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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 217 records · Page 12
All sourcesNASA NTRSDOE OSTI
NASA NTRS1982

The origin of the Kirkwood gaps - A mapping for asteroidal motion near the 3/1 commensurability

A mapping of the phase space onto itself with the same low-order resonance structure as the 3/1 commensurability in the planar-elliptic restricted three-body problem is obtained. This mapping is about 1,000 times faster than the usual method of numerically integrating the averaged equations of motion. It exhibits some surprising behavior that might provide a key to the origin of the Kirkwood gaps. It is noted that a test asteroid placed in the gap may evolve for a million years with low eccentricity (less than 0.05) and then suddenly jump to large eccentricity (greater than 0.3), becoming a Mars crosser. The removal of the asteroid by a close encounter with Mars would then be possible. As a first test of this hypothesis, a distribution of 300 test asteroids in the area of the 3/1 commensurability was evolved for two million years. When the Mars crossers are removed, the distribution of initial conditions reveals a gap at the location of the 3/1 Kirkwood gap.

Wisdom, J.↗
NASA NTRS1987

Significance of foundation-soil separation in dynamic soil-structure interaction

THe dynamic response of flexible surface strip-foundations allowed to uplift is numerically obtained for externally applied forces of a transient time variation. The soil medium is represented by an isotropic, homogeneous and linear half-space. The soil is treated by a time domain boundary element method, while the flexible foundation is treated by the finite element method. It was concluded that intermediate relative stiffness leads to moderate deformations when uplift is permitted. Very flexible footings produce higher deformations in unilateral contact compared to bilateral contact, and thus should be considered in their design. Unilateral contact does not significantly increase deformations for stiff footings subjected to concentrated central loading. However, relatively large deformation differences occur when the loading is eccentric, necessitating consideration of uplift in their design.

Spyrakos, Constantine C.↗
NASA NTRS1991

Neuromuscular aspects in development of exercise countermeasures

The paper reviews data obtained at the Human Life Sciences Research Program at the Kennedy Space Center on the structural and functional characteristics of the human muscle and on the effects of simulated microgravity (head-down bed rest) and exercise on the muscle. It is shown that prolonged exposure to microgravity induced ultrastructural abnormalities and the atrophy of muscle and impaired muscle functioning (especially upon return to terrestrial gravity) and that ground-based models can be effectively used to study these changes. Results indicate that the incorporation of resistive exercise with a strong emphasis on the use of eccentric muscle action, in addition to concentric action, may provide a very effective countermeasure against muscle atrophy and dysfunction caused by long-duration exposures to microgravity.

Convertino, Victor A.↗
NASA NTRS2006

Geodesy at Mercury with MESSENGER

In 2011 the MESSENGER (MErcury Surface, Space ENvironment, GEochemistry, and Ranging) spacecraft will enter Mercury orbit and begin the mapping phase of the mission. As part of its science objectives the MESSENGER mission will determine the shape and gravity field of Mercury. These observations will enable the topography and the crustal thickness to be derived for the planet and will determine the small libration of the planet about its axis, the latter critical to constraining the state of the core. These measurements require very precise positioning of the MESSENGER spacecraft in its eccentric orbit, which has a periapsis altitude as low as 200 km, an apoapsis altitude near 15,000 km, and a closest approach to the surface varying from latitude 60 to about 70 N. The X-band tracking of MESSENGER and the laser altimetry are the primary data that will be used to measure the planetary shape and gravity field. The laser altimeter, which has an expected range of 1000 to 1200 km, is expected to provide significant data only over the northern hemisphere because of MESSENGER's eccentric orbit. For the southern hemisphere, radio occultation measurements obtained as the spacecraft passes behind the planet as seen from Earth and images obtained with the imaging system will be used to provide the long-wavelength shape of the planet. Gravity, derived from the tracking data, will also have greater resolution in the northern hemisphere, but full global models for both topography and gravity will be obtained at low harmonic order and degree. The limiting factor for both gravity and topography is expected to be knowledge of the spacecraft location. Present estimations are that in a combined tracking, altimetry, and occultation solution the spacecraft position uncertainty is likely to be of order 10 m. This accuracy should be adequate for establishing an initial geodetic coordinate system for Mercury that will enable positioning of imaged features on the surface, determination of the planet's obliquity, and detection of the librational motion of the planet about its axis.

