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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 199 records · Page 11
All sourcesNASA NTRSDOE OSTI
NASA NTRS1972

Two-stage magnetometer measures weak magnetic fields

Sensitive magnetometer capable of measuring field strengths of 10 nanogauss is described. High permeability core is aligned parallel to magnetic field in first stage. In second stage, ferromagnetic toroid saturates rapidly. Adjustment of turns and area ratios of each stage provides wide range of sensitivities.

Buntenbach, R. W.↗
NASA NTRS1971

Experiment M405: Tri-axis flux gate magnetometer

A tri-axis flux-gate magnetometer was used on four Gemini spacecraft for determination of the magnitude and direction of the local geomagnetic field with respect to the spacecraft. Conclusions derived from the data are not only important to the proton-electron spectrometer experiment, but also are of significance to any directional charged particle experiments that may be conducted. Even though the Gemini spacecraft was not clean magnetically, the data could be reduced to a form that supplied directional information on the magnetic field in relation to the spacecraft. Stray fields were the result of spacecraft structure, not the result of current flows that were produced within the spacecraft electrical systems. Efforts were made to reduce spacecraft stray fields and to facilitate the acquisition of more accurate data.

Womack, W. D.↗
NASA NTRS1971

Lunar conductivity models from the Apollo 12 magnetometer experiment

A number of conductivity models were investigated for compatibility with Apollo 12 magnetometer data. Except at the highest frequencies, a simple core-crust model is compatible with the observed dayside transfer function, which is expressed as the ratio of the lunar surface field spectrum to the interplanetary magnetic field spectrum. All conductivity profiles exhibit a peak near 1500 km, when the models are constrained to conform to the observed flat response at the higher frequencies. However, at frequencies above .01 Hz the long wavelength limitation of the theoretical model is no longer valid. A plausible explanation for the difference between the north-south and east-west transfer functions is that it is due to a time-varying compression of the remanent (dc) field at the Apollo 12 site by fluctuations in the solar wind plasma.

Sill, W. R.↗
NASA NTRS1971

Reduction and analysis of magnetometer data from Mariners 4 and 5

In studies of data from the Mariner 4 and Mariner 5 magnetometers evidence has been found that during the flights, negative (toward the sun) polarity dominated at latitudes above the solar equatorial plane and positive polarity dominated at latitudes below this plane. A subsequent check of data taken with other spacecraft during 1964 through 1967 provided additional evidence of this effect. It is suggested that the dominant polarity of the interplanetary magnetic field follows the hemisphere-dependent dipolar field of the sun. Thus, the photospheric dipolar field may be an important source of the interplanetary magnetic field, especially at quiet times. It has also been found that, for an interplanetary magnetic field of a given polarity, the north-south component has a nonzero mean value in regions above and below the solar equatorial plane.

Source record↗
NASA NTRS1972

Superconducting rock magnetometer system

A three axis magnetometer system intended for use in the magnetic measurement of lunar rock samples was designed, fabricated and delivered to NASA Manned Spacecraft Center. The system has a four inch diameter room temperature sample access region and is fitted with three orthogonal magnetic field sensors enclosing this region. Two superconducting magnetic shields are incorporated, which are designed to eliminate external magnetic noise from the sense coils. A superconducting solenoid is mounted coaxially with the sample region and this provides axial magnetic fields up to 1,000 gauss. The system was designed for measuring magnetic moments of geophysical samples, especially remanent moments of lunar samples. The sensitivity of the system in all three axes is about 2 x 10 to the -7th power EMU square root HZ peak to peak, measured in the 0 to 1 Hz bandwidth.

Source record↗
NASA NTRS1970

Lunar surface magnetometer design review

Design and fabrication parameters of a lunar surface magnetometer are discussed. Drawings and requirements for mechanical design, electronic packaging design, thermal design, quality assurance and systems testing are included.

Source record↗
NASA NTRS1972

Determination of sounding rocket position and attitude from radar and magnetometer data

The techniques are described that were used to determine the trajectories and orientations of three sounding rockets instrumented to study the aurora. The radar plot board data were fitted to a near earth expansion of the force of gravity to determine the trajectory. Only onboard magnetometer data were used to determine the attitude of the payload with respect to the earth's magnetic field. Computer programs in the FORTRAN language are available which generate the trajectory and attitude parameters.

Pongratz, M.↗
NASA NTRS1971

A pressure scanning Fabry-Perot magnetometer.

Description of an oscillating magnetic analyzer (KDP crystal plus Glan-Thompson prism) coupled to an echelle-interferometer spectrograph, and of single-slit magnetometer which by pressure variations can be made to scan the entire profiles of the circularly and linearly polarized Zeeman components. Freon gas is used as the scanner gas with wavelength displacements of 0.02 A per 0.1 in. Hg pressure change at the NaD lines. The available scan range is 15 A in the visual spectral region.

Fay, T. D.↗
NASA NTRS1972

A variable conductance heat pipe/radiator for the lunar surface magnetometer.

The device was developed to supplement the existing cooling system of the Apollo 16 Lunar Surface Magnetometer (LSM). Analysis and tests showed that two such devices, inserted by an astronaut into receptacles on opposite sides of the electronics package, would reduce the diurnal temperature variation by about 40% and thereby would considerably increase the reliability of 50,000 welded connections. The LSM design constraints, selection of a variable conductance technique, heat pipe/radiator design features, and thermal performance are discussed.

Kirkpatrick, J. P.↗