کد مقاله | کد نشریه | سال انتشار | مقاله انگلیسی | نسخه تمام متن |
---|---|---|---|---|
11263603 | 1666350 | 2018 | 12 صفحه PDF | دانلود رایگان |
عنوان انگلیسی مقاله ISI
Minimum mass laminate design for uncertain in-plane loading
ترجمه فارسی عنوان
طراحی لمینیت حداقل برای بارگذاری نامناسب در هواپیما
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موضوعات مرتبط
مهندسی و علوم پایه
مهندسی مواد
سرامیک و کامپوزیت
چکیده انگلیسی
Requirements for lower emissions and operating costs make mass reduction of composite structures a significant issue for future aircraft. Here, minimisation of normalised elastic energy under an uncertain, general in-plane loading is used to indicate laminate efficiency and by equivalence minimum mass. Results are the first to investigate the comparative robustness of standard and non-standard angles to uncertain loading. They indicate that weight reductions of up to 8% can be achieved if optimum design, using standard angle (θâ¯=â¯0°, ±45° or 90°) and industrial design rules, is replaced by optimising non-standard angles (0°â¯â¤â¯Î¸â¯â¤â¯180°) directly for uncertain loading. However, greater reductions of up to 20% are possible through alignment of laminate balancing axes with principal loading axes. As such, a non-standard angle design strategy is only shown to be warranted if the demonstrated non-uniqueness of optimum designs can be exploited to improve other performance drivers.
ناشر
Database: Elsevier - ScienceDirect (ساینس دایرکت)
Journal: Composites Part A: Applied Science and Manufacturing - Volume 115, December 2018, Pages 348-359
Journal: Composites Part A: Applied Science and Manufacturing - Volume 115, December 2018, Pages 348-359
نویسندگان
Mark W.D. Nielsen, Richard Butler, Andrew T. Rhead,