Updates from Tony.
This commit is contained in:
curt
parent
f38dcfd995
commit
bfcfbcaa5e
5 changed files with 250 additions and 251 deletions
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@ -123,9 +123,11 @@ SCALAR interp(SCALAR *y_table, SCALAR *x_table, int Ntable, SCALAR x)
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}
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else if(x >= x_table[Ntable-1])
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{
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y=y_table[Ntable-1];
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/* printf("x larger than x_table[N]: %g %g %d\n",x,x_table[NCL-1],Ntable-1); */
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}
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slope=(y_table[Ntable-1]-y_table[Ntable-2])/(x_table[Ntable-1]-x_table[Ntable-2]);
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y=slope*(x-x_table[Ntable-1]) +y_table[Ntable-1];
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/* printf("x larger than x_table[N]: %g %g %d\n",x,x_table[NCL-1],Ntable-1);
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*/ }
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else /*x is within the table, interpolate linearly to find y value*/
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{
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@ -150,11 +152,8 @@ void aero( SCALAR dt, int Initialize ) {
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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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/*Note that CLo,Cdo,Cmo will likely change with flap setting so
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they may not be declared static in the future */
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/* printf("Initialize= %d\n",Initialize); */
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/* if (Initialize != 0)
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{ */
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/* printf("Initializing aero model...Initialize= %d\n", Initialize);
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*/ CLadot=1.7;
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CLq=3.9;
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@ -196,7 +195,11 @@ void aero( SCALAR dt, int Initialize ) {
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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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/* } */
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MaxTakeoffWeight=2550;
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EmptyWeight=1500;
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Zcg=0.51;
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/*
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LaRCsim uses:
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@ -208,6 +211,29 @@ void aero( SCALAR dt, int Initialize ) {
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aileron > 0 => right wing up
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rudder > 0 => ANL
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*/
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/*do weight & balance here since there is no better place*/
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Weight=Mass / INVG;
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if(Weight > 2550)
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{ Weight=2550; }
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else if(Weight < 1500)
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{ Weight=1500; }
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if(Dx_cg > 0.5586)
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{ Dx_cg = 0.5586; }
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else if(Dx_cg < -0.4655)
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{ Dx_cg = -0.4655; }
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Cg=Dx_cg/cbar +0.25;
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Dz_cg=Zcg*cbar;
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long_trim=0;
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if(Aft_trim) long_trim = long_trim - trim_inc;
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if(Fwd_trim) long_trim = long_trim + trim_inc;
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@ -2,47 +2,51 @@
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/*global declarations of aero model parameters*/
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static SCALAR CLadot;
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static SCALAR CLq;
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static SCALAR CLde;
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static SCALAR CLo;
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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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static SCALAR Cdo;
