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flightgear/Simulator/FDM/LaRCsim/c172_main.c

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Added c172 model from Tony Peden.
1999-06-15 20:05:26 +00:00
// LaRCsim.cxx -- interface to the LaRCsim flight model
//
// Written by Curtis Olson, started October 1998.
//
// Copyright (C) 1998 Curtis L. Olson - curt@me.umn.edu
//
// 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; either version 2 of the
// License, or (at your option) any later version.
//
// 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., 675 Mass Ave, Cambridge, MA 02139, USA.
//
// $Id$
#include <FDM/LaRCsim/ls_cockpit.h>
#include <FDM/LaRCsim/ls_generic.h>
#include <FDM/LaRCsim/ls_interface.h>
#include <FDM/LaRCsim/ls_constants.h>
Updated Tony's c172 model code.
1999-08-19 21:24:03 +00:00
#include <FDM/LaRCsim/atmos_62.h>
/* #include <FDM/LaRCsim/ls_trim_fs.h> */
#include <FDM/LaRCsim/c172_aero.h>
#include <math.h>
#include <stdlib.h>
#include <stdio.h>
//simple "one-at-a-time" longitudinal trimming routine
typedef struct
{
double latitude,longitude,altitude;
double vc,alpha,beta,gamma;
double theta,phi,psi;
double weight,cg;
int use_gamma_tmg;
}InitialConditions;
// Units for setIC
// vc knots (calibrated airspeed, close to indicated)
// altitude ft
// all angles in degrees
// weight lbs
// cg %MAC
// if use_gamma_tmg =1 then theta will be computed
// from theta=alpha+gamma and the value given will
// be ignored. Otherwise gamma is computed from
// gamma=theta-alpha
void setIC(InitialConditions IC)
{
SCALAR vtfps,u,v,w,vt_east;
SCALAR vnu,vnv,vnw,vteu,vtev,vtew,vdu,vdv,vdw;
SCALAR alphar,betar,thetar,phir,psir,gammar;
SCALAR sigma,ps,Ts,a;
Mass=IC.weight*INVG;
Dx_cg=(IC.cg-0.25)*4.9;
Latitude=IC.latitude*DEG_TO_RAD;
Longitude=IC.longitude*DEG_TO_RAD;
Altitude=IC.altitude;
ls_geod_to_geoc( Latitude, Altitude, &Sea_level_radius, &Lat_geocentric);
ls_atmos(IC.altitude,&sigma,&a,&Ts,&ps);
vtfps=sqrt(1/sigma*IC.vc*IC.vc)*1.68781;
alphar=IC.alpha*DEG_TO_RAD;
betar=IC.beta*DEG_TO_RAD;
gammar=IC.gamma*DEG_TO_RAD;
phir=IC.phi*DEG_TO_RAD;
psir=IC.psi*DEG_TO_RAD;
if(IC.use_gamma_tmg == 1)
{
thetar=alphar+gammar;
}
else
{
thetar=IC.theta*DEG_TO_RAD;
gammar=thetar-alphar;
}
u=vtfps*cos(alphar)*cos(betar);
v=vtfps*sin(betar);
w=vtfps*sin(alphar)*cos(betar);
vnu=u*cos(thetar)*cos(psir);
vnv=v*(-sin(psir)*cos(phir)+sin(phir)*sin(thetar)*cos(psir));
vnw=w*(sin(phir)*sin(psir)+cos(phir)*sin(thetar)*cos(psir));
V_north=vnu+vnv+vnw;
vteu=u*cos(thetar)*sin(psir);
vtev=v*(cos(phir)*cos(psir)+sin(phir)*sin(thetar)*sin(psir));
vtew=w*(-sin(phir)*cos(psir)+cos(phir)*sin(thetar)*sin(psir));
vt_east=vteu+vtev+vtew;
V_east=vt_east+ OMEGA_EARTH*Sea_level_radius*cos(Lat_geocentric);
