// Convert from the LaRCsim generic_ struct to the fgFLIGHT struct
int fgLaRCsim_2_Flight (fgFLIGHT& 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 );
- /*
- f.get_Dx_pilot() = Dx_pilot;
- f.get_Dy_pilot() = Dy_pilot;
- f.get_Dz_pilot() = Dz_pilot;
- f.get_Dx_cg() = Dx_cg;
- f.get_Dy_cg() = Dy_cg;
- f.get_Dz_cg() = Dz_cg;
- f.get_F_X() = F_X;
- f.get_F_Y() = F_Y;
- f.get_F_Z() = F_Z;
- f.get_F_north() = F_north;
- f.get_F_east() = F_east;
- f.get_F_down() = F_down;
- f.get_F_X_aero() = F_X_aero;
- f.get_F_Y_aero() = F_Y_aero;
- f.get_F_Z_aero() = F_Z_aero;
- f.get_F_X_engine() = F_X_engine;
- f.get_F_Y_engine() = F_Y_engine;
- f.get_F_Z_engine() = F_Z_engine;
- f.get_F_X_gear() = F_X_gear;
- f.get_F_Y_gear() = F_Y_gear;
- f.get_F_Z_gear() = F_Z_gear;
- f.get_M_l_rp() = M_l_rp;
- f.get_M_m_rp() = M_m_rp;
- f.get_M_n_rp() = M_n_rp;
- f.get_M_l_cg() = M_l_cg;
- f.get_M_m_cg() = M_m_cg;
- f.get_M_n_cg() = M_n_cg;
- f.get_M_l_aero() = M_l_aero;
- f.get_M_m_aero() = M_m_aero;
- f.get_M_n_aero() = M_n_aero;
- f.get_M_l_engine() = M_l_engine;
- f.get_M_m_engine() = M_m_engine;
- f.get_M_n_engine() = M_n_engine;
- f.get_M_l_gear() = M_l_gear;
- f.get_M_m_gear() = M_m_gear;
- f.get_M_n_gear() = M_n_gear;
- f.get_V_dot_north() = V_dot_north;
- f.get_V_dot_east() = V_dot_east;
- f.get_V_dot_down() = V_dot_down;
- f.get_U_dot_body() = U_dot_body;
- f.get_V_dot_body() = V_dot_body;
- f.get_W_dot_body() = W_dot_body;
- f.get_A_X_cg() = A_X_cg;
- f.get_A_Y_cg() = A_Y_cg;
- f.get_A_Z_cg() = A_Z_cg;
- f.get_A_X_pilot() = A_X_pilot;
- f.get_A_Y_pilot() = A_Y_pilot;
- f.get_A_Z_pilot() = A_Z_pilot;
- f.get_N_X_cg() = N_X_cg;
- f.get_N_Y_cg() = N_Y_cg;
- f.get_N_Z_cg() = N_Z_cg;
- f.get_N_X_pilot() = N_X_pilot;
- f.get_N_Y_pilot() = N_Y_pilot;
- f.get_N_Z_pilot() = N_Z_pilot;
- f.get_P_dot_body() = P_dot_body;
- f.get_Q_dot_body() = Q_dot_body;
- f.get_R_dot_body() = R_dot_body;
- f.get_V_north() = V_north;
- f.get_V_east() = V_east;
- f.get_V_down() = V_down;
- f.get_V_north_rel_ground() = V_north_rel_ground;
- f.get_V_east_rel_ground() = V_east_rel_ground;
- f.get_V_down_rel_ground() = V_down_rel_ground;
- f.get_V_north_airmass() = V_north_airmass;
- f.get_V_east_airmass() = V_east_airmass;
- f.get_V_down_airmass() = V_down_airmass;
- f.get_V_north_rel_airmass() = V_north_rel_airmass;
- f.get_V_east_rel_airmass() = V_east_rel_airmass;
- f.get_V_down_rel_airmass() = V_down_rel_airmass;
- f.get_U_gust() = U_gust;
- f.get_V_gust() = V_gust;
- f.get_W_gust() = W_gust;
- f.get_U_body() = U_body;
- f.get_V_body() = V_body;
- f.get_W_body() = W_body;
- f.get_V_rel_wind() = V_rel_wind;
- f.get_V_true_kts() = V_true_kts;
- f.get_V_rel_ground() = V_rel_ground;
- f.get_V_inertial() = V_inertial;
- f.get_V_ground_speed() = V_ground_speed;
- f.get_V_equiv() = V_equiv;
- f.get_V_equiv_kts() = V_equiv_kts;
- f.get_V_calibrated() = V_calibrated;
- f.get_V_calibrated_kts() = V_calibrated_kts;
- f.get_P_body() = P_body;
- f.get_Q_body() = Q_body;
- f.get_R_body() = R_body;
- f.get_P_local() = P_local;
- f.get_Q_local() = Q_local;
- f.get_R_local() = R_local;
- f.get_P_total() = P_total;
- f.get_Q_total() = Q_total;
- f.get_R_total() = R_total;
- f.get_Phi_dot() = Phi_dot;
- f.get_Theta_dot() = Theta_dot;
