src/FDM/UIUCModel/Documentation/README-uiucDoc.txt

   1 ************************************************
   2 *                                              *
   3 *  FGFS Reconfigurable Aircraft Flight Model   *
   4 *  Input File Documentation                    *
   5 *  Version 0.73, June 27, 2000                 *
   6 *                                              *
   7 *  Authors:                                    *
   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  *
  13 *  Urbana, IL                                  *
  14 *  http://amber.aae.uiuc.edu/~m-selig          *
  15 *                                              *
  16 ************************************************
  17
  18
  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
  26        time.
  27 **********************************************************************
  28
  29 **********************************************************************
  30 This documentation includes:
  31  - Required and optional input lines.
  32  - Input line formats and conventions.
  33
  34   Viewing this file in emacs makefile-mode with color makes this file
  35   easier to read.
  36 **********************************************************************
  37
  38 **********************************************************************
  39 I. Conventions and Notations and Reading this Document:
  40
  41  # ...     Comments
  42  |         Input line not yet implemented
  43  |         Optional data
  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
  48  ||        Option disabled
  49  ...       Repeat similar data
  50  ->        Continue onto next line
  51 **********************************************************************
  52
  53 **********************************************************************
  54 II. General Input Line Format:
  55
  56 Examples input lines include
  57
  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
  61
  62 These follow the more general input line form
  63
  64 keyword  variableName  <value -or- file> | ->
  65     <value -or- file>  # [units]  <data source>
  66
  67 Each term of the input line will be discussed in turn.
  68
  69 (1) KEYWORDS
  70 ============
  71
  72 There currently exist the following variable keyword types:
  73
  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
  90
  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.
  94
  95 (2) VARIABLE NAMES
  96 ==================
  97
  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.
 105
 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.
 109
 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)).
 113
 114 The conventions used for naming the variables are provided below.
 115 Several of these variable names are not currently used.
 116
 117 1) variable class
 118 _                   denotes stability derivative
 119 f                   "function of" (indicates data table)
 120
 121 2) timing data (global simulator variables)
 122 Simtime             current simulator time                  [s]
 123 dt                  current simulator time step             [s]
 124
 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]
 135
 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]
 158
 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]
 202
 203 6) angles
 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]
 216
 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                 []
 221 M                   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?]
 229
 230 8) Earth properties
 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]
 251
 252 9) aircraft geometric variables
 253 bw        wingspan                              [ft]
 254 cbar      mean aerodynamic chord                [ft]
 255 Sw        wing planform area                    [ft^2]
 256 |iw       wing incidence angle                  [deg]
 257 |bc       canard span                           [ft]
 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]
 275
 276 10) aircraft control surface properties
 277 |Sa            aileron area                     [ft^2]
 278 |Se            elevator area                    [ft^2]
 279 |Sf            flap 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]
 291
 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]
 302
 303 12) mass variables
 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]
 310
 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) [%]
 316
 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                   []
 325
 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]
 357
 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]
 363
 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]
 371
 372 18) subscripts
 373 o       value for all angles = 0 (alfa, beta, etc)
 374 a       angle of attack
 375 a2      alpha squared
 376 a3      alpha cubed
 377 adot    rate change in angle alpha
 378 beta    sideslip angle
 379 b2      beta squared
 380 b3      beta cubed
 381 bdot    rate change in beta
 382 p       roll rate
 383 q       pitch rate
 384 r       yaw rate
 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
 391 dr      rudder deflection
 392 |df      flap deflection
 393 |df2    flap deflection for second set
 394 |df3    flap deflection for third set
 395 max     maximum
 396 min     minimum
 397
 398 19) miscellaneous
 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                   []
 404
 405 (3) | [OPTIONAL DATA]
 406 =====================
 407
 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
 412 them.
 413
 414 (4) # [COMMENTS]
 415 ================
 416
 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
 419 was drawn from.
 420 **********************************************************************
 421
 422 **********************************************************************
 423 III. Sample Input Lines:
 424
 425 CONSTANTS
 426 =========
 427
 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
 431
 432 LOOKUP TABLES
 433 =============
 434
 435 CD CDfCL    <file.dat>  # CD(CL), drag polar data file
 436 Cm Cmfade   <file.dat>  # Cm(alpha,delta_e), moment data file
 437
 438 HARD-CODED EQUATION
 439 ===================
 440
 441 CD CDfCL                # CD(CL), drag calculated in code based on CL
 442 (none currently in use)
 443
 444 **********************************************************************
 445
 446 **********************************************************************
 447 IV. Input Line Definitions:
 448
 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.
