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Comparison of Concepts: Classic Jet Propulsion, Turbo-Electric Propulsion and Turbo-Hydraulic Propulsion

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Comparison of Concepts: Classic Jet Propulsion, Turbo-Electric Propulsion and Turbo-Hydraulic Propulsion ( comparison-concepts-classic-jet-propulsion-turbo-electric-pr )

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52 4.4 Direct Operating Costs The cost analysis of every aircraft designed in the previous chapters will be computed in this chapter. There are many different cost analysis models that can be used to estimate the costs of an aircraft operator and the model used in this thesis is Direct Operating Costs (DOC)Since cost is one of the biggest design drivers for engineers developing an aircraft and selling point to customers, it is important to evaluate the direct operating costs with optimum detail and ac- curacy with a simple method. The DOC method followed in this chapter is according to AEA 1989 a method (Scholz 2019). 𝐶 =𝐶 +𝐶 +𝐶 +𝐶+𝐶+𝐶+𝐶 (4.49) (4.49) is method that DOC is calculated with. Various cost elements and aircraft parameters are utilized. The cost elements are defined briefly below. For detailed explanation, Scholz (2019) should be referred. 4.4.1 Depreciation Costs 𝐶 = 𝑃 1 − 𝑃𝑃 (4.50) 𝑛 The depreciation costs (𝐶 )of an aircraft is considered because the value of the aircraft de- creases over the years in its service lifetime (𝑛 ) of 14 years. The total price (𝑃 ) is the acquisition price of an aircraft when it is new. 𝑃 is the sum of delivery price, spares, en- gine and airframe prices. The delivery price can be calculated by various methods but in this case, the relevance of operating empty mass is significant. This is because additional mass is added due to propulsion system can be represented with 𝑚 tained with statistical data and the value is 0.10. 4.4.2 Interest and Insurance Costs 𝐶 =𝑘 ∙𝑃 𝐶 =𝑘 ∙𝑃 . 𝑃 ⁄𝑃 , is ratio ob- (4.51) (4.52)

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