Probing General Relativity and New Physics with Lunar Laser Ranging

NASA Astrophysics Data System (ADS)

Dell'Agnello, S.; Maiello, M.; Currie, D. G.; Boni, A.; Berardi, S.; Cantone, C.; Delle Monache, G. O.; Intaglietta, N.; Lops, C.; Garattini, M.; Martini, M.; Patrizi, G.; Porcelli, L.; Tibuzzi, M.; Vittori, R.; Bianco, G.; Coradini, A.; Dionisio, C.; March, R.; Bellettini, G.; Tauraso, R.; Chandler, J.

2012-11-01

Over the past 40 years, Lunar Laser Ranging (LLR, developed by the Univ. of Maryland (PI) and INFN-LNF (Co-PI)) to the Apollo Cube Corner Retroreflector (CCR) arrays have supplied almost all the significant tests of General Relativity (Currie et al., 2009 [12]). LLR can evaluate the PPN (Post Newtonian Parameters), addressing this way both the possible changes in the gravitational constant and the self-energy properties of the gravitational field. In addition, the LLR has provided significant information on the composition and origin of the Moon. This is the only Apollo experiment that is still in operation. Initially the Apollo LLR arrays contributed a negligible fraction of the ranging error budget. Over the decades, the ranging capabilities of the ground stations have improved by more than two orders of magnitude. Now, because of the lunar librations, the existing Apollo retroreflector arrays contribute a significant fraction of the limiting errors in the range measurements. We built a new experimental apparatus (the ‘Satellite/Lunar Laser Ranging Characterization Facility', SCF) and created a new test procedure (the SCF-Test) to characterize and model the detailed thermal behavior and the optical performance of cube corner laser retroreflectors in space for industrial and scientific applications (Dell'Agnello et al., 2011 [13]). Our key experimental innovation is the concurrent measurement and modeling of the optical Far Field Diffraction Pattern (FFDP) and the temperature distribution of the SLR retroreflector payload under thermal conditions produced with a close-match solar simulator. The apparatus includes infrared cameras for non-invasive thermometry, thermal control and real-time movement of the payload to experimentally simulate satellite orientation on orbit with respect to both solar illumination and laser interrogation beams. These unique capabilities provide experimental validation of the space segment for SLR and Lunar Laser Ranging (LLR). The primary goal of these innovative tools is to provide critical design and diagnostic capabilities for Satellite Laser Ranging (SLR) to Galileo and other GNSS (Global Navigation Satellite System) constellations. Implementation of new retroreflector designs being studied will help to improve GNSS orbits, which will then increase the accuracy, stability, and distribution of the International Terrestrial Reference Frame (ITRF) [4], to provide better definition of the geocenter (origin) and the scale (length unit). The SCF is also actively used to develop, validate and optimize the second generation LLR arrays for precision gravity and lunar science measurements to be performed with robotic missions of the International Lunar Network in which NASA and ASI participate (ILN). The capability will allow us to optimize the design of GNSS laser retroreflector payloads to maximize ranging efficiency, to improve signal-to-noise conditions in daylight and to provide pre-launch validation of retroreflector performance under laboratory-simulated space conditions. For the MAGIA lunar orbiter Phase A study funded by ASI (Dell'Agnello et al., 2010 [14]), we studied fundamental physics and absolute positioning metrology experiments, to improve test of the gravitational redshift in the Earth-Moon system predicted by General Relativity and a precursor test of our second generation LLR payload.

Study of wire electrical discharge machined folded-up corner cube retroreflector with a tunable cantilever beam

NASA Astrophysics Data System (ADS)

Chen, Yu-Fan; Wang, Yen-Hung; Tsai, Jui-che

2018-03-01

This work has developed an approach to construct a corner cube retroreflector (CCR). A two-dimensional cutout pattern is first fabricated with wire electrical discharge machining process. It is then folded up into a three-dimensional CCR suspended on a cantilever beam. The folded-up CCR may be driven through external actuators for optical modulation; it can also mechanically respond to perturbation, acceleration, etc., to function as a sensor. Mechanical (static and dynamic modeling) and optical (ray tracing) analyses are also performed.

Cryogenic Scan Mechanism for Fourier Transform Spectrometer

NASA Technical Reports Server (NTRS)

Brasunas, John C.; Francis, John L.

2011-01-01

A compact and lightweight mechanism has been developed to accurately move a Fourier transform spectrometer (FTS) scan mirror (a cube corner) in a near-linear fashion with near constant speed at cryogenic temperatures. This innovation includes a slide mechanism to restrict motion to one dimension, an actuator to drive the motion, and a linear velocity transducer (LVT) to measure the speed. The cube corner mirror is double-passed in one arm of the FTS; double-passing is required to compensate for optical beam shear resulting from tilting of the moving cube corner. The slide, actuator, and LVT are off-the-shelf components that are capable of cryogenic vacuum operation. The actuator drives the slide for the required travel of 2.5 cm. The LVT measures translation speed. A proportional feedback loop compares the LVT voltage with the set voltage (speed) to derive an error signal to drive the actuator and achieve near constant speed. When the end of the scan is reached, a personal computer reverses the set voltage. The actuator and LVT have no moving parts in contact, and have magnetic properties consistent with cryogenic operation. The unlubricated slide restricts motion to linear travel, using crossed roller bearings consistent with 100-million- stroke operation. The mechanism tilts several arc seconds during transport of the FTS mirror, which would compromise optical fringe efficiency when using a flat mirror. Consequently, a cube corner mirror is used, which converts a tilt into a shear. The sheared beam strikes (at normal incidence) a flat mirror at the end of the FTS arm with the moving mechanism, thereby returning upon itself and compensating for the shear

A Q-switched Ho:YAG laser with double anti-misalignment corner cubes pumped by a diode-pumped Tm:YLF laser

NASA Astrophysics Data System (ADS)

Wang, Y. P.; Dai, T. Y.; Wu, J.; Ju, Y. L.; Yao, B. Q.

2018-06-01

We report the acousto-optically Q-switched Ho:YAG laser with double anti-misalignment corner cubes pumped by a diode-pumped Tm:YLF laser. In the continuous-wave operation of Ho:YAG laser, the maximum s-polarized output power of 3.2 W at 2090.3 nm was obtained under the absorbed pump power of 12.9 W by rotating the fast axis of quarter-wave plate to change the output transmission of laser cavity. The corresponding optical-to-optical conversion efficiency was 24.8% and the slope efficiency was 55.7%. When one of the corner cubes was rotated to 11.8° around vertical direction or 6.7° around horizontal direction, the laser could still operate stably. For the Q-switched operation, the pulse energy of Ho:YAG laser was 9.9 mJ with a pulse width of 53 ns at the repetition rate of 100 Hz, resulting in a peak power of 186.8 kW. The beam quality factor M2 of Ho:YAG laser was 1.3.

View of Central Texas as seen from Apollo 9

NASA Technical Reports Server (NTRS)

1969-01-01

Central Texas area as photographed from the Apollo 9 spacecraft during its earth-orbital mission. Interstate 35 runs from Austin (right center edge of pictures) to Waco (near bottom left corner). Also, visible are the cities of Georgetown, Taylor, Temple and Killeen. The Colorado River runs through Austin. The Brazos River flows through Waco. Lake Travis is upstream from Austin. Lake Whitney is at bottom left corner of picture. The Belton Reservoir is near bottom center. The lake formed by the dam on the Lampasas River near Belton is also clearly visible.

11. Threequarter view of southwest corner of building 500 and ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

11. Three-quarter view of southwest corner of building 500 and G-wing, looking northeast, from Apollo Drive - Offutt Air Force Base, Strategic Air Command Headquarters & Command Center, Headquarters Building, 901 SAC Boulevard, Bellevue, Sarpy County, NE

Automatic Alignment of Displacement-Measuring Interferometer

NASA Technical Reports Server (NTRS)

Halverson, Peter; Regehr, Martin; Spero, Robert; Alvarez-Salazar, Oscar; Loya, Frank; Logan, Jennifer

2006-01-01

A control system strives to maintain the correct alignment of a laser beam in an interferometer dedicated to measuring the displacement or distance between two fiducial corner-cube reflectors. The correct alignment of the laser beam is parallel to the line between the corner points of the corner-cube reflectors: Any deviation from parallelism changes the length of the optical path between the reflectors, thereby introducing a displacement or distance measurement error. On the basis of the geometrical optics of corner-cube reflectors, the length of the optical path can be shown to be L = L(sub 0)cos theta, where L(sub 0) is the distance between the corner points and theta is the misalignment angle. Therefore, the measurement error is given by DeltaL = L(sub 0)(cos theta - 1). In the usual case in which the misalignment is small, this error can be approximated as DeltaL approximately equal to -L(sub 0)theta sup 2/2. The control system (see figure) is implemented partly in hardware and partly in software. The control system includes three piezoelectric actuators for rapid, fine adjustment of the direction of the laser beam. The voltages applied to the piezoelectric actuators include components designed to scan the beam in a circular pattern so that the beam traces out a narrow cone (60 microradians wide in the initial application) about the direction in which it is nominally aimed. This scan is performed at a frequency (2.5 Hz in the initial application) well below the resonance frequency of any vibration of the interferometer. The laser beam makes a round trip to both corner-cube reflectors and then interferes with the launched beam. The interference is detected on a photodiode. The length of the optical path is measured by a heterodyne technique: A 100- kHz frequency shift between the launched beam and a reference beam imposes, on the detected signal, an interferometric phase shift proportional to the length of the optical path. A phase meter comprising analog filters and specialized digital circuitry converts the phase shift to an indication of displacement, generating a digital signal proportional to the path length.

Single-color laser ranging with a cube-corner-retroreflector array

NASA Technical Reports Server (NTRS)

Song, G. Hugh

1987-01-01

Lidar cross section of some typical types of cube-corner retroreflectors (CCRs) having a three corner mirror system is investigated for the case that the CCR is tilted from the normal illumination axis. Analytic expressions for the effective aperture area for the two typical window types (circular and hexagonal) of CCRs are obtained for the case that the CCR is tilted. The range of incidence angle in which only the total reflection occurs at all three uncoated corner mirrors has been found to vary considerably with the orientation of CCR and the refractive index of the CCR prism. The analytical expression for the far-field diffraction pattern of a tilted CCR is obtained by taking different polarization transformation of the six sectors of the effective reflecting aperture into account. This expression is essential when evaluating the lidar cross section of a moving CCR which is tilted in general. Formulas for the angles defining the six sectors have also been obtained.

12. Threequarter view of southwest corner of building 500, Gwing, ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

12. Three-quarter view of southwest corner of building 500, G-wing, and loading dock looking northeast, from Apollo Drive - Offutt Air Force Base, Strategic Air Command Headquarters & Command Center, Headquarters Building, 901 SAC Boulevard, Bellevue, Sarpy County, NE

Vertical view Apollo 16 Descartes landing sites as photographed by Apollo 14

NASA Image and Video Library

1971-01-12

S72-00147 (January 1972) --- An almost vertical view of the Apollo 16 Descartes landing area, as photographed from the Apollo 14 spacecraft. Overlays are provided to point out extravehicular activity (EVA) Lunar Roving Vehicle (LRV) traverse routes and the nicknames of features. Hold picture with South Ray Crater in lower left corner. North will then be at the top. The Roman numerals indicate EVA numbers and the Arabic numbers point out stations or traverse stops.

View of Central Texas as seen from Apollo 9

NASA Image and Video Library

1969-03-09

AS09-22-3341 (3-13 March 1969) --- Central Texas area as photographed from the Apollo 9 spacecraft during its Earth-orbital mission. Interstate 35 runs from Austin (right center edge of picture) to Waco (near bottom left corner). Also visible are the cities of Georgetown, Taylor, Temple and Killeen. The Colorado River runs through Austin. The Brazos River flows through Waco. Lake Travis is upstream from Austin. Lake Whitney is at bottom left corner of picture. The Belton Reservoir is near bottom center. The lake formed by the dam on the Lampasas River near Belton is also clearly visible.

Dual surface interferometer

DOEpatents

Pardue, R.M.; Williams, R.R.

1980-09-12

A double-pass interferometer is provided which allows direct measurement of relative displacement between opposed surfaces. A conventional plane mirror interferometer may be modified by replacing the beam-measuring path cube-corner reflector with an additional quarterwave plate. The beam path is altered to extend to an opposed plane mirrored surface and the reflected beam is placed in interference with a retained reference beam split from dual-beam source and retroreflected by a reference cube-corner reflector mounted stationary with the interferometer housing. This permits direct measurement of opposed mirror surfaces by laser interferometry while doubling the resolution as with a conventional double-pass plane mirror laser interferometer system.

Dual surface interferometer

DOEpatents

Pardue, Robert M.; Williams, Richard R.

1982-01-01

A double-pass interferometer is provided which allows direct measurement of relative displacement between opposed surfaces. A conventional plane mirror interferometer may be modified by replacing the beam-measuring path cube-corner reflector with an additional quarter-wave plate. The beam path is altered to extend to an opposed plane mirrored surface and the reflected beam is placed in interference with a retained reference beam split from dual-beam source and retroreflected by a reference cube-corner reflector mounted stationary with the interferometer housing. This permits direct measurement of opposed mirror surfaces by laser interferometry while doubling the resolution as with a conventional double-pass plane mirror laser interferometer system.

Animal-eyeball vs. road-sign retroreflectors.

PubMed

Greene, Nathaniel R; Filko, Brian J

2010-01-01

The retroreflective characteristics of ex-vitro cow and deer eyeballs were compared to those of man-made materials used in road signs and bicycle-style reflectors. Reflected intensities were measured using a goniometer that consists of a green He-Ne laser as the light source, and a photomultiplier tube as the detector. It was found that the best quality road-sign reflector, made from a 200-micron-scale, close-packed array of corner cubes, is approximately six times more efficient than a cow eyeball at returning light in the direction of the incoming beam. Less expensive man-made retroreflectors, utilizing 35-micron glass beads (as in mailbox decals) or millimeter-scale arrays of corner cubes (bicycle-style reflectors) are, however, less efficient than the cow eye. The high quality of animal eyeball optics is evidenced by their extremely tight angular spread (full width half maximum congruent with 1 degrees) of retroreflected intensity about the incident path. Moreover, as the reflector itself is rotated relative to the incident beam, the eyeballs preserve their efficiency of retroreflection better than the man-made materials. Interference-diffraction patterns were observed in the retroreflected beams from the small-scale corner cubes, but were not observed in eyeball retroreflection.

The Corner Reflector.

ERIC Educational Resources Information Center

Harris, Whitney S., Jr.

1983-01-01

The nature of the corner reflector array left on the moon by the July 1969 Apollo astronauts is described. The array was used to reflect earth-originating laser beams back to earth, and yielded a more accurate determination (to within six inches) of distance from the earth to the moon. (MP)

Experimental evaluation of the performance of pulsed two-color laser-ranging systems

NASA Technical Reports Server (NTRS)

Im, Kwaifong E.; Gardner, Chester S.; Abshire, James B.; Mcgarry, Jan F.

1987-01-01

Two-color laser-ranging systems can be used to estimate the atmospheric delay by measuring the difference in propagation times between two optical pulses transmitted at different wavelengths. This paper describes horizontal-path ranging experiments that were conducted using flat diffuse targets and cube-corner reflector arrays. Measurements of the timing accuracy of the cross-correlation estimator, atmospheric delay, received pulse shapes, and signal power spectra are presented. The results are in general agreement with theory and indicate that target speckle can be the dominant noise source when the target is small and is located far from the ranging system or when the target consists of a small number of cube-corner reflectors.

Laser radar range and detection performance for MEMS corner cube retroreflector arrays

NASA Astrophysics Data System (ADS)

Grasso, Robert J.; Odhner, Jefferson E.; Stewart, Hamilton; McDaniel, Robert V.

2004-12-01

BAE SYSTEMS reports on a program to characterize the performance of MEMS corner cube retroreflector arrays under laser illumination. These arrays have significant military and commercial application in the areas of: 1) target identification; 2) target tracking; 3) target location; 4) identification friend-or-foe (IFF); 5) parcel tracking, and; 6) search and rescue assistance. BAE SYSTEMS has theoretically determined the feasibility of these devices to learn if sufficient signal-to-noise performance exists to permit a cooperative laser radar sensor to be considered for device location and interrogation. Results indicate that modest power-apertures are required to achieve SNR performance consistent with high probability of detection and low false alarm rates.

Laser radar range and detection performance for MEMS corner cube retroreflector arrays

NASA Astrophysics Data System (ADS)

Grasso, Robert J.; Jost, Steven R.; Smith, M. J.; McDaniel, Robert V.

2004-01-01

BAE SYSTEMS reports on a program to characterize the performance of MEMS corner cube retroreflector arrays under laser illumination. These arrays have significant military and commercial application in the areas of: (1) target identification; (2) target tracking; (3) target location; (4) identification friend-or-foe (IFF); (5) parcel tracking, and; (6) search and rescue assistance. BAE SYSTEMS has theoretically determined the feasibility of these devices to learn if sufficient signal-to-noise performance exists to permit a cooperative laser radar sensor to be considered for device location and interrogation. Results indicate that modest power-apertures are required to achieve SNR performance consistent with high probability of detection and low false alarm rates.

KSC-04pd0651

NASA Image and Video Library

2004-03-26

KENNEDY SPACE CENTER, FLA. -- This aerial photo shows the storage area containing Launch Umbilical Towers that were used during the early years of the Space Program. In the lower left corner of the storage field is a Caterpillar excavator with a 48-inch shear demolishing LUT-1, used to launch Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

KSC-04pd0649

NASA Image and Video Library

2004-03-26

KENNEDY SPACE CENTER, FLA. -- This aerial photo shows the storage area containing Launch Umbilical Towers that were used during the early years of the Space Program. In the lower right corner of the storage field is a Caterpillar excavator with a 48-inch shear demolishing LUT-1, used to launch Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

KSC-04pd0648

NASA Image and Video Library

2004-03-26

KENNEDY SPACE CENTER, FLA. -- This aerial photo shows the storage area containing Launch Umbilical Towers that were used during the early years of the Space Program. In the upper right corner of the storage field is a Caterpillar excavator with a 48-inch shear demolishing LUT-1, used to launch Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

Vertical view of Arab Republic of Egypt from ASTP mission

NASA Image and Video Library

1975-07-19

AST-09-555 (19 July 1975) --- A vertical view of a portion of the Arab Republic of Egypt, as photographed from the Apollo spacecraft in Earth orbit during the joint U.S.-USSR Apollo-Soyuz Test Project mission. The Nile Delta is in the most northerly corner of the picture. The City of Cairo on the Nile River is in the center of the photograph. The Gulf of Suez is in the most easterly corner of the picture. El Faiyum is south-southwest of Cairo. This picture was taken at an altitude of 223 kilometers (138 statute miles), with a 70mm Hasselblad camera using medium-speed Ektachrome QX-807 type film.

Apollo 9 Mission image - Earth Observation - Georgia

NASA Image and Video Library

1969-03-03

AS09-23-3567 (3-13 March 1969) --- Oblique view of the Atlanta, Georgia area as photographed from the Apollo 9 spacecraft during its Earth-orbital mission. The Chattahoochee River runs from Lake Sidney Lanier, near Gainesville (at upper left corner), south-westward by Atlanta and between Newnan and Carrollton (lower right). Allatoona Lake is at left center.

Noise properties of a corner-cube Michelson interferometer LWIR hyperspectral imager

NASA Astrophysics Data System (ADS)

Bergstrom, D.; Renhorn, I.; Svensson, T.; Persson, R.; Hallberg, T.; Lindell, R.; Boreman, G.

2010-04-01

Interferometric hyperspectral imagers using infrared focal plane array (FPA) sensors have received increasing interest within the field of security and defence. Setups are commonly based upon either the Sagnac or the Michelson configuration, where the former is usually preferred due to its mechanical robustness. However, the Michelson configuration shows advantages in larger FOV due to better vignetting performance and improved signal-to-noise ratio and cost reduction due to relaxation of beamsplitter specifications. Recently, a laboratory prototype of a more robust and easy-to-align corner-cube Michelson hyperspectral imager has been demonstrated. The prototype is based upon an uncooled bolometric FPA in the LWIR (8-14 μm) spectral band and in this paper the noise properties of this hyperspectral imager are discussed.

Development of the Laser Retroreflector Array (LRA) for SARAL

NASA Astrophysics Data System (ADS)

Costes, Vincent; Gasc, Karine; Sengenes, Pierre; Salcedo, Corinne; Imperiali, Stéphan; du Jeu, Christian

2017-11-01

CNES (French spatial agency) will provide the AltiKa high resolution altimeter, Doris instrument and the LRA (Laser Retroreflector Array) for SARAL (Satellite with Argos and AltiKa) in cooperation with ISRO (Indian space agency). The LRA is a passive equipment reflecting the laser beams coming from the Earth ground stations. Computing the send-return time travel of the laser beams allows the determination of the satellite altitude within an accuracy of a few millimeters. The reflective function is done by a set of 9 corner cube reflectors, with a conical arrangement providing a 150 degrees wide field of view over the full 360 degrees azimuth angle. According to CNES optomechanical specifications, the LRA has been developed by SESO (French optical firm). SESO has succeeded in providing the corner cube reflectors with a very stringent dihedral angle error of 1.6 arcsec and an accuracy within +/-0.5 arcsec. During this development, SESO has performed mechanical, thermal and thermo-optical analyses. The optical gradient of each corner cube, as well as angular deviations and PSF (Point Spread Function) in each laser range finding direction, have been computed. Mechanical and thermal tests have been successfully performed. A thermo-optical test has successfully confirmed the optical effect of the predicted in-flight thermal gradients. Each reflector is characterized in order to find its best location in the LRA housing and give the maximum optimization to the space telemetering mission.

Gold coatings for cube-corner retro-reflectors

NASA Astrophysics Data System (ADS)

Dligatch, Svetlana; Gross, Mark; Netterfield, Roger P.; Pereira, Nathan; Platt, Benjamin C.; Nemati, Bijan

2005-09-01

The Space Interferometry Mission (SIM) PlanetQuest is managed by the Jet Propulsion Laboratory for the National Aeronautics and Space Administration. SIM requires, among other things, high precision double cube-corner retroreflectors. A test device has recently been fabricated for this project with demanding specifications on the optical surfaces and gold reflective coatings. Several gold deposition techniques were examined to meet the stringent specifications on uniformity, optical properties, micro-roughness and surface quality. We report on a comparative study of optical performance of gold films deposited by resistive and e-beam pvaporation, including measurements of the scattering from the coated surfaces. The effects of oxygen bombardment and titanium under-layer on optical properties and adhesion were evaluated. The influence of surface preparation on the optical properties was examined also.

Apollo 11 Command/Service modules photographed from Lunar Module in orbit

NASA Image and Video Library

1969-07-20

AS11-37-5445 (20 July 1969) --- The Apollo 11 Command and Service Modules (CSM) are photographed from the Lunar Module (LM) in lunar orbit during the Apollo 11 lunar landing mission. The lunar surface below is in the north central Sea of Fertility. The coordinates of the center of the picture are 51 degrees east longitude and 1 degree north latitude. About half of the crater Taruntius G is visible in the lower left corner of the picture. Part of Taruntius H can be seen at lower right.

Next-generation Lunar Laser Retroreflectors for Precision Tests of General Relativity

NASA Astrophysics Data System (ADS)

Ciocci, Emanuele; dell'Agnello, Simone; Delle Monache, Giovanni; Martini, Manuele; Contessa, Stefania; Porcelli, Luca; Tibuzzi, Mattia; Salvatori, Lorenzo; Patrizi, Giordano; Maiello, Mauro; Intaglietta, Nicola; Mondaini, Chiara; Currie, Douglas; Chandler, John; Bianco, Giuseppe; Murphy, Tom

2016-04-01

Since 1969, Lunar Laser Ranging (LLR) to the Apollo Cube Corner Retroreflectors (CCRs) has supplied almost all significant tests of General Relativity (GR). When first installed in the 1970s, the Apollo CCRs geometry contributed only a negligible fraction of the ranging error budget. Today, because of lunar librations, this contribution dominates the error budget, limiting the precision of the experimental tests of gravitational theories. The new MoonLIGHT-2 (Moon Laser Instrumentation for General relativity High-accuracy Tests) apparatus is a new-generation LLR payload developed by the SCF_Lab (http://www.lnf.infn.it/esperimenti/etrusco/) at INFN-LNF in collaboration with the Maryland University. With the unique design of a single large CCR unaffected by librations, MoonLIGHT-2 can increase up to a factor 100 the precision of the measurement of the lunar geodetic precession and other General Relativity (GR) tests respect to Apollo CCRs. MoonLIGHT-2 is approved to be launched with the Moon Express mission MEX-1 and will be deployed on the Moon surface in 2018. MoonLIGHT-2 is also proposed for the Roscosmos mission Luna-27. To validate/optimize MoonLIGHT-2 for MEX-1, the SCF_Lab is carrying out a unique experimental test called SCF-Test: the concurrent measurement of the optical Far Field Diffraction Pattern (FFDP) and the temperature distribution of the CCR under thermal conditions produced with a close-match solar simulator and simulated space environment. We perform test of GR with current LLR data and also different GR simulation of the expected improvement in GR test provided by MoonLIGHT-2, using the Planetary Ephemeris Program in collaboration with CfA. Our ultimate goal is to improve GR tests by a factor up to 100, and provide constraints on the new gravitational theories like non-miminally coupled gravity and spacetime torision.

Thermophysical properties of Apollo 14 fines

NASA Technical Reports Server (NTRS)

Cremers, C. J.

1974-01-01

The vacuum thermal conductivity of lunar fines sample 14163 was measured for the approximate temperature range of 100 to 400 K. Sample densities of 1500 kg/cu m and 1800 kg/cu m were used. The temperature dependence of the conductivity was found to be well represented by the relation k = A + BT-cubed, which is predicted by elementary theory. The coefficients A and B were obtained by least-squares analysis of the data. The thermal diffusivity was calculated for the various densities using specific heat data from the literature along with the measured conductivities. The results are compared with those obtained for Apollo 11, Apollo 12, and terrestrial basalt samples.

Nominal SARAL Transfer Function

NASA Technical Reports Server (NTRS)

Arnold, David A.; Lemoine, Frank (Editor)

2015-01-01

This paper gives a calculation of the range correction and cross section of the SARAL (Satellite with Argos and ALtiKa) Indian/French ocean radar satellite retroreflector array assuming the cube corners are coated and have a dihedral angle offset of about 1.5 arcseconds to account for velocity aberration. The cubes are assumed to all have the same orientation within the mounting. The derived range correction may be applied in precise orbit determination analyses that use Satellite Laser Ranging (SLR) data to SARAL.

Laser interferometry method for absolute measurement of the acceleration of gravity

NASA Technical Reports Server (NTRS)

Hudson, O. K.

1971-01-01

Gravimeter permits more accurate and precise absolute measurement of g without reference to Potsdam values as absolute standards. Device is basically Michelson laser beam interferometer in which one arm is mass fitted with corner cube reflector.

Near vertical view of Lubbock area in west Texas as seen from Apollo 9

NASA Image and Video Library

1969-03-11

AS09-23-3561 (3-13 March 1969) --- Near vertical view of the Lubbock area in west Texas as photographed from the Apollo 9 spacecraft during its Earth-orbital mission. Conspicuous patterns of farmland surround the city and extend eastward (up) to the Caprock Escarpment. The Double Mountain fork of the Brazos River drains east (toward upper center); Leeland is at lower center; Brownfield at lower right. The sharp edge of a cloud disk cuts across the upper right corner.

Dallas-Fort Worth, Texas as seen from the Apollo 6 unmanned spacecraft

NASA Image and Video Library

1968-04-06

AS06-02-1462 (4 April 1968) --- View of the Dallas-Fort Worth, Texas, area as photographed from the unmanned Apollo 6 (Spacecraft 020/Saturn 502) space mission. The highway and expressway system in and around both cities is clearly visible. North is toward left side of picture. Grapevine Reservoir and Garza-Little Elm Reservoir are to the north-west of Dallas. The city of Denton can be seen in left center of picture at conjunction of highways leading to both Fort Worth and Dallas. The Brazos River is in lower right corner. This photograph was made three hours and nine minutes after liftoff of the Apollo 6 space flight.

Don't Forget the Reflector.

ERIC Educational Resources Information Center

Morton, N.

1991-01-01

Various modes of reflection are classified and practical examples of devices, such as cat's eyes, are discussed. Typical light rays are traced through several systems, providing exercises with varying degrees of difficulty. Corner-cube retroreflectors, glass spheres, reflecting luminaries, light concentrators, parabolic reflectors, and off-set and…

Development Challenges of Utilizing a Corner Cube Mechanism Design with Successful IASI Flight Heritage for the Infrared Sounder (IRS) on MTG: Recurrent Mechanical Design not Correlated to Recurrent Development

NASA Astrophysics Data System (ADS)

Spanoudakis, Peter; Schwab, Philippe; Kiener, Lionel; Saudan, Herve; Perruchoud, Gerald

2015-09-01

The Corner Cube Mechanism (CCM) design for the Infra-Red Sounder (IRS) on MTG is based on the successful mechanism currently in orbit on the Infrared Atmospheric Sounding Interferometers (IASI) on the Metop satellites. The overall CCM performance is described with attention given to the specific design developments for the MTG project. A description is presented of the modifications introduced and challenges encountered to adapt the IASI space heritage design (which is only 15 years old) to meet the MTG specifications. A detailed account is provided regarding the tests performed on the adapted components for the new programme. The major issues encountered and solutions proposed are illustrated concerning the voice- coil actuator development, optical switch design, fatigue life of the flexure components and the adaptation of the launch locking device. Nevertheless, an Engineering Qualification Model was rapidly manufactured and now undergoing a qualification test campaign.

Ammoniated alkali fullerides (ND(3))(x)NaA(2)C(60): ammonia specific effects and superconductivity.

PubMed

Margadonna, Serena; Aslanis, Efstathios; Prassides, Kosmas

2002-08-28

The crystal structure of the superconducting (ND(3))(x)()NaA(2)C(60) (0.7 < or = x < or = 1, A= K, Rb) fullerides (T(c)= 6-15 K) has been studied by synchrotron X-ray and neutron powder diffraction. It is face-centered cubic (fcc) to low temperatures with Na(+)-ND(3) pairs residing in the octahedral interstices. These are disordered over the corners of two "interpenetrating" cubes with the Na(+) ions and the N atoms displaced by approximately 2.0 A and approximately 0.5 A from the center of the site and statically disordered over the corners of the inner and outer cube, respectively. Close contacts between the D atoms of the ND(3) molecules and electron rich 6:6 C-C bonds of neighboring C(60) units provide the signature of weak N-D.pi hydrogen-bonding interactions, which control the intermolecular packing in the crystal and may determine the unusual superconducting properties.

Food packages for Space Shuttle

NASA Technical Reports Server (NTRS)

Fohey, M. F.; Sauer, R. L.; Westover, J. B.; Rockafeller, E. F.

1978-01-01

The paper reviews food packaging techniques used in space flight missions and describes the system developed for the Space Shuttle. Attention is directed to bite-size food cubes used in Gemini, Gemini rehydratable food packages, Apollo spoon-bowl rehydratable packages, thermostabilized flex pouch for Apollo, tear-top commercial food cans used in Skylab, polyethylene beverage containers, Skylab rehydratable food package, Space Shuttle food package configuration, duck-bill septum rehydration device, and a drinking/dispensing nozzle for Space Shuttle liquids. Constraints and testing of packaging is considered, a comparison of food package materials is presented, and typical Shuttle foods and beverages are listed.

9. Threequarter view of building 500 looking northeast from the ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

9. Three-quarter view of building 500 looking northeast from the corner of Apollo Drive and SAC Boulevard at the outbound gate - Offutt Air Force Base, Strategic Air Command Headquarters & Command Center, Headquarters Building, 901 SAC Boulevard, Bellevue, Sarpy County, NE

Apollo 9 Mission image - S0-65 Multispectral Photography - Mexico

NASA Image and Video Library

2009-02-19

AS09-26A-3780A (11 March 1969) --- Colored infrared photograph of northern Baja California, Mexico, as seen from the Apollo 9 spacecraft during its 121st revolution of Earth. This picture was taken as a part of the SO65 Multispectral Terrain Photography Experiment. Prominent point jutting out into the Pacific Ocean is Punta Colnett. The Sierra de Juarez Mountains are in center of picture. "Arrow" formed by Pacific generally points northward. Punta San Felipe on the Gulf of California is in southeast corner of picture.

Apollo 9 Mission image - S0-65 Multispectral Photography - California and Mexico

NASA Image and Video Library

1969-03-12

AS09-26A-3799A (12 March 1969) --- Color infrared photograph of the Salton Sea and Imperial Valley area of Southern California as seen from the Apollo 9 spacecraft. This picture was taken as a part of the SO-65 Multispectral Terrain Photography Experiment. On the eastern edge of the picture are the Colorado River and a small portion of Arizona. Yuma, Arizona, is at the bottom right corner. The cities of El Centro, California, and Mexicali, Mexico, are at the bottom center.

Making a Cat's Eye in a Classroom

ERIC Educational Resources Information Center

Rovsek, Barbara

2010-01-01

Three plain mirrors, perpendicular to each other, reflect a beam of light back into the direction it came from. An activity is suggested where pupils can employ this feature of perpendicular mirrors and make their own corner cube retroreflector--a kind of cat's eye. (Contains 7 figures and 1 footnote.)

MoonLIGHT: A USA-Italy lunar laser ranging retroreflector array for the 21st century

NASA Astrophysics Data System (ADS)

Martini, M.; Dell'Agnello, S.; Currie, D.; Delle Monache, G.; Vittori, R.; Chandler, J. F.; Cantone, C.; Boni, A.; Berardi, S.; Patrizi, G.; Maiello, M.; Garattini, M.; Lops, C.; March, R.; Bellettini, G.; Tauraso, R.; Intaglietta, N.; Tibuzzi, M.; Murphy, T. W.; Bianco, G.; Ciocci, E.

2012-12-01

Since the 1970s Lunar Laser Ranging (LLR) to the Apollo Cube Corner Retroreflector (CCR) arrays (developed by the University of Maryland, UMD) have supplied significant tests of General Relativity: possible changes in the gravitational constant, gravitational self-energy, weak equivalence principle, geodetic precession, inverse-square force-law. LLR has also provided significant information on the composition and origin of the Moon. This is the only Apollo experiment still in operation. In the 1970s Apollo LLR arrays contributed a negligible fraction of the ranging error budget. Since the ranging capabilities of ground stations improved by more than two orders of magnitude, now, because of the lunar librations, Apollo CCR arrays dominate the error budget. With the project MoonLIGHT (Moon Laser Instrumentation for General relativity High-accuracy Tests), in 2006 INFN-LNF joined UMD in the development and test of a new-generation LLR payload made by a single, large CCR (100 mm diameter) unaffected by librations. In particular, INFN-LNF built and is operating a new experimental apparatus (Satellite/lunar laser ranging Characterization Facility, SCF) and created a new industry-standard test procedure (SCF-Test) to characterize and model the detailed thermal behavior and the optical performance of CCRs in laboratory-simulated space conditions, for industrial and scientific applications. Our key experimental innovation is the concurrent measurement and modeling of the optical Far Field Diffraction Pattern (FFDP) and the temperature distribution of retroreflector payloads under thermal conditions produced with a solar simulator. The apparatus includes infrared cameras for non-invasive thermometry, thermal control and real-time payload movement to simulate satellite orientation on orbit with respect to solar illumination and laser interrogation beams. These capabilities provide: unique pre-launch performance validation of the space segment of LLR/SLR (Satellite Laser Ranging); retroreflector design optimization to maximize ranging efficiency and signal-to-noise conditions in daylight. Results of the SCF-Test of our CCR payload will be presented. Negotiations are underway to propose our payload and SCF-Test services for precision gravity and lunar science measurements with next robotic lunar landing missions. We will describe the addition of the CCR optical Wavefront Fizeau Interferogram (WFI) concurrently to FFDP/temperature measurements in the framework of an ASI-INFN project, ETRUSCO-2. The main goals of the latter are: development of a standard GNSS (Global Navigation Satellite System) laser Retroreflector Array; a second SCF; SCF-Test of Galileo, GPS and other 'as-built' GNSS retroreflector payloads. Results on analysis of Apollo LLR data and search of new gravitational physics with LLR, Mercury Radar Ranging will be presented.

A Lunar Laser Ranging Retroreflector for the 21st Century

NASA Astrophysics Data System (ADS)

Currie, D.; Dell-Agnello, S.; Delle Monache, G.

Over the past forty years, Lunar Laser Ranging (LLR) to the Apollo Cube Corner (CCR) Retroreflector arrays has supplied almost all of the significant tests of General Relativity. The LLR program has evaluated the PPN parameters and addressed, for example, the possible change in the gravitational constant and the properties of the self-energy of the gravitational field. In addition, LLR has provided significant information on the composition and origin of the moon. These arrays are the only experiment of the Apollo program that are still in operation. Initially the Apollo Lunar Arrays contributed a negligible portion of the error budget used to achieve these results. Over the decades, the performance of ground stations has greatly upgraded so that the ranging accuracy has improved by more than two orders of magnitude, i.e., a factor of 140. Now, after forty years, because of the lunar librations the existing Apollo retroreflector arrays contribute significant fraction of the limiting errors in the range measurements. The University of Maryland, as the Principal Investigator for the original Apollo arrays, is now proposing a new approach to the Lunar Laser CCR array technology. The investigation of this new technology, with Professor Currie as Principal Investigator, is currently being supported by two NASA programs and, in part, also by INFN/LNF. Thus after the proposed installation on the next Lunar landing, the new arrays will support ranging observations that are a factor 100 more accurate than the current Apollo LLRRAs, from the centimeter level to the micron level. The new fundamental physics and the lunar physics that this new LLRRA can provide will be described. In the design of the new array, there are three major challenges: 1) Validate that the specifications of the CCR required for the new array, with are significantly beyond the properties of current CCRs, can indeed be achieved. 2) Address the thermal and optical effects of the absorption of solar radiation within the CCR, reduce the transfer of heat from the hot housing to the CCR and 3) Define a method of emplacing the CCR package on the lunar surface such that the relation between the optical center of the array and the center of mass of the moon remains stable over the lunar day/night cycle. The design approach, the computer simulations using Thermal Desktop, Code V and locally developed IDL software, and the results of the thermal vacuum testing conducted at the INFN/LNF's SCF facility at Frascati, Italy of the new array will also be presented. For example, the new lunar CCR housing has been built at INFN/LNF. The innovations in the LLRRA-21 with respect to the Apollo LLRR Arrays and current satellite retroreflector packages will be described. The new requirements for ground stations will be briefly addressed. This new concept for the LLRRA-21 is being considered for the NASA Manned Lunar Landings, for the NASA Anchor Nodes for the International Lunar Network and for the proposed Italian Space Agency's MAGIA lunar orbiter mission.

Gold coatings for cube-corner retro-reflectors

NASA Technical Reports Server (NTRS)

Dligatch, Svetlana; Gross, Mark; Netterfield, Roger P.; Pereira, Nathan; Platt, Benjamin C.; Nemati, Bijan

2005-01-01

We report on a comparative study of optical performance of gold films deposited by resistive and e-beam evaporation, including measurements of the scattering from the coated surfaces. The effects of oxygen bombardment and titanium under-layer on optical properties and adhesion were evaluated. The influence of surface preparation on the optical properties was examined also.

Semiconductor laser-based ranging instrument for earth gravity measurements

NASA Technical Reports Server (NTRS)

Abshire, James B.; Millar, Pamela S.; Sun, Xiaoli

1995-01-01

A laser ranging instrument is being developed to measure the spatial variations in the Earth's gravity field. It will range in space to a cube corner on a passive co-orbiting sub-satellite with a velocity accuracy of 20 to 50 microns/sec by using AlGaAs lasers intensity modulated at 2 GHz.

Apollo 9 Mission image - S0-65 Multispectral Photography - Mississippi

NASA Image and Video Library

2009-02-19

AS09-26A-3741A (9 March 1969) --- Color infrared photograph of the Mississippi River between Vicksburg and Greenville as photographed from the Apollo 9 spacecraft during its 92nd revolution of Earth. This picture was a part of the SO65 Multispectral Terrain Photography Experiment. The City of Vicksburg is located in the southeast corner of the picture. Note Interstate 20 under construction running east and west. Greenville is just out of picture at top center. All east of river is Mississippi; Louisiana is at lower left; and Arkansas is at upper left.

LANDING SITE - APOLLO XVII

NASA Image and Video Library

1972-09-28

S72-49760 (October 1972) --- An artist's concept illustrating the topographical layout of the Taurus-Littrow landing site of the Apollo 17 lunar landing mission. The Lunar Module touchdown point is in the center of the smooth area in the middle of the picture. The imposing mountain in the center is South Massif. A portion of North Massif is in the lower right corner of the photograph. Note the ridge-like feature extending from South Massif to North Massif. The southern portion of the ridge is called Lee Scarp and the northerly portion Lincoln Scarp. (This concept is by JSC artist Jerry Elmore).

View of crater Posidonius at edge of Sea of Serenity seen by Apollo 15

NASA Technical Reports Server (NTRS)

1971-01-01

An oblique view of a portion of the large crater Posidonius at the northeastern edge of the Sea of Serenity, as photographed from the Apollo 15 spacecraft in lunar orbit. Posidonius P is in the corner of the picture. The much smaller crater nearby is Posidonius F. The crater inside Posidonius is Posidonius A. Rima Posidonius II extends along inside Posidonius. The diamter of Posidonius is approximately 100 kilometers (about 62 statute miles). Posidonius is partly filled and the rim partly covered with mare material. This view is looking northwestward.

Molecular structure of Ti8C12 and related complexes.

PubMed Central

Pauling, L

1992-01-01

Application of valence-bond theory leads to the assignment to the molecule Ti8C12 of a cubic structure, point group Ohm3m, with 8 Ti at the cube corners, +/-(x x x, x, x x [symbol, see text]) where x = 1.78 A, and with 12 C in pairs in the cube faces, +/-(0 y z, [symbol, see text], 0, y z [symbol, see text]) where y = 1.78 A and z = 0.71 A. The Ti-C and C-C bonds have bond number 4/3, corresponding to resonance of single and double bonds in 2:1 ratio. PMID:11607323

Two Comments on Bond Angles

NASA Astrophysics Data System (ADS)

Glaister, P.

1997-09-01

Tetrahedral Bond Angle from Elementary Trigonometry The alternative approach of using the scalar (or dot) product of vectors enables the determination of the bond angle in a tetrahedral molecule in a simple way. There is, of course, an even more straightforward derivation suitable for students who are unfamiliar with vectors, or products thereof, but who do know some elementary trigonometry. The starting point is the figure showing triangle OAB. The point O is the center of a cube, and A and B are at opposite corners of a face of that cube in which fits a regular tetrahedron. The required bond angle alpha = AÔB; and using Pythagoras' theorem, AB = 2(square root 2) is the diagonal of a face of the cube. Hence from right-angled triangle OEB, tan(alpha/2) = (square root 2) and therefore alpha = 2tan-1(square root 2) is approx. 109° 28' (see Fig. 1).

Wide-Field Retroreflectors

NASA Technical Reports Server (NTRS)

Page, Norman A.; Tubbs, Eldred F.

1994-01-01

Retroreflectors made of concentric spherical optical elements developed for use in interferometric metrological systems. Used to provide reference point on structure to be aligned precisely in two or three dimensions by use of intersecting laser beams. Acceptance angle much larger than that of cat's-eye or corner-cube retroreflector: Simultaneously reflects laser beams separated by angles as large as 180 degrees.

A novel plane mirror interferometer without using corner cube reflectors

NASA Astrophysics Data System (ADS)

Büchner, H.-J.; Jäger, G.

2006-04-01

The conception and properties will be introduced of an interferometer that exclusively uses plane mirrors as reflectors; thus, these interferometers correspond well to the original Michelson interferometer. First, the relationship between the interference conditions and the detection with photodiodes will be discussed using the example of known interferometers as well as reasons given for primarily using corner cube reflectors in these devices. Next, the conceptual design of the plane mirror interferometer will be presented. This type of interferometer possesses new properties which are significant for metrological and technical applications. Only one measuring beam exists between the polarizing beam splitter and the measuring mirror and this beam alone represents the Abbe axis. This property allows the significant reduction of the Abbe error. The interferometer is able to tolerate tilting on the order of about 1'. This ensures the orthogonality between the measuring beam and the measuring mirror during the measurement. This property can be used in three-dimensional measurements to erect the three measuring beams as a x-y-z Cartesian coordinate system on the basis of three orthogonal mirrors. The plane-mirror interferometer also allows non-contact measurements of planar and curved surfaces, e.g. silicon wafers.

A study of the micro- and nanoscale deformation behavior of individual austenitic dendrites in a FeCrMoVC cast alloy using micro- and nanoindentation experiments

DOE Office of Scientific and Technical Information (OSTI.GOV)

Zeisig, J., E-mail: j.zeisig@ifw-dresden.de; Hufenbach, J.; Wendrock, H.

2016-04-04

Micro- and nanoindentation experiments were conducted to investigate the deformation mechanisms in a Fe79.4Cr13Mo5V1C1.6 (wt. %) cast alloy. This alloy consists of an as cast microstructure mainly composed of austenite, martensite, and a complex carbide network. During microhardness testing, metastable austenite transforms partially into martensite confirmed by electron backscatter diffraction. For nanoindentation tests, two different indenter geometries were applied (Berkovich and cube corner type). Load-displacement curves of nanoindentation in austenitic dendrites depicted pop-ins after transition into plastic deformation for both nanoindenters. Characterizations of the region beneath a nanoindent by transmission electron microscopy revealed a martensitic transformation as an activated deformationmore » mechanism and suggest a correlation with the pop-in phenomena of the load-displacement curves. Furthermore, due to an inhomogeneous chemical composition within the austenitic dendrites, more stabilized regions deform by mechanical twinning. This additional deformation mechanism was only observed for the cube corner indenter with the sharper geometry since higher shear stresses are induced beneath the contact area.« less

Performance analysis of next-generation lunar laser retroreflectors

NASA Astrophysics Data System (ADS)

Ciocci, Emanuele; Martini, Manuele; Contessa, Stefania; Porcelli, Luca; Mastrofini, Marco; Currie, Douglas; Delle Monache, Giovanni; Dell'Agnello, Simone

2017-09-01

Starting from 1969, Lunar Laser Ranging (LLR) to the Apollo and Lunokhod Cube Corner Retroreflectors (CCRs) provided several tests of General Relativity (GR). When deployed, the Apollo/Lunokhod CCRs design contributed only a negligible fraction of the ranging error budget. Today the improvement over the years in the laser ground stations makes the lunar libration contribution relevant. So the libration now dominates the error budget limiting the precision of the experimental tests of gravitational theories. The MoonLIGHT-2 project (Moon Laser Instrumentation for General relativity High-accuracy Tests - Phase 2) is a next-generation LLR payload developed by the Satellite/lunar/GNSS laser ranging/altimetry and Cube/microsat Characterization Facilities Laboratory (SCF _ Lab) at the INFN-LNF in collaboration with the University of Maryland. With its unique design consisting of a single large CCR unaffected by librations, MoonLIGHT-2 can significantly reduce error contribution of the reflectors to the measurement of the lunar geodetic precession and other GR tests compared to Apollo/Lunokhod CCRs. This paper treats only this specific next-generation lunar laser retroreflector (MoonLIGHT-2) and it is by no means intended to address other contributions to the global LLR error budget. MoonLIGHT-2 is approved to be launched with the Moon Express 1(MEX-1) mission and will be deployed on the Moon surface in 2018. To validate/optimize MoonLIGHT-2, the SCF _ Lab is carrying out a unique experimental test called SCF-Test: the concurrent measurement of the optical Far Field Diffraction Pattern (FFDP) and the temperature distribution of the CCR under thermal conditions produced with a close-match solar simulator and simulated space environment. The focus of this paper is to describe the SCF _ Lab specialized characterization of the performance of our next-generation LLR payload. While this payload will improve the contribution of the error budget of the space segment (MoonLIGHT-2) to GR tests and to constraints on new gravitational theories (like non-minimally coupled gravity and spacetime torsion), the description of the associated physics analysis and global LLR error budget is outside of the chosen scope of present paper. We note that, according to Reasenberg et al. (2016), software models used for LLR physics and lunar science cannot process residuals with an accuracy better than few centimeters and that, in order to process millimeter ranging data (or better) coming from (not only) future reflectors, it is necessary to update and improve the respective models inside the software package. The work presented here on results of the SCF-test thermal and optical analysis shows that a good performance is expected by MoonLIGHT-2 after its deployment on the Moon. This in turn will stimulate improvements in LLR ground segment hardware and help refine the LLR software code and models. Without a significant improvement of the LLR space segment, the acquisition of improved ground LLR hardware and challenging LLR software refinements may languish for lack of motivation, since the librations of the old generation LLR payloads largely dominate the global LLR error budget.

Apollo 17 Lunar Surface Experiments package

NASA Image and Video Library

1972-05-10

S72-37260 (November 1972) --- The remote antenna for the Lunar Seismic Profiling Experiment, Numbered S-203, a component of the Apollo Lunar Surface Experiments Package which will be carried on the Apollo 17 lunar landing mission. LSPE components are four geophones similar to those used in earlier active seismic experiments an electronics package in the ALSEP central station, and eight explosive packages which will be deployed during the geology traverse. The four geophones will be placed one in the center and at each corner of a 90-meter equilateral triangle. Explosive charges placed on the surface will generate seismic waves of varying strengths to provide data on the structural profile of the landing site. After the charges have been fired by ground command, the experiment will settle down into a passive listening mode, detecting moonquakes, meteorite impacts and the thump caused by the Lunar Module ascent stage impact. The antenna is of the telescoping type.

Apollo 17 Lunar Surface Experiment equipment

NASA Image and Video Library

1972-11-30

S72-37259 (November 1972) --- The Geophone Module and Cable Reels of the Lunar Seismic Profiling Experiment (S-203), a component of the Apollo Lunar Surface Experiments Package which will be carried on the Apollo 17 lunar landing mission. LSPE components are four geophones similar to those used in an earlier active seismic experiment, an electronics package in the ALSEP central station, and eight explosive packages which will be deployed during the geology traverse. The four geophones will be placed one in the center and one at each corner of a 90-meter equilateral triangle. Explosive charges placed on the surface will generate seismic waves of varying strengths to provide data on the structural profile of the landing site. After the charges have been fired by ground command, the experiment will settle down into a passive listening mode, detecting moonquakes, meteorite impacts and the thump caused by the Lunar Module ascent stage impact.

Lunar cement and lunar concrete

NASA Technical Reports Server (NTRS)

Lin, T. D.

1991-01-01

Results of a study to investigate methods of producing cements from lunar materials are presented. A chemical process and a differential volatilization process to enrich lime content in selected lunar materials were identified. One new cement made from lime and anorthite developed compressive strengths of 39 Mpa (5500 psi) for 1 inch paste cubes. The second, a hypothetical composition based on differential volatilization of basalt, formed a mineral glass which was activated with an alkaline additive. The 1 inch paste cubes, cured at 100C and 100 percent humidity, developed compressive strengths in excess of 49 Mpa (7100 psi). Also discussed are tests made with Apollo 16 lunar soil and an ongoing investigation of a proposed dry mix/steam injection procedure for casting concrete on the Moon.

The Moon as a Laser-ranged Test Body for General Relativity and New Gravitational Physics

NASA Astrophysics Data System (ADS)

Dell'Agnello, Simone; Currie, Douglas

Since the 1970s Lunar Laser Ranging (LLR) to the Apollo/Lunokhod Cube Corner Retroreflector (CCR) Arrays supplied some of the best tests of General Relativity (GR): possible changes in the gravitational constant, gravitational self-energy (PPN parameter beta), weak equivalence principle, geodetic precession, inverse-square force-law. Secondly, LLR has provided significant information on the composition of the deep interior of the Moon. LLR physics analysis also allows to set constraints on extensions of GR (like spacetime torsion) and, possibly, on new gravitational physics which may explain the gravitational universe without Dark Matter and Dark Energy (like, for example, Non-Minimally Coupled gravity, NMC). LLR is the only Apollo/Lunokhod experiment still in operation, since 45 years. In the 1970s Apollo/Lunokohd LLR Arrays contributed a negligible fraction of the ranging error budget. Since the ranging capabilities of ground stations improved by more than two orders of magnitude, now, because of the lunar librations, Apollo/Lunokhod CCR arrays dominate the error budget. With the US/Italy project "LLRRA21/MoonLIGHT (Lunar Laser Ranging Retroreflector Array for the 21st century / Moon Laser Instrumentation for General relativity High accuracy Tests)", University of Maryland and INFN-LNF developed and tested a next-generation LLR payload made by a single, large CCR (100 mm diameter), unaffected by the effect of librations. In fact, we will show that MoonLIGHT reflectors will improve the LLR accuracy by a factor of ten to one hundred in a few years. INFN-LNF also developed a laser retroreflector micropayload to be deployed on the lunar surface to be laser-ranged by lunar orbiters. The latter micropayload will further extend the physics reach of Apollo, Lunokhod and MoonLIGHT CCRs to improve all precision tests of GR and new gravitational physics using LLR data. As an added value for the LRR and SLR (Satellite Laser ranging) disciplines INFN-LNF built and is operating a unique ground infrastructure, the SCF-Lab (Satellite/lunar/GNSS laser ranging and altimetry Characterization Facilities Laboratory) and created a new industry-standard test procedure (SCF-Test) to characterize and model the detailed thermal behavior and the optical performance of CCRs in accurately laboratory-simulated space conditions for science (like LLR) and for industrial applications (for example to the Galileo and Copernicus European flagship space programs). Our key experimental innovation is the concurrent measurement and modeling of the optical Far Field Diffraction Pattern (FFDP), Wavefront Fizeau Interferometry (WFI) and the temperature distribution of laser retroreflector payloads under thermal conditions produced with up to two close-match AM0 solar simulators. The SCF-Lab includes infrared cameras for non-invasive thermometry, thermal control and real-time payload movement to simulate satellite orientation on orbit with respect to solar illumination and laser interrogation beams. These capabilities provide: unique pre-launch performance validation of the space segment of LLR/SLR; retroreflector design optimization to maximize ranging efficiency and signal-to-noise conditions in daylight. Negotiations are underway to propose our payload and SCF-Test services for precision gravity and lunar science measurements with next robotic lunar landing missions. Results on analysis of Apollo LLR data and search of new gravitational physics with LLR, Mercury Radar Ranging, SLR of LAGEOS (Laser GEOdynamics Satellite) will also be presented.

Apollo 9 Mission image - S0-65 Multispectral Photography - Alabama

NASA Image and Video Library

2009-02-19

AS09-26A-3790A (11 March 1969) --- Color infrared photograph of the Birmingham to Gadsden area of Alabama as seen from the Apollo 9 spacecraft during its 121st revolution of Earth. This picture was taken as a part of the SO65 Multispectral Terrain Photography Experiment. Birmingham is at left center edge of picture; Gadsden is near top center edge of photograph. Note folded mountains of southern Appalachian chain extending northeast-southwest. The major river in picture which runs generally southward is the Coosa River. The Tallapoosa River, which flows into Lake Martin, is in the southeast corner of picture. Interstate 20 runs from Birmingham eastward toward Atlanta. The City of Anniston is south of Gadsden on Interstate 20.

Mexico, Arizona, Gulf of California as seen from Apollo 6 unmanned spacecraft

NASA Image and Video Library

1968-04-04

AS06-02-1436 (4 April 1968) --- View of the mouth of the Colorado River and the Gulf of California in northwestern Mexico as photographed from the unmanned Apollo 6 (Spacecraft 020/Saturn 502) space mission. Altitude of the spacecraft at the time picture was taken was 120 nautical miles. NORTH IS TOWARD LEFT SIDE OF PICTURE. At bottom edge of photograph is Baja California. In the upper left corner is the Mexican state of Sonora showing the Sonoran Desert and the Pinacate Mountains. This photograph was made three hours and seven minutes after liftoff using Eastman Kodak SO-121 high resolution aerial Ektachrome film (exposure setting was f/5.6 at 1/500 second) in a J.A. Maurer model 2200 camera.

Determination of the crystal structure and composition of Li6Be4OH12 by the stochastic method.

PubMed Central

Pauling, L

1990-01-01

Because of the failure to find a structure for LiBeH3 with a face-centered unit cube with edge 5.09 A, the x-ray powder pattern has been reindexed for a body-centered unit cube with edge 7.24 A. Application of the principles of structural chemistry leads to the formula Li6Be4OH12 and to a structure involving Be4OH12 clusters formed by 4 BeOH3 tetrahedra with their O corner shared, Be--(H,O) bond length 1.59 A, and with the clusters joined to one another by Li with octahedral or rectangular-planar coordination of 6 H or 4 H, Li-H bond lengths about 1.92 A. PMID:11607052

Determination of the crystal structure and composition of Li6Be4OH12 by the stochastic method.

