docs-mini/README.uiuc

   1 ************************************************
   2 *                                              *
   3 *  FGFS Reconfigurable Aircraft Flight Model   *
   4 *  Input File Documentation                    *
   5 *  Version 0.81, September 14, 2001            *
   6 *                                              *
   7 *  Authors:                                    *
   8 *  Jeff Scott (jscott@mail.com)                *
   9 *  Bipin Sehgal (bsehgal@uiuc.edu)             *
  10 *  Robert Deters (rdeters@uiuc.edu)            *
  11 *  Michael Selig (m-selig@uiuc.edu)            *
  12 *  Dept of Aero and Astro Engineering          *
  13 *  University of Illinois at Urbana-Champaign  *
  14 *  Urbana, IL                                  *
  15 *  http://amber.aae.uiuc.edu/~m-selig          *
  16 *                                              *
  17 ************************************************
  18
  19
  20 **********************************************************************
  21 NOTE:  Most of the commands discussed in this documentation are
  22        currently implemented in the UIUC aerodynamics model.  Those
  23        denoted by '|' are proposed and will likely be added in the
  24        future but are not currently implemented.  Some commands are
  25        in use but not producing the desired results.  These are
  26        clearly noted, so please do not attempt to use them at this
  27        time.
  28 **********************************************************************
  29
  30 **********************************************************************
  31 This documentation includes:
  32  - Required and optional input lines.
  33  - Input line formats and conventions.
  34
  35   Viewing this file in emacs makefile-mode with color makes this file
  36   easier to read.
  37 **********************************************************************
  38
  39 **********************************************************************
  40 I. Conventions and Notations and Reading this Document:
  41
  42  # ...     Comments
  43  |         Input line not yet implemented
  44  |         Optional data
  45  |         Sometimes indicates a feature not yet used,
  46            but proposed convention is indicated nevertheless.
  47  <...>     Value or file name to be placed here
  48  ||        Input line disabled
  49  ||        Option disabled
  50  ...       Repeat similar data
  51  ->        Continue onto next line
  52 **********************************************************************
  53
  54 **********************************************************************
  55 II. General Input Line Format:
  56
  57 Examples input lines include
  58
  59 Cm Cmo           0.194  # []          Bray pg 33
  60 Cm Cm_a         -2.12   # [/rad]      Bray pg 33
  61 CL CLfa CLfa.dat 0 1    # []          Bray pg 50, Table 4.7
  62
  63 These follow the more general input line form
  64
  65 keyword  variableName  <value -or- file> | ->
  66     <value -or- file>  # [units]  <data source>
  67
  68 Each term of the input line will be discussed in turn.
  69
  70 (1) KEYWORDS
  71 ============
  72
  73 There currently exist the following variable keyword types:
  74
  75 init            Initial values for equation of motion
  76 geometry        Aircraft-specific geometric quantities
  77 controlSurface  Control surface deflections and properties
  78 |controlsMixer  Control surface mixer options
  79 mass            Aircraft-specific mass properties
  80 engine          Propulsion data
  81 CD              Aerodynamic x-force quantities (longitudinal)
  82 CL              Aerodynamic z-force quantities (longitudinal)
  83 Cm              Aerodynamic m-moment quantities (longitudinal)
  84 CY              Aerodynamic y-force quantities (lateral)
  85 Cl              Aerodynamic l-moment quantities (lateral)
  86 Cn              Aerodynamic n-moment quantities (lateral)
  87 gear            Landing gear model quantities
  88 ice             Icing model parameters
  89 record          Record desired quantites to file
  90 misc            Miscellaneous inputs
  91 fog             Fog field quantities
  92
  93 As each line of the input file is read, the code recognizes the
  94 keyword, enters the appropriate switch statement in the code, and
  95 proceeds to read the next term in the input line.
  96
  97 (2) VARIABLE NAMES
  98 ==================
  99
 100 The variable name indicates the form of the variable itself.  This
 101 form may be a constant, a stability derivative (a specific form of a
 102 constant), or a variable-dimensional lookup table.  More variable
 103 types can be easily prescribed by defining a new convention.  The
 104 variable name may also indicate that the quantity is to be calculated
 105 from a hard-coded equation or set of equations provided at an
 106 appropriate location within the code.
 107
 108 If the parameter name denotes a constant, a numerical value will
 109 follow the variable name.  If a lookup table, the name of the table
 110 containing the data will follow.
 111
 112 More than one value or file name can be specified if the code is
 113 intended to read in multiple pieces of data when implementing the
 114 particular switch in question (see also OPTIONAL data, section (3)).
 115
 116 The conventions used for naming the variables are provided below.
 117 Several of these variable names are not currently used.
 118
 119 1) variable class
 120 _                   denotes stability derivative
 121 f                   "function of" (indicates data table)
 122
 123 2) timing data (global simulator variables)
 124 Simtime             current simulator time                  [s]
 125 dt                  current simulator time step             [s]
