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22 3 Methods for Sizing and Performance of Hybrid-Electric Aircraft laws and semi-empirical equations the weight of the aircraft components is determined. Ac- cording to the size of the aircraft, the drag polar characteristics of the aircraft are computed. Knowing the aerodynamic efficiency, the aircraft weight and the propulsion system charac- teristics, the mission performance and the point performance requirements are analysed. The mission analysis module determines the total fuel mass required to fulfil the design mission. If the total fuel mass is higher than the first estimated fuel mass, the MTOW is increased by iteration. If the performance constraints are not fulfilled, the aircraft sizing paramet- ers namely 𝑃/𝑀𝑇𝑂𝑊 and 𝑀𝑇𝑂𝑊/𝑆𝑟𝑒𝑓 are adjusted through iteration. Once the mission performance requirement and the performance constraints are fulfilled, the aircraft is finally sized for its transport task. The consideration of hybrid-electric propulsion system disrupts the traditional sizing pro- cess. In particular, the introduction of an additional electric propulsion chain requires the establishment of new design variables to determine the power and energy split between the conventional and the electrical system as described in Section 3.2.1. The total fuel mass is currently the single energy-based constraint assessed in the traditional methods. An addi- tional energy constraint needs to be established in the aircraft sizing process to take into account the electrical energy available and in order to size subsequently the electric energy and power devices as discussed in Section 3.2.6. Moreover the presence of electrical compon- ents constituting to the propulsion requires the development of components sizing methods and principles as established in Section 3.2.7. 3.2 Methods for Sizing and Performance of Hybrid-Electric Aircraft The traditional methods presented in the previous section are adequate for the sizing of conventional transport aircraft. Proprietary or commercially available aircraft performance programs or design environments such as the FLight Optimization System (FLOPS) [99], the Aircraft Performance Program (APP) [100], the aircraft analysis tool Piano (Piano) [101] and the PACELab Aircraft Preliminary Design (PACELab APD) [102] rely on these conven- tional methods. However, the integration of novel propulsion systems such as hybrid-electric propulsion system disrupts the conventional sizing and integrated performance analysis pro- cess. The methods need to be extended to capture the specifics of the nature of hybrid-electric propulsion system within the aircraft sizing and performance environment. Due to the integration of an electrical system contributing to the propulsion, new system design parameters come into place. The design variables specific to the sizing of hybrid- electric propulsion systems need to be identified and implemented within the sizing process of the aircraft. The design parameters for the sizing of hybrid-electric aircraft are defined in Section 3.2.1. In the traditional design environment electrical system components are not available. The characteristics of the electrical system components need consequently to be modelled and interfaced to the aircraft sizing environment. The electrical propulsion com- ponents characteristics are described at system level in Section 3.2.3. The mapping of the components and the integration within the design environment are discussed in Section 3.2.4.PDF Image | Conceptual Design Methods Hybrid-Electric Transport Aircraft
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