yıldız tekn

yıldız tekn - 8....

Info iconThis preview shows pages 1–3. Sign up to view the full content.

View Full Document Right Arrow Icon
8. Uluslar Aras Õ K ÕUÕ lma Konferans Õ Bildiriler Kitab Õ 7 – 9 Kas Õ m 2007 Prooceedings of 8th International Fracture Conference 7 – 9 November 2007 Istanbul/TURKEY 554 M BA ö LANTILI TABAKALI KOMPOZ ø T PLAKADA ÖN GER ø LME MOMENT ø ø LE GEOMETR ø K PARAMETRE DE öøùø0ø1ø N HASAR ANAL ø=ø NE ETK ø6ø Yeliz PEKBEY Ege Üniversitesi, Makina Mühendisli ÷ i Bölümü,Bornova, ø zmir, Türkiye ÖZET Bu çal Õú mada, pim ba ÷ lant ÕOÕ kompozit plakan Õ n hasar yükü ve hasar modu deneysel olarak tespit edilmi ú tir. Kompozit malzeme, [0/90/±60]s dizilimine sahip ve hacimce fiber yüzdesi yaklas Õ k %60 olan cam lifi–epoksidir. Ayr Õ ca, ön gerilme momenti (M), plakan Õ n bir kenar Õ ndan delik merkezine olan mesafesinin delik çap Õ na oran Õ (E/D) ve kompozit plaka geni ú li ÷ inin delik çap Õ na oran Õ (W/D) gibi parametrelerin, hasara olan etkileri incelenmi ú tir. Malzemeye ait mekanik özellikler, ASTM standartlar Õ na uygun (ASTM 3039-76, ASTM 3518-76, ASTM D 5379, ASTM 3410-75) olarak haz Õ rlanan numuneler üzerinde yap Õ lan deneylerle tespit edilmi ú tir. Bu çal Õú mada toplam 150 adet deney numunesi kullan Õ lm ÕúWÕ r. Deney numunelerinde, ön gerilme momenti (M), E/D ve W/D oranlar Õ s Õ ras Õ yla; 0-4 Nm, 1 den 5’e kadar ve 2 den 6’a kadar de ÷Lú tirilmi ú tir. Ön gerilme momentsiz deneylerde, plakan Õ n deli ÷ i, rijit bir pim taraf Õ ndan çekme yüküne maruz kalm ÕúWÕ r. Ön gerilme momentli deneylerde ise, ön gerilme momenti, bir torkmetre yard ÕPÕ yla, civata 4 Nm s ÕNÕ larak elde edilmi ú tir. Yap Õ lan deneylerle, numuneler üzerindeki hasar tipleri ve maksimum hasar yükleri tespit edilmi ú tir. Tüm numunelerde, E/D ve W/D oranlar Õ na ba ÷OÕ olarak yatak, kayma, net çeki ve bunlar Õ n kombinasyonlar Õ olan hasar tipleri olu ú mu ú tur. Ayr Õ ca, ön gerilme momentinin, yatak mukavemetini art ÕUÕFÕ bir etkiye sahip oldu ÷ u görülmü ú tür. Anahtar kelimeler : Cam lifi-epoksi, Hasar modu, Hasar yükü, Ön gerilme momenti, Yatak gerilmesi. EFFECT OF PRELOAD MOMENT AND GEOMETRICAL PARAMETERS TO FAILURE BEHAVIOUR OF PIN-LOADED LAMINATED COMPOSITE PLATES ABSTRACT In this study, failure mode and failure loads of composite plate were determined experimentally. The composite material which have the stacking sequence of [0/90/±60]s and aproximately 60% fiber volume fraction was E glass-Epoxy. Besides, it was investigated effect of failure behaviour of the preload moment (M), end distance to diameter (E/D) and width to diameter ratios (W/D). The mechanical properties of the composite material were obtained from standard tests: ASTM 3039-76, ASTM 3518-76,ASTM D 5379, ASTM 3410- 75. In this study, a total of 150 different pin-loaded composite plate specimens were tested under static loading conditions. In experiments, the preload moment (M), end distance to diameter (E/D) and width to diameter ratios (W/D) changed from 0-4 Nm, 1 to 5 and 2 to 6 respectively. In experiments without a preload moment, the hole of the plate exposed to a
Background image of page 1

Info iconThis preview has intentionally blurred sections. Sign up to view the full version.

View Full DocumentRight Arrow Icon
8. Uluslar Aras Õ K ÕUÕ
Background image of page 2
Image of page 3
This is the end of the preview. Sign up to access the rest of the document.

This note was uploaded on 02/24/2011 for the course AERO 520 taught by Professor Rs during the Spring '11 term at Istanbul Technical University.

Page1 / 9

yıldız tekn - 8....

This preview shows document pages 1 - 3. Sign up to view the full document.

View Full Document Right Arrow Icon
Ask a homework question - tutors are online