680 lines
36 KiB
Text
680 lines
36 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 0.64, March 28, 2000 *
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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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* 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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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 # [] 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 15 types of variable keywords:
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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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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 to be multiplied by something
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f "function of" (indicates an m*n matrix data table is given)
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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 state variables
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Dx_pilot x-location [ft]
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Dy_pilot y-location [ft]
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Dz_pilot z-location [ft]
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Dx_cg center of gravity x-location [ft]
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Dy_cg center of gravity y-location [ft]
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Dz_cg center of gravity z-location [ft]
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V_north x-velocity [ft/s]
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V_east y-velocity [ft/s]
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V_down z-velocity [ft/s]
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V_rel_wind total velocity [ft/s]
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Dynamic_pressure dynamic pressure [lb/ft^2]
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Alpha angle of attack [rad]
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Alpha_dot rate of change of alpha [rad/s]
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Beta sideslip angle [rad]
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Beta_dot rate of change of beta [rad]
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Gamma flight path angle [rad]
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P_body roll rate [rad/s]
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Q_body pitch rate [rad/s]
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R_body yaw rate [rad/s]
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Phi bank angle [rad]
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Theta pitch attitude angle [rad]
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Theta_dot rate change of theta [rad/s]
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Psi heading angle [rad]
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|long_trim
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|trim_inc
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M Mach number []
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Re Reynolds number []
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4) atmosphere properties
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Density air density [slug/ft^3]
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5) 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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6) 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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Lat_control roll control input [?]
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Long_control pitch control input [?]
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Rudder_pedal yaw control input [?]
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aileron aileron deflection [rad]
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elevator elevator deflection [rad]
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rudder rudder deflection [rad]
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|flap flap deflection [rad]
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7) mass variables
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|Weight gross takeoff weight [lb]
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Mass aircraft mass (used by LaRC) [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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8) engine/propulsion variables
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|thrust thrust [lb]
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simpleSingle simple single engine max thrust [lb]
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|Throttle_pct throttle input [] # ie, this is the stick
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|Throttle[3] throttle deflection [%] # this is what gets used to determine thrust
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9) 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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10) 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 [lb]
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F_Y total y-force [lb]
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F_Z total z-force [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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11) landing gear properties
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|cgear gear damping constant [?]
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|kgear gear spring constant [?]
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|muGear gear rolling friction coef [?]
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|strutLength gear strut length [ft]
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12) 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_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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13) 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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adot rate change in angle alpha
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beta sideslip angle
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|betadot 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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(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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**********************************************************************
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**********************************************************************
