Thrust Shock Vector Control of an Axisymmetric C-D Nozzle via Transverse Gas Injection

Abstract

The flowfield resulting from the transverse gas injection into the supersonic cross-flow is the problematic of many aerospace applications ranging from the scram-jet fuel injection to the reaction jets and fluidic thrust vectoring(FTV). The prominent case of FTV by the use of the secondary injection represents promisingly attractive and effective way of control for small aerospace vehicles. Main advantages of the FTV are light-weightiness, simplicity and potential efficiency of such system comparing to the conventional mechanical TVC and mechanical deflectors. [5] Elimination of heavy and robust actuators and their replacement with only the fast-opening valves leads to the very significant reduction in mass. Fast dynamic response (~500Hz) to the conventional (~30Hz) [8] , very small losses in specific impulse and thus thrust are promising efficiency benefits. The CNES ”Perseus” project which this study is part of and design concept have aim of incorporating fluidic TVC on the future ”micro” launcher. Some of the results from the ongoing investigation are presented in this article.