1170 lines
68 KiB
Text
1170 lines
68 KiB
Text
************************************************
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* *
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* FGFS Reconfigurable Aircraft Flight Model *
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* Input File Documentation *
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* Version 0.81, September 14, 2001 *
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* *
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* Authors: *
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* Jeff Scott (jscott@mail.com) *
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* Bipin Sehgal (bsehgal@uiuc.edu) *
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* Robert Deters (rdeters@uiuc.edu) *
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* Michael Selig (m-selig@uiuc.edu) *
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* Dept of Aero and Astro Engineering *
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* University of Illinois at Urbana-Champaign *
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* Urbana, IL *
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* http://amber.aae.uiuc.edu/~m-selig *
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* *
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************************************************
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**********************************************************************
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NOTE: Most of the commands discussed in this documentation are
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currently implemented in the UIUC aerodynamics model. Those
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denoted by '|' are proposed and will likely be added in the
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future but are not currently implemented. Some commands are
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in use but not producing the desired results. These are
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clearly noted, so please do not attempt to use them at this
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time.
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**********************************************************************
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**********************************************************************
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This documentation includes:
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- Required and optional input lines.
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- Input line formats and conventions.
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Viewing this file in emacs makefile-mode with color makes this file
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easier to read.
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**********************************************************************
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**********************************************************************
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I. Conventions and Notations and Reading this Document:
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# ... Comments
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| Input line not yet implemented
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| Optional data
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| Sometimes indicates a feature not yet used,
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but proposed convention is indicated nevertheless.
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<...> Value or file name to be placed here
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|| Input line disabled
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|| Option disabled
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... Repeat similar data
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-> Continue onto next line
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**********************************************************************
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**********************************************************************
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II. General Input Line Format:
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Examples input lines include
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Cm Cmo 0.194 # [] Bray pg 33
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Cm Cm_a -2.12 # [/rad] Bray pg 33
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CL CLfa CLfa.dat 0 1 # [] Bray pg 50, Table 4.7
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These follow the more general input line form
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keyword variableName <value -or- file> | ->
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<value -or- file> # [units] <data source>
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Each term of the input line will be discussed in turn.
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(1) KEYWORDS
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============
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There currently exist the following variable keyword types:
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init Initial values for equation of motion
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geometry Aircraft-specific geometric quantities
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controlSurface Control surface deflections and properties
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|controlsMixer Control surface mixer options
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mass Aircraft-specific mass properties
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engine Propulsion data
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CD Aerodynamic x-force quantities (longitudinal)
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CL Aerodynamic z-force quantities (longitudinal)
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Cm Aerodynamic m-moment quantities (longitudinal)
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CY Aerodynamic y-force quantities (lateral)
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Cl Aerodynamic l-moment quantities (lateral)
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Cn Aerodynamic n-moment quantities (lateral)
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gear Landing gear model quantities
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ice Icing model parameters
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record Record desired quantites to file
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misc Miscellaneous inputs
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fog Fog field quantities
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As each line of the input file is read, the code recognizes the
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keyword, enters the appropriate switch statement in the code, and
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proceeds to read the next term in the input line.
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(2) VARIABLE NAMES
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==================
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The variable name indicates the form of the variable itself. This
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form may be a constant, a stability derivative (a specific form of a
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constant), or a variable-dimensional lookup table. More variable
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types can be easily prescribed by defining a new convention. The
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variable name may also indicate that the quantity is to be calculated
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from a hard-coded equation or set of equations provided at an
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appropriate location within the code.
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If the parameter name denotes a constant, a numerical value will
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follow the variable name. If a lookup table, the name of the table
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containing the data will follow.
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More than one value or file name can be specified if the code is
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intended to read in multiple pieces of data when implementing the
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particular switch in question (see also OPTIONAL data, section (3)).
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The conventions used for naming the variables are provided below.
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Several of these variable names are not currently used.
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1) variable class
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_ denotes stability derivative
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f "function of" (indicates data table)
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2) timing data (global simulator variables)
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Simtime current simulator time [s]
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dt current simulator time step [s]
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3) aircraft position data
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Lat_geocentric geocentric latitude of CG [rad]
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Lon_geocentric geocentric longitude of CG [rad]
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Radius_to_vehicle distance of CG from inertial frame [ft]
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Latitude geodetic latitude of CG [rad]
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Longitude geodetic longitude of CG [rad]
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Altitude height of CG above reference ellipsoid [ft]
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Phi Euler bank/roll angle [rad]
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Theta Euler pitch attitude angle [rad]
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Psi Euler heading angle [rad]
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4) aircraft accelerations
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V_dot_north local x-acceleration [ft/s^2]
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V_dot_east local y-acceleration [ft/s^2]
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V_dot_down local z-acceleration [ft/s^2]
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U_dot_body body x-acceleration [ft/s^2]
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V_dot_body body y-acceleration [ft/s^2]
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W_dot_body body z-acceleration [ft/s^2]
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A_X_pilot pilot x-acceleration [ft/s^2]
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A_Y_pilot pilot y-acceleration [ft/s^2]
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A_Z_pilot pilot z-acceleration [ft/s^2]
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A_X_cg center of gravity x-acceleration [ft/s^2]
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A_Y_cg center of gravity x-acceleration [ft/s^2]
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A_Z_cg center of gravity x-acceleration [ft/s^2]
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N_X_pilot pilot x-acceleration [ft/s^2]
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N_Y_pilot pilot y-acceleration [ft/s^2]
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N_Z_pilot pilot z-acceleration [ft/s^2]
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N_X_cg center of gravity x-acceleration [ft/s^2]
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N_Y_cg center of gravity Y-acceleration [ft/s^2]
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N_Z_cg center of gravity Z-acceleration [ft/s^2]
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P_dot_body roll rate acceleration [rad/s^2]
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Q_dot_body pitch rate acceleration [rad/s^2]
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R_dot_body yaw rate acceleration [rad/s^2]
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5) aircraft velocities
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V_north local x-velocity [ft/s]
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V_east local y-velocity [ft/s]
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V_down local z-velocity [ft/s]
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V_north_rel_ground local x-velocity with respect to ground [ft/s]
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V_east_rel_ground local y-velocity with respect to ground [ft/s]
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V_down_rel_ground local z-velocity with respect to ground [ft/s]
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V_north_airmass local x-velocity of steady airmass [ft/s]
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V_east_airmass local y-velocity of steady airmass [ft/s]
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V_down_airmass local z-velocity of steady airmass [ft/s]
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V_north_rel_airmass local x-velocity wrt steady airmass [ft/s]
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V_east_rel_airmass local y-velocity wrt steady airmass [ft/s]
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V_down_rel_airmass local z-velocity wrt steady airmass [ft/s]
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U_gust local linear turbulence x-velocity [ft/s]
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V_gust local linear turbulence y-velocity [ft/s]
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W_gust local linear turbulence z-velocity [ft/s]
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U_body wind x-velocity in body axis [ft/s]
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V_body wind y-velocity in body axis [ft/s]
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W_body wind z-velocity in body axis [ft/s]
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V_rel_wind total wind velocity (freestream) [ft/s]
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V_true_kts true velocity [kts]
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V_rel_ground total velocity wrt ground [ft/s]
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V_inertial total inertial velocity [ft/s]
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V_ground_speed velocity at right angles to local vertical [ft/s]
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V_equiv equivalent airspeed [ft/s]
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V_equiv_kts equivalent airspeed [kts]
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V_calibrated calibrated indicated airspeed [ft/s]
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V_calibrated_kts calibrated indicated airspeed [kts]
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P_local local roll rate [rad/s]
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Q_local local pitch rate [rad/s]
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R_local local yaw rate [rad/s]
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P_body body roll rate [rad/s]
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Q_body body pitch rate [rad/s]
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R_body body yaw rate [rad/s]
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P_total roll rate of body axis wrt local axis [rad/s]
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Q_total pitch rate of body axis wrt local axis [rad/s]
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R_total yaw rate of body axis wrt local axis [rad/s]
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Phi_dot change in bank angle rate [rad/s]
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Theta_dot change in pitch attitude angle rate [rad/s]
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Psi_dot change in heading angle rate [rad/s]
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Latitude_dot change in geocentric latitude rate [rad/s]
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Longitude_dot change in geocentric longitude rate [rad/s]
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Radius_dot change in geocentric radius rate [ft/s]
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6) angles
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Alpha angle of attack [rad]
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Alpha_deg angle of attack [deg]
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Alpha_dot rate of change of alpha [rad/s]
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Alpha_dot_deg rate of change of alpha [deg/s]
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Beta sideslip angle [rad]
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Beta_deg sideslip angle [deg]
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Beta_dot rate of change of beta [rad]
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Beta_dot_deg rate of change of beta [deg]
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Gamma_vert local vertical flight path angle [rad]
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Gamma_ver_deg local vertical flight path angle [deg]
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Gamma_horiz local horizontal flight path angle [rad]
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Gamma_horiz_deg local horizontal flight path angle [deg]
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7) atmosperic properties
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Density atmospheric density [slug/ft^3]
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V_sound speed of sound [ft/s]
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Mach_number free-stream Mach number []
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M Mach number []
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Re Reynolds number []
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Static_pressure static pressure [lb/ft^2]
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Total_pressure total pressure [lb/ft^2]
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Impact_pressure impact pressure [lb/ft^2]
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Dynamic_pressure dynamic pressure [lb/ft^2]
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Static_temperature static temperature [deg F?]
