1 // flight.h -- define shared flight model parameters
3 // Written by Curtis Olson, started May 1997.
5 // Copyright (C) 1997 Curtis L. Olson - curt@infoplane.com
7 // This program is free software; you can redistribute it and/or
8 // modify it under the terms of the GNU General Public License as
9 // published by the Free Software Foundation; either version 2 of the
10 // License, or (at your option) any later version.
12 // This program is distributed in the hope that it will be useful, but
13 // WITHOUT ANY WARRANTY; without even the implied warranty of
14 // MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU
15 // General Public License for more details.
17 // You should have received a copy of the GNU General Public License
18 // along with this program; if not, write to the Free Software
19 // Foundation, Inc., 675 Mass Ave, Cambridge, MA 02139, USA.
22 // (Log is kept at end of this file)
29 #include <Flight/Slew/slew.hxx>
33 # error This library requires C++
37 // Define the various supported flight models (most not yet implemented)
39 enum fgFlightModelKind {
40 // Slew (in MS terminology)
43 // The only "real" model that is currently implemented
53 // Driven externally via a serial port, net, file, etc.
58 typedef double FG_VECTOR_3[3];
61 // This is based heavily on LaRCsim/ls_generic.h
66 /*================== Mass properties and geometry values ==================*/
69 double mass, i_xx, i_yy, i_zz, i_xz;
70 inline double get_Mass() const { return mass; }
71 inline double get_I_xx() const { return i_xx; }
72 inline double get_I_yy() const { return i_yy; }
73 inline double get_I_zz() const { return i_zz; }
74 inline double get_I_xz() const { return i_xz; }
76 // Pilot location rel to ref pt
77 FG_VECTOR_3 d_pilot_rp_body_v;
78 inline double * get_D_pilot_rp_body_v() {
79 return d_pilot_rp_body_v;
81 inline double get_Dx_pilot() const { return d_pilot_rp_body_v[0]; }
82 inline double get_Dy_pilot() const { return d_pilot_rp_body_v[1]; }
83 inline double get_Dz_pilot() const { return d_pilot_rp_body_v[2]; }
85 // CG position w.r.t. ref. point
86 FG_VECTOR_3 d_cg_rp_body_v;
87 inline double * get_D_cg_rp_body_v() { return d_cg_rp_body_v; }
88 inline double get_Dx_cg() const { return d_cg_rp_body_v[0]; }
89 inline double get_Dy_cg() const { return d_cg_rp_body_v[1]; }
90 inline double get_Dz_cg() const { return d_cg_rp_body_v[2]; }
92 /*================================ Forces =================================*/
94 FG_VECTOR_3 f_body_total_v;
95 inline double * get_F_body_total_v() { return f_body_total_v; }
96 inline double get_F_X() const { return f_body_total_v[0]; }
97 inline double get_F_Y() const { return f_body_total_v[1]; }
98 inline double get_F_Z() const { return f_body_total_v[2]; }
100 FG_VECTOR_3 f_local_total_v;
101 inline double * get_F_local_total_v() { return f_local_total_v; }
102 inline double get_F_north() const { return f_local_total_v[0]; }
103 inline double get_F_east() const { return f_local_total_v[1]; }
104 inline double get_F_down() const { return f_local_total_v[2]; }
106 FG_VECTOR_3 f_aero_v;
107 inline double * get_F_aero_v() { return f_aero_v; }
108 inline double get_F_X_aero() const { return f_aero_v[0]; }
109 inline double get_F_Y_aero() const { return f_aero_v[1]; }
110 inline double get_F_Z_aero() const { return f_aero_v[2]; }
112 FG_VECTOR_3 f_engine_v;
113 inline double * get_F_engine_v() { return f_engine_v; }
114 inline double get_F_X_engine() const { return f_engine_v[0]; }
115 inline double get_F_Y_engine() const { return f_engine_v[1]; }
116 inline double get_F_Z_engine() const { return f_engine_v[2]; }
118 FG_VECTOR_3 f_gear_v;
119 inline double * get_F_gear_v() { return f_gear_v; }
120 inline double get_F_X_gear() const { return f_gear_v[0]; }
121 inline double get_F_Y_gear() const { return f_gear_v[1]; }
122 inline double get_F_Z_gear() const { return f_gear_v[2]; }