vdu=u*-sin(thetar);
vdv=v*cos(thetar)*sin(phir);
vdw=w*cos(thetar)*cos(phir);
V_down=vdu+vdv+vdw;
Theta=thetar;
Phi=phir;
Psi=psir;
}
int trim_long(int kmax, InitialConditions IC)
{
double elevator,alpha;
double tol=1E-3;
double a_tol=tol/10;
double alpha_step=0.001;
int k=0,i,j=0,jmax=10,sum=0;
ls_loop(0.0,-1);
do{
//printf("k: %d\n",k);
while((fabs(W_dot_body) > tol) && (j < jmax))
{
IC.alpha+=W_dot_body*0.05;
if((IC.alpha < -5) || (IC.alpha > 21))
j=jmax;
setIC(IC);
ls_loop(0.0,-1);
/* printf("IC.alpha: %g, Alpha: %g, wdot: %g\n",IC.alpha,Alpha*RAD_TO_DEG,W_dot_body);
*/ j++;
}
sum+=j;
/* printf("\tTheta: %7.4f, Alpha: %7.4f, wdot: %10.6f, j: %d\n",Theta*RAD_TO_DEG,Alpha*RAD_TO_DEG,W_dot_body,j);
*/ j=0;
while((fabs(U_dot_body) > tol) && (j < jmax))
{
Throttle_pct-=U_dot_body*0.005;
if((Throttle_pct < 0) || (Throttle_pct > 1))
Throttle_pct=0.2;
setIC(IC);
ls_loop(0.0,-1);
j++;
}
sum+=j;
/* printf("\tThrottle_pct: %7.4f, udot: %10.6f, j: %d\n",Throttle_pct,U_dot_body,j);
*/ j=0;
while((fabs(Q_dot_body) > a_tol) && (j < jmax))
{
Long_control+=Q_dot_body*0.001;
if((Long_control < -1) || (Long_control > 1))
j=jmax;
setIC(IC);
ls_loop(0.0,-1);
j++;
}
sum+=j;
if(Long_control >= 0)
elevator=Long_control*23;
else
elevator=Long_control*28;
/* printf("\televator: %7.4f, qdot: %10.6f, j: %d\n",elevator,Q_dot_body,j);
*/ k++;j=0;
}while(((fabs(W_dot_body) > tol) || (fabs(U_dot_body) > tol) || (fabs(Q_dot_body) > tol)) && (k < kmax));
/* printf("Total Iterations: %d\n",sum); */
return k;
}
int trim_ground(int kmax, InitialConditions IC)
{
double elevator,alpha,qdot_prev,alt_prev,step;
double tol=1E-3;
double a_tol=tol/10;
double alpha_step=0.001;
int k=0,i,j=0,jmax=40,sum=0,m=0;
Throttle_pct=0;
Brake_pct=1;
Theta=5*DEG_TO_RAD;
IC.altitude=Runway_altitude;
printf("udot: %g\n",U_dot_body);
setIC(IC);
printf("Altitude: %g, Runway_altitude: %g\n",Altitude,Runway_altitude);
qdot_prev=1.0E6;
ls_loop(0.0,-1);
do{
//printf("k: %d\n",k);
step=1;
printf("IC.altitude: %g, Altitude: %g, Runway_altitude: %g,wdot: %g,F_Z_gear: %g, M_m_gear: %g,F_Z: %g\n",IC.altitude,Altitude,Runway_altitude,W_dot_body,F_Z_gear,M_m_gear,F_Z);
m=0;
while((fabs(W_dot_body) > tol) && (m < 10))
{
j=0;
do{
alt_prev=IC.altitude;
IC.altitude+=step;
setIC(IC);
ls_loop(0.0,-1);
printf("IC.altitude: %g, Altitude: %g, Runway_altitude: %g,wdot: %g,F_Z: %g\n",IC.altitude,Altitude,Runway_altitude,W_dot_body,F_Z);
j++;
}while((W_dot_body < 0) && (j < jmax));
IC.altitude-=step;
step/=10;
printf("step: %g\n",step);
m++;
}
sum+=j;
printf("IC.altitude: %g, Altitude: %g, Runway_altitude: %g,wdot: %g,F_Z_gear: %g, M_m_gear: %g,F_Z: %g\n",IC.altitude,Altitude,Runway_altitude,W_dot_body,F_Z_gear,M_m_gear,F_Z);
j=0;
