Cnfada, and Cnfbetadr switches
04/15/2000 (JS) broke up into multiple
uiuc_coef_xxx functions
- 06/18/2001 (RD) Added initialization of Alpha and
- Beta. Added aileron_input and rudder_input.
+ 06/18/2001 (RD) Added initialization of Std_Alpha and
+ Std_Beta. Added aileron_input and rudder_input.
Added pilot_elev_no, pilot_ail_no, and
pilot_rud_no.
07/05/2001 (RD) Added pilot_(elev,ail,rud)_no=false
- 01/11/2002 (AP) Added call to uiuc_bootTime()
+ 01/11/2002 (AP) Added call to uiuc_iceboot()
+ 12/02/2002 (RD) Moved icing demo interpolations to its
+ own function
----------------------------------------------------------------------
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.
+ Foundation, Inc., 51 Franklin Street, Fifth Floor, Boston, MA 02110-1301, USA.
**********************************************************************/
#include "uiuc_coefficients.h"
-
void uiuc_coefficients(double dt)
{
+ static string uiuc_coefficients_error = " (from uiuc_coefficients.cpp) ";
double l_trim, l_defl;
double V_rel_wind_dum, U_body_dum;
if (Alpha_init_true && Simtime==0)
- Alpha = Alpha_init;
+ Std_Alpha = Alpha_init;
if (Beta_init_true && Simtime==0)
- Beta = Beta_init;
+ Std_Beta = Beta_init;
// calculate rate derivative nondimensionalization factors
// check if speed is sufficient to compute dynamic pressure terms
+ if (dyn_on_speed==0)
+ {
+ uiuc_warnings_errors(5, uiuc_coefficients_error);
+ }
if (nondim_rate_V_rel_wind || use_V_rel_wind_2U) // c172_aero uses V_rel_wind
{
if (V_rel_wind > dyn_on_speed)
{
cbar_2U = cbar / (2.0 * V_rel_wind);
b_2U = bw / (2.0 * V_rel_wind);
- // ch is the horizontal tail chord
- ch_2U = ch / (2.0 * V_rel_wind);
+ // chord_h is the horizontal tail chord
+ ch_2U = chord_h / (2.0 * V_rel_wind);
}
else if (use_dyn_on_speed_curve1)
{
V_rel_wind_dum = dyn_on_speed_zero + V_rel_wind * (dyn_on_speed - dyn_on_speed_zero)/dyn_on_speed;
cbar_2U = cbar / (2.0 * V_rel_wind_dum);
b_2U = bw / (2.0 * V_rel_wind_dum);
- ch_2U = ch / (2.0 * V_rel_wind_dum);
- Alpha_dot = 0.0;
+ ch_2U = chord_h / (2.0 * V_rel_wind_dum);
+ Std_Alpha_dot = 0.0;
}
else
{
cbar_2U = 0.0;
b_2U = 0.0;
ch_2U = 0.0;
- Alpha_dot = 0.0;
+ Std_Alpha_dot = 0.0;
}
}
else if(use_abs_U_body_2U) // use absolute(U_body)
{
cbar_2U = cbar / (2.0 * fabs(U_body));
b_2U = bw / (2.0 * fabs(U_body));
- ch_2U = ch / (2.0 * fabs(U_body));
+ ch_2U = chord_h / (2.0 * fabs(U_body));
}
else if (use_dyn_on_speed_curve1)
{
U_body_dum = dyn_on_speed_zero + fabs(U_body) * (dyn_on_speed - dyn_on_speed_zero)/dyn_on_speed;
cbar_2U = cbar / (2.0 * U_body_dum);
b_2U = bw / (2.0 * U_body_dum);
- ch_2U = ch / (2.0 * U_body_dum);
