Interceptor regulation modeling of the thrust vector direction of a rocket engine

  • Oleksandr Ihnatyev
  • Gennadiy Strelnikov
  • Olena Tokareva


The topic relevance is the need to develop а combined system of the thrust vector control of a rocket engine using solid obstacles (interceptors) with simultaneously injecting exhaust gas or liquid components of rocket fuels through them.
Analysis of recent research and publications. The interceptor method of the thrust vector direction control hasn’t so far been well explored. The experiments conducted earlier made it possible to establish generalized empirical dependences and to obtain a picture of a perturbed supersonic flow.
The purpose of the work is modeling and numerical study of the interceptor regulation of the thrust vector direction, the selection of the most effective way of regulation.
Modeling is based on solving the Reynolds-averaged Navier-Stokes equations using the ANSYS FLUENT software package (SST-modification of the k-ω model).
A model of a gas-dynamic method for control the thrust vector direction based on the extension of a solid obstacle (interceptor) into the supersonic flow of combustion rocket fuel products is developed. New results have been obtained on the patterns of perturbed flow and the efficiency of supersonic flow control during interceptor control. The results were verified by previous experimental studies. Based on the results of comparing the generated elementary lateral forces, the possibility of increasing the control efficiency of the thrust vector direction by extending the interceptor with simultaneous gas injection is shown.
A numerical simulation of the supersonic perturbed flow in the rocket engine nozzle is carried out, based on the solution of the Navier-Stokes equations. According to the results, the flow in the engine nozzle was visualized when the whole interceptor and the interceptor with an opened hole were pulled out, through the last gas was blown into the boundary layer towards the flow of combustion products. The data of previous experimental studies are confirmed. The developed model can serve as the basis for conducting numerical experiments of the interceptor method for regulating the thrust vector direction. The obtained results can be used to simplify and reduce the terms of design development of controls when creating new and modernizing standard models of rocket technology.


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