The work reported herein is a preliminary numerical study of a resonant igniter for rocket engines. Resonant igniters are very attractive and promising for in-space thrusters, since they are simple, highly reliable and lightweight. Fine-tuning of various parameters is required to initiate and maintain the resonance conditions required for heat generation. A numerical study based on a finite element discretisation of the compressible Navier-Stokes equations is performed in order to analyze the main physical phenomena which govern the behaviour of the igniter.

Preliminary study of a resonant igniter for Rocket Engines / Conte, Antonietta; Ferrero, Andrea; Pastrone, Dario Giuseppe. - ELETTRONICO. - (2020). ((Intervento presentato al convegno 17th International Conference of Numerical Analysis and Applied Mathematics ICNAAM 2019 tenutosi a Rhodes, Greece nel 23-28 September 2019 [10.1063/5.0026699].

Preliminary study of a resonant igniter for Rocket Engines

Antonietta Conte;Andrea Ferrero;Dario Pastrone
2020

Abstract

The work reported herein is a preliminary numerical study of a resonant igniter for rocket engines. Resonant igniters are very attractive and promising for in-space thrusters, since they are simple, highly reliable and lightweight. Fine-tuning of various parameters is required to initiate and maintain the resonance conditions required for heat generation. A numerical study based on a finite element discretisation of the compressible Navier-Stokes equations is performed in order to analyze the main physical phenomena which govern the behaviour of the igniter.
978-073544025-8
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Utilizza questo identificativo per citare o creare un link a questo documento: http://hdl.handle.net/11583/2782256