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Abstract
Abstract Hypersonic transport fueled with liquid hydrogen (LH2-HST) is currently considered as long-term future technology of civil aviation to fly with speeds greater than Mach 5 at stratospheric altitudes of 25–38 km. In this paper, we present a comprehensive methodology to assess the emission mitigation potential (via NOx and H2O) of future LH2-HST through operational measures, considering realistic constraints such as the sonic boom carpet as well as tolerable g-forces acting on the passengers while flying with hypersonic speeds. Both NOx- and H2O-optimal 4D-trajectories are identified by a brute-force algorithm that varies the initial cruise altitude from 30 to 36 km. As case study, the Mach 8 passenger aircraft STRATOFLY-MR3, which was conceptually developed in the framework of the H2020 STRATOFLY project, is operated on a single route from Brussels (BRU) to Sydney (MYA). The findings are highlighted as relative changes regarding MR3's design flight altitude set at 32 km, respectively, 105 000 ft. As scientific contribution, 3D emission inventories are calculated and made publicly available for a world fleet of MR3 aircraft operated along the BRU-MYA route on both NOx- and H2O-optimal mission profiles in the year 2075.
Highlights
The era of hypersonic flight began on June 23, 1963, when Robert White was the first person to reach a hypersonic flight speed of Mach 5.24 as part of the North American X-15 flight program [1]
Within the Hypersonic Trajectory Calculation Module (HTCM), particular emphasis was placed on a detailed modelling of the intricate mechanics of hypersonic flight on the one hand, which causes distinct phenomena that are not present in conventional aircraft such as fictitious forces due to the curvature of Earth (Term✭; Eq 4), and a sufficient numerical calculation accuracy on the other hand that enables a realistic implication of the quantity and distribution of high-altitude emissions for a single mission, which can subsequently be scaled to a global fleet level
This paper describes a comprehensive methodology to quantify the mitigation potential of N Ox and H 2O emissions for a Mach 8 passenger aircraft fuelled with liquid hydrogen
Summary
The era of hypersonic flight began on June 23, 1963, when Robert White was the first person to reach a hypersonic flight speed of Mach 5.24 as part of the North American X-15 flight program [1]. HST could revolutionize long-haul air travel primary through a major reduction in flight times, especially for antipodal routes, and secondary by “decarbonizing” air transport within Europe. This would be achieved through the adoption of new advanced high-speed propulsion systems such as combined-cycle turbojet/scramjet engines powered by postfossil, renewable fuels like green hydrogen, whose overall CO2-balance is considered neutral in the biogenic carbon cycle, but whose production is very energy-intensive and not yet deployed due to a lack of infrastructure.
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