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NASA NTRS1973

An unusual meteor spectrum

An extraordinary spectrum of a meteor at a velocity of about 18.5 + or - 1.0 km/s was observed with an image orthicon camera. The radiant of the meteor was at an altitude of about 49 deg. It was first seen showing a yellow red continuous spectrum alone at a height of 137 + or - 8 km which is ascribed to the first positive group of nitrogen bands. After the meteor had descended to 116 + or - 6 km above sea level it brightened rapidly from its previous threshold brightness into a uniform continuum, the D-line of neutral sodium appeared, and at height 105 + or - 5 km all the other lines of the spectrum also appeared. The continuum remained dominant to the end. Water of hydration and entrained carbon flakes of characteristic dimension about 0.2 micron or less are proposed as constituents of the meteoroid to explain these phenomena.

Cook, A. F.↗

NASA NTRS1974

Design, fabrication, and test of lightweight shell structure

A cylindrical shell skirt structure was subjected to a design and analysis study using a wide variety of structural materials and concepts. The design loading, axial compression, and torsion is representative of that expected on a typical space tug skirt section. Structural concepts evaluated included honeycomb sandwich, truss, isogrid, and skin/stringer/frame. The materials considered included a wide variety of structural metals as well as glass, graphite, and boron-reinforced composites. Honeycomb sandwich with aluminum faceskins, honeycomb sandwich with graphite/epoxy faceskins, and aluminum truss with fiberglass meteoroid protection layers were the designs selected for further evaluation. Procurement of materials required for fabrication is reported and the structural test plan and fabrication drawings are included. Construction of the graphite/epoxy faceskins, chem mill of the aluminum faceskins, chem mill of aluminum truss components, and fabrication of the graphite/epoxy honeycomb sandwich development panel is also reported.

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NASA NTRS1974

MSFC Skylab Orbital Workshop, volume 1

The technical aspects of the Skylab-Orbital Workshop are discussed. Original concepts, goals, design philosophy, hardware, and testing are reported. The final flight configuration, overall test program, and mission performance are analyzed. The systems which are examined are: (1) the structural system, (2) the meteoroid shield systems, and (3) the environmental/thermal control subsystem.

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NASA NTRS1973

Estimates of the size of the particles in the rings of Saturn and their cosmogonic implications

Observations are discussed which are consistent with the ring particles having a very high single scattering albedo at radio wavelengths, with multiple scattering effects being important. Comparison of scattering calculations for ice and silicate particles with the radio and radar observations imply a mean particle radius of about 1 cm. The ice bands observed in the near-infrared reflectivity spectra of the rings are formed by scattering within a microstructure on the surface of the ring particles, with the scattering centers being 25 to 125 micrometers in size. The Poynting-Robertson effect has caused a significant spiraling-in of the ring particles, probably resulting in a broadening of the rings. The inferred mean size is consistent with a model in which meteoroid impacts have caused a substantial reduction in the mean particle size from its initial value.

Pollack, J. B.↗

NASA NTRS1973

Velocity structure and evolution of the moon

Seismic data from the Apollo Passive Seismic Network stations are analyzed to determine the velocity structure and to infer the composition and physical properties of the lunar interior. Data from artificial impacts (SIBV booster and LM-ascent stage) cover a distance range of 9 to 1750 km. Travel times and amplitudes, as well as theoretical seismograms, are used to derive a velocity model for the outer 150 km of the moon. The P-wave velocity model confirms an earlier report of a lunar crust in the eastern part of Oceanus Procellarum. The crust is about 60 km thick and may consist of two layers in the mare regions. Possible values for the P-wave velocity in the uppermost mantle are between 7.6 and 9.0 km/sec. The 9 km/sec velocity represents either a localized heterogeneous unit, or a thin layer less than about 40 km in thickness. The elastic properties of the deep interior, as inferred from the seismograms of natural events (meteoroid impacts and moonquakes) occurring at great distances, indicate that there is an increase in attenuation and a possible decrease of velocity at depths below about 1000 km.

