Results 91 to 100 of about 10,740 (231)
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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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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Three stage rocket vehicle with parallel staging [PDF]
, 1984 A three stage rocket vehicle has a large forward propellant tank and a small aft propellant tank axially aligned. Secured to the rear end of the aft propellant tank is an engine mount structure carrying rocket engines.
Marshall, W. R.
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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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Technical Assessments of Future European Space Transportation Options [PDF]
, 2007 The paper describes some of the most recent activities in Germany in the technical assessment of future European launcher architecture. In focus is a joint effort of DLR-SART with German launcher industry in the definition of a next generation upper ...
Dutheil, Jean-Philippe +3 more
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Launch Vehicle Description [PDF]
, 1970 The Thorad-Agena is a two-stage launch vehicle consisting of a Thorad first-stage and an Agena second-stage, connected by a booster adapter. The composite vehicle, including the shroud and the booster adapter, is about 33 meters (109 ft) long.
Coffey, E. E., Geye, R. P.
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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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