2 // Author: Phil Schubert
3 // Date started: 12/03/99
4 // Purpose: Models a Continental IO-520-M Engine
5 // Called by: FGSimExec
7 // Copyright (C) 1999 Philip L. Schubert (philings@ozemail.com.au)
9 // This program is free software; you can redistribute it and/or
10 // modify it under the terms of the GNU General Public License as
11 // published by the Free Software Foundation; either version 2 of the
12 // License, or (at your option) any later version.
14 // This program is distributed in the hope that it will be useful, but
15 // WITHOUT ANY WARRANTY; without even the implied warranty of
16 // MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU
17 // General Public License for more details.
19 // You should have received a copy of the GNU General Public License
20 // along with this program; if not, write to the Free Software
21 // Foundation, Inc., 59 Temple Place - Suite 330, Boston, MA
24 // Further information about the GNU General Public License can also
25 // be found on the world wide web at http://www.gnu.org.
27 // FUNCTIONAL DESCRIPTION
28 // ------------------------------------------------------------------------
29 // Models a Continental IO-520-M engine. This engine is used in Cessna
30 // 210, 310, Beechcraft Bonaza and Baron C55. The equations used below
31 // were determined by a first and second order curve fits using Excel.
32 // The data is from the Cessna Aircraft Corporations Engine and Flight
33 // Computer for C310. Part Number D3500-13
36 // ------------------------------------------------------------------------
40 // ------------------------------------------------------------------------
41 // 12/03/99 PLS Created
42 // 07/03/99 PLS Added Calculation of Density, and Prop_Torque
43 // 07/03/99 PLS Restructered Variables to allow easier implementation
45 // 15/03/99 PLS Added Oil Pressure, Oil Temperature and CH Temp
46 // ------------------------------------------------------------------------
48 // ------------------------------------------------------------------------
53 #define NEVS_PROP_MODEL
55 #ifndef NEVS_PROP_MODEL
56 #define PHILS_PROP_MODEL
71 float CONVERT_HP_TO_WATTS;
72 float CONVERT_CUBIC_INCHES_TO_METERS_CUBED;
74 // Control and environment inputs
76 // 0 = Closed, 100 = Fully Open
77 float Throttle_Lever_Pos;
78 // 0 = Full Course 100 = Full Fine
79 float Propeller_Lever_Pos;
80 // 0 = Idle Cut Off 100 = Full Rich
81 float Mixture_Lever_Pos;
83 // Engine Specific Variables used by this program that have limits.
84 // Will be set in a parameter file to be read in to create
85 // and instance for each engine.
86 float Max_Manifold_Pressure; //will be lower than ambient pressure for a non turbo/super charged engine due to losses through the throttle. This is the sea level full throttle value.
87 float Min_Manifold_Pressure; //Closed throttle valueat idle - governed by the idle bypass valve
91 float Mag_Derate_Percent;
95 // Initialise Engine Variables used by this instance
96 float Percentage_Power; // Power output as percentage of maximum power output
97 float Manifold_Pressure; // Inches
99 float Fuel_Flow; // lbs/hour
101 float CHT; // Cylinder head temperature
102 float EGT; // Exhaust gas temperature
104 float Oil_Pressure; // PSI
105 float Oil_Temp; // Deg C
106 float HP; // Current power output in HP
107 float Power_SI; // Current power output in Watts
108 float Torque_SI; // Torque in Nm
110 float Torque_Imbalance;
111 float Desired_RPM; // The RPM that we wish the constant speed prop to maintain if possible
112 bool started; //flag to indicate the engine is running self sustaining
113 bool cranking; //flag to indicate the engine is being cranked
116 float volumetric_efficiency;
117 float combustion_efficiency;
118 float equivalence_ratio;
123 float True_Manifold_Pressure; //in Hg
124 float rho_air_manifold;
126 float p_amb_sea_level; // Pascals
127 float p_amb; // Pascals
128 float T_amb; // deg Kelvin
129 float calorific_value_fuel;
131 float delta_T_exhaust;
132 float displacement; // Engine displacement in cubic inches - to be read in from config file for each engine
133 float displacement_SI; // ditto in meters cubed
134 float Cp_air; // J/KgK
135 float Cp_fuel; // J/KgK
136 float heat_capacity_exhaust;
137 float enthalpy_exhaust;
138 float Percentage_of_best_power_mixture_power;
139 float abstract_mixture; //temporary hack
140 float engine_inertia; //kg.m^2
141 float prop_inertia; //kg.m^2
142 float angular_acceleration; //rad/s^2
145 // Initialise Propellor Variables used by this instance
146 float FGProp1_Angular_V;
147 float FGProp1_Coef_Drag;
148 float FGProp1_Torque;
149 float FGProp1_Thrust;
151 float FGProp1_Coef_Lift;
153 float FGProp1_Blade_Angle;
154 float FGProp_Fine_Pitch_Stop;
156 #ifdef NEVS_PROP_MODEL
157 //Extra Propellor variables used by Nev's prop model
158 float prop_fudge_factor;
159 float prop_torque; //Nm
162 float allowance_for_spinner;
165 float number_of_blades;
166 float forward_velocity;
167 float angular_velocity_SI;
171 float element_torque;
173 float prop_power_consumed_SI;
174 float prop_power_consumed_HP;
175 float theta[6]; //prop angle of each element
176 #endif // NEVS_PROP_MODEL
178 // Other internal values
181 // Calculate Engine RPM based on Propellor Lever Position
182 float Calc_Engine_RPM (float Position);
184 // Calculate combustion efficiency based on equivalence ratio
185 float Lookup_Combustion_Efficiency(float thi_actual);
187 // Calculate exhaust gas temperature rise
188 float Calculate_Delta_T_Exhaust(void);
196 // outfile.open("FGEngine.dat", ios::out|ios::trunc);
204 // set initial default values
205 void init(double dt);
207 // update the engine model based on current control positions
210 inline void set_IAS( float value ) { IAS = value; }
211 inline void set_Throttle_Lever_Pos( float value ) {
212 Throttle_Lever_Pos = value;
214 inline void set_Propeller_Lever_Pos( float value ) {
215 Propeller_Lever_Pos = value;
217 inline void set_Mixture_Lever_Pos( float value ) {
218 Mixture_Lever_Pos = value;
222 inline float get_RPM() const { return RPM; }
223 inline float get_Manifold_Pressure() const { return Manifold_Pressure; }
224 inline float get_FGProp1_Thrust() const { return FGProp1_Thrust; }
225 inline float get_FGProp1_Blade_Angle() const { return FGProp1_Blade_Angle; }
227 inline float get_Rho() const { return Rho; }
228 inline float get_MaxHP() const { return MaxHP; }
229 inline float get_Percentage_Power() const { return Percentage_Power; }
230 inline float get_EGT() const { return EGT; }
231 inline float get_prop_thrust_SI() const { return prop_thrust; }
235 #endif // _10520D_HXX_