1 ************************************************
3 * FGFS Reconfigurable Aircraft Flight Model *
4 * Input File Documentation *
5 * Version 0.81, September 14, 2001 *
8 * Jeff Scott (jscott@mail.com) *
9 * Bipin Sehgal (bsehgal@uiuc.edu) *
10 * Robert Deters (rdeters@uiuc.edu) *
11 * Michael Selig (m-selig@uiuc.edu) *
12 * Dept of Aero and Astro Engineering *
13 * University of Illinois at Urbana-Champaign *
15 * http://amber.aae.uiuc.edu/~m-selig *
17 ************************************************
20 **********************************************************************
21 NOTE: Most of the commands discussed in this documentation are
22 currently implemented in the UIUC aerodynamics model. Those
23 denoted by '|' are proposed and will likely be added in the
24 future but are not currently implemented. Some commands are
25 in use but not producing the desired results. These are
26 clearly noted, so please do not attempt to use them at this
28 **********************************************************************
30 **********************************************************************
31 This documentation includes:
32 - Required and optional input lines.
33 - Input line formats and conventions.
35 Viewing this file in emacs makefile-mode with color makes this file
37 **********************************************************************
39 **********************************************************************
40 I. Conventions and Notations and Reading this Document:
43 | Input line not yet implemented
45 | Sometimes indicates a feature not yet used,
46 but proposed convention is indicated nevertheless.
47 <...> Value or file name to be placed here
48 || Input line disabled
50 ... Repeat similar data
51 -> Continue onto next line
52 **********************************************************************
54 **********************************************************************
55 II. General Input Line Format:
57 Examples input lines include
59 Cm Cmo 0.194 # [] Bray pg 33
60 Cm Cm_a -2.12 # [/rad] Bray pg 33
61 CL CLfa CLfa.dat 0 1 # [] Bray pg 50, Table 4.7
63 These follow the more general input line form
65 keyword variableName <value -or- file> | ->
66 <value -or- file> # [units] <data source>
68 Each term of the input line will be discussed in turn.
73 There currently exist the following variable keyword types:
75 init Initial values for equation of motion
76 geometry Aircraft-specific geometric quantities
77 controlSurface Control surface deflections and properties
78 |controlsMixer Control surface mixer options
79 mass Aircraft-specific mass properties
80 engine Propulsion data
81 CD Aerodynamic x-force quantities (longitudinal)
82 CL Aerodynamic z-force quantities (longitudinal)
83 Cm Aerodynamic m-moment quantities (longitudinal)
84 CY Aerodynamic y-force quantities (lateral)
85 Cl Aerodynamic l-moment quantities (lateral)
86 Cn Aerodynamic n-moment quantities (lateral)
87 gear Landing gear model quantities
88 ice Icing model parameters
89 record Record desired quantites to file
90 misc Miscellaneous inputs
91 fog Fog field quantities
93 As each line of the input file is read, the code recognizes the
94 keyword, enters the appropriate switch statement in the code, and
95 proceeds to read the next term in the input line.
100 The variable name indicates the form of the variable itself. This
101 form may be a constant, a stability derivative (a specific form of a
102 constant), or a variable-dimensional lookup table. More variable
103 types can be easily prescribed by defining a new convention. The
104 variable name may also indicate that the quantity is to be calculated
105 from a hard-coded equation or set of equations provided at an
106 appropriate location within the code.
108 If the parameter name denotes a constant, a numerical value will
109 follow the variable name. If a lookup table, the name of the table
110 containing the data will follow.
112 More than one value or file name can be specified if the code is
113 intended to read in multiple pieces of data when implementing the
114 particular switch in question (see also OPTIONAL data, section (3)).
116 The conventions used for naming the variables are provided below.
117 Several of these variable names are not currently used.
120 _ denotes stability derivative
121 f "function of" (indicates data table)
123 2) timing data (global simulator variables)
124 Simtime current simulator time [s]
125 dt current simulator time step [s]
