Combustion chamber inlet manifold separates vapor from liquid [PDF]
, 1966 Circular manifold with tangential orifices at the inner circumference provides for the vapor constituent of a vaporized cryogenic propellant to enter a rocket combustion chamber before the liquid constituent.
Baker, D. I.
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IT modeling technologies of credible rocket propellants in liquid rocket engines processes [PDF]
, 2013 Р.Р. Назырова +1 more
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The prediction of the nonlinear behavior of unstable liquid rockets [PDF]
Analytical technique for solving nonlinear combustion problems associated with liquid propellant rocket ...
Powell, E. A., Zinn, B. T.
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Further studies of liquid sloshing in rocket propellant tanks Final report, 25 Mar. 1961 - 31 Dec. 1965 [PDF]
Liquid sloshing and dynamics in rocket propellant tanks annotated bibliography with ...
Abramson, H. N.
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Mathematical Model and Experimental Results for Cryogenic Densification and Sub-Cooling Using a Submerged Cooling Source [PDF]
, 2011 Among the many factors that determine overall rocket performance, propellant density is important because it affects the size of the rocket. Thus, in order to decrease the size of a rocket, it may be desirable to increase the density of propellants. This
Johnson, W. L. +3 more
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Development of test stand for experimental investigation of chemical and physical phenomena in Liquid Rocket Engine [PDF]
Journal of Aerospace Technology and Management, 2011 The main objective of this work was to present the specification of an experimental firing test stand for liquid rocket engines (LRE) and develop a program for control and acquisition of data.
Emerson Andrade Santos +3 more
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Statistical derivation of design criteria for liquid rocket combustion instability Final report [PDF]
Statistical correlation between engine design and combustion stability in liquid propellant rocket ...
Bastress, E. K. +2 more
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Design considerations for a pressure-driven multi-stage rocket [PDF]
, 2002 The purpose of this study was to examine the feasibility of using propellant tank pressurization to eliminate the use of high-pressure turbopumps in multi-stage liquid-fueled satellite launchers.
Sauerwein, Steven Craig
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Application of a double-dead-time model describing chugging to liquid propellant rocket engines having multielement injectors [PDF]
Double-dead-time model describing chugging to liquid propellant rocket engines having multielement ...
Szuch, J. R.
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