X-Git-Url: https://git.mxchange.org/?a=blobdiff_plain;f=docs-mini%2FREADME.uiuc;h=9c215871ac29ec100f6ae13a6a6addd42e9733d0;hb=934ce52a235cda3827866f64a9af492f2ea1e63e;hp=da0c3ec483c2a0ca95c380358de9e8a35e7a84d6;hpb=7c2ebec7160a92793740725ce292d0993506a6df;p=flightgear.git diff --git a/docs-mini/README.uiuc b/docs-mini/README.uiuc index da0c3ec48..9c215871a 100644 --- a/docs-mini/README.uiuc +++ b/docs-mini/README.uiuc @@ -2,11 +2,12 @@ * * * FGFS Reconfigurable Aircraft Flight Model * * Input File Documentation * -* Version 0.63, March 17, 2000 * +* Version 0.81, September 14, 2001 * * * * Authors: * -* Jeff Scott (jscott@uiuc.edu) * +* Jeff Scott (jscott@mail.com) * * Bipin Sehgal (bsehgal@uiuc.edu) * +* Robert Deters (rdeters@uiuc.edu) * * Michael Selig (m-selig@uiuc.edu) * * Dept of Aero and Astro Engineering * * University of Illinois at Urbana-Champaign * @@ -15,14 +16,24 @@ * * ************************************************ - + +********************************************************************** +NOTE: Most of the commands discussed in this documentation are + currently implemented in the UIUC aerodynamics model. Those + denoted by '|' are proposed and will likely be added in the + future but are not currently implemented. Some commands are + in use but not producing the desired results. These are + clearly noted, so please do not attempt to use them at this + time. +********************************************************************** + ********************************************************************** This documentation includes: - Required and optional input lines. - Input line formats and conventions. -Viewing this file in emacs makefile-mode with color makes this file -easier to read. + Viewing this file in emacs makefile-mode with color makes this file + easier to read. ********************************************************************** ********************************************************************** @@ -33,6 +44,7 @@ I. Conventions and Notations and Reading this Document: | Optional data | Sometimes indicates a feature not yet used, but proposed convention is indicated nevertheless. + <...> Value or file name to be placed here || Input line disabled || Option disabled ... Repeat similar data @@ -44,9 +56,9 @@ II. General Input Line Format: Examples input lines include -Cm Cmo 0.194 # [] Bray pg 33 -Cm Cm_a -2.12 # [/rad] Bray pg 33 -CL CLfa CLfa.dat # [] Bray pg 50, Table 4.7 +Cm Cmo 0.194 # [] Bray pg 33 +Cm Cm_a -2.12 # [/rad] Bray pg 33 +CL CLfa CLfa.dat 0 1 # [] Bray pg 50, Table 4.7 These follow the more general input line form @@ -58,7 +70,7 @@ Each term of the input line will be discussed in turn. (1) KEYWORDS ============ -There currently exist 15 types of variable keywords: +There currently exist the following variable keyword types: init Initial values for equation of motion geometry Aircraft-specific geometric quantities @@ -72,9 +84,11 @@ Cm Aerodynamic m-moment quantities (longitudinal) CY Aerodynamic y-force quantities (lateral) Cl Aerodynamic l-moment quantities (lateral) Cn Aerodynamic n-moment quantities (lateral) -|gear Landing gear model quantities -ice Aircraft icing model parameters -record Record desired quantities to the file: uiuc_record.dat +gear Landing gear model quantities +ice Icing model parameters +record Record desired quantites to file +misc Miscellaneous inputs +fog Fog field quantities As each line of the input file is read, the code recognizes the keyword, enters the appropriate switch statement in the code, and @@ -103,146 +117,275 @@ The conventions used for naming the variables are provided below. Several of these variable names are not currently used. 1) variable class -_ denotes stability derivative to be multiple by something -f "function of" (indicates an m*n matrix data table is given) +_ denotes stability derivative +f "function of" (indicates data table) 2) timing data (global simulator variables) -Simtime current simulator time [s] -dt current simulator time step [s] - -3) aircraft state variables -Dx_pilot x-location [ft] -Dy_pilot y-location [ft] -Dz_pilot z-location [ft] -Dx_cg center of gravity x-location [ft] -Dy_cg center of gravity y-location [ft] -Dz_cg center of gravity z-location [ft] -V_north x-velocity [ft/s] -V_east y-velocity [ft/s] -V_down z-velocity [ft/s] -V_rel_wind total velocity [ft/s] -Dynamic_pressure dynamic pressure [lb/ft^2] -Alpha angle of attack [rad] -Alpha_dot rate of change of alpha [rad/s] -Beta sideslip angle [rad] -Beta_dot rate of change of beta [rad] -Gamma flight path angle [rad] -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] -Theta_dot rate change of theta [rad/s] -Psi heading angle [rad] -|long_trim -|trim_inc -M Mach number [] -Re Reynolds number [] - -4) atmosphere properties -Density air density [slug/ft^3] - -5) geometric variables -bw wingspan [ft] -cbar