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Total_temperature total temperature [deg F?]
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8) Earth properties
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Gravity acceleration due to gravity [ft/s^2]
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Sea_level_radius local Earth radius [ft]
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Earth_position_angle Earth rotation angle since reference time [rad]
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Runway_altitude runway height above local sea level [ft]
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Runway_latitude runway latitude [rad]
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Runway_longitude runway longitude [rad]
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Runway_heading runway heading [rad]
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Radius_to_rwy geocentric radius to runway [ft]
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D_pilot_north_of_rwy local pilot x-distance from runway [ft]
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D_pilot_east_of_rwy local pilot y-distance from runway [ft]
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D_pilot_down_of_rwy local pilot z-distance from runway [ft]
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X_pilot_rwy pilot x-distance from rwy in rwy axis [ft]
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Y_pilot_rwy pilot y-distance from rwy in rwy axis [ft]
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H_pilot_rwy pilot z-distance from rwy in rwy axis [ft]
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D_cg_north_of_rwy local cg x-distance from runway [ft]
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D_cg_east_of_rwy local cg y-distance from runway [ft]
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D_cg_down_of_rwy local cg z-distance from runway [ft]
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X_cg_rwy cg x-distance from rwy in rwy axis [ft]
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Y_cg_rwy cg y-distance from rwy in rwy axis [ft]
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H_cg_rwy cg z-distance from rwy in rwy axis [ft]
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9) aircraft geometric variables
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bw wingspan [ft]
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cbar mean aerodynamic chord [ft]
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Sw wing planform area [ft^2]
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|iw wing incidence angle [deg]
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|bc canard span [ft]
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|cc canard (mean) chord [ft]
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|Sc canard area [ft^2]
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|ic canard incidence angle [deg]
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bh horizontal tail span [ft]
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ch horizontal tail (mean) chord [ft]
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Sh horizontal tail area [ft^2]
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ih horizontal tail incidence angle [deg]
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|bv vertical tail span (height) [ft]
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|cv vertical tail (mean) chord [ft]
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|iv vertical tail incidence angle [deg]
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|Sv vertical tail area [ft^2]
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Dx_pilot reference pilot x-location [ft]
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Dy_pilot reference pilot y-location [ft]
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Dz_pilot referende pilot z-location [ft]
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Dx_cg reference center of gravity x-loc [ft]
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Dy_cg reference center of gravity y-loc [ft]
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Dz_cg reference center of gravity z-loc [ft]
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10) aircraft control surface properties
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|Sa aileron area [ft^2]
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|Se elevator area [ft^2]
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|Sf flap area [ft^2]
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|Sr rudder area [ft^2]
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Long_control pitch control input []
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Long_trim longitudinal trim input [rad]
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set_Long_trim set longitudinal trim to constant[rad]
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zero_Long_trim set longitudinal trim to zero [deg]
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elevator elevator deflection [rad]
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Lat_control roll control input []
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aileron aileron deflection [rad]
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Rudder_pedal yaw control input []
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rudder rudder deflection [rad]
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|flap flap deflection [rad]
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11) user-specified control surface deflections
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elevator_step_angle elevator step input angle [deg]
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elevator_step_startTime elevator step input starting time [s]
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elevator_singlet_angle elevator singlet input angle [deg]
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elevator_singlet_startTime elevator singlet input starting time [s]
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elevator_singlet_duration elevator singlet time duration [s]
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elevator_doublet_angle elevator singlet input angle [deg]
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elevator_doublet_startTime elevator doublet input starting time [s]
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elevator_doublet_duration elevator doublet TOTAL time duration [s]
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elevator_input_file file of elevator deflections vs. time [s,deg]
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aileron_input_file file of aileron deflections vs. time [s,deg]
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rudder_input_file file of rudder deflections vs. time [s,deg]
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12) mass variables
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Weight gross takeoff weight [lb]
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Mass aircraft mass (used by LaRCsim) [slug]
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I_xx roll inertia [slug-ft^2]
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I_yy pitch inertia [slug-ft^2]
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I_zz yaw inertia [slug-ft^2]
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I_xz lateral cross inertia [slug-ft^2]
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13) engine/propulsion variables
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|thrust engine thrust [lb]
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simpleSingle treat all engines as one; max thrust [lb]
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Throttle_pct throttle input ("stick") []
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Throttle_3 throttle deflection (determines thrust) [%]
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14) force/moment coefficients
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CD coefficient of drag []
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CY coefficient of side-force []
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CL coefficient of lift []
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Cl coefficient of roll moment []
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Cm coefficient of pitching moment []
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Cn coefficient of yaw moment []
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|CT coefficient of thrust []
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15) total forces/moments
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F_X_wind aerodynamic x-force in wind-axes [lb]
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F_Y_wind aerodynamic y-force in wind-axes [lb]
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F_Z_wind aerodynamic z-force in wind-axes [lb]
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F_X_aero aerodynamic x-force in body-axes [lb]
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F_Y_aero aerodynamic y-force in body-axes [lb]
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F_Z_aero aerodynamic z-force in body-axes [lb]
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F_X_engine propulsion x-force in body axes [lb]
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F_Y_engine propulsion y-force in body axes [lb]
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F_Z_engine propulsion z-force in body axes [lb]
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F_X_gear gear x-force in body axes [lb]
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F_Y_gear gear y-force in body axes [lb]
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F_Z_gear gear z-force in body axes [lb]
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F_X total x-force in body-axes [lb]
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F_Y total y-force in body-axes [lb]
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F_Z total z-force in body-axes [lb]
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F_north total x-force in local-axes [lb]
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F_east total y-force in local-axes [lb]
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F_down total z-force in local-axes [lb]
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M_l_aero aero roll-moment in body-axes [ft-lb]
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M_m_aero aero pitch-moment in body-axes [ft-lb]
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M_n_aero aero yaw-moment in body-axes [ft-lb]
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M_l_engine prop roll-moment in body axes [ft-lb]
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M_m_engine prop pitch-moment in body axes [ft-lb]
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M_n_engine prop yaw-moment in body axes [ft-lb]
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M_l_gear gear roll-moment in body axes [ft-lb]
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M_m_gear gear pitch-moment in body axes [ft-lb]
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M_n_gear gear yaw-moment in body axes [ft-lb]
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M_l_rp total roll-moment [ft-lb]
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M_m_rp total pitch-moment [ft-lb]
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M_n_rp total yaw-moment [ft-lb]
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16) landing gear properties
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Dx_gear x-offset from CG [ft]
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Dy_gear y-offset from CG [ft]
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Dz_gear z-offset from CG [ft]
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cgear gear damping constant [lb/ft/s]
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kgear gear spring constant [lb/ft]
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muGear gear rolling friction coef [-]
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|strutLength gear strut length [ft]
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17) icing model parameters
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iceTime time when icing begins [s]
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transientTime time period over which eta increases to final [s]
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eta_ice_final icing severity factor at end of transient time []
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kCA icing constants for associated aero coef. [] (see IV)
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beta_probe_wing location of flow angle probe on wing [ft]
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beta_probe_tail location of flow angle probe on tail [ft]
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18) subscripts
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o value for all angles = 0 (alfa, beta, etc)
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a angle of attack
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a2 alpha squared
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a3 alpha cubed
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adot rate change in angle alpha
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beta sideslip angle
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b2 beta squared
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b3 beta cubed
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bdot rate change in beta
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p roll rate
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q pitch rate
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r yaw rate
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|pdot rate change in p
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|qdot rate change in q
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|rdot rate change in r
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|udot rate change in x-velocity
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da aileron deflection
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de elevator deflection
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dr rudder deflection
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|df flap deflection
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|df2 flap deflection for second set
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|df3 flap deflection for third set
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max maximum
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min minimum
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19) miscellaneous
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recordRate number of times to record data per second [/s]
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recordStartTime time to start recording outpud data [s]
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dyn_on_speed speed when dynamic pressure terms first computed [ft/s]
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nondim_rate_V_rel_wind use V_rel_wind to compute control rates []
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|simpleHingeMomentCoef hinge moment coefficient []
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20) fog
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fog_segments number of fog points following this line
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fog_points fog intensity and the time at which it occurs
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(3) | [OPTIONAL DATA]
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=====================
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An input line may also be used to provide optional data that
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will be used if provided but is not necessary for the code to
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operate. As with the variable data described in section (2), multiple
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values or data files may be provided if the code is written to use
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them.
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(4) # [COMMENTS]
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================
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Appended comments should be provided with each input line to indicate
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units on the variable in question and to indicate the source the data
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was drawn from.
