Experimental evaluation of a two-directional electron-bombardment ion thrustor.
Electron bombardment ion thrustors with two accelerator-grid systems for producing ion beams in directions 180 or 90 degrees apart
THRUST CONTROL↗
Engineering topics
Kerslake, W. R.
Publications and source records attributed to Kerslake, W. R..
The distribution of neutral atoms and charge-exchange ions downstream of an ion thrustor
Distribution of neutral atoms and charge exchange ions downstream of ion thrustor
NEUTRAL PARTICLE↗
Preliminary operation of oxide-coated brush cathodes in electron-bombardment ion thrustors
Experimental results with oxide film coated brush cathodes in electron bombardment yielding longer thrustor lifetime
OXIDE FILM↗
A mercury electron-bombardment ion thrustor suitable for spacecraft station keeping and altitude control
Mercury electron bombardment ion thrustor with radial flow propellant distributor for spacecraft attitude control
MERCURY /METAL/↗
Combustion of gaseous hydrogen at low pressures in a 35 deg sector of a 28-inch-diameter ramjet combustor
Shrouded fuel injector for low pressure hydrogen combustion in high-altitude ramjet engine
HYDROGEN FUEL↗
Tests with hydrogen fuel in a simulated afterburner
Hydrogen fuel combustion analysis in simulated afterburner
COMBUSTION↗
A Method for Prevention of Screaming in Rocket Engines
Lateral and longitudinal combustion-pressure oscillations that occurred in screaming combustion of a 1000-pound-thrust rocket engine using white fuming nitric acid and JP-4 fuel as propellants were successfully prevented by means of longitudinal fins in the combustion chamber. Fin position was critical, and complete attenuation was achieved only when the fins were located in a zone approximately 8 to 16 inches from the injector. Fins located in other zones, that is, near the injector or far downstream from the injector, did not stop the oscillations. When oscillations occurred in finned chambers, the longitudinal mode seemed more dominant than the lateral mode; in chambers without fins, the lateral mode tended to be dominant. The lateral oscillation was distorted and its intensity diminished by the fins. Fins, however, did not affect the frequencies; the longitudinal frequency varied inversely with chamber length, and lateral frequencies varied only slightly from an average of 6000 cycles per second.
ROCKET ENGINE NOISE↗