 126
 127 3) aircraft position data
 128 Lat_geocentric      geocentric latitude of CG               [rad]
 129 Lon_geocentric      geocentric longitude of CG              [rad]
 130 Radius_to_vehicle   distance of CG from inertial frame      [ft]
 131 Latitude            geodetic latitude of CG                 [rad]
 132 Longitude           geodetic longitude of CG                [rad]
 133 Altitude            height of CG above reference ellipsoid  [ft]
 134 Phi                 Euler bank/roll angle                   [rad]
 135 Theta               Euler pitch attitude angle              [rad]
 136 Psi                 Euler heading angle                     [rad]
 137
 138 4) aircraft accelerations
 139 V_dot_north         local x-acceleration                    [ft/s^2]
 140 V_dot_east          local y-acceleration                    [ft/s^2]
 141 V_dot_down          local z-acceleration                    [ft/s^2]
 142 U_dot_body          body x-acceleration                     [ft/s^2]
 143 V_dot_body          body y-acceleration                     [ft/s^2]
 144 W_dot_body          body z-acceleration                     [ft/s^2]
 145 A_X_pilot           pilot x-acceleration                    [ft/s^2]
 146 A_Y_pilot           pilot y-acceleration                    [ft/s^2]
 147 A_Z_pilot           pilot z-acceleration                    [ft/s^2]
 148 A_X_cg              center of gravity x-acceleration        [ft/s^2]
 149 A_Y_cg              center of gravity x-acceleration        [ft/s^2]
 150 A_Z_cg              center of gravity x-acceleration        [ft/s^2]
 151 N_X_pilot           pilot x-acceleration                    [ft/s^2]
 152 N_Y_pilot           pilot y-acceleration                    [ft/s^2]
 153 N_Z_pilot           pilot z-acceleration                    [ft/s^2]
 154 N_X_cg              center of gravity x-acceleration        [ft/s^2]
 155 N_Y_cg              center of gravity Y-acceleration        [ft/s^2]
 156 N_Z_cg              center of gravity Z-acceleration        [ft/s^2]
 157 P_dot_body          roll rate acceleration                  [rad/s^2]
 158 Q_dot_body          pitch rate acceleration                 [rad/s^2]
 159 R_dot_body          yaw rate acceleration                   [rad/s^2]
 160
 161 5) aircraft velocities
 162 V_north             local x-velocity                        [ft/s]
 163 V_east              local y-velocity                        [ft/s]
 164 V_down              local z-velocity                        [ft/s]
 165 V_north_rel_ground  local x-velocity with respect to ground [ft/s]
 166 V_east_rel_ground   local y-velocity with respect to ground [ft/s]
 167 V_down_rel_ground   local z-velocity with respect to ground [ft/s]
 168 V_north_airmass     local x-velocity of steady airmass      [ft/s]
 169 V_east_airmass      local y-velocity of steady airmass      [ft/s]
 170 V_down_airmass      local z-velocity of steady airmass      [ft/s]
 171 V_north_rel_airmass local x-velocity wrt steady airmass     [ft/s]
 172 V_east_rel_airmass  local y-velocity wrt steady airmass     [ft/s]
 173 V_down_rel_airmass  local z-velocity wrt steady airmass     [ft/s]
 174 U_gust              local linear turbulence x-velocity      [ft/s]
 175 V_gust              local linear turbulence y-velocity      [ft/s]
 176 W_gust              local linear turbulence z-velocity      [ft/s]
 177 U_body              wind x-velocity in body axis            [ft/s]
 178 V_body              wind y-velocity in body axis            [ft/s]
 179 W_body              wind z-velocity in body axis            [ft/s]
 180 V_rel_wind          total wind velocity (freestream)        [ft/s]
 181 V_true_kts          true velocity                           [kts]
 182 V_rel_ground        total velocity wrt ground               [ft/s]
 183 V_inertial          total inertial velocity                 [ft/s]
 184 V_ground_speed      velocity at right angles to local vertical [ft/s]
 185 V_equiv             equivalent airspeed                     [ft/s]
 186 V_equiv_kts         equivalent airspeed                     [kts]
 187 V_calibrated        calibrated indicated airspeed           [ft/s]
 188 V_calibrated_kts    calibrated indicated airspeed           [kts]
 189 P_local             local roll rate                         [rad/s]
 190 Q_local             local pitch rate                        [rad/s]
 191 R_local             local yaw rate                          [rad/s]
 192 P_body              body roll rate                          [rad/s]
 193 Q_body              body pitch rate                         [rad/s]
 194 R_body              body yaw rate                           [rad/s]
 195 P_total             roll rate of body axis wrt local axis   [rad/s]
 196 Q_total             pitch rate of body axis wrt local axis  [rad/s]
 197 R_total             yaw rate of body axis wrt local axis    [rad/s]
 198 Phi_dot             change in bank angle rate               [rad/s]
 199 Theta_dot           change in pitch attitude angle rate     [rad/s]
 200 Psi_dot             change in heading angle rate            [rad/s]
 201 Latitude_dot        change in geocentric latitude rate      [rad/s]
 202 Longitude_dot       change in geocentric longitude rate     [rad/s]
 203 Radius_dot          change in geocentric radius rate        [ft/s]
 204
 205 6) angles
 206 Alpha               angle of attack                         [rad]
 207 Alpha_deg           angle of attack                         [deg]
 208 Alpha_dot           rate of change of alpha                 [rad/s]
 209 Alpha_dot_deg       rate of change of alpha                 [deg/s]
 210 Beta                sideslip angle                          [rad]
 211 Beta_deg            sideslip angle                          [deg]
 212 Beta_dot            rate of change of beta                  [rad]
 213 Beta_dot_deg        rate of change of beta                  [deg]
 214 Gamma_vert          local vertical flight path angle        [rad]
 215 Gamma_ver_deg       local vertical flight path angle        [deg]
 216 Gamma_horiz         local horizontal flight path angle      [rad]
 217 Gamma_horiz_deg     local horizontal flight path angle      [deg]
 218
 219 7) atmosperic properties
 220 Density             atmospheric density                     [slug/ft^3]
 221 V_sound             speed of sound                          [ft/s]
 222 Mach_number         free-stream Mach number                 []
 223 M                   Mach number                             []
 224 Re                  Reynolds number                         []
 225 Static_pressure     static pressure                         [lb/ft^2]
 226 Total_pressure      total pressure                          [lb/ft^2]
 227 Impact_pressure     impact pressure                         [lb/ft^2]
 228 Dynamic_pressure    dynamic pressure                        [lb/ft^2]
 229 Static_temperature  static temperature                      [deg F?]
 230 Total_temperature   total temperature                       [deg F?]
 231
 232 8) Earth properties
 233 Gravity             acceleration due to gravity             [ft/s^2]
 234 Sea_level_radius    local Earth radius                      [ft]
 235 Earth_position_angle Earth rotation angle since reference time [rad]
 236 Runway_altitude     runway height above local sea level     [ft]
 237 Runway_latitude     runway latitude                         [rad]
 238 Runway_longitude    runway longitude                        [rad]
 239 Runway_heading      runway heading                          [rad]
 240 Radius_to_rwy       geocentric radius to runway             [ft]
 241 D_pilot_north_of_rwy  local pilot x-distance from runway    [ft]
 242 D_pilot_east_of_rwy   local pilot y-distance from runway    [ft]
 243 D_pilot_down_of_rwy   local pilot z-distance from runway    [ft]
 244 X_pilot_rwy         pilot x-distance from rwy in rwy axis   [ft]
 245 Y_pilot_rwy         pilot y-distance from rwy in rwy axis   [ft]
 246 H_pilot_rwy         pilot z-distance from rwy in rwy axis   [ft]
 247 D_cg_north_of_rwy   local cg x-distance from runway         [ft]
 248 D_cg_east_of_rwy    local cg y-distance from runway         [ft]
 249 D_cg_down_of_rwy    local cg z-distance from runway         [ft]
 250 X_cg_rwy            cg x-distance from rwy in rwy axis      [ft]
 251 Y_cg_rwy            cg y-distance from rwy in rwy axis      [ft]
 252 H_cg_rwy            cg z-distance from rwy in rwy axis      [ft]
 253
 254 9) aircraft geometric variables
 255 bw        wingspan                              [ft]
 256 cbar      mean aerodynamic chord                [ft]
 257 Sw        wing planform area                    [ft^2]
 258 |iw       wing incidence angle                  [deg]
 259 |bc       canard span                           [ft]
 260 |cc       canard (mean) chord                   [ft]
