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55 4.5 Life Cycle Assessment The design crucial design driver for an aircraft is its fuel efficiency, costs and aviation regula- tions that govern the overall design requirements. It is important to take into account of the environmental impact (EI) caused by the aircraft from the time of conceptualization till the end of life. The methodology followed here is created by Johanning (2013). A tool was creat- ed study the impact throughout all the phases of an aircraft by Johanning (2016). This tool was used to evaluate all the aircraft concepts proposed in this thesis. The working principle of the tool is briefly explained here. Design & Development Production Operation Computer use during design Material production Cruise flight LTO-cycle Wind tunnel testing Use of production facilities Energy generation and consumption at airports Operation of ground handling vehicles Flight test campaign Kerosene production End-of-life Reuse Landfill Figure 4.7 Processes considered in life cycle assessment (Johanning 2013) All the input and output emissions that lead to climate change is normalized to CO2- equivalent emissions. PKM is used as a functional unit. It stands for per passenger over one kilometre. The comparison is done using CO2-equivalent per PKM. The tool uses the ReCiPe method which calculates 18 mid-point categories and 3 end-point categories. In this tool, the above processes are mainly considered for calculating the EI in terms of Single Score (SS). The SS is a summary of EI of an aircraft in one score which will be used for comparison. For the purpose of this thesis, CO2 emissions during cruise flight, absolute share of CO2 and sin- gle score will be determined. Initially, a basic set of parameters are calculated. Then, all the inputs and outputs are calculat- ed in terms of PKM from all the processes that are being considered. This leads to determina- tion of results from the inventory analysis, that is magnitude of emissions. The mid-point and end-point categories are calculated next that provides single score along with the summary of impact assessment. The inputs for LCA for this thesis are trip range, trip fuel mass, engine mass, cruise altitude, flight time and number of flights from the preliminary sizing of the air- craft. To understand how the flight parameters of an aircraft can be optimized to reduce the environmental impact, one should refer to Caers 2019.PDF Image | Comparison of Concepts: Classic Jet Propulsion, Turbo-Electric Propulsion and Turbo-Hydraulic Propulsion
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