1 /**********************************************************************
3 FILENAME: uiuc_coef_roll.cpp
5 ----------------------------------------------------------------------
7 DESCRIPTION: computes aggregated aerodynamic roll coefficient
9 ----------------------------------------------------------------------
13 ----------------------------------------------------------------------
15 REFERENCES: Roskam, Jan. Airplane Flight Dynamics and Automatic
16 Flight Controls, Part I. Lawrence, KS: DARcorporation,
19 ----------------------------------------------------------------------
21 HISTORY: 04/15/2000 initial release
22 10/25/2001 (RD) Added new variables needed for the non-
23 linear Twin Otter model at zero flaps
25 11/12/2001 (RD) Added new variables needed for the non-
26 linear Twin Otter model with flaps
27 (Clfxxf). Zero flap vairables removed.
28 02/13/2002 (RD) Added variables so linear aero model
29 values can be recorded
30 02/18/2002 (RD) Added uiuc_3Dinterp_quick() function
31 for a quicker 3D interpolation. Takes
32 advantage of "nice" data.
34 ----------------------------------------------------------------------
36 AUTHOR(S): Bipin Sehgal <bsehgal@uiuc.edu>
37 Jeff Scott <jscott@mail.com>
38 Robert Deters <rdeters@uiuc.edu>
40 ----------------------------------------------------------------------
44 ----------------------------------------------------------------------
49 -roll coefficient components
53 ----------------------------------------------------------------------
57 ----------------------------------------------------------------------
59 CALLED BY: uiuc_coefficients.cpp
61 ----------------------------------------------------------------------
63 CALLS TO: uiuc_1Dinterpolation
69 ----------------------------------------------------------------------
71 COPYRIGHT: (C) 2000 by Michael Selig
73 This program is free software; you can redistribute it and/or
74 modify it under the terms of the GNU General Public License
75 as published by the Free Software Foundation.
77 This program is distributed in the hope that it will be useful,
78 but WITHOUT ANY WARRANTY; without even the implied warranty of
79 MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
80 GNU General Public License for more details.
82 You should have received a copy of the GNU General Public License
83 along with this program; if not, write to the Free Software
84 Foundation, Inc., 59 Temple Place - Suite 330, Boston, MA 02111-1307,
85 USA or view http://www.gnu.org/copyleft/gpl.html.
87 **********************************************************************/
89 #include "uiuc_coef_roll.h"
101 command_list = aeroRollParts -> getCommands();
103 for (LIST command_line = command_list.begin(); command_line!=command_list.end(); ++command_line)
105 linetoken1 = aeroRollParts -> getToken(*command_line, 1);
106 linetoken2 = aeroRollParts -> getToken(*command_line, 2);
108 switch(Cl_map[linetoken2])
114 Clo = uiuc_ice_filter(Clo_clean,kClo);
124 Cl_beta = uiuc_ice_filter(Cl_beta_clean,kCl_beta);
126 Cl_beta_save = Cl_beta * Beta;
127 Cl += Cl_beta * Beta;
134 Cl_p = uiuc_ice_filter(Cl_p_clean,kCl_p);
136 /* Cl_p must be mulitplied by b/2U
137 (see Roskam Control book, Part 1, pg. 147) */
138 Cl_p_save = Cl_p * P_body * b_2U;
139 Cl += Cl_p * P_body * b_2U;
146 Cl_r = uiuc_ice_filter(Cl_r_clean,kCl_r);
148 /* Cl_r must be mulitplied by b/2U
149 (see Roskam Control book, Part 1, pg. 147) */
150 Cl_r_save = Cl_r * R_body * b_2U;
151 Cl += Cl_r * R_body * b_2U;
158 Cl_da = uiuc_ice_filter(Cl_da_clean,kCl_da);
160 Cl_da_save = Cl_da * aileron;
161 Cl += Cl_da * aileron;
168 Cl_dr = uiuc_ice_filter(Cl_dr_clean,kCl_dr);
170 Cl_dr_save = Cl_dr * rudder;
171 Cl += Cl_dr * rudder;
178 Cl_daa = uiuc_ice_filter(Cl_daa_clean,kCl_daa);
180 Cl_daa_save = Cl_daa * aileron * Alpha;
181 Cl += Cl_daa * aileron * Alpha;
186 ClfadaI = uiuc_2Dinterpolation(Clfada_aArray,
198 ClfbetadrI = uiuc_2Dinterpolation(Clfbetadr_betaArray,
201 Clfbetadr_nBetaArray,
210 if (Clfabetaf_nice == 1)
211 ClfabetafI = uiuc_3Dinterp_quick(Clfabetaf_fArray,
212 Clfabetaf_aArray_nice,
213 Clfabetaf_bArray_nice,
222 ClfabetafI = uiuc_3Dinterpolation(Clfabetaf_fArray,
226 Clfabetaf_nAlphaArray,
237 if (Clfadaf_nice == 1)
238 ClfadafI = uiuc_3Dinterp_quick(Clfadaf_fArray,
240 Clfadaf_daArray_nice,
249 ClfadafI = uiuc_3Dinterpolation(Clfadaf_fArray,
264 if (Clfadrf_nice == 1)
265 ClfadrfI = uiuc_3Dinterp_quick(Clfadrf_fArray,
267 Clfadrf_drArray_nice,
276 ClfadrfI = uiuc_3Dinterpolation(Clfadrf_fArray,
291 p_nondim = P_body * b_2U;
292 if (Clfapf_nice == 1)
293 ClfapfI = uiuc_3Dinterp_quick(Clfapf_fArray,
304 ClfapfI = uiuc_3Dinterpolation(Clfapf_fArray,
319 r_nondim = R_body * b_2U;
320 if (Clfarf_nice == 1)
321 ClfarfI = uiuc_3Dinterp_quick(Clfarf_fArray,
332 ClfarfI = uiuc_3Dinterpolation(Clfarf_fArray,
351 // end uiuc_coef_roll.cpp