摘要: The aerospace community is invested in research into hybrid-electric aircraft to meet its challenging emission reduction targets. These hybrid-electric aircraft provide several design challenges, such as lower battery energy densi... 展开 The aerospace community is invested in research into hybrid-electric aircraft to meet its challenging emission reduction targets. These hybrid-electric aircraft provide several design challenges, such as lower battery energy density than typical aviation fuel, both from a mass and volume point of view. In addition, aircraft fuel can easily fill out complex shapes of the wing and fuselage tanks. To allocate sufficient space for batteries, the conceptual designer must consider the battery cell types, arrangements, thermal management system and other physical constraints. This paper proposes a method to estimate the battery pack size and dimensions suitable for conceptual design. The battery layout is defined based on individual cells grouped to form many modules that form the overall pack. The battery pack sizing method accounts for the volumetric and gravimetric contributions of energy-producing components (cells) and non-energy-producing components (such as cooling to meet aircraft certification requirements). The method is validated for lithium-ion battery packs; pack size and mass predictions are compared with the manufacturer data for electric aircraft and electric ground vehicles. The achieved accuracy is satisfactory; the approach achieves conceptual design needs, enabling battery volume and layout considerations in addition to weight. This new capability is demonstrated in a hybrid-electric retrofit case study on the Dornier DO-228 aircraft, in which the lithium-ion batteries replace sections of the wing fuel tanks. Overall, the proposed method is the first step to closing a gap in conceptual design tools for electric and hybrid-electric aircraft. 收起