Abstract
Tests of rocket engines are expensive, among other things, due to a necessity of using costly propellants during the tests, hydrogen peroxide especially. If the tests involve application of different doses of the fuel and the oxidizer, their costs may be reduced owing to application of valves that make it possible to change the flow capacity of the liquid during operation of the engine. The authors elaborated a design of a valve with a cavitation Venturi tube, in which the throttling needle is displaced by means of a screw gear driven by a DC motor. Simulation study of the designed valve confirmed its capability for performing complex functions, including realization of the whole cycle, from closing to full opening of the valve, within a time no longer than 20 ms.
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Krawczyk, M., Bartkowiak, B., Wierciak, J. (2018). Valve for Testing Rocket Engines. In: Březina, T., Jabłoński, R. (eds) Mechatronics 2017. MECHATRONICS 2017. Advances in Intelligent Systems and Computing, vol 644. Springer, Cham. https://doi.org/10.1007/978-3-319-65960-2_12
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DOI: https://doi.org/10.1007/978-3-319-65960-2_12
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