Numerical studies on augmented thrust vectoring system for pintle nozzle using secondary sonic jet

Harisrinivasan, U and Baskaran, RV and Sanal Kumar, VR (2018) Numerical studies on augmented thrust vectoring system for pintle nozzle using secondary sonic jet. In: 54th AIAA/SAE/ASEE Joint Propulsion Conference, 2018, 9 July - 11 July 2018, Cincinnati, Ohio.

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Abstract

In this paper numerical studies have been carried out to design a thrust vector control system for an augmented thrust propulsion and steering using a pintle nozzle facilitated with a secondary sonic jet bypassing through the pintle. Numerical studies have been carried out using a validated 2D density based, SST k-ω turbulence model. In the numerical study, a fully implicit finite volume scheme of the compressible, Navier–Stokes equations is employed. As a part of the code validation and calibration, the numerically predicted boundary-layer blockage at the Sanal flow choking condition for channel flow is verified using the closed-form analytical model of V.R. Sanal Kumar et al. [1] (AIP Advances, 8, 025315, 2018) and found excellent agreement with the exact solution. During the parametric analytical studies we observed that when the location of the sonic jet was near to the nozzle throat an undesirable normal shock wave generated. On the other hand when the location of the sonic jet was near to the nozzle exit the benefit of the augmented thrust vectoring was negated. Therefore, optimizing the geometry of the pintle and the selection of the axial location of the secondary sonic jet are important for getting an efficient and lucrative thrust vectoring. We conjectured through the parametric analytical studies that there is an optimum design for the secondary sonic jet pipe, jet location and angle of injection for getting a desirable and an efficient thrust vectoring in the given operating conditions of every pintle nozzle. We concluded that the geometry optimization of the secondary sonic jet pipe is inevitable for case by case for getting an augmented vectoring in all the operating conditions of the aerospace vehicles navigating with the pintle nozzle technology, which will enable us for finding solutions for flexible design options for a lucrative thrust vectoring throughout the flight regime with the pintle nozzle. This sequel paper is a pointer towards for the 3D geometry optimization of a pintle nozzle integrated with a secondary bypass jet for getting optimum performance of thrust vectoring for various industrial applications.

Item Type:	Conference Paper
Publication:	2018 Joint Propulsion Conference
Publisher:	American Institute of Aeronautics and Astronautics Inc, AIAA
Additional Information:	The copyright for this article belongs to the American Institute of Aeronautics and Astronautics Inc, AIAA.
Keywords:	Boundary layers; Flight control systems; Geometry; Location; Navier Stokes equations; Nozzles; Propulsion; Shock waves; Turbulence models, Finite volume schemes; Geometry optimization; K-Omega turbulence model; Normal shock waves; Operating condition; Optimum performance; Thrust vector control systems; Thrust vectoring systems, Nozzle design
Department/Centre:	Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited:	10 Aug 2022 11:13
Last Modified:	10 Aug 2022 11:13
URI:	https://eprints.iisc.ac.in/id/eprint/75754

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