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**********************************************************************
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**********************************************************************
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III. Sample Input Lines:
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CONSTANTS
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=========
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geometry bw <value> # geometric parameter, wingspan
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Cm Cm_a <value> # stability derivative, d(Cm)/d(alpha)
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controlSurface de <value> <value> # max and min elevator deflections
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LOOKUP TABLES
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=============
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CD CDfCL <file.dat> # CD(CL), drag polar data file
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Cm Cmfade <file.dat> # Cm(alpha,delta_e), moment data file
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HARD-CODED EQUATION
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===================
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CD CDfCL # CD(CL), drag calculated in code based on CL
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(none currently in use)
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**********************************************************************
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**********************************************************************
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IV. Input Line Definitions:
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|
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Of all the possible permutations of variable names described above in
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section II, only some are curently implemented in the code. These are
|
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described below. Comments, denoted by '#,' are used to define the
|
|
lines and to indicate examples of the data if additional clarity is
|
|
needed for unique situations. Again, those lines beginning with '|'
|
|
are not currently implemented in the code, but indicate planned
|
|
conventions in later versions.
|
|
|
|
# Key Variable Data Units Description Where Defined
|
|
#------------------------------------------------------------------------------------
|
|
|
|
init recordRate <recordRate> # [/s] record data n times per second uiuc_aircraft.h
|
|
|
|
# [s] time to start recording output data uiuc_aircraft.h
|
|
init recordStartTime <recordStartTime>
|
|
|
|
# [] use V_rel_wind to compute control rates (instead of U_body) uiuc_aircraft.h
|
|
init nondim_rate_V_rel_wind <nondim_rate_V_rel_wind>
|
|
|
|
# [ft/s] speed at which dynamic pressure terms are first computed uiuc_aircraft.h
|
|
init dyn_on_speed <dyn_on_speed>
|
|
|
|
init Dx_pilot <Dx_pilot> # [ft] reference pilot x-position ls_generic.h
|
|
init Dy_pilot <Dy_pilot> # [ft] reference pilot y-position ls_generic.h
|
|
init Dz_pilot <Dz_pilot> # [ft] reference pilot z-position ls_generic.h
|
|
|
|
# the following commands are currently conflicting with Flight
|
|
# Gear and are not working correctly:
|
|
|init Dx_cg <Dx_cg> # [ft] reference cg x_location ls_generic.h
|
|
|init Dy_cg <Dy_cg> # [ft] reference cg y_location ls_generic.h
|
|
|init Dz_cg <Dz_cg> # [ft] reference cg z_location ls_generic.h
|
|
|init V_north <V_north> # [ft/s] initial local x-velocity ls_generic.h
|
|
|init V_east <V_east> # [ft/s] initial local y-velocity ls_generic.h
|
|
|init V_down <V_down> # [ft/s] initial local z-velocity ls_generic.h
|
|
|init Altitude <Altitude> # [ft/s] initial altitude ls_generic.h
|
|
|
|
init U_body <U_body> # [ft/s] initial x-velocity in body axis ls_generic.h
|
|
init V_body <V_body> # [ft/s] initial y-velocity in body axis ls_generic.h
|
|
init W_body <W_body> # [ft/s] initial z-velocity in body axis ls_generic.h
|
|
init P_body <P_body> # [rad/s] initial roll rate ls_generic.h
|
|
init Q_body <Q_body> # [rad/s] initial pitch rate ls_generic.h
|
|
init R_body <R_body> # [rad/s] initial yaw rate ls_generic.h
|
|
init Phi <Phi> # [rad] initial bank angle ls_generic.h
|
|
init Theta <Theta> # [rad] initial pitch attitude angle ls_generic.h
|
|
init Psi <Psi> # [rad] initial heading angle ls_generic.h
|
|
init Alpha <Alpha> # [deg] initial angle of attack ls_generic.h
|
|
init Beta <Beta> # [deg] initial side slip angle ls_generic.h
|
|
init Long_trim <Long_trim> # [rad] longitudinal trim ls_cockpit.h
|
|
|
|
geometry bw <bw> # [ft] wingspan uiuc_aircraft.h
|
|
geometry cbar <cbar> # [ft] wing mean aero chord uiuc_aircraft.h
|
|
geometry Sw <Sw> # [ft^2] wing reference area uiuc_aircraft.h
|
|
|geometry iw <iw> # [deg] wing incidence angle uiuc_aircraft.h
|
|
|geometry bc <bc> # [ft] canard span uiuc_aircraft.h
|
|
|geometry cc <cc> # [ft] canard chord uiuc_aircraft.h
|
|
|geometry Sc <Sc> # [sq-ft] canard area uiuc_aircraft.h
|
|
|geometry ic <ic> # [deg] canard incidence angle uiuc_aircraft.h
|
|
geometry bh <bh> # [ft] horizontal tail span uiuc_aircraft.h
|
|
geometry ch <ch> # [ft] horizontal tail chord uiuc_aircraft.h
|
|
geometry Sh <Sh> # [sq-ft] horizontal tail area uiuc_aircraft.h
|
|
geometry ih <ih> # [deg] horiz tail incidence angle uiuc_aircraft.h
|
|
|geometry bv <bv> # [ft] vertical tail span uiuc_aircraft.h
|
|
|geometry cv <cv> # [ft] vertical tail chord uiuc_aircraft.h
|
|
|geometry Sv <Sv> # [sq-ft] vertical tail area uiuc_aircraft.h
|
|
|geometry iv <iv> # [deg] vert tail incidence angle uiuc_aircraft.h
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|
|
|
|controlSurface Se <Se> # [ft^2] elevator area uiuc_aircraft.h
|
|
|controlSurface Sa <Sa> # [ft^2] aileron area uiuc_aircraft.h
|
|
|controlSurface Sr <Sr> # [ft^2] rudder area uiuc_aircraft.h
|
|
|controlSurface Sf <Sf> # [ft^2] flap area uiuc_aircraft.h
|
|
controlSurface de <demax> <demin> # [deg] max/min elev deflections uiuc_aircraft.h
|
|
controlSurface da <damax> <damin> # [deg] max/min ail deflections uiuc_aircraft.h
|
|
controlSurface dr <drmax> <drmin> # [deg] max/min rud deflections uiuc_aircraft.h
|
|
|controlSurface df <dfmax> <dfmin> # [deg] max/min flap deflections uiuc_aircraft.h
|
|
|
|
# trim always set to some fixed input value (radians) [rad] uiuc_aircraft.h
|
|
controlSurface set_Long_trim <elevator_tab>
|
|
# Note: Do not use. Only works with pilot_elev_no and elevator_input. Use an elevator input file instead
|
|
|
|
# trim always set to some fixed input value (degrees) [deg] uiuc_aircraft.h
|
|
controlSurface set_Long_trim_deg <elevator_tab>
|
|
# Note: Do not use. Only works with pilot_elev_no and elevator_input. Use an elevator input file instead
|
|
|
|
controlSurface zero_Long_trim # [deg] trim always set to zero uiuc_aircraft.h
|
|
|
|
# elevator step input with deflection angle [deg] and starting time [s] uiuc_aircraft.h
|
|
