1 /**********************************************************************
3 FILENAME: uiuc_engine.cpp
5 ----------------------------------------------------------------------
7 DESCRIPTION: determine the engine forces and moments
9 ----------------------------------------------------------------------
13 ----------------------------------------------------------------------
15 REFERENCES: simple and c172 models based on portions of
16 c172_engine.c, called from ls_model;
17 cherokee model based on cherokee_engine.c
19 ----------------------------------------------------------------------
21 HISTORY: 01/30/2000 initial release
22 06/18/2001 (RD) Added Throttle_pct_input.
24 ----------------------------------------------------------------------
26 AUTHOR(S): Bipin Sehgal <bsehgal@uiuc.edu>
27 Jeff Scott <jscott@mail.com>
28 Robert Deters <rdeters@uiuc.edu>
29 Michael Selig <m-selig@uiuc.edu>
31 ----------------------------------------------------------------------
35 ----------------------------------------------------------------------
39 ----------------------------------------------------------------------
45 ----------------------------------------------------------------------
47 CALLED BY: uiuc_wrapper.cpp
49 ----------------------------------------------------------------------
53 ----------------------------------------------------------------------
55 COPYRIGHT: (C) 2000 by Michael Selig
57 This program is free software; you can redistribute it and/or
58 modify it under the terms of the GNU General Public License
59 as published by the Free Software Foundation.
61 This program is distributed in the hope that it will be useful,
62 but WITHOUT ANY WARRANTY; without even the implied warranty of
63 MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
64 GNU General Public License for more details.
66 You should have received a copy of the GNU General Public License
67 along with this program; if not, write to the Free Software
68 Foundation, Inc., 59 Temple Place - Suite 330, Boston, MA 02111-1307,
69 USA or view http://www.gnu.org/copyleft/gpl.html.
71 **********************************************************************/
72 #include <simgear/compiler.h>
74 #include "uiuc_engine.h"
84 if (outside_control == false)
85 pilot_throttle_no = false;
86 if (Throttle_pct_input)
88 double Throttle_pct_input_endTime = Throttle_pct_input_timeArray[Throttle_pct_input_ntime];
89 if (Simtime >= Throttle_pct_input_startTime &&
90 Simtime <= (Throttle_pct_input_startTime + Throttle_pct_input_endTime))
92 double time = Simtime - Throttle_pct_input_startTime;
93 Throttle_pct = uiuc_1Dinterpolation(Throttle_pct_input_timeArray,
94 Throttle_pct_input_dTArray,
95 Throttle_pct_input_ntime,
97 pilot_throttle_no = true;
101 Throttle[3] = Throttle_pct;
103 command_list = engineParts -> getCommands();
106 if (command_list.begin() == command_list.end())
108 cerr << "ERROR: Engine not specified. Aircraft cannot fly without the engine" << endl;
113 for (LIST command_line = command_list.begin(); command_line!=command_list.end(); ++command_line)
115 //cout << *command_line << endl;
117 linetoken1 = engineParts -> getToken(*command_line, 1);
118 linetoken2 = engineParts -> getToken(*command_line, 2);
120 switch(engine_map[linetoken2])
122 case simpleSingle_flag:
124 F_X_engine = Throttle[3] * simpleSingleMaxThrust;
127 case simpleSingleModel_flag:
129 /* simple model based on Hepperle's equation
130 * exponent dtdvvt was computed in uiuc_menu.cpp */
131 F_X_engine = Throttle[3] * t_v0 * (1 - pow((V_rel_wind/v_t0),dtdvvt));
132 if (b_slipstreamEffects) {
