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Energies 2018, 11, 217 9 of 26 described in detail in [51]. Therefore, within this contribution only a brief introduction of the main features is provided. It highlights the most relevant methods developed for the current hybrid electric propulsion applications instead of giving a general detailed description of the tool. Figure 3 describes the general approach of the modeling structure, which follows a typical aircraft conceptual/preliminary design logic [52–55]. Some important points are discussed in the following to better illustrate the features and modeling strategies. Figure 3. Flow diagram of the general approach for modeling HEA. Design requirements and constraints such as landing and takeoff (LTO) as well as climb to fulfil certification requirements are included in the HEA modeling for a given design payload and design range. For example, the methods to determine the power-to-weight (P/W) ratio boundary for second climb gradient constraint at one-engine-inoperative condition are added to reflect the impact of the DoH. This means that the case of four or six engines installed is considered in the power rating sizing of the engines. It can lead to less performance oversizing of each propulsor. Like the multidisciplinary design optimization (MDO) approach for conventional aircraft design, aircraft planform parameters, such as wing aspect ratio, taper ratio and operational parameters such as flight altitude and speed can be selected as design variables or can be considered as design parameters. Besides the HEA strategy parameters the propulsion parameters are included into the modeling approach. Within mission iterations, the HEA parameters are utilized to deliver corresponding component information and energy requirements. Similar to the engine performance estimation methods for turbofan engines introduced in [51], within this contribution a modified method has been developed for turbo-prop engines. The engine performance calculations are based on published data, such as FAA/EASA engine certification data and ICAO engine emission database. Howe [56] has formulated several empirical methods for engine available thrust at different flight speeds and flight altitudes as well as the specific fuel consumption depending on speed and altitude. Improvements are done to give more reliable prediction of the engine performance data. This is extremely important for new entry into service engines as they usually incorporate new technologies that can significantly enhance the engine performance compared to historical performance data. Reliable data of the gas turbine performance in 2035 are not found in literature. Hence, a state-of-the-art engine performancePDF Image | Design of Operation Strategies for Hybrid Electric Aircraft
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