1089 lines
40 KiB
C++
1089 lines
40 KiB
C++
// flight.hxx -- define shared flight model parameters
|
|
//
|
|
// Written by Curtis Olson, started May 1997.
|
|
//
|
|
// Copyright (C) 1997 Curtis L. Olson - curt@infoplane.com
|
|
//
|
|
// This program is free software; you can redistribute it and/or
|
|
// modify it under the terms of the GNU General Public License as
|
|
// published by the Free Software Foundation; either version 2 of the
|
|
// License, or (at your option) any later version.
|
|
//
|
|
// This program is distributed in the hope that it will be useful, but
|
|
// WITHOUT ANY WARRANTY; without even the implied warranty of
|
|
// MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU
|
|
// General Public License for more details.
|
|
//
|
|
// You should have received a copy of the GNU General Public License
|
|
// along with this program; if not, write to the Free Software
|
|
// Foundation, Inc., 675 Mass Ave, Cambridge, MA 02139, USA.
|
|
//
|
|
// $Id$
|
|
|
|
|
|
#ifndef _FLIGHT_HXX
|
|
#define _FLIGHT_HXX
|
|
|
|
|
|
#ifndef __cplusplus
|
|
# error This library requires C++
|
|
#endif
|
|
|
|
|
|
/* Required get_()
|
|
|
|
`FGInterface::get_Longitude ()'
|
|
`FGInterface::get_Latitude ()'
|
|
`FGInterface::get_Altitude ()'
|
|
`FGInterface::get_Phi ()'
|
|
`FGInterface::get_Theta ()'
|
|
`FGInterface::get_Psi ()'
|
|
`FGInterface::get_V_equiv_kts ()'
|
|
|
|
`FGInterface::get_Mass ()'
|
|
`FGInterface::get_I_xx ()'
|
|
`FGInterface::get_I_yy ()'
|
|
`FGInterface::get_I_zz ()'
|
|
`FGInterface::get_I_xz ()'
|
|
|
|
`FGInterface::get_V_north ()'
|
|
`FGInterface::get_V_east ()'
|
|
`FGInterface::get_V_down ()'
|
|
|
|
`FGInterface::get_P_Body ()'
|
|
`FGInterface::get_Q_Body ()'
|
|
`FGInterface::get_R_Body ()'
|
|
|
|
`FGInterface::get_Gamma_vert_rad ()'
|
|
`FGInterface::get_Climb_Rate ()'
|
|
`FGInterface::get_Alpha ()'
|
|
`FGInterface::get_Beta ()'
|
|
|
|
`FGInterface::get_Runway_altitude ()'
|
|
|
|
`FGInterface::get_Lon_geocentric ()'
|
|
`FGInterface::get_Lat_geocentric ()'
|
|
`FGInterface::get_Sea_level_radius ()'
|
|
`FGInterface::get_Earth_position_angle ()'
|
|
|
|
`FGInterface::get_Latitude_dot()'
|
|
`FGInterface::get_Longitude_dot()'
|
|
`FGInterface::get_Radius_dot()'
|
|
|
|
`FGInterface::get_Dx_cg ()'
|
|
`FGInterface::get_Dy_cg ()'
|
|
`FGInterface::get_Dz_cg ()'
|
|
|
|
`FGInterface::get_T_local_to_body_11 ()' ... `FGInterface::get_T_local_to_body_33 ()'
|
|
|
|
`FGInterface::get_Radius_to_vehicle ()'
|
|
|
|
*/
|
|
|
|
|
|
#include <simgear/compiler.h>
|
|
|
|
#include <math.h>
|
|
|
|
#include <list>
|
|
#include <vector>
|
|
#include <string>
|
|
|
|
#include <simgear/constants.h>
|
|
#include <simgear/timing/timestamp.hxx>
|
|
|
|
#include <Main/fgfs.hxx>
|
|
|
|
SG_USING_STD(list);
|
|
SG_USING_STD(vector);
|
|
SG_USING_STD(string);
|
|
|
|
|
|
typedef double FG_VECTOR_3[3];
|
|
|
|
// This is based heavily on LaRCsim/ls_generic.h
|
|
class FGInterface : public FGSubsystem {
|
|
|
|
private:
|
|
|
|
// Has the init() method been called. This is used to delay
|
|
// initialization until scenery can be loaded and we know the true
|
|
// ground elevation.