Smith, David E.↗
NASA NTRS2015

Constraints on the Gas Content of the Fomalhaut Debris Belt: Can Gas-Dust Interactions Explain the Belt's Morphology?

Context. The 440 Myr old main-sequence A-star Fomalhaut is surrounded by an eccentric debris belt with sharp edges. This sort of a morphology is usually attributed to planetary perturbations, but the orbit of the only planetary candidate detected so far, Fomalhaut b, is too eccentric to efficiently shape the belt. Alternative models that could account for the morphology without invoking a planet are stellar encounters and gas-dust interactions. Aims. We aim to test the possibility of gas-dust interactions as the origin of the observed morphology by putting upper limits on the total gas content of the Fomalhaut belt. Methods. We derive upper limits on the CII158 microns and OI 63 microns emission by using non-detections from the Photodetector Array Camera and Spectrometer (PACS) onboard the Herschel Space Observatory. Line fluxes are converted into total gas mass using the non-local thermodynamic equilibrium (non-LTE) code radex. We consider two different cases for the elemental abundances of the gas: solar abundances and abundances similar to those observed for the gas in the Beta Pictoris debris disc. Results. The gas mass is shown to be below the millimetre dust mass by a factor of at least approx. 3 (for solar abundances) respectively approx. 300 (for Beta Pic-like abundances). Conclusions. The lack of gas co-spatial with the dust implies that gas-dust interactions cannot efficiently shape the Fomalhaut debris belt. The morphology is therefore more likely due to a yet unseen planet (Fomalhaut c) or stellar encounters.

Fomalhaut b↗
NASA NTRS1982

Rings of Uranus - A review of occultation results

The structure and orbits of the nine confirmed rings of Uranus are reviewed based on occultation observations from ring discovery in March 1977 through April 1981. Observations of stellar occultations by Uranus have revealed the rings to be characterized by narrow widths (up to 100 km) and sharp edges, with possible internal structure, and to have orbits fitting the coplanar precession model, and showing a decreasing eccentricity with semimajor axis. Occultation results have also allowed the determination of the J2 and J4 coefficients of the Uranian gravity potential, the coordinates of the ring plane pole, planetary equatorial radius and ellipticity and the rotation period. The sharp edges and narrow widths of the rings may be explained by small satellites orbiting near the rings, and the uniform precession of three of the rings is attributed to self-gravity. Future plans for Uranus ring observations include further occultation studies, the Voyager 2 fly-by, and Space Telescope data.

Elliot, J. L.↗
NASA NTRS1992

Libration point staging options for SEI lunar missions - Station keeping implications

Libration point staging is one alternative to lunar orbit rendezvous which is being examined for the Space Exploration Initiative lunar missions. The libration point staging strategy being considered would eliminate the lunar mid-latitude accessibility constraint for long duration missions. Staging options for such a strategy are discussed with particular emphasis on the impact of the libration points' stability. The equations of motion for a satellite at the libration points are numerically integrated to investigate the stability and to determine the station-keeping requirements. These requirements are presented, and overall requirements for libration point staging briefly summarized. The results indicate that the slight eccentricity of the Moon's orbit would result in excessive station-keeping requirements for long duration missions.

Haynes, Davy A.↗
NASA NTRS1992

Galileo and Ulysses dust measurements - From Venus to Jupiter

The Galileo and Ulysses spaceprobes carry two similar dust detectors through interplanetary space from Venus to Jupiter. Impacts are reported which correspond to dust particles above a mass threshold of about 10 exp 13 g for which complete records exist. Between December 1989 and January 1992 Galileo repeatedly traversed interplanetary space between 0.7 and 2.26 AU and recorded 374 impacts. The observed impact rates ranged from 0.1 to about 3 impacts per day strongly dependent on whether the spacecraft moved toward or away from the sun. From October 1990 to January 1992 the Ulysses spacecraft had reached a distance of 5.17 AU from the sun and had recorded 72 impacts at rates between 0.1 and 0.5 per day. Inside about 2 AU the observed fluxes are compatible with a population of interplanetary dust particles moving on low to moderately eccentric and low inclination orbits. Outside this distance a dust particle population on different orbits is required in order to explain the Ulysses data.

