Added flaps support to c172 model.
This commit is contained in:
curt
parent
0c0071533c
commit
06b966ee53
7 changed files with 298 additions and 112 deletions
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@ -89,6 +89,7 @@ int FGLaRCsim::update( int multiloop ) {
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Long_control = controls.get_elevator();
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Long_trim = controls.get_elevator_trim();
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Rudder_pedal = controls.get_rudder();
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Flap_handle = 30.0 * controls.get_flaps();
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Throttle_pct = controls.get_throttle( 0 ) * 1.0;
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Brake_pct = controls.get_brake( 0 );
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@ -95,6 +95,7 @@
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#define NCL 11
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#define Ndf 4
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#define DYN_ON_SPEED 33 /*20 knots*/
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@ -140,41 +141,62 @@ SCALAR interp(SCALAR *y_table, SCALAR *x_table, int Ntable, SCALAR x)
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}
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void aero( SCALAR dt, int Initialize ) {
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static int init = 0;
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static int flap_dir=0;
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static SCALAR lastFlapHandle=0;
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static SCALAR trim_inc = 0.0002;
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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};
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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};
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static SCALAR flap_ind[Ndf]={0,10,20,30};
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static SCALAR dCLf[Ndf]={0,0.20,0.30,0.35};
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static SCALAR dCdf[Ndf]={0,0.0021,0.0085,0.0191};
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static SCALAR dCmf[Ndf]={0,-0.186,-0.28,-0.325};
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static SCALAR flap_transit_rate=2.5;
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/* printf("Initialize= %d\n",Initialize); */
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/* printf("Initializing aero model...Initialize= %d\n", Initialize);
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*/ CLadot=1.7;
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*/
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/*nondimensionalization quantities*/
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/*units here are ft and lbs */
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cbar=4.9; /*mean aero chord ft*/
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b=35.8; /*wing span ft */
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Sw=174; /*wing planform surface area ft^2*/
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rPiARe=0.054; /*reciprocal of Pi*AR*e*/
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lbare=3.682; /*elevator moment arm / MAC*/
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CLadot=1.7;
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CLq=3.9;
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CLde=0.43;
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CLo=0;
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CLob=0;
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Cdo=0.031;
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Cdob=0.031;
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Cda=0.13; /*Not used*/
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Cdde=0.06;
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Cma=-0.89;
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Cma=-1.8;
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Cmadot=-5.2;
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Cmq=-12.4;
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Cmo=-0.015;
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Cmde=-1.28;
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Cmob=-0.00;
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Cmde=-1.00;
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CLde=-Cmde / lbare; /* kinda backwards, huh? */
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Clbeta=-0.089;
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Clp=-0.47;
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Clr=0.096;
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Clda=-0.178;
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Clda=-0.09;
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Cldr=0.0147;
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Cnbeta=0.065;
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@ -189,12 +211,7 @@ void aero( SCALAR dt, int Initialize ) {
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Cyda=0.0;
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Cydr=0.187;
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/*nondimensionalization quantities*/
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/*units here are ft and lbs */
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cbar=4.9; /*mean aero chord ft*/
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b=35.8; /*wing span ft */
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Sw=174; /*wing planform surface area ft^2*/
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rPiARe=0.054; /*reciprocal of Pi*AR*e*/
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MaxTakeoffWeight=2550;
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EmptyWeight=1500;
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@ -230,9 +247,51 @@ void aero( SCALAR dt, int Initialize ) {
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Dz_cg=Zcg*cbar;
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if(Flap_handle < flap_ind[0])
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{
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Flap_handle=flap_ind[0];
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Flap_Position=flap_ind[0];
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}
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else if(Flap_handle > flap_ind[3])
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{
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Flap_handle=flap_ind[3];
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Flap_Position=flap_ind[3];
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}
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else
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{
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if((Flap_handle != lastFlapHandle) && (dt > 0))
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Flaps_In_Transit=1;
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else if(dt <= 0)
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Flap_Position=Flap_handle;
