Analytical methodology for the design of load-bearing anisotropic panels for the wingbox of a light aircraft subject to geometric nonlinearity under compression

Maksim Shkurin

Makale detayları

Analytical methodology for the design of load-bearing anisotropic panels for the wingbox of a light aircraft subject to geometric nonlinearity under compression

Yazarlar:

Maksim Shkurin

Yayıncı:

Yildiz Technical University

Ana Başlıklar:

Building (Other)

Dergi:

Sigma Journal of Engineering and Natural Sciences Vol.42 Issue 6, pp.1756-1762

Belge Tipi:

Makale

Yayın Tarihi:

9/2024

Belge Dili:

İngilizce

Document ID (Org No.):

2001333112

pISSN:

1304-7191

Anahtar kelimeler:

Özet:

 The subject of this research is the upper load-bearing anisotropic panels of the wingbox of the forward-swept wing of a light aircraft, exposed mainly to longitudinal compression. The panels are fixed along the long sides. The paper considers how to determine the minimum thickness of these panels at a postbuckling state under loads exceeding the operational level. Based on the analytical solution for geometrically nonlinear problems obtained by the Bub-nov-Galerkin method, a technique for designing anisotropic panels at a postbuckling state is proposed. To determine the panels thickness, the strength criteria for a monolayer of the composite material were used. The main result of the work is a nonlinear equation for the panels minimum thickness. It incorporates the equivalence of the membrane stresses due to panel buckling and the limit stresses of the composite package monolayer.

 The subject of this research is the upper load-bearing anisotropic panels of the wingbox of the forward-swept wing of a light aircraft, exposed mainly to longitudinal compression. The panels are fixed along the long sides. The paper considers how to determine the minimum thickness of these panels at a postbuckling state under loads exceeding the operational level. Based on the analytical solution for geometrically nonlinear problems obtained by the Bub-nov-Galerkin method, a technique for designing anisotropic panels at a postbuckling state is proposed. To determine the panels thickness, the strength criteria for a monolayer of the composite material were used. The main result of the work is a nonlinear equation for the panels minimum thickness. It incorporates the equivalence of the membrane stresses due to panel buckling and the limit stresses of the composite package monolayer.

 The subject of this research is the upper load-bearing anisotropic panels of the wingbox of the forward-swept wing of a light aircraft, exposed mainly to longitudinal compression. The panels are fixed along the long sides. The paper considers how to determine the minimum thickness of these panels at a postbuckling state under loads exceeding the operational level. Based on the analytical solution for geometrically nonlinear problems obtained by the Bub-nov-Galerkin method, a technique for designing anisotropic panels at a postbuckling state is proposed. To determine the panels thickness, the strength criteria for a monolayer of the composite material were used. The main result of the work is a nonlinear equation for the panels minimum thickness. It incorporates the equivalence of the membrane stresses due to panel buckling and the limit stresses of the composite package monolayer.

 The subject of this research is the upper load-bearing anisotropic panels of the wingbox of the forward-swept wing of a light aircraft, exposed mainly to longitudinal compression. The panels are fixed along the long sides. The paper considers how to determine the minimum thickness of these panels at a postbuckling state under loads exceeding the operational level. Based on the analytical solution for geometrically nonlinear problems obtained by the Bub-nov-Galerkin method, a technique for designing anisotropic panels at a postbuckling state is proposed. To determine the panels thickness, the strength criteria for a monolayer of the composite material were used. The main result of the work is a nonlinear equation for the panels minimum thickness. It incorporates the equivalence of the membrane stresses due to panel buckling and the limit stresses of the composite package monolayer.

Makale detayları

Analytical methodology for the design of load-bearing anisotropic panels for the wingbox of a light aircraft subject to geometric nonlinearity under compression

Yazarlar:

Maksim Shkurin

Yayıncı:

Yildiz Technical University

Ana Başlıklar:

Building (Other)

Dergi:

Sigma Journal of Engineering and Natural Sciences Vol.42 Issue 6, pp.1756-1762

Belge Tipi:

Makale

Yayın Tarihi:

9/2024

Belge Dili:

İngilizce

Document ID (Org No.):

2001333112

pISSN:

1304-7191

Geometrically Non-Linear Behavior

Anisotropic Material

Rectangular Panels

Longitudinal Compression

Sayı

Makale detayları

Analytical methodology for the design of load-bearing anisotropic panels for the wingbox of a light aircraft subject to geometric nonlinearity under compression

Yazarlar: Maksim Shkurin

Yayıncı: Yildiz Technical University

Ana Başlıklar: Building (Other)

Dergi: Sigma Journal of Engineering and Natural Sciences Vol.42 Issue 6, pp.1756-1762

Belge Tipi: Makale

Yayın Tarihi: 9/2024

Belge Dili: İngilizce

Document ID (Org No.): 2001333112

pISSN: 1304-7191

Geometrically Non-Linear Behavior

Anisotropic Material

Rectangular Panels

Longitudinal Compression

Sayı

Yazarlar:

Maksim Shkurin

Yayıncı:

Yildiz Technical University

Ana Başlıklar:

Building (Other)

Dergi:

Sigma Journal of Engineering and Natural Sciences Vol.42 Issue 6, pp.1756-1762

Belge Tipi:

Makale

Yayın Tarihi:

9/2024

Belge Dili:

İngilizce

Document ID (Org No.):

2001333112

pISSN:

1304-7191