Differential Throttling and Fluidic Thrust Vectoring in a Linear Aerospike

Aerospike nozzles represent an interesting solution for Single-Stage-To-Orbit or clustered launchers owing to their self-adapting capability, which can lead better performance compared classical nozzles. Furthermore, they provide thrust vectoring in several ways. A simple consists of applying differential throttling when multiple combustion chambers are used. An alternative is represented by fluidic vectoring, requires the injection a secondary flow from slot. In this work, field linear aerospike nozzle was investigated numerically and both were studied. The predicted solving Reynolds-averaged Navier–Stokes equations. evaluated terms side force generation axial reduction. effectiveness changing mass rate location. results show that response system be non-monotone with respect injection. contrast, provides behaviour but it only applied configurations chambers. Finally, effects different plug truncation levels discussed.