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static SCALAR Cda; /*Not used*/
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static SCALAR Cdde;
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SCALAR Cdo;
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SCALAR Cda; /*Not used*/
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SCALAR Cdde;
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static SCALAR Cma;
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static SCALAR Cmadot;
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static SCALAR Cmq;
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static SCALAR Cmo;
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static SCALAR Cmde;
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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 Cmde;
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static SCALAR Clbeta;
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static SCALAR Clp;
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static SCALAR Clr;
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static SCALAR Clda;
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static SCALAR Cldr;
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SCALAR Clbeta;
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SCALAR Clp;
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SCALAR Clr;
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SCALAR Clda;
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SCALAR Cldr;
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static SCALAR Cnbeta;
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static SCALAR Cnp;
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static SCALAR Cnr;
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static SCALAR Cnda;
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static SCALAR Cndr;
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SCALAR Cnbeta;
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SCALAR Cnp;
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SCALAR Cnr;
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SCALAR Cnda;
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SCALAR Cndr;
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static SCALAR Cybeta;
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static SCALAR Cyp;
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static SCALAR Cyr;
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static SCALAR Cyda;
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static SCALAR Cydr;
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SCALAR Cybeta;
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SCALAR Cyp;
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SCALAR Cyr;
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SCALAR Cyda;
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SCALAR Cydr;
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/*nondimensionalization quantities*/
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/*units here are ft and lbs */
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static SCALAR cbar; /*mean aero chord ft*/
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static SCALAR b; /*wing span ft */
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static SCALAR Sw; /*wing planform surface area ft^2*/
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static SCALAR rPiARe; /*reciprocal of Pi*AR*e*/
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SCALAR cbar; /*mean aero chord ft*/
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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 Weight; /*lbs*/
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SCALAR MaxTakeoffWeight,EmptyWeight;
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SCALAR Cg; /*%MAC*/
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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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@ -65,6 +65,7 @@ $Header$
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#include "ls_generic.h"
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#include "ls_sim_control.h"
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#include "ls_cockpit.h"
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#include "c172_aero.h"
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extern SIM_CONTROL sim_control_;
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@ -77,6 +78,8 @@ void engine( SCALAR dt, int init ) {
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/* F_Z_engine = Throttle[3]*11.36/0.2; */ /* original code */
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F_X_engine = Throttle[3]*350/0.83;
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F_Z_engine = Throttle[3]*4.9/0.83;
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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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@ -12,8 +12,7 @@