|
|
bool inited;
|
|
|
|
// Have we bound to the property system
|
|
bool bound;
|
|
|
|
// periodic update management variable. This is a scheme to run
|
|
// the fdm with a fixed delta-t. We control how many iteration of
|
|
// the fdm to run with the fixed dt based on the elapsed time from
|
|
// the last update. This allows us to maintain sync with the real
|
|
// time clock, even though each frame could take a random amount
|
|
// of time. Since "dt" is unlikely to divide evenly into the
|
|
// elapse time, we keep track of the remainder and add it into the
|
|
// next elapsed time. This yields a small amount of temporal
|
|
// jitter ( < dt ) but in practice seems to work well.
|
|
|
|
double delta_t; // delta "t"
|
|
SGTimeStamp time_stamp; // time stamp of last run
|
|
long elapsed; // time elapsed since last run
|
|
long remainder; // remainder time from last run
|
|
int multi_loop; // number of iterations of "delta_t" to run
|
|
|
|
// Pilot location rel to ref pt
|
|
FG_VECTOR_3 d_pilot_rp_body_v;
|
|
|
|
// CG position w.r.t. ref. point
|
|
FG_VECTOR_3 d_cg_rp_body_v;
|
|
|
|
// Forces
|
|
FG_VECTOR_3 f_body_total_v;
|
|
FG_VECTOR_3 f_local_total_v;
|
|
FG_VECTOR_3 f_aero_v;
|
|
FG_VECTOR_3 f_engine_v;
|
|
FG_VECTOR_3 f_gear_v;
|
|
|
|
// Moments
|
|
FG_VECTOR_3 m_total_rp_v;
|
|
FG_VECTOR_3 m_total_cg_v;
|
|
FG_VECTOR_3 m_aero_v;
|
|
FG_VECTOR_3 m_engine_v;
|
|
FG_VECTOR_3 m_gear_v;
|
|
|
|
// Accelerations
|
|
FG_VECTOR_3 v_dot_local_v;
|
|
FG_VECTOR_3 v_dot_body_v;
|
|
FG_VECTOR_3 a_cg_body_v;
|
|
FG_VECTOR_3 a_pilot_body_v;
|
|
FG_VECTOR_3 n_cg_body_v;
|
|
FG_VECTOR_3 n_pilot_body_v;
|
|
FG_VECTOR_3 omega_dot_body_v;
|
|
|
|
// Velocities
|
|
FG_VECTOR_3 v_local_v;
|
|
FG_VECTOR_3 v_local_rel_ground_v; // V rel w.r.t. earth surface
|
|
FG_VECTOR_3 v_local_airmass_v; // velocity of airmass (steady winds)
|
|
FG_VECTOR_3 v_local_rel_airmass_v; // velocity of veh. relative to airmass
|
|
FG_VECTOR_3 v_local_gust_v; // linear turbulence components, L frame
|
|
FG_VECTOR_3 v_wind_body_v; // Wind-relative velocities in body axis
|
|
|
|
FG_VECTOR_3 omega_body_v; // Angular B rates
|
|
FG_VECTOR_3 omega_local_v; // Angular L rates
|
|
FG_VECTOR_3 omega_total_v; // Diff btw B & L
|
|
FG_VECTOR_3 euler_rates_v;
|
|
FG_VECTOR_3 geocentric_rates_v; // Geocentric linear velocities
|
|
|
|
// Positions
|
|
FG_VECTOR_3 geocentric_position_v;
|
|
FG_VECTOR_3 geodetic_position_v;
|
|
FG_VECTOR_3 euler_angles_v;
|
|
|
|
// Miscellaneous Quantities
|
|
FG_VECTOR_3 d_cg_rwy_local_v; // CG rel. to rwy in local coords
|
|
FG_VECTOR_3 d_cg_rwy_rwy_v; // CG relative to rwy, in rwy coordinates
|
|
FG_VECTOR_3 d_pilot_rwy_local_v; // pilot rel. to rwy in local coords
|
|
FG_VECTOR_3 d_pilot_rwy_rwy_v; // pilot rel. to rwy, in rwy coords.
