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3.2 Methods for Sizing and Performance of Hybrid-Electric Aircraft 23 Besides weight and volume of the systems, the design and off-design thrust characteristics within the operational envelop are of importance for integrated performance analysis. The modelling of the thrust capabilities of hybrid-electric propulsion systems is described in Sec- tion 3.2.4.1. Another challenge to consider for the integration of hybrid-electric propulsion systems in traditional performance programs is the mapping of the electric energy within the integrated mission performance computation. As indicated previously, the traditional methods present a limitation as the fuel flow table can only take into account fuel flow characteristics. The method proposed to extend the implementation of the propulsion system properties in order to interface the electric energy is discussed in Section 3.2.4.3. In addition, the presence of multiple energy and power systems which contribute each to the propulsion of the aircraft requires the establishment of power management strategies. Power sharing strategies enable managing the energy pathways between different sources of the hybrid-electric propulsion system. As only one common fuel flow table is implemented to represent the characteristics of the propulsion system for the complete mission, the establishment of power management strategies according to the different operational settings of the hybrid-electric propulsion sys- tem cannot be considered within the traditional approach. The extension of the method to determine the energy characteristics of hybrid-electric propulsion system are discussed in Section 3.2.4.3. The interfacing of the hybrid-electric propulsion characteristics in terms of thrust and energy requirement with the flight performance module is described in Section 3.2.5. The sizing characteristics of electric components are elaborated in Section 3.2.6 and the over- all sizing process of hybrid-electric aircraft is described in Section 3.2.7. According to the physical behaviour of the components constituting the hybrid-electric propulsion architecture, the new constraints emanating from the specificities of hybrid-electric propulsion system are highlighted in the sizing process. Finally, metrics for vehicular efficiency assessment have to be introduced as the consumption of electric energy needs to be taken into account in the total energy evaluation of the aircraft. New figures-of-merit for the evaluation of vehicular efficiency and for the establishment of optimum flight techniques of hybrid-electric aircraft are derived in Chapter 4. Beyond the state-of-the-art in traditional conceptual design methods, several pre-design meth- ods for the sizing of hybrid-energy aircraft have been published to this date. A review of the published literature which contributed to the development of pre-sizing methods for hybrid-electric aircraft can be found in Perullo and Mavris [12]. These methods rely mainly on first-order equations for the modelling of the aircraft and the propulsion system. The method is based on linear scaling laws assuming constant gravimetric and constant efficiency values irrespective of scale and operational conditions. As the result these methods cannot account for detailed secondary effects such as the interactions between the operations of the electrical system and the conventional propulsion system; for instance, the efficiency change of the gas-turbine forced to operate into part power due to the concurrent utilization of an electric motor in a parallel topology. The aim of this chapter is the development of conceptual design methods which resolve the identified shortcomings of the contemporary methods and which offer higher fidelity modelling than pre-design methods through the use of efficiencyPDF Image | Conceptual Design Methods Hybrid-Electric Transport Aircraft
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