mean aerodynamic chord [ft] -Sw wing planform area [ft^2] -iw wing incidence angle [deg] -bc canard span [ft] -cc canard (mean) chord [ft] -Sc canard area [ft^2] -ic canard incidence angle [deg] -bh horizontal tail span [ft] -ch horizontal tail (mean) chord [ft] -Sh horizontal tail area [ft^2] -ih horizontal tail incidence angle [deg] -bv vertical tail span (height) [ft] -cv vertical tail (mean) chord [ft] -iv vertical tail incidence angle [deg] -Sv vertical tail area [ft^2] - -6) control surface properties -Sa aileron area [ft^2] -Se elevator area [ft^2] -Sf flap area [ft^2] -Sr rudder area [ft^2] -Lat_control roll control input [?] -Long_control pitch control input [?] -Rudder_pedal yaw control input [?] -aileron aileron deflection [rad] -elevator elevator deflection [rad] -rudder rudder deflection [rad] -|flap flap deflection [rad] - -7) mass variables -|Weight gross takeoff weight [lb] -Mass aircraft mass (used by LaRC) [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] - -8) engine/propulsion variables -|thrust thrust [lb] -simpleSingle simple single engine max thrust [lb] -|Throttle_pct throttle input [] # ie, this is the stick -|Throttle[3] throttle deflection [%] # this is what gets used to determine thrust - -9) force/moment coefficients -CD coefficient of drag [] -CY coefficient of side-force [] -CL coefficient of lift [] -Cl coefficient of roll moment [] -Cm coefficient of pitching moment [] -Cn coefficient of yaw moment [] -|CT coefficient of thrust [] - -10) total forces/moments -F_X_wind aerodynamic x-force in wind-axes [lb] -F_Y_wind aerodynamic y-force in wind-axes [lb] -F_Z_wind aerodynamic z-force in wind-axes [lb] -F_X_aero aerodynamic x-force in body-axes [lb] -F_Y_aero aerodynamic y-force in body-axes [lb] -F_Z_aero aerodynamic z-force in body-axes [lb] -F_X_engine propulsion x-force in body axes [lb] -F_Y_engine propulsion y-force in body axes [lb] -F_Z_engine propulsion z-force in body axes [lb] -F_X_gear gear x-force in body axes [lb] -F_Y_gear gear y-force in body axes [lb] -F_Z_gear gear z-force in body axes [lb] -F_X total x-force [lb] -F_Y total y-force [lb] -F_Z total z-force [lb] -M_l_aero aero roll-moment in body-axes [ft-lb] -M_m_aero aero pitch-moment in body-axes [ft-lb] -M_n_aero aero yaw-moment in body-axes [ft-lb] -M_l_engine prop roll-moment in body axes [ft-lb] -M_m_engine prop pitch-moment in body axes [ft-lb] -M_n_engine prop yaw-moment in body axes [ft-lb] -M_l_gear gear roll-moment in body axes [ft-lb] -M_m_gear gear pitch-moment in body axes [ft-lb] -M_n_gear gear yaw-moment in body axes [ft-lb] -M_l_rp total roll-moment [ft-lb] -M_m_rp total pitch-moment [ft-lb] -M_n_rp total yaw-moment [ft-lb] - -11) landing gear properties -|cgear gear damping constant [?] -|kgear gear spring constant [?] -|muGear gear rolling friction coef [?] -|strutLength gear strut length [ft] - -12) icing model paramters +Simtime current simulator time [s] +dt current simulator time step [s] + +3) aircraft position data +Lat_geocentric geocentric latitude of CG [rad] +Lon_geocentric geocentric longitude of CG [rad] +Radius_to_vehicle distance of CG from inertial frame [ft] +Latitude geodetic latitude of CG [rad] +Longitude geodetic longitude of CG [rad] +Altitude height of CG above reference ellipsoid [ft] +Phi Euler bank/roll angle [rad] +Theta Euler pitch attitude angle [rad] +Psi Euler heading angle [rad] + +4) aircraft accelerations +V_dot_north local x-acceleration [ft/s^2] +V_dot_east local y-acceleration [ft/s^2] +V_dot_down local z-acceleration [ft/s^2] +U_dot_body body x-acceleration [ft/s^2] +V_dot_body body y-acceleration [ft/s^2] +W_dot_body body z-acceleration [ft/s^2] +A_X_pilot pilot x-acceleration [ft/s^2] +A_Y_pilot pilot y-acceleration [ft/s^2] +A_Z_pilot pilot z-acceleration [ft/s^2] +A_X_cg center of gravity x-acceleration [ft/s^2] +A_Y_cg center of gravity x-acceleration [ft/s^2] +A_Z_cg center of gravity x-acceleration [ft/s^2] +N_X_pilot pilot x-acceleration [ft/s^2] +N_Y_pilot pilot y-acceleration [ft/s^2] +N_Z_pilot pilot z-acceleration [ft/s^2] +N_X_cg center of gravity x-acceleration [ft/s^2] +N_Y_cg center of gravity Y-acceleration [ft/s^2] +N_Z_cg center of gravity Z-acceleration [ft/s^2] +P_dot_body roll rate acceleration [rad/s^2] +Q_dot_body pitch rate acceleration [rad/s^2] +R_dot_body yaw rate acceleration [rad/s^2] + +5) aircraft velocities +V_north local x-velocity [ft/s] +V_east local y-velocity [ft/s] +V_down local z-velocity [ft/s] +V_north_rel_ground local x-velocity with respect to ground [ft/s] +V_east_rel_ground local y-velocity with respect to ground [ft/s] +V_down_rel_ground local z-velocity with respect to ground [ft/s] +V_north_airmass local x-velocity of steady airmass [ft/s] +V_east_airmass local y-velocity of steady airmass [ft/s] +V_down_airmass local z-velocity of steady airmass [ft/s] +V_north_rel_airmass local