Detailed instructions for use are in the User's Guide.
[. . . ] Aerospace Toolbox 2 User's Guide
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The software described in this document is furnished under a license agreement. The software may be used or copied only under the terms of the license agreement. [. . . ] free.
Function of. . .
alpha, delta, mach, alt alpha, delta, mach, alt alpha, delta, mach, alt
fhmcoeff_free Flap-hinge moment coefficients tab fhmcoeff_lock Flap-hinge moment coefficients tab
locked.
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datcomimport
High-Lift and Control Fields Available for Control/Trim Tabs for the 1976 Version (Continued) Field Matrix of. . . gearing.
ttab_def
Function of. . .
alpha, delta, mach, alt alpha, delta, mach, alt
fhmcoeff_gear Flap-hinge moment coefficients due to
Trim-tab deflections for zero stick force.
High-Lift and Control Fields Available for Trim for the 1976 Version Field
cl_utrim cd_utrim cm_utrim
Matrix of. . . Untrimmed lift coefficients, which are defined positive for an up-acting load. Untrimmed drag coefficients, which are defined positive for an aft-acting load. Untrimmed pitching-moment coefficients, which are defined positive for a nose-up rotation. Trimmed incremental lift coefficients in the linear-lift angle of attack range due to deflection of control surface. Trimmed incremental minimum drag coefficients due to control or flap deflection.
Function of. . .
alpha, mach, alt alpha, mach, alt alpha, mach, alt
delt_trim dcl_trim
alpha, mach, alt alpha, mach, alt
dclmax_trim dcdi_trim dcdmin_trim
alpha, mach, alt alpha, mach, alt alpha, mach, alt
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datcomimport
High-Lift and Control Fields Available for Trim for the 1976 Version (Continued) Field
cha_trim chd_trim cl_tailutrim
Matrix of. . . Trimmed control-surface hinge-moment derivatives due to angle of attack. Trimmed control-surface hinge-moment derivatives due to control deflection. Untrimmed stabilizer lift coefficients, which are defined positive for an up-acting load. Untrimmed stabilizer drag coefficients, which are defined positive for an aft-acting load. Untrimmed stabilizer pitching-moment coefficients, which are defined positive for a nose-up rotation. Untrimmed stabilizer hinge-moment coefficients, which are defined positive for a stabilizer rotation with leading edge up and trailing edge down. Trimmed stabilizer lift coefficients, which are defined positive for an up-acting load. Trimmed stabilizer drag coefficients, which are defined positive for an aft-acting load. Trimmed stabilizer pitching-moment coefficients, which are defined positive for a nose-up rotation.
Function of. . .
alpha, mach, alt alpha, mach, alt alpha, mach, alt
cd_tailutrim
alpha, mach, alt
cm_tailutrim
alpha, mach, alt
hm_tailutrim
alpha, mach, alt
aliht_tailtrim cl_tailtrim cd_tailtrim cm_tailtrim
alpha, mach, alt alpha, mach, alt alpha, mach, alt alpha, mach, alt
4-115
datcomimport
High-Lift and Control Fields Available for Trim for the 1976 Version (Continued) Field
hm_tailtrim
Matrix of. . . Trimmed stabilizer hinge-moment coefficients, which are defined positive for a stabilizer rotation with leading edge up and trailing edge down. These coefficients are defined positive for an aft-acting load.
Function of. . .
alpha, mach, alt
cl_trimi
alpha, mach, alt
cd_trimi
alpha, mach, alt
Transverse Jet Control Fields for the 1976 Version Field
time ctrlfrc locmach reynum locpres dynpres blayer ctrlcoeff corrcoeff sonicamp ampfact
Description Matrix of times. Matrix of amplification factors.
Stored with Indices of. . .
mach, alt, alpha mach, alt, alpha mach, alt, alpha mach, alt, alpha mach, alt, alpha mach, alt, alpha mach, alt, alpha mach, alt, alpha mach, alt, alpha mach, alt, alpha mach, alt, alpha
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datcomimport
Transverse Jet Control Fields for the 1976 Version (Continued) Field
vacthr minpres minjet jetpres massflow propelwt
Description Matrix of vacuum thrusts. Matrix of propellant weights.
Stored with Indices of. . .
mach, alt, alpha mach, alt, alpha mach, alt, alpha mach, alt, alpha mach, alt, alpha mach, alt, alpha
Hypersonic Fields for the 1976 Version Field
df_normal df_axial cm_normal cm_axial cp_normal cp_axial
Matrix of. . . Increments in pitching moment due to normal force per spanwise foot of control. Increments in pitching moment due to axial force per spanwise foot of control. [. . . ] This customization allows you to simultaneously run multiple FlightGear objects if you want to use · Multiple FlightGear sessions · Different ports to connect to those sessions
Examples
Set the MATLAB timer for animation of the FlightGear animation object, h:
h = Aero. FlightGearAnimation h. SetTimer
Set the MATLAB timer used for animation of the FlightGear animation object, h, and assign a custom name, MyFGTimer, to the timer:
h = Aero. FlightGearAnimation h. SetTimer('MyFGTimer')
See Also
ClearTimer
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Aero. Animation. show
Purpose Syntax Description
Show animation object figure
show(h) h. show show(h) and h. show create the figure graphics object for the animation object h. Use the Aero. Animation. hide function to close the figure.
Input Arguments Examples
h
Animation object.
Show the animation object, h.
h = Aero. Animation; idx1 = h. createBody('pa24-250_orange. ac', 'Ac3d'); h. show;
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update (Aero. Body)
Purpose Syntax Description
Change body position and orientation as function of time
update(h, t) h. update(t) update(h, t) and h. update(t) change body position and orientation of body h as a function of time t. t is a scalar in seconds.
Note This function requires that you load the body geometry and time series data first.
Examples
Update the body b with time in seconds of 5.
b=Aero. Body; b. load('pa24-250_orange. ac', 'Ac3d'); tsdata = [ . . . 10 2, 2, 2, 1, 1, 1; ]; b. TimeSeriesSource = tsdata; b. update(5);
See Also
load
4-291
update (Aero. Camera)
Purpose Syntax Description
Update camera position based on time and position of other Aero. Body objects
update(h, newtime, bodies) h. update(newtime, bodies) update(h, newtime, bodies) and h. update(newtime, bodies) update the camera object, h, position and aim point data based on the new time, newtime, and position of other Aero. Body objects, bodies. [. . . ]