controlSurface elevator_step <elevator_step_angle> <elevator_step_startTime>
|
|
|
|
# elevator singlet input with deflection angle [deg], starting time [s],
|
|
# and duration of input [s] uiuc_aircraft.h
|
|
controlSurface elevator_singlet <elevator_singlet_angle> ->
|
|
<elevator_singlet_startTime> <elevator_singlet_duration>
|
|
|
|
# elevator doublet input with deflection angle [deg], starting time [s],
|
|
# and TOTAL duration of input (both up and down deflections) [s] uiuc_aircraft.h
|
|
controlSurface elevator_doublet <elevator_doublet_angle> ->
|
|
<elevator_doublet_startTime> <elevator_doublet_duration>
|
|
|
|
# tabulated elevator input (as function of time) with conversion
|
|
# factor codes and starting time [s] uiuc_aircraft.h
|
|
controlSurface elevator_input <elevator_input_file> ->
|
|
<token_value_convert1> <token_value_convert2> ->
|
|
<elevator_input_startTime>
|
|
|
|
# tabulated aileron input (as function of time) with conversion
|
|
# factor codes and starting time [s] uiuc_aircraft.h
|
|
controlSurface aileron_input <aileron_input_file> ->
|
|
<token_value_convert1> <token_value_convert2> ->
|
|
<aileron_input_startTime>
|
|
|
|
# tabulated rudder input (as function of time) with conversion
|
|
# factor codes and starting time [s] uiuc_aircraft.h
|
|
controlSurface rudder_input <rudder_input_file> ->
|
|
<token_value_convert1> <token_value_convert2> ->
|
|
<rudder_input_startTime>
|
|
|
|
# ignore elevator input from the joystick/keyboard/mouse [-] uiuc_aircraf.h
|
|
controlSurface pilot_elev_no
|
|
# Note: Only works if elevator_input is used
|
|
|
|
# ignore aileron input from the joystick/keyboard/mouse [-] uiuc_aircraf.h
|
|
controlSurface pilot_ail_no
|
|
# Note: Only works if aileron_input is used
|
|
|
|
# ignore rudder input from the joystick/keyboard/mouse [-] uiuc_aircraf.h
|
|
controlSurface pilot_rud_no
|
|
# Note: Only works if rudder_input is used
|
|
|
|
|controlsMixer nomix <?> # [] no controls mixing uiuc_aircraft.h
|
|
|
|
|
|
mass Weight <Weight> # [lb] gross takeoff weight uiuc_aircraft.h
|
|
mass Mass <Mass> # [slug] gross takeoff mass ls_generic.h
|
|
mass I_xx <I_xx> # [slug-ft^2] roll inertia ls_generic.h
|
|
mass I_yy <I_yy> # [slug-ft^2] pitch inertia ls_generic.h
|
|
mass I_zz <I_zz> # [slug-ft^2] yaw inertia ls_generic.h
|
|
mass I_xz <I_xz> # [slug-ft^2] lateral cross inertia ls_generic.h
|
|
|
|
|
|
# maximum and minimum engine thrust [lb] uiuc_aircraft.h
|
|
|engine thrust <thrustMax> <thrustMin>
|
|
|
|
# simple single engine maximum thrust [lb] uiuc_aircraft.h
|
|
engine simpleSingle <simpleSingleMaxThrust>
|
|
|
|
engine c172 # use Cessna 172 engine model of Tony Peden
|
|
engine cherokee # use Piper Cherokee engine model
|
|
|
|
|
|
CL CLo <CLo> # [] lift coef for all angles = 0 uiuc_aircraft.h
|
|
CL CL_a <CL_a> # [/rad] lift curve slope, d(CL)/d(alpha) uiuc_aircraft.h
|
|
CL CL_adot <CL_adot> # [/rad] d(CL)/d(alpha)/da(time) uiuc_aircraft.h
|
|
CL CL_q <CL_q> # [/rad] d(CL)/d(q) uiuc_aircraft.h
|
|
CL CL_ih <CL_ih> # [/rad] CL due to horiz tail incidence uiuc_aircraft.h
|
|
CL CL_de <CL_de> # [/rad] d(CL)/d(de) uiuc_aircraft.h
|
|
|
|
# CL(alpha), conversion for CL, for alpha [] uiuc_aircraft.h
|
|
CL CLfa <CLfa.dat> <token_value_convert1> <token_value_convert2>
|
|
|
|
# CL(alpha,delta_e), conversion for CL, for alpha, for delta_e [] uiuc_aircraft.h
|
|
CL CLfade <CLfade.dat> <token_value_convert1> <token_value_convert2> ->
|
|
<token_value_convert3>
|
|
|
|
# the following are lift coefficients in the body axis
|
|
CL CZo <CZo> # [] lift coef for all angles = 0 uiuc_aircraft.h
|
|
CL CZ_a <Cz_a> # [/rad] lift curve slope, d(CZ)/d(alpha) uiuc_aircraft.h
|
|
CL CZ_a2 <CZ_a2> # [/rad] d(CZ)/d(alpha squared) uiuc_aircraft.h
|
|
CL CZ_a3 <CZ_a3> # [/rad] d(CZ)/d(alpha cubed) uiuc_aircraft.h
|
|
CL CZ_adot <CZ_adot> # [/rad] d(CZ)/d(alpha)/d(time) uiuc_aircraft.h
|
|
CL CZ_q <CZ_q> # [/rad] d(CZ)/d(q) uiuc_aircraft.h
|
|
CL CZ_de <CZ_de> # [/rad] d(CZ)/d(de) uiuc_aircraft.h
|
|
CL CZ_deb2 <CZ_deb2> # [/rad] d(CZ)/d(de, beta squared) uiuc_aircraft.h
|
|
CL CZ_df <CZ_df> # [/rad] d(CZ)/d(df) uiuc_aircraft.h
|
|
CL CZ_adf <CZ_adf> # [/rad] d(CZ)/d(alpha, df) uiuc_aircraft.h
|
|
|
|
# CZ(alpha), conversion for CZ, for alpha [] uiuc_aircraft.h
|
|
CL CZfa <CZfa.dat> <token_value_convert1> <token_value_convert2>
|
|
|
|
|CL CLfCT <CLfCT.dat> # CL(thrust coef) uiuc_aircraft.h
|
|
|CL CLfRe # CL(Reynolds #), equation uiuc_aircraft.h
|
|
|CL CL_afaM <CL_afaM.dat> # CL_alpha(alpha,Mach #) uiuc_aircraft.h
|
|
# these are sample examples that might be used in later versions of the code
|
|
|
|
|
|
# note that CD terms must come after CL for induced drag to be computed
|
|
CD CDo <CDo> # [] drag coef for all angles = 0 uiuc_aircraft.h
|
|
CD CDK <CDK> # [] induced drag constant 1/(pi*e*AR) uiuc_aircraft.h
|
|
CD CD_a <CD_a> # [/rad] d(CD)/d(alpha) uiuc_aircraft.h
|
|
CD CD_ih <CD_ih> # [/rad] CD due to horiz tail incidence uiuc_aircraft.h
|
|
CD CD_de <CD_de> # [/rad] d(CD)/d(delta_e) uiuc_aircraft.h
|
|
|
|
# CD(alpha), conversion for CD, for alpha [] uiuc_aircraft.h
|
|
CD CDfa <CDfa.dat> <token_value_convert1> <token_value_convert2>
|
|
|
|
# CD(CL) drag polar, conversion for CD, for CL [] uiuc_aircraft.h
|
|
CD CDfCL <CDfCL.dat> <token_value_convert1> <token_value_convert2>
|
|
|
|
# CD(alpha,delta_e), conversion for CD, for alpha, for delta_e [] uiuc_aircraft.h
|
|
CD CDfade <CDfade.dat> <token_value_convert1> <token_value_convert2> ->
|
|
<token_value_convert3>
|
|
|
|
# the following are drag coefficients in the body axis
|
|
CD CXo <CXo> # [] drag coef for all angles = 0 uiuc_aircraft.h
|
|
CD CXK <CXK> # [] induced drag constant 1/(pi*e*AR) uiuc_aircraft.h
|
|
CD CX_a <CX_a> # [/rad] d(CX)/d(alpha) uiuc_aircraft.h
|
|
CD CX_a2 <CX_a2> # [/rad] d(CX)/d(alpha squared) uiuc_aircraft.h
|
|
CD CX_a3 <CX_a3> # [/rad] d(CX)/d(alpha cubed) uiuc_aircraft.h
|
|
CD CX_q <CX_q> # [/rad] d(CX)/d(q) uiuc_aircraft.h
|
|
CD CX_de <CX_de> # [/rad] d(CX)/d(de) uiuc_aircraft.h
|
|
CD CX_dr <CX_dr> # [/rad] d(CX)/d(dr) uiuc_aircraft.h
|
|
CD CX_df <CX_df> # [/rad] d(CX)/d(df) uiuc_aircraft.h
|
|
CD CX_adf <CX_adf> # [/rad] d(CX)/d(alpha, df) uiuc_aircraft.h
|
|
|
|
|
|
Cm Cmo <Cmo> # [] pitch mom coef for all angles=0 uiuc_aircraft.h
|
|
Cm Cm_a <Cm_a> # [/rad] d(Cm)/d(alpha) uiuc_aircraft.h
|
|
Cm Cm_a2 <Cm_a2> # [/rad] d(Cm)/d(alpha squared) uiuc_aircraft.h
|
|
Cm Cm_adot <Cm_adot> # [/rad] d(Cm)/d(alpha)/d(time) uiuc_aircraft.h
|
|
Cm Cm_q <Cm_q> # [/rad] d(Cm)/d(q) uiuc_aircraft.h
|
|
Cm Cm_ih <Cm_ih> # [/rad] Cm due to horiz tail incidence uiuc_aircraft.h
|
|
Cm Cm_de <Cm_de> # [/rad] d(Cm)/d(de) uiuc_aircraft.h
|
|
Cm Cm_de <Cm_b2> # [/rad] d(Cm)/d(beta squared) uiuc_aircraft.h
|
|
Cm Cm_r <Cm_r> # [/rad] d(Cm)/d(r) uiuc_aircraft.h
|
|
Cm Cm_df <Cm_df> # [/rad] d(Cm)/d(df) uiuc_aircraft.h
|
|
|
|
# Cm(alpha), conversion for Cm, for alpha [] uiuc_aircraft.h
|
|
Cm Cmfa <Cmfa.dat> <token_value_convert1> <token_value_convert2>
|
|
|
|
# Cm(alpha,delta_e), conversion for Cm, for alpha, for delta_e [] uiuc_aircraft.h
|
|
Cm Cmfade <Cmfade.dat> <token_value_convert1> <token_value_convert2> ->
|
|
<token_value_convert3>
