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flightgear/src/FDM/UIUCModel/uiuc_coef_roll.cpp

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/**********************************************************************
FILENAME: uiuc_coef_roll.cpp
----------------------------------------------------------------------
DESCRIPTION: computes aggregated aerodynamic roll coefficient
----------------------------------------------------------------------
STATUS: alpha version
----------------------------------------------------------------------
REFERENCES: Roskam, Jan. Airplane Flight Dynamics and Automatic
Flight Controls, Part I. Lawrence, KS: DARcorporation,
1995.
----------------------------------------------------------------------
HISTORY: 04/15/2000 initial release
10/25/2001 (RD) Added new variables needed for the non-
linear Twin Otter model at zero flaps
(Clfxxf0)
11/12/2001 (RD) Added new variables needed for the non-
linear Twin Otter model with flaps
(Clfxxf). Zero flap vairables removed.
02/13/2002 (RD) Added variables so linear aero model
values can be recorded
02/18/2002 (RD) Added uiuc_3Dinterp_quick() function
for a quicker 3D interpolation. Takes
advantage of "nice" data.
----------------------------------------------------------------------
AUTHOR(S): Bipin Sehgal <bsehgal@uiuc.edu>
Jeff Scott <jscott@mail.com>
Robert Deters <rdeters@uiuc.edu>
----------------------------------------------------------------------
VARIABLES:
----------------------------------------------------------------------
INPUTS: -Alpha
-aileron
-rudder
-roll coefficient components
-icing parameters
-b_2U multiplier
----------------------------------------------------------------------
OUTPUTS: -Cl
----------------------------------------------------------------------
CALLED BY: uiuc_coefficients.cpp
----------------------------------------------------------------------
CALLS TO: uiuc_1Dinterpolation
uiuc_2Dinterpolation
uiuc_ice_filter
uiuc_3Dinterpolation
uiuc_3Dinterp_quick
----------------------------------------------------------------------
COPYRIGHT: (C) 2000 by Michael Selig
This program is free software; you can redistribute it and/or
modify it under the terms of the GNU General Public License
as published by the Free Software Foundation.
This program is distributed in the hope that it will be useful,
but WITHOUT ANY WARRANTY; without even the implied warranty of
MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
GNU General Public License for more details.
You should have received a copy of the GNU General Public License
along with this program; if not, write to the Free Software
Foundation, Inc., 51 Franklin Street, Fifth Floor, Boston, MA 02110-1301, USA.
**********************************************************************/
#include "uiuc_coef_roll.h"
void uiuc_coef_roll()
{
string linetoken1;
string linetoken2;
stack command_list;
double p_nondim;
double r_nondim;
command_list = aeroRollParts -> getCommands();
for (LIST command_line = command_list.begin(); command_line!=command_list.end(); ++command_line)
{
linetoken1 = aeroRollParts -> getToken(*command_line, 1);
linetoken2 = aeroRollParts -> getToken(*command_line, 2);
switch(Cl_map[linetoken2])
{
case Clo_flag:
{
if (ice_on)
{
Clo = uiuc_ice_filter(Clo_clean,kClo);
}
Clo_save = Clo;
Cl += Clo_save;
break;
}
case Cl_beta_flag:
{
if (ice_on)
{
Cl_beta = uiuc_ice_filter(Cl_beta_clean,kCl_beta);
}
Cl_beta_save = Cl_beta * Std_Beta;
if (eta_q_Cl_beta_fac)
{
Cl += Cl_beta_save * eta_q_Cl_beta_fac;
}
else
{
Cl += Cl_beta_save;
}
break;
}
case Cl_p_flag:
{
if (ice_on)
{
Cl_p = uiuc_ice_filter(Cl_p_clean,kCl_p);
}
/* Cl_p must be mulitplied by b/2U
(see Roskam Control book, Part 1, pg. 147) */
