void fgAircraftInit( void ) {
FG_LOG( FG_AIRCRAFT, FG_INFO, "Initializing Aircraft structure" );
- current_aircraft.fdm_state = &cur_fdm_state;
+ current_aircraft.fdm_state = cur_fdm_state;
current_aircraft.controls = &controls;
}
static inline double get_ground_speed( void ) {
// starts in ft/s so we convert to kts
- double ft_s = current_aircraft.fdm_state->get_V_ground_speed()
+ double ft_s = cur_fdm_state->get_V_ground_speed()
* current_options.get_speed_up();;
double kts = ft_s * FEET_TO_METER * 3600 * METER_TO_NM;
return kts;
}
static inline double get_speed( void ) {
- return( current_aircraft.fdm_state->get_V_equiv_kts() );
+ return( cur_fdm_state->get_V_equiv_kts() );
}
static inline double get_aoa( void ) {
- return( current_aircraft.fdm_state->get_Gamma_vert_rad() * RAD_TO_DEG );
+ return( cur_fdm_state->get_Gamma_vert_rad() * RAD_TO_DEG );
}
static inline double fgAPget_latitude( void ) {
- return( current_aircraft.fdm_state->get_Latitude() * RAD_TO_DEG );
+ return( cur_fdm_state->get_Latitude() * RAD_TO_DEG );
}
static inline double fgAPget_longitude( void ) {
- return( current_aircraft.fdm_state->get_Longitude() * RAD_TO_DEG );
+ return( cur_fdm_state->get_Longitude() * RAD_TO_DEG );
}
static inline double fgAPget_roll( void ) {
- return( current_aircraft.fdm_state->get_Phi() * RAD_TO_DEG );
+ return( cur_fdm_state->get_Phi() * RAD_TO_DEG );
}
static inline double get_pitch( void ) {
- return( current_aircraft.fdm_state->get_Theta() );
+ return( cur_fdm_state->get_Theta() );
}
double fgAPget_heading( void ) {
- return( current_aircraft.fdm_state->get_Psi() * RAD_TO_DEG );
+ return( cur_fdm_state->get_Psi() * RAD_TO_DEG );
}
static inline double fgAPget_altitude( void ) {
- return( current_aircraft.fdm_state->get_Altitude() * FEET_TO_METER );
+ return( cur_fdm_state->get_Altitude() * FEET_TO_METER );
}
static inline double fgAPget_climb( void ) {
// return in meters per minute
- return( current_aircraft.fdm_state->get_Climb_Rate() * FEET_TO_METER * 60 );
+ return( cur_fdm_state->get_Climb_Rate() * FEET_TO_METER * 60 );
}
static inline double get_sideslip( void ) {
- return( current_aircraft.fdm_state->get_Beta() );
+ return( cur_fdm_state->get_Beta() );
}
static inline double fgAPget_agl( void ) {
double agl;
- agl = current_aircraft.fdm_state->get_Altitude() * FEET_TO_METER
+ agl = cur_fdm_state->get_Altitude() * FEET_TO_METER
- scenery.cur_elev;
return( agl );
char NewAltitudeLabel[] = "Enter New Altitude";
char *s;
- float alt = current_aircraft.fdm_state->get_Altitude();
+ float alt = cur_fdm_state->get_Altitude();
if ( current_options.get_units() == fgOPTIONS::FG_UNITS_METERS) {
alt *= FEET_TO_METER;
#include "JSBsim.hxx"
-// The default aircraft
-FGFDMExec FDMExec;
-
-
// Initialize the JSBsim flight model, dt is the time increment for
// each subsequent iteration through the EOM
-int fgJSBsimInit(double dt, FGInterface& f) {
- FG_LOG( FG_FLIGHT, FG_INFO, "Starting initializing JSBsim" );
+int FGJSBsim::init( double dt ) {
+ FG_LOG( FG_FLIGHT, FG_INFO, "Starting and initializing JSBsim" );
FG_LOG( FG_FLIGHT, FG_INFO, " created FDMExec" );
current_options.get_uBody(),
current_options.get_vBody(),
current_options.get_wBody(),
- f.get_Phi(),
- f.get_Theta(),
- f.get_Psi(),
- f.get_Latitude(),
- f.get_Longitude(),
- f.get_Altitude()
+ get_Phi(),
+ get_Theta(),
+ get_Psi(),
+ get_Latitude(),
+ get_Longitude(),
+ get_Altitude()
);
// FDMExec.GetState()->Setlatitude(f.get_Latitude());
FG_LOG( FG_FLIGHT, FG_INFO, " loaded initial conditions" );
- FDMExec.GetState()->Setdt(dt);
+ FDMExec.GetState()->Setdt( dt );
FG_LOG( FG_FLIGHT, FG_INFO, " set dt" );
FG_LOG( FG_FLIGHT, FG_INFO, "Finished initializing JSBsim" );
+ copy_from_JSBsim();
+
return 1;
}
// Run an iteration of the EOM (equations of motion)
-int fgJSBsimUpdate(FGInterface& f, int multiloop) {
+int FGJSBsim::update( int multiloop ) {
double save_alt = 0.0;
+ double time_step = (1.0 / current_options.get_model_hz()) * multiloop;
+ double start_elev = get_Altitude();
// lets try to avoid really screwing up the JSBsim model
- if ( f.get_Altitude() < -9000 ) {
- save_alt = f.get_Altitude();
- f.set_Altitude( 0.0 );
+ if ( get_Altitude() < -9000 ) {
+ save_alt = get_Altitude();
+ set_Altitude( 0.0 );
}
// copy control positions into the JSBsim structure
// FCS->SetBrake( controls.get_brake( 0 ) );
// Inform JSBsim of the local terrain altitude
- // Runway_altitude = f.get_Runway_altitude();
+ // Runway_altitude = get_Runway_altitude();
// old -- FGInterface_2_JSBsim() not needed except for Init()
// translate FG to JSBsim structure
// autopilot (and the rest of the sim can use the updated
// values
- fgJSBsim_2_FGInterface(f);
+ copy_from_JSBsim();
// but lets restore our original bogus altitude when we are done
if ( save_alt < -9000.0 ) {
- f.set_Altitude( save_alt );
+ set_Altitude( save_alt );
+ }
+
+ double end_elev = get_Altitude();
+ if ( time_step > 0.0 ) {
+ // feet per second
+ set_Climb_Rate( (end_elev - start_elev) / time_step );
}
return 1;
// Convert from the FGInterface struct to the JSBsim generic_ struct
-int FGInterface_2_JSBsim (FGInterface& f) {
-
+int FGJSBsim::copy_to_JSBsim() {
return 1;
}
// Convert from the JSBsim generic_ struct to the FGInterface struct
-int fgJSBsim_2_FGInterface (FGInterface& f) {
+int FGJSBsim::copy_from_JSBsim() {
// Velocities
- f.set_Velocities_Local( FDMExec.GetPosition()->GetVn(),
+ set_Velocities_Local( FDMExec.GetPosition()->GetVn(),
FDMExec.GetPosition()->GetVe(),
FDMExec.GetPosition()->GetVd() );
- // f.set_Velocities_Ground( V_north_rel_ground, V_east_rel_ground,