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lastFlapHandle=Flap_handle;
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if((Flaps_In_Transit) && (dt > 0))
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{
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if(Flap_Position < 10)
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flap_transit_rate = 2.5;
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else
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flap_transit_rate=5;
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if(Flaps_In_Transit)
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{
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if(Flap_Position < Flap_handle)
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flap_dir=1;
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else
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flap_dir=-1;
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if(fabs(Flap_Position - Flap_handle) > dt*flap_transit_rate)
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Flap_Position+=flap_dir*flap_transit_rate*dt;
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if(fabs(Flap_Position - Flap_handle) < dt*flap_transit_rate)
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{
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Flaps_In_Transit=0;
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Flap_Position=Flap_handle;
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}
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}
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}
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}
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long_trim=0;
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if(Aft_trim) long_trim = long_trim - trim_inc;
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@ -258,6 +317,8 @@ void aero( SCALAR dt, int Initialize ) {
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/*hack to avoid divide by zero*/
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/*the dynamic terms might be negligible at low ground speeds anyway*/
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/* printf("Vinf: %g, Span: %g\n",V_rel_wind,b);
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*/
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if(V_rel_wind > DYN_ON_SPEED)
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{
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cbar_2V=cbar/(2*V_rel_wind);
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@ -278,21 +339,33 @@ void aero( SCALAR dt, int Initialize ) {
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/* 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);
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*/ //printf("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);
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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);
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*/
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/* sum coefficients */
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CLwbh = interp(CLtable,alpha_ind,NCL,Alpha);
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CLo = CLob + interp(dCLf,flap_ind,Ndf,Flap_Position);
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Cdo = Cdob + interp(dCdf,flap_ind,Ndf,Flap_Position);
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Cmo = Cmob + interp(dCmf,flap_ind,Ndf,Flap_Position);
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/* printf("FP: %g\n",Flap_Position);
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printf("CLo: %g\n",CLo);
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printf("Cdo: %g\n",Cdo);
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printf("Cmo: %g\n",Cmo);
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*/
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CL = CLo + CLwbh + (CLadot*Alpha_dot + CLq*Theta_dot)*cbar_2V + CLde*elevator;
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cd = Cdo + rPiARe*CL*CL + Cdde*elevator;
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cy = Cybeta*Beta + (Cyp*P_body + Cyr*R_body)*b_2V + Cyda*aileron + Cydr*rudder;
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cm = Cmo + Cma*Alpha + (Cmq*Q_body + Cmadot*Alpha_dot)*cbar_2V + Cmde*(elevator+long_trim);
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cm = Cmo + Cma*Alpha + (Cmq*Q_body + Cmadot*Alpha_dot)*cbar_2V + Cmde*(elevator);
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cn = Cnbeta*Beta + (Cnp*P_body + Cnr*R_body)*b_2V + Cnda*aileron + Cndr*rudder;
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croll=Clbeta*Beta + (Clp*P_body + Clr*R_body)*b_2V + Clda*aileron + Cldr*rudder;
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/* 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);
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*/ /*calculate wind axes forces*/
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*/
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/*calculate wind axes forces*/
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F_X_wind=-1*cd*qS;
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F_Y_wind=cy*qS;
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F_Z_wind=-1*CL*qS;
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@ -315,8 +388,9 @@ void aero( SCALAR dt, int Initialize ) {
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/* 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);
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*/
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/* printf("Fxaero: %7.4f Fyaero: %7.4f Fzaero: %7.4f Weight: %7.4f\n",F_X_aero,F_Y_aero,F_Z_aero,W);
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*//* printf("Maero: %7.4f Naero: %7.4f Raero: %7.4f\n",M_m_aero,M_n_aero,M_l_aero);
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/* printf("Fxaero: %7.4f Fyaero: %7.4f Fzaero: %7.4f Weight: %7.4f\n",F_X_aero,F_Y_aero,F_Z_aero,Weight);
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*/
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/* printf("Maero: %7.4f Naero: %7.4f Raero: %7.4f\n",M_m_aero,M_n_aero,M_l_aero);
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*/
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}
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@ -5,17 +5,17 @@
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SCALAR CLadot;
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SCALAR CLq;
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SCALAR CLde;
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SCALAR CLo;
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SCALAR CLob;
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SCALAR Cdo;
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SCALAR Cdob;
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SCALAR Cda; /*Not used*/
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SCALAR Cdde;
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SCALAR Cma;
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SCALAR Cmadot;
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SCALAR Cmq;
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SCALAR Cmo;
