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flightgear/src/FDM/UIUCModel/uiuc_coef_pitch.cpp

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/**********************************************************************
FILENAME: uiuc_coef_pitch.cpp
----------------------------------------------------------------------
DESCRIPTION: computes aggregated aerodynamic pitch 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
(Cmfxxf0)
11/12/2001 (RD) Added new variables needed for the non-
linear Twin Otter model with flaps
(Cmfxxf). 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
-elevator
-pitch coefficient components
-icing parameters
-cbar_2U multiplier
----------------------------------------------------------------------
OUTPUTS: -Cm
----------------------------------------------------------------------
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., 59 Temple Place - Suite 330, Boston, MA 02111-1307,
USA or view http://www.gnu.org/copyleft/gpl.html.
**********************************************************************/
#include "uiuc_coef_pitch.h"
void uiuc_coef_pitch()
{
string linetoken1;
string linetoken2;
stack command_list;
double q_nondim;
command_list = aeroPitchParts -> getCommands();
for (LIST command_line = command_list.begin(); command_line!=command_list.end(); ++command_line)
{
linetoken1 = aeroPitchParts -> getToken(*command_line, 1);
linetoken2 = aeroPitchParts -> getToken(*command_line, 2);
switch(Cm_map[linetoken2])
{
case Cmo_flag:
{
if (ice_on)
{
Cmo = uiuc_ice_filter(Cmo_clean,kCmo);
}
Cmo_save = Cmo;
Cm += Cmo_save;
break;
}
case Cm_a_flag:
{
if (ice_on)
{
Cm_a = uiuc_ice_filter(Cm_a_clean,kCm_a);
}
Cm_a_save = Cm_a * Std_Alpha;
Cm += Cm_a_save;
break;
}
case Cm_a2_flag:
{
if (ice_on)
{
Cm_a2 = uiuc_ice_filter(Cm_a2_clean,kCm_a2);
}
Cm_a2_save = Cm_a2 * Std_Alpha * Std_Alpha;
Cm += Cm_a2_save;
break;
}
case Cm_adot_flag:
{
if (ice_on)
{
Cm_adot = uiuc_ice_filter(Cm_adot_clean,kCm_adot);
}
/* Cm_adot must be mulitplied by cbar/2U
(see Roskam Control book, Part 1, pg. 147) */
Cm_adot_save = Cm_adot * Std_Alpha_dot * cbar_2U;
if (eta_q_Cm_adot_fac)
{
Cm += Cm_adot_save * eta_q_Cm_adot_fac;
}
else
{
Cm += Cm_adot_save;
}
break;
}
case Cm_q_flag:
{
if (ice_on)
{
Cm_q = uiuc_ice_filter(Cm_q_clean,kCm_q);
}
/* Cm_q must be mulitplied by cbar/2U
(see Roskam Control book, Part 1, pg. 147) */
Cm_q_save = Cm_q * Q_body * cbar_2U;
if (eta_q_Cm_q_fac)
{
Cm += Cm_q_save * eta_q_Cm_q_fac;
}
else
{
Cm += Cm_q_save;
}
break;
}
case Cm_ih_flag:
{
Cm_ih_save = Cm_ih * ih;
Cm += Cm_ih_save;
break;
}
case Cm_de_flag:
{
if (ice_on)
{
Cm_de = uiuc_ice_filter(Cm_de_clean,kCm_de);
}
Cm_de_save = Cm_de * elevator;
if (eta_q_Cm_de_fac)
{
Cm += Cm_de_save * eta_q_Cm_de_fac;
}
else
{
Cm += Cm_de_save;
}
break;
}
case Cm_b2_flag:
{
if (ice_on)
{
Cm_b2 = uiuc_ice_filter(Cm_b2_clean,kCm_b2);
}
Cm_b2_save = Cm_b2 * Std_Beta * Std_Beta;
Cm += Cm_b2_save;
break;
}
case Cm_r_flag:
{
if (ice_on)
{
Cm_r = uiuc_ice_filter(Cm_r_clean,kCm_r);
}
Cm_r_save = Cm_r * R_body * b_2U;
