staticStability
Class: Aero.FixedWing
Namespace: Aero
Syntax
stability = staticStability(aircraft,state)
stability = staticStability(___,Name,Value)
[stability,derivatives] = staticStability(___)
Description
calculates the static stability stability
= staticStability(aircraft
,state
)stability
of a fixed-wing aircraft
aircraft
at an Aero.FixedWing.State
state
. This method calculates static stability from changes in body
forces and moments due to perturbations of an aircraft state. By default, these states are
airspeed, angle of attack, angle of side slip, and body roll rates. To change these states,
see criteriaTable
.
The staticStability
method evaluates the changes in body forces and
moments after a perturbation as either greater than, equal to, or less than 0 using the
matching entry in the criteria table.
If the evaluation of a criterion is met, the aircraft is statically stable at that condition.
If the evaluation of a criterion is not met, the aircraft is statically unstable at that condition.
If the perturbation value is set to
0
, the aircraft is statically neutral at that condition.
calculates the static stability result with the specified stability
= staticStability(___,Name,Value
)Name,Value
arguments. Specify any of the input argument combinations in the previous syntaxes followed by
Name,Value
pairs as the last input arguments.
[
returns the body forces and moments derivatives table along with the static stability. Specify
any of the input argument combinations in the previous syntaxes.stability
,derivatives
] = staticStability(___)
Input Arguments
Output Arguments
Examples
Version History
Introduced in R2021a
See Also
Aero.FixedWing
| criteriaTable
| forcesAndMoments
| linearize