Protective coating for refractory metals in rocket engines supplemental report, mar. 8, 1963 - mar. 15, 1964
Protective coating systems for refractory metal used in rocket engine nozzles - rocket engine test firing
TEST FIRING↗
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Results for “rockets”
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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Rocket-motor spin-test apparatus
Rocket motor spin test apparatus capable of subjecting solid rocket motors to dynamic spin or roll environments encountered in flight
FLIGHT TEST INSTRUMENT↗
Rocket propagation experiment
Electron densities and collision frequencies from Nike-Apache rocket firings, results of eclipse experiment in South America, and instrumentation for rocket propagation studies
ELECTRON DENSITY↗
Experimental investigation of a lightweight rocket chamber
Experiments have been conducted with a jacketed rocket combustion chamber that was fabricated by hydraulic-forming from sheet metal. Rocket combustion chambers made by this method have been used successfully. Runs with these combustion chambers have been made at over-all heat-transfer rates 1.7 Btu per square inch per second with water cooling and also ammonia as a regenerative coolant.
ENGINES, ROCKET↗
Advanced and Additive Manufacturing Technologies for Liquid Rocket Engine Components
Overview of advanced manufacturing and additive manufacturing development at NASA for liquid rocket engines. Presentation includes various material, process, design, and hot-fire testing developments demonstrating the use of advanced components for liquid rocket engines on launch vehicles and in-space systems.
Additive Manufacturing↗
A Review Towards the Design Optimization of High-Performance Additively Manufactured Rotating Detonation Rocket Engine Injectors
Rotating Detonation Rocket Engines (RDRE) have been marketed primarily for their higher specific impulse potential over constant pressure (CP) liquid rocket engines. However, several other performance advantages exist such as heat transfer advantages for gas expander cycle, increased completeness of combustion at low chamber L*, compact engine design, reduced coolant channel pressure drop potential, and improved injector C* performance. NASA has paved the way for liquid engine system performance enhancement since the Apollo program and continues to do so with metal additive manufacturing (AM), new advanced materials, and advanced propulsion concepts. A team of propulsion development engineers at NASA are in the process of developing high-performance 7K lbf class RDRE hardware for their potential use in lander, upper stage, and even launch vehicle applications. Clear advantages have been demonstrated with AM including program cost and schedule reductions of up to 50%. It is well known that injector performance is integrally linked to the global performance of a combustion device. This is especially the case for RDREs since detonation stability is heavily dependent on the mixedness of propellants. A major goal of this work is to identify what has been done in the open experimental literature and what injectors design features are conducive to high performance in the detonation cycle. This paper reviews the available literature and reports the primary gaps in the knowledge base needed by the pressure gain combustion (PGC) community. Major conclusions are documented, and suggestions given towards the design of high-performance liquid RDRE injectors. In addition, the integration of metal AM into the design of liquid RDRE injector schemes is included.
rotating detonation rocket engine↗
MODELING TECHNIQUES FOR LIQUID PROPELLANT ROCKET COMBUSTION PROCESSES
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.
COMBUSTION↗
The Effects of Wind on Sounding Rockets
A theory to account for the effects of wind on sounding rockets is developed and discussed. A rapid method for calculating the effects of wind is presented. The results of a series of calculations are compared with experimental values. Several suggestions are made to reduce the sensitivity of sounding rockets to winus and to provide better predictions.
SOUNDING ROCKET↗
Effect of Thrustor Arcing on Ion Rocket System Design
Arcing between the electrodes of an ion rocket thrustor is investigated for the effect it will have on the overall design of ion rocket systems. The effect of generator, transformer, and inserted impedances on system stability and efficiency, and on operating lifetime of thrustor components are considered. Rate of arcing, preferential arc paths, speed of arc interruption, and response of thrustors to voltage transients are also discussed. The study indicates that arcing is a system hazard and that arcing rates are of prime importance in the design and development of thrustors, thrustor arrays, and system components. Two system models for reducing the hazard are proposed, based on principles developed herein, published data, and experience available from operation of nine-module electron-bombardment thrustor array. Experimental investigation of these models is presently underway.
THRUSTOR↗
Inferences of stratospheric and mesospheric circulation systems from rocket experiments
Synoptic rocket grenade experiments and meteorological rocket network soundings related to conventional circulation systems in upper stratosphere and mesosphere
SYNOPTIC METEOROLOGY↗
Investigation of light hydrocarbon fuels with flox mixtures as liquid rocket propellants final report, 30 jun. 1964 - 30 jun. 1965
An analysis was completed for determination of the most promising hydrocarbon fuels for use with flox in upper stage rocket engines. Experimental rocket firings in uncooled, transpiration cooled, and regeneratively cooled thrust chambers were conducted using flox with methane, propane, butene-1, and a eutectic blend of pentane and isopentane. Experimental heated tube heat transfer and hypergolicity tests were conducted, and laboratory determinations of physical properties of various blends of hydrocarbon compounds were made.
HYDROCARBON FUEL↗
Analysis of the turbulent mixing between a reactive gas-particle rocket exhaust and a confined airstream.
Air-augmented rocket engine performance prediction requires detailed study of mixing region between reactive gas-particle rocket exhaust and confined airstream
THRUST AUGMENTATION↗
Contribution of combustion noise to overall rocket exhaust jet noise
Low frequency noise measurements of Saturn rocket engine, and combustion noise contribution to overall rocket exhaust jet noise
NOISE MEASUREMENT↗
Effects of exhaust plasmas upon signal transmission to and from rocket powered vehicles.
Signal transmission disturbances caused by presence of rocket exhaust plasmas in propagation medium between ground station and rocket powered vehicle
SIGNAL TRANSMISSION↗
Data report of the meteorological rocket network firings Volume LIV - February 1966 firings
Printouts and graphs of rocket winds, radiosonde observations and/or thermodynamics of February 1966 firings of Meteorological Rocket Network
GRAPH↗
Nuclear rocket propulsion.
Nuclear rocket propulsion development, noting nuclear rocket engine test program
REACTOR TECHNOLOGY↗
Flight Investigation of the Performance of a Two-stage Solid-propellant Nike-deacon (DAN) Meteorological Sounding Rocket
A flight investigation of two Nike-Deacon (DAN) two-stage solid-propellant rocket vehicles indicated satisfactory performance may be expected from the DAN meteorological sounding rocket. Peak altitudes of 356,000 and 350,000 feet, respectively, were recorded for the two flight tests when both vehicles were launched from sea level at an elevation angle of 75 degrees. Performance calculations based on flight-test results show that altitudes between 358,000 feet and 487,000 feet may be attained with payloads varying between 60 pounds and 10 pounds.
MISSILES, SPECIFIC TYPES↗
An Investigation of High-frequency Combustion Oscillations in Liquid-propellant Rocket Engines
An experimental investigation of high-frequency combustion oscillations (screaming) was conducted with a 100-pound-thrust acid-hydrocarbon rocket engine and a 500-pound-thrust oxygen-fuel rocket engine. The oscillation frequencies could be correlated as a linear function of the parameter C/L, where C is the experimentally measured characteristic velocity and L is the combustion-chamber length. The tendency of the engines to scream increased as chamber length was increased. With engine configurations that normally had a low efficiency, screaming resulted in increased performance; at the same time, a five to tenfold increase in heat-transfer rate occurred. It was possible, however, to achieve good performance without screaming.
COMBUSTION - EFFECT OF ENGINE OPERATING CONDITIONS↗