Mathematical model for heat transfer in variable thickness fins for rocket engines
Challenges and Issues of Modern SciencePurpose. 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
Volodymyr Sliusariev, Valerii Bucharskyi
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Investigation of the existing methods for designing pre-combustion chambers in hybrid rocket engines
Авіаційно-космічна техніка та технологіяHybrid propellant rocket engines (HPRE) have been under development and advancement since the beginning of rocket propulsion research, alongside liquid and solid propellant rocket motors.
Maurício Sá Gontijo
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Simulations on Optimization of Liquid Spray Burners & Operating Parameters
International Journal of Aviation, Aeronautics, and Aerospace, 2019 Spray burners form an essential part of any liquid propulsion system as they are responsible for injecting, atomizing, mixing and combusting the liquid fuel.
Pallavi Gajjar, Vinayak Malhotra
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Liquid-hydrogen rocket engine development at Aerojet, 1944 - 1950 [PDF]
This program demonstrated the feasibility of virtually all the components in present-day, high-energy, liquid-rocket engines. Transpiration and film-cooled thrust chambers were successfully operated.
Coplen, H. L. +3 more
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Comparative analysis of the designs and implementation of vehicles based on reactive propulsion proposed during the nineteenth and beginning of the twentieth centuries [PDF]
Examination of the presently known historical scientific literature related to the problem of reactive flight indicates that considerable attention had already been given to the idea of reactive propulsion in the nineteenth century; about thirty designs ...
Sokolskiy, V. N.
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The problem of combustion instability in liquid rocket engines
Challenges and Issues of Modern ScienceThe 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.
Samir Vekilov +2 more
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Numerical Analysis of a Supercritical Heat Transfer of Cryogenic Methane in Regeneratively Cooled Rocket Engine [PDF]
INCAS BulletinA comparative study of supercritical heat transfer in a regeneratively cooled rocket engine was conducted using three-dimensional numerical simulations for two channel geometries: rectangular and square. Various constant heat fluxes, flow velocities, and
Mohammed Amine DJEFFAL +5 more
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Design issues for lunar in situ aluminum/oxygen propellant rocket engines [PDF]
Design issues for lunar ascent and lunar descent rocket engines fueled by aluminum/oxygen propellant produced in situ at the lunar surface were evaluated.
Meyer, Michael L.
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Modelling of the processes inside the nozzle of resistojet and arcjet with molecular propellant
Авіаційно-космічна техніка та технологіяThe first sample of the resistojet, which together with the arcjet belongs to the class of electrothermal thrusters, was developed in 1929-33 by the Ukrainian designer Valentyn Hlushko.
Serhii Nesterenko, Peng Shuai
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Chemistry: Space resources for teachers including suggestions for classroom activities and laboratory experiments [PDF]
, 1971 Curriculum supplement to assist general chemistry teachers in updating instruction materials with aerospace ...
Bowman, W. H., Lawrence, R. M.
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