The aerospike nozzle represents an interesting technology for Single-Stage-To-Orbit vehicles because of its self-adapting capability. It is possible to get thrust vectoring capabilities in different ways. A straightforward solution consists in applying differential throttling to multiple combustion chambers which feed the nozzle. An alternative technology, which can be used in the presence of a common combustion chamber, is represented by fluidic thrust vectoring which requires the injection of a secondary flow from a slot on the wall. In this work, the flow field in a linear aerospike nozzle is numerically investigated by means of RANS simulations and both differential throttling and shock vectoring are studied. A parametric study is performed to evaluate the potential of the two technologies.

A Comparison Of Different Technologies For Thrust Vectoring In A Linear Aerospike / Ferlauto, M.; Ferrero, A.; Marsicovetere, M.; Marsilio, R.. - ELETTRONICO. - 700:(2021). ((Intervento presentato al convegno 14th World Congress in Computational Mechanics (WCCM) ECCOMAS Congress 2020 tenutosi a Virtual nel 11-–15 January 2021 [10.23967/wccm-eccomas.2020.006].

A Comparison Of Different Technologies For Thrust Vectoring In A Linear Aerospike

Ferlauto, M.;Ferrero, A.;Marsilio, R.
2021

Abstract

The aerospike nozzle represents an interesting technology for Single-Stage-To-Orbit vehicles because of its self-adapting capability. It is possible to get thrust vectoring capabilities in different ways. A straightforward solution consists in applying differential throttling to multiple combustion chambers which feed the nozzle. An alternative technology, which can be used in the presence of a common combustion chamber, is represented by fluidic thrust vectoring which requires the injection of a secondary flow from a slot on the wall. In this work, the flow field in a linear aerospike nozzle is numerically investigated by means of RANS simulations and both differential throttling and shock vectoring are studied. A parametric study is performed to evaluate the potential of the two technologies.
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11583/2924546