Updates from Tony, mostly to landing gear.
This commit is contained in:
curt
parent
40a1a07730
commit
5bcd8c700b
4 changed files with 222 additions and 202 deletions
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@ -147,6 +147,7 @@ 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 Ai;
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static SCALAR trim_inc = 0.0002;
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@ -180,9 +181,8 @@ void aero( SCALAR dt, int Initialize ) {
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CLob=0;
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/* original */ /* Cdob=0.031; */
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Cdob=0.046;
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Ai=1.24;
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Cdob=0.036;
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Cda=0.13; /*Not used*/
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Cdde=0.06;
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@ -263,11 +263,13 @@ void aero( SCALAR dt, int Initialize ) {
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{
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if((Flap_handle != lastFlapHandle) && (dt > 0)) {
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if((Flap_handle != lastFlapHandle) && (dt > 0))
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{
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Flaps_In_Transit=1;
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} else if(dt <= 0) {
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}
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else if(dt <= 0)
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Flap_Position=Flap_handle;
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}
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lastFlapHandle=Flap_handle;
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if((Flaps_In_Transit) && (dt > 0))
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@ -317,7 +319,7 @@ void aero( SCALAR dt, int Initialize ) {
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/*calculate rate derivative nondimensionalization (is that a word?) factors */
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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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/*the dynamic terms are 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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@ -357,12 +359,14 @@ void aero( SCALAR dt, int Initialize ) {
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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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printf("Cmo: %g\n",Cmo); */
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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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cd = Cdo + rPiARe*Ai*Ai*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);
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@ -70,18 +70,26 @@ $Header$
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extern SIM_CONTROL sim_control_;
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void engine( SCALAR dt, int init ) {
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/* if (init) { */
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float v,h,pa;
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float bhp=160;
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Throttle[3] = Throttle_pct;
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/* } */
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/* F_X_engine = Throttle[3]*813.4/0.2; */ /* original code */
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/* F_Z_engine = Throttle[3]*11.36/0.2; */ /* original code */
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F_X_engine = Throttle[3]*400/0.83;
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F_Z_engine = Throttle[3]*4.9/0.83;
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v=V_rel_wind;
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h=Altitude;
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if(V_rel_wind < 10)
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v=10;
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if(Altitude < 0)
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h=0;
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pa=(0.00144*v + 0.546)*(1 - 1.6E-5*h)*bhp;
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if(pa < 0)
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pa=0;
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F_X_engine= Throttle[3]*(pa*550)/v;
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M_m_engine = F_X_engine*0.734*cbar;
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/* 0.734 - estimated (WAGged) location of thrust line in the z-axis*/
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Throttle_pct = Throttle[3];
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}
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@ -36,12 +36,8 @@
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$Header$
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$Log$
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Revision 1.10 1999/11/03 16:46:24 curt
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Patches from Tony to enable brakes.
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Revision 1.9 1999/11/01 18:17:16 curt
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c172 updates from Tony. Fix extra yaw when using ailerons. Flaps and elevator
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tweaks.
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Revision 1.11 1999/11/15 22:54:07 curt
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Updates from Tony, mostly to landing gear.
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----------------------------------------------------------------------------
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@ -71,6 +67,8 @@ tweaks.
