Kompozit esaslı katı roket yakıt numunesinin karaktersitik özelliklerinin deneysel incelenmesi
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Dosyalar
Tarih
2018
Yazarlar
Dergi Başlığı
Dergi ISSN
Cilt Başlığı
Yayıncı
Kırıkkale Üniversitesi
Erişim Hakkı
info:eu-repo/semantics/openAccess
Özet
Sunulan tez çalışması ile numune kompozit katı roket yakıtının karakteristik özelliklerinin belirlenmesi için deneysel çalışmalar yapılmıştır. Katı roket yakıtlarında roket performansını belirleyen en önemli faktörlerden biri yanma hızıdır. Katı yakıtlı roket motorlarında yanma hızı, yakıt çekirdeği yüzeyinde ateşlemenin başlatılması ile oluşan yanma reaksiyonunun yanma yüzeyine dik geriye doğru yanma gerilemesi olarak ifade edilmektedir. Katı roket yakıtı yanma hızını etkileyen birçok parametre vardır. Yanma hızını artırmak için çeşitli yüksek enerjili maddeler ilavesi gibi yöntemler uygulanmaktadır. Yakıt numunelerinin yanma ısıları (enerji seviyeleri) kapalı bomba kalorimetresiyle ölçülmüş, yakıt enerji seviyesi değeri çizelge halinde verilmiştir. Yakıtın yanma hızı değerleri farklı basınç ve sıcaklıklarda bilgisayar kontrollü kapalı bomba ve Strand Burner cihazında ölçülerek yanma hızları belirlenmiştir ve çizelge olarak gösterilmiştir. SEM ve TEM görüntüleme yöntemi ile numune yakıtın mikro yapıları ve ayrıca DSC ve TGA yöntemleri ile numune yakıtın bozunma davranışları incelenmiştir. FTIR analizi ile numunenin organik veya inorganik bileşenlerine bakılmıştır. Böylece, yapılan incelemelerle yeni üretilen yakıt numunesinin genel karakteristik yapısı belirlenmiştir
Experimental studies have been carried out to determine the characterization of sample composite solid rocket propellant with the thesis study presented. One of the most important factor determining the rocket performance in solid rocket propellant is the burning rate. In solid fuel rocket engines, the burning rate is expressed as the burnback regression which is perpendicular to the combustion surface of the combustion reaction occured by the initiation of the ignition on the surface of the fuel core. There are many parameters that affect the burning rate of the propellant. Various high energy materials are added to increase the burning rate. The heats of combustion (energy levels) of the propellant samples were measured by a closed bomb calorimeter and the energy levels of the propellant were shown on a chart. The burning rates of the fuel were determined at different pressures and temperatures by being measured in the computer-controlled closed bomb device and Strand Burner device and they were shown on a chart. The microstructure of the sample propellant was examined by SEM and TEM imaging methods. In addition, the decomposition behaviors of the sample propellant was determined by means of DSC and TGA methods. Organic and inorganic components of the sample were analyzed by FTIR analysis. Thus, as a result of the examinations, the general characteristic structure of the newly produced propellant sample has been determined.
Experimental studies have been carried out to determine the characterization of sample composite solid rocket propellant with the thesis study presented. One of the most important factor determining the rocket performance in solid rocket propellant is the burning rate. In solid fuel rocket engines, the burning rate is expressed as the burnback regression which is perpendicular to the combustion surface of the combustion reaction occured by the initiation of the ignition on the surface of the fuel core. There are many parameters that affect the burning rate of the propellant. Various high energy materials are added to increase the burning rate. The heats of combustion (energy levels) of the propellant samples were measured by a closed bomb calorimeter and the energy levels of the propellant were shown on a chart. The burning rates of the fuel were determined at different pressures and temperatures by being measured in the computer-controlled closed bomb device and Strand Burner device and they were shown on a chart. The microstructure of the sample propellant was examined by SEM and TEM imaging methods. In addition, the decomposition behaviors of the sample propellant was determined by means of DSC and TGA methods. Organic and inorganic components of the sample were analyzed by FTIR analysis. Thus, as a result of the examinations, the general characteristic structure of the newly produced propellant sample has been determined.
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