Low Velocity Bird-Like Impact Behavior on Honeycomb Composite Structure

Yıl 2024, ERKEN GÖRÜNÜM, 1 - 1

Faruk Elaldı

Öz

Composite materials are widely used in primary aerospace structures such as wing components and fuselage panels; however, their major disadvantage is their vulnerability to transverse impact loads that can lead to internal delamination and fibre/matrix separation.

In this study, the effect of a low-velocity impact which simulates bird impact on a honeycomb sandwich composite plates produced by a co-curing technique for a typical unmanned air vehicle (UAV) was studied both experimentally and numerically. The surface plates of the composite samples were produced from carbon fibre/epoxy prepreg material. Nomex honeycomb core material was used to make the composite sandwich structure via an autoclave process. For the bird-like impact test, the tip of the impactor was coated with thick, tough rubber to simulate a bird strike; the diameter of the impactor was 25 mm to ensure similarity with a bird called Pica nuttalli (magpie), which has a mass of 155 g and is the closest bird body to the simulations. Three different predetermined impact scenarios with kinetic energy 380 Joule, 276 Joule, and 224 Joule were applied to the samples with rubber impactors of similar density, to simulate bird impact events with different impact directions.

The impact behaviour was characterised by velocity-time, force-time, and displacement-time graphs. Different levels of damage were observed in the composite samples, but none of the sandwich test samples were perforated, and it could therefore be concluded that the unmanned air vehicle could land without risk to flight safety. This low-velocity bird-like impact was also modelled and analysed using a numerical program to verify the results, and it was concluded that the verified model could also be used for the preliminary design verification of dynamic bird-impact tests within the 10% sensitivity range.

Anahtar Kelimeler

low velocity, impact, bird strike

KOMPOZİT GÖVDELİ HAVA ARAÇLARINA DÜŞÜK HIZLI KUŞ ÇARPMASININ PERFORMANSA ETKİSİ

Öz

Bu çalışmada, bir hava aracının kalkış ve inişlerinde meydana gelebilecek kuş çarpma olaylarında bal peteği (honeycomb) yapılı kompozit yapıların hasar davranışı hakkında deneysel ve sayısal çalışmayı öngören bir araştırma sunulmaktadır. Hava araçlarında sıklıkla kullanılan kompozit malzemelerin düşük hızlı çarpma sonucunda perfore olmaması yani hava aracı içine ulaşmaması beklenmektedir. Kompozit malzemede düşük hızlı çarpma davranışını ve meydana gelen hasar tiplerini incelemek amacıyla 75mm x 75 mm ölçülerindeki bal peteği yapılı kompozit numunelerin yüzey plakaları prepreg karbon fiber malzemeden üretilmiştir. Kompozit malzemenin alt ve üst yüzey plakaları eşit kalınlıktadır. Kuş çarpmasını kısmen simüle edecek impektör uç kısmı 25 mm çapında ve kuş çarpma deneylerinde kullanılan impektör geometrisine uygun şekilde küresel kauçuk malzemeden imal edilmiştir. Kauçuk impektör ile kompozit malzemeye 380 joule, 276 joule ve 224 joule’ lük üç farklı düzeyde enerji seviyesi uygulanmıştır. Numune yüzeylerinde gözlemlenen hasarlar, hız-zaman, kuvvet-zaman, deplasman-zaman, enerji-zaman ve deplasman-enerji grafikleri ile karakterize edilmiştir. İnsansız hava aracına, 165 gram ağırlığındaki saksağan kuşunun 68 m/sn hızı ile çarpması sonucunda perforasyon oluşumu gözlemlenmemiştir. Bu duruma bağlı olarak, uçuş emniyetini riske etmeden hava aracının güvenli şekilde iniş yapabileceği değerlendirilmektedir. Ansys sayısal modelleme programı kullanarak yapılan sayısal analizlerle deneysel sonuçlar mukayese edilmiş ve hasar yüzeyleri incelenmiştir. Deneysel ve sayısal çalışmaların sonucunda birbirine yakın neticeler elde edilmiştir. Elde edilen model %10 maksimum sapma ile statik ve dinamik testlerin ön tasarım doğrulamasında kullanılabilecektir.

Anahtar Kelimeler

kuş çarpması, kompozit, düşük hızlı çarpma

Kaynakça

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