124 /*================================ Moments ================================*/
126 FG_VECTOR_3 m_total_rp_v;
127 inline double * get_M_total_rp_v() { return m_total_rp_v; }
128 inline double get_M_l_rp() const { return m_total_rp_v[0]; }
129 inline double get_M_m_rp() const { return m_total_rp_v[1]; }
130 inline double get_M_n_rp() const { return m_total_rp_v[2]; }
132 FG_VECTOR_3 m_total_cg_v;
133 inline double * get_M_total_cg_v() { return m_total_cg_v; }
134 inline double get_M_l_cg() const { return m_total_cg_v[0]; }
135 inline double get_M_m_cg() const { return m_total_cg_v[1]; }
136 inline double get_M_n_cg() const { return m_total_cg_v[2]; }
138 FG_VECTOR_3 m_aero_v;
139 inline double * get_M_aero_v() { return m_aero_v; }
140 inline double get_M_l_aero() const { return m_aero_v[0]; }
141 inline double get_M_m_aero() const { return m_aero_v[1]; }
142 inline double get_M_n_aero() const { return m_aero_v[2]; }
144 FG_VECTOR_3 m_engine_v;
145 inline double * get_M_engine_v() { return m_engine_v; }
146 inline double get_M_l_engine() const { return m_engine_v[0]; }
147 inline double get_M_m_engine() const { return m_engine_v[1]; }
148 inline double get_M_n_engine() const { return m_engine_v[2]; }
150 FG_VECTOR_3 m_gear_v;
151 inline double * get_M_gear_v() { return m_gear_v; }
152 inline double get_M_l_gear() const { return m_gear_v[0]; }
153 inline double get_M_m_gear() const { return m_gear_v[1]; }
154 inline double get_M_n_gear() const { return m_gear_v[2]; }
156 /*============================== Accelerations ============================*/
158 FG_VECTOR_3 v_dot_local_v;
159 inline double * get_V_dot_local_v() { return v_dot_local_v; }
160 inline double get_V_dot_north() const { return v_dot_local_v[0]; }
161 inline double get_V_dot_east() const { return v_dot_local_v[1]; }
162 inline double get_V_dot_down() const { return v_dot_local_v[2]; }
164 FG_VECTOR_3 v_dot_body_v;
165 inline double * get_V_dot_body_v() { return v_dot_body_v; }
166 inline double get_U_dot_body() const { return v_dot_body_v[0]; }
167 inline double get_V_dot_body() const { return v_dot_body_v[1]; }
168 inline double get_W_dot_body() const { return v_dot_body_v[2]; }
170 FG_VECTOR_3 a_cg_body_v;
171 inline double * get_A_cg_body_v() { return a_cg_body_v; }
172 inline double get_A_X_cg() const { return a_cg_body_v[0]; }
173 inline double get_A_Y_cg() const { return a_cg_body_v[1]; }
174 inline double get_A_Z_cg() const { return a_cg_body_v[2]; }
176 FG_VECTOR_3 a_pilot_body_v;
177 inline double * get_A_pilot_body_v() { return a_pilot_body_v; }
178 inline double get_A_X_pilot() const { return a_pilot_body_v[0]; }
179 inline double get_A_Y_pilot() const { return a_pilot_body_v[1]; }
180 inline double get_A_Z_pilot() const { return a_pilot_body_v[2]; }
182 FG_VECTOR_3 n_cg_body_v;
183 inline double * get_N_cg_body_v() { return n_cg_body_v; }
184 inline double get_N_X_cg() const { return n_cg_body_v[0]; }
185 inline double get_N_Y_cg() const { return n_cg_body_v[1]; }
186 inline double get_N_Z_cg() const { return n_cg_body_v[2]; }
188 FG_VECTOR_3 n_pilot_body_v;
189 inline double * get_N_pilot_body_v() { return n_pilot_body_v; }
190 inline double get_N_X_pilot() const { return n_pilot_body_v[0]; }
191 inline double get_N_Y_pilot() const { return n_pilot_body_v[1]; }
192 inline double get_N_Z_pilot() const { return n_pilot_body_v[2]; }
194 FG_VECTOR_3 omega_dot_body_v;
195 inline double * get_Omega_dot_body_v() { return omega_dot_body_v; }
196 inline double get_P_dot_body() const { return omega_dot_body_v[0]; }
197 inline double get_Q_dot_body() const { return omega_dot_body_v[1]; }
198 inline double get_R_dot_body() const { return omega_dot_body_v[2]; }
201 /*============================== Velocities ===============================*/
203 FG_VECTOR_3 v_local_v;
204 inline double * get_V_local_v() { return v_local_v; }
