1 ************************************************
3 * FGFS Reconfigurable Aircraft Flight Model *
4 * Input File Documentation *
5 * Version 0.73, June 27, 2000 *
8 * Jeff Scott (jscott@mail.com) *
9 * Bipin Sehgal (bsehgal@uiuc.edu) *
10 * Michael Selig (m-selig@uiuc.edu) *
11 * Dept of Aero and Astro Engineering *
12 * University of Illinois at Urbana-Champaign *
14 * http://amber.aae.uiuc.edu/~m-selig *
16 ************************************************
19 **********************************************************************
20 NOTE: Most of the commands discussed in this documentation are
21 currently implemented in the UIUC aerodynamics model. Those
22 denoted by '|' are proposed and will likely be added in the
23 future but are not currently implemented. Some commands are
24 in use but not producing the desired results. These are
25 clearly noted, so please do not attempt to use them at this
27 **********************************************************************
29 **********************************************************************
30 This documentation includes:
31 - Required and optional input lines.
32 - Input line formats and conventions.
34 Viewing this file in emacs makefile-mode with color makes this file
36 **********************************************************************
38 **********************************************************************
39 I. Conventions and Notations and Reading this Document:
42 | Input line not yet implemented
44 | Sometimes indicates a feature not yet used,
45 but proposed convention is indicated nevertheless.
46 <...> Value or file name to be placed here
47 || Input line disabled
49 ... Repeat similar data
50 -> Continue onto next line
51 **********************************************************************
53 **********************************************************************
54 II. General Input Line Format:
56 Examples input lines include
58 Cm Cmo 0.194 # [] Bray pg 33
59 Cm Cm_a -2.12 # [/rad] Bray pg 33
60 CL CLfa CLfa.dat 0 1 # [] Bray pg 50, Table 4.7
62 These follow the more general input line form
64 keyword variableName <value -or- file> | ->
65 <value -or- file> # [units] <data source>
67 Each term of the input line will be discussed in turn.
72 There currently exist the following variable keyword types:
74 init Initial values for equation of motion
75 geometry Aircraft-specific geometric quantities
76 controlSurface Control surface deflections and properties
77 |controlsMixer Control surface mixer options
78 mass Aircraft-specific mass properties
79 engine Propulsion data
80 CD Aerodynamic x-force quantities (longitudinal)
81 CL Aerodynamic z-force quantities (longitudinal)
82 Cm Aerodynamic m-moment quantities (longitudinal)
83 CY Aerodynamic y-force quantities (lateral)
84 Cl Aerodynamic l-moment quantities (lateral)
85 Cn Aerodynamic n-moment quantities (lateral)
86 |gear Landing gear model quantities
87 ice Icing model parameters
88 record Record desired quantites to file
89 misc Miscellaneous inputs
91 As each line of the input file is read, the code recognizes the
92 keyword, enters the appropriate switch statement in the code, and
93 proceeds to read the next term in the input line.
98 The variable name indicates the form of the variable itself. This
99 form may be a constant, a stability derivative (a specific form of a
100 constant), or a variable-dimensional lookup table. More variable
101 types can be easily prescribed by defining a new convention. The
102 variable name may also indicate that the quantity is to be calculated
103 from a hard-coded equation or set of equations provided at an
104 appropriate location within the code.
106 If the parameter name denotes a constant, a numerical value will
107 follow the variable name. If a lookup table, the name of the table
108 containing the data will follow.
110 More than one value or file name can be specified if the code is
111 intended to read in multiple pieces of data when implementing the
112 particular switch in question (see also OPTIONAL data, section (3)).
114 The conventions used for naming the variables are provided below.
115 Several of these variable names are not currently used.
118 _ denotes stability derivative
119 f "function of" (indicates data table)
121 2) timing data (global simulator variables)
122 Simtime current simulator time [s]
123 dt current simulator time step [s]
