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

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.

Numerical and experimental assessment of a linear aerospike

“…One example is, for instance, differential throttling, a simple control strategy which can be applied in clustered aerospike engines with multiple independent combustion chambers. Since the mass flow rate and the pressure can be controlled independently, it is possible to generate an asymmetry in thrust, creating a lateral force component [7]. Another possible solution could be the Shock Vector Control approach, which consists in injecting a secondary flow from the plug wall.…”