Hysteresis phenomena for shock wave reflections in the supersonic jet were already studied in the literature and reported that hysteretic behaviors were affected by the transient pressure ratio. However, there is no investigation on the hysteresis phenomenon in counter-flow thrust-vector control. The objective of the present work is illustrating effective influences of hysteretic behaviors on deflection angle, static pressure distribution along the upper-suction collar, and the secondary mass-flow ratio in a counter-flow thrust-vector control system. The fully implicit finite volume method was selected to solve unsteady, compressible Reynolds-averaged Navier-Stokes equations with boundary conditions of pressure inlet and pressure outlet. Two-dimensional numerical simulations were carried out based on the standard turbulence model and standard wall function. Second-order accuracy was ensured to illustrate more insight into hysteresis phenomena in counter-flow thrust-vector control. Hysteretic behaviors were studied by changing pressure ratios with time linearly, which include the nozzle-pressure ratio and the secondary pressure ratio. Numerical results indicated that hysteresis loops of the deflection angle and the secondary mass-flow ratio were formed by varying the nozzle-pressure ratio or the secondary pressure ratio with time, respectively.
Hysteretic Behaviors in Counter-Flow Thrust Vector Control
Journal of Aerospace Engineering ; 32 , 4
2019-04-25
Aufsatz (Zeitschrift)
Elektronische Ressource
Unbekannt
Fluidic thrust vector control based on counter-flow concept
SAGE Publications | 2019
|Taylor & Francis Verlag | 1989
|NTIS | 1967
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