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SCALAR Cmob;
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SCALAR Cmde;
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SCALAR Clbeta;
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@ -42,6 +42,7 @@
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SCALAR b; /*wing span ft */
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SCALAR Sw; /*wing planform surface area ft^2*/
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SCALAR rPiARe; /*reciprocal of Pi*AR*e*/
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SCALAR lbare; /*elevator moment arm MAC*/
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SCALAR Weight; /*lbs*/
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SCALAR MaxTakeoffWeight,EmptyWeight;
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@ -49,7 +50,8 @@
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SCALAR Zcg; /*%MAC*/
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SCALAR CLwbh,CL,cm,cd,cn,cy,croll,cbar_2V,b_2V,qS,qScbar,qSb,ps,rs;
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SCALAR CLwbh,CL,cm,cd,cn,cy,croll,cbar_2V,b_2V,qS,qScbar,qSb;
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SCALAR CLo,Cdo,Cmo;
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SCALAR F_X_wind,F_Y_wind,F_Z_wind;
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@ -57,3 +59,8 @@
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SCALAR elevator, aileron, rudder;
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SCALAR Flap_Position;
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/* float Flap_Handle; */
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int Flaps_In_Transit;
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@ -60,6 +60,7 @@
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#include "ls_generic.h"
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#include "ls_cockpit.h"
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#include "ls_constants.h"
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#include "c172_aero.h"
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void model_init( void ) {
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@ -71,6 +72,8 @@ void model_init( void ) {
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I_yy=1346;
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I_zz=1967;
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I_xz=0;
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Flap_Position=Flap_handle;
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Flaps_In_Transit=0;
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}
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@ -40,13 +40,31 @@
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//simple "one-at-a-time" longitudinal trimming routine
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typedef struct
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{
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double latitude,longitude,altitude;
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double vc,alpha,beta,gamma;
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double theta,phi,psi;
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double weight,cg;
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SCALAR latitude,longitude,altitude;
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SCALAR vc,alpha,beta,gamma;
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SCALAR theta,phi,psi;
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SCALAR weight,cg;
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SCALAR throttle,long_control,lat_control,rudder_pedal,flap_handle;
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int use_gamma_tmg;
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}InitialConditions;
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void initIC(InitialConditions *IC)
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{
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IC->latitude=IC->longitude=IC->altitude=0;
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IC->vc=IC->alpha=IC->beta=IC->gamma=0;
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IC->theta=IC->phi=IC->psi=0;
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IC->weight=IC->cg=0;
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IC->throttle=IC->long_control=IC->lat_control=IC->rudder_pedal=IC->flap_handle=0;
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}
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void checkLimits(float *control, SCALAR min, SCALAR max)
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{
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if(*control < min)
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*control=min;
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else if(*control > max)
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*control=max;
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}
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// Units for setIC
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// vc knots (calibrated airspeed, close to indicated)
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// altitude ft
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@ -118,6 +136,22 @@ void setIC(InitialConditions IC)
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Theta=thetar;
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Phi=phir;
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Psi=psir;
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Throttle_pct=IC.throttle;
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checkLimits(&Throttle_pct,0,1);
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Long_control=IC.long_control;
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checkLimits(&Long_control,-1,1);
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Lat_control=IC.lat_control;
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checkLimits(&Lat_control,-1,1);
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Rudder_pedal=IC.rudder_pedal;
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checkLimits(&Rudder_pedal,-1,1);
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Flap_Handle=IC.flap_handle;
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checkLimits(&Flap_Handle,0,30);
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}
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@ -128,7 +162,7 @@ int trim_long(int kmax, InitialConditions IC)
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double tol=1E-3;
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double a_tol=tol/10;
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double alpha_step=0.001;
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int k=0,i,j=0,jmax=10,sum=0;
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int k=0,i,j=0,jmax=40,sum=0,trim_failed=0;
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ls_loop(0.0,-1);
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do{
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//printf("k: %d\n",k);
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@ -144,39 +178,47 @@ int trim_long(int kmax, InitialConditions IC)