Toksoz, M. N.↗

NASA NTRS1974

Strongly differentiated material in high-inclination and retrograde orbits

Two definitive spectra of strongly differentiated meteors are discussed. The meteors entered the earth's atmosphere at velocities greater than 40 km/sec from high-inclination and retrograde orbits. Both were magnesium-calcium particles, and their spectra show them to be highly deficient in iron and sodium. The moon and the asteroids have been discussed as sources of such calcium-rich achondrites, but these sources give low or intermediate geocentric velocities. Long-period comets and meteoroids of probable cometary origin are the only objects now known to have orbits similar to the orbits of these two meteors.

Harvey, G. A.↗

NASA NTRS1974

MSFC's utilization of existing design technology in the Skylab program

In the design of Skylab use was made in a number of cases of technological experience obtained in connection with earlier phases of the space program. In the development of the payload shroud use was made of Saturn V flight data. The shroud thrusting joint system was an adaptation of a system flown on the Titan IIIC. Scientific airlock hardware for Skylab was available from the Apollo Program. The design of the Orbital Workshop was based on the technology base provided by Saturn programs. Details regarding the repair tools used for correcting orbital workshop meteoroid shield/solar array anomalies which occurred during the ascent are discussed along with a commercial concept for coolant resupply, giving attention to aid provided by already existing technological developments.

Eudy, R. G.↗

NASA NTRS1974

Magnetogasdynamic compression of a coaxial plasma accelerator flow for micrometeoroid simulation

A new configuration of a coaxial plasma accelerator with self-energized magnetic compressor coil attached is described. It is shown that the circuit may be treated theoretically by analyzing an equivalent circuit mesh. The results obtained from the theoretical analysis compare favorably with the results measured experimentally. Using this accelerator configuration, glass beads of 125 micron diameter were accelerated to velocities as high as 11 kilometers per second, while 700 micron diameter glass beads were accelerated to velocities as high as 5 kilometers per second. The velocities are within the hypervelocity regime of meteoroids.

Igenbergs, E. B.↗

NASA NTRS1974

Self-energized plasma compressor

The self-energized plasma compressor is described which compresses plasma discharged from a coaxial plasma generator. The device includes a helically shaped coil which is coaxially aligned with the center axis of the coaxial plasma generator. The plasma generator creates a current through the helical coil which, in turn, generates a time varying magnetic field that creates a force which acts radially upon the plasma. The coaxial plasma generator and helical coil move the plasma under high pressure and temperature to the narrow end of the coil. Positioned adjacent to the narrow end of the coil are beads which are engaged by the plasma to be accelerated to hypervelocities for simulating meteoroids.

Shriver, E. L.↗

NASA NTRS1974

The Sisyphus particle detector

The particle measurement subsystem planned for the MJS 77 mission is described. Scientific objectives with respect to Saturn's rings are as follows: (1) measure particles outside the visible rings, including particulates orbiting in more distant rings and particles scattered out of visible rings, (2) measure meteoroid environment in vicinity of Saturn, and (3) develop an understanding of the dynamics of the rings with respect to their collisional interaction with the environment.

Soberman, R. K.↗

NASA NTRS1975

Design and fabrication of a flexible tunnel for Sortie Laboratory

A program was conducted to update a prototype design and to fabricate a flexible tunnel for a space shuttle/spacelab interface structure. The significant changes in the prototype are as follows: (1) elimination of foam from bladder laminate to increase bladder flexibility, (2) heat treat pulley brackets, bolts, and hinge pin to 160,000 psi minimum tensile strength, and (3) reduction of the meteoroid barrier from 0.5 inch to 0.375 inch. The thermal blanket installation study resulted in developing a method of installation by properly folding the various layers so that a uniform thickness could be maintained under the clamps. A single-lobe mockup was fabricated and cycled open and closed several times with no apparent damage to the blanket.

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NASA NTRS1975

Design, fabrication and test of lightweight shell structure

A cylindrical shell structure 3.66 m (144 in.) high by 4.57 m (180 in.) diameter was designed using a wide variety of materials and structural concepts to withstand design ultimate combined loading 1225.8 N/cm (700 lb/in.) axial compression and 245.2 N/cm (140 lb/in.) torsion. The overall cylinder geometry and design loading are representative of that expected on a high performance space tug vehicle. The relatively low design load level results in designs that use thin gage metals and fibrous-composite laminates. Fabrication and structural tests of small panels and components representative of many of the candidate designs served to demonstrate proposed fabrication techniques and to verify design and analysis methods. Three of the designs evaluated, honeycomb sandwich with aluminum faceskins, honeycomb sandwich with graphite/epoxy faceskins, and aluminum truss with fiber-glass meteoroid protection layers, were selected for further evaluation.