 261 |Sc       canard area                           [ft^2]
 262 |ic       canard incidence angle                [deg]
 263 bh        horizontal tail span                  [ft]
 264 ch        horizontal tail (mean) chord          [ft]
 265 Sh        horizontal tail area                  [ft^2]
 266 ih        horizontal tail incidence angle       [deg]
 267 |bv       vertical tail span (height)           [ft]
 268 |cv       vertical tail (mean) chord            [ft]
 269 |iv       vertical tail incidence angle         [deg]
 270 |Sv       vertical tail area                    [ft^2]
 271 Dx_pilot  reference pilot x-location            [ft]
 272 Dy_pilot  reference pilot y-location            [ft]
 273 Dz_pilot  referende pilot z-location            [ft]
 274 Dx_cg     reference center of gravity x-loc     [ft]
 275 Dy_cg     reference center of gravity y-loc     [ft]
 276 Dz_cg     reference center of gravity z-loc     [ft]
 277
 278 10) aircraft control surface properties
 279 |Sa            aileron area                     [ft^2]
 280 |Se            elevator area                    [ft^2]
 281 |Sf            flap area                        [ft^2]
 282 |Sr            rudder area                      [ft^2]
 283 Long_control   pitch control input              []
 284 Long_trim      longitudinal trim input          [rad]
 285 set_Long_trim  set longitudinal trim to constant[rad]
 286 zero_Long_trim set longitudinal trim to zero    [deg]
 287 elevator       elevator deflection              [rad]
 288 Lat_control    roll control input               []
 289 aileron        aileron deflection               [rad]
 290 Rudder_pedal   yaw control input                []
 291 rudder         rudder deflection                [rad]
 292 |flap          flap deflection                  [rad]
 293
 294 11) user-specified control surface deflections
 295 elevator_step_angle        elevator step input angle             [deg]
 296 elevator_step_startTime    elevator step input starting time     [s]
 297 elevator_singlet_angle     elevator singlet input angle          [deg]
 298 elevator_singlet_startTime elevator singlet input starting time  [s]
 299 elevator_singlet_duration  elevator singlet time duration        [s]
 300 elevator_doublet_angle     elevator singlet input angle          [deg]
 301 elevator_doublet_startTime elevator doublet input starting time  [s]
 302 elevator_doublet_duration  elevator doublet TOTAL time duration  [s]
 303 elevator_input_file        file of elevator deflections vs. time [s,deg]
 304 aileron_input_file         file of aileron deflections vs. time  [s,deg]
 305 rudder_input_file          file of rudder deflections vs. time   [s,deg]
 306
 307 12) mass variables
 308 Weight              gross takeoff weight                    [lb]
 309 Mass                aircraft mass (used by LaRCsim)         [slug]
 310 I_xx                roll inertia                            [slug-ft^2]
 311 I_yy                pitch inertia                           [slug-ft^2]
 312 I_zz                yaw inertia                             [slug-ft^2]
 313 I_xz                lateral cross inertia                   [slug-ft^2]
 314
 315 13) engine/propulsion variables
 316 |thrust             engine thrust                           [lb]
 317 simpleSingle        treat all engines as one; max thrust    [lb]
 318 Throttle_pct        throttle input ("stick")                []
 319 Throttle_3          throttle deflection (determines thrust) [%]
 320
 321 14) force/moment coefficients
 322 CD                  coefficient of drag                     []
 323 CY                  coefficient of side-force               []
 324 CL                  coefficient of lift                     []
 325 Cl                  coefficient of roll moment              []
 326 Cm                  coefficient of pitching moment          []
 327 Cn                  coefficient of yaw moment               []
 328 |CT                 coefficient of thrust                   []
 329
 330 15) total forces/moments
 331 F_X_wind            aerodynamic x-force in wind-axes        [lb]
 332 F_Y_wind            aerodynamic y-force in wind-axes        [lb]
 333 F_Z_wind            aerodynamic z-force in wind-axes        [lb]
 334 F_X_aero            aerodynamic x-force in body-axes        [lb]
 335 F_Y_aero            aerodynamic y-force in body-axes        [lb]
 336 F_Z_aero            aerodynamic z-force in body-axes        [lb]
 337 F_X_engine          propulsion x-force in body axes         [lb]
 338 F_Y_engine          propulsion y-force in body axes         [lb]
 339 F_Z_engine          propulsion z-force in body axes         [lb]
 340 F_X_gear            gear x-force in body axes               [lb]
 341 F_Y_gear            gear y-force in body axes               [lb]
 342 F_Z_gear            gear z-force in body axes               [lb]
 343 F_X                 total x-force in body-axes              [lb]
 344 F_Y                 total y-force in body-axes              [lb]
 345 F_Z                 total z-force in body-axes              [lb]
 346 F_north             total x-force in local-axes             [lb]
 347 F_east              total y-force in local-axes             [lb]
 348 F_down              total z-force in local-axes             [lb]
 349 M_l_aero            aero roll-moment in body-axes           [ft-lb]
 350 M_m_aero            aero pitch-moment in body-axes          [ft-lb]
 351 M_n_aero            aero yaw-moment in body-axes            [ft-lb]
 352 M_l_engine          prop roll-moment in body axes           [ft-lb]
 353 M_m_engine          prop pitch-moment in body axes          [ft-lb]
 354 M_n_engine          prop yaw-moment in body axes            [ft-lb]
 355 M_l_gear            gear roll-moment in body axes           [ft-lb]
 356 M_m_gear            gear pitch-moment in body axes          [ft-lb]
 357 M_n_gear            gear yaw-moment in body axes            [ft-lb]
 358 M_l_rp              total roll-moment                       [ft-lb]
 359 M_m_rp              total pitch-moment                      [ft-lb]
 360 M_n_rp              total yaw-moment                        [ft-lb]
 361
 362 16) landing gear properties
 363 Dx_gear             x-offset from CG                        [ft]
 364 Dy_gear             y-offset from CG                        [ft]
 365 Dz_gear             z-offset from CG                        [ft]
 366 cgear               gear damping constant                   [lb/ft/s]
 367 kgear               gear spring constant                    [lb/ft]
 368 muGear              gear rolling friction coef              [-]
 369 |strutLength        gear strut length                       [ft]
 370
 371 17) icing model parameters
 372 iceTime       time when icing begins                         [s]
 373 transientTime time period over which eta increases to final  [s]
 374 eta_ice_final icing severity factor at end of transient time []
 375 kCA           icing constants for associated aero coef.      [] (see IV)
 376 beta_probe_wing  location of flow angle probe on wing        [ft]
 377 beta_probe_tail  location of flow angle probe on tail        [ft]
 378
 379 18) subscripts
 380 o       value for all angles = 0 (alfa, beta, etc)
 381 a       angle of attack
 382 a2      alpha squared
 383 a3      alpha cubed
 384 adot    rate change in angle alpha
 385 beta    sideslip angle
 386 b2      beta squared
 387 b3      beta cubed
 388 bdot    rate change in beta
 389 p       roll rate
 390 q       pitch rate
 391 r       yaw rate
 392 |pdot   rate change in p
 393 |qdot   rate change in q
 394 |rdot   rate change in r
 395 |udot   rate change in x-velocity
 396 da      aileron deflection
 397 de      elevator deflection
 398 dr      rudder deflection
 399 |df      flap deflection
 400 |df2    flap deflection for second set
 401 |df3    flap deflection for third set
 402 max     maximum
 403 min     minimum
 404
 405 19) miscellaneous
 406 recordRate              number of times to record data per second  [/s]
 407 recordStartTime         time to start recording outpud data        [s]
 408 dyn_on_speed            speed when dynamic pressure terms first computed [ft/s]
 409 nondim_rate_V_rel_wind  use V_rel_wind to compute control rates    []
 410 |simpleHingeMomentCoef  hinge moment coefficient                   []
 411
 412 20) fog
 413 fog_segments    number of fog points following this line
 414 fog_points      fog intensity and the time at which it occurs
 415
 416 (3) | [OPTIONAL DATA]
 417 =====================
 418
 419 An input line may also be used to provide optional data that
 420 will be used if provided but is not necessary for the code to
 421 operate.  As with the variable data described in section (2), multiple
 422 values or data files may be provided if the code is written to use
 423 them.
