Within the European space programme, a new upper stage engine (Vinci) for the Ariane
5 launcher is being developed, and the Volvo Aero Corporation (VAC) is
contributing with tur-bines for the fuel turbopumps. This MSc thesis
investigates the possibility of designing the Turbine Exhaust Duct (TED)
of the Vinci-engine in a carbon fibre composite material with
adhesively attached titanium flanges. The focus of the project has been
on stress analyses of the adhesive joints using Finite Element Methods
(FEM), more specifically by using a cohe-sive zone material (CZM) to
model the adhesive layer. Analysing adhesive joints is complex and an
important part of the work has been to develop and concretise analysis methods for future use within VAC
To obtain
the specialised material parameters needed for a CZM analysis,
FE-models of ten-sile test specimens were analysed and the results
compared to those of equivalent experimen-tal tensile tests. These
parameters were then used when analysing the TED geometry with load
cases specified to simulate the actual operation conditions of the Vinci
engine. Both two-dimensional axisymmetric and fully three-dimensional
models were analysed and, addition-ally, a study was performed to
evaluate the effect of cryogenic temperatures on the strength of the
joint
The results show that the applied thermal and structural
loading causes local stress concentra-tions on the adhesive surface, but
the stresses are not high enough to cause damage to the joint if a
suitable joint design is used. Cryogenic temperatures (-150 C) caused a
significant strength reduction in the tensile specimens, partially
through altered adhesive properties, but no such severe effects were
seen in the temperature-dependent FE-analyses of the TED. It should be
pointed out however, that some uncertainties about the material
parameters exist, since these were obtained in a rather unconventional
way. There are also several other impor-tant questions, beside the
strength of the adhesive joint, that need to be answered before a metal-composite TED can be realised.
پروژه تحلیل اتصالات چسبی ف به کامپوزیت در کاربردهای فضایی (Analysis of Metal to Composite Adhesive Joints in Space Applications)، مشتمل بر 7 فصل، 115 صفحه، به زبان انگلیسی، تایپ شده، به همراه تصاویر، با فرمت pdf به ترتیب زیر گردآوری شده است:
Chapter 1: PROJECT BACKGROUND
Chapter 2: THEORETIC BACKGROUND
Chapter 3: ANALYSIS METHODS
Chapter 4: RESULTS
Chapter 5: DISCUSSION
Chapter 6: CONCLUSIONS
Chapter 7: REFERENCES
APPENDIX
جهت دانلود پروژه تحلیل اتصالات چسبی ف به کامپوزیت در کاربردهای فضایی (Analysis of Metal to Composite Adhesive Joints in Space Applications)، بر لینک زیر کلیک نمایید.
بررسی میزان تاثیر اندازه ابزار و نرخ پیشروی بر عمر ابزار
جزوه آموزشی خطرات مواد شیمیایی
تحليل و طراحي برنامه نت در سيستم های توليد ايستگاهی بوسيله شبيه سازی
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