Numerical Simulation of Fluidic Thrust-Vectoring

Ferlauto, Michele; Marsilio, Roberto

doi:10.1007/bf03404724

Cited by 18 publications

(12 citation statements)

References 25 publications

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“…shock waves and flow separations). [24][25][26] The DTN exhibited a typical behavior to step forcing in open-loop control. The system responses including overshoots, undershoots, and damped oscillations, were observed after a step input.…”

Section: Introductionmentioning

confidence: 99%

Experimental and numerical investigation of an axisymmetric divergent dual throat nozzle

Wang

Huang

et al. 2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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The dual throat nozzle achieves higher thrust vectoring efficiencies and lesser thrust loss than other fluidic thrust-vectoring nozzles. Separation always occurs at the bottom of the cavity with complex three-dimensional characteristics for the dual throat nozzle. In this paper, by comparing the flow structure, nozzle surface static pressure distributions and skin friction lines, which are obtained by numerical simulations and wind tunnel experiments, an axisymmetric divergent dual throat nozzle is investigated in detail. The main results show the following findings. (1) The experimental schlieren photographs confirm again that the divergent nozzle configuration has the starting problem from an intuitive perspective. Meanwhile, the flow structure and nozzle surface static pressure distributions obtained by numerical simulations are consistent with the experimental results, except for the low nozzle pressure ratios. (2) The circumferential pressure difference is negligible upstream of the separation line but obvious downstream of the separation line. The skin friction lines and nozzle surface static pressure distributions of different circumferential angles obtained by experiments both prove that the actual flow in the axisymmetric divergent dual throat nozzle indeed possesses three-dimensional characteristics. Therefore, it is necessary to utilize the full three-dimensional computational domain to study the complex three-dimensional characteristics of the flow for the axisymmetric divergent dual throat nozzle thoroughly.

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Section: Introductionmentioning

confidence: 99%

Experimental and numerical investigation of an axisymmetric divergent dual throat nozzle

Wang

Huang

et al. 2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Thrust vector control technologies commonly have two categories, namely, fluidic and mechanical vectoring controls [2]. Figures 1(a)-1(g) show seven representative fluidic control techniques employing a gas or liquid injection, involving coflow [3,4], counterflow [5][6][7][8], shock vector [9][10][11][12], bypass shock vector [13,14], throat shifting [15][16][17], dual throat nozzle [18,19], and bypass dual throat nozzle [20,21]. The above fluidic techniques have some outstanding advantages, for example, fast response, simple mechanical structure, and less thrust loss [10,11].…”

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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“…Subsequently, the DTN-TVC was developed as an in-depth study of the TS-TVC and emphatically investigated because of its higher thrust coefficient. Ferlauto and Marsilio 14 computationally investigated a typical DTN-TVC system and expounded that the thrust vector angle generated by per unit secondary stream is very less. Later, a new fluidic vector nozzle was developed by adding a bypass passage, namely, BDTN-TVC.…”

Section: Introductionmentioning

confidence: 99%

Numerical parametric study on three-dimensional rectangular counter-flow thrust vectoring control

Zhang

Kim

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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Recently, fluidic thrust vectoring control is popular for micro space launcher propulsion systems due to its several advantages, such as fast dynamic responsiveness, better control effectiveness, and no moving mechanical equipment. Counter-flow thrust vectoring control is an especially effective technique by utilizing less suction flow to control the mainstream deflection flexibly. In the current work, theoretical and numerical analyses are performed together to elaborate on the performance of the three-dimensional rectangular counter-flow thrust vectoring control system. A new propulsion nozzle of Mach 2.5 is devised by method of characteristics. To testify the feasibility and accuracy of the present research methodology, numerical results were validated against experimental data from the open literature. The computational result using the standard k-epsilon turbulence model reveals a good match with experimentally measured static pressure values along the centerline of the upper suction collar. The influence of several key parameters on vectoring performance is investigated herein, including the mainstream temperature, collar radius, horizontal collar length, and gap height. Critical parameters have been quantitatively analyzed, such as static pressure distribution along the centerline of the upper suction collar, pitching angle, suction mass flow ratio, and thrust coefficient. Furthermore, the flow-field features are qualitatively expounded based on the static pressure contour, streamline, iso-turbulent kinetic energy contour, and iso-Mach number contour. Some important conclusions are offered for further studies. The mainstream temperature mainly affects different dynamic characteristics of the mixing shear layer, including the convective Mach number of the shear layer, density ratio, and flow velocity ratio. The collar radius influences the pressure gradient near the suction collar surface significantly. The pitching angle increases rapidly with the increasing collar radius. As the horizontal collar length increases, the systematic deflection angle initially increases then decreases. The highest pitching angle is obtained for L/ H = 3.53. With regard to the gap height, a larger gap height can achieve a higher pitching angle.

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Numerical Simulation of Fluidic Thrust-Vectoring

Cited by 18 publications

References 25 publications

Experimental and numerical investigation of an axisymmetric divergent dual throat nozzle

Experimental and numerical investigation of an axisymmetric divergent dual throat nozzle

Numerical Study on Rod Thrust Vector Control for Physical Applications

Numerical parametric study on three-dimensional rectangular counter-flow thrust vectoring control

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