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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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Performance tests and characteristics of short length, double annular ram induction turbojet combustion chambers for supersonic flight
Simulation of nozzle environment in gas core nuclear rocket with induction coupled arc plasma system
Induction heating of metallurgical specimens to high temperatures in coil furnace
Automatic power supply circuit design for driving inductive loads and minimizing power consumption including solenoid example
Radiation measurements, low frequency, and high pressure investigations of induction heated plasma torch to simulate gas core nuclear rocket requirements
Double-induction variable speed system for constant-frequency electrical power generation
Vortex and coaxial flow of argon and helium plasmas heated inductively, and strong magnetic field effects on turbulent plasma mixing, for gas core reactors
Electron-cyclotron wave resonance in inductively coupled HF ring discharges
Induction plasma calcining of pigment particles for thermal control coatings on space vehicles
Hydrogen-oxygen induction period kinetics behind shock waves, monitoring OH concentration by UV line absorption method
Magnetically coupled tunnel diode oscillator with square loop core, calculating leakage and source inductances effect on switching pattern
Induction and wave drag due to Alfven waves on long cylindrical satellite in ionosphere, investigating radiated power integral
Pure superconducting Al wire surface inductance measurement as function of temperature, noting penetration depth value
Continuing research has resulted in significant advances in induction-heated plasma torch technology which extend and enhance its potential for broad range of uses in chemical processing, materials development and testing, and development of large illumination sources. Summaries of these advances are briefly described.
Circuit, based on use of power transistors which do not display second breakdown under valve loading, drives inductive loads. Peak voltages, power dissipations, heat sink requirements, and thermal stability considerations can be obtained by theoretical analysis.
Induction plasma heating techniques were studied for calcining zinc orthotitanate particles for use in thermal control coatings. Previous studies indicated that the optimum calcining temperature is between 1400 and 1750 C. An intermediate temperature (1670 C) was chosen as a reference point for running a temperature series at the reference point and 220 C on both sides. The effect of varying chamber temperature on the reflectance spectra, before and after vacuum UV irradiation, is presented. The correlation between Zn2Ti04 paramagnetic resonance activity and its susceptibility to vacuum UV damage is discussed.
Three induction-coupled plasma torches were operated at 9600 Hz to determine specific operating parameters and supply data for gas core nuclear rocket simulation studies. Two air-cooled torches, one 16 cm in diameter and one 30 cm in diameter, and a water-cooled torch 14 cm in diameter, were tested. Complete energy balances for the operating systems were obtained during operation. A series of operating points, including pressures from 30 torr to 1 atmosphere, power levels up to 343 kw, and gas flows from 1.1 to 35 g/sec, were documented. Complete operating data for approximately thirty runs are presented, along with graphs of significant operating parameters.
A test program was conducted to evaluate the altitude relight capabilities of a short-length, double-annular, ram-induction combustor which was designed for Mach 3 cruise operation. The use of distorted inlet-air flow profiles was tried to evaluate their effect on the relight performance. No significant improvement in altitude relight performance was obtained with this approach. A study was also made to determine the effects of the reference Mach number, the fuel temperature, and the fuel volatility (ASTM-A1 against JP-4) on the altitude relight performance. Decreasing the reference Mach number, increasing the fuel temperature, and using more volatile fuel all decrease the combustor pressure necessary for relight.