127 3) aircraft position data
128 Lat_geocentric geocentric latitude of CG [rad]
129 Lon_geocentric geocentric longitude of CG [rad]
130 Radius_to_vehicle distance of CG from inertial frame [ft]
131 Latitude geodetic latitude of CG [rad]
132 Longitude geodetic longitude of CG [rad]
133 Altitude height of CG above reference ellipsoid [ft]
134 Phi Euler bank/roll angle [rad]
135 Theta Euler pitch attitude angle [rad]
136 Psi Euler heading angle [rad]
138 4) aircraft accelerations
139 V_dot_north local x-acceleration [ft/s^2]
140 V_dot_east local y-acceleration [ft/s^2]
141 V_dot_down local z-acceleration [ft/s^2]
142 U_dot_body body x-acceleration [ft/s^2]
143 V_dot_body body y-acceleration [ft/s^2]
144 W_dot_body body z-acceleration [ft/s^2]
145 A_X_pilot pilot x-acceleration [ft/s^2]
146 A_Y_pilot pilot y-acceleration [ft/s^2]
147 A_Z_pilot pilot z-acceleration [ft/s^2]
148 A_X_cg center of gravity x-acceleration [ft/s^2]
149 A_Y_cg center of gravity x-acceleration [ft/s^2]
150 A_Z_cg center of gravity x-acceleration [ft/s^2]
151 N_X_pilot pilot x-acceleration [ft/s^2]
152 N_Y_pilot pilot y-acceleration [ft/s^2]
153 N_Z_pilot pilot z-acceleration [ft/s^2]
154 N_X_cg center of gravity x-acceleration [ft/s^2]
155 N_Y_cg center of gravity Y-acceleration [ft/s^2]
156 N_Z_cg center of gravity Z-acceleration [ft/s^2]
157 P_dot_body roll rate acceleration [rad/s^2]
158 Q_dot_body pitch rate acceleration [rad/s^2]
159 R_dot_body yaw rate acceleration [rad/s^2]
161 5) aircraft velocities
162 V_north local x-velocity [ft/s]
163 V_east local y-velocity [ft/s]
164 V_down local z-velocity [ft/s]
165 V_north_rel_ground local x-velocity with respect to ground [ft/s]
166 V_east_rel_ground local y-velocity with respect to ground [ft/s]
167 V_down_rel_ground local z-velocity with respect to ground [ft/s]
168 V_north_airmass local x-velocity of steady airmass [ft/s]
169 V_east_airmass local y-velocity of steady airmass [ft/s]
170 V_down_airmass local z-velocity of steady airmass [ft/s]
171 V_north_rel_airmass local x-velocity wrt steady airmass [ft/s]
172 V_east_rel_airmass local y-velocity wrt steady airmass [ft/s]
173 V_down_rel_airmass local z-velocity wrt steady airmass [ft/s]
174 U_gust local linear turbulence x-velocity [ft/s]
175 V_gust local linear turbulence y-velocity [ft/s]
176 W_gust local linear turbulence z-velocity [ft/s]
177 U_body wind x-velocity in body axis [ft/s]
178 V_body wind y-velocity in body axis [ft/s]
179 W_body wind z-velocity in body axis [ft/s]
180 V_rel_wind total wind velocity (freestream) [ft/s]
181 V_true_kts true velocity [kts]
182 V_rel_ground total velocity wrt ground [ft/s]
183 V_inertial total inertial velocity [ft/s]
184 V_ground_speed velocity at right angles to local vertical [ft/s]
185 V_equiv equivalent airspeed [ft/s]
186 V_equiv_kts equivalent airspeed [kts]
187 V_calibrated calibrated indicated airspeed [ft/s]
188 V_calibrated_kts calibrated indicated airspeed [kts]
189 P_local local roll rate [rad/s]
190 Q_local local pitch rate [rad/s]
191 R_local local yaw rate [rad/s]
192 P_body body roll rate [rad/s]
193 Q_body body pitch rate [rad/s]
194 R_body body yaw rate [rad/s]
195 P_total roll rate of body axis wrt local axis [rad/s]
196 Q_total pitch rate of body axis wrt local axis [rad/s]
197 R_total yaw rate of body axis wrt local axis [rad/s]
198 Phi_dot change in bank angle rate [rad/s]
199 Theta_dot change in pitch attitude angle rate [rad/s]
200 Psi_dot change in heading angle rate [rad/s]
201 Latitude_dot change in geocentric latitude rate [rad/s]
202 Longitude_dot change in geocentric longitude rate [rad/s]
203 Radius_dot change in geocentric radius rate [ft/s]
206 Alpha angle of attack [rad]
207 Alpha_deg angle of attack [deg]
208 Alpha_dot rate of change of alpha [rad/s]
209 Alpha_dot_deg rate of change of alpha [deg/s]
210 Beta sideslip angle [rad]
211 Beta_deg sideslip angle [deg]
212 Beta_dot rate of change of beta [rad]
213 Beta_dot_deg rate of change of beta [deg]
214 Gamma_vert local vertical flight path angle [rad]
215 Gamma_ver_deg local vertical flight path angle [deg]
216 Gamma_horiz local horizontal flight path angle [rad]
217 Gamma_horiz_deg local horizontal flight path angle [deg]
219 7) atmosperic properties
220 Density atmospheric density [slug/ft^3]
221 V_sound speed of sound [ft/s]
222 Mach_number free-stream Mach number []
224 Re Reynolds number []
225 Static_pressure static pressure [lb/ft^2]
226 Total_pressure total pressure [lb/ft^2]
227 Impact_pressure impact pressure [lb/ft^2]
228 Dynamic_pressure dynamic pressure [lb/ft^2]
229 Static_temperature static temperature [deg F?]
230 Total_temperature total temperature [deg F?]
233 Gravity acceleration due to gravity [ft/s^2]
234 Sea_level_radius local Earth radius [ft]
235 Earth_position_angle Earth rotation angle since reference time [rad]
236 Runway_altitude runway height above local sea level [ft]
237 Runway_latitude runway latitude [rad]
238 Runway_longitude runway longitude [rad]
239 Runway_heading runway heading [rad]
240 Radius_to_rwy geocentric radius to runway [ft]
241 D_pilot_north_of_rwy local pilot x-distance from runway [ft]
242 D_pilot_east_of_rwy local pilot y-distance from runway [ft]
243 D_pilot_down_of_rwy local pilot z-distance from runway [ft]
244 X_pilot_rwy pilot x-distance from rwy in rwy axis [ft]
245 Y_pilot_rwy pilot y-distance from rwy in rwy axis [ft]
246 H_pilot_rwy pilot z-distance from rwy in rwy axis [ft]
247 D_cg_north_of_rwy local cg x-distance from runway [ft]
248 D_cg_east_of_rwy local cg y-distance from runway [ft]
249 D_cg_down_of_rwy local cg z-distance from runway [ft]
250 X_cg_rwy cg x-distance from rwy in rwy axis [ft]
251 Y_cg_rwy cg y-distance from rwy in rwy axis [ft]
252 H_cg_rwy cg z-distance from rwy in rwy axis [ft]
254 9) aircraft geometric variables
256 cbar mean aerodynamic chord [ft]
257 Sw wing planform area [ft^2]
258 |iw wing incidence angle [deg]
260 |cc canard (mean) chord [ft]
261 |Sc canard area [ft^2]
262 |ic canard incidence angle [deg]
263 bh horizontal tail span [ft]
264 ch horizontal tail (mean) chord [ft]
265 Sh horizontal tail area [ft^2]
266 ih horizontal tail incidence angle [deg]
267 |bv vertical tail span (height) [ft]
268 |cv vertical tail (mean) chord [ft]
269 |iv vertical tail incidence angle [deg]
270 |Sv vertical tail area [ft^2]
271 Dx_pilot reference pilot x-location [ft]
272 Dy_pilot reference pilot y-location [ft]
273 Dz_pilot referende pilot z-location [ft]
274 Dx_cg reference center of gravity x-loc [ft]
275 Dy_cg reference center of gravity y-loc [ft]
276 Dz_cg reference center of gravity z-loc [ft]
278 10) aircraft control surface properties
279 |Sa aileron area [ft^2]
280 |Se elevator area [ft^2]
282 |Sr rudder area [ft^2]
283 Long_control pitch control input []
284 Long_trim longitudinal trim input [rad]
285 set_Long_trim set longitudinal trim to constant[rad]
286 zero_Long_trim set longitudinal trim to zero [deg]
287 elevator elevator deflection [rad]
288 Lat_control roll control input []
289 aileron aileron deflection [rad]
290 Rudder_pedal yaw control input []
291 rudder rudder deflection [rad]
292 |flap flap deflection [rad]
294 11) user-specified control surface deflections
295 elevator_step_angle elevator step input angle [deg]
296 elevator_step_startTime elevator step input starting time [s]
297 elevator_singlet_angle elevator singlet input angle [deg]
298 elevator_singlet_startTime elevator singlet input starting time [s]
299 elevator_singlet_duration elevator singlet time duration [s]
300 elevator_doublet_angle elevator singlet input angle [deg]
301 elevator_doublet_startTime elevator doublet input starting time [s]
302 elevator_doublet_duration elevator doublet TOTAL time duration [s]
303 elevator_input_file file of elevator deflections vs. time [s,deg]
304 aileron_input_file file of aileron deflections vs. time [s,deg]
305 rudder_input_file file of rudder deflections vs. time [s,deg]
308 Weight gross takeoff weight [lb]
309 Mass aircraft mass (used by LaRCsim) [slug]
310 I_xx roll inertia [slug-ft^2]
311 I_yy pitch inertia [slug-ft^2]
312 I_zz yaw inertia [slug-ft^2]
313 I_xz lateral cross inertia [slug-ft^2]
315 13) engine/propulsion variables
316 |thrust engine thrust [lb]
317 simpleSingle treat all engines as one; max thrust [lb]
318 Throttle_pct throttle input ("stick") []
319 Throttle_3 throttle deflection (determines thrust) [%]
321 14) force/moment coefficients
322 CD coefficient of drag []
323 CY coefficient of side-force []
324 CL coefficient of lift []
325 Cl coefficient of roll moment []
326 Cm coefficient of pitching moment []
327 Cn coefficient of yaw moment []
328 |CT coefficient of thrust []
330 15) total forces/moments
331 F_X_wind aerodynamic x-force in wind-axes [lb]
332 F_Y_wind aerodynamic y-force in wind-axes [lb]
333 F_Z_wind aerodynamic z-force in wind-axes [lb]
334 F_X_aero aerodynamic x-force in body-axes [lb]
335 F_Y_aero aerodynamic y-force in body-axes [lb]
336 F_Z_aero aerodynamic z-force in body-axes [lb]
337 F_X_engine propulsion x-force in body axes [lb]
338 F_Y_engine propulsion y-force in body axes [lb]
339 F_Z_engine propulsion z-force in body axes [lb]
340 F_X_gear gear x-force in body axes [lb]
341 F_Y_gear gear y-force in body axes [lb]
342 F_Z_gear gear z-force in body axes [lb]
343 F_X total x-force in body-axes [lb]
344 F_Y total y-force in body-axes [lb]
345 F_Z total z-force in body-axes [lb]
346 F_north total x-force in local-axes [lb]
347 F_east total y-force in local-axes [lb]
348 F_down total z-force in local-axes [lb]
349 M_l_aero aero roll-moment in body-axes [ft-lb]
350 M_m_aero aero pitch-moment in body-axes [ft-lb]
351 M_n_aero aero yaw-moment in body-axes [ft-lb]
352 M_l_engine prop roll-moment in body axes [ft-lb]
353 M_m_engine prop pitch-moment in body axes [ft-lb]
354 M_n_engine prop yaw-moment in body axes [ft-lb]
355 M_l_gear gear roll-moment in body axes [ft-lb]
356 M_m_gear gear pitch-moment in body axes [ft-lb]
357 M_n_gear gear yaw-moment in body axes [ft-lb]
358 M_l_rp total roll-moment [ft-lb]
359 M_m_rp total pitch-moment [ft-lb]
360 M_n_rp total yaw-moment [ft-lb]
362 16) landing gear properties
363 Dx_gear x-offset from CG [ft]
364 Dy_gear y-offset from CG [ft]
365 Dz_gear z-offset from CG [ft]
366 cgear gear damping constant [lb/ft/s]
367 kgear gear spring constant [lb/ft]
368 muGear gear rolling friction coef [-]
369 |strutLength gear strut length [ft]
371 17) icing model parameters
372 iceTime time when icing begins [s]
373 transientTime time period over which eta increases to final [s]
374 eta_ice_final icing severity factor at end of transient time []
375 kCA icing constants for associated aero coef. [] (see IV)
376 beta_probe_wing location of flow angle probe on wing [ft]
377 beta_probe_tail location of flow angle probe on tail [ft]
380 o value for all angles = 0 (alfa, beta, etc)
384 adot rate change in angle alpha
388 bdot rate change in beta
392 |pdot rate change in p
393 |qdot rate change in q
394 |rdot rate change in r
395 |udot rate change in x-velocity
396 da aileron deflection
397 de elevator deflection
400 |df2 flap deflection for second set
401 |df3 flap deflection for third set
406 recordRate number of times to record data per second [/s]
407 recordStartTime time to start recording outpud data [s]
408 dyn_on_speed speed when dynamic pressure terms first computed [ft/s]
409 nondim_rate_V_rel_wind use V_rel_wind to compute control rates []
410 |simpleHingeMomentCoef hinge moment coefficient []
413 fog_segments number of fog points following this line
414 fog_points fog intensity and the time at which it occurs
416 (3) | [OPTIONAL DATA]
417 =====================
419 An input line may also be used to provide optional data that
420 will be used if provided but is not necessary for the code to
421 operate. As with the variable data described in section (2), multiple
422 values or data files may be provided if the code is written to use
428 Appended comments should be provided with each input line to indicate
429 units on the variable in question and to indicate the source the data
431 **********************************************************************
433 **********************************************************************
434 III. Sample Input Lines:
439 geometry bw <value> # geometric parameter, wingspan
440 Cm Cm_a <value> # stability derivative, d(Cm)/d(alpha)
441 controlSurface de <value> <value> # max and min elevator deflections
446 CD CDfCL <file.dat> # CD(CL), drag polar data file
447 Cm Cmfade <file.dat> # Cm(alpha,delta_e), moment data file
452 CD CDfCL # CD(CL), drag calculated in code based on CL
453 (none currently in use)
455 **********************************************************************
457 **********************************************************************
458 IV. Input Line Definitions:
460 Of all the possible permutations of variable names described above in
461 section II, only some are curently implemented in the code. These are
462 described below. Comments, denoted by '#,' are used to define the
463 lines and to indicate examples of the data if additional clarity is
464 needed for unique situations. Again, those lines beginning with '|'
465 are not currently implemented in the code, but indicate planned
466 conventions in later versions.