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#include "ls_generic.h"
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#include "ls_cockpit.h"
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#define HEIGHT_AGL_WHEEL d_wheel_rwy_local_v[2]
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sub3( DATA v1[], DATA v2[], DATA result[] )
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{
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@ -115,7 +113,7 @@ clear3( DATA v[] )
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gear()
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{
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char rcsid[] = "$Id$";
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char gear_strings[3][12]={"nose","right main", "left main"};
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/*
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* Aircraft specific initializations and data goes here
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*/
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@ -125,14 +123,14 @@ char rcsid[] = "$Id$";
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static int num_wheels = NUM_WHEELS; /* number of wheels */
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static DATA d_wheel_rp_body_v[NUM_WHEELS][3] = /* X, Y, Z locations */
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{
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{ 10., 0., 4. }, /* in feet */
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{ -1., 3., 4. },
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{ -1., -3., 4. }
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{ 5, 0., 7.0 }, /*nose*/ /* in feet */
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{ -2.0, 3.6, 6.5 }, /*right main*/
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{ -2.0, -3.6, 6.5 } /*left main*/
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};
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static DATA spring_constant[NUM_WHEELS] = /* springiness, lbs/ft */
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{ 1500., 5000., 5000. };
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static DATA spring_damping[NUM_WHEELS] = /* damping, lbs/ft/sec */
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{ 100., 150., 150. };
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{ 1000., 1500., 1500. };
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static DATA percent_brake[NUM_WHEELS] = /* percent applied braking */
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{ 0., 0., 0. }; /* 0 = none, 1 = full */
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static DATA caster_angle_rad[NUM_WHEELS] = /* steerable tires - in */
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@ -202,117 +200,134 @@ char rcsid[] = "$Id$";
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percent_brake[1] = Brake_pct; /* replace with cockpit brake handle connection code */
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percent_brake[2] = percent_brake[1];
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caster_angle_rad[0] = 0.03*Rudder_pedal;
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caster_angle_rad[0] = 0.52*Rudder_pedal;
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for (i=0;i<num_wheels;i++) /* Loop for each wheel */
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for (i=0;i<num_wheels;i++) /* Loop for each wheel */
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{
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/*========================================*/
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/* Calculate wheel position w.r.t. runway */
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/*========================================*/
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/* First calculate wheel location w.r.t. cg in body (X-Y-Z) axes... */
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sub3( d_wheel_rp_body_v[i], D_cg_rp_body_v, d_wheel_cg_body_v );
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/* then converting to local (North-East-Down) axes... */
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multtrans3x3by3( T_local_to_body_m, d_wheel_cg_body_v, d_wheel_cg_local_v );
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/* Runway axes correction - third element is Altitude, not (-)Z... */
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d_wheel_cg_local_v[2] = -d_wheel_cg_local_v[2]; /* since altitude = -Z */
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/* Add wheel offset to cg location in local axes */
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add3( d_wheel_cg_local_v, D_cg_rwy_local_v, d_wheel_rwy_local_v );
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/* remove Runway axes correction so right hand rule applies */
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d_wheel_cg_local_v[2] = -d_wheel_cg_local_v[2]; /* now Z positive down */
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/*============================*/
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/* Calculate wheel velocities */
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/*============================*/
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/* contribution due to angular rates */
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cross3( Omega_body_v, d_wheel_cg_body_v, temp3a );
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/* transform into local axes */
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multtrans3x3by3( T_local_to_body_m, temp3a, temp3b );
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/* printf("%s:\n",gear_strings[i]); */
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/* plus contribution due to cg velocities */
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/*========================================*/
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/* Calculate wheel position w.r.t. runway */
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/*========================================*/