 424
 425 (4) # [COMMENTS]
 426 ================
 427
 428 Appended comments should be provided with each input line to indicate
 429 units on the variable in question and to indicate the source the data
 430 was drawn from.
 431 **********************************************************************
 432
 433 **********************************************************************
 434 III. Sample Input Lines:
 435
 436 CONSTANTS
 437 =========
 438
 439 geometry bw   <value>   # geometric parameter, wingspan
 440 Cm Cm_a       <value>   # stability derivative, d(Cm)/d(alpha)
 441 controlSurface de <value> <value>  # max and min elevator deflections
 442
 443 LOOKUP TABLES
 444 =============
 445
 446 CD CDfCL    <file.dat>  # CD(CL), drag polar data file
 447 Cm Cmfade   <file.dat>  # Cm(alpha,delta_e), moment data file
 448
 449 HARD-CODED EQUATION
 450 ===================
 451
 452 CD CDfCL                # CD(CL), drag calculated in code based on CL
 453 (none currently in use)
 454
 455 **********************************************************************
 456
 457 **********************************************************************
 458 IV. Input Line Definitions:
 459
 460 Of all the possible permutations of variable names described above in
 461 section II, only some are curently implemented in the code.  These are
 462 described below.  Comments, denoted by '#,' are used to define the
 463 lines and to indicate examples of the data if additional clarity is
 464 needed for unique situations.  Again, those lines beginning with '|'
 465 are not currently implemented in the code, but indicate planned
 466 conventions in later versions.
 467
 468 # Key  Variable  Data      Units      Description                       Where Defined
 469 #------------------------------------------------------------------------------------
 470
 471 init recordRate <recordRate> # [/s]   record data n times per second    uiuc_aircraft.h
 472
 473 # [s]   time to start recording output data                             uiuc_aircraft.h
 474 init recordStartTime <recordStartTime>
 475
 476 # []    use V_rel_wind to compute control rates (instead of U_body)     uiuc_aircraft.h
 477 init nondim_rate_V_rel_wind <nondim_rate_V_rel_wind>
 478
 479 # [ft/s] speed at which dynamic pressure terms are first computed       uiuc_aircraft.h
 480 init dyn_on_speed <dyn_on_speed>
 481
 482 init Dx_pilot <Dx_pilot> # [ft]       reference pilot x-position        ls_generic.h
 483 init Dy_pilot <Dy_pilot> # [ft]       reference pilot y-position        ls_generic.h
 484 init Dz_pilot <Dz_pilot> # [ft]       reference pilot z-position        ls_generic.h
 485
 486 # the following commands are currently conflicting with Flight
 487 # Gear and are not working correctly:
 488 |init Dx_cg <Dx_cg>      # [ft]       reference cg x_location           ls_generic.h
 489 |init Dy_cg <Dy_cg>      # [ft]       reference cg y_location           ls_generic.h
 490 |init Dz_cg <Dz_cg>      # [ft]       reference cg z_location           ls_generic.h
 491 |init V_north <V_north>  # [ft/s]     initial local x-velocity          ls_generic.h
 492 |init V_east <V_east>    # [ft/s]     initial local y-velocity          ls_generic.h
 493 |init V_down <V_down>    # [ft/s]     initial local z-velocity          ls_generic.h
 494 |init Altitude <Altitude> # [ft/s]    initial altitude                  ls_generic.h
 495
 496 init U_body <U_body>     # [ft/s]     initial x-velocity in body axis   ls_generic.h
 497 init V_body <V_body>     # [ft/s]     initial y-velocity in body axis   ls_generic.h
 498 init W_body <W_body>     # [ft/s]     initial z-velocity in body axis   ls_generic.h
 499 init P_body <P_body>     # [rad/s]    initial roll rate                 ls_generic.h
 500 init Q_body <Q_body>     # [rad/s]    initial pitch rate                ls_generic.h
 501 init R_body <R_body>     # [rad/s]    initial yaw rate                  ls_generic.h
 502 init Phi <Phi>           # [rad]      initial bank angle                ls_generic.h
 503 init Theta <Theta>       # [rad]      initial pitch attitude angle      ls_generic.h
 504 init Psi <Psi>           # [rad]      initial heading angle             ls_generic.h
 505 init Alpha <Alpha>       # [deg]      initial angle of attack           ls_generic.h
 506 init Beta <Beta>         # [deg]      initial side slip angle           ls_generic.h
 507 init Long_trim <Long_trim> # [rad]    longitudinal trim                 ls_cockpit.h
 508
 509 geometry bw <bw>        # [ft]        wingspan                          uiuc_aircraft.h
 510 geometry cbar <cbar>    # [ft]        wing mean aero chord              uiuc_aircraft.h
 511 geometry Sw <Sw>        # [ft^2]      wing reference area               uiuc_aircraft.h
 512 |geometry iw <iw>       # [deg]       wing incidence angle              uiuc_aircraft.h
 513 |geometry bc <bc>       # [ft]        canard span                       uiuc_aircraft.h
 514 |geometry cc <cc>       # [ft]        canard chord                      uiuc_aircraft.h
 515 |geometry Sc <Sc>       # [sq-ft]     canard area                       uiuc_aircraft.h
 516 |geometry ic <ic>       # [deg]       canard incidence angle            uiuc_aircraft.h
 517 geometry bh <bh>        # [ft]        horizontal tail span              uiuc_aircraft.h
 518 geometry ch <ch>        # [ft]        horizontal tail chord             uiuc_aircraft.h
 519 geometry Sh <Sh>        # [sq-ft]     horizontal tail area              uiuc_aircraft.h
 520 geometry ih <ih>        # [deg]       horiz tail incidence angle        uiuc_aircraft.h
 521 |geometry bv <bv>       # [ft]        vertical tail span                uiuc_aircraft.h
 522 |geometry cv <cv>       # [ft]        vertical tail chord               uiuc_aircraft.h
 523 |geometry Sv <Sv>       # [sq-ft]     vertical tail area                uiuc_aircraft.h
 524 |geometry iv <iv>       # [deg]       vert tail incidence angle         uiuc_aircraft.h
 525
 526 |controlSurface Se <Se>  # [ft^2]     elevator area                     uiuc_aircraft.h
 527 |controlSurface Sa <Sa>  # [ft^2]     aileron area                      uiuc_aircraft.h
 528 |controlSurface Sr <Sr>  # [ft^2]     rudder area                       uiuc_aircraft.h
 529 |controlSurface Sf <Sf>  # [ft^2]     flap area                         uiuc_aircraft.h
 530 controlSurface de <demax> <demin>   # [deg]  max/min elev deflections   uiuc_aircraft.h
 531 controlSurface da <damax> <damin>   # [deg]  max/min ail deflections    uiuc_aircraft.h
 532 controlSurface dr <drmax> <drmin>   # [deg]  max/min rud deflections    uiuc_aircraft.h
 533 |controlSurface df <dfmax> <dfmin>  # [deg]  max/min flap deflections   uiuc_aircraft.h
 534
 535 # trim always set to some fixed input value (radians)             [rad] uiuc_aircraft.h
 536 controlSurface set_Long_trim <elevator_tab>
 537 # Note: Do not use.  Only works with pilot_elev_no and elevator_input.  Use an elevator input file instead
 538
 539 # trim always set to some fixed input value (degrees)             [deg] uiuc_aircraft.h
 540 controlSurface set_Long_trim_deg <elevator_tab>
 541 # Note: Do not use.  Only works with pilot_elev_no and elevator_input.  Use an elevator input file instead
 542
 543 controlSurface zero_Long_trim       # [deg]  trim always set to zero    uiuc_aircraft.h
 544
 545 # elevator step input with deflection angle [deg] and starting time [s] uiuc_aircraft.h
 546 controlSurface elevator_step <elevator_step_angle> <elevator_step_startTime>
 547
 548 # elevator singlet input with deflection angle [deg], starting time [s],
 549 # and duration of input [s]                                             uiuc_aircraft.h
 550 controlSurface elevator_singlet <elevator_singlet_angle> ->
 551         <elevator_singlet_startTime> <elevator_singlet_duration>
 552
 553 # elevator doublet input with deflection angle [deg], starting time [s],
 554 # and TOTAL duration of input (both up and down deflections) [s]        uiuc_aircraft.h
 555 controlSurface elevator_doublet <elevator_doublet_angle> ->
 556         <elevator_doublet_startTime> <elevator_doublet_duration>
 557
 558 # tabulated elevator input (as function of time) with conversion
 559 # factor codes and starting time [s]                                    uiuc_aircraft.h
 560 controlSurface elevator_input <elevator_input_file> ->
 561         <token_value_convert1> <token_value_convert2> ->
 562         <elevator_input_startTime>
 563
 564 # tabulated aileron input (as function of time) with conversion
 565 # factor codes and starting time [s]                                    uiuc_aircraft.h
 566 controlSurface aileron_input <aileron_input_file> ->
 567         <token_value_convert1> <token_value_convert2> ->
 568         <aileron_input_startTime>
 569
 570 # tabulated rudder input (as function of time) with conversion
 571 # factor codes and starting time [s]                                    uiuc_aircraft.h
 572 controlSurface rudder_input <rudder_input_file> ->
 573         <token_value_convert1> <token_value_convert2> ->
 574         <rudder_input_startTime>
 575
 576 # ignore elevator input from the joystick/keyboard/mouse [-]            uiuc_aircraf.h
 577 controlSurface pilot_elev_no
 578 # Note: Only works if elevator_input is used
 579
 580 # ignore aileron input from the joystick/keyboard/mouse [-]             uiuc_aircraf.h
 581 controlSurface pilot_ail_no
 582 # Note: Only works if aileron_input is used
 583
 584 # ignore rudder input from the joystick/keyboard/mouse [-]              uiuc_aircraf.h
 585 controlSurface pilot_rud_no
 586 # Note: Only works if rudder_input is used
 587
 588 |controlsMixer nomix <?> # []         no controls mixing                uiuc_aircraft.h
 589
 590
 591 mass Weight <Weight>    # [lb]        gross takeoff weight              uiuc_aircraft.h
 592 mass Mass <Mass>        # [slug]      gross takeoff mass                ls_generic.h
 593 mass I_xx <I_xx>        # [slug-ft^2] roll inertia                      ls_generic.h
 594 mass I_yy <I_yy>        # [slug-ft^2] pitch inertia                     ls_generic.h
 595 mass I_zz <I_zz>        # [slug-ft^2] yaw inertia                       ls_generic.h
 596 mass I_xz <I_xz>        # [slug-ft^2] lateral cross inertia             ls_generic.h
 597
 598
 599 # maximum and minimum engine thrust                             [lb]    uiuc_aircraft.h
 600 |engine thrust <thrustMax> <thrustMin>
 601
 602 # simple single engine maximum thrust                           [lb]    uiuc_aircraft.h
 603 engine simpleSingle <simpleSingleMaxThrust>
 604
 605 engine c172             # use Cessna 172 engine model of Tony Peden
 606 engine cherokee         # use Piper Cherokee engine model
 607
 608
 609 CL CLo <CLo>            # []          lift coef for all angles = 0      uiuc_aircraft.h
 610 CL CL_a <CL_a>          # [/rad]      lift curve slope, d(CL)/d(alpha)  uiuc_aircraft.h