125 3) aircraft position data
126 Lat_geocentric geocentric latitude of CG [rad]
127 Lon_geocentric geocentric longitude of CG [rad]
128 Radius_to_vehicle distance of CG from inertial frame [ft]
129 Latitude geodetic latitude of CG [rad]
130 Longitude geodetic longitude of CG [rad]
131 Altitude height of CG above reference ellipsoid [ft]
132 Phi Euler bank/roll angle [rad]
133 Theta Euler pitch attitude angle [rad]
134 Psi Euler heading angle [rad]
136 4) aircraft accelerations
137 V_dot_north local x-acceleration [ft/s^2]
138 V_dot_east local y-acceleration [ft/s^2]
139 V_dot_down local z-acceleration [ft/s^2]
140 U_dot_body body x-acceleration [ft/s^2]
141 V_dot_body body y-acceleration [ft/s^2]
142 W_dot_body body z-acceleration [ft/s^2]
143 A_X_pilot pilot x-acceleration [ft/s^2]
144 A_Y_pilot pilot y-acceleration [ft/s^2]
145 A_Z_pilot pilot z-acceleration [ft/s^2]
146 A_X_cg center of gravity x-acceleration [ft/s^2]
147 A_Y_cg center of gravity x-acceleration [ft/s^2]
148 A_Z_cg center of gravity x-acceleration [ft/s^2]
149 N_X_pilot pilot x-acceleration [ft/s^2]
150 N_Y_pilot pilot y-acceleration [ft/s^2]
151 N_Z_pilot pilot z-acceleration [ft/s^2]
152 N_X_cg center of gravity x-acceleration [ft/s^2]
153 N_Y_cg center of gravity Y-acceleration [ft/s^2]
154 N_Z_cg center of gravity Z-acceleration [ft/s^2]
155 P_dot_body roll rate acceleration [rad/s^2]
156 Q_dot_body pitch rate acceleration [rad/s^2]
157 R_dot_body yaw rate acceleration [rad/s^2]
159 5) aircraft velocities
160 V_north local x-velocity [ft/s]
161 V_east local y-velocity [ft/s]
162 V_down local z-velocity [ft/s]
163 V_north_rel_ground local x-velocity with respect to ground [ft/s]
164 V_east_rel_ground local y-velocity with respect to ground [ft/s]
165 V_down_rel_ground local z-velocity with respect to ground [ft/s]
166 V_north_airmass local x-velocity of steady airmass [ft/s]
167 V_east_airmass local y-velocity of steady airmass [ft/s]
168 V_down_airmass local z-velocity of steady airmass [ft/s]
169 V_north_rel_airmass local x-velocity wrt steady airmass [ft/s]
170 V_east_rel_airmass local y-velocity wrt steady airmass [ft/s]
171 V_down_rel_airmass local z-velocity wrt steady airmass [ft/s]
172 U_gust local linear turbulence x-velocity [ft/s]
173 V_gust local linear turbulence y-velocity [ft/s]
174 W_gust local linear turbulence z-velocity [ft/s]
175 U_body wind x-velocity in body axis [ft/s]
176 V_body wind y-velocity in body axis [ft/s]
177 W_body wind z-velocity in body axis [ft/s]
178 V_rel_wind total wind velocity (freestream) [ft/s]
179 V_true_kts true velocity [kts]
180 V_rel_ground total velocity wrt ground [ft/s]
181 V_inertial total inertial velocity [ft/s]
182 V_ground_speed velocity at right angles to local vertical [ft/s]
183 V_equiv equivalent airspeed [ft/s]
184 V_equiv_kts equivalent airspeed [kts]
185 V_calibrated calibrated indicated airspeed [ft/s]
186 V_calibrated_kts calibrated indicated airspeed [kts]
187 P_local local roll rate [rad/s]
188 Q_local local pitch rate [rad/s]
189 R_local local yaw rate [rad/s]
190 P_body body roll rate [rad/s]
191 Q_body body pitch rate [rad/s]
192 R_body body yaw rate [rad/s]
193 P_total roll rate of body axis wrt local axis [rad/s]
194 Q_total pitch rate of body axis wrt local axis [rad/s]
195 R_total yaw rate of body axis wrt local axis [rad/s]
196 Phi_dot change in bank angle rate [rad/s]
197 Theta_dot change in pitch attitude angle rate [rad/s]
198 Psi_dot change in heading angle rate [rad/s]
199 Latitude_dot change in geocentric latitude rate [rad/s]
200 Longitude_dot change in geocentric longitude rate [rad/s]
201 Radius_dot change in geocentric radius rate [ft/s]
204 Alpha angle of attack [rad]
205 Alpha_deg angle of attack [deg]
206 Alpha_dot rate of change of alpha [rad/s]
207 Alpha_dot_deg rate of change of alpha [deg/s]
208 Beta sideslip angle [rad]
209 Beta_deg sideslip angle [deg]
210 Beta_dot rate of change of beta [rad]
211 Beta_dot_deg rate of change of beta [deg]
212 Gamma_vert local vertical flight path angle [rad]
213 Gamma_ver_deg local vertical flight path angle [deg]
214 Gamma_horiz local horizontal flight path angle [rad]
215 Gamma_horiz_deg local horizontal flight path angle [deg]
217 7) atmosperic properties
218 Density atmospheric density [slug/ft^3]
219 V_sound speed of sound [ft/s]
220 Mach_number free-stream Mach number []
222 Re Reynolds number []
223 Static_pressure static pressure [lb/ft^2]
224 Total_pressure total pressure [lb/ft^2]
225 Impact_pressure impact pressure [lb/ft^2]
226 Dynamic_pressure dynamic pressure [lb/ft^2]
227 Static_temperature static temperature [deg F?]
228 Total_temperature total temperature [deg F?]
231 Gravity acceleration due to gravity [ft/s^2]
232 Sea_level_radius local Earth radius [ft]
233 Earth_position_angle Earth rotation angle since reference time [rad]
234 Runway_altitude runway height above local sea level [ft]
235 Runway_latitude runway latitude [rad]
236 Runway_longitude runway longitude [rad]
237 Runway_heading runway heading [rad]
238 Radius_to_rwy geocentric radius to runway [ft]
239 D_pilot_north_of_rwy local pilot x-distance from runway [ft]
240 D_pilot_east_of_rwy local pilot y-distance from runway [ft]
241 D_pilot_down_of_rwy local pilot z-distance from runway [ft]
242 X_pilot_rwy pilot x-distance from rwy in rwy axis [ft]
243 Y_pilot_rwy pilot y-distance from rwy in rwy axis [ft]
244 H_pilot_rwy pilot z-distance from rwy in rwy axis [ft]
245 D_cg_north_of_rwy local cg x-distance from runway [ft]
246 D_cg_east_of_rwy local cg y-distance from runway [ft]
247 D_cg_down_of_rwy local cg z-distance from runway [ft]
248 X_cg_rwy cg x-distance from rwy in rwy axis [ft]
249 Y_cg_rwy cg y-distance from rwy in rwy axis [ft]
250 H_cg_rwy cg z-distance from rwy in rwy axis [ft]
252 9) aircraft geometric variables
254 cbar mean aerodynamic chord [ft]
255 Sw wing planform area [ft^2]
256 |iw wing incidence angle [deg]
258 |cc canard (mean) chord [ft]
259 |Sc canard area [ft^2]
260 |ic canard incidence angle [deg]
261 bh horizontal tail span [ft]
262 ch horizontal tail (mean) chord [ft]
263 Sh horizontal tail area [ft^2]
264 ih horizontal tail incidence angle [deg]
265 |bv vertical tail span (height) [ft]
266 |cv vertical tail (mean) chord [ft]
267 |iv vertical tail incidence angle [deg]
268 |Sv vertical tail area [ft^2]
269 Dx_pilot reference pilot x-location [ft]
270 Dy_pilot reference pilot y-location [ft]
271 Dz_pilot referende pilot z-location [ft]
272 Dx_cg reference center of gravity x-loc [ft]
273 Dy_cg reference center of gravity y-loc [ft]
274 Dz_cg reference center of gravity z-loc [ft]
276 10) aircraft control surface properties
277 |Sa aileron area [ft^2]
278 |Se elevator area [ft^2]
280 |Sr rudder area [ft^2]
281 Long_control pitch control input []
282 Long_trim longitudinal trim input [rad]
283 set_Long_trim set longitudinal trim to constant[rad]
284 zero_Long_trim set longitudinal trim to zero [deg]
285 elevator elevator deflection [rad]
286 Lat_control roll control input []
287 aileron aileron deflection [rad]
288 Rudder_pedal yaw control input []
289 rudder rudder deflection [rad]
290 |flap flap deflection [rad]
292 11) user-specified control surface deflections
293 elevator_step_angle elevator step input angle [deg]
294 elevator_step_startTime elevator step input starting time [s]
295 elevator_singlet_angle elevator singlet input angle [deg]
296 elevator_singlet_startTime elevator singlet input starting time [s]
297 elevator_singlet_duration elevator singlet time duration [s]
298 elevator_doublet_angle elevator singlet input angle [deg]
299 elevator_doublet_startTime elevator doublet input starting time [s]
300 elevator_doublet_duration elevator doublet TOTAL time duration [s]
301 elevator_input_file file of elevator deflections vs. time [s,deg]
304 Weight gross takeoff weight [lb]
305 Mass aircraft mass (used by LaRCsim) [slug]
306 I_xx roll inertia [slug-ft^2]
307 I_yy pitch inertia [slug-ft^2]
308 I_zz yaw inertia [slug-ft^2]
309 I_xz lateral cross inertia [slug-ft^2]
311 13) engine/propulsion variables
312 |thrust engine thrust [lb]
313 simpleSingle treat all engines as one; max thrust [lb]
314 Throttle_pct throttle input ("stick") []
315 Throttle_3 throttle deflection (determines thrust) [%]
317 14) force/moment coefficients
318 CD coefficient of drag []
319 CY coefficient of side-force []
320 CL coefficient of lift []
321 Cl coefficient of roll moment []
322 Cm coefficient of pitching moment []
323 Cn coefficient of yaw moment []
324 |CT coefficient of thrust []
326 15) total forces/moments
327 F_X_wind aerodynamic x-force in wind-axes [lb]
328 F_Y_wind aerodynamic y-force in wind-axes [lb]
329 F_Z_wind aerodynamic z-force in wind-axes [lb]
330 F_X_aero aerodynamic x-force in body-axes [lb]
331 F_Y_aero aerodynamic y-force in body-axes [lb]
332 F_Z_aero aerodynamic z-force in body-axes [lb]
333 F_X_engine propulsion x-force in body axes [lb]
334 F_Y_engine propulsion y-force in body axes [lb]
335 F_Z_engine propulsion z-force in body axes [lb]
336 F_X_gear gear x-force in body axes [lb]
337 F_Y_gear gear y-force in body axes [lb]
338 F_Z_gear gear z-force in body axes [lb]
339 F_X total x-force in body-axes [lb]
340 F_Y total y-force in body-axes [lb]
341 F_Z total z-force in body-axes [lb]
342 F_north total x-force in local-axes [lb]
343 F_east total y-force in local-axes [lb]
344 F_down total z-force in local-axes [lb]
345 M_l_aero aero roll-moment in body-axes [ft-lb]
346 M_m_aero aero pitch-moment in body-axes [ft-lb]
347 M_n_aero aero yaw-moment in body-axes [ft-lb]
348 M_l_engine prop roll-moment in body axes [ft-lb]
349 M_m_engine prop pitch-moment in body axes [ft-lb]
350 M_n_engine prop yaw-moment in body axes [ft-lb]
351 M_l_gear gear roll-moment in body axes [ft-lb]
352 M_m_gear gear pitch-moment in body axes [ft-lb]
353 M_n_gear gear yaw-moment in body axes [ft-lb]
354 M_l_rp total roll-moment [ft-lb]
355 M_m_rp total pitch-moment [ft-lb]
356 M_n_rp total yaw-moment [ft-lb]
358 16) landing gear properties
359 |cgear gear damping constant [?]
360 |kgear gear spring constant [?]
361 |muGear gear rolling friction coef [?]
