flightgear/FDM/flight.hxx

// flight.h -- 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.
//
// $Id$
// (Log is kept at end of this file)


#ifndef _FLIGHT_H
#define _FLIGHT_H


#include <Flight/Slew/slew.hxx>


#ifndef __cplusplus                                                          
# error This library requires C++
#endif                                   


// Define the various supported flight models (most not yet implemented)

enum fgFlightModelKind {
    // Slew (in MS terminology)
    FG_SLEW = 0,

    // The only "real" model that is currently implemented
    FG_LARCSIM = 1,

    FG_ACM = 2,
    FG_SUPER_SONIC = 3,
    FG_HELICOPTER = 4,
    FG_AUTOGYRO = 5,
    FG_BALLOON = 6,
    FG_PARACHUTE = 7,

    // Driven externally via a serial port, net, file, etc.
    FG_EXTERN = 8
};


typedef double FG_VECTOR_3[3];


// This is based heavily on LaRCsim/ls_generic.h
class fgFLIGHT {

public:

/*================== Mass properties and geometry values ==================*/

    // Inertias
    double mass, i_xx, i_yy, i_zz, i_xz;
    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
    FG_VECTOR_3 d_pilot_rp_body_v;
    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]; }

    // CG position w.r.t. ref. point
    FG_VECTOR_3 d_cg_rp_body_v;
    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 =================================*/

    FG_VECTOR_3 f_body_total_v;
    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]; }

    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]; }

    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]; }
    
    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]; }

    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]; }

    /*================================ Moments ================================*/

    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]; }

    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]; }

    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]; }

    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]; }

    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]; }

    /*============================== Accelerations ============================*/

    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]; }

    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]; }

    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]; }

    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]; }

    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]; }

    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]; }

    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]; }


    /*============================== Velocities ===============================*/

    FG_VECTOR_3    v_local_v;
    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]; }

    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_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];
    }

    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]; }

    FG_VECTOR_3    v_local_rel_airmass_v;  /* velocity of veh. relative to */
    /* 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];
    }

    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]; }

    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]; }

    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 double get_V_true_kts() const { return v_true_kts; }
    inline double get_V_rel_ground() const { return v_rel_ground; }
    inline double get_V_inertial() const { return v_inertial; }
    inline double get_V_ground_speed() const { return v_ground_speed; }
    inline double get_V_equiv() const { return v_equiv; }
    inline double get_V_equiv_kts() const { return v_equiv_kts; }
    inline double get_V_calibrated() const { return v_calibrated; }
    inline double get_V_calibrated_kts() const { return v_calibrated_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]; }

    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]; }

    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]; }

    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]; }

    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]; }

    /*=============================== Positions ===============================*/

    FG_VECTOR_3    geocentric_position_v;
    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 void set_Radius_to_vehicle(double radius) {
	geocentric_position_v[2] = radius;
    }

    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 double get_Altitude() const { return geodetic_position_v[2]; }
    inline void set_Altitude(double altitude) {
	geodetic_position_v[2] = altitude;
    }

    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]; }

    /*======================= Miscellaneous quantities ========================*/

    double    t_local_to_body_m[3][3];    /* Transformation matrix L to B */
    // 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];
    }

    double    gravity;            /* Local acceleration due to G  */
    inline double get_Gravity() const { return gravity; }

    double    centrifugal_relief; /* load factor reduction due to speed */
    inline double get_Centrifugal_relief() const { return centrifugal_relief; }

    double    alpha, beta, alpha_dot, beta_dot;   /* in radians   */
    inline double get_Alpha() const { return alpha; }
    inline double get_Beta() const { return beta; }
    inline double get_Alpha_dot() const { return alpha_dot; }
    inline double get_Beta_dot() const { return beta_dot; }

    double    cos_alpha, sin_alpha, cos_beta, sin_beta;
    inline double get_Cos_alpha() const { return cos_alpha; }
    inline double get_Sin_alpha() const { return sin_alpha; }
    inline double get_Cos_beta() const { return cos_beta; }
    inline double get_Sin_beta() const { return sin_beta; }

    double    cos_phi, sin_phi, cos_theta, sin_theta, cos_psi, sin_psi;
    inline double get_Cos_phi() const { return cos_phi; }
    inline double get_Sin_phi() const { return sin_phi; }
    inline double get_Cos_theta() const { return cos_theta; }
    inline double get_Sin_theta() const { return sin_theta; }
    inline double get_Cos_psi() const { return cos_psi; }
    inline double get_Sin_psi() const { return sin_psi; }

    double    gamma_vert_rad, gamma_horiz_rad;    /* Flight path angles   */
    inline double get_Gamma_vert_rad() const { return gamma_vert_rad; }
    inline double get_Gamma_horiz_rad() const { return gamma_horiz_rad; }

