From 43143ef3584f92d8a611fde38af1d468ff21f311 Mon Sep 17 00:00:00 2001 From: curt Date: Mon, 1 Nov 1999 19:17:16 +0000 Subject: [PATCH] c172 updates from Tony. Fix extra yaw when using ailerons. Flaps and elevator tweaks. --- src/FDM/LaRCsim/c172_aero.c | 38 +- src/FDM/LaRCsim/c172_aero.h | 9 + src/FDM/LaRCsim/c172_gear.c | 5 +- src/FDM/LaRCsim/c172_init.c | 2 +- src/FDM/LaRCsim/c172_main.c | 931 ++++++++++++------------------------ 5 files changed, 331 insertions(+), 654 deletions(-) diff --git a/src/FDM/LaRCsim/c172_aero.c b/src/FDM/LaRCsim/c172_aero.c index 6cce2ef20..7eb5931b8 100644 --- a/src/FDM/LaRCsim/c172_aero.c +++ b/src/FDM/LaRCsim/c172_aero.c @@ -94,7 +94,7 @@ #include -#define NCL 11 +#define NCL 9 #define Ndf 4 #define DYN_ON_SPEED 33 /*20 knots*/ @@ -150,13 +150,13 @@ void aero( SCALAR dt, int Initialize ) { static SCALAR trim_inc = 0.0002; - static SCALAR alpha_ind[NCL]={-0.087,0,0.175,0.209,0.24,0.262,0.278,0.303,0.314,0.332,0.367}; - static SCALAR CLtable[NCL]={-0.14,0.31,1.21,1.376,1.51249,1.591,1.63,1.60878,1.53712,1.376,1.142}; + static SCALAR alpha_ind[NCL]={-0.087,0,0.14,0.21,0.24,0.26,0.28,0.31,0.35}; + static SCALAR CLtable[NCL]={-0.22,0.25,1.02,1.252,1.354,1.44,1.466,1.298,0.97}; static SCALAR flap_ind[Ndf]={0,10,20,30}; static SCALAR dCLf[Ndf]={0,0.20,0.30,0.35}; static SCALAR dCdf[Ndf]={0,0.0021,0.0085,0.0191}; - static SCALAR dCmf[Ndf]={0,-0.186,-0.28,-0.325}; + static SCALAR dCmf[Ndf]={0,-0.0654,-0.0981,-0.114}; static SCALAR flap_transit_rate=2.5; @@ -188,8 +188,8 @@ void aero( SCALAR dt, int Initialize ) { Cma=-1.8; Cmadot=-5.2; Cmq=-12.4; - Cmob=-0.00; - Cmde=-1.00; + Cmob=-0.02; + Cmde=-1.28; CLde=-Cmde / lbare; /* kinda backwards, huh? */ @@ -202,7 +202,7 @@ void aero( SCALAR dt, int Initialize ) { Cnbeta=0.065; Cnp=-0.03; Cnr=-0.099; - Cnda=-0.053; + Cnda=-0.0053; Cndr=-0.0657; Cybeta=-0.31; @@ -247,6 +247,7 @@ void aero( SCALAR dt, int Initialize ) { Dz_cg=Zcg*cbar; + if(Flap_handle < flap_ind[0]) { Flap_handle=flap_ind[0]; @@ -341,10 +342,13 @@ void aero( SCALAR dt, int Initialize ) { /* printf("aero: Wb: %7.4f, Ub: %7.4f, Alpha: %7.4f, elev: %7.4f, ail: %7.4f, rud: %7.4f, long_trim: %7.4f\n",W_body,U_body,Alpha*RAD_TO_DEG,elevator*RAD_TO_DEG,aileron*RAD_TO_DEG,rudder*RAD_TO_DEG,long_trim*RAD_TO_DEG); printf("aero: Theta: %7.4f, Gamma: %7.4f, Beta: %7.4f, Phi: %7.4f, Psi: %7.4f\n",Theta*RAD_TO_DEG,Gamma_vert_rad*RAD_TO_DEG,Beta*RAD_TO_DEG,Phi*RAD_TO_DEG,Psi*RAD_TO_DEG); */ + /* sum coefficients */ CLwbh = interp(CLtable,alpha_ind,NCL,Alpha); +/* printf("CLwbh: %g\n",CLwbh); + */ CLo = CLob + interp(dCLf,flap_ind,Ndf,Flap_Position); Cdo = Cdob + interp(dCdf,flap_ind,Ndf,Flap_Position); Cmo = Cmob + interp(dCmf,flap_ind,Ndf,Flap_Position); @@ -352,8 +356,9 @@ void aero( SCALAR dt, int Initialize ) { /* printf("FP: %g\n",Flap_Position); printf("CLo: %g\n",CLo); printf("Cdo: %g\n",Cdo); - printf("Cmo: %g\n",Cmo); - */ + printf("Cmo: %g\n",Cmo); */ + + CL = CLo + CLwbh + (CLadot*Alpha_dot + CLq*Theta_dot)*cbar_2V + CLde*elevator; cd = Cdo + rPiARe*CL*CL + Cdde*elevator; @@ -365,13 +370,15 @@ void aero( SCALAR dt, int Initialize ) { /* printf("aero: CL: %7.4f, Cd: %7.4f, Cm: %7.4f, Cy: %7.4f, Cn: %7.4f, Cl: %7.4f\n",CL,cd,cm,cy,cn,croll); */ + /*calculate wind axes forces*/ F_X_wind=-1*cd*qS; F_Y_wind=cy*qS; F_Z_wind=-1*CL*qS; /* printf("V_rel_wind: %7.4f, Fxwind: %7.4f Fywind: %7.4f Fzwind: %7.4f\n",V_rel_wind,F_X_wind,F_Y_wind,F_Z_wind); - */ + */ + /*calculate moments and body axis forces */ @@ -387,11 +394,12 @@ void aero( SCALAR dt, int Initialize ) { M_n_aero = cn*qSb; /* printf("I_yy: %7.4f, qScbar: %7.4f, qbar: %7.4f, Sw: %7.4f, cbar: %7.4f, 0.5*rho*V^2: %7.4f\n",I_yy,qScbar,Dynamic_pressure,Sw,cbar,0.5*0.0023081*V_rel_wind*V_rel_wind); - */ -/* printf("Fxaero: %7.4f Fyaero: %7.4f Fzaero: %7.4f Weight: %7.4f\n",F_X_aero,F_Y_aero,F_Z_aero,Weight); - */ -/* printf("Maero: %7.4f Naero: %7.4f Raero: %7.4f\n",M_m_aero,M_n_aero,M_l_aero); - */ + + printf("Fxaero: %7.4f Fyaero: %7.4f Fzaero: %7.4f Weight: %7.4f\n",F_X_aero,F_Y_aero,F_Z_aero,Weight); + + printf("Maero: %7.4f Naero: %7.4f Raero: %7.4f\n",M_m_aero,M_n_aero,M_l_aero); + */ + } diff --git a/src/FDM/LaRCsim/c172_aero.h b/src/FDM/LaRCsim/c172_aero.h index 922a4b52e..bba9e1c50 100644 --- a/src/FDM/LaRCsim/c172_aero.h +++ b/src/FDM/LaRCsim/c172_aero.h @@ -1,5 +1,12 @@ /*c172_aero.h*/ +#ifndef __C172_AERO_H +#define __C172_AERO_H + + + +#include + /*global declarations of aero model parameters*/ SCALAR CLadot; @@ -64,3 +71,5 @@ /* float Flap_Handle; */ int Flaps_In_Transit; +#endif + diff --git a/src/FDM/LaRCsim/c172_gear.c b/src/FDM/LaRCsim/c172_gear.c index 34482f887..b95aec32e 100644 --- a/src/FDM/LaRCsim/c172_gear.c +++ b/src/FDM/LaRCsim/c172_gear.c @@ -36,8 +36,9 @@ $Header$ $Log$ -Revision 1.8 1999/08/24 21:17:05 curt -Updates from Tony. +Revision 1.9 1999/11/01 18:17:16 curt +c172 updates from Tony. Fix extra yaw when using ailerons. Flaps and elevator +tweaks. ---------------------------------------------------------------------------- diff --git a/src/FDM/LaRCsim/c172_init.c b/src/FDM/LaRCsim/c172_init.c index 9c25e5bb8..ab935ee87 100644 --- a/src/FDM/LaRCsim/c172_init.c +++ b/src/FDM/LaRCsim/c172_init.c @@ -72,8 +72,8 @@ void model_init( void ) { I_yy=1346; I_zz=1967; I_xz=0; + Flap_Position=Flap_handle; Flaps_In_Transit=0; - } diff --git a/src/FDM/LaRCsim/c172_main.c b/src/FDM/LaRCsim/c172_main.c index 0b0f06084..6813fa0ad 100644 --- a/src/FDM/LaRCsim/c172_main.c +++ b/src/FDM/LaRCsim/c172_main.c @@ -31,330 +31,308 @@ #include /* #include */ #include +#include #include #include #include +#include -//simple "one-at-a-time" longitudinal trimming routine -typedef struct -{ - SCALAR latitude,longitude,altitude; - SCALAR vc,alpha,beta,gamma; - SCALAR theta,phi,psi; - SCALAR weight,cg; - SCALAR throttle,long_control,lat_control,rudder_pedal,flap_handle; - int use_gamma_tmg; -}InitialConditions; -void initIC(InitialConditions *IC) -{ - IC->latitude=IC->longitude=IC->altitude=0; - IC->vc=IC->alpha=IC->beta=IC->gamma=0; - IC->theta=IC->phi=IC->psi=0; - IC->weight=IC->cg=0; - IC->throttle=IC->long_control=IC->lat_control=IC->rudder_pedal=IC->flap_handle=0; -} -void checkLimits(float *control, SCALAR min, SCALAR max) -{ - if(*control < min) - *control=min; - else if(*control > max) - *control=max; -} - -// 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; - - Throttle_pct=IC.throttle; - checkLimits(&Throttle_pct,0,1); - - Long_control=IC.long_control; - checkLimits(&Long_control,-1,1); - - Lat_control=IC.lat_control; - checkLimits(&Lat_control,-1,1); - - Rudder_pedal=IC.rudder_pedal; - checkLimits(&Rudder_pedal,-1,1); - - Flap_Handle=IC.flap_handle; - checkLimits(&Flap_Handle,0,30); - - -} - - -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=40,sum=0,trim_failed=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; - if(trim_failed) - printf("\tAlpha: %7.4f, wdot: %10.6f, j: %d\n",Alpha*RAD_TO_DEG,W_dot_body,j); - j=0; - while((fabs(U_dot_body) > tol) && (j < jmax)) - { - - IC.throttle-=U_dot_body*0.01; - setIC(IC); - ls_loop(0.0,-1); - j++; - } - sum+=j; - if(trim_failed) - 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)) - { - - IC.long_control+=Q_dot_body*0.01; - setIC(IC); - ls_loop(0.0,-1); - j++; - } - if(trim_failed) - printf("\tLong_control: %7.4f, qdot: %10.6f, j: %d\n",Long_control,Q_dot_body,j); - - sum+=j; - if(k == kmax-2) - { - if((fabs(W_dot_body) > tol) || (fabs(U_dot_body) > tol) || (fabs(Q_dot_body) > a_tol)); - { - trim_failed=1; - jmax=kmax; - printf("\nTrim failed at: %6.1f knots, %g lbs, %5.3f %MAC\n",V_calibrated_kts,Weight,Cg); - IC.alpha=0;IC.throttle=0;IC.long_control=0; - setIC(IC); - ls_loop(0.0,-1); - } - } - k++;j=0; - }while(((fabs(W_dot_body) > tol) || (fabs(U_dot_body) > tol) || (fabs(Q_dot_body) > a_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 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.oldCmde.out","w"); + int k=0,i,j; + double speed,elevator,cmcl,maxspeed; + out=fopen("trims.out","w"); speed=55; - for(i=1;i<=5;i++) + for(j=0;j<=30;j+=10) { - switch(i) + IC.flap_handle=j; + for(i=1;i<=5;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; + 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; + } - 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",W_dot_body,U_dot_body,Q_dot_body); - printf("Alpha: %g, Throttle_pct: %g, Long_control: %g\n\n",Alpha*RAD_TO_DEG,Throttle_pct,Long_control); - */ } - speed+=10; - } - } + speed=40; + if(j > 0) { maxspeed = 90; } + else { maxspeed = 170; } + while(speed <= maxspeed) + { + 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,Flap_Position,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, Flaps: %g\n",V_calibrated_kts,Weight,Cg,Flap_Position); + printf("wdot: %g, udot: %g, qdot: %g\n",W_dot_body,U_dot_body,Q_dot_body); + printf("Alpha: %g, Throttle_pct: %g, Long_control: %g\n\n",Alpha*RAD_TO_DEG,Throttle_pct,Long_control); + } + speed+=10; + } + } + } fclose(out); } +void find_trim_stall(int kmax,FILE *out,InitialConditions IC) +{ + int k=0,i,j; + int failf; + char axis[10]; + double speed,elevator,cmcl,speed_inc,lastgood; + out=fopen("trim_stall.summary","w"); + speed=90; + speed_inc=10; + //failf=malloc(sizeof(int)); + + for(j=0;j<=30;j+=10) + { + IC.flap_handle=j; + for(i=1;i<=6;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=2400;IC.cg=0.155;break; + case 