Gruen, E.↗
NASA NTRSDate not supplied

Structural Architectures for Self-Erecting Lunar Towers

The load carrying performance for deployable lunar tower architectures utilizing thin-ply composite booms are parametrically evaluated in this paper. These self-erecting towers support a communications and sensor platform on the lunar surface. The primary design consists of the Corrugated Rollable Tubular Boom (COROTUB) acting as the primary mast of the tower which supports the payload tip mass. Guy wires connecting the boom tip to spreader bars attached at the base deployer serve to correct any lateral eccentricities and provide dimensional stability. The analysis compares the maximum tip mass that this primary design can carry relative to a reference design that does not contain any guy wires or spreader bars. The results provide insights into whether the additional system mass and complexity associated with the cable-stayed design is worth the increased payload mass that can be supported. By setting the design limiting condition to a nominal maximum allowable deflection, the analysis reveals that primary design outperforms reference design for the majority of the design space. This outcome is found to be the case when the spreader bar length relative to the tower height exceeds7 a critical value. The analysis is extended to lunar towers with Collapsible Tubular Mast (CTM) booms, and similar trends are observed.

Jacob G Daye↗
NASA NTRSDate not supplied

Structural Architectures for Self-Erecting Lunar Towers

The load carrying performance for deployable lunar tower architectures utilizing thin-ply composite booms are parametrically evaluated in this paper. These self-erecting towers support a communications and sensor platform on the lunar surface. The primary design consists of the Corrugated Rollable Tubular Boom (COROTUB) acting as the primary mast of the tower which supports the payload tip mass. Guy wires connecting the boom tip to spreader bars attached at the base deployer serve to correct any lateral eccentricities and provide dimensional stability. The analysis compares the maximum tip mass that this primary design can carry relative to a reference design that does not contain any guy wires or spreader bars. The results provide insights into whether the additional system mass and complexity associated with the cable-stayed design is worth the increased payload mass that can be supported. By setting the design limiting condition to a nominal maximum allowable deflection, the analysis reveals that primary design outperforms reference design for the majority of the design space. This outcome is found to be the case when the spreader bar length relative to the tower height exceeds a critical value. The analysis is extended to lunar towers with Collapsible Tubular Mast (CTM) booms, and similar trends are observed.

Jacob G Daye↗
NASA NTRS2023

Lunar Solar Occultation Explorer (Lunasox)

In the present decade and beyond, now 51 years after the last Apollo landing, the NASA Artemis human exploration program will offer abundant opportunities for heliophysics investigations from, by, and of the Moon from the vantage points of the lunar orbit and the surface. The Lunar Solar Occultation Explorer (LunaSOX) concept uses the lunar limb to occult the solar disk for high-resolution coronal observations at hourly, daily, to biweekly cadences from spacecraft either in the lunar orbit or at the surface. A 0.2 m diameter solar telescope in orbit with white light and narrow-band visible filters would provide arcsecond spectroscopic imaging of the low-to-high corona (1–10 R☉) with an upper limit of 10 –12 B☉ on the local scattered light background from lunar atmospheric dust, as compared to 10 –9 B☉ for Earth ground-based solar eclipse observations looking up through the atmosphere at totality. For eclipse observations from and by the Moon, there would be no significant atmospheric disturbances that otherwise limit seeing to arcsec resolution from Earth’s surface. The present eccentric orbits of the ARTEMIS P1 and P2 spacecraft are used as models for a 1 × 10 Rm orbit of LunaSOX to compute the times of solar eclipse intervals, up to 2 hours in duration between the east and west solar hemispheres at a daily cadence for coronal observations at 1–16 R☉ when the orbital aposelene is in anti-sunward directions. In a low-altitude circular orbit and from the surface, the observational cadences would, respectively, be hourly and biweekly. LunaSOX satellites also carrying in situ space environment instruments could integrate into a network of orbital platforms for space weather monitoring and communications relay to far-side surface lander and permanent base sites, e.g., for low-frequency radio cosmology and detection of exoplanet magnetospheres.

