Registration Number
0226U000824,
(0124U000389)
, R & D reports
Title
Mathematical simulation of the functioning of control jet engines and their jet effect on spacecraft
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Проведення числових параметричних розрахунків стосовно нових систем двигунів малої тяги з урахуванням їх струминного впливу на функціональні вузли КА
Head
Tymoshenko Valerii I., д.ф.-м.н.
Registration Date
16-01-2026
Organization
Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine
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Improvement and application of mathematical simulation methods for the operation of low-thrust jet engine systems and determination of their plume impact on functional components of new spacecraft during design
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The object of the research - numerical modeling algorithms and software for determining parameters of hydraulic and aerothermo-gasdynamic processes during the operation of low-thrust rocket engines (LTRE) on spacecraft (SC). The aim of the work - to perform parametric calculations of new LTRE systems, taking into account their plume impact on SC functional units. The research methods - numerical simulation of processes in LTRE propellant feed systems, valves, and combustion chambers, plume formation of combustion products, and numerical modeling of plume interaction with sensitive elements and units of SC.
An analysis was carried out and a set of input data was formulated for numerical simulation of LTRE system operation using environmentally friendly monopropellant LMP-103S, taking into account hydraulic and thermogasdynamic processes in the engines and plume parameters of combustion products for three-dimensional flow modeling around SC functional units.
Calculations of unsteady hydraulic and thermogasdynamic processes were performed for single LTREs and LTRE systems with nominal thrusts of 1 N, 5 N, and 22 N over a wide range of propellant inlet pressures. The results agree with experimental test data of the engine developer (Swedish company ECAPS).
Numerical determination of aerogasdynamic parameters was performed for plume flow around mock-ups of SC units in the form of a cone and a flat plate at various angles of attack. The calculation results are consistent with experimental data in the literature.
A series of calculations of plume impingement from a 5 N LTRE at various angles on solar array panels of a hexagonal CubeSat developed at SE “Yuzhnoye Design Office” was carried out. A certificate confirming practical application of the calculated data was obtained.
The results can be applied in the Ukrainian rocket and space industry for spacecraft propulsion system design and selection of their placement on SC with minimal plume impact on critical units.
Product Description
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Larysa L. Pecherytsia
Tetiana G. Smila
Ivanova Galyna O.
Yuriy V. Knyshenko
Valerii I. Tуmoshenko
Petrushenko Mykola V.
Volodymyr I. Shcherbakov
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2026-01-16