|
|
|
|
|
|
CY CYo <CYo> # [] side-force coef for all angles=0 uiuc_aircraft.h
|
|
CY CY_beta <CY_beta> # [/rad] d(CY)/d(beta) uiuc_aircraft.h
|
|
CY CY_p <CY_p> # [/rad] d(CY)/d(p) uiuc_aircraft.h
|
|
CY CY_r <CY_r> # [/rad] d(CY)/d(r) uiuc_aircraft.h
|
|
CY CY_da <CY_da> # [/rad] d(CY)/d(da) uiuc_aircraft.h
|
|
CY CY_dr <CY_dr> # [/rad] d(CY)/d(dr) uiuc_aircraft.h
|
|
CY CY_dra <CY_dra> # [/rad] d(CY)/d(dr, alpha) uiuc_aircraft.h
|
|
CY CY_dra <CY_bdot> # [/rad] d(CY)/d(beta)/d(time) uiuc_aircraft.h
|
|
|
|
# CY(alpha,delta_a), conversion for CY, for alpha, for delta_a [] uiuc_aircraft.h
|
|
CY CYfada <CYfada.dat> <token_value_convert1> <token_value_convert2> ->
|
|
<token_value_convert3>
|
|
|
|
# CY(beta,delta_r), conversion for CY, for beta, for delta_r [] uiuc_aircraft.h
|
|
CY CYfbetadr <CYfbetadr.dat> <token_value_convert1> <token_value_convert2> ->
|
|
<token_value_convert3>
|
|
|
|
|
|
Cl Clo <Clo> # [] roll mom coef for all angles=0 uiuc_aircraft.h
|
|
Cl Cl_beta <Cl_beta> # [/rad] d(Cl)/d(beta) uiuc_aircraft.h
|
|
Cl Cl_p <Cl_p> # [/rad] d(Cl)/d(p) uiuc_aircraft.h
|
|
Cl Cl_r <Cl_r> # [/rad] d(Cl)/d(r) uiuc_aircraft.h
|
|
Cl Cl_da <Cl_da> # [/rad] d(Cl)/d(da) uiuc_aircraft.h
|
|
Cl Cl_dr <Cl_dr> # [/rad] d(Cl)/d(dr) uiuc_aircraft.h
|
|
Cl Cl_daa <Cl_daa> # [/rad] d(Cl)/d(da, alpha) uiuc_aircraft.h
|
|
|
|
# Cl(alpha,delta_a), conversion for Cl, for alpha, for delta_a [] uiuc_aircraft.h
|
|
Cl Clfada <CYfada.dat> <token_value_convert1> <token_value_convert2> ->
|
|
<token_value_convert3>
|
|
|
|
# Cl(beta,delta_r), conversion for Cl, for beta, for delta_r [] uiuc_aircraft.h
|
|
Cl Clfbetadr <CYfbetadr.dat> <token_value_convert1> <token_value_convert2> ->
|
|
<token_value_convert3>
|
|
|
|
|
|
Cn Cno <Cno> # [] yaw mom coef for all angles=0 uiuc_aircraft.h
|
|
Cn Cn_beta <Cn_beta> # [/rad] d(Cn)/d(beta) uiuc_aircraft.h
|
|
Cn Cn_p <Cn_p> # [/rad] d(Cn)/d(p) uiuc_aircraft.h
|
|
Cn Cn_r <Cn_r> # [/rad] d(Cn)/d(r) uiuc_aircraft.h
|
|
Cn Cn_da <Cn_da> # [/rad] d(Cn)/d(da) uiuc_aircraft.h
|
|
Cn Cn_dr <Cn_dr> # [/rad] d(Cn)/d(dr) uiuc_aircraft.h
|
|
Cn Cn_q <Cn_q> # [/rad] d(Cn)/d(q) uiuc_aircraft.h
|
|
Cn Cn_b3 <Cn_b3> # [/rad] d(Cn)/d(beta cubed) uiuc_aircraft.h
|
|
|
|
# Cn(alpha,delta_a), conversion for Cn, for alpha, for delta_a [] uiuc_aircraft.h
|
|
Cn Cnfada <Cnfada.dat> <token_value_convert1> <token_value_convert2> ->
|
|
<token_value_convert3>
|
|
|
|
# Cn(beta,delta_r), conversion for Cn, for beta, for delta_r [] uiuc_aircraft.h
|
|
Cn Cnfbetadr <Cnfbetadr.dat> <token_value_convert1> <token_value_convert2> ->
|
|
<token_value_convert3>
|
|
|
|
=============================CONVERSION CODES================================
|
|
|
|
To calculate the aero forces, angles (eg, alfa, beta, elevator deflection, etc)
|
|
must be in radians. To convert input data in degree to radian, use a
|
|
conversion code of 1. To use no conversion, use a conversion code of 0.
|
|
|
|
------------------------------------------------
|
|
convert1/2/3 Action
|
|
------------------------------------------------
|
|
0 no conversion (multiply by 1)
|
|
1 convert degrees to radians
|
|
=============================================================================
|
|
|
|
|
|
gear Dx_gear <position> <Dx_gear> # [ft] x-offset from CG uiuc_aircraft.h
|
|
gear Dy_gear <position> <Dy_gear> # [ft] y-offset from CG uiuc_aircraft.h
|
|
gear Dz_gear <position> <Dz_gear> # [ft] z-offset from CG uiuc_aircraft.h
|
|
gear cgear <position> <cgear> # [lb/ft/s] gear damping constant uiuc_aircraft.h
|
|
gear kgear <position> <kgear> # [lb/ft] gear spring constant uiuc_aircraft.h
|
|
gear muRoll <position> <muRoll> # [-] gear rolling friction coef uiuc_aircraft.h
|
|
|gear strutLength <position> <sL> # [ft] gear strut length uiuc_aircraft.h
|
|
|
|
================================GEAR POSITION================================
|
|
|
|
There are 16 gear positions. Currently only the first three positions are
|
|
rolling wheels. Position 1 is reserved for the nose wheel, position 2 is
|
|
reserved for the right wheel, and position 3 is reserved for the left wheel.
|
|
The rest of the positions can be left out or used to define locations on the
|
|
plane such as the wing tips or tail. This way the wing tips or tail will not
|
|
go "through" the ground but "bounce off" the ground.
|
|
=============================================================================
|
|
|
|
|
|
ice iceTime <iceTime> # [s] time when icing begins uiuc_aircraft.h
|
|
|
|
# [s] period for eta_ice to reach eta_final uiuc_aircraft.h
|
|
ice transientTime <transientTime>
|
|
|
|
# [] icing severity factor uiuc_aircraft.h
|
|
ice eta_ice_final <eta_ice_final>
|
|
|
|
ice kCDo <kCDo> # [] icing constant for CDo uiuc_aircraft.h
|
|
ice kCDK <kCDo> # [] icing constant for CDK uiuc_aircraft.h
|
|
ice kCD_a <kCD_a> # [] icing constant for CD_a uiuc_aircraft.h
|
|
ice kCD_q <kCD_q> # [] icing constant for CD_q uiuc_aircraft.h
|
|
ice kCD_de <kCD_de> # [] icing constant for CD_de uiuc_aircraft.h
|
|
ice kCD_dr <kCD_dr> # [] icing constant for CD_dr uiuc_aircraft.h
|
|
ice kCD_df <kCD_df> # [] icing constant for CD_df uiuc_aircraft.h
|
|
ice kCD_adf <kCD_adf> # [] icing constant for CD_adf uiuc_aircraft.h
|
|
|
|
ice kCXo <kCXo> # [] icing constant for CXo uiuc_aircraft.h
|
|
ice kCXK <kCXo> # [] icing constant for CXK uiuc_aircraft.h
|
|
ice kCX_a <kCX_a> # [] icing constant for CX_a uiuc_aircraft.h
|
|
ice kCX_a2 <kCX_a2> # [] icing constant for CX_a2 uiuc_aircraft.h
|
|
ice kCX_a3 <kCX_a3> # [] icing constant for CX_a3 uiuc_aircraft.h
|
|
ice kCX_q <kCX_q> # [] icing constant for CX_q uiuc_aircraft.h
|
|
ice kCX_de <kCX_de> # [] icing constant for CX_de uiuc_aircraft.h
|
|
ice kCX_dr <kCX_dr> # [] icing constant for CX_dr uiuc_aircraft.h
|
|
ice kCX_df <kCX_df> # [] icing constant for CX_df uiuc_aircraft.h
|
|
ice kCX_adf <kCX_adf> # [] icing constant for CX_adf uiuc_aircraft.h
|
|
|
|
ice kCLo <kCLo> # [] icing constant for CLo uiuc_aircraft.h
|
|
ice kCL_a <kCL_a> # [] icing constant for CL_a uiuc_aircraft.h
|
|
ice kCL_adot <kCL_adot> # [] icing constant for CL_adot uiuc_aircraft.h
|
|
ice kCL_q <kCL_q> # [] icing constant for CL_q uiuc_aircraft.h
|
|
ice kCL_de <kCL_de> # [] icing constant for CL_de uiuc_aircraft.h
|
|
ice kCL_df <kCL_df> # [] icing constant for CL_df uiuc_aircraft.h
|
|
ice kCL_adf <kCL_adf> # [] icing constant for CL_adf uiuc_aircraft.h
|
|
|
|
ice kCZo <kCZo> # [] icing constant for CZo uiuc_aircraft.h
|
|
ice kCZ_a <kCZ_a> # [] icing constant for CZ_a uiuc_aircraft.h
|
|
ice kCZ_a2 <kCZ_a2> # [] icing constant for CZ_a2 uiuc_aircraft.h
|
|
ice kCZ_a3 <kCZ_a3> # [] icing constant for CZ_a3 uiuc_aircraft.h
|
|
ice kCZ_adot <kCZ_adot> # [] icing constant for CZ_adot uiuc_aircraft.h
|
|
ice kCZ_q <kCZ_q> # [] icing constant for CZ_q uiuc_aircraft.h
|
|
ice kCZ_de <kCZ_de> # [] icing constant for CZ_de uiuc_aircraft.h
|
|
ice kCZ_df <kCZ_df> # [] icing constant for CZ_df uiuc_aircraft.h
|
|
ice kCZ_adf <kCZ_adf> # [] icing constant for CZ_adf uiuc_aircraft.h
|
|
ice kCZ_deb2 <kCZ_deb2> # [] icing constant for CZ_deb2 uiuc_aircraft.h
|
|
|
|