- f.get_Psi_dot() = Psi_dot;
- f.get_Latitude_dot() = Latitude_dot;
- f.get_Longitude_dot() = Longitude_dot;
- f.get_Radius_dot() = Radius_dot;
- f.get_Lat_geocentric() = Lat_geocentric;
- f.get_Lon_geocentric() = Lon_geocentric;
- f.get_Radius_to_vehicle() = Radius_to_vehicle;
- f.get_Latitude() = Latitude;
- f.get_Longitude() = Longitude;
- f.get_Altitude() = Altitude;
- f.get_Phi() = Phi;
- f.get_Theta() = Theta;
- f.get_Psi() = Psi;
- f.get_T_local_to_body_11() = T_local_to_body_11;
- f.get_T_local_to_body_12() = T_local_to_body_12;
- f.get_T_local_to_body_13() = T_local_to_body_13;
- f.get_T_local_to_body_21() = T_local_to_body_21;
- f.get_T_local_to_body_22() = T_local_to_body_22;
- f.get_T_local_to_body_23() = T_local_to_body_23;
- f.get_T_local_to_body_31() = T_local_to_body_31;
- f.get_T_local_to_body_32() = T_local_to_body_32;
- f.get_T_local_to_body_33() = T_local_to_body_33;
- f.get_Gravity() = Gravity;
- f.get_Centrifugal_relief() = Centrifugal_relief;
- f.get_Alpha() = Alpha;
- f.get_Beta() = Beta;
- f.get_Alpha_dot() = Alpha_dot;
- f.get_Beta_dot() = Beta_dot;
- f.get_Cos_alpha() = Cos_alpha;
- f.get_Sin_alpha() = Sin_alpha;
- f.get_Cos_beta() = Cos_beta;
- f.get_Sin_beta() = Sin_beta;
- f.get_Cos_phi() = Cos_phi;
- f.get_Sin_phi() = Sin_phi;
- f.get_Cos_theta() = Cos_theta;
- f.get_Sin_theta() = Sin_theta;
- f.get_Cos_psi() = Cos_psi;
- f.get_Sin_psi() = Sin_psi;
- f.get_Gamma_vert_rad() = Gamma_vert_rad;
- f.get_Gamma_horiz_rad() = Gamma_horiz_rad;
- f.get_Sigma() = Sigma;
- f.get_Density() = Density;
- f.get_V_sound() = V_sound;
- f.get_Mach_number() = Mach_number;
- f.get_Static_pressure() = Static_pressure;
- f.get_Total_pressure() = Total_pressure;
- f.get_Impact_pressure() = Impact_pressure;
- f.get_Dynamic_pressure() = Dynamic_pressure;
- f.get_Static_temperature() = Static_temperature;
- f.get_Total_temperature() = Total_temperature;
- f.get_Sea_level_radius() = Sea_level_radius;
- f.get_Earth_position_angle() = Earth_position_angle;
- f.get_Runway_altitude() = Runway_altitude;
- f.get_Runway_latitude() = Runway_latitude;
- f.get_Runway_longitude() = Runway_longitude;
- f.get_Runway_heading() = Runway_heading;
- f.get_Radius_to_rwy() = Radius_to_rwy;
- f.get_D_cg_north_of_rwy() = D_cg_north_of_rwy;
- f.get_D_cg_east_of_rwy() = D_cg_east_of_rwy;
- f.get_D_cg_above_rwy() = D_cg_above_rwy;
- f.get_X_cg_rwy() = X_cg_rwy;
- f.get_Y_cg_rwy() = Y_cg_rwy;
- f.get_H_cg_rwy() = H_cg_rwy;
- f.get_D_pilot_north_of_rwy() = D_pilot_north_of_rwy;
- f.get_D_pilot_east_of_rwy() = D_pilot_east_of_rwy;
- f.get_D_pilot_above_rwy() = D_pilot_above_rwy;
- f.get_X_pilot_rwy() = X_pilot_rwy;
- f.get_Y_pilot_rwy() = Y_pilot_rwy;
- f.get_H_pilot_rwy() = H_pilot_rwy;
- */
- return ( 0 );
+ // 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 );
+
+ // 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 );
+
+ return 0;
}
// $Log$
+// Revision 1.5 1998/12/03 04:25:02 curt
+// Working on fixing up new fgFLIGHT class.
+//
// Revision 1.4 1998/12/03 01:16:37 curt
// Converted fgFLIGHT to a class.
//
-// flight.h -- define shared flight model parameters
+// flight.hxx -- define shared flight model parameters
//
// Written by Curtis Olson, started May 1997.
