A resonance igniter for hydrogen-oxygen combustors
Resonance ignition technique for gaseous oxygen and hydrogen rocket propellants
Conrad, E. W.↗
SEARCH · Search NASA
Results for “IGNITION”
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.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
Characteristics of solid propellant motor aft- end ignition
Aft-end igniter design and placement for solid propellant rocket motors avoiding overpressurization and nozzle pressure oscillations
Fitch, R. E.↗
Dynamics of arc ignition and cathode spot movement of thermionically emitting cathode surfaces
Arc ignition and cathode spot movement dynamics of thermionically emitting cathode surfaces in heat feedback plasma
Cheng, D. Y.↗
Ignition system for space shuttle auxiliary propulsion system Quarterly technical progress narrative, 29 Jun. - 27 Sep. 1970
Design of spark and plasma pulse igniters for space shuttle propulsion system
Rosenberg, S. D.↗
Method of igniting solid propellants Patent
Method for igniting solid propellant rocket motors by injecting hypergolic fluids
Allen, H., Jr.↗
Review of factors affecting ignition of metals in high pressure oxygen systems
Factors affecting ignition of metals in high pressure oxygen systems
Kimzey, J. H.↗
Solid rocket motor igniters. NASA space vehicle design criteria, chemical propulsion
Design approach for solid propellant rocket igniters
Source record↗
The investigation of flame spreading over the surface of igniting solid propellants Final summary report
Flame spreading over surface of igniting solid propellants in different gas mixtures at various pressures
Magee, R. S.↗
Flame spreading over the surface of igniting solid rocket propellants and propellant ingredients, part 4
Flame spreading over surface of igniting solid rocket propellants at different pressures, and oxygen-nitrogen mixtures
Horowitz, F. A.↗
Advanced ignition systems
Low cost, lightweight ignition system for hydrogen oxygen engine system incorporating multicombustor thrust chambers
Source record↗
Analytical study of the steady-state behavior of a hydrogen-oxygen catalytic ignition system
Hydrogen-oxygen catalytic ignition system steady state model for predicting temperature and concentration profiles
Kesten, A. S.↗
Shock-wave ignition of liquid fuel drops
Shock wave ignition of liquid fuel drop in oxidizing atmosphere, discussing combustion process
Kauffman, C. W.↗
Ignition temperature of metals in oxygen atmospheres
Metals bulk ignition temperature in oxygen atmospheres, emphasizing preignition surface oxidation effects
Glassman, I.↗
On the shock-induced ignition of explosive gases
Shock induced ignition in explosive homogeneous hydrogen-oxygen gaseous mixtures
Meyer, J. W.↗
Experimental burning rates of single laser- ignited beryllium droplets
Burning rates of single laser ignited beryllium droplets, considering particle size effect
Prentice, J. L.↗
Coherence theory of the strong ignition limit
Coherence theory of strong shock induced explosive gas ignition limit
Meyer, J. W.↗
Design criteria monograph on solid rocket motor igniters
Summary of large and loosely organized body of existing successful design techniques and practices for solid rocket motor igniters is presented.
Source record↗
Rocket propulsion by thermonuclear micro-bombs ignited with intense relativistic electron beams.
Discussion of a method for the ignition of a thermonuclear microbomb by means of an intense relativistic electron beam with regard to its potential application to rocket propulsion. With such a system, exhaust velocities up to 1000 km/sec, corresponding to a specific impulse of 100,000 sec, seem to be within the realm of possibility. The rocket is propelled by a chain of thermonuclear microbombs exploded in a concave magnetic mirror produced by superconducting field coils. The magnetic pressure of the field reflects the fireball generated by the explosion. For the large capacitor bank required to generate the intense relativistic electron beam, a desirable lightweight design may be possible through use of ferroelectric materials. Because of the high cost of the T-D and He 3-D thermonuclear material, the system has to be optimized by minimizing the T-D and He 3-D consumption by a proper TD and He 3-D fuel to hydrogen propellant mass ratio, leading to a larger total system mass than would be absolutely necessary.
Winterberg, F.↗