362 |strutLength gear strut length [ft]
364 17) icing model parameters
365 iceTime time when icing begins [s]
366 transientTime time period over which eta increases to final [s]
367 eta_ice_final icing severity factor at end of transient time []
368 kCA icing constants for associated aero coef. [] (see IV)
369 beta_probe_wing location of flow angle probe on wing [ft]
370 beta_probe_tail location of flow angle probe on tail [ft]
373 o value for all angles = 0 (alfa, beta, etc)
377 adot rate change in angle alpha
381 bdot rate change in beta
385 |pdot rate change in p
386 |qdot rate change in q
387 |rdot rate change in r
388 |udot rate change in x-velocity
389 da aileron deflection
390 de elevator deflection
393 |df2 flap deflection for second set
394 |df3 flap deflection for third set
399 recordRate number of times to record data per second [/s]
400 recordStartTime time to start recording outpud data [s]
401 dyn_on_speed speed when dynamic pressure terms first computed [ft/s]
402 nondim_rate_V_rel_wind use V_rel_wind to compute control rates []
403 |simpleHingeMomentCoef hinge moment coefficient []
405 (3) | [OPTIONAL DATA]
406 =====================
408 An input line may also be used to provide optional data that
409 will be used if provided but is not necessary for the code to
410 operate. As with the variable data described in section (2), multiple
411 values or data files may be provided if the code is written to use
417 Appended comments should be provided with each input line to indicate
418 units on the variable in question and to indicate the source the data
420 **********************************************************************
422 **********************************************************************
423 III. Sample Input Lines:
428 geometry bw <value> # geometric parameter, wingspan
429 Cm Cm_a <value> # stability derivative, d(Cm)/d(alpha)
430 controlSurface de <value> <value> # max and min elevator deflections
435 CD CDfCL <file.dat> # CD(CL), drag polar data file
436 Cm Cmfade <file.dat> # Cm(alpha,delta_e), moment data file
441 CD CDfCL # CD(CL), drag calculated in code based on CL
442 (none currently in use)
444 **********************************************************************
446 **********************************************************************
447 IV. Input Line Definitions:
449 Of all the possible permutations of variable names described above in
450 section II, only some are curently implemented in the code. These are
451 described below. Comments, denoted by '#,' are used to define the
452 lines and to indicate examples of the data if additional clarity is
453 needed for unique situations. Again, those lines beginning with '|'
454 are not currently implemented in the code, but indicate planned
455 conventions in later versions.
457 # Key Variable Data Units Description Where Defined
458 #------------------------------------------------------------------------------------
460 init recordRate <recordRate> # [/s] record data n times per second uiuc_aircraft.h
462 # [s] time to start recording output data uiuc_aircraft.h
463 init recordStartTime <recordStartTime>
465 # [] use V_rel_wind to compute control rates (instead of U_body) uiuc_aircraft.h
466 init nondim_rate_V_rel_wind <nondim_rate_V_rel_wind>
468 # [ft/s] speed at which dynamic pressure terms are first computed uiuc_aircraft.h
469 init dyn_on_speed <dyn_on_speed>
471 init Dx_pilot <Dx_pilot> # [ft] reference pilot x-position ls_generic.h
472 init Dy_pilot <Dy_pilot> # [ft] reference pilot y-position ls_generic.h
473 init Dz_pilot <Dz_pilot> # [ft] reference pilot z-position ls_generic.h
475 # the following commands are currently conflicting with Flight
476 # Gear and are not working correctly:
477 |init Dx_cg <Dx_cg> # [ft] reference cg x_location ls_generic.h
478 |init Dy_cg <Dy_cg> # [ft] reference cg y_location ls_generic.h
479 |init Dz_cg <Dz_cg> # [ft] reference cg z_location ls_generic.h
480 |init V_north <V_north> # [ft/s] initial local x-velocity ls_generic.h
481 |init V_east <V_east> # [ft/s] initial local y-velocity ls_generic.h
482 |init V_down <V_down> # [ft/s] initial local z-velocity ls_generic.h
483 |init Altitude <Altitude> # [ft/s] initial altitude ls_generic.h
485 init P_body <P_body> # [rad/s] initial roll rate ls_generic.h
486 init Q_body <Q_body> # [rad/s] initial pitch rate ls_generic.h
487 init R_body <R_body> # [rad/s] initial yaw rate ls_generic.h
488 init Phi <Phi> # [rad] initial bank angle ls_generic.h
489 init Theta <Theta> # [rad] initial pitch attitude angle ls_generic.h
490 init Psi <Psi> # [rad] initial heading angle ls_generic.h
491 init Long_trim <Long_trim> # [rad] longitudinal trim ls_cockpit.h
493 geometry bw <bw> # [ft] wingspan uiuc_aircraft.h
494 geometry cbar <cbar> # [ft] wing mean aero chord uiuc_aircraft.h
495 geometry Sw <Sw> # [ft^2] wing reference area uiuc_aircraft.h
496 |geometry iw <iw> # [deg] wing incidence angle uiuc_aircraft.h
497 |geometry bc <bc> # [ft] canard span uiuc_aircraft.h
498 |geometry cc <cc> # [ft] canard chord uiuc_aircraft.h
499 |geometry Sc <Sc> # [sq-ft] canard area uiuc_aircraft.h
500 |geometry ic <ic> # [deg] canard incidence angle uiuc_aircraft.h
501 geometry bh <bh> # [ft] horizontal tail span uiuc_aircraft.h
502 geometry ch <ch> # [ft] horizontal tail chord uiuc_aircraft.h
503 geometry Sh <Sh> # [sq-ft] horizontal tail area uiuc_aircraft.h
504 geometry ih <ih> # [deg] horiz tail incidence angle uiuc_aircraft.h
505 |geometry bv <bv> # [ft] vertical tail span uiuc_aircraft.h
506 |geometry cv <cv> # [ft] vertical tail chord uiuc_aircraft.h
507 |geometry Sv <Sv> # [sq-ft] vertical tail area uiuc_aircraft.h
508 |geometry iv <iv> # [deg] vert tail incidence angle uiuc_aircraft.h
510 |controlSurface Se <Se> # [ft^2] elevator area uiuc_aircraft.h
511 |controlSurface Sa <Sa> # [ft^2] aileron area uiuc_aircraft.h
512 |controlSurface Sr <Sr> # [ft^2] rudder area uiuc_aircraft.h
513 |controlSurface Sf <Sf> # [ft^2] flap area uiuc_aircraft.h
514 controlSurface de <demax> <demin> # [deg] max/min elev deflections uiuc_aircraft.h
515 controlSurface da <damax> <damin> # [deg] max/min ail deflections uiuc_aircraft.h
516 controlSurface dr <drmax> <drmin> # [deg] max/min rud deflections uiuc_aircraft.h
