Experimental Study of the Wall Pressure Distribution in a Convergent-Divergent Nozzle with Strut Injection

Srinivas, A. Lakshmi; Sridhar, B. T. N.

doi:10.1134/s0015462820010139

Cited by 9 publications

(8 citation statements)

References 7 publications

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“…There are known modeling methods and characteristics of the disturbed gas flow by a solid obstacle on the wall; the principles of designing such systems for controlling the lateral force arising from the disturbance of the flow; measures to protect the obstacle from the effect of a high-temperature gas flow in the rocket engine nozzle and on external surfaces in a supersonic flow. 3,17,19,20 However, the problems of choosing the obstacle location along the nozzle length for obtaining the maximum efficiency of the rocket engine thrust vector control have not yet been investigated. It should be noted that the perturbation of the flow in the subcritical part of the nozzle can be the basis for solving various problems with the installation of an obstacle in the subsonic part of the nozzle.…”

Section: Aim and Tasksmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Efficiency of rocket engine thrust vector control by solid obstacle on the nozzle wall

Strelnikov

Ihnatiev

Pryadko

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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The thrust vector control of a rocket engine by disturbing the supersonic flow in its nozzle is used for missile development for various purposes in different countries. Disturbance of the supersonic flow in the jet engine nozzle can be caused by various obstacles on the nozzle wall: solid obstacle, liquid or gas jet, combinations of solid obstacle with injected jets. The simplest and most effective way to create a disturbance is to disturb it by setting a solid cylindrical obstacle on the nozzle wall. The high efficiency is explained by the lack of the working fluid consumption on board the aircraft to create a control force, or its minimum amount necessary to protect the obstacle from the high-temperature oncoming gas flow in the rocket engine nozzle. This paper presents the study results of gas flow simulation with cylindrical obstacle perturbation on the wall of the Laval rocket engine nozzle in its subsonic and supersonic parts. The optimal placement in the nozzle is determined to obtain the maximum lateral control force. As a result of research, it was found that the perturbation of a supersonic flow in a rocket engine nozzle by a cylindrical obstacle has practically the same character when its position changes along the length of the nozzle. In the subsonic part of the nozzle in the median plane, the perturbed pressure on the wall has a positive sign, and on the obstacle wall its sign-alternating. When an obstacle is in the subsonic part of the nozzle, the integral value of the lateral force is negative in comparison with positive for the supersonic part.

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Section: Aim and Tasksmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Efficiency of rocket engine thrust vector control by solid obstacle on the nozzle wall

Strelnikov

Ihnatiev

Pryadko

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Experimental data of the shock pattern configurations near the inserted rod are accumulated in [3], [6] and [7]. The data is compared with CFD modeling results in this articles.…”

Section: Introductionmentioning

confidence: 99%

Computational study of gas flow characteristics when using intra-nozzle interceptors for thrust vector control

Brykov

Tischenko

2022

J. Phys.: Conf. Ser.

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This article proposes the use of cylindrical nozzle interceptors (probes) as an alternative method of rocket engine thrust vector control, which can replace traditional thrust vector control systems. The objective of this paper was to perform a three-dimensional CFD simulation of the gas flow in a rocket engine nozzle with a rod interceptor taken out of the wall without secondary injection, analyzing the calculated flow data and estimating the lateral force. The simulations will be performed in steady-state mode. In the CFD simulations, velocity distribution contours were obtained on the symmetry plane for all positions and values of the interceptor height.

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“…Subsequently, Babaeyan and Hojaji [31] experimentally investigated a new dual-rod penetration technique in the opposite direction to control the flow deflection and illustrated that dual-rod penetration can obtain a maximum vectoring angle of 4.35 degrees, whereas the axial thrust declines up to 5.5% owing to the occurrence of various opposite shocks. Srinivas and Sridhar [32] experimentally explored the feasibility of a single rectangular strut on the vectoring performance of the axisymmetric nozzle and elucidated that it can achieve an effective control by changing the strut penetration height.…”

Section: Introductionmentioning

confidence: 99%

Numerical Study on Rod Thrust Vector Control for Physical Applications

2021

International Journal of Aerospace Engineering

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Mechanical thrust vector control is a classical and significant branch in the thrust vector control field, offering an extremely reliable control effect. In this article, steady-state and unsteady-state aerodynamic characteristics of the rod thrust vector control technology are numerically investigated in a two-dimensional supersonic nozzle. Complex flow phenomena caused by the penetrating rod in the diverging part of the supersonic nozzle are elucidated with the purpose of a profound understanding of this simple flow control technique for physical applications. Published experimental data are used to validate the dependability of current computational fluid dynamics results. A grid sensitivity study is carried through and analyzed. The result section discusses the impacts of two important factors on steady-state aerodynamic features, involving the rod penetration height and the rod location. Furthermore, unsteady-state flow features are analyzed under various rod penetration heights for the first time. Significant vectoring performance variations and flow topology descriptions are illuminated in full detail. While the rod penetration height increases, the vectoring angle increases, whereas the thrust coefficient decreases. As the rod location moves downstream close to the nozzle exit, the vectoring angle and thrust coefficient increase. In terms of unsteady-state aerodynamic effects, certain pressure oscillations occur upstream of the rod, which resulted from the expanding and shrinking of the upstream anticlockwise separation bubbles.

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Experimental Study of the Wall Pressure Distribution in a Convergent-Divergent Nozzle with Strut Injection

Cited by 9 publications

References 7 publications

Efficiency of rocket engine thrust vector control by solid obstacle on the nozzle wall

Efficiency of rocket engine thrust vector control by solid obstacle on the nozzle wall

Computational study of gas flow characteristics when using intra-nozzle interceptors for thrust vector control

Numerical Study on Rod Thrust Vector Control for Physical Applications

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