468 # Key Variable Data Units Description Where Defined
469 #------------------------------------------------------------------------------------
471 init recordRate <recordRate> # [/s] record data n times per second uiuc_aircraft.h
473 # [s] time to start recording output data uiuc_aircraft.h
474 init recordStartTime <recordStartTime>
476 # [] use V_rel_wind to compute control rates (instead of U_body) uiuc_aircraft.h
477 init nondim_rate_V_rel_wind <nondim_rate_V_rel_wind>
479 # [ft/s] speed at which dynamic pressure terms are first computed uiuc_aircraft.h
480 init dyn_on_speed <dyn_on_speed>
482 init Dx_pilot <Dx_pilot> # [ft] reference pilot x-position ls_generic.h
483 init Dy_pilot <Dy_pilot> # [ft] reference pilot y-position ls_generic.h
484 init Dz_pilot <Dz_pilot> # [ft] reference pilot z-position ls_generic.h
486 # the following commands are currently conflicting with Flight
487 # Gear and are not working correctly:
488 |init Dx_cg <Dx_cg> # [ft] reference cg x_location ls_generic.h
489 |init Dy_cg <Dy_cg> # [ft] reference cg y_location ls_generic.h
490 |init Dz_cg <Dz_cg> # [ft] reference cg z_location ls_generic.h
491 |init V_north <V_north> # [ft/s] initial local x-velocity ls_generic.h
492 |init V_east <V_east> # [ft/s] initial local y-velocity ls_generic.h
493 |init V_down <V_down> # [ft/s] initial local z-velocity ls_generic.h
494 |init Altitude <Altitude> # [ft/s] initial altitude ls_generic.h
496 init U_body <U_body> # [ft/s] initial x-velocity in body axis ls_generic.h
497 init V_body <V_body> # [ft/s] initial y-velocity in body axis ls_generic.h
498 init W_body <W_body> # [ft/s] initial z-velocity in body axis ls_generic.h
499 init P_body <P_body> # [rad/s] initial roll rate ls_generic.h
500 init Q_body <Q_body> # [rad/s] initial pitch rate ls_generic.h
501 init R_body <R_body> # [rad/s] initial yaw rate ls_generic.h
502 init Phi <Phi> # [rad] initial bank angle ls_generic.h
503 init Theta <Theta> # [rad] initial pitch attitude angle ls_generic.h
504 init Psi <Psi> # [rad] initial heading angle ls_generic.h
505 init Alpha <Alpha> # [deg] initial angle of attack ls_generic.h
506 init Beta <Beta> # [deg] initial side slip angle ls_generic.h
507 init Long_trim <Long_trim> # [rad] longitudinal trim ls_cockpit.h
509 geometry bw <bw> # [ft] wingspan uiuc_aircraft.h
510 geometry cbar <cbar> # [ft] wing mean aero chord uiuc_aircraft.h
511 geometry Sw <Sw> # [ft^2] wing reference area uiuc_aircraft.h
512 |geometry iw <iw> # [deg] wing incidence angle uiuc_aircraft.h
513 |geometry bc <bc> # [ft] canard span uiuc_aircraft.h
514 |geometry cc <cc> # [ft] canard chord uiuc_aircraft.h
515 |geometry Sc <Sc> # [sq-ft] canard area uiuc_aircraft.h
516 |geometry ic <ic> # [deg] canard incidence angle uiuc_aircraft.h
517 geometry bh <bh> # [ft] horizontal tail span uiuc_aircraft.h
518 geometry ch <ch> # [ft] horizontal tail chord uiuc_aircraft.h
519 geometry Sh <Sh> # [sq-ft] horizontal tail area uiuc_aircraft.h
520 geometry ih <ih> # [deg] horiz tail incidence angle uiuc_aircraft.h
521 |geometry bv <bv> # [ft] vertical tail span uiuc_aircraft.h
522 |geometry cv <cv> # [ft] vertical tail chord uiuc_aircraft.h
523 |geometry Sv <Sv> # [sq-ft] vertical tail area uiuc_aircraft.h
524 |geometry iv <iv> # [deg] vert tail incidence angle uiuc_aircraft.h
526 |controlSurface Se <Se> # [ft^2] elevator area uiuc_aircraft.h
527 |controlSurface Sa <Sa> # [ft^2] aileron area uiuc_aircraft.h
528 |controlSurface Sr <Sr> # [ft^2] rudder area uiuc_aircraft.h
529 |controlSurface Sf <Sf> # [ft^2] flap area uiuc_aircraft.h
530 controlSurface de <demax> <demin> # [deg] max/min elev deflections uiuc_aircraft.h
531 controlSurface da <damax> <damin> # [deg] max/min ail deflections uiuc_aircraft.h
532 controlSurface dr <drmax> <drmin> # [deg] max/min rud deflections uiuc_aircraft.h
533 |controlSurface df <dfmax> <dfmin> # [deg] max/min flap deflections uiuc_aircraft.h
535 # trim always set to some fixed input value (radians) [rad] uiuc_aircraft.h
536 controlSurface set_Long_trim <elevator_tab>
537 # Note: Do not use. Only works with pilot_elev_no and elevator_input. Use an elevator input file instead
539 # trim always set to some fixed input value (degrees) [deg] uiuc_aircraft.h
540 controlSurface set_Long_trim_deg <elevator_tab>
541 # Note: Do not use. Only works with pilot_elev_no and elevator_input. Use an elevator input file instead
543 controlSurface zero_Long_trim # [deg] trim always set to zero uiuc_aircraft.h
545 # elevator step input with deflection angle [deg] and starting time [s] uiuc_aircraft.h
546 controlSurface elevator_step <elevator_step_angle> <elevator_step_startTime>
548 # elevator singlet input with deflection angle [deg], starting time [s],
549 # and duration of input [s] uiuc_aircraft.h
550 controlSurface elevator_singlet <elevator_singlet_angle> ->
551 <elevator_singlet_startTime> <elevator_singlet_duration>
553 # elevator doublet input with deflection angle [deg], starting time [s],
554 # and TOTAL duration of input (both up and down deflections) [s] uiuc_aircraft.h
555 controlSurface elevator_doublet <elevator_doublet_angle> ->
556 <elevator_doublet_startTime> <elevator_doublet_duration>
558 # tabulated elevator input (as function of time) with conversion
559 # factor codes and starting time [s] uiuc_aircraft.h
560 controlSurface elevator_input <elevator_input_file> ->
561 <token_value_convert1> <token_value_convert2> ->
562 <elevator_input_startTime>
564 # tabulated aileron input (as function of time) with conversion
565 # factor codes and starting time [s] uiuc_aircraft.h
566 controlSurface aileron_input <aileron_input_file> ->
567 <token_value_convert1> <token_value_convert2> ->
568 <aileron_input_startTime>
570 # tabulated rudder input (as function of time) with conversion
571 # factor codes and starting time [s] uiuc_aircraft.h
572 controlSurface rudder_input <rudder_input_file> ->
573 <token_value_convert1> <token_value_convert2> ->
574 <rudder_input_startTime>
576 # ignore elevator input from the joystick/keyboard/mouse [-] uiuc_aircraf.h
577 controlSurface pilot_elev_no
578 # Note: Only works if elevator_input is used
580 # ignore aileron input from the joystick/keyboard/mouse [-] uiuc_aircraf.h
581 controlSurface pilot_ail_no
582 # Note: Only works if aileron_input is used
584 # ignore rudder input from the joystick/keyboard/mouse [-] uiuc_aircraf.h
585 controlSurface pilot_rud_no
