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craft to have the same components mass, the correction mass (π to the π of the redesigned aircraft. π =π+π π π, =π βπ, πππ ) is introduced and added (4.27) (4.28) 44 Typically, the operating empty mass is calculated using the ratio between π and π . Since this aircraft is redesigned only for integrating a new propulsion system, it is assumed that all the other components of the A320 is the same for the redesigned aircraft. The operat- ing empty mass (π ) of the aircraft is calculated using (4.24). All the values used in this equation is taken from the A320 aircraft, since it is assumed that redesigned aircraft have sim- ilar component masses. The propulsion system mass (π ) can have three values. Ini- tially, for the first redesigned aircraft the mass of the turbofan engine given in Table 4.7 is used. For the Turbo-hydraulic/electric propulsion system aircraft, Equation (4.25a, b) can be used. The mass of the gas turbine engine (π ) can either be mass of turboprop engine (chap- ter 3.3.1) or mass of turboshaft engine (chapter 3.3.2) depending on the configuration of the aircraft. The operating empty mass of the A320 aircraft is 41244 kg. The mass of most of the components that constitute to π of A320 have been found. In order for the redesigned air- Typically, the π is calculated using the relative operating empty mass. The relative oper- ating empty mass is the ratio between π and π . This ratio can be determined using sta- tistical data and from various literature. However, when this method was implemented, a βcir- cular referenceβ error was identified in excel. Therefore, another solution was found to calcu- late the π . The π can be calculated using (4.27). The power required for take-off by one engine (π , βπ ), is calculated by multiplying the power to weight ratio with maximum take-off mass divided by the number of engines. This value of power to weight ratio is used as an input to determine the mass of HPS and EPS and the complete mass estimation is iterated.PDF Image | Comparison of Concepts: Classic Jet Propulsion, Turbo-Electric Propulsion and Turbo-Hydraulic Propulsion
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