//
// (Log is kept at end of this file)
-#ifndef _FLIGHT_H
-#define _FLIGHT_H
+#ifndef _FLIGHT_HXX
+#define _FLIGHT_HXX
#include <Flight/Slew/slew.hxx>
inline double get_I_yy() const { return i_yy; }
inline double get_I_zz() const { return i_zz; }
inline double get_I_xz() const { return i_xz; }
-
+ inline void set_Inertias( double m, double xx, double yy,
+ double zz, double xz)
+ {
+ mass = m;
+ i_xx = xx;
+ i_yy = yy;
+ i_zz = zz;
+ i_xz = xz;
+ }
+
// Pilot location rel to ref pt
FG_VECTOR_3 d_pilot_rp_body_v;
inline double * get_D_pilot_rp_body_v() {
inline double get_Dx_pilot() const { return d_pilot_rp_body_v[0]; }
inline double get_Dy_pilot() const { return d_pilot_rp_body_v[1]; }
inline double get_Dz_pilot() const { return d_pilot_rp_body_v[2]; }
+ inline void set_Pilot_Location( double dx, double dy, double dz ) {
+ d_pilot_rp_body_v[0] = dx;
+ d_pilot_rp_body_v[1] = dy;
+ d_pilot_rp_body_v[2] = dz;
+ }
// CG position w.r.t. ref. point
FG_VECTOR_3 d_cg_rp_body_v;
inline double get_Dx_cg() const { return d_cg_rp_body_v[0]; }
inline double get_Dy_cg() const { return d_cg_rp_body_v[1]; }
inline double get_Dz_cg() const { return d_cg_rp_body_v[2]; }
+ inline void set_CG_Position( double dx, double dy, double dz ) {
+ d_cg_rp_body_v[0] = dx;
+ d_cg_rp_body_v[1] = dy;
+ d_cg_rp_body_v[2] = dz;
+ }
/*================================ Forces =================================*/
inline double get_F_X() const { return f_body_total_v[0]; }
inline double get_F_Y() const { return f_body_total_v[1]; }
inline double get_F_Z() const { return f_body_total_v[2]; }
+ inline void set_Forces_Body_Total( double x, double y, double z ) {
+ f_body_total_v[0] = x;
+ f_body_total_v[1] = y;
+ f_body_total_v[2] = z;
+ }
FG_VECTOR_3 f_local_total_v;
inline double * get_F_local_total_v() { return f_local_total_v; }
inline double get_F_north() const { return f_local_total_v[0]; }
inline double get_F_east() const { return f_local_total_v[1]; }
inline double get_F_down() const { return f_local_total_v[2]; }
+ inline void set_Forces_Local_Total( double x, double y, double z ) {
+ f_local_total_v[0] = x;
+ f_local_total_v[1] = y;
+ f_local_total_v[2] = z;
+ }
FG_VECTOR_3 f_aero_v;
inline double * get_F_aero_v() { return f_aero_v; }
inline double get_F_X_aero() const { return f_aero_v[0]; }
inline double get_F_Y_aero() const { return f_aero_v[1]; }
inline double get_F_Z_aero() const { return f_aero_v[2]; }
+ inline void set_Forces_Aero( double x, double y, double z ) {
+ f_aero_v[0] = x;
+ f_aero_v[1] = y;
+ f_aero_v[2] = z;
+ }
FG_VECTOR_3 f_engine_v;
inline double * get_F_engine_v() { return f_engine_v; }
inline double get_F_X_engine() const { return f_engine_v[0]; }
inline double get_F_Y_engine() const { return f_engine_v[1]; }
inline double get_F_Z_engine() const { return f_engine_v[2]; }
+ inline void set_Forces_Engine( double x, double y, double z ) {
+ f_engine_v[0] = x;
+ f_engine_v[1] = y;
+ f_engine_v[2] = z;
+ }
FG_VECTOR_3 f_gear_v;
inline double * get_F_gear_v() { return f_gear_v; }
inline double get_F_X_gear() const { return f_gear_v[0]; }
inline double get_F_Y_gear() const { return f_gear_v[1]; }
inline double get_F_Z_gear() const { return f_gear_v[2]; }
+ inline void set_Forces_Gear( double x, double y, double z ) {
+ f_gear_v[0] = x;
+ f_gear_v[1] = y;
+ f_gear_v[2] = z;
+ }
/*================================ Moments ================================*/
- FG_VECTOR_3 m_total_rp_v;
+ FG_VECTOR_3 m_total_rp_v;
inline double * get_M_total_rp_v() { return m_total_rp_v; }
inline double get_M_l_rp() const { return m_total_rp_v[0]; }
inline double get_M_m_rp() const { return m_total_rp_v[1]; }
inline double get_M_n_rp() const { return m_total_rp_v[2]; }
+ inline void set_Moments_Total_RP( double l, double m, double n ) {
+ m_total_rp_v[0] = l;
+ m_total_rp_v[1] = m;
+ m_total_rp_v[2] = n;
+ }
- FG_VECTOR_3 m_total_cg_v;
+ FG_VECTOR_3 m_total_cg_v;
inline double * get_M_total_cg_v() { return m_total_cg_v; }
inline double get_M_l_cg() const { return m_total_cg_v[0]; }
inline double get_M_m_cg() const { return m_total_cg_v[1]; }
inline double get_M_n_cg() const { return m_total_cg_v[2]; }
+ inline void set_Moments_Total_CG( double l, double m, double n ) {