ice kCmo <kCmo> # [] icing constant for Cmo uiuc_aircraft.h
|
|
ice kCm_a <kCm_a> # [] icing constant for Cm_a uiuc_aircraft.h
|
|
ice kCm_a2 <kCm_a2> # [] icing constant for Cm_a2 uiuc_aircraft.h
|
|
ice kCm_a3 <kCm_a3> # [] icing constant for Cm_a3 uiuc_aircraft.h
|
|
ice kCm_adot <kCm_adot> # [] icing constant for Cm_adot uiuc_aircraft.h
|
|
ice kCm_q <kCm_q> # [] icing constant for Cm_q uiuc_aircraft.h
|
|
ice kCm_r <kCm_r> # [] icing constant for Cm_r uiuc_aircraft.h
|
|
ice kCm_de <kCm_de> # [] icing constant for Cm_de uiuc_aircraft.h
|
|
ice kCm_df <kCm_df> # [] icing constant for Cm_df uiuc_aircraft.h
|
|
|
|
ice kCYo <kCYo> # [] icing constant for CYo uiuc_aircraft.h
|
|
ice kCY_beta <kCy_beta> # [] icing constant for CY_beta uiuc_aircraft.h
|
|
ice kCY_p <kCY_p> # [] icing constant for CY_p uiuc_aircraft.h
|
|
ice kCY_r <kCY_r> # [] icing constant for CY_r uiuc_aircraft.h
|
|
ice kCY_da <kCY_da> # [] icing constant for CY_da uiuc_aircraft.h
|
|
ice kCY_dr <kCY_dr> # [] icing constant for CY_dr uiuc_aircraft.h
|
|
ice kCY_dra <kCY_dra> # [] icing constant for CY_dra uiuc_aircraft.h
|
|
ice kCY_bdot <kCY_bdot> # [] icing constant for CY_bdot uiuc_aircraft.h
|
|
|
|
ice kClo <kClo> # [] icing constant for Clo uiuc_aircraft.h
|
|
ice kCl_beta <kCl_beta> # [] icing constant for Cl_beta uiuc_aircraft.h
|
|
ice kCl_p <kCl_p> # [] icing constant for Cl_p uiuc_aircraft.h
|
|
ice kCl_r <kCl_r> # [] icing constant for Cl_r uiuc_aircraft.h
|
|
ice kCl_da <kCl_da> # [] icing constant for Cl_da uiuc_aircraft.h
|
|
ice kCl_dr <kCl_dr> # [] icing constant for Cl_dr uiuc_aircraft.h
|
|
ice kCl_daa <kCl_daa> # [] icing constant for Cl_daa uiuc_aircraft.h
|
|
|
|
ice kCno <kCno> # [] icing constant for Cno uiuc_aircraft.h
|
|
ice kCn_beta <kCn_beta> # [] icing constant for Cn_beta uiuc_aircraft.h
|
|
ice kCn_b3 <kCn_b3> # [] icing constant for Cn_b3 uiuc_aircraft.h
|
|
ice kCn_p <kCn_p> # [] icing constant for Cn_p uiuc_aircraft.h
|
|
ice kCn_q <kCn_q> # [] icing constant for Cn_q uiuc_aircraft.h
|
|
ice kCn_r <kCn_r> # [] icing constant for Cn_r uiuc_aircraft.h
|
|
ice kCn_da <kCn_da> # [] icing constant for Cn_da uiuc_aircraft.h
|
|
ice kCn_dr <kCn_dr> # [] icing constant for Cn_dr uiuc_aircraft.h
|
|
|
|
ice beta_probe_wing <x_probe_wing> # wing flow angle probe location uiuc_aircraft.h
|
|
ice beta_probe_wing <x_probe_tail> # tail flow angle probe location uiuc_aircraft.h
|
|
|
|
|
|
record Simtime # [s] current sim time global
|
|
record dt # [s] current time step global
|
|
record Weight # [lb] aircraft gross takeoff weight uiuc_aircraft.h
|
|
record Mass # [slug] aircraft mass ls_generic.h
|
|
record I_xx # [slug-ft^2] roll inertia ls_generic.h
|
|
record I_yy # [slug-ft^2] pitch inertia ls_generic.h
|
|
record I_zz # [slug-ft^2] yaw inertia ls_generic.h
|
|
record I_xz # [slug-ft^2] lateral cross inertia ls_generic.h
|
|
record Dx_pilot # [ft] reference pilot x-location ls_generic.h
|
|
record Dy_pilot # [ft] reference pilot y-location ls_generic.h
|
|
record Dz_pilot # [ft] reference pilot z-location ls_generic.h
|
|
record Dx_cg # [ft] cg x_location ls_generic.h
|
|
record Dy_cg # [ft] cg y_location ls_generic.h
|
|
record Dz_cg # [ft] cg z_location ls_generic.h
|
|
record Lat_geocentric # [rad] geocentric latitude ls_generic.h
|
|
record Lon_geocentric # [rad] geocentric longitude ls_generic.h
|
|
record Radius_to_vehicle # [ft] geocentric distance ls_generic.h
|
|
record Latitude # [rad] geodetic latitude ls_generic.h
|
|
record Longitude # [rad] geodetic longitude ls_generic.h
|
|
record Altitude # [ft] geodetic altitude ls_generic.h
|
|
record Phi # [rad] Euler bank angle ls_generic.h
|
|
record Theta # [rad] Euler pitch attitude angle ls_generic.h
|
|
record Psi # [rad] Euler heading angle ls_generic.h
|
|
record V_dot_north # [ft/s^2] local x-acceleration ls_generic.h
|
|
record V_dot_east # [ft/s^2] local y-acceleration ls_generic.h
|
|
record V_dot_down # [ft/s^2] local z-acceleration ls_generic.h
|
|
record U_dot_body # [ft/s^2] body x-acceleration ls_generic.h
|
|
record V_dot_body # [ft/s^2] body y-acceleration ls_generic.h
|
|
record W_dot_body # [ft/s^2] body z-acceleration ls_generic.h
|
|
record A_X_pilot # [ft/s^2] pilot x-acceleration ls_generic.h
|
|
record A_Y_pilot # [ft/s^2] pilot y-acceleration ls_generic.h
|
|
record A_Z_pilot # [ft/s^2] pilot z-acceleration ls_generic.h
|
|
record A_X_cg # [ft/s^2] cg x-acceleration ls_generic.h
|
|
record A_Y_cg # [ft/s^2] cg y-acceleration ls_generic.h
|
|
record A_Z_cg # [ft/s^2] cg z-acceleration ls_generic.h
|
|
record N_X_pilot # [ft/s^2] pilot x-acceleration ls_generic.h
|
|
record N_Y_pilot # [ft/s^2] pilot y-acceleration ls_generic.h
|
|
record N_Z_pilot # [ft/s^2] pilot z-acceleration ls_generic.h
|
|
record N_X_cg # [ft/s^2] cg x-acceleration ls_generic.h
|
|
record N_Y_cg # [ft/s^2] cg y-acceleration ls_generic.h
|
|
record N_Z_cg # [ft/s^2] cg z-acceleration ls_generic.h
|
|
record P_dot_body # [rad/s^2] roll rate acceleration ls_generic.h
|
|
record Q_dot_body # [rad/s^2] pitch rate acceleration ls_generic.h
|
|
record R_dot_body # [rad/s^2] yaw rate acceleration ls_generic.h
|
|
record V_north # [ft/s] local x-velocity ls_generic.h
|
|
record V_east # [ft/s] local y-velocity ls_generic.h
|
|
record V_down # [ft/s] local z-velocity ls_generic.h
|
|
record V_north_rel_ground # [ft/s] local x-velocity wrt ground ls_generic.h
|
|
record V_east_rel_ground # [ft/s] local y-velocity wrt ground ls_generic.h
|
|
record V_down_rel_ground # [ft/s] local z-velocity wrt ground ls_generic.h
|
|
record V_north_airmass # [ft/s] local x-velocity of airmass ls_generic.h
|
|
record V_east_airmass # [ft/s] local y-velocity of airmass ls_generic.h
|
|
record V_down_airmass # [ft/s] local z-velocity of airmass ls_generic.h
|
|
record V_north_rel_airmass # [ft/s] local x-velocity wrt airmass ls_generic.h
|
|
record V_east_rel_airmass # [ft/s] local y-velocity wrt airmass ls_generic.h
|
|
record V_down_rel_airmass # [ft/s] local z-velocity wrt airmass ls_generic.h
|
|
record U_gust # [ft/s] local turbulence x-velocity ls_generic.h
|
|
record V_gust # [ft/s] local turbulence y-velocity ls_generic.h
|
|
record W_gust # [ft/s] local turbulence z-velocity ls_generic.h
|
|
record U_body # [ft/s] wind x-velocity in body axis ls_generic.h
|
|
record V_body # [ft/s] wind y-velocity in body axis ls_generic.h
|
|
record W_body # [ft/s] wind z-velocity in body axis ls_generic.h
|
|
record V_rel_wind # [ft/s] total freestream velocity ls_generic.h
|
|
record V_true_kts # [kts] true velocity ls_generic.h
|
|
record V_rel_ground # [ft/s] total velocity wrt ground ls_generic.h
|
|
record V_inertial # [ft/s] total inertial velocity ls_generic.h
|
|
record V_ground_speed # [ft/s] airspeed wrt ground ls_generic.h
|
|
record V_equiv # [ft/s] equivalent airspeed ls_generic.h
|
|
record V_equiv_kts # [kts] equivalent airspeed ls_generic.h
|
|
record V_calibrated # [ft/s] calibrated airspeed ls_generic.h
|
|
record V_calibrated_kts # [kts] calibrated airspeed ls_generic.h
|
|
record P_local # [rad/s] local roll rate ls_generic.h
|
|
record Q_local # [rad/s] local pitch rate ls_generic.h
|
|
record R_local # [rad/s] local yaw rate ls_generic.h
