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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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π‘š =π‘š +π‘š +π‘š +π‘š +π‘š +π‘š +π‘š π‘š =π‘š +π‘š π‘š =π‘š +π‘š +π‘š (4.24) (4.25π‘Ž) (4.25𝑏) (4.26) 43 The mission fuel fraction (𝑀 ) is a parameter that is used to calculate the fuel consumed for a complete flight. In order to calculate 𝑀 , the mission fuel fraction of all the flight phases must be taken in to account. This is shown in Table 4.6 and previously. The standard mission fuel fraction (𝑀 , ) and the reserve mission fuel fraction (𝑀 , ) are multiplied to calcu- late𝑀 . π‘š =π‘š βˆ™π‘› +π‘š (4.23) The mass of payload (π‘š ) is the sum of product of number of passengers (𝑛 ) and mass of on passenger (π‘š ) and mass of cargo (π‘š ). This aircraft is designed for 180 passengers and mass of a passenger along with their bag is 93 kg. It is assumed that this aircraft is de- signed only for passenger transport, therefore mass of cargo is ignored. Although, the A320 aircraft is designed to carry cargo, the MTOW for the redesigned aircraft is taken from Figure 4.1 for the exact payload mass of this aircraft. Therefore, the total payload mass is equal to 16740 kg. Or, π‘š =π‘š, Table 4.7 Component Fuselage π‘š Wing π‘š Horizontal Tail π‘š Vertical Tail π‘š Landing Gear π‘š Systems π‘š CFM 56-5B4 with Nacelle π‘š Correction π‘š βˆ’π‘š +π‘š+π‘š+π‘š+π‘š+π‘š +π‘š Component mass of A320 (Nita 2013) Mass 9235.12 π‘˜π‘” 6189.53 π‘˜π‘” 635.83 π‘˜π‘” 463.00 π‘˜π‘” 2247.42 π‘˜π‘” 7685.94 π‘˜π‘” 3886.34 π‘˜π‘” 7014.46 π‘˜π‘”

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