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Energies 2018, 11, 217 14 of 26 Figure 6. Figures of merit in case of Battery 2 (0.65 kWh/kg, 1 kW/kg): (a) Fuel burn in kg (heat map) and DOC per flight (contour lines); (b) DOC for RTP-0-0 and RTP-0.9-0.9. A further analysis in Figure 6b emphasizes that DOC of HEA configurations are dominated by costs depending on the MTOW and high battery capital costs. Compared to the conventional aircraft, RTP-0-0, the battery and aircraft investment, maintenance costs and fees increase for a HEA, because these correlate with the MTOW and battery mass. Energy costs are reduced due to the higher propulsion efficiency of electric systems and lower costs for electricity. More information about the dependencies of each cost factor is provided in Appendix A. 4.2. Different Batteries The previous analysis clarifies the importance of defining an optimal battery operation strategy. In this section, batteries with varying P/E-ratios as well as power and energy densities are tested. Generally, a required P/E-ratio can be determined for every mission profile of HEA or FEA configurations. Within this contribution a simplified mission profile is used, which includes 5 min takeoff with a maximum total power of 4 MW, 70% power for 15 min climb, 40% total power for 55 min cruise, 10 min descent in idle mode and 5 min 30% power for landing. This equals 2.6 MWh of mission energy and a mission P/E-ratio of 1.54 kW/kWh. Operation strategies as power peak shaving of takeoff and/or climb shown in Table 3 require higher P/E-ratios. Table 3. P/E-ratio specifications of different operation strategies. Operation Strategy Full mission energy Takeoff power peak shaving Takeoff and climb power peak shaving Maximum Electric Power Requirement 4 MW 0.3 × 4 MW = 1.2 MW 0.6 × 4 MW = 2.4 MW Total Energy Requirement 1 2.6 MWh 0.1 MWh 0.5 MWh P/E-Ratio 1.54 kW/kWh 12 kW/kWh 4.8 kW/kWh 1 Assumptions: 5 min takeoff with full power, 15 min climb with 70% power setting, 55 min cruise with 40% power setting, 10 min descend in idle, 5 min landing with 30% power setting. The electrochemical energy storages listed in Table 1 are compared in Figure 7 to test the influence of the different power and energy requirements. Battery 1 has a low P/E-ratio of 0.62 kW/kWh and a power density of 0.4 kW/kg. This leads to high unexploited battery energy in the FEA and power peak shaving configurations (Figure 7a). Thus, the low power performance causes very high battery weights. These reach technologically feasibility limits for HP > 0.4 (Figure 7b). Nevertheless, the battery usage is shown for the simulation results that exceed reasonable limits to clarify the battery exploitationPDF Image | Design of Operation Strategies for Hybrid Electric Aircraft
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