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2 1 Introduction 1.1 The Need for Hybrid-Electric Technology Towards an All- Electric Economy The application of electrical technology to transport aircraft could revolutionize aircraft propulsion and power systems. The progress of electrical component technologies, the devel- opment perspective of key enabling technologies and the electrical system configuration for synergistic integration at aircraft level make the field of electrically driven propulsion and power system very promising in providing the technological rupture required for the fulfil- ment of the future goals. The feasibility of electric propulsion system application to transport aircraft will depend upon the improvement in energy and power capability of storage device, the development of components key performance characteristics such as gravimetric specific power and effi- ciency, the scalability potential of electrical components [5, 6] as well as the maturation of key technology such as high-temperature superconductive (HTS) technology [7, 8]. While striving for the development of universally-electric transport aircraft [7–10], offering a vision for zero-in-flight emissions, significant progress in electrical component technology needs to be achieved to reach the technological requirement enabling universally-electric commercial flight. In order to match the propulsion system requirement of transport aircraft and the de- velopment pace of the electrical technology, hybrid-electric approach to propulsion and power will pave the way towards universally-electric propulsion system. Referring to the emergence of an all-electric economy, Sehra and Shin [11] stated that “hybrid propulsion system will be required to meet the challenges of transition and timely introduction of fledgling new power systems”. The feasibility of applying hybrid-electric technology to the propulsion system of transport aircraft has to be examined and the potential advantages assessed at aircraft level. The be- nefits of hybrid-electric aircraft need to be evaluated for future market segments in terms of emission reduction potentials, vehicular efficiency change and operating economics. 1.2 Definition of the Research Objectives The integration of an electrical drive to the propulsion system of an aircraft disrupts the traditional sizing and performance methods. The design variables and objective functions for the sizing and optimization of the aircraft need to be redefined due notably to the electrical energy source participating to the propulsion of the aircraft. The tracking of the electrical energy requires the development of methods to map this additional energy source within the integrated performance calculation. The characteristics of the electrical components need to be considered for the sizing of the propulsion system. According to intrinsic physical beha- viours of the electrical components new constraints need to be taken into account within the sizing process. Aiming at evaluating the prospects of hybrid-electric aircraft in the conceptual design phase, new methods need to be developed to enable the design, sizing and perform- ance assessment of hybrid-electric transport aircraft. Pre-design methods for the sizing and performance of hybrid-electric aircraft found in the literature [12, 13] are based mainly onPDF Image | Conceptual Design Methods Hybrid-Electric Transport Aircraft
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