Vacuum technology and space simulation
Manual on vacuum technology and space simulation
PRESSURE GAUGE↗
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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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An application of pressure division for calibrating ionization gauges
Pressure-division system for vacuum ionization gauge calibration
PRESSURE APPARATUS↗
Foam-in-place dielectric materials for embedment of aircraft and space vehicle electronic networks operating at 3000 volts.
Rigid polyurethane foam encapsulation of high- voltage aerospace electronic systems, noting vacuum effect
DIELECTRIC MATERIAL↗
Out of vacuum electron beam welding
Explore the source record for details and available documents.
ELECTRON BEAM WELDING↗
Study of low pressure application of the orbitron
Evaluation of low pressure performance of orbitron ionization gauge
LOW PRESSURE CHAMBER↗
Ultrahigh vacuum produced by a combination of turbomolecular and titanium sublimation pumping.
Ultrahigh vacuum produced by combination of turbomolecular and titanium sublimation pumping
VACUUM SYSTEM↗
Angular distribution of flow from orifices and tubes at high Knudsen numbers.
Cesium vapor flow from orifices and tubes into vacuum analyzed, noting dependence of angular distribution and center line intensity on Knudsen numbers
KNUDSEN NUMBER↗
Space evacuation of NRC-2 insulation for liquid hydrogen tankage.
Space evacuation of NRC-2 insulation for liquid hydrogen tankage, noting vacuum test apparatus and cold plate test
THERMAL INSULATION↗
The venting of saturated liquids in zero gravity.
Vacuum vaporization of saturated liquids on weightlessness, showing that separated bubbles remain in nucleation sites
WEIGHTLESSNESS↗
Molecular sink.
Molecular sink for simulated testing of spacecraft components noting vessel construction, vacuum pump system, molecular trap array, etc
MOLECULAR PUMP↗
A double-guarded cold-plate thermal- conductivity apparatus.
Double-guarded cold plate apparatus for measuring thermal conductivity of multilayer insulations, powders, fibers and foams
THERMAL INSULATION↗
Antechamber facilitates loading and unloading of vacuum furnace
Antechamber facilitates the use of a furnace in which materials are heat treated in a high vacuum or a gas atmosphere. It has a high vacuum pumping system, a means for backfilling with a selected gas, an access door, glove ports, and a motor driven platform.
Kramer, P. J.↗
Solar cell cover glass development Quarterly technical progress report, 1 Oct. 1967 - 1 Apr. 1968
Development and optimization of high vacuum sputtering system for fabrication of thick integral coverslips for silicon solar cells
Source record↗
Automatic controls for facilities and mercury ion thrusters in durability testing.
Mercury ion thrusters and facilities automatic controls durability testing, discussing vacuum chamber systems, unattended operation and control
Nichols, C. R.↗
Certain problems with regard to the use of acceletrons /mechanically controlled vacuum tubes/ in designing moving systems, and the prospects of using them in medicine
Acceletron use for recording physiological functions
Yegorov, A. V.↗
Automatic controls for facilities and Mercury ion thrusters in durability testing.
Mercury ion thrusters and facilities automatic controls durability testing, discussing vacuum chamber systems, unattended operation and control
Nichols, C. R.↗
Open-celled polyurethane foam
Open-celled polyurethane foam has a density of 8.3 pounds per cubic foot and a compressive strength of 295 to 325 psi. It is useful as a porous spacer in layered insulation and as an insulation material in vacuum tight systems.
Russell, L. W.↗
Space simulation experiments on reaction control system thruster plumes.
A space simulation procedure was developed for studying rocket plume contamination effects using a 5-lb bipropellant reaction control system thrustor. Vacuum chamber pressures of 0.00003 torr (70 miles altitude) were achieved with the thrustor firing in pulse trains consisting of eight pulses - 50 msec on, 100 msec off, and seven minutes between pulse trains. The final vacuum was achieved by cooling all vacuum chamber surfaces to liquid-helium temperature and by introducing a continuous argon leak of 48 std. cc/sec into the test chamber. Fast time response liquid flow rate measurements showed that large variations occurred in the ratio of oxidizer to fuel flow for pulse-on times up to 120 msec. These variations could lead to poor combustion efficiency and the production of contamination.
Cassidy, J. F.↗