Abstract The paper aims to study an issues of ensuring the safe launch of spacecraft. The phenomenon of a turbulent boundary layer separation from the rocket engine nozzle wall intensively studied in the overexpansion mode that is realized at the start–up stage at sea–level. The emergence of the so–called restricted flow separation leads to the side loads on the wall of the nozzle, the shaking the structure and the destruction of the engine. The conditions for the realization of restricted or free shock separation in the thrust–optimized contoured nozzles of rocket engines are studied numerically. A hysteresis was obtained when changing the type of separation at the stages of increasing and decreasing pressure at the nozzle inlet with the same ambient pressure. Two ways of controlling the transition from one type of separation to another one were studied numerically. The numerical simulation of separated flow in a model nozzle with a back cone shaped extension was carried out. The numerical results confirm that in the nozzle with the large back cone the restricted shock separation can arise and this result appears to be in agreement with experiment.
Highlights Free and restricted shock-induced separation in nozzle. Separation type gas dynamical hysteresis. Nozzle with an annular slot for preventing of separation type transition. Nozzle with an injection for preventing of separation type transition. Restricted shock-induced separation in a nozzle with a back cone extension.
Numerical study of ways to prevent side loads in an over–expanded rocket nozzles during the launch stage
Acta Astronautica ; 163 ; 196-201
2019-02-24
6 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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