586 # Note: Only works if rudder_input is used
588 |controlsMixer nomix <?> # [] no controls mixing uiuc_aircraft.h
591 mass Weight <Weight> # [lb] gross takeoff weight uiuc_aircraft.h
592 mass Mass <Mass> # [slug] gross takeoff mass ls_generic.h
593 mass I_xx <I_xx> # [slug-ft^2] roll inertia ls_generic.h
594 mass I_yy <I_yy> # [slug-ft^2] pitch inertia ls_generic.h
595 mass I_zz <I_zz> # [slug-ft^2] yaw inertia ls_generic.h
596 mass I_xz <I_xz> # [slug-ft^2] lateral cross inertia ls_generic.h
599 # maximum and minimum engine thrust [lb] uiuc_aircraft.h
600 |engine thrust <thrustMax> <thrustMin>
602 # simple single engine maximum thrust [lb] uiuc_aircraft.h
603 engine simpleSingle <simpleSingleMaxThrust>
605 engine c172 # use Cessna 172 engine model of Tony Peden
606 engine cherokee # use Piper Cherokee engine model
609 CL CLo <CLo> # [] lift coef for all angles = 0 uiuc_aircraft.h
610 CL CL_a <CL_a> # [/rad] lift curve slope, d(CL)/d(alpha) uiuc_aircraft.h
611 CL CL_adot <CL_adot> # [/rad] d(CL)/d(alpha)/da(time) uiuc_aircraft.h
612 CL CL_q <CL_q> # [/rad] d(CL)/d(q) uiuc_aircraft.h
613 CL CL_ih <CL_ih> # [/rad] CL due to horiz tail incidence uiuc_aircraft.h
614 CL CL_de <CL_de> # [/rad] d(CL)/d(de) uiuc_aircraft.h
616 # CL(alpha), conversion for CL, for alpha [] uiuc_aircraft.h
617 CL CLfa <CLfa.dat> <token_value_convert1> <token_value_convert2>
619 # CL(alpha,delta_e), conversion for CL, for alpha, for delta_e [] uiuc_aircraft.h
620 CL CLfade <CLfade.dat> <token_value_convert1> <token_value_convert2> ->
621 <token_value_convert3>
623 # the following are lift coefficients in the body axis
624 CL CZo <CZo> # [] lift coef for all angles = 0 uiuc_aircraft.h
625 CL CZ_a <Cz_a> # [/rad] lift curve slope, d(CZ)/d(alpha) uiuc_aircraft.h
626 CL CZ_a2 <CZ_a2> # [/rad] d(CZ)/d(alpha squared) uiuc_aircraft.h
627 CL CZ_a3 <CZ_a3> # [/rad] d(CZ)/d(alpha cubed) uiuc_aircraft.h
628 CL CZ_adot <CZ_adot> # [/rad] d(CZ)/d(alpha)/d(time) uiuc_aircraft.h
629 CL CZ_q <CZ_q> # [/rad] d(CZ)/d(q) uiuc_aircraft.h
630 CL CZ_de <CZ_de> # [/rad] d(CZ)/d(de) uiuc_aircraft.h
631 CL CZ_deb2 <CZ_deb2> # [/rad] d(CZ)/d(de, beta squared) uiuc_aircraft.h
632 CL CZ_df <CZ_df> # [/rad] d(CZ)/d(df) uiuc_aircraft.h
633 CL CZ_adf <CZ_adf> # [/rad] d(CZ)/d(alpha, df) uiuc_aircraft.h
635 # CZ(alpha), conversion for CZ, for alpha [] uiuc_aircraft.h
636 CL CZfa <CZfa.dat> <token_value_convert1> <token_value_convert2>
638 |CL CLfCT <CLfCT.dat> # CL(thrust coef) uiuc_aircraft.h
639 |CL CLfRe # CL(Reynolds #), equation uiuc_aircraft.h
640 |CL CL_afaM <CL_afaM.dat> # CL_alpha(alpha,Mach #) uiuc_aircraft.h
641 # these are sample examples that might be used in later versions of the code
644 # note that CD terms must come after CL for induced drag to be computed
645 CD CDo <CDo> # [] drag coef for all angles = 0 uiuc_aircraft.h
646 CD CDK <CDK> # [] induced drag constant 1/(pi*e*AR) uiuc_aircraft.h
647 CD CD_a <CD_a> # [/rad] d(CD)/d(alpha) uiuc_aircraft.h
648 CD CD_ih <CD_ih> # [/rad] CD due to horiz tail incidence uiuc_aircraft.h
649 CD CD_de <CD_de> # [/rad] d(CD)/d(delta_e) uiuc_aircraft.h
651 # CD(alpha), conversion for CD, for alpha [] uiuc_aircraft.h
652 CD CDfa <CDfa.dat> <token_value_convert1> <token_value_convert2>
654 # CD(CL) drag polar, conversion for CD, for CL [] uiuc_aircraft.h
655 CD CDfCL <CDfCL.dat> <token_value_convert1> <token_value_convert2>
657 # CD(alpha,delta_e), conversion for CD, for alpha, for delta_e [] uiuc_aircraft.h
658 CD CDfade <CDfade.dat> <token_value_convert1> <token_value_convert2> ->
659 <token_value_convert3>
661 # the following are drag coefficients in the body axis
662 CD CXo <CXo> # [] drag coef for all angles = 0 uiuc_aircraft.h
663 CD CXK <CXK> # [] induced drag constant 1/(pi*e*AR) uiuc_aircraft.h
664 CD CX_a <CX_a> # [/rad] d(CX)/d(alpha) uiuc_aircraft.h
665 CD CX_a2 <CX_a2> # [/rad] d(CX)/d(alpha squared) uiuc_aircraft.h
666 CD CX_a3 <CX_a3> # [/rad] d(CX)/d(alpha cubed) uiuc_aircraft.h
667 CD CX_q <CX_q> # [/rad] d(CX)/d(q) uiuc_aircraft.h
668 CD CX_de <CX_de> # [/rad] d(CX)/d(de) uiuc_aircraft.h
669 CD CX_dr <CX_dr> # [/rad] d(CX)/d(dr) uiuc_aircraft.h
670 CD CX_df <CX_df> # [/rad] d(CX)/d(df) uiuc_aircraft.h
671 CD CX_adf <CX_adf> # [/rad] d(CX)/d(alpha, df) uiuc_aircraft.h
674 Cm Cmo <Cmo> # [] pitch mom coef for all angles=0 uiuc_aircraft.h
675 Cm Cm_a <Cm_a> # [/rad] d(Cm)/d(alpha) uiuc_aircraft.h
676 Cm Cm_a2 <Cm_a2> # [/rad] d(Cm)/d(alpha squared) uiuc_aircraft.h
677 Cm Cm_adot <Cm_adot> # [/rad] d(Cm)/d(alpha)/d(time) uiuc_aircraft.h
678 Cm Cm_q <Cm_q> # [/rad] d(Cm)/d(q) uiuc_aircraft.h
679 Cm Cm_ih <Cm_ih> # [/rad] Cm due to horiz tail incidence uiuc_aircraft.h
680 Cm Cm_de <Cm_de> # [/rad] d(Cm)/d(de) uiuc_aircraft.h
681 Cm Cm_de <Cm_b2> # [/rad] d(Cm)/d(beta squared) uiuc_aircraft.h
682 Cm Cm_r <Cm_r> # [/rad] d(Cm)/d(r) uiuc_aircraft.h
683 Cm Cm_df <Cm_df> # [/rad] d(Cm)/d(df) uiuc_aircraft.h
685 # Cm(alpha), conversion for Cm, for alpha [] uiuc_aircraft.h
686 Cm Cmfa <Cmfa.dat> <token_value_convert1> <token_value_convert2>
688 # Cm(alpha,delta_e), conversion for Cm, for alpha, for delta_e [] uiuc_aircraft.h
689 Cm Cmfade <Cmfade.dat> <token_value_convert1> <token_value_convert2> ->
690 <token_value_convert3>
693 CY CYo <CYo> # [] side-force coef for all angles=0 uiuc_aircraft.h
694 CY CY_beta <CY_beta> # [/rad] d(CY)/d(beta) uiuc_aircraft.h
695 CY CY_p <CY_p> # [/rad] d(CY)/d(p) uiuc_aircraft.h
696 CY CY_r <CY_r> # [/rad] d(CY)/d(r) uiuc_aircraft.h
697 CY CY_da <CY_da> # [/rad] d(CY)/d(da) uiuc_aircraft.h
698 CY CY_dr <CY_dr> # [/rad] d(CY)/d(dr) uiuc_aircraft.h
699 CY CY_dra <CY_dra> # [/rad] d(CY)/d(dr, alpha) uiuc_aircraft.h
700 CY CY_dra <CY_bdot> # [/rad] d(CY)/d(beta)/d(time) uiuc_aircraft.h
702 # CY(alpha,delta_a), conversion for CY, for alpha, for delta_a [] uiuc_aircraft.h
703 CY CYfada <CYfada.dat> <token_value_convert1> <token_value_convert2> ->
704 <token_value_convert3>
706 # CY(beta,delta_r), conversion for CY, for beta, for delta_r [] uiuc_aircraft.h
707 CY CYfbetadr <CYfbetadr.dat> <token_value_convert1> <token_value_convert2> ->
708 <token_value_convert3>
711 Cl Clo <Clo> # [] roll mom coef for all angles=0 uiuc_aircraft.h
712 Cl Cl_beta <Cl_beta> # [/rad] d(Cl)/d(beta) uiuc_aircraft.h
713 Cl Cl_p <Cl_p> # [/rad] d(Cl)/d(p) uiuc_aircraft.h
714 Cl Cl_r <Cl_r> # [/rad] d(Cl)/d(r) uiuc_aircraft.h
715 Cl Cl_da <Cl_da> # [/rad] d(Cl)/d(da) uiuc_aircraft.h
