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Roshanbin, Sholeh 2010 (English)Independent thesis Advanced level (professional degree), 20 credits / 30 HE creditsStudent thesis

Abstract [en] : Carbon fibre composites for use in the design of a light aircraft have been investigated in terms of static uniaxial compressive strength, stiffness and to some extent, static shear properties and misalignment sensitivity. Several different test methods have been evaluated, to appoint a preferred method to determine the compressive properties of very thin fabric composites. Various standard handbooks are employed to provide the customer with an accurate, aerospace industry standard evaluation of the appropriate material properties, using a proper confidence level, for the design phase of the project. The fibre distribution in a prototype wing spar is mapped and investigated for local fibre content and local compressive strength, which is found to differ greatly from the manufacturer’s specifications. Image analysis is performed by use of two slightly different methods to extract the local fibre volume fraction, which is averaged over the spar crosssection. A model for the compressive strength of the fabrics is evaluated, based on fibre inclination and shear strength properties. A good agreement with experimental results is found, and a more recent model for off-axis compressive strength is evaluated.

Place, publisher, year, edition, pages: 2010.

Keyword [en] : Physics Chemistry Maths, Carbon fibres, prepreg fabrics, compressive test methods, compressive mechanical properties

Keyword [sv] : Fysik, Kemi, Matematik

Identifiers: URN: urn:nbn:se:ltu:diva-58516ISRN: LTU-EX--10/054--SELocal ID: f1897604-923c-4401-9e9f-77b3a287fe34OAI: diva2:1031904

Subject / course: Student thesis, at least 30 credits

Educational program: Space Engineering, master's level

Examiners : Varna, Janis

Note: Validerat; 20101217 (root)Available from: 2016-10-04 Created: 2016-10-04Bibliographically approved

Autor: Häll, Niklas


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