while((Q_dot_body <= qdot_prev) && (j < jmax))
{
qdot_prev=Q_dot_body;
IC.theta+=Q_dot_body;
setIC(IC);
ls_loop(0.0,-1);
j++;
printf("\tTheta: %7.4f, qdot: %10.6f, qdot_prev: %10.6f, j: %d\n",Theta*RAD_TO_DEG,Q_dot_body,qdot_prev,j);
}
IC.theta-=qdot_prev;
sum+=j;
printf("\tTheta: %7.4f, qdot: %10.6f, W_dot_body: %g\n",Theta,Q_dot_body,W_dot_body);
j=0;
if(W_dot_body > tol)
{
step=1;
while((W_dot_body > 0) && (j <jmax))
{
IC.altitude-=step;
setIC(IC);
ls_loop(0.0,-1);
j++;
}
}
k++;j=0;
}while(((fabs(W_dot_body) > tol) || (fabs(Q_dot_body) > tol)) && (k < kmax));
printf("Total Iterations: %d\n",sum);
return k;
}
void do_trims(int kmax,FILE *out,InitialConditions IC)
{
int k=0,i;
double speed,elevator,cmcl;
out=fopen("trims.out","w");
speed=55;
for(i=1;i<=5;i++)
{
switch(i)
{
case 1: IC.weight=1500;IC.cg=0.155;break;
case 2: IC.weight=1500;IC.cg=0.364;break;
case 3: IC.weight=1950;IC.cg=0.155;break;
case 4: IC.weight=2550;IC.cg=0.257;break;
case 5: IC.weight=2550;IC.cg=0.364;break;
}
speed=50;
while(speed <= 150)
{
IC.vc=speed;
Long_control=0;Theta=0;Throttle_pct=0.0;
k=trim_long(kmax,IC);
if(Long_control <= 0)
elevator=Long_control*28;
else
elevator=Long_control*23;
if(fabs(CL) > 1E-3)
{
cmcl=cm / CL;
}
if(k < kmax)
{
fprintf(out,"%g,%g,%g,%g,%g,%d",V_calibrated_kts,Alpha*RAD_TO_DEG,Long_control,Throttle_pct,Gamma_vert_rad,k);
fprintf(out,",%g,%g,%g,%g,%g\n",CL,cm,cmcl,Weight,Cg);
/* printf("%g,%g,%g,%g,%g,%g,%g,%g,%g,%g\n",V_calibrated_kts,Alpha*RAD_TO_DEG,elevator,CL,cm,Cmo,Cma,Cmde,Mass*32.174,Dx_cg);
*/ }
else
{
printf("kmax exceeded at: %g knots, %g lbs, %g %%MAC\n",V_calibrated_kts,Weight,Cg);
printf("wdot: %g, udot: %g, qdot: %g\n\n",W_dot_body,U_dot_body,Q_dot_body);
}
speed+=10;
}
}
fclose(out);
}
void do_stick_pull(int kmax, SCALAR tmax,FILE *out,InitialConditions IC)
{
SCALAR htarget,hgain,hdiffgain,herr,herr_diff,herrprev;
SCALAR theta_trim,elev_trim,time;
int k;
k=trim_long(kmax,IC);
printf("Trim:\n\tAlpha: %10.6f, elev: %10.6f, Throttle: %10.6f\n\twdot: %10.6f, qdot: %10.6f, udot: %10.6f\n",Alpha*RAD_TO_DEG,Long_control,Throttle_pct,W_dot_body,U_dot_body,Q_dot_body);
Added c172 model from Tony Peden.
1999-06-15 20:05:26 +00:00
Updated Tony's c172 model code.
1999-08-19 21:24:03 +00:00
htarget=0;
hgain=1;
hdiffgain=1;
elev_trim=Long_control;
out=fopen("stick_pull.out","w");
herr=Q_body-htarget;
//fly steady-level for 2 seconds, well, zero pitch rate anyway
while(time < 2.0)
{
herrprev=herr;
ls_update(1);
herr=Q_body-htarget;
herr_diff=herr-herrprev;
Long_control=elev_trim+(hgain*herr + hdiffgain*herr_diff);
time+=0.01;
/* printf("Time: %7.4f, Alt: %7.4f, Alpha: %7.4f, pelev: %7.4f, qdot: %7.4f, udot: %7.4f, Phi: %7.4f, Psi: %7.4f\n",time,Altitude,Alpha*RAD_TO_DEG,Long_control*100,Q_body*RAD_TO_DEG,U_dot_body,Phi,Psi);
