SIZING OF A TURBOPROP UNMANNED AIR VEHICLE AND ITS PROPULSION SYSTEM

Bu çalışmada, bir insansız hava aracının (İHA) ve turboprop motorunun analitik yöntemle boyutlandırılması için özgün bir bilgisayar yazılımı geliştirilmiştir. Faydalı yük ve yakıt ağırlıkları, İHA boyut ve ağırlığını (taşıma ve sürükleme kuvvetleri gibi temel uçuş performans parametreleri açısından karşılanması gereken) etkileyen başlıca faktörlerdir. Görev profilindeki irtifa, uçak hızı gibi parametreler, motor tipini seçmek için anahtardır. Motor özgül yakıt tüketimi (SFC) uçağın genel boyutlarını ve toplam ağırlığını etkileyen ve uçuş sırasında depolanıp taşınacak olan toplam yakıt miktarını tanımlar. Kompresör basınç oranı ve türbin giriş sıcaklığı gibi bazı motor parametrelerinin, SFC üzerinde doğrudan etkisi vardır. Bu çalışma kapsamında geliştirilen turboprop motor alt yazılımı İHAnın tüm görev noktalarında mil gücü, pervane itkisi, SFC vb. değerler için ticari motor çevrim analiz yazılımı olan "GasTurb" ile ±%1 uyum içerisindedir. İHAnın hesaplanan ağırlık, boyut, dayanıklılık değerlerinin literatür değerlerine yakın olduğu görülmüştür. Literatür değerleri, özellikle azami uçuş süresi (endurance) ve uçak boş ağırlığı için tutarsızlıklar göstermektedir. En güvenilir referanslar ve girdilerin mantıksal kombinasyonları göz önüne alındığında, İHA ağırlığı ile boyutundaki hesaplama hatası yaklaşık ±%1,5 ve azami uçuş irtifası ±%3 olarak hesaplanmıştır. Ayrıca, hesaplanan azami uçuş süresi değerleri literatürde verilen aralıklardadır.

BİR TURBOPROP İNSANSIZ HAVA ARACININ VE İTKİ SİSTEMİNİN BOYUTLANDIRILMASI

In this study, a genuine computer code for sizing of an unmanned aerial vehicle (UAV) and its turboprop engine by analytical method is developed. Payload and fuel weights are primary factors affecting UAV size and weight (which need to be fulfilled in terms of flight performance parameters, e.g. lift and drag). The parameters within mission profile such as altitude, speed of aircraft are keys for selecting engine type. Engine specific fuel consumption (SFC) defines the total fuel amount to be stored and carried during the flight, which affects the general dimensions and the gross weight of the aircraft. Some engine parameters namely, compressor pressure ratio and turbine inlet temperature, have direct influence on SFC. Turboprop engine subroutine code developed in this study is within ±1% agreement with commercial engine cycle analysis software GasTurb for shaft power, propeller thrust and SFC etc. values, at all mission points of UAV. Calculated weight, size, endurance values of UAV are seen to be close to literature values. Literature values indicate some inconsistencies especially for endurance and empty weight of aircraft. Considering most dependable references and logical combinations of inputs, error in calculation of UAV weight and size is about ±1,5% and for maximum operating altitude is around ±3%. Moreover, calculated endurance values are within range of literature values. Keywords: unmanned air vehicle design, aircraft sizing, propulsion, turboprop, gas turbine engine, cycle analysis

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