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Engines, Energy and ThermotechnicsMathematical model for heat transfer in variable thickness fins for rocket engines

Mathematical model for heat transfer in variable thickness fins for rocket engines

Mathematical model for heat transfer in variable thickness fins for rocket engines Volodymyr Sliusariev ORCID: https://orcid.org/0009-0004-2883-7467 Oles Honchar Dnipro National University Valerii Bucharskyi ORCID: https://orcid.org/0000-0002-8245-5652 Oles Honchar Dnipro National University Purpose. This article aims to develop a mathematical model for a fin in the cooling system of liquid propellant rocket engines. The objective is to enable calculations for fins with arbitrary thickness variation. The developed mathematical model will be valuable and in demand for calculating heat transfer in the chambers …

Engines, Energy and ThermotechnicsAnalysis of constructions and methods of calculation of fuel oil burners for heating systems

Analysis of constructions and methods of calculation of fuel oil burners for heating systems

Analysis of constructions and methods of calculation of fuel oil burners for heating systems Ihor Tokarskyi ORCID: https://orcid.org/0009-0009-4677-2210 Oles Honchar Dnipro National University Volodymyr Habrinets ORCID: https://orcid.org/0000-0002-6115-7162 Oles Honchar Dnipro National University Purpose. This article aims to show the principle and methodology of developing simple fuel oil burners for autonomous heating boilers that will provide room and water heating, making buildings independent of centralized heat supply. Design / Method / Approach. The research is based on the analysis of existing …

Engines, Energy and ThermotechnicsAnalysis of the possibility of improving rocket engine nozzles

Analysis of the possibility of improving rocket engine nozzles

Analysis of the possibility of improving rocket engine nozzles Oleksandr Zolotko ORCID: https://orcid.org/0009-0008-5600-500X Oles Honchar Dnipro National University It is possible to significantly increase the impulse characteristics of the rocket engine due to the use of effective nozzles in which the flow of atmospheric air optimizes the jet. The purpose of the work is to analyze the characteristics of slotted nozzles, nozzles with ground and height contours, nozzles with a central body, nozzle blocks with nozzles covered by a common …

Engines, Energy and ThermotechnicsThe problem of combustion instability in liquid rocket engines

The problem of combustion instability in liquid rocket engines

The problem of combustion instability in liquid rocket engines Samir Vekilov ORCID: https://orcid.org/0000-0001-5736-6300 Oles Honchar Dnipro National University Volodymyr Lipovskyi ORCID: https://orcid.org/0000-0002-7939-7973 Oles Honchar Dnipro National University Roman Pustovyi ORCID: https://orcid.org/0009-0002-6066-9788 Dnipro Aerospace LLC, Ukraine The purpose of this work is to carry out an overview on combustion instability in liquid propellant rocket engines, its classification, the main principles of occurrence as well as ways to prevent the phenomena while designing of the prospective engine. A new approach is based …

Engines, Energy and ThermotechnicsDetermination of the components to be taken into account when calculating the total mass of working substance of an electric propulsion system based on a Hall thruster

Determination of the components to be taken into account when calculating the total mass of working substance of an electric propulsion system based on a Hall thruster

Determination of the components to be taken into account when calculating the total mass of working substance of an electric propulsion system based on a Hall thruster Serhii Asmolovskyi ORCID: https://orcid.org/0009-0000-5423-9365 Oles Honchar Dnipro National University Serhii Bondarenko ORCID: https://orcid.org/0009-0007-2478-0290 Oles Honchar Dnipro National University The total impulse is one of the main requirements for a spacecraft propulsion system. Its fulfillment depends on the specific impulse of the thruster and the propellant mass. The propellant mass consists of a working …

Engines, Energy and ThermotechnicsMathematical model of the propellant tank pressurization system with respect of heat exchange

Mathematical model of the propellant tank pressurization system with respect of heat exchange

Mathematical model of the propellant tank pressurization system with respect of heat exchange Vitalii Alieksieienko ORCID: https://orcid.org/0009-0000-8317-0096 Oles Honchar Dnipro National University Valerii Bucharskyi ORCID: https://orcid.org/0000-0002-8245-5652 Oles Honchar Dnipro National University The pressurization system for launch vehicle fuel tanks is designed to maintain excess pressure in the gas cushion of the tanks according to the calculated dependency, determined by the requirements for the supply of fuel components and the tank design. To achieve this, it is necessary to coordinate the …