x-velocity wrt steady airmass [ft/s] +V_east_rel_airmass local y-velocity wrt steady airmass [ft/s] +V_down_rel_airmass local z-velocity wrt steady airmass [ft/s] +U_gust local linear turbulence x-velocity [ft/s] +V_gust local linear turbulence y-velocity [ft/s] +W_gust local linear turbulence z-velocity [ft/s] +U_body wind x-velocity in body axis [ft/s] +V_body wind y-velocity in body axis [ft/s] +W_body wind z-velocity in body axis [ft/s] +V_rel_wind total wind velocity (freestream) [ft/s] +V_true_kts true velocity [kts] +V_rel_ground total velocity wrt ground [ft/s] +V_inertial total inertial velocity [ft/s] +V_ground_speed velocity at right angles to local vertical [ft/s] +V_equiv equivalent airspeed [ft/s] +V_equiv_kts equivalent airspeed [kts] +V_calibrated calibrated indicated airspeed [ft/s] +V_calibrated_kts calibrated indicated airspeed [kts] +P_local local roll rate [rad/s] +Q_local local pitch rate [rad/s] +R_local local yaw rate [rad/s] +P_body body roll rate [rad/s] +Q_body body pitch rate [rad/s] +R_body body yaw rate [rad/s] +P_total roll rate of body axis wrt local axis [rad/s] +Q_total pitch rate of body axis wrt local axis [rad/s] +R_total yaw rate of body axis wrt local axis [rad/s] +Phi_dot change in bank angle rate [rad/s] +Theta_dot change in pitch attitude angle rate [rad/s] +Psi_dot change in heading angle rate [rad/s] +Latitude_dot change in geocentric latitude rate [rad/s] +Longitude_dot change in geocentric longitude rate [rad/s] +Radius_dot change in geocentric radius rate [ft/s] + +6) angles +Alpha angle of attack [rad] +Alpha_deg angle of attack [deg] +Alpha_dot rate of change of alpha [rad/s] +Alpha_dot_deg rate of change of alpha [deg/s] +Beta sideslip angle [rad] +Beta_deg sideslip angle [deg] +Beta_dot rate of change of beta [rad] +Beta_dot_deg rate of change of beta [deg] +Gamma_vert local vertical flight path angle [rad] +Gamma_ver_deg local vertical flight path angle [deg] +Gamma_horiz local horizontal flight path angle [rad] +Gamma_horiz_deg local horizontal flight path angle [deg] + +7) atmosperic properties +Density atmospheric density [slug/ft^3] +V_sound speed of sound [ft/s] +Mach_number free-stream Mach number [] +M Mach number [] +Re Reynolds number [] +Static_pressure static pressure [lb/ft^2] +Total_pressure total pressure [lb/ft^2] +Impact_pressure impact pressure [lb/ft^2] +Dynamic_pressure dynamic pressure [lb/ft^2] +Static_temperature static temperature [deg F?] +Total_temperature total temperature [deg F?] + +8) Earth properties +Gravity acceleration due to gravity [ft/s^2] +Sea_level_radius local Earth radius [ft] +Earth_position_angle Earth rotation angle since reference time [rad] +Runway_altitude runway height above local sea level [ft] +Runway_latitude runway latitude [rad] +Runway_longitude runway longitude [rad] +Runway_heading runway heading [rad] +Radius_to_rwy geocentric radius to runway [ft] +D_pilot_north_of_rwy local pilot x-distance from runway [ft] +D_pilot_east_of_rwy local pilot y-distance from runway [ft] +D_pilot_down_of_rwy local pilot z-distance from runway [ft] +X_pilot_rwy pilot x-distance from rwy in rwy axis [ft] +Y_pilot_rwy pilot y-distance from rwy in rwy axis [ft] +H_pilot_rwy pilot z-distance from rwy in rwy axis [ft] +D_cg_north_of_rwy local cg x-distance from runway [ft] +D_cg_east_of_rwy local cg y-distance from runway [ft] +D_cg_down_of_rwy local cg z-distance from runway [ft] +X_cg_rwy cg x-distance from rwy in rwy axis [ft] +Y_cg_rwy cg y-distance from rwy in rwy axis [ft] +H_cg_rwy cg z-distance from rwy in rwy axis [ft] + +9) aircraft geometric variables +bw wingspan [ft] +cbar mean aerodynamic chord [ft] +Sw wing planform area [ft^2] +|iw wing incidence angle [deg] +|bc canard span [ft] +|cc canard (mean) chord [ft] +|Sc canard area [ft^2] +|ic canard incidence angle [deg] +bh horizontal tail span [ft] +ch horizontal tail (mean) chord [ft] +Sh horizontal tail area [ft^2] +ih horizontal tail incidence angle [deg] +|bv vertical tail span (height) [ft] +|cv vertical tail (mean) chord [ft] +|iv vertical tail incidence angle [deg] +|Sv vertical tail area [ft^2] +Dx_pilot reference pilot x-location [ft] +Dy_pilot reference pilot y-location [ft] +Dz_pilot referende pilot z-location [ft] +Dx_cg reference center of gravity x-loc [ft] +Dy_cg reference center of gravity y-loc [ft] +Dz_cg reference center of gravity z-loc [ft] + +10) aircraft control surface properties +|Sa aileron area [ft^2] +|Se elevator area [ft^2] +|Sf flap area [ft^2] +|Sr rudder area [ft^2] +Long_control pitch control input [] +Long_trim longitudinal trim input [rad] +set_Long_trim set longitudinal trim to constant[rad] +zero_Long_trim set longitudinal trim to zero [deg] +elevator elevator deflection [rad] +Lat_control roll control input [] +aileron aileron deflection [rad] +Rudder_pedal yaw control input [] +rudder rudder deflection [rad] +|flap flap deflection [rad] + +11) user-specified control surface deflections +elevator_step_angle elevator step input angle [deg] +elevator_step_startTime elevator step input starting time [s] +elevator_singlet_angle elevator singlet input angle [deg] +elevator_singlet_startTime elevator singlet input starting time [s] +elevator_singlet_duration elevator singlet time duration [s] +elevator_doublet_angle elevator singlet input angle [deg] +elevator_doublet_startTime elevator doublet input starting time [s] +elevator_doublet_duration elevator doublet TOTAL time duration [s] +elevator_input_file file of elevator deflections vs. time [s,deg] +aileron_input_file file of aileron deflections vs. time [s,deg] +rudder_input_file file of rudder deflections vs. time [s,deg] + +12) mass variables +Weight gross takeoff weight [lb] +Mass aircraft mass (used by LaRCsim) [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] + +13) engine/propulsion variables +|thrust engine thrust [lb] +simpleSingle treat all engines as one; max thrust [lb] +Throttle_pct throttle input ("stick") [] +Throttle_3 throttle deflection (determines thrust) [%] + +14) force/moment coefficients +CD coefficient of drag [] +CY coefficient of side-force [] +CL coefficient of lift [] +Cl coefficient of roll moment [] +Cm coefficient of pitching moment [] +Cn coefficient of yaw moment [] +|CT coefficient of thrust [] + +15) total forces/moments +F_X_wind aerodynamic x-force in wind-axes [lb] +F_Y_wind aerodynamic y-force in wind-axes [lb] +F_Z_wind aerodynamic z-force in wind-axes [lb] +F_X_aero aerodynamic x-force in body-axes [lb] +F_Y_aero aerodynamic y-force in body-axes [lb] +F_Z_aero aerodynamic z-force in body-axes [lb] +F_X_engine propulsion x-force in body axes [lb] +F_Y_engine propulsion y-force in body axes [lb] +F_Z_engine propulsion z-force in body axes [lb] +F_X_gear gear x-force in body axes [lb] +F_Y_gear gear y-force in body axes [lb] +F_Z_gear gear z-force in body axes [lb] +F_X total x-force in body-axes [lb] +F_Y total y-force in body-axes [lb] +F_Z total z-force in body-axes [lb] +F_north total x-force in local-axes [lb] +F_east total y-force in local-axes [lb] +F_down total z-force in local-axes [lb] +M_l_aero aero roll-moment in body-axes [ft-lb] +M_m_aero aero pitch-moment in body-axes [ft-lb] +M_n_aero aero yaw-moment in body-axes [ft-lb] +M_l_engine prop roll-moment in body axes [ft-lb] +M_m_engine prop pitch-moment in body axes [ft-lb] +M_n_engine prop yaw-moment in body axes [ft-lb] +M_l_gear gear roll-moment in body axes [ft-lb] +M_m_gear gear pitch-moment in body axes [ft-lb] +M_n_gear gear yaw-moment in body axes [ft-lb] +M_l_rp total roll-moment [ft-lb] +M_m_rp total pitch-moment [ft-lb] +M_n_rp total yaw-moment [ft-lb] + +16) landing gear properties +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 [-] +|strutLength gear strut length [ft] + +17) icing model parameters iceTime time when icing begins [s] transientTime time period over which eta increases to final [s] -eta_final icing severity factor at end of transient time [-] -kCA icing constants for associated aero coef. [-] (see IV) +eta_ice_final icing severity factor at end of transient time [] +kCA icing constants for associated aero coef. [] (see IV) +beta_probe_wing location of flow angle probe on wing [ft] +beta_probe_tail location of flow angle probe on tail [ft] -13) subscripts +18) subscripts o value for all angles = 0 (alfa, beta, etc) a angle of attack +a2 alpha squared +a3 alpha cubed adot rate change in angle alpha beta sideslip angle -|betadot rate change in beta +b2 beta squared +b3 beta cubed +bdot rate change in beta p roll rate q pitch rate r yaw rate @@ -253,13 +396,24 @@ r yaw rate da aileron deflection de elevator deflection dr rudder deflection -df flap deflection +|df flap deflection |df2 flap deflection for second set |df3 flap deflection for third set max maximum min minimum -(3) | (OPTIONAL DATA) +19) miscellaneous +recordRate number of times to record data per second [/s] +recordStartTime time to start recording outpud data [s] +dyn_on_speed speed when dynamic pressure terms first computed [ft/s] +nondim_rate_V_rel_wind use V_rel_wind to compute control rates [] +|simpleHingeMomentCoef hinge moment coefficient [] + +20) fog +fog_segments number of fog points following this line +fog_points fog intensity and the time at which it occurs + +(3) | [OPTIONAL DATA] ===================== An input line may also be used to provide optional data that @@ -268,7 +422,7 @@ operate. As with the variable data described in section (2), multiple values or data files may be provided if the code is written to use them. -(4) # (COMMENTS) +(4) # [COMMENTS] ================ Appended comments should be provided with each input line to indicate @@ -282,29 +436,30 @@ III. Sample Input Lines: CONSTANTS ========= -geometry bw # geometric