716 Cl Cl_dr <Cl_dr> # [/rad] d(Cl)/d(dr) uiuc_aircraft.h
717 Cl Cl_daa <Cl_daa> # [/rad] d(Cl)/d(da, alpha) uiuc_aircraft.h
719 # Cl(alpha,delta_a), conversion for Cl, for alpha, for delta_a [] uiuc_aircraft.h
720 Cl Clfada <CYfada.dat> <token_value_convert1> <token_value_convert2> ->
721 <token_value_convert3>
723 # Cl(beta,delta_r), conversion for Cl, for beta, for delta_r [] uiuc_aircraft.h
724 Cl Clfbetadr <CYfbetadr.dat> <token_value_convert1> <token_value_convert2> ->
725 <token_value_convert3>
728 Cn Cno <Cno> # [] yaw mom coef for all angles=0 uiuc_aircraft.h
729 Cn Cn_beta <Cn_beta> # [/rad] d(Cn)/d(beta) uiuc_aircraft.h
730 Cn Cn_p <Cn_p> # [/rad] d(Cn)/d(p) uiuc_aircraft.h
731 Cn Cn_r <Cn_r> # [/rad] d(Cn)/d(r) uiuc_aircraft.h
732 Cn Cn_da <Cn_da> # [/rad] d(Cn)/d(da) uiuc_aircraft.h
733 Cn Cn_dr <Cn_dr> # [/rad] d(Cn)/d(dr) uiuc_aircraft.h
734 Cn Cn_q <Cn_q> # [/rad] d(Cn)/d(q) uiuc_aircraft.h
735 Cn Cn_b3 <Cn_b3> # [/rad] d(Cn)/d(beta cubed) uiuc_aircraft.h
737 # Cn(alpha,delta_a), conversion for Cn, for alpha, for delta_a [] uiuc_aircraft.h
738 Cn Cnfada <Cnfada.dat> <token_value_convert1> <token_value_convert2> ->
739 <token_value_convert3>
741 # Cn(beta,delta_r), conversion for Cn, for beta, for delta_r [] uiuc_aircraft.h
742 Cn Cnfbetadr <Cnfbetadr.dat> <token_value_convert1> <token_value_convert2> ->
743 <token_value_convert3>
745 =============================CONVERSION CODES================================
747 To calculate the aero forces, angles (eg, alfa, beta, elevator deflection, etc)
748 must be in radians. To convert input data in degree to radian, use a
749 conversion code of 1. To use no conversion, use a conversion code of 0.
751 ------------------------------------------------
753 ------------------------------------------------
754 0 no conversion (multiply by 1)
755 1 convert degrees to radians
756 =============================================================================
759 gear Dx_gear <position> <Dx_gear> # [ft] x-offset from CG uiuc_aircraft.h
760 gear Dy_gear <position> <Dy_gear> # [ft] y-offset from CG uiuc_aircraft.h
761 gear Dz_gear <position> <Dz_gear> # [ft] z-offset from CG uiuc_aircraft.h
762 gear cgear <position> <cgear> # [lb/ft/s] gear damping constant uiuc_aircraft.h
763 gear kgear <position> <kgear> # [lb/ft] gear spring constant uiuc_aircraft.h
764 gear muRoll <position> <muRoll> # [-] gear rolling friction coef uiuc_aircraft.h
765 |gear strutLength <position> <sL> # [ft] gear strut length uiuc_aircraft.h
767 ================================GEAR POSITION================================
769 There are 16 gear positions. Currently only the first three positions are
770 rolling wheels. Position 1 is reserved for the nose wheel, position 2 is
771 reserved for the right wheel, and position 3 is reserved for the left wheel.
772 The rest of the positions can be left out or used to define locations on the
773 plane such as the wing tips or tail. This way the wing tips or tail will not
774 go "through" the ground but "bounce off" the ground.
775 =============================================================================
778 ice iceTime <iceTime> # [s] time when icing begins uiuc_aircraft.h
780 # [s] period for eta_ice to reach eta_final uiuc_aircraft.h
781 ice transientTime <transientTime>
783 # [] icing severity factor uiuc_aircraft.h
784 ice eta_ice_final <eta_ice_final>
786 ice kCDo <kCDo> # [] icing constant for CDo uiuc_aircraft.h
787 ice kCDK <kCDo> # [] icing constant for CDK uiuc_aircraft.h
788 ice kCD_a <kCD_a> # [] icing constant for CD_a uiuc_aircraft.h
789 ice kCD_q <kCD_q> # [] icing constant for CD_q uiuc_aircraft.h
790 ice kCD_de <kCD_de> # [] icing constant for CD_de uiuc_aircraft.h
791 ice kCD_dr <kCD_dr> # [] icing constant for CD_dr uiuc_aircraft.h
792 ice kCD_df <kCD_df> # [] icing constant for CD_df uiuc_aircraft.h
793 ice kCD_adf <kCD_adf> # [] icing constant for CD_adf uiuc_aircraft.h
795 ice kCXo <kCXo> # [] icing constant for CXo uiuc_aircraft.h
796 ice kCXK <kCXo> # [] icing constant for CXK uiuc_aircraft.h
797 ice kCX_a <kCX_a> # [] icing constant for CX_a uiuc_aircraft.h
798 ice kCX_a2 <kCX_a2> # [] icing constant for CX_a2 uiuc_aircraft.h
799 ice kCX_a3 <kCX_a3> # [] icing constant for CX_a3 uiuc_aircraft.h
800 ice kCX_q <kCX_q> # [] icing constant for CX_q uiuc_aircraft.h
801 ice kCX_de <kCX_de> # [] icing constant for CX_de uiuc_aircraft.h
802 ice kCX_dr <kCX_dr> # [] icing constant for CX_dr uiuc_aircraft.h
803 ice kCX_df <kCX_df> # [] icing constant for CX_df uiuc_aircraft.h
804 ice kCX_adf <kCX_adf> # [] icing constant for CX_adf uiuc_aircraft.h
806 ice kCLo <kCLo> # [] icing constant for CLo uiuc_aircraft.h
807 ice kCL_a <kCL_a> # [] icing constant for CL_a uiuc_aircraft.h
808 ice kCL_adot <kCL_adot> # [] icing constant for CL_adot uiuc_aircraft.h
809 ice kCL_q <kCL_q> # [] icing constant for CL_q uiuc_aircraft.h
810 ice kCL_de <kCL_de> # [] icing constant for CL_de uiuc_aircraft.h
811 ice kCL_df <kCL_df> # [] icing constant for CL_df uiuc_aircraft.h
812 ice kCL_adf <kCL_adf> # [] icing constant for CL_adf uiuc_aircraft.h
814 ice kCZo <kCZo> # [] icing constant for CZo uiuc_aircraft.h
815 ice kCZ_a <kCZ_a> # [] icing constant for CZ_a uiuc_aircraft.h
816 ice kCZ_a2 <kCZ_a2> # [] icing constant for CZ_a2 uiuc_aircraft.h
817 ice kCZ_a3 <kCZ_a3> # [] icing constant for CZ_a3 uiuc_aircraft.h
818 ice kCZ_adot <kCZ_adot> # [] icing constant for CZ_adot uiuc_aircraft.h
819 ice kCZ_q <kCZ_q> # [] icing constant for CZ_q uiuc_aircraft.h
820 ice kCZ_de <kCZ_de> # [] icing constant for CZ_de uiuc_aircraft.h
821 ice kCZ_df <kCZ_df> # [] icing constant for CZ_df uiuc_aircraft.h
822 ice kCZ_adf <kCZ_adf> # [] icing constant for CZ_adf uiuc_aircraft.h
823 ice kCZ_deb2 <kCZ_deb2> # [] icing constant for CZ_deb2 uiuc_aircraft.h
825 ice kCmo <kCmo> # [] icing constant for Cmo uiuc_aircraft.h
826 ice kCm_a <kCm_a> # [] icing constant for Cm_a uiuc_aircraft.h
827 ice kCm_a2 <kCm_a2> # [] icing constant for Cm_a2 uiuc_aircraft.h
828 ice kCm_a3 <kCm_a3> # [] icing constant for Cm_a3 uiuc_aircraft.h
829 ice kCm_adot <kCm_adot> # [] icing constant for Cm_adot uiuc_aircraft.h
830 ice kCm_q <kCm_q> # [] icing constant for Cm_q uiuc_aircraft.h
831 ice kCm_r <kCm_r> # [] icing constant for Cm_r uiuc_aircraft.h
832 ice kCm_de <kCm_de> # [] icing constant for Cm_de uiuc_aircraft.h