|
|
|
|
// Inertias
|
|
double mass, i_xx, i_yy, i_zz, i_xz;
|
|
|
|
// Normal Load Factor
|
|
double nlf;
|
|
|
|
// Velocities
|
|
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;
|
|
|
|
// Miscellaneious Quantities
|
|
double t_local_to_body_m[3][3]; // Transformation matrix L to B
|
|
double gravity; // Local acceleration due to G
|
|
double centrifugal_relief; // load factor reduction due to speed
|
|
double alpha, beta, alpha_dot, beta_dot; // in radians
|
|
double cos_alpha, sin_alpha, cos_beta, sin_beta;
|
|
double cos_phi, sin_phi, cos_theta, sin_theta, cos_psi, sin_psi;
|
|
double gamma_vert_rad, gamma_horiz_rad; // Flight path angles
|
|
double sigma, density, v_sound, mach_number;
|
|
double static_pressure, total_pressure, impact_pressure;
|
|
double dynamic_pressure;
|
|
double static_temperature, total_temperature;
|
|
double sea_level_radius, earth_position_angle;
|
|
double runway_altitude, runway_latitude, runway_longitude;
|
|
double runway_heading;
|
|
double radius_to_rwy;
|
|
double climb_rate; // in feet per second
|
|
double sin_lat_geocentric, cos_lat_geocentric;
|
|
double sin_longitude, cos_longitude;
|
|
double sin_latitude, cos_latitude;
|
|
double altitude_agl;
|
|
|
|
double daux[16]; // auxilliary doubles
|
|
float faux[16]; // auxilliary floats
|
|
int iaux[16]; // auxilliary ints
|
|
|
|
// SGTimeStamp valid_stamp; // time this record is valid
|
|
// SGTimeStamp next_stamp; // time this record is valid
|
|
|
|
// protected:
|
|
public:
|
|
|
|
// deliberately not virtual so that
|
|
// FGInterface constructor will call
|
|
// the right version
|
|
void _setup();
|
|
|
|
void _busdump(void);
|
|
void _updateGeodeticPosition( double lat, double lon, double alt );
|
|
void _updateGeocentricPosition( double lat_geoc, double lon, double alt );
|
|
void _updateWeather( void );
|
|
|
|
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;
|
|
}
|
|
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;
|
|
}
|
|
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;
|
|
}
|
|
inline void _set_Accels_Body( double u, double v, double w ) {
|
|
v_dot_body_v[0] = u;
|
|
v_dot_body_v[1] = v;
|
|
v_dot_body_v[2] = w;
|
|
}
|
|
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;
|
|
}
|
|
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;
|
|
}
|
|
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;
|
|
}
|
|
void _set_Nlf(double n) { nlf=n; }
|
|
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;
|
|
}
|
|
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;
|
|
}
|
|
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;
|
|
}
|
|
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;
|
|
}
|
|
inline void _set_V_rel_wind(double vt) { v_rel_wind = vt; }
|
|
inline void _set_V_ground_speed( double v) { v_ground_speed = v; }
|
|
inline void _set_V_equiv_kts( double kts ) { v_equiv_kts = kts; }
|
|
inline void _set_V_calibrated_kts( double kts ) { v_calibrated_kts = kts; }
|
|
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;
|
|
}
|
|
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;
|
|
}
|
|
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;
|
|
}
|
|
#if 0
|
|
inline void _set_Radius_to_vehicle(double radius) {
