Shock Vector Control Technique for Aerospike Nozzles

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.