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add3( temp3b, V_local_rel_ground_v, v_wheel_local_v );
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/*===========================================*/
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/* Calculate forces & moments for this wheel */
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/*===========================================*/
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/* Add any anticipation, or frame lead/prediction, here... */
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/* no lead used at present */
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/* Calculate sideward and forward velocities of the wheel
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in the runway plane */
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cos_wheel_hdg_angle = cos(caster_angle_rad[i] + Psi);
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sin_wheel_hdg_angle = sin(caster_angle_rad[i] + Psi);
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v_wheel_forward = v_wheel_local_v[0]*cos_wheel_hdg_angle
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+ v_wheel_local_v[1]*sin_wheel_hdg_angle;
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v_wheel_sideward = v_wheel_local_v[1]*cos_wheel_hdg_angle
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- v_wheel_local_v[0]*sin_wheel_hdg_angle;
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/* First calculate wheel location w.r.t. cg in body (X-Y-Z) axes... */
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/* Calculate normal load force (simple spring constant) */
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reaction_normal_force = 0.;
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if( d_wheel_rwy_local_v[2] < 0. )
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{
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reaction_normal_force = spring_constant[i]*d_wheel_rwy_local_v[2]
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- v_wheel_local_v[2]*spring_damping[i];
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if (reaction_normal_force > 0.) reaction_normal_force = 0.;
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/* to prevent damping component from swamping spring component */
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}
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/* Calculate friction coefficients */
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forward_mu = (max_brake_mu - rolling_mu)*percent_brake[i] + rolling_mu;
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abs_v_wheel_sideward = sqrt(v_wheel_sideward*v_wheel_sideward);
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sideward_mu = sliding_mu;
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if (abs_v_wheel_sideward < skid_v)
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sideward_mu = (abs_v_wheel_sideward - bkout_v)*beta_mu;
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if (abs_v_wheel_sideward < bkout_v) sideward_mu = 0.;
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sub3( d_wheel_rp_body_v[i], D_cg_rp_body_v, d_wheel_cg_body_v );
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/* then converting to local (North-East-Down) axes... */
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multtrans3x3by3( T_local_to_body_m, d_wheel_cg_body_v, d_wheel_cg_local_v );
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/* Runway axes correction - third element is Altitude, not (-)Z... */
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d_wheel_cg_local_v[2] = -d_wheel_cg_local_v[2]; /* since altitude = -Z */
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/* Add wheel offset to cg location in local axes */
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add3( d_wheel_cg_local_v, D_cg_rwy_local_v, d_wheel_rwy_local_v );
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/* remove Runway axes correction so right hand rule applies */
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d_wheel_cg_local_v[2] = -d_wheel_cg_local_v[2]; /* now Z positive down */
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/*============================*/
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/* Calculate wheel velocities */
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/*============================*/
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/* contribution due to angular rates */
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cross3( Omega_body_v, d_wheel_cg_body_v, temp3a );
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/* transform into local axes */
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multtrans3x3by3( T_local_to_body_m, temp3a, temp3b );
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/* plus contribution due to cg velocities */
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add3( temp3b, V_local_rel_ground_v, v_wheel_local_v );
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clear3(f_wheel_local_v);
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reaction_normal_force=0;
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if( HEIGHT_AGL_WHEEL < 0. )
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/*the wheel is underground -- which implies ground contact
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so calculate reaction forces */
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{
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/*===========================================*/
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/* Calculate forces & moments for this wheel */
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/*===========================================*/
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/* Add any anticipation, or frame lead/prediction, here... */
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/* no lead used at present */
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/* Calculate sideward and forward velocities of the wheel