|
|
geocentric_position_v[2] = radius;
|
|
}
|
|
#endif
|
|
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;
|
|
}
|
|
inline void _set_Latitude(double lat) { geodetic_position_v[0] = lat; }
|
|
inline void _set_Longitude(double lon) { geodetic_position_v[1] = lon; }
|
|
inline void _set_Altitude(double altitude) {
|
|
geodetic_position_v[2] = altitude;
|
|
}
|
|
inline void _set_Altitude_AGL(double agl) {
|
|
altitude_agl = agl;
|
|
}
|
|
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;
|
|
}
|
|
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;
|
|
}
|
|
inline void _set_T_Local_to_Body( int i, int j, double value) {
|
|
t_local_to_body_m[i-1][j-1] = value;
|
|
}
|
|
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];
|
|
}
|
|
}
|
|
}
|
|
inline void _set_Alpha( double a ) { alpha = a; }
|
|
inline void _set_Beta( double b ) { beta = b; }
|
|
inline void _set_Cos_phi( double cp ) { cos_phi = cp; }
|
|
inline void _set_Cos_theta( double ct ) { cos_theta = ct; }
|
|
inline void _set_Gamma_vert_rad( double gv ) { gamma_vert_rad = gv; }
|
|
inline void _set_Density( double d ) { density = d; }
|
|
inline void _set_Mach_number( double m ) { mach_number = m; }
|
|
inline void _set_Static_pressure( double sp ) { static_pressure = sp; }
|
|
inline void _set_Static_temperature( double t ) { static_temperature = t; }
|
|
inline void _set_Sea_level_radius( double r ) { sea_level_radius = r; }
|
|
inline void _set_Earth_position_angle(double a) {
|
|
earth_position_angle = a;
|
|
}
|
|
inline void _set_Runway_altitude( double alt ) { runway_altitude = alt; }
|
|
inline void _set_Climb_Rate(double rate) { climb_rate = rate; }
|
|
inline void _set_sin_lat_geocentric(double parm) {
|
|
sin_lat_geocentric = sin(parm);
|
|
}
|
|
inline void _set_cos_lat_geocentric(double parm) {
|
|
cos_lat_geocentric = cos(parm);
|
|
}
|
|
inline void _set_sin_cos_longitude(double parm) {
|
|
sin_longitude = sin(parm);
|
|
cos_longitude = cos(parm);
|
|
}
|
|
inline void _set_sin_cos_latitude(double parm) {
|
|
sin_latitude = sin(parm);
|
|
cos_latitude = cos(parm);
|
|
}
|
|
|
|
inline void _set_daux( int n, double value ) { daux[n] = value; }
|
|
inline void _set_faux( int n, float value ) { faux[n] = value; }
|
|
inline void _set_iaux( int n, int value ) { iaux[n] = value; }
|
|
|
|
public:
|
|
|
|
FGInterface();
|
|
FGInterface( double dt );
|
|
virtual ~FGInterface();
|
|
|
|
virtual void init ();
|
|
virtual void bind ();
|
|
virtual void unbind ();
|
|
virtual void update(int dt);
|
|
virtual bool ToggleDataLogging(bool state) { return false; }
|
|
virtual bool ToggleDataLogging(void) { return false; }
|
|
|
|
// Define the various supported flight models (many not yet implemented)
|
|
enum {
|
|
// Magic Carpet mode
|
|
FG_MAGICCARPET = 0,
|
|
|
|
// The NASA LaRCsim (Navion) flight model
|
|
FG_LARCSIM = 1,
|
|
|
|
// Jon S. Berndt's new FDM written from the ground up in C++
|
|
FG_JSBSIM = 2,
|
|
|
|
// Christian's hot air balloon simulation
|
|
FG_BALLOONSIM = 3,
|
|
|
|
// Aeronautical DEvelopment AGEncy, Bangalore India
|
|
FG_ADA = 4,
|
|
|
|
// The following aren't implemented but are here to spark
|
|
// thoughts and discussions, and maybe even action.
