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forcesAndMoments

Class: Aero.FixedWing
Package: Aero

Calculate forces and moments of fixed-wing aircraft

Syntax

[F,M] = forcesAndMoments(aircraft,state)
[F,M] = forcesAndMoments(aircraft,state,OutputReferenceFrame=outputReference)

Description

[F,M] = forcesAndMoments(aircraft,state) calculates the forces and moments of a fixed-wing aircraft, aircraft, based around a state state.

[F,M] = forcesAndMoments(aircraft,state,OutputReferenceFrame=outputReference) calculates the forces and moments using an output reference.

Input Arguments

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Aero.FixedWing object, specified as a scalar.

Aero.FixedWing.State object, specified as a scalar.

Output reference frame of the forces and moments calculation, specified as:

  • "Body"

  • "Wind"

  • "Stability"

Example: OutputReferenceFrame="Stability"

Output Arguments

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Forces output in OutputReferenceFrame, returned as a three-element vector.

Moments output in OutputReferenceFrame, returned as a three-element vector.

Examples

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Calculate the forces and moments of a Cessna 182.

[C182,CruiseState] = astC182();
[F,M] = forcesAndMoments(C182, CruiseState)
F =
 -233.0908
         0
   -0.3300

M =
   1.0e+03 *

         0
    1.8739
         0

Version History

Introduced in R2021a