Numerical Simulation of a Hot Gas Injection Thrust Vector Control System Performance

Raj, L. Prince; Rejith, P.; Balu, Raman

doi:10.1016/j.proeng.2012.06.212

Cited by 6 publications

(3 citation statements)

References 5 publications

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“…The static pressure increased by more than three times than the undisturbed nozzle flow. Study shows that by injecting from two ports simultaneously control force along a given direction can be achieved by placing these ports appropriately [2]. M Deepu et.al examines the effect over the secondary fuel injection system for expanding as well as non-expanding supersonic flow and also analyses the effect of thrust augmentation on a rocket engine.…”

Section: Icdmme-2021mentioning

confidence: 99%

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

Sharma¹,

Manohar

Mishra³

2022

J. Phys.: Conf. Ser.

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The motive of this analysis is to compare the performance parameters of a single secondary fuel injector and performance of Dual Secondary fuel injector system for Thrust Vector Control (SITVC) in a supersonic nozzle for different distances between the two ports. With the help of Computational Fluid Dynamics (CFD) the performance characteristics of SITVC has been analyzed. Experimental and numerical investigations have been done with various circumstances to examine the performance augmentations of the 2-D nozzle.

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Section: Icdmme-2021mentioning

confidence: 99%

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

Sharma¹,

Manohar

Mishra³

2022

J. Phys.: Conf. Ser.

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“…This research has produced a three-dimensional, viscous network with the organization and considered two Baldwin-Lomax and A-K algebraic turbulence models. The effects of the angle of the divergent part of the nozzle and the injection location on the system's efficiency have been investigated [27][28][29][30].…”

Section: Introductionmentioning

confidence: 99%

Aircraft Thrust Vector Control Using Variable Vanes; Numerical Simulation and Optimization

Salimi,

Askari,

Hassani

2023

Preprint

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Among the various thrust vector control methods, this study investigates the utilization of mechanical deviation of the nozzle by incorporating a flow deflector path in the flow emanating from the nozzle outlet which is applied in the aviation industry. The researchers conducted simulations to assess the deviation of the thrust vector using exit vanes within the nozzle. Two parameters, namely the thrust force ratio and the axial force ratio, were calculated to regulate the thrust vector. The results demonstrated that employing vanes successfully deviated the thrust vector, resulting in a reduction in force coefficients. Notably, vanes with lower angles proved more suitable for thrust vector deviation. To forecast the performance of the vanes based on their angle and nozzle pressure ratio (NPR), optimization and prediction were conducted. The prediction outcomes exhibited favorable agreement with the simulation results, confirming the accuracy of the prediction method. This research provides valuable insights into the thrust vector control mechanism employing mechanical deviation of the nozzle and underscores the significance of predicting vane performance for optimal thrust vector selection.

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“…Zmijanovic et al [26] investigated experimentally and numerically the effects of FTV within the framework of a small satellite launcher. Prince Raj et al [27] used a fluent code to solve the three-dimensional governing equations to analyze the flow field produced by secondary hot gas injection in a nozzle rocket motor. Rajendran et al [28] carried out numerical studies using the two-dimensional RNG k − ε turbulence model to compare between injecting sonic and supersonic jets for thrust vector control.…”

Section: Introductionmentioning

confidence: 99%

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

Noaman

Khalil

2019

International Journal of Aerospace Engineering

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A numerical study has been performed to characterize the nozzle flow field of secondary injection thrust vector control (SITVC) and to estimate the performance parameters of SITVC. After validating the CFD turbulence models with an experimental data, a numerical simulation has been conducted in order to investigate the influence of changing the injection location, the injection angle, and the primary nozzle divergence half angle on the SITVC nozzle flow field structure and on the SITVC performance parameters. The secondary mass flow rate was kept constant for all cases during the simulation. The results showed that downstream injection near the nozzle exit Mp=2.75 increases the high-pressure zone upstream the injection leading to an increase in the side force; also, the higher divergence half angle 15° slightly increases the side force and it provides a wide range of deflection without shock impingement on the opposite wall becoming more effective for SITVC. The injection angle in the upstream direction 135° increases the side force, and by decreasing the injection angle to downstream direction 45°, the side force decreases. However, the SITVC performance parameters and the flow field structure are more influenced by the injection location and the primary nozzle divergence half angle while being less influenced by the injection angle.

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Numerical Simulation of a Hot Gas Injection Thrust Vector Control System Performance

Cited by 6 publications

References 5 publications

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

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

Aircraft Thrust Vector Control Using Variable Vanes; Numerical Simulation and Optimization

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

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