517 |controlSurface df <dfmax> <dfmin> # [deg] max/min flap deflections uiuc_aircraft.h
519 # Note: Currently demin/damin/drmin are not used in the code, and the max/min is +-dema
521 # trim always set to some fixed input value (radians) [rad] uiuc_aircraft.h
522 controlSurface set_Long_trim <elevator_tab>
524 # trim always set to some fixed input value (degrees) [deg] uiuc_aircraft.h
525 controlSurface set_Long_trim_deg <elevator_tab>
527 controlSurface zero_Long_trim # [deg] trim always set to zero uiuc_aircraft.h
529 # elevator step input with deflection angle [deg] and starting time [s] uiuc_aircraft.h
530 controlSurface elevator_step <elevator_step_angle> <elevator_step_startTime>
532 # elevator singlet input with deflection angle [deg], starting time [s],
533 # and duration of input [s] uiuc_aircraft.h
534 controlSurface elevator_singlet <elevator_singlet_angle> ->
535 <elevator_singlet_startTime> <elevator_singlet_duration>
537 # elevator doublet input with deflection angle [deg], starting time [s],
538 # and TOTAL duration of input (both up and down deflections) [s] uiuc_aircraft.h
539 controlSurface elevator_doublet <elevator_doublet_angle> ->
540 <elevator_doublet_startTime> <elevator_doublet_duration>
542 # tabulated elevator input (as function of time) with conversion
543 # factor codes and starting time [s] uiuc_aircraft.h
544 controlSurface elevator_input <elevator_input_file> ->
545 <token_value_convert1> <token_value_convert2> ->
546 <elevator_input_startTime>
549 |controlsMixer nomix <?> # [] no controls mixing uiuc_aircraft.h
552 mass Weight <Weight> # [lb] gross takeoff weight uiuc_aircraft.h
553 mass Mass <Mass> # [slug] gross takeoff mass ls_generic.h
554 mass I_xx <I_xx> # [slug-ft^2] roll inertia ls_generic.h
555 mass I_yy <I_yy> # [slug-ft^2] pitch inertia ls_generic.h
556 mass I_zz <I_zz> # [slug-ft^2] yaw inertia ls_generic.h
557 mass I_xz <I_xz> # [slug-ft^2] lateral cross inertia ls_generic.h
560 # maximum and minimum engine thrust [lb] uiuc_aircraft.h
561 |engine thrust <thrustMax> <thrustMin>
563 # simple single engine maximum thrust [lb] uiuc_aircraft.h
564 engine simpleSingle <simpleSingleMaxThrust>
566 engine c172 # use Cessna 172 engine model of Tony Peden
567 engine cherokee # use Piper Cherokee engine model
570 CL CLo <CLo> # [] lift coef for all angles = 0 uiuc_aircraft.h
571 CL CL_a <CL_a> # [/rad] lift curve slope, d(CL)/d(alpha) uiuc_aircraft.h
572 CL CL_adot <CL_adot> # [/rad] d(CL)/d(alpha)/da(time) uiuc_aircraft.h
573 CL CL_q <CL_q> # [/rad] d(CL)/d(q) uiuc_aircraft.h
574 CL CL_ih <CL_ih> # [/rad] CL due to horiz tail incidence uiuc_aircraft.h
575 CL CL_de <CL_de> # [/rad] d(CL)/d(de) uiuc_aircraft.h
577 # CL(alpha), conversion for CL, for alpha [] uiuc_aircraft.h
578 CL CLfa <CLfa.dat> <token_value_convert1> <token_value_convert2>
580 # CL(alpha,delta_e), conversion for CL, for alpha, for delta_e [] uiuc_aircraft.h
581 CL CLfade <CLfade.dat> <token_value_convert1> <token_value_convert2> ->
582 <token_value_convert3>
584 # the following are lift coefficients in the body axis
585 CL CZo <CZo> # [] lift coef for all angles = 0 uiuc_aircraft.h
586 CL CZ_a <Cz_a> # [/rad] lift curve slope, d(CZ)/d(alpha) uiuc_aircraft.h
587 CL CZ_a2 <CZ_a2> # [/rad] d(CZ)/d(alpha squared) uiuc_aircraft.h
588 CL CZ_a3 <CZ_a3> # [/rad] d(CZ)/d(alpha cubed) uiuc_aircraft.h
589 CL CZ_adot <CZ_adot> # [/rad] d(CZ)/d(alpha)/d(time) uiuc_aircraft.h
590 CL CZ_q <CZ_q> # [/rad] d(CZ)/d(q) uiuc_aircraft.h
591 CL CZ_de <CZ_de> # [/rad] d(CZ)/d(de) uiuc_aircraft.h
592 CL CZ_deb2 <CZ_deb2> # [/rad] d(CZ)/d(de, beta squared) uiuc_aircraft.h
593 CL CZ_df <CZ_df> # [/rad] d(CZ)/d(df) uiuc_aircraft.h
594 CL CZ_adf <CZ_adf> # [/rad] d(CZ)/d(alpha, df) uiuc_aircraft.h
596 |CL CLfCT <CLfCT.dat> # CL(thrust coef) uiuc_aircraft.h
597 |CL CLfRe # CL(Reynolds #), equation uiuc_aircraft.h
598 |CL CL_afaM <CL_afaM.dat> # CL_alpha(alpha,Mach #) uiuc_aircraft.h
599 # these are sample examples that might be used in later versions of the code
602 # note that CD terms must come after CL for induced drag to be computed
603 CD CDo <CDo> # [] drag coef for all angles = 0 uiuc_aircraft.h
604 CD CDK <CDK> # [] induced drag constant 1/(pi*e*AR) uiuc_aircraft.h
605 CD CD_a <CD_a> # [/rad] d(CD)/d(alpha) uiuc_aircraft.h
606 CD CD_ih <CD_ih> # [/rad] CD due to horiz tail incidence uiuc_aircraft.h
607 CD CD_de <CD_de> # [/rad] d(CD)/d(delta_e) uiuc_aircraft.h
609 # CD(alpha), conversion for CD, for alpha [] uiuc_aircraft.h
610 CD CDfa <CDfa.dat> <token_value_convert1> <token_value_convert2>
612 # CD(CL) drag polar, conversion for CD, for CL [] uiuc_aircraft.h
613 CD CDfCL <CDfCL.dat> <token_value_convert1> <token_value_convert2>
615 # CD(alpha,delta_e), conversion for CD, for alpha, for delta_e [] uiuc_aircraft.h
616 CD CDfade <CDfade.dat> <token_value_convert1> <token_value_convert2> ->
617 <token_value_convert3>
619 # the following are drag coefficients in the body axis
620 CD CXo <CXo> # [] drag coef for all angles = 0 uiuc_aircraft.h
621 CD CXK <CXK> # [] induced drag constant 1/(pi*e*AR) uiuc_aircraft.h
622 CD CX_a <CX_a> # [/rad] d(CX)/d(alpha) uiuc_aircraft.h
623 CD CX_a2 <CX_a2> # [/rad] d(CX)/d(alpha squared) uiuc_aircraft.h
624 CD CX_a3 <CX_a3> # [/rad] d(CX)/d(alpha cubed) uiuc_aircraft.h
625 CD CX_q <CX_q> # [/rad] d(CX)/d(q) uiuc_aircraft.h
626 CD CX_de <CX_de> # [/rad] d(CX)/d(de) uiuc_aircraft.h
627 CD CX_dr <CX_dr> # [/rad] d(CX)/d(dr) uiuc_aircraft.h
628 CD CX_df <CX_df> # [/rad] d(CX)/d(df) uiuc_aircraft.h
629 CD CX_adf <CX_adf> # [/rad] d(CX)/d(alpha, df) uiuc_aircraft.h
632 Cm Cmo <Cmo> # [] pitch mom coef for all angles=0 uiuc_aircraft.h
633 Cm Cm_a <Cm_a> # [/rad] d(Cm)/d(alpha) uiuc_aircraft.h
634 Cm Cm_a2 <Cm_a2> # [/rad] d(Cm)/d(alpha squared) uiuc_aircraft.h
635 Cm Cm_adot <Cm_adot> # [/rad] d(Cm)/d(alpha)/d(time) uiuc_aircraft.h
636 Cm Cm_q <Cm_q> # [/rad] d(Cm)/d(q) uiuc_aircraft.h
637 Cm Cm_ih <Cm_ih> # [/rad] Cm due to horiz tail incidence uiuc_aircraft.h
638 Cm Cm_de <Cm_de> # [/rad] d(Cm)/d(de) uiuc_aircraft.h
639 Cm Cm_de <Cm_b2> # [/rad] d(Cm)/d(beta squared) uiuc_aircraft.h
640 Cm Cm_r <Cm_r> # [/rad] d(Cm)/d(r) uiuc_aircraft.h
641 Cm Cm_df <Cm_df> # [/rad] d(Cm)/d(df) uiuc_aircraft.h
643 # Cm(alpha), conversion for Cm, for alpha [] uiuc_aircraft.h
644 Cm Cmfa <Cmfa.dat> <token_value_convert1> <token_value_convert2>