 611 CL CL_adot <CL_adot>    # [/rad]      d(CL)/d(alpha)/da(time)           uiuc_aircraft.h
 612 CL CL_q <CL_q>          # [/rad]      d(CL)/d(q)                        uiuc_aircraft.h
 613 CL CL_ih <CL_ih>        # [/rad]      CL due to horiz tail incidence    uiuc_aircraft.h
 614 CL CL_de <CL_de>        # [/rad]      d(CL)/d(de)                       uiuc_aircraft.h
 615
 616 # CL(alpha), conversion for CL, for alpha                           []  uiuc_aircraft.h
 617 CL CLfa <CLfa.dat> <token_value_convert1> <token_value_convert2>
 618
 619 # CL(alpha,delta_e), conversion for CL, for alpha, for delta_e      []  uiuc_aircraft.h
 620 CL CLfade <CLfade.dat> <token_value_convert1> <token_value_convert2> ->
 621           <token_value_convert3>
 622
 623   # the following are lift coefficients in the body axis
 624 CL CZo <CZo>            # []          lift coef for all angles = 0      uiuc_aircraft.h
 625 CL CZ_a <Cz_a>          # [/rad]      lift curve slope, d(CZ)/d(alpha)  uiuc_aircraft.h
 626 CL CZ_a2 <CZ_a2>        # [/rad]      d(CZ)/d(alpha squared)            uiuc_aircraft.h
 627 CL CZ_a3 <CZ_a3>        # [/rad]      d(CZ)/d(alpha cubed)              uiuc_aircraft.h
 628 CL CZ_adot <CZ_adot>    # [/rad]      d(CZ)/d(alpha)/d(time)            uiuc_aircraft.h
 629 CL CZ_q <CZ_q>          # [/rad]      d(CZ)/d(q)                        uiuc_aircraft.h
 630 CL CZ_de <CZ_de>        # [/rad]      d(CZ)/d(de)                       uiuc_aircraft.h
 631 CL CZ_deb2 <CZ_deb2>    # [/rad]      d(CZ)/d(de, beta squared)         uiuc_aircraft.h
 632 CL CZ_df <CZ_df>        # [/rad]      d(CZ)/d(df)                       uiuc_aircraft.h
 633 CL CZ_adf <CZ_adf>      # [/rad]      d(CZ)/d(alpha, df)                uiuc_aircraft.h
 634
 635 # CZ(alpha), conversion for CZ, for alpha                           []  uiuc_aircraft.h
 636 CL CZfa <CZfa.dat> <token_value_convert1> <token_value_convert2>
 637
 638 |CL CLfCT <CLfCT.dat>   #             CL(thrust coef)                   uiuc_aircraft.h
 639 |CL CLfRe               #             CL(Reynolds #), equation          uiuc_aircraft.h
 640 |CL CL_afaM <CL_afaM.dat> #           CL_alpha(alpha,Mach #)            uiuc_aircraft.h
 641    # these are sample examples that might be used in later versions of the code
 642
 643
 644 # note that CD terms must come after CL for induced drag to be computed
 645 CD CDo <CDo>            # []          drag coef for all angles = 0      uiuc_aircraft.h
 646 CD CDK <CDK>            # []          induced drag constant 1/(pi*e*AR) uiuc_aircraft.h
 647 CD CD_a <CD_a>          # [/rad]      d(CD)/d(alpha)                    uiuc_aircraft.h
 648 CD CD_ih <CD_ih>        # [/rad]      CD due to horiz tail incidence    uiuc_aircraft.h
 649 CD CD_de <CD_de>        # [/rad]      d(CD)/d(delta_e)                  uiuc_aircraft.h
 650
 651 # CD(alpha), conversion for CD, for alpha                           []  uiuc_aircraft.h
 652 CD CDfa <CDfa.dat> <token_value_convert1> <token_value_convert2>
 653
 654 # CD(CL) drag polar, conversion for CD, for CL                      []  uiuc_aircraft.h
 655 CD CDfCL <CDfCL.dat> <token_value_convert1> <token_value_convert2>
 656
 657 # CD(alpha,delta_e), conversion for CD, for alpha, for delta_e      []  uiuc_aircraft.h
 658 CD CDfade <CDfade.dat> <token_value_convert1> <token_value_convert2> ->
 659           <token_value_convert3>
 660
 661   # the following are drag coefficients in the body axis
 662 CD CXo <CXo>            # []          drag coef for all angles = 0      uiuc_aircraft.h
 663 CD CXK <CXK>            # []          induced drag constant 1/(pi*e*AR) uiuc_aircraft.h
 664 CD CX_a <CX_a>          # [/rad]      d(CX)/d(alpha)                    uiuc_aircraft.h
 665 CD CX_a2 <CX_a2>        # [/rad]      d(CX)/d(alpha squared)            uiuc_aircraft.h
 666 CD CX_a3 <CX_a3>        # [/rad]      d(CX)/d(alpha cubed)              uiuc_aircraft.h
 667 CD CX_q <CX_q>          # [/rad]      d(CX)/d(q)                        uiuc_aircraft.h
 668 CD CX_de <CX_de>        # [/rad]      d(CX)/d(de)                       uiuc_aircraft.h
 669 CD CX_dr <CX_dr>        # [/rad]      d(CX)/d(dr)                       uiuc_aircraft.h
 670 CD CX_df <CX_df>        # [/rad]      d(CX)/d(df)                       uiuc_aircraft.h
 671 CD CX_adf <CX_adf>      # [/rad]      d(CX)/d(alpha, df)                uiuc_aircraft.h
 672
 673
 674 Cm Cmo <Cmo>            # []          pitch mom coef for all angles=0   uiuc_aircraft.h
 675 Cm Cm_a <Cm_a>          # [/rad]      d(Cm)/d(alpha)                    uiuc_aircraft.h
 676 Cm Cm_a2 <Cm_a2>        # [/rad]      d(Cm)/d(alpha squared)            uiuc_aircraft.h
 677 Cm Cm_adot <Cm_adot>    # [/rad]      d(Cm)/d(alpha)/d(time)            uiuc_aircraft.h
 678 Cm Cm_q <Cm_q>          # [/rad]      d(Cm)/d(q)                        uiuc_aircraft.h
 679 Cm Cm_ih <Cm_ih>        # [/rad]      Cm due to horiz tail incidence    uiuc_aircraft.h
 680 Cm Cm_de <Cm_de>        # [/rad]      d(Cm)/d(de)                       uiuc_aircraft.h
 681 Cm Cm_de <Cm_b2>        # [/rad]      d(Cm)/d(beta squared)             uiuc_aircraft.h
 682 Cm Cm_r <Cm_r>          # [/rad]      d(Cm)/d(r)                        uiuc_aircraft.h
 683 Cm Cm_df <Cm_df>        # [/rad]      d(Cm)/d(df)                       uiuc_aircraft.h
 684
 685 # Cm(alpha), conversion for Cm, for alpha                           []  uiuc_aircraft.h
 686 Cm Cmfa <Cmfa.dat> <token_value_convert1> <token_value_convert2>
 687
 688 # Cm(alpha,delta_e), conversion for Cm, for alpha, for delta_e      []  uiuc_aircraft.h
 689 Cm Cmfade <Cmfade.dat> <token_value_convert1> <token_value_convert2> ->
 690           <token_value_convert3>
 691
 692
 693 CY CYo <CYo>            # []          side-force coef for all angles=0  uiuc_aircraft.h
 694 CY CY_beta <CY_beta>    # [/rad]      d(CY)/d(beta)                     uiuc_aircraft.h
 695 CY CY_p <CY_p>          # [/rad]      d(CY)/d(p)                        uiuc_aircraft.h
 696 CY CY_r <CY_r>          # [/rad]      d(CY)/d(r)                        uiuc_aircraft.h
 697 CY CY_da <CY_da>        # [/rad]      d(CY)/d(da)                       uiuc_aircraft.h
 698 CY CY_dr <CY_dr>        # [/rad]      d(CY)/d(dr)                       uiuc_aircraft.h
 699 CY CY_dra <CY_dra>      # [/rad]      d(CY)/d(dr, alpha)                uiuc_aircraft.h
 700 CY CY_dra <CY_bdot>     # [/rad]      d(CY)/d(beta)/d(time)             uiuc_aircraft.h
 701
 702 # CY(alpha,delta_a), conversion for CY, for alpha, for delta_a      []  uiuc_aircraft.h
 703 CY CYfada <CYfada.dat> <token_value_convert1> <token_value_convert2> ->
 704           <token_value_convert3>
 705
 706 # CY(beta,delta_r), conversion for CY, for beta, for delta_r        []  uiuc_aircraft.h
 707 CY CYfbetadr <CYfbetadr.dat> <token_value_convert1> <token_value_convert2> ->
 708           <token_value_convert3>
 709
 710
 711 Cl Clo <Clo>            # []          roll mom coef for all angles=0    uiuc_aircraft.h
 712 Cl Cl_beta <Cl_beta>    # [/rad]      d(Cl)/d(beta)                     uiuc_aircraft.h
 713 Cl Cl_p <Cl_p>          # [/rad]      d(Cl)/d(p)                        uiuc_aircraft.h
 714 Cl Cl_r <Cl_r>          # [/rad]      d(Cl)/d(r)                        uiuc_aircraft.h
 715 Cl Cl_da <Cl_da>        # [/rad]      d(Cl)/d(da)                       uiuc_aircraft.h
 716 Cl Cl_dr <Cl_dr>        # [/rad]      d(Cl)/d(dr)                       uiuc_aircraft.h
 717 Cl Cl_daa <Cl_daa>      # [/rad]      d(Cl)/d(da, alpha)                uiuc_aircraft.h
 718
 719 # Cl(alpha,delta_a), conversion for Cl, for alpha, for delta_a      []  uiuc_aircraft.h
 720 Cl Clfada <CYfada.dat> <token_value_convert1> <token_value_convert2> ->
 721           <token_value_convert3>
 722
 723 # Cl(beta,delta_r), conversion for Cl, for beta, for delta_r        []  uiuc_aircraft.h
 724 Cl Clfbetadr <CYfbetadr.dat> <token_value_convert1> <token_value_convert2> ->
 725           <token_value_convert3>
 726
 727
 728 Cn Cno <Cno>            # []          yaw mom coef for all angles=0     uiuc_aircraft.h
 729 Cn Cn_beta <Cn_beta>    # [/rad]      d(Cn)/d(beta)                     uiuc_aircraft.h
 730 Cn Cn_p <Cn_p>          # [/rad]      d(Cn)/d(p)                        uiuc_aircraft.h
 731 Cn Cn_r <Cn_r>          # [/rad]      d(Cn)/d(r)                        uiuc_aircraft.h
 732 Cn Cn_da <Cn_da>        # [/rad]      d(Cn)/d(da)                       uiuc_aircraft.h
 733 Cn Cn_dr <Cn_dr>        # [/rad]      d(Cn)/d(dr)                       uiuc_aircraft.h
 734 Cn Cn_q <Cn_q>          # [/rad]      d(Cn)/d(q)                        uiuc_aircraft.h
 735 Cn Cn_b3 <Cn_b3>        # [/rad]      d(Cn)/d(beta cubed)               uiuc_aircraft.h
 736
 737 # Cn(alpha,delta_a), conversion for Cn, for alpha, for delta_a      []  uiuc_aircraft.h
 738 Cn Cnfada <Cnfada.dat> <token_value_convert1> <token_value_convert2> ->
 739           <token_value_convert3>
 740
 741 # Cn(beta,delta_r), conversion for Cn, for beta, for delta_r        []  uiuc_aircraft.h
 742 Cn Cnfbetadr <Cnfbetadr.dat> <token_value_convert1> <token_value_convert2> ->
 743           <token_value_convert3>
 744
 745 =============================CONVERSION CODES================================
 746
 747 To calculate the aero forces, angles (eg, alfa, beta, elevator deflection, etc)
 748 must be in radians.  To convert input data in degree to radian, use a
 749 conversion code of 1.  To use no conversion, use a conversion code of 0.
 750
 751 ------------------------------------------------
 752 convert1/2/3  Action
 753 ------------------------------------------------
 754   0           no conversion (multiply by 1)
 755   1           convert degrees to radians
 756 =============================================================================
 757
 758
 759 gear Dx_gear <position> <Dx_gear> # [ft]      x-offset from CG           uiuc_aircraft.h
 760 gear Dy_gear <position> <Dy_gear> # [ft]      y-offset from CG           uiuc_aircraft.h
 761 gear Dz_gear <position> <Dz_gear> # [ft]      z-offset from CG           uiuc_aircraft.h
 762 gear cgear   <position> <cgear>   # [lb/ft/s] gear damping constant      uiuc_aircraft.h
 763 gear kgear   <position> <kgear>   # [lb/ft]   gear spring constant       uiuc_aircraft.h
 764 gear muRoll  <position> <muRoll>  # [-]       gear rolling friction coef uiuc_aircraft.h
 765 |gear strutLength <position> <sL> # [ft]      gear strut length          uiuc_aircraft.h
 766
 767 ================================GEAR POSITION================================
 768
 769 There are 16 gear positions. Currently only the first three positions are
 770 rolling wheels.  Position 1 is reserved for the nose wheel, position 2 is
 771 reserved for the right wheel, and position 3 is reserved for the left wheel.
 772 The rest of the positions can be left out or used to define locations on the
 773 plane such as the wing tips or tail.  This way the wing tips or tail will not
 774 go "through" the ground but "bounce off" the ground.
