Thrust Vector Control using movable probes

Cavalleri, Robert; Tiarn, Weihnurng; Readey, Harvey

doi:10.2514/6.1990-562

Cited by 9 publications

(7 citation statements)

References 2 publications

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“…The weight of the entire system is much lighter than that of other techniques. 26 Some empirical correlations had to be employed to determine the pressure distribution and the shock shape caused by the protuberant probe. A CFD evaluation of this advanced method was carried through by Tiarn and Cavalleri 27 under the assumption of infinite probe penetration height.…”

Section: Introductionmentioning

confidence: 99%

“…What needs to be emphasized is that the experiment is carried out in a uniform freestream instead of an accelerating supersonic flow like a converging–diverging nozzle flow. Cavalleri 29 attempted to mount the probe within the 40%–60% length of the divergent part of a supersonic nozzle and testified excellent pitching and yawing control effectiveness using four probes with an interval of 90°. Mokhtari et al 30 experimentally studied the impact of a single cylindrical rod penetration height on the conical nozzle performance and found that it affects the vectoring angle remarkably.…”

Section: Introductionmentioning

confidence: 99%

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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%

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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“…Nevertheless, overweight components and overcomplicated structures limit further development in future applications. To overcome the above techniques' limitations, a new idea using a simple rod is explored to control the vectoring angle, as shown in Figure 1(l) [26].…”

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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“…As shown in Fig. 2, the jet vane, movable nozzle, axial movable plate, vertical movable rod, revolving jet tab techniques are belonging to the branch of mechanical vectoring controls [3][4][5][6][7]. A large number of mechanical pieces of equipment cause overweight, wear, and overcomplicated structure problems [8].…”

Section: Introductionmentioning

confidence: 99%

A fluidic thrust vector control using the bypass flow in a dual throat nozzle

Kim

2021

J Mech Sci Technol

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The present study is to explore an active mass flow control technology for an emerging bypass dual throat nozzle. A new arc-shaped bypass system has been applied to replace the previous V-shaped bypass for the bypass dual throat nozzle, which can decrease the total pressure loss significantly. The bypass passage has a contraction part with a variable area ratio. The vector control effectiveness is discussed with different contraction area ratios of the bypass passage. The obtained results reveal that friction choking and geometry choking play crucial roles to affect the bypass mass flow, respectively. When the bypass passage is fully open, the choking location of the bypass flow occurs at the bypass exit, owing to the viscous boundary layer along the constant area passage. A contraction area ratio less than 0.5 does not change the choking position of the bypass flow, because the viscous boundary layer is larger than the geometry contraction height. While the contraction area ratio reaches or exceeds 0.5, the geometry choking takes place in the contraction section. The vectoring angle and bypass mass flow ratio decrease with an increase in the contraction area ratio, whereas thrust coefficient, thrust efficiency, and total pressure loss increase.

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Thrust Vector Control using movable probes

Cited by 9 publications

References 2 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 Rod Thrust Vector Control for Physical Applications

A fluidic thrust vector control using the bypass flow in a dual throat nozzle

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