4: IC.weight=2400;IC.cg=0.364;break; + case 5: IC.weight=2550;IC.cg=0.257;break; + case 6: IC.weight=2550;IC.cg=0.364;break; + } + + speed=90; + speed_inc=10; + while(speed_inc >= 0.5) + { + IC.vc=speed; + Long_control=0;Theta=0;Throttle_pct=0.0; + failf=trim_longfr(kmax,IC); + if(Long_control <= 0) + elevator=Long_control*28; + else + elevator=Long_control*23; + if(fabs(CL) > 1E-3) + { + cmcl=cm / CL; + } + if(failf == 0) + { + lastgood=speed; + axis[0]='\0'; + //fprintf(out,"%g,%g,%g,%g,%g,%d",V_calibrated_kts,Alpha*RAD_TO_DEG,Long_control,Throttle_pct,Flap_Position,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("trim failed at: %g knots, %g lbs, %g %%MAC, Flaps: %g\n",V_calibrated_kts,Weight,Cg,Flap_Position); + printf("wdot: %g, udot: %g, qdot: %g\n",W_dot_body,U_dot_body,Q_dot_body); + printf("Alpha: %g, Throttle_pct: %g, Long_control: %g\n\n",Alpha*RAD_TO_DEG,Throttle_pct,Long_control); + printf("Speed increment: %g\n",speed_inc); + speed+=speed_inc; + speed_inc/=2; + } + speed-=speed_inc; + + + } + printf("failf %d\n",failf); + if(failf == 1) + strcpy(axis,"lift"); + else if(failf == 2) + strcpy(axis,"thrust"); + else if(failf == 3) + strcpy(axis,"pitch"); + fprintf(out,"Last good speed: %g, Flaps: %g, Weight: %g, CG: %g, failed axis: %s\n",lastgood,Flap_handle,Weight,Cg,axis); + + + } + } + fclose(out); + //free(failf); +} + + +// 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); +} + + + +// Run an iteration of the EOM (equations of motion) +int main(int argc, char *argv[]) { + + + double save_alt = 0.0; + int multiloop=1,k=0,i,j; + double time=0,elev_trim,elev_trim_save,elevator,speed,cmcl; + FILE *out; + double hgain,hdiffgain,herr,herrprev,herr_diff,htarget; + double lastVt,vtdots,vtdott; + InitialConditions IC; + SCALAR *control[7]; + SCALAR *state[7]; + float old_state,effectiveness,tol,delta_state,lctrim; + + if(argc < 6) + { + printf("Need args: $c172 speed alt alpha elev throttle\n"); + exit(1); + } + initIC(&IC); + + 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=0; + IC.beta=0; + IC.gamma=strtod(argv[3],NULL); + IC.use_gamma_tmg=1; + IC.phi=0; + IC.psi=10; + IC.weight=2300; + IC.cg=0.25; + IC.flap_handle=0; + IC.long_control=strtod(argv[4],NULL); + IC.rudder_pedal=0; + + printf("IC.vc: %g\n",IC.vc); + ls_ForceAltitude(IC.altitude); + fgLaRCsimInit(0.01); + printf("\nLong_control: %g\n\n",Long_control); + + + IC.altitude=1000; + setIC(IC); + ls_loop(0.0,-1); + IC.flap_handle=10; + setIC(IC); + ls_loop(0.0,-1); + IC.flap_handle=20; + setIC(IC); + ls_loop(0.0,-1); + IC.flap_handle=30; + setIC(IC); + ls_loop(0.0,-1); + + /* find_trim_stall(200,out,IC); + + IC.vc=120; + IC.altitude=8000; + IC.weight=2300; + IC.cg=0.25; + IC.flap_handle=0; + + + setIC(IC); + printIC(IC); + k=trim_long(100,IC); + + printf("Flap_handle: %g, Flap_Position: %g\n",Flap_handle,Flap_Position); + printf("k: %d, %g knots, %g lbs, %g %%MAC\n",k,V_calibrated_kts,Weight,Cg); + printf("wdot: %g, udot: %g, qdot: %g\n",W_dot_body,U_dot_body,Q_dot_body); + printf("Alpha: %g, Throttle_pct: %g, Long_control: %g\n\n",Alpha,Throttle_pct,Long_control); + + printf("Cme: %g, elevator: %g, Cmde: %g\n",elevator*Cmde,elevator,Cmde); + + IC.cg=0.155; + setIC(IC); + k=trim_long(100,IC); + + printf("Flap_handle: %g, Flap_Position: %g\n",Flap_handle,Flap_Position); + printf("k: %d, %g knots, %g lbs, %g %%MAC\n",k,V_calibrated_kts,Weight,Cg); + printf("wdot: %g, udot: %g, qdot: %g\n",W_dot_body,U_dot_body,Q_dot_body); + printf("Alpha: %g, Throttle_pct: %g, Long_control: %g\n\n",Alpha,Throttle_pct,Long_control); + + printf("Cme: %g, elevator: %g, Cmde: %g\n",elevator*Cmde,elevator,Cmde); + + IC.cg=0.364; + setIC(IC); + k=trim_long(100,IC); + + printf("Flap_handle: %g, Flap_Position: %g\n",Flap_handle,Flap_Position); + printf("k: %d, %g knots, %g lbs, %g %%MAC\n",k,V_calibrated_kts,Weight,Cg); + printf("wdot: %g, udot: %g, qdot: %g\n",W_dot_body,U_dot_body,Q_dot_body); + printf("Alpha: %g, Throttle_pct: %g, Long_control: %g\n\n",Alpha,Throttle_pct,Long_control); + + printf("Cme: %g, elevator: %g, Cmde: %g\n",elevator*Cmde,elevator,Cmde); + */ + + + + + + /* do_trims(400,out,IC); */ + + /* ls_loop(0.0,-1); + + control[1]=&IC.long_control; + control[2]=&IC.throttle; + control[3]=&IC.alpha; + control[4]=&IC.beta; + control[5]=&IC.phi; + control[6]=&IC.lat_control; + + state[1]=&Q_dot_body;state[2]=&U_dot_body;state[3]=&W_dot_body; + state[4]=&R_dot_body;state[5]=&V_dot_body;state[6]=&P_dot_body; + + + for(i=1;i<=6;i++) + { + old_state=*state[i]; + tol=1E-4; + for(j=1;j<=6;j++) + { + *control[j]+=0.1; + setIC(IC); + ls_loop(0.0,-1); + delta_state=*state[i]-old_state; + effectiveness=(delta_state)/ 0.1; + if(delta_state < tol) + effectiveness = 0; + printf("%8.4f,",delta_state); + *control[j]-=0.1; + + } + printf("\n"); + setIC(IC); + ls_loop(0.0,-1); + } */ + + return 1; +} + +/* void do_stick_pull(int kmax, SCALAR tmax,FILE *out,InitialConditions IC) { @@ -382,9 +360,9 @@ void do_stick_pull(int kmax, SCALAR tmax,FILE *out,InitialConditions IC) 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); + //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); } @@ -407,9 +385,9 @@ void do_stick_pull(int kmax, SCALAR tmax,FILE *out,InitialConditions IC) 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); + //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); @@ -432,14 +410,14 @@ void do_takeoff(FILE *out) out=fopen("takeoff.out","w"); herr=Q_body-htarget; - //attempt to maintain zero pitch rate during the roll + // attempt to maintain zero pitch rate during the roll while((V_calibrated_kts < 61) && (time < 30.0)) { - /* herrprev=herr;*/ + // herrprev=herr ls_update(1); - /*herr=Q_body-htarget; - herr_diff=herr-herrprev; - Long_control=elev_trim+(hgain*herr + hdiffgain*herr_diff); */ + // 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); @@ -486,325 +464,6 @@ void do_takeoff(FILE *out) -} - -// 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); -} - - - -// Run an iteration of the EOM (equations of motion) -int main(int argc, char *argv[]) { - - - double save_alt = 0.0; - int multiloop=1,k=0,i,j; - double time=0,elev_trim,elev_trim_save,elevator,speed,cmcl; - FILE *out; - double hgain,hdiffgain,herr,herrprev,herr_diff,htarget; - double