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----------------------------------------------------------------------------
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GENEALOGY: Renamed navion_gear.c originally created 931012 by E. B. Jackson
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GENEALOGY: Created 931012 by E. B. Jackson
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----------------------------------------------------------------------------
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@ -37,34 +36,9 @@
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$Header$
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$Log$
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Revision 1.6 1999/08/08 15:12:33 curt
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Revision 1.7 1999/08/17 19:18:16 curt
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Updates from Tony.
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Revision 1.1.1.1 1999/04/05 21:32:45 curt
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Start of 0.6.x branch.
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Revision 1.6 1998/10/17 01:34:16 curt
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C++ ifying ...
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Revision 1.5 1998/09/29 02:03:00 curt
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Added a brake + autopilot mods.
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Revision 1.4 1998/08/06 12:46:40 curt
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Header change.
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Revision 1.3 1998/02/03 23:20:18 curt
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Lots of little tweaks to fix various consistency problems discovered by
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Solaris' CC. Fixed a bug in fg_debug.c with how the fgPrintf() wrapper
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passed arguments along to the real printf(). Also incorporated HUD changes
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by Michele America.
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Revision 1.2 1998/01/19 18:40:29 curt
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Tons of little changes to clean up the code and to remove fatal errors
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when building with the c++ compiler.
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Revision 1.1 1997/05/29 00:10:02 curt
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Initial Flight Gear revision.
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----------------------------------------------------------------------------
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@ -93,52 +67,51 @@ Initial Flight Gear revision.
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#include "ls_generic.h"
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#include "ls_cockpit.h"
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/* SCALAR Brake_pct; */
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void sub3( DATA v1[], DATA v2[], DATA result[] )
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sub3( DATA v1[], DATA v2[], DATA result[] )
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{
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result[0] = v1[0] - v2[0];
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result[1] = v1[1] - v2[1];
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result[2] = v1[2] - v2[2];
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}
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void add3( DATA v1[], DATA v2[], DATA result[] )
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add3( DATA v1[], DATA v2[], DATA result[] )
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{
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result[0] = v1[0] + v2[0];
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result[1] = v1[1] + v2[1];
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result[2] = v1[2] + v2[2];
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}
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void cross3( DATA v1[], DATA v2[], DATA result[] )
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cross3( DATA v1[], DATA v2[], DATA result[] )
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{
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result[0] = v1[1]*v2[2] - v1[2]*v2[1];
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result[1] = v1[2]*v2[0] - v1[0]*v2[2];
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result[2] = v1[0]*v2[1] - v1[1]*v2[0];
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}
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void multtrans3x3by3( DATA m[][3], DATA v[], DATA result[] )
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multtrans3x3by3( DATA m[][3], DATA v[], DATA result[] )
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{
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result[0] = m[0][0]*v[0] + m[1][0]*v[1] + m[2][0]*v[2];
