Choice if gas-dynamic thrust vector control typr in ricket engine project developments

Heading: 
Space Energy, Power and Propulsion
Strelnikov, НO, 1Pryadko, NS, 1Ternova, KV, 1Katrenko, МО
1Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and State Space Agency of Ukraine, Dnipro, Ukraine
Space Sci. & Technol. 2025, 31 ;(2):03-11
https://doi.org/10.15407/knit2025.02.003
Publication Language: Ukrainian
Abstract: 
One of the important tasks of ensuring controllability for designing rockets is the type and efficiency choice of the executive bodies for the thrust vectorcontrol of the rocket engine. The efficiency and physical principle analysis of executive control rocket system bodies makes it possible to state that nowadays there is no universal executive control body for different rocket types. Thus, the choice of control system type may have non-typical, alternative executive bodies or systems.
         The combined thrust vector control system included mechanical and gas-dynamic subsystems has developed in Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and State Space Agency of Ukraine This system has the combined advantages of its component subsystems. In addition, such a system obtains an additional advantage - greater thrust vector control reliability due to the subsystem duplication. For such system designing the task of rational type choice of gas-dynamic thrust vector control body inevitably arises. Comparing the characteristics of different gas-dynamic thrust vector control bodies in the rocket engine development project with a combined thrust vector control system and developing recommendations for choosing of used rational gas-dynamic system scheme becomes an urgent task in engine design.
          Computational studies of gas-dynamic thrust vector control body characteristics have been carried out. At the same time, a semi-empirical calculation method of various gas-dynamic executive bodytype efficiency is used, based on ratios describing the supersonic flow disturbance in the rocket engine nozzle by different obstacles: injection, blow-in, solid obstacle on the nozzle wall. The main calculation features of gas-dynamic processes of engine control are shown. Practical recommendations for the use of gas-dynamic thrust vector control systems have been developed, which can be used in the design of various rocket engine types. This allows you to choose a rational thrust vector control system and determine its characteristics at the design stage.
Keywords: control system, efficiency, executive controls, injection, jet nozzle, parameter, rocket engine, supersonic flow disturbance, thrust vector
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