PubMed

Pauling, L

1990-01-01

Because of the failure to find a structure for LiBeH3 with a face-centered unit cube with edge 5.09 A, the x-ray powder pattern has been reindexed for a body-centered unit cube with edge 7.24 A. Application of the principles of structural chemistry leads to the formula Li6Be4OH12 and to a structure involving Be4OH12 clusters formed by 4 BeOH3 tetrahedra with their O corner shared, Be--(H,O) bond length 1.59 A, and with the clusters joined to one another by Li with octahedral or rectangular-planar coordination of 6 H or 4 H, Li-H bond lengths about 1.92 A.

Asynchronous Communication Scheme For Hypercube Computer

NASA Technical Reports Server (NTRS)

Madan, Herb S.

1988-01-01

Scheme devised for asynchronous-message communication system for Mark III hypercube concurrent-processor network. Network consists of up to 1,024 processing elements connected electrically as though were at corners of 10-dimensional cube. Each node contains two Motorola 68020 processors along with Motorola 68881 floating-point processor utilizing up to 4 megabytes of shared dynamic random-access memory. Scheme intended to support applications requiring passage of both polled or solicited and unsolicited messages.

Retro-detective control structures for free-space optical communication links.

PubMed

Jin, Xian; Barg, Jason E; Holzman, Jonathan F

2009-12-21

A corner-cube-based retro-detection photocell is introduced. The structure consists of three independent and mutually perpendicular photodiodes (PDs), whose differential photocurrents can be used to probe the alignment state of incident beams. These differential photocurrents are used in an actively-controlled triangulation procedure to optimize the communication channel alignment in a free-space optical (FSO) system. The active downlink and passive uplink communication capabilities of this system are demonstrated.

Preliminary results from the portable standard satellite laser ranging intercomparison with MOBLAS-7

NASA Technical Reports Server (NTRS)

Selden, Michael; Varghese, Thomas K.; Heinick, Michael; Oldham, Thomas

1993-01-01

Conventional Satellite Laser Ranging (SLR) instrumentation has been configured and successfully used to provide high-accuracy laboratory measurements on the LAGEOS-2 and TOPEX cube-corner arrays. The instrumentation, referred to as the Portable Standard, has also been used for field measurements of satellite ranges in tandem with MOBLAS-7. Preliminary results of the SLR measurements suggest that improved range accuracy can be achieved using this system. Results are discussed.

Jones's matrix representation of optical instruments. II - Fourier interferometers /spectrometers and spectropolarimeters/.

NASA Technical Reports Server (NTRS)

Fymat, A. L.

1971-01-01

Our method of matrix synthesis of optical components and instruments is applied to the derivation of Jones's matrices appropriate for Fourier interferometers (spectrometers and spectropolarimeters). These matrices are obtained for both the source beam and the detector beam. In the course of synthesis, Jones's matrices of the various reflectors (plane mirrors; retroreflectors: roofed mirror, trihedral and prism cube corner, cat's eye) used by these interferometers are also obtained.

Determination of Atomic and Molecular Excited-State Lifetimes Using an Opto-electronic Cross-Correlation Method.

DTIC Science & Technology

1981-10-07

new instrument (cf. Fig. 1) is simply a four - quadrant ring-diode multi- 5 plier (Fig. 2). The reference frequency (RF) and local oscillator (LO) inputs...movement, and scan speed of the corner-cube. Other Components. A rotating-sector chopper modulates the laser pulse train at a frequency of approximately 50...the cross-correlation experiment. In this application, the detection bandpass is simply displaced from DC to the chopper frequency; problems arising

Method of calculating retroreflector-array transfer functions. [laser range finders

NASA Technical Reports Server (NTRS)

Arnold, D. A.

1978-01-01

Techniques and equations used in calculating the transfer functions to relate the observed return laser pulses to the center of mass of the Lageos satellite retroflector array, and for most of the retroreflector-equipped satellites now in orbit are described. The methods derived include the effects of coherent interference, diffraction, polarization, and dihedral-angle offsets. Particular emphasis is given to deriving expressions for the diffraction pattern and active reflecting area of various cube-corner designs.

Vertical high-precision Michelson wavemeter

NASA Astrophysics Data System (ADS)

Morales, A.; de Urquijo, J.; Mendoza, A.

1993-01-01

We have designed and tested a traveling, Michelson-type vertical wavemeter for the wavelength measurement of tunable continuous-wave lasers in the visible part of the spectrum. The interferometer has two movable corner cubes, suspending vertically from a driving setup resembling Atwood's machine. To reduce the fraction-of-fringe error, a vernier-type coincidence circuit was used. Although simple, this wavemeter has a relative precision of 3.2 parts in 109 for an overall fringe count of about 7×106.

TEM in situ cube-corner indentation analysis using ViBe motion detection algorithm

NASA Astrophysics Data System (ADS)

Yano, K. H.; Thomas, S.; Swenson, M. J.; Lu, Y.; Wharry, J. P.

2018-04-01

Transmission electron microscopic (TEM) in situ mechanical testing is a promising method for understanding plasticity in shallow ion irradiated layers and other volume-limited materials. One of the simplest TEM in situ experiments is cube-corner indentation of a lamella, but the subsequent analysis and interpretation of the experiment is challenging, especially in engineering materials with complex microstructures. In this work, we: (a) develop MicroViBE, a motion detection and background subtraction-based post-processing approach, and (b) demonstrate the ability of MicroViBe, in combination with post-mortem TEM imaging, to carry out an unbiased qualitative interpretation of TEM indentation videos. We focus this work around a Fe-9%Cr oxide dispersion strengthened (ODS) alloy, irradiated with Fe2+ ions to 3 dpa at 500 °C. MicroViBe identifies changes in Laue contrast that are induced by the indentation; these changes accumulate throughout the mechanical loading to generate a "heatmap" of features in the original TEM video that change the most during the loading. Dislocation loops with b = ½ <111> identified by post-mortem scanning TEM (STEM) imaging correspond to hotspots on the heatmap, whereas positions of dislocation loops with b = <100> do not correspond to hotspots. Further, MicroViBe enables consistent, objective quantitative approximation of the b = ½ <111> dislocation loop number density.

Flexible corner cube retroreflector array for temperature and strain sensing† †Electronic supplementary information (ESI) available. See DOI: 10.1039/c7ra13284k

PubMed Central

Khalid, Muhammad Waqas; Ahmed, Rajib; Yetisen, Ali K.

2018-01-01

Optical sensors for detecting temperature and strain play a crucial role in the analysis of environmental conditions and real-time remote sensing. However, the development of a single optical device that can sense temperature and strain simultaneously remains a challenge. Here, a flexible corner cube retroreflector (CCR) array based on passive dual optical sensing (temperature and strain) is demonstrated. A mechanical embossing process was utilised to replicate a three-dimensional (3D) CCR array in a soft flexible polymer film. The fabricated flexible CCR array samples were experimentally characterised through reflection measurements followed by computational modelling. As fabricated samples were illuminated with a monochromatic laser beam (635, 532, and 450 nm), a triangular shape reflection was obtained at the far-field. The fabricated flexible CCR array samples tuned retroreflected light based on external stimuli (temperature and strain as an applied force). For strain and temperature sensing, an applied force and temperature, in the form of weight suspension, and heat flow was applied to alter the replicated CCR surface structure, which in turn changed its optical response. Directional reflection from the heated flexible CCR array surface was also measured with tilt angle variation (max. up to 10°). Soft polymer CCRs may have potential in remote sensing applications, including measuring the temperature in space and in nuclear power stations. PMID:29568510

45 Mbps cat's eye modulating retro-reflector link over 7 Km

NASA Astrophysics Data System (ADS)

Rabinovich, W. S.; Mahon, R.; Goetz, P. G.; Swingen, L.; Murphy, J.; Ferraro, M.; Burris, R.; Suite, M.; Moore, C. I.; Gilbreath, G. C.; Binari, S.

2006-09-01

Modulating retro-reflectors (MRR) allow free space optical links with no need for pointing, tracking or a laser on one end of the link. They work by coupling a passive optical retro-reflector with an optical modulator. The most common kind of MRR uses a corner cube retro-reflector. These devices must have a modulator whose active area is as large as the area of the corner cube. This limits the ability to close longer range high speed links because the large aperture need to return sufficient light implies a large modulator capacitance. To overcome this limitation we developed the concept of a cat's eye MRR. Cat's eye MRRs place the modulator in the focal plane of a lens system designed to passively retro-reflect light. Because the light focuses onto the modulator, a small, low capacitance, modulator can be used with a large optical aperture. However, the position of the focal spot varies with the angle of incidence so an array of modulators must be placed in the focal plane, In addition, to avoid having to drive all the modulator pixels, an angle of arrival sensor must be used. We discuss several cat's eye MRR systems with near diffraction limited performance and bandwidths of 45 Mbps. We also discuss a link to a cat's eye MRR over a 7 Km range.

Physical properties of concrete made with Apollo 16 lunar soil sample

NASA Technical Reports Server (NTRS)

Lin, T. D.; Love, H.; Stark, D.

1992-01-01

This paper describes the first phase of the long-term investigation for the construction of concrete lunar bases. In this phase, petrographic and scanning electron microscope examinations showed that the morphology and elemental composition of the lunar soil made it suitable for use as a fine aggregate for concrete. Based on this finding, calcium aluminate cement and distilled water were mixed with the lunar soil to fabricate test specimens. The test specimens consisted of a 1-in cube, a 1/2-in cube, and three 0.12 x 0.58 x 3.15-in beam specimens. Tests were performed on these specimens to determine compressive strength, modulus of rupture, modulus of elasticity, and thermal coefficient of expansion. Based on examination of the material and test results, it is concluded that lunar soil can be used as a fine aggregate for concrete.

The Apollo Capsule Optimization for Improved Stability and Computational/Experimental Data Comparisons

NASA Technical Reports Server (NTRS)

Cliff, Susan E.; Thomas, Scott D.

2005-01-01

Numerical optimization was employed on the Apollo Command Module to modify its external shape. The Apollo Command Module (CM) that was used on all NASA human space flights during the Apollo Space Program is stable and trimmed in an apex forward (alpha of approximately 40 to 80 degrees) position. This poses a safety risk if the CM separates from the launch tower during abort. Optimization was employed on the Apollo CM to remedy the undesirable stability characteristics of the configuration. Geometric shape changes were limited to axisymmetric modifications that altered the radius of the apex (R(sub A)), base radius (R(sub O)), corner radius (R(sub C)), and the cone half angle (theta), while the maximum diameter of the CM was held constant. The results of multipoint optimization on the CM indicated that the cross-range performance can be improved while maintaining robust apex-aft stability with a single trim point. Navier-Stokes computations were performed on the baseline and optimized configurations and confirmed the Euler-based optimization results. Euler Analysis of ten alternative CM vehicles with different values of the above four parameters are compared with the published experimental results of numerous wind tunnel tests during the late 1960's. These comparisons cover a wide Mach number range and a full 180-degree pitch range and show that the Euler methods are capable of fairly accurate force and moment computations and can separate the vehicle characteristics of these ten alternative configurations.

Development of a Single-Longitudinal-Mode Ho:YAG Laser Based on Corner Cube

NASA Astrophysics Data System (ADS)

Jing, Wu; You-Lun, Ju; Tong-Yu, Dai; Zhen-Guo, Zhang; Bao-Quan, Yao; Yue-Zhu, Wang

2016-04-01

Not Available Supported by the National Natural Science Foundation of China under Grant Nos 61308009 and 61405047, the China Postdoctoral Science Foundation Funded Project under Grant No 2013M540288, the Fundamental Research Funds for the Central Universities under Grant Nos HIT.NSRIF.2014044 and HIT.NSRIF.2015042, the Science Fund for Outstanding Youths of Heilongjiang Province under Grant No JQ201310, and the Heilongjiang Postdoctoral Science Foundation Funded Project under Grant No LBH-Z14085.

Next-generation laser retroreflectors for GNSS, solar system exploration, geodesy, gravitational physics and earth observation

NASA Astrophysics Data System (ADS)

Dell'Agnello, S.; Boni, A.; Cantone, C.; Ciocci, E.; Martini, M.; Patrizi, G.; Tibuzzi, M.; Delle Monache, G.; Vittori, R.; Bianco, G.; Currie, D.; Intaglietta, N.; Salvatori, L.; Lops, C.; Contessa, S.; Porcelli, L.; Mondaini, C.; Tuscano, P.; Maiello, M.

2017-11-01

The SCF_Lab (Satellite/lunar/gnss laser ranging and altimetry Characterization Facility Laboratory) of INFNLNF is designed to cover virtually LRAs (Laser Retroreflector Arrays) of CCRs (Cube Corner Retroreflectors) for missions in the whole solar system, with a modular organization of its instrumentation, two redundant SCF (SCF_Lab Characterization Facilities), and an evolutionary measurement approach, including customization and potentially upgrade on-demand. See http://www.lnf.infn.it/esperimenti/etrusco/ for a general description.

Enhanced backscatter of optical beams reflected in turbulent air

NASA Astrophysics Data System (ADS)

Nelson, W.; Palastro, J. P.; Wu, C.; Davis, C. C.

2015-07-01

Optical beams propagating through air acquire phase distortions from turbulent fluctuations in the refractive index. While these distortions are usually deleterious to propagation, beams reflected in a turbulent medium can undergo a local recovery of spatial coherence and intensity enhancement referred to as enhanced backscatter (EBS). Using a combination of lab-scale experiments and simulations, we investigate the EBS of optical beams reflected from corner cubes and rough surfaces, and identify the regimes in which EBS is most distinctly observed.

InGaAs Multiple Quantum Well Modulating Retro-reflector for Free Space Optical Communications

DTIC Science & Technology

2002-01-01

PIN optical modulators grown on GaAs substrates by molecular beam epitaxy ,J. Vac Sci. B 18, 1609-16 13 (2000). Peter G. Goetz, W. S. Rabinovich...reflector is then interrogated by a cw laser beam from a conventional optical communications system and returns a modulated signal beam to the...optical communication systems. By mounting an electro-optic shutter in front of the corner- cube, the retro-reflected beam can be turned on or off (or at

Research on ground-based LWIR hyperspectral imaging remote gas detection

NASA Astrophysics Data System (ADS)

Yang, Zhixiong; Yu, Chunchao; Zheng, Weijian; Lei, Zhenggang; Yan, Min; Yuan, Xiaochun; Zhang, Peizhong

2015-10-01

The new progress of ground-based long-wave infrared remote sensing is presented, which describes the windowing spatial and temporal modulation Fourier spectroscopy imaging in details. The prototype forms the interference fringes based on the corner-cube of spatial modulation of Michelson interferometer, using cooled long-wave infrared photovoltaic staring FPA (focal plane array) detector. The LWIR hyperspectral imaging is achieved by the process of collection, reorganization, correction, apodization, FFT etc. from data cube. Noise equivalent sensor response (NESR), which is the sensitivity index of CHIPED-1 LWIR hyperspectral imaging prototype, can reach 5.6×10-8W/(cm-1.sr.cm2) at single sampling. Hyperspectral imaging is used in the field of organic gas VOC infrared detection. Relative to wide band infrared imaging, it has some advantages. Such as, it has high sensitivity, the strong anti-interference ability, identify the variety, and so on.

High-order central ENO finite-volume scheme for hyperbolic conservation laws on three-dimensional cubed-sphere grids

NASA Astrophysics Data System (ADS)

Ivan, L.; De Sterck, H.; Susanto, A.; Groth, C. P. T.

2015-02-01

A fourth-order accurate finite-volume scheme for hyperbolic conservation laws on three-dimensional (3D) cubed-sphere grids is described. The approach is based on a central essentially non-oscillatory (CENO) finite-volume method that was recently introduced for two-dimensional compressible flows and is extended to 3D geometries with structured hexahedral grids. Cubed-sphere grids feature hexahedral cells with nonplanar cell surfaces, which are handled with high-order accuracy using trilinear geometry representations in the proposed approach. Varying stencil sizes and slope discontinuities in grid lines occur at the boundaries and corners of the six sectors of the cubed-sphere grid where the grid topology is unstructured, and these difficulties are handled naturally with high-order accuracy by the multidimensional least-squares based 3D CENO reconstruction with overdetermined stencils. A rotation-based mechanism is introduced to automatically select appropriate smaller stencils at degenerate block boundaries, where fewer ghost cells are available and the grid topology changes, requiring stencils to be modified. Combining these building blocks results in a finite-volume discretization for conservation laws on 3D cubed-sphere grids that is uniformly high-order accurate in all three grid directions. While solution-adaptivity is natural in the multi-block setting of our code, high-order accurate adaptive refinement on cubed-sphere grids is not pursued in this paper. The 3D CENO scheme is an accurate and robust solution method for hyperbolic conservation laws on general hexahedral grids that is attractive because it is inherently multidimensional by employing a K-exact overdetermined reconstruction scheme, and it avoids the complexity of considering multiple non-central stencil configurations that characterizes traditional ENO schemes. Extensive numerical tests demonstrate fourth-order convergence for stationary and time-dependent Euler and magnetohydrodynamic flows on cubed-sphere grids, and robustness against spurious oscillations at 3D shocks. Performance tests illustrate efficiency gains that can be potentially achieved using fourth-order schemes as compared to second-order methods for the same error level. Applications on extended cubed-sphere grids incorporating a seventh root block that discretizes the interior of the inner sphere demonstrate the versatility of the spatial discretization method.

SU-F-T-661: Dependence of Gold Nano Particles Cluster Morphology On Dose Enhancement of Photon Radiation Therapy Apply for Radiation Biology Effect

DOE Office of Scientific and Technical Information (OSTI.GOV)

Ahn, S; Chung, K; Han, Y

Purpose: Injected gold nano particles (GNPs) to a body for dose enhancement are known to form in the tumorcell cluster morphology. We investigated the dependence of dose enhancement on the morphology characteristic with an approximated morphology model by using Monte Carlo simulations. Methods: For MC simulation, TOPAS version 2.0P-03 was used. GNP cluster morphology was approximated as a body center cubic(BCC) model by placing 8 GNPs at the corner and one at the center of cube with length from 2.59 µm to 0.25 µm located in a 4 µm length water filled cube phantom. 4 µm length square shaped beamsmore » of poly-energetic 50, 260 kVp photons were irradiated to the water filled cube phantom with 100 nm diameter GNPs in it. Dose enhancement ratio(DER) was computed as a function of distance from the surface of the GNP at the cube center for 18 cubes geometries. For scoring particles, 10 nm width of concentric shell shaped detector was constructed up to 100 nm from the center. Total dose in a sphere of 100 nm radius of detector were normalized to 2.59 µm length cube morphology. To verified biological effect of BCC model applied to cell survival curve fitting. Results: DER increase as the distance of the GNPs reduces. DER was largest for 0.25 µm length cube. Dependence of GNP distance DER increment was 1.73, 1.60 for 50 kVp, 260 kVp photons, respectively. Also, Using BCC model applied to cell survival curve was well prediction. Conclusion: DER with GNPs was larger when they are closely packed in the phantom. Therefore, better therapeutic effects can be expected with close-packed GNPs. This research was supported by the NRF funded by the Ministry of Science, ICT & Future Planning (2012M3A9B6055201 and 2012R1A1A2042414), Samsung Medical Center grant[GFO1130081].« less

Self-Assembly of Flux-Closure Polygons from Magnetite Nanocubes.

PubMed

Szyndler, Megan W; Corn, Robert M

2012-09-06

Well-defined nanoscale flux-closure polygons (nanogons) have been fabricated on hydrophilic surfaces from the face-to-face self-assembly of magnetite nanocubes. Uniform ferrimagnetic magnetite nanocubes (∼86 nm) were synthesized and characterized with a combination of electron microscopy, diffraction, and magnetization measurements. The nanocubes were subsequently cast onto hydrophilic substrates, wherein the cubes lined up face-to-face and formed a variety of polygons due to magnetostatic and hydrophobic interactions. The generated surfaces consist primarily of three- and four-sided nanogons; polygons ranging from two to six sides were also observed. Further examination of the nanogons showed that the constraints of the face-to-face assembly of nanocubes often led to bowed sides, strained cube geometries, and mismatches at the acute angle vertices. Additionally, extra nanocubes were often present at the vertices, suggesting the presence of external magnetostatic fields at the polygon corners. These nanogons are inimitable nanoscale magnetic structures with potential applications in the areas of magnetic memory storage and high-frequency magnetics.

SU-E-T-570: New Quality Assurance Method Using Motion Tracking for 6D Robotic Couches

DOE Office of Scientific and Technical Information (OSTI.GOV)

Cheon, W; Cho, J; Ahn, S

Purpose: To accommodate geometrically accurate patient positioning, a robotic couch that is capable of 6-degrees of freedom has been introduced. However, conventional couch QA methods are not sufficient to enable the necessary accuracy of tests. Therefore, we have developed a camera based motion detection and geometry calibration system for couch QA. Methods: Employing a Visual-Tracking System (VTS, BonitaB10, Vicon, UK) which tracks infrared reflective(IR) markers, camera calibration was conducted using a 5.7 × 5.7 × 5.7 cm{sup 3} cube attached with IR markers at each corner. After positioning a robotic-couch at the origin with the cube on the table top,more » 3D coordinates of the cube’s eight corners were acquired by VTS in the VTS coordinate system. Next, positions in reference coordinates (roomcoordinates) were assigned using the known relation between each point. Finally, camera calibration was completed by finding a transformation matrix between VTS and reference coordinate systems and by applying a pseudo inverse matrix method. After the calibration, the accuracy of linear and rotational motions as well as couch sagging could be measured by analyzing the continuously acquired data of the cube while the couch moves to a designated position. Accuracy of the developed software was verified through comparison with measurement data when using a Laser tracker (FARO, Lake Mary, USA) for a robotic-couch installed for proton therapy. Results: VTS system could track couch motion accurately and measured position in room-coordinates. The VTS measurements and Laser tracker data agreed within 1% of difference for linear and rotational motions. Also because the program analyzes motion in 3-Dimension, it can compute couch sagging. Conclusion: Developed QA system provides submillimeter/ degree accuracy which fulfills the high-end couch QA. This work was supported by the National Research Foundation of Korea funded by Ministry of Science, ICT & Future Planning. (2013M2A2A7043507 and 2012M3A9B6055201)« less

Study of hollow corner retroreflectors for use in a synchronous orbit

NASA Technical Reports Server (NTRS)

Yoder, P. R., Jr.

1975-01-01

The performance of a hollow corner cube retroreflector made up of three mutually perpendicular optically flat mirrors when undergoing the thermal-mechanical strains induced by a spacecraft environment was studied. Of particular interest was a device of 200 square centimeter optical aperture used on a satellite in a synchronous orbit. It was assumed that the reflector always faces the earth. The effects of direct solar irradiance, earthshine, and albedo were considered. The results included the maximum mirror surface temperature during the orbit as well as the worst-case loss of optical performance due to thermally-induced mirror distortions. It was concluded that a device made of three suitably coated flat ULE mirrors, optically contacted to each other and supported mechanically in a nonrigid mount, would be expected to concentrate over 80 percent of the theoretical maximum energy in the central of the far field diffraction pattern. Continued development of the device through a detailed design, fabrication, and test phase was recommended.

The study of the mission instruments of GOSAT-2

NASA Astrophysics Data System (ADS)

Suto, H.; Nakajima, M.; Kuze, A.; Shiomi, K.; Shimoda, H.

2012-12-01

Greenhouse Gases Observing Satellite "GOSAT" was launched in January of 2009 and have observed the carbon dioxide and the methane almost four years. Additionally, the Level 1B algorithm has been improved based on the on board calibration and ground test using Engineering model and the accuracy of the level 1B data, that is the spectrum, has been improved. This has led to the more accurate calculation of the concentration of carbon dioxide and methane with small bias. At the same time, some issues have become clearer little by little through the on orbit operation. Especially a lot of data have been affected by the cloud, so few data have been used until now. However, the satellite has come to be recognized as an effective means of the detection of the global distribution of the greenhouse gases concentration. And in addition to the effort to resolve the issues which have become clear until now, the improvement of the observation performance have been required by a lot of users. Therefore, we researched the concrete requirements of users and set the mission requirements for GOSAT-2. Based on this mission requirement, we have studied the possibilities of these requirements. This study was implemented as premises for the usage of the Fourier Transform Spectrometer to detect the greenhouse gases as well as GOSAT. We considered the methods to increase the number of the useful data. For example, the reduction of the footprints size, increase of the number of the IFOV, the intelligent pointing and so on. It's necessary to maintain the Signal to Noise ration of the GOSAT. In addition to the method to increase the number of the useful data, we have researched the size of the aperture of the optics to maintain the signal to noise ratio corresponding to the reduction of the footprint seize. But the possibility of the corner cube used in the Fourier transform spectrometer limits the aperture size. We decided the aperture size (and corner cube size) based on the trade-off among corner cube size, footprint size and signal to noise ratio and the opinions of the scientists. In addition to the improvements of the performaces, the following requirements has been presented. To evaluate the relative matters of the anthropogenic emissions, to contribute to the MRV of REDD+ and so on. In order to meet these requirements the Fourier Transform Spectrometer on GOSAT-2 will has the additional observation channel for the carbon monoxide and Imager will has the spectrometer using the grating for Nitorgen Dioxide. Now we are investigating the possibilities of these additional functions and increase of the performances and we will decide the specifications of GOSAT-2 within one year.

A quantitative study on magnesium alloy stent biodegradation.

PubMed

Gao, Yuanming; Wang, Lizhen; Gu, Xuenan; Chu, Zhaowei; Guo, Meng; Fan, Yubo

2018-06-06

Insufficient scaffolding time in the process of rapid corrosion is the main problem of magnesium alloy stent (MAS). Finite element method had been used to investigate corrosion of MAS. However, related researches mostly described all elements suffered corrosion in view of one-dimensional corrosion. Multi-dimensional corrosions significantly influence mechanical integrity of MAS structures such as edges and corners. In this study, the effects of multi-dimensional corrosion were studied using experiment quantitatively, then a phenomenological corrosion model was developed to consider these effects. We implemented immersion test with magnesium alloy (AZ31B) cubes, which had different numbers of exposed surfaces to analyze differences of dimension. It was indicated that corrosion rates of cubes are almost proportional to their exposed-surface numbers, especially when pitting corrosions are not marked. The cubes also represented the hexahedron elements in simulation. In conclusion, corrosion rate of every element accelerates by increasing corrosion-surface numbers in multi-dimensional corrosion. The damage ratios among elements with the same size are proportional to the ratios of corrosion-surface numbers under uniform corrosion. The finite element simulation using proposed model provided more details of changes of morphology and mechanics in scaffolding time by removing 25.7% of elements of MAS. The proposed corrosion model reflected the effects of multi-dimension on corrosions. It would be used to predict degradation process of MAS quantitatively. Copyright © 2018 Elsevier Ltd. All rights reserved.

Preliminary Neutronics Analysis of the ITER Toroidal Interferometer and Polarimeter Diagnostic Corner Cube Retroreflectors

DOE Office of Scientific and Technical Information (OSTI.GOV)

Tresemer, K. R.

2015-07-01

ITER is an international project under construction in France that will demonstrate nuclear fusion at a power plant-relevant scale. The Toroidal Interferometer and Polarimeter (TIP) Diagnostic will be used to measure the plasma electron line density along 5 laser-beam chords. This line-averaged density measurement will be input to the ITER feedback-control system. The TIP is considered the primary diagnostic for these measurements, which are needed for basic ITER machine control. Therefore, system reliability & accuracy is a critical element in TIP’s design. There are two major challenges to the reliability of the TIP system. First is the survivability and performancemore » of in-vessel optics and second is maintaining optical alignment over long optical paths and large vessel movements. Both of these issues greatly depend on minimizing the overall distortion due to neutron & gamma heating of the Corner Cube Retroreflectors (CCRs). These are small optical mirrors embedded in five first wall locations around the vacuum vessel, corresponding to certain plasma tangency radii. During the development of the design and location of these CCRs, several iterations of neutronics analyses were performed to determine and minimize the total distortion due to nuclear heating of the CCRs. The CCR corresponding to TIP Channel 2 was chosen for analysis as a good middle-road case, being an average distance from the plasma (of the five channels) and having moderate neutron shielding from its blanket shield housing. Results show that Channel 2 meets the requirements of the TIP Diagnostic, but barely. These results suggest other CCRs might be at risk of exceeding thermal deformation due to nuclear heating.« less

Measuring Cyclic Error in Laser Heterodyne Interferometers

NASA Technical Reports Server (NTRS)

Ryan, Daniel; Abramovici, Alexander; Zhao, Feng; Dekens, Frank; An, Xin; Azizi, Alireza; Chapsky, Jacob; Halverson, Peter

2010-01-01

An improved method and apparatus have been devised for measuring cyclic errors in the readouts of laser heterodyne interferometers that are configured and operated as displacement gauges. The cyclic errors arise as a consequence of mixing of spurious optical and electrical signals in beam launchers that are subsystems of such interferometers. The conventional approach to measurement of cyclic error involves phase measurements and yields values precise to within about 10 pm over air optical paths at laser wavelengths in the visible and near infrared. The present approach, which involves amplitude measurements instead of phase measurements, yields values precise to about .0.1 microns . about 100 times the precision of the conventional approach. In a displacement gauge of the type of interest here, the laser heterodyne interferometer is used to measure any change in distance along an optical axis between two corner-cube retroreflectors. One of the corner-cube retroreflectors is mounted on a piezoelectric transducer (see figure), which is used to introduce a low-frequency periodic displacement that can be measured by the gauges. The transducer is excited at a frequency of 9 Hz by a triangular waveform to generate a 9-Hz triangular-wave displacement having an amplitude of 25 microns. The displacement gives rise to both amplitude and phase modulation of the heterodyne signals in the gauges. The modulation includes cyclic error components, and the magnitude of the cyclic-error component of the phase modulation is what one needs to measure in order to determine the magnitude of the cyclic displacement error. The precision attainable in the conventional (phase measurement) approach to measuring cyclic error is limited because the phase measurements are af-

Aerial 3D display by use of a 3D-shaped screen with aerial imaging by retro-reflection (AIRR)

NASA Astrophysics Data System (ADS)

Kurokawa, Nao; Ito, Shusei; Yamamoto, Hirotsugu

2017-06-01

The purpose of this paper is to realize an aerial 3D display. We design optical system that employs a projector below a retro-reflector and a 3D-shaped screen. A floating 3D image is formed with aerial imaging by retro-reflection (AIRR). Our proposed system is composed of a 3D-shaped screen, a projector, a quarter-wave retarder, a retro-reflector, and a reflective polarizer. Because AIRR forms aerial images that are plane-symmetric of the light sources regarding the reflective polarizer, the shape of the 3D screen is inverted from a desired aerial 3D image. In order to expand viewing angle, the 3D-shaped screen is surrounded by a retro-reflector. In order to separate the aerial image from reflected lights on the retro- reflector surface, the retro-reflector is tilted by 30 degrees. A projector is located below the retro-reflector at the same height of the 3D-shaped screen. The optical axis of the projector is orthogonal to the 3D-shaped screen. Scattered light on the 3D-shaped screen forms the aerial 3D image. In order to demonstrate the proposed optical design, a corner-cube-shaped screen is used for the 3D-shaped screen. Thus, the aerial 3D image is a cube that is floating above the reflective polarizer. For example, an aerial green cube is formed by projecting a calculated image on the 3D-shaped screen. The green cube image is digitally inverted in depth by our developed software. Thus, we have succeeded in forming aerial 3D image with our designed optical system.

Next generation retroreflector for lunar laser ranging: science, design and flight status

NASA Astrophysics Data System (ADS)

Currie, Douglas; Richards, Robert; Delle Monache, Giovanni

2016-07-01

The retroreflectors deployed during the Apollo Mission are still operating after 45 years. Analysis of the ranging data has resulted in the discovery and measurement of the liquid core of the moon about 15 years ago. This lunar laser ranging (LLR) program has also produced most of the best tests of Gravitation and General Relativity. However, over the years the ground stations have improved by a factor of ~200 so today the limit in ranging accuracy is due to the combination of the libration of the moon and the design of the Cube Corner Reflector (CCR) arrays. To address this, the University of Maryland, College Park (UMCP) and the INFN-LNF are developing the Next Generation Retroreflectors (NGR. Recently the UMCP and the LNF have signed an agreement with Moon Express, Inc., a commercial company pursuing the Google Lunar X Prize and a space transport business, to deploy four NGRs on the lunar surface, the first of which is expected to fly in the second quarter of 2017. A brief discussion will address the expected improvements in the understanding of Gravitational and General Relativity and the impact this may have on the multiple theories that have been proposed to explain Dark Matter and Dark Energy. The basic objectives, requirements and design will be reviewed. In particular, in order to maintain a signal level similar to that of Apollo 15, thermal gradients within the CCR must be maintain to less than 0.2oK. Since during lunar morning the CCR is at about 70oK and the housing is more than 300oK, the thermal design is critical. The structure and results of the required simulation programs will be reviewed. Finally, the current design of the entire package will be addressed. Looking toward the future, two areas look particularly interesting in extending the coverage of the theories of Gravitation, General Relativity, Dark Matter and Dark Energy. They will support even greater ranging accuracy, additional ground stations and increased coverage. The first is to provide a system that is not reliant on the location and orientation of the lander. This would consist of a system that, immediately after deployment, would detect the location of the earth, point toward the proper direction and then permanently lock to that pointing. The second is to ameliorate the vertical motion of the lander and regolith due to the thermal expansion from lunar night to lunar day. This would take advantage of the thermal stability found about one meter in depth in the regolith.

Current developments in optical engineering and commercial optics; Proceedings of the Meeting, San Diego, CA, Aug. 7-11, 1989

NASA Technical Reports Server (NTRS)

Fischer, Robert E. (Editor); Pollicove, Harvey M. (Editor); Smith, Warren J. (Editor)

1989-01-01

Various papers on current developments in optical engineering and commercial optics are presented. Individual topics addressed include: large optics fabrication technology drivers and new manufacturing techniques, new technology for beryllium mirror production, design examples of hybrid refractive-diffractive lenses, optical sensor designs for detecting cracks in optical materials, retroreflector field-of-view properties for open and solid cube corners, correction of misalignment-dependent aberrations of the HST via phase retrieval, basic radiometry review for seeker test set, radiation effects on visible optical elements, and nonlinear simulation of efficiency for large-orbit nonwiggler FELs.

Laser-ranging scanning system to observe topographical deformations of volcanoes.

PubMed

Aoki, T; Takabe, M; Mizutani, K; Itabe, T

1997-02-20

We have developed a laser-ranging system to observe the topographical structure of volcanoes. This system can be used to measure the distance to a target by a laser and shows the three-dimensional topographical structure of a volcano with an accuracy of 30 cm. This accuracy is greater than that of a typical laser-ranging system that uses a corner-cube reflector as a target because the reflected light jitters as a result of inclination and unevenness of the target ground surface. However, this laser-ranging system is useful for detecting deformations of topographical features in which placement of a reflector is difficult, such as in volcanic regions.

An operational theory of laser-radar selenodesy

USGS Publications Warehouse

Wildey, R.L.; Schlier, R.E.; Hull, J.A.; Larson, G.

1967-01-01

A theory of the utilization of laser techniques for ranging from the Earth to the Moon for the purpose of providing control points on the lunar surface at which the figure of the Moon is measured to an accuracy at least an order of magnitude better than that of the present astrometric measurements is presented. This, in turn, increases the accuracy of the horizontal selenocentric coordinates of topographical features measured by present astrometric methods. The improvement in the vertical and horizontal coordinates of control points in the Apollo landing zone will aid in the analysis of Unmanned Lunar Orbiter photographs for the selection of Apollo landing sites. The present discussion proposes the means of obtaining the ground control upon which the Orbiter photogrammetry is to be fastened. In addition, a technique of combining Goldstone tracking data to show where the resulting lunar figure is positioned relative to the Moon's center of mass is presented. If corner reflectors are placed on the lunar surface, as suggested by many members of the scientific community, or on a lunar orbiting vehicle, one or more Earth-based laser ranging systems are essential. These reflectors will give enough enhancement in return signal to allow for an additional increase in range accuracy of one to two orders of magnitude. In addition to the primary data on the figure of the Moon, a number of other measurements of scientific importance are then readily obtainable. As far as the measurement of control points is concerned, however, the use of corner reflectors is not essential for the success of this project. Questions regarding the influence on the present shape of the Moon of the frozen tide, isostasy, and past impacts of large asteroids appear in large part answerable through the data which are indicated to be obtainable under the present theory. ?? 1967.

Artist's concept of topographical layout of Taurus-Littrow landing site

NASA Image and Video Library

1972-10-01

S72-49761 (October 1972) --- An artist's concept illustrating the topographical layout of the Taurus-Littrow landing site of the Apollo 17 lunar landing mission. The Lunar Module touchdown point is in the center of the smooth area in the middle of the picture. The imposing mountain in the center is South Massif. A portion of North Massif is in the lower right corner of the photograph. Note the ridge-like feature extending from South Massif to North Massif. The southern portion of the ridge is called Lee Scarp and the northerly portion Lincoln Scarp. (This concept is by JSC artist Jerry Elmore).

Enhanced backscatter of optical beams reflected in atmospheric turbulence

NASA Astrophysics Data System (ADS)

Nelson, W.; Palastro, J. P.; Wu, C.; Davis, C. C.

2014-10-01

Optical beams propagating through the atmosphere acquire phase distortions from turbulent fluctuations in the refractive index. While these distortions are usually deleterious to propagation, beams reflected in a turbulent medium can undergo a local recovery of spatial coherence and intensity enhancement referred to as enhanced backscatter (EBS). Using simulations, we investigate the EBS of optical beams reflected from mirrors, corner cubes, and rough surfaces, and identify the regimes in which EBS is most distinctly observed. Standard EBS detection requires averaging the reflected intensity over many passes through uncorrelated turbulence. Here we present an algorithm called the "tilt-shift method" which allows detection of EBS in static turbulence, improving its suitability for potential applications.

Computer access security code system

NASA Technical Reports Server (NTRS)

Collins, Earl R., Jr. (Inventor)

1990-01-01

A security code system for controlling access to computer and computer-controlled entry situations comprises a plurality of subsets of alpha-numeric characters disposed in random order in matrices of at least two dimensions forming theoretical rectangles, cubes, etc., such that when access is desired, at least one pair of previously unused character subsets not found in the same row or column of the matrix is chosen at random and transmitted by the computer. The proper response to gain access is transmittal of subsets which complete the rectangle, and/or a parallelepiped whose opposite corners were defined by first groups of code. Once used, subsets are not used again to absolutely defeat unauthorized access by eavesdropping, and the like.

Evaluation of a MMW active through-the-wall surveillance system

NASA Astrophysics Data System (ADS)

Currie, Nicholas C.; Stiefvater, Kenneth

2002-08-01

This paper discusses the TWS data collected with a state-of- the-art 100 GHz radar imager developed for law enforcement use by Millivision, PPC. The system collects a cube of data consisting of 16 azimuth elements by 16 elevation elements by 256 range elements. The cube represents 11 degrees by 11 degrees by 25 m of coverage. The relatively narrow field-of- view (fov) was extended by physically moving the antenna in 11 degree segments and collecting data which is stitched together into larger images, e.g. a 3X3 stitched image represents 33 degrees by 33 degrees by 26 m of coverage. Unfortunately, this stitching process required up to 5 minutes to collect a single (3X3) stitched image. Thus, motion had to be simulated. The paper will discuss the phenomenology of the MMW radar return from various objects including walls, wall-corners, desks and other furniture, and persons simulating walking. Successive frames from a simulated move of a man and woman walking will be presented, and the actual movie shown at the presentation. Comments will be offered as to the practicality of active MMW imaging for TWS application.

New perspectives for high accuracy SLR with second generation geodesic satellites

NASA Technical Reports Server (NTRS)

Lund, Glenn

1993-01-01

This paper reports on the accuracy limitations imposed by geodesic satellite signatures, and on the potential for achieving millimetric performances by means of alternative satellite concepts and an optimized 2-color system tradeoff. Long distance laser ranging, when performed between a ground (emitter/receiver) station and a distant geodesic satellite, is now reputed to enable short arc trajectory determinations to be achieved with an accuracy of 1 to 2 centimeters. This state-of-the-art accuracy is limited principally by the uncertainties inherent to single-color atmospheric path length correction. Motivated by the study of phenomena such as postglacial rebound, and the detailed analysis of small-scale volcanic and strain deformations, the drive towards millimetric accuracies will inevitably be felt. With the advent of short pulse (less than 50 ps) dual wavelength ranging, combined with adequate detection equipment (such as a fast-scanning streak camera or ultra-fast solid-state detectors) the atmospheric uncertainty could potentially be reduced to the level of a few millimeters, thus, exposing other less significant error contributions, of which by far the most significant will then be the morphology of the retroreflector satellites themselves. Existing geodesic satellites are simply dense spheres, several 10's of cm in diameter, encrusted with a large number (426 in the case of LAGEOS) of small cube-corner reflectors. A single incident pulse, thus, results in a significant number of randomly phased, quasi-simultaneous return pulses. These combine coherently at the receiver to produce a convolved interference waveform which cannot, on a shot to shot basis, be accurately and unambiguously correlated to the satellite center of mass. This paper proposes alternative geodesic satellite concepts, based on the use of a very small number of cube-corner retroreflectors, in which the above difficulties are eliminated while ensuring, for a given emitted pulse, the return of a single clean pulse with an adequate cross-section.

Wave-optics simulation of the double-pass beam propagation in modulating retro-reflector FSO systems using a corner cube reflector.

PubMed

Yang, Guowei; You, Shengzui; Bi, Meihua; Fan, Bing; Lu, Yang; Zhou, Xuefang; Li, Jing; Geng, Hujun; Wang, Tianshu

2017-09-10

Free-space optical (FSO) communication utilizing a modulating retro-reflector (MRR) is an innovative way to convey information between the traditional optical transceiver and the semi-passive MRR unit that reflects optical signals. The reflected signals experience turbulence-induced fading in the double-pass channel, which is very different from that in the traditional single-pass FSO channel. In this paper, we consider the corner cube reflector (CCR) as the retro-reflective device in the MRR. A general geometrical model of the CCR is established based on the ray tracing method to describe the ray trajectory inside the CCR. This ray tracing model could treat the general case that the optical beam is obliquely incident on the hypotenuse surface of the CCR with the dihedral angle error and surface nonflatness. Then, we integrate this general CCR model into the wave-optics (WO) simulation to construct the double-pass beam propagation simulation. This double-pass simulation contains the forward propagation from the transceiver to the MRR through the atmosphere, the retro-reflection of the CCR, and the backward propagation from the MRR to the transceiver, which can be realized by a single-pass WO simulation, the ray tracing CCR model, and another single-pass WO simulation, respectively. To verify the proposed CCR model and double-pass WO simulation, the effective reflection area, the incremental phase, and the reflected beam spot on the transceiver plane of the CCR are analyzed, and the numerical results are in agreement with the previously published results. Finally, we use the double-pass WO simulation to investigate the double-pass channel in the MRR FSO systems. The histograms of the turbulence-induced fading in the forward and backward channels are obtained from the simulation data and are fitted by gamma-gamma (ΓΓ) distributions. As the two opposite channels are highly correlated, we model the double-pass channel fading by the product of two correlated ΓΓ random variables (RVs).

a Portable Apparatus for Absolute Measurements of the Earth's Gravity.

NASA Astrophysics Data System (ADS)

Zumberge, Mark Andrew

We have developed a new, portable apparatus for making absolute measurements of the acceleration due to the earth's gravity. We use the method of interferometrically determining the acceleration of a freely falling corner -cube prism. The falling object is surrounded by a chamber which is driven vertically inside a fixed vacuum chamber. This falling chamber is servoed to track the falling corner -cube to shield it from drag due to background gas. In addition, the drag-free falling chamber removes the need for a magnetic release, shields the falling object from electrostatic forces, and provides a means of both gently arresting the falling object and quickly returning it to its start position, to allow rapid acquisition of data. A synthesized long period isolation device reduces the noise due to seismic oscillations. A new type of Zeeman laser is used as the light source in the interferometer, and is compared with the wavelength of an iodine stabilized laser. The times of occurrence of 45 interference fringes are measured to within 0.2 nsec over a 20 cm drop and are fit to a quadratic by an on-line minicomputer. 150 drops can be made in ten minutes resulting in a value of g having a precision of 3 to 6 parts in 10('9). Systematic errors have been determined to be less than 5 parts in 10('9) through extensive tests. Three months of gravity data have been obtained with a reproducibility ranging from 5 to 10 parts in 10('9). The apparatus has been designed to be easily portable. Field measurements are planned for the immediate future. An accuracy of 6 parts in 10('9) corresponds to a height sensitivity of 2 cm. Vertical motions in the earth's crust and tectonic density changes that may precede earthquakes are to be investigated using this apparatus.

LUNETTE - A Discovery Class Mission to the Moon to Establish a Geophysical Network

NASA Astrophysics Data System (ADS)

Neal, C. R.; Banerdt, W. B.; Alkalai, L.

2009-12-01

Lunette is a Discovery mission concept that is designed to deliver three landed geophysical packages (“nodes”) to widely spaced (3000-5000 km) locations on the lunar surface. This mission will provide detailed information on the interior of the Moon through seismic, thermal, electromagnetic, and precision laser ranging measurements, and will substantially address the lunar interior science objectives set out in “The Scientific Context for the Exploration of the Moon” (NRC, 2008) and ”The Final Report for the International Lunar Network Anchor Nodes Science Definition Team” (NASA, 2009). Each node will contain: a very broad band seismometer that is at least an order of magnitude more sensitive over a wider frequency band than the seismometers used during Apollo; a heat flow probe, delivered via a self-penetrating “mole” device; a low-frequency electromagnetic sounding instrument, which will measure the electromagnetic properties of the outermost few hundred km of the Moon; and a corner-cube laser retroreflector for lunar laser ranging. These instruments will provide an enormous advance in our knowledge of the structure and processes of the lunar interior over that provided by Apollo-era data, allowing insights into the earliest history of the formation and evolution of the Moon. The instruments that comprise the individual nodes are all optimized for low power operation and this mission will not rely on a radioisotope power supply. Improvements in solar energy and battery technology, along with an Event Timer Module which allows the lander to shut down its electronics for most of the lunar night, enables a solar/battery mission architecture with continuous instrument operation and a two-year nominal lifetime. The instruments have a combined mass of <12 kg, and the dry mass of each lander will be on the order of 100 kg, including solar panels, batteries, and communications. The most power hungry instrument is the heat flow “mole”, which requires ~ 11 W during penetration and ~5-6 W during the active heating tests for thermal conductivity measurements. Normal operations of the mole only require 2.2 W. The nodes will operate during the lunar night in a low power mode where only systems required for data acquisition are powered. Communications back to Earth will only occur during the lunar day so there is data storage on the order of 3-4 Gbits to enable continuous operations during the lunar night (up to 16 earth days). The direct-to-Earth link is S-band at 120 kbps to a DSN 34 m ground station. UHF cross-links from remote units to the communications hub will utilize small, low power UHF transceiver for two-way communication at 128 kbps.

Spectral behavior of a terahertz quantum-cascade laser.

PubMed

Hensley, J M; Montoya, Juan; Allen, M G; Xu, J; Mahler, L; Tredicucci, A; Beere, H E; Ritchie, D A

2009-10-26

In this paper, the spectral behavior of two terahertz (THz) quantum cascade lasers (QCLs) operating both pulsed and cw is characterized using a heterodyne technique. Both lasers emitting around 2.5 THz are combined onto a whisker contact Schottky diode mixer mounted in a corner cube reflector. The resulting difference frequency beatnote is recorded in both the time and frequency domain. From the frequency domain data, we measure the effective laser linewidth and the tuning rates as a function of both temperature and injection current and show that the current tuning behavior cannot be explained by temperature tuning mechanisms alone. From the time domain data, we characterize the intrapulse frequency tuning behavior, which limits the effective linewidth to approximately 5 MHz.

Whole-angle spherical retroreflector using concentric layers of homogeneous optical media.

PubMed

Oakley, John P

2007-03-01

Spherical retroreflectors have a much greater acceptance angle than conventional retroreflectors such as corner cubes. However, the optical performance of known spherical reflectors is limited by spherical aberration. It is shown that third-order spherical aberration may be corrected by using two or more layers of homogeneous optical media of different refractive indices. The performance of the retroreflector is characterized by the scattering (or radar) cross section, which is calculated by using optical design software. A practical spherical reflector is described that offers a significant increase in optical performance over existing devices. No gradient index components are required, and the device is constructed by using conventional optical materials and fabrication techniques. The experimental results confirm that the device operates correctly at the design wavelength of 690 nm.

Study on dependence of dose enhancement on cluster morphology of gold nanoparticles in radiation therapy using a body-centred cubic model.

PubMed

Ahn, Sang Hee; Chung, Kwangzoo; Shin, Jung Wook; Cheon, Wonjoong; Han, Youngyih; Park, Hee Chul; Choi, Doo Ho

2017-09-15

Gold nanoparticles (GNPs) injected in a body for dose enhancement in radiation therapy are known to form clusters. We investigated the dependence of dose enhancement on the GNP morphology using Monte-Carlo simulations and compared the model predictions with experimental data. The cluster morphology was approximated as a body-centred cubic (BCC) structure by placing GNPs at the 8 corners and the centre of a cube with an edge length of 0.22-1.03 µm in a 4  ×  4  ×  4 µm 3 water-filled phantom. We computed the dose enhancement ratio (DER) for 50 and 260 kVp photons as a function of the distance from the cube centre for 12 different cube sizes. A 10 nm-wide concentric shell shaped detector was placed up to 100 nm away from a GNP at the cube centre. For model validation, simulations based on BCC and nanoparticle random distribution (NRD) models were performed using parameters that corresponded to the experimental conditions, which measured increases in the relative biological effect due to GNPs. We employed the linear quadratic model to compute cell surviving fraction (SF) and sensitizer enhancement ratio (SER). The DER is inversely proportional to the distance to the GNPs. The largest DERs were 1.97 and 1.80 for 50 kVp and 260 kVp photons, respectively. The SF predicted by the BCC model agreed with the experimental value within 10%, up to a 5 Gy dose, while the NRD model showed a deviation larger than 10%. The SERs were 1.21  ±  0.13, 1.16  ±  0.11, and 1.08  ±  0.11 according to the experiment, BCC, and NRD models, respectively. We most accurately predicted the GNP radiosensitization effect using the BCC approximation and suggest that the BCC model is effective for use in nanoparticle dosimetry.

Study on dependence of dose enhancement on cluster morphology of gold nanoparticles in radiation therapy using a body-centred cubic model

NASA Astrophysics Data System (ADS)

Ahn, Sang Hee; Chung, Kwangzoo; Shin, Jung Wook; Cheon, Wonjoong; Han, Youngyih; Park, Hee Chul; Choi, Doo Ho

2017-10-01

Gold nanoparticles (GNPs) injected in a body for dose enhancement in radiation therapy are known to form clusters. We investigated the dependence of dose enhancement on the GNP morphology using Monte-Carlo simulations and compared the model predictions with experimental data. The cluster morphology was approximated as a body-centred cubic (BCC) structure by placing GNPs at the 8 corners and the centre of a cube with an edge length of 0.22-1.03 µm in a 4  ×  4  ×  4 µm3 water-filled phantom. We computed the dose enhancement ratio (DER) for 50 and 260 kVp photons as a function of the distance from the cube centre for 12 different cube sizes. A 10 nm-wide concentric shell shaped detector was placed up to 100 nm away from a GNP at the cube centre. For model validation, simulations based on BCC and nanoparticle random distribution (NRD) models were performed using parameters that corresponded to the experimental conditions, which measured increases in the relative biological effect due to GNPs. We employed the linear quadratic model to compute cell surviving fraction (SF) and sensitizer enhancement ratio (SER). The DER is inversely proportional to the distance to the GNPs. The largest DERs were 1.97 and 1.80 for 50 kVp and 260 kVp photons, respectively. The SF predicted by the BCC model agreed with the experimental value within 10%, up to a 5 Gy dose, while the NRD model showed a deviation larger than 10%. The SERs were 1.21  ±  0.13, 1.16  ±  0.11, and 1.08  ±  0.11 according to the experiment, BCC, and NRD models, respectively. We most accurately predicted the GNP radiosensitization effect using the BCC approximation and suggest that the BCC model is effective for use in nanoparticle dosimetry.

Two cubesat mission to study the Didymos asteroid system

NASA Astrophysics Data System (ADS)

Wahlund, J.-E.; Vinterhav, E.; Trigo-Rodríguez, J. M.; Hallmann, M.; Barabash, S.; Ivchenko, N.

2015-10-01

Among the growing interest about asteroid impact hazard mitigation in our community the Asteroid Impact & Deflection Assessment (AIDA) mission will be the first space experiment to use a kinetic impactor to demonstrate its capability as reliable deflection system [1]. As a part of the AIDA mission, we have proposed a set of two three-axis stabilized 3U CubeSats (with up to 5 science sensors) to simultaneously rendezvous at close range (<500m) with both the primary and the secondary component of the Didymos asteroid system. The CubeSats will be hosted on the ESA component of the AIDA mission, the monitoring satellite AIM (Asteroid Impact Mission). The CubeSats will characterise the magnetization, the main bulk chemical composition and presence of volatiles as well as do superresolution surface imaging of the Didymos components. The CubeSats will also support the plume characterisation resulting from the DART impact (Double Asteroid Redirection Test, a NASA component of the AIDA mission) at much closer range than the AIM main spacecraft, and provide imaging, composition, and temperature of the plume material. At end of the mission, the two CubeSats can optionally land on one of the asteroids for continued science operation. The science sensors consist of a dual fluxgate magnetometer (MAG), one miniaturized volatile composition analyser (VCA), a narrow angle camera (NAC) and a Video Emission Spectrometer (VES) with a diffraction grating for allowing a sequential chemical study of the emission spectra associated with the impact flare and the expanding plume. Consequently, the different envisioned instruments onboard the CubeSats can provide significant insight into the complex response of asteroid materials during impacts that has been theoretically studied using different techniques [2]. The two CubeSats will remain stowed in CubeSat dispensers aboard the main AIM spacecraft. They will be deployed and commissioned before the AIM impactor reaches the secondary and record the impact event from a closer vantage point than the main spacecraft. The two CubeSats are equipped with relative navigation systems capable of estimating the spacecraft position relative to the asteroids and propulsion system that allow them to operate close to the asteroid bodies. The two CubeSats will rely on mapping data relayed via the AIM main spacecraft but operate autonomously and individually based on schedules and navigation maps uploaded from ground. AIDA's target is the binary Apollo asteroid 65803 Didymos that is also catalogued as Potentially Hazardous Asteroid (PHA) because it experiences close approaches to Earth. Didymos' primary has a diameter of ˜800 meters and the secondary is ˜150 m across. Both bodies are separated about 1.1 km [3]. The rotation period and asymmetry of the secondary object is unknown, and it might be tidally locked to the larger primary body. At least the primary body is expected to be associated with ordinary chondrite material, consisting mostly of silicates, and metal, but the earlier made Xk classification suggested a rubble-pile type with large amount of volatile content. The secondary companion spectral class is unknown, but the total mass of the system suggests that the secondary companion could be of similar class. Detailed empirical information on the physical properties of the Didymos asteroid system, in particular the magnetic field, the (mineralogical) surface composition, the internal composition via the bulk density, the ages of surface units through crater counts and other morphological surface features is valuable in order to make progress in the asteroid field of science. Furthermore, the periodic effect of such a close dynamic system in the presence and temporal displacement of the surface regolith is EPSC Abstracts Vol. 10, EPSC2015-698, 2015 European Planetary Science Congress 2015 c Author(s) 2015 EPSC European Planetary Science Congress unknown, and could be followed using close-up video systems provided by the CubeSats. In conclusion, the proposed two CubeSats as part of the AIDA mission can therefore contribute significantly, since they can monitor the Didymos asteroid components at a very close range around hundred meters, and at the same time monitor in-situ an impact plume when it is created.

A multi-channel capacitive probe for electrostatic fluctuation measurement in the Madison Symmetric Torus reversed field pinch.