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result[1] = m[0][1]*v[0] + m[1][1]*v[1] + m[2][1]*v[2];
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result[2] = m[0][2]*v[0] + m[1][2]*v[1] + m[2][2]*v[2];
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}
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void mult3x3by3( DATA m[][3], DATA v[], DATA result[] )
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mult3x3by3( DATA m[][3], DATA v[], DATA result[] )
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{
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result[0] = m[0][0]*v[0] + m[0][1]*v[1] + m[0][2]*v[2];
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result[1] = m[1][0]*v[0] + m[1][1]*v[1] + m[1][2]*v[2];
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result[2] = m[2][0]*v[0] + m[2][1]*v[1] + m[2][2]*v[2];
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}
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void clear3( DATA v[] )
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clear3( DATA v[] )
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{
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v[0] = 0.; v[1] = 0.; v[2] = 0.;
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}
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void gear( SCALAR dt, int Initialize ) {
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gear()
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{
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char rcsid[] = "$Id$";
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/*
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* Aircraft specific initializations and data goes here
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*/
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@ -210,8 +183,6 @@ char rcsid[] = "$Id$";
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int i; /* per wheel loop counter */
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Brake_pct=0;
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/*
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* Execution starts here
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*/
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@ -224,8 +195,7 @@ char rcsid[] = "$Id$";
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* Put aircraft specific executable code here
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*/
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/* replace with cockpit brake handle connection code */
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percent_brake[1] = Brake_pct;
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percent_brake[1] = 0.; /* 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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@ -43,6 +43,7 @@ typedef struct
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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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int use_gamma_tmg;
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}InitialConditions;
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@ -50,6 +51,8 @@ typedef struct
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// vc knots (calibrated airspeed, close to indicated)
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// altitude ft
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// all angles in degrees
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// weight lbs
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// cg %MAC
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// if use_gamma_tmg =1 then theta will be computed
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// from theta=alpha+gamma and the value given will
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// be ignored. Otherwise gamma is computed from
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@ -61,6 +64,9 @@ void setIC(InitialConditions IC)
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SCALAR alphar,betar,thetar,phir,psir,gammar;
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SCALAR sigma,ps,Ts,a;
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Mass=IC.weight*INVG;
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Dx_cg=(IC.cg-0.25)*4.9;
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Latitude=IC.latitude*DEG_TO_RAD;
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Longitude=IC.longitude*DEG_TO_RAD;
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Altitude=IC.altitude;
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@ -122,7 +128,7 @@ 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=75,sum=0;
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int k=0,i,j=0,jmax=10,sum=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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@ -175,33 +181,135 @@ int trim_long(int kmax, InitialConditions IC)
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return k;