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in the runway plane */
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cos_wheel_hdg_angle = cos(caster_angle_rad[i] + Psi);
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sin_wheel_hdg_angle = sin(caster_angle_rad[i] + Psi);
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v_wheel_forward = v_wheel_local_v[0]*cos_wheel_hdg_angle
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+ v_wheel_local_v[1]*sin_wheel_hdg_angle;
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v_wheel_sideward = v_wheel_local_v[1]*cos_wheel_hdg_angle
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- v_wheel_local_v[0]*sin_wheel_hdg_angle;
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/* Calculate normal load force (simple spring constant) */
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reaction_normal_force = 0.;
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reaction_normal_force = spring_constant[i]*HEIGHT_AGL_WHEEL
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- v_wheel_local_v[2]*spring_damping[i];
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if (reaction_normal_force > 0.) reaction_normal_force = 0.;
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/* to prevent damping component from swamping spring component */
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/* Calculate friction coefficients */
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forward_mu = (max_brake_mu - rolling_mu)*percent_brake[i] + rolling_mu;
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abs_v_wheel_sideward = sqrt(v_wheel_sideward*v_wheel_sideward);
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sideward_mu = sliding_mu;
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if (abs_v_wheel_sideward < skid_v)
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sideward_mu = (abs_v_wheel_sideward - bkout_v)*beta_mu;
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if (abs_v_wheel_sideward < bkout_v) sideward_mu = 0.;
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/* Calculate foreward and sideward reaction forces */
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forward_wheel_force = forward_mu*reaction_normal_force;
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sideward_wheel_force = sideward_mu*reaction_normal_force;
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if(v_wheel_forward < 0.) forward_wheel_force = -forward_wheel_force;
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if(v_wheel_sideward < 0.) sideward_wheel_force = -sideward_wheel_force;
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/* printf("\tFfwdgear: %g Fsidegear: %g\n",forward_wheel_force,sideward_wheel_force);
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*/
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/* Rotate into local (N-E-D) axes */
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f_wheel_local_v[0] = forward_wheel_force*cos_wheel_hdg_angle
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- sideward_wheel_force*sin_wheel_hdg_angle;
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f_wheel_local_v[1] = forward_wheel_force*sin_wheel_hdg_angle
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+ sideward_wheel_force*cos_wheel_hdg_angle;
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f_wheel_local_v[2] = reaction_normal_force;
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/* Convert reaction force from local (N-E-D) axes to body (X-Y-Z) */
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mult3x3by3( T_local_to_body_m, f_wheel_local_v, tempF );
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/* Calculate moments from force and offsets in body axes */
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cross3( d_wheel_cg_body_v, tempF, tempM );
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/* Sum forces and moments across all wheels */
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add3( tempF, F_gear_v, F_gear_v );
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add3( tempM, M_gear_v, M_gear_v );
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}
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/* printf("\tN: %g,dZrwy: %g\n",reaction_normal_force,HEIGHT_AGL_WHEEL);
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printf("\tFxgear: %g Fygear: %g, Fzgear: %g\n",F_X_gear,F_Y_gear,F_Z_gear);
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printf("\tMgear: %g, Lgear: %g, Ngear: %g\n\n",M_m_gear,M_l_gear,M_n_gear); */
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/* Calculate foreward and sideward reaction forces */
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forward_wheel_force = forward_mu*reaction_normal_force;
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sideward_wheel_force = sideward_mu*reaction_normal_force;
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if(v_wheel_forward < 0.) forward_wheel_force = -forward_wheel_force;
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if(v_wheel_sideward < 0.) sideward_wheel_force = -sideward_wheel_force;
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/* Rotate into local (N-E-D) axes */
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f_wheel_local_v[0] = forward_wheel_force*cos_wheel_hdg_angle
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- sideward_wheel_force*sin_wheel_hdg_angle;
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f_wheel_local_v[1] = forward_wheel_force*sin_wheel_hdg_angle
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+ sideward_wheel_force*cos_wheel_hdg_angle;
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f_wheel_local_v[2] = reaction_normal_force;
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/* Convert reaction force from local (N-E-D) axes to body (X-Y-Z) */
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mult3x3by3( T_local_to_body_m, f_wheel_local_v, tempF );
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/* Calculate moments from force and offsets in body axes */
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cross3( d_wheel_cg_body_v, tempF, tempM );
