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- W2321803294 abstract "To design a launcher system competitive to current launcher technology high combustion chamber pressure is required. In this paper two types of turbo-pumps technologies have been considered in relation to hybrid propulsion systems: (i) spill of hot gas from the combustion chamber, (ii) regenerative cycle. To evaluate effectiveness of each technology in relation with the selected mission profile a global hybrid thruster model has been applied. The model performs both internal ballistic calculation and provides a preliminary size of the thruster structure in term of masses and dimension. Effectiveness of pressurization technology has been evaluated for the following mission profiles: Ariane booster, first and second stage, VEGA first and second stage, Soyuz first second and third stage. For each configuration a comparison among hybrid and state of the art propulsion technology has also been done based on propulsion system mass, size, safety issues and reliability." @default.
- W2321803294 created "2016-06-24" @default.
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- W2321803294 date "2008-07-21" @default.
- W2321803294 modified "2023-09-25" @default.
- W2321803294 title "Turbo-Pump Pressurization Concept for Hybrid Propulsion Thrusters Application to Launch Vehicles" @default.
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- W2321803294 doi "https://doi.org/10.2514/6.2008-4934" @default.
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