 775 =============================================================================
 776
 777
 778 ice iceTime <iceTime>   # [s]         time when icing begins            uiuc_aircraft.h
 779
 780 # [s]   period for eta_ice to reach eta_final                           uiuc_aircraft.h
 781 ice transientTime <transientTime>
 782
 783 # []    icing severity factor                                           uiuc_aircraft.h
 784 ice eta_ice_final <eta_ice_final>
 785
 786 ice kCDo <kCDo>         # []          icing constant for CDo            uiuc_aircraft.h
 787 ice kCDK <kCDo>         # []          icing constant for CDK            uiuc_aircraft.h
 788 ice kCD_a <kCD_a>       # []          icing constant for CD_a           uiuc_aircraft.h
 789 ice kCD_q <kCD_q>       # []          icing constant for CD_q           uiuc_aircraft.h
 790 ice kCD_de <kCD_de>     # []          icing constant for CD_de          uiuc_aircraft.h
 791 ice kCD_dr <kCD_dr>     # []          icing constant for CD_dr          uiuc_aircraft.h
 792 ice kCD_df <kCD_df>     # []          icing constant for CD_df          uiuc_aircraft.h
 793 ice kCD_adf <kCD_adf>   # []          icing constant for CD_adf         uiuc_aircraft.h
 794
 795 ice kCXo <kCXo>         # []          icing constant for CXo            uiuc_aircraft.h
 796 ice kCXK <kCXo>         # []          icing constant for CXK            uiuc_aircraft.h
 797 ice kCX_a <kCX_a>       # []          icing constant for CX_a           uiuc_aircraft.h
 798 ice kCX_a2 <kCX_a2>     # []          icing constant for CX_a2          uiuc_aircraft.h
 799 ice kCX_a3 <kCX_a3>     # []          icing constant for CX_a3          uiuc_aircraft.h
 800 ice kCX_q <kCX_q>       # []          icing constant for CX_q           uiuc_aircraft.h
 801 ice kCX_de <kCX_de>     # []          icing constant for CX_de          uiuc_aircraft.h
 802 ice kCX_dr <kCX_dr>     # []          icing constant for CX_dr          uiuc_aircraft.h
 803 ice kCX_df <kCX_df>     # []          icing constant for CX_df          uiuc_aircraft.h
 804 ice kCX_adf <kCX_adf>   # []          icing constant for CX_adf         uiuc_aircraft.h
 805
 806 ice kCLo <kCLo>         # []          icing constant for CLo            uiuc_aircraft.h
 807 ice kCL_a <kCL_a>       # []          icing constant for CL_a           uiuc_aircraft.h
 808 ice kCL_adot <kCL_adot> # []          icing constant for CL_adot        uiuc_aircraft.h
 809 ice kCL_q <kCL_q>       # []          icing constant for CL_q           uiuc_aircraft.h
 810 ice kCL_de <kCL_de>     # []          icing constant for CL_de          uiuc_aircraft.h
 811 ice kCL_df <kCL_df>     # []          icing constant for CL_df          uiuc_aircraft.h
 812 ice kCL_adf <kCL_adf>   # []          icing constant for CL_adf         uiuc_aircraft.h
 813
 814 ice kCZo <kCZo>         # []          icing constant for CZo            uiuc_aircraft.h
 815 ice kCZ_a <kCZ_a>       # []          icing constant for CZ_a           uiuc_aircraft.h
 816 ice kCZ_a2 <kCZ_a2>     # []          icing constant for CZ_a2          uiuc_aircraft.h
 817 ice kCZ_a3 <kCZ_a3>     # []          icing constant for CZ_a3          uiuc_aircraft.h
 818 ice kCZ_adot <kCZ_adot> # []          icing constant for CZ_adot        uiuc_aircraft.h
 819 ice kCZ_q <kCZ_q>       # []          icing constant for CZ_q           uiuc_aircraft.h
 820 ice kCZ_de <kCZ_de>     # []          icing constant for CZ_de          uiuc_aircraft.h
 821 ice kCZ_df <kCZ_df>     # []          icing constant for CZ_df          uiuc_aircraft.h
 822 ice kCZ_adf <kCZ_adf>   # []          icing constant for CZ_adf         uiuc_aircraft.h
 823 ice kCZ_deb2 <kCZ_deb2> # []          icing constant for CZ_deb2        uiuc_aircraft.h
 824
 825 ice kCmo <kCmo>         # []          icing constant for Cmo            uiuc_aircraft.h
 826 ice kCm_a <kCm_a>       # []          icing constant for Cm_a           uiuc_aircraft.h
 827 ice kCm_a2 <kCm_a2>     # []          icing constant for Cm_a2          uiuc_aircraft.h
 828 ice kCm_a3 <kCm_a3>     # []          icing constant for Cm_a3          uiuc_aircraft.h
 829 ice kCm_adot <kCm_adot> # []          icing constant for Cm_adot        uiuc_aircraft.h
 830 ice kCm_q <kCm_q>       # []          icing constant for Cm_q           uiuc_aircraft.h
 831 ice kCm_r <kCm_r>       # []          icing constant for Cm_r           uiuc_aircraft.h
 832 ice kCm_de <kCm_de>     # []          icing constant for Cm_de          uiuc_aircraft.h
 833 ice kCm_df <kCm_df>     # []          icing constant for Cm_df          uiuc_aircraft.h
 834
 835 ice kCYo <kCYo>         # []          icing constant for CYo            uiuc_aircraft.h
 836 ice kCY_beta <kCy_beta> # []          icing constant for CY_beta        uiuc_aircraft.h
 837 ice kCY_p <kCY_p>       # []          icing constant for CY_p           uiuc_aircraft.h
 838 ice kCY_r <kCY_r>       # []          icing constant for CY_r           uiuc_aircraft.h
 839 ice kCY_da <kCY_da>     # []          icing constant for CY_da          uiuc_aircraft.h
 840 ice kCY_dr <kCY_dr>     # []          icing constant for CY_dr          uiuc_aircraft.h
 841 ice kCY_dra <kCY_dra>   # []          icing constant for CY_dra         uiuc_aircraft.h
 842 ice kCY_bdot <kCY_bdot> # []          icing constant for CY_bdot        uiuc_aircraft.h
 843
 844 ice kClo <kClo>         # []          icing constant for Clo            uiuc_aircraft.h
 845 ice kCl_beta <kCl_beta> # []          icing constant for Cl_beta        uiuc_aircraft.h
 846 ice kCl_p <kCl_p>       # []          icing constant for Cl_p           uiuc_aircraft.h
 847 ice kCl_r <kCl_r>       # []          icing constant for Cl_r           uiuc_aircraft.h
 848 ice kCl_da <kCl_da>     # []          icing constant for Cl_da          uiuc_aircraft.h
 849 ice kCl_dr <kCl_dr>     # []          icing constant for Cl_dr          uiuc_aircraft.h
 850 ice kCl_daa <kCl_daa>   # []          icing constant for Cl_daa         uiuc_aircraft.h
 851
 852 ice kCno <kCno>         # []          icing constant for Cno            uiuc_aircraft.h
 853 ice kCn_beta <kCn_beta> # []          icing constant for Cn_beta        uiuc_aircraft.h
 854 ice kCn_b3 <kCn_b3>     # []          icing constant for Cn_b3          uiuc_aircraft.h
 855 ice kCn_p <kCn_p>       # []          icing constant for Cn_p           uiuc_aircraft.h
 856 ice kCn_q <kCn_q>       # []          icing constant for Cn_q           uiuc_aircraft.h
 857 ice kCn_r <kCn_r>       # []          icing constant for Cn_r           uiuc_aircraft.h
 858 ice kCn_da <kCn_da>     # []          icing constant for Cn_da          uiuc_aircraft.h
 859 ice kCn_dr <kCn_dr>     # []          icing constant for Cn_dr          uiuc_aircraft.h
 860
 861 ice beta_probe_wing <x_probe_wing> #  wing flow angle probe location    uiuc_aircraft.h
 862 ice beta_probe_wing <x_probe_tail> #  tail flow angle probe location    uiuc_aircraft.h
 863
 864
 865 record Simtime                # [s]       current sim time              global
 866 record dt                     # [s]       current time step             global
 867 record Weight                 # [lb]      aircraft gross takeoff weight uiuc_aircraft.h
 868 record Mass                   # [slug]    aircraft mass                 ls_generic.h
 869 record I_xx                   # [slug-ft^2] roll inertia                ls_generic.h
 870 record I_yy                   # [slug-ft^2] pitch inertia               ls_generic.h
 871 record I_zz                   # [slug-ft^2] yaw inertia                 ls_generic.h
 872 record I_xz                   # [slug-ft^2] lateral cross inertia       ls_generic.h
 873 record Dx_pilot               # [ft]      reference pilot x-location    ls_generic.h
 874 record Dy_pilot               # [ft]      reference pilot y-location    ls_generic.h
 875 record Dz_pilot               # [ft]      reference pilot z-location    ls_generic.h
 876 record Dx_cg                  # [ft]      cg x_location                 ls_generic.h
 877 record Dy_cg                  # [ft]      cg y_location                 ls_generic.h
 878 record Dz_cg                  # [ft]      cg z_location                 ls_generic.h
 879 record Lat_geocentric         # [rad]     geocentric latitude           ls_generic.h
 880 record Lon_geocentric         # [rad]     geocentric longitude          ls_generic.h
 881 record Radius_to_vehicle      # [ft]      geocentric distance           ls_generic.h
 882 record Latitude               # [rad]     geodetic latitude             ls_generic.h
 883 record Longitude              # [rad]     geodetic longitude            ls_generic.h
 884 record Altitude               # [ft]      geodetic altitude             ls_generic.h
 885 record Phi                    # [rad]     Euler bank angle              ls_generic.h
 886 record Theta                  # [rad]     Euler pitch attitude angle    ls_generic.h
 887 record Psi                    # [rad]     Euler heading angle           ls_generic.h
 888 record V_dot_north            # [ft/s^2]  local x-acceleration          ls_generic.h
 889 record V_dot_east             # [ft/s^2]  local y-acceleration          ls_generic.h
 890 record V_dot_down             # [ft/s^2]  local z-acceleration          ls_generic.h
 891 record U_dot_body             # [ft/s^2]  body x-acceleration           ls_generic.h
 892 record V_dot_body             # [ft/s^2]  body y-acceleration           ls_generic.h
 893 record W_dot_body             # [ft/s^2]  body z-acceleration           ls_generic.h
 894 record A_X_pilot              # [ft/s^2]  pilot x-acceleration          ls_generic.h
 895 record A_Y_pilot              # [ft/s^2]  pilot y-acceleration          ls_generic.h
 896 record A_Z_pilot              # [ft/s^2]  pilot z-acceleration          ls_generic.h
 897 record A_X_cg                 # [ft/s^2]  cg x-acceleration             ls_generic.h
 898 record A_Y_cg                 # [ft/s^2]  cg y-acceleration             ls_generic.h
 899 record A_Z_cg                 # [ft/s^2]  cg z-acceleration             ls_generic.h
 900 record N_X_pilot              # [ft/s^2]  pilot x-acceleration          ls_generic.h
 901 record N_Y_pilot              # [ft/s^2]  pilot y-acceleration          ls_generic.h