John F Cooper↗
NASA NTRS2011

Common Warm Dust Temperatures Around Main Sequence Stars

We compare the properties of warm dust emission from a sample of main-sequence A-type stars (B8-A7) to those of dust around solar-type stars (F5-KO) with similar Spitzer Space Telescope Infrared Spectrograph/MIPS data and similar ages. Both samples include stars with sources with infrared spectral energy distributions that show evidence of multiple components. Over the range of stellar types considered, we obtain nearly the same characteristic dust temperatures (∼ 190 K and ∼60 K for the inner and outer dust components, respectively)-slightly above the ice evaporation temperature for the inner belts. The warm inner dust temperature is readily explained if populations of small grains are being released by sublimation of ice from icy planetesimals. Evaporation of low-eccentricity icy bodies at ∼ 150 K can deposit particles into an inner/warm belt, where the small grains are heated to dust Temperatures of -190 K. Alternatively, enhanced collisional processing of an asteroid belt-like system of parent planetesimals just interior to the snow line may account for the observed uniformity in dust temperature. The similarity in temperature of the warmer dust across our B8-KO stellar sample strongly suggests that dust-producing planetesimals are not found at similar radial locations around all stars, but that dust production is favored at a characteristic temperature horizon.

Morales, Farisa↗
NASA NTRS1976

The transient periodic X-ray source in Taurus, A0535+26

Eighteen X-ray light curves of the 104-sec periodicity in the Taurus X-ray nova A 0535+26 are analyzed which were obtained by SAS-3 in six energy intervals between 1 and 35 keV during the period from May 30 to June 2, 1975. It is shown that the pulse structure is relatively simple at energies above 19 keV, but develops a complex series of five irregularly spaced maxima at lower energies. The energy spectrum averaged over the 104-sec period is found to be extremely hard, with a best-fit temperature of about 30 keV for the exponential spectrum, an excess at about 15 keV, and a steepening above 20 keV. It is suggested that A 0535+26 may be a compact object in a binary system containing the peculiar Be star HDE 245770. The transient behavior could arise due to episodic mass loss by the primary or because the compact object is in a highly eccentric orbit about the companion, with appreciable mass transfer occurring only at periastron.

Bradt, H.↗
NASA NTRS1991

Studies in planetary rings

Progress made in research devoted to examining Voyager imaging data for the purpose of understanding the kinematics and dynamics of the Neptune ring arcs is reported. It was found that a radial distortion of amplitude 30 km is traveling through the arcs with a perturbation by the nearby satellite 1989N4. Two new and smaller arcs within the outer Neptunian ring were also discovered. The longitudinal spacing of all arcs is roughly that expected for corotational arc shepherding by 1989N4 provided that not all corotation sites in the arc region are filled. The semimajor axis of the arcs' orbit inferred from their observed mean motion and the latest Neptune gravitational parameters is, within uncertainties, identical to the location of the 42:43 corotation-inclination resonance of 1989N4: an observation which supports the notion of corotational arc-shepherding. This hypothesis also explains that the 15 km radial width of the arcs are due to a spread in forced orbital eccentricities. Clumps within the arcs were observed at a greater frequency than previously reported. These features may be the manifestation of big bodies within the arcs providing a source of ring dust, or they may be a kinematical effect associated with the crossing of eccentric orbits at quadrature. The inclusion of ground based observations of the arcs taken up to five years ago will lengthen the baseline over which arc dynamics may be studied and should lead to a refinement in the position of the Neptune spin and invariable plane poles.

Porco, Carolyn C.↗
NASA NTRS1989

Gravitational experiments on a solar probe mission: Scientific objectives and technology considerations

The concept of a solar impact probe (either solar plunger or sun grazer) led to the initiation of a NASA study at JPL in 1978 on the engineering and scientific feasibility of a Solar Probe Mission, named Starprobe, in which a spacecraft is placed in a high eccentricity orbit with a perihelion near 4 solar radii. The Starprobe study showed that the concept was feasible and in fact preliminary mission and spacecraft designs were developed. In the early stages of the Solar Probe studies the emphasis was placed on gravitational science, but by the time of a workshop at Caltech in May 1978 (Neugebauer and Davies, 1978) there was about an equal division of interest between heliospheric physics and gravitation. The last of the gravitational studies for Solar Probe was conducted at JPL in 1983. Since that time, the Committee on Solar and Space Physics (CSSP) of the National Academy of Sciences has recommended the pursuit of a focused mission, featuring fields and particles instrumentation and emphasizing studies of the solar wind source region. Such a solar probe mission is currently listed as the 1994 Major New Star candidate. In the remainder of this review, the unique gravitational science that can be accomplished with a solar probe mission is reviewed. In addition the technology issues that were identified in 1980 by the ad hoc working group for Gravity and Relativity Science are addressed.