205 inline double get_V_north() const { return v_local_v[0]; }
206 inline double get_V_east() const { return v_local_v[1]; }
207 inline double get_V_down() const { return v_local_v[2]; }
209 FG_VECTOR_3 v_local_rel_ground_v; /* V rel w.r.t. earth surface */
210 inline double * get_V_local_rel_ground_v() { return v_local_rel_ground_v; }
211 inline double get_V_north_rel_ground() const {
212 return v_local_rel_ground_v[0];
214 inline double get_V_east_rel_ground() const {
215 return v_local_rel_ground_v[1];
217 inline double get_V_down_rel_ground() const {
218 return v_local_rel_ground_v[2];
221 FG_VECTOR_3 v_local_airmass_v; /* velocity of airmass (steady winds) */
222 inline double * get_V_local_airmass_v() { return v_local_airmass_v; }
223 inline double get_V_north_airmass() const { return v_local_airmass_v[0]; }
224 inline double get_V_east_airmass() const { return v_local_airmass_v[1]; }
225 inline double get_V_down_airmass() const { return v_local_airmass_v[2]; }
227 FG_VECTOR_3 v_local_rel_airmass_v; /* velocity of veh. relative to */
229 inline double * get_V_local_rel_airmass_v() {
230 return v_local_rel_airmass_v;
232 inline double get_V_north_rel_airmass() const {
233 return v_local_rel_airmass_v[0];
235 inline double get_V_east_rel_airmass() const {
236 return v_local_rel_airmass_v[1];
238 inline double get_V_down_rel_airmass() const {
239 return v_local_rel_airmass_v[2];
242 FG_VECTOR_3 v_local_gust_v; /* linear turbulence components, L frame */
243 inline double * get_V_local_gust_v() { return v_local_gust_v; }
244 inline double get_U_gust() const { return v_local_gust_v[0]; }
245 inline double get_V_gust() const { return v_local_gust_v[1]; }
246 inline double get_W_gust() const { return v_local_gust_v[2]; }
248 FG_VECTOR_3 v_wind_body_v; /* Wind-relative velocities in body axis */
249 inline double * get_V_wind_body_v() { return v_wind_body_v; }
250 inline double get_U_body() const { return v_wind_body_v[0]; }
251 inline double get_V_body() const { return v_wind_body_v[1]; }
252 inline double get_W_body() const { return v_wind_body_v[2]; }
254 double v_rel_wind, v_true_kts, v_rel_ground, v_inertial;
255 double v_ground_speed, v_equiv, v_equiv_kts;
256 double v_calibrated, v_calibrated_kts;
257 inline double get_V_rel_wind() const { return v_rel_wind; }
258 inline double get_V_true_kts() const { return v_true_kts; }
259 inline double get_V_rel_ground() const { return v_rel_ground; }
260 inline double get_V_inertial() const { return v_inertial; }
261 inline double get_V_ground_speed() const { return v_ground_speed; }
262 inline double get_V_equiv() const { return v_equiv; }
263 inline double get_V_equiv_kts() const { return v_equiv_kts; }
264 inline double get_V_calibrated() const { return v_calibrated; }
265 inline double get_V_calibrated_kts() const { return v_calibrated_kts; }
267 FG_VECTOR_3 omega_body_v; /* Angular B rates */
268 inline double * get_Omega_body_v() { return omega_body_v; }
269 inline double get_P_body() const { return omega_body_v[0]; }
270 inline double get_Q_body() const { return omega_body_v[1]; }
271 inline double get_R_body() const { return omega_body_v[2]; }
273 FG_VECTOR_3 omega_local_v; /* Angular L rates */
274 inline double * get_Omega_local_v() { return omega_local_v; }
275 inline double get_P_local() const { return omega_local_v[0]; }
276 inline double get_Q_local() const { return omega_local_v[1]; }
277 inline double get_R_local() const { return omega_local_v[2]; }
279 FG_VECTOR_3 omega_total_v; /* Diff btw B & L */
280 inline double * get_Omega_total_v() { return omega_total_v; }
281 inline double get_P_total() const { return omega_total_v[0]; }
282 inline double get_Q_total() const { return omega_total_v[1]; }
283 inline double get_R_total() const { return omega_total_v[2]; }
285 FG_VECTOR_3 euler_rates_v;