 456
 457 # Key  Variable  Data      Units      Description                       Where Defined
 458 #------------------------------------------------------------------------------------
 459
 460 init recordRate <recordRate> # [/s]   record data n times per second    uiuc_aircraft.h
 461
 462 # [s]   time to start recording output data                             uiuc_aircraft.h
 463 init recordStartTime <recordStartTime>
 464
 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>
 467
 468 # [ft/s] speed at which dynamic pressure terms are first computed       uiuc_aircraft.h
 469 init dyn_on_speed <dyn_on_speed>
 470
 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
 474
 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
 484
 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
 492
 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
 509
 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
 518
 519 # Note: Currently demin/damin/drmin are not used in the code, and the max/min is +-dema
 520
 521 # trim always set to some fixed input value (radians)             [rad] uiuc_aircraft.h
 522 controlSurface set_Long_trim <elevator_tab>
 523
 524 # trim always set to some fixed input value (degrees)             [deg] uiuc_aircraft.h
 525 controlSurface set_Long_trim_deg <elevator_tab>
 526
 527 controlSurface zero_Long_trim       # [deg]  trim always set to zero    uiuc_aircraft.h
 528
 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>
 531
 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>
 536
 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>
 541
 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>
 547
 548
 549 |controlsMixer nomix <?> # []         no controls mixing                uiuc_aircraft.h
 550
 551
 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
 558
 559
 560 # maximum and minimum engine thrust                             [lb]    uiuc_aircraft.h
 561 |engine thrust <thrustMax> <thrustMin>
 562
 563 # simple single engine maximum thrust                           [lb]    uiuc_aircraft.h
 564 engine simpleSingle <simpleSingleMaxThrust>
 565
 566 engine c172             # use Cessna 172 engine model of Tony Peden
 567 engine cherokee         # use Piper Cherokee engine model
 568
 569
 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
 576
 577 # CL(alpha), conversion for CL, for alpha                           []  uiuc_aircraft.h
 578 CL CLfa <CLfa.dat> <token_value_convert1> <token_value_convert2>
 579
 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>
 583
 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
 595
 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
 600
 601
 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
 608
 609 # CD(alpha), conversion for CD, for alpha                           []  uiuc_aircraft.h
 610 CD CDfa <CDfa.dat> <token_value_convert1> <token_value_convert2>
 611
 612 # CD(CL) drag polar, conversion for CD, for CL                      []  uiuc_aircraft.h
 613 CD CDfCL <CDfCL.dat> <token_value_convert1> <token_value_convert2>
 614
 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>
 618
 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
 630
 631
 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
 642
 643 # Cm(alpha), conversion for Cm, for alpha                           []  uiuc_aircraft.h
 644 Cm Cmfa <Cmfa.dat> <token_value_convert1> <token_value_convert2>
 645
 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>
 649
 650
 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
 659
 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>
 663
 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>
 667
 668
 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
 676
 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>
 680
 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>
 684
 685
 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
 694
 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>
 698
 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>
 702
 703 =============================CONVERSION CODES================================
 704
 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.
 708
 709 ------------------------------------------------
 710 convert1/2/3  Action
 711 ------------------------------------------------
 712   0           no conversion (multiply by 1)
 713   1           convert degrees to radians
 714 =============================================================================
 715
 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
 720
 721
 722 ice iceTime <iceTime>   # [s]         time when icing begins            uiuc_aircraft.h
 723
 724 # [s]   period for eta_ice to reach eta_final                           uiuc_aircraft.h
 725 ice transientTime <transientTime>
 726
 727 # []    icing severity factor                                           uiuc_aircraft.h
 728 ice eta_ice_final <eta_ice_final>
 729
 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
 738
 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
 749
 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
 757
 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
 768
 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
 778
 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
 787
 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
 795
 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
 804
 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
 807
 808
 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
1032
1033
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>
1038
1039 **********************************************************************
1040
1041 **********************************************************************
1042 V. Mandatory Input:
1043
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
1046 probably crash.
1047
1048 1) aircraft geometry   (UIUC Aero Model)
1049 bw        wingspan                       [ft]
1050 cbar      mean aerodynamic chord         [ft]
1051 Sw        wing planform area             [ft^2]
1052
1053 2) engine properties   (UIUC Engine Model)
1054 (some engine model must be specified, such as...)
1055 engine simpleSingle
1056           <or>
1057 engine c172
1058
1059 3) mass variables   (LaRCsim)
1060 Weight    aircraft gross takeoff weight  [lb]
1061           <or>
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]
1067
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          []
1073           <or>
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]
1080
1081 5) gear properties   (none yet)
1082
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)
1086
1087 **********************************************************************