646 # Cm(alpha,delta_e), conversion for Cm, for alpha, for delta_e [] uiuc_aircraft.h
647 Cm Cmfade <Cmfade.dat> <token_value_convert1> <token_value_convert2> ->
648 <token_value_convert3>
651 CY CYo <CYo> # [] side-force coef for all angles=0 uiuc_aircraft.h
652 CY CY_beta <CY_beta> # [/rad] d(CY)/d(beta) uiuc_aircraft.h
653 CY CY_p <CY_p> # [/rad] d(CY)/d(p) uiuc_aircraft.h
654 CY CY_r <CY_r> # [/rad] d(CY)/d(r) uiuc_aircraft.h
655 CY CY_da <CY_da> # [/rad] d(CY)/d(da) uiuc_aircraft.h
656 CY CY_dr <CY_dr> # [/rad] d(CY)/d(dr) uiuc_aircraft.h
657 CY CY_dra <CY_dra> # [/rad] d(CY)/d(dr, alpha) uiuc_aircraft.h
658 CY CY_dra <CY_bdot> # [/rad] d(CY)/d(beta)/d(time) uiuc_aircraft.h
660 # CY(alpha,delta_a), conversion for CY, for alpha, for delta_a [] uiuc_aircraft.h
661 CY CYfada <CYfada.dat> <token_value_convert1> <token_value_convert2> ->
662 <token_value_convert3>
664 # CY(beta,delta_r), conversion for CY, for beta, for delta_r [] uiuc_aircraft.h
665 CY CYfbetadr <CYfbetadr.dat> <token_value_convert1> <token_value_convert2> ->
666 <token_value_convert3>
669 Cl Clo <Clo> # [] roll mom coef for all angles=0 uiuc_aircraft.h
670 Cl Cl_beta <Cl_beta> # [/rad] d(Cl)/d(beta) uiuc_aircraft.h
671 Cl Cl_p <Cl_p> # [/rad] d(Cl)/d(p) uiuc_aircraft.h
672 Cl Cl_r <Cl_r> # [/rad] d(Cl)/d(r) uiuc_aircraft.h
673 Cl Cl_da <Cl_da> # [/rad] d(Cl)/d(da) uiuc_aircraft.h
674 Cl Cl_dr <Cl_dr> # [/rad] d(Cl)/d(dr) uiuc_aircraft.h
675 Cl Cl_daa <Cl_daa> # [/rad] d(Cl)/d(da, alpha) uiuc_aircraft.h
677 # Cl(alpha,delta_a), conversion for Cl, for alpha, for delta_a [] uiuc_aircraft.h
678 Cl Clfada <CYfada.dat> <token_value_convert1> <token_value_convert2> ->
679 <token_value_convert3>
681 # Cl(beta,delta_r), conversion for Cl, for beta, for delta_r [] uiuc_aircraft.h
682 Cl Clfbetadr <CYfbetadr.dat> <token_value_convert1> <token_value_convert2> ->
683 <token_value_convert3>
686 Cn Cno <Cno> # [] yaw mom coef for all angles=0 uiuc_aircraft.h
687 Cn Cn_beta <Cn_beta> # [/rad] d(Cn)/d(beta) uiuc_aircraft.h
688 Cn Cn_p <Cn_p> # [/rad] d(Cn)/d(p) uiuc_aircraft.h
689 Cn Cn_r <Cn_r> # [/rad] d(Cn)/d(r) uiuc_aircraft.h
690 Cn Cn_da <Cn_da> # [/rad] d(Cn)/d(da) uiuc_aircraft.h
691 Cn Cn_dr <Cn_dr> # [/rad] d(Cn)/d(dr) uiuc_aircraft.h
692 Cn Cn_q <Cn_q> # [/rad] d(Cn)/d(q) uiuc_aircraft.h
693 Cn Cn_b3 <Cn_b3> # [/rad] d(Cn)/d(beta cubed) uiuc_aircraft.h
695 # Cn(alpha,delta_a), conversion for Cn, for alpha, for delta_a [] uiuc_aircraft.h
696 Cn Cnfada <Cnfada.dat> <token_value_convert1> <token_value_convert2> ->
697 <token_value_convert3>
699 # Cn(beta,delta_r), conversion for Cn, for beta, for delta_r [] uiuc_aircraft.h
700 Cn Cnfbetadr <Cnfbetadr.dat> <token_value_convert1> <token_value_convert2> ->
701 <token_value_convert3>
703 =============================CONVERSION CODES================================
705 To calculate the aero forces, angles (eg, alfa, beta, elevator deflection, etc)
706 must be in radians. To convert input data in degree to radian, use a
707 conversion code of 1. To use no conversion, use a conversion code of 0.
709 ------------------------------------------------
711 ------------------------------------------------
712 0 no conversion (multiply by 1)
713 1 convert degrees to radians
714 =============================================================================
716 |gear kgear <kgear> # [] gear spring constant(s) uiuc_aircraft.h
717 |gear muRoll <muRoll> # [] gear rolling friction coef(s) uiuc_aircraft.h
718 |gear cgear <cgear> # [] gear damping constant(s) uiuc_aircraft.h
719 |gear strutLength <sL> # [ft] gear strut length uiuc_aircraft.h
722 ice iceTime <iceTime> # [s] time when icing begins uiuc_aircraft.h
724 # [s] period for eta_ice to reach eta_final uiuc_aircraft.h
725 ice transientTime <transientTime>
727 # [] icing severity factor uiuc_aircraft.h
728 ice eta_ice_final <eta_ice_final>
730 ice kCDo <kCDo> # [] icing constant for CDo uiuc_aircraft.h
731 ice kCDK <kCDo> # [] icing constant for CDK uiuc_aircraft.h
732 ice kCD_a <kCD_a> # [] icing constant for CD_a uiuc_aircraft.h
733 ice kCD_q <kCD_q> # [] icing constant for CD_q uiuc_aircraft.h
734 ice kCD_de <kCD_de> # [] icing constant for CD_de uiuc_aircraft.h
735 ice kCD_dr <kCD_dr> # [] icing constant for CD_dr uiuc_aircraft.h
736 ice kCD_df <kCD_df> # [] icing constant for CD_df uiuc_aircraft.h
737 ice kCD_adf <kCD_adf> # [] icing constant for CD_adf uiuc_aircraft.h
739 ice kCXo <kCXo> # [] icing constant for CXo uiuc_aircraft.h
740 ice kCXK <kCXo> # [] icing constant for CXK uiuc_aircraft.h
741 ice kCX_a <kCX_a> # [] icing constant for CX_a uiuc_aircraft.h
742 ice kCX_a2 <kCX_a2> # [] icing constant for CX_a2 uiuc_aircraft.h
743 ice kCX_a3 <kCX_a3> # [] icing constant for CX_a3 uiuc_aircraft.h
744 ice kCX_q <kCX_q> # [] icing constant for CX_q uiuc_aircraft.h
745 ice kCX_de <kCX_de> # [] icing constant for CX_de uiuc_aircraft.h
746 ice kCX_dr <kCX_dr> # [] icing constant for CX_dr uiuc_aircraft.h
747 ice kCX_df <kCX_df> # [] icing constant for CX_df uiuc_aircraft.h
748 ice kCX_adf <kCX_adf> # [] icing constant for CX_adf uiuc_aircraft.h
750 ice kCLo <kCLo> # [] icing constant for CLo uiuc_aircraft.h
751 ice kCL_a <kCL_a> # [] icing constant for CL_a uiuc_aircraft.h
752 ice kCL_adot <kCL_adot> # [] icing constant for CL_adot uiuc_aircraft.h
753 ice kCL_q <kCL_q> # [] icing constant for CL_q uiuc_aircraft.h
754 ice kCL_de <kCL_de> # [] icing constant for CL_de uiuc_aircraft.h
755 ice kCL_df <kCL_df> # [] icing constant for CL_df uiuc_aircraft.h
756 ice kCL_adf <kCL_adf> # [] icing constant for CL_adf uiuc_aircraft.h
758 ice kCZo <kCZo> # [] icing constant for CZo uiuc_aircraft.h
759 ice kCZ_a <kCZ_a> # [] icing constant for CZ_a uiuc_aircraft.h
760 ice kCZ_a2 <kCZ_a2> # [] icing constant for CZ_a2 uiuc_aircraft.h
761 ice kCZ_a3 <kCZ_a3> # [] icing constant for CZ_a3 uiuc_aircraft.h
762 ice kCZ_adot <kCZ_adot> # [] icing constant for CZ_adot uiuc_aircraft.h
763 ice kCZ_q <kCZ_q> # [] icing constant for CZ_q uiuc_aircraft.h
764 ice kCZ_de <kCZ_de> # [] icing constant for CZ_de uiuc_aircraft.h
765 ice kCZ_df <kCZ_df> # [] icing constant for CZ_df uiuc_aircraft.h
766 ice kCZ_adf <kCZ_adf> # [] icing constant for CZ_adf uiuc_aircraft.h
767 ice kCZ_deb2 <kCZ_deb2> # [] icing constant for CZ_deb2 uiuc_aircraft.h