+ // 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,
+ // set_Velocities_Local_Airmass( V_north_airmass, V_east_airmass,
// V_down_airmass );
- // f.set_Velocities_Local_Rel_Airmass( V_north_rel_airmass,
+ // 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 );
+ // set_Velocities_Gust( U_gust, V_gust, W_gust );
+ // 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 );
+ // set_V_rel_wind( V_rel_wind );
+ // set_V_true_kts( V_true_kts );
+ // set_V_rel_ground( V_rel_ground );
+ // set_V_inertial( V_inertial );
+ // set_V_ground_speed( V_ground_speed );
+ // set_V_equiv( V_equiv );
- /* ***FIXME*** */ f.set_V_equiv_kts( FDMExec.GetState()->GetVt() );
- // f.set_V_calibrated( V_calibrated );
- // f.set_V_calibrated_kts( V_calibrated_kts );
+ /* ***FIXME*** */ set_V_equiv_kts( FDMExec.GetState()->GetVt() );
+ // set_V_calibrated( V_calibrated );
+ // set_V_calibrated_kts( V_calibrated_kts );
- f.set_Omega_Body( FDMExec.GetRotation()->GetP(),
+ set_Omega_Body( FDMExec.GetRotation()->GetP(),
FDMExec.GetRotation()->GetQ(),
FDMExec.GetRotation()->GetR() );
- // f.set_Omega_Local( P_local, Q_local, R_local );
- // f.set_Omega_Total( P_total, Q_total, R_total );
+ // set_Omega_Local( P_local, Q_local, R_local );
+ // set_Omega_Total( P_total, Q_total, R_total );
- // f.set_Euler_Rates( Phi_dot, Theta_dot, Psi_dot );
- // ***FIXME*** f.set_Geocentric_Rates( Latitude_dot, Longitude_dot, Radius_dot );
+ // set_Euler_Rates( Phi_dot, Theta_dot, Psi_dot );
+ // ***FIXME*** set_Geocentric_Rates( Latitude_dot, Longitude_dot, Radius_dot );
// Positions
double lat_geoc = FDMExec.GetState()->Getlatitude();
<< " sl_radius2 = " << sl_radius2 * METER_TO_FEET
<< " Equator = " << EQUATORIAL_RADIUS_FT );
- f.set_Geocentric_Position( lat_geoc, lon,
+ set_Geocentric_Position( lat_geoc, lon,
sl_radius2 * METER_TO_FEET + alt );
- f.set_Geodetic_Position( lat_geod, lon, alt );
- f.set_Euler_Angles( FDMExec.GetRotation()->Getphi(),
+ set_Geodetic_Position( lat_geod, lon, alt );
+ set_Euler_Angles( FDMExec.GetRotation()->Getphi(),
FDMExec.GetRotation()->Gettht(),
FDMExec.GetRotation()->Getpsi() );
// 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( FDMExec.GetTranslation()->Getalpha() );
- f.set_Beta( FDMExec.GetTranslation()->Getbeta() );
- // 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 );
-
- // ***ATTENDTOME*** 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 );
-
- /* **FIXME*** */ f.set_Sea_level_radius( sl_radius2 * METER_TO_FEET );
- /* **FIXME*** */ f.set_Earth_position_angle( 0.0 );
-
- /* ***FIXME*** */ f.set_Runway_altitude( 0.0 );
- // 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,
+ // set_T_Local_to_Body(T_local_to_body_m);
+ // set_Gravity( Gravity );
+ // set_Centrifugal_relief( Centrifugal_relief );
+
+ set_Alpha( FDMExec.GetTranslation()->Getalpha() );
+ set_Beta( FDMExec.GetTranslation()->Getbeta() );
+ // set_Alpha_dot( Alpha_dot );
+ // set_Beta_dot( Beta_dot );
+
+ // set_Cos_alpha( Cos_alpha );
+ // set_Sin_alpha( Sin_alpha );
+ // set_Cos_beta( Cos_beta );
+ // set_Sin_beta( Sin_beta );
+
+ // set_Cos_phi( Cos_phi );
+ // set_Sin_phi( Sin_phi );
+ // set_Cos_theta( Cos_theta );
+ // set_Sin_theta( Sin_theta );
+ // set_Cos_psi( Cos_psi );
+ // set_Sin_psi( Sin_psi );
+
+ // ***ATTENDTOME*** set_Gamma_vert_rad( Gamma_vert_rad );
+ // set_Gamma_horiz_rad( Gamma_horiz_rad );
+
+ // set_Sigma( Sigma );
+ // set_Density( Density );
+ // set_V_sound( V_sound );
+ // set_Mach_number( Mach_number );
+
+ // set_Static_pressure( Static_pressure );
+ // set_Total_pressure( Total_pressure );
+ // set_Impact_pressure( Impact_pressure );
+ // set_Dynamic_pressure( Dynamic_pressure );
+
+ // set_Static_temperature( Static_temperature );
+ // set_Total_temperature( Total_temperature );
+
+ /* **FIXME*** */ set_Sea_level_radius( sl_radius2 * METER_TO_FEET );
+ /* **FIXME*** */ set_Earth_position_angle( 0.0 );
+
+ /* ***FIXME*** */ set_Runway_altitude( 0.0 );
+ // set_Runway_latitude( Runway_latitude );
+ // set_Runway_longitude( Runway_longitude );
+ // set_Runway_heading( Runway_heading );
+ // set_Radius_to_rwy( Radius_to_rwy );
+
+ // set_CG_Rwy_Local( D_cg_north_of_rwy, D_cg_east_of_rwy, D_cg_above_rwy);
+ // set_CG_Rwy_Rwy( X_cg_rwy, Y_cg_rwy, H_cg_rwy );
+ // 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 );
+ // set_Pilot_Rwy_Rwy( X_pilot_rwy, Y_pilot_rwy, H_pilot_rwy );
- f.set_sin_lat_geocentric( lat_geoc );
- f.set_cos_lat_geocentric( lat_geoc );
- f.set_sin_cos_longitude( lon );
- f.set_sin_cos_latitude( lat_geod );
+ set_sin_lat_geocentric( lat_geoc );
+ set_cos_lat_geocentric( lat_geoc );
+ set_sin_cos_longitude( lon );
+ set_sin_cos_latitude( lat_geod );
- return 0;
+ return 1;
}
#include <Aircraft/aircraft.hxx>
-// reset flight params to a specific position
-int fgJSBsimInit(double dt, FGInterface& f);
+class FGJSBsim: public FGInterface {
-// update position based on inputs, positions, velocities, etc.
-int fgJSBsimUpdate(FGInterface& f, int multiloop);
+ // The aircraft for this instance
+ FGFDMExec FDMExec;
-// Convert from the FGInterface struct to the JSBsim generic_ struct
-int FGInterface_2_JSBsim (FGInterface& f);
+public:
-// Convert from the JSBsim generic_ struct to the FGInterface struct
-int fgJSBsim_2_FGInterface (FGInterface& f);
+ // copy FDM state to LaRCsim structures
+ int copy_to_JSBsim();
+
+ // copy FDM state from LaRCsim structures
+ int copy_from_JSBsim();
+
+ // reset flight params to a specific position
+ int init( double dt );
+
+ // update position based on inputs, positions, velocities, etc.
