*/
-#include <Include/compiler.h>
+#include <simgear/compiler.h>
#include <math.h>
FG_VECTOR_3 v_dot_local_v;
// inline double * get_V_dot_local_v() { return v_dot_local_v; }
- // 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 ) {
+ 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; }
}
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 ) {
+ 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 ) {
+ 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;
- } */
+ }
+
+ double nlf; //Normal Load Factor
+ double get_Nlf(void) { return nlf; }
+ void set_Nlf(double n) { nlf=n; }
FG_VECTOR_3 omega_dot_body_v;
// inline double * get_Omega_dot_body_v() { return omega_dot_body_v; }
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,
+ 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
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 ) {
+ 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; }
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_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; }
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_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_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_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; }
#endif // _FLIGHT_HXX
-
-