Simulation of thrust control by fluidic injection and pintle in a solid rocket motor

Yan, Dongfeng; Wei, Zhijun; Xie, Kan; Wang, Ningfei

doi:10.1016/j.ast.2020.105711

Cited by 28 publications

(18 citation statements)

References 17 publications

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“…[8] But this kind of using the secondary jet method to achieve variable thrust is not stable. Dongfeng Yan [9] proposed a variable thrust plan combining secondary jet and pintle in his article. This plan is not only stable, but also the addition of secondary jet to a certain extent to protect the pintle from ablation.…”

Section: Figure 1 Fourth Generation Ejection Seatmentioning

confidence: 99%

“…The combination of the two schemes solves two problems at the same time. The Beijing University of Aeronautics and Astronautics' School of Astronautics team [9] conducted a dynamic response analysis of the dual pintle motor. They studied the electromagnetic subsystem, the pintle movement subsystem, the throttling subsystem, the combustion chamber pressure establishment subsystem, and the thrust subsystem.…”

Section: Figure 1 Fourth Generation Ejection Seatmentioning

confidence: 99%

“…Dongfeng Yan [9] of Beijing Institute of Technology and others, in order to solve the problems encountered by the secondary jet and the mechanical structure, they designed a scheme that combines the mechanical pintle structure and the secondary flow method.…”

Section: Pintle and Secondary Jetmentioning

confidence: 99%

See 2 more Smart Citations

Research on the Scheme of Variable Thrust Solid Rocket Motor

Yin

Zhou

et al. 2022

J. Phys.: Conf. Ser.

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The solid rocket motor is extremely widely used due to its many advantages, but the solid rocket motor also has the disadvantage that the thrust cannot be changed. To solve this problem, there are generally two solutions to this problem. One is to use a mechanical pintle structure to change the effective cross-sectional area of the nozzle, and then to change the size of the thrust. The other is to change the effective cross-sectional area through the secondary jet method. These two methods all can change the size of the thrust, but they also have their drawbacks. The domestic team proposed a plan that combines the two methods to make up for each other’s shortcomings.

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Section: Figure 1 Fourth Generation Ejection Seatmentioning

confidence: 99%

Section: Figure 1 Fourth Generation Ejection Seatmentioning

confidence: 99%

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Research on the Scheme of Variable Thrust Solid Rocket Motor

Yin

Zhou

et al. 2022

J. Phys.: Conf. Ser.

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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%

“…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]. However, some big storage tanks used to store and offer gas or liquid injectant and other assorted equipment increase the weight of the entire system remarkably.…”

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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The Effect of Fluidic Pintle Nozzle on the Ablative Features

Zheng

Xie

et al. 2023

Springer Proceedings in Physics

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Simulation of thrust control by fluidic injection and pintle in a solid rocket motor

Cited by 28 publications

References 17 publications

Research on the Scheme of Variable Thrust Solid Rocket Motor

Research on the Scheme of Variable Thrust Solid Rocket Motor

Numerical Study on Rod Thrust Vector Control for Physical Applications

The Effect of Fluidic Pintle Nozzle on the Ablative Features

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