Registration Number
0219U004584,
0119U000730
, R & D reports
Title
Simulation of the liquid-propellant rocket engine start-up, taking into account cavitation in the pumps and the feed lines dynamics of the first stage of a prospective launch vehicle with pogo vibration dampers.
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Head
Pylypenko Oleg Viktorovych, Доктор технічних наук
Registration Date
11-09-2019
Organization
The Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine
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The purpose of the research is to numerically determine and study the characteristics of transient processes when start-up the first-stage liquid-propellant engine of a prospective liquid propellant launch vehicle (LV) with pogo suppressors installed in feed lines, taking into account cavitation in the pumps. The object of the research is the process of start-up a liquid rocket propulsion system (LPRS), which contains four liquid-propellant rocket engines (LPREs) with a turbo-pump feed system and four pogo suppressors. Research methods include methods of the automatic control systems theory, the theory of rocket engines, the theory of oscillations. Results obtained: A non-linear mathematical model of start-up the first-stage LPRS of a prospective LV has been developed. On the basis of the developed model, the characteristics of transients when starting LPREs without pogo suppressors and with ones are determined, two options for the placement of pogo suppressors were considered: at the input to the oxidizer booster pumps (OBP) and near the main collector of the oxidizer. The analysis of the effect on the transient processes in the LPRE of the following factors has been carried out: cavitation phenomena in the pumps of the oxidizer and fuel; possible differences in the time sequence of start-up commands of each of the four engines; installation of pogo suppressors and the place of its installation. It is shown that the installation of pogo suppressors significantly improves the quality of transients when LPRE starts up, reducing the maximum pressure overshoots and maximum flow rate drops of propellant. It has been determined that it is more effective from the point of view of improving the quality of transient processes to place the pogo suppressors at the input to the OBP.
Product Description
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Башлій І. Д.
Долгополов С. І.
Ніколаєв О. Д.
Пилипенко О. В.
Хоряк Н. В.
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2020-04-02
