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@ -2,10 +2,10 @@
* * * *
* FGFS Reconfigurable Aircraft Flight Model * * FGFS Reconfigurable Aircraft Flight Model *
* Input File Documentation * * Input File Documentation *
* Version 0.63, March 17, 2000 * * Version 0.64, March 28, 2000 *
* * * *
* Authors: * * Authors: *
* Jeff Scott (jscott@uiuc.edu) * * Jeff Scott (jscott@mail.com) *
* Bipin Sehgal (bsehgal@uiuc.edu) * * Bipin Sehgal (bsehgal@uiuc.edu) *
* Michael Selig (m-selig@uiuc.edu) * * Michael Selig (m-selig@uiuc.edu) *
* Dept of Aero and Astro Engineering * * Dept of Aero and Astro Engineering *
@ -15,14 +15,14 @@
* * * *
************************************************ ************************************************
********************************************************************** **********************************************************************
This documentation includes: This documentation includes:
- Required and optional input lines. - Required and optional input lines.
- Input line formats and conventions. - Input line formats and conventions.
Viewing this file in emacs makefile-mode with color makes this file Viewing this file in emacs makefile-mode with color makes this file
easier to read. easier to read.
********************************************************************** **********************************************************************
********************************************************************** **********************************************************************
@ -33,6 +33,7 @@ I. Conventions and Notations and Reading this Document:
| Optional data | Optional data
| Sometimes indicates a feature not yet used, | Sometimes indicates a feature not yet used,
but proposed convention is indicated nevertheless. but proposed convention is indicated nevertheless.
<...> Value or file name to be placed here
|| Input line disabled || Input line disabled
|| Option disabled || Option disabled
... Repeat similar data ... Repeat similar data
@ -73,8 +74,8 @@ CY Aerodynamic y-force quantities (lateral)
Cl Aerodynamic l-moment quantities (lateral) Cl Aerodynamic l-moment quantities (lateral)
Cn Aerodynamic n-moment quantities (lateral) Cn Aerodynamic n-moment quantities (lateral)
|gear Landing gear model quantities |gear Landing gear model quantities
ice Aircraft icing model parameters ice Icing model parameters
record Record desired quantities to the file: uiuc_record.dat record Record desired quantites to file
As each line of the input file is read, the code recognizes the As each line of the input file is read, the code recognizes the
keyword, enters the appropriate switch statement in the code, and keyword, enters the appropriate switch statement in the code, and
@ -103,7 +104,7 @@ The conventions used for naming the variables are provided below.
Several of these variable names are not currently used. Several of these variable names are not currently used.
1) variable class 1) variable class
_ denotes stability derivative to be multiple by something _ denotes stability derivative to be multiplied by something
f "function of" (indicates an m*n matrix data table is given) f "function of" (indicates an m*n matrix data table is given)
2) timing data (global simulator variables) 2) timing data (global simulator variables)
@ -140,7 +141,7 @@ M Mach number []
Re Reynolds number [] Re Reynolds number []
4) atmosphere properties 4) atmosphere properties
Density air density [slug/ft^3] Density air density [slug/ft^3]
5) geometric variables 5) geometric variables
bw wingspan [ft] bw wingspan [ft]
@ -231,7 +232,7 @@ M_n_rp total yaw-moment [ft-lb]
|muGear gear rolling friction coef [?] |muGear gear rolling friction coef [?]
|strutLength gear strut length [ft] |strutLength gear strut length [ft]
12) icing model paramters 12) icing model parameters
iceTime time when icing begins [s] iceTime time when icing begins [s]
transientTime time period over which eta increases to final [s] transientTime time period over which eta increases to final [s]
eta_final icing severity factor at end of transient time [-] eta_final icing severity factor at end of transient time [-]
@ -259,7 +260,7 @@ df flap deflection
max maximum max maximum
min minimum min minimum
(3) | (OPTIONAL DATA) (3) | [OPTIONAL DATA]
===================== =====================
An input line may also be used to provide optional data that An input line may also be used to provide optional data that
@ -268,7 +269,7 @@ 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 values or data files may be provided if the code is written to use
them. them.