parameter, wingspan -Cm Cm_a # stability derivative, d(Cm)/d(alpha) +geometry bw # geometric parameter, wingspan +Cm Cm_a # stability derivative, d(Cm)/d(alpha) controlSurface de # max and min elevator deflections LOOKUP TABLES ============= -CD CDfCL # CD(CL), drag polar data file -Cm Cmfade # Cm(alpha,delta_e), moment data file +CD CDfCL # CD(CL), drag polar data file +Cm Cmfade # Cm(alpha,delta_e), moment data file HARD-CODED EQUATION =================== CD CDfCL # CD(CL), drag calculated in code based on CL +(none currently in use) ********************************************************************** ********************************************************************** -IV. Definitions of Input Lines Currently Available: +IV. Input Line Definitions: -Of all the possible permutation of variable names described above in -section II, only some are currently implemented in the code. These -are described below. Comments, denoted by '#,' are used to define the +Of all the possible permutations of variable names described above in +section II, only some are curently implemented in the code. These are +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 @@ -313,21 +468,43 @@ conventions in later versions. # Key Variable Data Units Description Where Defined #------------------------------------------------------------------------------------ -init Dx_pilot # [ft] initial x-position ls_generic.h -init Dy_pilot # [ft] initial y-position ls_generic.h -init Dz_pilot # [ft] initial z-position ls_generic.h -init Dx_cg # [ft] initial cg x_location ls_generic.h -init Dy_cg # [ft] initial cg y_location ls_generic.h -init Dz_cg # [ft] initial cg z_location ls_generic.h -|init V_north # [ft/s] initial x-velocity ls_generic.h -|init V_east # [ft/s] initial y-velocity ls_generic.h -|init V_down # [ft/s] initial z-velocity ls_generic.h +init recordRate # [/s] record data n times per second uiuc_aircraft.h + +# [s] time to start recording output data uiuc_aircraft.h +init recordStartTime + +# [] use V_rel_wind to compute control rates (instead of U_body) uiuc_aircraft.h +init nondim_rate_V_rel_wind + +# [ft/s] speed at which dynamic pressure terms are first computed uiuc_aircraft.h +init dyn_on_speed + +init Dx_pilot # [ft] reference pilot x-position ls_generic.h +init Dy_pilot # [ft] reference pilot y-position ls_generic.h +init 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 # [ft] reference cg x_location ls_generic.h +|init Dy_cg # [ft] reference cg y_location ls_generic.h +|init Dz_cg # [ft] reference cg z_location ls_generic.h +|init V_north # [ft/s] initial local x-velocity ls_generic.h +|init V_east # [ft/s] initial local y-velocity ls_generic.h +|init V_down # [ft/s] initial local z-velocity ls_generic.h +|init Altitude # [ft/s] initial altitude ls_generic.h + +init U_body # [ft/s] initial x-velocity in body axis ls_generic.h +init V_body # [ft/s] initial y-velocity in body axis ls_generic.h +init W_body # [ft/s] initial z-velocity in body axis ls_generic.h init P_body # [rad/s] initial roll rate ls_generic.h init Q_body # [rad/s] initial pitch rate ls_generic.h init R_body # [rad/s] initial yaw rate ls_generic.h init Phi # [rad] initial bank angle ls_generic.h init Theta # [rad] initial pitch attitude angle ls_generic.h init Psi # [rad] initial heading angle ls_generic.h +init Alpha # [deg] initial angle of attack ls_generic.h +init Beta # [deg] initial side slip angle ls_generic.h +init Long_trim # [rad] longitudinal trim ls_cockpit.h geometry bw # [ft] wingspan uiuc_aircraft.h geometry cbar # [ft] wing mean aero chord uiuc_aircraft.h @@ -337,10 +514,10 @@ geometry Sw # [ft^2] wing reference area uiuc_air |geometry cc # [ft] canard chord uiuc_aircraft.h |geometry Sc # [sq-ft] canard area uiuc_aircraft.h |geometry ic # [deg] canard incidence angle uiuc_aircraft.h -|geometry bh # [ft] horizontal tail span uiuc_aircraft.h -|geometry ch # [ft] horizontal tail chord uiuc_aircraft.h -|geometry Sh # [sq-ft] horizontal tail area uiuc_aircraft.h -|geometry ih # [deg] horiz tail incidence angle uiuc_aircraft.h +geometry bh # [ft] horizontal tail span uiuc_aircraft.h +geometry ch # [ft] horizontal tail chord uiuc_aircraft.h +geometry Sh # [sq-ft] horizontal tail area uiuc_aircraft.h +geometry ih # [deg] horiz tail incidence angle uiuc_aircraft.h |geometry bv # [ft] vertical tail span uiuc_aircraft.h |geometry cv # [ft] vertical tail chord uiuc_aircraft.h |geometry Sv # [sq-ft] vertical tail area uiuc_aircraft.h @@ -354,109 +531,216 @@ controlSurface de # [deg] max/min elev deflections uiuc_air controlSurface da # [deg] max/min ail deflections uiuc_aircraft.h controlSurface dr # [deg] max/min rud deflections uiuc_aircraft.h |controlSurface df # [deg] max/min flap deflections uiuc_aircraft.h -# Note: Currently demin is not used in the code, and the max/min is +-demax. +# trim always set to some