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• W2913725648 abstract "The structural and thermal loads during first stagereentry may impact significantly the structural andthermal design and thus influence the payload perfor-mance and launch service cost of expendable launchvehicles. Many studies have focused on the effectof counterflowing jets emanating from blunt capsuleson drag and aerothermal fluxes. However, for slenderrocket shape bodies the database is still sparse. Forthis purpose CFD studies of the flow fields around areusable first stage during reentry at freestream Machnumbers between 9.45 and 5.09 were carried out inclose conjunction with the system analysis and trajec-tory design of potential future European carrier sys-tems. The results of this study show that the inte-gral heat uptake with hot retro-propulsion is gener-ally higher than heat uptake at a ballistic state. How-ever, the supersonic retro-propulsion maneuver redis-tributes the high heat loads from the baseplate areato the entire vehicle surface, therefore reducing localthermal loads." @default.
• W2913725648 created "2019-02-21" @default.
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• W2913725648 date "2018-05-15" @default.
• W2913725648 modified "2023-09-22" @default.
• W2913725648 title "Aerothermal Analysis of Reusable Launcher Systems during Retro-Propulsion Reentry and Landing" @default.
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• W2913725648 hasPublicationYear "2018" @default.
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