 902 record N_Z_pilot              # [ft/s^2]  pilot z-acceleration          ls_generic.h
 903 record N_X_cg                 # [ft/s^2]  cg x-acceleration             ls_generic.h
 904 record N_Y_cg                 # [ft/s^2]  cg y-acceleration             ls_generic.h
 905 record N_Z_cg                 # [ft/s^2]  cg z-acceleration             ls_generic.h
 906 record P_dot_body             # [rad/s^2] roll rate acceleration        ls_generic.h
 907 record Q_dot_body             # [rad/s^2] pitch rate acceleration       ls_generic.h
 908 record R_dot_body             # [rad/s^2] yaw rate acceleration         ls_generic.h
 909 record V_north                # [ft/s]    local x-velocity              ls_generic.h
 910 record V_east                 # [ft/s]    local y-velocity              ls_generic.h
 911 record V_down                 # [ft/s]    local z-velocity              ls_generic.h
 912 record V_north_rel_ground     # [ft/s]    local x-velocity wrt ground   ls_generic.h
 913 record V_east_rel_ground      # [ft/s]    local y-velocity wrt ground   ls_generic.h
 914 record V_down_rel_ground      # [ft/s]    local z-velocity wrt ground   ls_generic.h
 915 record V_north_airmass        # [ft/s]    local x-velocity of airmass   ls_generic.h
 916 record V_east_airmass         # [ft/s]    local y-velocity of airmass   ls_generic.h
 917 record V_down_airmass         # [ft/s]    local z-velocity of airmass   ls_generic.h
 918 record V_north_rel_airmass    # [ft/s]    local x-velocity wrt airmass  ls_generic.h
 919 record V_east_rel_airmass     # [ft/s]    local y-velocity wrt airmass  ls_generic.h
 920 record V_down_rel_airmass     # [ft/s]    local z-velocity wrt airmass  ls_generic.h
 921 record U_gust                 # [ft/s]    local turbulence x-velocity   ls_generic.h
 922 record V_gust                 # [ft/s]    local turbulence y-velocity   ls_generic.h
 923 record W_gust                 # [ft/s]    local turbulence z-velocity   ls_generic.h
 924 record U_body                 # [ft/s]    wind x-velocity in body axis  ls_generic.h
 925 record V_body                 # [ft/s]    wind y-velocity in body axis  ls_generic.h
 926 record W_body                 # [ft/s]    wind z-velocity in body axis  ls_generic.h
 927 record V_rel_wind             # [ft/s]    total freestream velocity     ls_generic.h
 928 record V_true_kts             # [kts]     true velocity                 ls_generic.h
 929 record V_rel_ground           # [ft/s]    total velocity wrt ground     ls_generic.h
 930 record V_inertial             # [ft/s]    total inertial velocity       ls_generic.h
 931 record V_ground_speed         # [ft/s]    airspeed wrt ground           ls_generic.h
 932 record V_equiv                # [ft/s]    equivalent airspeed           ls_generic.h
 933 record V_equiv_kts            # [kts]     equivalent airspeed           ls_generic.h
 934 record V_calibrated           # [ft/s]    calibrated airspeed           ls_generic.h
 935 record V_calibrated_kts       # [kts]     calibrated airspeed           ls_generic.h
 936 record P_local                # [rad/s]   local roll rate               ls_generic.h
 937 record Q_local                # [rad/s]   local pitch rate              ls_generic.h
 938 record R_local                # [rad/s]   local yaw rate                ls_generic.h
 939 record P_body                 # [rad/s]   body roll rate                ls_generic.h
 940 record Q_body                 # [rad/s]   body pitch rate               ls_generic.h
 941 record R_body                 # [rad/s]   body yaw rate                 ls_generic.h
 942 record P_total                # [rad/s]   total roll rate               ls_generic.h
 943 record Q_total                # [rad/s]   total pitch rate              ls_generic.h
 944 record R_total                # [rad/s]   total yaw rate                ls_generic.h
 945 record Phi_dot                # [rad/s]   bank angle rate               ls_generic.h
 946 record Theta_dot              # [rad/s]   pitch attitude angle rate     ls_generic.h
 947 record Psi_dot                # [rad/s]   heading angle rate            ls_generic.h
 948 record Latitude_dot           # [rad/s]   latitude rate                 ls_generic.h
 949 record Longitude_dot          # [rad/s]   longitude rate                ls_generic.h
 950 record Radius_dot             # [rad/s]   radius rate                   ls_generic.h
 951 record Alpha                  # [rad]     angle of attack               ls_generic.h
 952 record Alpha_deg              # [deg]     angle of attack (in degrees)  uiuc_aircraft.h
 953 record Alpha_dot              # [rad/s]   rate of change of alpha       ls_generic.h
 954 record Alpha_dot_deg          # [rad/s]   rate of change of alpha       uiuc_aircraft.h
 955 record Beta                   # [rad]     sideslip angle                ls_generic.h
 956 record Beta_deg               # [rad]     sideslip angle                uiuc_aircraft.h
 957 record Beta_dot               # [rad/s]   rate of change of beta        ls_generic.h
 958 record Beta_dot_deg           # [rad/s]   rate of change of beta        uiuc_aircraft.h
 959 record Gamma_vert             # [rad]     vertical flight path angle    ls_generic.h
 960 record Gamma_vert_deg         # [deg]     vertical flight path angle    uiuc_aircraft.h
 961 record Gamma_horiz            # [rad]     horizontal flight path angle  ls_generic.h
 962 record Gamma_horiz_deg        # [deg]     horizontal flight path angle  uiuc_aircraft.h
 963 record Density                # [slug/ft^3] air density                 ls_generic.h
 964 record V_sound                # [ft/s]    speed of sound                ls_generic.h
 965 record Mach_number            # []        Mach number                   ls_generic.h
 966 record Static_pressure        # [lb/ft^2] static pressure               ls_generic.h
 967 record Total_pressure         # [lb/ft^2] total pressure                ls_generic.h
 968 record Impact_pressure        # [lb/ft^2] impact pressure               ls_generic.h
 969 record Dynamic_pressure       # [lb/ft^2] dynamic pressure              ls_generic.h
 970 record Static_temperature     # [?]       static temperature            ls_generic.h
 971 record Total_temperature      # [?]       total temperature             ls_generic.h
 972 record Gravity                # [ft/s^2]  acceleration due to gravity   ls_generic.h
 973 record Sea_level_radius       # [ft]      Earth radius                  ls_generic.h
 974 record Earth_position_angle   # [rad]     Earth rotation angle          ls_generic.h
 975 record Runway_altitude        # [ft]      runway altitude               ls_generic.h
 976 record Runway_latitude        # [rad]     runway latitude               ls_generic.h
 977 record Runway_longitude       # [rad]     runway longititude            ls_generic.h
 978 record Runway_heading         # [rad]     runway heading                ls_generic.h
 979 record Radius_to_rwy          # [ft]      geocentric radius to runway   ls_generic.h
 980 record D_pilot_north_of_rwy   # [ft]      local pilot x-dist from rwy   ls_generic.h
 981 record D_pilot_east_of_rwy    # [ft]      local pilot y-dist from rwy   ls_generic.h
 982 record D_pilot_down_of_rwy    # [ft]      local pilot z-dist from rwy   ls_generic.h
 983 record X_pilot_rwy            # [ft]      pilot x-dist from rwy         ls_generic.h
 984 record Y_pilot_rwy            # [ft]      pilot y-dist from rwy         ls_generic.h
 985 record H_pilot_rwy            # [ft]      pilot z-dist from rwy         ls_generic.h
 986 record D_cg_north_of_rwy      # [ft]      local cg x-dist from rwy      ls_generic.h
 987 record D_cg_east_of_rwy       # [ft]      local cg y-dist from rwy      ls_generic.h
 988 record D_cg_down_of_rwy       # [ft]      local cg z-dist from rwy      ls_generic.h
 989 record X_cg_rwy               # [ft]      cg x-dist from rwy            ls_generic.h
 990 record Y_cg_rwy               # [ft]      cg y-dist from rwy            ls_generic.h
 991 record H_cg_rwy               # [ft]      cg z-dist from rwy            ls_generic.h
 992 record Throttle_pct           # [%]       throttle input                ls_cockpit.h
 993 record Throttle_3             # [%]       throttle deflection           ls_cockpit.h
 994 record Long_control           # []        pitch input                   ls_cockpit.h
 995 record Long_trim              # [rad]     longitudinal trim             ls_cockpit.h
 996 record Long_trim_deg          # [deg]     longitudinal trim             uiuc_aircraft.h
 997 record elevator               # [rad]     elevator deflection           uiuc_aircraft.h
 998 record elevator_deg           # [deg]     elevator deflection           uiuc_aircraft.h
 999 record Lat_control            # []        roll input                    ls_cockpit.h
1000 record aileron                # [rad]     aileron deflection            uiuc_aircraft.h
1001 record aileron_deg            # [deg]     aileron deflection            uiuc_aircraft.h
1002 record Rudder_pedal           # []        yaw input                     ls_cockpit.h
1003 record rudder                 # [rad]     rudder deflection             uiuc_aircraft.h
1004 record rudder_deg             # [deg]     rudder deflection             uiuc_aircraft.h
1005 record CDfaI                  # []        CD(alpha)                     uiuc_aircraft.h
1006 record CDfCLI                 # []        CD(CL), drag polar            uiuc_aircraft.h
1007 record CDfadeI                # []        CD(alpha,delta_e)             uiuc_aircraft.h
1008 record CD                     # []        drag coefficient              uiuc_aircraft.h
1009 record CLfaI                  # []        CL(alpha)                     uiuc_aircraft.h
1010 record CLfadeI                # []        CL(alpha,delta_e)             uiuc_aircraft.h
1011 record CL                     # []        lift coefficient              uiuc_aircraft.h
1012 record CmfaI                  # []        Cm(alpha)                     uiuc_aircraft.h
1013 record CmfadeI                # []        Cm(alpha,delta_e)             uiuc_aircraft.h