Anderson, John D.↗
NASA NTRSDate not supplied

Assessing Utility of Different Orbits for a Lunar PNT Constellation

"As the Artemis program establishes a long-term presence on the lunar surface, lunar surface users will need an accurate source of Position, Navigation, and Timing (PNT). Under the LunaNet framework, NASA has proposed the Lunar Navigation System (LNS), a constellation of satellites in lunar orbit which will broadcast LunaNet’s Augmented Forward Signal (AFS) [1] to the lunar surface. LNS will have the objective of providing user position accuracies of 10 m and timing accuracies of 10 microseconds on the lunar surface and up to 200 km above the surface. Several classes of orbits are possibilities for the LNS constellation, including circular orbits, eccentric orbits, and various families of 3-body orbits. Each of these orbit classes have both advantages and disadvantages in their utility as PNT constellations. In this study we examine a wide variety of potential LNS constellations and evaluate their performance against several metrics, including: a. Dilution of Precision (DOP) performance over the lunar service volume and the South Pole region, during both the constellation buildup and after the constellation is completed. b. Number of satellites required to achieve required DOP performance. c. Relative dynamics of LNS satellites with respect to surface users. d. Signal in space error (SISE) performance, assuming orbit determination that includes the Global Positioning System (GPS), crosslinks, and monitor sites on the surface of the moon. e. Constellation insertion, station keeping, and disposal costs. f. Specific Concept of Operations (CONOPS) and engineering challenges associated with establishing and operating the constellations. (E.g., frequent station keeping, variable signal strength, divergent CONOPS for different planes of the constellation.) The system’s performance is considered both independently and in combination with other proposed systems, such as NASA’s Lunar Communication Relay and Navigation System (LCRNS) and ESA’s Moonlight constellation. The study concludes that a 3-plane Walker constellation at 6 lunar radii (slightly higher than GPS’s 4.2 earth radii from a geometry perspective, but significantly closer in an absolute sense) is a good candidate for the LNS constellation, providing the user with good SISE and DOP performance, while not requiring excessive station keeping or complex CONOPS. However, other viable concepts exist and could be chosen if early South Pole coverage is a driving factor in the system design."

navigation↗
NASA NTRS1984

Origin of the Greenland Ice Sheet

A climate model resolving the seasonal cycle and the two horizontal dimensions was developed and applied to several problems of current interest. Models of this type are useful when for various reasons a general circulation model experiment is not warranted or not feasible. For example, in cases where the signal to natural variability is small it may be advantageous to first consider such a statistical dynamical model because extremely long runs may be necessary in the application. In this case the simpler statistical dynamical model serves as a pilot study device. The model developed is a thermodynamic model whose solution yields the equilibrium seasonal cycle for the surface temperature field over the globe. The model is essentially a statement of the conservation of heat energy for individual columns of the earth atmosphere system. Various terms such as the infrared radiation flux to space are parameterized with earth radiation budget data from satellites such as Nimbus 6. The primary agent modulating the seasonal cycle amplitude is the heat capacity per unit area which is a strong function of surface type -- ocean surface can store 60 times more heat per unit time than land. By adjusting its few empirical parameters the model can be brought into remarkable agreement with the observed seasonal cycle. The model is then very useful for looking at the dependence of the seasonal cycle of the temperature on such externally defined variables as the Earth's orbital elements (eccentricity, tilt, precession of equinoxes) or the configuration of land-sea geography which can be changed by continental drift.

North, G. R.↗
NASA NTRS2002

Planetary Rings: An Update on Structure and Properties

Over the last several years there has been steady progress in several areas related to the structure and composition of planetary rings. Much of the progress was related to Saturn's rings: new observations by Hubble Space Telescope (HST) and NASA's Infrared Telescope Facility (IRTF), theoretical modeling of the vertical structure of, and particle properties in the rings, discovery of intriguing structural/spectral variations on small spatial scales, new observations and analysis of thermal emission from the rings, theoretical and observational constraints on the quadrupole brightness asymmetry at visual and microwave wavelengths, and new studies of "clumps" in and near the F ring. In addition, new observations were obtained of Jupiter's rings by Cassini, and new models were put forth to explain the narrow edges and apse alignment of the Uranian rings (and presumably other narrow eccentric rings).

Cuzzi, Jeff↗