lastVt,vtdots,vtdott; - InitialConditions IC; - SCALAR *control[7]; - SCALAR *state[7]; - float old_state,effectiveness,tol,delta_state,lctrim; - - if(argc < 6) - { - printf("Need args: $c172 speed alt alpha elev throttle\n"); - exit(1); - } - initIC(&IC); - 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=0; - IC.beta=0; - IC.gamma=strtod(argv[3],NULL); - IC.use_gamma_tmg=1; - IC.phi=0; - IC.psi=10; - IC.weight=2300; - IC.cg=0.25; - IC.flap_handle=0; - IC.long_control=strtod(argv[4],NULL); - IC.rudder_pedal=0; - - printf("IC.vc: %g\n",IC.vc); - ls_ForceAltitude(IC.altitude); - fgLaRCsimInit(0.01); - printf("\nLong_control: %g\n\n",Long_control); - - setIC(IC); - printf("V_down: %g, V_north: %g V_east: %g\n",V_down,V_north,V_east); - - ls_loop(0.0,-1); - printf("V_down: %g, V_north: %g V_east: %g\n",V_down,V_north,V_east); - printf("Flap_Handle: %g, Flap_Position: %g\n",Flap_Handle,Flap_Position); - printf("k:, %d, %g knots, %g lbs, %g %%MAC\n",k,V_calibrated_kts,Weight,Cg); - printf("wdot: %g, udot: %g, qdot: %g\n",W_dot_body,U_dot_body,Q_dot_body); - printf("Alpha: %g, Throttle_pct: %g, Long_control: %g\n\n",Alpha,Throttle_pct,Long_control); - - printf("Cme: %g, elevator: %g, Cmde: %g\n",elevator*Cmde,elevator,Cmde); - - k=trim_long(100,IC); - printf("Flap_Handle: %g, Flap_Position: %g\n",Flap_Handle,Flap_Position); - printf("k:, %d, %g knots, %g lbs, %g %%MAC\n",k,V_calibrated_kts,Weight,Cg); - printf("wdot: %g, udot: %g, qdot: %g\n",W_dot_body,U_dot_body,Q_dot_body); - printf("Alpha: %g, Throttle_pct: %g, Long_control: %g\n\n",Alpha,Throttle_pct,Long_control); - - printf("Cme: %g, elevator: %g, Cmde: %g\n",elevator*Cmde,elevator,Cmde); - - - i=0; - while(i < 20) - { - ls_update(1); - i++; - } - Flap_Handle=10; - while((Flap_Position < 5) && (i < 500)) - { - printf("Flap_Handle: %2.0f, Flap_Position: %5.2f",Flap_Handle,Flap_Position); - printf(" Flaps_In_Transit: %d\n", Flaps_In_Transit); -/* printf(" CLo: %7.4f, Cdo: %7.4f, Cmo: %7.4f\n",CLo,Cdo,Cmo); - */ - ls_update(1); - i++; - } - Flap_Handle=0; - while((Flap_Position > 0) || (i < 500)) - { - printf("Flap_Handle: %2.0f, Flap_Position: %5.2f",Flap_Handle,Flap_Position); - printf(" Flaps_In_Transit: %d\n", Flaps_In_Transit); -/* printf(" CLo: %7.4f, Cdo: %7.4f, Cmo: %7.4f\n",CLo,Cdo,Cmo); - */ - ls_update(1); - i++; - } - - - /* do_trims(400,out,IC); */ - - /* ls_loop(0.0,-1); - - control[1]=&IC.long_control; - control[2]=&IC.throttle; - control[3]=&IC.alpha; - control[4]=&IC.beta; - control[5]=&IC.phi; - control[6]=&IC.lat_control; - - state[1]=&Q_dot_body;state[2]=&U_dot_body;state[3]=&W_dot_body; - state[4]=&R_dot_body;state[5]=&V_dot_body;state[6]=&P_dot_body; - - - for(i=1;i<=6;i++) - { - old_state=*state[i]; - tol=1E-4; - for(j=1;j<=6;j++) - { - *control[j]+=0.1; - setIC(IC); - ls_loop(0.0,-1); - delta_state=*state[i]-old_state; - effectiveness=(delta_state)/ 0.1; - if(delta_state < tol) - effectiveness = 0; - printf("%8.4f,",delta_state); - *control[j]-=0.1; - - } - printf("\n"); - setIC(IC); - ls_loop(0.0,-1); - } */ - - 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 ); } */