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*/ j++;
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}
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sum+=j;
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/* 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);
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*/ j=0;
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if(trim_failed)
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printf("\tAlpha: %7.4f, wdot: %10.6f, j: %d\n",Alpha*RAD_TO_DEG,W_dot_body,j);
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j=0;
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while((fabs(U_dot_body) > tol) && (j < jmax))
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{
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Throttle_pct-=U_dot_body*0.005;
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if((Throttle_pct < 0) || (Throttle_pct > 1))
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Throttle_pct=0.2;
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IC.throttle-=U_dot_body*0.01;
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setIC(IC);
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ls_loop(0.0,-1);
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j++;
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}
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sum+=j;
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/* printf("\tThrottle_pct: %7.4f, udot: %10.6f, j: %d\n",Throttle_pct,U_dot_body,j);
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*/ j=0;
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if(trim_failed)
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printf("\tThrottle_pct: %7.4f, udot: %10.6f, j: %d\n",Throttle_pct,U_dot_body,j);
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j=0;
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while((fabs(Q_dot_body) > a_tol) && (j < jmax))
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{
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Long_control+=Q_dot_body*0.001;
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if((Long_control < -1) || (Long_control > 1))
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j=jmax;
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setIC(IC);
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IC.long_control+=Q_dot_body*0.01;
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setIC(IC);
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ls_loop(0.0,-1);
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j++;
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}
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if(trim_failed)
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printf("\tLong_control: %7.4f, qdot: %10.6f, j: %d\n",Long_control,Q_dot_body,j);
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sum+=j;
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if(Long_control >= 0)
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elevator=Long_control*23;
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else
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elevator=Long_control*28;
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/* printf("\televator: %7.4f, qdot: %10.6f, j: %d\n",elevator,Q_dot_body,j);
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*/ k++;j=0;
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}while(((fabs(W_dot_body) > tol) || (fabs(U_dot_body) > tol) || (fabs(Q_dot_body) > tol)) && (k < kmax));
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if(k == kmax-2)
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{
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if((fabs(W_dot_body) > tol) || (fabs(U_dot_body) > tol) || (fabs(Q_dot_body) > a_tol));
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{
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trim_failed=1;
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jmax=kmax;
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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;
|
||||
}
|
||||
|
|
@ -266,7 +308,7 @@ void do_trims(int kmax,FILE *out,InitialConditions IC)
|
|||
{
|
||||
int k=0,i;
|
||||
double speed,elevator,cmcl;
|
||||
out=fopen("trims.out","w");
|
||||
out=fopen("trims.oldCmde.out","w");
|
||||
speed=55;
|
||||
|
||||
for(i=1;i<=5;i++)
|
||||
|
|
@ -303,10 +345,10 @@ void do_trims(int kmax,FILE *out,InitialConditions IC)
|
|||
*/ }
|
||||
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);
|
||||
|
||||
}
|
||||
/* 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;
|
||||
}
|
||||
}
|
||||
|
|
@ -461,80 +503,131 @@ int main(int argc, char *argv[]) {
|
|||
|
||||
|
||||
double save_alt = 0.0;
|
||||
int multiloop=1,k=0,i;
|
||||
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=10;
|
||||
IC.alpha=0;
|
||||
IC.beta=0;
|
||||
IC.theta=strtod(argv[3],NULL);
|
||||
IC.use_gamma_tmg=0;
|
||||
IC.gamma=strtod(argv[3],NULL);
|
||||
IC.use_gamma_tmg=1;
|
||||
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");
|
||||
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);
|
||||
|
||||
while(IC.alpha < 30.0)
|
||||
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);
|
||||
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);
|
||||
|
||||
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);
|
||||
*/
|
||||
|
||||
/* Inform LaRCsim of the local terrain altitude */
|
||||
|
||||
|
||||
|
||||
return 1;
|
||||
return 1;
|
||||
}
|
||||
|
||||
|
||||
|
|
|
|||
|
|
@ -35,8 +35,11 @@
|
|||
|
||||
$Header$
|
||||
$Log$
|
||||
Revision 1.1 1999/06/17 18:07:34 curt
|
||||
Initial revision
|
||||
Revision 1.2 1999/10/29 16:08:32 curt
|
||||
Added flaps support to c172 model.
|
||||
|
||||
Revision 1.1.1.1 1999/06/17 18:07:34 curt
|
||||
Start of 0.7.x branch
|
||||
|
||||
Revision 1.2 1999/04/22 18:47:25 curt
|
||||
Wrap with extern "C" { } if building with __cplusplus compiler.
|
||||
|
|
@ -82,6 +85,7 @@ extern "C" {
|
|||
|
||||
typedef struct {
|
||||
float long_stick, lat_stick, rudder_pedal;
|
||||
float flap_handle;
|
||||
float long_trim;
|
||||
float throttle[4];
|
||||
short forward_trim, aft_trim, left_trim, right_trim;
|
||||
|
|
@ -96,6 +100,7 @@ extern COCKPIT cockpit_;
|
|||
#define Left_button cockpit_.left_pb_on_stick
|
||||
#define Right_button cockpit_.right_pb_on_stick
|
||||
#define Rudder_pedal cockpit_.rudder_pedal
|
||||
#define Flap_handle cockpit_.flap_handle
|
||||
#define Throttle cockpit_.throttle
|
||||
#define Throttle_pct cockpit_.throttle_pct
|
||||
#define First_trigger cockpit_.trig_pos_1
|
||||
|
|
|
|||
|
|
@ -50,8 +50,11 @@
|
|||
|
||||
$Header$
|
||||
$Log$
|
||||
Revision 1.1 1999/06/17 18:07:33 curt
|
||||
Initial revision
|
||||
Revision 1.2 1999/10/29 16:08:33 curt
|
||||
Added flaps support to c172 model.
|
||||
|
||||
Revision 1.1.1.1 1999/06/17 18:07:33 curt
|
||||
Start of 0.7.x branch
|
||||
|
||||
Revision 1.1.1.1 1999/04/05 21:32:45 curt
|
||||
Start of 0.6.x branch.
|
||||
|
|
@ -217,7 +220,7 @@ void ls_step( SCALAR dt, int Initialize ) {
|
|||
/* set flag; disable integrators */
|
||||
|
||||
inited = -1;
|
||||
dt = 0;
|
||||
dt = 0.0;
|
||||
|
||||
}
|
||||
|
||||
|
|
|
|||
Loading…
Add table
Reference in a new issue