833 ice kCm_df <kCm_df> # [] icing constant for Cm_df uiuc_aircraft.h
835 ice kCYo <kCYo> # [] icing constant for CYo uiuc_aircraft.h
836 ice kCY_beta <kCy_beta> # [] icing constant for CY_beta uiuc_aircraft.h
837 ice kCY_p <kCY_p> # [] icing constant for CY_p uiuc_aircraft.h
838 ice kCY_r <kCY_r> # [] icing constant for CY_r uiuc_aircraft.h
839 ice kCY_da <kCY_da> # [] icing constant for CY_da uiuc_aircraft.h
840 ice kCY_dr <kCY_dr> # [] icing constant for CY_dr uiuc_aircraft.h
841 ice kCY_dra <kCY_dra> # [] icing constant for CY_dra uiuc_aircraft.h
842 ice kCY_bdot <kCY_bdot> # [] icing constant for CY_bdot uiuc_aircraft.h
844 ice kClo <kClo> # [] icing constant for Clo uiuc_aircraft.h
845 ice kCl_beta <kCl_beta> # [] icing constant for Cl_beta uiuc_aircraft.h
846 ice kCl_p <kCl_p> # [] icing constant for Cl_p uiuc_aircraft.h
847 ice kCl_r <kCl_r> # [] icing constant for Cl_r uiuc_aircraft.h
848 ice kCl_da <kCl_da> # [] icing constant for Cl_da uiuc_aircraft.h
849 ice kCl_dr <kCl_dr> # [] icing constant for Cl_dr uiuc_aircraft.h
850 ice kCl_daa <kCl_daa> # [] icing constant for Cl_daa uiuc_aircraft.h
852 ice kCno <kCno> # [] icing constant for Cno uiuc_aircraft.h
853 ice kCn_beta <kCn_beta> # [] icing constant for Cn_beta uiuc_aircraft.h
854 ice kCn_b3 <kCn_b3> # [] icing constant for Cn_b3 uiuc_aircraft.h
855 ice kCn_p <kCn_p> # [] icing constant for Cn_p uiuc_aircraft.h
856 ice kCn_q <kCn_q> # [] icing constant for Cn_q uiuc_aircraft.h
857 ice kCn_r <kCn_r> # [] icing constant for Cn_r uiuc_aircraft.h
858 ice kCn_da <kCn_da> # [] icing constant for Cn_da uiuc_aircraft.h
859 ice kCn_dr <kCn_dr> # [] icing constant for Cn_dr uiuc_aircraft.h
861 ice beta_probe_wing <x_probe_wing> # wing flow angle probe location uiuc_aircraft.h
862 ice beta_probe_wing <x_probe_tail> # tail flow angle probe location uiuc_aircraft.h
865 record Simtime # [s] current sim time global
866 record dt # [s] current time step global
867 record Weight # [lb] aircraft gross takeoff weight uiuc_aircraft.h
868 record Mass # [slug] aircraft mass ls_generic.h
869 record I_xx # [slug-ft^2] roll inertia ls_generic.h
870 record I_yy # [slug-ft^2] pitch inertia ls_generic.h
871 record I_zz # [slug-ft^2] yaw inertia ls_generic.h
872 record I_xz # [slug-ft^2] lateral cross inertia ls_generic.h
873 record Dx_pilot # [ft] reference pilot x-location ls_generic.h
874 record Dy_pilot # [ft] reference pilot y-location ls_generic.h
875 record Dz_pilot # [ft] reference pilot z-location ls_generic.h
876 record Dx_cg # [ft] cg x_location ls_generic.h
877 record Dy_cg # [ft] cg y_location ls_generic.h
878 record Dz_cg # [ft] cg z_location ls_generic.h
879 record Lat_geocentric # [rad] geocentric latitude ls_generic.h
880 record Lon_geocentric # [rad] geocentric longitude ls_generic.h
881 record Radius_to_vehicle # [ft] geocentric distance ls_generic.h
882 record Latitude # [rad] geodetic latitude ls_generic.h
883 record Longitude # [rad] geodetic longitude ls_generic.h
884 record Altitude # [ft] geodetic altitude ls_generic.h
885 record Phi # [rad] Euler bank angle ls_generic.h
886 record Theta # [rad] Euler pitch attitude angle ls_generic.h
887 record Psi # [rad] Euler heading angle ls_generic.h
888 record V_dot_north # [ft/s^2] local x-acceleration ls_generic.h
889 record V_dot_east # [ft/s^2] local y-acceleration ls_generic.h
890 record V_dot_down # [ft/s^2] local z-acceleration ls_generic.h
891 record U_dot_body # [ft/s^2] body x-acceleration ls_generic.h
892 record V_dot_body # [ft/s^2] body y-acceleration ls_generic.h
893 record W_dot_body # [ft/s^2] body z-acceleration ls_generic.h
894 record A_X_pilot # [ft/s^2] pilot x-acceleration ls_generic.h
895 record A_Y_pilot # [ft/s^2] pilot y-acceleration ls_generic.h
896 record A_Z_pilot # [ft/s^2] pilot z-acceleration ls_generic.h
897 record A_X_cg # [ft/s^2] cg x-acceleration ls_generic.h
898 record A_Y_cg # [ft/s^2] cg y-acceleration ls_generic.h
899 record A_Z_cg # [ft/s^2] cg z-acceleration ls_generic.h
900 record N_X_pilot # [ft/s^2] pilot x-acceleration ls_generic.h
901 record N_Y_pilot # [ft/s^2] pilot y-acceleration ls_generic.h
902 record N_Z_pilot # [ft/s^2] pilot z-acceleration ls_generic.h
903 record N_X_cg # [ft/s^2] cg x-acceleration ls_generic.h
904 record N_Y_cg # [ft/s^2] cg y-acceleration ls_generic.h
905 record N_Z_cg # [ft/s^2] cg z-acceleration ls_generic.h
906 record P_dot_body # [rad/s^2] roll rate acceleration ls_generic.h
907 record Q_dot_body # [rad/s^2] pitch rate acceleration ls_generic.h
908 record R_dot_body # [rad/s^2] yaw rate acceleration ls_generic.h
909 record V_north # [ft/s] local x-velocity ls_generic.h
910 record V_east # [ft/s] local y-velocity ls_generic.h
911 record V_down # [ft/s] local z-velocity ls_generic.h
912 record V_north_rel_ground # [ft/s] local x-velocity wrt ground ls_generic.h
913 record V_east_rel_ground # [ft/s] local y-velocity wrt ground ls_generic.h
914 record V_down_rel_ground # [ft/s] local z-velocity wrt ground ls_generic.h
915 record V_north_airmass # [ft/s] local x-velocity of airmass ls_generic.h
916 record V_east_airmass # [ft/s] local y-velocity of airmass ls_generic.h
917 record V_down_airmass # [ft/s] local z-velocity of airmass ls_generic.h
918 record V_north_rel_airmass # [ft/s] local x-velocity wrt airmass ls_generic.h
919 record V_east_rel_airmass # [ft/s] local y-velocity wrt airmass ls_generic.h
920 record V_down_rel_airmass # [ft/s] local z-velocity wrt airmass ls_generic.h
921 record U_gust # [ft/s] local turbulence x-velocity ls_generic.h
922 record V_gust # [ft/s] local turbulence y-velocity ls_generic.h
923 record W_gust # [ft/s] local turbulence z-velocity ls_generic.h
924 record U_body # [ft/s] wind x-velocity in body axis ls_generic.h
925 record V_body # [ft/s] wind y-velocity in body axis ls_generic.h
926 record W_body # [ft/s] wind z-velocity in body axis ls_generic.h
927 record V_rel_wind # [ft/s] total freestream velocity ls_generic.h
928 record V_true_kts # [kts] true velocity ls_generic.h
929 record V_rel_ground # [ft/s] total velocity wrt ground ls_generic.h
930 record V_inertial # [ft/s] total inertial velocity ls_generic.h
931 record V_ground_speed # [ft/s] airspeed wrt ground ls_generic.h
932 record V_equiv # [ft/s] equivalent airspeed ls_generic.h
933 record V_equiv_kts # [kts] equivalent airspeed ls_generic.h
934 record V_calibrated # [ft/s] calibrated airspeed ls_generic.h