|
|
record P_body # [rad/s] body roll rate ls_generic.h
|
|
record Q_body # [rad/s] body pitch rate ls_generic.h
|
|
record R_body # [rad/s] body yaw rate ls_generic.h
|
|
record P_total # [rad/s] total roll rate ls_generic.h
|
|
record Q_total # [rad/s] total pitch rate ls_generic.h
|
|
record R_total # [rad/s] total yaw rate ls_generic.h
|
|
record Phi_dot # [rad/s] bank angle rate ls_generic.h
|
|
record Theta_dot # [rad/s] pitch attitude angle rate ls_generic.h
|
|
record Psi_dot # [rad/s] heading angle rate ls_generic.h
|
|
record Latitude_dot # [rad/s] latitude rate ls_generic.h
|
|
record Longitude_dot # [rad/s] longitude rate ls_generic.h
|
|
record Radius_dot # [rad/s] radius rate ls_generic.h
|
|
record Alpha # [rad] angle of attack ls_generic.h
|
|
record Alpha_deg # [deg] angle of attack (in degrees) uiuc_aircraft.h
|
|
record Alpha_dot # [rad/s] rate of change of alpha ls_generic.h
|
|
record Alpha_dot_deg # [rad/s] rate of change of alpha uiuc_aircraft.h
|
|
record Beta # [rad] sideslip angle ls_generic.h
|
|
record Beta_deg # [rad] sideslip angle uiuc_aircraft.h
|
|
record Beta_dot # [rad/s] rate of change of beta ls_generic.h
|
|
record Beta_dot_deg # [rad/s] rate of change of beta uiuc_aircraft.h
|
|
record Gamma_vert # [rad] vertical flight path angle ls_generic.h
|
|
record Gamma_vert_deg # [deg] vertical flight path angle uiuc_aircraft.h
|
|
record Gamma_horiz # [rad] horizontal flight path angle ls_generic.h
|
|
record Gamma_horiz_deg # [deg] horizontal flight path angle uiuc_aircraft.h
|
|
record Density # [slug/ft^3] air density ls_generic.h
|
|
record V_sound # [ft/s] speed of sound ls_generic.h
|
|
record Mach_number # [] Mach number ls_generic.h
|
|
record Static_pressure # [lb/ft^2] static pressure ls_generic.h
|
|
record Total_pressure # [lb/ft^2] total pressure ls_generic.h
|
|
record Impact_pressure # [lb/ft^2] impact pressure ls_generic.h
|
|
record Dynamic_pressure # [lb/ft^2] dynamic pressure ls_generic.h
|
|
record Static_temperature # [?] static temperature ls_generic.h
|
|
record Total_temperature # [?] total temperature ls_generic.h
|
|
record Gravity # [ft/s^2] acceleration due to gravity ls_generic.h
|
|
record Sea_level_radius # [ft] Earth radius ls_generic.h
|
|
record Earth_position_angle # [rad] Earth rotation angle ls_generic.h
|
|
record Runway_altitude # [ft] runway altitude ls_generic.h
|
|
record Runway_latitude # [rad] runway latitude ls_generic.h
|
|
record Runway_longitude # [rad] runway longititude ls_generic.h
|
|
record Runway_heading # [rad] runway heading ls_generic.h
|
|
record Radius_to_rwy # [ft] geocentric radius to runway ls_generic.h
|
|
record D_pilot_north_of_rwy # [ft] local pilot x-dist from rwy ls_generic.h
|
|
record D_pilot_east_of_rwy # [ft] local pilot y-dist from rwy ls_generic.h
|
|
record D_pilot_down_of_rwy # [ft] local pilot z-dist from rwy ls_generic.h
|
|
record X_pilot_rwy # [ft] pilot x-dist from rwy ls_generic.h
|
|
record Y_pilot_rwy # [ft] pilot y-dist from rwy ls_generic.h
|
|
record H_pilot_rwy # [ft] pilot z-dist from rwy ls_generic.h
|
|
record D_cg_north_of_rwy # [ft] local cg x-dist from rwy ls_generic.h
|
|
record D_cg_east_of_rwy # [ft] local cg y-dist from rwy ls_generic.h
|
|
record D_cg_down_of_rwy # [ft] local cg z-dist from rwy ls_generic.h
|
|
record X_cg_rwy # [ft] cg x-dist from rwy ls_generic.h
|
|
record Y_cg_rwy # [ft] cg y-dist from rwy ls_generic.h
|
|
record H_cg_rwy # [ft] cg z-dist from rwy ls_generic.h
|
|
record Throttle_pct # [%] throttle input ls_cockpit.h
|
|
record Throttle_3 # [%] throttle deflection ls_cockpit.h
|
|
record Long_control # [] pitch input ls_cockpit.h
|
|
record Long_trim # [rad] longitudinal trim ls_cockpit.h
|
|
record Long_trim_deg # [deg] longitudinal trim uiuc_aircraft.h
|
|
record elevator # [rad] elevator deflection uiuc_aircraft.h
|
|
record elevator_deg # [deg] elevator deflection uiuc_aircraft.h
|
|
record Lat_control # [] roll input ls_cockpit.h
|
|
record aileron # [rad] aileron deflection uiuc_aircraft.h
|
|
record aileron_deg # [deg] aileron deflection uiuc_aircraft.h
|
|
record Rudder_pedal # [] yaw input ls_cockpit.h
|
|
record rudder # [rad] rudder deflection uiuc_aircraft.h
|
|
record rudder_deg # [deg] rudder deflection uiuc_aircraft.h
|
|
record CDfaI # [] CD(alpha) uiuc_aircraft.h
|
|
record CDfCLI # [] CD(CL), drag polar uiuc_aircraft.h
|
|
record CDfadeI # [] CD(alpha,delta_e) uiuc_aircraft.h
|
|
record CD # [] drag coefficient uiuc_aircraft.h
|
|
record CLfaI # [] CL(alpha) uiuc_aircraft.h
|
|
record CLfadeI # [] CL(alpha,delta_e) uiuc_aircraft.h
|
|
record CL # [] lift coefficient uiuc_aircraft.h
|
|
record CmfaI # [] Cm(alpha) uiuc_aircraft.h
|
|
record CmfadeI # [] Cm(alpha,delta_e) uiuc_aircraft.h
|
|
record Cm # [] pitch moment coefficient uiuc_aircraft.h
|
|
record CYfadaI # [] CY(alpha,delta_a) uiuc_aircraft.h
|
|
record CYfbetadrI # [] CY(beta,delta_r) uiuc_aircraft.h
|
|
record CY # [] side-force coefficient uiuc_aircraft.h
|
|
record ClfadaI # [] Cl(alpha,delta_a) uiuc_aircraft.h
|
|
record ClfbetadrI # [] Cl(beta,delta_r) uiuc_aircraft.h
|
|
record Cl # [] roll moment coefficient uiuc_aircraft.h
|
|
record CnfadaI # [] Cn(alpha,delta_a) uiuc_aircraft.h
|
|
record CnfbetadrI # [] Cn(beta,delta_r) uiuc_aircraft.h
|
|
record Cn # [] yaw moment coefficient uiuc_aircraft.h
|
|
record CLclean_wing # [] wing clean lift coefficient uiuc_aircraft.h
|
|
record CLiced_wing # [] wing iced lift coefficient uiuc_aircraft.h
|
|
record CLclean_tail # [] tail clean lift coefficient uiuc_aircraft.h
|
|
record CLiced_tail # [] tail iced lift coefficient uiuc_aircraft.h
|
|
record Lift_clean_wing # [lb] wing clean lift force uiuc_aircraft.h
|
|
record Lift_iced_wing # [lb] wing iced lift force uiuc_aircraft.h
|
|
record Lift_clean_tail # [lb] tail clean lift force uiuc_aircraft.h
|
|
record Lift_iced_tail # [lb] tail iced lift force uiuc_aircraft.h
|
|
record Gamma_clean_wing # [ft^2/s] wing clean circulation uiuc_aircraft.h
|
|
record Gamma_iced_wing # [ft^2/s] wing iced circulation uiuc_aircraft.h
|
|
record Gamma_clean_tail # [ft^2/s] tail clean circulation uiuc_aircraft.h
|
|
record Gamma_iced_tail # [ft^2/s] tail iced circulation uiuc_aircraft.h
|
|
record w_clean_wing # [ft/s] wing clean downwash uiuc_aircraft.h
|
|
record w_iced_wing # [ft/s] wing iced downwash uiuc_aircraft.h
|
|
record w_clean_tail # [ft/s] tail clean downwash uiuc_aircraft.h
|
|
record w_iced_tail # [ft/s] tail iced downwash uiuc_aircraft.h
|
|
record V_total_clean_wing # [ft/s] wing clean velocity uiuc_aircraft.h
|
|
record V_total_iced_wing # [ft/s] wing iced velocity uiuc_aircraft.h
|
|
record V_total_clean_tail # [ft/s] tail clean velocity uiuc_aircraft.h
|
|
record V_total_iced_tail # [ft/s] tail iced velocity uiuc_aircraft.h
|
|
record beta_flow_clean_wing # [rad] wing clean flow angle uiuc_aircraft.h
|
|
record beta_flow_clean_wing_deg # [deg] wing clean flow angle uiuc_aircraft.h
|
|
record beta_flow_iced_wing # [rad] wing iced flow angle uiuc_aircraft.h
|
|
record beta_flow_iced_wing_deg # [deg] wing iced flow angle uiuc_aircraft.h
|
|
record beta_flow_clean_tail # [rad] tail clean flow angle uiuc_aircraft.h