Lager, J. R.↗

NASA NTRS1975

Natural environment design criteria for the Solar Electric Propulsion Stage (SEPS)

The natural environment design criteria are given for six different solar electric propulsion stage missions. These environment data include the neutral atmosphere; ionosphere, trapped radiation; free-space radiation environment; and meteoroid, asteroid, and comet environments. The electromagnetic radiation environment (direct, reflected, or scattered) at the planets and interplanetary regions is also included.

Wright, J. J.↗

NASA NTRS1975

Compaction by impact of unconsolidated lunar fines

New Hugoniot and release adiabat data for 1.8 g/cu cm lunar fines in the approximately 2 to 70 kbar range demonstrate that upon shock compression intrinsic crystal density (approximately 3.1 g/cu cm) is achieved under shock stress of 15 to 20 kbar. Release adiabat determinations indicate that measurable irreversible compaction occurs upon achieving shock pressures above approximately 4 kbar. For shocks in the approximately 7 to 15 kbar range, the inferred post-shock specific volumes observed decrease nearly linearly with increasing peak shock pressures. Upon shocking to approximately 15 kbar the post-shock density is approximately that of the intrinsic minerals. If the present data are taken to be representative of the response to impact of unconsolidated regolith material on the moon, it is inferred that the formation of appreciable quantities of soil breccia can be associated with the impact of meteoroids or ejecta at speeds as low as approximately 1 km/sec.

Ahrens, T. J.↗

NASA NTRS1975

The Relocation of Particulate Contamination During Space Flight

A computer simulation program to model the redistribution of particulate contaminants on a spacecraft after launch is developed. The component models for particulate adhesion, meteoroid impact, and electrostatic forces are described and intermediate results are presented. The results of a sample calculation show that the recontamination process is important.

Barengoltz, J.↗

NASA NTRS1974

Results of the asteroid/meteoroid particle experiment on Pioneer 10 /1.0-3.3 AU/

The asteroid/meteoroid detector (Sisyphus), an optical array to measure particle size and orbit, has been performing successfully on Pioneer 10 since it was initially activated on 9 March 1972. During the first ten months of operation over 200 meteoroid and asteroid events were detected between 1.0 and 3.3 AU. These events are being analyzed to determine the spatial concentration as a function of heliocentric distance. The early results of these analyses are presented with particular emphasis on the distribution in the asteroid belt. Preliminary orbital parameters for some particles which have been analyzed are presented with a discussion of instrumental limitations.

Neste, S. L.↗

NASA NTRS1974

The radial dependence of the zodiacal light

The asteroid/meteoroid detector (Sisyphus) has, in addition to its primary role of detecting and analyzing individual meteoroids, been used for measuring the brightness of the night sky from its platform on board the Pioneer 10 spacecraft. This spacecraft has traversed the asteroid belt and will fly by Jupiter in December 1973. It was quickly found that the brightness of the night sky in the antisolar hemisphere decreased rapidly with increasing distance from the sun. This decrease is due solely to the decrease in the brightness of the zodiacal light. The heliocentric dependence of the zodiacal light has been deduced from several months of data. Some data are shown to illustrate the sensitivity of the instrument to features in the night sky and the technique used for subtracting out the integrated brightness due to starlight is described. Preliminary results showing the decrease of the zodiacal light with solar distance is not inconsistent with an inverse square dependence.

Zook, H. A.↗

NASA NTRS1974

Flight operations and performance of Skylab life support and environmental control systems

The design and performance of the Skylab thermal and environmental control systems is considered. The Orbital Workshop had a combined active and passive thermal control system. The refrigeration system was designed to store food and biomedical samples and to cool drinking water. The atmosphere control system included active humidity control, molecular sieves and charcoal canisters to control carbon dioxide, odor, and contaminants, and the gas supply system. Mission support preparation, including instrumentation, ground data system, system troubleshooting, and training, is surveyed. Major in-flight anomalies occurred with the thermal control system when the meteoroid shield was lost during SL-1 ascent and when the Airlock Module coolant loop malfunctioned during SL-2 manned operations. The atmosphere control system performed without major anomaly throughout the manned missions.

Hopson, G. D.↗