286 inline double * get_Euler_rates_v() { return euler_rates_v; }
287 inline double get_Phi_dot() const { return euler_rates_v[0]; }
288 inline double get_Theta_dot() const { return euler_rates_v[1]; }
289 inline double get_Psi_dot() const { return euler_rates_v[2]; }
291 FG_VECTOR_3 geocentric_rates_v; /* Geocentric linear velocities */
292 inline double * get_Geocentric_rates_v() { return geocentric_rates_v; }
293 inline double get_Latitude_dot() const { return geocentric_rates_v[0]; }
294 inline double get_Longitude_dot() const { return geocentric_rates_v[1]; }
295 inline double get_Radius_dot() const { return geocentric_rates_v[2]; }
297 /*=============================== Positions ===============================*/
299 FG_VECTOR_3 geocentric_position_v;
300 inline double * get_Geocentric_position_v() {
301 return geocentric_position_v;
303 inline double get_Lat_geocentric() const {
304 return geocentric_position_v[0];
306 inline double get_Lon_geocentric() const {
307 return geocentric_position_v[1];
309 inline double get_Radius_to_vehicle() const {
310 return geocentric_position_v[2];
312 inline void set_Radius_to_vehicle(double radius) {
313 geocentric_position_v[2] = radius;
316 FG_VECTOR_3 geodetic_position_v;
317 inline double * get_Geodetic_position_v() { return geodetic_position_v; }
318 inline double get_Latitude() const { return geodetic_position_v[0]; }
319 inline void set_Latitude(double lat) { geodetic_position_v[0] = lat; }
320 inline double get_Longitude() const { return geodetic_position_v[1]; }
321 inline void set_Longitude(double lon) { geodetic_position_v[0] = lon; }
322 inline double get_Altitude() const { return geodetic_position_v[2]; }
323 inline void set_Altitude(double altitude) {
324 geodetic_position_v[2] = altitude;
327 FG_VECTOR_3 euler_angles_v;
328 inline double * get_Euler_angles_v() { return euler_angles_v; }
329 inline double get_Phi() const { return euler_angles_v[0]; }
330 inline double get_Theta() const { return euler_angles_v[1]; }
331 inline double get_Psi() const { return euler_angles_v[2]; }
333 /*======================= Miscellaneous quantities ========================*/
335 double t_local_to_body_m[3][3]; /* Transformation matrix L to B */
336 // inline double * get_T_local_to_body_m() { return t_local_to_body_m; }
337 inline double get_T_local_to_body_11() const {
338 return t_local_to_body_m[0][0];
340 inline double get_T_local_to_body_12() const {
341 return t_local_to_body_m[0][1];
343 inline double get_T_local_to_body_13() const {
344 return t_local_to_body_m[0][2];
346 inline double get_T_local_to_body_21() const {
347 return t_local_to_body_m[1][0];
349 inline double get_T_local_to_body_22() const {
350 return t_local_to_body_m[1][1];
352 inline double get_T_local_to_body_23() const {
353 return t_local_to_body_m[1][2];
355 inline double get_T_local_to_body_31() const {
356 return t_local_to_body_m[2][0];
358 inline double get_T_local_to_body_32() const {
359 return t_local_to_body_m[2][1];
361 inline double get_T_local_to_body_33() const {
362 return t_local_to_body_m[2][2];
365 double gravity; /* Local acceleration due to G */
366 inline double get_Gravity() const { return gravity; }
368 double centrifugal_relief; /* load factor reduction due to speed */
369 inline double get_Centrifugal_relief() const { return centrifugal_relief; }
371 double alpha, beta, alpha_dot, beta_dot; /* in radians */
372 inline double get_Alpha() const { return alpha; }
373 inline double get_Beta() const { return beta; }
374 inline double get_Alpha_dot() const { return alpha_dot; }
375 inline double get_Beta_dot() const { return beta_dot; }
377 double cos_alpha, sin_alpha, cos_beta, sin_beta;
378 inline double get_Cos_alpha() const { return cos_alpha; }
379 inline double get_Sin_alpha() const { return sin_alpha; }
380 inline double get_Cos_beta() const { return cos_beta; }
