Assessment of the Counter-Flow Thrust Vector Control in a Three-Dimensional Rectangular Nozzle

This work deals with theoretical aspects of thrust vector control in rocket nozzles by the injection of secondary gas into the supersonic region of the nozzle. The work is concerned mainly with two-dimensional flow, though some aspects of three-dimensional flow in axisymmetric nozzles are considered. The subject matter is divided into three parts. In Part I, the side force produced when a physical wedge is placed into the exit of a two-dimensional nozzle is considered. In Parts 2 and 3, the physical wedge is replaced by a wedge-shaped “dead water” region produced by the separation of the boundary layer upstream of a secondary injection port. The modifications which then have to be made to the theoretical relationships, given in Part 1, are enumerated. Theoretical relationships for side force, thrust augmentation and magnification parameter for two- and three-dimensional flow are given for secondary injection normal to the main nozzle axis. In addition, the advantages to be gained by secondary injection in an upstream direction are clearly illustrated. The theoretical results are compared with experimental work and a comparison is made with the theories of other workers.

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Numerical Characterisation of Jet-Vane based Thrust Vector Control Systems

Defence Science Journal ◽

10.14429/dsj.65.7960 ◽

2015 ◽

Vol 65 (4) ◽

pp. 261 ◽

Cited By ~ 1

Author(s):

M.S.R. Chandra Murthy ◽

Debasis Chakraborty

Keyword(s):

Vector Control ◽

Control Systems ◽

Stokes Equations ◽

Three Dimensional ◽

Operating Conditions ◽

Navier Stokes ◽

Navier Stokes Equations ◽

Static Tests ◽

Thrust Vector Control ◽

Thrust Vector

Computational fluid dynamics methodology was used in characterising jet vane based thrust vector control systems of tactical missiles. Three-dimensional Reynolds Averaged Navier-Stokes equations were solved along with two-equation turbulence model for different operating conditions. Nonlinear regression analysis was applied to the detailed CFD database to evolve a mathematical model for the thrust vector control system. The developed model was validated with series of ground based 6-Component static tests. The proven methodology is applied toa new configuration.Defence Science Journal, Vol. 65, No. 4, July 2015, pp. 261-264, DOI: http://dx.doi.org/10.14429/dsj.65.7960

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Experimental and numerical research of the influence of thrust vector control on the missile aerodynamics by cold and hot jet simulations

FME Transaction ◽

10.5937/fme2004770o ◽

2020 ◽

Vol 48 (4) ◽

pp. 770-778

Author(s):

Goran Ocokoljić ◽

Boško Rašuo ◽

Dijana Damljanović ◽

Saša Živković

Keyword(s):

Vector Control ◽

Three Dimensional ◽

Combustion Products ◽

Aerodynamic Characteristics ◽

Navier Stokes ◽

Cfd Model ◽

Thrust Vector Control ◽

Thrust Vector ◽

And Performance ◽

Definition Of

The flow field phenomena that occur as a result of thrust vector control (TVC) system activity on a missile with lateral jets are very complex and influence all other components of the missile. Influence is more significant when TVC is generating commands, when jets are asymmetrically directed. The main goal of these study was to determine the influence of of the hot rocket motor's combustion products on the basis of the CFD model proven with the cold-jet simulation. Based on obtained experimental aerodynamic coefficients for the cold-jet simulation the preliminary aerodynamic CFD model was designed. Three-dimensional Reynolds averaged Navier-Stokes numerical aerodynamic and hot-jet simulations were carried out to predict the aerodynamic loads of the missile based on the finite volume method. The study resulted in the definition of a methodology for the investigation of the jet reaction effects in a wind tunnel. A method for determining of the TVC system interference on the aerodynamic characteristics, as a basic prerequisite for structural, stability and performance analysis, was proposed. Mutual verification and validation process was carried out through experiment and proper application of the commercial CFD software code for calculation aerodynamic effects of the hot gases lateral jets on the performance of a guided missile. Experimental and computational results of the pitching moment coefficients are presented and agreed well with.

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Hysteretic Behaviors in Counter-Flow Thrust Vector Control

Journal of Aerospace Engineering ◽

10.1061/(asce)as.1943-5525.0001027 ◽

2019 ◽

Vol 32 (4) ◽

pp. 04019041 ◽

Cited By ~ 6

Author(s):

Kexin Wu ◽

Yingzi Jin ◽

Heuy Dong Kim

Keyword(s):

Vector Control ◽

Counter Flow ◽

Thrust Vector Control ◽

Thrust Vector

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Fluidic thrust vector control based on counter-flow concept

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1177/0954410017752580 ◽

2018 ◽

Vol 233 (4) ◽

pp. 1412-1422 ◽

Cited By ~ 7

Author(s):

Kexin Wu ◽

Heuy Dong Kim ◽

Yingzi Jin

Keyword(s):

Vector Control ◽

Mass Flow ◽

Deflection Angle ◽

Pressure Ratio ◽

Supersonic Nozzle ◽

Flow Ratio ◽

Counter Flow ◽

Thrust Vector Control ◽

Thrust Vector ◽

Mass Flow Ratio

Computational studies are conducted on the supersonic nozzle to investigate the possibility of utilizing counter-flow in fluidic thrust vector control. In this work, the design Mach number of the symmetric supersonic nozzle is set to be 2.5. For the validation of methodology, numerical results are compared with experimental data referred from the literature. Two-dimensional numerical simulations are based on well-assessed standard k–ɛ turbulence model with standard wall functions. Second-order accuracy is ensured to reveal more details of flow field. The system thrust ratio, deflection angle, and secondary mass flow ratio were studied for a wide range of nozzle pressure ratios and secondary pressure ratios. The results indicate that deflection angle and secondary mass flow ratio are found to be decreased with increasing nozzle pressure ratio as well as system thrust ratio. The secondary mass flow ratio and deflection angle decrease with the increase of secondary pressure ratio, and system thrust ratio increases with the increasing of secondary pressure ratio. The secondary mass flow rate remains under 2.4% of the primary flow to obtain efficient thrust vector control at high Mach number.

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