|
|
FG_ACM = 5,
|
|
FG_SUPER_SONIC = 6,
|
|
FG_HELICOPTER = 7,
|
|
FG_AUTOGYRO = 8,
|
|
FG_PARACHUTE = 9,
|
|
|
|
// Driven externally via a serial port, net, file, etc.
|
|
FG_EXTERNAL = 10
|
|
};
|
|
|
|
// initialization
|
|
inline bool get_inited() const { return inited; }
|
|
inline void set_inited( bool value ) { inited = value; }
|
|
|
|
inline bool get_bound() const { return bound; }
|
|
|
|
//perform initializion that is common to all FDM's
|
|
void common_init();
|
|
|
|
// time and update management values
|
|
inline double get_delta_t() const { return delta_t; }
|
|
inline void set_delta_t( double dt ) { delta_t = dt; }
|
|
inline SGTimeStamp get_time_stamp() const { return time_stamp; }
|
|
inline void set_time_stamp( SGTimeStamp s ) { time_stamp = s; }
|
|
inline void stamp() { time_stamp.stamp(); }
|
|
inline long get_elapsed() const { return elapsed; }
|
|
inline void set_elapsed( long e ) { elapsed = e; }
|
|
inline long get_remainder() const { return remainder; }
|
|
inline void set_remainder( long r ) { remainder = r; }
|
|
inline int get_multi_loop() const { return multi_loop; }
|
|
inline void set_multi_loop( int ml ) { multi_loop = ml; }
|
|
|
|
// Positions
|
|
virtual void set_Latitude(double lat); // geocentric
|
|
virtual void set_Longitude(double lon);
|
|
virtual void set_Altitude(double alt); // triggers re-calc of AGL altitude
|
|
virtual void set_AltitudeAGL(double altagl); // and vice-versa
|
|
virtual void set_Latitude_deg (double lat) {
|
|
set_Latitude(lat * SGD_DEGREES_TO_RADIANS);
|
|
}
|
|
virtual void set_Longitude_deg (double lon) {
|
|
set_Longitude(lon * SGD_DEGREES_TO_RADIANS);
|
|
}
|
|
|
|
// Speeds -- setting any of these will trigger a re-calc of the rest
|
|
virtual void set_V_calibrated_kts(double vc);
|
|
virtual void set_Mach_number(double mach);
|
|
virtual void set_Velocities_Local( double north, double east, double down );
|
|
inline void set_V_north (double north) {
|
|
set_Velocities_Local(north, v_local_v[1], v_local_v[2]);
|
|
}
|
|
inline void set_V_east (double east) {
|
|
set_Velocities_Local(v_local_v[0], east, v_local_v[2]);
|
|
}
|
|
inline void set_V_down (double down) {
|
|
set_Velocities_Local(v_local_v[0], v_local_v[1], down);
|
|
}
|
|
virtual void set_Velocities_Wind_Body( double u, double v, double w);
|
|
virtual void set_uBody (double uBody) {
|
|
set_Velocities_Wind_Body(uBody, v_wind_body_v[1], v_wind_body_v[2]);
|
|
}
|
|
virtual void set_vBody (double vBody) {
|
|
set_Velocities_Wind_Body(v_wind_body_v[0], vBody, v_wind_body_v[2]);
|
|
}
|
|
virtual void set_wBody (double wBody) {
|
|
set_Velocities_Wind_Body(v_wind_body_v[0], v_wind_body_v[1], wBody);
|
|
}
|
|
|
|
// Euler angles
|
|
virtual void set_Euler_Angles( double phi, double theta, double psi );
|
|
virtual void set_Phi (double phi) {
|
|
set_Euler_Angles(phi, get_Theta(), get_Psi());
|
|
}
|
|
virtual void set_Theta (double theta) {
|
|
set_Euler_Angles(get_Phi(), theta, get_Psi());
|
|
}
|
|
virtual void set_Psi (double psi) {
|
|
set_Euler_Angles(get_Phi(), get_Theta(), psi);
|
|
}
|
|
virtual void set_Phi_deg (double phi) { set_Phi(phi * SGD_DEGREES_TO_RADIANS); }
|
|
virtual void set_Theta_deg (double theta) {
|
|
set_Theta(theta * SGD_DEGREES_TO_RADIANS);
|
|
}
|
|
virtual void set_Psi_deg (double psi) { set_Psi(psi * SGD_DEGREES_TO_RADIANS); }
|
|
|
|
// Flight Path
|
|
virtual void set_Climb_Rate( double roc);
|
|
virtual void set_Gamma_vert_rad( double gamma);
|
|
|
|
// Earth
|
|
|
|