+ int update( int multiloop );
+};
#endif // _JSBSIM_HXX
// Initialize the LaRCsim flight model, dt is the time increment for
// each subsequent iteration through the EOM
-int fgLaRCsimInit(double dt) {
- ls_toplevel_init(dt);
+int FGLaRCsim::init( double dt ) {
+ // cout << "FGLaRCsim::init()" << endl;
- return(1);
+ double save_alt = 0.0;
+
+ if ( get_Altitude() < -9000.0 ) {
+ save_alt = get_Altitude();
+ set_Altitude( 0.0 );
+ }
+
+ // translate FG to LaRCsim structure
+ copy_to_LaRCsim();
+
+ // actual LaRCsim top level init
+ ls_toplevel_init( dt );
+
+ FG_LOG( FG_FLIGHT, FG_INFO, "FG pos = " <<
+ get_Latitude() );
+
+ // translate LaRCsim back to FG structure
+ copy_from_LaRCsim();
+
+ // but lets restore our original bogus altitude when we are done
+ if ( save_alt < -9000.0 ) {
+ set_Altitude( save_alt );
+ }
+
+ // set valid time for this record
+ stamp_time();
+
+ return 1;
}
// Run an iteration of the EOM (equations of motion)
-int fgLaRCsimUpdate(FGInterface& f, int multiloop) {
+int FGLaRCsim::update( int multiloop ) {
+ // cout << "FGLaRCsim::update()" << endl;
+
double save_alt = 0.0;
+ double time_step = (1.0 / current_options.get_model_hz()) * multiloop;
+ double start_elev = get_Altitude();
// lets try to avoid really screwing up the LaRCsim model
- if ( f.get_Altitude() < -9000.0 ) {
- save_alt = f.get_Altitude();
- f.set_Altitude( 0.0 );
+ if ( get_Altitude() < -9000.0 ) {
+ save_alt = get_Altitude();
+ set_Altitude( 0.0 );
}
// copy control positions into the LaRCsim structure
Brake_pct = controls.get_brake( 0 );
// Inform LaRCsim of the local terrain altitude
- Runway_altitude = f.get_Runway_altitude();
+ Runway_altitude = get_Runway_altitude();
// old -- FGInterface_2_LaRCsim() not needed except for Init()
// translate FG to LaRCsim structure
// translate LaRCsim back to FG structure so that the
// autopilot (and the rest of the sim can use the updated
// values
- fgLaRCsim_2_FGInterface(f);
+ copy_from_LaRCsim();
// but lets restore our original bogus altitude when we are done
if ( save_alt < -9000.0 ) {
- f.set_Altitude( save_alt );
+ set_Altitude( save_alt );
+ }
+
+ double end_elev = get_Altitude();
+ if ( time_step > 0.0 ) {
+ // feet per second
+ set_Climb_Rate( (end_elev - start_elev) / time_step );
}
return 1;
// Convert from the FGInterface struct to the LaRCsim generic_ struct
-int FGInterface_2_LaRCsim (FGInterface& f) {
-
- Mass = f.get_Mass();
- I_xx = f.get_I_xx();
- I_yy = f.get_I_yy();
- I_zz = f.get_I_zz();
- I_xz = f.get_I_xz();
- // Dx_pilot = f.get_Dx_pilot();
- // Dy_pilot = f.get_Dy_pilot();
- // Dz_pilot = f.get_Dz_pilot();
- Dx_cg = f.get_Dx_cg();
- Dy_cg = f.get_Dy_cg();
- Dz_cg = f.get_Dz_cg();
- // F_X = f.get_F_X();
- // F_Y = f.get_F_Y();
- // F_Z = f.get_F_Z();
- // F_north = f.get_F_north();
- // F_east = f.get_F_east();
- // F_down = f.get_F_down();
- // F_X_aero = f.get_F_X_aero();
- // F_Y_aero = f.get_F_Y_aero();
- // F_Z_aero = f.get_F_Z_aero();
- // F_X_engine = f.get_F_X_engine();
- // F_Y_engine = f.get_F_Y_engine();
- // F_Z_engine = f.get_F_Z_engine();
- // F_X_gear = f.get_F_X_gear();
- // F_Y_gear = f.get_F_Y_gear();
- // F_Z_gear = f.get_F_Z_gear();
- // M_l_rp = f.get_M_l_rp();
- // M_m_rp = f.get_M_m_rp();
- // M_n_rp = f.get_M_n_rp();
- // M_l_cg = f.get_M_l_cg();
- // M_m_cg = f.get_M_m_cg();
- // M_n_cg = f.get_M_n_cg();
- // M_l_aero = f.get_M_l_aero();
- // M_m_aero = f.get_M_m_aero();
- // M_n_aero = f.get_M_n_aero();
- // M_l_engine = f.get_M_l_engine();
- // M_m_engine = f.get_M_m_engine();
- // M_n_engine = f.get_M_n_engine();
- // M_l_gear = f.get_M_l_gear();
- // M_m_gear = f.get_M_m_gear();
- // M_n_gear = f.get_M_n_gear();
- // V_dot_north = f.get_V_dot_north();
- // V_dot_east = f.get_V_dot_east();
- // V_dot_down = f.get_V_dot_down();
- // U_dot_body = f.get_U_dot_body();
- // V_dot_body = f.get_V_dot_body();
- // W_dot_body = f.get_W_dot_body();
- // A_X_cg = f.get_A_X_cg();
- // A_Y_cg = f.get_A_Y_cg();
- // A_Z_cg = f.get_A_Z_cg();
- // A_X_pilot = f.get_A_X_pilot();
- // A_Y_pilot = f.get_A_Y_pilot();
- // A_Z_pilot = f.get_A_Z_pilot();
- // N_X_cg = f.get_N_X_cg();
- // N_Y_cg = f.get_N_Y_cg();
- // N_Z_cg = f.get_N_Z_cg();
- // N_X_pilot = f.get_N_X_pilot();
- // N_Y_pilot = f.get_N_Y_pilot();
- // N_Z_pilot = f.get_N_Z_pilot();
- // P_dot_body = f.get_P_dot_body();
- // Q_dot_body = f.get_Q_dot_body();
- // R_dot_body = f.get_R_dot_body();
- V_north = f.get_V_north();
- V_east = f.get_V_east();
- V_down = f.get_V_down();
- // V_north_rel_ground = f.get_V_north_rel_ground();
- // V_east_rel_ground = f.get_V_east_rel_ground();
- // V_down_rel_ground = f.get_V_down_rel_ground();
- // V_north_airmass = f.get_V_north_airmass();
- // V_east_airmass = f.get_V_east_airmass();
- // V_down_airmass = f.get_V_down_airmass();
- // V_north_rel_airmass = f.get_V_north_rel_airmass();
- // V_east_rel_airmass = f.get_V_east_rel_airmass();
- // V_down_rel_airmass = f.get_V_down_rel_airmass();
- // U_gust = f.get_U_gust();
- // V_gust = f.get_V_gust();
- // W_gust = f.get_W_gust();
- // U_body = f.get_U_body();
- // V_body = f.get_V_body();
- // W_body = f.get_W_body();
- // V_rel_wind = f.get_V_rel_wind();
- // V_true_kts = f.get_V_true_kts();
- // V_rel_ground = f.get_V_rel_ground();
- // V_inertial = f.get_V_inertial();
- // V_ground_speed = f.get_V_ground_speed();
- // V_equiv = f.get_V_equiv();
- // V_equiv_kts = f.get_V_equiv_kts();
- // V_calibrated = f.get_V_calibrated();
- // V_calibrated_kts = f.get_V_calibrated_kts();
- P_body = f.get_P_body();
- Q_body = f.get_Q_body();
- R_body = f.get_R_body();
- // P_local = f.get_P_local();
- // Q_local = f.get_Q_local();
- // R_local = f.get_R_local();
- // P_total = f.get_P_total();
- // Q_total = f.get_Q_total();
- // R_total = f.get_R_total();
- // Phi_dot = f.get_Phi_dot();
- // Theta_dot = f.get_Theta_dot();
- // Psi_dot = f.get_Psi_dot();
- // Latitude_dot = f.get_Latitude_dot();
- // Longitude_dot = f.get_Longitude_dot();
- // Radius_dot = f.get_Radius_dot();
- Lat_geocentric = f.get_Lat_geocentric();
- Lon_geocentric = f.get_Lon_geocentric();
- Radius_to_vehicle = f.get_Radius_to_vehicle();
- Latitude = f.get_Latitude();
- Longitude = f.get_Longitude();
- Altitude = f.get_Altitude();
- Phi = f.get_Phi();
- Theta = f.get_Theta();
- Psi = f.get_Psi();
- // T_local_to_body_11 = f.get_T_local_to_body_11();
- // T_local_to_body_12 = f.get_T_local_to_body_12();
- // T_local_to_body_13 = f.get_T_local_to_body_13();
- // T_local_to_body_21 = f.get_T_local_to_body_21();
- // T_local_to_body_22 = f.get_T_local_to_body_22();
- // T_local_to_body_23 = f.get_T_local_to_body_23();
- // T_local_to_body_31 = f.get_T_local_to_body_31();
- // T_local_to_body_32 = f.get_T_local_to_body_32();
- // T_local_to_body_33 = f.get_T_local_to_body_33();
- // Gravity = f.get_Gravity();
