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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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At least 73 records · Page 4

All sources NASA NTRS DOE OSTI

NASA NTRS1963

TEST RESULTS FOR A CESIUM ELECTRON BOMBARDMENT ION MOTOR

Experimental study of an electron bombardment ion motor using cesium as an expellant

ELECTRON BOMBARDMENT↗

NASA NTRS1963

STUDIES OF A LEWIS TYPE BOMBARDMENT ION ENGINE

Performance and design of the lewis-type electron bombardment ion engine

ELECTRON BOMBARDMENT↗

NASA NTRS1963

PROBE MEASUREMENTS OF THE DISCHARGE IN AN OPERATING ELECTRON BOMBARDMENT ENGINE

Properties of the plasma inside an operating kaufman-type electron bombardment engine, with langmuir probes

LANGMUIR PROBE↗

NASA NTRS1963

AN ELECTRON-BOMBARDMENT ION ROCKET WITH A PERMANENT MAGNET

Utilization of a permanent magnet circuit in an electron-bombardment ion rocket

IONIC PROPULSION↗

NASA NTRS1963

PROBE MEASUREMENTS OF THE DISCHARGE IN AN OPERATING ELECTRON BOMBARDMENT ENGINE

Experimental investigation of the properties of the plasma inside an operating kaufman-type electron bombardment engine, with langmuir probes

LANGMUIR PROBE↗

NASA NTRS1963

TWO-COMPONENT MICROBALANCE FOR MEASURING THE FORCES ON ION-BOMBARDED SURFACES

Ion bombardment forces on flat metal plate measured by two-component microbalance based on attracted disk electrometer principle

METAL PLATE↗

NASA NTRS1963

THE ELECTRON-BOMBARDMENT ION ROCKET

Proposed electron bombardment ion rocket, discussing ion chamber, magnetic field, cathode, accelerator and neutralizer in terms of spacecraft power requirements

PROPULSION CONFIGURATION↗

NASA NTRS1963

ELECTRON BOMBARDMENT ION SOURCE

Electron bombardment of propellant gas using a mercury ion source

ELECTRON BOMBARDMENT↗

NASA NTRS1963

Two-component microbalance for measuring the forces on ion-bombarded surfaces

Two-component microbalance for measuring forces on ion-bombarded surfaces

MICROBALANCE↗

NASA NTRS1964

Experimental Evaluation of Steady-State Control Properties of an Electron-Bombardment Ion Thrustor

Examined in this report are the experimental steady-state gains, or changes, in beam-current output with changes in thrustor inputs for a 10-centimeter-diameter electron-bombardment ion thrustor. A general leveling off of beam current as a function of an input variable was found at the upper range of each variable, At the design operating point, the filament-heating current exhibited the greatest sensitivity, or percentage beam-current output change for a percentage change in the input (2 to 4). Accelerator voltage showed the least effect (0.04) while discharge voltage, magnetic field, and neutral propellant flow exhibited about the same sensitivity (0.4 to 0.5). Some effects of nonlinearity are shown that may require consideration in the design of a closed-loop control system.

CONTROL↗

NASA NTRS1963