virtual void set_Static_pressure(double p);
|
|
virtual void set_Static_temperature(double T);
|
|
virtual void set_Density(double rho);
|
|
|
|
virtual void set_Velocities_Local_Airmass (double wnorth,
|
|
double weast,
|
|
double wdown );
|
|
|
|
// ========== Mass properties and geometry values ==========
|
|
|
|
// Inertias
|
|
inline double get_Mass() const { return mass; }
|
|
inline double get_I_xx() const { return i_xx; }
|
|
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; }
|
|
|
|
// Pilot location rel to ref pt
|
|
// inline double * get_D_pilot_rp_body_v() {
|
|
// return 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
|
|
// inline double * get_D_cg_rp_body_v() { return 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]; }
|
|
|
|
// ========== Forces ==========
|
|
|
|
// inline double * get_F_body_total_v() { return f_body_total_v; }
|
|
// 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;
|
|
} */
|
|
|
|
// 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;
|
|
} */
|
|
|
|
// 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;
|
|
} */
|
|
|
|
// 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;
|
|
} */
|
|
|
|
// 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 ==========
|
|
|
|
// 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;
|
|
} */
|
|
|
|
// 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;
|
|
} */
|
|
|
|
// 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;
|
|
} */
|
|
|
|
// 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;
|
|
} */
|
|
|
|
// 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_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 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 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 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 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 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;
|
|
// }
|
|
|
|
inline double get_Nlf(void) const { return nlf; }
|
|
|
|
// 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_local_v() { return v_local_v; }
|
|
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 double get_uBody () const { return v_wind_body_v[0]; }
|
|
inline double get_vBody () const { return v_wind_body_v[1]; }
|
|
inline double get_wBody () const { return v_wind_body_v[2]; }
|
|
|
|
// Please dont comment these out. fdm=ada uses these (see
|
|
// cockpit.cxx) --->
|
|
inline double * get_V_local_rel_ground_v() {
|
|
return v_local_rel_ground_v;
|
|
}
|
|
inline double get_V_north_rel_ground() const {
|
|
return v_local_rel_ground_v[0];
|
|
}
|
|
inline double get_V_east_rel_ground() const {
|
|
return v_local_rel_ground_v[1];
|
|
}
|
|
inline double get_V_down_rel_ground() const {
|
|
return v_local_rel_ground_v[2];
|
|
}
|
|
// <--- fdm=ada uses these (see cockpit.cxx)
|
|
|
|
// 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]; }
|
|
|
|
// airmass
|
|
// inline double * get_V_local_rel_airmass_v() {
|
|
// return v_local_rel_airmass_v;
|
|
// }
|
|
// inline double get_V_north_rel_airmass() const {
|
|
// return v_local_rel_airmass_v[0];
|
|
// }
|
|
// inline double get_V_east_rel_airmass() const {
|
|
// return v_local_rel_airmass_v[1];
|
|
// }
|
|
// 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;
|
|
} */
|
|
|
|
// 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;
|
|
} */
|
|
|
|
