Performance Analyses of Fluidic Thrust Vector Control System Using Dual Throat Nozzle

Maruyama, Yoshihiro; Sakata, Masashi; Takahashi, Yuichiro

doi:10.2514/1.j059696

Cited by 14 publications

(5 citation statements)

References 16 publications

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“…The study found that the arc-shaped BDTN not only achie high thrust efficiency and thrust coefficient but also significantly reduced total pres loss compared to BDTN with a V-shaped bypass channel. In additional, Maruyama et al [81] employed a direct simulation Monte C method to conduct a numerical analysis of the flow within a rocket motor nozzle. T investigation revealed that a steady thrust deflection of approximately 18° was achie when the secondary jet's mass flow rate accounted for 5% of the total fluid.…”

Section: Thrust Vectoringmentioning

confidence: 99%

“…To address this issue, they improved the nozzle de and discovered that by widening the second throat to 1.50 times the cross-sectional of the first throat, the unexpected thrust deflection during zero flow of the secondar was effectively suppressed (refer to Figure 17). In additional, Maruyama et al [81] employed a direct simulation Monte Carlo method to conduct a numerical analysis of the flow within a rocket motor nozzle. Their investigation revealed that a steady thrust deflection of approximately 18 • was achieved when the secondary jet's mass flow rate accounted for 5% of the total fluid.…”

Section: Thrust Vectoringmentioning

confidence: 99%

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Research Progress on Active Secondary Jet Technology in Supersonic Flow Field of Aerospace Propulsion Systems

Zhu,

Guo,

Sun

et al. 2023

Fluids

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As humans continue to explore the aerospace field, higher demands have been placed on new types of propulsion systems. Meanwhile, active secondary flow has been applied to various aspects of engines over the past seventy years, significantly enhancing engine performance. For the new generation of propulsion systems, active secondary flow remains a highly promising technology. This article provides an overview of the application of active secondary flow in engines, including a review of the past research on the secondary jet flow field, and an introduction of the more prominent applications of the jet in engines and its research progress. Finally, the problems existing in the current application of the secondary jet are summarized, and the future direction of the research is anticipated.

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Section: Thrust Vectoringmentioning

confidence: 99%

Section: Thrust Vectoringmentioning

confidence: 99%

Research Progress on Active Secondary Jet Technology in Supersonic Flow Field of Aerospace Propulsion Systems

Zhu,

Guo,

Sun

et al. 2023

Fluids

View full text Add to dashboard Cite

show abstract

“…The shock vector control (SVC) or thrust vector control (TVC) method involves injecting secondary flow into the divergence section of the nozzle to generate induced shock waves that deflect the primary flow and alter the direction of thrust [13][14][15]. This technique has been implemented in missiles such as the Minuteman 3 ICBM and the Julang 2 ICBM and has undergone significant advancements in recent years [13,[16][17][18][19].…”

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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“…The two dominant FTV mechanisms are co-flow [6][7][8] and counter-flow mechanisms [17][18][19], wherein the jet is blown in the same direction as the primary jet in the case of the former. In the latter mechanism, the secondary jet is sucked in against the outgoing primary jet.…”

Section: Introductionmentioning

confidence: 99%

“…The co-flow and its variant have been investigated by a number of researchers in recent times. For instance, Maruyama et al [18] examined the flow characteristics of a two-dimensional dual-throat nozzle (DTN) using numerical analysis. Computational work on flow dynamics behavior in two-dimension DTN using different input functions, such as step and ramp, were carried out by Ferlauto and Marsilio [19].…”

Section: Introductionmentioning

confidence: 99%

Mathematical Modelling and Fluidic Thrust Vectoring Control of a Delta Wing UAV

Tanveer

Ahmad

2023

Aerospace

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Pitch control of an unmanned aerial vehicle (UAV) using fluidic thrust vectoring (FTV) is a relatively novel technique requiring no moving control surfaces, such as elevators. In this paper, the authors’ previous work on the characterization of a static co-flow FTV rig is further validated using the free to pitch dynamic test bench. The deflection of a primary jet after injection of a high-velocity secondary jet was captured using the tuft flow visualization technique, along with the experimental recording of subsequent normal force impinged on the Coanda surface resulting in the pitching moment. The effect of primary and secondary flow velocities on exhaust jet deflection, as well as on the pitch angle of the aircraft, is examined. Aerodynamic gain as well as the inertia of a delta wing UAV test bench are computed through experiments and fed into the equation of motion (e.o.m). The e.o.m developed aided in the design of a model-based PID controller for pitch motion control using the multi-parameter root locus technique. The root locus tuned controller serves as a benchmark controller for performance evaluation of the genetic algorithm (GA) and particle swarm optimization (PSO) tuned controllers. Furthermore, the frequency domain metric of gain and phase margins were also employed to reach a robust control design. Experiments conducted in a simulation environment reveal that PSO-PID results in a better response of the UAV in comparison to the baseline pitch controller.

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Performance Analyses of Fluidic Thrust Vector Control System Using Dual Throat Nozzle

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Cited by 14 publications

References 16 publications

Research Progress on Active Secondary Jet Technology in Supersonic Flow Field of Aerospace Propulsion Systems

Research Progress on Active Secondary Jet Technology in Supersonic Flow Field of Aerospace Propulsion Systems

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

Mathematical Modelling and Fluidic Thrust Vectoring Control of a Delta Wing UAV

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