Döner kanatlı hava araçları için uçuş verileri kayıt cihazı tasarımı
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Dosyalar
Tarih
2017
Yazarlar
Dergi Başlığı
Dergi ISSN
Cilt Başlığı
Yayıncı
Kırıkkale Üniversitesi
Erişim Hakkı
info:eu-repo/semantics/openAccess
Özet
Bu çalışmada, helikopterlerde kullanılmak üzere Uçuş Verileri Kayıt Cihazı tasarlanmış, üretilmiş ve uluslararası havacılık standartlarına uyum göstermesi için testleri yapılmıştır. Çalışmanın ilk aşamasında, SOLİDWORKS programı kullanılarak hafıza modülünün katı modellemesi yapılmış ve sonra ANSYS programı kullanılarak dinamik, statik ve ısıl analizleri gerçekleştirilmiştir. Dinamik analizde, ANSYS 16.2 Dinamik Explicit modülü kullanılarak serbest düşme analizi yapılmış, deneysel çalışmada ise 227 kg ağırlık 3 m yükseklikten ağırlık altında pim olacak şekilde model üzerine düşürülmüştür. Parça üzerindeki kalıcı şekil değişimi deneysel testte 2.12 mm ölçülmüş, sayısal analizde 1.99 mm olarak hesaplanmıştır. Değerler arasındaki yaklaşık % 6 sapma kabul edilen sınır şartlarının gerçeğe yakın olduğunu göstermiştir. Statik analizde, ANSYS 16.2 Statik Yapısal modülü kullanılarak model üzerine 4500 kg yük uygulanmış ve sonuç incelenmiştir. Sistemin analitik çözümü yapılmış ve son aşamada deneysel testler yapılarak modele hidrolik presle 4500 kg uygulanmıştır. Alınan veriler sonucu sayısal analiz ve basma testinde deformasyon olmadığı, şekil değişiminin elastik bölgede kaldığı görülmüştür. Isıl analizde, ANSYS 16.2 Kısa Süreli Isıl Analiz modülü ile model üst cidarına 1100 0C sıcaklık uygulanmış ve model içerisindeki sıcaklık dağılımı incelenmiştir. Sistemin sayısal çözümü yapılmış ve hazırlanan test düzeneğinde deneysel çalışmalar yapılmıştır. Sayısal çözüm ve deneysel çalışmalar sonucu; hafıza modülü içerisindeki 150 0C dereceye dayanıklı kartın 90 0C sıcaklığa maruz kaldığı görülmüştür. Tasarlanan Uçuş Verileri Kayıt Cihazı üzerinde yapılan mekanik ve ısıl test sonuçlarının uluslararası havacılık standartları ile uyumlu olduğu görülmüş ve Uçuş Verileri Kayıt Cihazı helikoptere takılarak uçuş testleri gerçekleştirilmiştir.
In this study, a Flight Data Recorder to be used on helicopters was designed, produced and tested to show compliance to international aviation standards. At the first phase of the study, SOLIDWORKS Program has been used for modeling, and then ANSYS 16.2 Program has been used for dynamic, static and thermal analysis. In the dynamic analysis, drop analysis has been done by using ANSYS 16.2 Explicit Dynamic Module and in the experimental study 227 kg weight with a pin at the bottom has been dropped to the model from 3m height. The plastic deformation on the test specimen has been measured as 2.12 mm and calculated as 1.99 mm in the numerical analysis the 6% difference between the values show that accepted limit conditions are close to reality. In the static analysis, 4500 kg load has been applied on the model by using ANSYS 16.2 Static structural module and the results have been examined. System has been analytically resolved and in the final phase, 4500 kg has been applied to the specimen in hydraulic press for experimental testing. In accordance with the received data in numerical analysis and press test, it was seen that deformation didn't occur and strain was just in elastic region. In the thermal analysis, the external wall of the model has been exposed to 1100 0C using ANSYS 16.2 Transient Thermal module and temperature distribution has been investigated. The system has been numerically resolved and experimental studies have been done on the prepared test setup. In accordance with the numerical solution and experimental study's results, it was seen that the card in the memory module which is endurable up to 150 0C has been exposed to 90 0C. It was seen that, the results of mechanical and thermal tests which have been performed on designed Flight Data Recorder are compliant with international aviation standards and after installation of Flight Data Recorder on the helicopter, flight tests have been performed.
In this study, a Flight Data Recorder to be used on helicopters was designed, produced and tested to show compliance to international aviation standards. At the first phase of the study, SOLIDWORKS Program has been used for modeling, and then ANSYS 16.2 Program has been used for dynamic, static and thermal analysis. In the dynamic analysis, drop analysis has been done by using ANSYS 16.2 Explicit Dynamic Module and in the experimental study 227 kg weight with a pin at the bottom has been dropped to the model from 3m height. The plastic deformation on the test specimen has been measured as 2.12 mm and calculated as 1.99 mm in the numerical analysis the 6% difference between the values show that accepted limit conditions are close to reality. In the static analysis, 4500 kg load has been applied on the model by using ANSYS 16.2 Static structural module and the results have been examined. System has been analytically resolved and in the final phase, 4500 kg has been applied to the specimen in hydraulic press for experimental testing. In accordance with the received data in numerical analysis and press test, it was seen that deformation didn't occur and strain was just in elastic region. In the thermal analysis, the external wall of the model has been exposed to 1100 0C using ANSYS 16.2 Transient Thermal module and temperature distribution has been investigated. The system has been numerically resolved and experimental studies have been done on the prepared test setup. In accordance with the numerical solution and experimental study's results, it was seen that the card in the memory module which is endurable up to 150 0C has been exposed to 90 0C. It was seen that, the results of mechanical and thermal tests which have been performed on designed Flight Data Recorder are compliant with international aviation standards and after installation of Flight Data Recorder on the helicopter, flight tests have been performed.
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