Cm += Cm_r_save;
break;
}
case Cm_df_flag:
{
if (ice_on)
{
Cm_df = uiuc_ice_filter(Cm_df_clean,kCm_df);
}
Cm_df_save = Cm_df * flap_pos;
Cm += Cm_df_save;
break;
}
case Cm_ds_flag:
{
Cm_ds_save = Cm_ds * spoiler_pos;
Cm += Cm_ds_save;
break;
}
case Cm_dg_flag:
{
Cm_dg_save = Cm_dg * gear_pos_norm;
Cm += Cm_dg_save;
break;
}
case Cmfa_flag:
{
CmfaI = uiuc_1Dinterpolation(Cmfa_aArray,
Cmfa_CmArray,
Cmfa_nAlpha,
Std_Alpha);
Cm += CmfaI;
break;
}
case Cmfade_flag:
{
if(b_downwashMode)
{
// compute the induced velocity on the tail to account for tail downwash
switch(downwashMode)
{
case 100:
if (V_rel_wind < dyn_on_speed)
{
alphaTail = Std_Alpha;
}
else
{
gammaWing = V_rel_wind * Sw * CL / (2.0 * bw);
// printf("gammaWing = %.4f\n", (gammaWing));
downwash = downwashCoef * gammaWing;
downwashAngle = atan(downwash/V_rel_wind);
alphaTail = Std_Alpha - downwashAngle;
}
CmfadeI = uiuc_2Dinterpolation(Cmfade_aArray,
Cmfade_deArray,
Cmfade_CmArray,
Cmfade_nAlphaArray,
Cmfade_nde,
alphaTail,
elevator);
break;
}
}
else
{
CmfadeI = uiuc_2Dinterpolation(Cmfade_aArray,
Cmfade_deArray,
Cmfade_CmArray,
Cmfade_nAlphaArray,
Cmfade_nde,
Std_Alpha,
elevator);
}
if (eta_q_Cmfade_fac)
{
Cm += CmfadeI * eta_q_Cmfade_fac;
}
else
{
Cm += CmfadeI;
}
break;
}
case Cmfdf_flag:
{
CmfdfI = uiuc_1Dinterpolation(Cmfdf_dfArray,
Cmfdf_CmArray,
Cmfdf_ndf,
flap_pos);
Cm += CmfdfI;
break;
}
case Cmfadf_flag:
{
CmfadfI = uiuc_2Dinterpolation(Cmfadf_aArray,
Cmfadf_dfArray,
Cmfadf_CmArray,
Cmfadf_nAlphaArray,
Cmfadf_ndf,
Std_Alpha,
flap_pos);
Cm += CmfadfI;
break;
}
case Cmfabetaf_flag:
{
if (Cmfabetaf_nice == 1)
CmfabetafI = uiuc_3Dinterp_quick(Cmfabetaf_fArray,
Cmfabetaf_aArray_nice,
Cmfabetaf_bArray_nice,
Cmfabetaf_CmArray,
Cmfabetaf_na_nice,
Cmfabetaf_nb_nice,
Cmfabetaf_nf,
flap_pos,
Std_Alpha,
Std_Beta);
else
CmfabetafI = uiuc_3Dinterpolation(Cmfabetaf_fArray,
Cmfabetaf_aArray,
Cmfabetaf_betaArray,
Cmfabetaf_CmArray,
Cmfabetaf_nAlphaArray,
Cmfabetaf_nbeta,
Cmfabetaf_nf,
flap_pos,
Std_Alpha,
Std_Beta);
Cm += CmfabetafI;
break;
}
case Cmfadef_flag:
{
if (Cmfadef_nice == 1)
CmfadefI = uiuc_3Dinterp_quick(Cmfadef_fArray,
Cmfadef_aArray_nice,
Cmfadef_deArray_nice,
Cmfadef_CmArray,
Cmfadef_na_nice,
Cmfadef_nde_nice,
Cmfadef_nf,
flap_pos,
Std_Alpha,
elevator);
else
CmfadefI = uiuc_3Dinterpolation(Cmfadef_fArray,
Cmfadef_aArray,
Cmfadef_deArray,
Cmfadef_CmArray,
Cmfadef_nAlphaArray,
Cmfadef_nde,
Cmfadef_nf,
flap_pos,
Std_Alpha,
elevator);
Cm += CmfadefI;
break;
}
case Cmfaqf_flag:
{
q_nondim = Q_body * cbar_2U;
if (Cmfaqf_nice == 1)
CmfaqfI = uiuc_3Dinterp_quick(Cmfaqf_fArray,
Cmfaqf_aArray_nice,
Cmfaqf_qArray_nice,
Cmfaqf_CmArray,
Cmfaqf_na_nice,
Cmfaqf_nq_nice,
Cmfaqf_nf,
flap_pos,
Std_Alpha,
q_nondim);
else
CmfaqfI = uiuc_3Dinterpolation(Cmfaqf_fArray,
Cmfaqf_aArray,
Cmfaqf_qArray,
Cmfaqf_CmArray,
Cmfaqf_nAlphaArray,
Cmfaqf_nq,
Cmfaqf_nf,
flap_pos,
Std_Alpha,
q_nondim);
Cm += CmfaqfI;
break;
}
};
} // end Cm map
return;
}
// end uiuc_coef_pitch.cpp
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