- // Centrifugal_relief = f.get_Centrifugal_relief();
- // Alpha = f.get_Alpha();
- // Beta = f.get_Beta();
- // Alpha_dot = f.get_Alpha_dot();
- // Beta_dot = f.get_Beta_dot();
- // Cos_alpha = f.get_Cos_alpha();
- // Sin_alpha = f.get_Sin_alpha();
- // Cos_beta = f.get_Cos_beta();
- // Sin_beta = f.get_Sin_beta();
- // Cos_phi = f.get_Cos_phi();
- // Sin_phi = f.get_Sin_phi();
- // Cos_theta = f.get_Cos_theta();
- // Sin_theta = f.get_Sin_theta();
- // Cos_psi = f.get_Cos_psi();
- // Sin_psi = f.get_Sin_psi();
- // Gamma_vert_rad = f.get_Gamma_vert_rad();
- // Gamma_horiz_rad = f.get_Gamma_horiz_rad();
- // Sigma = f.get_Sigma();
- // Density = f.get_Density();
- // V_sound = f.get_V_sound();
- // Mach_number = f.get_Mach_number();
- // Static_pressure = f.get_Static_pressure();
- // Total_pressure = f.get_Total_pressure();
- // Impact_pressure = f.get_Impact_pressure();
- // Dynamic_pressure = f.get_Dynamic_pressure();
- // Static_temperature = f.get_Static_temperature();
- // Total_temperature = f.get_Total_temperature();
- Sea_level_radius = f.get_Sea_level_radius();
- Earth_position_angle = f.get_Earth_position_angle();
- Runway_altitude = f.get_Runway_altitude();
- // Runway_latitude = f.get_Runway_latitude();
- // Runway_longitude = f.get_Runway_longitude();
- // Runway_heading = f.get_Runway_heading();
- // Radius_to_rwy = f.get_Radius_to_rwy();
- // D_cg_north_of_rwy = f.get_D_cg_north_of_rwy();
- // D_cg_east_of_rwy = f.get_D_cg_east_of_rwy();
- // D_cg_above_rwy = f.get_D_cg_above_rwy();
- // X_cg_rwy = f.get_X_cg_rwy();
- // Y_cg_rwy = f.get_Y_cg_rwy();
- // H_cg_rwy = f.get_H_cg_rwy();
- // D_pilot_north_of_rwy = f.get_D_pilot_north_of_rwy();
- // D_pilot_east_of_rwy = f.get_D_pilot_east_of_rwy();
- // D_pilot_above_rwy = f.get_D_pilot_above_rwy();
- // X_pilot_rwy = f.get_X_pilot_rwy();
- // Y_pilot_rwy = f.get_Y_pilot_rwy();
- // H_pilot_rwy = f.get_H_pilot_rwy();
-
- return( 0 );
+int FGLaRCsim::copy_to_LaRCsim () {
+ Mass = get_Mass();
+ I_xx = get_I_xx();
+ I_yy = get_I_yy();
+ I_zz = get_I_zz();
+ I_xz = get_I_xz();
+ // Dx_pilot = get_Dx_pilot();
+ // Dy_pilot = get_Dy_pilot();
+ // Dz_pilot = get_Dz_pilot();
+ Dx_cg = get_Dx_cg();
+ Dy_cg = get_Dy_cg();
+ Dz_cg = get_Dz_cg();
+ // F_X = get_F_X();
+ // F_Y = get_F_Y();
+ // F_Z = get_F_Z();
+ // F_north = get_F_north();
+ // F_east = get_F_east();
+ // F_down = get_F_down();
+ // F_X_aero = get_F_X_aero();
+ // F_Y_aero = get_F_Y_aero();
+ // F_Z_aero = get_F_Z_aero();
+ // F_X_engine = get_F_X_engine();
+ // F_Y_engine = get_F_Y_engine();
+ // F_Z_engine = get_F_Z_engine();
+ // F_X_gear = get_F_X_gear();
+ // F_Y_gear = get_F_Y_gear();
+ // F_Z_gear = get_F_Z_gear();
+ // M_l_rp = get_M_l_rp();
+ // M_m_rp = get_M_m_rp();
+ // M_n_rp = get_M_n_rp();
+ // M_l_cg = get_M_l_cg();
+ // M_m_cg = get_M_m_cg();
+ // M_n_cg = get_M_n_cg();
+ // M_l_aero = get_M_l_aero();
+ // M_m_aero = get_M_m_aero();
+ // M_n_aero = get_M_n_aero();
+ // M_l_engine = get_M_l_engine();
+ // M_m_engine = get_M_m_engine();
+ // M_n_engine = get_M_n_engine();
+ // M_l_gear = get_M_l_gear();
+ // M_m_gear = get_M_m_gear();
+ // M_n_gear = get_M_n_gear();
+ // V_dot_north = get_V_dot_north();
+ // V_dot_east = get_V_dot_east();
+ // V_dot_down = get_V_dot_down();
+ // U_dot_body = get_U_dot_body();
+ // V_dot_body = get_V_dot_body();
+ // W_dot_body = get_W_dot_body();
+ // A_X_cg = get_A_X_cg();
+ // A_Y_cg = get_A_Y_cg();
+ // A_Z_cg = get_A_Z_cg();
+ // A_X_pilot = get_A_X_pilot();
+ // A_Y_pilot = get_A_Y_pilot();
+ // A_Z_pilot = get_A_Z_pilot();
+ // N_X_cg = get_N_X_cg();
+ // N_Y_cg = get_N_Y_cg();
+ // N_Z_cg = get_N_Z_cg();
+ // N_X_pilot = get_N_X_pilot();
+ // N_Y_pilot = get_N_Y_pilot();
+ // N_Z_pilot = get_N_Z_pilot();
+ // P_dot_body = get_P_dot_body();
+ // Q_dot_body = get_Q_dot_body();
+ // R_dot_body = get_R_dot_body();
+ V_north = get_V_north();
+ V_east = get_V_east();
+ V_down = get_V_down();
+ // V_north_rel_ground = get_V_north_rel_ground();
+ // V_east_rel_ground = get_V_east_rel_ground();
+ // V_down_rel_ground = get_V_down_rel_ground();
+ // V_north_airmass = get_V_north_airmass();
+ // V_east_airmass = get_V_east_airmass();
+ // V_down_airmass = get_V_down_airmass();
+ // V_north_rel_airmass = get_V_north_rel_airmass();
+ // V_east_rel_airmass = get_V_east_rel_airmass();
+ // V_down_rel_airmass = get_V_down_rel_airmass();
+ // U_gust = get_U_gust();
+ // V_gust = get_V_gust();
+ // W_gust = get_W_gust();
+ // U_body = get_U_body();
+ // V_body = get_V_body();
+ // W_body = get_W_body();
+ // V_rel_wind = get_V_rel_wind();
+ // V_true_kts = get_V_true_kts();
+ // V_rel_ground = get_V_rel_ground();
+ // V_inertial = get_V_inertial();
+ // V_ground_speed = get_V_ground_speed();
+ // V_equiv = get_V_equiv();
+ // V_equiv_kts = get_V_equiv_kts();
+ // V_calibrated = get_V_calibrated();
+ // V_calibrated_kts = get_V_calibrated_kts();
+ P_body = get_P_body();
+ Q_body = get_Q_body();
+ R_body = get_R_body();
+ // P_local = get_P_local();
+ // Q_local = get_Q_local();
+ // R_local = get_R_local();
+ // P_total = get_P_total();
+ // Q_total = get_Q_total();
+ // R_total = get_R_total();
+ // Phi_dot = get_Phi_dot();
+ // Theta_dot = get_Theta_dot();
+ // Psi_dot = get_Psi_dot();
+ // Latitude_dot = get_Latitude_dot();
+ // Longitude_dot = get_Longitude_dot();
+ // Radius_dot = get_Radius_dot();
+ Lat_geocentric = get_Lat_geocentric();
+ Lon_geocentric = get_Lon_geocentric();
+ Radius_to_vehicle = get_Radius_to_vehicle();
+ Latitude = get_Latitude();
+ Longitude = get_Longitude();
+ Altitude = get_Altitude();
+ Phi = get_Phi();
+ Theta = get_Theta();
+ Psi = get_Psi();
+ // T_local_to_body_11 = get_T_local_to_body_11();
+ // T_local_to_body_12 = get_T_local_to_body_12();
+ // T_local_to_body_13 = get_T_local_to_body_13();
+ // T_local_to_body_21 = get_T_local_to_body_21();
+ // T_local_to_body_22 = get_T_local_to_body_22();
+ // T_local_to_body_23 = get_T_local_to_body_23();
+ // T_local_to_body_31 = get_T_local_to_body_31();
+ // T_local_to_body_32 = get_T_local_to_body_32();
+ // T_local_to_body_33 = get_T_local_to_body_33();
+ // Gravity = get_Gravity();
+ // Centrifugal_relief = get_Centrifugal_relief();
+ // Alpha = get_Alpha();
+ // Beta = get_Beta();
+ // Alpha_dot = get_Alpha_dot();
+ // Beta_dot = get_Beta_dot();
+ // Cos_alpha = get_Cos_alpha();
+ // Sin_alpha = get_Sin_alpha();
+ // Cos_beta = get_Cos_beta();
+ // Sin_beta = get_Sin_beta();
+ // Cos_phi = get_Cos_phi();
+ // Sin_phi = get_Sin_phi();
+ // Cos_theta = get_Cos_theta();
+ // Sin_theta = get_Sin_theta();
+ // Cos_psi = get_Cos_psi();
+ // Sin_psi = get_Sin_psi();
+ // Gamma_vert_rad = get_Gamma_vert_rad();
+ // Gamma_horiz_rad = get_Gamma_horiz_rad();
+ // Sigma = get_Sigma();
+ // Density = get_Density();
+ // V_sound = get_V_sound();
+ // Mach_number = get_Mach_number();