+ m_total_cg_v[0] = l;
+ m_total_cg_v[1] = m;
+ m_total_cg_v[2] = n;
+ }
- FG_VECTOR_3 m_aero_v;
+ FG_VECTOR_3 m_aero_v;
inline double * get_M_aero_v() { return m_aero_v; }
inline double get_M_l_aero() const { return m_aero_v[0]; }
inline double get_M_m_aero() const { return m_aero_v[1]; }
inline double get_M_n_aero() const { return m_aero_v[2]; }
+ inline void set_Moments_Aero( double l, double m, double n ) {
+ m_aero_v[0] = l;
+ m_aero_v[1] = m;
+ m_aero_v[2] = n;
+ }
FG_VECTOR_3 m_engine_v;
inline double * get_M_engine_v() { return m_engine_v; }
inline double get_M_l_engine() const { return m_engine_v[0]; }
inline double get_M_m_engine() const { return m_engine_v[1]; }
inline double get_M_n_engine() const { return m_engine_v[2]; }
+ inline void set_Moments_Engine( double l, double m, double n ) {
+ m_engine_v[0] = l;
+ m_engine_v[1] = m;
+ m_engine_v[2] = n;
+ }
FG_VECTOR_3 m_gear_v;
inline double * get_M_gear_v() { return m_gear_v; }
inline double get_M_l_gear() const { return m_gear_v[0]; }
inline double get_M_m_gear() const { return m_gear_v[1]; }
inline double get_M_n_gear() const { return m_gear_v[2]; }
+ inline void set_Moments_Gear( double l, double m, double n ) {
+ m_gear_v[0] = l;
+ m_gear_v[1] = m;
+ m_gear_v[2] = n;
+ }
/*============================== Accelerations ============================*/
inline double get_V_dot_north() const { return v_dot_local_v[0]; }
inline double get_V_dot_east() const { return v_dot_local_v[1]; }
inline double get_V_dot_down() const { return v_dot_local_v[2]; }
+ inline void set_Accels_Local( double north, double east, double down ) {
+ v_dot_local_v[0] = north;
+ v_dot_local_v[1] = east;
+ v_dot_local_v[2] = down;
+ }
FG_VECTOR_3 v_dot_body_v;
inline double * get_V_dot_body_v() { return v_dot_body_v; }
inline double get_U_dot_body() const { return v_dot_body_v[0]; }
inline double get_V_dot_body() const { return v_dot_body_v[1]; }
inline double get_W_dot_body() const { return v_dot_body_v[2]; }
+ inline void set_Accels_Body( double u, double v, double w ) {
+ v_dot_local_v[0] = u;
+ v_dot_local_v[1] = v;
+ v_dot_local_v[2] = w;
+ }
FG_VECTOR_3 a_cg_body_v;
inline double * get_A_cg_body_v() { return a_cg_body_v; }
inline double get_A_X_cg() const { return a_cg_body_v[0]; }
inline double get_A_Y_cg() const { return a_cg_body_v[1]; }
inline double get_A_Z_cg() const { return a_cg_body_v[2]; }
+ inline void set_Accels_CG_Body( double x, double y, double z ) {
+ a_cg_body_v[0] = x;
+ a_cg_body_v[1] = y;
+ a_cg_body_v[2] = z;
+ }
FG_VECTOR_3 a_pilot_body_v;
inline double * get_A_pilot_body_v() { return a_pilot_body_v; }
inline double get_A_X_pilot() const { return a_pilot_body_v[0]; }
inline double get_A_Y_pilot() const { return a_pilot_body_v[1]; }
inline double get_A_Z_pilot() const { return a_pilot_body_v[2]; }
+ inline void set_Accels_Pilot_Body( double x, double y, double z ) {
+ a_pilot_body_v[0] = x;
+ a_pilot_body_v[1] = y;
+ a_pilot_body_v[2] = z;
+ }
FG_VECTOR_3 n_cg_body_v;
inline double * get_N_cg_body_v() { return n_cg_body_v; }
inline double get_N_X_cg() const { return n_cg_body_v[0]; }
inline double get_N_Y_cg() const { return n_cg_body_v[1]; }
inline double get_N_Z_cg() const { return n_cg_body_v[2]; }
+ inline void set_Accels_CG_Body_N( double x, double y, double z ) {
+ n_cg_body_v[0] = x;
+ n_cg_body_v[1] = y;
+ n_cg_body_v[2] = z;
+ }
FG_VECTOR_3 n_pilot_body_v;
inline double * get_N_pilot_body_v() { return n_pilot_body_v; }
inline double get_N_X_pilot() const { return n_pilot_body_v[0]; }
inline double get_N_Y_pilot() const { return n_pilot_body_v[1]; }
inline double get_N_Z_pilot() const { return n_pilot_body_v[2]; }
+ inline void set_Accels_Pilot_Body_N( double x, double y, double z ) {
+ n_pilot_body_v[0] = x;
+ n_pilot_body_v[1] = y;
+ n_pilot_body_v[2] = z;
+ }
FG_VECTOR_3 omega_dot_body_v;
inline double * get_Omega_dot_body_v() { return omega_dot_body_v; }
inline double get_P_dot_body() const { return omega_dot_body_v[0]; }
inline double get_Q_dot_body() const { return omega_dot_body_v[1]; }
inline double get_R_dot_body() const { return omega_dot_body_v[2]; }
+ inline void set_Accels_Omega( double p, double q, double r ) {
+ omega_dot_body_v[0] = p;
+ omega_dot_body_v[1] = q;