1014 record Cm                     # []        pitch moment coefficient      uiuc_aircraft.h
1015 record CYfadaI                # []        CY(alpha,delta_a)             uiuc_aircraft.h
1016 record CYfbetadrI             # []        CY(beta,delta_r)              uiuc_aircraft.h
1017 record CY                     # []        side-force coefficient        uiuc_aircraft.h
1018 record ClfadaI                # []        Cl(alpha,delta_a)             uiuc_aircraft.h
1019 record ClfbetadrI             # []        Cl(beta,delta_r)              uiuc_aircraft.h
1020 record Cl                     # []        roll moment coefficient       uiuc_aircraft.h
1021 record CnfadaI                # []        Cn(alpha,delta_a)             uiuc_aircraft.h
1022 record CnfbetadrI             # []        Cn(beta,delta_r)              uiuc_aircraft.h
1023 record Cn                     # []        yaw moment coefficient        uiuc_aircraft.h
1024 record CLclean_wing           # []        wing clean lift coefficient   uiuc_aircraft.h
1025 record CLiced_wing            # []        wing iced lift coefficient    uiuc_aircraft.h
1026 record CLclean_tail           # []        tail clean lift coefficient   uiuc_aircraft.h
1027 record CLiced_tail            # []        tail iced lift coefficient    uiuc_aircraft.h
1028 record Lift_clean_wing        # [lb]      wing clean lift force         uiuc_aircraft.h
1029 record Lift_iced_wing         # [lb]      wing iced lift force          uiuc_aircraft.h
1030 record Lift_clean_tail        # [lb]      tail clean lift force         uiuc_aircraft.h
1031 record Lift_iced_tail         # [lb]      tail iced lift force          uiuc_aircraft.h
1032 record Gamma_clean_wing       # [ft^2/s]  wing clean circulation        uiuc_aircraft.h
1033 record Gamma_iced_wing        # [ft^2/s]  wing iced circulation         uiuc_aircraft.h
1034 record Gamma_clean_tail       # [ft^2/s]  tail clean circulation        uiuc_aircraft.h
1035 record Gamma_iced_tail        # [ft^2/s]  tail iced circulation         uiuc_aircraft.h
1036 record w_clean_wing           # [ft/s]    wing clean downwash           uiuc_aircraft.h
1037 record w_iced_wing            # [ft/s]    wing iced downwash            uiuc_aircraft.h
1038 record w_clean_tail           # [ft/s]    tail clean downwash           uiuc_aircraft.h
1039 record w_iced_tail            # [ft/s]    tail iced downwash            uiuc_aircraft.h
1040 record V_total_clean_wing     # [ft/s]    wing clean velocity           uiuc_aircraft.h
1041 record V_total_iced_wing      # [ft/s]    wing iced velocity            uiuc_aircraft.h
1042 record V_total_clean_tail     # [ft/s]    tail clean velocity           uiuc_aircraft.h
1043 record V_total_iced_tail      # [ft/s]    tail iced velocity            uiuc_aircraft.h
1044 record beta_flow_clean_wing   # [rad]     wing clean flow angle         uiuc_aircraft.h
1045 record beta_flow_clean_wing_deg # [deg]   wing clean flow angle         uiuc_aircraft.h
1046 record beta_flow_iced_wing    # [rad]     wing iced flow angle          uiuc_aircraft.h
1047 record beta_flow_iced_wing_deg # [deg]    wing iced flow angle          uiuc_aircraft.h
1048 record beta_flow_clean_tail   # [rad]     tail clean flow angle         uiuc_aircraft.h
1049 record beta_flow_clean_tail_deg # [deg]   tail clean flow angle         uiuc_aircraft.h
1050 record beta_flow_iced_tail    # [rad]     tail iced flow angle          uiuc_aircraft.h
1051 record beta_flow_iced_tail_deg # [deg]    tail iced flow angle          uiuc_aircraft.h
1052 record Dbeta_flow_wing        # [rad]     difference in wing flow angle uiuc_aircraft.h
1053 record Dbeta_flow_wing_deg    # [deg]     difference in wing flow angle uiuc_aircraft.h
1054 record Dbeta_flow_tail        # [rad]     difference in tail flow angle uiuc_aircraft.h
1055 record Dbeta_flow_tail_deg    # [deg]     difference in tail flow angle uiuc_aircraft.h
1056 record pct_beta_flow_wing     # [%]       difference in wing flow angle uiuc_aircraft.h
1057 record pct_beta_flow_tail     # [%]       difference in tail flow angle uiuc_aircraft.h
1058 record F_X_wind               # [lb]      aero x-force in wind-axes     ls_generic.h
1059 record F_Y_wind               # [lb]      aero y-force in wind-axes     ls_generic.h
1060 record F_Z_wind               # [lb]      aero z-force in wind-axes     ls_generic.h
1061 record F_X_aero               # [lb]      aero x-force in body-axes     ls_generic.h
1062 record F_Y_aero               # [lb]      aero y-force in body-axes     ls_generic.h
1063 record F_Z_aero               # [lb]      aero z-force in body-axes     ls_generic.h
1064 record F_X_engine             # [lb]      prop x-force in body-axes     ls_generic.h
1065 record F_Y_engine             # [lb]      prop y-force in body-axes     ls_generic.h
1066 record F_Z_engine             # [lb]      prop z-force in body-axes     ls_generic.h
1067 record F_X_gear               # [lb]      gear x-force in body-axes     ls_generic.h
1068 record F_Y_gear               # [lb]      gear y-force in body-axes     ls_generic.h
1069 record F_Z_gear               # [lb]      gear z-force in body-axes     ls_generic.h
1070 record F_X                    # [lb]      total x-force in body-axes    ls_generic.h
1071 record F_Y                    # [lb]      total y-force in body-axes    ls_generic.h
1072 record F_Z                    # [lb]      total z-force in body-axes    ls_generic.h
1073 record F_nort                 # [lb]      total x-force in local-axes   ls_generic.h
1074 record F_east                 # [lb]      total y-force in local-axes   ls_generic.h
1075 record F_down                 # [lb]      total z-force in local-axes   ls_generic.h
1076 record M_l_aero               # [ft-lb]   aero roll mom in body axes    ls_generic.h
1077 record M_m_aero               # [ft-lb]   aero pitch mom in body axes   ls_generic.h
1078 record M_n_aero               # [ft-lb]   aero yaw mom in body axes     ls_generic.h
1079 record M_l_engine             # [ft-lb]   prop roll mom in body axes    ls_generic.h
1080 record M_m_engine             # [ft-lb]   prop pitch mom in body axes   ls_generic.h
1081 record M_n_engine             # [ft-lb]   prop yaw mom in body axes     ls_generic.h
1082 record M_l_gear               # [ft-lb]   gear roll mom in body axes    ls_generic.h
1083 record M_m_gear               # [ft-lb]   gear pitch mom in body axes   ls_generic.h
1084 record M_n_gear               # [ft-lb]   gear yaw mom in body axes     ls_generic.h
1085 record M_l_rp                 # [ft-lb]   total roll mom in body axes   ls_generic.h
1086 record M_m_rp                 # [ft-lb]   total pitch mom in body axes  ls_generic.h
1087 record M_n_rp                 # [ft-lb]   total yaw mom in body axes    ls_generic.h
1088
1089
1090 fog fog_segments <fog_segments> # [-] number of fog points after this line
1091 fog fog_point    <time> <intensity>
1092
1093 Note: Between each fog_point there is a linear interpolation
1094
1095 ============================FOG EXAMPLE===============================
1096
1097 fog fog_segments 4
1098 fog fog_point 30 500
1099 fog fog_point 35 200
1100 fog fog_point 40 -100
1101 fog fog_point 50 0
1102
1103 The first line says that there will be 4 fog_point statements following.
1104 From time 0 to 30 seconds, the fog will increase linearly to 500.  From
1105 30 to 35 seconds, the fog will decrease linearly to 200.  From 35 to 40
1106 seconds the fog will decrease to -100.  From 40 to 50 the fog will
1107 increase to 0.
1108 ======================================================================
1109
1110
1111 # the following command is implemented but the data is not used in any
1112 # equation of motion
1113 # hinge moment coefficient                                      []      uiuc_aircraft.h
1114 |misc simpleHingeMomentCoef <simpleHingeMomentCoef>
1115
1116
1117 **********************************************************************
1118
1119 **********************************************************************
1120 V. Mandatory Input:
1121
1122 The following data is required for the simulator to function;
1123 otherwise either the UIUC Aero Model or LaRCsim parts of the code will
1124 probably crash.
1125
1126 1) aircraft geometry   (UIUC Aero Model)
1127 bw        wingspan                       [ft]
1128 cbar      mean aerodynamic chord         [ft]
1129 Sw        wing planform area             [ft^2]
1130
1131 2) engine properties   (UIUC Engine Model)
1132 (some engine model must be specified, such as...)
1133 engine simpleSingle
1134           <or>
1135 engine c172
1136
1137 3) mass variables   (LaRCsim)
1138 Weight    aircraft gross takeoff weight  [lb]
1139           <or>
1140 Mass      aircraft mass                  [slug]
1141 I_xx      roll inertia                   [slug-ft^2]
1142 I_yy      pitch inertia                  [slug-ft^2]
1143 I_zz      yaw inertia                    [slug-ft^2]
1144 I_xz      lateral cross inertia          [slug-ft^2]
1145
1146 4) aerodynamic force/moment components   (Aero Model)
1147 CLo       lift coef for all angles = 0   []
1148 CL_a      lift curve slope, d(CL)/d(alpha) [/rad]
1149 CDo       drag coef for all angles = 0   []
1150 CDK       induced drag constant          []
1151           <or>
1152 CD_a      d(CD)/d(alpha)                 [/rad]
1153 Cmo       pitch mom coef for all angles=0 []
1154 Cm_a      d(Cm)/d(alpha)                 [/rad]
1155 CY_beta   d(CY)/d(beta)                  [/rad]
1156 Cl_beta   d(Cl)/d(beta)                  [/rad]
1157 Cn_beta   d(Cn)/d(beta)                  [/rad]
1158
1159 5) gear properties
1160 (some gear properties must be defined otherwise the aircraft
1161 will not behave properly on the ground)
1162 Dx_gear             x-offset from CG                        [ft]
1163 Dy_gear             y-offset from CG                        [ft]
1164 Dz_gear             z-offset from CG                        [ft]
1165 cgear               gear damping constant                   [lb/ft/s]
1166 kgear               gear spring constant                    [lb/ft]
1167 muGear              gear rolling friction coef              [-]
1168
1169
1170 **********************************************************************