Numerical investigation of freestream flow effects on thrust vector control performance

Forghany, F.; Taeibe-Rahni, Mohammad; Asadollahi-Ghohieh, Abdollah

doi:10.1016/j.asej.2017.12.004

Cited by 3 publications

(1 citation statement)

References 14 publications

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“…Zhang et al examined the application of shock vector control in a pulse detonation tube [22]. Furthermore, 3D detailed simulations and sensitivity analyses have rapidly progressed in this area [23][24][25].…”

Section: Introductionmentioning

confidence: 99%

Study on the Effect of Oxidative Jet and Vortex Structure in Fluidic Throat Combined with Thrust Vector Control

Yan

Xiao

et al. 2023

International Journal of Aerospace Engineering

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To examine the impact of oxidative jets on the thrust vector angle, secondary combustion efficiency, and combustion chamber pressure, inert gas (nitrogen) and pure oxygen are injected into the primary flow, which includes combustible components, at various locations in the divergence section and throat using different injection techniques. The simulations utilize Reynolds-averaged Navier-Stokes equations coupled with the SST k - ω turbulence model in two-dimensional numerical simulations and large-eddy simulation in three-dimensional studies. The numerical method is validated through schlieren experiments, and the vortex is identified using the Liutex-Omega method. The vortex structures and flow characteristics are analyzed. The results indicate that, at the same flow rate, the vector control effect of pure oxygen is superior to nitrogen only in the divergence section, but inferior to nitrogen in both the divergence section and throat. However, with improved vector control, the peak of the vector angle is achieved at a lower flow rate in the case of pure oxygen. When the secondary flow is introduced only in the divergence section, the flow ratio corresponding to the peak point in the pure oxygen case is approximately 14.3% earlier than that in the nitrogen case. The introduction of the pure oxygen jet enhances the secondary combustion efficiency of the primary flow, but to a limited extent. Additionally, when the jet is introduced at the throat, the effect of the pure oxygen case on adjusting the combustion chamber pressure is inferior to that of the nitrogen case. Concerning flow details, the trailing lower vortex replaces the trailing major vortex to become the highest magnitude vortex when the momentum flux ratio is small.

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Section: Introductionmentioning

confidence: 99%

Study on the Effect of Oxidative Jet and Vortex Structure in Fluidic Throat Combined with Thrust Vector Control

Yan

Xiao

et al. 2023

International Journal of Aerospace Engineering

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Simulation of a gas injection into the supersonic nozzle area in gas-dynamic thrust vector control

Ihnatiev,

Shevelova

2024

Teh. Meh.

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Solid-propellant rocket engines are simple in design, highly reliable, and able to store the propellant for a long time without its degradation. Their main feature is that the propellant is a mixture of a solid fuel and a solid oxidizer, thus ensuring a uniform combustion and a stable discharge of the combustion products. However, the combustion rate cannot be controlled, and the combustion cannot be stopped or restarted. This calls for efficient methods of thrust vector control. Gas-dynamic methods, such as a gas injection into the supersonic nozzle area, offer a required flight path control without complex high-power mechanical systems. The importance of this study lies in improving the accuracy and efficiency of rocket flight control, which is critical for today’s space and defense tasks. The numerical simulation of gas-dynamic control systems, in particular by an asymmetric gas injection, allows one to obtain detailed data on the flow behavior and optimize the design and operating conditions of the system. This study is concerned with a full-scale solid-propellant rocket engine with a gas-dynamic thrust vector control system based on the use of asymmetric forces that occur on the nozzle wall when the supersonic flow interacts with the injected transverse jets. To simulate the process in the Ansys Fluent software package, a geometric model of a nozzle with an asymmetric injection of the chamber gas into the supersonic area was developed. The injection flow rate was controlled by moving the valve flap. The simulation was carried out taking into account the temperature dependence of the main thermophysical gas parameters with consideration for dissociation processes by way of data approximation. The approximation was performed using piecewise polynomial functions. Nozzle flow patterns were obtained. The calculated results were compared with experimental test data and shown to be in satisfactory agreement with the lateral force measured during the fire bench tests of the prototype. From a practical point of view, the results obtained may be directly used to improve existing thrust vector control systems and develop new ones. This will improve rocket navigation accuracy, flight stability, and maneuverability, which is critical for complex space and defense tasks.

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A Study on Nozzle Performance Influence with Aft-deck Geometry

Lee¹,

Park²,

Jin³

et al. 2021

KSPE

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Numerical investigation of freestream flow effects on thrust vector control performance

Cited by 3 publications

References 14 publications

Study on the Effect of Oxidative Jet and Vortex Structure in Fluidic Throat Combined with Thrust Vector Control

Study on the Effect of Oxidative Jet and Vortex Structure in Fluidic Throat Combined with Thrust Vector Control

Simulation of a gas injection into the supersonic nozzle area in gas-dynamic thrust vector control

A Study on Nozzle Performance Influence with Aft-deck Geometry

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