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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Heat-transfer rates and coefficients and coolant pressure loss characteristics in regeneratively cooled liquid hydrogen-liquid fluorine rocket engine thrust chambers
Experimental performance of hydrogen-fluorine rocket engine at several chamber pressures and exhaust-nozzle expansion area ratios
A qualitative physical processes description of stable and unstable combustion in rockets is presented to establish the basis for choosing model hardware design criteria. It is concluded that it is not possible to scale rocket combustion processes in the usual sense of the term. The studies conducted at Rocketdyne have shown that model chambers which satisfactorily model the steady state behavior of large engines must be designed to maintain (1) the propellant injection density, and (2) the chamber to throat Contraction ratio (hence chamber pressure). For studies of destructive acoustic modes of combustion instability a third parameter, the frequency, must also be maintained.
A set of analyses was conducted to determine the heat transfer characteristics of metallized gelled liquid propellants in a rocket engine. These analyses used data from experiments conducted with a small 30- to 40-lbf thrust engine composed of a modular injector, igniter, chamber, and nozzle. The fuels used were traditional liquid RP-1 and gelled RP-1 with 0-, 5-, and 55-wt % loadings of aluminum (Al) with gaseous oxygen as the oxidizer. Heat transfer measurements were made with a calorimeter chamber and nozzle setup that had a total of 31 cooling channels. A gelled fuel coating, composed of unburned gelled fuel and partially combusted RP-1, formed in the 0-, 5- and 55-wt % engines. For the 0- and 5-wt % RP-1/Al, the coating caused a large decrease in calorimeter engine heat flux in the last half of the chamber. This heat flux reduction was analyzed by comparing engine firings and the changes in the heat flux during a firing at NASA Lewis Research Center's Rocket Laboratories. This work is part of an ongoing series of analyses of metallized gelled propellants.
Quantitative design criteria for priori injector designs yielding combustion process compatible with thrust chamber-nozzle materials
Launch vehicle technology has probably been the most controversial aspect of the manned space flight program as it has developed during the past twelve months. This paper is a hopefully concise exposition of the present lunar flight system concept, and necessarily represents the concerted efforts of numerous individuals within government and industry who are engaged in the Apollo/Saturn program, and whose substantial contributions must be acknowledged at the outset.
Significance of the performance factors, specific impulse and vehicle mass ratio of liquid propelled rockets, so as to produce maximum capability
Bladders, diaphragms and pistons used for earth- storable liquid rocket propellant expulsion in unmanned spacecraft
Spring constants for ellipsoid bulkheads used in longitudinal vibration analysis of liquid propellant launch vehicles
Hot-gas side heat-transfer rates for liquid oxygen and hydrogen propellant rocket nozzle
Oxidation tests of pyrolytic materials for use in free standing thrust chamber of liquid propellant rocket
Liquid rocket propulsion systems examining performance and properties of propellant combinations and components of subsystems
Interrelated design factors of launch vehicle and spacecraft examining characteristics of solid, liquid-solid and liquid propellant boosters
Radiation, vacuum, temperature and micrometeoroid flux effects on liquid rocket systems
Material requirements for liquid propellant, solid propellant, nuclear and electric propulsion systems
Advanced propulsion systems for unmanned spacecraft making simple pressure-fed systems, using storable propellants, thrust chambers and flexible propellant barriers
Integrated pulse modulated rocket chamber design with 60 lb thrust using nitrogen tetroxide and hydrazine mixture
Nonsteady flow conditions in subsonic section of Laval nozzle to investigate nonlinear transverse combustion instability in liquid propellant rocket motors