Journal Article

A Multidisciplinary Optimization Framework for Ecodesign of Reusable Microsatellite Launchers

Afonso, Frederico, Figueiras, Iara, Azeitona, Lara, Souza, Alain, Barata, Simão, Lau, Fernando, Musso, Girolamo, Costa, Ana Laura, Goubel, Héléna, Gonçalves, Afonso, Ferreira, Bruna, Ribeiro, Inês

2024

Overview

The commercial space launch sector is currently undergoing a significant shift, with increasing competition and demand for launch services, as well as growing concerns about the environmental impact of rocket launches. To address these challenges, within the New Space Portugal project scope, a multidisciplinary framework for designing and optimizing new launch vehicles is proposed. Creating a more resilient and responsible space industry can be achieved by combining technological innovation and environmental sustainability, as emphasized by the framework. The main scope of the framework was to couple all the disciplines relevant to the space vehicle design in a modular way. Significant emphasis was placed on the infusion of ecodesign principles, including Life Cycle Assessment (LCA) considerations. Optimization techniques were employed to enhance the design and help designers conduct trade-off studies. In general, this multidisciplinary framework aims to provide a comprehensive approach to designing next-generation launch vehicles that meet the demands of a rapidly changing market while also minimizing their environmental impact. A methodology that leverages the strengths of both genetic and gradient-based algorithms is employed for optimizations with the objectives of maximizing the apogee altitude and minimizing the Global Warming Potential (GWP). Despite only being tested at the moment for sounding rockets, the framework has demonstrated promising results. It has illuminated the potential of this approach, leading to the identification of three optimal designs: one for maximizing the apogee, another for minimizing GWP, and a compromise design that strikes a balance between the two objectives. The outcomes yielded a maximum apogee of 6.41 km, a minimum GWP of 9.06 kg CO2eq, and a balanced compromise design featuring an apogee of 5.75 km and a GWP of 25.64 kg CO2eq.

• Publisher: MDPI AG
• Subject: Aircraft / Algorithms / Apogees / Climate change / Collaboration / Design improvements / ecodesign / Emissions / Employee motivation / Environmental impact / Environmental policy / Global warming / Launch vehicles / Life cycle analysis / Life Cycle Assessment / Literature reviews / Maximization / microsatellite launchers / Microsatellites / Modular design / Multidisciplinary Design Optimization / New Space Portugal / Optimization / Rocket launching / Satellites / Sounding rockets / Space vehicles / sustainability / Sustainable design / Technological change / Vehicles