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- W3203406306 abstract "Nozzles are one of the most efficient ways of producing thrust. Most of the modern day launch vehicles use a conventional Converging-Diverging nozzle (CD nozzle). One of the critical drawbacks of using these nozzles is in their inability to provide the same efficiency under varying conditions of the course of the flight. CD nozzles when developed are designed to work at a certain range of altitudes, i.e. either at sea level or under near vacuum conditions. Hence, a sea level optimized nozzle can’t provide the same efficiency at higher altitudes and vice versa. Thus, modern day rockets have multiple stages (usually 2), with the first stage having a sea level optimized nozzle which lifts the rocket from the launch pad and takes it to an altitude before being ejected along with first stage and the second stage having vacuum optimized nozzle which propels the payload in vacuum of space to a desired orbit. This results in higher operating costs for a single launch, makes the process of payload deployment more complicated. The problem of having to use multiple nozzles can be solved by using an altitude compensating nozzle, with aerospike nozzle being one of them. These nozzles under operation provide the same efficiency throughout the course of flight under varying ambient conditions. This makes possible the development of a single stage to orbit vehicle, SSTO having a single aerospike nozzle. An SSTO vehicle unlike modern rockets doesn’t have components which require to be jettisoned during its flight and thus retains its expensive hardware even after being recovered. Hence, an SSTO vehicle results in less operating costs, having optimum payload capability. An SSTO having aerospike when developed properly is highly versatile it terms of thrust vectoring, and it has the potential of being completely reusable, by using a compact single structure similar to space shuttle and using aerodynamic re-entry. This paper analyses the performance of aerospike by comparison with CD nozzle using CFD (Computational Fluid Dynamics)." @default.
- W3203406306 created "2021-10-11" @default.
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- W3203406306 date "2021-01-01" @default.
- W3203406306 modified "2023-09-25" @default.
- W3203406306 title "Efficiency Analysis of Aerospike Nozzle by Comparison with a de-Lavel Nozzle Using Computational Fluid Dynamics" @default.
- W3203406306 cites W2122936421 @default.
- W3203406306 doi "https://doi.org/10.1007/978-981-16-0159-0_41" @default.
- W3203406306 hasPublicationYear "2021" @default.
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