3D Numerical Studies on Thrust Vectoring using Shock Induced Self Impinging Secondary Jets

Abstract

Numerical studies have been carried out using a validated two-dimensional standard k-omega turbulence model for the design optimization of a thrust vector control system using shock induced self-impinging supersonic secondary double jet. Parametric analytical studies have been carried out at different secondary injection locations to identifying the highest unsymmetrical distribution of the main gas flow due to shock waves, which produces a desirable side force more lucratively for vectoring. The results from the parametric studies of the case on hand reveal that the shock induced self-impinging supersonic secondary double jet is more efficient in certain locations at the divergent region of a CD nozzle than a case with supersonic single jet with same mass flow rate. We observed that the best axial location of the self-impinging supersonic secondary double jet nozzle with a given jet interaction angle, built-in to a CD nozzle having area ratio 1.797, is 0.991 times the primary nozzle throat diameter from the throat location. We also observed that the flexible steering is possible after invoking ON/OFF facility to the secondary nozzles for meeting the onboard mission requirements. Through our case studies we concluded that the supersonic selfimpinging secondary double jet at predesigned jet interaction angle and location can provide more flexible steering options facilitating with 8.81% higher thrust vectoring efficiency than the conventional supersonic single secondary jet without compromising the payload capability of any supersonic aerospace vehicle.

Numerical Simulation on the Influence of Injection Location, Injection Angle, and Divergence Half Angle on SITVC Nozzle Flow Field

“…Sriram and Mathew [24] used the fluent code to simulate the flow field of the nozzle utilized by Masuya et al [16] and Ko and Yoon [23] with different solution parameters. Vishnu et al [25] used the realizable k − ε turbulence model with enhanced wall treatment for the design optimization of SVC. Zmijanovic et al [26] investigated experimentally and numerically the effects of FTV within the framework of a small satellite launcher.…”

Analysis and optimization of Dual secondary fuel injector for Thrust vector control

“…In this two ports are used for injection of fluid for thrust vectoring control system. For the analysis, one port is left fixed and the other port is varied with specified distances [7][8][9]. Dual secondary fuel injection thrust vectoring control system gives better results as compared to usual one under certain circumstances, having same inlet conditions as usual SITVC it provides the better amount of thrust and stable control of the flow of fluid.…”