Analysis of performance of a hot gas injection thrust vector controlsystem

Balu, Raman; Marathe, AG; Paul, P.J.; Mukunda, H. S.

doi:10.2514/3.23365

Cited by 27 publications

(16 citation statements)

References 2 publications

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“…Resultant control force is decomposed to axial, normal, and side components.Now we may write the thrust coef cient, separated into three directions, in the following form 9 :…”

Section: Sitvc Propulsion Ef Cienciesmentioning

confidence: 99%

Performance Analysis of Secondary Gas Injection into a Conical Rocket Nozzle

Yoon

2002

Journal of Propulsion and Power

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The effects of injection location of secondary jet and nozzle divergent cone angle on the performance of secondary gas injection for thrust vector control (SITVC) were numerically investigated.Three-dimensionalReynoldsaveraged Navier-Stokes equations with an algebraic turbulence model solved the complex three-dimensional nozzle ows perturbed by the secondary gas jet. The numerical code was properly validated by experiment. The results showed that downstream secondary jet injection and smaller nozzle divergent cone angles lead to higher ef ciencies over a wide range of pressure ratios. The occurrence of re ected shock waves severely lowers SITVC propulsion performance. Upstream jet injection is more effective in a narrow range of de ection. Nomenclature A = cross-sectional area C f = thrust coef cient E = total energy per unit volume F = thrust K = speci c impulse ratio M = Mach number m = mass ow rate p = pressure q i = heat ux Re = Reynolds number r = radius, radial coordinate T = temperature v i = velocity x = axial distance (axial coordinate) from the primary nozzle throat x J = axial distance of secondary injection ori ce x L = length of divergent section of primary nozzle Z = axial coordinate ® = divergent cone half-angle ± = Kronecker delta µ = circumferential coordinate ½ = density ¿ i j = stress tensor Subscripts a = ambient state e = exit condition i = inlet condition n = normal direction p = primary ow s = secondary jet t = primary nozzle throat w = wall 0 = reference (total) state Superscript T = transpose

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“…Resultant control force is decomposed to axial, normal, and side components.Now we may write the thrust coef cient, separated into three directions, in the following form 9 :…”

Section: Sitvc Propulsion Ef Cienciesmentioning

confidence: 99%

Performance Analysis of Secondary Gas Injection into a Conical Rocket Nozzle

Yoon

2002

Journal of Propulsion and Power

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“…Other efforts have focused on using fluidic manipulation (see e.g. Balu et al 1991;Ko and Yoon 2002) to leverage the Coanda effect (see e.g. Grinstein and DeVore 1999).…”

Section: Introductionmentioning

confidence: 99%

Large-eddy simulations of plasma-based asymmetric control of supersonic round jets

González

Gaitonde

Lewis

2015

International Journal of Computational Fluid Dynamics

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Localised arc filament plasma actuators are modelled with a validated technique to examine asymmetric control of a perfectly expanded round free jet to deflect its downstream trajectory. The nominal Mach and Reynolds numbers are 1.3 and 1 million, respectively. No-control, symmetrically controlled, and under-expanded jets are also simulated for comparison purposes. Parametric variation of actuation frequency and duty cycle indicate that asymmetric control can alter the trajectory, and, within the confines of the parameters investigated, the optimal forcing scheme was found to correspond to the jet's columnmode frequency and a duty cycle of approximately 60%. Increasing frequency and duty cycle beyond these values have a detrimental effect on control, which is consistent with experimental findings. Asymmetric actuation resulted in significant mixing enhancement on the actuated side, as evidenced by the increased growth rate of the non-dimensional momentum thickness. The effectiveness of control is reduced for under-expanded jet conditions.

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“…From the different ways to deflect thrust vector of a flying vehicle, Secondary Injection Thrust Vector Control (SITVC) has been applied successfully since 1960's and is achieved by injecting secondary fluid to the supersonic flow inside the divergent part of the convergent-divergent nozzle. In contrast to mechanical thrust vector control systems, such as gimbaled nozzles, jet vanes/tabs, jetavators etc., that uses an actuation system to move the mechanical parts, SITVC does not use any movable parts and is governed by flow regulation, which minimize the losses of the axial thrust force during changing the thrust direction [1] The secondary injectant, (liquid or gas) can be supplied from the combustion chamber as a bleed or from a separate gas generator and it creates a complex flow field in the nozzle divergent part which contains not only a strong bow shock that creates asymmetry and a weak separation shock due to separation of the boundary layer upstream of the injector, but also downstream of the injector a Mach disk and reattachment region accompanied by recompression were created [2][3][4]. Figure1.…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of Nozzle Flow Field with Secondary Injection Thrust Vector Control

2018

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Numerical simulations are performed to characterize the secondary injection thrust vector control. For this objective the following measurements were taken: considering the flow to be compressible and turbulent using Realizable k-ε turbulence model accompanied by enhanced wall treatment, the comparison between the CFD results and the experimental results shows a very good agreement. Then a parametric study on injection mass flow rate (changing secondary stagnation pressure) with the same injection location and injection angle is done. The results stated that increasing the injectant mass flow rate lead to shock impingement from opposite wall at secondary stagnation pressure 1.4 of the primary stagnation pressure.

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Analysis of performance of a hot gas injection thrust vector controlsystem

Cited by 27 publications

References 2 publications

Performance Analysis of Secondary Gas Injection into a Conical Rocket Nozzle

Performance Analysis of Secondary Gas Injection into a Conical Rocket Nozzle

Large-eddy simulations of plasma-based asymmetric control of supersonic round jets

Numerical Simulation of Nozzle Flow Field with Secondary Injection Thrust Vector Control

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