A load/cost/mass comparison of aluminium, glass, carbon and asbestos fibre composites for immediate application to aircraft primary structures
| dc.contributor.author | Salva, Joao Manuel Correia | |
| dc.date.accessioned | 2015-09-09T11:39:07Z | |
| dc.date.available | 2015-09-09T11:39:07Z | |
| dc.date.issued | 2015-09-09 | |
| dc.description | A Dissertation Submitted to the Faculty of Engineering, University of the W i twatersrand, Johannesburg in fulfilment of the requirements for the degree of Master of Science in Engineering. Johannesburg 1979. | en_ZA |
| dc.description.abstract | A comparison of 4 different materials for immediate app l i cation to aircraft primary structures was made on the basis of load-to-buckle/cost/mass. The materials tested were: Al-2024 T3 (Alclad) , glass fibre cloth, carbon fibre and asbestos fibre (Noramite) composites. A m a t h e matical formulation of the problem was used which was found to give very satisfactory res ults. This method made use of beam vibration modes and the Rayleigh-Ritz energy formulation and it was found that even with onl\ 4 modes of vibration, the results agreed very well with the computer analysis. A working equation lor the design of composite panels in shear is also given. | en_ZA |
| dc.identifier.uri | http://hdl.handle.net/10539/18603 | |
| dc.language.iso | en | en_ZA |
| dc.title | A load/cost/mass comparison of aluminium, glass, carbon and asbestos fibre composites for immediate application to aircraft primary structures | en_ZA |
| dc.type | Thesis | en_ZA |
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