Thrust vector control of supersonic nozzle flow using a moving plate

Kong, Fanshi; Jin, Yingzi; Kim, Heuy Dong

doi:10.1007/s12206-016-0224-4

Cited by 15 publications

(10 citation statements)

References 6 publications

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“…As a consequence, these techniques are less attractive for various long-distance or long-time flights. Traditional mechanical vectoring control technologies have jet vane, 22 movable nozzle, 23 axial movable plate, 24 and jet tab. 25 They can offer a dependable control effect.…”

Section: Introductionmentioning

confidence: 99%

Study on aerodynamic features of rod thrust vector control for physical applications

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Mechanical thrust vector control is a classical and important branch in the vectoring control field, offering an extremely reliable control effect. In this article, a simple technology using a cylindrical rod has been numerically investigated to achieve jet controls for three-dimensional conical axisymmetric nozzles. Complex flow phenomena caused by the cylindrical rod on a flat plate and in a converging–diverging nozzle are elucidated with the purpose of a profound understanding of this technique for physical applications. Published experimental data are used to validate the dependability of current CFD results. A grid sensitivity study is carried through and analyzed. The result section discusses the impacts of three factors on performance, involving the rod penetration height, rod location, and nozzle pressure ratio. Significant vectoring performance variations and flow topologies descriptions are illuminated in full detail. When the rod penetration height changes, this technique has an effective control range, namely H/Rt ≤ 0.4. In this effective control range, the vectoring angle and efficiency increase and the thrust coefficient decreases with a deeper rod insertion. As the rod location moves downstream towards the nozzle exit, the vectoring angle increases and the thrust coefficient decays. Moreover, the direction of jet deflection remarkably varies for diverse rod locations. While the nozzle pressure ratio increases, the vectoring angle initially increases to reach the maximum level and then decays slightly. Meanwhile, the thrust coefficient continuously increases.

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Section: Introductionmentioning

confidence: 99%

Study on aerodynamic features of rod thrust vector control for physical applications

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…In thrust vectoring methods, the control forces are obtained using a mechanical thrust vector control (MTVC) system or fluidic thrust vector control (FTVC) (Zmijanovic et al , 2014). The MTVC uses obstacles such as vanes (Kostić et al , 2017; Murty et al , 2010), tabs and plates (Kong et al , 2016) to create a shock wave and cause the jet to deflect in the desired direction. The FTVC system uses a secondary fluid that can be injected in the diverging portion of the nozzle for the shock vector control method (Forghany et al , 2019; Wu and Dong Kim, 2019), in the throat region for the throat-shifting method, in the direction of flow for the coflow (Sung and Heo, 2012) or in the direction opposite to the flow direction for the counter-flow method (Wu et al , 2020).…”

Section: Introductionmentioning

confidence: 99%

Numerical study on strut insertion based thrust vectoring control system

Soundararajan

B.T.N.²

2022

AEAT

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Purpose This study aims to numerically study the three-dimensional (3D) flow field characteristics in a conical convergent divergent (CD) nozzle with an internal strut system to describe the effect of struts on producing a side force for thrust vectoring applications. Design/methodology/approach Struts are solid bodies. When inserted into the supersonic region of the axisymmetric CD nozzle, it induces a shock wave that causes an asymmetric pressure distribution predominantly over the internal surface of the diverging wall of the C-D nozzle, creating a net side force similar to the secondary injection thrust vectoring control method. Numerical simulations were performed by solving Unsteady Reynolds Averaged Navier–Stokes equations with re-normalized group k–ϵ turbulence model. Cylindrical struts of various heights positioned at different locations in the divergent section of the nozzle were investigated at a nozzle pressure of 6.61. Findings Thrust vectoring angle of approximately 3.8 degrees was obtained using a single cylindrical strut with a dimensionless thrust (%) and total pressure loss of less than 2.36% and 2.67, respectively. It was shown that the thrust deflection direction could also be changed by changing the strut insertion location. A strut located at half of the diverging length produced a higher deflection per unit total pressure loss. Practical implications Using a lightweight and high-temperature resistant material, such as a strut, strut insertion-based thrust vectoring control might provide an alternative thrust vectoring method in applications where a longer period of control is needed with a reduced overall system weight. Originality/value This study describes the 3D flow field characteristics which result in side force generation by a supersonic nozzle with an internal strut.

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“…As a consequence, these techniques are less attractive for various long-distance or long-time flights. Figures 1(h)-1(k) exhibit five traditional mechanical vectoring control technologies, including jet vane [22], movable nozzle [23], axial movable plate [24], and jet table [25]. The benefits of these mechanical vectoring control methods are offering an extremely dependable control effect.…”

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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Thrust vector control of supersonic nozzle flow using a moving plate

Cited by 15 publications

References 6 publications

Study on aerodynamic features of rod thrust vector control for physical applications

Study on aerodynamic features of rod thrust vector control for physical applications

Numerical study on strut insertion based thrust vectoring control system

Numerical Study on Rod Thrust Vector Control for Physical Applications

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