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IV. Input Line Definitions:
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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
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lines and to indicate examples of the data if additional clarity is
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needed for unique situations. Again, those lines beginning with '|'
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are not currently implemented in the code, but indicate planned
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conventions in later versions.
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# Key Variable Data Units Description Where Defined
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#------------------------------------------------------------------------------------
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init Dx_pilot <Dx_pilot> # [ft] initial x-position ls_generic.h
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init Dy_pilot <Dy_pilot> # [ft] initial y-position ls_generic.h
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init Dz_pilot <Dz_pilot> # [ft] initial z-position ls_generic.h
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init Dx_cg <Dx_cg> # [ft] initial cg x_location ls_generic.h
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init Dy_cg <Dy_cg> # [ft] initial cg y_location ls_generic.h
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init Dz_cg <Dz_cg> # [ft] initial cg z_location ls_generic.h
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|init V_north <V_north> # [ft/s] initial x-velocity ls_generic.h
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|init V_east <V_east> # [ft/s] initial y-velocity ls_generic.h
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|init V_down <V_down> # [ft/s] initial z-velocity ls_generic.h
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init P_body <P_body> # [rad/s] initial roll rate ls_generic.h
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init Q_body <Q_body> # [rad/s] initial pitch rate ls_generic.h
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init R_body <R_body> # [rad/s] initial yaw rate ls_generic.h
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init Phi <Phi> # [rad] initial bank angle ls_generic.h
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init Theta <Theta> # [rad] initial pitch attitude angle ls_generic.h
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init Psi <Psi> # [rad] initial heading angle ls_generic.h
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geometry bw <bw> # [ft] wingspan uiuc_aircraft.h
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geometry cbar <cbar> # [ft] wing mean aero chord uiuc_aircraft.h
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geometry Sw <Sw> # [ft^2] wing reference area uiuc_aircraft.h
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|geometry iw <iw> # [deg] wing incidence angle uiuc_aircraft.h
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|geometry bc <bc> # [ft] canard span uiuc_aircraft.h
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|geometry cc <cc> # [ft] canard chord uiuc_aircraft.h
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|geometry Sc <Sc> # [sq-ft] canard area uiuc_aircraft.h
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|geometry ic <ic> # [deg] canard incidence angle uiuc_aircraft.h
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|geometry bh <bh> # [ft] horizontal tail span uiuc_aircraft.h
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|geometry ch <ch> # [ft] horizontal tail chord uiuc_aircraft.h
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|geometry Sh <Sh> # [sq-ft] horizontal tail area uiuc_aircraft.h
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|geometry ih <ih> # [deg] horiz tail incidence angle uiuc_aircraft.h
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|geometry bv <bv> # [ft] vertical tail span uiuc_aircraft.h
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|geometry cv <cv> # [ft] vertical tail chord uiuc_aircraft.h
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|geometry Sv <Sv> # [sq-ft] vertical tail area uiuc_aircraft.h
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|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
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|controlSurface Sa <Sa> # [ft^2] aileron area uiuc_aircraft.h
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|controlSurface Sr <Sr> # [ft^2] rudder area uiuc_aircraft.h
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|controlSurface Sf <Sf> # [ft^2] flap area uiuc_aircraft.h
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controlSurface de <demax> <demin> # [deg] max/min elev deflections uiuc_aircraft.h
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controlSurface da <damax> <damin> # [deg] max/min ail deflections uiuc_aircraft.h
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controlSurface dr <drmax> <drmin> # [deg] max/min rud deflections uiuc_aircraft.h
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|controlSurface df <dfmax> <dfmin> # [deg] max/min flap deflections uiuc_aircraft.h
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# Note: Currently demin is not used in the code, and the max/min is +-demax.
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|controlsMixer nomix <?> # [] no controls mixing uiuc_aircraft.h
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|mass Weight <Weight> # [lb] gross takeoff weight (not used)
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mass Mass <Mass> # [slug] gross takeoff mass ls_generic.h
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mass I_xx <I_xx> # [slug-ft^2] roll inertia ls_generic.h
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mass I_yy <I_yy> # [slug-ft^2] pitch inertia ls_generic.h
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mass I_zz <I_zz> # [slug-ft^2] yaw inertia ls_generic.h
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mass I_xz <I_xz> # [slug-ft^2] lateral cross inertia ls_generic.h
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# maximum and minimum engine thrust [lb] uiuc_aircraft.h
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|engine thrust <thrustMax> <thrustMin>
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# simple single engine maximum thrust [lb] uiuc_aircraft.h
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engine simpleSingle <simpleSingleMaxThrust>
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engine c172 # use Cessna 172 engine model of Tony Peden
