CONCEPTUAL AIRCRAFT SIZING USING SYSTEMS ENGINEERING FOR N+3 SUBSONIC HYBRID-ELECTRIC PROPULSION CONCEPTS

The demand for air travel is expected to rise in the future, leading to a significant increase in global air traffic. This growth raises concerns about environmental and public health, prompting the implementation of stricter aviation regulations. Emission standards have been introduced to reduce the aviation sector's impact on climate change, aligning with the objectives of the UN's Paris Climate Agreement. In response, the aviation industry is exploring more sustainable and efficient technologies to enhance both energy and cost performance. NASA has developed the 'N+i' goals to reduce fuel consumption, noise, and nitrogen oxide (NOx) emissions during landing and takeoff (LTO), while improving aircraft performance. The 'N+3' goal envisions technology three generations ahead, with 'N' representing the current generation of aircraft, and a technology readiness level expected to reach 4-6 by 2025, for service entry around 2035. To achieve these N+3 objectives, substantial advancements are needed in air transportation systems, airframe design, mission planning, and propulsion systems. Propulsion systems play a crucial role in reducing emissions, noise, and fuel consumption. This study evaluates the N+3 concepts using systems engineering methods and selects the most promising one. A detailed analysis of phase one of this project is conducted using Georgia Institute of Technology's Integrated Product-Process Development (IPPD) approach. The findings suggest that NASA's N3-X turbo-electric distributed propulsion (TeDP) concept is the most effective solution for meeting the N+3 goals based on the systems engineering evaluation.