|
|
record beta_flow_clean_tail_deg # [deg] tail clean flow angle uiuc_aircraft.h
|
|
record beta_flow_iced_tail # [rad] tail iced flow angle uiuc_aircraft.h
|
|
record beta_flow_iced_tail_deg # [deg] tail iced flow angle uiuc_aircraft.h
|
|
record Dbeta_flow_wing # [rad] difference in wing flow angle uiuc_aircraft.h
|
|
record Dbeta_flow_wing_deg # [deg] difference in wing flow angle uiuc_aircraft.h
|
|
record Dbeta_flow_tail # [rad] difference in tail flow angle uiuc_aircraft.h
|
|
record Dbeta_flow_tail_deg # [deg] difference in tail flow angle uiuc_aircraft.h
|
|
record pct_beta_flow_wing # [%] difference in wing flow angle uiuc_aircraft.h
|
|
record pct_beta_flow_tail # [%] difference in tail flow angle uiuc_aircraft.h
|
|
record F_X_wind # [lb] aero x-force in wind-axes ls_generic.h
|
|
record F_Y_wind # [lb] aero y-force in wind-axes ls_generic.h
|
|
record F_Z_wind # [lb] aero z-force in wind-axes ls_generic.h
|
|
record F_X_aero # [lb] aero x-force in body-axes ls_generic.h
|
|
record F_Y_aero # [lb] aero y-force in body-axes ls_generic.h
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record F_Z_aero # [lb] aero z-force in body-axes ls_generic.h
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record F_X_engine # [lb] prop x-force in body-axes ls_generic.h
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record F_Y_engine # [lb] prop y-force in body-axes ls_generic.h
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record F_Z_engine # [lb] prop z-force in body-axes ls_generic.h
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record F_X_gear # [lb] gear x-force in body-axes ls_generic.h
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record F_Y_gear # [lb] gear y-force in body-axes ls_generic.h
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record F_Z_gear # [lb] gear z-force in body-axes ls_generic.h
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record F_X # [lb] total x-force in body-axes ls_generic.h
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record F_Y # [lb] total y-force in body-axes ls_generic.h
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record F_Z # [lb] total z-force in body-axes ls_generic.h
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record F_nort # [lb] total x-force in local-axes ls_generic.h
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record F_east # [lb] total y-force in local-axes ls_generic.h
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record F_down # [lb] total z-force in local-axes ls_generic.h
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record M_l_aero # [ft-lb] aero roll mom in body axes ls_generic.h
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|
record M_m_aero # [ft-lb] aero pitch mom in body axes ls_generic.h
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record M_n_aero # [ft-lb] aero yaw mom in body axes ls_generic.h
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record M_l_engine # [ft-lb] prop roll mom in body axes ls_generic.h
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record M_m_engine # [ft-lb] prop pitch mom in body axes ls_generic.h
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|
record M_n_engine # [ft-lb] prop yaw mom in body axes ls_generic.h
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record M_l_gear # [ft-lb] gear roll mom in body axes ls_generic.h
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record M_m_gear # [ft-lb] gear pitch mom in body axes ls_generic.h
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record M_n_gear # [ft-lb] gear yaw mom in body axes ls_generic.h
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record M_l_rp # [ft-lb] total roll mom in body axes ls_generic.h
|
|
record M_m_rp # [ft-lb] total pitch mom in body axes ls_generic.h
|
|
record M_n_rp # [ft-lb] total yaw mom in body axes ls_generic.h
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|
|
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fog fog_segments <fog_segments> # [-] number of fog points after this line
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fog fog_point <time> <intensity>
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|
|
|
Note: Between each fog_point there is a linear interpolation
|
|
|
|
============================FOG EXAMPLE===============================
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|
|
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fog fog_segments 4
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fog fog_point 30 500
|
|
fog fog_point 35 200
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|
fog fog_point 40 -100
|
|
fog fog_point 50 0
|
|
|
|
The first line says that there will be 4 fog_point statements following.
|
|
From time 0 to 30 seconds, the fog will increase linearly to 500. From
|
|
30 to 35 seconds, the fog will decrease linearly to 200. From 35 to 40
|
|
seconds the fog will decrease to -100. From 40 to 50 the fog will
|
|
increase to 0.
|
|
======================================================================
|
|
|
|
|
|
# the following command is implemented but the data is not used in any
|
|
# equation of motion
|
|
# hinge moment coefficient [] uiuc_aircraft.h
|
|
|misc simpleHingeMomentCoef <simpleHingeMomentCoef>
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|
|
|
|
|
**********************************************************************
|
|
|
|
**********************************************************************
|
|
V. Mandatory Input:
|
|
|
|
The following data is required for the simulator to function;
|
|
otherwise either the UIUC Aero Model or LaRCsim parts of the code will
|
|
probably crash.
|
|
|
|
1) aircraft geometry (UIUC Aero Model)
|
|
bw wingspan [ft]
|
|
cbar mean aerodynamic chord [ft]
|
|
Sw wing planform area [ft^2]
|
|
|
|
2) engine properties (UIUC Engine Model)
|
|
(some engine model must be specified, such as...)
|
|
engine simpleSingle
|
|
<or>
|
|
engine c172
|
|
|
|
3) mass variables (LaRCsim)
|
|
Weight aircraft gross takeoff weight [lb]
|
|
<or>
|
|
Mass aircraft mass [slug]
|
|
I_xx roll inertia [slug-ft^2]
|
|
I_yy pitch inertia [slug-ft^2]
|
|
I_zz yaw inertia [slug-ft^2]
|
|
I_xz lateral cross inertia [slug-ft^2]
|
|
|
|
4) aerodynamic force/moment components (Aero Model)
|
|
CLo lift coef for all angles = 0 []
|
|
CL_a lift curve slope, d(CL)/d(alpha) [/rad]
|
|
CDo drag coef for all angles = 0 []
|
|
CDK induced drag constant []
|
|
<or>
|
|
CD_a d(CD)/d(alpha) [/rad]
|
|
Cmo pitch mom coef for all angles=0 []
|
|
Cm_a d(Cm)/d(alpha) [/rad]
|
|
CY_beta d(CY)/d(beta) [/rad]
|
|
Cl_beta d(Cl)/d(beta) [/rad]
|
|
Cn_beta d(Cn)/d(beta) [/rad]
|
|
|
|
5) gear properties
|
|
(some gear properties must be defined otherwise the aircraft
|
|
will not behave properly on the ground)
|
|
Dx_gear x-offset from CG [ft]
|
|
Dy_gear y-offset from CG [ft]
|
|
Dz_gear z-offset from CG [ft]
|
|
cgear gear damping constant [lb/ft/s]
|
|
kgear gear spring constant [lb/ft]
|
|
muGear gear rolling friction coef [-]
|
|
|
|
|
|
**********************************************************************
|