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CL CLo <CLo> # [] lift coef for all angles = 0 uiuc_aircraft.h
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CL CL_a <CL_a> # [/rad] lift curve slope, d(CL)/d(alpha) uiuc_aircraft.h
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CL CL_adot <CL_adot> # [/rad] d(CL)/d(alpha)/da(time) uiuc_aircraft.h
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CL CL_q <CL_q> # [/rad] d(CL)/delta(q) uiuc_aircraft.h
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CL CL_de <CL_de> # [/rad] d(CL)/d(de) uiuc_aircraft.h
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# CL(alpha), conversion for CL, for alpha [] uiuc_aircraft.h
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CL CLfa <CLfa.dat> <conversion1> <conversion2>
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# CL(alpha,delta_e), conversion for CL, for alpha, for delta_e [] uiuc_aircraft.h
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CL CLfade <CLfade.dat> <conversion1> <conversion2> <conversion3>
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|CL CLfCT <CLfCT.dat> # CL(thrust coef) uiuc_aircraft.h
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|CL CLfRe # CL(Reynolds #), equation uiuc_aircraft.h
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|CL CL_afaM <CL_afaM.dat> # CL_alpha(alpha,Mach #) uiuc_aircraft.h
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# these are sample examples that might be used in later versions of the code
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# note that CD terms must come after CL for induced drag to be computed
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CD CDo <CDo> # [] drag coef for all angles = 0 uiuc_aircraft.h
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CD CDK <CDK> # [] constant, as in CD=CDo+K*CL^2 uiuc_aircraft.h
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CD CD_a <CD_a> # [/rad] d(CD)/d(alpha) uiuc_aircraft.h
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CD CD_de <CD_de> # [/rad] d(CD)/d(delta_e) uiuc_aircraft.h
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# CD(alpha), conversion for CD, for alpha [] uiuc_aircraft.h
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CD CDfa <CDfa.dat> <conversion1> <conversion2>
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# CD(alpha,delta_e), conversion for CD, for alpha, for delta_e [] uiuc_aircraft.h
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CD CDfade <CDfade.dat> <conversion1> <conversion2> <conversion3>
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Cm Cmo <Cmo> # [] pitch mom coef for all angles=0 uiuc_aircraft.h
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Cm Cm_a <Cm_a> # [/rad] d(Cm)/d(alpha) uiuc_aircraft.h
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Cm Cm_adot <Cm_adot> # [/rad] d(Cm)/d(alpha)/d(time) uiuc_aircraft.h
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Cm Cm_q <Cm_q> # [/rad] d(Cm)/d(q) uiuc_aircraft.h
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Cm Cm_de <Cm_de> # [/rad] d(Cm)/d(de) uiuc_aircraft.h
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|Cm Cmfa <Cmfa.dat> # [] Cm(alpha) uiuc_aircraft.h
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Cm Cmfade <Cmfade.dat> # [] Cm(alpha,delta_e) uiuc_aircraft.h
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# Cm(alpha,delta_e), conversion for Cm, for alpha, for delta_e [] uiuc_aircraft.h
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Cm Cmfade <Cmfade.dat> <conversion1> <conversion2> <conversion3>
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CY CYo <CYo> # [] side-force coef for all angles=0 uiuc_aircraft.h
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CY CY_beta <CY_beta> # [/rad] d(CY)/d(beta) uiuc_aircraft.h
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CY CY_p <CY_p> # [/rad] d(CY)/d(p) uiuc_aircraft.h
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CY CY_r <CY_r> # [/rad] d(CY)/d(r) uiuc_aircraft.h
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CY CY_da <CY_da> # [/rad] d(CY)/d(delta_a) uiuc_aircraft.h
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CY CY_dr <CY_dr> # [/rad] d(CY)/d(delta_r) uiuc_aircraft.h
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# CY(alpha,delta_a), conversion for CY, for alpha, for delta_a [] uiuc_aircraft.h
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CY CYfada <CYfada.dat> <conversion1> <conversion2> <conversion3>
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# CY(beta,delta_r), conversion for CY, for beta, for delta_r [] uiuc_aircraft.h
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CY CYfbetadr <CYfbetadr.dat> <conversion1> <conversion2> <conversion3>
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Cl Clo <Clo> # [] roll mom coef for all angles=0 uiuc_aircraft.h
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Cl Cl_beta <Cl_beta> # [/rad] d(Cl)/d(beta) uiuc_aircraft.h
|
|
Cl Cl_betafCL # [/rad] Cl_beta(CL) equation 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_rfCL # [/rad] Cl_r(CL) equation uiuc_aircraft.h
|
|
Cl Cl_da <Cl_da> # [/rad] d(Cl)/d(delta_a) uiuc_aircraft.h
|
|
Cl Cl_dr <Cl_dr> # [/rad] d(Cl)/d(delta_r) uiuc_aircraft.h
|
|
Cl Clfada # [] Cl(alpha,delta_a), equation uiuc_aircraft.h
|
|
|
|
# Cl(alpha,delta_a), conversion for Cl, for alpha, for delta_a [] uiuc_aircraft.h
|
|
Cl Clfada <CYfada.dat> <conversion1> <conversion2> <conversion3>
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|
|
|
# Cl(beta,delta_r), conversion for Cl, for beta, for delta_r [] uiuc_aircraft.h
|
|
Cl Clfbetadr <CYfbetadr.dat> <conversion1> <conversion2> <conversion3>
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|
|
|
|
|
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_betafCL # [/rad] Cn_beta(CL) equation uiuc_aircraft.h
|
|
Cn Cn_p <Cn_p> # [/rad] d(Cn)/d(p) uiuc_aircraft.h
|
|
Cn Cn_pfCL # [/rad] Cn_p(CL) equation uiuc_aircraft.h
|
|
Cn Cn_r <Cn_r> # [/rad] d(Cn)/d(r) uiuc_aircraft.h
|
|
Cn Cn_rfCL # [/rad] Cn_r(CL) equation 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_drfCL # [/rad] Cn_dr(CL) equation uiuc_aircraft.h
|
|
|
|
# Cn(alpha,delta_a), conversion for Cn, for alpha, for delta_a [] uiuc_aircraft.h
|
|
Cn Cnfada <Cnfada.dat> <conversion1> <conversion2> <conversion3>
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|
|
|
# Cn(beta,delta_r), conversion for Cn, for beta, for delta_r [] uiuc_aircraft.h
|
|
Cn Cnfbetadr <Cnfbetadr.dat> <conversion1> <conversion2> <conversion3>
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|
|
|
=============================CONVERSION CODES================================
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|
|
|
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.
