In Flight Structural Loads. Sizing of Wing Box : Root sizing criteria

Root sizing criteria
In Flight Structural Loads. Sizing of Wing Box

Author : Yves GOURINAT

Publication date: May 10, 2019 | Lire en français

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2. Root sizing criteria

2.1 Bottom panel

2.1.1 Permissible stresses – Design principles

Remember that in a diaphragm, the flux (internal force per unit width) is also the product of the stress and the thickness (N_YY = σ_YYe_skin, T_YZ = τ_YZe_spar). Thus, the stresses applied in the current zone – excluding connections – in the various panels are :

in the intrados panel :
$σ_{Y Y intrados} = \frac{N_{Y Y intrados}}{e_{intrados}} = \frac{F}{a e_{intrados}}$

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Conclusion

Bibliography

(1) - MEGSON (T.H.G.) - Aircraft structures for engineering students. - Elsevier, 876 p. (2012).
(2) - LOMAX (T.L.) - Structural loads analysis : theory and practice for commercial aircraft. - American Institute of Aeronautics and Astronautics,...

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Root sizing criteria In Flight Structural Loads. Sizing of Wing Box

2. Root sizing criteria

2.1 Bottom panel

Bibliography

Bibliography

Root sizing criteria
In Flight Structural Loads. Sizing of Wing Box