PubMed

Tan, Mingsheng; Stone, Douglas R; Triana, Joseph C; Almagri, Abdulgader F; Fiksel, Gennady; Ding, Weixing; Sarff, John S; McCollam, Karsten J; Li, Hong; Liu, Wandong

2017-02-01

A 40-channel capacitive probe has been developed to measure the electrostatic fluctuations associated with the tearing modes deep into Madison Symmetric Torus (MST) reversed field pinch plasma. The capacitive probe measures the ac component of the plasma potential via the voltage induced on stainless steel electrodes capacitively coupled with the plasma through a thin annular layer of boron nitride (BN) dielectric (also serves as the particle shield). When bombarded by the plasma electrons, BN provides a sufficiently large secondary electron emission for the induced voltage to be very close to the plasma potential. The probe consists of four stalks each with ten cylindrical capacitors that are radially separated by 1.5 cm. The four stalks are arranged on a 1.3 cm square grid so that at each radial position, there are four electrodes forming a square grid. Every two adjacent radial sets of four electrodes form a cube. The fluctuating electric field can be calculated by the gradient of the plasma potential fluctuations at the eight corners of the cube. The probe can be inserted up to 15 cm (r/a = 0.7) into the plasma. The capacitive probe has a frequency bandwidth from 13 Hz to 100 kHz, amplifier-circuit limit, sufficient for studying the tearing modes (5-30 kHz) in the MST reversed-field pinch.

The Mount Wilson Optical Shop during the Second World War

NASA Astrophysics Data System (ADS)

Abrahams, P.

2004-12-01

During the Second World War, the Optical Shop of Mount Wilson Observatory, located in Pasadena, engaged in a variety of exacting and pioneering ventures in optical design and fabrication. Roof prisms for military optics were produced on a large scale, leading to the production of an instruction manual, for guidance in other workshops. Triple mirrors, or autocollimating corner cubes, were another precision part made in large numbers. Aerial photography was extensively developed. Test procedures for measuring resolution of lenses were researched. Various camera shutters and film sweep mechanisms were devised. The most significant work concerned Schmidt cameras, for possible use in night-time aerial photography. Variations included a solid Schmidt, and the Schmidt Cassegrain, which was fabricated for the first time at MWO. Key figures include Don Hendrix, Roger Hayward, Aden Meinel, and Walter Adams.

DE 102 - A numerically integrated ephemeris of the moon and planets spanning forty-four centuries

NASA Technical Reports Server (NTRS)

Newhall, X. X.; Standish, E. M.; Willams, J. G.

1983-01-01

It is pointed out that the 1960's were the turning point for the generation of lunar and planetary ephemerides. All previous measurements of the positions of solar system bodies were optical angular measurements. New technological improvements leading to immense changes in observational accuracy are related to developments concerning radar, Viking landers on Mars, and laser ranges to lunar corner cube retroreflectors. Suitable numerical integration techniques and more comprehensive physical models were developed to match the accuracy of the modern data types. The present investigation is concerned with the first integrated ephemeris, DE 102, which covers the entire span of the historical astronomical observations of usable accuracy which are known. The fit is made to modern data. The integration spans the time period from 1411 BC to 3002 AD.

Microinterferometer transducer

DOEpatents

Corey, III, Harry S.

1979-01-01

An air-bearing microinterferometer transducer is provided for increased accuracy, range and linearity over conventional displacement transducers. A microinterferometer system is housed within a small compartment of an air-bearing displacement transducer housing. A movable cube corner reflector of the interferometer is mounted to move with the displacement gauging probe of the transducer. The probe is disposed for axial displacement by means of an air-bearing. Light from a single frequency laser is directed into an interferometer system within the transducer housing by means of a self-focusing fiber optic cable to maintain light coherency. Separate fringe patterns are monitored by a pair of fiber optic cables which transmit the patterns to a detecting system. The detecting system includes a bidirectional counter which counts the light pattern fringes according to the direction of movement of the probe during a displacement gauging operation.

A description of the lunar ranging station at McDonald Observatory.

NASA Technical Reports Server (NTRS)

Silverberg, E. C.; Currie, D. G.

1972-01-01

The equipment of this station which has been in operation since the deployment of the first corner reflector by the Apollo 11 astronauts. The McDonald 2.7-m telescope is used for both transmission and reception of pulsed ruby laser light during three 45-minute daily laser runs about three weeks in a month. The present laser pulse width, timing system, calibration procedures, and signal levels are designed to achieve ranging with an accuracy to 1 nanosecond. The data rates obtained since September, 1970, are consistent with the scientific commitments of the lunar ranging program. Most of the over 200 acquisitions obtained have an accuracy to better than plus or minus 30 cm. Details of the telescope matching optics, guiding and timing equipment, and calibration procedures are discussed. Representative lunar range data are included.

Space Station/Skylab Sketch

NASA Technical Reports Server (NTRS)

1966-01-01

Seldom in aerospace history has a major decision been as promptly and concisely recorded as with the Skylab shown in this sketch. At a meeting at the Marshall Space Flight Center on August 19, 1966, George E. Mueller, NASA Associate Administrator for Marned Space Flight, used a felt pen and poster paper to pin down the final conceptual layout for the budding space station's (established as the Skylab in 1970) major elements. General Davy Jones, first program director, added his initials and those of Dr. Mueller in the lower right corner. The goals of the Skylab were to enrich our scientific knowledge of the Earth, the Sun, the stars, and cosmic space; to study the effects of weightlessness on living organisms, including man; to study the effects of the processing and manufacturing of materials utilizing the absence of gravity; and to conduct Earth resource observations. The Skylab also conducted 19 selected experiments submitted by high school students. Skylab's 3 different 3-man crews spent up to 84 days in Earth orbit. The Marshall Space Flight Center (MSFC) had responsibility for developing and integrating most of the major components of the Skylab: the Orbital Workshop (OWS), Airlock Module (AM), Multiple Docking Adapter (MDA), Apollo Telescope Mount (ATM), Payload Shroud (PS), and most of the experiments. MSFC was also responsible for providing the Saturn IB launch vehicles for three Apollo spacecraft and crews and a Saturn V launch vehicle for the Skylab.

Skylab

NASA Image and Video Library

1966-01-01

Seldom in aerospace history has a major decision been as promptly and concisely recorded as with the Skylab shown in this sketch. At a meeting at the Marshall Space Flight Center on August 19, 1966, George E. Mueller, NASA Associate Administrator for Marned Space Flight, used a felt pen and poster paper to pin down the final conceptual layout for the budding space station's (established as the Skylab in 1970) major elements. General Davy Jones, first program director, added his initials and those of Dr. Mueller in the lower right corner. The goals of the Skylab were to enrich our scientific knowledge of the Earth, the Sun, the stars, and cosmic space; to study the effects of weightlessness on living organisms, including man; to study the effects of the processing and manufacturing of materials utilizing the absence of gravity; and to conduct Earth resource observations. The Skylab also conducted 19 selected experiments submitted by high school students. Skylab's 3 different 3-man crews spent up to 84 days in Earth orbit. The Marshall Space Flight Center (MSFC) had responsibility for developing and integrating most of the major components of the Skylab: the Orbital Workshop (OWS), Airlock Module (AM), Multiple Docking Adapter (MDA), Apollo Telescope Mount (ATM), Payload Shroud (PS), and most of the experiments. MSFC was also responsible for providing the Saturn IB launch vehicles for three Apollo spacecraft and crews and a Saturn V launch vehicle for the Skylab.

OceanCubes: An Affordable Cabled Observatory System for Integrated Long-Term, High Frequency Biological, Chemical, and Physical Measurements for Understanding Coastal Ecosystems

NASA Astrophysics Data System (ADS)

Gallager, S. M.

2016-02-01

Understanding how coastal ocean processes are forcing and/or responding to ecosystem change is a central premise in current oceanographic research and monitoring. A distributed, high capacity observing capability is necessary to address biological processes requiring high frequency observations on short ( turbulence, internal waves), moderate (typhoons), and decadal time scales (e.g., NAO, El Nino-SO, PDO). The current belief that ocean observing systems need to be expensive, large, difficult to deploy and limited in capacity was tested by developing OceanCubes, an end-to-end cabled observational system with real-time telemetry, state-of-the-art sensor packages, high level of expandability, and diver maintained to reduce operating costs. A modular approach allows for a scalable system that can grow over time to accommodate budgets. The control volume design allows for measurement of material flux and energy from the water column to the benthos at a rate of s-1. The sensor package is connected by electro-optical cable to shore providing the capability for internet-based teleoperation by scientists world-wide. The central node provides underwater mateable connections for > 22 serial and Ethernet-based sensors (CTD, four ADCPs, chlorophyll and CDOM fluorescence, O2, nitrate, pCO2, pH, a bio-optical package, a Continuous Plankton Imaging and Classification Sensor (CPICS) for mesoplankton, a pan and tilt webcam, and two stereo cameras to observe and track fish communities. ADCPs and temperature strings mark the corners of the 162,000 m3 control volume. Disparate data streams are remotely archived, correlated, and analyzed while plankton and fish are identified using state-of-the-art machine vision and learning techniques. Two OceanCubes have been installed in Japan (Okinawa and Oshima Island, Tokyo) and have survived several typhoon seasons. Two additional systems are planned for either side of the Panamanian Isthmus. Results of these systems will be discussed.

Optical fabrication and testing; Proceedings of the Meeting, Singapore, Oct. 22-27, 1990

NASA Astrophysics Data System (ADS)

Lorenzen, Manfred; Campbell, Duncan R.; Johnson, Craig W.

1991-03-01

Various papers on optical fabrication and testing are presented. Individual topics addressed include: interferometry with laser diodes, new methods for economic production of prisms and lenses, interferometer accuracy and precision, optical testing with wavelength scanning interferometer, digital Talbot interferometer, high-sensitivity interferometric technique for strain measurements, absolute interferometric testing of spherical surfaces, contouring using gratings created on an LCD panel, three-dimensional inspection using laser-based dynamic fringe projection, noncontact optical microtopography, laser scan microscope and infrared laser scan microscope, photon scanning tunneling microscopy. Also discussed are: combination-matching problems in the layout design of minilaser rangefinder, design and testing of a cube-corner array for laser ranging, mode and far-field pattern of diode laser-phased arrays, new glasses for optics and optoelectronics, optical properties of Li-doped ZnO films, application and machining of Zerodur for optical purposes, finish machining of optical components in mass production.

High-frequency fluctuation measurements by far-infrared laser Faraday-effect polarimetry-interferometry and forward scattering system on MST.

PubMed

Ding, W X; Lin, L; Duff, J R; Brower, D L

2014-11-01

Magnetic fluctuation-induced transport driven by global tearing modes has been measured by Faraday-effect polarimetry and interferometry (phase measurements) in the MST reversed field pinch. However, the role of small-scale broadband magnetic and density turbulence in transport remains unknown. In order to investigate broadband magnetic turbulence, we plan to upgrade the existing detector system by using planar-diode fundamental waveguide mixers optimized for high sensitivity. Initial tests indicate these mixers have ×10 sensitivity improvement compared to currently employed corner-cube Schottky-diode mixers and ×5 lower noise. Compact mixer design will allow us to resolve the wavenumbers up to k ∼ 1-2 cm(-1) for beam width w = 1.5 cm and 15 cm(-1) for beam width w = 2 mm. The system can also be used to measure the scattered signal (amplitude measurement) induced by both plasma density and magnetic fluctuations.

High Precision Time Transfer in Space with a Hydrogen Maser on MIR

NASA Technical Reports Server (NTRS)

Mattison, Edward M.; Vessot, Robert F. C.

1996-01-01

An atomic hydrogen maser clock system designed for long term operation in space will be installed on the Russian space station Mir, in late 1997. The H-maser's frequency stability will be measured using pulsed laser time transfer techniques. Daily time comparisons made with a precision of better than 100 picoseconds will allow an assessment of the long term stability of the space maser at a level on the order of 1 part in 10(sup 15) or better. Laser pulse arrival times at the spacecraft will be recorded with a resolution of 10 picoseconds relative to the space clock's time scale. Cube corner reflectors will reflect the pulses back to the Earth laser station to determine the propagation delay and enable comparison with the Earth-based time scale. Data for relativistic and gravitational frequency corrections will be obtained from a Global Positioning System (GPS) receiver.

Earthquake stress via event ratio levels: Application to the 2011 and 2016 Oklahoma seismic sequences

DOE Office of Scientific and Technical Information (OSTI.GOV)

Walter, William R.; Yoo, Seung -Hoon; Mayeda, Kevin

Here, we develop a new methodology for determining earthquake stress drop and apparent stress values via spectral ratio asymptotic levels. With sufficient bandwidth, the stress ratio for a pair of events can be directly related to these low- and high-frequency levels. This avoids the need to assume a particular spectral model and derive stress drop from cubed corner frequency measures. The method can be applied to spectral ratios for any pair of closely related earthquakes and is particularly well suited for coda envelope methods that provide good azimuthally averaged, point-source measures. We apply the new method to the 2011 Praguemore » and 2016 Pawnee earthquake sequences in Oklahoma. The sequences show stress scaling with size and depth, with the largest events having apparent stress levels near 1 MPa and smaller and/or shallower events having systematically lower stress values.« less

Earthquake stress via event ratio levels: Application to the 2011 and 2016 Oklahoma seismic sequences

DOE PAGES

Walter, William R.; Yoo, Seung -Hoon; Mayeda, Kevin; ...

2017-04-03

Here, we develop a new methodology for determining earthquake stress drop and apparent stress values via spectral ratio asymptotic levels. With sufficient bandwidth, the stress ratio for a pair of events can be directly related to these low- and high-frequency levels. This avoids the need to assume a particular spectral model and derive stress drop from cubed corner frequency measures. The method can be applied to spectral ratios for any pair of closely related earthquakes and is particularly well suited for coda envelope methods that provide good azimuthally averaged, point-source measures. We apply the new method to the 2011 Praguemore » and 2016 Pawnee earthquake sequences in Oklahoma. The sequences show stress scaling with size and depth, with the largest events having apparent stress levels near 1 MPa and smaller and/or shallower events having systematically lower stress values.« less

Automated interferometric alignment system for paraboloidal mirrors

DOEpatents

Maxey, L. Curtis

1993-01-01

A method is described for a systematic method of interpreting interference fringes obtained by using a corner cube retroreflector as an alignment aid when aigning a paraboloid to a spherical wavefront. This is applicable to any general case where such alignment is required, but is specifically applicable in the case of aligning an autocollimating test using a diverging beam wavefront. In addition, the method provides information which can be systematically interpreted such that independent information about pitch, yaw and focus errors can be obtained. Thus, the system lends itself readily to automation. Finally, although the method is developed specifically for paraboloids, it can be seen to be applicable to a variety of other aspheric optics when applied in combination with a wavefront corrector that produces a wavefront which, when reflected from the correctly aligned aspheric surface will produce a collimated wavefront like that obtained from the paraboloid when it is correctly aligned to a spherical wavefront.

Automated interferometric alignment system for paraboloidal mirrors

DOEpatents

Maxey, L.C.

1993-09-28

A method is described for a systematic method of interpreting interference fringes obtained by using a corner cube retroreflector as an alignment aid when aligning a paraboloid to a spherical wavefront. This is applicable to any general case where such alignment is required, but is specifically applicable in the case of aligning an autocollimating test using a diverging beam wavefront. In addition, the method provides information which can be systematically interpreted such that independent information about pitch, yaw and focus errors can be obtained. Thus, the system lends itself readily to automation. Finally, although the method is developed specifically for paraboloids, it can be seen to be applicable to a variety of other aspheric optics when applied in combination with a wavefront corrector that produces a wavefront which, when reflected from the correctly aligned aspheric surface will produce a collimated wavefront like that obtained from the paraboloid when it is correctly aligned to a spherical wavefront. 14 figures.

Micromachined electrostatic vertical actuator

DOE Office of Scientific and Technical Information (OSTI.GOV)

Lee, Abraham P.; Sommargren, Gary E.; McConaghy, Charles F.

A micromachined vertical actuator utilizing a levitational force, such as in electrostatic comb drives, provides vertical actuation that is relatively linear in actuation for control, and can be readily combined with parallel plate capacitive position sensing for position control. The micromachined electrostatic vertical actuator provides accurate movement in the sub-micron to micron ranges which is desirable in the phase modulation instrument, such as optical phase shifting. For example, compact, inexpensive, and position controllable micromirrors utilizing an electrostatic vertical actuator can replace the large, expensive, and difficult-to-maintain piezoelectric actuators. A thirty pound piezoelectric actuator with corner cube reflectors, as utilized inmore » a phase shifting diffraction interferometer can be replaced with a micromirror and a lens. For any very precise and small amplitudes of motion` micromachined electrostatic actuation may be used because it is the most compact in size, with low power consumption and has more straightforward sensing and control options.« less

Micromachined electrostatic vertical actuator

DOE Office of Scientific and Technical Information (OSTI.GOV)

Lee, A.P.; Sommargren, G.E.; McConaghy, C.F.

A micromachined vertical actuator utilizing a levitational force, such as in electrostatic comb drives, provides vertical actuation that is relatively linear in actuation for control, and can be readily combined with parallel plate capacitive position sensing for position control. The micromachined electrostatic vertical actuator provides accurate movement in the sub-micron to micron ranges which is desirable in the phase modulation instrument, such as optical phase shifting. For example, compact, inexpensive, and position controllable micromirrors utilizing an electrostatic vertical actuator can replace the large, expensive, and difficult-to-maintain piezoelectric actuators. A thirty pound piezoelectric actuator with corner cube reflectors, as utilized inmore » a phase shifting diffraction interferometer can be replaced with a micromirror and a lens. For any very precise and small amplitudes of motion, micromachined electrostatic actuation may be used because it is the most compact in size, with low power consumption and has more straightforward sensing and control options.« less

Mobile quantum gravity sensor with unprecedented stability

NASA Astrophysics Data System (ADS)

Freier, C.; Hauth, M.; Schkolnik, V.; Leykauf, B.; Schilling, M.; Wziontek, H.; Scherneck, H.-G.; Müller, J.; Peters, A.

2016-06-01

Changes of surface gravity on Earth are of great interest in geodesy, earth sciences and natural resource exploration. They are indicative of Earth system's mass redistributions and vertical surface motion, and are usually measured with falling corner-cube- and superconducting gravimeters (FCCG and SCG). Here we report on absolute gravity measurements with a mobile quantum gravimeter based on atom interferometry. The measurements were conducted in Germany and Sweden over periods of several days with simultaneous SCG and FCCG comparisons. They show the best-reported performance of mobile atomic gravimeters to date with an accuracy of 39nm/s2, long-term stability of 0.5nm/s2 and short-term noise of 96nm/s2/√Hz. These measurements highlight the unique properties of atomic sensors. The achieved level of performance in a transportable instrument enables new applications in geodesy and related fields, such as continuous absolute gravity monitoring with a single instrument under rough environmental conditions.

Spectroscopic method for Earth-satellite-Earth laser long-path absorption measurements using Retroreflector In Space (RIS)

NASA Technical Reports Server (NTRS)

Sugimoto, Nobuo; Minato, Atsushi; Sasano, Yasuhiro

1992-01-01

The Retroreflector in Space (RIS) is a single element cube-corner retroreflector with a diameter of 0.5 m designed for earth-satellite-earth laser long-path absorption experiments. The RIS is to be loaded on the Advanced Earth Observing System (ADEOS) satellite which is scheduled for launch in Feb. 1996. The orbit for ADEOS is a sun synchronous subrecurrent polar-orbit with an inclination of 98.6 deg. It has a period of 101 minutes and an altitude of approximately 800 km. The local time at descending node is 10:15-10:45, and the recurrent period is 41 days. The velocity relative to the ground is approximately 7 km/s. In the RIS experiment, a laser beam transmitted from a ground station is reflected by RIS and received at the ground station. The absorption of the intervening atmosphere is measured in the round-trip optical path.

Optical fabrication and testing; Proceedings of the Meeting, Singapore, Oct. 22-27, 1990

DOE Office of Scientific and Technical Information (OSTI.GOV)

Lorenzen, M.; Campbell, D.R.; Johnson, C.W.

1991-01-01

Various papers on optical fabrication and testing are presented. Individual topics addressed include: interferometry with laser diodes, new methods for economic production of prisms and lenses, interferometer accuracy and precision, optical testing with wavelength scanning interferometer, digital Talbot interferometer, high-sensitivity interferometric technique for strain measurements, absolute interferometric testing of spherical surfaces, contouring using gratings created on an LCD panel, three-dimensional inspection using laser-based dynamic fringe projection, noncontact optical microtopography, laser scan microscope and infrared laser scan microscope, photon scanning tunneling microscopy. Also discussed are: combination-matching problems in the layout design of minilaser rangefinder, design and testing of a cube-corner arraymore » for laser ranging, mode and far-field pattern of diode laser-phased arrays, new glasses for optics and optoelectronics, optical properties of Li-doped ZnO films, application and machining of Zerodur for optical purposes, finish machining of optical components in mass production.« less

International, private-public, multi-mission, next-generation lunar laser retroreflectors

NASA Astrophysics Data System (ADS)

Dell'Agnello, Simone

2017-04-01

Since the 1970s Lunar Laser Ranging (LLR) to the Apollo/Lunokhod Cube Corner Retroreflector (CCR) arrays supplied some of the best tests of General Relativity (GR): possible changes in the gravitational constant, weak and strong equivalence principle, gravitational self-energy (PPN parameter beta), geodetic precession, inverse-square force-law [1][2]. LLR has also provided significant information on the composition of the deep interior of the Moon [3]. LLR physics analysis also allows for constraints on extensions of GR (like spacetime torsion [4]) and on new gravitational physics that may explain the gravitational universe without Dark Matter and Dark Energy (like Non-Minimally Coupled gravity [5]). LLR is the only Apollo/Lunokhod experiment still in operation. In the 1970s LLR arrays contributed a negligible fraction of the ranging error budget. Since the capabilities of ground stations of the International Laser Ranging Service (in particular APOLLO in USA) improved by more than two orders of magnitude, now, because of the lunar librations, current CCR arrays dominate the error. With the US/Italy project LLRRA21/MoonLIGHT (Lunar Laser Ranging Retroreflector Array for the 21st century/Moon Laser Instrumentation for General relativity High accuracy Tests) UMD (Univ. of Maryland) and INFN (Italian National Institute for Nuclear Physics) developed a new-generation LLR payload made by a single, large CCR (100 mm diameter), unaffected by the effect of librations, that will improve the LLR accuracy by a factor of ten to one hundred. The performance of this 'big CCR' is being characterized at the SCF_Lab test facility at INFN-LNF, Frascati, Italy [6]. INFN also developed INRRI (INstrument for landing-Roving laser Retroreflector Investigations), a microreflector payload for the lunar surface to be laser-ranged by orbiters [7]. This will further extend the physics and lunar science reach of LLR. INRRI can also provide positioning services on the far side (it is proposed for CNSA's Chang'E-4 mission). INRRI has been embarked on ESA's ExoMars lander "Schiaparelli" and it has been requested by NASA to ASI for the Mars 2020 Rover mission. LLR data are analized/simulated with the Planetary Ephemeris Program developed by CfA. INFN, UMD and MEI signed a private-public partnership, multi-mission agreement to deploy the big and the microreflectors on the Moon. Through existing MoUs between INFN and the Russian Academy of Sciences, international negotiations are also underway to propose the new lunar reflectors and the SCF_Lab services for the next robotic missions of the Russian space program. References: [1] Probing gravity with next-generation lunar la-ser ranging, M. Martini and S. Dell'Agnello, in R. Peron et al. (eds.), Gravity: Where Do We Stand?, DOI 10.1007/978-3-319-20224-2_5, Springer Inter-national Publishing, Switzerland (2016). [2] Formation flying, cosmology and general rel-ativity: a tribute to far-reaching dreams of Mino Freund, Currie, D.; Williams, J.; Dell'Agnello, S.; Monache, G.D.; Behr, B. and K. Zacny, in Springer Proceedings in Physics, vol. 150, ISBN-13: 978-3319022062, ISBN-10: 3319022067 (2014). [3] Williams, J. G., Turyshev, S. G., Boggs, D. H., Ratcliff, J. T., Lunar laser ranging science: Grav-itational physics and lunar interior and geodesy, Adv. Space Res. 37(1), 67-71 (2006). [4] Constraining spacetime torsion with Moon and Mercury, R. March, G. Bellettini, R. Taursaso, S. Dell'Agnello, Phys. Rev D 83, 104008 (2011). [5] Constraining nonminimally coupled gravity with laser ranging to the moon, N. Castel-Branco, J. Paramos, R. March and S. Dell'Agnello, in 3rd Euro-pean Lunar Symposium, Frascati, Italy (2014). [6] Creation of the new industry-standard space test of laser retroreflectors for the GNSS and LAGEOS, S. Dell'Agnello et al, Adv. Space Res. 47, 822-842 (2011). [7] Advanced Laser Retroreflectors for Astro-physics and Space Science, Dell'Agnello, S., et al, Journal of Applied Mathematics and Physics, 3, 218-227 (2015).

CANYVAL-X: Enabling a new class of scientific instruments

NASA Astrophysics Data System (ADS)

Shah, Neerav; Calhoun, Philip C.; Park, Sang-young; Keidar, Michael

2016-05-01

Significant new discoveries in space science can be realized by replacing the traditional large monolithic space telescopes with precision formation flying spacecraft to form a “virtual telescope.” Such virtual telescopes will revolutionize occulting imaging systems, provide images of the Sun, accretion disks, and other astronomical objects with unprecedented milli-arcsecond resolution (several orders of magnitude beyond current capability).Since the days of Apollo, NASA and other organizations have been conducting formation flying in space, but not with the precision required for virtual telescopes. These efforts have focused on rendezvous and docking (e.g., crew docking, satellite servicing, etc.) and/or ground-controlled coordinated flight (e.g., EO-1, GRAIL, MMS, etc.). While the TRL of the component level technology for formation flying is high, the capability for the system-level guidance, navigation, and control (GN&C) technology required to align a virtual telescope to an inertial astronomical target with sub-arcsecond precision is not fully developed.The CANYVAL-X (CubeSat Astronomy by NASA and Yonsei using Virtual Telescope Alignment eXperiment) mission is an engineering proof of concept featuring a pair of CubeSats flying as a tandem telescope with a goal of demonstrating the system-level GN&C needed to form a virtual telescope. NASA partnered with the George Washington University and the Yonsei University to design and develop CANYVAL-X. CANYVAL-X will demonstrate key technologies for using virtual telescopes in space, including micro-propulsion using millinewton thrusters, relative position sensing, and communications control between the two spacecraft. CANYVAL-X is scheduled to launch on a Flacon-9 in summer of 2016.

Local field potential spectral tuning in motor cortex during reaching.

PubMed

Heldman, Dustin A; Wang, Wei; Chan, Sherwin S; Moran, Daniel W

2006-06-01

In this paper, intracortical local field potentials (LFPs) and single units were recorded from the motor cortices of monkeys (Macaca fascicularis) while they preformed a standard three-dimensional (3-D) center-out reaching task. During the center-out task, the subjects held their hands at the location of a central target and then reached to one of eight peripheral targets forming the corners of a virtual cube. The spectral amplitudes of the recorded LFPs were calculated, with the high-frequency LFP (HF-LFP) defined as the average spectral amplitude change from baseline from 60 to 200 Hz. A 3-D linear regression across the eight center-out targets revealed that approximately 6% of the beta LFPs (18-26 Hz) and 18% of the HF-LFPs were tuned for velocity (p-value < 0.05), while 10% of the beta LFPs and 15% of the HF-LFPs were tuned for position. These results suggest that a multidegree-of-freedom brain-machine interface is possible using high-frequency LFP recordings in motor cortex.

Advances in laser technology for the atmospheric sciences; Proceedings of the Seminar, San Diego, Calif., August 25, 26, 1977

NASA Technical Reports Server (NTRS)

Trolinger, J. D. (Editor); Moore, W. W.

1977-01-01

These papers deal with recent research, developments, and applications in laser and electrooptics technology, particularly with regard to atmospheric effects in imaging and propagation, laser instrumentation and measurements, and particle measurement. Specific topics include advanced imaging techniques, image resolution through atmospheric turbulence over the ocean, an efficient method for calculating transmittance profiles, a comparison of a corner-cube reflector and a plane mirror in folded-path and direct transmission through atmospheric turbulence, line-spread instrumentation for propagation measurements, scaling laws for thermal fluctuations in the layer adjacent to ocean waves, particle sizing by laser photography, and an optical Fourier transform analysis of satellite cloud imagery. Other papers discuss a subnanosecond photomultiplier tube for laser application, holography of solid propellant combustion, diagnostics of turbulence by holography, a camera for in situ photography of cloud particles from a hail research aircraft, and field testing of a long-path laser transmissometer designed for atmospheric visibility measurements.

The SPQR experiment: detecting damage to orbiting spacecraft with ground-based telescopes

NASA Astrophysics Data System (ADS)

Paolozzi, Antonio; Porfilio, Manfredi; Currie, Douglas G.; Dantowitz, Ronald F.

2007-09-01

The objective of the Specular Point-like Quick Reference (SPQR) experiment was to evaluate the possibility of improving the resolution of ground-based telescopic imaging of manned spacecraft in orbit. The concept was to reduce image distortions due to atmospheric turbulence by evaluating the Point Spread Function (PSF) of a point-like light reference and processing the spacecraft image accordingly. The target spacecraft was the International Space Station (ISS) and the point-like reference was provided by a laser beam emitted by the ground station and reflected back to the telescope by a Cube Corner Reflector (CCR) mounted on an ISS window. The ultimate objective of the experiment was to demonstrate that it is possible to image spacecraft in Low Earth Orbit (LEO) with a resolution of 20 cm, which would have probably been sufficient to detect the damage which caused the Columbia disaster. The experiment was successfully performed from March to May 2005. The paper provides an overview of the SPQR experiment.

SLR tracking of GPS-35

NASA Technical Reports Server (NTRS)

Pavlis, Erricos C.

1994-01-01

An experiment was designed to launch a corner cube retroreflector array on one of the Global Positioning Satellites (GPS). The launch on Aug. 31, 1993 ushered in the era of SLR tracking of GPS spacecraft. Once the space operations group finished the check-out procedures for the new satellite, the agreed upon SLR sites were allowed to track it. The first site to acquire GPS-35 was the Russian system at Maidanak and closely after the MLRS system at McDonald Observatory, Texas. The laser tracking network is currently tracking the GPS spacecraft known as GPS-35 or PRN 5 with great success. From the NASA side there are five stations that contribute data regularly and nearly as many from the international partners. Upcoming modifications to the ground receivers will allow for a further increase in the tracking capabilities of several additional sites and add some desperately needed southern hemisphere tracking. We are analyzing the data and are comparing SLR-derived orbits to those determined on the basis of GPS radiometric data.

Avalanching strain dynamics during the hydriding phase transformation in individual palladium nanoparticles

DOE Office of Scientific and Technical Information (OSTI.GOV)

Ulvestad, A.; Welland, M. J.; Collins, S. S. E.

2015-12-11

Phase transitions in reactive environments are crucially important in energy and information storage, catalysis and sensors. Nanostructuring active particles can yield faster charging/ discharging kinetics, increased lifespan and record catalytic activities. However, establishing the causal link between structure and function is challenging for nanoparticles, as ensemble measurements convolve intrinsic single-particle properties with sample diversity. Here we study the hydriding phase transformation in individual palladium nanocubes in situ using coherent X-ray diffractive imaging. The phase transformation dynamics, which involve the nucleation and propagation of a hydrogen-rich region, are dependent on absolute time (aging) and involve intermittent dynamics (avalanching). A hydrogen-rich surfacemore » layer dominates the crystal strain in the hydrogen-poor phase, while strain inversion occurs at the cube corners in the hydrogen-rich phase. A three-dimensional phase-field model is used to interpret the experimental results. In conclusion, our experimental and theoretical approach provides a general framework for designing and optimizing phase transformations for single nanocrystals in reactive environments.« less

Catheter guided by optical coherence domain reflectometry

DOEpatents

Everett, Matthew; Colston, Billy W.; Da Silva, Luiz B.; Matthews, Dennis

2002-01-01

A guidance and viewing system based on multiplexed optical coherence domain reflectometry is incorporated into a catheter, endoscope, or other medical device to measure the location, thickness, and structure of the arterial walls or other intra-cavity regions at discrete points on the medical device during minimally invasive medical procedures. The information will be used both to guide the device through the body and to evaluate the tissue through which the device is being passed. Multiple optical fibers are situated along the circumference of the device. Light from the distal end of each fiber is directed onto the interior cavity walls via small diameter optics (such as gradient index lenses and mirrored corner cubes). Both forward viewing and side viewing fibers can be included. The light reflected or scattered from the cavity walls is then collected by the fibers and multiplexed at the proximal end to the sample arm of an optical low coherence reflectometer. The system may also be implemented in a nonmedical inspection device.

A magnetic hysteresis model

NASA Technical Reports Server (NTRS)

Flatley, Thomas W.; Henretty, Debra A.

1995-01-01

The Passive Aerodynamically Stabilized Magnetically Damped Satellite (PAMS) will be deployed from the Space Shuttle and used as a target for a Shuttle-mounted laser. It will be a cylindrical satellite with several corner cube reflectors on the ends. The center of mass of the cylinder will be near one end, and aerodynamic torques will tend to align the axis of the cylinder with the spacecraft velocity vector. Magnetic hysteresis rods will be used to provide passive despin and oscillation-damping torques on the cylinder. The behavior of the hysteresis rods depends critically on the 'B/H' curves for the combination of materials and rod length-to-diameter ratio ('l-over-d'). These curves are qualitatively described in most Physics textbooks in terms of major and minor 'hysteresis loops'. Mathematical modeling of the functional relationship between B and H is very difficult. In this paper, the physics involved is not addressed, but an algorithm is developed which provides a close approximation to empirically determined data with a few simple equations suitable for use in computer simulations.

Experimental Satellite Quantum Communications

NASA Astrophysics Data System (ADS)

Vallone, Giuseppe; Bacco, Davide; Dequal, Daniele; Gaiarin, Simone; Luceri, Vincenza; Bianco, Giuseppe; Villoresi, Paolo

2015-07-01

Quantum communication (QC), namely, the faithful transmission of generic quantum states, is a key ingredient of quantum information science. Here we demonstrate QC with polarization encoding from space to ground by exploiting satellite corner cube retroreflectors as quantum transmitters in orbit and the Matera Laser Ranging Observatory of the Italian Space Agency in Matera, Italy, as a quantum receiver. The quantum bit error ratio (QBER) has been kept steadily low to a level suitable for several quantum information protocols, as the violation of Bell inequalities or quantum key distribution (QKD). Indeed, by taking data from different satellites, we demonstrate an average value of QBER =4.6 % for a total link duration of 85 s. The mean photon number per pulse μsat leaving the satellites was estimated to be of the order of one. In addition, we propose a fully operational satellite QKD system by exploiting our communication scheme with orbiting retroreflectors equipped with a modulator, a very compact payload. Our scheme paves the way toward the implementation of a QC worldwide network leveraging existing receivers.

GLRS-R 2-colour retroreflector target design and predicted performance

NASA Astrophysics Data System (ADS)

Lund, Glenn

The retroreflector ground target design for the GLRS-R spaceborne dual wavelength laser ranging system is described. The passive design flows down from the requirements of high station autonomy, high global field of view, little or no multiple pulse returns, and adequate optical cross section for most ranging geometries. The solution makes use of five hollow cube corner retroreflectors of which one points to the zenith and the remaining four are inclined from the vertical at uniform azimuthal spacings. The need for large retroreflectors is expected to generate narrow diffraction lobes. A good compromise solution is found by spoiling just one of the retroereflector dihedral angles from 90 deg, thus generating two symmetrically oriented diffraction lobes in the return beam. The required spoil angles are found to have little dependance on ground target latitude. Various link budget analyses are presented. They show the influence of such factors as point ahead optimization, turbulence, ranging angle, atmospheric visibility, and ground target thermal deformations.

Optical coherence domain reflectometry guidewire

DOEpatents

Colston, Billy W.; Everett, Matthew; Da Silva, Luiz B.; Matthews, Dennis

2001-01-01

A guidewire with optical sensing capabilities is based on a multiplexed optical coherence domain reflectometer (OCDR), which allows it to sense location, thickness, and structure of the arterial walls or other intra-cavity regions as it travels through the body during minimally invasive medical procedures. This information will be used both to direct the guidewire through the body by detecting vascular junctions and to evaluate the nearby tissue. The guidewire contains multiple optical fibers which couple light from the proximal to distal end. Light from the fibers at the distal end of the guidewire is directed onto interior cavity walls via small diameter optics such as gradient index lenses and mirrored corner cubes. Both forward viewing and side viewing fibers can be included. The light reflected or scattered from the cavity walls is then collected by the fibers, which are multiplexed at the proximal end to the sample arm of an optical low coherence reflectometer. The guidewire can also be used in nonmedical applications.

Avalanching strain dynamics during the hydriding phase transformation in individual palladium nanoparticles

NASA Astrophysics Data System (ADS)

Ulvestad, A.; Welland, M. J.; Collins, S. S. E.; Harder, R.; Maxey, E.; Wingert, J.; Singer, A.; Hy, S.; Mulvaney, P.; Zapol, P.; Shpyrko, O. G.

2015-12-01

Phase transitions in reactive environments are crucially important in energy and information storage, catalysis and sensors. Nanostructuring active particles can yield faster charging/discharging kinetics, increased lifespan and record catalytic activities. However, establishing the causal link between structure and function is challenging for nanoparticles, as ensemble measurements convolve intrinsic single-particle properties with sample diversity. Here we study the hydriding phase transformation in individual palladium nanocubes in situ using coherent X-ray diffractive imaging. The phase transformation dynamics, which involve the nucleation and propagation of a hydrogen-rich region, are dependent on absolute time (aging) and involve intermittent dynamics (avalanching). A hydrogen-rich surface layer dominates the crystal strain in the hydrogen-poor phase, while strain inversion occurs at the cube corners in the hydrogen-rich phase. A three-dimensional phase-field model is used to interpret the experimental results. Our experimental and theoretical approach provides a general framework for designing and optimizing phase transformations for single nanocrystals in reactive environments.

Avalanching strain dynamics during the hydriding phase transformation in individual palladium nanoparticles

PubMed Central

Ulvestad, A.; Welland, M. J.; Collins, S. S. E.; Harder, R.; Maxey, E.; Wingert, J.; Singer, A.; Hy, S.; Mulvaney, P.; Zapol, P.; Shpyrko, O. G.

2015-01-01

Phase transitions in reactive environments are crucially important in energy and information storage, catalysis and sensors. Nanostructuring active particles can yield faster charging/discharging kinetics, increased lifespan and record catalytic activities. However, establishing the causal link between structure and function is challenging for nanoparticles, as ensemble measurements convolve intrinsic single-particle properties with sample diversity. Here we study the hydriding phase transformation in individual palladium nanocubes in situ using coherent X-ray diffractive imaging. The phase transformation dynamics, which involve the nucleation and propagation of a hydrogen-rich region, are dependent on absolute time (aging) and involve intermittent dynamics (avalanching). A hydrogen-rich surface layer dominates the crystal strain in the hydrogen-poor phase, while strain inversion occurs at the cube corners in the hydrogen-rich phase. A three-dimensional phase-field model is used to interpret the experimental results. Our experimental and theoretical approach provides a general framework for designing and optimizing phase transformations for single nanocrystals in reactive environments. PMID:26655832

Long-term frequency and amplitude stability of a solid-nitrogen-cooled, continuous wave THz quantum cascade laser

NASA Astrophysics Data System (ADS)

Danylov, Andriy A.; Waldman, Jerry; Light, Alexander R.; Goyette, Thomas M.; Giles, Robert H.; Qian, Xifeng; Chandrayan, Neelima; Goodhue, William D.; Nixon, William E.

2012-02-01

Operational temperature increase of CW THz QCLs to 77 K has enabled us to employ solid nitrogen (SN2) as the cryogen. A roughing pump was used to solidify liquid nitrogen and when the residual vapor pressure in the nitrogen reservoir reached the pumping system's minimum pressure the temperature equilibrated and remained constant until all the nitrogen sublimated. The hold time compared to liquid helium has thereby increased approximately 70-fold, and at a greatly reduced cost. The milliwatt CW QCL was at a temperature of approximately 60 K, dissipating 5 W of electrical power. To measure the long-term frequency, current, and temperature stability, we heterodyned the free-running 2.31 THz QCL with a CO2 pumped far-infrared gas laser line in methanol (2.314 THz) in a corner-cube Schottky diode and recorded the IF frequency, current and temperature. Under these conditions the performance characteristics of the QCL, which will be reported, exceeded that of a device mounted in a mechanical cryocooler.

InGaAs multiple quantum well modulating retro-reflector for free-space optical communications

NASA Astrophysics Data System (ADS)

Rabinovich, William S.; Gilbreath, G. Charmaine; Goetz, Peter G.; Mahon, Rita; Katzer, D. Scott; Ikossi-Anastasiou, Kiki; Binari, Steven C.; Meehan, Timothy J.; Stell, Mena F.; Sokolsky, Ilene; Vasquez, John A.; Vilcheck, Michael J.

2002-01-01

Modulating retro-reflectors provide means for free space optical communication without the need for a laser, telescope or pointer tracker on one end of the link. These systems work by coupling a retro-reflector with an electro- optic shutter. The modulating retro-reflector is then interrogated by a cw laser beam from a conventional optical communications system and returns a modulated signal beam to the interrogator. Over the last few years the Naval Research Laboratory has developed modulating retro-reflector based on corner cubes and large area Transmissive InGaAs multiple quantum well modulators. These devices can allow optical links at speeds up to about 10 Mbps. We will discuss the critical performance characteristics of such systems including modulating rate, power consumption, optical contrast ratio and operating wavelength. In addition a new modulating retro-reflector architecture based upon cat s eye retroreflectors will be discussed. This architecture has the possibility for data rates of hundreds of megabits per second at power consumptions below 100 mW.

Apollo 40th Anniversary Press Conference

NASA Image and Video Library

2009-07-19

Apollo astronauts from left, Walt Cunningham (Apollo 17), James Lovell (Apollo 8 Apollo 13), David Scott (Apollo 9 Apollo 15), Buzz Aldrin (Apollo 11), Charles Duke (Apollo 16), Thomas Stafford (Apollo 10) and Eugene Cernan (Apollo 17) are seen during the 40th anniversary of the Apollo 11 mission and the walk on the moon press conference, Monday, July 20, 2009, at NASA Headquarters in Washington. Photo Credit: (NASA/Paul E. Alers)

Artist's concept of topographical layout of Taurus-Littrow landing site

NASA Technical Reports Server (NTRS)

1972-01-01

An artist's concept illustrating the topographical layout of the Taurus-Littrow landing site, depicting the traverses planned on the Apollo 17 lunar landing mission using the Lunar Roving Vehicle. The Roman numerals indicate the three periods of extravehicular activity (EVA). The Arabic numbers represent the station stops. The mountain in the center of the picture is South Massif. A portion of North Massif is in the lower right corner of the photograph. The names of some of the craters are: Camelot (at Station 5); Emory (nearest Station 1); Sherlock (at station 10); Steno (between Emory and Sherlock); Amundsen (at Station 2); Lara (at Station 3); Henry (nearest Station 6); Shakespeare (nearest Station 9); Cochise (nearest Station 8); and Powell (halfway between Camelot and Emory). Note the ridge-like feature extending from Station 2 to North Massif. The southern portion of the ridge is called Lee Scarp; and the Northerly portion is Lincoln Scarp. This concept is by MSC artist Jerry Elm

Thermo-optical vacuum testing of Galileo In-Orbit Validation laser retroreflectors

NASA Astrophysics Data System (ADS)

Dell'Agnello, S.; Boni, A.; Cantone, C.; Ciocci, E.; Contessa, S.; Delle Monache, G.; Lops, C.; Martini, M.; Patrizi, G.; Porcelli, L.; Salvatori, L.; Tibuzzi, M.; Intaglietta, N.; Tuscano, P.; Mondaini, C.; Maiello, M.; Doyle, D.; García-Prieto, R.; Navarro-Reyes, D.

2016-06-01

The Galileo constellation is a space research and development program of the European Union to help navigate users all over the world. The Galileo IOV (In-Orbit Validation) are the first test satellites of the Galileo constellation and carry satellite laser retroreflectors as part of their payload systems for precision orbit determination and performance assessment. INFN-LNF SCF_Lab (Satellite/lunar/GNSS laser ranging/altimetry and Cube/microsat Characterization Facilities Laboratory) has been performing tests on a sample of the laser array segment under the Thermo-optical vacuum testing of Galileo IOV laser retro-reflectors of Galileo IOV LRA project, as defined in ESA-INFN Contract No. 4000108617/13/NL/PA. We will present the results of FFDP (Far Field Diffraction Pattern) and thermal relaxation times measurements in relevant space conditions of Galileo IOV CCRs (Cube Corner Retroreflectors) provided by ESA-ESTEC. A reference for the performance of laser ranging on Galileo satellites is the FFDP of a retroreflector in its design specifications and a Galileo retroreflector, in air and isothermal conditions, should have a minimum return intensity within the range [ 0.55 ×106m2- 2.14 ×106m2 ] (ESA-INFN, 2013). Measurements, performed in SCF_Lab facility, demonstrated that the 7 Galileo IOV laser retroreflectors under test were compliant with design performance expectations (Porcelli et al., 2015). The kind of tests carried out for this activity are the first performed on spare Galileo IOV hardware, made available after the launch of the four Galileo IOV satellites (2011 and 2012), which were the operational core of the constellation. The characterisation of the retroreflectors against their design requirements is important because LRAs (Laser Retroreflector Arrays) will be flown on all Galileo satellites.

Apollo 10 and 11 crews photographed during Apollo 10 debriefing

NASA Image and Video Library

1969-06-03

S69-35504 (June 1969) --- The prime crews of the Apollo 10 lunar orbit mission and the Apollo 11 lunar landing mission are photographed during an Apollo 10 postflight de-briefing session. Clockwise, from left foreground, are astronauts Michael Collins, Apollo 11 command module pilot; Edwin E. Aldrin Jr., Apollo 11 lunar module pilot; Eugene A. Cernan, Apollo 10 lunar module pilot; Thomas P. Stafford, Apollo 10 commander; Neil A. Armstrong, Apollo 11 commander; and John W. Young, Apollo 10 command module pilot.

Apollo 10 and 11 crews photographed during Apollo 10 debriefing

NASA Image and Video Library

1969-06-03

S69-35507 (June 1969) --- The prime crews of the Apollo 10 lunar orbit mission and the Apollo 11 lunar landing mission are photographed during an Apollo 10 postflight de-briefing session. Clockwise, from left, are astronauts Michael Collins, Apollo 11 command module pilot; Edwin E. Aldrin Jr., Apollo 11 lunar module pilot; Eugene A. Cernan, Apollo 10 lunar module pilot; Thomas P. Stafford, Apollo 10 commander; Neil A. Armstrong, Apollo 11 commander; and John W. Young, Apollo 10 command module pilot.

APOLLO X - CREW

NASA Image and Video Library

1969-06-03

S69-35505 (June 1969) --- The prime crews of the Apollo 10 lunar orbit mission and the Apollo 11 lunar landing mission are photographed during an Apollo 10 postflight de-briefing session. Clockwise, from left foreground, are astronauts Michael Collins, Apollo 11 command module pilot; Edwin E. Aldrin Jr., Apollo 11 lunar module pilot; Eugene A. Cernan, Apollo 10 lunar module pilot; Thomas P. Stafford, Apollo 10 commander; Neil A. Armstrong, Apollo 11 commander; and John W. Young, Apollo 10 command module pilot.

What's the Cube Quest Challenge?

NASA Technical Reports Server (NTRS)

Cockrell, Jim

2016-01-01

Cube Quest Challenge, sponsored by Space Technology Mission Directorates Centennial Challenges program, is NASAs first in-space prize competition. Cube Quest is open to any U.S.-based, non-government CubeSat developer. Entrants will compete for one of three available 6U CubeSat dispenser slots on the EM-1 mission the first un-crewed lunar flyby of the Orion spacecraft launched by the Space Launch System in early 2018. The Cube Quest Challenge will award up to $5M in prizes. The advanced CubeSat technologies demonstrated by Cube Quest winners will enable NASA, universities, and industry to more quickly and affordably accomplish science and exploration objectives. This paper describes the teams, their novel CubeSat designs, and the emerging technologies for CubeSat operations in deep space environment.

Photogrammetry Tool for Forensic Analysis

NASA Technical Reports Server (NTRS)

Lane, John

2012-01-01

A system allows crime scene and accident scene investigators the ability to acquire visual scene data using cameras for processing at a later time. This system uses a COTS digital camera, a photogrammetry calibration cube, and 3D photogrammetry processing software. In a previous instrument developed by NASA, the laser scaling device made use of parallel laser beams to provide a photogrammetry solution in 2D. This device and associated software work well under certain conditions. In order to make use of a full 3D photogrammetry system, a different approach was needed. When using multiple cubes, whose locations relative to each other are unknown, a procedure that would merge the data from each cube would be as follows: 1. One marks a reference point on cube 1, then marks points on cube 2 as unknowns. This locates cube 2 in cube 1 s coordinate system. 2. One marks reference points on cube 2, then marks points on cube 1 as unknowns. This locates cube 1 in cube 2 s coordinate system. 3. This procedure is continued for all combinations of cubes. 4. The coordinate of all of the found coordinate systems is then merged into a single global coordinate system. In order to achieve maximum accuracy, measurements are done in one of two ways, depending on scale: when measuring the size of objects, the coordinate system corresponding to the nearest cube is used, or when measuring the location of objects relative to a global coordinate system, a merged coordinate system is used. Presently, traffic accident analysis is time-consuming and not very accurate. Using cubes with differential GPS would give absolute positions of cubes in the accident area, so that individual cubes would provide local photogrammetry calibration to objects near a cube.

Crystal structure of tetra­wickmanite, Mn2+Sn4+(OH)6

PubMed Central

Lafuente, Barbara; Yang, Hexiong; Downs, Robert T.

2015-01-01

The crystal structure of tetra­wickmanite, ideally Mn2+Sn4+(OH)6 [mangan­ese(II) tin(IV) hexa­hydroxide], has been determined based on single-crystal X-ray diffraction data collected from a natural sample from Långban, Sweden. Tetra­wickmanite belongs to the octa­hedral-framework group of hydroxide-perovskite minerals, described by the general formula BB’(OH)6 with a perovskite derivative structure. The structure differs from that of an ABO3 perovskite in that the A site is empty while each O atom is bonded to an H atom. The perovskite B-type cations split into ordered B and B′ sites, which are occupied by Mn2+ and Sn4+, respectively. Tetra­wickmanite exhibits tetra­gonal symmetry and is topologically similar to its cubic polymorph, wickmanite. The tetra­wickmanite structure is characterized by a framework of alternating corner-linked [Mn2+(OH)6] and [Sn4+(OH)6] octa­hedra, both with point-group symmetry -1. Four of the five distinct H atoms in the structure are statistically disordered. The vacant A site is in a cavity in the centre of a distorted cube formed by eight octa­hedra at the corners. However, the hydrogen-atom positions and their hydrogen bonds are not equivalent in every cavity, resulting in two distinct environments. One of the cavities contains a ring of four hydrogen bonds, similar to that found in wickmanite, while the other cavity is more distorted and forms crankshaft-type chains of hydrogen bonds, as previously proposed for tetra­gonal stottite, Fe2+Ge4+(OH)6. PMID:25878828

An Optimum Space-to-Ground Communication Concept for CubeSat Platform Utilizing NASA Space Network and Near Earth Network

NASA Technical Reports Server (NTRS)

Wong, Yen F.; Kegege, Obadiah; Schaire, Scott H.; Bussey, George; Altunc, Serhat; Zhang, Yuwen; Patel Chitra

2016-01-01

National Aeronautics and Space Administration (NASA) CubeSat missions are expected to grow rapidly in the next decade. Higher data rate CubeSats are transitioning away from Amateur Radio bands to higher frequency bands. A high-level communication architecture for future space-to-ground CubeSat communication was proposed within NASA Goddard Space Flight Center. This architecture addresses CubeSat direct-to-ground communication, CubeSat to Tracking Data Relay Satellite System (TDRSS) communication, CubeSat constellation with Mothership direct-to-ground communication, and CubeSat Constellation with Mothership communication through K-Band Single Access (KSA). A study has been performed to explore this communication architecture, through simulations, analyses, and identifying technologies, to develop the optimum communication concepts for CubeSat communications. This paper presents details of the simulation and analysis that include CubeSat swarm, daughter ship/mother ship constellation, Near Earth Network (NEN) S and X-band direct to ground link, TDRSS Multiple Access (MA) array vs Single Access mode, notional transceiver/antenna configurations, ground asset configurations and Code Division Multiple Access (CDMA) signal trades for daughter ship/mother ship CubeSat constellation inter-satellite cross link. Results of space science X-band 10 MHz maximum achievable data rate study are summarized. CubeSat NEN Ka-Band end-to-end communication analysis is provided. Current CubeSat communication technologies capabilities are presented. Compatibility test of the CubeSat transceiver through NEN and SN is discussed. Based on the analyses, signal trade studies and technology assessments, the desired CubeSat transceiver features and operation concepts for future CubeSat end-to-end communications are derived.

Six Apollo astronauts in front of Saturn V at ASVC prior to grand opening

NASA Technical Reports Server (NTRS)

1997-01-01

Some of the former Apollo program astronauts pose in front of an Apollo Command and Service Module during a tour the new Apollo/Saturn V Center (ASVC) at KSC prior to the gala grand opening ceremony for the facility that was held Jan. 8, 1997. The astronauts were invited to participate in the event, which also featured NASA Administrator Dan Goldin and KSC Director Jay Honeycutt. The astronauts are (from left): Apollo 14 Lunar Module Pilot Edgar D. Mitchell; Apollo 10 Command Module Pilot and Apollo 16 Commander John W. Young; Apollo 11 Lunar Module Pilot Edwin E. 'Buzz' Aldrin, Jr.; Apollo 10 Commander Thomas P. Stafford; Apollo 10 Lunar Module Pilot and Apollo 17 Commander Eugene A. Cernan; and Apollo 9 Lunar Module Pilot Russell L. Schweikart. The ASVC also features several other Apollo program spacecraft components, multimedia presentations and a simulated Apollo/Saturn V liftoff. The facility will be a part of the KSC bus tour that embarks from the KSC Visitor Center.

RainCube 6U CubeSat

NASA Image and Video Library

2018-05-17

The RainCube 6U CubeSat with fully-deployed antenna. RainCube, CubeRRT and TEMPEST-D are currently integrated aboard Orbital ATKs Cygnus spacecraft and are awaiting launch on an Antares rocket. After the CubeSats have arrived at the station, they will be deployed into low-Earth orbit and will begin their missions to test these new technologies useful for predicting weather, ensuring data quality, and helping researchers better understand storms. https://photojournal.jpl.nasa.gov/catalog/PIA22457

CubeSat Artist Rendering and NASA M-Cubed/COVE

NASA Image and Video Library

2012-02-14

The image on the left is an artist rendering of Montana State University Explorer 1 CubeSat; at right is a CubeSat created by the University of Michigan designated the Michigan Mulitpurpose Mini-satellite, or M-Cubed.

Effect of contact angle on the orientation, stability, and assembly of dense floating cubes.

PubMed

Daniello, Robert; Khan, Kashan; Donnell, Michael; Rothstein, Jonathan P

2014-02-01

In this paper, the effect of contact angle, density, and size on the orientation, stability, and assembly of floating cubes was investigated. All the cubes tested were more dense than water. Floatation occurred as a result of capillary stresses induced by deformation of the air-water interface. The advancing contact angle of the bare acrylic cubes was measured to be 85°. The contact angle of the cubes was increased by painting the cubes with a commercially available superhydrophobic paint to reach an advancing contact angle of 150°. Depending on their size, density, and contact angle, the cubes were observed to float in one of three primary orientations: edge up, vertex up, and face up. An experimental apparatus was built such that the sum of the gravitational force, buoyancy force, and capillary forces could be measured using a force transducer as a function of cube position as it was lowered through the air-water interface. Measurements showed that the maximum capillary forces were always experienced for the face up orientation. However, when floatation was possible in the vertex up orientation, it was found to be the most stable cube orientation because it had the lowest center of gravity. A series of theoretical predictions were performed for the cubes floating in each of the three primary orientations to calculate the net force on the cube. The theoretical predictions were found to match the experimental measurements well. A cube stability diagram of cube orientation as a function of cube contact angle and size was prepared from the predictions of theory and found to match the experimental observations quite well. The assembly of cubes floating face up and vertex up were also studied for assemblies of two, three, and many cubes. Cubes floating face up were found to assemble face-to-face and form regular square lattice patterns with no free interface between cubes. Cubes floating vertex up were found to assemble in a variety of different arrangements including edge-to-edge, vertex-to-vertex, face-to-face, and vertex-to-face with the most probably assembly being edge-to-edge. Large numbers of vertex up cubes were found to pack with a distribution of orientations and alignments.