    double    sigma, density, v_sound, mach_number;
    inline double get_Sigma() const { return sigma; }
    inline double get_Density() const { return density; }
    inline double get_V_sound() const { return v_sound; }
    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 double get_Total_pressure() const { return total_pressure; }
    inline double get_Impact_pressure() const { return impact_pressure; }
    inline double get_Dynamic_pressure() const { return dynamic_pressure; }

    double    static_temperature, total_temperature;
    inline double get_Static_temperature() const { return static_temperature; }
    inline double get_Total_temperature() const { return total_temperature; }

    double    sea_level_radius, earth_position_angle;
    inline double get_Sea_level_radius() const { return sea_level_radius; }
    inline double get_Earth_position_angle() const {
	return earth_position_angle;
    }
    inline void set_Earth_position_angle(double angle) {
	earth_position_angle = angle;
    }

    double    runway_altitude, runway_latitude, runway_longitude;
    double    runway_heading;
    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 double get_Runway_longitude() const { return runway_longitude; }
    inline double get_Runway_heading() const { return runway_heading; }

    double    radius_to_rwy;
    inline double get_Radius_to_rwy() const { return radius_to_rwy; }

    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]; }

    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]; }

    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_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];
    }

    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]; }

    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;
    }
};


extern fgFLIGHT cur_flight_params;


/* General interface to the flight model routines */

/* Initialize the flight model parameters */
int fgFlightModelInit(int model, fgFLIGHT& f, double dt);

/* Run multiloop iterations of the flight model */
int fgFlightModelUpdate(int model, fgFLIGHT& f, int multiloop);

/* Set the altitude (force) */
void fgFlightModelSetAltitude(int model, fgFLIGHT& f, double alt_meters);


#endif /* _FLIGHT_H */


// $Log$
// Revision 1.3  1998/12/03 01:16:41  curt
// Converted fgFLIGHT to a class.
//
// Revision 1.2  1998/10/16 23:27:41  curt
// C++-ifying.
//
// Revision 1.1  1998/10/16 20:16:44  curt
// Renamed flight.[ch] to flight.[ch]xx
//
// Revision 1.20  1998/09/29 14:57:39  curt
// c++-ified comments.
//
// Revision 1.19  1998/09/29 02:02:41  curt
// Added a rate of climb calculation.
//
// Revision 1.18  1998/07/30 23:44:36  curt
// Beginning to add support for multiple flight models.
//
// Revision 1.17  1998/07/12 03:08:28  curt
// Added fgFlightModelSetAltitude() to force the altitude to something
// other than the current altitude.  LaRCsim doesn't let you do this by just
// changing FG_Altitude.
//
// Revision 1.16  1998/04/22 13:26:20  curt
// C++ - ifing the code a bit.
//
// Revision 1.15  1998/04/21 16:59:33  curt
// Integrated autopilot.
// Prepairing for C++ integration.
//
// Revision 1.14  1998/02/07 15:29:37  curt
// Incorporated HUD changes and struct/typedef changes from Charlie Hotchkiss
// <chotchkiss@namg.us.anritsu.com>
//
// Revision 1.13  1998/01/24 00:04:59  curt
// misc. tweaks.
//
// Revision 1.12  1998/01/22 02:59:32  curt
// Changed #ifdef FILE_H to #ifdef _FILE_H
//
// Revision 1.11  1998/01/19 19:27:03  curt
// Merged in make system changes from Bob Kuehne <rpk@sgi.com>
// This should simplify things tremendously.
//
// Revision 1.10  1997/12/10 22:37:43  curt
// Prepended "fg" on the name of all global structures that didn't have it yet.
// i.e. "struct WEATHER {}" became "struct fgWEATHER {}"
//
// Revision 1.9  1997/09/04 02:17:33  curt
// Shufflin' stuff.
//
// Revision 1.8  1997/08/27 03:30:06  curt
// Changed naming scheme of basic shared structures.
//
// Revision 1.7  1997/07/23 21:52:19  curt
// Put comments around the text after an #endif for increased portability.
//
// Revision 1.6  1997/06/21 17:52:22  curt
// Continue directory shuffling ... everything should be compilable/runnable
// again.
//
// Revision 1.5  1997/06/21 17:12:49  curt
// Capitalized subdirectory names.
//
// Revision 1.4  1997/05/29 22:39:57  curt
// Working on incorporating the LaRCsim flight model.
//
// Revision 1.3  1997/05/29 02:32:25  curt
// Starting to build generic flight model interface.
//
// Revision 1.2  1997/05/23 15:40:37  curt
// Added GNU copyright headers.
//
// Revision 1.1  1997/05/16 16:04:45  curt
// Initial revision.
//