printf("Mcg: %7.4f, Mrp: %7.4f, Maero: %7.4f, Meng: %7.4f, Mgear: %7.4f, Dx_cg: %7.4f, Dz_cg: %7.4f\n\n",M_m_cg,M_m_rp,M_m_aero,M_m_engine,M_m_gear,Dx_cg,Dz_cg);
*/ fprintf(out,"%20.8f,%20.8f,%20.8f,%20.8f,%20.8f,%20.8f,%20.8f,%20.8f,%20.8f,",time,V_true_kts,Theta*RAD_TO_DEG,Alpha*RAD_TO_DEG,Q_body*RAD_TO_DEG,Alpha_dot*RAD_TO_DEG,Q_dot_body*RAD_TO_DEG,Throttle_pct,elevator*RAD_TO_DEG);
fprintf(out,"%20.8f,%20.8f,%20.8f,%20.8f,%20.8f\n",CL,CLwbh,cm,cd,Altitude);
}
//begin untrimmed climb at theta_trim + 2 degrees
hgain=4;
hdiffgain=2;
theta_trim=Theta;
htarget=theta_trim;
herr=Theta-htarget;
while(time < tmax)
{
//ramp in the target theta
if(htarget < (theta_trim + 2*DEG_TO_RAD))
{
htarget+= 0.01*DEG_TO_RAD;
}
herrprev=herr;
ls_update(1);
herr=Theta-htarget;
herr_diff=herr-herrprev;
Long_control=elev_trim+(hgain*herr + hdiffgain*herr_diff);
time+=0.01;
/* printf("Time: %7.4f, Alt: %7.4f, Alpha: %7.4f, pelev: %7.4f, qdot: %7.4f, udot: %7.4f, Phi: %7.4f, Psi: %7.4f\n",time,Altitude,Alpha*RAD_TO_DEG,Long_control*100,Q_body*RAD_TO_DEG,U_dot_body,Phi,Psi);
printf("Mcg: %7.4f, Mrp: %7.4f, Maero: %7.4f, Meng: %7.4f, Mgear: %7.4f, Dx_cg: %7.4f, Dz_cg: %7.4f\n\n",M_m_cg,M_m_rp,M_m_aero,M_m_engine,M_m_gear,Dx_cg,Dz_cg);
*/ fprintf(out,"%20.8f,%20.8f,%20.8f,%20.8f,%20.8f,%20.8f,%20.8f,%20.8f,%20.8f,",time,V_true_kts,Theta*RAD_TO_DEG,Alpha*RAD_TO_DEG,Q_body*RAD_TO_DEG,Alpha_dot*RAD_TO_DEG,Q_dot_body*RAD_TO_DEG,Throttle_pct,elevator*RAD_TO_DEG);
fprintf(out,"%20.8f,%20.8f,%20.8f,%20.8f,%20.8f\n",CL,CLwbh,cm,cd,Altitude);
}
printf("%g,%g\n",theta_trim*RAD_TO_DEG,htarget*RAD_TO_DEG);
fclose(out);
}
void do_takeoff(FILE *out)
{
SCALAR htarget,hgain,hdiffgain,elev_trim,elev_trim_save,herr;
SCALAR time,herrprev,herr_diff;
htarget=0;
hgain=1;
hdiffgain=1;
elev_trim=Long_control;
elev_trim_save=elev_trim;
out=fopen("takeoff.out","w");
herr=Q_body-htarget;
//attempt to maintain zero pitch rate during the roll
while((V_calibrated_kts < 61) && (time < 30.0))
{
/* herrprev=herr;*/
ls_update(1);
/*herr=Q_body-htarget;
herr_diff=herr-herrprev;
Long_control=elev_trim+(hgain*herr + hdiffgain*herr_diff); */
time+=0.01;
printf("Time: %7.4f, Vc: %7.4f, Alpha: %7.4f, pelev: %7.4f, qdot: %7.4f, udot: %7.4f, U: %7.4f, W: %7.4f\n",time,V_calibrated_kts,Alpha*RAD_TO_DEG,Long_control*100,Q_body*RAD_TO_DEG,U_dot_body,U_body,W_body);
// printf("Mcg: %7.4f, Mrp: %7.4f, Maero: %7.4f, Meng: %7.4f, Mgear: %7.4f, Dx_cg: %7.4f, Dz_cg: %7.4f\n\n",M_m_cg,M_m_rp,M_m_aero,M_m_engine,M_m_gear,Dx_cg,Dz_cg);
// fprintf(out,"%20.8f,%20.8f,%20.8f,%20.8f,%20.8f,%20.8f,%20.8f,%20.8f,%20.8f,",time,V_calibrated_kts,Theta*RAD_TO_DEG,Alpha*RAD_TO_DEG,Q_body*RAD_TO_DEG,Alpha_dot*RAD_TO_DEG,Q_dot_body*RAD_TO_DEG,Throttle_pct,elevator*RAD_TO_DEG);