769 ice kCmo <kCmo> # [] icing constant for Cmo uiuc_aircraft.h
770 ice kCm_a <kCm_a> # [] icing constant for Cm_a uiuc_aircraft.h
771 ice kCm_a2 <kCm_a2> # [] icing constant for Cm_a2 uiuc_aircraft.h
772 ice kCm_a3 <kCm_a3> # [] icing constant for Cm_a3 uiuc_aircraft.h
773 ice kCm_adot <kCm_adot> # [] icing constant for Cm_adot uiuc_aircraft.h
774 ice kCm_q <kCm_q> # [] icing constant for Cm_q uiuc_aircraft.h
775 ice kCm_r <kCm_r> # [] icing constant for Cm_r uiuc_aircraft.h
776 ice kCm_de <kCm_de> # [] icing constant for Cm_de uiuc_aircraft.h
777 ice kCm_df <kCm_df> # [] icing constant for Cm_df uiuc_aircraft.h
779 ice kCYo <kCYo> # [] icing constant for CYo uiuc_aircraft.h
780 ice kCY_beta <kCy_beta> # [] icing constant for CY_beta uiuc_aircraft.h
781 ice kCY_p <kCY_p> # [] icing constant for CY_p uiuc_aircraft.h
782 ice kCY_r <kCY_r> # [] icing constant for CY_r uiuc_aircraft.h
783 ice kCY_da <kCY_da> # [] icing constant for CY_da uiuc_aircraft.h
784 ice kCY_dr <kCY_dr> # [] icing constant for CY_dr uiuc_aircraft.h
785 ice kCY_dra <kCY_dra> # [] icing constant for CY_dra uiuc_aircraft.h
786 ice kCY_bdot <kCY_bdot> # [] icing constant for CY_bdot uiuc_aircraft.h
788 ice kClo <kClo> # [] icing constant for Clo uiuc_aircraft.h
789 ice kCl_beta <kCl_beta> # [] icing constant for Cl_beta uiuc_aircraft.h
790 ice kCl_p <kCl_p> # [] icing constant for Cl_p uiuc_aircraft.h
791 ice kCl_r <kCl_r> # [] icing constant for Cl_r uiuc_aircraft.h
792 ice kCl_da <kCl_da> # [] icing constant for Cl_da uiuc_aircraft.h
793 ice kCl_dr <kCl_dr> # [] icing constant for Cl_dr uiuc_aircraft.h
794 ice kCl_daa <kCl_daa> # [] icing constant for Cl_daa uiuc_aircraft.h
796 ice kCno <kCno> # [] icing constant for Cno uiuc_aircraft.h
797 ice kCn_beta <kCn_beta> # [] icing constant for Cn_beta uiuc_aircraft.h
798 ice kCn_b3 <kCn_b3> # [] icing constant for Cn_b3 uiuc_aircraft.h
799 ice kCn_p <kCn_p> # [] icing constant for Cn_p uiuc_aircraft.h
800 ice kCn_q <kCn_q> # [] icing constant for Cn_q uiuc_aircraft.h
801 ice kCn_r <kCn_r> # [] icing constant for Cn_r uiuc_aircraft.h
802 ice kCn_da <kCn_da> # [] icing constant for Cn_da uiuc_aircraft.h
803 ice kCn_dr <kCn_dr> # [] icing constant for Cn_dr uiuc_aircraft.h
805 ice beta_probe_wing <x_probe_wing> # wing flow angle probe location uiuc_aircraft.h
806 ice beta_probe_wing <x_probe_tail> # tail flow angle probe location uiuc_aircraft.h
809 record Simtime # [s] current sim time global
810 record dt # [s] current time step global
811 record Weight # [lb] aircraft gross takeoff weight uiuc_aircraft.h
812 record Mass # [slug] aircraft mass ls_generic.h
813 record I_xx # [slug-ft^2] roll inertia ls_generic.h
814 record I_yy # [slug-ft^2] pitch inertia ls_generic.h
815 record I_zz # [slug-ft^2] yaw inertia ls_generic.h
816 record I_xz # [slug-ft^2] lateral cross inertia ls_generic.h
817 record Dx_pilot # [ft] reference pilot x-location ls_generic.h
818 record Dy_pilot # [ft] reference pilot y-location ls_generic.h
819 record Dz_pilot # [ft] reference pilot z-location ls_generic.h
820 record Dx_cg # [ft] cg x_location ls_generic.h
821 record Dy_cg # [ft] cg y_location ls_generic.h
822 record Dz_cg # [ft] cg z_location ls_generic.h
823 record Lat_geocentric # [rad] geocentric latitude ls_generic.h
824 record Lon_geocentric # [rad] geocentric longitude ls_generic.h
825 record Radius_to_vehicle # [ft] geocentric distance ls_generic.h
826 record Latitude # [rad] geodetic latitude ls_generic.h
827 record Longitude # [rad] geodetic longitude ls_generic.h
828 record Altitude # [ft] geodetic altitude ls_generic.h
829 record Phi # [rad] Euler bank angle ls_generic.h
830 record Theta # [rad] Euler pitch attitude angle ls_generic.h
831 record Psi # [rad] Euler heading angle ls_generic.h
832 record V_dot_north # [ft/s^2] local x-acceleration ls_generic.h
833 record V_dot_east # [ft/s^2] local y-acceleration ls_generic.h
834 record V_dot_down # [ft/s^2] local z-acceleration ls_generic.h
835 record U_dot_body # [ft/s^2] body x-acceleration ls_generic.h
836 record V_dot_body # [ft/s^2] body y-acceleration ls_generic.h
837 record W_dot_body # [ft/s^2] body z-acceleration ls_generic.h
838 record A_X_pilot # [ft/s^2] pilot x-acceleration ls_generic.h
839 record A_Y_pilot # [ft/s^2] pilot y-acceleration ls_generic.h
840 record A_Z_pilot # [ft/s^2] pilot z-acceleration ls_generic.h
841 record A_X_cg # [ft/s^2] cg x-acceleration ls_generic.h
842 record A_Y_cg # [ft/s^2] cg y-acceleration ls_generic.h
843 record A_Z_cg # [ft/s^2] cg z-acceleration ls_generic.h
844 record N_X_pilot # [ft/s^2] pilot x-acceleration ls_generic.h
845 record N_Y_pilot # [ft/s^2] pilot y-acceleration ls_generic.h
846 record N_Z_pilot # [ft/s^2] pilot z-acceleration ls_generic.h
847 record N_X_cg # [ft/s^2] cg x-acceleration ls_generic.h
848 record N_Y_cg # [ft/s^2] cg y-acceleration ls_generic.h
849 record N_Z_cg # [ft/s^2] cg z-acceleration ls_generic.h
850 record P_dot_body # [rad/s^2] roll rate acceleration ls_generic.h
851 record Q_dot_body # [rad/s^2] pitch rate acceleration ls_generic.h
852 record R_dot_body # [rad/s^2] yaw rate acceleration ls_generic.h
853 record V_north # [ft/s] local x-velocity ls_generic.h
854 record V_east # [ft/s] local y-velocity ls_generic.h
855 record V_down # [ft/s] local z-velocity ls_generic.h
856 record V_north_rel_ground # [ft/s] local x-velocity wrt ground ls_generic.h
857 record V_east_rel_ground # [ft/s] local y-velocity wrt ground ls_generic.h
858 record V_down_rel_ground # [ft/s] local z-velocity wrt ground ls_generic.h
859 record V_north_airmass # [ft/s] local x-velocity of airmass ls_generic.h
860 record V_east_airmass # [ft/s] local y-velocity of airmass ls_generic.h
861 record V_down_airmass # [ft/s] local z-velocity of airmass ls_generic.h
862 record V_north_rel_airmass # [ft/s] local x-velocity wrt airmass ls_generic.h
863 record V_east_rel_airmass # [ft/s] local y-velocity wrt airmass ls_generic.h
864 record V_down_rel_airmass # [ft/s] local z-velocity wrt airmass ls_generic.h
865 record U_gust # [ft/s] local turbulence x-velocity ls_generic.h
866 record V_gust # [ft/s] local turbulence y-velocity ls_generic.h
867 record W_gust # [ft/s] local turbulence z-velocity ls_generic.h
868 record U_body # [ft/s] wind x-velocity in body axis ls_generic.h