Enhanced optical discrimination system based on switchable retroreflective films

NASA Astrophysics Data System (ADS)

Schultz, Phillip; Heikenfeld, Jason

2016-04-01

Reported herein is the design, characterization, and demonstration of a laser interrogation and response optical discrimination system based on large-area corner-cube retroreflective films. The switchable retroreflective films use light-scattering liquid crystal to modulate retroreflected intensity. The system can operate with multiple wavelengths (visible to infrared) and includes variable divergence optics for irradiance adjustments and ease of system alignment. The electronic receiver and switchable retroreflector offer low-power operation (<4 mW standby) on coin cell batteries with rapid interrogation to retroreflected signal reception response times (<15 ms). The entire switchable retroreflector film is <1 mm thick and is flexible for optimal placement and increased angular response. The system was demonstrated in high ambient lighting conditions (daylight, 18k lux) with a visible 10-mW output 635-nm source out to a distance of 400 m (naked eye detection). Nighttime demonstrations were performed using a 1.5-mW, 850-nm infrared laser diode out to a distance of 400 m using a night vision camera. This system could have tagging and conspicuity applications in commercial or military settings.

Directable weathering of concave rock using curvature estimation.

PubMed

Jones, Michael D; Farley, McKay; Butler, Joseph; Beardall, Matthew

2010-01-01

We address the problem of directable weathering of exposed concave rock for use in computer-generated animation or games. Previous weathering models that admit concave surfaces are computationally inefficient and difficult to control. In nature, the spheroidal and cavernous weathering rates depend on the surface curvature. Spheroidal weathering is fastest in areas with large positive mean curvature and cavernous weathering is fastest in areas with large negative mean curvature. We simulate both processes using an approximation of mean curvature on a voxel grid. Both weathering rates are also influenced by rock durability. The user controls rock durability by editing a durability graph before and during weathering simulation. Simulations of rockfall and colluvium deposition further improve realism. The profile of the final weathered rock matches the shape of the durability graph up to the effects of weathering and colluvium deposition. We demonstrate the top-down directability and visual plausibility of the resulting model through a series of screenshots and rendered images. The results include the weathering of a cube into a sphere and of a sheltered inside corner into a cavern as predicted by the underlying geomorphological models.

Experimental quasi-single-photon transmission from satellite to earth.

PubMed

Yin, Juan; Cao, Yuan; Liu, Shu-Bin; Pan, Ge-Sheng; Wang, Jin-Hong; Yang, Tao; Zhang, Zhong-Ping; Yang, Fu-Min; Chen, Yu-Ao; Peng, Cheng-Zhi; Pan, Jian-Wei

2013-08-26

Free-space quantum communication with satellites opens a promising avenue for global secure quantum network and large-scale test of quantum foundations. Recently, numerous experimental efforts have been carried out towards this ambitious goal. However, one essential step--transmitting single photons from the satellite to the ground with high signal-to-noise ratio (SNR) at realistic environments--remains experimental challenging. Here, we report a direct experimental demonstration of the satellite-ground transmission of a quasi-single-photon source. In the experiment, single photons (~0.85 photon per pulse) are generated by reflecting weak laser pulses back to earth with a cube-corner retro-reflector on the satellite CHAMP, collected by a 600-mm diameter telescope at the ground station, and finally detected by single-photon counting modules after 400-km free-space link transmission. With the help of high accuracy time synchronization, narrow receiver field-of-view and high-repetition-rate pulses (76 MHz), a SNR of better than 16:1 is obtained, which is sufficient for a secure quantum key distribution. Our experimental results represent an important step towards satellite-ground quantum communication.

Post-Flight Estimation of Motion of Space Structures: Part 2

NASA Technical Reports Server (NTRS)

Brugarolas, Paul; Breckenridge, William

2008-01-01

A computer program related to the one described in the immediately preceding article estimates the relative position of two space structures that are hinged to each other. The input to the program consists of time-series data on distances, measured by two range finders at different positions on one structure, to a corner-cube retroreflector on the other structure. Given a Cartesian (x,y,z) coordinate system and the known x coordinate of the retroreflector relative to the y,z plane that contains the range finders, the program estimates the y and z coordinates of the retroreflector. The estimation process involves solving for the y,z coordinates of the intersection between (1) the y,z plane that contains the retroreflector and (2) spheres, centered on the range finders, having radii equal to the measured distances. In general, there are two such solutions and the program chooses the one consistent with the design of the structures. The program implements a Kalman filter. The output of the program is a time series of estimates of the relative position of the structures.

Macroscopic superpositions and gravimetry with quantum magnetomechanics.

PubMed

Johnsson, Mattias T; Brennen, Gavin K; Twamley, Jason

2016-11-21

Precision measurements of gravity can provide tests of fundamental physics and are of broad practical interest for metrology. We propose a scheme for absolute gravimetry using a quantum magnetomechanical system consisting of a magnetically trapped superconducting resonator whose motion is controlled and measured by a nearby RF-SQUID or flux qubit. By driving the mechanical massive resonator to be in a macroscopic superposition of two different heights our we predict that our interferometry protocol could, subject to systematic errors, achieve a gravimetric sensitivity of Δg/g ~ 2.2 × 10 -10  Hz -1/2 , with a spatial resolution of a few nanometres. This sensitivity and spatial resolution exceeds the precision of current state of the art atom-interferometric and corner-cube gravimeters by more than an order of magnitude, and unlike classical superconducting interferometers produces an absolute rather than relative measurement of gravity. In addition, our scheme takes measurements at ~10 kHz, a region where the ambient vibrational noise spectrum is heavily suppressed compared the ~10 Hz region relevant for current cold atom gravimeters.

Macroscopic superpositions and gravimetry with quantum magnetomechanics

PubMed Central

Johnsson, Mattias T.; Brennen, Gavin K.; Twamley, Jason

2016-01-01

Precision measurements of gravity can provide tests of fundamental physics and are of broad practical interest for metrology. We propose a scheme for absolute gravimetry using a quantum magnetomechanical system consisting of a magnetically trapped superconducting resonator whose motion is controlled and measured by a nearby RF-SQUID or flux qubit. By driving the mechanical massive resonator to be in a macroscopic superposition of two different heights our we predict that our interferometry protocol could, subject to systematic errors, achieve a gravimetric sensitivity of Δg/g ~ 2.2 × 10−10 Hz−1/2, with a spatial resolution of a few nanometres. This sensitivity and spatial resolution exceeds the precision of current state of the art atom-interferometric and corner-cube gravimeters by more than an order of magnitude, and unlike classical superconducting interferometers produces an absolute rather than relative measurement of gravity. In addition, our scheme takes measurements at ~10 kHz, a region where the ambient vibrational noise spectrum is heavily suppressed compared the ~10 Hz region relevant for current cold atom gravimeters. PMID:27869142

Lunar and Lagrangian Point L1 L2 CubeSat Communication and Navigation Considerations

NASA Technical Reports Server (NTRS)

Schaire, Scott; Wong, Yen F.; Altunc, Serhat; Bussey, George D.; Shelton, Marta; Folta, Dave; Gramling, Cheryl; Celeste, Peter; Anderson, Mike; Perrotto, Trish;

Apollo 40th Anniversary Press Conference

NASA Image and Video Library

2009-07-19

Astronaut James Lovell (Apollo 8 Apollo 13), center, flanked by Walt Cunningham (Apollo 7), left, and David Scott (Apollo 9 Apollo 15) responds during the 40th anniversary of the Apollo 11 mission and the walk on the moon press conference, Monday, July 20, 2009, at NASA Headquarters in Washington. Photo Credit: (NASA/Paul E. Alers)

Reinforcement of the Cube texture during recrystallization of a 1050 aluminum alloy partially recrystallized and 10% cold-rolled

DOE Office of Scientific and Technical Information (OSTI.GOV)

Wang Wei; Helbert, Anne-Laure, E-mail: anne-laure.helbert@u-psud.fr; Baudin, Thierry

In high purity Aluminum, very strong {l_brace}100{r_brace}<001> recrystallization texture is developed after 98% cold rolling and annealing at 500 Degree-Sign C. On the contrary, in Aluminum alloys of commercial purity, the Cube component hardly exceeds 30% after complete recrystallization. Parameters controlling Cube orientation development are mainly the solute dragging due to impurities in solid solution and the stored deformation energy. In the present study, besides the 85% cold rolling, two extra annealings and a slight cold rolling are introduced in the processing route to increase the Cube volume fraction. The Cube development was analyzed by X-ray diffraction and Electron BackScatteredmore » Diffraction (EBSD). The nucleation and growth mechanisms responsible for the large Cube growth were investigated using FEG/EBSD in-situ heating experiments. Continuous recrystallization was observed in Cube oriented grains and competed with SIBM (Strain Induced Boundary Migration) mechanism. This latter was favored by the stored energy gap introduced during the additional cold-rolling between the Cube grains and their neighbors. Finally, a Cube volume fraction of 65% was reached after final recrystallization. - Highlights: Black-Right-Pointing-Pointer EBSD in-situ heating experiments of aluminum alloy of commercial purity. Black-Right-Pointing-Pointer A 10% cold-rolling after a partial recrystallization improved Cube nucleation and growth. Black-Right-Pointing-Pointer Annealing before cold-rolling limited the solute drag effect and permitted a large Cube growth. Black-Right-Pointing-Pointer Cube development is enhanced by continuous recrystallization of Cube sub-grains. Black-Right-Pointing-Pointer The preferential Cube growth occurs by SIBM of small Cube grains.« less

Hybrid display of static image and aerial image by use of transparent acrylic cubes and retro-reflectors

NASA Astrophysics Data System (ADS)

Morita, Shogo; Ito, Shusei; Yamamoto, Hirotsugu

2017-02-01

Aerial display can form transparent floating screen in the mid-air and expected to provide aerial floating signage. We have proposed aerial imaging by retro-reflection (AIRR) to form a large aerial LED screen. However, luminance of aerial image is not sufficiently high so as to be used for signage under broad daylight. The purpose of this paper is to propose a novel aerial display scheme that features hybrid display of two different types of images. Under daylight, signs made of cubes are visible. At night, or under dark lighting situation, aerial LED signs become visible. Our proposed hybrid display is composed of an LED sign, a beam splitter, retro-reflectors, and transparent acrylic cubes. Aerial LED sign is formed with AIRR. Furthermore, we place transparent acrylic cubes on the beam splitter. Light from the LED sign enters transparent acrylic cubes, reflects twice in the transparent acrylic cubes, exit and converge to planesymmetrical position with light source regarding the cube array. Thus, transparent acrylic cubes also form the real image of the source LED sign. Now, we form a sign with the transparent acrylic cubes so that this cube-based sign is apparent under daylight. We have developed a proto-type display by use of 1-cm transparent cubes and retro-reflective sheeting and successfully confirmed aerial image forming with AIRR and transparent cubes as well as cube-based sign under daylight.

Five Apollo astronauts with Lunar Module at ASVC prior to grand opening

NASA Technical Reports Server (NTRS)

1997-01-01

Some of the former Apollo program astronauts observe a Lunar Module and Moon mockup during a tour the new Apollo/Saturn V Center (ASVC) at KSC prior to the gala grand opening ceremony for the facility that was held Jan. 8, 1997. The astronauts were invited to participate in the event, which also featured NASA Administrator Dan Goldin and KSC Director Jay Honeycutt. Some of the visiting astonauts were (from left): Apollo 10 Lunar Module Pilot and Apollo 17 Commander Eugene A. Cernan; Apollo 9 Lunar Module Pilot Russell L. Schweikart; Apollo 10 Command Module Pilot and Apollo 16 Commander John W. Young; Apollo 10 Commander Thomas P. Stafford; and Apollo 11 Lunar Module Pilot Edwin E. 'Buzz' Aldrin, Jr. The ASVC also features several other Apollo program spacecraft components, multimedia presentations and a simulated Apollo/Saturn V liftoff. The facility will be a part of the KSC bus tour that embarks from the KSC Visitor Center.

An Optimum Space-to-Ground Communication Concept for CubeSat Platform Utilizing NASA Space Network and Near Earth Network

NASA Technical Reports Server (NTRS)

Wong, Yen F.; Kegege, Obadiah; Schaire, Scott H.; Bussey, George; Altunc, Serhat; Zhang, Yuwen; Patel, Chitra

2016-01-01

National Aeronautics and Space Administration (NASA) CubeSat missions are expected to grow rapidly in the next decade. Higher data rate CubeSats are transitioning away from Amateur Radio bands to higher frequency bands. A high-level communication architecture for future space-to-ground CubeSat communication was proposed within NASA Goddard Space Flight Center. This architecture addresses CubeSat direct-to-ground communication, CubeSat to Tracking Data Relay Satellite System (TDRSS) communication, CubeSat constellation with Mothership direct-to-ground communication, and CubeSat Constellation with Mothership communication through K-Band Single Access (KSA).A Study has been performed to explore this communication architecture, through simulations, analyses, and identifying technologies, to develop the optimum communication concepts for CubeSat communications. This paper will present details of the simulation and analysis that include CubeSat swarm, daughter shipmother ship constellation, Near Earth Network (NEN) S and X-band direct to ground link, TDRS Multiple Access (MA) array vs Single Access mode, notional transceiverantenna configurations, ground asset configurations and Code Division Multiple Access (CDMA) signal trades for daughter mother CubeSat constellation inter-satellite crosslink. Results of Space Science X-band 10 MHz maximum achievable data rate study will be summarized. Assessment of Technology Readiness Level (TRL) of current CubeSat communication technologies capabilities will be presented. Compatibility test of the CubeSat transceiver through NEN and Space Network (SN) will be discussed. Based on the analyses, signal trade studies and technology assessments, the functional design and performance requirements as well as operation concepts for future CubeSat end-to-end communications will be derived.

CubeIndexer: Indexer for regions of interest in data cubes

NASA Astrophysics Data System (ADS)

Chilean Virtual Observatory; Araya, Mauricio; Candia, Gabriel; Gregorio, Rodrigo; Mendoza, Marcelo; Solar, Mauricio

2015-12-01

CubeIndexer indexes regions of interest (ROIs) in data cubes reducing the necessary storage space. The software can process data cubes containing megabytes of data in fractions of a second without human supervision, thus allowing it to be incorporated into a production line for displaying objects in a virtual observatory. The software forms part of the Chilean Virtual Observatory (ChiVO) and provides the capability of content-based searches on data cubes to the astronomical community.

Four Apollo astronauts with Command and Service Module at ASVC prior to grand opening

NASA Technical Reports Server (NTRS)

1997-01-01

Some of the former Apollo program astronauts admire an Apollo Command and Service Module during a tour the new Apollo/Saturn V Center (ASVC) at KSC prior to the gala grand opening ceremony for the facility that was held Jan. 8, 1997. The astronauts were invited to participate in the event, which also featured NASA Administrator Dan Goldin and KSC Director Jay Honeycutt. The astronauts are (from left): Apollo 10 Command Module Pilot and Apollo 16 Commander John W. Young;. Apollo 11 Lunar Module Pilot Edwin E. 'Buzz' Aldrin, Jr.; Apollo 17 Commander Eugene A. Cernan; and Apollo 10 Commander Thomas P. Stafford. The ASVC also features several other Apollo program spacecraft components, multimedia presentations and a simulated Apollo/Saturn V liftoff. The facility will be a part of the KSC bus tour that embarks from the KSC Visitor Center.

Engle, Cernan, Young, and Stafford under Saturn V at ASVC prior to grand opening

NASA Technical Reports Server (NTRS)

1997-01-01

Some of the former Apollo program astronauts recall the past as they tour the new Apollo/Saturn V Center (ASVC) at KSC prior to the gala grand opening ceremony for the facility that was held Jan. 8, 1997. The astronauts were invited to participate in the event, which also featured NASA Administrator Dan Goldin and KSC Director Jay Honeycutt. Standing underneath the KSC Apollo/Saturn V inside the building are (from left): Apollo 14 Back-up Lunar Module Pilot Joe H. Engle; Apollo 10 Lunar Module Pilot and Apollo 17 Commander Eugene A. Cernan; Apollo 10 Command Module Pilot and Apollo 16 Commander John W. Young; and Apollo 10 Commander Thomas P. Stafford. The ASVC also features several other Apollo program spacecraft components, multimedia presentations and a simulated Apollo/Saturn V liftoff. The facility will be a part of the KSC bus tour that embarks from the KSC Visitor Center.

Lunar and Lagrangian Point L1 L2 CubeSat Communication and Navigation Considerations

NASA Technical Reports Server (NTRS)

Schaire, Scott; Wong, Yen F.; Altunc, Serhat; Bussey, George; Shelton, Marta; Folta, Dave; Gramling, Cheryl; Celeste, Peter; Anderson, Mile; Perrotto, Trish;

Flight Operations reunion for the Apollo 11 20th anniversary of the first manned lunar landing

NASA Technical Reports Server (NTRS)

1989-01-01

The following major areas are presented: (1) the Apollo years; (2) official flight control manning list for Apollo 11; (3) original mission control emblem; (4) foundations of flight control; (5) Apollo-11 20th anniversary program and events; (6) Apollo 11 mission operations team certificate; (7) Apollo 11 mission summary (timeline); and (8) Apollo flight control team photographs and biographies.

Apollo 1 Lessons Learned Show

NASA Image and Video Library

2017-01-27

Mike Ciannilli, the Apollo, Challenger, Columbia Lessons Learned Program manager, welcomes participants to the Apollo 1 Lessons Learned presentation in the Training Auditorium at NASA’s Kennedy Space Center in Florida. The program's theme was "To There and Back Again." Guest panelists included Charlie Duke, former Apollo 16 astronaut and member of the Apollo 1 Emergency Egress Investigation Team; Ernie Reyes, retired, Apollo 1 senior operations engineer; and John Tribe, retired, Apollo 1 Reaction and Control System lead engineer. The event helped pay tribute to the Apollo 1 crew, Gus Grissom, Ed White II, and Roger Chaffee.

Integration and Environmental Qualification Testing of Spacecraft Structures in Support of the Naval Postgraduate School CubeSat Launcher Program

DTIC Science & Technology

2009-06-01

2 3. Space Access Challenges to the CubeSat Community........ 3 B. NPSCUL/NPSCUL-LITE PROGRAM HISTORY TO DATE...Astronautics, AIAA Space 2008 Conference and Exhibition, 2008. 3 3. Space Access Challenges to the CubeSat Community In less than ten years since... challenges to space access for CubeSats.5 Launch of a CubeSat aboard US launch vehicles from US launch facilities would allow CubeSats of a sensitive nature

Temporal mapping and analysis

NASA Technical Reports Server (NTRS)

O'Hara, Charles G. (Inventor); Shrestha, Bijay (Inventor); Vijayaraj, Veeraraghavan (Inventor); Mali, Preeti (Inventor)

2011-01-01

A compositing process for selecting spatial data collected over a period of time, creating temporal data cubes from the spatial data, and processing and/or analyzing the data using temporal mapping algebra functions. In some embodiments, the temporal data cube is creating a masked cube using the data cubes, and computing a composite from the masked cube by using temporal mapping algebra.

EarthCube's Assessment Framework: Ensuring Return on Investment

NASA Astrophysics Data System (ADS)

Lehnert, K.

2016-12-01

EarthCube is a community-governed, NSF-funded initiative to transform geoscience research by developing cyberinfrastructure that improves access, sharing, visualization, and analysis of all forms of geosciences data and related resources. EarthCube's goal is to enable geoscientists to tackle the challenges of understanding and predicting a complex and evolving solid Earth, hydrosphere, atmosphere, and space environment systems. EarthCube's infrastructure needs capabilities around data, software, and systems. It is essential for EarthCube to determine the value of new capabilities for the community and the progress of the overall effort to demonstrate its value to the science community and Return on Investment for the NSF. EarthCube is therefore developing an assessment framework for research proposals, projects funded by EarthCube, and the overall EarthCube program. As a first step, a software assessment framework has been developed that addresses the EarthCube Strategic Vision by promoting best practices in software development, complete and useful documentation, interoperability, standards adherence, open science, and education and training opportunities for research developers.

Saturn Apollo Program

NASA Image and Video Library

1972-04-01

The Lunar Roving Vehicle (LRV) was designed to transport astronauts and materials on the Moon. An LRV was used on each of the last three Apollo missions; Apollo 15, Apollo 16, and Apollo 17, in 1971 and 1972, to permit the crew to travel several miles from the lunar landing site. This photograph was taken during the Apollo 16 mission.

Active CryoCubeSat

NASA Technical Reports Server (NTRS)

Swenson, Charles

2016-01-01

The Active CryoCubeSat project will demonstrate an advanced thermal control system for a 6-Unit (6U) CubeSat platform. A miniature, active thermal control system, in which a fluid is circulated in a closed loop from thermal loads to radiators, will be developed. A miniature cryogenic cooler will be integrated with this system to form a two-stage thermal control system. Key components will be miniaturized by using advanced additive manufacturing techniques resulting in a thermal testbed for proving out these technologies. Previous CubeSat missions have not tackled the problem of active thermal control systems nor have any past or current CubeSat missions included cryogenic instrumentation. This Active CryoCubeSat development effort will provide completely new capacities for CubeSats and constitutes a major advancement over the state-of-the-art in CubeSat thermal control.

NASA Administrator Dan Goldin speaks at Apollo 11 anniversary banquet.

NASA Technical Reports Server (NTRS)

1999-01-01

NASA Administrator Daniel S. Goldin (right) addresses the audience at the Apollo 11 anniversary banquet honoring the Apollo team, the people who made the entire lunar landing program possible. The banquet was held in the Apollo/Saturn V Center, part of the KSC Visitor Complex, with seating under an unused Saturn V rocket like those that powered the Apollo launches . This is the 30th anniversary of the Apollo 11 launch and moon landing, July 16 and July 20, 1969. Among the guests at the banquet were former Apollo astronauts are Neil A. Armstrong and Edwin 'Buzz' Aldrin who flew on Apollo 11, the launch of the first moon landing; Gene Cernan, who flew on Apollo 10 and 17 and was the last man to walk on the moon; and Walt Cunningham, who flew on Apollo 7.

Apollo2Go: a web service adapter for the Apollo genome viewer to enable distributed genome annotation.

PubMed

Klee, Kathrin; Ernst, Rebecca; Spannagl, Manuel; Mayer, Klaus F X

2007-08-30

Apollo, a genome annotation viewer and editor, has become a widely used genome annotation and visualization tool for distributed genome annotation projects. When using Apollo for annotation, database updates are carried out by uploading intermediate annotation files into the respective database. This non-direct database upload is laborious and evokes problems of data synchronicity. To overcome these limitations we extended the Apollo data adapter with a generic, configurable web service client that is able to retrieve annotation data in a GAME-XML-formatted string and pass it on to Apollo's internal input routine. This Apollo web service adapter, Apollo2Go, simplifies the data exchange in distributed projects and aims to render the annotation process more comfortable. The Apollo2Go software is freely available from ftp://ftpmips.gsf.de/plants/apollo_webservice.

CubeSat Launch Initiative Overview and CubeSat 101

NASA Technical Reports Server (NTRS)

Higginbotham, Scott

2017-01-01

The National Aeronautics and Space Administration (NASA) recognizes the tremendous potential that CubeSats (very small satellites) have to inexpensively demonstrate advanced technologies, collect scientific data, and enhance student engagement in Science, Technology, Engineering, and Mathematics (STEM). The CubeSat Launch Initiative (CSLI) was created to provide launch opportunities for CubeSats developed by academic institutions, non-profit entities, and NASA centers. This presentation will provide an overview of the CSLI, its benefits, and its results. This presentation will also provide high level CubeSat 101 information for prospective CubeSat developers, describing the development process from concept through mission operations while highlighting key points that developers need to be mindful of.

Corner detection and sorting method based on improved Harris algorithm in camera calibration

NASA Astrophysics Data System (ADS)

Xiao, Ying; Wang, Yonghong; Dan, Xizuo; Huang, Anqi; Hu, Yue; Yang, Lianxiang

2016-11-01

In traditional Harris corner detection algorithm, the appropriate threshold which is used to eliminate false corners is selected manually. In order to detect corners automatically, an improved algorithm which combines Harris and circular boundary theory of corners is proposed in this paper. After detecting accurate corner coordinates by using Harris algorithm and Forstner algorithm, false corners within chessboard pattern of the calibration plate can be eliminated automatically by using circular boundary theory. Moreover, a corner sorting method based on an improved calibration plate is proposed to eliminate false background corners and sort remaining corners in order. Experiment results show that the proposed algorithms can eliminate all false corners and sort remaining corners correctly and automatically.

NASA Administrator Dan Goldin speaks at Apollo 11 anniversary banquet.

NASA Technical Reports Server (NTRS)

1999-01-01

NASA Administrator Daniel S. Goldin addresses the audience at the Apollo 11 anniversary banquet honoring the Apollo team, the people who made the entire lunar landing program possible. The banquet was held in the Apollo/Saturn V Center, part of the KSC Visitor Complex. This is the 30th anniversary of the Apollo 11 launch and moon landing, July 16 and July 20, 1969. Among the guests at the banquet were former Apollo astronauts are Neil A. Armstrong and Edwin 'Buzz' Aldrin who flew on Apollo 11, the launch of the first moon landing; Gene Cernan, who flew on Apollo 10 and 17 and was the last man to walk on the moon; and Walt Cunningham, who flew on Apollo 7.

Apollo 1 Lessons Learned Show

NASA Image and Video Library

2017-01-27

Charlie Duke, former Apollo 16 astronaut and member of the Apollo 1 Emergency Egress Investigation Team, speaks to participants during the Apollo 1 Lessons Learned presentation in the Training Auditorium at NASA's Kennedy Space Center in Florida. The program's theme was "To There and Back Again." Other guest panelists included Ernie Reyes, retired, Apollo 1 senior operations engineer; and John Tribe, retired, Apollo 1 Reaction and Control System lead engineer. The event helped pay tribute to the Apollo 1 crew, Gus Grissom, Ed White II, and Roger Chaffee.

CubeRovers for Lunar Exploration

NASA Astrophysics Data System (ADS)

Tallaksen, A. P.; Horchler, A. D.; Boirum, C.; Arnett, D.; Jones, H. L.; Fang, E.; Amoroso, E.; Chomas, L.; Papincak, L.; Sapunkov, O. B.; Whittaker, W. L.

2017-10-01

CubeRover is a 2-kg class of lunar rover that seeks to standardize and democratize surface mobility and science, analogous to CubeSats. This CubeRover will study in-situ lunar surface trafficability and descent engine blast ejecta phenomena.

Chemistry Cube Game - Exploring Basic Principles of Chemistry by Turning Cubes.

PubMed

Müller, Markus T

2018-02-01

The Chemistry Cube Game invites students at secondary school level 1 and 2 to explore basic concepts of chemistry in a playful way, either as individuals or in teams. It consists of 15 different cubes, 9 cubes for different acids, their corresponding bases and precursors, and 6 cubes for different reducing and oxidising agents. The cubes can be rotated in those directions indicated. Each 'allowed' vertical or horizontal rotation of 90° stands for a chemical reaction or a physical transition. Two different games and playing modes are presented here: First, redox chemistry is introduced for the formation of salts from elementary metals and non-metals. Second, the speciation of acids and bases at different pH-values is shown. The cubes can be also used for games about environmental chemistry such as the carbon and sulphur cycle, covering the topic of acid rain, or the nitrogen cycle including ammoniac synthesis, nitrification and de-nitrification.

Methods for gas detection using stationary hyperspectral imaging sensors

DOEpatents

Conger, James L [San Ramon, CA; Henderson, John R [Castro Valley, CA

2012-04-24

According to one embodiment, a method comprises producing a first hyperspectral imaging (HSI) data cube of a location at a first time using data from a HSI sensor; producing a second HSI data cube of the same location at a second time using data from the HSI sensor; subtracting on a pixel-by-pixel basis the second HSI data cube from the first HSI data cube to produce a raw difference cube; calibrating the raw difference cube to produce a calibrated raw difference cube; selecting at least one desired spectral band based on a gas of interest; producing a detection image based on the at least one selected spectral band and the calibrated raw difference cube; examining the detection image to determine presence of the gas of interest; and outputting a result of the examination. Other methods, systems, and computer program products for detecting the presence of a gas are also described.

View of the orange soil which Apollo 17 crewmen found at Station 4 during EVA

NASA Image and Video Library

1972-12-12

AS17-137-20989 (12 Dec. 1972) --- A close-up view of the much-publicized orange soil which the Apollo 17 crewmen found at Station 4 (Shorty Crater) during the second Apollo 17 extravehicular activity (EVA) at the Taurus-Littrow landing site. The orange soil was first spotted by scientist-astronaut Harrison H. Schmitt. While astronauts Schmitt and Eugene A. Cernan descended in the Lunar Module (LM) "Challenger" to explore the lunar surface, astronaut Ronald E. Evans remained with the Apollo 17 Command and Service Modules (CSM) in lunar orbit. The orange soil was never seen by the crewmen of the other lunar landing missions - Apollo 11 (Sea of Tranquility); Apollo 12 (Ocean of Storms); Apollo 14 (Fra Mauro); Apollo 15 (Hadley-Apennines); and Apollo 16 (Descartes).

KSC-99pp0877

NASA Image and Video Library

1999-07-16

KENNEDY SPACE CENTER, FLA. -- During an anniversary banquet honoring the Apollo program team, the people who made the entire lunar landing program possible, former Apollo astronaut Gene Cernan relates a humorous comment while Wally Schirra (background) gestures behind him. Cernan, who flew on Apollo 10 and 17, was the last man to walk on the moon; Schirra flew on Apollo 7. The banquet was held in the Apollo/Saturn V Center, part of the KSC Visitor Complex. This is the 30th anniversary of the Apollo 11 launch and moon landing, July 16 and July 20, 1969. Other guests at the banquet were former Apollo astronauts are Neil A. Armstrong and Edwin "Buzz" Aldrin who flew on Apollo 11, the launch of the first moon landing, and Walt Cunningham, who also flew on Apollo 7

Cernan, Stafford, and Young talk at ASVC prior to grand opening

NASA Technical Reports Server (NTRS)

1997-01-01

Some of the former Apollo program astronauts tour the new Apollo/Saturn V Center (ASVC) at KSC prior to the gala grand opening ceremony for the facility that was held Jan. 8, 1997. The astronauts were invited to participate in the event, which also featured NASA Administrator Dan Goldin and KSC Director Jay Honeycutt. Discussing old times beneath the KSC Apollo/Saturn V rocket inside the building are (from left) Apollo 10 Lunar Module Pilot and Apollo 17 Commander Eugene A. Cernan; Apollo 10 Commander Thomas P. Stafford and Apollo 16 Commander John W. Young. The ASVC also features several other Apollo program spacecraft components, multimedia presentations and a simulated Apollo/ Saturn V liftoff. The facility will be a part of the KSC bus tour that embarks from the KSC Visitor Center.

Random sequential adsorption of cubes

NASA Astrophysics Data System (ADS)

Cieśla, Michał; Kubala, Piotr

2018-01-01

Random packings built of cubes are studied numerically using a random sequential adsorption algorithm. To compare the obtained results with previous reports, three different models of cube orientation sampling were used. Also, three different cube-cube intersection algorithms were tested to find the most efficient one. The study focuses on the mean saturated packing fraction as well as kinetics of packing growth. Microstructural properties of packings were analyzed using density autocorrelation function.

BurstCube: A CubeSat for Gravitational Wave Counterparts

NASA Astrophysics Data System (ADS)

Perkins, Jeremy S.; Racusin, Judith; Briggs, Michael; de Nolfo, Georgia; Caputo, Regina; Krizmanic, John; McEnery, Julie E.; Shawhan, Peter; Morris, David; Connaughton, Valerie; Kocevski, Dan; Wilson-Hodge, Colleen A.; Hui, Michelle; Mitchell, Lee; McBreen, Sheila

2018-01-01

We present BurstCube, a novel CubeSat that will detect and localize Gamma-ray Bursts (GRBs). BurstCube is a selected mission that will detect long GRBs, attributed to the collapse of massive stars, short GRBs (sGRBs), resulting from binary neutron star mergers, as well as other gamma-ray transients in the energy range 10-1000 keV. sGRBs are of particular interest because they are predicted to be the counterparts of gravitational wave (GW) sources soon to be detectable by LIGO/Virgo. BurstCube contains 4 CsI scintillators coupled with arrays of compact low-power Silicon photomultipliers (SiPMs) on a 6U Dellingr bus, a flagship modular platform that is easily modifiable for a variety of 6U CubeSat architectures. BurstCube will complement existing facilities such as Swift and Fermi in the short term, and provide a means for GRB detection, localization, and characterization in the interim time before the next generation future gamma-ray mission flies, as well as space-qualify SiPMs and test technologies for future use on larger gamma-ray missions. The ultimate configuration of BurstCube is to have a set of ~10 BurstCubes to provide all-sky coverage to GRBs for substantially lower cost than a full-scale mission.

Prime crew photographed during Apollo 7 mission

NASA Technical Reports Server (NTRS)

1968-01-01

Astronaut Walter M. Schirra Jr., Apollo 7 commander, is photographed during the Apollo 7 mission (1582); Astronaut Donn F. Eisele, Apollo 7 command module pilot, is photographed during the mission (1583); Astronaut Walter Cunningham, Apollo 7 lunar module pilot, is photographed during mission (1584).

Prime crew photographed during Apollo 7 mission

NASA Technical Reports Server (NTRS)

1968-01-01

Astronaut Walter M. Schirra Jr., Apollo 7 commander, is photographed during the Apollo 7 mission (1582); Astronaut Donn F. Eisele, Apollo 7 command module pilot, is phtographed during the mission (1583); Astronaut Walter Cunningham, Apollo 7 lunar module pilot, is photographed during mission (1584).

Apollo 1 Lessons Learned Show

NASA Image and Video Library

2017-01-27

Kennedy Space Center Director Bob Cabana welcomes participants to the Apollo 1 Lessons Learned presentation in the Training Auditorium at NASA’s Kennedy Space Center in Florida. The program's theme was "To There and Back Again." Guest panelists included Charlie Duke, former Apollo 16 astronaut and member of the Apollo 1 Emergency Egress Investigation Team; Ernie Reyes, retired, Apollo 1 senior operations engineer; and John Tribe, retired, Apollo 1 Reaction and Control System lead engineer. The event helped pay tribute to the Apollo 1 crew, Gus Grissom, Ed White II, and Roger Chaffee.

Apollo 13 Emblem

NASA Image and Video Library

1969-12-01

S69-60662 (December 1969) --- This is the insignia of the Apollo 13 lunar landing mission. The Apollo 13 prime crew will be astronauts James A. Lovell Jr., commander; Thomas K. Mattingly II, command module pilot; and Fred W. Haise Jr., lunar module pilot. Represented in the Apollo 13 emblem is Apollo, the sun god of Greek mythology, symbolizing how the Apollo flights have extended the light of knowledge to all mankind. The Latin phrase Ex Luna, Scientia means "From the Moon, Knowledge." Apollo 13 will be the National Aeronautics and Space Administration's (NASA) third lunar landing mission.

Effects of the Large June 1975 Meteoroid Storm on Earth's Ionosphere.

PubMed

Kaufmann, P; Kuntz, V L; Leme, N M; Piazza, L R; Boas, J W; Brecher, K; Crouchley, J

1989-11-10

The June 1975 meteoroid storm detected on the moon by the Apollo seismometers was the largest ever observed. Reexamination of radio data taken at that time showed that the storm also produced pronounced disturbances on Earth, which were recorded as unique phase anomalies on very low frequency (VLF) radio propagation paths in the low terrestrial ionosphere. Persistent effects were observed for the major storm period (20 to 30 June 1975), including reductions in the diurnal phase variation, advances in the nighttime and daytime phase levels, and reductions in the sunset phase delay rate. Large nighttime phase advances, lasting a few hours, were detected on some days at all VLF transmissions, and for the shorter propagation path they were comparable to solar Lyman alpha daytime ionization. Ion production rates attributable to the meteor storm were estimated to be about 0.6 to 3.0 ions per centimeter cubed per second at the E and D regions, respectively. The storm was a sporadic one with a radiant (that is, the point of apparent origin in the sky) located in the Southern Hemisphere, with a right ascension 1 to 2 hours larger than the sun's right ascension.

KSC-99pp0875

NASA Image and Video Library

1999-07-16

KENNEDY SPACE CENTER, FLA. -- NASA Administrator Daniel S. Goldin (right) addresses the audience at the Apollo 11 anniversary banquet honoring the Apollo team, the people who made the entire lunar landing program possible. The banquet was held in the Apollo/Saturn V Center, part of the KSC Visitor Complex, with seating under an unused Saturn V rocket like those that powered the Apollo launches . This is the 30th anniversary of the Apollo 11 launch and moon landing, July 16 and July 20, 1969. Among the guests at the banquet were former Apollo astronauts are Neil A. Armstrong and Edwin "Buzz" Aldrin who flew on Apollo 11, the launch of the first moon landing; Gene Cernan, who flew on Apollo 10 and 17 and was the last man to walk on the moon; and Walt Cunningham, who flew on Apollo 7

NASA Administrator Dan Goldin greets Neil Armstrong at Apollo 11 anniversary banquet.

NASA Technical Reports Server (NTRS)

1999-01-01

During an anniversary banquet honoring the Apollo team, the people who made the entire lunar landing program possible, former Apollo astronaut Neil A. Armstrong (left) shakes the hand of Judy Goldin (center), wife of NASA Administrator Daniel S. Goldin (right). The banquet was held in the Apollo/Saturn V Center, part of the KSC Visitor Complex. This is the 30th anniversary of the Apollo 11 launch and moon landing, July 16 and July 20, 1969. Among the guests at the banquet were former Apollo astronauts are Neil A. Armstrong and Edwin 'Buzz' Aldrin who flew on Apollo 11, the launch of the first moon landing; Gene Cernan, who flew on Apollo 10 and 17 and was the last man to walk on the moon; and Walt Cunningham, who flew on Apollo 7.

Apollo2Go: a web service adapter for the Apollo genome viewer to enable distributed genome annotation

PubMed Central

Klee, Kathrin; Ernst, Rebecca; Spannagl, Manuel; Mayer, Klaus FX

2007-01-01

Background Apollo, a genome annotation viewer and editor, has become a widely used genome annotation and visualization tool for distributed genome annotation projects. When using Apollo for annotation, database updates are carried out by uploading intermediate annotation files into the respective database. This non-direct database upload is laborious and evokes problems of data synchronicity. Results To overcome these limitations we extended the Apollo data adapter with a generic, configurable web service client that is able to retrieve annotation data in a GAME-XML-formatted string and pass it on to Apollo's internal input routine. Conclusion This Apollo web service adapter, Apollo2Go, simplifies the data exchange in distributed projects and aims to render the annotation process more comfortable. The Apollo2Go software is freely available from . PMID:17760972

Apollo 13 emblem

NASA Technical Reports Server (NTRS)

1969-01-01

This is the insignia of the Apollo 13 lunar landing mission. Represented in the Apollo 13 emblem is Apollo, the sun god of Greek mythology, symbolizing how the Apollo flights have extended the light of knowledge to all mankind. The Latin phrase Ex Luna, Scientia means 'From the Moon, Knowledge'.

Apollo 17: On the Shoulders of Giants

NASA Technical Reports Server (NTRS)

1973-01-01

A documentary view of the Apollo 17 journey to Taurus-Littrow, the final lunar landing mission in the Apollo program is discussed. The film depicts the highlights of the mission and relates the Apollo program to Skylab, the Apollo-Soyuz linkup and the Space Shuttle.

CUBES Project Support

NASA Technical Reports Server (NTRS)

Jenkins, Kenneth T., Jr.

2012-01-01

CUBES stands for Creating Understanding and Broadening Education through Satellites. The goal of the project is to allow high school students to build a small satellite, or CubeSat. Merritt Island High School (MIHS) was selected to partner with NASA, and California Polytechnic State University (Cal-Poly}, to build a CubeSat. The objective of the mission is to collect flight data to better characterize maximum predicted environments inside the CubeSat launcher, Poly-Picosatellite Orbital Deplorer (P-POD), while attached to the launch vehicle. The MIHS CubeSat team will apply to the NASA CubeSat Launch Initiative, which provides opportunities for small satellite development teams to secure launch slots on upcoming expendable launch vehicle missions. The MIHS team is working to achieve a test launch, or proof of concept flight aboard a suborbital launch vehicle in early 2013.

Apollo 12 crewmembers shown in Apollo Lunar Module Mission Simulator

NASA Image and Video Library

1969-11-04

S69-56699 (22 Oct. 1969) --- Astronauts Charles Conrad Jr. (left), Apollo 12 commander; and Alan L. Bean, lunar module pilot, are shown in the Apollo Lunar Module Mission Simulator during simulator training at the Kennedy Space Center (KSC). Apollo 12 will be the National Aeronautics and Space Administration's (NASA) second lunar landing mission. The third Apollo 12 crewmember will be astronaut Richard F. Gordon Jr., command module pilot.

EarthCube - A Community-led, Interdisciplinary Collaboration for Geoscience Cyberinfrastructure

NASA Astrophysics Data System (ADS)

Allison, M. L.; Keane, C. M.; Robinson, E.

2015-12-01

The EarthCube Test Enterprise Governance Project completed its initial two-year long process to engage the community and test a demonstration governing organization with the goal of facilitating a community-led process on designing and developing a geoscience cyberinfrastructure. Conclusions are that EarthCube is viable, has engaged a broad spectrum of end-users and contributors, and has begun to foster a sense of urgency around the importance of open and shared data. Levels of trust among participants are growing. At the same time, the active participants in EarthCube represent a very small sub-set of the larger population of geoscientists. Results from Stage I of this project have impacted NSF decisions on the direction of the EarthCube program. The overall tone of EarthCube events has had a constructive, problem-solving orientation. The technical and organizational elements of EarthCube are poised to support a functional infrastructure for the geosciences community. The process for establishing shared technological standards has notable progress but there is a continuing need to expand technological and cultural alignment. Increasing emphasis is being given to the interdependencies among EarthCube funded projects. The newly developed EarthCube Technology Plan highlights important progress in this area by five working groups focusing on: 1. Use cases; 2. Funded project gap analysis; 3. Testbed development; 4. Standards; and 5. Architecture. There is ample justification to continue running a community-led governance framework that facilitates agreement on a system architecture, guides EarthCube activities, and plays an increasing role in making the EarthCube vision of cyberinfrastructure for the geosciences operational. There is widespread community expectation for support of a multiyear EarthCube governing effort to put into practice the science, technical, and organizational plans that have and are continuing to emerge.

Apollo 40th Anniversary Press Conference

NASA Image and Video Library

2009-08-11

Eugene Cernan (Apollo 10, Apollo 17) , right, speaks, as Thomas Stafford (Apollo 10) looks on during the 40th anniversary of the Apollo 11 mission and the walk on the moon press conference, Monday, July 20, 2009, at NASA Headquarters in Washington Photo Credit: (NASA/Paul E. Alers)

Build an Earthquake City! Grades 6-8.

ERIC Educational Resources Information Center

Rushton, Erik; Ryan, Emily; Swift, Charles

In this activity, students build a city out of sugar cubes, bouillon cubes, and gelatin cubes. The city is then put through simulated earthquakes to see which cube structures withstand the shaking the best. This activity requires a 50-minute time period for completion. (Author/SOE)

Saturn Apollo Program

NASA Image and Video Library

1970-06-01

This image depicts the Apollo 16 mission astronauts John Young (right) and Charles Duke (left) in pressure suits during a final crew training on the Lunar Roving Vehicle (LRV) at the Marshall Space Flight Center (MSFC), building 4619. Developed by the MSFC, the LRV was the lightweight electric car designed to increase the range of mobility and productivity of astronauts on the lunar surface. It was used on the last three Apollo missions; Apollo 15, Apollo 16, and Apollo 17.

Project management in the Apollo program: An interdisciplinary study

NASA Technical Reports Server (NTRS)

Drucker, E. E.; Pooler, W. S.; Wilemon, D. L.; Wood, B. D.

1972-01-01

Findings concerning project management in the NASA Apollo program are presented. The Apollo program in the context of the total NASA organization is examined along with the nature of project management and the manner in which project managers functioned in the Apollo program. The utilization of the in-house technical competence in the support of the Apollo program, and the formal and informal relationships between Apollo managers and the contractors are discussed.

Apollo 1 Lessons Learned Show

NASA Image and Video Library

2017-01-27

Mike Ciannilli, at left, the Apollo, Challenger, Columbia Lessons Learned Program manager, presents a certificate to Charlie Duke, former Apollo 16 astronaut and member of the Apollo 1 Emergency Egress Investigation Team, during the Apollo 1 Lessons Learned presentation in the Training Auditorium at NASA's Kennedy Space Center in Florida. The program's theme was "To There and Back Again." The event helped pay tribute to the Apollo 1 crew, Gus Grissom, Ed White II, and Roger Chaffee.

Apollo 1 Lessons Learned Show

NASA Image and Video Library

2017-01-27

Mike Ciannilli, the Apollo, Challenger, Columbia Lessons Learned Program manager, far right, is pictured with panelists from the Apollo 1 Lessons Learned event in the Training Auditorium at NASA's Kennedy Space Center in Florida. In the center, are Ernie Reyes, retired, former Apollo 1 senior operations manager; and John Tribe, retired, former Apollo 1 Reaction and Control System lead engineer. At far left is Zulie Cipo, the Apollo, Challenger, Columbia Lessons Learned Program event support team lead. The theme of the program was "To there and Back Again." The event helped pay tribute to the Apollo 1 crew, Gus Grissom, Ed White II, and Roger Chaffee.

Apollo 1 Lessons Learned Show

NASA Image and Video Library

2017-01-27

Suzy Cunningham, with the Communication and Public Engagement Directorate, sings the National Anthem before the start of the Apollo 1 Lessons Learned presentation in the Training Auditorium at NASA’s Kennedy Space Center in Florida. The program's theme was "To There and Back Again." Guest panelists included Charlie Duke, former Apollo 16 astronaut and member of the Apollo 1 Emergency Egress Investigation Team; Ernie Reyes, retired, Apollo 1 senior operations engineer; and John Tribe, retired, Apollo 1 Reaction and Control System lead engineer. The event helped pay tribute to the Apollo 1 crew, Gus Grissom, Ed White II, and Roger Chaffee.

KSC-99pp0874

NASA Image and Video Library

1999-07-16

KENNEDY SPACE CENTER, FLA. -- NASA Administrator Daniel S. Goldin addresses the audience at the Apollo 11 anniversary banquet honoring the Apollo team, the people who made the entire lunar landing program possible. The banquet was held in the Apollo/Saturn V Center, part of the KSC Visitor Complex. This is the 30th anniversary of the Apollo 11 launch and moon landing, July 16 and July 20, 1969. Among the guests at the banquet were former Apollo astronauts are Neil A. Armstrong and Edwin "Buzz" Aldrin who flew on Apollo 11, the launch of the first moon landing; Gene Cernan, who flew on Apollo 10 and 17 and was the last man to walk on the moon; and Walt Cunningham, who flew on Apollo 7

Cernan, Stafford, and Young talk at ASVC prior to grand opening

NASA Technical Reports Server (NTRS)

1997-01-01

Some of the former Apollo program astronauts tour the new Apollo/Saturn V Center (ASVC) at KSC prior to the gala grand opening ceremony for the facility that was held Jan. 8, 1997. The astronauts were invited to participate in the event, which also featured NASA Administrator Dan Goldin and KSC Director Jay Honeycutt. Discussing old times are (from left) Apollo 10 Lunar Module Pilot and Apollo 17 Commander Eugene A. Cernan; Apollo 10 Commander Thomas P. Stafford and Apollo 16 Commander John W. Young. The ASVC also features several other Apollo program spacecraft components, multimedia presentations and a simulated Apollo/ Saturn V liftoff. The facility will be a part of the KSC bus tour that embarks from the KSC Visitor Center.

Apollo 13 MCC - MSC

NASA Image and Video Library

1970-04-14

S70-34986 (14 April 1970) --- A group of six astronauts and two flight controllers monitor the console activity in the Mission Operations Control Room (MOCR) of the Mission Control Center (MCC) during the problem-plagued Apollo 13 lunar landing mission. Seated, left to right, are MOCR Guidance Officer Raymond F. Teague; astronaut Edgar D. Mitchell, Apollo 14 prime crew lunar module pilot; and astronaut Alan B. Shepard Jr., Apollo 14 prime crew commander. Standing, left to right, are scientist-astronaut Anthony W. England; astronaut Joe H. Engle, Apollo 14 backup crew lunar module pilot; astronaut Eugene A. Cernan, Apollo 14 backup crew commander; astronaut Ronald E. Evans, Apollo 14 backup crew command module pilot; and M.P. Frank, a flight controller. When this picture was made, the Apollo 13 moon landing had already been canceled, and the Apollo 13 crew men were in trans-Earth trajectory attempting to bring their damaged spacecraft back home.

CubeSat Initiatives at KSC

NASA Technical Reports Server (NTRS)

Berg, Jared J.

2014-01-01

Even though the Small PayLoad Integrated Testing Services or SPLITS line of business is newly established, KSC has been involved in a variety of CubeSat projects and programs. CubeSat development projects have been initiated through educational outreach partnerships with schools and universities, commercial partnerships and internal training initiatives. KSC has also been involved in CubeSat deployment through programs to find launch opportunities to fly CubeSats as auxiliary payloads on previously planned missions and involvement in the development of new launch capabilities for small satellites. This overview will highlight the CubeSat accomplishments at KSC and discuss planning for future projects and opportunities.

Recognition and classification of oscillatory patterns of electric brain activity using artificial neural network approach

NASA Astrophysics Data System (ADS)

Pchelintseva, Svetlana V.; Runnova, Anastasia E.; Musatov, Vyacheslav Yu.; Hramov, Alexander E.

2017-03-01

In the paper we study the problem of recognition type of the observed object, depending on the generated pattern and the registered EEG data. EEG recorded at the time of displaying cube Necker characterizes appropriate state of brain activity. As an image we use bistable image Necker cube. Subject selects the type of cube and interpret it either as aleft cube or as the right cube. To solve the problem of recognition, we use artificial neural networks. In our paper to create a classifier we have considered a multilayer perceptron. We examine the structure of the artificial neural network and define cubes recognition accuracy.

Interplanetary CubeSat Navigational Challenges

NASA Technical Reports Server (NTRS)

Martin-Mur, Tomas J.; Gustafson, Eric D.; Young, Brian T.

2015-01-01

CubeSats are miniaturized spacecraft of small mass that comply with a form specification so they can be launched using standardized deployers. Since the launch of the first CubeSat into Earth orbit in June of 2003, hundreds have been placed into orbit. There are currently a number of proposals to launch and operate CubeSats in deep space, including MarCO, a technology demonstration that will launch two CubeSats towards Mars using the same launch vehicle as NASA's Interior Exploration using Seismic Investigations, Geodesy and Heat Transport (InSight) Mars lander mission. The MarCO CubeSats are designed to relay the information transmitted by the InSight UHF radio during Entry, Descent, and Landing (EDL) in real time to the antennas of the Deep Space Network (DSN) on Earth. Other CubeSatts proposals intend to demonstrate the operation of small probes in deep space, investigate the lunar South Pole, and visit a near Earth object, among others. Placing a CubeSat into an interplanetary trajectory makes it even more challenging to pack the necessary power, communications, and navigation capabilities into such a small spacecraft. This paper presents some of the challenges and approaches for successfully navigating CubeSats and other small spacecraft in deep space.

How CubeSats contribute to Science and Technology in Astronomy and Astrophysics

NASA Astrophysics Data System (ADS)

Cahoy, Kerri Lynn; Douglas, Ewan; Carlton, Ashley; Clark, James; Haughwout, Christian

2017-01-01

CubeSats are nanosatellites, spacecraft typically the size of a shoebox or backpack. CubeSats are made up of one or more 10 cm x 10 cm x 10 cm units weighing 1.33 kg (each cube is called a “U”). CubeSats benefit from relatively easy and inexpensive access to space because they are designed to slide into fully enclosed spring-loaded deployer pods before being attached as an auxiliary payload to a larger vehicle, without adding risk to the vehicle or its primary payload(s). Even though CubeSats have inherent resource and aperture limitations due to their small size, over the past fifteen years, researchers and engineers have miniaturized components and subsystems, greatly increasing the capabilities of CubeSats. We discuss how state of the art CubeSats can address both science objectives and technology objectives in Astronomy and Astrophysics. CubeSats can contribute toward science objectives such as cosmic dawn, galactic evolution, stellar evolution, extrasolar planets and interstellar exploration.CubeSats can contribute to understanding how key technologies for larger missions, like detectors, microelectromechanical systems, and integrated optical elements, can not only survive launch and operational environments (which can often be simulated on the ground), but also meet performance specifications over long periods of time in environments that are harder to simulate properly, such as ionizing radiation, the plasma environment, spacecraft charging, and microgravity. CubeSats can also contribute to both science and technology advancements as multi-element space-based platforms that coordinate distributed measurements and use formation flying and large separation baselines to counter their restricted individual apertures.

Achieving Science with CubeSats: Thinking Inside the Box

NASA Astrophysics Data System (ADS)

Zurbuchen, Thomas H.; Lal, Bhavya

2017-01-01

We present the results of a study conducted by the National Academies of Sciences, Engineering, and Medicine. The study focused on the scientific potential and technological promise of CubeSats. We will first review the growth of the CubeSat platform from an education-focused technology toward a platform of importance for technology development, science, and commercial use, both in the United States and internationally. The use has especially exploded in recent years. For example, of the over 400 CubeSats launched since 2000, more than 80% of all science-focused ones have been launched just in the past four years. Similarly, more than 80% of peer-reviewed papers describing new science based on CubeSat data have been published in the past five years.We will then assess the technological and science promise of CubeSats across space science disciplines, and discuss a subset of priority science goals that can be achieved given the current state of CubeSat capabilities. Many of these goals address targeted science, often in coordination with other spacecraft, or by using sacrificial or high-risk orbits that lead to the demise of the satellite after critical data have been collected. Other goals relate to the use of CubeSats as constellations or swarms, deploying tens to hundreds of CubeSats that function as one distributed array of measurements.Finally, we will summarize our conclusions and recommendations from this study; especially those focused on nearterm investment that could improve the capabilities of CubeSats toward increased science and technological return and enable the science communities’ use of CubeSats.

Achieving Science with CubeSats: Thinking Inside the Box

NASA Astrophysics Data System (ADS)

Lal, B.; Zurbuchen, T.

2016-12-01

In this paper, we present a study conducted by the National Academies of Sciences, Engineering, and Medicine. The study focused on the scientific potential and technological promise of CubeSats. We will first review the growth of the CubeSat platform from an education-focused technology toward a platform of importance for technology development, science, and commercial use, both in the United States and internationally. The use has especially exploded in recent years. For example, of the over 400 CubeSats launched since 2000, more than 80% of all science-focused ones have been launched just in the past four years. Similarly, more than 80% of peer-reviewed papers describing new science based on CubeSat data have been published in the past five years. We will then assess the technological and science promise of CubeSats across space science disciplines, and discuss a subset of priority science goals that can be achieved given the current state of CubeSat capabilities. Many of these goals address targeted science, often in coordination with other spacecraft, or by using sacrificial or high-risk orbits that lead to the demise of the satellite after critical data have been collected. Other goals relate to the use of CubeSats as constellations or swarms, deploying tens to hundreds of CubeSats that function as one distributed array of measurements. Finally, we will summarize our conclusions and recommendations from this study; especially those focused on near-term investment that could improve the capabilities of CubeSats toward increased science and technological return and enable the science communities' use of CubeSats.

Apollo 12 crewmembers shown in Apollo Lunar Module Mission Simulator

NASA Image and Video Library

1969-11-04

S69-56700 (22 Oct. 1969) --- A fish-eye lens view of astronauts Charles Conrad Jr. (on left), Apollo 12 commander, and Alan L. Bean, lunar module pilot, inside the Apollo Lunar Module Mission Simulator during simulator training at the Kennedy Space Center (KSC). Apollo 12 will be the National Aeronautics and Space Administration's (NASA) second lunar landing mission. The third Apollo 12 crewmember will be astronaut Richard F. Gordon Jr., command module pilot.

IceCube

Science.gov Websites

. PDF file High pT muons in Cosmic-Ray Air Showers with IceCube. PDF file IceCube Performance with Artificial Light Sources: the road to a Cascade Analyses + Energy scale calibration for EHE. PDF file , 2006. PDF file Thorsten Stetzelberger "IceCube DAQ Design & Performance" Nov 2005 PPT

Saturn Apollo Program

NASA Image and Video Library

1972-01-01

This photograph was taken during the testing of the Lunar Roving Vehicle (LRV) at the Johnson Space Center. Developed by the MSFC, the LRV was the lightweight electric car designed to increase the range of mobility and productivity of astronauts on the lunar surface. It was used on the last three Apollo missions; Apollo 15, Apollo 16, and Apollo 17.