+ // Static_pressure = get_Static_pressure();
+ // Total_pressure = get_Total_pressure();
+ // Impact_pressure = get_Impact_pressure();
+ // Dynamic_pressure = get_Dynamic_pressure();
+ // Static_temperature = get_Static_temperature();
+ // Total_temperature = get_Total_temperature();
+ Sea_level_radius = get_Sea_level_radius();
+ Earth_position_angle = get_Earth_position_angle();
+ Runway_altitude = get_Runway_altitude();
+ // Runway_latitude = get_Runway_latitude();
+ // Runway_longitude = get_Runway_longitude();
+ // Runway_heading = get_Runway_heading();
+ // Radius_to_rwy = get_Radius_to_rwy();
+ // D_cg_north_of_rwy = get_D_cg_north_of_rwy();
+ // D_cg_east_of_rwy = get_D_cg_east_of_rwy();
+ // D_cg_above_rwy = get_D_cg_above_rwy();
+ // X_cg_rwy = get_X_cg_rwy();
+ // Y_cg_rwy = get_Y_cg_rwy();
+ // H_cg_rwy = get_H_cg_rwy();
+ // D_pilot_north_of_rwy = get_D_pilot_north_of_rwy();
+ // D_pilot_east_of_rwy = get_D_pilot_east_of_rwy();
+ // D_pilot_above_rwy = get_D_pilot_above_rwy();
+ // X_pilot_rwy = get_X_pilot_rwy();
+ // Y_pilot_rwy = get_Y_pilot_rwy();
+ // H_pilot_rwy = get_H_pilot_rwy();
+
+ return 1;
}
// Convert from the LaRCsim generic_ struct to the FGInterface struct
-int fgLaRCsim_2_FGInterface (FGInterface& f) {
+int FGLaRCsim::copy_from_LaRCsim() {
// 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 );
+ set_Inertias( Mass, I_xx, I_yy, I_zz, I_xz );
+ // set_Pilot_Location( Dx_pilot, Dy_pilot, Dz_pilot );
+ 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 );
+ // set_Forces_Body_Total( F_X, F_Y, F_Z );
+ // set_Forces_Local_Total( F_north, F_east, F_down );
+ // set_Forces_Aero( F_X_aero, F_Y_aero, F_Z_aero );
+ // set_Forces_Engine( F_X_engine, F_Y_engine, F_Z_engine );
+ // 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 );
+ // set_Moments_Total_RP( M_l_rp, M_m_rp, M_n_rp );
+ // set_Moments_Total_CG( M_l_cg, M_m_cg, M_n_cg );
+ // set_Moments_Aero( M_l_aero, M_m_aero, M_n_aero );
+ // set_Moments_Engine( M_l_engine, M_m_engine, M_n_engine );
+ // 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 );
+ // set_Accels_Local( V_dot_north, V_dot_east, V_dot_down );
+ set_Accels_Body( U_dot_body, V_dot_body, W_dot_body );
+ set_Accels_CG_Body( A_X_cg, A_Y_cg, A_Z_cg );
+ set_Accels_Pilot_Body( A_X_pilot, A_Y_pilot, A_Z_pilot );
+ // set_Accels_CG_Body_N( N_X_cg, N_Y_cg, N_Z_cg );
+ // set_Accels_Pilot_Body_N( N_X_pilot, N_Y_pilot, N_Z_pilot );
+ // 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,
+ set_Velocities_Local( V_north, V_east, V_down );
+ // 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,
+ // set_Velocities_Local_Airmass( V_north_airmass, V_east_airmass,
// V_down_airmass );
- // f.set_Velocities_Local_Rel_Airmass( V_north_rel_airmass,
+ // 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 );
+ // set_Velocities_Gust( U_gust, V_gust, W_gust );
+ set_Velocities_Wind_Body( U_body, V_body, W_body );
+
+ // set_V_rel_wind( V_rel_wind );
+ // set_V_true_kts( V_true_kts );
+ // set_V_rel_ground( V_rel_ground );
+ // set_V_inertial( V_inertial );
+ set_V_ground_speed( V_ground_speed );
+ // set_V_equiv( V_equiv );
+ set_V_equiv_kts( V_equiv_kts );
+ // set_V_calibrated( V_calibrated );
+ // set_V_calibrated_kts( V_calibrated_kts );
+
+ set_Omega_Body( P_body, Q_body, R_body );
+ // set_Omega_Local( P_local, Q_local, R_local );
+ // 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 );
+ // set_Euler_Rates( Phi_dot, Theta_dot, Psi_dot );
+ set_Geocentric_Rates( Latitude_dot, Longitude_dot, Radius_dot );
FG_LOG( FG_FLIGHT, FG_DEBUG, "lon = " << Longitude
<< " lat_geoc = " << Lat_geocentric << " lat_geod = " << Latitude
while ( tmp_lon > FG_PI ) { tmp_lon -= FG_2PI; }
// Positions
- f.set_Geocentric_Position( Lat_geocentric, tmp_lon_geoc,
+ set_Geocentric_Position( Lat_geocentric, tmp_lon_geoc,
Radius_to_vehicle );
- f.set_Geodetic_Position( Latitude, tmp_lon, Altitude );
- f.set_Euler_Angles( Phi, Theta, Psi );
+ set_Geodetic_Position( Latitude, tmp_lon, Altitude );
+ 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,
+ set_T_Local_to_Body(T_local_to_body_m);
+ // set_Gravity( Gravity );
+ // set_Centrifugal_relief( Centrifugal_relief );
+
+ set_Alpha( Alpha );
+ set_Beta( Beta );
+ // set_Alpha_dot( Alpha_dot );
+ // set_Beta_dot( Beta_dot );
+
+ // set_Cos_alpha( Cos_alpha );
+ // set_Sin_alpha( Sin_alpha );
+ // set_Cos_beta( Cos_beta );
+ // set_Sin_beta( Sin_beta );
+
+ set_Cos_phi( Cos_phi );
+ // set_Sin_phi( Sin_phi );
+ set_Cos_theta( Cos_theta );
+ // set_Sin_theta( Sin_theta );
+ // set_Cos_psi( Cos_psi );
+ // set_Sin_psi( Sin_psi );
+
+ set_Gamma_vert_rad( Gamma_vert_rad );
+ // set_Gamma_horiz_rad( Gamma_horiz_rad );
+
+ // set_Sigma( Sigma );
+ // set_Density( Density );
+ // set_V_sound( V_sound );
+ // set_Mach_number( Mach_number );
+
+ // set_Static_pressure( Static_pressure );
+ // set_Total_pressure( Total_pressure );
+ // set_Impact_pressure( Impact_pressure );
+ // set_Dynamic_pressure( Dynamic_pressure );
+
+ // set_Static_temperature( Static_temperature );
+ // set_Total_temperature( Total_temperature );
+
+ set_Sea_level_radius( Sea_level_radius );
+ set_Earth_position_angle( Earth_position_angle );
+
+ set_Runway_altitude( Runway_altitude );
+ // set_Runway_latitude( Runway_latitude );
+ // set_Runway_longitude( Runway_longitude );
+ // set_Runway_heading( Runway_heading );
+ // set_Radius_to_rwy( Radius_to_rwy );
+
+ // set_CG_Rwy_Local( D_cg_north_of_rwy, D_cg_east_of_rwy, D_cg_above_rwy);
+ // set_CG_Rwy_Rwy( X_cg_rwy, Y_cg_rwy, H_cg_rwy );
+ // 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 );
+ // 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);
+ set_sin_lat_geocentric(Lat_geocentric);
+ set_cos_lat_geocentric(Lat_geocentric);
+ set_sin_cos_longitude(Longitude);
+ 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());
+ // get_sin_latitude(), get_cos_latitude());
// printf("sin_lon %f cos_lon %f\n",
- // f.get_sin_longitude(), f.get_cos_longitude());
+ // get_sin_longitude(), get_cos_longitude());
- return 0;
+ return 1;
}
#include "flight.hxx"
-// reset flight params to a specific position
-int fgLaRCsimInit(double dt);
+class FGLaRCsim: public FGInterface {
-// update position based on inputs, positions, velocities, etc.
-int fgLaRCsimUpdate(FGInterface& f, int multiloop);
+public:
-// Convert from the FGInterface struct to the LaRCsim generic_ struct
-int FGInterface_2_LaRCsim (FGInterface& f);
+ // copy FDM state to LaRCsim structures
+ int copy_to_LaRCsim();
-// Convert from the LaRCsim generic_ struct to the FGInterface struct
-int fgLaRCsim_2_FGInterface (FGInterface& f);
+ // copy FDM state from LaRCsim structures
+ int copy_from_LaRCsim();
+
+ // reset flight params to a specific position
+ int init( double dt );
+
+ // update position based on inputs, positions, velocities, etc.
