+ FGNetFDM2Props( &fdm, false );
+ }
+#endif
+}
+
+
+// Process remote FDM "set" commands
+
+void FGExternalPipe::process_set_command( const string_list &tokens ) {
+ if ( tokens[1] == "geodetic_position" ) {
+ double lat_rad = atof( tokens[2].c_str() );
+ double lon_rad = atof( tokens[3].c_str() );
+ double alt_m = atof( tokens[4].c_str() );
+ _updateGeodeticPosition( lat_rad, lon_rad,
+ alt_m * SG_METER_TO_FEET );
+
+ double agl_m = alt_m - get_Runway_altitude_m();
+ _set_Altitude_AGL( agl_m * SG_METER_TO_FEET );
+ } else if ( tokens[1] == "euler_angles" ) {
+ double phi_rad = atof( tokens[2].c_str() );
+ double theta_rad = atof( tokens[3].c_str() );
+ double psi_rad = atof( tokens[4].c_str() );
+ _set_Euler_Angles( phi_rad, theta_rad, psi_rad );
+ } else if ( tokens[1] == "euler_rates" ) {
+ double phidot = atof( tokens[2].c_str() );
+ double thetadot = atof( tokens[3].c_str() );
+ double psidot = atof( tokens[4].c_str() );
+ _set_Euler_Rates( phidot, thetadot, psidot );
+ } else if ( tokens[1] == "ned" ) {
+ double north_fps = atof( tokens[2].c_str() );
+ double east_fps = atof( tokens[3].c_str() );
+ double down_fps = atof( tokens[4].c_str() );
+ _set_Velocities_Local( north_fps, east_fps, down_fps );
+ } else if ( tokens[1] == "alpha" ) {
+ _set_Alpha( atof(tokens[2].c_str()) );
+ } else if ( tokens[1] == "beta" ) {
+ _set_Beta( atof(tokens[2].c_str()) );
+
+#if 0
+ _set_V_calibrated_kts( net->vcas );
+ _set_Climb_Rate( net->climb_rate );
+ _set_Velocities_Local( net->v_north,
+ net->v_east,
+ net->v_down );
+ _set_Velocities_Wind_Body( net->v_wind_body_north,
+ net->v_wind_body_east,
+ net->v_wind_body_down );
+
+ _set_Accels_Pilot_Body( net->A_X_pilot,
+ net->A_Y_pilot,
+ net->A_Z_pilot );
+#endif
+ } else {
+ fgSetString( tokens[1].c_str(), tokens[2].c_str() );
+ }
+}
+
+
+// Run an iteration of the EOM.
+void FGExternalPipe::update_property( double dt ) {
+ // cout << "update_property()" << endl;
+
+#ifdef HAVE_MKFIFO
+ // SG_LOG( SG_IO, SG_INFO, "Start FGExternalPipe::udpate()" );
+
+ int result;
+ char cmd[256];
+
+ if ( is_suspended() ) {
+ return;
+ }
+
+ int iterations = _calc_multiloop(dt);
+
+ double weight = fgGetDouble( "/sim/aircraft-weight-lbs" );
+ static double last_weight = 0.0;
+ if ( fabs( weight - last_weight ) > 0.01 ) {
+ sprintf( cmd, "init aircraft-weight-lbs=%.2f", weight );
+ result = write_property( pd1, cmd );