// 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 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 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 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 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 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;
|
|
} */
|
|
|
|
// 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;
|
|
} */
|
|
|
|
// 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 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]; }
|
|
|
|
// ========== Positions ==========
|
|
|
|
// inline double * get_Geocentric_position_v() {
|
|
// return geocentric_position_v;
|
|
// }
|
|
inline double get_Lat_geocentric() const {
|
|
return geocentric_position_v[0];
|
|
}
|
|
inline double get_Lon_geocentric() const {
|
|
return geocentric_position_v[1];
|
|
}
|
|
inline double get_Radius_to_vehicle() const {
|
|
return geocentric_position_v[2];
|
|
}
|
|
|
|
// inline double * get_Geodetic_position_v() { return geodetic_position_v; }
|
|
inline double get_Latitude() const { return geodetic_position_v[0]; }
|
|
inline double get_Longitude() const { return geodetic_position_v[1]; }
|
|
inline double get_Altitude() const { return geodetic_position_v[2]; }
|
|
inline double get_Altitude_AGL(void) const { return altitude_agl; }
|
|
|
|
inline double get_Latitude_deg () const {
|
|
return get_Latitude() * SGD_RADIANS_TO_DEGREES;
|
|
}
|
|
inline double get_Longitude_deg () const {
|
|
return get_Longitude() * SGD_RADIANS_TO_DEGREES;
|
|
}
|
|
|
|
// 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 double get_Phi_deg () const { return get_Phi() * SGD_RADIANS_TO_DEGREES; }
|
|
inline double get_Theta_deg () const { return get_Theta() * SGD_RADIANS_TO_DEGREES; }
|
|
inline double get_Psi_deg () const { return get_Psi() * SGD_RADIANS_TO_DEGREES; }
|
|
|
|
|
|
// ========== Miscellaneous quantities ==========
|
|
|
|
// inline double * get_T_local_to_body_m() { return t_local_to_body_m; }
|
|
inline double get_T_local_to_body_11() const {
|
|
return t_local_to_body_m[0][0];
|
|
}
|
|
inline double get_T_local_to_body_12() const {
|
|
return t_local_to_body_m[0][1];
|
|
}
|
|
inline double get_T_local_to_body_13() const {
|
|
return t_local_to_body_m[0][2];
|
|
}
|
|
inline double get_T_local_to_body_21() const {
|
|
return t_local_to_body_m[1][0];
|
|
}
|
|
inline double get_T_local_to_body_22() const {
|
|
return t_local_to_body_m[1][1];
|
|
}
|
|
inline double get_T_local_to_body_23() const {
|
|
return t_local_to_body_m[1][2];
|
|
}
|
|
inline double get_T_local_to_body_31() const {
|
|
return t_local_to_body_m[2][0];
|
|
}
|
|
inline double get_T_local_to_body_32() const {
|
|
return t_local_to_body_m[2][1];
|
|
}
|
|
inline double get_T_local_to_body_33() const {
|
|
return t_local_to_body_m[2][2];
|
|
}
|
|
|
|
// inline double get_Gravity() const { return gravity; }
|
|
// inline void set_Gravity(double g) { gravity = g; }
|
|
|
|
// inline double get_Centrifugal_relief() const {
|
|
// return centrifugal_relief;
|
|
// }
|
|
// inline void set_Centrifugal_relief(double cr) {
|
|
// centrifugal_relief = cr;
|
|
// }
|
|
|
|
inline double get_Alpha() const { return alpha; }
|
|
inline double get_Alpha_deg() const { return alpha * SGD_RADIANS_TO_DEGREES; }
|
|
inline double get_Beta() const { return beta; }
|
|
inline double get_Beta_deg() const { return beta * SGD_RADIANS_TO_DEGREES; }
|
|
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; }
|
|
|
|
// 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; }
|
|
|
|
inline double get_Cos_phi() const { return cos_phi; }
|
|