fprintf(out,"%20.8f,%20.8f,%20.8f,%20.8f,%20.8f\n",CL,CLwbh,cm,cd,Altitude);
}
//At Vr, ramp in 10% nose up elevator in 0.5 seconds
elev_trim_save=0;
printf("At Vr, rotate...\n");
while((Q_body < 3.0*RAD_TO_DEG) && (time < 30.0))
{
Long_control-=0.01;
ls_update(1);
printf("Time: %7.4f, Vc: %7.4f, Alpha: %7.4f, pelev: %7.4f, q: %7.4f, cm: %7.4f, U: %7.4f, W: %7.4f\n",time,V_calibrated_kts,Alpha*RAD_TO_DEG,Long_control*100,Q_body*RAD_TO_DEG,cm,U_body,W_body);
fprintf(out,"%20.8f,%20.8f,%20.8f,%20.8f,%20.8f,%20.8f,%20.8f,%20.8f,%20.8f,",time,V_calibrated_kts,Theta*RAD_TO_DEG,Alpha*RAD_TO_DEG,Q_body*RAD_TO_DEG,Alpha_dot*RAD_TO_DEG,Q_dot_body*RAD_TO_DEG,Throttle_pct,elevator*RAD_TO_DEG);
fprintf(out,"%20.8f,%20.8f,%20.8f,%20.8f,%20.8f\n",CL,CLwbh,cm,cd,Altitude);
time +=0.01;
}
//Maintain 15 degrees theta for the climbout
htarget=15*DEG_TO_RAD;
herr=Theta-htarget;
hgain=10;
hdiffgain=1;
elev_trim=Long_control;
while(time < 30.0)
{
herrprev=herr;
ls_update(1);
herr=Theta-htarget;
herr_diff=herr-herrprev;
Long_control=elev_trim+(hgain*herr + hdiffgain*herr_diff);
time+=0.01;
printf("Time: %7.4f, Alt: %7.4f, Speed: %7.4f, Theta: %7.4f\n",time,Altitude,V_calibrated_kts,Theta*RAD_TO_DEG);
fprintf(out,"%20.8f,%20.8f,%20.8f,%20.8f,%20.8f,%20.8f,%20.8f,%20.8f,%20.8f,",time,V_calibrated_kts,Theta*RAD_TO_DEG,Alpha*RAD_TO_DEG,Q_body*RAD_TO_DEG,Alpha_dot*RAD_TO_DEG,Q_dot_body*RAD_TO_DEG,Throttle_pct,elevator*RAD_TO_DEG);
fprintf(out,"%20.8f,%20.8f,%20.8f,%20.8f,%20.8f\n",CL,CLwbh,cm,cd,Altitude);
}
fclose(out);
printf("Speed: %7.4f, Alt: %7.4f, Alpha: %7.4f, pelev: %7.4f, q: %7.4f, udot: %7.4f\n",V_true_kts,Altitude,Alpha*RAD_TO_DEG,Long_control,Q_body*RAD_TO_DEG,U_dot_body);
printf("F_down_total: %7.4f, F_Z_aero: %7.4f, F_X: %7.4f, M_m_cg: %7.4f\n\n",F_down+Mass*Gravity,F_Z_aero,F_X,M_m_cg);
}
Added c172 model from Tony Peden.
1999-06-15 20:05:26 +00:00
// Initialize the LaRCsim flight model, dt is the time increment for
// each subsequent iteration through the EOM
int fgLaRCsimInit(double dt) {
ls_toplevel_init(dt);
return(1);
}
Updated Tony's c172 model code.
1999-08-19 21:24:03 +00:00
Added c172 model from Tony Peden.
1999-06-15 20:05:26 +00:00
// Run an iteration of the EOM (equations of motion)
Updated Tony's c172 model code.
1999-08-19 21:24:03 +00:00
int main(int argc, char *argv[]) {
Added c172 model from Tony Peden.
1999-06-15 20:05:26 +00:00
double save_alt = 0.0;
Updated Tony's c172 model code.
1999-08-19 21:24:03 +00:00
int multiloop=1,k=0,i;
double time=0,elev_trim,elev_trim_save,elevator,speed,cmcl;
FILE *out;
double hgain,hdiffgain,herr,herrprev,herr_diff,htarget;
InitialConditions IC;
Added c172 model from Tony Peden.
