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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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Preliminary identification and evaluation of promising liquid oxygen/ hydrocarbon (LO2/HC) rocket engine cycles is reported. A consistent and reliable data base for vehicle optimization and design studies, to demonstrate the significance of propulsion system improvements, and to select the critical technology areas necessary to realize such advances is presented.
This viewgraph presentation provides information on the transfer of rocket engine flow simulation technology to work involving the development of blood pumps. Details are offered regarding the design and requirements of mechanical heart assist devices, or VADs (ventricular assist device). There are various computational fluid dynamics issues involved in the visualization of flow in such devices, and these are highlighted and compared to those of rocket turbopumps.
Hydrodynamic differential and difference equations and computer algorithm for nonlinear combustion instability in liquid propellant rocket engines, and Fortran IV listing
Engine design and operating parameters studied for effects on rocket engine ignition and popping
Base heating scaling criteria for four-engine rocket cluster operating at high altitude
Specific nuclear light bulb and open-cycle vortex stabilized gaseous nuclear rocket engine designs
Double dead-time model for combustion stability analysis in liquid bipropellant rocket engines
Spacecraft rocket engine chamber insulation materials - silica fabric/molybdenum foil layer, carbon fabric/tantalum foil, and fine tungsten powder in hollow zirconia microsphere matrix
Correlation equations for predicting gas-side heat transfer of axisymmetric rocket engine nozzles
Design, development, and testing of 1000 pound thrust FLOX-propane ablative rocket engine
Cement materials to attach thermocouple to stainless steel tubing in nuclear rocket engine nozzle, considering thermal conductivity, bond and tensile and compressive strengths
Design guide for seals in liquid rocket engines with emphasis on rotating seals
Bearing requirements for liquid rocket engine turbopumps
The expert system described in this paper analyzes spectral emissions of rocket engine exhaust plumes and shows major promise for use in engine health diagnostics. Plume emission spectroscopy is an important tool for diagnosing engine anomalies, but it is time-consuming and requires highly skilled personnel. The expert system was created to alleviate such problems. The system accepts a spectral plot in the form of wavelength vs intensity pairs and finds the emission peaks in the spectrum, lists the elemental emitters present in the data and deduces the emitter that produced each peak. The system consists of a conventional language component and a commercially available inference engine that runs on an Apple Macintosh computer. The expert system has undergone limited preliminary testing. It detects elements well and significantly decreases analysis time.
This viewgraph presentation gives an overview of laser ignition technology for bipropellant rocket engines applications. The objectives of this project include: (1) the selection test chambers and flows; (2) definition of the laser ignition setup; (3) pulse format optimization; (4) fiber optic coupled laser ignition system analysis; and (5) chamber integration issues definition. The testing concludes that rocket combustion chamber laser ignition is imminent. Support technologies (multiplexing, window durability/cleaning, and fiber optic durability) are feasible.
Spectral radiance of rocket exhaust plumes at high altitudes
Relative erosion resistance of ablative materials for nozzle sections of storable-propellant rocket engine
Effect of turbulent mixing on average fuel temperatures in gas-core nuclear rocket engine