Cl_p_save = Cl_p * P_body * b_2U;
// if (Cl_p_save > 0.1) {
// Cl_p_save = 0.1;
// }
// if (Cl_p_save < -0.1) {
// Cl_p_save = -0.1;
// }
if (eta_q_Cl_p_fac)
{
Cl += Cl_p_save * eta_q_Cl_p_fac;
}
else
{
Cl += Cl_p_save;
}
break;
}
case Cl_r_flag:
{
if (ice_on)
{
Cl_r = uiuc_ice_filter(Cl_r_clean,kCl_r);
}
/* Cl_r must be mulitplied by b/2U
(see Roskam Control book, Part 1, pg. 147) */
Cl_r_save = Cl_r * R_body * b_2U;
if (eta_q_Cl_r_fac)
{
Cl += Cl_r_save * eta_q_Cl_r_fac;
}
else
{
Cl += Cl_r_save;
}
break;
}
case Cl_da_flag:
{
if (ice_on)
{
Cl_da = uiuc_ice_filter(Cl_da_clean,kCl_da);
}
Cl_da_save = Cl_da * aileron;
Cl += Cl_da_save;
break;
}
case Cl_dr_flag:
{
if (ice_on)
{
Cl_dr = uiuc_ice_filter(Cl_dr_clean,kCl_dr);
}
Cl_dr_save = Cl_dr * rudder;
if (eta_q_Cl_dr_fac)
{
Cl += Cl_dr_save * eta_q_Cl_dr_fac;
}
else
{
Cl += Cl_dr_save;
}
break;
}
case Cl_daa_flag:
{
if (ice_on)
{
Cl_daa = uiuc_ice_filter(Cl_daa_clean,kCl_daa);
}
Cl_daa_save = Cl_daa * aileron * Std_Alpha;
Cl += Cl_daa_save;
break;
}
case Clfada_flag:
{
ClfadaI = uiuc_2Dinterpolation(Clfada_aArray,
Clfada_daArray,
Clfada_ClArray,
Clfada_nAlphaArray,
Clfada_nda,
Std_Alpha,
aileron);
Cl += ClfadaI;
break;
}
case Clfbetadr_flag:
{
ClfbetadrI = uiuc_2Dinterpolation(Clfbetadr_betaArray,
Clfbetadr_drArray,
Clfbetadr_ClArray,
Clfbetadr_nBetaArray,
Clfbetadr_ndr,
Std_Beta,
rudder);
Cl += ClfbetadrI;
break;
}
case Clfabetaf_flag:
{
if (Clfabetaf_nice == 1)
ClfabetafI = uiuc_3Dinterp_quick(Clfabetaf_fArray,
Clfabetaf_aArray_nice,
Clfabetaf_bArray_nice,
Clfabetaf_ClArray,
Clfabetaf_na_nice,
Clfabetaf_nb_nice,
Clfabetaf_nf,
flap_pos,
Std_Alpha,
Std_Beta);
else
ClfabetafI = uiuc_3Dinterpolation(Clfabetaf_fArray,
Clfabetaf_aArray,
Clfabetaf_betaArray,
Clfabetaf_ClArray,
Clfabetaf_nAlphaArray,
Clfabetaf_nbeta,
Clfabetaf_nf,
flap_pos,
Std_Alpha,
Std_Beta);
Cl += ClfabetafI;
break;
}
case Clfadaf_flag:
{
if (Clfadaf_nice == 1)
ClfadafI = uiuc_3Dinterp_quick(Clfadaf_fArray,
Clfadaf_aArray_nice,
Clfadaf_daArray_nice,
Clfadaf_ClArray,
Clfadaf_na_nice,
Clfadaf_nda_nice,
Clfadaf_nf,
flap_pos,
Std_Alpha,
aileron);
else
ClfadafI = uiuc_3Dinterpolation(Clfadaf_fArray,
Clfadaf_aArray,
Clfadaf_daArray,
Clfadaf_ClArray,
Clfadaf_nAlphaArray,
Clfadaf_nda,
Clfadaf_nf,
flap_pos,
Std_Alpha,
aileron);
Cl += ClfadafI;
break;
}
case Clfadrf_flag:
{
if (Clfadrf_nice == 1)
ClfadrfI = uiuc_3Dinterp_quick(Clfadrf_fArray,
Clfadrf_aArray_nice,
Clfadrf_drArray_nice,
Clfadrf_ClArray,
Clfadrf_na_nice,
Clfadrf_ndr_nice,
Clfadrf_nf,
flap_pos,
Std_Alpha,
rudder);
else
ClfadrfI = uiuc_3Dinterpolation(Clfadrf_fArray,
Clfadrf_aArray,
Clfadrf_drArray,
Clfadrf_ClArray,
Clfadrf_nAlphaArray,
Clfadrf_ndr,
Clfadrf_nf,
flap_pos,
Std_Alpha,
rudder);
Cl += ClfadrfI;
break;
}
case Clfapf_flag:
{
p_nondim = P_body * b_2U;
if (Clfapf_nice == 1)
ClfapfI = uiuc_3Dinterp_quick(Clfapf_fArray,
Clfapf_aArray_nice,
Clfapf_pArray_nice,
Clfapf_ClArray,
Clfapf_na_nice,
Clfapf_np_nice,
Clfapf_nf,
flap_pos,
Std_Alpha,
p_nondim);
else
ClfapfI = uiuc_3Dinterpolation(Clfapf_fArray,
Clfapf_aArray,
Clfapf_pArray,
Clfapf_ClArray,
Clfapf_nAlphaArray,
Clfapf_np,
Clfapf_nf,
flap_pos,
Std_Alpha,
p_nondim);
Cl += ClfapfI;
break;
}
case Clfarf_flag:
{
r_nondim = R_body * b_2U;
if (Clfarf_nice == 1)
ClfarfI = uiuc_3Dinterp_quick(Clfarf_fArray,
Clfarf_aArray_nice,
Clfarf_rArray_nice,
Clfarf_ClArray,
Clfarf_na_nice,
Clfarf_nr_nice,
Clfarf_nf,
flap_pos,
Std_Alpha,
r_nondim);
else
ClfarfI = uiuc_3Dinterpolation(Clfarf_fArray,
Clfarf_aArray,
Clfarf_rArray,
Clfarf_ClArray,
Clfarf_nAlphaArray,
Clfarf_nr,
Clfarf_nf,
flap_pos,
Std_Alpha,
r_nondim);
Cl += ClfarfI;
break;
}
};
} // end Cl map
return;
}
// end uiuc_coef_roll.cpp
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