+ omega_dot_body_v[2] = r;
+ }
/*============================== Velocities ===============================*/
inline double get_V_north() const { return v_local_v[0]; }
inline double get_V_east() const { return v_local_v[1]; }
inline double get_V_down() const { return v_local_v[2]; }
+ inline void set_Velocities_Local( double north, double east, double down ) {
+ v_local_v[0] = north;
+ v_local_v[1] = east;
+ v_local_v[2] = down;
+ }
FG_VECTOR_3 v_local_rel_ground_v; /* V rel w.r.t. earth surface */
inline double * get_V_local_rel_ground_v() { return v_local_rel_ground_v; }
inline double get_V_down_rel_ground() const {
return v_local_rel_ground_v[2];
}
+ inline void set_Velocities_Ground(double north, double east, double down) {
+ v_local_rel_ground_v[0] = north;
+ v_local_rel_ground_v[1] = east;
+ v_local_rel_ground_v[2] = down;
+ }
FG_VECTOR_3 v_local_airmass_v; /* velocity of airmass (steady winds) */
inline double * get_V_local_airmass_v() { return v_local_airmass_v; }
inline double get_V_north_airmass() const { return v_local_airmass_v[0]; }
inline double get_V_east_airmass() const { return v_local_airmass_v[1]; }
inline double get_V_down_airmass() const { return v_local_airmass_v[2]; }
+ inline void set_Velocities_Local_Airmass( double north, double east,
+ double down)
+ {
+ v_local_airmass_v[0] = north;
+ v_local_airmass_v[1] = east;
+ v_local_airmass_v[2] = down;
+ }
FG_VECTOR_3 v_local_rel_airmass_v; /* velocity of veh. relative to */
/* airmass */
inline double get_V_down_rel_airmass() const {
return v_local_rel_airmass_v[2];
}
+ inline void set_Velocities_Local_Rel_Airmass( double north, double east,
+ double down)
+ {
+ v_local_rel_airmass_v[0] = north;
+ v_local_rel_airmass_v[1] = east;
+ v_local_rel_airmass_v[2] = down;
+ }
FG_VECTOR_3 v_local_gust_v; /* linear turbulence components, L frame */
inline double * get_V_local_gust_v() { return v_local_gust_v; }
inline double get_U_gust() const { return v_local_gust_v[0]; }
inline double get_V_gust() const { return v_local_gust_v[1]; }
inline double get_W_gust() const { return v_local_gust_v[2]; }
-
+ inline void set_Velocities_Gust( double u, double v, double w)
+ {
+ v_local_gust_v[0] = u;
+ v_local_gust_v[1] = v;
+ v_local_gust_v[2] = w;
+ }
+
FG_VECTOR_3 v_wind_body_v; /* Wind-relative velocities in body axis */
inline double * get_V_wind_body_v() { return v_wind_body_v; }
inline double get_U_body() const { return v_wind_body_v[0]; }
inline double get_V_body() const { return v_wind_body_v[1]; }
inline double get_W_body() const { return v_wind_body_v[2]; }
+ inline void set_Velocities_Wind_Body( double u, double v, double w)
+ {
+ v_wind_body_v[0] = u;
+ v_wind_body_v[1] = v;
+ v_wind_body_v[2] = w;
+ }
double v_rel_wind, v_true_kts, v_rel_ground, v_inertial;
double v_ground_speed, v_equiv, v_equiv_kts;
double v_calibrated, v_calibrated_kts;
+
inline double get_V_rel_wind() const { return v_rel_wind; }
+ inline void set_V_rel_wind(double wind) { v_rel_wind = wind; }
+
inline double get_V_true_kts() const { return v_true_kts; }
+ inline void set_V_true_kts(double kts) { v_true_kts = kts; }
+
inline double get_V_rel_ground() const { return v_rel_ground; }
+ inline void set_V_rel_ground( double v ) { v_rel_ground = v; }
+
inline double get_V_inertial() const { return v_inertial; }
+ inline void set_V_inertial(double v) { v_inertial = v; }
+
inline double get_V_ground_speed() const { return v_ground_speed; }
+ inline void set_V_ground_speed( double v) { v_ground_speed = v; }
+
inline double get_V_equiv() const { return v_equiv; }
+ inline void set_V_equiv( double v ) { v_equiv = v; }
+
inline double get_V_equiv_kts() const { return v_equiv_kts; }
+ inline void set_V_equiv_kts( double kts ) { v_equiv_kts = kts; }
+
inline double get_V_calibrated() const { return v_calibrated; }
+ inline void set_V_calibrated( double v ) { v_calibrated = v; }
+
inline double get_V_calibrated_kts() const { return v_calibrated_kts; }
+ inline void set_V_calibrated_kts( double kts ) { v_calibrated_kts = kts; }
FG_VECTOR_3 omega_body_v; /* Angular B rates */
inline double * get_Omega_body_v() { return omega_body_v; }
inline double get_P_body() const { return omega_body_v[0]; }