KSC-99pp0876

NASA Image and Video Library

1999-07-16

KENNEDY SPACE CENTER, FLA. -- During an anniversary banquet honoring the Apollo team, the people who made the entire lunar landing program possible, former Apollo astronaut Neil A. Armstrong (left) shakes the hand of Judy Goldin (center), wife of NASA Administrator Daniel S. Goldin (right). The banquet was held in the Apollo/Saturn V Center, part of the KSC Visitor Complex. This is the 30th anniversary of the Apollo 11 launch and moon landing, July 16 and July 20, 1969. Among the guests at the banquet were former Apollo astronauts are Neil A. Armstrong and Edwin "Buzz" Aldrin who flew on Apollo 11, the launch of the first moon landing; Gene Cernan, who flew on Apollo 10 and 17 and was the last man to walk on the moon; and Walt Cunningham, who flew on Apollo 7

Structural Stability Assessment of the High Frequency Antenna for Use on the Buccaneer CubeSat in Low Earth Orbit

DTIC Science & Technology

2014-05-01

UNCLASSIFIED UNCLASSIFIED Structural Stability Assessment of the High Frequency Antenna for Use on the Buccaneer CubeSat in Low Earth...DSTO-TN-1295 ABSTRACT The Buccaneer CubeSat will be fitted with a high frequency antenna made from spring steel measuring tape. The geometry...High Frequency Antenna for Use on the Buccaneer CubeSat in Low Earth Orbit Executive Summary The Buccaneer CubeSat will be fitted with a

Apollo 14 - Press Kit

NASA Technical Reports Server (NTRS)

1971-01-01

Apollo 14, the sixth United States manned flight to the Moon and fourth Apollo mission with an objective of landing men on the Moon, is scheduled for launch Jan. 31 at 3:23 p.m. EST from Kennedy Space Center, Fla. The Apollo 14 lunar module is to land in the hilly upland region north of the Fra Mauro crater for a stay of about 33 hours, during which the landing crew will leave the spacecraft twice to set up scientific experiments on the lunar surface and to continue geological explorations. The two earlier Apollo lunar landings were Apollo 11 at Tranquility Base and Apollo 12 at Surveyor 3 crater in the Ocean of Storms.

Apollo experience report: Mission planning for Apollo entry

NASA Technical Reports Server (NTRS)

Graves, C. A.; Harpold, J. C.

1972-01-01

The problems encountered and the experience gained in the entry mission plans, flight software, trajectory-monitoring procedures, and backup trajectory-control techniques of the Apollo Program should provide a foundation upon which future spacecraft programs can be developed. Descriptions of these entry activities are presented. Also, to provide additional background information needed for discussion of the Apollo entry experience, descriptions of the entry targeting for the Apollo 11 mission and the postflight analysis of the Apollo 10 mission are presented.

Neil Armstrong chats with attendees at Apollo 11 anniversary banquet.

NASA Technical Reports Server (NTRS)

1999-01-01

Former Apollo 11 astronaut Neil A. Armstrong talks with a former Apollo team member during an anniversary banquet honoring the Apollo team, the people who made the entire lunar landing program possible. The banquet was held in the Apollo/Saturn V Center, part of the KSC Visitor Complex. This is the 30th anniversary of the Apollo 11 launch and moon landing, July 16 and July 20, 1969. Neil Armstrong was the first man to set foot on the moon.

Controlled formation of intense hot spots in Pd@Ag core-shell nanooctapods for efficient photothermal conversion

NASA Astrophysics Data System (ADS)

Liu, Maochang; Yang, Yang; Li, Naixu; Du, Yuanchang; Song, Dongxing; Ma, Lijing; Wang, Yi; Zheng, Yiqun; Jing, Dengwei

2017-08-01

Plasmonic Ag nanostructures have been of great interest for such applications in cancer therapy and catalysis, etc. However, the relatively week Ag-Ag interaction and spontaneous atom diffusion make it very difficult to generate concaved or branched structures in Ag nanocrystals with sizes less than 100 nm, which has been considered very favorable for plasmonic effects. Herein, by employing a cubic Pd seed and a specific reducing agent to restrict the surface diffusion of Ag atoms, Pd@Ag core-shell nanooctapod structures where Ag atoms can be selectively deposited onto the corner sites of the Pd cubes were obtained. Such selective decoration enables us to precisely control the locations for the hot spot formation during light irradiation. We find that the branched nanooctapod structure shows strong absorption in the visible-light region and generates intense hot spots around the octapod arms of Ag. As such, the photothermal conversion efficiency could be significantly improved by more than 50% with a colloid solution containing only ppm-level nanooctapods compared with pure water. The reported nanostructure is expected to find extensive applications due to its controlled formation of light-induced hot spots at certain points on the crystal surface.

High accuracy step gauge interferometer

NASA Astrophysics Data System (ADS)

Byman, V.; Jaakkola, T.; Palosuo, I.; Lassila, A.

2018-05-01

Step gauges are convenient transfer standards for the calibration of coordinate measuring machines. A novel interferometer for step gauge calibrations implemented at VTT MIKES is described. The four-pass interferometer follows Abbe’s principle and measures the position of the inductive probe attached to a measuring head. The measuring head of the instrument is connected to a balanced boom above the carriage by a piezo translation stage. A key part of the measuring head is an invar structure on which the inductive probe and the corner cubes of the measuring arm of the interferometer are attached. The invar structure can be elevated so that the probe is raised without breaking the laser beam. During probing, the bending of the probe and the interferometer readings are recorded and the measurement face position is extrapolated to zero force. The measurement process is fully automated and the face positions of the steps can be measured up to a length of 2 m. Ambient conditions are measured continuously and the refractive index of air is compensated for. Before measurements the step gauge is aligned with an integrated 2D coordinate measuring system. The expanded uncertainty of step gauge calibration is U=\\sqrt{{{(64 nm)}2}+{{(88× {{10}-9}L)}2}} .

Robust feature detection and local classification for surfaces based on moment analysis.

PubMed

Clarenz, Ulrich; Rumpf, Martin; Telea, Alexandru

2004-01-01

The stable local classification of discrete surfaces with respect to features such as edges and corners or concave and convex regions, respectively, is as quite difficult as well as indispensable for many surface processing applications. Usually, the feature detection is done via a local curvature analysis. If concerned with large triangular and irregular grids, e.g., generated via a marching cube algorithm, the detectors are tedious to treat and a robust classification is hard to achieve. Here, a local classification method on surfaces is presented which avoids the evaluation of discretized curvature quantities. Moreover, it provides an indicator for smoothness of a given discrete surface and comes together with a built-in multiscale. The proposed classification tool is based on local zero and first moments on the discrete surface. The corresponding integral quantities are stable to compute and they give less noisy results compared to discrete curvature quantities. The stencil width for the integration of the moments turns out to be the scale parameter. Prospective surface processing applications are the segmentation on surfaces, surface comparison, and matching and surface modeling. Here, a method for feature preserving fairing of surfaces is discussed to underline the applicability of the presented approach.

GLRS-R 2-colour retroreflector target design and predicted performance

NASA Technical Reports Server (NTRS)

Lund, Glenn

1993-01-01

This paper reports on the retroreflector ground-target design for the GLRS-R spaceborne dual-wavelength laser ranging system. The described passive design flows down from the requirements of high station autonomy, high global FOV (up to 60 degrees zenith angle), little or no multiple pulse returns, and adequate optical cross section for most ranging geometries. The proposed solution makes use of 5 hollow cube-corner retroreflectors of which one points to the zenith and the remaining four are inclined from the vertical at uniform azimuthal spacings. The need for fairly large (is approximately 10 cm) retroreflectors is expected (within turbulence limitations) to generate quite narrow diffraction lobes, thus placing non-trivial requirements on the vectorial accuracy of velocity aberration corrections. A good compromise solution is found by appropriately spoiling just one of the retroreflector dihedral angles from 90 degrees, thus generating two symmetrically oriented diffraction lobes in the return beam. The required spoil angles are found to have little dependence on ground target latitude. Various link budget analyses are presented, showing the influence of such factors as point-ahead optimization, turbulence, ranging angle, atmospheric visibility and ground target thermal deformations.

A study of 35-ghz radar-assisted orbital maneuvering vehicle/space telescope docking

NASA Technical Reports Server (NTRS)

Mcdonald, M. W.

1986-01-01

An experiment was conducted to study the effects of measuring range and range rate information from a complex radar target (a one-third scale model of the Edwin P. Hubble Space Telescope). The radar ranging system was a 35-GHz frequency-modulated continuous wave unit developed in the Communication Systems Branch of the Information and Electronic Systems Laboratory at Marshall Space Flight Cneter. Measurements were made over radar-to-target distances of 5 meters to 15 meters to simulate the close distance realized in the final stages of space vehicle docking. The Space Telescope model target was driven by an antenna positioner through a range of azimuth and elevation (pitch) angles to present a variety of visual aspects of the aft end to the radar. Measurements were obtained with and without a cube corner reflector mounted in the center of the aft end of the model. The results indicate that range and range rate measurements are performed significantly more accurately with the cooperative radar reflector affixed. The results further reveal that range rate (velocity) can be measured accurately enough to support the required soft docking with the Space Telescope.

Laser ranging application to time transfer using geodetic satellite and to other Japanese space programs

NASA Technical Reports Server (NTRS)

Kunimori, Hiroo; Takahashi, Fujinobu; Itabe, Toshikazu; Yamamoto, Atsushi

1993-01-01

Communications Research Laboratory (CRL) has been developing a laser time transfer system using a satellite laser ranging (SLR) system. We propose Japanese geodetic satellite 'AJISAI', launched in 1986 as a target satellite. The surface is covered not only with corner cube reflectors but also with mirrors. The mirrors are originally designed for observation of flushing solar light reflected by the separate mirrors while the satellite is spinning. In the experiment, synchronized laser pulses are transferred via specified mirror from one station to another while the satellite is up on the horizon to both stations. The system is based on the epoch timing ranging system with 40 ps ranging precision, connected together with UTC(CRL). Simulation study indicates that two stations at thousands of km distance from each other can be linked with signal strength of more than 10 photons and the distributed images of laser beam from AJISAI mirrors give many chances for two stations to link each other during a single AJISAI pass. Retro-reflector In Space for Advanced Earth Observation Satellite (ADEOS) and RendDezVous docking mission of Experimental Technology Satellite-7 (ETS-7) are briefly presented.

Gravity and the geoid in the Nepal Himalaya

NASA Technical Reports Server (NTRS)

Bilham, Roger

1992-01-01

Materials within the Himalaya are rising due to convergence between India and Asia. If the rate of erosion is comparable to the rate of uplift, the mean surface elevation will remain constant. Any slight imbalance in these two processes will lead to growth or attrition of the Himalaya. Although buried rocks, minerals and surface control points in the Himalaya are undoubtably rising, the growth or collapse or the Himalaya depends on the erosion rate which is invisible to geodetic measurements. A way to measure erosion rate is to measure the rate of change of gravity in a region of uplift. Essentially gravity should change precisely in accord with a change in elevation of the point in a free air gradient if erosion equals uplift rate. A measurement of absolute gravity was made simultaneously with measurements of GPS height within the Himalaya. Absolute gravity is estimated from the change in velocity per unit distance of a falling corner cube in a vacuum. Time is measured with an atomic clock and the unit distance corresponds to the wavelength of an iodine stabilized laser. An experiment undertaken in the Himalaya in 1991 provide a site description also with a instrument description.

GLRS-R 2-colour retroreflector target design and predicted performance

NASA Astrophysics Data System (ADS)

Lund, Glenn

1993-06-01

This paper reports on the retroreflector ground-target design for the GLRS-R spaceborne dual-wavelength laser ranging system. The described passive design flows down from the requirements of high station autonomy, high global FOV (up to 60 degrees zenith angle), little or no multiple pulse returns, and adequate optical cross section for most ranging geometries. The proposed solution makes use of 5 hollow cube-corner retroreflectors of which one points to the zenith and the remaining four are inclined from the vertical at uniform azimuthal spacings. The need for fairly large (is approximately 10 cm) retroreflectors is expected (within turbulence limitations) to generate quite narrow diffraction lobes, thus placing non-trivial requirements on the vectorial accuracy of velocity aberration corrections. A good compromise solution is found by appropriately spoiling just one of the retroreflector dihedral angles from 90 degrees, thus generating two symmetrically oriented diffraction lobes in the return beam. The required spoil angles are found to have little dependence on ground target latitude. Various link budget analyses are presented, showing the influence of such factors as point-ahead optimization, turbulence, ranging angle, atmospheric visibility and ground target thermal deformations.

Nitrogen removal in moving bed sequencing batch reactor using polyurethane foam cubes of various sizes as carrier materials.

PubMed

Lim, Jun-Wei; Seng, Chye-Eng; Lim, Poh-Eng; Ng, Si-Ling; Sujari, Amat-Ngilmi Ahmad

2011-11-01

The performance of moving bed sequencing batch reactors (MBSBRs) added with 8 % (v/v) of polyurethane (PU) foam cubes as carrier media in nitrogen removal was investigated in treating low COD/N wastewater. The results indicate that MBSBR with 8-mL cubes achieved the highest total nitrogen (TN) removal efficiency of 37% during the aeration period, followed by 31%, 24% and 19 % for MBSBRs with 27-, 64- and 125-mL cubes, respectively. The increased TN removal in MBSBRs was mainly due to simultaneous nitrification and denitrification (SND) process which was verified by batch studies. The relatively lower TN removal in MBSBR with larger PU foam cubes was attributed to the observation that larger PU foam cubes were not fully attached by biomass. Higher concentrations of 8-mL PU foam cubes in batch reactors yielded higher TN removal. Copyright © 2011 Elsevier Ltd. All rights reserved.

Preliminary examination of lunar samples from apollo 14.

PubMed

1971-08-20

The major findings of the preliminary examination of the lunar samples are as follows: 1) The samples from Fra Mauro base may be contrasted with those from Tranquillity base and the Ocean of Storms in that about half the Apollo 11 samples consist of basaltic rocks, and all but three Apollo 12 rocks are basaltic, whereas in the Apollo 14 samples only two rocks of the 33 rocks over 50 grams have basaltic textures. The samples from Fra Mauro base consist largely of fragmental rocks containing clasts of diverse lithologies and histories. Generally the rocks differ modally from earlier lunar samples in that they contain more plagioclase and contain orthopyroxene. 2) The Apollo 14 samples differ chemically from earlier lunar rocks and from their closest meteorite and terrestrial analogs. The lunar material closest in composition is the KREEP component (potassium, rare earth elements, phosphorus), "norite," "mottled gray fragments" (9) from the soil samples (in particular, sample 12033) from the Apollo 12 site, and the dark portion of rock 12013 (10). The Apollo 14 material is richer in titanium, iron, magnesium, and silicon than the Surveyor 7 material, the only lunar highlands material directly analyzed (11). The rocks also differ from the mare basalts, having much lower contents of iron, titanium, manganese, chromium, and scandium and higher contents of silicon, aluminum, zirconium, potassium, uranium, thorium, barium, rubidium, sodium, niobium, lithium, and lanthanum. The ratios of potassium to uranium are lower than those of terrestrial rocks and similar to those of earlier lunar samples. 3) The chemical composition of the soil closely resembles that of the fragmental rocks and the large basaltic rock (sample 14310) except that some elements (potassium, lanthanum, ytterbium, and barium) may be somewhat depleted in the soil with respect to the average rock composition. 4) Rocks display characteristic surface features of lunar material (impact microcraters, rounding) and shock effects similar to those observed in rocks and soil from the Apollo 11 and Apollo 12 missions. The rocks show no evidence of exposure to water, and their content of metallic iron suggests that they, like the Apollo 11 and Apollo 12 material, were formed and have remained in an environment with low oxygen activity. 5) The concentration of solar windimplanted material in the soil is large, as was the case for Apollo 11 and Apollo 12 soil. However, unlike previous fragmental rocks, Apollo 14 fragmental rocks possess solar wind contents ranging from approximately that of the soil to essentially zero, with most rocks investigated falling toward one extreme of this range. A positive correlation appears to exist between the solar wind components, carbon, and (20)Ne, of fragmental rocks and their friability (Fig. 12). 6) Carbon contents lie within the range of carbon contents for Apollo 11 and Apollo 12 samples. 7) Four fragmental rocks show surface exposure times (10 x 10(6) to 20 x 10(6) years) about an order of magnitude less than typical exposure times of Apollo 11 and Apollo 12 rocks. 8) A much broader range of soil mechanics properties was encountered at the Apollo 14 site than has been observed at the Apollo 11, Apollo 12, and Surveyor landing sites. At different points along the traverses of the Apollo 14 mission, lesser cohesion, coarser grain size, and greater resistance to penetration was found than at the Apollo 11 and Apollo 12 sites. These variations are indicative of a very complex, heterogeneous deposit. The soils are more poorly sorted, but the range of grain size is similar to those of the Apollo 11 and Apollo 12 soils. 9) No evidence of biological material has been found in the samples to date.

Apollo 40th Anniversary Morning Television

NASA Image and Video Library

2009-07-19

Apollo astronaut Alan Bean, center, laughs at a comment made by Apollo astronaut Charles Duke, right, as Apollo astronaut Buzz Aldrin, left, looks on during a live television interview on Monday, July 20, 2009, at NASA Headquarters in Washington. Monday marked the 40th Anniversary of the historic landing of Apollo 11 on the Moon. Photo Credit: (NASA/Paul E. Alers)

Astronaut Alan Bean deploys ALSEP during first Apollo 12 EVA on moon

NASA Technical Reports Server (NTRS)

1969-01-01

Astronaut Alan L. Bean, Apollo 12 lunar module pilot, deploys components of the Apollo Lunar Surface Experiments Package (ALSEP) during the first Apollo 12 extravehicular activity (EVA) on the moon. The photo was made by Astronaut Charles Conrad Jr., Apollo 12 commander, using a 70mm handheld Haselblad camera modified for lunar surface usage.

JPL-20180416-INSIGHf-0001-Marco Media Reel 1

NASA Image and Video Library

2018-04-16

Mars Cube One is a Mars flyby mission consisting of two CubeSats that is planned for launch alongside NASA's InSight Mars lander mission. This will be the first interplanetary CubeSat mission. If successful, the CubeSats will relay entry, descent, and landing (EDL) data to Earth during InSight's landing.

Massively Clustered CubeSats NCPS Demo Mission

NASA Technical Reports Server (NTRS)

Robertson, Glen A.; Young, David; Kim, Tony; Houts, Mike

2013-01-01

Technologies under development for the proposed Nuclear Cryogenic Propulsion Stage (NCPS) will require an un-crewed demonstration mission before they can be flight qualified over distances and time frames representative of a crewed Mars mission. In this paper, we describe a Massively Clustered CubeSats platform, possibly comprising hundreds of CubeSats, as the main payload of the NCPS demo mission. This platform would enable a mechanism for cost savings for the demo mission through shared support between NASA and other government agencies as well as leveraged commercial aerospace and academic community involvement. We believe a Massively Clustered CubeSats platform should be an obvious first choice for the NCPS demo mission when one considers that cost and risk of the payload can be spread across many CubeSat customers and that the NCPS demo mission can capitalize on using CubeSats developed by others for its own instrumentation needs. Moreover, a demo mission of the NCPS offers an unprecedented opportunity to invigorate the public on a global scale through direct individual participation coordinated through a web-based collaboration engine. The platform we describe would be capable of delivering CubeSats at various locations along a trajectory toward the primary mission destination, in this case Mars, permitting a variety of potential CubeSat-specific missions. Cameras on various CubeSats can also be used to provide multiple views of the space environment and the NCPS vehicle for video monitoring as well as allow the public to "ride along" as virtual passengers on the mission. This collaborative approach could even initiate a brand new Science, Technology, Engineering and Math (STEM) program for launching student developed CubeSat payloads beyond Low Earth Orbit (LEO) on future deep space technology qualification missions. Keywords: Nuclear Propulsion, NCPS, SLS, Mars, CubeSat.

Pesticide Manufacturers, Formulators, Producers, and Registrants

Science.gov Websites

International Apollo Industries, Inc. (see Apollo Technologies, Inc.) Apollo Technologies, Inc. Applied Products, Inc.) SPECKoZ, Inc. Spectrum Brands (aka Spectrum Group) Speer Products, Inc. (see Apollo

OFFICIAL EMBLEM - APOLLO-SOYUZ TEST PROJECT (ASTP)

NASA Image and Video Library

1974-03-01

S74-17843 (March 1974) --- This is the official emblem of the Apollo-Soyuz Test Project chosen by NASA and the Soviet Academy of Sciences. The joint U.S.-USSR space mission is scheduled to be flown in July 1975. Of circular design, the emblem has the words Apollo in English and Soyuz in Russian around a center disc which depicts the two spacecraft docked together in Earth orbit. The Apollo-Soyuz Test Project will be carried out by a Soviet Soyuz spacecraft and a U.S. Apollo spacecraft which will rendezvous and dock in orbit. Soyuz and Apollo will remain docked for as long as two days in which period, the three Apollo astronauts will enter Soyuz and the two Soyuz cosmonauts will visit Apollo via a docking module. The Russian word "soyuz" means "union" in English.

NASA Near Earth Network (NEN) Support for Lunar and L1/L2 CubeSats

NASA Technical Reports Server (NTRS)

Schaire, Scott; Altunc, Serhat; Wong, Yen; Shelton, Marta; Celeste, Peter; Anderson, Michael; Perrotto, Trish

2017-01-01

The NASA Near Earth Network (NEN) consists of globally distributed tracking stations, including NASA, commercial, and partner ground stations, that are strategically located to maximize the coverage provided to a variety of orbital and suborbital missions, including those in LEO, GEO, HEO, lunar and L1/L2 orbits. The NENs future mission set includes and will continue to include CubeSat missions. The majority of the CubeSat missions destined to fly on EM-1, launching in late 2018, many in a lunar orbit, will communicate with ground based stations via X-band and will utilize the NASA Jet Propulsion Laboratory (JPL) developed IRIS radio. The NEN recognizes the important role CubeSats are beginning to play in carrying out NASAs mission and is therefore investigating the modifications needed to provide IRIS radio compatibility. With modification, the NEN could potentially expand support to the EM-1 lunar CubeSats.The NEN could begin providing significant coverage to lunar CubeSat missions utilizing three to four of the NENs mid-latitude sites. This coverage would supplement coverage provided by the JPL Deep Space Network (DSN). The NEN, with smaller apertures than DSN, provides the benefit of a larger beamwidth that could be beneficial in the event of uncertain ephemeris data. In order to realize these benefits the NEN would need to upgrade stations targeted based on coverage ability and current configuration/ease of upgrade, to ensure compatibility with the IRIS radio. In addition, the NEN is working with CubeSat radio developers to ensure NEN compatibility with alternative CubeSat radios for Lunar and L1/L2 CubeSats. The NEN has provided NEN compatibility requirements to several radio developers who are developing radios that offer lower cost and, in some cases, more capabilities with fewer constraints. The NEN is ready to begin supporting CubeSat missions. The NEN is considering network upgrades to broaden the types of CubeSat missions that can be supported and is supporting both the CubeSat community and radio developers to ensure future CubeSat missions have multiple options when choosing a network for their communications support.

CubeSats for Astrophysics: The Current Perspective

NASA Astrophysics Data System (ADS)

Ardila, David R.; Shkolnik, Evgenya; Gorjian, Varoujan

2017-01-01

Cubesats are small satellites built to multiples of 1U (1000 cm3). The 2016 NRC Report “Achieving Science with CubeSats” indicates that between 2013 and 2018 NASA and NSF sponsored 104 CubeSats. Of those, only one is devoted to astrophysics: HaloSat (PI: P. Kaaret), a 6U CubeSat with an X-ray payload to study the hot galactic halo.Despite this paucity of missions, CubeSats have a lot of potential for astrophysics. To assess the science landscape that a CubeSat astrophysics mission may occupy, we consider the following parameters:1-Wavelength: CubeSats are not competitive in the visible, unless the application (e.g. high precision photometry) is difficult to do from the ground. Thermal IR science is limited by the lack of low-power miniaturized cryocoolers and by the large number of infrared astrophysical missions launched or planned. In the UV, advances in δ-doping processes result in larger sensitivity with smaller apertures. Commercial X-ray detectors also allow for competitive science.2-Survey vs. Pointed observations: All-sky surveys have been done at most wavelengths from X-rays to Far-IR and CubeSats will not be able to compete in sensitivity with them. CubeSat science should then center on specific objects or object classes. Due to poor attitude control, unresolved photometry is scientifically more promising that extended imaging.3-Single-epoch vs. time domain: CubeSat apertures cannot compete in sensitivity with big satellites when doing single-epoch observations. However, time-domain astrophysics is an area in which CubeSats can provide very valuable science return.Technologically, CubeSat astrophysics is limited by:1-Lack of large apertures: The largest aperture CubeSat launched is ~10 cm, although deployable apertures as large as 20 cm could be fitted to 6U buses.2-Poor attitude control: State-of-the-art systems have demonstrated jitter of ~10” on timescales of seconds. Jitter imposes limits on image quality and, coupled with detector errors, limits the S/N.Other technology limitations include the lack of high-bandwidth communication and low-power miniaturized cryocoolers. However, even with today’s technological limitations, astrophysics applications of CubeSats are only limited by our imagination.

Near Earth Network (NEN) CubeSat Communications

NASA Technical Reports Server (NTRS)

Schaire, Scott

2017-01-01

The NASA Near Earth Network (NEN) consists of globally distributed tracking stations, including NASA, commercial, and partner ground stations, that are strategically located to maximize the coverage provided to a variety of orbital and suborbital missions, including those in LEO (Low Earth Orbit), GEO (Geosynchronous Earth Orbit), HEO (Highly Elliptical Orbit), lunar and L1-L2 orbits. The NEN's future mission set includes and will continue to include CubeSat missions. The first NEN-supported CubeSat mission will be the Cubesat Proximity Operations Demonstration (CPOD) launching into LEO in 2017. The majority of the CubeSat missions destined to fly on EM-1, launching in late 2018, many in a lunar orbit, will communicate with ground-based stations via X-band and will utilize the NASA Jet Propulsion Laboratory (JPL)-developed IRIS (Satellite Communication for Air Traffic Management) radio. The NEN recognizes the important role CubeSats are beginning to play in carrying out NASAs mission and is therefore investigating the modifications needed to provide IRIS radio compatibility. With modification, the NEN could potentially expand support to the EM-1 (Exploration Mission-1) lunar CubeSats. The NEN could begin providing significant coverage to lunar CubeSat missions utilizing three to four of the NEN's mid-latitude sites. This coverage would supplement coverage provided by the JPL Deep Space Network (DSN). The NEN, with smaller apertures than DSN, provides the benefit of a larger beamwidth that could be beneficial in the event of uncertain ephemeris data. In order to realize these benefits the NEN would need to upgrade stations targeted based on coverage ability and current configuration ease of upgrade, to ensure compatibility with the IRIS radio. In addition, the NEN is working with CubeSat radio developers to ensure NEN compatibility with alternative CubeSat radios for Lunar and L1-L2 CubeSats. The NEN has provided NEN compatibility requirements to several radio developers who are developing radios that offer lower cost and, in some cases, more capabilities with fewer constraints. The NEN is ready to begin supporting CubeSat missions. The NEN is considering network upgrades to broaden the types of CubeSat missions that can be supported and is supporting both the CubeSat community and radio developers to ensure future CubeSat missions have multiple options when choosing a network for their communications support.

NASA Near Earth Network (NEN) Support for Lunar and L1/L2 CubeSats

NASA Technical Reports Server (NTRS)

Schaire, Scott H.

2017-01-01

The NASA Near Earth Network (NEN) consists of globally distributed tracking stations, including NASA, commercial, and partner ground stations, that are strategically located to maximize the coverage provided to a variety of orbital and suborbital missions, including those in LEO, GEO, HEO, lunar and L1/L2 orbits. The NENs future mission set includes and will continue to include CubeSat missions. The first NEN supported CubeSat mission will be the Cubesat Proximity Operations Demonstration (CPOD) launching into low earth orbit (LEO) in early 2017. The majority of the CubeSat missions destined to fly on EM-1, launching in late 2018, many in a lunar orbit, will communicate with ground based stations via X-band and will utilize the NASA Jet Propulsion Laboratory (JPL) developed IRIS radio. The NEN recognizes the important role CubeSats are beginning to play in carrying out NASAs mission and is therefore investigating the modifications needed to provide IRIS radio compatibility. With modification, the NEN could potentially expand support to the EM-1 lunar CubeSats. The NEN could begin providing significant coverage to lunar CubeSat missions utilizing three to four of the NENs mid-latitude sites. This coverage would supplement coverage provided by the JPL Deep Space Network (DSN). The NEN, with smaller apertures than DSN, provides the benefit of a larger beamwidth that could be beneficial in the event of uncertain ephemeris data. In order to realize these benefits the NEN would need to upgrade stations targeted based on coverage ability and current configurationease of upgrade, to ensure compatibility with the IRIS radio.In addition, the NEN is working with CubeSat radio developers to ensure NEN compatibility with alternative CubeSat radios for Lunar and L1/L2 CubeSats. The NEN has provided NEN compatibility requirements to several radio developers who are developing radios that offer lower cost and, in some cases, more capabilities with fewer constraints. The NEN is ready to begin supporting CubeSat missions. The NEN is considering network upgrades to broaden the types of CubeSat missions that can be supported and is supporting both the CubeSat community and radio developers to ensure future CubeSat missions have multiple options when choosing a network for their communications support.

Privacy-preserving data cube for electronic medical records: An experimental evaluation.

PubMed

Kim, Soohyung; Lee, Hyukki; Chung, Yon Dohn

2017-01-01

The aim of this study is to evaluate the effectiveness and efficiency of privacy-preserving data cubes of electronic medical records (EMRs). An EMR data cube is a complex of EMR statistics that are summarized or aggregated by all possible combinations of attributes. Data cubes are widely utilized for efficient big data analysis and also have great potential for EMR analysis. For safe data analysis without privacy breaches, we must consider the privacy preservation characteristics of the EMR data cube. In this paper, we introduce a design for a privacy-preserving EMR data cube and the anonymization methods needed to achieve data privacy. We further focus on changes in efficiency and effectiveness that are caused by the anonymization process for privacy preservation. Thus, we experimentally evaluate various types of privacy-preserving EMR data cubes using several practical metrics and discuss the applicability of each anonymization method with consideration for the EMR analysis environment. We construct privacy-preserving EMR data cubes from anonymized EMR datasets. A real EMR dataset and demographic dataset are used for the evaluation. There are a large number of anonymization methods to preserve EMR privacy, and the methods are classified into three categories (i.e., global generalization, local generalization, and bucketization) by anonymization rules. According to this classification, three types of privacy-preserving EMR data cubes were constructed for the evaluation. We perform a comparative analysis by measuring the data size, cell overlap, and information loss of the EMR data cubes. Global generalization considerably reduced the size of the EMR data cube and did not cause the data cube cells to overlap, but incurred a large amount of information loss. Local generalization maintained the data size and generated only moderate information loss, but there were cell overlaps that could decrease the search performance. Bucketization did not cause cells to overlap and generated little information loss; however, the method considerably inflated the size of the EMR data cubes. The utility of anonymized EMR data cubes varies widely according to the anonymization method, and the applicability of the anonymization method depends on the features of the EMR analysis environment. The findings help to adopt the optimal anonymization method considering the EMR analysis environment and goal of the EMR analysis. Copyright © 2016 Elsevier Ireland Ltd. All rights reserved.

CubeSat Integration into the Space Situational Awareness Architecture

NASA Astrophysics Data System (ADS)

Morris, K.; Wolfson, M.; Brown, J.

2013-09-01

Lockheed Martin Space Systems Company has recently been involved in developing GEO Space Situational Awareness architectures, which allows insights into how cubesats can augment the current national systems. One hole that was identified in the current architecture is the need for timelier metric track observations to aid in the chain of custody. Obtaining observations of objects at GEO can be supported by CubeSats. These types of small satellites are increasing being built and flown by government agencies like NASA and SMDC. CubeSats are generally mass and power constrained allowing for only small payloads that cannot typically mimic traditional flight capability. CubeSats do not have a high reliability and care must be taken when choosing mission orbits to prevent creating more debris. However, due to the low costs, short development timelines, and available hardware, CubeSats can supply very valuable benefits to these complex missions, affordably. For example, utilizing CubeSats for advanced focal plane demonstrations to support technology insertion into the next generation situational awareness sensors can help to lower risks before the complex sensors are developed. CubeSats can augment the planned ground and space based assets by creating larger constellations with more access to areas of interest. To aid in maintaining custody of objects, a CubeSat constellation at 500 km above GEO would provide increased point of light tracking that can augment the ground SSA assets. Key features of the Cubesat include a small visible camera looking along the GEO belt, a small propulsion system that allows phasing between CubeSats, and an image processor to reduce the data sent to the ground. An elegant communications network will also be used to provide commands to and data from multiple CubeSats. Additional CubeSats can be deployed on GSO launches or through ride shares to GEO, replenishing or adding to the constellation with each launch. Each CubeSat would take images of the GEO belt, process out the stars, and then downlink the data to the ground. This data can then be combined with the existing metric track data to enhance the coverage and timeliness. With the current capability of CubeSats and their payloads, along with the launch constraints, the near term focus is to integrate into existing architectures by reducing technology risks, understanding unique phenomenology, and augment mission collection capability. Understanding the near term benefits of utilizing CubeSats will better inform the SSA mission developers how to integrate CubeSats into the next generation of architectures from the start.

Detail, corner pilaster remnant, gable return on facade, Our Corner ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Detail, corner pilaster remnant, gable return on facade, Our Corner Saloon, view to northeast (210mm lens with electronic flash fill) - Our Corner Saloon, 301 First Street, Eureka, Humboldt County, CA

Last chance at Taurus-Littrow

NASA Technical Reports Server (NTRS)

Wilhelms, D. E.

1992-01-01

By the fall of 1971, it was known that only two more Apollos would land on the Moon. Most geoscientists agreed that both should concentrate on the previously neglected terrae (highlands). In June 1991, the Apollo Site Selection Board (ASSB) had chosen Descartes as the site of the Apollo 16 terra landing, scheduled for April 1972. Therefore, we had to assess how many pre-Apollo objectives the first four landings had met, how many Apollo 16 was likely to meet, and how to meet the remaining ones with Apollo 17. Geologists convened at Caltech in November 1971 and formulated a list of major lunar problems. An edited version of the list is presented, and how the remaining problems influenced the Apollo 16 and 17 landing site selection process is discussed with particular emphasis on the selection of Taurus-Littrow as the landing site for Apollo 17. Apollo 17 returned a fine collection from the massifs, bright mantle, Sculptured Hills, subfloor basalt, and dark mantle of Taurus-Littrow. They answered many of 1971's questions, showed others to have been wrongly asked, and left others for us to ponder still today. A brief discussion of the problems solved and the questions raised by the Apollo Program are presented.

Development of Novel Integrated Antennas for CubeSats

NASA Technical Reports Server (NTRS)

Jackson, David; Fink, Patrick W.; Martinez, Andres; Petro, Andrew

2015-01-01

The Development of Novel Integrated Antennas for CubeSats project is directed at the development of novel antennas for CubeSats to replace the bulky and obtrusive antennas (e.g., whip antennas) that are typically used. The integrated antennas will not require mechanical deployment and thus will allow future CubeSats to avoid potential mechanical problems and therefore improve mission reliability. Furthermore, the integrated antennas will have improved functionality and performance, such as circular polarization for improved link performance, compared with the conventional antennas currently used on CubeSats.

Apollo experience report: Guidance and control systems. Mission control programmer for unmanned missions AS-202, Apollo 4, and Apollo 6

NASA Technical Reports Server (NTRS)

Holloway, G. F.

1975-01-01

An unmanned test flight program required to evaluate the command module heat shield and the structural integrity of the command and service module/Saturn launch vehicle is described. The mission control programer was developed to provide the unmanned interface between the guidance and navigation computer and the other spacecraft systems for mission event sequencing and real-time ground control during missions AS-202, Apollo 4, and Apollo 6. The development of this unmanned programer is traced from the initial concept through the flight test phase. Detailed discussions of hardware development problems are given with the resulting solutions. The mission control programer functioned correctly without any flight anomalies for all missions. The Apollo 4 mission control programer was reused for the Apollo 6 flight, thus being one of the first subsystems to be reflown on an Apollo space flight.

Apollo 8 Astronaut Anders Suits Up For Countdown Demonstration Test

NASA Technical Reports Server (NTRS)

1968-01-01

Apollo 8 astronaut William Anders, Lunar Module (LM) pilot, is suited up for the Apollo 8 mission countdown demonstration test. The first manned Apollo mission launched aboard the Saturn V and first manned Apollo craft to enter lunar orbit, the SA-503, Apollo 8 mission lift off occurred on December 21, 1968 and returned safely to Earth on December 27, 1968. Aboard were Anders and fellow astronauts James Lovell, Command Module (CM) pilot; and Frank Borman, commander. The mission achieved operational experience and tested the Apollo command module systems, including communications, tracking, and life-support, in cis-lunar space and lunar orbit, and allowed evaluation of crew performance on a lunar orbiting mission. The crew photographed the lunar surface, both far side and near side, obtaining information on topography and landmarks as well as other scientific information necessary for future Apollo landings. All systems operated within allowable parameters and all objectives of the mission were achieved.

[327] Biomedical Research Deferred in the Aftermath of the Apollo Fire: Impact to Progress in Human Spaceflight

NASA Technical Reports Server (NTRS)

Charles, John B.

2017-01-01

Before Apollo fire, early Apollo missions were expected to continue pattern established in Gemini program of accommodating significant scientific and biological experimentation, including human biomedical studies, during flights. Apollo1 and Apollo2, both 2-week engineering test flights, were to carry almost as many biomedical studies as Gemini 7, a 2-week medical test mission.

Launch of the Apollo 17 lunar landing mission

NASA Image and Video Library

1972-12-07

S72-55482 (7 Dec. 1972) --- The huge, 363-feet tall Apollo 17 (Spacecraft 114/Lunar Module 12/Saturn 512) space vehicle is launched from Pad A., Launch Complex 39, Kennedy Space Center (KSC), Florida, at 12:33 a.m. (EST), Dec. 7, 1972. Apollo 17, the final lunar landing mission in NASA's Apollo program, was the first nighttime liftoff of the Saturn V launch vehicle. Aboard the Apollo 17 spacecraft were astronaut Eugene A. Cernan, commander; astronaut Ronald E. Evans, command module pilot; and scientist-astronaut Harrison H. Schmitt, lunar module pilot. Flame from the five F-1 engines of the Apollo/Saturn first (S-1C) stage illuminates the nighttime scene. A two-hour and 40-minute hold delayed the Apollo 17 launching.

Launch of the Apollo 17 lunar landing mission

NASA Image and Video Library

1972-09-07

S72-55070 (7 Dec. 1972) --- The huge, 363-feet tall Apollo 17 (Spacecraft 114/Lunar Module 12/Saturn 512) space vehicle is launched from Pad A, Launch Complex 39, Kennedy Space Center (KSC), Florida, at 12:33 a.m. (EST), Dec. 7, 1972. Apollo 17, the final lunar landing mission in NASA's Apollo program, was the first nighttime liftoff of the Saturn V launch vehicle. Aboard the Apollo 17 spacecraft were astronaut Eugene A. Cernan, commander; astronaut Ronald E. Evans, command module pilot; and scientist-astronaut Harrison H. Schmitt, lunar module pilot. Flame from the five F-1 engines of the Apollo/Saturn first (S-1C) stage illuminates the nighttime scene. A two-hour and 40-minute hold delayed the Apollo 17 launching.

EarthCube - A Community-led, Interdisciplinary Collaboration for Geoscience Cyberinfrastructure

NASA Astrophysics Data System (ADS)

Dick, Cindy; Allison, Lee

2016-04-01

The US NSF EarthCube Test Enterprise Governance Project completed its initial two-year long process to engage the community and test a demonstration governing organization with the goal of facilitating a community-led process on designing and developing a geoscience cyberinfrastructure. Conclusions are that EarthCube is viable, has engaged a broad spectrum of end-users and contributors, and has begun to foster a sense of urgency around the importance of open and shared data. Levels of trust among participants are growing. At the same time, the active participants in EarthCube represent a very small sub-set of the larger population of geoscientists. Results from Stage I of this project have impacted NSF decisions on the direction of the EarthCube program. The overall tone of EarthCube events has had a constructive, problem-solving orientation. The technical and organizational elements of EarthCube are poised to support a functional infrastructure for the geosciences community. The process for establishing shared technological standards has notable progress but there is a continuing need to expand technological and cultural alignment. Increasing emphasis is being given to the interdependencies among EarthCube funded projects. The newly developed EarthCube Technology Plan highlights important progress in this area by five working groups focusing on: 1. Use cases; 2. Funded project gap analysis; 3. Testbed development; 4. Standards; and 5. Architecture. The EarthCube governance implementing processes to facilitate community convergence on a system architecture, which is expected to emerge naturally from a set of data principles, user requirements, science drivers, technology capabilities, and domain needs.

Linking Humans to Data: Designing an Enterprise Architecture for EarthCube

NASA Astrophysics Data System (ADS)

Xu, C.; Yang, C.; Meyer, C. B.

2013-12-01

National Science Foundation (NSF)'s EarthCube is a strategic initiative towards a grand enterprise that holistically incorporates different geoscience research domains. The EarthCube as envisioned by NSF is a community-guided cyberinfrastructure (NSF 2011). The design of EarthCube enterprise architecture (EA) offers a vision to harmonize processes between the operations of EarthCube and its information technology foundation, the geospatial cyberinfrastructure. (Yang et al. 2010). We envision these processes as linking humans to data. We report here on fundamental ideas that would ultimately materialize as a conceptual design of EarthCube EA. EarthCube can be viewed as a meta-science that seeks to advance knowledge of the Earth through cross-disciplinary connections made using conventional domain-based earth science research. In order to build capacity that enables crossing disciplinary chasms, a key step would be to identify the cornerstones of the envisioned enterprise architecture. Human and data inputs are the two key factors to the success of EarthCube (NSF 2011), based upon which three hypotheses have been made: 1) cross disciplinary collaboration has to be achieved through data sharing; 2) disciplinary differences need to be articulated and captured in both computer and human understandable formats; 3) human intervention is crucial for crossing the disciplinary chasms. We have selected the Federal Enterprise Architecture Framework (FEAF, CIO Council 2013) as the baseline for the envisioned EarthCube EA, noting that the FEAF's deficiencies can be improved upon with inputs from three other popular EA frameworks. This presentation reports the latest on the conceptual design of an enterprise architecture in support of EarthCube.

Apollo 40th Anniversary Press Conference

NASA Image and Video Library

2009-07-19

Astronaut James Lovell (Apollo 8 Apollo 13) gestures during the 40th anniversary of the Apollo 11 mission and the walk on the moon press conference, Monday, July 20, 2009, at NASA Headquarters in Washington. Photo Credit: (NASA/Paul E. Alers)

Automatic Modelling of Rubble Mound Breakwaters from LIDAR Data

NASA Astrophysics Data System (ADS)

Bueno, M.; Díaz-Vilariño, L.; González-Jorge, H.; Martínez-Sánchez, J.; Arias, P.

2015-08-01

Rubble mound breakwaters maintenance is critical to the protection of beaches and ports. LiDAR systems provide accurate point clouds from the emerged part of the structure that can be modelled to make it more useful and easy to handle. This work introduces a methodology for the automatic modelling of breakwaters with armour units of cube shape. The algorithm is divided in three main steps: normal vector computation, plane segmentation, and cube reconstruction. Plane segmentation uses the normal orientation of the points and the edge length of the cube. Cube reconstruction uses the intersection of three perpendicular planes and the edge length. Three point clouds cropped from the main point cloud of the structure are used for the tests. The number of cubes detected is around 56 % for two of the point clouds and 32 % for the third one over the total physical cubes. Accuracy assessment is done by comparison with manually drawn cubes calculating the differences between the vertexes. It ranges between 6.4 cm and 15 cm. Computing time ranges between 578.5 s and 8018.2 s. The computing time increases with the number of cubes and the requirements of collision detection.

An evaluation of space time cube representation of spatiotemporal patterns.

PubMed

Kristensson, Per Ola; Dahlbäck, Nils; Anundi, Daniel; Björnstad, Marius; Gillberg, Hanna; Haraldsson, Jonas; Mårtensson, Ingrid; Nordvall, Mathias; Ståhl, Josefine

2009-01-01

Space time cube representation is an information visualization technique where spatiotemporal data points are mapped into a cube. Information visualization researchers have previously argued that space time cube representation is beneficial in revealing complex spatiotemporal patterns in a data set to users. The argument is based on the fact that both time and spatial information are displayed simultaneously to users, an effect difficult to achieve in other representations. However, to our knowledge the actual usefulness of space time cube representation in conveying complex spatiotemporal patterns to users has not been empirically validated. To fill this gap, we report on a between-subjects experiment comparing novice users' error rates and response times when answering a set of questions using either space time cube or a baseline 2D representation. For some simple questions, the error rates were lower when using the baseline representation. For complex questions where the participants needed an overall understanding of the spatiotemporal structure of the data set, the space time cube representation resulted in on average twice as fast response times with no difference in error rates compared to the baseline. These results provide an empirical foundation for the hypothesis that space time cube representation benefits users analyzing complex spatiotemporal patterns.

Reply to ‘No correction for the light propagation within the cube: Comment on Relativistic theory of the falling cube gravimeter’

NASA Astrophysics Data System (ADS)

Ashby, Neil

2018-06-01

The comment (Nagornyi 2018 Metrologia) claims that, notwithstanding the conclusions stated in the paper Relativistic theory of the falling cube gravimeter (Ashby 2008 Metrologia 55 1–10), there is no need to consider the dimensions or refractive index of the cube in fitting data from falling cube absolute gravimeters; additional questions are raised about matching quartic polynomials while determining only three quantities. The comment also suggests errors were made in Ashby (2008 Metrologia 55 1–10) while implementing the fitting routines on which the conclusions were based. The main contention of the comment is shown to be invalid because retarded time was not properly used in constructing a fictitious cube position. Such a fictitious position, fixed relative to the falling cube, is derived and shown to be dependent on cube dimensions and refractive index. An example is given showing how in the present context, polynomials of fourth order can be effectively matched by determining only three quantities, and a new compact characterization of the interference signal arriving at the detector is given. Work of the U.S. government, not subject to copyright.

Survey on the implementation and reliability of CubeSat electrical bus interfaces

NASA Astrophysics Data System (ADS)

Bouwmeester, Jasper; Langer, Martin; Gill, Eberhard

2017-06-01

This paper provides results and conclusions on a survey on the implementation and reliability aspects of CubeSat bus interfaces, with an emphasis on the data bus and power distribution. It provides recommendations for a future CubeSat bus standard. The survey is based on a literature study and a questionnaire representing 60 launched CubeSats and 44 to be launched CubeSats. It is found that the bus interfaces are not the main driver for mission failures. However, it is concluded that the Inter Integrated Circuit (I2C) data bus, as implemented in a great majority of the CubeSats, caused some catastrophic satellite failures and a vast amount of bus lockups. The power distribution may lead to catastrophic failures if the power lines are not protected against overcurrent. A connector and wiring standard widely implemented in CubeSats is based on the PC/104 standard. Most participants find the 104 pin connector of this standard too large. For a future CubeSat bus interface standard, it is recommended to implement a reliable data bus, a power distribution with overcurrent protection and a wiring harness with smaller connectors compared with PC/104.

Crew Training - Apollo X (Apollo Mission Simulator [AMS]) - KSC

NASA Image and Video Library

1969-04-05

S69-32788 (3 April 1969) --- Astronaut John W. Young, Apollo 10 prime crew command module pilot, participates in simulation activity in the Apollo Mission Simulator at the Kennedy Space Center during preparations for his scheduled lunar orbit mission.

CREW TRAINING - APOLLO X (APOLLO MISSION SIMULATOR [AMS]) - KSC

NASA Image and Video Library

1969-04-05

S69-32789 (3 April 1969) --- Astronaut John W. Young, Apollo 10 prime crew command module pilot, participates in simulation activity in the Apollo Mission Simulator at the Kennedy Space Center during preparations for his scheduled lunar orbit mission.

Apollo A-7L Spacesuit Tests and Certification, and Apollo 7 Through 14 Missions Experience

NASA Technical Reports Server (NTRS)

McBarron, James W., II

2015-01-01

As a result of his 50 years of experience and research, Jim McBarron shared his significant knowledge about Apollo A-7L spacesuit certification testing and Apollo 7 through 14 missions' spacesuit details.

Apollo 1 Lessons Learned Show

NASA Image and Video Library

2017-01-27

Mike Ciannilli, at left, the Apollo, Challenger, Columbia Lessons Learned Program manager, presents a certificate to John Tribe, retired, Apollo 1 Reaction and Control System lead engineer, during the Apollo 1 Lessons Learned presentation in the Training Auditorium at NASA's Kennedy Space Center in Florida. The theme of the program was "To there and Back Again." The event helped pay tribute to the Apollo 1 crew, Gus Grissom, Ed White II, and Roger Chaffee.

KSC-2011-1308

NASA Image and Video Library

2011-01-29

CAPE CANAVERAL, Fla. -- Lunar module pilot of Apollo 10 and commander of Apollo 17 Gene Cernan talks to attendees of the Apollo 14 Anniversary Soirée at the Kennedy Space Center Visitor Complex's Saturn V Center. The celebration was hosted by the Astronaut Scholarship Foundation. Apollo 14 landed on the lunar surface 40 years ago on Feb. 5, 1971. Cernan was the backup commander for the Apollo 14 mission. Photo credit: NASA/Kim Shiflett

Apollo 1 Lessons Learned Show

NASA Image and Video Library

2017-01-27

Mike Ciannilli, the Apollo, Challenger, Columbia Lessons Learned program manager, at left, presents a certificate to Ernie Reyes, retired, former Apollo 1 senior operations manager, during the Apollo 1 Lessons Learned presentation in the Training Auditorium at NASA's Kennedy Space Center in Florida. The theme of the program was "To there and Back Again." The event helped pay tribute to the Apollo 1 crew, Gus Grissom, Ed White II, and Roger Chaffee.

Saturn Apollo Program

NASA Image and Video Library

1968-10-01

AS-205, the fifth Saturn IB launch vehicle developed by the Marshall Space Flight Center (MSFC), lifts off from Cape Canaveral, Florida on the first marned Apollo-Saturn mission, Apollo 7. Primary mission objectives included demonstration of the Apollo crew (Walter Schirra, Don Eisele, and Walter Cunningham) capabilities and the Command/Service Module rendezvous capability. In all, nine Saturn IB flights were made, ending with the Apollo-Soyuz Test Project in July 1975.

Apollo Spacesuit Modifications for the Apollo-Soyuz Test Project (ASTP) Spacesuit

NASA Technical Reports Server (NTRS)

McBarron, James W., II

2015-01-01

With over 50 years of experience with NASA spacesuit development and operations, as well as for early U.S. Air Force pressure suits, Jim McBarron shared his significant knowledge about modifications to the Apollo spacesuit for use in the Apollo-Soyuz Test Project (ASTP). This included requirements and design changes implemented to establish the ASTP spacesuit design baseline. Additionally, he identified Apollo spacesuit contact details including quantity of spacesuits delivered to support the Apollo and Skylab Programs, and the ASTP. He concluded by identifying a summary of noteworthy lessons learned with recommendations for future spacesuit development.

KSC-2012-1845

NASA Image and Video Library

2012-02-17

Apollo Capsule/Lunar Lander: The goal of Project Apollo was to land man on the moon and return them safely to the Earth. The Apollo spacecraft consisted of a command module serving as the crew’s quarters and flight control section and the lunar module, carrying two crewmembers to the surface of the moon. The first Apollo spacecraft to land on the moon was Apollo 11 on July 20, 1969. The program concluded with Apollo 17 in December 1972 after putting 27 men into lunar orbit and 12 of them on the surface of the moon. Poster designed by Kennedy Space Center Graphics Department/Greg Lee. Credit: NASA

Artist's concept of oxygen tanks of the Apollo 14 spacecraft

NASA Image and Video Library

1971-01-12

S71-16745 (January 1971) --- An artist's concept illustrating a cutaway view of one of the three oxygen tanks of the Apollo 14 spacecraft. This is the new Apollo oxygen tank design, developed since the Apollo 13 oxygen tank explosion. Apollo 14 has three oxygen tanks redesigned to eliminate ignition sources, minimize the use of combustible materials, and simplify the fabrication process. The third tank has been added to the Apollo 14 Service Module, located in the SM's sector one, apart from the pair of oxygen tanks in sector four. Arrows point out various features of the oxygen tank.

GreenCube and RocketCube: Low-Resource Sensorcraft for Atmospheric and Ionospheric Science

NASA Astrophysics Data System (ADS)

Bracikowski, P. J.; Lynch, K. A.; Slagle, A. K.; Fagin, M. H.; Currey, S. R.; Siddiqui, M. U.

2009-12-01

In situ atmospheric and ionospheric studies benefit greatly from the ability to separate variations in space from variations in time. Arrays of many probes are a method of doing this, but because of the technical character and expense of developing large arrays, so far probe arrays have been the domain of well-funded science missions. CubeSats and low-resource craft (``Picosats") are an avenue for bringing array-based studies of the atmosphere and ionosphere into the mainstream. The Lynch Rocket Lab at Dartmouth College is attempting to develop the instruments, experience, and heritage to implement arrays of many low-resource sensorcraft while doing worthwhile science in the development process. We are working on two CubeSat projects to reach this goal: GreenCube for atmospheric studies and RocketCube for ionospheric studies. GreenCube is an undergraduate student-directed high-altitude balloon-borne 3U CubeSat. GreenCube I was a bus, telemetry, and mechanical system development project. GreenCube I flew in the fall of 2008. The flight was successfully recovered and tracked over the 97km range and through the 29km altitude rise. GreenCube I carried six thermal housekeeping sensors, a GPS, a magnetometer, and a HAM radio telemetry system with a reporting rate of once every 30 seconds. The velocity profile obtained from the GPS data implies the presence of atmospheric gravity waves during the flight. GreenCube II flew in August 2009 with the science goal of detecting atmospheric gravity waves over the White Mountains of New Hampshire. Two balloons with identical payloads were released 90 seconds apart to make 2-point observations. Each payload carried a magnetometer, 5 thermistors for ambient temperature readings, a GPS, and an amateur radio telemetry system with a 7 second reporting cadence. A vertically oriented video camera on one payload and a horizontally oriented video camera on the other recorded the characteristics of gravity waves in the nearby clouds. We expect to be able to detect atmospheric gravity waves from the GPS-derived position and velocity of the two balloons and the ambient temperature profiles. Preliminary analysis of the temperature data shows indications of atmospheric gravity waves. RocketCube is a graduate student-designed low-resource sensorcraft development project being designed for future ionospheric multi-point missions. The FPGA-based bus system, based on GreenCube’s systems, will be able to control and digitize analog data from any low voltage instrument and telemeter that data. RocketCube contains a GPS and high-resolution magnetometer for position and orientation information. The Lynch Rocket Lab's initial interest in developing RocketCube is to investigate the k-spectrum of density irregularities in the auroral ionosphere. To this end, RocketCube will test a new Petite retarding potential analyzer Ion Probe (PIP) for examining subsonic and supersonic thermal ion populations in the ionosphere. The tentatively planned launch will be from a Wallops Flight Facility sounding rocket test flight in 2011. RocketCube serves as a step toward a scientific auroral sounding rocket mission that will feature an array of subpayloads to study the auroral ionosphere.

View of the Skylab 1 space station cluster from the Skylab 2 Command Module

NASA Image and Video Library

1973-05-25

S73-26738 (25 May 1973) --- A close-up view of the Skylab 1 space station cluster can be seen in this reproduction taken from a color television transmission made by a TV camera aboard the Skylab 2 Command Module during its ?fly-around? inspection of the cluster. The numbers across the top of the picture indicate the Skylab 1 ground lapse time. Note the missing portion of the micrometeoroid shield on the Orbital Workshop. The shield area was reported to be solid gold by the Skylab 2 crewmen. A cable appears to be wrapped around the damaged OWS solar array system wing. The crewmen reported that the other OWS solar panel was completely gone, with only tubes and wiring sticking out. One of the discone antennas extends out form the Airlock Module. The Multiple Docking Adapter is in the lower left corner of the picture. A portion of a solar panel on the Apollo Telescope Mount is visible at the bottom and at the left edge. In their ?fly around? inspection the crewmen noted that portions of the micrometeoroid shield had slid back underneath the OWS solar wing. Photo credit: NASA

Cluster analysis in systems of magnetic spheres and cubes

NASA Astrophysics Data System (ADS)

Pyanzina, E. S.; Gudkova, A. V.; Donaldson, J. G.; Kantorovich, S. S.

