Results 91 to 100 of about 10,741 (228)
Review of Combustion Stability Characteristics of Swirl Coaxial Element Injectors [PDF]
Liquid propellant rocket engine injectors using coaxial elements where the center liquid is swirled have become more common in the United States over the past several decades, although primarily for technology or advanced development programs. Currently,
Casiano, M. J., Hulka, J. R.
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Passively regulated water electrolysis rocket engine Patent [PDF]
, 1970 Water electrolysis rocket engine with self- regulating stoichiometric fuel mixing ...
Grant, D. J.
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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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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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Rocket motor system Patent [PDF]
, 1964 Igniter capsule for chemical ignition of liquid rocket ...
Gregory, J. W., Straight, D. M.
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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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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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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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Launch vehicle performance using metallized propellants [PDF]
Metallized propellant propulsion systems are considered as replacements for the solid rocket boosters and liquid sustainer stages on the current launch vehicles: both the Space Transportation System (STS) and the Titan 4.
Palaszewski, Bryan A., Powell, Richard
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