Aerospike nozzles represent an interesting solution for future launchers based on a Single Stage To Orbit (SSTO) configuration. This is due not only to their self-adaptation capability but also to the possibility of obtaining thrust vectoring with different strategies. It is indeed possible to deflect the thrust by using differential throttling when different combustion chambers are employed. In order to further increase the control capability, or in the case of a single combustion chamber, Fluidic Thrust Vectoring (FTV) can be adopted by injecting a secondary flow in the plug. In the present work the efficacy of this technology is investigated in several working conditions on linear aerospikes truncated at different lengths. The flow field is studied by means of RANS simulations with the Spalart-Allmaras turbulence closure. The effects of the secondary injection on the side and axial components of the force acting on the aerospike are evaluated for several levels of secondary mass flow rate.

Shock Vector Control Technique for Aerospike Nozzles / Ferlauto, Michele; Ferrero, Andrea; Marsilio, Roberto. - ELETTRONICO. - (2020). ((Intervento presentato al convegno AIAA SciTech Forum 2020 tenutosi a Orlando, FL nel 6-10 January 2020 [10.2514/6.2020-2246].

Shock Vector Control Technique for Aerospike Nozzles

Michele Ferlauto;Andrea Ferrero;Roberto Marsilio
2020

Abstract

Aerospike nozzles represent an interesting solution for future launchers based on a Single Stage To Orbit (SSTO) configuration. This is due not only to their self-adaptation capability but also to the possibility of obtaining thrust vectoring with different strategies. It is indeed possible to deflect the thrust by using differential throttling when different combustion chambers are employed. In order to further increase the control capability, or in the case of a single combustion chamber, Fluidic Thrust Vectoring (FTV) can be adopted by injecting a secondary flow in the plug. In the present work the efficacy of this technology is investigated in several working conditions on linear aerospikes truncated at different lengths. The flow field is studied by means of RANS simulations with the Spalart-Allmaras turbulence closure. The effects of the secondary injection on the side and axial components of the force acting on the aerospike are evaluated for several levels of secondary mass flow rate.
File in questo prodotto:
File Dimensione Formato  
aiaa-2020-2246.pdf

non disponibili

Descrizione: postprint
Tipologia: 2a Post-print versione editoriale / Version of Record
Licenza: Non Pubblico - Accesso privato/ristretto
Dimensione 1.52 MB
Formato Adobe PDF
1.52 MB Adobe PDF   Visualizza/Apri   Richiedi una copia
Pubblicazioni consigliate

I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.

Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11583/2780178