- Alpha_dot = 0.0;
+ ch_2U = chord_h / (2.0 * U_body_dum);
+ Std_Alpha_dot = 0.0;
}
else
{
cbar_2U = 0.0;
b_2U = 0.0;
ch_2U = 0.0;
- Alpha_dot = 0.0;
+ Std_Alpha_dot = 0.0;
}
}
else // use U_body
{
cbar_2U = cbar / (2.0 * U_body);
b_2U = bw / (2.0 * U_body);
- ch_2U = ch / (2.0 * U_body);
+ ch_2U = chord_h / (2.0 * U_body);
}
else if (use_dyn_on_speed_curve1)
{
U_body_dum = dyn_on_speed_zero + U_body * (dyn_on_speed - dyn_on_speed_zero)/dyn_on_speed;
cbar_2U = cbar / (2.0 * U_body_dum);
b_2U = bw / (2.0 * U_body_dum);
- ch_2U = ch / (2.0 * U_body_dum);
- Alpha_dot = 0.0;
+ ch_2U = chord_h / (2.0 * U_body_dum);
+ Std_Alpha_dot = 0.0;
beta_flow_clean_tail = cbar_2U;
}
else
cbar_2U = 0.0;
b_2U = 0.0;
ch_2U = 0.0;
- Alpha_dot = 0.0;
+ Std_Alpha_dot = 0.0;
}
}
- // check if speed is sufficient to "trust" Alpha_dot value
+ // check if speed is sufficient to "trust" Std_Alpha_dot value
if (use_Alpha_dot_on_speed)
{
if (V_rel_wind < Alpha_dot_on_speed)
- Alpha_dot = 0.0;
+ Std_Alpha_dot = 0.0;
}
}
// check to see if data files are used for control deflections
- pilot_elev_no = false;
- pilot_ail_no = false;
- pilot_rud_no = false;
- if (elevator_step || elevator_singlet || elevator_doublet || elevator_input || aileron_input || rudder_input)
+ if (outside_control == false)
+ {
+ pilot_elev_no = false;
+ pilot_ail_no = false;
+ pilot_rud_no = false;
+ }
+ if (elevator_step || elevator_singlet || elevator_doublet || elevator_input || aileron_input || rudder_input || flap_pos_input)
{
uiuc_controlInput();
}
+ //if (Simtime >=10.0)
+ // {
+ // ap_hh_on = 1;
+ // ap_Psi_ref_rad = 0*DEG_TO_RAD;
+ // }
+
+ if (ap_pah_on || ap_alh_on || ap_rah_on || ap_hh_on)
+ {
+ uiuc_auto_pilot(dt);
+ }
+
CD = CX = CL = CZ = Cm = CY = Cl = Cn = 0.0;
CLclean_wing = CLiced_wing = CLclean_tail = CLiced_tail = 0.0;
CZclean_wing = CZiced_wing = CZclean_tail = CZiced_tail = 0.0;
CXclean_wing = CXiced_wing = CXclean_tail = CXiced_tail = 0.0;
+ CL_clean = CL_iced = 0.0;
+ CY_clean = CY_iced = 0.0;
+ CD_clean = CD_iced = 0.0;
+ Cm_iced = Cm_clean = 0.0;
+ Cl_iced = Cl_clean = 0.0;
+ Cn_iced = Cn_clean = 0.0;
uiuc_coef_lift();
uiuc_coef_drag();
uiuc_coef_sideforce();
uiuc_coef_roll();
uiuc_coef_yaw();
- if (ice_case)
+
+ //uncomment next line to always run icing functions
+ //nonlin_ice_case = 1;
+
+ if (nonlin_ice_case)
{
- eta_tail = sublimation(OATemperature_F, eta_tail, dt);
- eta_wing_left = sublimation(OATemperature_F, eta_wing_left, dt);
- eta_wing_right = sublimation(OATemperature_F, eta_wing_right, dt);
- //removed shed until new model is created
- //eta_tail = shed(0.0, eta_tail, OATemperature_F, 0.0, dt);