inline double get_Q_body() const { return omega_body_v[1]; }
inline double get_R_body() const { return omega_body_v[2]; }
+ inline void set_Omega_Body( double p, double q, double r ) {
+ omega_body_v[0] = p;
+ omega_body_v[1] = q;
+ omega_body_v[2] = r;
+ }
FG_VECTOR_3 omega_local_v; /* Angular L rates */
inline double * get_Omega_local_v() { return omega_local_v; }
inline double get_P_local() const { return omega_local_v[0]; }
inline double get_Q_local() const { return omega_local_v[1]; }
inline double get_R_local() const { return omega_local_v[2]; }
+ inline void set_Omega_Local( double p, double q, double r ) {
+ omega_local_v[0] = p;
+ omega_local_v[1] = q;
+ omega_local_v[2] = r;
+ }
FG_VECTOR_3 omega_total_v; /* Diff btw B & L */
inline double * get_Omega_total_v() { return omega_total_v; }
inline double get_P_total() const { return omega_total_v[0]; }
inline double get_Q_total() const { return omega_total_v[1]; }
inline double get_R_total() const { return omega_total_v[2]; }
+ inline void set_Omega_Total( double p, double q, double r ) {
+ omega_total_v[0] = p;
+ omega_total_v[1] = q;
+ omega_total_v[2] = r;
+ }
FG_VECTOR_3 euler_rates_v;
inline double * get_Euler_rates_v() { return euler_rates_v; }
inline double get_Phi_dot() const { return euler_rates_v[0]; }
inline double get_Theta_dot() const { return euler_rates_v[1]; }
inline double get_Psi_dot() const { return euler_rates_v[2]; }
+ inline void set_Euler_Rates( double phi, double theta, double psi ) {
+ euler_rates_v[0] = phi;
+ euler_rates_v[1] = theta;
+ euler_rates_v[2] = psi;
+ }
FG_VECTOR_3 geocentric_rates_v; /* Geocentric linear velocities */
inline double * get_Geocentric_rates_v() { return geocentric_rates_v; }
inline double get_Latitude_dot() const { return geocentric_rates_v[0]; }
inline double get_Longitude_dot() const { return geocentric_rates_v[1]; }
inline double get_Radius_dot() const { return geocentric_rates_v[2]; }
+ inline void set_Geocentric_Rates( double lat, double lon, double rad ) {
+ geocentric_rates_v[0] = lat;
+ geocentric_rates_v[1] = lon;
+ geocentric_rates_v[2] = rad;
+ }
/*=============================== Positions ===============================*/
inline void set_Radius_to_vehicle(double radius) {
geocentric_position_v[2] = radius;
}
+ inline void set_Geocentric_Position( double lat, double lon, double rad ) {
+ geocentric_position_v[0] = lat;
+ geocentric_position_v[1] = lon;
+ geocentric_position_v[2] = rad;
+ }
FG_VECTOR_3 geodetic_position_v;
inline double * get_Geodetic_position_v() { return geodetic_position_v; }
inline double get_Latitude() const { return geodetic_position_v[0]; }
inline void set_Latitude(double lat) { geodetic_position_v[0] = lat; }
inline double get_Longitude() const { return geodetic_position_v[1]; }
- inline void set_Longitude(double lon) { geodetic_position_v[0] = lon; }
+ inline void set_Longitude(double lon) { geodetic_position_v[1] = lon; }
inline double get_Altitude() const { return geodetic_position_v[2]; }
inline void set_Altitude(double altitude) {
geodetic_position_v[2] = altitude;
}
+ inline void set_Geodetic_Position( double lat, double lon, double alt ) {
+ geodetic_position_v[0] = lat;
+ geodetic_position_v[1] = lon;
+ geodetic_position_v[2] = alt;
+ }
- FG_VECTOR_3 euler_angles_v;
+ FG_VECTOR_3 euler_angles_v;
inline double * get_Euler_angles_v() { return euler_angles_v; }
inline double get_Phi() const { return euler_angles_v[0]; }
inline double get_Theta() const { return euler_angles_v[1]; }
inline double get_Psi() const { return euler_angles_v[2]; }
+ inline void set_Euler_Angles( double phi, double theta, double psi ) {
+ euler_angles_v[0] = phi;
+ euler_angles_v[1] = theta;
+ euler_angles_v[2] = psi;
+ }
+
/*======================= Miscellaneous quantities ========================*/
inline double get_T_local_to_body_33() const {
return t_local_to_body_m[2][2];
}
+ inline void set_T_Local_to_Body( double m[3][3] ) {
+ int i, j;
+ for ( i = 0; i < 3; i++ ) {
+ for ( j = 0; j < 3; j++ ) {
+ t_local_to_body_m[i][j] = m[i][j];
+ }
+ }
+ }
double gravity; /* Local acceleration due to G */
inline double get_Gravity() const { return gravity; }
-
+ inline void set_Gravity(double g) { gravity = g; }
+