fixed input value (radians) [rad] uiuc_aircraft.h +controlSurface set_Long_trim +# 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 +# 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 singlet input with deflection angle [deg], starting time [s], +# and duration of input [s] uiuc_aircraft.h +controlSurface elevator_singlet -> + + +# 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 -> + + +# tabulated elevator input (as function of time) with conversion +# factor codes and starting time [s] uiuc_aircraft.h +controlSurface elevator_input -> + -> + + +# tabulated aileron input (as function of time) with conversion +# factor codes and starting time [s] uiuc_aircraft.h +controlSurface aileron_input -> + -> + + +# tabulated rudder input (as function of time) with conversion +# factor codes and starting time [s] uiuc_aircraft.h +controlSurface rudder_input -> + -> + + +# 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 # [lb] gross takeoff weight (not used) + +mass Weight # [lb] gross takeoff weight uiuc_aircraft.h mass Mass # [slug] gross takeoff mass ls_generic.h mass I_xx # [slug-ft^2] roll inertia ls_generic.h mass I_yy # [slug-ft^2] pitch inertia ls_generic.h mass I_zz # [slug-ft^2] yaw inertia ls_generic.h mass I_xz # [slug-ft^2] lateral cross inertia ls_generic.h -|engine thrust # [lb] max/min engine thrust uiuc_aircraft.h -engine simpleSingle # [lb] simple single engine uiuc_aircraft.h -engine c172 # use Cessna 172 engine model of Tony Peden + +# maximum and minimum engine thrust [lb] uiuc_aircraft.h +|engine thrust + +# simple single engine maximum thrust [lb] uiuc_aircraft.h +engine simpleSingle + +engine c172 # use Cessna 172 engine model of Tony Peden +engine cherokee # use Piper Cherokee engine model + CL CLo # [] lift coef for all angles = 0 uiuc_aircraft.h CL CL_a # [/rad] lift curve slope, d(CL)/d(alpha) uiuc_aircraft.h CL CL_adot # [/rad] d(CL)/d(alpha)/da(time) uiuc_aircraft.h -CL CL_q # [/rad] d(CL)/delta(q) uiuc_aircraft.h +CL CL_q # [/rad] d(CL)/d(q) uiuc_aircraft.h +CL CL_ih # [/rad] CL due to horiz tail incidence uiuc_aircraft.h CL CL_de # [/rad] d(CL)/d(de) uiuc_aircraft.h # CL(alpha), conversion for CL, for alpha [] uiuc_aircraft.h -CL CLfa +CL CLfa # CL(alpha,delta_e), conversion for CL, for alpha, for delta_e [] uiuc_aircraft.h -CL CLfade +CL CLfade -> + + + # the following are lift coefficients in the body axis +CL CZo # [] lift coef for all angles = 0 uiuc_aircraft.h +CL CZ_a # [/rad] lift curve slope, d(CZ)/d(alpha) uiuc_aircraft.h +CL CZ_a2 # [/rad] d(CZ)/d(alpha squared) uiuc_aircraft.h +CL CZ_a3 # [/rad] d(CZ)/d(alpha cubed) uiuc_aircraft.h +CL CZ_adot # [/rad] d(CZ)/d(alpha)/d(time) uiuc_aircraft.h +CL CZ_q # [/rad] d(CZ)/d(q) uiuc_aircraft.h +CL CZ_de # [/rad] d(CZ)/d(de) uiuc_aircraft.h +CL CZ_deb2 # [/rad] d(CZ)/d(de, beta squared) uiuc_aircraft.h +CL CZ_df # [/rad] d(CZ)/d(df) uiuc_aircraft.h +CL CZ_adf # [/rad] d(CZ)/d(alpha, df) uiuc_aircraft.h + +# CZ(alpha), conversion for CZ, for alpha [] uiuc_aircraft.h +CL CZfa |CL CLfCT # CL(thrust coef) uiuc_aircraft.h |CL CLfRe # CL(Reynolds #), equation uiuc_aircraft.h |CL CL_afaM # CL_alpha(alpha,Mach #) uiuc_aircraft.h -# there are examples that might later be included in the code + # 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 # [] drag coef for all angles = 0 uiuc_aircraft.h -CD CDK # [] constant, as in CD=CDo+K*CL^2 uiuc_aircraft.h +CD CDK # [] induced drag constant 1/(pi*e*AR) uiuc_aircraft.h CD CD_a # [/rad] d(CD)/d(alpha) uiuc_aircraft.h +CD CD_ih # [/rad] CD due to horiz tail incidence uiuc_aircraft.h CD CD_de # [/rad] d(CD)/d(delta_e) uiuc_aircraft.h # CD(alpha), conversion for CD, for alpha [] uiuc_aircraft.h -CD CDfa +CD CDfa + +# CD(CL) drag polar, conversion for CD, for CL [] uiuc_aircraft.h +CD CDfCL # CD(alpha,delta_e), conversion for CD, for alpha, for delta_e [] uiuc_aircraft.h -CD CDfade +CD CDfade -> + + + # the following are drag coefficients in the body axis +CD CXo # [] drag coef for all angles = 0 uiuc_aircraft.h +CD CXK # [] induced drag constant 1/(pi*e*AR) uiuc_aircraft.h +CD CX_a # [/rad] d(CX)/d(alpha) uiuc_aircraft.h +CD CX_a2 # [/rad] d(CX)/d(alpha squared) uiuc_aircraft.h +CD CX_a3 # [/rad] d(CX)/d(alpha cubed) uiuc_aircraft.h +CD CX_q # [/rad] d(CX)/d(q) uiuc_aircraft.h +CD CX_de # [/rad] d(CX)/d(de) uiuc_aircraft.h +CD CX_dr # [/rad] d(CX)/d(dr) uiuc_aircraft.h +CD CX_df # [/rad] d(CX)/d(df) uiuc_aircraft.h +CD CX_adf # [/rad] d(CX)/d(alpha, df) uiuc_aircraft.h Cm Cmo # [] pitch mom coef for all angles=0 uiuc_aircraft.h Cm Cm_a # [/rad] d(Cm)/d(alpha) uiuc_aircraft.h +Cm Cm_a2 # [/rad] d(Cm)/d(alpha squared) uiuc_aircraft.h Cm Cm_adot # [/rad] d(Cm)/d(alpha)/d(time) uiuc_aircraft.h Cm Cm_q # [/rad] d(Cm)/d(q) uiuc_aircraft.h +Cm Cm_ih # [/rad] Cm due to horiz tail incidence uiuc_aircraft.h Cm Cm_de # [/rad] d(Cm)/d(de) uiuc_aircraft.h -|Cm Cmfa # [] Cm(alpha) uiuc_aircraft.h -Cm Cmfade # [] Cm(alpha,delta_e) uiuc_aircraft.h +Cm Cm_de # [/rad] d(Cm)/d(beta squared) uiuc_aircraft.h +Cm Cm_r # [/rad] d(Cm)/d(r) uiuc_aircraft.h +Cm Cm_df # [/rad] d(Cm)/d(df) uiuc_aircraft.h + +# Cm(alpha), conversion for Cm, for alpha [] uiuc_aircraft.h +Cm Cmfa + # Cm(alpha,delta_e), conversion for Cm, for alpha, for delta_e [] uiuc_aircraft.h -Cm Cmfade +Cm Cmfade -> + + CY CYo # [] side-force coef for all angles=0 uiuc_aircraft.h CY CY_beta # [/rad] d(CY)/d(beta) uiuc_aircraft.h CY CY_p # [/rad] d(CY)/d(p) uiuc_aircraft.h CY CY_r # [/rad] d(CY)/d(r) uiuc_aircraft.h -CY CY_da # [/rad] d(CY)/d(delta_a) uiuc_aircraft.h -CY CY_dr # [/rad] d(CY)/d(delta_r) uiuc_aircraft.h +CY CY_da # [/rad] d(CY)/d(da) uiuc_aircraft.h +CY CY_dr # [/rad] d(CY)/d(dr) uiuc_aircraft.h +CY CY_dra # [/rad] d(CY)/d(dr, alpha) uiuc_aircraft.h +CY CY_dra # [/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 +CY CYfada -> + # CY(beta,delta_r), conversion for CY, for beta, for delta_r [] uiuc_aircraft.h -CY CYfbetadr +CY CYfbetadr -> + Cl Clo # [] roll mom coef for all angles=0 uiuc_aircraft.h Cl Cl_beta # [/rad] d(Cl)/d(beta) uiuc_aircraft.h -Cl Cl_betafCL # [/rad] Cl_beta(CL) equation uiuc_aircraft.h Cl Cl_p # [/rad] d(Cl)/d(p) uiuc_aircraft.h Cl Cl_r # [/rad] d(Cl)/d(r) uiuc_aircraft.h -Cl Cl_rfCL # [/rad] Cl_r(CL) equation uiuc_aircraft.h -Cl Cl_da # [/rad] d(Cl)/d(delta_a) uiuc_aircraft.h -Cl Cl_dr # [/rad] d(Cl)/d(delta_r) uiuc_aircraft.h -Cl Clfada # [] Cl(alpha,delta_a), equation uiuc_aircraft.h +Cl Cl_da # [/rad] d(Cl)/d(da) uiuc_aircraft.h +Cl Cl_dr # [/rad] d(Cl)/d(dr) uiuc_aircraft.h +Cl 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 +Cl Clfada -> + # Cl(beta,delta_r), conversion for Cl, for beta, for delta_r [] uiuc_aircraft.h -Cl Clfbetadr +Cl Clfbetadr -> + Cn Cno # [] yaw mom coef for all angles=0 uiuc_aircraft.h Cn Cn_beta # [/rad] d(Cn)/d(beta) uiuc_aircraft.h -Cn Cn_betafCL # [/rad] Cn_beta(CL) equation uiuc_aircraft.h Cn Cn_p # [/rad] d(Cn)/d(p) uiuc_aircraft.h -Cn Cn_pfCL # [/rad] Cn_p(CL) equation uiuc_aircraft.h Cn Cn_r # [/rad] d(Cn)/d(r) uiuc_aircraft.h -Cn Cn_rfCL # [/rad] Cn_r(CL) equation uiuc_aircraft.h Cn Cn_da # [/rad] d(Cn)/d(da) uiuc_aircraft.h Cn Cn_dr # [/rad] d(Cn)/d(dr) uiuc_aircraft.h -Cn Cn_drfCL # [/rad] Cn_dr(CL) equation uiuc_aircraft.h +Cn Cn_q # [/rad] d(Cn)/d(q) uiuc_aircraft.h +Cn 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 +Cn Cnfada -> + # Cn(beta,delta_r), conversion for Cn, for beta, for delta_r [] uiuc_aircraft.h -Cn Cnfbetadr +Cn Cnfbetadr -> + =============================CONVERSION CODES================================ @@ -465,106 +749,267 @@ 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 +convert1/2/3 Action ------------------------------------------------ 0 no conversion (multiply by 1) 1 convert degrees to radians ============================================================================= -|gear kgear # [] gear spring constant(s) uiuc_aircraft.h -|gear muRoll # [] gear rolling friction coef(s) uiuc_aircraft.h -|gear cgear # [] gear damping constant(s) uiuc_aircraft.h -|gear strutLength # [ft] gear strut length uiuc_aircraft.h + +gear Dx_gear # [ft] x-offset from CG uiuc_aircraft.h +gear Dy_gear # [ft] y-offset from CG uiuc_aircraft.h +gear Dz_gear # [ft] z-offset from CG uiuc_aircraft.h +gear cgear # [lb/ft/s] gear damping constant uiuc_aircraft.h +gear kgear # [lb/ft] gear spring constant uiuc_aircraft.h +gear muRoll # [-] gear rolling friction coef uiuc_aircraft.h +|gear strutLength # [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 # [s] time when icing begins uiuc_aircraft.h -ice transientTime # [s] period for eta to reach eta_final uiuc_aircraft.h -ice eta_final # [] icing severity factor uiuc_aircraft.h + +# [s] period for eta_ice to reach eta_final uiuc_aircraft.h +ice transientTime + +# [] icing severity factor uiuc_aircraft.h +ice eta_ice_final + ice kCDo # [] icing constant for CDo uiuc_aircraft.h ice kCDK # [] icing constant for CDK uiuc_aircraft.h ice kCD_a # [] icing constant for CD_a uiuc_aircraft.h -|ice kCD_q # [] icing constant for CD_q uiuc_aircraft.h +ice kCD_q # [] icing constant for CD_q uiuc_aircraft.h ice kCD_de # [] icing constant for CD_de uiuc_aircraft.h -|ice kCD_dr # [] icing constant for CD_dr uiuc_aircraft.h -|ice kCD_df # [] icing constant for CD_df uiuc_aircraft.h -|ice kCD_adf # [] icing constant for CD_adf uiuc_aircraft.h +ice kCD_dr # [] icing constant for CD_dr uiuc_aircraft.h +ice kCD_df # [] icing constant for CD_df uiuc_aircraft.h +ice kCD_adf # [] icing constant for CD_adf uiuc_aircraft.h + +ice kCXo # [] icing constant for CXo uiuc_aircraft.h +ice kCXK # [] icing constant for CXK uiuc_aircraft.h +ice kCX_a # [] icing constant for CX_a uiuc_aircraft.h +ice kCX_a2 # [] icing constant for CX_a2 uiuc_aircraft.h +ice kCX_a3 # [] icing constant for CX_a3 