The study focuses on launcher air intakes for aerobic/rocket-propelled spacecraft. A series of studies enabled the authors to define a non-definitive reference geometry for the air intake that can be used as a working basis for subsequent systems and propulsion studies. Research included a study to quantify the aerodynamic coefficients of the air intake. The additive drag and lift of several engines were arrived at and the performance of the launcher estimated. The structural problems of the air intake (sizing and materials) were defined by estimating the pressure and temperature levels along it. The authors were able to presize the mass with these calculations.
Entree d'Air pour un Lanceur Hypersonique (Air Intake for a Hypersonic Launcher)
1988
19 pages
Report
No indication
English
Entrée d’air pour nacelle d’une turbomachine d’aéronef et procédé de montage d’une entrée d’air
European Patent Office | 2023
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