935 record V_calibrated_kts # [kts] calibrated airspeed ls_generic.h
936 record P_local # [rad/s] local roll rate ls_generic.h
937 record Q_local # [rad/s] local pitch rate ls_generic.h
938 record R_local # [rad/s] local yaw rate ls_generic.h
939 record P_body # [rad/s] body roll rate ls_generic.h
940 record Q_body # [rad/s] body pitch rate ls_generic.h
941 record R_body # [rad/s] body yaw rate ls_generic.h
942 record P_total # [rad/s] total roll rate ls_generic.h
943 record Q_total # [rad/s] total pitch rate ls_generic.h
944 record R_total # [rad/s] total yaw rate ls_generic.h
945 record Phi_dot # [rad/s] bank angle rate ls_generic.h
946 record Theta_dot # [rad/s] pitch attitude angle rate ls_generic.h
947 record Psi_dot # [rad/s] heading angle rate ls_generic.h
948 record Latitude_dot # [rad/s] latitude rate ls_generic.h
949 record Longitude_dot # [rad/s] longitude rate ls_generic.h
950 record Radius_dot # [rad/s] radius rate ls_generic.h
951 record Alpha # [rad] angle of attack ls_generic.h
952 record Alpha_deg # [deg] angle of attack (in degrees) uiuc_aircraft.h
953 record Alpha_dot # [rad/s] rate of change of alpha ls_generic.h
954 record Alpha_dot_deg # [rad/s] rate of change of alpha uiuc_aircraft.h
955 record Beta # [rad] sideslip angle ls_generic.h
956 record Beta_deg # [rad] sideslip angle uiuc_aircraft.h
957 record Beta_dot # [rad/s] rate of change of beta ls_generic.h
958 record Beta_dot_deg # [rad/s] rate of change of beta uiuc_aircraft.h
959 record Gamma_vert # [rad] vertical flight path angle ls_generic.h
960 record Gamma_vert_deg # [deg] vertical flight path angle uiuc_aircraft.h
961 record Gamma_horiz # [rad] horizontal flight path angle ls_generic.h
962 record Gamma_horiz_deg # [deg] horizontal flight path angle uiuc_aircraft.h
963 record Density # [slug/ft^3] air density ls_generic.h
964 record V_sound # [ft/s] speed of sound ls_generic.h
965 record Mach_number # [] Mach number ls_generic.h
966 record Static_pressure # [lb/ft^2] static pressure ls_generic.h
967 record Total_pressure # [lb/ft^2] total pressure ls_generic.h
968 record Impact_pressure # [lb/ft^2] impact pressure ls_generic.h
969 record Dynamic_pressure # [lb/ft^2] dynamic pressure ls_generic.h
970 record Static_temperature # [?] static temperature ls_generic.h
971 record Total_temperature # [?] total temperature ls_generic.h
972 record Gravity # [ft/s^2] acceleration due to gravity ls_generic.h
973 record Sea_level_radius # [ft] Earth radius ls_generic.h
974 record Earth_position_angle # [rad] Earth rotation angle ls_generic.h
975 record Runway_altitude # [ft] runway altitude ls_generic.h
976 record Runway_latitude # [rad] runway latitude ls_generic.h
977 record Runway_longitude # [rad] runway longititude ls_generic.h
978 record Runway_heading # [rad] runway heading ls_generic.h
979 record Radius_to_rwy # [ft] geocentric radius to runway ls_generic.h
980 record D_pilot_north_of_rwy # [ft] local pilot x-dist from rwy ls_generic.h
981 record D_pilot_east_of_rwy # [ft] local pilot y-dist from rwy ls_generic.h
982 record D_pilot_down_of_rwy # [ft] local pilot z-dist from rwy ls_generic.h
983 record X_pilot_rwy # [ft] pilot x-dist from rwy ls_generic.h
984 record Y_pilot_rwy # [ft] pilot y-dist from rwy ls_generic.h
985 record H_pilot_rwy # [ft] pilot z-dist from rwy ls_generic.h
986 record D_cg_north_of_rwy # [ft] local cg x-dist from rwy ls_generic.h
987 record D_cg_east_of_rwy # [ft] local cg y-dist from rwy ls_generic.h
988 record D_cg_down_of_rwy # [ft] local cg z-dist from rwy ls_generic.h
989 record X_cg_rwy # [ft] cg x-dist from rwy ls_generic.h
990 record Y_cg_rwy # [ft] cg y-dist from rwy ls_generic.h
991 record H_cg_rwy # [ft] cg z-dist from rwy ls_generic.h
992 record Throttle_pct # [%] throttle input ls_cockpit.h
993 record Throttle_3 # [%] throttle deflection ls_cockpit.h
994 record Long_control # [] pitch input ls_cockpit.h
995 record Long_trim # [rad] longitudinal trim ls_cockpit.h
996 record Long_trim_deg # [deg] longitudinal trim uiuc_aircraft.h
997 record elevator # [rad] elevator deflection uiuc_aircraft.h
998 record elevator_deg # [deg] elevator deflection uiuc_aircraft.h
999 record Lat_control # [] roll input ls_cockpit.h
1000 record aileron # [rad] aileron deflection uiuc_aircraft.h
1001 record aileron_deg # [deg] aileron deflection uiuc_aircraft.h
1002 record Rudder_pedal # [] yaw input ls_cockpit.h
1003 record rudder # [rad] rudder deflection uiuc_aircraft.h
1004 record rudder_deg # [deg] rudder deflection uiuc_aircraft.h
1005 record CDfaI # [] CD(alpha) uiuc_aircraft.h
1006 record CDfCLI # [] CD(CL), drag polar uiuc_aircraft.h
1007 record CDfadeI # [] CD(alpha,delta_e) uiuc_aircraft.h
1008 record CD # [] drag coefficient uiuc_aircraft.h
1009 record CLfaI # [] CL(alpha) uiuc_aircraft.h
1010 record CLfadeI # [] CL(alpha,delta_e) uiuc_aircraft.h
1011 record CL # [] lift coefficient uiuc_aircraft.h
1012 record CmfaI # [] Cm(alpha) uiuc_aircraft.h
1013 record CmfadeI # [] Cm(alpha,delta_e) uiuc_aircraft.h
1014 record Cm # [] pitch moment coefficient uiuc_aircraft.h
1015 record CYfadaI # [] CY(alpha,delta_a) uiuc_aircraft.h
1016 record CYfbetadrI # [] CY(beta,delta_r) uiuc_aircraft.h
1017 record CY # [] side-force coefficient uiuc_aircraft.h
1018 record ClfadaI # [] Cl(alpha,delta_a) uiuc_aircraft.h
1019 record ClfbetadrI # [] Cl(beta,delta_r) uiuc_aircraft.h
1020 record Cl # [] roll moment coefficient uiuc_aircraft.h
1021 record CnfadaI # [] Cn(alpha,delta_a) uiuc_aircraft.h
1022 record CnfbetadrI # [] Cn(beta,delta_r) uiuc_aircraft.h
1023 record Cn # [] yaw moment coefficient uiuc_aircraft.h
1024 record CLclean_wing # [] wing clean lift coefficient uiuc_aircraft.h
1025 record CLiced_wing # [] wing iced lift coefficient uiuc_aircraft.h
1026 record CLclean_tail # [] tail clean lift coefficient uiuc_aircraft.h
1027 record CLiced_tail # [] tail iced lift coefficient uiuc_aircraft.h
1028 record Lift_clean_wing # [lb] wing clean lift force uiuc_aircraft.h
1029 record Lift_iced_wing # [lb] wing iced lift force uiuc_aircraft.h
1030 record Lift_clean_tail # [lb] tail clean lift force uiuc_aircraft.h
1031 record Lift_iced_tail # [lb] tail iced lift force uiuc_aircraft.h
1032 record Gamma_clean_wing # [ft^2/s] wing clean circulation uiuc_aircraft.h
1033 record Gamma_iced_wing # [ft^2/s] wing iced circulation uiuc_aircraft.h
1034 record Gamma_clean_tail # [ft^2/s] tail clean circulation uiuc_aircraft.h