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}
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int trim_ground(int kmax, InitialConditions IC)
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{
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double elevator,alpha,qdot_prev,alt_prev,step;
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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=40,sum=0,m=0;
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Throttle_pct=0;
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Brake_pct=1;
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Theta=5*DEG_TO_RAD;
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IC.altitude=Runway_altitude;
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printf("udot: %g\n",U_dot_body);
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setIC(IC);
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printf("Altitude: %g, Runway_altitude: %g\n",Altitude,Runway_altitude);
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qdot_prev=1.0E6;
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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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step=1;
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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);
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m=0;
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while((fabs(W_dot_body) > tol) && (m < 10))
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{
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j=0;
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do{
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alt_prev=IC.altitude;
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IC.altitude+=step;
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setIC(IC);
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ls_loop(0.0,-1);
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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);
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j++;
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}while((W_dot_body < 0) && (j < jmax));
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IC.altitude-=step;
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step/=10;
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printf("step: %g\n",step);
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m++;
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}
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sum+=j;
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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);
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j=0;
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while((Q_dot_body <= qdot_prev) && (j < jmax))
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{
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qdot_prev=Q_dot_body;
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IC.theta+=Q_dot_body;
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setIC(IC);
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ls_loop(0.0,-1);
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j++;
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printf("\tTheta: %7.4f, qdot: %10.6f, qdot_prev: %10.6f, j: %d\n",Theta*RAD_TO_DEG,Q_dot_body,qdot_prev,j);
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}
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IC.theta-=qdot_prev;
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sum+=j;
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printf("\tTheta: %7.4f, qdot: %10.6f, W_dot_body: %g\n",Theta,Q_dot_body,W_dot_body);
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j=0;
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if(W_dot_body > tol)
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{
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step=1;
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while((W_dot_body > 0) && (j <jmax))
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{
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IC.altitude-=step;
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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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}
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k++;j=0;
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}while(((fabs(W_dot_body) > tol) || (fabs(Q_dot_body) > tol)) && (k < kmax));
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printf("Total Iterations: %d\n",sum);
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return k;
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}
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void do_trims(int kmax,FILE *out,InitialConditions IC)
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{
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int k=0;