869 record V_body # [ft/s] wind y-velocity in body axis ls_generic.h
870 record W_body # [ft/s] wind z-velocity in body axis ls_generic.h
871 record V_rel_wind # [ft/s] total freestream velocity ls_generic.h
872 record V_true_kts # [kts] true velocity ls_generic.h
873 record V_rel_ground # [ft/s] total velocity wrt ground ls_generic.h
874 record V_inertial # [ft/s] total inertial velocity ls_generic.h
875 record V_ground_speed # [ft/s] airspeed wrt ground ls_generic.h
876 record V_equiv # [ft/s] equivalent airspeed ls_generic.h
877 record V_equiv_kts # [kts] equivalent airspeed ls_generic.h
878 record V_calibrated # [ft/s] calibrated airspeed ls_generic.h
879 record V_calibrated_kts # [kts] calibrated airspeed ls_generic.h
880 record P_local # [rad/s] local roll rate ls_generic.h
881 record Q_local # [rad/s] local pitch rate ls_generic.h
882 record R_local # [rad/s] local yaw rate ls_generic.h
883 record P_body # [rad/s] body roll rate ls_generic.h
884 record Q_body # [rad/s] body pitch rate ls_generic.h
885 record R_body # [rad/s] body yaw rate ls_generic.h
886 record P_total # [rad/s] total roll rate ls_generic.h
887 record Q_total # [rad/s] total pitch rate ls_generic.h
888 record R_total # [rad/s] total yaw rate ls_generic.h
889 record Phi_dot # [rad/s] bank angle rate ls_generic.h
890 record Theta_dot # [rad/s] pitch attitude angle rate ls_generic.h
891 record Psi_dot # [rad/s] heading angle rate ls_generic.h
892 record Latitude_dot # [rad/s] latitude rate ls_generic.h
893 record Longitude_dot # [rad/s] longitude rate ls_generic.h
894 record Radius_dot # [rad/s] radius rate ls_generic.h
895 record Alpha # [rad] angle of attack ls_generic.h
896 record Alpha_deg # [deg] angle of attack (in degrees) uiuc_aircraft.h
897 record Alpha_dot # [rad/s] rate of change of alpha ls_generic.h
898 record Alpha_dot_deg # [rad/s] rate of change of alpha uiuc_aircraft.h
899 record Beta # [rad] sideslip angle ls_generic.h
900 record Beta_deg # [rad] sideslip angle uiuc_aircraft.h
901 record Beta_dot # [rad/s] rate of change of beta ls_generic.h
902 record Beta_dot_deg # [rad/s] rate of change of beta uiuc_aircraft.h
903 record Gamma_vert # [rad] vertical flight path angle ls_generic.h
904 record Gamma_vert_deg # [deg] vertical flight path angle uiuc_aircraft.h
905 record Gamma_horiz # [rad] horizontal flight path angle ls_generic.h
906 record Gamma_horiz_deg # [deg] horizontal flight path angle uiuc_aircraft.h
907 record Density # [slug/ft^3] air density ls_generic.h
908 record V_sound # [ft/s] speed of sound ls_generic.h
909 record Mach_number # [] Mach number ls_generic.h
910 record Static_pressure # [lb/ft^2] static pressure ls_generic.h
911 record Total_pressure # [lb/ft^2] total pressure ls_generic.h
912 record Impact_pressure # [lb/ft^2] impact pressure ls_generic.h
913 record Dynamic_pressure # [lb/ft^2] dynamic pressure ls_generic.h
914 record Static_temperature # [?] static temperature ls_generic.h
915 record Total_temperature # [?] total temperature ls_generic.h
916 record Gravity # [ft/s^2] acceleration due to gravity ls_generic.h
917 record Sea_level_radius # [ft] Earth radius ls_generic.h
918 record Earth_position_angle # [rad] Earth rotation angle ls_generic.h
919 record Runway_altitude # [ft] runway altitude ls_generic.h
920 record Runway_latitude # [rad] runway latitude ls_generic.h
921 record Runway_longitude # [rad] runway longititude ls_generic.h
922 record Runway_heading # [rad] runway heading ls_generic.h
923 record Radius_to_rwy # [ft] geocentric radius to runway ls_generic.h
924 record D_pilot_north_of_rwy # [ft] local pilot x-dist from rwy ls_generic.h
925 record D_pilot_east_of_rwy # [ft] local pilot y-dist from rwy ls_generic.h
926 record D_pilot_down_of_rwy # [ft] local pilot z-dist from rwy ls_generic.h
927 record X_pilot_rwy # [ft] pilot x-dist from rwy ls_generic.h
928 record Y_pilot_rwy # [ft] pilot y-dist from rwy ls_generic.h
929 record H_pilot_rwy # [ft] pilot z-dist from rwy ls_generic.h
930 record D_cg_north_of_rwy # [ft] local cg x-dist from rwy ls_generic.h
931 record D_cg_east_of_rwy # [ft] local cg y-dist from rwy ls_generic.h
932 record D_cg_down_of_rwy # [ft] local cg z-dist from rwy ls_generic.h
933 record X_cg_rwy # [ft] cg x-dist from rwy ls_generic.h
934 record Y_cg_rwy # [ft] cg y-dist from rwy ls_generic.h
935 record H_cg_rwy # [ft] cg z-dist from rwy ls_generic.h
936 record Throttle_pct # [%] throttle input ls_cockpit.h
937 record Throttle_3 # [%] throttle deflection ls_cockpit.h
938 record Long_control # [] pitch input ls_cockpit.h
939 record Long_trim # [rad] longitudinal trim ls_cockpit.h
940 record Long_trim_deg # [deg] longitudinal trim uiuc_aircraft.h
941 record elevator # [rad] elevator deflection uiuc_aircraft.h
942 record elevator_deg # [deg] elevator deflection uiuc_aircraft.h
943 record Lat_control # [] roll input ls_cockpit.h
944 record aileron # [rad] aileron deflection uiuc_aircraft.h
945 record aileron_deg # [deg] aileron deflection uiuc_aircraft.h
946 record Rudder_pedal # [] yaw input ls_cockpit.h
947 record rudder # [rad] rudder deflection uiuc_aircraft.h
948 record rudder_deg # [deg] rudder deflection uiuc_aircraft.h
949 record CDfaI # [] CD(alpha) uiuc_aircraft.h
950 record CDfCLI # [] CD(CL), drag polar uiuc_aircraft.h
951 record CDfadeI # [] CD(alpha,delta_e) uiuc_aircraft.h
952 record CD # [] drag coefficient uiuc_aircraft.h
953 record CLfaI # [] CL(alpha) uiuc_aircraft.h
954 record CLfadeI # [] CL(alpha,delta_e) uiuc_aircraft.h
955 record CL # [] lift coefficient uiuc_aircraft.h
956 record CmfaI # [] Cm(alpha) uiuc_aircraft.h
957 record CmfadeI # [] Cm(alpha,delta_e) uiuc_aircraft.h
958 record Cm # [] pitch moment coefficient uiuc_aircraft.h
959 record CYfadaI # [] CY(alpha,delta_a) uiuc_aircraft.h
960 record CYfbetadrI # [] CY(beta,delta_r) uiuc_aircraft.h
961 record CY # [] side-force coefficient uiuc_aircraft.h
962 record ClfadaI # [] Cl(alpha,delta_a) uiuc_aircraft.h
963 record ClfbetadrI # [] Cl(beta,delta_r) uiuc_aircraft.h
964 record Cl # [] roll moment coefficient uiuc_aircraft.h
965 record CnfadaI # [] Cn(alpha,delta_a) uiuc_aircraft.h
966 record CnfbetadrI # [] Cn(beta,delta_r) uiuc_aircraft.h
967 record Cn # [] yaw moment coefficient uiuc_aircraft.h
968 record CLclean_wing # [] wing clean lift coefficient uiuc_aircraft.h