2017-06-01

In the present work we use molecular dynamics simulations and graph-theory based cluster analysis to compare self-assembly in systems of magnetic spheres, and cubes where the dipole moment is oriented along the side of the cube in the [001] crystallographic direction. We show that under the same conditions cubes aggregate far less than their spherical counterparts. This difference can be explained in terms of the volume of phase space in which the formation of the bond is thermodynamically advantageous. It follows that this volume is much larger for a dipolar sphere than for a dipolar cube.

ELaNa - Educational Launch of Nanosatellite Providing Routine RideShare Opportunities

NASA Technical Reports Server (NTRS)

Skrobot, Garrett Lee; Coelho, Roland

2012-01-01

Since the creation of the NASA CubeSat Launch Initiative (NCSLI), the need for CubeSat rideshares has dramatically increased. After only three releases of the initiative, a total of 66 CubeSats now await launch opportunities. So, how is this challenge being resolved? NASA's Launch Services Program (LSP) has studied how to integrate PPODs on Athena, Atlas V, and Delta IV launch vehicles and has been instrumental in developing several carrier systems to support CubeSats as rideshares on NASA missions. In support of the first two ELaNa missions the Poly-Picosatellite Orbital Deployer (P-POD) was adapted for use on a Taurus XL (ELaNa I) and a Delta n (ELaNa III). Four P-PODs, which contained a total eight CubeSats, were used on these first ELaNa missions. Next up is ELaNa VI, which will launch on an Atlas V in August 2012. The four ELaNa VI CubeSats, in three P-PODs, are awaiting launch, having been integrated in the NPSCuLite. To increase rideshare capabilities, the Launch Services Program (LSP) is working to integrate P-PODs on Falcon 9 missions. The proposed Falcon 9 manifest will provide greater opportunities for the CubeSat community. For years, the standard CubeSat size was 1 U to 3U. As the desire to include more science in each cube grows, so does the standard CubeSat size. No longer is a 1 U, 1.5U, 2U or 3U CubeSat the only option available; the new CubeSat standard will include 6U and possibly even 12U. With each increase in CubeSat size, the CubeSat community is pushing the capability of the current P-POD design. Not only is the carrier system affected, but integration to the Launch Vehicle is also a concern. The development of a system to accommodate not only the 3U P-POD but also carriers for larger CubeSats is ongoing. LSP considers payloads in the lkg to 180 kg range rideshare or small/secondary payloads. As new and emerging small payloads are developed, rideshare opportunities and carrier systems need to be identified and secured. The development of a rideshare carrier system is not always cost effective. Sometimes a launch vehicle with an excellent performance record appears to be a great rideshare candidate however, after completing a feasibility study, LSP may determine that the cost of the rideshare carrier system is too great and, due to budget constraints, the development cannot go forward. With the current budget environment, one cost effective way to secure rideshare opportunities is to look for synergy with other government organizations that share the same interest.

SpaceCube Version 1.5

NASA Technical Reports Server (NTRS)

Geist, Alessandro; Lin, Michael; Flatley, Tom; Petrick, David

2013-01-01

SpaceCube 1.5 is a high-performance and low-power system in a compact form factor. It is a hybrid processing system consisting of CPU (central processing unit), FPGA (field-programmable gate array), and DSP (digital signal processor) processing elements. The primary processing engine is the Virtex- 5 FX100T FPGA, which has two embedded processors. The SpaceCube 1.5 System was a bridge to the SpaceCube 2.0 and SpaceCube 2.0 Mini processing systems. The SpaceCube 1.5 system was the primary avionics in the successful SMART (Small Rocket/Spacecraft Technology) Sounding Rocket mission that was launched in the summer of 2011. For SMART and similar missions, an avionics processor is required that is reconfigurable, has high processing capability, has multi-gigabit interfaces, is low power, and comes in a rugged/compact form factor. The original SpaceCube 1.0 met a number of the criteria, but did not possess the multi-gigabit interfaces that were required and is a higher-cost system. The SpaceCube 1.5 was designed with those mission requirements in mind. The SpaceCube 1.5 features one Xilinx Virtex-5 FX100T FPGA and has excellent size, weight, and power characteristics [4×4×3 in. (approx. = 10×10×8 cm), 3 lb (approx. = 1.4 kg), and 5 to 15 W depending on the application]. The estimated computing power of the two PowerPC 440s in the Virtex-5 FPGA is 1100 DMIPS each. The SpaceCube 1.5 includes two Gigabit Ethernet (1 Gbps) interfaces as well as two SATA-I/II interfaces (1.5 to 3.0 Gbps) for recording to data drives. The SpaceCube 1.5 also features DDR2 SDRAM (double data rate synchronous dynamic random access memory); 4- Gbit Flash for storing application code for the CPU, FPGA, and DSP processing elements; and a Xilinx Platform Flash XL to store FPGA configuration files or application code. The system also incorporates a 12 bit analog to digital converter with the ability to read 32 discrete analog sensor inputs. The SpaceCube 1.5 design also has a built-in accelerometer. In addition, the system has 12 receive and transmit RS- 422 interfaces for legacy support. The SpaceCube 1.5 processor card represents the first NASA Goddard design in a compact form factor featuring the Xilinx Virtex- 5. The SpaceCube 1.5 incorporates backward compatibility with the Space- Cube 1.0 form factor and stackable architecture. It also makes use of low-cost commercial parts, but is designed for operation in harsh environments.

IceCube

Science.gov Websites

Press and Public Interest IceCube Acronym Dictionary Articles about IceCube "Inside Story the End of the Earth" LBNL CRD Report Education/ Public Interest A New Window on the Universe Ice

CubeSat evolution: Analyzing CubeSat capabilities for conducting science missions

NASA Astrophysics Data System (ADS)

Poghosyan, Armen; Golkar, Alessandro

2017-01-01

Traditionally, the space industry produced large and sophisticated spacecraft handcrafted by large teams of engineers and budgets within the reach of only a few large government-backed institutions. However, over the last decade, the space industry experienced an increased interest towards smaller missions and recent advances in commercial-off-the-shelf (COTS) technology miniaturization spurred the development of small spacecraft missions based on the CubeSat standard. CubeSats were initially envisioned primarily as educational tools or low cost technology demonstration platforms that could be developed and launched within one or two years. Recently, however, more advanced CubeSat missions have been developed and proposed, indicating that CubeSats clearly started to transition from being solely educational and technology demonstration platforms to offer opportunities for low-cost real science missions with potential high value in terms of science return and commercial revenue. Despite the significant progress made in CubeSat research and development over the last decade, some fundamental questions still habitually arise about the CubeSat capabilities, limitations, and ultimately about their scientific and commercial value. The main objective of this review is to evaluate the state of the art CubeSat capabilities with a special focus on advanced scientific missions and a goal of assessing the potential of CubeSat platforms as capable spacecraft. A total of over 1200 launched and proposed missions have been analyzed from various sources including peer-reviewed journal publications, conference proceedings, mission webpages as well as other publicly available satellite databases and about 130 relatively high performance missions were downselected and categorized into six groups based on the primary mission objectives including "Earth Science and Spaceborne Applications", "Deep Space Exploration", "Heliophysics: Space Weather", "Astrophysics", "Spaceborne In Situ Laboratory", and "Technology Demonstration" for in-detail analysis. Additionally, the evolution of CubeSat enabling technologies are surveyed for evaluating the current technology state of the art as well as identifying potential areas that will benefit the most from further technology developments for enabling high performance science missions based on CubeSat platforms.

Artist's drawing of internal arrangement of orbiting Apollo and Soyuz crafts

NASA Technical Reports Server (NTRS)

1974-01-01

Artist's drawing illustrating the internal arrangement of orbiting the Apollo and Soyuz spacecraft in Earth orbit in a docked configuration. The three American Apollo crewmen and the two Soviet Soyuz crewmen will transfer to each other's spacecraft during the July Apollo Soyuz Test Project (ASTP) mission. The four ASTP visible components are, left to right, the Apollo Command Module, the Docking Module, the Soyuz Orbital Module and the Soyuz Descent Vehicle.

Electroosmotic flow mixing in zigzag microchannels.

PubMed

Chen, Jia-Kun; Yang, Ruey-Jen

2007-03-01

In this study we performed numerical and experimental investigations into the mixing of EOFs in zigzag microchannels with two different corner geometries, namely sharp corners and flat corners. In the zigzag microchannel with sharp corners, the flow travels more rapidly near the inner wall of the corner than near the outer wall as a result of the higher electric potential drop. The resulting velocity gradient induces a racetrack effect, which enhances diffusion within the fluid and hence improves the mixing performance. The simulation results reveal that the mixing index is approximately 88.83%. However, the sharp-corner geometry causes residual liquid or bubbles to become trapped in the channel at the point where the flow is almost stationary, when the channel is in the process of cleaning. Accordingly, a zigzag microchannel with flat-corner geometry is developed. The flat-corner geometry forms a convergent-divergent type nozzle which not only enhances the mixing performance in the channel, but also prevents the accumulation of residual liquid or bubbles. Scaling analysis reveals that this corner geometry leads to an effective increase in the mixing length. The experimental results reveal that the mixing index is increased to 94.30% in the flat-corner zigzag channel. Hence, the results demonstrate that the mixing index of the flat-corner zigzag channel is better than that of the conventional sharp-corner microchannel. Finally, the results of Taguchi analysis indicate that the attainable mixing index is determined primarily by the number of corners in the microchannel and by the flow passing height at each corner.

APOLLO X - CREW TRAINING

NASA Image and Video Library

1969-06-03

S69-35503 (June 1969) --- Astronaut Eugene A. Cernan (left), lunar module pilot of the Apollo 10 lunar orbit mission, confers with astronaut Edwin E. Aldrin Jr. during an Apollo 10 postflight de-briefing session. Aldrin is the lunar module pilot of the Apollo 11 lunar landing mission.

Apollo 17 KREEPy basalts - Evidence for nonuniformity of KREEP

NASA Technical Reports Server (NTRS)

Salpas, Peter A.; Taylor, Lawrence A.; Lindstrom, Marilyn M.

1987-01-01

Breccia 72275 contains pristine KREEPy basalt clasts that are not found among other samples collected at Apollo 17. These basalts occur as discrete clasts and as clasts enclosed within basaltic microbreccias. Mineral and whole-rock chemical analyses reveal that the microbreccias are compositionally indistinguishable from the basalt clasts. Samples of the 72275 matrix also have the same compositions as the basalts and the basaltic microbreccias. 72275 was assembled in situ from a single flow or series of closely related flows of Apollo 17 KREEPy basalt before it was transported to the Apollo 17 site. As a rock type, Apollo 17 KREEPy basalts are distinct from Apollo 15 KREEP basalts. The Apollo 17 samples have lower REE concentrations, steeper negative slopes of the HREE, and are less magnesian than the Apollo 15 samples. The two basalt types cannot be related by fractional crystallization, partial melting, or assimilation. This is evidence for the compositional nonuniformity of KREEP as a function of geography.

Cyclic Peptidic Mimetics of Apollo Peptides Targeting Telomeric Repeat Binding Factor 2 (TRF2) and Apollo Interaction.

PubMed

Chen, Xia; Liu, Liu; Chen, Yong; Yang, Yuting; Yang, Chao-Yie; Guo, Tianyue; Lei, Ming; Sun, Haiying; Wang, Shaomeng

2018-05-10

Telomeric repeat binding factor 2 (TRF2) is a telomere-associated protein that plays an important role in the formation of the 3' single strand DNA overhang and the "T loop", two structures critical for the stability of the telomeres. Apollo is a 5'-exonuclease recruited by TRF2 to the telomere and contributes to the formation of the 3' single strand DNA overhang. Knocking down of Apollo can induce DNA damage response similar to that caused by the knocking down of TRF2. In this Letter, we report the design and synthesis of a class of cyclic peptidic mimetics of the TRFH binding motif of Apollo (Apollo TBM ). We found conformational control of the C terminal residues of Apollo TBM can effectively improve the binding affinity. We have obtained a crystal structure of a cyclic peptidic Apollo peptide mimetic ( 34 ) complexed with TRF2, which provides valuable guidance to the future design of TRF2 inhibitors.

Apollo contributes to G overhang maintenance and protects leading-end telomeres.

PubMed

Wu, Peng; van Overbeek, Megan; Rooney, Sean; de Lange, Titia

2010-08-27

Mammalian telomeres contain a single-stranded 3' overhang that is thought to mediate telomere protection. Here we identify the TRF2-interacting factor Apollo as a nuclease that contributes to the generation/maintenance of this overhang. The function of mouse Apollo was determined using Cre-mediated gene deletion, complementation with Apollo mutants, and the TRF2-F120A mutant that cannot bind Apollo. Cells lacking Apollo activated the ATM kinase at their telomeres in S phase and showed leading-end telomere fusions. These telomere dysfunction phenotypes were accompanied by a reduction in the telomeric overhang signal. The telomeric functions of Apollo required its TRF2-interaction and nuclease motifs. Thus, TRF2 recruits the Apollo nuclease to process telomere ends synthesized by leading-strand DNA synthesis, thereby creating a terminal structure that avoids ATM activation and resists end-joining. These data establish that the telomeric overhang is required for the protection of telomeres from the DNA damage response. Copyright (c) 2010 Elsevier Inc. All rights reserved.

EarthCube - Results of Test Governance in Geoscience Cyberinfrastructure

NASA Astrophysics Data System (ADS)

Davis, R.; Allison, M. L.; Keane, C. M.; Robinson, E.

2016-12-01

In September 2016, the EarthCube Test Enterprise Governance Project completed its three-year long process to engage the community and test a demonstration governing organization with the goal of facilitating a community-led process on designing and developing a geoscience cyberinfrastructure to transform geoscience research. The EarthCube initiative is making an important transition from creating a coherent community towards adoption and implemention of technologies that can serve scientists working in and across many domains. The emerging concept of a "system of systems" approach to cyberinfrastructure architecture is a critical concept in the EarthCube program, but has not been fully defined. Recommendations from an NSF-appointed Advisory Committee include: a. developing a succinct definition of EarthCube; b. changing the community-elected governance approach towards structured rather than consensus-driven decision-making; c. restructuring the process to articulate program solicitations; and d. producing an effective implementation roadmap. These are seen as prerequisites to adoption of best practices, system concepts, and evolving to a production track. The EarthCube governing body is preparing responses to the Advisory Committee findings and recommendations with a target delivery date of late 2016 but broader involvement may be warranted. We conclude that there is ample justification to continue evolving to a governance framework that facilitates convergence on a system architecture that guides EarthCube activities and plays an influential role in making operational the EarthCube vision of cyberinfrastructure for the geosciences. There is widespread community expectation for support of a multiyear EarthCube governing effort to put into practice the science, technical, and organizational plans that are continuing to emerge. However, the active participants in EarthCube represent a small sub-set of the larger population of geoscientists.

D Visualization of Volcanic Ash Dispersion Prediction with Spatial Information Open Platform in Korea

NASA Astrophysics Data System (ADS)

Youn, J.; Kim, T.

2016-06-01

Visualization of disaster dispersion prediction enables decision makers and civilian to prepare disaster and to reduce the damage by showing the realistic simulation results. With advances of GIS technology and the theory of volcanic disaster prediction algorithm, the predicted disaster dispersions are displayed in spatial information. However, most of volcanic ash dispersion predictions are displayed in 2D. 2D visualization has a limitation to understand the realistic dispersion prediction since its height could be presented only by colour. Especially for volcanic ash, 3D visualization of dispersion prediction is essential since it could bring out big aircraft accident. In this paper, we deals with 3D visualization techniques of volcanic ash dispersion prediction with spatial information open platform in Korea. First, time-series volcanic ash 3D position and concentrations are calculated with WRF (Weather Research and Forecasting) model and Modified Fall3D algorithm. For 3D visualization, we propose three techniques; those are 'Cube in the air', 'Cube in the cube', and 'Semi-transparent plane in the air' methods. In the 'Cube in the Air', which locates the semitransparent cubes having different color depends on its particle concentration. Big cube is not realistic when it is zoomed. Therefore, cube is divided into small cube with Octree algorithm. That is 'Cube in the Cube' algorithm. For more realistic visualization, we apply 'Semi-transparent Volcanic Ash Plane' which shows the ash as fog. The results are displayed in the 'V-world' which is a spatial information open platform implemented by Korean government. Proposed techniques were adopted in Volcanic Disaster Response System implemented by Korean Ministry of Public Safety and Security.

Evolution of Deformation and Recrystallization Textures in High-Purity Ni and the Ni-5 at. pct W Alloy

NASA Astrophysics Data System (ADS)

Bhattacharjee, Pinaki P.; Ray, Ranjit K.; Tsuji, Nobuhiro

2010-11-01

An attempt has been made to study the evolution of texture in high-purity Ni and Ni-5 at. pct W alloy prepared by the powder metallurgy route followed by heavy cold rolling ( 95 pct deformation) and recrystallization. The deformation textures of the two materials are of typical pure metal or Cu-type texture. Cube-oriented ( left\\{ {00 1} right\\}left< { 100} rightrangle ) regions are present in the deformed state as long thin bands, elongated in the rolling direction (RD). These bands are characterized by a high orientation gradient inside, which is a result of the rotation of the cube-oriented cells around the RD toward the RD-rotated cube ( left\\{ {0 1 3} right\\}left< { 100} rightrangle ). Low-temperature annealing produces a weak cube texture along with the left\\{ {0 1 3} right\\}left< { 100} rightrangle component, with the latter being much stronger in high-purity Ni than in the Ni-W alloy. At higher temperatures, the cube texture is strengthened considerably in the Ni-W alloy; however, the cube volume fraction in high-purity Ni is significantly lower because of the retention of the left\\{ {0 1 3} right\\}left< { 100} rightrangle component. The difference in the relative strengths of the cube, and the left\\{ {0 1 3} right\\}left< { 100} rightrangle components in the two materials is evident from the beginning of recrystallization in which more left\\{ {0 1 3} right\\}left< { 100} rightrangle -oriented grains than near cube grains form in high-purity Ni. The preferential nucleation of the near cube and the left\\{ {0 1 3} right\\}left< { 100} rightrangle grains in these materials seems to be a result of the high orientation gradients associated with the cube bands that offer a favorable environment for early nucleation.

DAsHER CD: Developing a Data-Oriented Human-Centric Enterprise Architecture for EarthCube

NASA Astrophysics Data System (ADS)

Yang, C. P.; Yu, M.; Sun, M.; Qin, H.; Robinson, E.

2015-12-01

One of the biggest challenges that face Earth scientists is the resource discovery, access, and sharing in a desired fashion. EarthCube is targeted to enable geoscientists to address the challenges by fostering community-governed efforts that develop a common cyberinfrastructure for the purpose of collecting, accessing, analyzing, sharing and visualizing all forms of data and related resources, through the use of advanced technological and computational capabilities. Here we design an Enterprise Architecture (EA) for EarthCube to facilitate the knowledge management, communication and human collaboration in pursuit of the unprecedented data sharing across the geosciences. The design results will provide EarthCube a reference framework for developing geoscience cyberinfrastructure collaborated by different stakeholders, and identifying topics which should invoke high interest in the community. The development of this EarthCube EA framework leverages popular frameworks, such as Zachman, Gartner, DoDAF, and FEAF. The science driver of this design is the needs from EarthCube community, including the analyzed user requirements from EarthCube End User Workshop reports and EarthCube working group roadmaps, and feedbacks or comments from scientists obtained by organizing workshops. The final product of this Enterprise Architecture is a four-volume reference document: 1) Volume one is this document and comprises an executive summary of the EarthCube architecture, serving as an overview in the initial phases of architecture development; 2) Volume two is the major body of the design product. It outlines all the architectural design components or viewpoints; 3) Volume three provides taxonomy of the EarthCube enterprise augmented with semantics relations; 4) Volume four describes an example of utilizing this architecture for a geoscience project.

Comparative Planetary Mineralogy: Basaltic Plagioclase from Earth, Moon, Mars and 4 Vesta

NASA Technical Reports Server (NTRS)

Karner, J. M.; Papike, J. J.; Shearer, C. K.

2003-01-01

Major, minor and trace element analysis of silicates has allowed for the study of planetary basalts in a comparative planetary mineralogy context. We continue this initiative by exploring the chemistry of plagioclase feldspar in basalts from the Earth, Moon, Mars and 4 Vesta. This paper presents new data on plagioclase from six terrestrial basalt suites including Keweenawan, Island Arc, Hawaiian, Columbia Plateau, Taos Plateau, and Ocean Floor; six lunar basalt suites including Apollo 11 Low K, Apollo 12 Ilmenite, Apollo 12 Olivine, Apollo 12 Pigeonite, Apollo 15 Olivine, and Apollo 15 Pigeonite; two basaltic martian meteorites, Shergotty and QUE 94201; and one unequilibrated eucrite, Pasamonte.

Schweickart and guest at ASVC prior to grand opening

NASA Technical Reports Server (NTRS)

1997-01-01

Apollo 9 Lunar Module Pilot Russell L. Schweikart poses in front of an Apollo Command and Service Module in the the new Apollo/Saturn V Center (ASVC) at KSC prior to the gala grand opening ceremony for the facility that was held Jan. 8, 1997. Several Apollo astronauts were invited to participate in the event, which also featured NASA Administrator Dan Goldin and KSC Director Jay Honeycutt. The ASVC also features several other Apollo program spacecraft components, multimedia presentations and a simulated Apollo/Saturn V liftoff. The facility will be a part of the KSC bus tour that embarks from the KSC Visitor Center.

Apollo 13 - Press Kit

NASA Technical Reports Server (NTRS)

1970-01-01

Apollo 13, the third U.S. manned lunar landing mission, will be launched April 11 from Kennedy Space Center, Fla., to explore a hilly upland region of the Moon and bring back rocks perhaps five billion years old. The Apollo 13 lunar module will stay on the Moon more than 33 hours and the landing crew will leave the spacecraft twice to emplace scientific experiments on the lunar surface and to continue geological investigations. The Apollo 13 landing site is in the Fra Mauro uplands; the two National Aeronautics and Space Administration previous landings were in mare or 'sea' areas, Apollo 11 in the Sea of Tranquility and Apollo 12 in the Ocean of Storms.

KSC-99pp0844

NASA Image and Video Library

1999-07-16

KENNEDY SPACE CENTER, FLA. -- In the Apollo/Saturn V Center, Lisa Malone (left), chief of KSC's Media Services branch, laughs at a humorous comment along with former Apollo astronauts Neil A. Armstrong and Edwin "Buzz" Aldrin who flew on Apollo 11, the launch to the moon; Gene Cernan, who flew on Apollo 10 and 17; and Walt Cunningham, who flew on Apollo 7. The four met with the media before an anniversary banquet celebrating the accomplishments of the Apollo program team. This is the 30th anniversary of the launch and moon landing, July 16 and July 20, 1969. Neil Armstrong was the first man to set foot on the moon

Integration of Apollo Lunar Sample Data into Google Moon

NASA Technical Reports Server (NTRS)

Dawson, Melissa D.; Todd, Nancy S.; Lofgren, Gary

2010-01-01

The Google Moon Apollo Lunar Sample Data Integration project is a continuation of the Apollo 15 Google Moon Add-On project, which provides a scientific and educational tool for the study of the Moon and its geologic features. The main goal of this project is to provide a user-friendly interface for an interactive and educational outreach and learning tool for the Apollo missions. Specifically, this project?s focus is the dissemination of information about the lunar samples collected during the Apollo missions by providing any additional information needed to enhance the Apollo mission data on Google Moon. Apollo missions 15 and 16 were chosen to be completed first due to the availability of digitized lunar sample photographs and the amount of media associated with these missions. The user will be able to learn about the lunar samples collected in these Apollo missions, as well as see videos, pictures, and 360 degree panoramas of the lunar surface depicting the lunar samples in their natural state, following collection and during processing at NASA. Once completed, these interactive data layers will be submitted for inclusion into the Apollo 15 and 16 missions on Google Moon.

Experimental Evaluation of Turning Vane Designs for High-speed and Coupled Fan-drive Corners of 0.1-scale Model of NASA Lewis Research Center's Proposed Altitude Wind Tunnel

NASA Technical Reports Server (NTRS)

Gelder, Thomas F.; Moore, Royce D.; Shyne, Rickey J.; Boldman, Donald R.

1987-01-01

Two turning vane designs were experimentally evaluated for the fan-drive corner (corner 2) coupled to an upstream diffuser and the high-speed corner (corner 1) of the 0.1 scale model of NASA Lewis Research Center's proposed Altitude Wind Tunnel. For corner 2 both a controlled-diffusion vane design (vane A4) and a circular-arc vane design (vane B) were studied. The corner 2 total pressure loss coefficient was about 0.12 with either vane design. This was about 25 percent less loss than when corner 2 was tested alone. Although the vane A4 design has the advantage of 20 percent fewer vanes than the vane B design, its vane shape is more complex. The effects of simulated inlet flow distortion on the overall losses for corner 1 or 2 were small.

Apollo 7 Mission,Apollo Commander Walter Schirra Jr. inside Co

NASA Image and Video Library

1968-10-20

AS07-04-1596 (20 Oct. 1968) --- A heavy beard covers the face of astronaut Walter M. Schirra Jr., Apollo 7 commander, as he looks out the rendezvous window in front of the commander's station on the ninth day of the Apollo 7 mission.

76 FR 7853 - Patient Safety Organizations: Voluntary Delisting From Apollo Publishing, Inc.

Federal Register 2010, 2011, 2012, 2013, 2014

2011-02-11

... Organizations: Voluntary Delisting From Apollo Publishing, Inc. AGENCY: Agency for Healthcare Research and Quality (AHRQ), HHS. ACTION: Notice of Delisting. SUMMARY: Apollo Publishing, Inc.: AHRQ has accepted a notification of voluntary relinquishment from Apollo Publishing, Inc., of its status as a Patient Safety...

Propulsion System and Orbit Maneuver Integration in CubeSats: Trajectory Control Strategies Using Micro Ion Propulsion

NASA Technical Reports Server (NTRS)

Hudson, Jennifer; Martinez, Andres; Petro, Andrew

2015-01-01

The Propulsion System and Orbit Maneuver Integration in CubeSats project aims to solve the challenges of integrating a micro electric propulsion system on a CubeSat in order to perform orbital maneuvers and control attitude. This represents a fundamentally new capability for CubeSats, which typically do not contain propulsion systems and cannot maneuver far beyond their initial orbits.

Keeping It in Three Dimensions: Measuring the Development of Mental Rotation in Children with the Rotated Colour Cube Test (RCCT)

ERIC Educational Resources Information Center

Lutke, Nikolay; Lange-Kuttner, Christiane

2015-01-01

This study introduces the new Rotated Colour Cube Test (RCCT) as a measure of object identification and mental rotation using single 3D colour cube images in a matching-to-sample procedure. One hundred 7- to 11-year-old children were tested with aligned or rotated cube models, distracters and targets. While different orientations of distracters…

Apollo program flight summary report: Apollo missions AS-201 through Apollo 16, revision 11

NASA Technical Reports Server (NTRS)

Holcomb, J. K.

1972-01-01

A summary of the Apollo flights from AS-201 through Apollo 16 is presented. The following subjects are discussed for each flight: (1) mission primary objectives, (2) principle objectives of the launch vehicle and spacecraft, (3) secondary objectives of the launch vehicle and spacecraft, (4) unusual features of the mission, (5) general information on the spacecraft and launch vehicle, (6) space vehicle and pre-launch data, and (7) recovery data.

Apollo 40th Anniversary Morning Television

NASA Image and Video Library

2009-07-19

Apollo 11 astronaut Buzz Aldrin, the second man to walk on the Moon, seated left, responds to a question during a live television interview on Monday, July 20, 2009, at NASA Headquarters in Washington as Apollo 12 astronaut Alan Bean and Apollo 16 astronaut Charles Duke, right look on. The three sat in for interviews with morning talks shows covering the 40th Anniversary of the Apollo 11 landing on the Moon. Photo Credit: (NASA/Paul E. Alers)

Cube search, revisited.

PubMed

Zhang, Xuetao; Huang, Jie; Yigit-Elliott, Serap; Rosenholtz, Ruth

2015-03-16

Observers can quickly search among shaded cubes for one lit from a unique direction. However, replace the cubes with similar 2-D patterns that do not appear to have a 3-D shape, and search difficulty increases. These results have challenged models of visual search and attention. We demonstrate that cube search displays differ from those with "equivalent" 2-D search items in terms of the informativeness of fairly low-level image statistics. This informativeness predicts peripheral discriminability of target-present from target-absent patches, which in turn predicts visual search performance, across a wide range of conditions. Comparing model performance on a number of classic search tasks, cube search does not appear unexpectedly easy. Easy cube search, per se, does not provide evidence for preattentive computation of 3-D scene properties. However, search asymmetries derived from rotating and/or flipping the cube search displays cannot be explained by the information in our current set of image statistics. This may merely suggest a need to modify the model's set of 2-D image statistics. Alternatively, it may be difficult cube search that provides evidence for preattentive computation of 3-D scene properties. By attributing 2-D luminance variations to a shaded 3-D shape, 3-D scene understanding may slow search for 2-D features of the target. © 2015 ARVO.

Cube search, revisited

PubMed Central

Zhang, Xuetao; Huang, Jie; Yigit-Elliott, Serap; Rosenholtz, Ruth

2015-01-01

Observers can quickly search among shaded cubes for one lit from a unique direction. However, replace the cubes with similar 2-D patterns that do not appear to have a 3-D shape, and search difficulty increases. These results have challenged models of visual search and attention. We demonstrate that cube search displays differ from those with “equivalent” 2-D search items in terms of the informativeness of fairly low-level image statistics. This informativeness predicts peripheral discriminability of target-present from target-absent patches, which in turn predicts visual search performance, across a wide range of conditions. Comparing model performance on a number of classic search tasks, cube search does not appear unexpectedly easy. Easy cube search, per se, does not provide evidence for preattentive computation of 3-D scene properties. However, search asymmetries derived from rotating and/or flipping the cube search displays cannot be explained by the information in our current set of image statistics. This may merely suggest a need to modify the model's set of 2-D image statistics. Alternatively, it may be difficult cube search that provides evidence for preattentive computation of 3-D scene properties. By attributing 2-D luminance variations to a shaded 3-D shape, 3-D scene understanding may slow search for 2-D features of the target. PMID:25780063

Working RideShare for the U Class Payload

NASA Technical Reports Server (NTRS)

Skrobot, Garrett L.

2014-01-01

Presentation to describe current status of the Launch Services Program's (LSP) education launch of nano satellite project. U class are payloads that are of a form factor of the 1U CubeSats - 10cm Cubed. Over the past three years these small spacecraft have grown in popularity in both the Government and the Commercial market. There is an increase in the number of NASA CubeSats selected and yet a very low launch rate. Why the low launch rate? - Funding, more money = more launches - CubeSat being selective about the orbit - CubeSats not being ready. This trend is expected to continue with current manifesting practices.

Trajectory design for a cislunar CubeSat leveraging dynamical systems techniques: The Lunar IceCube mission

NASA Astrophysics Data System (ADS)

Bosanac, Natasha; Cox, Andrew D.; Howell, Kathleen C.; Folta, David C.

2018-03-01

Lunar IceCube is a 6U CubeSat that is designed to detect and observe lunar volatiles from a highly inclined orbit. This spacecraft, equipped with a low-thrust engine, is expected to be deployed from the upcoming Exploration Mission-1 vehicle. However, significant uncertainty in the deployment conditions for secondary payloads impacts both the availability and geometry of transfers that deliver the spacecraft to the lunar vicinity. A framework that leverages dynamical systems techniques is applied to a recently updated set of deployment conditions and spacecraft parameter values for the Lunar IceCube mission, demonstrating the capability for rapid trajectory design.

KSC-2013-3996

NASA Image and Video Library

2013-11-17

CAPE CANAVERAL, Fla. -- At the News Center at NASA's Kennedy Space Center in Florida, Andrew Petro, the agency's acting director of the Early Stage Innovation Division of the Office of the Chief Technologist, discusses the agency’s CubeSat Launch initiative. CubeSats provide opportunities for small satellite payloads to fly on rockets planned for upcoming launches. CubeSats, a class of research spacecraft called nanosatellites, are flown as auxiliary payloads on previously planned missions. The cube-shaped satellites are approximately four inches long, have a volume of about one quart and weigh about three pounds. For more information, visit: http://www.nasa.gov/directorates/heo/home/CubeSats_initiative.html Photo credit: NASA/Kim Shiflett

KSC-2013-3993

NASA Image and Video Library

2013-11-17

CAPE CANAVERAL, Fla. -- At the News Center at NASA's Kennedy Space Center in Florida, Andrew Petro, the agency's acting director of the Early Stage Innovation Division of the Office of the Chief Technologist, discusses the agency’s CubeSat Launch initiative. CubeSats provide opportunities for small satellite payloads to fly on rockets planned for upcoming launches. CubeSats, a class of research spacecraft called nanosatellites, are flown as auxiliary payloads on previously planned missions. The cube-shaped satellites are approximately four inches long, have a volume of about one quart and weigh about three pounds. For more information, visit: http://www.nasa.gov/directorates/heo/home/CubeSats_initiative.html Photo credit: NASA/Kim Shiflett

KSC-2013-3995

NASA Image and Video Library

2013-11-17

CAPE CANAVERAL, Fla. -- At the News Center at NASA's Kennedy Space Center in Florida, Andrew Petro, the agency's acting director of the Early Stage Innovation Division of the Office of the Chief Technologist, discusses the agency’s CubeSat Launch initiative. CubeSats provide opportunities for small satellite payloads to fly on rockets planned for upcoming launches. CubeSats, a class of research spacecraft called nanosatellites, are flown as auxiliary payloads on previously planned missions. The cube-shaped satellites are approximately four inches long, have a volume of about one quart and weigh about three pounds. For more information, visit: http://www.nasa.gov/directorates/heo/home/CubeSats_initiative.html Photo credit: NASA/Kim Shiflett

KSC-2013-3994

NASA Image and Video Library

2013-11-17

CAPE CANAVERAL, Fla. -- At the News Center at NASA's Kennedy Space Center in Florida, Andrew Petro, the agency's acting director of the Early Stage Innovation Division of the Office of the Chief Technologist, discusses the agency’s CubeSat Launch initiative. CubeSats provide opportunities for small satellite payloads to fly on rockets planned for upcoming launches. CubeSats, a class of research spacecraft called nanosatellites, are flown as auxiliary payloads on previously planned missions. The cube-shaped satellites are approximately four inches long, have a volume of about one quart and weigh about three pounds. For more information, visit: http://www.nasa.gov/directorates/heo/home/CubeSats_initiative.html Photo credit: NASA/Kim Shiflett

Collapsible Cubes and Other Curiosities.

ERIC Educational Resources Information Center

Johnson, Scott; Walser, Hans

1997-01-01

Describes some general techniques for making collapsible models, including spiral models, for all the Platonic solids except the cube. Discusses the nature of the dissections of the faces necessary for the construction of the spiral cube. (ASK)

Kennedy Center Salute To Apollo

NASA Image and Video Library

2009-07-17

Apollo 11 astronaut Buzz Aldrin reads an introduction to Gustav Holst: The Planets Suite during the "Salute to Apollo" ceremony at the Kennedy Center for the Performing Arts, Saturday, July 18, 2009 in Washington. The event was part of NASA's week long celebration of the Apollo 40th Anniversary. Photo Credit: (NASA/Bill Ingalls)

Topographic mapping of the Apollo 16 landing site

NASA Technical Reports Server (NTRS)

Hill, R. O.; Bender, M. J.

1972-01-01

The techniques are described for obtaining high resolution photographs from the Apollo 14 lunar orbiter for topographic mapping of the Descartes landing site for use in planning Apollo 16. The Apollo 16 spacecraft landed approximately 250 m from the selected target point, and few topographic surprises were encountered.

ASTRONAUT LOVELL, JAMES A., JR. - APOLLO VIII (GUIDANCE & NAVIGATION [G&N])

NASA Image and Video Library

1969-05-25

S69-35099 (21-27 Dec. 1968) --- Astronaut James A. Lovell Jr., Apollo 8 command module pilot, is seen at the Apollo 8 Spacecraft Command Module's Guidance and Navigation station during the Apollo 8 lunar orbit mission. This picture was taken from 16mm motion picture film.

Saturn Apollo Program

NASA Image and Video Library

1968-06-03

Pictured left to right, in the Apollo 7 Crew Portrait, are astronauts R. Walter Cunningham, Lunar Module pilot; Walter M. Schirra, Jr., commander; and Donn F. Eisele, Command Module Pilot. The Apollo 7 mission, boosted by a Saturn IB launch vehicle on October 11, 1968, was the first manned flight of the Apollo spacecraft.

Using Additive Manufacturing to Print a CubeSat Propulsion System

NASA Technical Reports Server (NTRS)

Marshall, William M.

2015-01-01

CubeSats are increasingly being utilized for missions traditionally ascribed to larger satellites CubeSat unit (1U) defined as 10 cm x 10 cm x 11 cm. Have been built up to 6U sizes. CubeSats are typically built up from commercially available off-the-shelf components, but have limited capabilities. By using additive manufacturing, mission specific capabilities (such as propulsion), can be built into a system. This effort is part of STMD Small Satellite program Printing the Complete CubeSat. Interest in propulsion concepts for CubeSats is rapidly gaining interest-Numerous concepts exist for CubeSat scale propulsion concepts. The focus of this effort is how to incorporate into structure using additive manufacturing. End-use of propulsion system dictates which type of system to develop-Pulse-mode RCS would require different system than a delta-V orbital maneuvering system. Team chose an RCS system based on available propulsion systems and feasibility of printing using a materials extrusion process. Initially investigated a cold-gas propulsion system for RCS applications-Materials extrusion process did not permit adequate sealing of part to make this a functional approach.

Girls in detail, boys in shape: gender differences when drawing cubes in depth.

PubMed

Lange-Küttner, C; Ebersbach, M

2013-08-01

The current study tested gender differences in the developmental transition from drawing cubes in two- versus three dimensions (3D), and investigated the underlying spatial abilities. Six- to nine-year-old children (N = 97) drew two occluding model cubes and solved several other spatial tasks. Girls more often unfolded the various sides of the cubes into a layout, also called diagrammatic cube drawing (object design detail). In girls, the best predictor for drawing the cubes was Mental Rotation Test (MRT) accuracy. In contrast, boys were more likely to preserve the optical appearance of the cube array. Their drawing in 3D was best predicted by MRT reaction time and the Embedded Figures Test (EFT). This confirmed boys' stronger focus on the contours of an object silhouette (object shape). It is discussed whether the two gender-specific approaches to drawing in three dimensions reflect two sides of the appearance-reality distinction in drawing, that is graphic syntax of object design features versus visual perception of projective space. © 2012 The British Psychological Society.

Disorganized behavior on Link's cube test is sensitive to right hemispheric frontal lobe damage in stroke patients

PubMed Central

Kopp, Bruno; Rösser, Nina; Tabeling, Sandra; Stürenburg, Hans Jörg; de Haan, Bianca; Karnath, Hans-Otto; Wessel, Karl

2014-01-01

One of Luria's favorite neuropsychological tasks for challenging frontal lobe functions was Link's cube test (LCT). The LCT is a cube construction task in which the subject must assemble 27 small cubes into one large cube in such a manner that only the painted surfaces of the small cubes are visible. We computed two new LCT composite scores, the constructive plan composite score, reflecting the capability to envisage a cubical-shaped volume, and the behavioral (dis-) organization composite score, reflecting the goal-directedness of cube construction. Voxel-based lesion-behavior mapping (VLBM) was used to test the relationship between performance on the LCT and brain injury in a sample of stroke patients with right hemisphere damage (N = 32), concentrated in the frontal lobe. We observed a relationship between the measure of behavioral (dis-) organization on the LCT and right frontal lesions. Further work in a larger sample, including left frontal lobe damage and with more power to detect effects of right posterior brain injury, is necessary to determine whether this observation is specific for right frontal lesions. PMID:24596552

Software Requirements Specification for Lunar IceCube

NASA Astrophysics Data System (ADS)

Glaser-Garbrick, Michael R.

Lunar IceCube is a 6U satellite that will orbit the moon to measure water volatiles as a function of position, altitude, and time, and measure in its various phases. Lunar IceCube, is a collaboration between Morehead State University, Vermont Technical University, Busek, and NASA. The Software Requirements Specification will serve as contract between the overall team and the developers of the flight software. It will provide a system's overview of the software that will be developed for Lunar IceCube, in that it will detail all of the interconnects and protocols for each subsystem's that Lunar IceCube will utilize. The flight software will be written in SPARK to the fullest extent, due to SPARK's unique ability to make software free of any errors. The LIC flight software does make use of a general purpose, reusable application framework called CubedOS. This framework imposes some structuring requirements on the architecture and design of the flight software, but it does not impose any high level requirements. It will also detail the tools that we will be using for Lunar IceCube, such as why we will be utilizing VxWorks.

High Data Rates for AubieSat-2 A & B, Two CubeSats Performing High Energy Science in the Upper Atmosphere

NASA Technical Reports Server (NTRS)

Sims, William H.

2015-01-01

This paper will discuss a proposed CubeSat size (3 Units / 6 Units) telemetry system concept being developed at Marshall Space Flight Center (MSFC) in cooperation with Auburn University. The telemetry system incorporates efficient, high-bandwidth communications by developing flight-ready, low-cost, PROTOFLIGHT software defined radio (SDR) payload for use on CubeSats. The current telemetry system is slightly larger in dimension of footprint than required to fit within a 0.75 Unit CubeSat volume. Extensible and modular communications for CubeSat technologies will provide high data rates for science experiments performed by two CubeSats flying in formation in Low Earth Orbit. The project is a collaboration between the University of Alabama in Huntsville and Auburn University to study high energy phenomena in the upper atmosphere. Higher bandwidth capacity will enable high-volume, low error-rate data transfer to and from the CubeSats, while also providing additional bandwidth and error correction margin to accommodate more complex encryption algorithms and higher user volume.

Corner stores: the perspective of urban youth.

PubMed

Sherman, Sandra; Grode, Gabrielle; McCoy, Tara; Vander Veur, Stephanie S; Wojtanowski, Alexis; Sandoval, Brianna Almaguer; Foster, Gary D

2015-02-01

We examined the perspectives of low-income, urban youth about the corner store experience to inform the development of corner store interventions. Focus groups were conducted to understand youth perceptions regarding their early shopping experiences, the process of store selection, reasons for shopping in a corner store, parental guidance about corner stores, and what their ideal, or "dream corner store" would look like. Thematic analysis was employed to identify themes using ATLAS.ti (version 6.1, 2010, ATLAS.ti GmbH) and Excel (version 2010, Microsoft Corp). Focus groups were conducted in nine kindergarten-through-grade 8 (K-8) public schools in low-income neighborhoods with 40 fourth- to sixth-graders with a mean age of 10.9±0.8 years. Youth report going to corner stores with family members at an early age. By second and third grades, a growing number of youth reported shopping unaccompanied by an older sibling or adult. Youth reported that the products sold in stores were the key reason they choose a specific store. A small number of youth said their parents offered guidance on their corner store purchases. When youth were asked what their dream corner store would look like, they mentioned wanting a combination of healthy and less-healthy foods. These data suggest that, among low-income, urban youth, corner store shopping starts at a very young age and that product, price, and location are key factors that affect corner store selection. The data also suggest that few parents offer guidance about corner store purchases, and youth are receptive to having healthier items in corner stores. Corner store intervention efforts should target young children and their parents/caregivers and aim to increase the availability of affordable, healthier products. Copyright © 2015 Academy of Nutrition and Dietetics. Published by Elsevier Inc. All rights reserved.

Endocrine Laboratory Results Apollo Missions 14 and 15

NASA Technical Reports Server (NTRS)

Leach, C. S.

1972-01-01

Endocrine/metabolic responses to space flight have been measured on the crewmen of Apollo missions 14 and 15. There were significant biochemical changes in the crewmen of both missions immediately postflight. However, the Apollo 15 mission results differed from Apollo 14 and preflight shown by a normal to increased urine volume with slight increases in antidiuretic hormone. Although Apollo 15 was the first mission in which the exchangeable potassium measurement was made (a decrease), results from other missions were indicative of similar conclusions.

Neil Armstrong chats with attendees at Apollo 11 anniversary banquet.

NASA Technical Reports Server (NTRS)

1999-01-01

Former Apollo 11 astronaut Neil A. Armstrong poses for a photograph with fans who attended the anniversary banquet honoring the Apollo team, the people who made the entire lunar landing program possible. The banquet was held in the Apollo/Saturn V Center, part of the KSC Visitor Complex. This is the 30th anniversary of the Apollo 11 launch and moon landing, July 16 and July 20, 1969. Neil Armstrong was the first man to set foot on the moon.

Glenn Lecture With Crew of Apollo 11

NASA Image and Video Library

2009-07-18

On the eve of the fortieth anniversary of Apollo 11's first human landing on the Moon, Apollo 11 crew member, Michael Collins speaks during a lecture in honor of Apollo 11 at the National Air and Space Museum in Washington, Sunday, July 19, 2009. Guest speakers included Former NASA Astronaut and U.S. Senator John Glenn, NASA Mission Control creator and former NASA Johnson Space Center director Chris Kraft and the crew of Apollo 11. Photo Credit: (NASA/Bill Ingalls)

Glenn Lecture With Crew of Apollo 11

NASA Image and Video Library

2009-07-18

On the eve of the fortieth anniversary of Apollo 11's first human landing on the Moon, Apollo 11 crew member, Buzz Aldrin speaks during a lecture in honor of Apollo 11 at the National Air and Space Museum in Washington, Sunday, July 19, 2009. Guest speakers included Former NASA Astronaut and U.S. Senator John Glenn, NASA Mission Control creator and former NASA Johnson Space Center director Chris Kraft and the crew of Apollo 11. Photo Credit: (NASA/Bill Ingalls)

Apollo 1 Lessons Learned Show

NASA Image and Video Library

2017-01-27

NASA Kennedy Space Center Director Bob Cabana, at left, moderates a panel discussion during the Apollo 1 Lessons Learned event in the Training Auditorium at NASA’s Kennedy Space Center in Florida. The theme of the presentation was "To There and Back Again." Answering questions are Ernie Reyes, retired, Apollo 1 senior operations engineer; and John Tribe, retired, Apollo 1 Reaction and Control System lead engineer. The event helped pay tribute to the Apollo 1 crew, Gus Grissom, Ed White II, and Roger Chaffee.

KSC-99pp0855

NASA Image and Video Library

1999-07-16

KENNEDY SPACE CENTER, FLA. -- Former Apollo 11 astronaut Neil A. Armstrong talks with a former Apollo team member during an anniversary banquet honoring the Apollo team, the people who made the entire lunar landing program possible. The banquet was held in the Apollo/Saturn V Center, part of the KSC Visitor Complex. This is the 30th anniversary of the Apollo 11 launch and moon landing, July 16 and July 20, 1969. Neil Armstrong was the first man to set foot on the moon

Dedication Ceremony

NASA Technical Reports Server (NTRS)

1999-01-01

Alabama Governor Don Seigleman cuts the ribbon marking the dedication of the Saturn V rocket replica that was constructed at the U. S. Space and Rocket Center in honor of the 30th arniversary of the lunar landing. Accompanying the Governor are (L/R): Mike Wing, CEO US Space Rocket Center; Mike Gillespie, Madison County Commissioner, Dist. Seven; Buzz Aldrin, Apollo 11 Astronaut; Governor Seigleman; Walt Cunningham, Apollo 7 Astronaut; Dick Gordon, Apollo 12 Astronaut; Ed Mitchell, Apollo 14 Astronaut; Charlie Duke, Apollo 16 Astronaut; and Owen Garriott, Skylab 3 Astronaut.

Around Marshall

NASA Image and Video Library

1999-07-16

Alabama Governor Don Seigleman cuts the ribbon marking the dedication of the Saturn V rocket replica that was constructed at the U. S. Space and Rocket Center in honor of the 30th arniversary of the lunar landing. Accompanying the Governor are (L/R): Mike Wing, CEO US Space Rocket Center; Mike Gillespie, Madison County Commissioner, Dist. Seven; Buzz Aldrin, Apollo 11 Astronaut; Governor Seigleman; Walt Cunningham, Apollo 7 Astronaut; Dick Gordon, Apollo 12 Astronaut; Ed Mitchell, Apollo 14 Astronaut; Charlie Duke, Apollo 16 Astronaut; and Owen Garriott, Skylab 3 Astronaut.

Artist's drawing of internal arrangement of orbiting Apollo & Soyuz crafts

NASA Image and Video Library

1974-12-01

S74-05269 (December 1974) --- An artist?s drawing illustrating the internal arrangement of the Apollo and Soyuz spacecraft in Earth orbit in a docked configuration. The three American Apollo crewmen and the two Soviet Soyuz crewmen will transfer to each other?s spacecraft during the July 1975 ASTP mission. The four Apollo-Soyuz Test Project visible components are, left to right, the Apollo Command Module, the Docking Module, the Soyuz Orbital Module and the Soyuz Descent Vehicle.

Apollo 16 astronauts in Apollo Command Module Mission Simulator

NASA Technical Reports Server (NTRS)

1972-01-01

Astronaut Thomas K. Mattingly II, command module pilot of the Apollo 16 lunar landing mission, participates in extravehicular activity (EVA) training in bldg 5 at the Manned Spacecraft Center (MSC). In the right background is Astronaut Charles M. Duke Jr., lunar module pilot. They are inside the Apollo Command Module Mission Simulator (31046); Mattingly (right foreground) and Duke (right backgroung) in the Apollo Command Module Mission Simulator for EVA simulation and training. Astronaut John W. Young, commander, can be seen in the left background (31047).

INFLIGHT - APOLLO X (CREW ACTIVITIES)

NASA Image and Video Library

1969-05-18

S69-33999 (18 May 1969) --- A close-up view of the face of astronaut, Thomas P. Stafford, Apollo 10 commander, is seen in this color reproduction taken from the third television transmission made by the color television camera aboard the Apollo 10 spacecraft. When this picture was made the Apollo 10 spacecraft was on a trans-lunar course, and was already about 36,000 nautical miles from Earth. Also, aboard Apollo 10 were astronauts John W. Young, command module pilot, and Eugene A. Cernan, lunar module pilot.

CubeSat Launch Initiative

NASA Technical Reports Server (NTRS)

Higginbotham, Scott

2016-01-01

The National Aeronautics and Space Administration (NASA) recognizes the tremendous potential that CubeSats (very small satellites) have to inexpensively demonstrate advanced technologies, collect scientific data, and enhance student engagement in Science, Technology, Engineering, and Mathematics (STEM). The CubeSat Launch Initiative (CSLI) was created to provide launch opportunities for CubeSats developed by academic institutions, non-profit entities, and NASA centers. This presentation will provide an overview of the CSLI, its benefits, and its results.

Power generation and solar panels for an MSU CubeSat

NASA Astrophysics Data System (ADS)

Sassi, Soundouss

This thesis is a power generation study of a proposed CubeSat at Mississippi State University (MSU). CubeSats are miniaturized satellites of 10 x 10 x 10 cm in dimension. Their power source once in orbit is the sun during daylight and the batteries during eclipse. MSU CubeSat is equipped with solar panels. This effort will discuss two types of cells: Gallium Arsenide and Silicon; and which one will suit MSU CubeSat best. Once the cell type is chosen, another decision regarding the electrical power subsystem will be made. Solar array design can only be done once the choice of the electrical power subsystem and the solar cells is made. Then the power calculation for different mission durations will start along with the sizing of the solar arrays. In the last part the batteries are introduced and discussed in order to choose one type of batteries for MSU CubeSat.

Teaching group theory using Rubik's cubes

NASA Astrophysics Data System (ADS)

Cornock, Claire

2015-10-01

Being situated within a course at the applied end of the spectrum of maths degrees, the pure mathematics modules at Sheffield Hallam University have an applied spin. Pure topics are taught through consideration of practical examples such as knots, cryptography and automata. Rubik's cubes are used to teach group theory within a final year pure elective based on physical examples. Abstract concepts, such as subgroups, homomorphisms and equivalence relations are explored with the cubes first. In addition to this, conclusions about the cubes can be made through the consideration of algebraic approaches through a process of discovery. The teaching, learning and assessment methods are explored in this paper, along with the challenges and limitations of the methods. The physical use of Rubik's cubes within the classroom and examination will be presented, along with the use of peer support groups in this process. The students generally respond positively to the teaching methods and the use of the cubes.

ECITE: A Testbed for Assessment of Technology Interoperability and Integration wiht Architecture Components

NASA Astrophysics Data System (ADS)

Graves, S. J.; Keiser, K.; Law, E.; Yang, C. P.; Djorgovski, S. G.

2016-12-01

ECITE (EarthCube Integration and Testing Environment) is providing both cloud-based computational testing resources and an Assessment Framework for Technology Interoperability and Integration. NSF's EarthCube program is funding the development of cyberinfrastructure building block components as technologies to address Earth science research problems. These EarthCube building blocks need to support integration and interoperability objectives to work towards a coherent cyberinfrastructure architecture for the program. ECITE is being developed to provide capabilities to test and assess the interoperability and integration across funded EarthCube technology projects. EarthCube defined criteria for interoperability and integration are applied to use cases coordinating science problems with technology solutions. The Assessment Framework facilitates planning, execution and documentation of the technology assessments for review by the EarthCube community. This presentation will describe the components of ECITE and examine the methodology of cross walking between science and technology use cases.

EarthCube: A Community-Driven Cyberinfrastructure for the Geosciences

NASA Astrophysics Data System (ADS)

Koskela, Rebecca; Ramamurthy, Mohan; Pearlman, Jay; Lehnert, Kerstin; Ahern, Tim; Fredericks, Janet; Goring, Simon; Peckham, Scott; Powers, Lindsay; Kamalabdi, Farzad; Rubin, Ken; Yarmey, Lynn

2017-04-01

EarthCube is creating a dynamic, System of Systems (SoS) infrastructure and data tools to collect, access, analyze, share, and visualize all forms of geoscience data and resources, using advanced collaboration, technological, and computational capabilities. EarthCube, as a joint effort between the U.S. National Science Foundation Directorate for Geosciences and the Division of Advanced Cyberinfrastructure, is a quickly growing community of scientists across all geoscience domains, as well as geoinformatics researchers and data scientists. EarthCube has attracted an evolving, dynamic virtual community of more than 2,500 contributors, including earth, ocean, polar, planetary, atmospheric, geospace, computer and social scientists, educators, and data and information professionals. During 2017, EarthCube will transition to the implementation phase. The implementation will balance "innovation" and "production" to advance cross-disciplinary science goals as well as the development of future data scientists. This presentation will describe the current architecture design for the EarthCube cyberinfrastructure and implementation plan.

Miniature Radioisotope Thermoelectric Power Cubes

NASA Technical Reports Server (NTRS)

Patel, Jagdish U.; Fleurial, Jean-Pierre; Snyder, G. Jeffrey; Caillat, Thierry

2004-01-01

Cube-shaped thermoelectric devices energized by a particles from radioactive decay of Cm-244 have been proposed as long-lived sources of power. These power cubes are intended especially for incorporation into electronic circuits that must operate in dark, extremely cold locations (e.g., polar locations or deep underwater on Earth, or in deep interplanetary space). Unlike conventional radioisotope thermoelectric generators used heretofore as central power sources in some spacecraft, the proposed power cubes would be small enough (volumes would range between 0.1 and 0.2 cm3) to play the roles of batteries that are parts of, and dedicated to, individual electronic-circuit packages. Unlike electrochemical batteries, these power cubes would perform well at low temperatures. They would also last much longer: given that the half-life of Cm-244 is 18 years, a power cube could remain adequate as a power source for years, depending on the power demand in its particular application.

Apollo 16 astronauts in Apollo Command Module Mission Simulator

NASA Image and Video Library

1972-03-14

S72-31047 (March 1972) --- Astronaut Thomas K. Mattingly II (right foreground), command module pilot of the Apollo 16 lunar landing mission, participates in extravehicular activity (EVA) training in Building 5 at the Manned Spacecraft Center (MSC). Mattingly is scheduled to perform EVA during the Apollo 16 journey home from the moon. Astronaut John W. Young, commander, can be seen in the left background. In the right background is astronaut Charles M. Duke Jr., lunar module pilot. They are inside the Apollo Command Module Mission Simulator. While Mattingly remains with the Apollo 16 Command and Service Modules (CSM) in lunar orbit, Young and Duke will descend in the Lunar Module (LM) to the moon's Descartes landing site.