1999-06-15 20:05:26 +00:00
Updated Tony's c172 model code.
1999-08-19 21:24:03 +00:00
if(argc < 6)
{
printf("Need args: $c172 speed alt alpha elev throttle\n");
exit(1);
}
Added c172 model from Tony Peden.
1999-06-15 20:05:26 +00:00
Updated Tony's c172 model code.
1999-08-19 21:24:03 +00:00
IC.latitude=47.5299892; //BFI
IC.longitude=122.3019561;
Runway_altitude = 18.0;
IC.altitude=strtod(argv[2],NULL);
IC.vc=strtod(argv[1],NULL);
IC.alpha=10;
IC.beta=0;
IC.theta=strtod(argv[3],NULL);
IC.use_gamma_tmg=0;
IC.phi=0;
IC.psi=0;
IC.weight=1500;
IC.cg=0.155;
Long_control=strtod(argv[4],NULL);
setIC(IC);
printf("Out setIC\n");
ls_ForceAltitude(IC.altitude);
fgLaRCsimInit(0.01);
Added c172 model from Tony Peden.
1999-06-15 20:05:26 +00:00
Updated Tony's c172 model code.
1999-08-19 21:24:03 +00:00
while(IC.alpha < 30.0)
{
setIC(IC);
ls_loop(0.0,-1);
printf("CL: %g ,Alpha: %g\n",CL,IC.alpha);
IC.alpha+=1.0;
}
/*trim_ground(10,IC);*/
/* printf("%g,%g\n",Theta,Gamma_vert_rad);
printf("trim_long():\n");
k=trim_long(200,IC);
Throttle_pct=Throttle_pct-0.2;
printf("%g,%g\n",Theta,Gamma_vert_rad);
out=fopen("dive.out","w");
time=0;
while(time < 30.0)
{
ls_update(1);
cmcl=cm/CL;
fprintf(out,"%g,%g,%g,%g,%g,%d",V_calibrated_kts,Alpha*RAD_TO_DEG,Long_control,Throttle_pct,Gamma_vert_rad,k);
fprintf(out,",%g,%g,%g\n",CL,cm,cmcl);
time+=0.01;
}
fclose(out);
printf("V_rel_wind: %8.2f, Alpha: %8.2f, Beta: %8.2f\n",V_rel_wind,Alpha*RAD_TO_DEG,Beta*RAD_TO_DEG);
printf("Theta: %8.2f, Gamma: %8.2f, Alpha_tmg: %8.2f\n",Theta*RAD_TO_DEG,Gamma_vert_rad*RAD_TO_DEG,Theta*RAD_TO_DEG-Gamma_vert_rad*RAD_TO_DEG);
printf("V_north: %8.2f, V_east_rel_ground: %8.2f, V_east: %8.2f, V_down: %8.2f\n",V_north,V_east_rel_ground,V_east,V_down);
printf("Long_control: %8.2f, Throttle_pct: %8.2f\n",Long_control,Throttle_pct);
printf("k: %d, udot: %8.4f, wdot: %8.4f, qdot: %8.5f\n",k,U_dot_body,W_dot_body,Q_dot_body);
Added c172 model from Tony Peden.
1999-06-15 20:05:26 +00:00
Updated Tony's c172 model code.
1999-08-19 21:24:03 +00:00
printf("\nls_update():\n");
ls_update(1);
printf("V_rel_wind: %8.2f, Alpha: %8.2f, Beta: %8.2f\n",V_rel_wind,Alpha*RAD_TO_DEG,Beta*RAD_TO_DEG);
printf("Theta: %8.2f, Gamma: %8.2f, Alpha_tmg: %8.2f\n",Theta*RAD_TO_DEG,Gamma_vert_rad*RAD_TO_DEG,Theta*RAD_TO_DEG-Gamma_vert_rad*RAD_TO_DEG);
*/
Added c172 model from Tony Peden.
1999-06-15 20:05:26 +00:00
/* Inform LaRCsim of the local terrain altitude */
Updated Tony's c172 model code.
1999-08-19 21:24:03 +00:00
Added c172 model from Tony Peden.