969 record CLiced_wing # [] wing iced lift coefficient uiuc_aircraft.h
970 record CLclean_tail # [] tail clean lift coefficient uiuc_aircraft.h
971 record CLiced_tail # [] tail iced lift coefficient uiuc_aircraft.h
972 record Lift_clean_wing # [lb] wing clean lift force uiuc_aircraft.h
973 record Lift_iced_wing # [lb] wing iced lift force uiuc_aircraft.h
974 record Lift_clean_tail # [lb] tail clean lift force uiuc_aircraft.h
975 record Lift_iced_tail # [lb] tail iced lift force uiuc_aircraft.h
976 record Gamma_clean_wing # [ft^2/s] wing clean circulation uiuc_aircraft.h
977 record Gamma_iced_wing # [ft^2/s] wing iced circulation uiuc_aircraft.h
978 record Gamma_clean_tail # [ft^2/s] tail clean circulation uiuc_aircraft.h
979 record Gamma_iced_tail # [ft^2/s] tail iced circulation uiuc_aircraft.h
980 record w_clean_wing # [ft/s] wing clean downwash uiuc_aircraft.h
981 record w_iced_wing # [ft/s] wing iced downwash uiuc_aircraft.h
982 record w_clean_tail # [ft/s] tail clean downwash uiuc_aircraft.h
983 record w_iced_tail # [ft/s] tail iced downwash uiuc_aircraft.h
984 record V_total_clean_wing # [ft/s] wing clean velocity uiuc_aircraft.h
985 record V_total_iced_wing # [ft/s] wing iced velocity uiuc_aircraft.h
986 record V_total_clean_tail # [ft/s] tail clean velocity uiuc_aircraft.h
987 record V_total_iced_tail # [ft/s] tail iced velocity uiuc_aircraft.h
988 record beta_flow_clean_wing # [rad] wing clean flow angle uiuc_aircraft.h
989 record beta_flow_clean_wing_deg # [deg] wing clean flow angle uiuc_aircraft.h
990 record beta_flow_iced_wing # [rad] wing iced flow angle uiuc_aircraft.h
991 record beta_flow_iced_wing_deg # [deg] wing iced flow angle uiuc_aircraft.h
992 record beta_flow_clean_tail # [rad] tail clean flow angle uiuc_aircraft.h
993 record beta_flow_clean_tail_deg # [deg] tail clean flow angle uiuc_aircraft.h
994 record beta_flow_iced_tail # [rad] tail iced flow angle uiuc_aircraft.h
995 record beta_flow_iced_tail_deg # [deg] tail iced flow angle uiuc_aircraft.h
996 record Dbeta_flow_wing # [rad] difference in wing flow angle uiuc_aircraft.h
997 record Dbeta_flow_wing_deg # [deg] difference in wing flow angle uiuc_aircraft.h
998 record Dbeta_flow_tail # [rad] difference in tail flow angle uiuc_aircraft.h
999 record Dbeta_flow_tail_deg # [deg] difference in tail flow angle uiuc_aircraft.h
1000 record pct_beta_flow_wing # [%] difference in wing flow angle uiuc_aircraft.h
1001 record pct_beta_flow_tail # [%] difference in tail flow angle uiuc_aircraft.h
1002 record F_X_wind # [lb] aero x-force in wind-axes ls_generic.h
1003 record F_Y_wind # [lb] aero y-force in wind-axes ls_generic.h
1004 record F_Z_wind # [lb] aero z-force in wind-axes ls_generic.h
1005 record F_X_aero # [lb] aero x-force in body-axes ls_generic.h
1006 record F_Y_aero # [lb] aero y-force in body-axes ls_generic.h
1007 record F_Z_aero # [lb] aero z-force in body-axes ls_generic.h
1008 record F_X_engine # [lb] prop x-force in body-axes ls_generic.h
1009 record F_Y_engine # [lb] prop y-force in body-axes ls_generic.h
1010 record F_Z_engine # [lb] prop z-force in body-axes ls_generic.h
1011 record F_X_gear # [lb] gear x-force in body-axes ls_generic.h
1012 record F_Y_gear # [lb] gear y-force in body-axes ls_generic.h
1013 record F_Z_gear # [lb] gear z-force in body-axes ls_generic.h
1014 record F_X # [lb] total x-force in body-axes ls_generic.h
1015 record F_Y # [lb] total y-force in body-axes ls_generic.h
1016 record F_Z # [lb] total z-force in body-axes ls_generic.h
1017 record F_nort # [lb] total x-force in local-axes ls_generic.h
1018 record F_east # [lb] total y-force in local-axes ls_generic.h
1019 record F_down # [lb] total z-force in local-axes ls_generic.h
1020 record M_l_aero # [ft-lb] aero roll mom in body axes ls_generic.h
1021 record M_m_aero # [ft-lb] aero pitch mom in body axes ls_generic.h
1022 record M_n_aero # [ft-lb] aero yaw mom in body axes ls_generic.h
1023 record M_l_engine # [ft-lb] prop roll mom in body axes ls_generic.h
1024 record M_m_engine # [ft-lb] prop pitch mom in body axes ls_generic.h
1025 record M_n_engine # [ft-lb] prop yaw mom in body axes ls_generic.h
1026 record M_l_gear # [ft-lb] gear roll mom in body axes ls_generic.h
1027 record M_m_gear # [ft-lb] gear pitch mom in body axes ls_generic.h
1028 record M_n_gear # [ft-lb] gear yaw mom in body axes ls_generic.h
1029 record M_l_rp # [ft-lb] total roll mom in body axes ls_generic.h
1030 record M_m_rp # [ft-lb] total pitch mom in body axes ls_generic.h
1031 record M_n_rp # [ft-lb] total yaw mom in body axes ls_generic.h
1034 # the following command is implemented but the data is not used in any
1035 # equation of motion
1036 # hinge moment coefficient [] uiuc_aircraft.h
1037 |misc simpleHingeMomentCoef <simpleHingeMomentCoef>
1039 **********************************************************************
1041 **********************************************************************
1044 The following data is required for the simulator to function;
1045 otherwise either the UIUC Aero Model or LaRCsim parts of the code will
1048 1) aircraft geometry (UIUC Aero Model)
1050 cbar mean aerodynamic chord [ft]
1051 Sw wing planform area [ft^2]
1053 2) engine properties (UIUC Engine Model)
1054 (some engine model must be specified, such as...)
1059 3) mass variables (LaRCsim)
1060 Weight aircraft gross takeoff weight [lb]
1062 Mass aircraft mass [slug]
1063 I_xx roll inertia [slug-ft^2]
1064 I_yy pitch inertia [slug-ft^2]
1065 I_zz yaw inertia [slug-ft^2]
1066 I_xz lateral cross inertia [slug-ft^2]
1068 4) aerodynamic force/moment components (Aero Model)
1069 CLo lift coef for all angles = 0 []
1070 CL_a lift curve slope, d(CL)/d(alpha) [/rad]
1071 CDo drag coef for all angles = 0 []
1072 CDK induced drag constant []
1074 CD_a d(CD)/d(alpha) [/rad]
1075 Cmo pitch mom coef for all angles=0 []
1076 Cm_a d(Cm)/d(alpha) [/rad]
1077 CY_beta d(CY)/d(beta) [/rad]
1078 Cl_beta d(Cl)/d(beta) [/rad]
1079 Cn_beta d(Cn)/d(beta) [/rad]
1081 5) gear properties (none yet)
1083 With the current version, the C172 model gear model is used for *ALL*
1084 aircraft. This can produce some interesting effects with heavy
1085 aircraft (eg, Convair model), and light aircraft (eg, Pioneer UAV)
1087 **********************************************************************