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double speed,elevator;
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int k=0,i;
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double speed,elevator,cmcl;
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out=fopen("trims.out","w");
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speed=55;
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while(speed < 150)
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for(i=1;i<=5;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;
|
||||
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=0.2;
|
||||
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;
|
||||
|
||||
fprintf(out,"%g,%g,%g,%g,%g,%d\n",V_calibrated_kts,Alpha*RAD_TO_DEG,Long_control,Throttle_pct,Gamma_vert_rad,k);
|
||||
printf("%g,%g,%g,%g,%d,%g,%g,%g\n",V_calibrated_kts,Alpha*RAD_TO_DEG,elevator,Throttle_pct,k,W_body,U_body,Q_body);
|
||||
|
||||
if(k >= kmax)
|
||||
if(fabs(CL) > 1E-3)
|
||||
{
|
||||
printf("kmax exceeded at: %g knots\n",V_calibrated_kts);
|
||||
cmcl=cm / CL;
|
||||
}
|
||||
if(k < kmax)
|
||||
{
|
||||
fprintf(out,"%g,%g,%g,%g,%g,%d",V_calibrated_kts,Alpha*RAD_TO_DEG,Long_control,Throttle_pct,Gamma_vert_rad,k);
|
||||
fprintf(out,",%g,%g,%g,%g,%g\n",CL,cm,cmcl,Weight,Cg);
|
||||
/* printf("%g,%g,%g,%g,%g,%g,%g,%g,%g,%g\n",V_calibrated_kts,Alpha*RAD_TO_DEG,elevator,CL,cm,Cmo,Cma,Cmde,Mass*32.174,Dx_cg);
|
||||
*/ }
|
||||
else
|
||||
{
|
||||
printf("kmax exceeded at: %g knots, %g lbs, %g %%MAC\n",V_calibrated_kts,Weight,Cg);
|
||||
printf("wdot: %g, udot: %g, qdot: %g\n\n",W_dot_body,U_dot_body,Q_dot_body);
|
||||
|
||||
}
|
||||
speed+=10;
|
||||
}
|
||||
}
|
||||
fclose(out);
|
||||
}
|
||||
|
||||
|
|
@ -354,7 +462,7 @@ int main(int argc, char *argv[]) {
|
|||
|
||||
double save_alt = 0.0;
|
||||
int multiloop=1,k=0,i;
|
||||
double time=0,elev_trim,elev_trim_save,elevator,speed;
|
||||
double time=0,elev_trim,elev_trim_save,elevator,speed,cmcl;
|
||||
FILE *out;
|
||||
double hgain,hdiffgain,herr,herrprev,herr_diff,htarget;
|
||||
InitialConditions IC;
|
||||
|
|
@ -370,22 +478,46 @@ int main(int argc, char *argv[]) {
|
|||
Runway_altitude = 18.0;
|
||||
IC.altitude=strtod(argv[2],NULL);
|
||||
IC.vc=strtod(argv[1],NULL);
|
||||
IC.alpha=strtod(argv[3],NULL);
|
||||
IC.alpha=10;
|
||||
IC.beta=0;
|
||||
IC.gamma=strtod(argv[3],NULL);
|
||||
IC.use_gamma_tmg=1;
|
||||
IC.theta=strtod(argv[3],NULL);
|
||||
IC.use_gamma_tmg=0;
|
||||
IC.phi=0;
|
||||
IC.psi=0;
|
||||
IC.weight=1500;
|
||||
IC.cg=0.155;
|
||||
Long_control=strtod(argv[4],NULL);
|
||||
setIC(IC);
|
||||
printf("Out setIC\n");
|
||||
ls_ForceAltitude(IC.altitude);
|
||||
fgLaRCsimInit(0.01);
|
||||
|
||||
/* printf("trim_long():\n");
|
||||
k=trim_long(200,IC); */
|
||||
while(IC.alpha < 30.0)
|
||||
{
|
||||
setIC(IC);
|
||||
ls_loop(0.0,-1);
|
||||
printf("CL: %g ,Alpha: %g\n",CL,IC.alpha);
|
||||
IC.alpha+=1.0;
|
||||
}
|
||||
|
||||
/*trim_ground(10,IC);*/
|
||||
/* printf("%g,%g\n",Theta,Gamma_vert_rad);
|
||||
printf("trim_long():\n");
|
||||
k=trim_long(200,IC);
|
||||
Throttle_pct=Throttle_pct-0.2;
|
||||
printf("%g,%g\n",Theta,Gamma_vert_rad);
|
||||
out=fopen("dive.out","w");
|
||||
time=0;
|
||||
while(time < 30.0)
|
||||
{
|
||||
ls_update(1);
|
||||
|
||||
cmcl=cm/CL;
|
||||
fprintf(out,"%g,%g,%g,%g,%g,%d",V_calibrated_kts,Alpha*RAD_TO_DEG,Long_control,Throttle_pct,Gamma_vert_rad,k);
|
||||
fprintf(out,",%g,%g,%g\n",CL,cm,cmcl);
|
||||
time+=0.01;
|
||||
}
|
||||
fclose(out);
|
||||
printf("V_rel_wind: %8.2f, Alpha: %8.2f, Beta: %8.2f\n",V_rel_wind,Alpha*RAD_TO_DEG,Beta*RAD_TO_DEG);
|
||||
printf("Theta: %8.2f, Gamma: %8.2f, Alpha_tmg: %8.2f\n",Theta*RAD_TO_DEG,Gamma_vert_rad*RAD_TO_DEG,Theta*RAD_TO_DEG-Gamma_vert_rad*RAD_TO_DEG);
|
||||
printf("V_north: %8.2f, V_east_rel_ground: %8.2f, V_east: %8.2f, V_down: %8.2f\n",V_north,V_east_rel_ground,V_east,V_down);
|
||||
|
|
@ -396,12 +528,12 @@ int main(int argc, char *argv[]) {
|
|||
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 */
|
||||
|
||||
|
||||
do_trims(200,out,IC);
|
||||
|
||||
return 1;
|
||||
}
|
||||
|
||||
|
|
@ -581,143 +713,7 @@ int FGInterface_2_LaRCsim (FGInterface& f) {
|
|||
|
||||
return( 0 );
|
||||
}
|
||||
*/
|
||||
|
||||
|
||||
// Convert from the LaRCsim generic_ struct to the FGInterface struct
|
||||
int fgLaRCsim_2_FGInterface (FGInterface& f) {
|
||||
|
||||
// Mass properties and geometry values
|
||||
f.set_Inertias( Mass, I_xx, I_yy, I_zz, I_xz );
|
||||
// f.set_Pilot_Location( Dx_pilot, Dy_pilot, Dz_pilot );
|
||||
f.set_CG_Position( Dx_cg, Dy_cg, Dz_cg );
|
||||
|
||||
// Forces
|
||||
// f.set_Forces_Body_Total( F_X, F_Y, F_Z );
|
||||
// f.set_Forces_Local_Total( F_north, F_east, F_down );
|
||||
// f.set_Forces_Aero( F_X_aero, F_Y_aero, F_Z_aero );
|
||||
// f.set_Forces_Engine( F_X_engine, F_Y_engine, F_Z_engine );
|
||||
// f.set_Forces_Gear( F_X_gear, F_Y_gear, F_Z_gear );
|
||||
|
||||
// Moments
|
||||
// f.set_Moments_Total_RP( M_l_rp, M_m_rp, M_n_rp );
|
||||
// f.set_Moments_Total_CG( M_l_cg, M_m_cg, M_n_cg );
