https://openscholarship.wustl.edu/mems500/314/
*Authors: *Raymond J. Hogea *21 December 2025* *Abstract* This paper presents the conceptual design and performance analysis of a hydrogen-powered, high-altitude aircraft developed for long-endurance aerosol dispersion missions. Raymer’s methodology is used for initial sizing of the aircraft, followed by utilizing a hybrid weight estimation method comparing the Raymer, Torenbeek, NASA, and Roskam weight estimation methodologies to create a robust weight estimation. Analysis of aerodynamic, propulsion, weight, stability, and mission performance is conducted in RDSwin to demonstrate a sustained operation for a mission including a 65,000 ft altitude, 3.5-hour cruise segment for dispersing a 50,000 lb aerosol payload. Numerous iterations of the aircraft are performed to refine aircraft performance towards a more robust and efficient design. Simulation results showed that a conventional tube-wing aircraft using hydrogen propulsion is capable of efficient high-altitude flight with adequate thrust margin, structural feasibility, and subsystem compatibility per the mission requirements. Overall, the study verifies the hydrogen tube-wing concept as a viable platform for long-duration, high-altitude missions requiring substantial payload capacity and endurance. *Source: WashU* -- You received this message because you are subscribed to the Google Groups "geoengineering" group. To unsubscribe from this group and stop receiving emails from it, send an email to [email protected]. To view this discussion visit https://groups.google.com/d/msgid/geoengineering/CAHJsh9_teLbTkpwTZGOxeS96v1bLk0YwgzWYQqZu_7X2H7c%2B5g%40mail.gmail.com.