double centrifugal_relief; /* load factor reduction due to speed */
inline double get_Centrifugal_relief() const { return centrifugal_relief; }
+ inline void set_Centrifugal_relief(double cr) { centrifugal_relief = cr; }
double alpha, beta, alpha_dot, beta_dot; /* in radians */
inline double get_Alpha() const { return alpha; }
+ inline void set_Alpha( double a ) { alpha = a; }
inline double get_Beta() const { return beta; }
+ inline void set_Beta( double b ) { beta = b; }
inline double get_Alpha_dot() const { return alpha_dot; }
+ inline void set_Alpha_dot( double ad ) { alpha_dot = ad; }
inline double get_Beta_dot() const { return beta_dot; }
+ inline void set_Beta_dot( double bd ) { beta_dot = bd; }
double cos_alpha, sin_alpha, cos_beta, sin_beta;
inline double get_Cos_alpha() const { return cos_alpha; }
+ inline void set_Cos_alpha( double ca ) { cos_alpha = ca; }
inline double get_Sin_alpha() const { return sin_alpha; }
+ inline void set_Sin_alpha( double sa ) { sin_alpha = sa; }
inline double get_Cos_beta() const { return cos_beta; }
+ inline void set_Cos_beta( double cb ) { cos_beta = cb; }
inline double get_Sin_beta() const { return sin_beta; }
+ inline void set_Sin_beta( double sb ) { sin_beta = sb; }
double cos_phi, sin_phi, cos_theta, sin_theta, cos_psi, sin_psi;
inline double get_Cos_phi() const { return cos_phi; }
+ inline void set_Cos_phi( double cp ) { cos_phi = cp; }
inline double get_Sin_phi() const { return sin_phi; }
+ inline void set_Sin_phi( double sp ) { sin_phi = sp; }
inline double get_Cos_theta() const { return cos_theta; }
+ inline void set_Cos_theta( double ct ) { cos_theta = ct; }
inline double get_Sin_theta() const { return sin_theta; }
+ inline void set_Sin_theta( double st ) { sin_theta = st; }
inline double get_Cos_psi() const { return cos_psi; }
+ inline void set_Cos_psi( double cp ) { cos_psi = cp; }
inline double get_Sin_psi() const { return sin_psi; }
+ inline void set_Sin_psi( double sp ) { sin_psi = sp; }
double gamma_vert_rad, gamma_horiz_rad; /* Flight path angles */
inline double get_Gamma_vert_rad() const { return gamma_vert_rad; }
+ inline void set_Gamma_vert_rad( double gv ) { gamma_vert_rad = gv; }
inline double get_Gamma_horiz_rad() const { return gamma_horiz_rad; }
+ inline void set_Gamma_horiz_rad( double gh ) { gamma_horiz_rad = gh; }
double sigma, density, v_sound, mach_number;
inline double get_Sigma() const { return sigma; }
+ inline void set_Sigma( double s ) { sigma = s; }
inline double get_Density() const { return density; }
+ inline void set_Density( double d ) { density = d; }
inline double get_V_sound() const { return v_sound; }
+ inline void set_V_sound( double v ) { v_sound = v; }
inline double get_Mach_number() const { return mach_number; }
+ inline void set_Mach_number( double m ) { mach_number = m; }
double static_pressure, total_pressure, impact_pressure;
double dynamic_pressure;
inline double get_Static_pressure() const { return static_pressure; }
+ inline void set_Static_pressure( double sp ) { static_pressure = sp; }
inline double get_Total_pressure() const { return total_pressure; }
+ inline void set_Total_pressure( double tp ) { total_pressure = tp; }
inline double get_Impact_pressure() const { return impact_pressure; }
+ inline void set_Impact_pressure( double ip ) { impact_pressure = ip; }
inline double get_Dynamic_pressure() const { return dynamic_pressure; }
+ inline void set_Dynamic_pressure( double dp ) { dynamic_pressure = dp; }
double static_temperature, total_temperature;
inline double get_Static_temperature() const { return static_temperature; }
+ inline void set_Static_temperature( double t ) { static_temperature = t; }
inline double get_Total_temperature() const { return total_temperature; }
+ inline void set_Total_temperature( double t ) { total_temperature = t; }
double sea_level_radius, earth_position_angle;
inline double get_Sea_level_radius() const { return sea_level_radius; }
+ inline void set_Sea_level_radius( double r ) { sea_level_radius = r; }
inline double get_Earth_position_angle() const {
return earth_position_angle;
}
- inline void set_Earth_position_angle(double angle) {
- earth_position_angle = angle;
+ inline void set_Earth_position_angle(double a) {
+ earth_position_angle = a;