uiuc_aircraft.h +ice kCX_q # [] icing constant for CX_q uiuc_aircraft.h +ice kCX_de # [] icing constant for CX_de uiuc_aircraft.h +ice kCX_dr # [] icing constant for CX_dr uiuc_aircraft.h +ice kCX_df # [] icing constant for CX_df uiuc_aircraft.h +ice kCX_adf # [] icing constant for CX_adf uiuc_aircraft.h + ice kCLo # [] icing constant for CLo uiuc_aircraft.h ice kCL_a # [] icing constant for CL_a uiuc_aircraft.h ice kCL_adot # [] icing constant for CL_adot uiuc_aircraft.h ice kCL_q # [] icing constant for CL_q uiuc_aircraft.h ice kCL_de # [] icing constant for CL_de uiuc_aircraft.h -|ice kCL_df # [] icing constant for CL_df uiuc_aircraft.h -|ice kCL_adf # [] icing constant for CL_adf uiuc_aircraft.h +ice kCL_df # [] icing constant for CL_df uiuc_aircraft.h +ice kCL_adf # [] icing constant for CL_adf uiuc_aircraft.h + +ice kCZo # [] icing constant for CZo uiuc_aircraft.h +ice kCZ_a # [] icing constant for CZ_a uiuc_aircraft.h +ice kCZ_a2 # [] icing constant for CZ_a2 uiuc_aircraft.h +ice kCZ_a3 # [] icing constant for CZ_a3 uiuc_aircraft.h +ice kCZ_adot # [] icing constant for CZ_adot uiuc_aircraft.h +ice kCZ_q # [] icing constant for CZ_q uiuc_aircraft.h +ice kCZ_de # [] icing constant for CZ_de uiuc_aircraft.h +ice kCZ_df # [] icing constant for CZ_df uiuc_aircraft.h +ice kCZ_adf # [] icing constant for CZ_adf uiuc_aircraft.h +ice kCZ_deb2 # [] icing constant for CZ_deb2 uiuc_aircraft.h + ice kCmo # [] icing constant for Cmo uiuc_aircraft.h ice kCm_a # [] icing constant for Cm_a uiuc_aircraft.h +ice kCm_a2 # [] icing constant for Cm_a2 uiuc_aircraft.h +ice kCm_a3 # [] icing constant for Cm_a3 uiuc_aircraft.h ice kCm_adot # [] icing constant for Cm_adot uiuc_aircraft.h ice kCm_q # [] icing constant for Cm_q uiuc_aircraft.h -|ice kCm_r # [] icing constant for Cm_r uiuc_aircraft.h +ice kCm_r # [] icing constant for Cm_r uiuc_aircraft.h ice kCm_de # [] icing constant for Cm_de uiuc_aircraft.h -|ice kCm_df # [] icing constant for Cm_df uiuc_aircraft.h +ice kCm_df # [] icing constant for Cm_df uiuc_aircraft.h + ice kCYo # [] icing constant for CYo uiuc_aircraft.h ice kCY_beta # [] icing constant for CY_beta uiuc_aircraft.h ice kCY_p # [] icing constant for CY_p uiuc_aircraft.h ice kCY_r # [] icing constant for CY_r uiuc_aircraft.h ice kCY_da # [] icing constant for CY_da uiuc_aircraft.h ice kCY_dr # [] icing constant for CY_dr uiuc_aircraft.h +ice kCY_dra # [] icing constant for CY_dra uiuc_aircraft.h +ice kCY_bdot # [] icing constant for CY_bdot uiuc_aircraft.h + ice kClo # [] icing constant for Clo uiuc_aircraft.h ice kCl_beta # [] icing constant for Cl_beta uiuc_aircraft.h ice kCl_p # [] icing constant for Cl_p uiuc_aircraft.h ice kCl_r # [] icing constant for Cl_r uiuc_aircraft.h ice kCl_da # [] icing constant for Cl_da uiuc_aircraft.h ice kCl_dr # [] icing constant for Cl_dr uiuc_aircraft.h +ice kCl_daa # [] icing constant for Cl_daa uiuc_aircraft.h + ice kCno # [] icing constant for Cno uiuc_aircraft.h ice kCn_beta # [] icing constant for Cn_beta uiuc_aircraft.h +ice kCn_b3 # [] icing constant for Cn_b3 uiuc_aircraft.h ice kCn_p # [] icing constant for Cn_p uiuc_aircraft.h +ice kCn_q # [] icing constant for Cn_q uiuc_aircraft.h ice kCn_r # [] icing constant for Cn_r uiuc_aircraft.h ice kCn_da # [] icing constant for Cn_da uiuc_aircraft.h ice 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 +ice beta_probe_wing # wing flow angle probe location uiuc_aircraft.h +ice beta_probe_wing # 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 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 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 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 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 Mass # [slug] aircraft mass ls_generic.h -record Simtime # [s] current sim time global -record dt # [s] current time step global +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 Lat_control # [] roll input ls_cockpit.h -record Rudder_pedal # [] yaw input ls_cockpit.h -|record Throttle_pct # [%] throttle 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 Throttle[3] # [%] throttle deflection ls_cockpit.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 @@ -576,6 +1021,40 @@ record Cl # [] roll moment coefficient uiuc_air 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 @@ -591,6 +1070,9 @@ record F_Z_gear # [lb] gear z-force in body-axes ls_gener 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 F_nort # [lb] total x-force in local-axes ls_generic.h +record F_east # [lb] total y-force in local-axes ls_generic.h +record F_down # [lb] total z-force in local-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 @@ -604,6 +1086,34 @@ record M_l_rp # [ft-lb] total roll mom in body axes ls_gener 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 + +fog fog_segments # [-] number of fog points after this line +fog fog_point