|
|
|
|
------------------------------------------------
|
|
conversion1
|
|
conversion2
|
|
conversion3 Action
|
|
------------------------------------------------
|
|
0 no conversion (multiply by 1)
|
|
1 convert degrees to radians
|
|
=============================================================================
|
|
|
|
|gear kgear <kgear> # [] gear spring constant(s) uiuc_aircraft.h
|
|
|gear muRoll <muRoll> # [] gear rolling friction coef(s) uiuc_aircraft.h
|
|
|gear cgear <cgear> # [] gear damping constant(s) uiuc_aircraft.h
|
|
|gear strutLength <sL> # [ft] gear strut length uiuc_aircraft.h
|
|
|
|
ice iceTime <iceTime> # [s] time when icing begins uiuc_aircraft.h
|
|
ice transientTime <tT> # [s] period for eta to reach eta_final uiuc_aircraft.h
|
|
ice eta_final <eta_f> # [] icing severity factor uiuc_aircraft.h
|
|
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 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 kCmo <kCmo> # [] icing constant for Cmo uiuc_aircraft.h
|
|
ice kCm_a <kCm_a> # [] icing constant for Cm_a 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 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 kCno <kCno> # [] icing constant for Cno uiuc_aircraft.h
|
|
ice kCn_beta <kCn_beta> # [] icing constant for Cn_beta uiuc_aircraft.h
|
|
ice kCn_p <kCn_p> # [] icing constant for Cn_p 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
|
|
|
|
record Dx_pilot # [ft] x-location ls_generic.h
|
|
record Dy_pilot # [ft] y-loaction ls_generic.h
|
|
record Dz_pilot # [ft] 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 V_north # [ft/s] x-velocity ls_generic.h
|
|
record V_east # [ft/s] y-velocity ls_generic.h
|
|
record V_down # [ft/s] z-velocity ls_generic.h
|
|
record V_rel_wind # [ft/s] total velocity ls_generic.h
|
|
record Dynamic_pressure # [lb/ft^2] dynamic pressure ls_generic.h
|
|
record Alpha # [rad] angle of attack ls_generic.h
|
|
record Alpha_dot # [rad/s] rate of change of alpha ls_generic.h
|
|
record Beta # [rad] sideslip angle ls_generic.h
|
|
record Beta_dot # [rad/s] rate of change of beta ls_generic.h
|
|
record Gamma # [rad] flight path angle ls_generic.h
|
|
record P_body # [rad] roll rate ls_generic.h
|
|
record Q_body # [rad] pitch rate ls_generic.h
|
|
record R_body # [rad] yaw rate ls_generic.h
|
|
record Phi # [rad] bank angle ls_generic.h
|
|
record Theta # [rad] pitch attitude angle ls_generic.h
|
|
record Theta_dot # [rad] rate change of theta ls_generic.h
|
|
record Psi # [rad] heading angle ls_generic.h
|
|
|record long_trim
|
|
|record trim_inc
|
|
record Density # [slug/ft^3] air density ls_generic.h
|
|
record Mass # [slug] aircraft mass ls_generic.h
|
|
record Simtime # [s] current sim time global
|
|
record dt # [s] current time step global
|
|
record Long_control # [] pitch input ls_cockpit.h
|
|
record Lat_control # [] roll input ls_cockpit.h
|
|
record Rudder_pedal # [] yaw input ls_cockpit.h
|
|
|record Throttle_pct # [%] throttle input ls_cockpit.h
|
|
record elevator # [rad] elevator deflection uiuc_aircraft.h
|
|
record aileron # [rad] aileron deflection uiuc_aircraft.h
|
|
record rudder # [rad] rudder deflection uiuc_aircraft.h
