190 lines
5.6 KiB
C++
190 lines
5.6 KiB
C++
/**********************************************************************
|
|
|
|
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
|
|
|
|
----------------------------------------------------------------------
|
|
|
|
AUTHOR(S): Bipin Sehgal <bsehgal@uiuc.edu>
|
|
Jeff Scott <jscott@mail.com>
|
|
|
|
----------------------------------------------------------------------
|
|
|
|
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
|
|
|
|
----------------------------------------------------------------------
|
|
|
|
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_roll.h"
|
|
|
|
|
|
void uiuc_coef_roll()
|
|
{
|
|
string linetoken1;
|
|
string linetoken2;
|
|
stack command_list;
|
|
|
|
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);
|
|
}
|
|
Cl += Clo;
|
|
break;
|
|
}
|
|
case Cl_beta_flag:
|
|
{
|
|
if (ice_on)
|
|
{
|
|
Cl_beta = uiuc_ice_filter(Cl_beta_clean,kCl_beta);
|
|
}
|
|
Cl += Cl_beta * Beta;
|
|
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 += Cl_p * P_body * b_2U;
|
|
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 += Cl_r * R_body * b_2U;
|
|
break;
|
|
}
|
|
case Cl_da_flag:
|
|
{
|
|
if (ice_on)
|
|
{
|
|
Cl_da = uiuc_ice_filter(Cl_da_clean,kCl_da);
|
|
}
|
|
Cl += Cl_da * aileron;
|
|
break;
|
|
}
|
|
case Cl_dr_flag:
|
|
{
|
|
if (ice_on)
|
|
{
|
|
Cl_dr = uiuc_ice_filter(Cl_dr_clean,kCl_dr);
|
|
}
|
|
Cl += Cl_dr * rudder;
|
|
break;
|
|
}
|
|
case Cl_daa_flag:
|
|
{
|
|
if (ice_on)
|
|
{
|
|
Cl_daa = uiuc_ice_filter(Cl_daa_clean,kCl_daa);
|
|
}
|
|
Cl += Cl_daa * aileron * Alpha;
|
|
break;
|
|
}
|
|
case Clfada_flag:
|
|
{
|
|
ClfadaI = uiuc_2Dinterpolation(Clfada_aArray,
|
|
Clfada_daArray,
|
|
Clfada_ClArray,
|
|
Clfada_nAlphaArray,
|
|
Clfada_nda,
|
|
Alpha,
|
|
aileron);
|
|
Cl += ClfadaI;
|
|
break;
|
|
}
|
|
case Clfbetadr_flag:
|
|
{
|
|
ClfbetadrI = uiuc_2Dinterpolation(Clfbetadr_betaArray,
|
|
Clfbetadr_drArray,
|
|
Clfbetadr_ClArray,
|
|
Clfbetadr_nBetaArray,
|
|
Clfbetadr_ndr,
|
|
Beta,
|
|
rudder);
|
|
Cl += ClfbetadrI;
|
|
break;
|
|
}
|
|
};
|
|
} // end Cl map
|
|
|
|
return;
|
|
}
|
|
|
|
// end uiuc_coef_roll.cpp
|