- //eta_wing_left = shed(0.0, eta_wing_left, OATemperature_F, 0.0, dt);
- //eta_wing_right = shed(0.0, eta_wing_right, OATemperature_F, 0.0, dt);
-
+ if (eta_from_file)
+ {
+ if (eta_tail_input) {
+ double time = Simtime - eta_tail_input_startTime;
+ eta_tail = uiuc_1Dinterpolation(eta_tail_input_timeArray,
+ eta_tail_input_daArray,
+ eta_tail_input_ntime,
+ time);
+ }
+ if (eta_wing_left_input) {
+ double time = Simtime - eta_wing_left_input_startTime;
+ eta_wing_left = uiuc_1Dinterpolation(eta_wing_left_input_timeArray,
+ eta_wing_left_input_daArray,
+ eta_wing_left_input_ntime,
+ time);
+ }
+ if (eta_wing_right_input) {
+ double time = Simtime - eta_wing_right_input_startTime;
+ eta_wing_right = uiuc_1Dinterpolation(eta_wing_right_input_timeArray,
+ eta_wing_right_input_daArray,
+ eta_wing_right_input_ntime,
+ time);
+ }
+ }
+
+ delta_CL = delta_CD = delta_Cm = delta_Cl = delta_Cn = 0.0;
Calc_Iced_Forces();
add_ice_effects();
+ tactilefadefI = 0.0;
+ if (eta_tail == 0.2 && tactile_pitch && tactilefadef)
+ {
+ if (tactilefadef_nice == 1)
+ tactilefadefI = uiuc_3Dinterp_quick(tactilefadef_fArray,
+ tactilefadef_aArray_nice,
+ tactilefadef_deArray_nice,
+ tactilefadef_tactileArray,
+ tactilefadef_na_nice,
+ tactilefadef_nde_nice,
+ tactilefadef_nf,
+ flap_pos,
+ Std_Alpha,
+ elevator);
+ else
+ tactilefadefI = uiuc_3Dinterpolation(tactilefadef_fArray,
+ tactilefadef_aArray,
+ tactilefadef_deArray,
+ tactilefadef_tactileArray,
+ tactilefadef_nAlphaArray,
+ tactilefadef_nde,
+ tactilefadef_nf,
+ flap_pos,
+ Std_Alpha,
+ elevator);
+ }
+ else if (demo_tactile)
+ {
+ double time = Simtime - demo_tactile_startTime;
+ tactilefadefI = uiuc_1Dinterpolation(demo_tactile_timeArray,
+ demo_tactile_daArray,
+ demo_tactile_ntime,
+ time);
+ }
+ if (icing_demo)
+ uiuc_icing_demo();
}
if (pilot_ail_no)
Lat_control = - aileron / damin * RAD_TO_DEG;
}
+ // can go past real limits
+ // add flag to behave like trim_case2 later
if (pilot_elev_no)
{
- l_trim = elevator_tab;
- l_defl = elevator - elevator_tab;
- if (l_trim <=0 )
- Long_trim = l_trim / demax * RAD_TO_DEG;
- else
- Long_trim = l_trim / demin * RAD_TO_DEG;
- if (l_defl <= 0)
- Long_control = l_defl / demax * RAD_TO_DEG;
- else
- Long_control = l_defl / demin * RAD_TO_DEG;
+ if (outside_control == false)
+ {
+ l_trim = elevator_tab;
+ l_defl = elevator - elevator_tab;
+ if (l_trim <=0 )
+ Long_trim = l_trim / demax * RAD_TO_DEG;
+ else
+ Long_trim = l_trim / demin * RAD_TO_DEG;
+ if (l_defl <= 0)
+ Long_control = l_defl / demax * RAD_TO_DEG;
+ else
+ Long_control = l_defl / demin * RAD_TO_DEG;
+ }
}
if (pilot_rud_no)
projects / flightgear.git / blobdiff