1035 record Gamma_iced_tail # [ft^2/s] tail iced circulation uiuc_aircraft.h
1036 record w_clean_wing # [ft/s] wing clean downwash uiuc_aircraft.h
1037 record w_iced_wing # [ft/s] wing iced downwash uiuc_aircraft.h
1038 record w_clean_tail # [ft/s] tail clean downwash uiuc_aircraft.h
1039 record w_iced_tail # [ft/s] tail iced downwash uiuc_aircraft.h
1040 record V_total_clean_wing # [ft/s] wing clean velocity uiuc_aircraft.h
1041 record V_total_iced_wing # [ft/s] wing iced velocity uiuc_aircraft.h
1042 record V_total_clean_tail # [ft/s] tail clean velocity uiuc_aircraft.h
1043 record V_total_iced_tail # [ft/s] tail iced velocity uiuc_aircraft.h
1044 record beta_flow_clean_wing # [rad] wing clean flow angle uiuc_aircraft.h
1045 record beta_flow_clean_wing_deg # [deg] wing clean flow angle uiuc_aircraft.h
1046 record beta_flow_iced_wing # [rad] wing iced flow angle uiuc_aircraft.h
1047 record beta_flow_iced_wing_deg # [deg] wing iced flow angle uiuc_aircraft.h
1048 record beta_flow_clean_tail # [rad] tail clean flow angle uiuc_aircraft.h
1049 record beta_flow_clean_tail_deg # [deg] tail clean flow angle uiuc_aircraft.h
1050 record beta_flow_iced_tail # [rad] tail iced flow angle uiuc_aircraft.h
1051 record beta_flow_iced_tail_deg # [deg] tail iced flow angle uiuc_aircraft.h
1052 record Dbeta_flow_wing # [rad] difference in wing flow angle uiuc_aircraft.h
1053 record Dbeta_flow_wing_deg # [deg] difference in wing flow angle uiuc_aircraft.h
1054 record Dbeta_flow_tail # [rad] difference in tail flow angle uiuc_aircraft.h
1055 record Dbeta_flow_tail_deg # [deg] difference in tail flow angle uiuc_aircraft.h
1056 record pct_beta_flow_wing # [%] difference in wing flow angle uiuc_aircraft.h
1057 record pct_beta_flow_tail # [%] difference in tail flow angle uiuc_aircraft.h
1058 record F_X_wind # [lb] aero x-force in wind-axes ls_generic.h
1059 record F_Y_wind # [lb] aero y-force in wind-axes ls_generic.h
1060 record F_Z_wind # [lb] aero z-force in wind-axes ls_generic.h
1061 record F_X_aero # [lb] aero x-force in body-axes ls_generic.h
1062 record F_Y_aero # [lb] aero y-force in body-axes ls_generic.h
1063 record F_Z_aero # [lb] aero z-force in body-axes ls_generic.h
1064 record F_X_engine # [lb] prop x-force in body-axes ls_generic.h
1065 record F_Y_engine # [lb] prop y-force in body-axes ls_generic.h
1066 record F_Z_engine # [lb] prop z-force in body-axes ls_generic.h
1067 record F_X_gear # [lb] gear x-force in body-axes ls_generic.h
1068 record F_Y_gear # [lb] gear y-force in body-axes ls_generic.h
1069 record F_Z_gear # [lb] gear z-force in body-axes ls_generic.h
1070 record F_X # [lb] total x-force in body-axes ls_generic.h
1071 record F_Y # [lb] total y-force in body-axes ls_generic.h
1072 record F_Z # [lb] total z-force in body-axes ls_generic.h
1073 record F_nort # [lb] total x-force in local-axes ls_generic.h
1074 record F_east # [lb] total y-force in local-axes ls_generic.h
1075 record F_down # [lb] total z-force in local-axes ls_generic.h
1076 record M_l_aero # [ft-lb] aero roll mom in body axes ls_generic.h
1077 record M_m_aero # [ft-lb] aero pitch mom in body axes ls_generic.h
1078 record M_n_aero # [ft-lb] aero yaw mom in body axes ls_generic.h
1079 record M_l_engine # [ft-lb] prop roll mom in body axes ls_generic.h
1080 record M_m_engine # [ft-lb] prop pitch mom in body axes ls_generic.h
1081 record M_n_engine # [ft-lb] prop yaw mom in body axes ls_generic.h
1082 record M_l_gear # [ft-lb] gear roll mom in body axes ls_generic.h
1083 record M_m_gear # [ft-lb] gear pitch mom in body axes ls_generic.h
1084 record M_n_gear # [ft-lb] gear yaw mom in body axes ls_generic.h
1085 record M_l_rp # [ft-lb] total roll mom in body axes ls_generic.h
1086 record M_m_rp # [ft-lb] total pitch mom in body axes ls_generic.h
1087 record M_n_rp # [ft-lb] total yaw mom in body axes ls_generic.h
1090 fog fog_segments <fog_segments> # [-] number of fog points after this line
1091 fog fog_point <time> <intensity>
1093 Note: Between each fog_point there is a linear interpolation
1095 ============================FOG EXAMPLE===============================
1098 fog fog_point 30 500
1099 fog fog_point 35 200
1100 fog fog_point 40 -100
1103 The first line says that there will be 4 fog_point statements following.
1104 From time 0 to 30 seconds, the fog will increase linearly to 500. From
1105 30 to 35 seconds, the fog will decrease linearly to 200. From 35 to 40
1106 seconds the fog will decrease to -100. From 40 to 50 the fog will
1108 ======================================================================
1111 # the following command is implemented but the data is not used in any
1112 # equation of motion
1113 # hinge moment coefficient [] uiuc_aircraft.h
1114 |misc simpleHingeMomentCoef <simpleHingeMomentCoef>
1117 **********************************************************************
1119 **********************************************************************
1122 The following data is required for the simulator to function;
1123 otherwise either the UIUC Aero Model or LaRCsim parts of the code will
1126 1) aircraft geometry (UIUC Aero Model)
1128 cbar mean aerodynamic chord [ft]
1129 Sw wing planform area [ft^2]
1131 2) engine properties (UIUC Engine Model)
1132 (some engine model must be specified, such as...)
1137 3) mass variables (LaRCsim)
1138 Weight aircraft gross takeoff weight [lb]
1140 Mass aircraft mass [slug]
1141 I_xx roll inertia [slug-ft^2]
1142 I_yy pitch inertia [slug-ft^2]
1143 I_zz yaw inertia [slug-ft^2]
1144 I_xz lateral cross inertia [slug-ft^2]
1146 4) aerodynamic force/moment components (Aero Model)
1147 CLo lift coef for all angles = 0 []
1148 CL_a lift curve slope, d(CL)/d(alpha) [/rad]
1149 CDo drag coef for all angles = 0 []
1150 CDK induced drag constant []
1152 CD_a d(CD)/d(alpha) [/rad]
1153 Cmo pitch mom coef for all angles=0 []
1154 Cm_a d(Cm)/d(alpha) [/rad]
1155 CY_beta d(CY)/d(beta) [/rad]
1156 Cl_beta d(Cl)/d(beta) [/rad]
1157 Cn_beta d(Cn)/d(beta) [/rad]
1160 (some gear properties must be defined otherwise the aircraft
1161 will not behave properly on the ground)
1162 Dx_gear x-offset from CG [ft]
1163 Dy_gear y-offset from CG [ft]
1164 Dz_gear z-offset from CG [ft]
1165 cgear gear damping constant [lb/ft/s]
1166 kgear gear spring constant [lb/ft]
1167 muGear gear rolling friction coef [-]
1170 **********************************************************************