+ int update( int multiloop );
+};
#endif // _LARCSIM_HXX
// world time, so we introduce cur_fdm_state which is extrapolated by
// the difference between sim time and real world time
-FGInterface cur_fdm_state;
+FGInterface * cur_fdm_state;
FGInterface base_fdm_state;
+int FGInterface::init( double dt ) {
+ cout << "dummy init() ... SHOULDN'T BE CALLED!" << endl;
+ return 0;
+}
+
+int FGInterface::update( int multi_loop ) {
+ cout << "dummy update() ... SHOULDN'T BE CALLED!" << endl;
+ return 0;
+}
+
+FGInterface::~FGInterface() {
+}
+
// Extrapolate fdm based on time_offset (in usec)
void FGInterface::extrapolate( int time_offset ) {
double dt = time_offset / 1000000.0;
}
+#if 0
// Initialize the flight model parameters
int fgFDMInit(int model, FGInterface& f, double dt) {
double save_alt = 0.0;
return 1;
}
+#endif
+#if 0
// Run multiloop iterations of the flight model
int fgFDMUpdate(int model, FGInterface& f, int multiloop, int time_offset) {
double time_step, start_elev, end_elev;
return 1;
}
+#endif
// Set the altitude (force)
// Set the local ground elevation
void fgFDMSetGroundElevation(int model, double ground_meters) {
base_fdm_state.set_Runway_altitude( ground_meters * METER_TO_FEET );
- cur_fdm_state.set_Runway_altitude( ground_meters * METER_TO_FEET );
+ cur_fdm_state->set_Runway_altitude( ground_meters * METER_TO_FEET );
}
public:
+ virtual int init( double dt );
+ virtual int update( int multi_loop );
+ virtual ~FGInterface();
+
// Define the various supported flight models (many not yet implemented)
enum {
// Slew (in MS terminology)
typedef fdm_state_list::const_iterator const_fdm_state_list_iterator;
-extern FGInterface cur_fdm_state;
+extern FGInterface * cur_fdm_state;
// General interface to the flight model routines
#include <Astro/solarsystem.hxx>
#include <Autopilot/autopilot.hxx>
#include <Cockpit/cockpit.hxx>
+#include <FDM/LaRCsim.hxx>
+#include <FDM/JSBsim.hxx>
#include <Include/fg_constants.h>
#include <Include/general.hxx>
#include <Joystick/joystick.hxx>
FG_LOG( FG_GENERAL, FG_INFO, "Initialize Subsystems");
FG_LOG( FG_GENERAL, FG_INFO, "========== ==========");
+ if ( current_options.get_flight_model() == FGInterface::FG_LARCSIM ) {
+ cur_fdm_state = new FGLaRCsim;
+ } else if ( current_options.get_flight_model() == FGInterface::FG_JSBSIM ) {
+ cur_fdm_state = new FGJSBsim;
+ } else {
+ FG_LOG( FG_GENERAL, FG_ALERT,
+ "No flight model, can't init aircraft" );
+ exit(-1);
+ }
+
// allocates structures so must happen before any of the flight
// model or control parameters are set
fgAircraftInit(); // In the future this might not be the case.
// now handled inside of the fgTileMgrUpdate()
/*
- geod_pos = Point3D( cur_fdm_state.get_Longitude(), cur_fdm_state.get_Latitude(), 0.0);
+ geod_pos = Point3D( cur_fdm_state->get_Longitude(), cur_fdm_state->get_Latitude(), 0.0);
tmp_abs_view_pos = fgGeodToCart(geod_pos);
FG_LOG( FG_GENERAL, FG_DEBUG,
"Initial abs_view_pos = " << tmp_abs_view_pos );
scenery.cur_elev =
- fgTileMgrCurElev( cur_fdm_state.get_Longitude(), cur_fdm_state.get_Latitude(),
+ fgTileMgrCurElev( cur_fdm_state->get_Longitude(), cur_fdm_state->get_Latitude(),
tmp_abs_view_pos );
FG_LOG( FG_GENERAL, FG_DEBUG,
"Altitude after update " << scenery.cur_elev );
scenery.cur_elev );
// Reset our altitude if we are below ground
- FG_LOG( FG_GENERAL, FG_DEBUG, "Current altitude = " << cur_fdm_state.get_Altitude() );
+ FG_LOG( FG_GENERAL, FG_DEBUG, "Current altitude = " << cur_fdm_state->get_Altitude() );
FG_LOG( FG_GENERAL, FG_DEBUG, "Current runway altitude = " <<
- cur_fdm_state.get_Runway_altitude() );
+ cur_fdm_state->get_Runway_altitude() );
- if ( cur_fdm_state.get_Altitude() < cur_fdm_state.get_Runway_altitude() + 3.758099) {
- cur_fdm_state.set_Altitude( cur_fdm_state.get_Runway_altitude() + 3.758099 );
+ if ( cur_fdm_state->get_Altitude() < cur_fdm_state->get_Runway_altitude() + 3.758099) {
+ cur_fdm_state->set_Altitude( cur_fdm_state->get_Runway_altitude() + 3.758099 );
}
FG_LOG( FG_GENERAL, FG_INFO,
"Updated position (after elevation adj): ("
- << (cur_fdm_state.get_Latitude() * RAD_TO_DEG) << ", "
- << (cur_fdm_state.get_Longitude() * RAD_TO_DEG) << ", "
- << (cur_fdm_state.get_Altitude() * FEET_TO_METER) << ")" );
+ << (cur_fdm_state->get_Latitude() * RAD_TO_DEG) << ", "
+ << (cur_fdm_state->get_Longitude() * RAD_TO_DEG) << ", "
+ << (cur_fdm_state->get_Altitude() * FEET_TO_METER) << ")" );
// We need to calculate a few more values here that would normally
// be calculated by the FDM so that the v->UpdateViewMath()
double sea_level_radius_meters;
double lat_geoc;
// Set the FG variables first
- fgGeodToGeoc( cur_fdm_state.get_Latitude(), cur_fdm_state.get_Altitude(),
+ fgGeodToGeoc( cur_fdm_state->get_Latitude(), cur_fdm_state->get_Altitude(),
&sea_level_radius_meters, &lat_geoc);
- cur_fdm_state.set_Geocentric_Position( lat_geoc, cur_fdm_state.get_Longitude(),
- cur_fdm_state.get_Altitude() +
+ cur_fdm_state->set_Geocentric_Position( lat_geoc, cur_fdm_state->get_Longitude(),
+ cur_fdm_state->get_Altitude() +
(sea_level_radius_meters * METER_TO_FEET) );
- cur_fdm_state.set_Sea_level_radius( sea_level_radius_meters * METER_TO_FEET );
+ cur_fdm_state->set_Sea_level_radius( sea_level_radius_meters * METER_TO_FEET );
- cur_fdm_state.set_sin_cos_longitude(cur_fdm_state.get_Longitude());
- cur_fdm_state.set_sin_cos_latitude(cur_fdm_state.get_Latitude());
+ cur_fdm_state->set_sin_cos_longitude(cur_fdm_state->get_Longitude());
+ cur_fdm_state->set_sin_cos_latitude(cur_fdm_state->get_Latitude());
- cur_fdm_state.set_sin_lat_geocentric(sin(lat_geoc));
- cur_fdm_state.set_cos_lat_geocentric(cos(lat_geoc));
+ cur_fdm_state->set_sin_lat_geocentric(sin(lat_geoc));
+ cur_fdm_state->set_cos_lat_geocentric(cos(lat_geoc));
// The following section sets up the flight model EOM parameters
// and should really be read in from one or more files.
