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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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Method for continuous variation of propellant flow and thrust in propulsive devices Patent [PDF]
, 1962 Continuous variation of propellant flow and thrust by application of liquid foam flow theory to injection ...
Morrell, G.
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Trajectory-correction propulsion system Patent [PDF]
, 1966 Spacecraft trajectory correction propulsion ...
Schmitz, B. W., Smith, W. W.
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AerospaceAccurate quantification of metallic contaminants in rocket exhaust plumes serves as a critical diagnostic indicator for engine wear monitoring. This paper develops a hybrid method combining atomic emission spectroscopy (AES) theory with a genetic ...
Siyang Tan +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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Simulation Study on Outflow Characteristics of Cryogenic Propellant during Rocket Ascent
Zhileng xuebao, 2020 At the rocket launching stage, it is very important to supply sufficient and vapor-free liquid propellant to maintain the functioning of the main engine.
Huang Xiaoning +4 more
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Modeling of Shutdown Process in Liquid Propellant Rocket Engines [PDF]
فصلنامه علوم و فناوری فضایی, 2014 The effects of liquid propellant rocket engines thrust termination transients are important in achieving the launch vehicle’s desired final velocity with the required precision.
M. Shafiey Dehaj +4 more
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Design issues for propulsion systems using metallized propellants [PDF]
Metallized propellants are liquid propellants that contain metal particles. These particles are suspended in a gelled fuel or oxidizer. Aluminum is used as the metal additive.
Palaszewski, Bryan, Rapp, Douglas
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