|
||||
// f.set_Moments_Aero( M_l_aero, M_m_aero, M_n_aero );
|
||||
// f.set_Moments_Engine( M_l_engine, M_m_engine, M_n_engine );
|
||||
// f.set_Moments_Gear( M_l_gear, M_m_gear, M_n_gear );
|
||||
|
||||
// Accelerations
|
||||
// f.set_Accels_Local( V_dot_north, V_dot_east, V_dot_down );
|
||||
// f.set_Accels_Body( U_dot_body, V_dot_body, W_dot_body );
|
||||
// f.set_Accels_CG_Body( A_X_cg, A_Y_cg, A_Z_cg );
|
||||
// f.set_Accels_Pilot_Body( A_X_pilot, A_Y_pilot, A_Z_pilot );
|
||||
// f.set_Accels_CG_Body_N( N_X_cg, N_Y_cg, N_Z_cg );
|
||||
// f.set_Accels_Pilot_Body_N( N_X_pilot, N_Y_pilot, N_Z_pilot );
|
||||
// f.set_Accels_Omega( P_dot_body, Q_dot_body, R_dot_body );
|
||||
|
||||
// Velocities
|
||||
f.set_Velocities_Local( V_north, V_east, V_down );
|
||||
// f.set_Velocities_Ground( V_north_rel_ground, V_east_rel_ground,
|
||||
// V_down_rel_ground );
|
||||
// f.set_Velocities_Local_Airmass( V_north_airmass, V_east_airmass,
|
||||
// V_down_airmass );
|
||||
// f.set_Velocities_Local_Rel_Airmass( V_north_rel_airmass,
|
||||
// V_east_rel_airmass, V_down_rel_airmass );
|
||||
// f.set_Velocities_Gust( U_gust, V_gust, W_gust );
|
||||
// f.set_Velocities_Wind_Body( U_body, V_body, W_body );
|
||||
|
||||
// f.set_V_rel_wind( V_rel_wind );
|
||||
// f.set_V_true_kts( V_true_kts );
|
||||
// f.set_V_rel_ground( V_rel_ground );
|
||||
// f.set_V_inertial( V_inertial );
|
||||
// f.set_V_ground_speed( V_ground_speed );
|
||||
// f.set_V_equiv( V_equiv );
|
||||
f.set_V_equiv_kts( V_equiv_kts );
|
||||
// f.set_V_calibrated( V_calibrated );
|
||||
// f.set_V_calibrated_kts( V_calibrated_kts );
|
||||
|
||||
f.set_Omega_Body( P_body, Q_body, R_body );
|
||||
// f.set_Omega_Local( P_local, Q_local, R_local );
|
||||
// f.set_Omega_Total( P_total, Q_total, R_total );
|
||||
|
||||
// f.set_Euler_Rates( Phi_dot, Theta_dot, Psi_dot );
|
||||
f.set_Geocentric_Rates( Latitude_dot, Longitude_dot, Radius_dot );
|
||||
|
||||
FG_LOG( FG_FLIGHT, FG_DEBUG, "lon = " << Longitude
|
||||
<< " lat_geoc = " << Lat_geocentric << " lat_geod = " << Latitude
|
||||
<< " alt = " << Altitude << " sl_radius = " << Sea_level_radius
|
||||
<< " radius_to_vehicle = " << Radius_to_vehicle );
|
||||
|
||||
// Positions
|
||||
f.set_Geocentric_Position( Lat_geocentric, Lon_geocentric,
|
||||
Radius_to_vehicle );
|
||||
f.set_Geodetic_Position( Latitude, Longitude, Altitude );
|
||||
f.set_Euler_Angles( Phi, Theta, Psi );
|
||||
|
||||
// Miscellaneous quantities
|
||||
f.set_T_Local_to_Body(T_local_to_body_m);
|
||||
// f.set_Gravity( Gravity );
|
||||
// f.set_Centrifugal_relief( Centrifugal_relief );
|
||||
|
||||
f.set_Alpha( Alpha );
|
||||
f.set_Beta( Beta );
|
||||
// f.set_Alpha_dot( Alpha_dot );
|
||||
// f.set_Beta_dot( Beta_dot );
|
||||
|
||||
// f.set_Cos_alpha( Cos_alpha );
|
||||
// f.set_Sin_alpha( Sin_alpha );
|
||||
// f.set_Cos_beta( Cos_beta );
|
||||
// f.set_Sin_beta( Sin_beta );
|
||||
|
||||
// f.set_Cos_phi( Cos_phi );
|
||||
// f.set_Sin_phi( Sin_phi );
|
||||
// f.set_Cos_theta( Cos_theta );
|
||||
// f.set_Sin_theta( Sin_theta );
|
||||
// f.set_Cos_psi( Cos_psi );
|
||||
// f.set_Sin_psi( Sin_psi );
|
||||
|
||||
f.set_Gamma_vert_rad( Gamma_vert_rad );
|
||||
// f.set_Gamma_horiz_rad( Gamma_horiz_rad );
|
||||
|
||||
// f.set_Sigma( Sigma );
|
||||
// f.set_Density( Density );
|
||||
// f.set_V_sound( V_sound );
|
||||
// f.set_Mach_number( Mach_number );
|
||||
|
||||
// f.set_Static_pressure( Static_pressure );
|
||||
// f.set_Total_pressure( Total_pressure );
|
||||
// f.set_Impact_pressure( Impact_pressure );
|
||||
// f.set_Dynamic_pressure( Dynamic_pressure );
|
||||
|
||||
// f.set_Static_temperature( Static_temperature );
|
||||
// f.set_Total_temperature( Total_temperature );
|
||||
|
||||
f.set_Sea_level_radius( Sea_level_radius );
|
||||
f.set_Earth_position_angle( Earth_position_angle );
|
||||
|
||||
f.set_Runway_altitude( Runway_altitude );
|
||||
// f.set_Runway_latitude( Runway_latitude );
|
||||
// f.set_Runway_longitude( Runway_longitude );
|
||||
// f.set_Runway_heading( Runway_heading );
|
||||
// f.set_Radius_to_rwy( Radius_to_rwy );
|
||||
|
||||
// f.set_CG_Rwy_Local( D_cg_north_of_rwy, D_cg_east_of_rwy, D_cg_above_rwy);
|
||||
// f.set_CG_Rwy_Rwy( X_cg_rwy, Y_cg_rwy, H_cg_rwy );
|
||||
// f.set_Pilot_Rwy_Local( D_pilot_north_of_rwy, D_pilot_east_of_rwy,
|
||||
// D_pilot_above_rwy );
|
||||
// f.set_Pilot_Rwy_Rwy( X_pilot_rwy, Y_pilot_rwy, H_pilot_rwy );
|
||||
|
||||
f.set_sin_lat_geocentric(Lat_geocentric);
|
||||
f.set_cos_lat_geocentric(Lat_geocentric);
|
||||
f.set_sin_cos_longitude(Longitude);
|
||||
f.set_sin_cos_latitude(Latitude);
|
||||
|
||||
// printf("sin_lat_geo %f cos_lat_geo %f\n", sin_Lat_geoc, cos_Lat_geoc);
|
||||
// printf("sin_lat %f cos_lat %f\n",
|
||||
// f.get_sin_latitude(), f.get_cos_latitude());
|
||||
// printf("sin_lon %f cos_lon %f\n",
|
||||
// f.get_sin_longitude(), f.get_cos_longitude());
|
||||
|
||||
return 0;
|
||||
} */
|
||||
|
||||
|
||||
|
|
|
|||
Loading…
Reference in a new issue