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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 397 records · Page 22
All sourcesNASA NTRSDOE OSTI
NASA NTRS1970

Motor brush wear measured with strain gages

Balanced bridge circuit, supplied with low-voltage direct current and connected to a readout device, measures remaining brush material, rate of brush wear, armature runout, and brush signature.

Farrell, W. T.↗
NASA NTRS1971

CSM programs SM RCS propellant quantity gaging systems program

Computer program calculates actual and useable remaining propellant quantities as required in positive expulsion rocket engine propellant feed system. Program establishes relationship between helium system pressures and temperatures and propellant weight remaining in tanks. Program is written in FORTRAN 4 for IBM-360 computer.

Cox, G. R.↗
NASA NTRS1971

Ultra thin gage plastic film

Process utilizing specially modified conventional equipment, with changes in process temperature, pressure, and cooling requirements produces ultra thin 1.56 micron /0.0614 mil/ thick polyethylene film.

Cox, D. W., Jr.↗
NASA NTRS1972

Neutral density measurements near 400 kilometers by a microphone density gage on Ogo 6 during July 12-15, 1969.

Analysis of persistent density peaks (maxima) measured near 400 km during daytime (1425 LT) by a microphone density gauge on Ogo 6 during July 12 to 15, 1969. Most of the density peaks occurred between geomagnetic latitudes 50 and 61 N and L values 2.3 and 4.7. The average density change in the peaks was 27%. Most of the peaks appeared in the longitude sector from 150 to 350 E. No density peaks were measured in the 50 to 130 E sector during the 3-1/2 day observation period. A persistent pair of density peaks was present on seven successive orbits during July 13 and July 14 (both geomagnetically disturbed days) near geomagnetic latitudes 53 and 61 N, respectively.

Anderson, A. D.↗
NASA NTRS1972

Piston manometer as an absolute standard for vacuum-gage calibration in the range 2 to 500 millitorr

A thin disk is suspended, with very small annular clearance, in a cylindrical opening in the base plate of a calibration chamber. A continuous flow of calibration gas passes through the chamber and annular opening to a downstream high vacuum pump. The ratio of pressures on the two faces of the disk is very large, so that the upstream pressure is substantially equal to net force on the disk divided by disk area. This force is measured with a dynamometer that is calibrated in place with dead weights. A probable error of + or - (0.2 millitorr plus 0.2 percent) is attainable when downstream pressure is known to 10 percent.

Warshawsky, I.↗
NASA NTRS1972

Piston manometer as an absolute standard for vacuum gage calibration in the range 10 to 700 microtorr

Total pressure in a calibration chamber is determined by measuring the force on a disk suspended in an orifice in the baseplate of the chamber. The disk forms a narrow annular gap with the orifice. A continuous flow of calibration gas passes through the chamber and annulus to a downstream pumping system. The ratio of pressures on the two faces of the disk exceeds 100:1, so that chamber pressure is substantially equal to the product of disk area and net force on the disk. This force is measured with an electrodynamometer that can be calibrated in situ with dead weights. Probable error in pressure measurement is plus or minus (0.5 microtorr + 0.6 percent).

Warshawsky, I.↗
NASA NTRS1973

Strain gage installation on the YF-12 aircraft.

A flight-loads measurement program on the YF-12 aircraft required the mounting of 101 strain-gauge bridges in the fuselage, fuel tanks, control surfaces, and three stations on the left wing. The sensors were to be installed primarily on titanium and were required to operate between -70 and +600 F. Strain gauges with modified Karma filaments and backings of glass-fiber reinforced epoxy resin matrices were selected and were installed with an epoxy adhesive. Attention is given to the calibration, mounting, and performance of the sensors in flight-load measurements.

Wilson, E. J.↗
NASA NTRS1973

In situ transfer standard for ultrahigh vacuum gage calibration

A compact insitu calibration assembly, for ultrahigh vacuum gauges is described. The system depends on the repeatable generation of a specific gas pressure by the dissociation of a solid solution chemical compound when subjected to a given temperature. A precise temperature measurement is related to the pressure generated within the vacuum by the properties of the solid solution compound. this accurately establishes the gas pressure which in turn is used to calibrate a vacuum gauge. Also included is a metering orifice used in the calibration system and which is made movable to facilitate the degassing bakeout required in ultrahigh vacuum devices.

Outlaw, R. A.↗
NASA NTRS1976

High Temperature Strain Gage Calibration Fixture

An apparatus and method are described for calibrating high temperature strain gases which serve for both dead weight and constant deflection measurements. A cantilever support arm allows the test unit to slide into a furnace while one end is subjected to bending strain either by hanging weights upon it or by deflecting it with a push rod. The dual nature of the fixture permits both tests to be run without change of the test specimen or removal from the furnace.

Vranas, T.↗
NASA NTRS1977

Attaching strain gages by ultrasonic plastic welding

Technique employs application of pressure and ultrasound to effect welding of encapsulated strain gates to metallic surfaces. Process requires no heat or adhesives. Technique might also be used to simplify curing of epoxy adhesives and for attachment problems like bonding cryogenic temperature sensors to structural parts.

Sheppard, A. T.↗