get_fuel_flow_gals_hr() / (2 * 3600))
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* get_delta_t() );
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reduce_Tank2Fuel( (eng.get_fuel_flow_gals_hr() / (2 * 3600))
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* get_delta_t() );
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#if 0
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FG_LOG( FG_FLIGHT, FG_INFO, "Throttle = "
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@ -113,12 +113,13 @@ private:
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// outputs
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double RPM;
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double Manifold_Pressure;
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double Manifold_Pressure; //inches
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double MaxHP;
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double Percentage_Power;
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double EGT;
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double CHT;
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double prop_thrust;
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double Percentage_Power; //HP
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double EGT; //deg F
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double CHT; //deg F
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double prop_thrust; //lbs
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double Fuel_Flow; //Gals/hr
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/* others...
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double PercentN1,N1; //GE,CFM
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@ -145,6 +146,7 @@ public:
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inline double get_EGT() const { return EGT; }
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inline double get_CHT() const { return CHT; }
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inline double get_prop_thrust() const { return prop_thrust; }
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inline double get_Fuel_Flow() const { return Fuel_Flow; }
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inline void set_Throttle( double t ) { Throttle = t; }
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inline void set_Mixture( double m ) { Mixture = m; }
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@ -156,6 +158,7 @@ public:
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inline void set_EGT( double e ) { EGT = e; }
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inline void set_CHT( double c ) { CHT = c; }
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inline void set_prop_thrust( double t ) { prop_thrust = t; }
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inline void set_Fuel_Flow( double f ) { Fuel_Flow = f; }
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};
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@ -269,6 +272,8 @@ private:
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double sin_longitude, cos_longitude;
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double sin_latitude, cos_latitude;
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double altitude_agl;
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double Tank1Fuel; // Gals
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double Tank2Fuel; // Gals
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// Engine list
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engine_list engines;
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@ -541,7 +546,22 @@ public:
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virtual void set_Velocities_Local_Airmass (double wnorth,
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double weast,
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double wdown );
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// Consumables
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inline void set_Tank1Fuel( double f ) { Tank1Fuel = f; }
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inline void set_Tank2Fuel( double f ) { Tank2Fuel = f; }
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inline void reduce_Tank1Fuel( double f ) {
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Tank1Fuel -= f;
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if(Tank1Fuel < 0)
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Tank1Fuel = 0;
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}
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inline void reduce_Tank2Fuel( double f ) {
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Tank2Fuel -= f;
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if(Tank2Fuel < 0)
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Tank2Fuel = 0;
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}
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// ========== Mass properties and geometry values ==========
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@ -1079,6 +1099,10 @@ public:
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return cos_latitude;
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}
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// Consumables
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inline double get_Tank1Fuel() const { return Tank1Fuel; }
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inline double get_Tank2Fuel() const { return Tank2Fuel; }
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// engines
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inline double get_num_engines() const {
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return engines.size();
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@ -69,8 +69,8 @@ fgfs_LDADD = \
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$(top_builddir)/src/Time/libTime.a \
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$(WEATHER_LIBS) \
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$(top_builddir)/src/Joystick/libJoystick.a \
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-lsgroute -lsgsky -lsgephem -lsgtiming -lsgio -lsgscreen -lsgmath \
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-lsgbucket -lsgdebug -lsgmagvar -lsgmisc -lsgxml \
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-lsgroute -lsgsky -lsgephem -lsgmetar -lsgtiming -lsgio -lsgscreen \
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-lsgmath -lsgbucket -lsgdebug -lsgmagvar -lsgmisc -lsgxml \
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$(SERIAL_LIBS) \
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-lplibpu -lplibfnt -lplibssg -lplibsg \
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-lmk4 -lz \
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@ -190,6 +190,11 @@ FGBFI::init ()
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fgTie("/engines/engine0/egt", getEGT);
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fgTie("/engines/engine0/cht", getCHT);
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fgTie("/engines/engine0/mp", getMP);
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fgTie("/engines/engine0/fuel-flow", getFuelFlow);
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//consumables
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fgTie("/consumables/fuel/tank1/level", getTank1Fuel, setTank1Fuel, false);
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fgTie("/consumables/fuel/tank2/level", getTank2Fuel, setTank2Fuel, false);
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// Autopilot
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fgTie("/autopilot/locks/altitude", getAPAltitudeLock, setAPAltitudeLock);
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@ -322,7 +327,7 @@ FGBFI::setDateString (string date_string)
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mktime(&new_time) - mktime(current_time) + globals->get_warp();
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double lon = current_aircraft.fdm_state->get_Longitude();
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double lat = current_aircraft.fdm_state->get_Latitude();
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double alt = current_aircraft.fdm_state->get_Altitude() * FEET_TO_METER;
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// double alt = current_aircraft.fdm_state->get_Altitude() * FEET_TO_METER;
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globals->set_warp(warp);
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st->update(lon, lat, warp);
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fgUpdateSkyAndLightingParams();
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@ -560,7 +565,7 @@ FGBFI::getCHT ()
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/**
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* Return the current engine0 CHT.
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* Return the current engine0 Manifold Pressure.
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*/
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double
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FGBFI::getMP ()
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@ -572,6 +577,52 @@ FGBFI::getMP ()
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}
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}
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/**
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* Return the current engine0 fuel flow
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*/
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double
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FGBFI::getFuelFlow ()
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{
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if ( current_aircraft.fdm_state->get_engine(0) != NULL ) {
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return current_aircraft.fdm_state->get_engine(0)->get_Fuel_Flow();
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} else {
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return 0.0;
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}
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}
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////////////////////////////////////////////////////////////////////////
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// Consumables
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////////////////////////////////////////////////////////////////////////
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/**
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* Return the fuel level in tank 1
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*/
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double
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FGBFI::getTank1Fuel ()
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{
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return current_aircraft.fdm_state->get_Tank1Fuel();
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}
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void
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FGBFI::setTank1Fuel ( double gals )
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{
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current_aircraft.fdm_state->set_Tank1Fuel( gals );
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}
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/**
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* Return the fuel level in tank 2
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*/
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double
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FGBFI::getTank2Fuel ()
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{
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return current_aircraft.fdm_state->get_Tank2Fuel();
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}
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void
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FGBFI::setTank2Fuel ( double gals )
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{
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current_aircraft.fdm_state->set_Tank2Fuel( gals );
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}
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////////////////////////////////////////////////////////////////////////
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@ -1292,7 +1343,7 @@ FGBFI::setWindDown (double speed)
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double
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FGBFI::getFOV ()
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{
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globals->get_current_view()->get_fov();
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return globals->get_current_view()->get_fov();
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}
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void
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@ -101,9 +101,16 @@ public:
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static double getRPM (); // revolutions/minute
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static void setRPM ( double rpm ); // revolutions/minute
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static double getEGT (); // [unit??]
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static double getCHT (); // [unit??]
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static double getMP (); // [unit??]
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static double getEGT (); // deg Fahrenheit
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static double getCHT (); // deg Fahrenheit
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static double getMP (); // inches mercury
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static double getFuelFlow (); // gals/hr
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// Consumables
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static double getTank1Fuel (); // gals
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static void setTank1Fuel( double gals );
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static double getTank2Fuel (); // gals
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static void setTank2Fuel( double gals );
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// Velocities
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static double getAirspeed (); // knots
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Add table
Reference in a new issue