381 inline double get_Sin_beta() const { return sin_beta; }
383 double cos_phi, sin_phi, cos_theta, sin_theta, cos_psi, sin_psi;
384 inline double get_Cos_phi() const { return cos_phi; }
385 inline double get_Sin_phi() const { return sin_phi; }
386 inline double get_Cos_theta() const { return cos_theta; }
387 inline double get_Sin_theta() const { return sin_theta; }
388 inline double get_Cos_psi() const { return cos_psi; }
389 inline double get_Sin_psi() const { return sin_psi; }
391 double gamma_vert_rad, gamma_horiz_rad; /* Flight path angles */
392 inline double get_Gamma_vert_rad() const { return gamma_vert_rad; }
393 inline double get_Gamma_horiz_rad() const { return gamma_horiz_rad; }
395 double sigma, density, v_sound, mach_number;
396 inline double get_Sigma() const { return sigma; }
397 inline double get_Density() const { return density; }
398 inline double get_V_sound() const { return v_sound; }
399 inline double get_Mach_number() const { return mach_number; }
401 double static_pressure, total_pressure, impact_pressure;
402 double dynamic_pressure;
403 inline double get_Static_pressure() const { return static_pressure; }
404 inline double get_Total_pressure() const { return total_pressure; }
405 inline double get_Impact_pressure() const { return impact_pressure; }
406 inline double get_Dynamic_pressure() const { return dynamic_pressure; }
408 double static_temperature, total_temperature;
409 inline double get_Static_temperature() const { return static_temperature; }
410 inline double get_Total_temperature() const { return total_temperature; }
412 double sea_level_radius, earth_position_angle;
413 inline double get_Sea_level_radius() const { return sea_level_radius; }
414 inline double get_Earth_position_angle() const {
415 return earth_position_angle;
417 inline void set_Earth_position_angle(double angle) {
418 earth_position_angle = angle;
421 double runway_altitude, runway_latitude, runway_longitude;
422 double runway_heading;
423 inline double get_Runway_altitude() const { return runway_altitude; }
424 inline void set_Runway_altitude( double alt ) { runway_altitude = alt; }
425 inline double get_Runway_latitude() const { return runway_latitude; }
426 inline double get_Runway_longitude() const { return runway_longitude; }
427 inline double get_Runway_heading() const { return runway_heading; }
429 double radius_to_rwy;
430 inline double get_Radius_to_rwy() const { return radius_to_rwy; }
432 FG_VECTOR_3 d_cg_rwy_local_v; /* CG rel. to rwy in local coords */
433 inline double * get_D_cg_rwy_local_v() { return d_cg_rwy_local_v; }
434 inline double get_D_cg_north_of_rwy() const { return d_cg_rwy_local_v[0]; }
435 inline double get_D_cg_east_of_rwy() const { return d_cg_rwy_local_v[1]; }
436 inline double get_D_cg_above_rwy() const { return d_cg_rwy_local_v[2]; }
438 FG_VECTOR_3 d_cg_rwy_rwy_v; /* CG relative to rwy, in rwy coordinates */
439 inline double * get_D_cg_rwy_rwy_v() { return d_cg_rwy_rwy_v; }
440 inline double get_X_cg_rwy() const { return d_cg_rwy_rwy_v[0]; }
441 inline double get_Y_cg_rwy() const { return d_cg_rwy_rwy_v[1]; }
442 inline double get_H_cg_rwy() const { return d_cg_rwy_rwy_v[2]; }
444 FG_VECTOR_3 d_pilot_rwy_local_v; /* pilot rel. to rwy in local coords */
445 inline double * get_D_pilot_rwy_local_v() { return d_pilot_rwy_local_v; }
446 inline double get_D_pilot_north_of_rwy() const {
447 return d_pilot_rwy_local_v[0];
449 inline double get_D_pilot_east_of_rwy() const {
450 return d_pilot_rwy_local_v[1];
452 inline double get_D_pilot_above_rwy() const {
453 return d_pilot_rwy_local_v[2];
456 FG_VECTOR_3 d_pilot_rwy_rwy_v; /* pilot rel. to rwy, in rwy coords. */
457 inline double * get_D_pilot_rwy_rwy_v() { return d_pilot_rwy_rwy_v; }
458 inline double get_X_pilot_rwy() const { return d_pilot_rwy_rwy_v[0]; }
459 inline double get_Y_pilot_rwy() const { return d_pilot_rwy_rwy_v[1]; }