|
|
|record Throttle[3] # [%] throttle deflection ls_cockpit.h
|
|
record CDfaI # [] CD(alpha) 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 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 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
|
|
record F_Z_aero # [lb] aero z-force in body-axes ls_generic.h
|
|
record F_X_engine # [lb] prop x-force in body-axes ls_generic.h
|
|
record F_Y_engine # [lb] prop y-force in body-axes ls_generic.h
|
|
record F_Z_engine # [lb] prop z-force in body-axes ls_generic.h
|
|
record F_X_gear # [lb] gear x-force in body-axes ls_generic.h
|
|
record F_Y_gear # [lb] gear y-force in body-axes ls_generic.h
|
|
record F_Z_gear # [lb] gear z-force in body-axes ls_generic.h
|
|
record F_X # [lb] total x-force in body-axes ls_generic.h
|
|
record F_Y # [lb] total y-force in body-axes ls_generic.h
|
|
record F_Z # [lb] total z-force in body-axes ls_generic.h
|
|
record M_l_aero # [ft-lb] aero roll mom in body axes ls_generic.h
|
|
record M_m_aero # [ft-lb] aero pitch mom in body axes ls_generic.h
|
|
record M_n_aero # [ft-lb] aero yaw mom in body axes ls_generic.h
|
|
record M_l_engine # [ft-lb] prop roll mom in body axes ls_generic.h
|
|
record M_m_engine # [ft-lb] prop pitch mom in body axes ls_generic.h
|
|
record M_n_engine # [ft-lb] prop yaw mom in body axes ls_generic.h
|
|
record M_l_gear # [ft-lb] gear roll mom in body axes ls_generic.h
|
|
record M_m_gear # [ft-lb] gear pitch mom in body axes ls_generic.h
|
|
record M_n_gear # [ft-lb] gear yaw mom in body axes ls_generic.h
|
|
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
|
|
|
|
**********************************************************************
|
|
|
|
**********************************************************************
|
|
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) initial aircraft state (LaRCsim)
|
|
Dx_pilot x-location [ft]
|
|
Dy_pilot y-location [ft]
|
|
Dz_pilot z-location [ft]
|
|
|
|
(items below causing conflict with Flight Gear)
|
|
|V_north x-velocity [ft/s]
|
|
|V_east y-velocity [ft/s]
|
|
|V_down z-velocity [ft/s]
|
|
|
|
P_body roll rate [rad/s]
|
|
Q_body pitch rate [rad/s]
|
|
R_body yaw rate [rad/s]
|
|
Phi bank angle [rad]
|
|
Theta pitch attitude angle [rad]
|
|
Psi heading angle [rad]
|
|
|
|
2) aircraft geometry (UIUC Aero Model)
|
|
bw wingspan [ft]
|
|
cbar mean aerodynamic chord [ft]
|
|
Sw wing planform area [ft^2]
|
|
|
|
3) engine properties (UIUC Engine Model)
|
|
(some engine model must be specified, such as...)
|
|
engine simpleSingle
|
|
<or>
|
|
engine c172
|
|
|
|
4) mass variables (LaRCsim)
|
|
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]
|
|
|
|
5) 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 constant, as in CD=CDo+K*CL^2 []
|
|
<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]
|
|
|
|
7) gear properties (none yet)
|
|
|
|
With the current version, the C172 model gear model is used for *ALL*
|
|
aircraft. This can produce some interesting effects with heavy
|
|
aircraft (eg, Convair model), and light aircraft (eg, Pioneer UAV)
|
|
|
|
**********************************************************************
|