1999-06-15 20:05:26 +00:00
return 1;
}
/*// Convert from the FGInterface struct to the LaRCsim generic_ struct
int FGInterface_2_LaRCsim (FGInterface& f) {
Mass = f.get_Mass();
I_xx = f.get_I_xx();
I_yy = f.get_I_yy();
I_zz = f.get_I_zz();
I_xz = f.get_I_xz();
// Dx_pilot = f.get_Dx_pilot();
// Dy_pilot = f.get_Dy_pilot();
// Dz_pilot = f.get_Dz_pilot();
Dx_cg = f.get_Dx_cg();
Dy_cg = f.get_Dy_cg();
Dz_cg = f.get_Dz_cg();
// F_X = f.get_F_X();
// F_Y = f.get_F_Y();
// F_Z = f.get_F_Z();
// F_north = f.get_F_north();
// F_east = f.get_F_east();
// F_down = f.get_F_down();
// F_X_aero = f.get_F_X_aero();
// F_Y_aero = f.get_F_Y_aero();
// F_Z_aero = f.get_F_Z_aero();
// F_X_engine = f.get_F_X_engine();
// F_Y_engine = f.get_F_Y_engine();
// F_Z_engine = f.get_F_Z_engine();
// F_X_gear = f.get_F_X_gear();
// F_Y_gear = f.get_F_Y_gear();
// F_Z_gear = f.get_F_Z_gear();
// M_l_rp = f.get_M_l_rp();
// M_m_rp = f.get_M_m_rp();
// M_n_rp = f.get_M_n_rp();
// M_l_cg = f.get_M_l_cg();
// M_m_cg = f.get_M_m_cg();
// M_n_cg = f.get_M_n_cg();
// M_l_aero = f.get_M_l_aero();
// M_m_aero = f.get_M_m_aero();
// M_n_aero = f.get_M_n_aero();
// M_l_engine = f.get_M_l_engine();
// M_m_engine = f.get_M_m_engine();
// M_n_engine = f.get_M_n_engine();
// M_l_gear = f.get_M_l_gear();
// M_m_gear = f.get_M_m_gear();
// M_n_gear = f.get_M_n_gear();
// V_dot_north = f.get_V_dot_north();
// V_dot_east = f.get_V_dot_east();
// V_dot_down = f.get_V_dot_down();
// U_dot_body = f.get_U_dot_body();
// V_dot_body = f.get_V_dot_body();
// W_dot_body = f.get_W_dot_body();
// A_X_cg = f.get_A_X_cg();
// A_Y_cg = f.get_A_Y_cg();
// A_Z_cg = f.get_A_Z_cg();
// A_X_pilot = f.get_A_X_pilot();
// A_Y_pilot = f.get_A_Y_pilot();
// A_Z_pilot = f.get_A_Z_pilot();
// N_X_cg = f.get_N_X_cg();
// N_Y_cg = f.get_N_Y_cg();
// N_Z_cg = f.get_N_Z_cg();
// N_X_pilot = f.get_N_X_pilot();
// N_Y_pilot = f.get_N_Y_pilot();
// N_Z_pilot = f.get_N_Z_pilot();
// P_dot_body = f.get_P_dot_body();
// Q_dot_body = f.get_Q_dot_body();
// R_dot_body = f.get_R_dot_body();
V_north = f.get_V_north();
V_east = f.get_V_east();
V_down = f.get_V_down();
// V_north_rel_ground = f.get_V_north_rel_ground();
// V_east_rel_ground = f.get_V_east_rel_ground();
// V_down_rel_ground = f.get_V_down_rel_ground();
// V_north_airmass = f.get_V_north_airmass();
// V_east_airmass = f.get_V_east_airmass();
// V_down_airmass = f.get_V_down_airmass();
// V_north_rel_airmass = f.get_V_north_rel_airmass();
// V_east_rel_airmass = f.get_V_east_rel_airmass();
// V_down_rel_airmass = f.get_V_down_rel_airmass();
// U_gust = f.get_U_gust();
// V_gust = f.get_V_gust();
// W_gust = f.get_W_gust();
// U_body = f.get_U_body();
// V_body = f.get_V_body();
// W_body = f.get_W_body();
// V_rel_wind = f.get_V_rel_wind();
// V_true_kts = f.get_V_true_kts();
// V_rel_ground = f.get_V_rel_ground();
// V_inertial = f.get_V_inertial();
// V_ground_speed = f.get_V_ground_speed();
// V_equiv = f.get_V_equiv();
// V_equiv_kts = f.get_V_equiv_kts();
// V_calibrated = f.get_V_calibrated();
// V_calibrated_kts = f.get_V_calibrated_kts();
P_body = f.get_P_body();
Q_body = f.get_Q_body();
R_body = f.get_R_body();