// Initial Velocity
- cur_fdm_state.set_Velocities_Local( current_options.get_uBody(),
+ cur_fdm_state->set_Velocities_Local( current_options.get_uBody(),
current_options.get_vBody(),
current_options.get_wBody());
// Initial Orientation
- cur_fdm_state.set_Euler_Angles( current_options.get_roll() * DEG_TO_RAD,
+ cur_fdm_state->set_Euler_Angles( current_options.get_roll() * DEG_TO_RAD,
current_options.get_pitch() * DEG_TO_RAD,
current_options.get_heading() * DEG_TO_RAD );
// Initial Angular Body rates
- cur_fdm_state.set_Omega_Body( 7.206685E-05, 0.0, 9.492658E-05 );
+ cur_fdm_state->set_Omega_Body( 7.206685E-05, 0.0, 9.492658E-05 );
- cur_fdm_state.set_Earth_position_angle( 0.0 );
+ cur_fdm_state->set_Earth_position_angle( 0.0 );
// Mass properties and geometry values
- cur_fdm_state.set_Inertias( 8.547270E+01,
+ cur_fdm_state->set_Inertias( 8.547270E+01,
1.048000E+03, 3.000000E+03, 3.530000E+03, 0.000000E+00 );
// CG position w.r.t. ref. point
- cur_fdm_state.set_CG_Position( 0.0, 0.0, 0.0 );
+ cur_fdm_state->set_CG_Position( 0.0, 0.0, 0.0 );
// Initialize the event manager
global_events.Init();
fgEVENT::FG_EVENT_READY, 60000 );
// Initialize the time dependent variables
- t->init(cur_fdm_state);
- t->update(cur_fdm_state);
+ t->init(*cur_fdm_state);
+ t->update(*cur_fdm_state);
// Initialize view parameters
FG_LOG( FG_GENERAL, FG_DEBUG, "Before v->init()");
v->Init();
FG_LOG( FG_GENERAL, FG_DEBUG, "After v->init()");
- v->UpdateViewMath(cur_fdm_state);
+ v->UpdateViewMath(*cur_fdm_state);
FG_LOG( FG_GENERAL, FG_DEBUG, " abs_view_pos = " << v->get_abs_view_pos());
// v->UpdateWorldToEye(f);
// Initialize the flight model subsystem data structures base on
// above values
- fgFDMInit( current_options.get_flight_model(), cur_fdm_state,
- 1.0 / current_options.get_model_hz() );
+ // fgFDMInit( current_options.get_flight_model(), cur_fdm_state,
+ // 1.0 / current_options.get_model_hz() );
+ cur_fdm_state->init( 1.0 / current_options.get_model_hz() );
// I'm just sticking this here for now, it should probably move
// eventually
- scenery.cur_elev = cur_fdm_state.get_Runway_altitude() * FEET_TO_METER;
+ scenery.cur_elev = cur_fdm_state->get_Runway_altitude() * FEET_TO_METER;
- if ( cur_fdm_state.get_Altitude() < cur_fdm_state.get_Runway_altitude() + 3.758099) {
- cur_fdm_state.set_Altitude( cur_fdm_state.get_Runway_altitude() + 3.758099 );
+ if ( cur_fdm_state->get_Altitude() < cur_fdm_state->get_Runway_altitude() + 3.758099) {
+ cur_fdm_state->set_Altitude( cur_fdm_state->get_Runway_altitude() + 3.758099 );
}
FG_LOG( FG_GENERAL, FG_INFO,
"Updated position (after elevation adj): ("
- << (cur_fdm_state.get_Latitude() * RAD_TO_DEG) << ", "
- << (cur_fdm_state.get_Longitude() * RAD_TO_DEG) << ", "
- << (cur_fdm_state.get_Altitude() * FEET_TO_METER) << ")" );
+ << (cur_fdm_state->get_Latitude() * RAD_TO_DEG) << ", "
+ << (cur_fdm_state->get_Longitude() * RAD_TO_DEG) << ", "
+ << (cur_fdm_state->get_Altitude() * FEET_TO_METER) << ")" );
// end of thing that I just stuck in that I should probably move
// Joystick support
scenery.cur_elev );
// Reset our altitude if we are below ground
- FG_LOG( FG_GENERAL, FG_DEBUG, "Current altitude = " << cur_fdm_state.get_Altitude() );
+ FG_LOG( FG_GENERAL, FG_DEBUG, "Current altitude = " << cur_fdm_state->get_Altitude() );
FG_LOG( FG_GENERAL, FG_DEBUG, "Current runway altitude = " <<
- cur_fdm_state.get_Runway_altitude() );
+ cur_fdm_state->get_Runway_altitude() );
- if ( cur_fdm_state.get_Altitude() < cur_fdm_state.get_Runway_altitude() + 3.758099) {
- cur_fdm_state.set_Altitude( cur_fdm_state.get_Runway_altitude() + 3.758099 );
+ if ( cur_fdm_state->get_Altitude() < cur_fdm_state->get_Runway_altitude() + 3.758099) {
+ cur_fdm_state->set_Altitude( cur_fdm_state->get_Runway_altitude() + 3.758099 );
}
double sea_level_radius_meters;
double lat_geoc;
// Set the FG variables first
- fgGeodToGeoc( cur_fdm_state.get_Latitude(), cur_fdm_state.get_Altitude(),
+ fgGeodToGeoc( cur_fdm_state->get_Latitude(), cur_fdm_state->get_Altitude(),
&sea_level_radius_meters, &lat_geoc);
- cur_fdm_state.set_Geocentric_Position( lat_geoc, cur_fdm_state.get_Longitude(),
- cur_fdm_state.get_Altitude() +
+ cur_fdm_state->set_Geocentric_Position( lat_geoc, cur_fdm_state->get_Longitude(),
+ cur_fdm_state->get_Altitude() +
(sea_level_radius_meters * METER_TO_FEET) );
- cur_fdm_state.set_Sea_level_radius( sea_level_radius_meters * METER_TO_FEET );
+ cur_fdm_state->set_Sea_level_radius( sea_level_radius_meters * METER_TO_FEET );
- cur_fdm_state.set_sin_cos_longitude(cur_fdm_state.get_Longitude());
- cur_fdm_state.set_sin_cos_latitude(cur_fdm_state.get_Latitude());
+ cur_fdm_state->set_sin_cos_longitude(cur_fdm_state->get_Longitude());
+ cur_fdm_state->set_sin_cos_latitude(cur_fdm_state->get_Latitude());
- cur_fdm_state.set_sin_lat_geocentric(sin(lat_geoc));
- cur_fdm_state.set_cos_lat_geocentric(cos(lat_geoc));
+ cur_fdm_state->set_sin_lat_geocentric(sin(lat_geoc));
+ cur_fdm_state->set_cos_lat_geocentric(cos(lat_geoc));
// The following section sets up the flight model EOM parameters
// and should really be read in from one or more files.