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/* Sum forces and moments across all wheels */
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add3( tempF, F_gear_v, F_gear_v );
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add3( tempM, M_gear_v, M_gear_v );
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}
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}
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@ -43,22 +43,22 @@
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void do_trims(int kmax,FILE *out,InitialConditions IC)
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{
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int k=0,i,j;
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int bad_trim=0,i,j;
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double speed,elevator,cmcl,maxspeed;
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out=fopen("trims.out","w");
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speed=55;
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for(j=0;j<=30;j+=10)
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for(j=0;j<=0;j+=10)
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{
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IC.flap_handle=j;
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for(i=1;i<=5;i++)
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for(i=4;i<=4;i++)
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{
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switch(i)
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{
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case 1: IC.weight=1500;IC.cg=0.155;break;
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case 2: IC.weight=1500;IC.cg=0.364;break;
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case 3: IC.weight=1950;IC.cg=0.155;break;
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case 4: IC.weight=2550;IC.cg=0.257;break;
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case 4: IC.weight=2400;IC.cg=0.257;break;
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case 5: IC.weight=2550;IC.cg=0.364;break;
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}
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@ -70,7 +70,7 @@ void do_trims(int kmax,FILE *out,InitialConditions IC)
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IC.vc=speed;
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Long_control=0;Theta=0;Throttle_pct=0.0;
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k=trim_long(kmax,IC);
|
||||
bad_trim=trim_long(kmax,IC);
|
||||
if(Long_control <= 0)
|
||||
elevator=Long_control*28;
|
||||
else
|
||||
|
|
@ -79,15 +79,15 @@ void do_trims(int kmax,FILE *out,InitialConditions IC)
|
|||
{
|
||||
cmcl=cm / CL;
|
||||
}
|
||||
if(k < kmax)
|
||||
if(!bad_trim)
|
||||
{
|
||||
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",V_calibrated_kts,Alpha*RAD_TO_DEG,Long_control,Throttle_pct,Flap_Position);
|
||||
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("kmax exceeded at: %g knots, %g lbs, %g %%MAC, Flaps: %g\n",V_true_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);
|
||||
}
|
||||
|
|
@ -96,7 +96,38 @@ void do_trims(int kmax,FILE *out,InitialConditions IC)
|
|||
}
|
||||
}
|
||||
fclose(out);
|
||||
}
|
||||
}
|
||||
|
||||
find_max_alt(int kmax,InitialConditions IC)
|
||||
{
|
||||
int bad_trim=0,i=0;
|
||||
float min=0,max=30000;
|
||||
IC.use_gamma_tmg=1;
|
||||
IC.gamma=0;
|
||||
IC.vc=73;
|
||||
IC.altitude==1000;
|
||||
while(!bad_trim)
|
||||
{
|
||||
bad_trim=trim_long(200,IC);
|
||||
IC.altitude+=1000;
|
||||
}
|
||||
while((fabs(max-min) > 100) && (i < 50))
|
||||
{
|
||||
|
||||
IC.altitude=(max-min)/2 + min;
|
||||
printf("\nIC.altitude: %g, max: %g, min: %g, bad_trim: %d\n",IC.altitude,max,min,bad_trim);
|
||||
printf("Alpha: %g, Throttle_pct: %g, Long_control: %g\n\n",Alpha*RAD_TO_DEG,Throttle_pct,Long_control);
|
||||
|
||||
bad_trim=trim_long(200,IC);
|
||||
|
||||
if(bad_trim == 1 )
|
||||
max=IC.altitude;
|
||||
else
|
||||
min=IC.altitude;
|
||||
i++;
|
||||
}
|
||||
}
|
||||
|
||||
|
||||
void find_trim_stall(int kmax,FILE *out,InitialConditions IC)
|
||||
{
|
||||
|
|
@ -213,79 +244,41 @@ int main(int argc, char *argv[]) {
|
|||
IC.latitude=47.5299892; //BFI
|
||||
IC.longitude=122.3019561;
|
||||
Runway_altitude = 18.0;
|
||||
|
||||
IC.altitude=strtod(argv[2],NULL);
|
||||
printf("h: %g, argv[2]: %s\n",IC.altitude,argv[2]);
|
||||
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.theta=strtod(argv[3],NULL);
|
||||
IC.use_gamma_tmg=0;
|
||||
IC.phi=strtod(argv[4],NULL);
|
||||
IC.psi=0;
|
||||
IC.weight=2400;
|
||||
IC.cg=0.25;
|
||||
IC.flap_handle=0;
|
||||
IC.long_control=strtod(argv[4],NULL);
|
||||
IC.long_control=0;
|
||||
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.cg=0.155;
|
||||
IC.alpha=-5;
|
||||
setIC(IC);ls_loop(0.0,-1);
|
||||
newcm=CLwbh*(IC.cg - 0.557);
|
||||
lastcm=newcm;
|
||||
out=fopen("cmcl.out","w");
|
||||
while(IC.alpha < 22)
|
||||
{
|
||||
IC.alpha+=1;
|
||||
setIC(IC);ls_loop(0.0,-1);
|
||||
newcm=CLwbh*(IC.cg - 0.557);
|
||||
cmalpha=newcm-lastcm;
|
||||
printf("alpha: %4.0f, CL: %5.2f, Cm: %5.2f, Cma: %7.4f\n",Alpha*RAD_TO_DEG,CLwbh,newcm,cmalpha);
|
||||
fprintf(out,"%g %g\n",newcm,CLwbh);
|
||||
lastcm=newcm;
|
||||
}
|
||||
fclose(out);
|
||||
/* 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);
|
||||
ls_loop(0,-1);
|
||||
printf("\nAltitude: %g\n\n",Altitude);
|
||||
i=0;
|
||||
while(i <= 1)
|
||||
{
|
||||
if(i > 0)
|
||||
Brake_pct=1;
|
||||
ls_update(1);
|
||||
printf("\tAltitude: %g, Theta: %g, Phi: %g\n\n",Altitude,Theta*RAD_TO_DEG,Phi*RAD_TO_DEG);
|
||||
i++;
|
||||
}
|
||||
printf("w: %g, u: %g, q: %g\n",W_body,U_body,Q_body);
|
||||
|
||||
|
||||
printf("Flap_handle: %g, Flap_Position: %g\n",Flap_handle,Flap_Position);
|
||||
/*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);
|
||||
|
|
@ -297,7 +290,7 @@ int main(int argc, char *argv[]) {
|
|||
|
||||
|
||||
|
||||
/* do_trims(400,out,IC); */
|
||||
|
||||
|
||||
/* ls_loop(0.0,-1);
|
||||
|
||||
|
|
|
|||
Loading…
Reference in a new issue