(4) # (COMMENTS) (4) # [COMMENTS]
================ ================
Appended comments should be provided with each input line to indicate Appended comments should be provided with each input line to indicate
@ -300,11 +301,11 @@ CD CDfCL # CD(CL), drag calculated in code based on CL
********************************************************************** **********************************************************************
********************************************************************** **********************************************************************
IV. Definitions of Input Lines Currently Available: IV. Input Line Definitions:
Of all the possible permutation of variable names described above in Of all the possible permutations of variable names described above in
section II, only some are currently implemented in the code. These section II, only some are curently implemented in the code. These are
are described below. Comments, denoted by '#,' are used to define the described below. Comments, denoted by '#,' are used to define the
lines and to indicate examples of the data if additional clarity is lines and to indicate examples of the data if additional clarity is
needed for unique situations. Again, those lines beginning with '|' needed for unique situations. Again, those lines beginning with '|'
are not currently implemented in the code, but indicate planned are not currently implemented in the code, but indicate planned
@ -366,9 +367,15 @@ mass I_yy <I_yy> # [slug-ft^2] pitch inertia ls_gener
mass I_zz <I_zz> # [slug-ft^2] yaw inertia ls_generic.h mass I_zz <I_zz> # [slug-ft^2] yaw inertia ls_generic.h
mass I_xz <I_xz> # [slug-ft^2] lateral cross inertia ls_generic.h mass I_xz <I_xz> # [slug-ft^2] lateral cross inertia ls_generic.h
|engine thrust <thrustMax> <thrustMin> # [lb] max/min engine thrust uiuc_aircraft.h
engine simpleSingle <sSMaxThrust> # [lb] simple single engine uiuc_aircraft.h # maximum and minimum engine thrust [lb] uiuc_aircraft.h
engine c172 # use Cessna 172 engine model of Tony Peden |engine thrust <thrustMax> <thrustMin>
# simple single engine maximum thrust [lb] uiuc_aircraft.h
engine simpleSingle <simpleSingleMaxThrust>
engine c172 # use Cessna 172 engine model of Tony Peden
CL CLo <CLo> # [] lift coef for all angles = 0 uiuc_aircraft.h CL CLo <CLo> # [] lift coef for all angles = 0 uiuc_aircraft.h
CL CL_a <CL_a> # [/rad] lift curve slope, d(CL)/d(alpha) uiuc_aircraft.h CL CL_a <CL_a> # [/rad] lift curve slope, d(CL)/d(alpha) uiuc_aircraft.h
@ -385,7 +392,8 @@ CL CLfade <CLfade.dat> <conversion1> <conversion2> <conversion3>
|CL CLfCT <CLfCT.dat> # CL(thrust coef) uiuc_aircraft.h |CL CLfCT <CLfCT.dat> # CL(thrust coef) uiuc_aircraft.h
|CL CLfRe # CL(Reynolds #), equation uiuc_aircraft.h |CL CLfRe # CL(Reynolds #), equation uiuc_aircraft.h
|CL CL_afaM <CL_afaM.dat> # CL_alpha(alpha,Mach #) uiuc_aircraft.h |CL CL_afaM <CL_afaM.dat> # 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 # note that CD terms must come after CL for induced drag to be computed
CD CDo <CDo> # [] drag coef for all angles = 0 uiuc_aircraft.h CD CDo <CDo> # [] drag coef for all angles = 0 uiuc_aircraft.h
@ -407,9 +415,11 @@ Cm Cm_q <Cm_q> # [/rad] d(Cm)/d(q) uiuc_air
Cm Cm_de <Cm_de> # [/rad] d(Cm)/d(de) uiuc_aircraft.h Cm Cm_de <Cm_de> # [/rad] d(Cm)/d(de) uiuc_aircraft.h
|Cm Cmfa <Cmfa.dat> # [] Cm(alpha) uiuc_aircraft.h |Cm Cmfa <Cmfa.dat> # [] Cm(alpha) uiuc_aircraft.h
Cm Cmfade <Cmfade.dat> # [] Cm(alpha,delta_e) uiuc_aircraft.h Cm Cmfade <Cmfade.dat> # [] Cm(alpha,delta_e) uiuc_aircraft.h
# Cm(alpha,delta_e), conversion for Cm, for alpha, for delta_e [] uiuc_aircraft.h # Cm(alpha,delta_e), conversion for Cm, for alpha, for delta_e [] uiuc_aircraft.h
Cm Cmfade <Cmfade.dat> <conversion1> <conversion2> <conversion3> Cm Cmfade <Cmfade.dat> <conversion1> <conversion2> <conversion3>
CY CYo <CYo> # [] side-force coef for all angles=0 uiuc_aircraft.h CY CYo <CYo> # [] side-force coef for all angles=0 uiuc_aircraft.h
CY CY_beta <CY_beta> # [/rad] d(CY)/d(beta) uiuc_aircraft.h CY CY_beta <CY_beta> # [/rad] d(CY)/d(beta) uiuc_aircraft.h
CY CY_p <CY_p> # [/rad] d(CY)/d(p) uiuc_aircraft.h CY CY_p <CY_p> # [/rad] d(CY)/d(p) uiuc_aircraft.h