KSC-2012-6147

NASA Image and Video Library

2012-11-03

CAPE CANAVERAL, Fla. – Charles Duke, chairman of the board of directors for the Astronaut Scholarship Foundation welcomes guests who have gathered for the organization's dinner at the Radisson Resort at the Port in Cape Canaveral celebrating the 40th anniversary of Apollo 17. The gala commemorating the anniversary of Apollo 17 included mission commander Eugene Cernan and other astronauts who flew Apollo missions. Launched Dec. 7, 1972, Cernan and lunar module pilot Harrison Schmitt landed in the moon's Taurus-Littrow highlands while command module pilot Ronald Evans remained in lunar orbit operating a scientific instrument module. For more information, visit http://www-pao.ksc.nasa.gov/history/apollo/apollo-17/apollo-17.htm Photo credit: NASA/Kim Shiflett

KSC-2012-6146

NASA Image and Video Library

2012-11-03

CAPE CANAVERAL, Fla. – Charles Duke, chairman of the board of directors for the Astronaut Scholarship Foundation welcomes guests who have gathered for the organization's dinner at the Radisson Resort at the Port in Cape Canaveral celebrating the 40th anniversary of Apollo 17. The gala commemorating the anniversary of Apollo 17 included mission commander Eugene Cernan and other astronauts who flew Apollo missions. Launched Dec. 7, 1972, Cernan and lunar module pilot Harrison Schmitt landed in the moon's Taurus-Littrow highlands while command module pilot Ronald Evans remained in lunar orbit operating a scientific instrument module. For more information, visit http://www-pao.ksc.nasa.gov/history/apollo/apollo-17/apollo-17.htm Photo credit: NASA/Kim Shiflett

Radioactivities vs. depth in Apollo 16 and 17 soil

NASA Technical Reports Server (NTRS)

Fireman, E. L.; D'Amico, J.; Defelice, J.

1973-01-01

The radioactivities of Ar-37, Ar-39, and H-3 measured at a number of depths for Apollo 16 and 17 soil are reported. The Ar-37 activities vs depth in the Apollo 16 drill string increased with depth and reached a broad maximum in the neighborhood of 50 g per sq cm before decreasing. The Ar-39 activities in Apollo 17 soil were higher than in Apollo 16 soil, probably owing to the higher Fe and Ti contents. The H-3 activities in Apollo 16 and 17 soil were quite similar and indicate that the 4 August 1972 flare produced very little H-3 compared to the amount produced by solar flares during the previous 50 years.

Results of the Apollo 15 and 16 X-ray experiment

NASA Technical Reports Server (NTRS)

Adler, I.; Trombka, J. I.; Schmadebeck, R.; Lowman, P.; Blodget, H.; Yin, L.; Eller, E.; Podwysocki, M.; Weidner, J. R.; Bickel, A. L.

1973-01-01

Except for some minor modifications the Apollo 16 X-ray fluorescence experiment was similar to that flown aboard Apollo 15. The Apollo 16 provided data for a number of features not previously covered such as Mare Cognitum, Mare Nubium, Ptolemaeus, Descartes, Mendeleev, and other areas. Many data points were obtained by the X-ray experiments, so that comparisons could be drawn between Apollo 15 and 16 flights. The agreement was generally within about 10%. Al/Si concentration ratios ranged from 0.38% in Mare Cognitum to 0.67% in the Descartes area highlands. A comparison of the Apollo 16 data Al/Si values with optical albedo values along the ground tracks showed the same positive correlation as in the Apollo 15 flight. A reexamination of the detector and collimator geometries showed that the spatial resolution was better by almost a factor of two than the initial estimates.

Saturn Apollo Program

NASA Image and Video Library

1968-12-19

Pictured from left to right, the Apollo 9 astronauts, James A. McDivitt, David R. Scott, and Russell L. Schweickart, pause in front of the Apollo/Saturn V space vehicle that would launch the Apollo 8 crew. The launch of the Apollo 9 (Saturn V launch vehicle, SA-504) took place on March 3, 1968. The Apollo 9 spacecraft, in the lunar mission configuration, was tested in Earth orbit. The mission was designed to rehearse all the steps and reproduce all the events of the Apollo 11 mission with the exception of the lunar touchdown, stay, and liftoff. The command and service modules, and the lunar module were used in flight procedures identical to those that would later take similar vehicles to the Moon, and a landing. The flight mechanics, mission support systems, communications, and recording of data were tested in a final round of verification. Astronauts Scott and Schweickart conducted Extravehicular Activity during this mission.

Kennedy Center Salute To Apollo

NASA Image and Video Library

2009-07-17

Apollo 11 astronaut Buzz Aldrin, left, meets with Gene Kranz, retired NASA Flight Director and manager, back stage after the "Salute to Apollo" ceremony at the Kennedy Center for the Performing Arts, Saturday, July 18, 2009 in Washington. The event was part of NASA's week long celebration of the Apollo 40th Anniversary. Photo Credit: (NASA/Bill Ingalls)

Apollo 7 prime crew during water egress training in Gulf of Mexico

NASA Technical Reports Server (NTRS)

1968-01-01

The prime crew of the first manned Apollo space mission, Apollo 7, is seen in Apollo Command Module Boilerplate 1102 during water egress training in the Gulf of Mexico. In foreground is Astronaut Walter M. Schirra Jr., in center is Astronaut Donn F. Eisele, and in background is Astronaut Walter Cunningham.

Lunar Reconnaissance Orbiter Camera

Science.gov Websites

them out » Traverse featurette Traverse the Apollo Landing Sites & More. By combining LROC imagery , data, and historical data, we've created detailed, interactive maps of the Apollo Landing Sites and taken by the original Apollo crews. ASU maintains the Apollo Digital Image Archive and the March to the

COMMAND MODULE - APOLLO - INTERIOR - SPACECRAFT (S/C) 101 - PANEL - CONTROL - NORTH AMERICAN AVIATION (NAA), CA

NASA Image and Video Library

1967-01-27

S67-23078 (27 Jan. 1967) --- Three astronauts (later to be named the Apollo 9 prime crew) in Apollo spacecraft 101 Command module during Apollo crew compartment fit and function test. Left to right are astronauts James A. McDivitt, David R. Scott, and Russell L. Schweickart.

Apollo 9 - Prime Crew - Apollo Command Module (CM)-103 - Post-Test

NASA Image and Video Library

1968-07-19

S68-42164 (19 July 1968) --- The prime crew of the third manned Apollo space mission stands in front of the Apollo Command Module 103 after egress during crew compartment fit and function test activity. Left to right are astronauts Russell L. Schweickart, David R. Scott, and James A. McDivitt.

The Lunar Landing Research Vehicle; Prelude to the Arrival at Tranquility Base

NASA Technical Reports Server (NTRS)

Gelzer, Christian

2006-01-01

The flight of Apollo 11 was the end of a decade-long race to reach the moon, a race between the US and Soviet Union, but also a race with time, for we as a nation only had the 1960s to reach our objective. Most of us remember that particular day, July 20, 1969, but the further we are from any date the harder it is to recall details. It s easy to forget, for instance, how close together the Apollo flights came to each other as the lunar flight date approached. Apollo 7 circled Earth for almost 11 days testing the systems of the spacecraft in October 1968; Apollo 8 gave us the first glimpse of our entire planet while circling the moon during Christmas of 1968. Apollo 9 lifted off on March 3 of 1969, and Apollo 10 returned to Earth on May 26 of that year. Less than two months later, on 16 July, Apollo 11 lifted off on its mission of landing on the moon. That s five Apollo launches in ten months, three of which went to the moon.

Function of Apollo (SNM1B) at telomere highlighted by a splice variant identified in a patient with Hoyeraal–Hreidarsson syndrome

PubMed Central

Touzot, Fabien; Callebaut, Isabelle; Soulier, Jean; Gaillard, Laetitia; Azerrad, Chantal; Durandy, Anne; Fischer, Alain; de Villartay, Jean-Pierre; Revy, Patrick

2010-01-01

Telomeres, the protein–DNA complexes at the ends of linear chromosomes, are protected and regulated by the shelterin molecules, the telomerase complex, and other accessory factors, among which is Apollo, a DNA repair factor of the β-lactamase/β-CASP family. Impaired telomere protection in humans causes dyskeratosis congenita and Hoyeraal–Hreidarsson (HH) syndrome, characterized by premature aging, bone marrow failure, and immunodeficiency. We identified a unique Apollo splice variant (designated Apollo-Δ) in fibroblasts from a patient with HH syndrome. Apollo-Δ generates a dominant negative form of Apollo lacking the telomeric repeat-binding factor homology (TRFH)-binding motif (TBM) required for interaction with the shelterin TRF2 at telomeres. Apollo-Δ hampers the proper replication of telomeres, leading to major telomeric dysfunction and cellular senescence, but maintains its DNA interstrand cross-link repair function in the whole genome. These results identify Apollo as a crucial actor in telomere maintenance in vivo, independent of its function as a general DNA repair factor. PMID:20479256

Function of Apollo (SNM1B) at telomere highlighted by a splice variant identified in a patient with Hoyeraal-Hreidarsson syndrome.

PubMed

Touzot, Fabien; Callebaut, Isabelle; Soulier, Jean; Gaillard, Laetitia; Azerrad, Chantal; Durandy, Anne; Fischer, Alain; de Villartay, Jean-Pierre; Revy, Patrick

2010-06-01

Telomeres, the protein-DNA complexes at the ends of linear chromosomes, are protected and regulated by the shelterin molecules, the telomerase complex, and other accessory factors, among which is Apollo, a DNA repair factor of the beta-lactamase/beta-CASP family. Impaired telomere protection in humans causes dyskeratosis congenita and Hoyeraal-Hreidarsson (HH) syndrome, characterized by premature aging, bone marrow failure, and immunodeficiency. We identified a unique Apollo splice variant (designated Apollo-Delta) in fibroblasts from a patient with HH syndrome. Apollo-Delta generates a dominant negative form of Apollo lacking the telomeric repeat-binding factor homology (TRFH)-binding motif (TBM) required for interaction with the shelterin TRF2 at telomeres. Apollo-Delta hampers the proper replication of telomeres, leading to major telomeric dysfunction and cellular senescence, but maintains its DNA interstrand cross-link repair function in the whole genome. These results identify Apollo as a crucial actor in telomere maintenance in vivo, independent of its function as a general DNA repair factor.

A Wideband Corner-Reflector Antenna for 240 to 400 MHz.

DTIC Science & Technology

1983-09-19

8217 .; ,:,:. .-.:.,.;.. - -... - .- . -.. .-- v...- ..... .-. .-.- 1,.:..- FIGURES 1. Corner Reflector with Open-Sleeve Dipole Feed ............ ...... 7 2...Open-Sleeve Dipole Feed for Corner Reflector, 240-400 MHz........ 8 3. Closeup Photo of Open-Sleeve Dpole ..................... ...... 8 4. VSWR of...4-ft Corner Reflector, Open-Sleeve Dipole Feed .......... 9 5. Gain of Corner Reflector............ .............. . ....... 9 6. Measured E- and H

The telomeric protein SNM1B/Apollo is required for normal cell proliferation and embryonic development

PubMed Central

Akhter, Shamima; Lam, Yung C.; Chang, Sandy; Legerski, Randy J.

2013-01-01

Summary Conserved metallo β-Lactamase and β-CASP (CPSF-Artemis-Snm1-Pso2) domain nuclease family member SNM1B/Apollo is a shelterin-associated protein that localizes to telomeres through its interaction with TRF2. To study its in vivo role, we generated a knockout of SNM1B/Apollo in a mouse model. Snm1B/Apollo homozygous null mice die at birth with developmental delay and defects in multiple organ systems. Cell proliferation defects were observed in Snm1B/Apollo mutant mouse embryonic fibroblasts (MEFs) owing to high levels of telomeric end-to-end fusions. Deficiency of the nonhomologous end-joining (NHEJ) factor Ku70, but not p53, rescued the developmental defects and lethality observed in Snm1B/Apollo mutant mice as well as the impaired proliferation of Snm1B/Apollo-deficient MEFs. These findings demonstrate that SNM1B/Apollo is required to protect telomeres against NHEJ-mediated repair, which results in genomic instability and the consequent multi-organ developmental failure. Although Snm1B/Apollo-deficient MEFs exhibited high levels of apoptosis, abrogation of p53-dependent programmed cell death did not rescue the multi-organ developmental failure in the mice. PMID:20854421

Experimental Study of Fillets to Reduce Corner Effects in an Oblique Shock-Wave/Boundary Layer Interaction

NASA Technical Reports Server (NTRS)

Hirt, Stefanie M.

2015-01-01

A test was conducted in the 15 cm x 15 cm supersonic wind tunnel at NASA Glenn Research Center that focused on corner effects of an oblique shock-wave/boundary-layer interaction. In an attempt to control the interaction in the corner region, eight corner fillet configurations were tested. Three parameters were considered for the fillet configurations: the radius, the fillet length, and the taper length from the square corner to the fillet radius. Fillets effectively reduced the boundary-layer thickness in the corner; however, there was an associated penalty in the form of increased boundary-layer thickness at the tunnel centerline. Larger fillet radii caused greater reductions in boundary-layer thickness along the corner bisector. To a lesser, but measureable, extent, shorter fillet lengths resulted in thinner corner boundary layers. Overall, of the configurations tested, the largest radius resulted in the best combination of control in the corner, evidenced by a reduction in boundary-layer thickness, coupled with minimal impacts at the tunnel centerline.

Method for protecting chip corners in wet chemical etching of wafers

DOEpatents

Hui, Wing C.

1994-01-01

The present invention is a corner protection mask design that protects chip corners from undercutting during anisotropic etching of wafers. The corner protection masks abut the chip corner point and extend laterally from segments along one or both corner sides of the corner point, forming lateral extensions. The protection mask then extends from the lateral extensions, parallel to the direction of the corner side of the chip and parallel to scribe lines, thus conserving wafer space. Unmasked bomb regions strategically formed in the protection mask facilitate the break-up of the protection mask during etching. Corner protection masks are useful for chip patterns with deep grooves and either large or small chip mask areas. Auxiliary protection masks form nested concentric frames that etch from the center outward are useful for small chip mask patterns. The protection masks also form self-aligning chip mask areas. The present invention is advantageous for etching wafers with thin film windows, microfine and micromechanical structures, and for forming chip structures more elaborate than presently possible.

Method for protecting chip corners in wet chemical etching of wafers

DOEpatents

Hui, W.C.

1994-02-15

The present invention is a corner protection mask design that protects chip corners from undercutting during anisotropic etching of wafers. The corner protection masks abut the chip corner point and extend laterally from segments along one or both corner sides of the corner point, forming lateral extensions. The protection mask then extends from the lateral extensions, parallel to the direction of the corner side of the chip and parallel to scribe lines, thus conserving wafer space. Unmasked bomb regions strategically formed in the protection mask facilitate the break-up of the protection mask during etching. Corner protection masks are useful for chip patterns with deep grooves and either large or small chip mask areas. Auxiliary protection masks form nested concentric frames that etch from the center outward are useful for small chip mask patterns. The protection masks also form self-aligning chip mask areas. The present invention is advantageous for etching wafers with thin film windows, microfine and micromechanical structures, and for forming chip structures more elaborate than presently possible. 63 figures.

The generation of tire cornering forces in aircraft with a free-swiveling nose gear

NASA Technical Reports Server (NTRS)

Daugherty, R. H.; Stubbs, S. M.

1985-01-01

An experimental investigation was conducted to study the effect of various parameters on the cornering forces produced by a rolling aircraft tire installed on a tilted, free-swiveling nose gear. The parameters studied included tilt angle, trial, tire inflation pressure, rake angle, vertical load, and whether or not a twin tire configuration corotates. These parameters were evaluated by measuring the cornering force produced by an aircraft tire installed on the nose gear of a modified vehicle as it was towed slowly. Cornering force coefficient increased with increasing tilt angle. Increasing trial or rake angle decreased the magnitude of the cornering force coefficient. Tire inflation pressure had no effect on the cornering force coefficient. Increasing vertical load decreased the cornering force coefficient. When the tires of a twin tire system rotated independently, the cornering force coefficients were the same as those for the single-tire configuration. When the twin tire system was made to corotate, however, the cornering force coefficients increased significantly.

A study of the cornering forces generated by aircraft tires on a tilted, free-swiveling nose gear

NASA Technical Reports Server (NTRS)

Daugherty, R. H.; Stubbs, S. M.

1985-01-01

An experimental investigation was conducted to study the effect of various parameters on the cornering forces produced by a rolling aircraft tire installed on a tilted, free-swiveling nose gear. The parameters studied included tilt angle, trial, tire inflation pressure, rake angle, vertical load, and whether or not a twin tire configuration corotates. These parameters were evaluated by measuring the cornering force produced by an aircraft tire installed on the nose gear of a modified vehicle as it was towed slowly. Cornering force coefficient increased with increasing tilt angle. Increasing trial or rake angle decreased the magnitude of the cornering force coefficient. Tire inflation pressure had no effect on the cornering force coefficient. Increasing vertical load decreased the cornering force coefficient. When the tires of a twin tire system rotated independently, the cornering force coefficients were the same as those for the single-tire configuration. When the twin tire system was made to corotate, however, the cornering force coefficients increased significantly.

APOLLO_NG - a probabilistic interpretation of the APOLLO legacy for AVHRR heritage channels

NASA Astrophysics Data System (ADS)

Klüser, L.; Killius, N.; Gesell, G.

2015-10-01

The cloud processing scheme APOLLO (AVHRR Processing scheme Over cLouds, Land and Ocean) has been in use for cloud detection and cloud property retrieval since the late 1980s. The physics of the APOLLO scheme still build the backbone of a range of cloud detection algorithms for AVHRR (Advanced Very High Resolution Radiometer) heritage instruments. The APOLLO_NG (APOLLO_NextGeneration) cloud processing scheme is a probabilistic interpretation of the original APOLLO method. It builds upon the physical principles that have served well in the original APOLLO scheme. Nevertheless, a couple of additional variables have been introduced in APOLLO_NG. Cloud detection is no longer performed as a binary yes/no decision based on these physical principles. It is rather expressed as cloud probability for each satellite pixel. Consequently, the outcome of the algorithm can be tuned from being sure to reliably identify clear pixels to conditions of reliably identifying definitely cloudy pixels, depending on the purpose. The probabilistic approach allows retrieving not only the cloud properties (optical depth, effective radius, cloud top temperature and cloud water path) but also their uncertainties. APOLLO_NG is designed as a standalone cloud retrieval method robust enough for operational near-realtime use and for application to large amounts of historical satellite data. The radiative transfer solution is approximated by the same two-stream approach which also had been used for the original APOLLO. This allows the algorithm to be applied to a wide range of sensors without the necessity of sensor-specific tuning. Moreover it allows for online calculation of the radiative transfer (i.e., within the retrieval algorithm) giving rise to a detailed probabilistic treatment of cloud variables. This study presents the algorithm for cloud detection and cloud property retrieval together with the physical principles from the APOLLO legacy it is based on. Furthermore a couple of example results from NOAA-18 are presented.

APOLLO_NG - a probabilistic interpretation of the APOLLO legacy for AVHRR heritage channels

NASA Astrophysics Data System (ADS)

Klüser, L.; Killius, N.; Gesell, G.

2015-04-01

The cloud processing scheme APOLLO (Avhrr Processing scheme Over cLouds, Land and Ocean) has been in use for cloud detection and cloud property retrieval since the late 1980s. The physics of the APOLLO scheme still build the backbone of a range of cloud detection algorithms for AVHRR (Advanced Very High Resolution Radiometer) heritage instruments. The APOLLO_NG (APOLLO_NextGeneration) cloud processing scheme is a probabilistic interpretation of the original APOLLO method. While building upon the physical principles having served well in the original APOLLO a couple of additional variables have been introduced in APOLLO_NG. Cloud detection is not performed as a binary yes/no decision based on these physical principals but is expressed as cloud probability for each satellite pixel. Consequently the outcome of the algorithm can be tuned from clear confident to cloud confident depending on the purpose. The probabilistic approach allows to retrieving not only the cloud properties (optical depth, effective radius, cloud top temperature and cloud water path) but also their uncertainties. APOLLO_NG is designed as a standalone cloud retrieval method robust enough for operational near-realtime use and for the application with large amounts of historical satellite data. Thus the radiative transfer solution is approximated by the same two stream approach which also had been used for the original APOLLO. This allows the algorithm to be robust enough for being applied to a wide range of sensors without the necessity of sensor-specific tuning. Moreover it allows for online calculation of the radiative transfer (i.e. within the retrieval algorithm) giving rise to a detailed probabilistic treatment of cloud variables. This study presents the algorithm for cloud detection and cloud property retrieval together with the physical principles from the APOLLO legacy it is based on. Furthermore a couple of example results from on NOAA-18 are presented.

AGILE confirmation of gamma-ray activity from the IceCube-170922A error region

NASA Astrophysics Data System (ADS)

Lucarelli, F.; Piano, G.; Pittori, C.; Verrecchia, F.; Tavani, M.; Bulgarelli, A.; Munar-Adrover, P.; Minervini, G.; Ursi, A.; Vercellone, S.; Donnarumma, I.; Fioretti, V.; Zoli, A.; Striani, E.; Cardillo, M.; Gianotti, F.; Trifoglio, M.; Giuliani, A.; Mereghetti, S.; Caraveo, P.; Perotti, F.; Chen, A.; Argan, A.; Costa, E.; Del Monte, E.; Evangelista, Y.; Feroci, M.; Lazzarotto, F.; Lapshov, I.; Pacciani, L.; Soffitta, P.; Sabatini, S.; Vittorini, V.; Pucella, G.; Rapisarda, M.; Di Cocco, G.; Fuschino, F.; Galli, M.; Labanti, C.; Marisaldi, M.; Pellizzoni, A.; Pilia, M.; Trois, A.; Barbiellini, G.; Vallazza, E.; Longo, F.; Morselli, A.; Picozza, P.; Prest, M.; Lipari, P.; Zanello, D.; Cattaneo, P. W.; Rappoldi, A.; Colafrancesco, S.; Parmiggiani, N.; Ferrari, A.; Paoletti, F.; Antonelli, A.; Giommi, P.; Salotti, L.; Valentini, G.; D'Amico, F.

2017-09-01

Following the IceCube observation of a high-energy neutrino candidate event, IceCube-170922A, at T0 = 17/09/22 20:54:30.43 UT (https://gcn.gsfc.nasa.gov/gcn3/21916.gcn3), and the detection of increased gamma-ray activity from a previously known Fermi-LAT gamma-ray source (3FGL J0509.4+0541) in the IceCube-170922A error region (ATel #10791), we have analysed the AGILE-GRID data acquired in the days before and after the neutrino event T0, searching for significant gamma-ray excess above 100 MeV from a position compatible with the IceCube and Fermi-LAT error regions.

Expanding Access: An Evaluation of ReadCube Access as an ILL Alternative.

PubMed

Grabowsky, Adelia

2016-01-01

ReadCube Access is a patron-driven, document delivery system that provides immediate access to articles from journals owned by Nature Publishing Group. The purpose of this study was to evaluate the use of ReadCube Access as an interlibrary loan (ILL) alternative for nonsubscribed Nature journals at Auburn University, a research university with a School of Pharmacy and a School of Veterinary Medicine. An analysis of ten months' usage and costs are presented along with the results of a user satisfaction survey. Auburn University Libraries found ReadCube to be an acceptable alternative to ILL for unsubscribed Nature journals and at current levels of use and cost, consider ReadCube to be financially sustainable.

Constraining sterile neutrinos with AMANDA and IceCube atmospheric neutrino data

DOE Office of Scientific and Technical Information (OSTI.GOV)

Esmaili, Arman; Peres, O.L.G.; Halzen, Francis, E-mail: aesmaili@ifi.unicamp.br, E-mail: halzen@icecube.wisc.edu, E-mail: orlando@ifi.unicamp.br

2012-11-01

We demonstrate that atmospheric neutrino data accumulated with the AMANDA and the partially deployed IceCube experiments constrain the allowed parameter space for a hypothesized fourth sterile neutrino beyond the reach of a combined analysis of all other experiments, for Δm{sup 2}{sub 41}∼<1 eV{sup 2}. Although the IceCube data wins the statistics in the analysis, the advantage of a combined analysis of AMANDA and IceCube data is the partial remedy of yet unknown instrumental systematic uncertainties. We also illustrate the sensitivity of the completed IceCube detector, that is now taking data, to the parameter space of 3+1 model.

CubeSub

NASA Technical Reports Server (NTRS)

Slettebo, Christian; Jonsson, Lars Jonas

2016-01-01

This presentation introduces and discusses the development of the CubeSub submersible concept, an Autonomous Underwater Vehicle (AUV) designed around the CubeSat satellite form factor. The presented work is part of the author's MSc thesis in Aerospace Engineering at the Royal Institute of Technology, Stockholm, Sweden, and was performed during an internship at the Mission Design Division of the NASA Ames Research Center, Moffett Field, CA. Still in the early stages of its development, the CubeSub is to become a submersible test-bed for technology qualified for underwater and space environments. With the long-term goal of exploring the underwater environments in outer space, such as the alleged subsurface ocean of Jupiter's moon Europa, a number of technology and operational procedures must be developed and matured. To assist in this, the CubeSub platform is introduced as a tool to allow engineers and scientists to easily test qualified technology underwater. A CubeSat is a class of miniaturized satellite built to a standardized size. The base size is 1U (U for unit), corresponding to a 100 x 100 x 113.5 cu mm cube. A 1U CubeSat can in other words easily be held in one hand. Stacking units give larger satellite sizes such as the also commonly used 1.5U, 2U and 3U. The CubeSat standard is in itself already well established and hundreds of CubeSats have to date been launched into space. Compatible technology is readily available and the know-how exists in the space industry, all of which makes it a firm ground to stand on for the CubeSub. The rationale behind using the CubeSat form factor is to make use of this pre-existing foundation, making the CubeSub easy to develop, modular and readily available. It will thereby aid in the process of maturing the concept of a fully space qualified submersible headed for outer space. As a further clarification, the CubeSub is itself not meant for outer space, but to facilitate development of such a vessel. Along with its uses as a testbed, the CubeSub also holds the potential to become a useful tool for exploration and experimentation here on Earth. A highly standardized system utilizing well-known hardware can reduce the cost and required work load for researchers wishing to perform experiments and exploration. Users could design sensors and experiments to comply with the already well established CubeSat standard, which are then carried by the CubeSub to the region of interest. This in turn means that the end users can focus more on formulating the experiment itself and less about how to get it where they want it. The CubeSub is designed to be built up by modules, which can be assembled in different configurations to fulfill different needs. Each module will be powered individually and intermodular communication will be wireless, removing the need for wiring. The inside of the cylindrical hull will be flooded with ambient water to enhance the interaction between payloads and surrounding environment. The overall torpedo-like shape is similar to that of a conventional AUV, slender and smooth. This is to make for a low drag, reduce the risk of snagging on surrounding objects and make it possible to deploy through an ice sheet via a narrow borehole or navigate in tight areas. To keep costs low and further accelerate development, rapid prototyping is utilized wherever possible. Full-scale prototypes are being constructed through 3D-printing and using COTS (Commercial Off-The-Shelf) components. 3D-printing is used both for the largest hull components and the relatively small and delicate propellers. Arduino boards are used for control and internal communication

DOE Office of Scientific and Technical Information (OSTI.GOV)

Abercrombie, Robert Knox; Richardson, Gregory David; Scudiere, Matthew Bligh

A pad is disclosed for use in a weighing system for weighing a load. The pad includes a weighing platform, load cells, and foot members. Improvements to the pad reduce or substantially eliminate rotation of one or more of the corner foot members. A flexible foot strap disposed between the corner foot members reduces rotation of the respective foot members about vertical axes through the corner foot members and couples the corner foot members such that rotation of one corner foot member results in substantially the same amount of rotation of the other corner foot member. In a strapless variantmore » one or more fasteners prevents substantially all rotation of a foot member. In a diagonal variant, a foot strap extends between a corner foot member and the weighing platform to reduce rotation of the foot member about a vertical axis through the corner foot member.« less

Saturn Apollo Program

NASA Image and Video Library

1979-05-01

This montage depicts the flight crew patches for the manned Apollo 7 thru Apollo 17 missions. The Apollo 7 through 10 missions were basically manned test flights that paved the way for lunar landing missions. Primary objectives met included the demonstration of the Command Service Module (CSM) crew performance; crew/space vehicle/mission support facilities performance and testing during a manned CSM mission; CSM rendezvous capability; translunar injection demonstration; the first manned Apollo docking, the first Apollo Extra Vehicular Activity (EVA), performance of the first manned flight of the lunar module (LM); the CSM-LM docking in translunar trajectory, LM undocking in lunar orbit, LM staging in lunar orbit, and manned LM-CSM docking in lunar orbit. Apollo 11 through 17 were lunar landing missions with the exception of Apollo 13 which was forced to circle the moon without landing due to an onboard explosion. The craft was,however, able to return to Earth safely. Apollo 11 was the first manned lunar landing mission and performed the first lunar surface EVA. Landing site was the Sea of Tranquility. A message for mankind was delivered, the U.S. flag was planted, experiments were set up and 47 pounds of lunar surface material was collected for analysis back on Earth. Apollo 12, the 2nd manned lunar landing mission landed in the Ocean of Storms and retrieved parts of the unmanned Surveyor 3, which had landed on the Moon in April 1967. The Apollo Lunar Surface Experiments Package (ALSEP) was deployed, and 75 pounds of lunar material was gathered. Apollo 14, the 3rd lunar landing mission landed in Fra Mauro. ALSEP and other instruments were deployed, and 94 pounds of lunar materials were gathered, using a hand cart for first time to transport rocks. Apollo 15, the 4th lunar landing mission landed in the Hadley-Apennine region. With the first use of the Lunar Roving Vehicle (LRV), the crew was bale to gather 169 pounds of lunar material. Apollo 16, the 5th lunar landing mission, landed in the Descartes Highlands for the first study of highlands area. Selected surface experiments were deployed, the ultraviolet camera/spectrograph was used for first time on the Moon, and the LRV was used for second time for a collection of 213 pounds of lunar material. The Apollo program came to a close with Apollo 17, the 6th and final manned lunar landing mission that landed in the Taurus-Littrow highlands and valley area. This mission hosted the first scientist-astronaut, Schmitt, to land on the Moon. The 6th automated research station was set up, and 243 ponds of lunar material was gathered using the LRV.

Montage of Apollo Crew Patches

NASA Technical Reports Server (NTRS)

1979-01-01

This montage depicts the flight crew patches for the manned Apollo 7 thru Apollo 17 missions. The Apollo 7 through 10 missions were basically manned test flights that paved the way for lunar landing missions. Primary objectives met included the demonstration of the Command Service Module (CSM) crew performance; crew/space vehicle/mission support facilities performance and testing during a manned CSM mission; CSM rendezvous capability; translunar injection demonstration; the first manned Apollo docking, the first Apollo Extra Vehicular Activity (EVA), performance of the first manned flight of the lunar module (LM); the CSM-LM docking in translunar trajectory, LM undocking in lunar orbit, LM staging in lunar orbit, and manned LM-CSM docking in lunar orbit. Apollo 11 through 17 were lunar landing missions with the exception of Apollo 13 which was forced to circle the moon without landing due to an onboard explosion. The craft was,however, able to return to Earth safely. Apollo 11 was the first manned lunar landing mission and performed the first lunar surface EVA. Landing site was the Sea of Tranquility. A message for mankind was delivered, the U.S. flag was planted, experiments were set up and 47 pounds of lunar surface material was collected for analysis back on Earth. Apollo 12, the 2nd manned lunar landing mission landed in the Ocean of Storms and retrieved parts of the unmanned Surveyor 3, which had landed on the Moon in April 1967. The Apollo Lunar Surface Experiments Package (ALSEP) was deployed, and 75 pounds of lunar material was gathered. Apollo 14, the 3rd lunar landing mission landed in Fra Mauro. ALSEP and other instruments were deployed, and 94 pounds of lunar materials were gathered, using a hand cart for first time to transport rocks. Apollo 15, the 4th lunar landing mission landed in the Hadley-Apennine region. With the first use of the Lunar Roving Vehicle (LRV), the crew was bale to gather 169 pounds of lunar material. Apollo 16, the 5th lunar landing mission, landed in the Descartes Highlands for the first study of highlands area. Selected surface experiments were deployed, the ultraviolet camera/spectrograph was used for first time on the Moon, and the LRV was used for second time for a collection of 213 pounds of lunar material. The Apollo program came to a close with Apollo 17, the 6th and final manned lunar landing mission that landed in the Taurus-Littrow highlands and valley area. This mission hosted the first scientist-astronaut, Schmitt, to land on the Moon. The 6th automated research station was set up, and 243 ponds of lunar material was gathered using the LRV.

NPS CubeSat Launcher Design, Process and Requirements

DTIC Science & Technology

2009-06-01

Soviet era ICBM. The first Dnepr launch in July 2006 consisted of fourteen CubeSats in five P-PODs, while the second in April 2007 consisted of...Regulations (ITAR). ITAR restricts the export of defense-related products and technology on the United States Munitions List. Although one might not...think that CubeSat technology would fall under ITAR, in fact a large amount of Aerospace technology , including some that could be used on CubeSats is

The design and performance of IceCube DeepCore

NASA Astrophysics Data System (ADS)

Abbasi, R.; Abdou, Y.; Abu-Zayyad, T.; Ackermann, M.; Adams, J.; Aguilar, J. A.; Ahlers, M.; Allen, M. M.; Altmann, D.; Andeen, K.; Auffenberg, J.; Bai, X.; Baker, M.; Barwick, S. W.; Bay, R.; Bazo Alba, J. L.; Beattie, K.; Beatty, J. J.; Bechet, S.; Becker, J. K.; Becker, K.-H.; Benabderrahmane, M. L.; BenZvi, S.; Berdermann, J.; Berghaus, P.; Berley, D.; Bernardini, E.; Bertrand, D.; Besson, D. Z.; Bindig, D.; Bissok, M.; Blaufuss, E.; Blumenthal, J.; Boersma, D. J.; Bohm, C.; Bose, D.; Böser, S.; Botner, O.; Brown, A. M.; Buitink, S.; Caballero-Mora, K. S.; Carson, M.; Chirkin, D.; Christy, B.; Clevermann, F.; Cohen, S.; Colnard, C.; Cowen, D. F.; Cruz Silva, A. H.; D'Agostino, M. V.; Danninger, M.; Daughhetee, J.; Davis, J. C.; De Clercq, C.; Degner, T.; Demirörs, L.; Descamps, F.; Desiati, P.; de Vries-Uiterweerd, G.; DeYoung, T.; Díaz-Vélez, J. C.; Dierckxsens, M.; Dreyer, J.; Dumm, J. P.; Dunkman, M.; Eisch, J.; Ellsworth, R. W.; Engdegård, O.; Euler, S.; Evenson, P. A.; Fadiran, O.; Fazely, A. R.; Fedynitch, A.; Feintzeig, J.; Feusels, T.; Filimonov, K.; Finley, C.; Fischer-Wasels, T.; Fox, B. D.; Franckowiak, A.; Franke, R.; Gaisser, T. K.; Gallagher, J.; Gerhardt, L.; Gladstone, L.; Glüsenkamp, T.; Goldschmidt, A.; Goodman, J. A.; Góra, D.; Grant, D.; Griesel, T.; Groß, A.; Grullon, S.; Gurtner, M.; Ha, C.; Haj Ismail, A.; Hallgren, A.; Halzen, F.; Han, K.; Hanson, K.; Heinen, D.; Helbing, K.; Hellauer, R.; Hickford, S.; Hill, G. C.; Hoffman, K. D.; Hoffmann, B.; Homeier, A.; Hoshina, K.; Huelsnitz, W.; Hülß, J.-P.; Hulth, P. O.; Hultqvist, K.; Hussain, S.; Ishihara, A.; Jacobi, E.; Jacobsen, J.; Japaridze, G. S.; Johansson, H.; Kampert, K.-H.; Kappes, A.; Karg, T.; Karle, A.; Kenny, P.; Kiryluk, J.; Kislat, F.; Klein, S. R.; Köhne, J.-H.; Kohnen, G.; Kolanoski, H.; Köpke, L.; Koskinen, D. J.; Kowalski, M.; Kowarik, T.; Krasberg, M.; Kroll, G.; Kurahashi, N.; Kuwabara, T.; Labare, M.; Laihem, K.; Landsman, H.; Larson, M. J.; Lauer, R.; Lünemann, J.; Madsen, J.; Marotta, A.; Maruyama, R.; Mase, K.; Matis, H. S.; Meagher, K.; Merck, M.; Mészáros, P.; Meures, T.; Miarecki, S.; Middell, E.; Milke, N.; Miller, J.; Montaruli, T.; Morse, R.; Movit, S. M.; Nahnhauer, R.; Nam, J. W.; Naumann, U.; Nygren, D. R.; Odrowski, S.; Olivas, A.; Olivo, M.; O'Murchadha, A.; Panknin, S.; Paul, L.; Pérez de los Heros, C.; Petrovic, J.; Piegsa, A.; Pieloth, D.; Porrata, R.; Posselt, J.; Price, P. B.; Przybylski, G. T.; Rawlins, K.; Redl, P.; Resconi, E.; Rhode, W.; Ribordy, M.; Richman, M.; Rodrigues, J. P.; Rothmaier, F.; Rott, C.; Ruhe, T.; Rutledge, D.; Ruzybayev, B.; Ryckbosch, D.; Sander, H.-G.; Santander, M.; Sarkar, S.; Schatto, K.; Schmidt, T.; Schönwald, A.; Schukraft, A.; Schultes, A.; Schulz, O.; Schunck, M.; Seckel, D.; Semburg, B.; Seo, S. H.; Sestayo, Y.; Seunarine, S.; Silvestri, A.; Spiczak, G. M.; Spiering, C.; Stamatikos, M.; Stanev, T.; Stezelberger, T.; Stokstad, R. G.; Stößl, A.; Strahler, E. A.; Ström, R.; Stüer, M.; Sullivan, G. W.; Swillens, Q.; Taavola, H.; Taboada, I.; Tamburro, A.; Tepe, A.; Ter-Antonyan, S.; Tilav, S.; Toale, P. A.; Toscano, S.; Tosi, D.; van Eijndhoven, N.; Vandenbroucke, J.; Van Overloop, A.; van Santen, J.; Vehring, M.; Voge, M.; Walck, C.; Waldenmaier, T.; Wallraff, M.; Walter, M.; Weaver, Ch.; Wendt, C.; Westerhoff, S.; Whitehorn, N.; Wiebe, K.; Wiebusch, C. H.; Williams, D. R.; Wischnewski, R.; Wissing, H.; Wolf, M.; Wood, T. R.; Woschnagg, K.; Xu, C.; Xu, D. L.; Xu, X. W.; Yanez, J. P.; Yodh, G.; Yoshida, S.; Zarzhitsky, P.; Zoll, M.

2012-05-01

The IceCube neutrino observatory in operation at the South Pole, Antarctica, comprises three distinct components: a large buried array for ultrahigh energy neutrino detection, a surface air shower array, and a new buried component called DeepCore. DeepCore was designed to lower the IceCube neutrino energy threshold by over an order of magnitude, to energies as low as about 10 GeV. DeepCore is situated primarily 2100 m below the surface of the icecap at the South Pole, at the bottom center of the existing IceCube array, and began taking physics data in May 2010. Its location takes advantage of the exceptionally clear ice at those depths and allows it to use the surrounding IceCube detector as a highly efficient active veto against the principal background of downward-going muons produced in cosmic-ray air showers. DeepCore has a module density roughly five times higher than that of the standard IceCube array, and uses photomultiplier tubes with a new photocathode featuring a quantum efficiency about 35% higher than standard IceCube PMTs. Taken together, these features of DeepCore will increase IceCube's sensitivity to neutrinos from WIMP dark matter annihilations, atmospheric neutrino oscillations, galactic supernova neutrinos, and point sources of neutrinos in the northern and southern skies. In this paper we describe the design and initial performance of DeepCore.

The Design and Performance of IceCube DeepCore

NASA Technical Reports Server (NTRS)

Stamatikos, M.

2012-01-01

The IceCube neutrino observatory in operation at the South Pole, Antarctica, comprises three distinct components: a large buried array for ultrahigh energy neutrino detection, a surface air shower array, and a new buried component called DeepCore. DeepCore was designed to lower the IceCube neutrino energy threshold by over an order of magnitude, to energies as low as about 10 GeV. DeepCore is situated primarily 2100 m below the surface of the icecap at the South Pole, at the bottom center of the existing IceCube array, and began taking pbysics data in May 2010. Its location takes advantage of the exceptionally clear ice at those depths and allows it to use the surrounding IceCube detector as a highly efficient active veto against the principal background of downward-going muons produced in cosmic-ray air showers. DeepCore has a module density roughly five times higher than that of the standard IceCube array, and uses photomultiplier tubes with a new photocathode featuring a quantum efficiency about 35% higher than standard IceCube PMTs. Taken together, these features of DeepCore will increase IceCube's sensitivity to neutrinos from WIMP dark matter annihilations, atmospheric neutrino oscillations, galactic supernova neutrinos, and point sources of neutrinos in the northern and southern skies. In this paper we describe the design and initial performance of DeepCore.

EarthCube: A Community Organization for Geoscience Cyberinfrastructure

NASA Astrophysics Data System (ADS)

Patten, K.; Allison, M. L.

2014-12-01

The National Science Foundation's (NSF) EarthCube initiative is a community-driven approach to building cyberinfrastructure for managing, sharing, and exploring geoscience data and information to better address today's grand-challenge science questions. The EarthCube Test Enterprise Governance project is a two-year effort seeking to engage diverse geo- and cyber-science communities in applying a responsive approach to the development of a governing system for EarthCube. During Year 1, an Assembly of seven stakeholder groups representing the broad EarthCube community developed a draft Governance Framework. Finalized at the June 2014 EarthCube All Hands Meeting, this framework will be tested during the demonstration phase in Year 2, beginning October 2014. A brief overview of the framework: Community-elected members of the EarthCube Leadership Council will be responsible for managing strategic direction and identifying the scope of EarthCube. Three Standing Committees will also be established to oversee the development of technology and architecture, to coordinate among new and existing data facilities, and to represent the academic geosciences community in driving development of EarthCube cyberinfrastructure. An Engagement Team and a Liaison Team will support communication and partnerships with internal and external stakeholders, and a central Office will serve a logistical support function to the governance as a whole. Finally, ad hoc Working Groups and Special Interest Groups will take on other issues related to EarthCube's goals. The Year 2 demonstration phase will test the effectiveness of the proposed framework and allow for elements to be changed to better meet community needs. It will begin by populating committees and teams, and finalizing leadership and decision-making processes to move forward on community-selected priorities including identifying science drivers, coordinating emerging technical elements, and coming to convergence on system architecture. A January mid-year review will assemble these groups to analyze the effectiveness of the framework and make adjustments as necessary. If successful, this framework will move EarthCube forward as a collaborative platform and potentially act as a model for future NSF investments in geoscience cyberinfrastructure.

Apollo 1 Lessons Learned Show

NASA Image and Video Library

2017-01-27

John Tribe, retired, Apollo 1 Reaction and Control System lead engineer, answers questions during the Apollo 1 Lessons Learned event in the Training Auditorium at NASA’s Kennedy Space Center in Florida. The theme of the presentation was "To There and Back Again." The event helped pay tribute to the Apollo 1 crew, Gus Grissom, Ed White II, and Roger Chaffee.

Vertical view Apollo 16 Descartes landing sites as photographed by Apollo 14

NASA Technical Reports Server (NTRS)

1972-01-01

An almost vertical view of the Apollo 16 Descartes landing sites as photographed from the Apollo 14 spacecraft. Overlays are provided to point out extravehicular activity (EVA), Lunar Roving Vehicle (LRV) travers routes and the nicknames of features. The Roman numerals indicate the EVA numbers and the Arabic numbers point out stations or traverse stops.

Apollo Project

NASA Image and Video Library

2012-09-07

Image L61-8036 is available as an electronic file from the photo lab. See URL. -- Photographed on 12/05/1961. -- Multiple exposure of an impact test of the Apollo command module. In this test the Apollo capsule was tested making a sand landing. -- Published in James R. Hansen, Spaceflight Revolution: NASA Langley Research Center From Sputnik to Apollo, (Washington: NASA, 1995), pp. 361-366.

Apollo 11: A good ending to a bad decade

NASA Technical Reports Server (NTRS)

1979-01-01

The Gemini program and the Apollo program which culminated in landing a man on the moon and safely returning him to earth are highlighted. The space program in the aftermath of Apollo 11 is briefly summarized, including: Skylab, Apollo Soyuz, Mars and Venus probes, improved world communications, remote sensing of world resources, and finally, space shuttle.

Apollo 1 Lessons Learned Show

NASA Image and Video Library

2017-01-27

Ernie Reyes, retired, former Apollo 1 senior operations manager, signs a book for a worker after the Apollo 1 Lessons Learned presentation in the Training Auditorium at NASA's Kennedy Space Center in Florida. The theme of the program was "To there and Back Again." The event helped pay tribute to the Apollo 1 crew, Gus Grissom, Ed White II, and Roger Chaffee.

KSC-99pp0859

NASA Image and Video Library

1999-07-16

KENNEDY SPACE CENTER, FLA. -- Former Apollo astronaut Gene Cernan makes a point during a presentation at the Apollo 11 anniversary banquet honoring the Apollo team, the people who made the entire lunar landing program possible. The banquet was held in the Apollo/Saturn V Center, part of the KSC Visitor Complex. This is the 30th anniversary of the Apollo 11 launch and moon landing, July 16 and July 20, 1969. Cernan appeared with other former astronauts Neil Armstrong, the first man to walk on the moon; Edwin "Buzz" Aldrin; Walt Cunningham; and others

APOLLO XII - LAUNCH DAY ACTIVITIES - LAUNCH COMPLEX 39A - KSC

NASA Image and Video Library

1969-11-14

S69-58880 (14 Nov. 1969) --- Astronaut Alan L. Bean, Apollo 12 lunar module pilot, suits up in the Kennedy Space Center's (KSC) Manned Spacecraft Operations Building during the Apollo 12 prelaunch countdown. Minutes later astronauts Bean; Charles Conrad Jr., commander; and Richard F. Gordon Jr., command module pilot, rode a special transport van over to Pad A, Launch Complex 39, where their spacecraft awaited. The Apollo 12 liftoff occurred at 11:22 a.m. (EST), Nov. 14, 1969. Apollo 12 is the United States' second lunar landing mission.

Lightning around the Apollo 15 stack prior to launch

NASA Image and Video Library

1971-07-25

S89-41564 (25 July 1971) --- Lightning streaks through the sky around the Apollo 15 stack of hardware prior to the Apollo 15 launch. The huge 363-feet tall Apollo 15 (Spacecraft 112/Lunar Module 10/Saturn 510) space vehicle is scheduled to launch from Pad A, Launch Complex 39, at 9:34:00:79 p.m. (EDT) on July 26, 1971. The prime crewmembers for the Apollo 15 mission are astronauts David R. Scott, commander; James B. Irwin, lunar module pilot; and Alfred M. Worden, command module pilot.

INFLIGHT - APOLLO 10 (CREW ACTIVITIES)

NASA Image and Video Library

1969-05-20

S69-34313 (20 May 1969) --- Astronaut Eugene A. Cernan is shown spinning a water bag to demonstrate the collection of hydrogen bubbles in this color reproduction taken from the fifth telecast made by the color television camera aboard the Apollo 10 spacecraft. When this picture was made the Apollo 10 spacecraft was approximately 175,300 nautical miles from Earth, and only 43,650 nautical miles from the moon. Cernan is the Apollo 10 lunar module pilot. Also, aboard Apollo 10 were astronauts Thomas P. Stafford, commander; and John W. Young, command module pilot.

KSC-2012-6140

NASA Image and Video Library

2012-11-03

CAPE CANAVERAL, Fla. – The Astronaut Scholarship Foundation hosts a dinner at the Radisson Resort at the Port in Cape Canaveral celebrating the 40th anniversary of Apollo 17. An auction of space-related memorabilia was held with proceeds supporting college scholarships for students who exhibit imagination and exceptional performance in science, technology, engineering and math. The gala commemorating the anniversary of Apollo 17 included mission commander Eugene Cernan and other astronauts who flew Apollo missions. Launched Dec. 7, 1972, Cernan and lunar module pilot Harrison Schmitt landed in the moon's Taurus-Littrow highlands while command module pilot Ronald Evans remained in lunar orbit operating a scientific instrument module. For more information, visit http://www-pao.ksc.nasa.gov/history/apollo/apollo-17/apollo-17.htm Photo credit: NASA/Kim Shiflett

SpaceCube Mini

NASA Technical Reports Server (NTRS)

Lin, Michael; Petrick, David; Geist, Alessandro; Flatley, Thomas

2012-01-01

This version of the SpaceCube will be a full-fledged, onboard space processing system capable of 2500+ MIPS, and featuring a number of plug-andplay gigabit and standard interfaces, all in a condensed 3x3x3 form factor [less than 10 watts and less than 3 lb (approximately equal to 1.4 kg)]. The main processing engine is the Xilinx SIRF radiation- hardened-by-design Virtex-5 FX-130T field-programmable gate array (FPGA). Even as the SpaceCube 2.0 version (currently under test) is being targeted as the platform of choice for a number of the upcoming Earth Science Decadal Survey missions, GSFC has been contacted by customers who wish to see a system that incorporates key features of the version 2.0 architecture in an even smaller form factor. In order to fulfill that need, the SpaceCube Mini is being designed, and will be a very compact and low-power system. A similar flight system with this combination of small size, low power, low cost, adaptability, and extremely high processing power does not otherwise exist, and the SpaceCube Mini will be of tremendous benefit to GSFC and its partners. The SpaceCube Mini will utilize space-grade components. The primary processing engine of the Mini is the Xilinx Virtex-5 SIRF FX-130T radiation-hardened-by-design FPGA for critical flight applications in high-radiation environments. The Mini can also be equipped with a commercial Xilinx Virtex-5 FPGA with integrated PowerPCs for a low-cost, high-power computing platform for use in the relatively radiation- benign LEOs (low-Earth orbits). In either case, this version of the Space-Cube will weigh less than 3 pounds (.1.4 kg), conform to the CubeSat form-factor (10x10x10 cm), and will be low power (less than 10 watts for typical applications). The SpaceCube Mini will have a radiation-hardened Aeroflex FPGA for configuring and scrubbing the Xilinx FPGA by utilizing the onboard FLASH memory to store the configuration files. The FLASH memory will also be used for storing algorithm and application code for the PowerPCs and the Xilinx FPGA. In addition, it will feature highspeed DDR SDRAM (double data rate synchronous dynamic random-access memory) to store the instructions and data of active applications. This version will also feature SATA-II and Gigabit Ethernet interfaces. Furthermore, there will also be general-purpose, multi-gigabit interfaces. In addition, the system will have dozens of transceivers that can support LVDS (low-voltage differential signaling), RS-422, or SpaceWire. The SpaceCube Mini includes an I/O card that can be customized to meet the needs of each mission. This version of the SpaceCube will be designed so that multiple Minis can be networked together using SpaceWire, Ethernet, or even a custom protocol. Scalability can be provided by networking multiple SpaceCube Minis together. Rigid-Flex technology is being targeted for the construction of the SpaceCube Mini, which will make the extremely compact and low-weight design feasible. The SpaceCube Mini is designed to fit in the compact CubeSat form factor, thus allowing deployment in a new class of missions that the previous SpaceCube versions were not suited for. At the time of this reporting, engineering units should be available in the summer 2012.

ELaNa - Educational Launch of Nanosatellite Enhance Education Through Space Flight

NASA Technical Reports Server (NTRS)

Skrobot, Garrett Lee

2011-01-01

One of NASA's missions is to attract and retain students in the science, technology, engineering and mathematics (STEM) disciplines. Creating missions or programs to achieve this important goal helps strengthen NASA and the nation's future work force as well as engage and inspire Americans and the rest of the world. During the last three years, in an attempt to revitalize educational space flight, NASA generated a new and exciting initiative. This initiative, NASA's Educational Launch of Nanosatellite (ELaNa), is now fully operational and producing exciting results. Nanosatellites are small secondary satellite payloads called CubeSats. One of the challenges that the CubeSat community faced over the past few years was the lack of rides into space. Students were building CubeSats but they just sat on the shelf until an opportunity arose. In some cases, these opportunities never developed and so the CubeSat never made it to orbit. The ELaNa initiative is changing this by providing sustainable launch opportunities for educational CubeSats. Across America, these CubeSats are currently being built by students in high school all the way through graduate school. Now students know that if they build their CubeSat, submit their proposal and are selected for an ELaNa mission, they will have the opportunity to fly their satellite. ELaNa missions are the first educational cargo to be carried on expendable launch vehicles (ELY) for NASA's Launch Services Program (LSP). The first ELaNa CubeSats were slated to begin their journey to orbit in February 2011 with NASA's Glory mission. Due to an anomaly with the launch vehicle, ELaNa II and Glory failed to reach orbit. This first ELaNa mission was comprised of three IU CubeSats built by students at Montana State University (Explorer Prime Flight 1), the University of Colorado (HERMES), and Kentucky Space, a consortium of state universities (KySat). The interface between the launch vehicle and the CubeSat, the Poly-Picosatellite Orbital Deployer (P-POD), was developed and built by students at California Polytechnic State University (Cal Poly). Integrating a P-POD on a NASA ELV was not an easy task. The creation of new processes and requirements as well as numerous reviews and approvals were necessary within NASA before the first ELaNa mission could be attached to a NASA launch vehicle (LV). One of the key objectives placed on an ELaNa mission is that the CubeSat and PPOD does not increase the baseline risk to the primary mission and launch vehicle. The ELaNa missions achieve this objective by placing a rigorous management and engineering process on both the LV and CubeSat teams. So, what is the future of ELaNa? Currently there are 16 P-POD missions manifested across four launch vehicles to support educational CubeSats selected under the NASA CubeSat Initiative. From this initiative, a rigorous selection process produced 22-student CubeSat missions that are scheduled to fly before the end of 2012. For the initiative to continue, organizations need to submit proposals to the annual CubeSat initiative call so they have the opportunity to be manifested and launched.

Three-dimensional construction and omni-directional rolling analysis of a novel frame-like lattice modular robot

NASA Astrophysics Data System (ADS)

Ding, Wan; Wu, Jianxu; Yao, Yan'an

2015-07-01

Lattice modular robots possess diversity actuation methods, such as electric telescopic rod, gear rack, magnet, robot arm, etc. The researches on lattice modular robots mainly focus on their hardware descriptions and reconfiguration algorithms. Meanwhile, their design architectures and actuation methods perform slow telescopic and moving speeds, relative low actuation force verse weight ratio, and without internal space to carry objects. To improve the mechanical performance and reveal the locomotion and reconfiguration binary essences of the lattice modular robots, a novel cube-shaped, frame-like, pneumatic-based reconfigurable robot module called pneumatic expandable cube(PE-Cube) is proposed. The three-dimensional(3D) expanding construction and omni-directional rolling analysis of the constructed robots are the main focuses. The PE-Cube with three degrees of freedom(DoFs) is assembled by replacing the twelve edges of a cube with pneumatic cylinders. The proposed symmetric construction condition makes the constructed robots possess the same properties in each supporting state, and a binary control strategy cooperated with binary actuator(pneumatic cylinder) is directly adopted to control the PE-Cube. Taking an eight PE-Cube modules' construction as example, its dynamic rolling simulation, static rolling condition, and turning gait are illustrated and discussed. To testify telescopic synchronization, respond speed, locomotion feasibility, and repeatability and reliability of hardware system, an experimental pneumatic-based robotic system is built and the rolling and turning experiments of the eight PE-Cube modules' construction are carried out. As an extension, the locomotion feasibility of a thirty-two PE-Cube modules' construction is analyzed and proved, including dynamic rolling simulation, static rolling condition, and dynamic analysis in free tipping process. The proposed PE-Cube module, construction method, and locomotion analysis enrich the family of the lattice modular robot and provide the instruction to design the lattice modular robot.

PolarCube: A High Resolution Passive Microwave Satellite for Sounding and Imaging at 118 GHz

NASA Astrophysics Data System (ADS)

Weaver, R. L.; Gallaher, D. W.; Gasiewski, A. J.; Sanders, B.; Periasamy, L.; Hwang, K.; Alvarenga, G.; Hickey, A. M.