// P_local = f.get_P_local();
// Q_local = f.get_Q_local();
// R_local = f.get_R_local();
// P_total = f.get_P_total();
// Q_total = f.get_Q_total();
// R_total = f.get_R_total();
// Phi_dot = f.get_Phi_dot();
// Theta_dot = f.get_Theta_dot();
// Psi_dot = f.get_Psi_dot();
// Latitude_dot = f.get_Latitude_dot();
// Longitude_dot = f.get_Longitude_dot();
// Radius_dot = f.get_Radius_dot();
Lat_geocentric = f.get_Lat_geocentric();
Lon_geocentric = f.get_Lon_geocentric();
Radius_to_vehicle = f.get_Radius_to_vehicle();
Latitude = f.get_Latitude();
Longitude = f.get_Longitude();
Altitude = f.get_Altitude();
Phi = f.get_Phi();
Theta = f.get_Theta();
Psi = f.get_Psi();
// T_local_to_body_11 = f.get_T_local_to_body_11();
// T_local_to_body_12 = f.get_T_local_to_body_12();
// T_local_to_body_13 = f.get_T_local_to_body_13();
// T_local_to_body_21 = f.get_T_local_to_body_21();
// T_local_to_body_22 = f.get_T_local_to_body_22();
// T_local_to_body_23 = f.get_T_local_to_body_23();
// T_local_to_body_31 = f.get_T_local_to_body_31();
// T_local_to_body_32 = f.get_T_local_to_body_32();
// T_local_to_body_33 = f.get_T_local_to_body_33();
// Gravity = f.get_Gravity();
// Centrifugal_relief = f.get_Centrifugal_relief();
// Alpha = f.get_Alpha();
// Beta = f.get_Beta();
// Alpha_dot = f.get_Alpha_dot();
// Beta_dot = f.get_Beta_dot();
// Cos_alpha = f.get_Cos_alpha();
// Sin_alpha = f.get_Sin_alpha();
// Cos_beta = f.get_Cos_beta();
// Sin_beta = f.get_Sin_beta();
// Cos_phi = f.get_Cos_phi();
// Sin_phi = f.get_Sin_phi();
// Cos_theta = f.get_Cos_theta();
// Sin_theta = f.get_Sin_theta();
// Cos_psi = f.get_Cos_psi();
// Sin_psi = f.get_Sin_psi();
// Gamma_vert_rad = f.get_Gamma_vert_rad();
// Gamma_horiz_rad = f.get_Gamma_horiz_rad();
// Sigma = f.get_Sigma();
// Density = f.get_Density();
// V_sound = f.get_V_sound();
// Mach_number = f.get_Mach_number();
// Static_pressure = f.get_Static_pressure();
// Total_pressure = f.get_Total_pressure();
// Impact_pressure = f.get_Impact_pressure();
// Dynamic_pressure = f.get_Dynamic_pressure();
// Static_temperature = f.get_Static_temperature();
// Total_temperature = f.get_Total_temperature();
Sea_level_radius = f.get_Sea_level_radius();
Earth_position_angle = f.get_Earth_position_angle();
Runway_altitude = f.get_Runway_altitude();
// Runway_latitude = f.get_Runway_latitude();
// Runway_longitude = f.get_Runway_longitude();
// Runway_heading = f.get_Runway_heading();
// Radius_to_rwy = f.get_Radius_to_rwy();
// D_cg_north_of_rwy = f.get_D_cg_north_of_rwy();
// D_cg_east_of_rwy = f.get_D_cg_east_of_rwy();
// D_cg_above_rwy = f.get_D_cg_above_rwy();
// X_cg_rwy = f.get_X_cg_rwy();
// Y_cg_rwy = f.get_Y_cg_rwy();
// H_cg_rwy = f.get_H_cg_rwy();
// D_pilot_north_of_rwy = f.get_D_pilot_north_of_rwy();
// D_pilot_east_of_rwy = f.get_D_pilot_east_of_rwy();
// D_pilot_above_rwy = f.get_D_pilot_above_rwy();
// X_pilot_rwy = f.get_X_pilot_rwy();
// Y_pilot_rwy = f.get_Y_pilot_rwy();
// H_pilot_rwy = f.get_H_pilot_rwy();
return( 0 );
}
Updated Tony's c172 model code.
1999-08-19 21:24:03 +00:00
*/
Added c172 model from Tony Peden.
1999-06-15 20:05:26 +00:00
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