}
double runway_altitude, runway_latitude, runway_longitude;
inline double get_Runway_altitude() const { return runway_altitude; }
inline void set_Runway_altitude( double alt ) { runway_altitude = alt; }
inline double get_Runway_latitude() const { return runway_latitude; }
+ inline void set_Runway_latitude( double lat ) { runway_latitude = lat; }
inline double get_Runway_longitude() const { return runway_longitude; }
+ inline void set_Runway_longitude( double lon ) { runway_longitude = lon; }
inline double get_Runway_heading() const { return runway_heading; }
+ inline void set_Runway_heading( double h ) { runway_heading = h; }
double radius_to_rwy;
inline double get_Radius_to_rwy() const { return radius_to_rwy; }
+ inline void set_Radius_to_rwy( double r ) { radius_to_rwy = r; }
FG_VECTOR_3 d_cg_rwy_local_v; /* CG rel. to rwy in local coords */
inline double * get_D_cg_rwy_local_v() { return d_cg_rwy_local_v; }
inline double get_D_cg_north_of_rwy() const { return d_cg_rwy_local_v[0]; }
inline double get_D_cg_east_of_rwy() const { return d_cg_rwy_local_v[1]; }
inline double get_D_cg_above_rwy() const { return d_cg_rwy_local_v[2]; }
+ inline void set_CG_Rwy_Local( double north, double east, double above )
+ {
+ d_cg_rwy_local_v[0] = north;
+ d_cg_rwy_local_v[1] = east;
+ d_cg_rwy_local_v[2] = above;
+ }
FG_VECTOR_3 d_cg_rwy_rwy_v; /* CG relative to rwy, in rwy coordinates */
inline double * get_D_cg_rwy_rwy_v() { return d_cg_rwy_rwy_v; }
inline double get_X_cg_rwy() const { return d_cg_rwy_rwy_v[0]; }
inline double get_Y_cg_rwy() const { return d_cg_rwy_rwy_v[1]; }
inline double get_H_cg_rwy() const { return d_cg_rwy_rwy_v[2]; }
+ inline void set_CG_Rwy_Rwy( double x, double y, double h )
+ {
+ d_cg_rwy_rwy_v[0] = x;
+ d_cg_rwy_rwy_v[1] = y;
+ d_cg_rwy_rwy_v[2] = h;
+ }
FG_VECTOR_3 d_pilot_rwy_local_v; /* pilot rel. to rwy in local coords */
inline double * get_D_pilot_rwy_local_v() { return d_pilot_rwy_local_v; }
inline double get_D_pilot_above_rwy() const {
return d_pilot_rwy_local_v[2];
}
+ inline void set_Pilot_Rwy_Local( double north, double east, double above )
+ {
+ d_pilot_rwy_local_v[0] = north;
+ d_pilot_rwy_local_v[1] = east;
+ d_pilot_rwy_local_v[2] = above;
+ }
FG_VECTOR_3 d_pilot_rwy_rwy_v; /* pilot rel. to rwy, in rwy coords. */
inline double * get_D_pilot_rwy_rwy_v() { return d_pilot_rwy_rwy_v; }
inline double get_X_pilot_rwy() const { return d_pilot_rwy_rwy_v[0]; }
inline double get_Y_pilot_rwy() const { return d_pilot_rwy_rwy_v[1]; }
inline double get_H_pilot_rwy() const { return d_pilot_rwy_rwy_v[2]; }
+ inline void set_Pilot_Rwy_Rwy( double x, double y, double h )
+ {
+ d_pilot_rwy_rwy_v[0] = x;
+ d_pilot_rwy_rwy_v[1] = y;
+ d_pilot_rwy_rwy_v[2] = h;
+ }
double climb_rate; /* in feet per second */
inline double get_Climb_Rate() const { return climb_rate; }
inline void set_Climb_Rate(double rate) { climb_rate = rate; }
-
- // Additional convenience functions
-
- // Inertias
- inline void set_Inertias( double m, double xx, double yy,
- double zz, double xz)
- {
- mass = m;
- i_xx = xx;
- i_yy = yy;
- i_zz = zz;
- i_xz = xz;
- }
-
- // Local velocities
- inline void set_Local_Velocities( double v_north,
- double v_east,
- double v_down )
- {
- v_local_v[0] = v_north;
- v_local_v[1] = v_east;
- v_local_v[2] = v_down;
- }
-
- // Orientation
- inline void set_Euler_Orientation( double phi,
- double theta,
- double psi )
- {
- euler_angles_v[0] = phi;
- euler_angles_v[1] = theta;
- euler_angles_v[2] = psi;
- }
-
- // Body Rates
- inline void set_Body_Rates( double p_body, double q_body, double r_body )
- {
- omega_body_v[0] = p_body;
- omega_body_v[1] = q_body;
- omega_body_v[2] = r_body;
- }
-
- // Center of Gravity position w.r.t. ref. point
- inline void set_CG_Position( double dx, double dy, double dz )
- {
- d_cg_rp_body_v[0] = dx;
- d_cg_rp_body_v[1] = dy;
- d_cg_rp_body_v[2] = dz;
- }
};
void fgFlightModelSetAltitude(int model, fgFLIGHT& f, double alt_meters);
-#endif /* _FLIGHT_H */
+#endif // _FLIGHT_HXX
// $Log$
+// Revision 1.4 1998/12/03 04:25:03 curt
+// Working on fixing up new fgFLIGHT class.
+//
// Revision 1.3 1998/12/03 01:16:41 curt
// Converted fgFLIGHT to a class.
//
projects / flightgear.git / commitdiff