Connexion
S'inscrire
Réinitialiser le mot de passe
Publier & Distribuer
Solutions d'édition
Solutions de distribution
Thèmes
Architecture et design
Arts
Business et économie
Chimie
Chimie industrielle
Droit
Géosciences
Histoire
Informatique
Ingénierie
Intérêt général
Linguistique et sémiotique
Littérature
Mathématiques
Musique
Médecine
Pharmacie
Philosophie
Physique
Sciences bibliothécaires et de l'information, études du livre
Sciences des matériaux
Sciences du vivant
Sciences sociales
Sport et loisirs
Théologie et religion
Études classiques et du Proche-Orient ancient
Études culturelles
Études juives
Publications
Journaux
Livres
Comptes-rendus
Éditeurs
Blog
Contact
Chercher
EUR
USD
GBP
Français
English
Deutsch
Polski
Español
Français
Italiano
Panier
Home
Journaux
Transactions on Aerospace Research
Édition 2023 (2023): Edition 2 (June 2023)
Accès libre
Modelling of the Monolithic Stiffener Forming Process from a Paek Thermoplastic Composite Matrix Using Pam-Form Software
Witold Polański
Witold Polański
| 12 juin 2023
Transactions on Aerospace Research
Édition 2023 (2023): Edition 2 (June 2023)
À propos de cet article
Article précédent
Article suivant
Résumé
Article
Figures et tableaux
Références
Auteurs
Articles dans cette édition
Aperçu
PDF
Citez
Partagez
Article Category:
research article
Publié en ligne:
12 juin 2023
Pages:
58 - 75
Reçu:
18 mars 2021
Accepté:
13 avr. 2023
DOI:
https://doi.org/10.2478/tar-2023-0012
Mots clés
thermoplastic composite
,
thermoforming
,
fabric
,
PAEK
,
numerical analysis
,
monolithic part
,
aviation
© 2023 Witold Polański, published by Sciendo
This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.
Figure 1.
Model of monolithic door stiffening part for the ILX-34 aircraft [11].
Figure 2.
Dimensions of the ILX-34 aircraft door in millimetres [11].
Figure 3.
Examples of spring fastenings using ‘colds pots’ zones [5].
Figure 4.
Example of mounting the blank on a transport frame.
Figure 5.
a) Block diagram of the thermoforming process [13], b) process chart.
Figure 6.
Scheme of a composite sample for determining the shear angle: a) before applying force, b) after reaching the maximum elongation [16].
Figure 7.
a) Model of the stretched sample (shear angle in degrees), b) illustrative photo of the stretched sample [18].
Figure 8.
Graph of the theoretical shear angle change.
Figure 9.
Tensile test result [15].
Figure 10.
Shear stiffness in the plane of the layer G.
Figure 11.
Comparison of stretching graphs of the composite sample at 360°C and the result of numerical analysis.
Figure 12.
Comparison of theoretical shear angle and shear angle diagrams obtained in the numerical analysis.
Figure 13.
Diagram of the test stand for bending the sample.
Figure 14.
Sample model during free overhanging: a) fibre direction 0°, b) displacement values in [mm] for 0° direction at T = 360°C.
Figure 15.
Comparison of the shape of the bent sample at T = 360°C in the direction of the fibres 0°.
Figure 16.
Comparison of the shape of the bent sample at T = 360°C in the direction of the fibres 90°.
Figure 17.
Diagram of a numerical model.
Figure 18.
Stamp displacement profile.
Figure 19.
Graph of spring stiffness used in the analysis.
Figure 20.
a) Blank displacements in the y direction, b) shear angles in the 45 layer.
Figure 21.
Comparison of the part shape with the result of the analysis.
Figure 22.
Mesh comparison: a) without local mesh ‘refinement’ option, b) local ‘refinement’ option at level 3.
Figure 23.
Shear angle values for: a) 0° layer, b) 45° layer.
Figure 24.
Values of bending moments in fibres during the process, for: a) 0° layer, b) 45° layer.
Figure 25.
Comparison of wrinkle formation as a result of the shear angle in the part with the result of the analysis.
Figure 26.
Formation of wrinkles as a result of bending the material.
Figure 27.
Values of friction coefficient during the process for a) 0° layer, b) 45° layer.
Aperçu