133 tc = F_X_engine/(Dynamic_pressure * LS_PI * propDia * propDia / 4);
134 w_induced = 0.5 * V_rel_wind * (-1 + pow((1+tc),.5));
135 eta_q = (2* w_induced + V_rel_wind)*(2* w_induced + V_rel_wind)/(V_rel_wind * V_rel_wind);
136 /* add in a die-off function so that eta falls off w/ alfa and beta */
137 eta_q = Cos_alpha * Cos_alpha * Cos_beta * Cos_beta * eta_q;
138 /* determine the eta_q values for the respective coefficients */
139 if (eta_q_Cm_q_fac) {eta_q_Cm_q *= eta_q * eta_q_Cm_q_fac;}
140 if (eta_q_Cm_adot_fac) {eta_q_Cm_adot *= eta_q * eta_q_Cm_adot_fac;}
141 if (eta_q_Cmfade_fac) {eta_q_Cmfade *= eta_q * eta_q_Cmfade_fac;}
142 if (eta_q_Cm_de_fac) {eta_q_Cm_de *= eta_q * eta_q_Cm_de_fac;}
143 if (eta_q_Cl_beta_fac) {eta_q_Cl_beta *= eta_q * eta_q_Cl_beta_fac;}
144 if (eta_q_Cl_p_fac) {eta_q_Cl_p *= eta_q * eta_q_Cl_p_fac;}
145 if (eta_q_Cl_r_fac) {eta_q_Cl_r *= eta_q * eta_q_Cl_r_fac;}
146 if (eta_q_Cl_dr_fac) {eta_q_Cl_dr *= eta_q * eta_q_Cl_dr_fac;}
147 if (eta_q_CY_beta_fac) {eta_q_CY_beta *= eta_q * eta_q_CY_beta_fac;}
148 if (eta_q_CY_p_fac) {eta_q_CY_p *= eta_q * eta_q_CY_p_fac;}
149 if (eta_q_CY_r_fac) {eta_q_CY_r *= eta_q * eta_q_CY_r_fac;}
150 if (eta_q_CY_dr_fac) {eta_q_CY_dr *= eta_q * eta_q_CY_dr_fac;}
151 if (eta_q_Cn_beta_fac) {eta_q_Cn_beta *= eta_q * eta_q_Cn_beta_fac;}
152 if (eta_q_Cn_p_fac) {eta_q_Cn_p *= eta_q * eta_q_Cn_p_fac;}
153 if (eta_q_Cn_r_fac) {eta_q_Cn_r *= eta_q * eta_q_Cn_r_fac;}
154 if (eta_q_Cn_dr_fac) {eta_q_Cn_dr *= eta_q * eta_q_Cn_dr_fac;}
156 /* Need engineOmega for gyroscopic moments */
157 engineOmega = minOmega + Throttle[3] * (maxOmega - minOmega);
162 //c172 engine lines ... looks like 0.83 is just a thrust increase
163 F_X_engine = Throttle[3] * 350 / 0.83;
164 F_Z_engine = Throttle[3] * 4.9 / 0.83;
165 M_m_engine = F_X_engine * 0.734 * cbar;
171 dP = (180.0-117.0)*745.7, // Watts
172 dn = (2700.0-2350.0)/60.0, // d_rpm (I mean d_rps, in seconds)
173 D = 6.17*0.3048, // prop diameter
174 dPh = (58.0-180.0)*745.7, // change of power as function of height
180 J, // advance ratio (ratio of horizontal speed to prop tip speed)
184 eta_engine; // engine efficiency
186 /* assumption -> 0.0 <= Throttle[3] <=1.0 */
187 P = fabs(Throttle[3]) * 180.0 * 745.7; /*180.0*745.7 ->max avail power [W]*/
188 n = dn/dP * (P-117.0*745.7) + 2350.0/60.0;
191 V = (V_rel_wind < 10.0 ? 10.0 : V_rel_wind*0.3048);
194 /* Propeller efficiency */
195 eta_engine = (J < 0.7 ? ((0.8-0.55)/(.7-.3)*(J-0.3) + 0.55) :
196 (J > 0.85 ? ((0.6-0.8)/(1.0-0.85)*(J-0.85) + 0.8) : 0.8));
198 /* power on Altitude */
199 H = Altitude * 0.3048; /* H == Altitude [m] */
200 P *= (dPh/dH * H + 180.0*745.7) / (180.0*745.7);
201 T = eta_engine * P/V; /* Thrust [N] */
203 /*assumption: Engine's line of thrust passes through cg */
204 F_X_engine = T * 0.2248; /* F_X_engine in lb */
211 double Xp_input_endTime = Xp_input_timeArray[Xp_input_ntime];
212 if (Simtime >= Xp_input_startTime &&
213 Simtime <= (Xp_input_startTime + Xp_input_endTime))
215 double time = Simtime - Xp_input_startTime;
216 F_X_engine = uiuc_1Dinterpolation(Xp_input_timeArray,
221 double Zp_input_endTime = Zp_input_timeArray[Zp_input_ntime];
222 if (Simtime >= Zp_input_startTime &&
223 Simtime <= (Zp_input_startTime + Zp_input_endTime))
225 double time = Simtime - Zp_input_startTime;
226 F_Z_engine = uiuc_1Dinterpolation(Zp_input_timeArray,
231 double Mp_input_endTime = Mp_input_timeArray[Mp_input_ntime];
232 if (Simtime >= Mp_input_startTime &&
233 Simtime <= (Mp_input_startTime + Mp_input_endTime))
235 double time = Simtime - Mp_input_startTime;
236 M_m_engine = uiuc_1Dinterpolation(Mp_input_timeArray,
247 // end uiuc_engine.cpp