// 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 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; }
|
|
|
|
inline double get_Gamma_vert_rad() const { return gamma_vert_rad; }
|
|
// inline double get_Gamma_horiz_rad() const { return gamma_horiz_rad; }
|
|
// inline void set_Gamma_horiz_rad( double gh ) { gamma_horiz_rad = gh; }
|
|
|
|
// inline double get_Sigma() const { return sigma; }
|
|
// inline void set_Sigma( double s ) { sigma = s; }
|
|
inline double get_Density() const { return density; }
|
|
// 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 double get_Static_pressure() const { return static_pressure; }
|
|
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; }
|
|
|
|
inline double get_Static_temperature() const { return static_temperature; }
|
|
inline double get_Total_temperature() const { return total_temperature; }
|
|
// inline void set_Total_temperature( double t ) { total_temperature = t; }
|
|
|
|
inline double get_Sea_level_radius() const { return sea_level_radius; }
|
|
inline double get_Earth_position_angle() const {
|
|
return earth_position_angle;
|
|
}
|
|
|
|
inline double get_Runway_altitude() const { return runway_altitude; }
|
|
// 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; }
|
|
|
|
// inline double get_Radius_to_rwy() const { return radius_to_rwy; }
|
|
// inline void set_Radius_to_rwy( double r ) { radius_to_rwy = r; }
|
|
|
|
// 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;
|
|
} */
|
|
|
|
// 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;
|
|
} */
|
|
|
|
// inline double * get_D_pilot_rwy_local_v() { return d_pilot_rwy_local_v; }
|
|
// inline double get_D_pilot_north_of_rwy() const {
|
|
// return d_pilot_rwy_local_v[0];
|
|
// }
|
|
// inline double get_D_pilot_east_of_rwy() const {
|
|
// return d_pilot_rwy_local_v[1];
|
|
// }
|
|
// 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;
|
|
} */
|
|
|
|
// 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;
|
|
} */
|
|
|
|
inline double get_Climb_Rate() const { return climb_rate; }
|
|
|
|
// inline SGTimeStamp get_time_stamp() const { return valid_stamp; }
|
|
// inline void stamp_time() { valid_stamp = next_stamp; next_stamp.stamp(); }
|
|
|
|
// Extrapolate FDM based on time_offset (in usec)
|
|
void extrapolate( int time_offset );
|
|
|
|
// sin/cos lat_geocentric
|
|
inline double get_sin_lat_geocentric(void) const {
|
|
return sin_lat_geocentric;
|
|
}
|
|
inline double get_cos_lat_geocentric(void) const {
|
|
return cos_lat_geocentric;
|
|
}
|
|
|
|
inline double get_sin_longitude(void) const {
|
|
return sin_longitude;
|
|
}
|
|
inline double get_cos_longitude(void) const {
|
|
return cos_longitude;
|
|
}
|
|
|
|
inline double get_sin_latitude(void) const {
|
|
return sin_latitude;
|
|
}
|
|
inline double get_cos_latitude(void) const {
|
|
return cos_latitude;
|
|
}
|
|
|
|
// Auxilliary variables
|
|
inline double get_daux( int n ) const { return daux[n]; }
|
|
inline float get_faux( int n ) const { return faux[n]; }
|
|
inline int get_iaux( int n ) const { return iaux[n]; }
|
|
|
|
};
|
|
|
|
|
|
typedef list < FGInterface > fdm_state_list;
|
|
typedef fdm_state_list::iterator fdm_state_list_iterator;
|
|
typedef fdm_state_list::const_iterator const_fdm_state_list_iterator;
|
|
|
|
|
|
extern FGInterface * cur_fdm_state;
|
|
|
|
|
|
// General interface to the flight model routines
|
|
|
|
|
|
// Toggle data logging on/off
|
|
void fgToggleFDMdataLogging(void);
|
|
|
|
|
|
#endif // _FLIGHT_HXX
|