// Initial Velocity
- cur_fdm_state.set_Velocities_Local( current_options.get_uBody(),
+ cur_fdm_state->set_Velocities_Local( current_options.get_uBody(),
current_options.get_vBody(),
current_options.get_wBody());
// Initial Orientation
- cur_fdm_state.set_Euler_Angles( current_options.get_roll() * DEG_TO_RAD,
+ cur_fdm_state->set_Euler_Angles( current_options.get_roll() * DEG_TO_RAD,
current_options.get_pitch() * DEG_TO_RAD,
current_options.get_heading() * DEG_TO_RAD );
// Initial Angular Body rates
- cur_fdm_state.set_Omega_Body( 7.206685E-05, 0.0, 9.492658E-05 );
+ cur_fdm_state->set_Omega_Body( 7.206685E-05, 0.0, 9.492658E-05 );
- cur_fdm_state.set_Earth_position_angle( 0.0 );
+ cur_fdm_state->set_Earth_position_angle( 0.0 );
// Mass properties and geometry values
- cur_fdm_state.set_Inertias( 8.547270E+01,
+ cur_fdm_state->set_Inertias( 8.547270E+01,
1.048000E+03, 3.000000E+03, 3.530000E+03, 0.000000E+00 );
// CG position w.r.t. ref. point
- cur_fdm_state.set_CG_Position( 0.0, 0.0, 0.0 );
+ cur_fdm_state->set_CG_Position( 0.0, 0.0, 0.0 );
// Initialize view parameters
// FG_LOG( FG_GENERAL, FG_DEBUG, "Before v->init()");
v->set_goal_view_offset( 0.0 );
FG_LOG( FG_GENERAL, FG_DEBUG, "After v->init()");
- v->UpdateViewMath(cur_fdm_state);
+ v->UpdateViewMath(*cur_fdm_state);
FG_LOG( FG_GENERAL, FG_DEBUG, " abs_view_pos = " << v->get_abs_view_pos());
// v->UpdateWorldToEye(f);
- fgFDMInit( current_options.get_flight_model(), cur_fdm_state,
- 1.0 / current_options.get_model_hz() );
+ // fgFDMInit( current_options.get_flight_model(), cur_fdm_state,
+ // 1.0 / current_options.get_model_hz() );
+ cur_fdm_state->init( 1.0 / current_options.get_model_hz() );
- scenery.cur_elev = cur_fdm_state.get_Runway_altitude() * FEET_TO_METER;
+ scenery.cur_elev = cur_fdm_state->get_Runway_altitude() * FEET_TO_METER;
- if ( cur_fdm_state.get_Altitude() < cur_fdm_state.get_Runway_altitude() + 3.758099) {
- cur_fdm_state.set_Altitude( cur_fdm_state.get_Runway_altitude() + 3.758099 );
+ if ( cur_fdm_state->get_Altitude() < cur_fdm_state->get_Runway_altitude() + 3.758099) {
+ cur_fdm_state->set_Altitude( cur_fdm_state->get_Runway_altitude() + 3.758099 );
}
controls.reset_all();
// end of hack
// update view volume parameters
- current_view.UpdateViewParams(cur_fdm_state);
+ current_view.UpdateViewParams(*cur_fdm_state);
// set the sun position
xglLightfv( GL_LIGHT0, GL_POSITION, l->sun_vec );
// we've changed things elsewhere
FGMaterialSlot m_slot;
FGMaterialSlot *m_ptr = &m_slot;
- if ( material_mgr.find( "Default", m_ptr ) );
- m_ptr->get_state()->force();
+ if ( material_mgr.find( "Default", m_ptr ) ) {
+ m_ptr->get_state()->force();
+ }
// draw the ssg scene
ssgCullAndDraw( scene );
// Update internal time dependent calculations (i.e. flight model)
void fgUpdateTimeDepCalcs(int multi_loop, int remainder) {
static fdm_state_list fdm_list;
- FGInterface fdm_state;
+ // FGInterface fdm_state;
fgLIGHT *l = &cur_light_params;
FGTime *t = FGTime::cur_time_params;
// FGView *v = ¤t_view;
multi_loop = 1;
}
- fdm_state = cur_fdm_state;
+ // fdm_state = *cur_fdm_state;
if ( !t->getPause() ) {
// run Autopilot system
fgAPRun();
// printf("updating flight model x %d\n", multi_loop);
- fgFDMUpdate( current_options.get_flight_model(),
+ /* fgFDMUpdate( current_options.get_flight_model(),
fdm_state,
multi_loop * current_options.get_speed_up(),
- remainder );
+ remainder ); */
+ cur_fdm_state->update( multi_loop * current_options.get_speed_up() );
} else {
- fgFDMUpdate( current_options.get_flight_model(),
- fdm_state, 0, remainder );
+ // fgFDMUpdate( current_options.get_flight_model(),
+ // fdm_state, 0, remainder );
+ cur_fdm_state->update( 0 );
}
+ /*
fdm_list.push_back( fdm_state );
while ( fdm_list.size() > 25 ) {
fdm_list.pop_front();
}
if ( current_options.get_view_mode() == fgOPTIONS::FG_VIEW_FIRST_PERSON ) {
- cur_fdm_state = fdm_state;
+ *cur_fdm_state = fdm_state;
} else if ( current_options.get_view_mode() == fgOPTIONS::FG_VIEW_FOLLOW ) {
- cur_fdm_state = fdm_list.front();
+ *cur_fdm_state = fdm_list.front();
}
+ */
// update the view angle
for ( i = 0; i < multi_loop; i++ ) {
}
double tmp = -(l->sun_rotation + FG_PI)
- - (cur_fdm_state.get_Psi() - current_view.get_view_offset() );
+ - (cur_fdm_state->get_Psi() - current_view.get_view_offset() );
while ( tmp < 0.0 ) {
tmp += FG_2PI;
}
/* printf("Before - ground = %.2f runway = %.2f alt = %.2f\n",
scenery.cur_elev,
- cur_fdm_state.get_Runway_altitude() * FEET_TO_METER,
- cur_fdm_state.get_Altitude() * FEET_TO_METER); */
+ cur_fdm_state->get_Runway_altitude() * FEET_TO_METER,
+ cur_fdm_state->get_Altitude() * FEET_TO_METER); */
if ( scenery.cur_elev > -9990 ) {
- if ( cur_fdm_state.get_Altitude() * FEET_TO_METER <
+ if ( cur_fdm_state->get_Altitude() * FEET_TO_METER <
(scenery.cur_elev + alt_adjust_m - 3.0) ) {
// now set aircraft altitude above ground
printf("Current Altitude = %.2f < %.2f forcing to %.2f\n",
- cur_fdm_state.get_Altitude() * FEET_TO_METER,
+ cur_fdm_state->get_Altitude() * FEET_TO_METER,
scenery.cur_elev + alt_adjust_m - 3.0,
scenery.cur_elev + alt_adjust_m );
fgFDMForceAltitude( current_options.get_flight_model(),
FG_LOG( FG_ALL, FG_DEBUG,
"<*> resetting altitude to "
- << cur_fdm_state.get_Altitude() * FEET_TO_METER << " meters" );
+ << cur_fdm_state->get_Altitude() * FEET_TO_METER << " meters" );
}
fgFDMSetGroundElevation( current_options.get_flight_model(),
scenery.cur_elev ); // meters
/* printf("Adjustment - ground = %.2f runway = %.2f alt = %.2f\n",
scenery.cur_elev,
- cur_fdm_state.get_Runway_altitude() * FEET_TO_METER,
- cur_fdm_state.get_Altitude() * FEET_TO_METER); */
+ cur_fdm_state->get_Runway_altitude() * FEET_TO_METER,
+ cur_fdm_state->get_Altitude() * FEET_TO_METER); */
// update "time"
- t->update(cur_fdm_state);
+ t->update(*cur_fdm_state);
// Get elapsed time (in usec) for this past frame
elapsed = fgGetTimeInterval();
double pitch = log((controls.get_throttle(0) * 14.0) + 1.0);
//fprintf(stderr, "pitch1: %f ", pitch);
- if (controls.get_throttle(0) > 0.0 || cur_fdm_state.v_rel_wind > 40.0) {
- //fprintf(stderr, "rel_wind: %f ", cur_fdm_state.v_rel_wind);
+ if (controls.get_throttle(0) > 0.0 || cur_fdm_state->v_rel_wind > 40.0) {
+ //fprintf(stderr, "rel_wind: %f ", cur_fdm_state->v_rel_wind);
// only add relative wind and AoA if prop is moving
// or we're really flying at idle throttle
if (pitch < 5.4) { // this needs tuning
// prop tips not breaking sound barrier
- pitch += log(cur_fdm_state.v_rel_wind + 0.8)/2;
+ pitch += log(cur_fdm_state->v_rel_wind + 0.8)/2;
} else {
// prop tips breaking sound barrier
- pitch += log(cur_fdm_state.v_rel_wind + 0.8)/10;
+ pitch += log(cur_fdm_state->v_rel_wind + 0.8)/10;
}
//fprintf(stderr, "pitch2: %f ", pitch);
//fprintf(stderr, "AoA: %f ", FG_Gamma_vert_rad);
// Angle of Attack next... -x^3(e^x) is my best guess Just
// need to calculate some reasonable scaling factor and
// then clamp it on the positive aoa (neg adj) side
- double aoa = cur_fdm_state.get_Gamma_vert_rad() * 2.2;
+ double aoa = cur_fdm_state->get_Gamma_vert_rad() * 2.2;
double tmp = 3.0;
double aoa_adj = pow(-aoa, tmp) * pow(M_E, aoa);
if (aoa_adj < -0.8) aoa_adj = -0.8;
//fprintf(stderr, "pitch4: %f\n", pitch);
double volume = controls.get_throttle(0) * 1.15 + 0.3 +
- log(cur_fdm_state.v_rel_wind + 1.0)/14.0;
+ log(cur_fdm_state->v_rel_wind + 1.0)/14.0;
// fprintf(stderr, "volume: %f\n", volume);
pitch_envelope.setStep ( 0, 0.01, pitch );
// the main loop, so this will now work without seg faulting
// the system.
solarSystemRebuild();
- current_view.UpdateViewParams(cur_fdm_state);
+ current_view.UpdateViewParams(*cur_fdm_state);
if ( current_options.get_panel_status() ) {
FGPanel::OurPanel->ReInit(0, 0, 1024, 768);
}
projects / flightgear.git / commitdiff