460 inline double get_H_pilot_rwy() const { return d_pilot_rwy_rwy_v[2]; }
462 double climb_rate; /* in feet per second */
463 inline double get_Climb_Rate() const { return climb_rate; }
464 inline void set_Climb_Rate(double rate) { climb_rate = rate; }
466 // Additional convenience functions
469 inline void set_Inertias( double m, double xx, double yy,
470 double zz, double xz)
480 inline void set_Local_Velocities( double v_north,
484 v_local_v[0] = v_north;
485 v_local_v[1] = v_east;
486 v_local_v[2] = v_down;
490 inline void set_Euler_Orientation( double phi,
494 euler_angles_v[0] = phi;
495 euler_angles_v[1] = theta;
496 euler_angles_v[2] = psi;
500 inline void set_Body_Rates( double p_body, double q_body, double r_body )
502 omega_body_v[0] = p_body;
503 omega_body_v[1] = q_body;
504 omega_body_v[2] = r_body;
507 // Center of Gravity position w.r.t. ref. point
508 inline void set_CG_Position( double dx, double dy, double dz )
510 d_cg_rp_body_v[0] = dx;
511 d_cg_rp_body_v[1] = dy;
512 d_cg_rp_body_v[2] = dz;
517 extern fgFLIGHT cur_flight_params;
520 /* General interface to the flight model routines */
522 /* Initialize the flight model parameters */
523 int fgFlightModelInit(int model, fgFLIGHT& f, double dt);
525 /* Run multiloop iterations of the flight model */
526 int fgFlightModelUpdate(int model, fgFLIGHT& f, int multiloop);
528 /* Set the altitude (force) */
529 void fgFlightModelSetAltitude(int model, fgFLIGHT& f, double alt_meters);
532 #endif /* _FLIGHT_H */
536 // Revision 1.3 1998/12/03 01:16:41 curt
537 // Converted fgFLIGHT to a class.
539 // Revision 1.2 1998/10/16 23:27:41 curt
542 // Revision 1.1 1998/10/16 20:16:44 curt
543 // Renamed flight.[ch] to flight.[ch]xx
545 // Revision 1.20 1998/09/29 14:57:39 curt
546 // c++-ified comments.
548 // Revision 1.19 1998/09/29 02:02:41 curt
549 // Added a rate of climb calculation.
551 // Revision 1.18 1998/07/30 23:44:36 curt
552 // Beginning to add support for multiple flight models.
554 // Revision 1.17 1998/07/12 03:08:28 curt
555 // Added fgFlightModelSetAltitude() to force the altitude to something
556 // other than the current altitude. LaRCsim doesn't let you do this by just
557 // changing FG_Altitude.
559 // Revision 1.16 1998/04/22 13:26:20 curt
560 // C++ - ifing the code a bit.
562 // Revision 1.15 1998/04/21 16:59:33 curt
563 // Integrated autopilot.
564 // Prepairing for C++ integration.
566 // Revision 1.14 1998/02/07 15:29:37 curt
567 // Incorporated HUD changes and struct/typedef changes from Charlie Hotchkiss
568 // <chotchkiss@namg.us.anritsu.com>
570 // Revision 1.13 1998/01/24 00:04:59 curt
573 // Revision 1.12 1998/01/22 02:59:32 curt
574 // Changed #ifdef FILE_H to #ifdef _FILE_H
576 // Revision 1.11 1998/01/19 19:27:03 curt
577 // Merged in make system changes from Bob Kuehne <rpk@sgi.com>
578 // This should simplify things tremendously.
580 // Revision 1.10 1997/12/10 22:37:43 curt
581 // Prepended "fg" on the name of all global structures that didn't have it yet.
582 // i.e. "struct WEATHER {}" became "struct fgWEATHER {}"
584 // Revision 1.9 1997/09/04 02:17:33 curt
587 // Revision 1.8 1997/08/27 03:30:06 curt
588 // Changed naming scheme of basic shared structures.
590 // Revision 1.7 1997/07/23 21:52:19 curt
591 // Put comments around the text after an #endif for increased portability.
593 // Revision 1.6 1997/06/21 17:52:22 curt
594 // Continue directory shuffling ... everything should be compilable/runnable
597 // Revision 1.5 1997/06/21 17:12:49 curt
598 // Capitalized subdirectory names.
600 // Revision 1.4 1997/05/29 22:39:57 curt
601 // Working on incorporating the LaRCsim flight model.
603 // Revision 1.3 1997/05/29 02:32:25 curt
604 // Starting to build generic flight model interface.
606 // Revision 1.2 1997/05/23 15:40:37 curt
607 // Added GNU copyright headers.
609 // Revision 1.1 1997/05/16 16:04:45 curt