2013-12-01

PolarCube is a 3U CubeSat hosting an eight-channel passive microwave spectrometer operating at the 118.7503 GHz oxygen resonance that is currently in development. The project has an anticipated launch date in early 2015. It is currently being designed to operate for approximately12 months on orbit to provide the first global 118-GHz spectral imagery of the Earth over full seasonal cycle and to sound Arctic vertical temperature structure. The principles used by PolarCube for temperature sounding are well established in number of peer-reviewed papers going back more than two decades, although the potential for sounding from a CubeSat has never before been demonstrated in space. The PolarCube channels are selected to probe atmospheric emission over a range of vertical levels from the surface to lower stratosphere. This capability has been available operationally for over three decades, but at lower frequencies and higher altitudes that do not provide the spatial resolution that will be achieved by PolarCube. While the NASA JPSS ATMS satellite sensor provides global coverage at ~32 km resolution, the PolarCube will improve on this resolution by a factor of two, thus facilitating the primary science goal of determining sea ice concentration and extent while at the same time collecting profile data on atmospheric temperature. Additionally, we seek to correlate freeze-thaw line data from SMAP with our near simultaneously collected atmospheric temperature data. In addition to polar science, PolarCube will provide a first demonstration of a very low cost passive microwave sounder that if operated in a fleet configuration would have the potential to fulfill the goals of the Precipitation Atmospheric Temperature and Humidity (PATH) mission, as defined in the NRC Decadal Survey. PolarCube 118-GHz passive microwave spectrometer in deployed configuration

Neutrino Astronomy with IceCube

NASA Astrophysics Data System (ADS)

Meagher, Kevin J.

The IceCube Neutrino Observatory is a cubic kilometer neutrino telescope located at the Geographic South Pole. Cherenkov radiation emitted by charged secondary particles from neutrino interactions is observed by IceCube using an array of 5160 photomultiplier tubes embedded between a depth of 1.5 km to 2.5 km in the Antarctic glacial ice. The detection of astrophysical neutrinos is a primary goal of IceCube and has now been realized with the discovery of a diffuse, high-energy flux consisting of neutrino events from tens of TeV up to several PeV. Many analyses have been performed to identify the source of these neutrinos: correlations with active galactic nuclei, gamma-ray bursts, and the galactic plane. IceCube also conducts multi-messenger campaigns to alert other observatories of possible neutrino transients in real-time. However, the source of these neutrinos remains elusive as no corresponding electromagnetic counterparts have been identified. This proceeding will give an overview of the detection principles of IceCube, the properties of the observed astrophysical neutrinos, the search for corresponding sources (including real-time searches), and plans for a next-generation neutrino detector, IceCube-Gen2.

Laser geodynamic satellite thermal/optical/vibrational analysis and testing, volume 2, book 2. [cubes and far fields

NASA Technical Reports Server (NTRS)

1975-01-01

The main tasks described involved an interferometric evaluation of several cubes, a prediction of their dihedral angles, a comparison of these predictions with independent measurements, a prediction and comparison of far field performance, recommendations as to revised dihedral angles and a subsequent analysis of cubes which were reworked to confirm the recommendations. A tolerance study and theoretical evaluation of several cubes was also performed to aid in understanding the results. The far field characteristics evaluated included polarization effects and treated both intensity distribution and encircled energy data. The energy in the 13.2 - 16.9 arc-sec annular region was tabulated as an indicator of performance sensitivity. The results are provided in viewgraph form, and show the average dihedral angle of an original set of test cubes to have been 1.8 arc-sec with an average far field annulus diameter of 18 arc-sec. Since the peak energy in the 13.2 - 16.9 arc-sec annulus was found to occur for a 1.35 arc-sec cube, and since cube tolerances were shown to increase the annulus diameter slightly, a nominal dihedral angle of 1.25 arc-sec was recommended.

CUBE: Information-optimized parallel cosmological N-body simulation code

NASA Astrophysics Data System (ADS)

Yu, Hao-Ran; Pen, Ue-Li; Wang, Xin

2018-05-01

CUBE, written in Coarray Fortran, is a particle-mesh based parallel cosmological N-body simulation code. The memory usage of CUBE can approach as low as 6 bytes per particle. Particle pairwise (PP) force, cosmological neutrinos, spherical overdensity (SO) halofinder are included.

Evaluation of the Impact of an Additive Manufacturing Enhanced CubeSat Architecture on the CubeSat Development Process

DTIC Science & Technology

2016-09-15

Investigative Questions This research will quantitatively address the impact of proposed benefits of a 3D printed satellite architecture on the...subsystems of a CubeSat. The objective of this research is to bring a quantitative analysis to the discussion of whether a fully 3D printed satellite...manufacturers to quantitatively address what impact the architecture would have on the subsystems of a CubeSat. Summary of Research Gap, Research Questions, and

Force Limited Vibration Testing and Subsequent Redesign of the Naval Postgraduate School CubeSat Launcher

DTIC Science & Technology

2014-06-01

release is controlled by a non-explosive actuator (NEA). Once the NEA is actuated, it releases the P-POD door, which springs open due to torsion ...deemed to be undesirable to OSL as it limited flexibility in final CubeSat position choices on NPSCuL. 24 Building on the lessons learned from the...OUTSat mission that included maintaining flexibility of CubeSat positions on NPSCuL, it was decided that the option to proto-qualify a CubeSat on the

Ground Demonstration on the Autonomous Docking of Two 3U CubeSats Using a Novel Permanent-Magnet Docking Mechanism

NASA Technical Reports Server (NTRS)

Pei, Jing; Murchison, Luke; BenShabat, Adam; Stewart, Victor; Rosenthal, James; Follman, Jacob; Branchy, Mark; Sellers, Drew; Elandt, Ryan; Elliott, Sawyer;

Apollo Mission Techniques Lunar Orbit Activities - Part 1a

NASA Technical Reports Server (NTRS)

Interbartolo, Michael A.

2009-01-01

This slide presentation reviews the planned sequence of events and the rationale for all lunar missions, and the flight experiences and lessons learned for the lunar orbit activities from a trajectory perspective. Shown are trajectories which include the moon's position at the various stages in the complete trip from launch, to the return and reentry. Included in the presentation are objectives and the sequence of events,for the Apollo 8, and Apollo 10. This is followed by a discussion of Apollo 11, including: the primary mission objective, the sequence of events, and the flight experience. The next mission discussed was Apollo 12. It reviews the objectives, the ground tracking, procedure changes, and the sequence of events. The aborted Apollo 13 mission is reviewed, including the objectives, and the sequence of events. Brief summaries of the flight experiences for Apollo 14-16 are reviewed. The flight sequence of events of Apollo 17 are discussed. In summary each mission consistently performing precision landings required that Apollo lunar orbit activities devote considerable attention to: (1) Improving fidelity of lunar gravity models, (2) Maximizing availability of ground tracking, (3) Minimizing perturbations on the trajectory, (4) Maximizing LM propellant reserves for hover time. Also the use of radial separation maneuvers (1) allows passive re-rendezvous after each rev, but ... (2) sensitive to small dispersions in initial sep direction

The telomeric protein SNM1B/Apollo is required for normal cell proliferation and embryonic development.

PubMed

Akhter, Shamima; Lam, Yung C; Chang, Sandy; Legerski, Randy J

2010-12-01

Conserved metallo β-Lactamase and β-CASP (CPSF-Artemis-Snm1-Pso2) domain nuclease family member SNM1B/Apollo is a shelterin-associated protein that localizes to telomeres through its interaction with TRF2. To study its in vivo role, we generated a knockout of SNM1B/Apollo in a mouse model. Snm1B/Apollo homozygous null mice die at birth with developmental delay and defects in multiple organ systems. Cell proliferation defects were observed in Snm1B/Apollo mutant mouse embryonic fibroblasts (MEFs) owing to high levels of telomeric end-to-end fusions. Deficiency of the nonhomologous end-joining (NHEJ) factor Ku70, but not p53, rescued the developmental defects and lethality observed in Snm1B/Apollo mutant mice as well as the impaired proliferation of Snm1B/Apollo-deficient MEFs. These findings demonstrate that SNM1B/Apollo is required to protect telomeres against NHEJ-mediated repair, which results in genomic instability and the consequent multi-organ developmental failure. Although Snm1B/Apollo-deficient MEFs exhibited high levels of apoptosis, abrogation of p53-dependent programmed cell death did not rescue the multi-organ developmental failure in the mice. © 2010 The Authors. Aging Cell © 2010 Blackwell Publishing Ltd/Anatomical Society of Great Britain and Ireland.

Astronaut Vance Brand seen in hatchway leading to Apollo Docking module

NASA Technical Reports Server (NTRS)

1975-01-01

Astronaut Vance D. Brand, command module pilot of the American Apollo Soyuz Test Project (ASTP) crew, is seen in the hatchway leading from the Apollo Command Module (CM) into the Apollo Docking Module (DM) during joint U.S.-USSR ASTP docking in Earth orbit mission. The 35mm camera is looking from the DM into the CM.

Air and Space Museum Apollo 40th Celebration

NASA Image and Video Library

2009-07-19

Guest, front row from right, U.S. Senator Bill Nelson (D-FL), Apollo 11 Command Module Pilot Michael Collins, U.S. Congresswoman Gabrielle Giffords (D-AZ), and Apollo 11 Lunar Module Pilot Buzz Aldrin, listen during the Apollo 40th anniversary celebration held at the National Air and Space Museum, Monday, July 20, 2009 in Washington. Photo Credit: (NASA/Bill Ingalls)

APOLLO XIII CREW - MISSION OPERATIONS CONTROL ROOM (MOCR) - APOLLO XII - LUNAR EXTRAVEHICULAR ACTIVITY (EVA) - MSC

NASA Image and Video Library

1969-11-21

S69-59525 (19 Nov. 1969) --- Overall view of activity in the Mission Operations Control Room (MOCR) in the Mission Control Center (MCC), Building 30, during the Apollo 12 lunar landing mission. When this picture was made the first Apollo 12 extravehicular activity (EVA) was being televised from the surface of the moon. Photo credit: NASA

Exploring the Moon: A Teacher's Guide with Activities for Earth and Space Sciences.

ERIC Educational Resources Information Center

National Aeronautics and Space Administration, Washington, DC.

This educational guide concerns exploring the moon. Activities are divided into three units: Pre-Apollo, Learning from Apollo, and The Future. These correspond, at least roughly, to exercises that can be done before the Lunar Sample Disk (available from NASA) arrives to the school (Pre-Apollo), while it is there (Learning from Apollo), and after…

President Obama Meets with Crew of Apollo 11

NASA Image and Video Library

2014-07-22

President Barack Obama meets with Apollo 11 astronauts Michael Collins, seated left, Buzz Aldrin, center, Carol Armstrong, widow of Apollo 11 commander, Neil Armstrong, and NASA Administrator Charles Bolden, Tuesday, July 22, 2014, in the Oval Office of the White House in Washington, during the 45th anniversary week of the Apollo 11 lunar landing. Photo Credit: (NASA/Bill Ingalls)

KSC-2011-1310

NASA Image and Video Library

2011-01-29

CAPE CANAVERAL, Fla. -- Command module pilot of Apollo 9 and commander of Apollo 15 David Scott talks to attendees of the Apollo 14 Anniversary Soirée at the Kennedy Space Center Visitor Complex's Saturn V Center. The celebration was hosted by the Astronaut Scholarship Foundation. Apollo 14 landed on the lunar surface 40 years ago on Feb. 5, 1971. Photo credit: NASA/Kim Shiflett

KSC-2011-1314

NASA Image and Video Library

2011-01-29

CAPE CANAVERAL, Fla. -- Command module pilot of Apollo 9 and commander of Apollo 15 David Scott talks to attendees of the Apollo 14 Anniversary Soirée at the Kennedy Space Center Visitor Complex's Saturn V Center. The celebration was hosted by the Astronaut Scholarship Foundation. Apollo 14 landed on the lunar surface 40 years ago on Feb. 5, 1971. Photo credit: NASA/Kim Shiflett

Astronaut Eugene Cernan sleeping aboard Apollo 17 spacecraft

NASA Image and Video Library

1972-12-17

AS17-162-24049 (7-19 Dec. 1972) --- A fellow crewman took this picture of astronaut Eugene A. Cernan dozing aboard the Apollo 17 spacecraft during the final lunar landing mission in NASA's Apollo program. Also, aboard Apollo 17 were astronaut Ronald E. Evans, command module pilot, and scientist-astronaut Harrison H. "Jack" Schmitt, lunar module pilot. Cernan was the mission commander.

President Nixon on deck of U.S.S. Hornet awaiting Apollo 11 crew arrival

NASA Image and Video Library

1969-07-24

S69-21736 (24 July 1969) --- President Richard M. Nixon photographed on the deck of the USS Hornet, prime recovery ship for the Apollo 11 lunar landing mission, awaiting the Apollo 11 crew arrival. Apollo 11 splashed down at 11:40 a.m. (EDT), July 24, 1969, about 812 nautical miles southwest of Hawaii.

Apollo 17 Mission Report

NASA Technical Reports Server (NTRS)

1973-01-01

Operational and engineering aspects of the Apollo 17 mission are outlined. The vehicle configuration was similar to those of Apollo 15 and 16. There were significant differences in the science payload for Apollo 17 and spacecraft hardware differences and experiment equipment are described. The mission achieved a landing in the Taurus-Littrow region of the moon and returned samples of the pre-Imbrium highlands and young craters.

Apollo experience report: Battery subsystem

NASA Technical Reports Server (NTRS)

Trout, J. B.

1972-01-01

Experience with the Apollo command service module and lunar module batteries is discussed. Significant hardware development concepts and hardware test results are summarized, and the operational performance of batteries on the Apollo 7 to 13 missions is discussed in terms of performance data, mission constraints, and basic hardware design and capability. Also, the flight performance of the Apollo battery charger is discussed. Inflight data are presented.

SNMIB/Apollo protects leading-strand telomeres against NHEJ-mediated repair.

PubMed

Lam, Yung C; Akhter, Shamima; Gu, Peili; Ye, Jing; Poulet, Anaïs; Giraud-Panis, Marie-Josèphe; Bailey, Susan M; Gilson, Eric; Legerski, Randy J; Chang, Sandy

2010-07-07

Progressive telomere attrition or deficiency of the protective shelterin complex elicits a DNA damage response as a result of a cell's inability to distinguish dysfunctional telomeric ends from DNA double-strand breaks. SNMIB/Apollo is a shelterin-associated protein and a member of the SMN1/PSO2 nuclease family that localizes to telomeres through its interaction with TRF2. Here, we generated SNMIB/Apollo knockout mouse embryo fibroblasts (MEFs) to probe the function of SNMIB/Apollo at mammalian telomeres. SNMIB/Apollo null MEFs exhibit an increased incidence of G2 chromatid-type fusions involving telomeres created by leading-strand DNA synthesis, reflective of a failure to protect these telomeres after DNA replication. Mutations within SNMIB/Apollo's conserved nuclease domain failed to suppress this phenotype, suggesting that its nuclease activity is required to protect leading-strand telomeres. SNMIB/Apollo(-/-)ATM(-/-) MEFs display robust telomere fusions when Trf2 is depleted, indicating that ATM is dispensable for repair of uncapped telomeres in this setting. Our data implicate the 5'-3' exonuclease function of SNM1B/Apollo in the generation of 3' single-stranded overhangs at newly replicated leading-strand telomeres to protect them from engaging the non-homologous end-joining pathway.

KSC-2014-3249

NASA Image and Video Library

2014-07-21

CAPE CANAVERAL, Fla. -- Apollo astronauts and their families receive a briefing in one of the remodeled firing rooms in the Launch Control Center at NASA's Kennedy Space Center in Florida. The facility's firing rooms were used to conduct the Saturn V countdowns during the Apollo Program. The tour followed a ceremony renaming the refurbished Operations and Checkout Building for Apollo 11 astronaut Neil Armstrong, the first person to set foot on the moon. Second from left is Apollo 11 moonwalker Buzz Aldrin and former astronaut Jim Lovell, a member of the Apollo 8 and Apollo 13 crews, standing next to him, at center. The ceremony was part of NASA's 45th anniversary celebration of the Apollo 11 moon landing. As the world watched, Neil Armstrong and Buzz Aldrin landed in the moon's Sea of Tranquility on July 20, 1969, aboard the lunar module Eagle. Meanwhile, crewmate Michael Collins orbited above in the command module Columbia. For more, visit http://www.nasa.gov/press/2014/july/nasa-honors-historic-first-moon-landing-eyes-first-mars-mission. Photo credit: NASA/Kim Shiflett

PDS Lunar Data Node Restoration of Apollo In-Situ Surface Data

NASA Technical Reports Server (NTRS)

Williams, David R.; Hills, H. Kent; Guinness, Edward A.; Lowman, Paul D.; Taylor, Patrick T.

2010-01-01

The Apollo missions between 1969 and 1972 deployed scientific instruments on the Moon's surface which made in-situ measurements of the lunar environment. Apollo II had the short-term Early Apollo Surface Experiments Package (EASEP) and Apollos 12, 14, 15, 16, and 17 each set up an Apollo Lunar Surface Experiments Package (ALSEP). Each ALSEP package contained a different suite of instruments which took measurements and radioed the results back to Earth over periods from 5 to 7 years until they were turned off on 30 September 1977. To this day the ALSEP data remain the only long-term in-situ information on the Moon's surface environment. The Lunar Data Node (LDN) has been formed under the auspices of the Planetary Data System (PDS) Geosciences Node to put relevant, scientifically important Apollo data into accessible digital form for use by researchers and mission planners. We will report on progress made since last year and plans for future data restorations.

Teaching Chemistry Using From the Earth to the Moon

NASA Astrophysics Data System (ADS)

Goll, James G.; Mundinger, Stacie L.

2003-03-01

The space program and media based on it have provided fascinating examples that can be used to expore chemical principles. The HBO series From the Earth to the Moon and a documentary Moonshot provide examples for teaching chemical principles from the Apollo missions. A docking problem between two spacecrafts occurred during the Apollo 14 mission. This situation can be used to discuss the conditions necessary for a chemical reaction. A catastrophic fire on Apollo 1 can be used to illustrate the influence of different conditions on the rate of a reaction. Lightning striking Apollo 12 during liftoff showed the consequence of adding ions to solution. The landing of Apollo 12, which touched down only 535 feet from Surveyor 3, can be used to teach accuracy and absolute and relative error. The astronauts of Apollo 15 discovered a sample of the primordial lunar crust, and during Apollo 17, astronauts discovered orange dust on the moon. These discoveries can be used to demonstrate the importance of trained observation skills and analytical thinking.

APOLLO clock performance and normal point corrections

NASA Astrophysics Data System (ADS)

Liang, Y.; Murphy, T. W., Jr.; Colmenares, N. R.; Battat, J. B. R.

2017-12-01

The Apache point observatory lunar laser-ranging operation (APOLLO) has produced a large volume of high-quality lunar laser ranging (LLR) data since it began operating in 2006. For most of this period, APOLLO has relied on a GPS-disciplined, high-stability quartz oscillator as its frequency and time standard. The recent addition of a cesium clock as part of a timing calibration system initiated a comparison campaign between the two clocks. This has allowed correction of APOLLO range measurements—called normal points—during the overlap period, but also revealed a mechanism to correct for systematic range offsets due to clock errors in historical APOLLO data. Drift of the GPS clock on  ∼1000 s timescales contributed typically 2.5 mm of range error to APOLLO measurements, and we find that this may be reduced to  ∼1.6 mm on average. We present here a characterization of APOLLO clock errors, the method by which we correct historical data, and the resulting statistics.

Cu₂O template synthesis of high-performance PtCu alloy yolk-shell cube catalysts for direct methanol fuel cells.

PubMed

Ye, Sheng-Hua; He, Xu-Jun; Ding, Liang-Xin; Pan, Zheng-Wei; Tong, Ye-Xiang; Wu, Mingmei; Li, Gao-Ren

2014-10-21

Novel PtCu alloy yolk-shell cubes were fabricated via the disproportionation and displacement reactions in Cu2O yolk-shell cubes, and they exhibit significantly improved catalytic activity and durability for methanol electrooxidation.

First Image from MarCO-B

NASA Image and Video Library

2018-05-15

The first image captured by one of NASA's Mars Cube One (MarCO) CubeSats. The image, which shows both the CubeSat's unfolded high-gain antenna at right and the Earth and its moon in the center, was acquired by MarCO-B on May 9. MarCO is a pair of small spacecraft accompanying NASA's InSight (Interior Investigations Using Seismic Investigations, Geodesy and Heat Transport) lander. Together, MarCO-A and MarCO-B are the first CubeSats ever sent to deep space. InSight is the first mission to ever explore Mars' deep interior. If the MarCO CubeSats make the entire journey to Mars, they will attempt to relay data about InSight back to Earth as the lander enters the Martian atmosphere and lands. MarCO will not collect any science, but are intended purely as a technology demonstration. They could serve as a pathfinder for future CubeSat missions. An annotated version is available at https://photojournal.jpl.nasa.gov/catalog/PIA22323

An Asymmetric Image Encryption Based on Phase Truncated Hybrid Transform

NASA Astrophysics Data System (ADS)

Khurana, Mehak; Singh, Hukum

2017-09-01

To enhance the security of the system and to protect it from the attacker, this paper proposes a new asymmetric cryptosystem based on hybrid approach of Phase Truncated Fourier and Discrete Cosine Transform (PTFDCT) which adds non linearity by including cube and cube root operation in the encryption and decryption path respectively. In this cryptosystem random phase masks are used as encryption keys and phase masks generated after the cube operation in encryption process are reserved as decryption keys and cube root operation is required to decrypt image in decryption process. The cube and cube root operation introduced in the encryption and decryption path makes system resistant against standard attacks. The robustness of the proposed cryptosystem has been analysed and verified on the basis of various parameters by simulating on MATLAB 7.9.0 (R2008a). The experimental results are provided to highlight the effectiveness and suitability of the proposed cryptosystem and prove the system is secure.

Monosodium glutamate in chicken and beef stock cubes using high-performance liquid chromatography.

PubMed

Demirhan, Buket Er; Demirhan, Burak; Sönmez, Ceren; Torul, Hilal; Tamer, Uğur; Yentür, Gülderen

2015-01-01

In this survey monosodium glutamate (MSG) levels in chicken and beef stock cube samples were determined. A total number of 122 stock cube samples (from brands A, B, C, D) were collected from local markets in Ankara, Turkey. High-performance liquid chromatography with diode array detection (HPLC-DAD) was used for quantitative MSG determination. Mean MSG levels (±SE) in samples of A, B, C and D brands were 14.6 ± 0.2 g kg⁻¹, 11.9 ± 0.3 g kg⁻¹, 9.7 ± 0.1 g kg⁻¹ and 7.2 ± 0.1 g kg⁻¹, respectively. Differences between mean levels of brands were significant. Also, mean levels of chicken stock cube samples were lower than in beef stock cubes. Maximum limits for MSG in stock cubes are not specified in the Turkish Food Codex (TFC). Generally the limit for MSG in foods (except some foods) is established as 10 g kg⁻¹ (individually or in combination).

Ka-Band Parabolic Deployable Antenna (KaPDA) Enabling High Speed Data Communication for CubeSats

NASA Technical Reports Server (NTRS)

Sauder, Jonathan F.; Chahat, Nacer; Hodges, Richard; Thomson, Mark W.; Rahmat-Samii, Yahya

2015-01-01

CubeSats are at a very exciting point as their mission capabilities and launch opportunities are increasing. But as instruments become more advanced and operational distances between CubeSats and earth increase communication data rate becomes a mission-limiting factor. Improving data rate has become critical enough for NASA to sponsor the Cube Quest Centennial Challenge when: one of the key metrics is transmitting as much data as possible from the moon and beyond Currently, many CubeSats communicate on UHF bands and those that have high data rate abilities use S-band or X-band patch antennas. The CubeSat Aneas, which was launched in September 2012, pushed the envelope with a half-meter S-band dish which could achieve 100x the data rate of patch antennas. A half-meter parabolic antenna operating at Ka-band would increase data rates by over 100x that of the AMOS antenM and 10,000 that of X-band patch antennas.

Neutrino astronomy at the South Pole: Latest results from the IceCube neutrino observatory and its future development

NASA Astrophysics Data System (ADS)

Toscano, S.; IceCube Collaboration

2017-12-01

The IceCube Neutrino Observatory is a cubic-kilometer neutrino telescope located at the geographic South Pole. Buried deep under the Antarctic ice sheet, an array of 5160 Digital Optical Modules (DOMs) is used to capture the Cherenkov light emitted by relativistic particles generated from neutrino interactions. The main goal of IceCube is the detection of astrophysical neutrinos. In 2013 the IceCube neutrino telescope discovered a high-energy diffuse flux of neutrino events with energy ranging from tens of TeV up to few PeV of cosmic origin. Meanwhile, different analyses confirm the discovery and search for possible correlations with astrophysical sources. However, the source of these neutrinos remains a mystery, since no counterparts have been identified yet. In this contribution we give an overview of the detection principles of IceCube, the most recent results, and the plans for a next-generation neutrino detector, dubbed IceCube-Gen2.

KSC-2012-6142

NASA Image and Video Library

2012-11-03

CAPE CANAVERAL, Fla. – A guest checks out an item available for auction at the Astronaut Scholarship Foundation's dinner at the Radisson Resort at the Port in Cape Canaveral celebrating the 40th anniversary of Apollo 17. The auction of space-related memorabilia was held with proceeds supporting college scholarships for students who exhibit imagination and exceptional performance in science, technology, engineering and math. The gala commemorating the anniversary of Apollo 17 included mission commander Eugene Cernan and other astronauts who flew Apollo missions. Launched Dec. 7, 1972, Cernan and lunar module pilot Harrison Schmitt landed in the moon's Taurus-Littrow highlands while command module pilot Ronald Evans remained in lunar orbit operating a scientific instrument module. For more information, visit http://www-pao.ksc.nasa.gov/history/apollo/apollo-17/apollo-17.htm Photo credit: NASA/Kim Shiflett

Winners of student essay contest receive awards

NASA Technical Reports Server (NTRS)

1999-01-01

At the Apollo/Saturn V Center, George Meguiar (center left) and George English (center right) present scholarships to two students who entered an essay contest in conjunction with the 30th Anniversary of Apollo 11. The winners shown are Kyla Davis Horn, of Cocoa Beach, and Kyle Rukaczewski, of Satellite Beach. A third winner, Jason Gagnon, of Viera, was unable to attend. Meguiar and English head the Apollo 11 Commemoration Association which sponsored the contest in conjunction with Florida Today newspaper. The presentation was made at the Apollo/Saturn V Center during an anniversary banquet that honored all the people who made the Apollo Program possible. Special guests included former Apollo astronauts Neil Armstrong, Edwin 'Buzz' Aldrin, Gene Cernan and Walt Cunningham, who shared their experiences with the audience.

View of Mission Control Center during Apollo 13 splashdown

NASA Technical Reports Server (NTRS)

1970-01-01

Overall view of Mission Operations Control Room in Mission Control Center at the Manned Spacecraft Center (MSC) during the ceremonies aboard the U.S.S. Iwo Jima, prime recovery ship for the Apollo 13 mission. Dr. Donald K. Slayton (in black shirt, left of center), Director of Flight Crew Operations at MSC, and Chester M. Lee of the Apollo Program Directorate, Office of Manned Space Flight, NASA Headquarters, shake hands, while Dr. Rocco A. Petrone, Apollo Program Director, Office of Manned Space Flight, NASA Headquarters (standing, near Lee), watches the large screen showing Astronaut James A. Lovell Jr., Apollo 13 commander, during the on-board ceremonies. In the foreground, Glynn S. Lunney (extreme left) and Eugene F. Kranz (smoking a cigar), two Apollo 13 Flight Directors, view the activity from their consoles.

Saturn V Vehicle for the Apollo 4 Mission in the Vehicle Assembly Building

NASA Technical Reports Server (NTRS)

1967-01-01

This photograph depicts the Saturn V vehicle (SA-501) for the Apollo 4 mission in the Vehicle Assembly Building (VAB) at the Kennedy Space Center (KSC). After the completion of the assembly operation, the work platform was retracted and the vehicle was readied to rollout from the VAB to the launch pad. The Apollo 4 mission was the first launch of the Saturn V launch vehicle. Objectives of the unmanned Apollo 4 test flight were to obtain flight information on launch vehicle and spacecraft structural integrity and compatibility, flight loads, stage separation, and subsystems operation including testing of restart of the S-IVB stage, and to evaluate the Apollo command module heat shield. The Apollo 4 was launched on November 9, 1967 from KSC.

Apollo 1 Prime and Backup Crews

NASA Image and Video Library

1966-04-01

S66-30238 (1 April 1966) --- The National Aeronautics and Space Administration (NASA) has named these astronauts as the prime crew of the first manned Apollo Space Flight. Left to right, are Edward H. White II, command module pilot; Virgil I. Grissom, mission commander; and Roger B. Chaffee, lunar module pilot. On the second row are the Apollo 1 backup crew members, astronauts David R. Scott, James A. McDivitt and Russell L. Schweickart. EDITOR'S NOTE: Astronauts Grissom, White and Chaffee lost their lives in a Jan. 27, 1967 fire in the Apollo CM during testing at Cape Canaveral. McDivitt, Scott and Schweickart later served as crewmembers for the Apollo 9 Earth-orbital mission, which was one of the important stair-step missions leading up to the Apollo 11 manned lunar landing mission of July 1969.

Analyzing Molecular Clouds with the Spectral Correlation Function

NASA Astrophysics Data System (ADS)

Rosolowsky, E. W.; Goodman, A. A.; Williams, J. P.; Wilner, D. J.

1997-12-01

The Spectral Correlation Function (SCF) is a new data analysis algorithm that measures how the properites of spectra vary from position to position in a spectral-line map. For each spectrum in a data cube, the SCF measures the ``difference" between that spectrum and a specified subset of its neighbors. This algorithm is intended for use on both simulated and observed position-position-velocity data cubes. In initial tests of the SCF, we have shown that a histogram of the SCF for a map is a good descriptor of the spatial-velocity distribution of material. In one test, we compare the SCF distributions for: 1) a real data cube; 2) a cube made from the real cube's spectra with randomized positions; and 3) the results of a preliminary MHD simulation by Gammie, Ostriker, and Stone. The results of the test show that the real cloud and the simulation are much closer to each other in their SCF distributions than is either to the randomized cube. We are now in the process of applying the SCF to a larger set of observed and simulated data cubes. Our ultimate aim is to use the SCF both on its own, as a descriptor of the spatial-kinetic properties of interstellar gas, and also as a tool for evaluating how well simulations resemble observations. Our expectation is that the SCF will be more discriminatory (less likely to produce a false match) than the data cube descriptors currently available.

The Effects of Composition and gamma'/gamma Lattice Parameter Mismatch on the Critical Resolved Shear Stresses for Octahedral and Cube Slip in NiAlCrX Alloys

NASA Technical Reports Server (NTRS)

Miner, R. V.

1997-01-01

Prototypical single-crystal NiAlCrX superalloys were studied to examine the effects of the common major alloying elements, Co, Mo, Nb, Ta, Ti, and W, on yielding behavior. The alloys contained about 10 at. pct Cr, 60 vol pct of the gamma' phase, and about 3 at. pct of X in the gamma'. The critical resolved shear stresses (CRSSs) for octahedral and primary cube slip were measured at 760 C, which is about the peak strength temperature. The CRSS(sub oct) and CRSS(sub cube) are discussed in relation to those of Ni, (Al, X) gamma' alloys taken from the literature and the gamma'/gamma lattice mismatch. The CRSS(sub oct) of the gamma + gamma' alloys reflected a similar compositional dependence to that of both the CRSS(sub cube) of the gamma' phase and the gamma'/gamma lattice parameter mismatch. The CRSS(sub cube) of the gamma + gamma' alloys also reflected the compositional dependence of the gamma'/gamma mismatch, but bore no similarity to that of CRSS(sub cube) for gamma' alloys since it is controlled by the gamma matrix. The ratio of CRSS(sub cube)/CRSS(sub oct) was decreased by all alloying elements except Co, which increased the ratio. The decrease in CRSS(sub cube)/CRSS(sub oct) was related to the degree in which elements partition to the gamma' rather than the gamma phase.

EarthCube Cyberinfrastructure: The Importance of and Need for International Strategic Partnerships to Enhance Interconnectivity and Interoperability

NASA Astrophysics Data System (ADS)

Ramamurthy, M. K.; Lehnert, K.; Zanzerkia, E. E.

2017-12-01

The United States National Science Foundation's EarthCube program is a community-driven activity aimed at transforming the conduct of geosciences research and education by creating a well-connected cyberinfrastructure for sharing and integrating data and knowledge across all geoscience disciplines in an open, transparent, and inclusive manner and to accelerate our ability to understand and predict the Earth system. After five years of community engagement, governance, and development activities, EarthCube is now transitioning into an implementation phase. In the first phase of implementing the EarthCube architecture, the project leadership has identified the following architectural components as the top three priorities, focused on technologies, interfaces and interoperability elements that will address: a) Resource Discovery; b) Resource Registry; and c) Resource Distribution and Access. Simultaneously, EarthCube is exploring international partnerships to leverage synergies with other e-infrastructure programs and projects in Europe, Australia, and other regions and discuss potential partnerships and mutually beneficial collaborations to increase interoperability of systems for advancing EarthCube's goals in an efficient and effective manner. In this session, we will present the progress of EarthCube on a number of fronts and engage geoscientists and data scientists in the future steps toward the development of EarthCube for advancing research and discovery in the geosciences. The talk will underscore the importance of strategic partnerships with other like eScience projects and programs across the globe.

Design of a Base Station for MEMS CCR Localization in an Optical Sensor Network

PubMed Central

Park, Chan Gook; Jeon, Hyun Cheol; Kim, Hyoun Jin; Kim, Jae Yoon

2014-01-01

This paper introduces a design and implementation of a base station, capable of positioning sensor nodes using an optical scheme. The base station consists of a pulse laser module, optical detectors and beam splitter, which are mounted on a rotation-stage, and a Time to Digital Converter (TDC). The optical pulse signal transmitted to the sensor node with a Corner Cube Retro-reflector (CCR) is reflected to the base station, and the Time of Flight (ToF) data can be obtained from the two detectors. With the angle and flight time data, the position of the sensor node can be calculated. The performance of the system is evaluated by using a commercial CCR. The sensor nodes are placed at different angles from the base station and scanned using the laser. We analyze the node position error caused by the rotation and propose error compensation methods, namely the outlier sample exception and decreasing the confidence factor steadily using the recursive least square (RLS) methods. Based on the commercial CCR results, the MEMS CCR is also tested to demonstrate the compatibility between the base station and the proposed methods. The result shows that the localization performance of the system can be enhanced with the proposed compensation method using the MEMS CCR. PMID:24815681

Design of a base station for MEMS CCR localization in an optical sensor network.

PubMed

Park, Chan Gook; Jeon, Hyun Cheol; Kim, Hyoun Jin; Kim, Jae Yoon

2014-05-08

This paper introduces a design and implementation of a base station, capable of positioning sensor nodes using an optical scheme. The base station consists of a pulse laser module, optical detectors and beam splitter, which are mounted on a rotation-stage, and a Time to Digital Converter (TDC). The optical pulse signal transmitted to the sensor node with a Corner Cube Retro-reflector (CCR) is reflected to the base station, and the Time of Flight (ToF) data can be obtained from the two detectors. With the angle and flight time data, the position of the sensor node can be calculated. The performance of the system is evaluated by using a commercial CCR. The sensor nodes are placed at different angles from the base station and scanned using the laser. We analyze the node position error caused by the rotation and propose error compensation methods, namely the outlier sample exception and decreasing the confidence factor steadily using the recursive least square (RLS) methods. Based on the commercial CCR results, the MEMS CCR is also tested to demonstrate the compatibility between the base station and the proposed methods. The result shows that the localization performance of the system can be enhanced with the proposed compensation method using the MEMS CCR.

An absolute method for determination of misalignment of an immersion ultrasonic transducer.

PubMed

Narayanan, M M; Singh, Narender; Kumar, Anish; Babu Rao, C; Jayakumar, T

2014-12-01

An absolute methodology has been developed for quantification of misalignment of an ultrasonic transducer using a corner-cube retroreflector. The amplitude based and the time of flight (TOF) based C-scans of the reflector are obtained for various misalignments of the transducer. At zero degree orientation of the transducer, the vertical positions of the maximum amplitude and the minimum TOF in the C-scan coincide. At any other orientation of the transducer with the horizontal plane, there is a vertical shift in the position of the maximum amplitude with respect to the minimum TOF. The position of the minimum (TOF) remains the same irrespective of the orientation of the transducer and hence is used as a reference for any misalignment of the transducer. With the measurement of the vertical shift and the horizontal distance between the transducer and the vertex of the reflector, the misalignment of the transducer is quantified. Based on the methodology developed in the present study, retroreflectors are placed in the Indian 500MWe Prototype Fast Breeder Reactor for assessment of the orientation of the ultrasonic transducer prior to the under-sodium ultrasonic scanning for detection of any protrusion of the subassemblies. Copyright © 2014 Elsevier B.V. All rights reserved.

Neil Armstrong chats with attendees at Apollo 11 anniversary banquet.

NASA Technical Reports Server (NTRS)

1999-01-01

Former Apollo 11 astronaut Neil A. Armstrong is the center of attention at the anniversary banquet honoring the Apollo team, the people who made the entire lunar landing program possible. The banquet was held in the Apollo/Saturn V Center, part of the KSC Visitor Complex. This is the 30th anniversary of the Apollo 11 launch and moon landing, July 16 and July 20, 1969. Neil Armstrong was the first man to set foot on the moon. He appeared at the banquet with other former astronauts Edwin 'Buzz' Aldrin, Gene Cernan, Walt Cunningham and others.

KSC-99pp0843

NASA Image and Video Library

1999-07-16

KENNEDY SPACE CENTER, FLA. -- In the Apollo/Saturn V Center, Lisa Malone (left), chief of KSC's Media Services branch, identifies a reporter to pose a question to one of the former Apollo astronauts seated next to her. From left, they are Neil A. Armstrong and Edwin "Buzz" Aldrin who flew on Apollo 11, the launch to the moon; Gene Cernan, who flew on Apollo 10 and 17; and Walt Cunningham, who flew on Apollo 7. This is the 30th anniversary of the launch and moon landing, July 16 and July 20, 1969. Neil Armstrong was the first man to set foot on the moon

Neil Armstrong gets round of applaus at Apollo 11 anniversary banquet.

NASA Technical Reports Server (NTRS)

1999-01-01

Former Apollo 11 astronaut Neil A. Armstrong stands to a round of applause after being introduced at the anniversary banquet honoring the Apollo team, the people who made the entire lunar landing program possible. The banquet was held in the Apollo/Saturn V Center, part of the KSC Visitor Complex. This is the 30th anniversary of the Apollo 11 launch and moon landing, July 16 and July 20, 1969. Neil Armstrong was the first man to set foot on the moon. He appeared at the banquet with other former astronauts Edwin 'Buzz' Aldrin, Gene Cernan, Walt Cunningham and others.

Official Emblem - Apollo 7 - First (1st) Manned Apollo Space Mission

NASA Image and Video Library

1968-06-01

S68-26668 (June 1968) --- The official emblem of Apollo 7, the first manned Apollo space mission. The crew will consist of astronauts Walter M. Schirra Jr., Donn F. Eisele, and Walter Cunningham. The NASA insignia design for Apollo flights is reserved for use by the astronauts and for the official use as the NASA Administrator may authorize. Public availability has been approved only in the form of illustrations by the various news media. When and if there is any change in this policy, which we do not anticipate, it will be publicly announced.

Apollo 4 launch

NASA Image and Video Library

1967-09-11

S67-50903 (9 Nov. 1967) --- The Apollo 4 (Spacecraft 017/Saturn 501) space mission was launched from Pad A, Launch Complex 39, Kennedy Space Center, Florida. The liftoff of the huge 363-feet tall Apollo/Saturn V space vehicle was at 7:00:01 a.m. (EST), Nov. 9, 1967. The successful objectives of the Apollo 4 Earth-orbital unmanned space mission obtained included (1) flight information on launch vehicle and spacecraft structural integrity and compatibility, flight loads, stage separation, subsystem operation, emergency detection subsystem, and (2) evaluation of the Apollo Command Module heat shield under conditions encountered on return from a moon mission.

An annotated bibliography of the Apollo program

NASA Technical Reports Server (NTRS)

Launius, Roger D.; Hunley, J. D.

1994-01-01

The topics presented include the following: general works, the space race, decisions, Apollo technology, operations, popular culture and promotion, science, astronauts, the management of the Apollo Program, and juvenile literature.

NanoRacks CubeSat Deployment

NASA Image and Video Library

2014-02-11

ISS038-E-044916 (11 Feb. 2014) --- A set of NanoRacks CubeSats is photographed by an Expedition 38 crew member after the deployment by the Small Satellite Orbital Deployer (SSOD). The CubeSats program contains a variety of experiments such as Earth observations and advanced electronics testing.

SpaceCube Technology Brief Hybrid Data Processing System

NASA Technical Reports Server (NTRS)

Petrick, Dave

2016-01-01

The intent of this presentation is to give status to multiple audience types on the SpaceCube data processing technology at GSFC. SpaceCube has grown to support multiple missions inside and outside of NASA, and we are being requested to give technology overviews in various forums.

Applications of Nano-Satellites and Cube-Satellites in Microwave and RF Domain

NASA Technical Reports Server (NTRS)

Simons, Rainee N.; Goverdhanam, Kavita

2015-01-01

This paper presents an overview of microwave technologies for Small Satellites including NanoSats and CubeSats. In addition, examples of space communication technology demonstration projects using CubeSats are presented. Furthermore, examples of miniature instruments for Earth science measurements are discussed.

Applications of Nano-satellites and Cube-satellites in Microwave and RF Domain

NASA Technical Reports Server (NTRS)

Simons, Rainee N.; Goverdhanam, Kavita

2015-01-01

This paper presents an overview of microwave technologies for Small Satellites including NanoSats and CubeSats. In addition, examples of space communication technology demonstration projects using CubeSats are presented. Furthermore, examples of miniature instruments for Earth science measurements are discussed.

The Apollo Structured Vocabulary: an OWL2 ontology of phenomena in infectious disease epidemiology and population biology for use in epidemic simulation.

PubMed

Hogan, William R; Wagner, Michael M; Brochhausen, Mathias; Levander, John; Brown, Shawn T; Millett, Nicholas; DePasse, Jay; Hanna, Josh

2016-08-18

We developed the Apollo Structured Vocabulary (Apollo-SV)-an OWL2 ontology of phenomena in infectious disease epidemiology and population biology-as part of a project whose goal is to increase the use of epidemic simulators in public health practice. Apollo-SV defines a terminology for use in simulator configuration. Apollo-SV is the product of an ontological analysis of the domain of infectious disease epidemiology, with particular attention to the inputs and outputs of nine simulators. Apollo-SV contains 802 classes for representing the inputs and outputs of simulators, of which approximately half are new and half are imported from existing ontologies. The most important Apollo-SV class for users of simulators is infectious disease scenario, which is a representation of an ecosystem at simulator time zero that has at least one infection process (a class) affecting at least one population (also a class). Other important classes represent ecosystem elements (e.g., households), ecosystem processes (e.g., infection acquisition and infectious disease), censuses of ecosystem elements (e.g., censuses of populations), and infectious disease control measures. In the larger project, which created an end-user application that can send the same infectious disease scenario to multiple simulators, Apollo-SV serves as the controlled terminology and strongly influences the design of the message syntax used to represent an infectious disease scenario. As we added simulators for different pathogens (e.g., malaria and dengue), the core classes of Apollo-SV have remained stable, suggesting that our conceptualization of the information required by simulators is sound. Despite adhering to the OBO Foundry principle of orthogonality, we could not reuse Infectious Disease Ontology classes as the basis for infectious disease scenarios. We thus defined new classes in Apollo-SV for host, pathogen, infection, infectious disease, colonization, and infection acquisition. Unlike IDO, our ontological analysis extended to existing mathematical models of key biological phenomena studied by infectious disease epidemiology and population biology. Our ontological analysis as expressed in Apollo-SV was instrumental in developing a simulator-independent representation of infectious disease scenarios that can be run on multiple epidemic simulators. Our experience suggests the importance of extending ontological analysis of a domain to include existing mathematical models of the phenomena studied by the domain. Apollo-SV is freely available at: http://purl.obolibrary.org/obo/apollo_sv.owl .

A potpourrie of regolith breccias: ``New'' samples from the Apollo 14, 16, and 17 landing sites

NASA Astrophysics Data System (ADS)

Jerde, Eric A.; Warren, Paul H.; Morris, Richard V.; Heiken, Grant H.; Vaniman, David T.

1987-09-01

Forty suspected regolith breccias from the Apollo 14, 16, and 17 landing sites were studied as part of a search for regolith samples exotic to the small traverse areas associated with these missions, as well as a general effort to constrain the nature and origins of regolith breccias. Of these 40 samples, 31 are indeed regolith breccias. Regolith breccias from Apollo 14 exhibit much greater compositional diversity than their soil (sensu stricto) counterparts: 14004,55 displays incompatible element concentrations about 1.4× those found in typical Apollo 14 regolith, while 14315 is radically different in many respects (higher Al, lower Mg and Fe, lower incompatible elements) from all other Apollo 14 regolith materials, and hence probably exotic to the Apollo 14 traverse area. Application of ``mixing'' models to Apollo 14 regolith materials suggests that whereas ``normal'' Apollo 14 regolith contains only slightly more ferroan anorthosite (FA) than alkali anorthosite (AA) and far more KREEP than FA and AA combined, 14315 contains more FA than KREEP and roughly 10 times more FA than AA. Three ``new'' regolith breccias from Apollo 16 bring to 20 the total number of regolith breccias that have been analyzed for Mg and Fe from the site. The molar Mg/)Mg+Fe) (or mg*) ratios of lunar regolith breccias are of great interest, because lunar meteorite ALH81005 has a much higher mg* than two other lunar meteoritic regolith breccias (Y791197 and Y82192/3), even though these three samples are remarkably similar in all other compositional respects. A bimodality in mg* among Apollo 16 regolith breccias may result from: (1) statistical scattering among the small number of samples, (2) a tendency for older regolith breccias from this site to be compositionally distinct form their younger counterparts, or (3) differences between the Cayley and Descartes Formations. Among 10 samples from Apollo 17, all but one proved to be typical Apollo 17 regolith breccias. However, 72504,10 is >99% pure pyroclastic glass, compositionally identical to the Apollo 1 orange galss (74220), even though 72504,10 was obtained at a location over 4 km from Shorty Crater where 74220 was obtained. The nearly pure concentration of 74220-identical glass spherules in 72504-10 attests to the widespread distribution of these distinctive deposits.

Formative evaluation for a healthy corner store initiative in Pitt County, North Carolina: engaging stakeholders for a healthy corner store initiative, part 2.

PubMed

Pitts, Stephanie B Jilcott; Bringolf, Karamie R; Lloyd, Cameron L; McGuirt, Jared T; Lawton, Katherine K; Morgan, Jo

2013-07-18

We examined the feasibility of increasing access to healthful food in corner stores to inform a Communities Putting Prevention to Work (CPPW) initiative by engaging stakeholders (corner store owners and customers) in a formative evaluation. Qualitative interviews were conducted with corner store owners and managers (n = 11). Customer intercept surveys (n = 179) were also conducted with customers of 9 stores. Corner stores were located in rural food deserts (municipalities without a chain supermarket) and in low-income, urban municipalities in eastern North Carolina. Interviews were transcribed verbatim and double-coded. Qualitative themes related to feasibility of increasing access to healthful foods were extracted. Shopping patterns of rural and urban customers were compared by using t tests. Corner store owners were willing to stock more healthful foods, but they perceived that customer demand for these foods was low. Rural customers reported more frequently shopping at corner stores than urban customers and more frequently stated that the reason they do not eat more fruits and vegetables is that the stores in which they shop do not sell them. Most customers reported they would be very or somewhat likely to purchase fresh produce at a corner store. Corner stores may be an important source of food for rural and low-income residents and thus a good place in which to intervene. The results of this formative evaluation were used to plan and evaluate a CPPW healthy corner store initiative.

KSC-2009-4186

NASA Image and Video Library

2009-07-16

CAPE CANAVERAL, Fla. – CNN Correspondent John Zarella (left), moderates NASA's 40th Anniversary of Apollo Celebration of the moon launch and landing in July 1969, which was held in the Apollo/Saturn V Center at NASA's Kennedy Space Center in Florida. At right are Apollo astronauts Buzz Aldrin, Walt Cunningham and Edgar Mitchell. Eight Apollo astronauts shared their experiences with a crowd of guests. Photo credit: NASA/Kim Shiflett

Apollo 9 prime crew inside Apollo command module boilerplate during training

NASA Image and Video Library

1968-11-05

S68-54850 (5 Nov. 1968) --- The prime crew of the Apollo 9 (Spacecraft 104/Lunar Module 3/Saturn 504) space mission are seen inside an Apollo command module boilerplate during water egress training activity in the Gulf of Mexico. From foreground, are astronauts James A. McDivitt, commander; David R. Scott, command module pilot; and Russell L. Schweickart, lunar module pilot.

Alan Bean Art Exhibit

NASA Image and Video Library

2009-07-19

NASA Apollo 7 Astronaut Walt Cunningham, left, and NASA STS-125 Mission Specialist Michael Massimino talk with another guest during the opening of "Alan Bean: Painting Apollo, First Artist on Another World" by NASA Apollo 12 Astronaut and Artist Alan Bean at the National Air and Space Museum, Monday, July 20, 2009 in Washington. The show opening coincided with the 40th anniversary celebration of Apollo. Photo Credit: (NASA/Bill Ingalls)

Artist's concept of Apollo/Soyuz spacecraft docking approach

NASA Image and Video Library

1973-08-01

S73-02395 (August 1973) --- An artist?s concept illustrating an Apollo-type spacecraft (on left) about to dock with a Soviet Soyuz-type spacecraft. A recent agreement between the United States and the Union of Soviet Socialist Republics provides for the docking in space of the Soyuz and Apollo-type spacecraft in Earth orbit in 1975. The joint venture is called the Apollo-Soyuz Test Project.

President Nixon on deck of U.S.S. Hornet awaiting Apollo 11 crew arrival

NASA Technical Reports Server (NTRS)

1969-01-01

President Richard M. Nixon photographed on the deck of the U.S.S. Hornet, prime recovery ship for the Apollo 11 lunar landing mission, awaiting the Apollo 11 crew arrival. swimmer. All four men are wearing biological isolation garments. Apollo 11 splashed down at 11:40 a.m., July 24, 1969, about 812 nautical miles southwest of Hawaii.

Notes on lunar ilmenite

NASA Technical Reports Server (NTRS)

Hutson, M. L.

1989-01-01

Opaques (mostly ilmenite) make up 0 to 5 percent of highland rocks, 1 to 11 percent of low-Ti mare basalts, and 10 to 34 percent of high-Ti mare basalts (Carter 1988). Apollos 11 and 17 sampled high-Ti basalts. Apollos 12 and 14 sampled low-Ti basalts. Apollo 15 sampled a complex mixture of mare and highland material. Apollo 16 sampled mainly highland material (Taylor 1975).

Apollo 13 lunar photography

NASA Technical Reports Server (NTRS)

Anderson, A. T.; Michlovitz, C. K.; Hug, K.

1970-01-01

A data users' note announces the availability of Apollo 13 pictorial data and aids the investigator in the selection of Apollo 13 photographs for study. This note provides guidance in the interpretation of the photographs. The note includes brief descriptions of the Apollo 13 mission objectives, photographic equipment, and photographic coverage and quality. The National Space Science Data Center (NSSDC) can provide all forms of the photographs described.

APOLLO 9 - PRELAUNCH (CDDT) - KSC

NASA Image and Video Library

1969-02-20

S69-27089 (11 March 1969) --- Overall view of Pad B, Launch Complex 39, Kennedy Space Center, showing the Apollo 10 (Spacecraft 106/Lunar Module-4/Saturn 505) space vehicle during a Countdown Demonstration Test. The Apollo 10 flight is scheduled as a lunar orbit mission. The Apollo 10 crew will be astronauts Thomas P. Stafford, commander; John W. Young, command module pilot; and Eugene A. Cernan, lunar module pilot.

Lunar Exploration Insights Recognized from Chandrayaan-1 M3 Imaging Spectrometer

NASA Astrophysics Data System (ADS)

Pieters, Carle; Green, Robert O.; Boardman, Joseph

2016-07-01

One of the most important lessons learned from the renaissance of lunar exploration over the last decade is that new discoveries and surprises occur with every new mission to the Moon. Although the color of the Moon had been measured using Earth-based telescopes even before Apollo, modern instruments sent to orbit the Moon provide a scope of inquiry unimaginable during the last century. Spacecraft have now been successfully sent to the Moon by six different space agencies from around the world and the number is growing. The Indian Chandrayaan- 1 spacecraft carried a suite of indigenous instruments as well as several guest instruments from other countries, including the Moon Mineralogy Mapper (M-cube) supplied by NASA. Even though Chandrayaan's lifetime in orbit was shortened by technical constraints, M3 provided a taste of the power of near-infrared imaging spectroscopy used for science and exploration at the Moon. Contrary to expectations, the lunar surface was discovered to be hydrated, which is now known to result from solar wind H combining with O of rocks and soil. Surficial hydration was found to be pervasive across the Moon and the limited data hint at both local concentrations and temporal variations. The prime objective of M3 was to characterize lunar mineralogy in a spatial context. Working in tandem with related instruments on JAXA's SELENE, M3 readily recognized and mapped known minerals from mare and highland terrains (pyroxenes, olivine) at high resolution, but also detected diagnostic properties of crystalline plagioclase which, when mapped across a spatial context, enabled the unambiguous identification of a massive crustal layer of plagioclase that clearly resulted from an early magma ocean. An additional surprise came with the discovery of a new rock type on the Moon that had not been recognized in samples returned by Apollo and Luna: a Mg-rich spinel anorthosite associated with material excavated from some of the greatest lunar depths. In addition to the sophisticated science queries enabled by M3 data, a growing list of prime lunar targets is identified for the next generation of sample return missions to the Moon.

Success Factors in Human Space Programs - Why Did Apollo Succeed Better Than Later Programs?

NASA Technical Reports Server (NTRS)

Jones, Harry W.

2015-01-01

The Apollo Program reached the moon, but the Constellation Program (CxP) that planned to return to the moon and go on to Mars was cancelled. Apollo is NASA's greatest achievement but its success is poorly understood. The usual explanation is that President Kennedy announced we were going to the moon, the scientific community and the public strongly supported it, and Congress provided the necessary funding. This is partially incorrect and does not actually explain Apollo's success. The scientific community and the public did not support Apollo. Like Apollo, Constellation was announced by a president and funded by Congress, with elements that continued on even after it was cancelled. Two other factors account for Apollo's success. Initially, the surprise event of Uri Gagarin's first human space flight created political distress and a strong desire for the government to dramatically demonstrate American space capability. Options were considered and Apollo was found to be most effective and technically feasible. Political necessity overrode both the lack of popular and scientific support and the extremely high cost and risk. Other NASA human space programs were either canceled, such as the Space Exploration Initiative (SEI), repeatedly threatened with cancellation, such as International Space Station (ISS), or terminated while still operational, such as the space shuttle and even Apollo itself. Large crash programs such as Apollo are initiated and continued if and only if urgent political necessity produces the necessary political will. They succeed if and only if they are technically feasible within the provided resources. Future human space missions will probably require gradual step-by-step development in a more normal environment.

Learning Experiences in a Giant Interactive Environment: Insights from The Cube

ERIC Educational Resources Information Center

Stoodley, Ian; Sayyad Abdi, Elham; Bruce, Christine; Hughes, Hilary

2018-01-01

In November 2012, Queensland University of Technology in Australia launched a giant interactive learning environment known as "The Cube". This article reports a phenomenographic investigation into visitors' different experiences of learning in The Cube. At present very little is known about people's learning experience in spaces…

Search for counterpart to IceCube-171015A with ANTARES

NASA Astrophysics Data System (ADS)

Dornic, Damien; Colei, Alexis

2017-10-01

Damien Dornic (CPPM/CNRS) and Alexis Coleiro (IFIC/APC) report on behalf of the ANTARES Collaboration. Using online data from the ANTARES detector, we have performed a follow-up analysis of the recently reported high-energy starting event (HESE) neutrino IceCube-171015 (AMON IceCube HESE 56068624_130126).

Invariant Deformation Element Model Interpretation to the Crystallography of Diffusional Body-Centered-Cube to Face-Centered-Cube Phase Transformations

NASA Astrophysics Data System (ADS)

Liu, Hongwei; Liu, Jiangwen; Su, Guangcai; Li, Weizhou; Zeng, Jianmin; Hu, Zhiliu

2012-10-01

The crystallography of body-centered-cube to face-centered cube (bcc-to-fcc) diffusion phase transformations in a duplex stainless steel and a Cu-Zn alloy, including long axis, orientation relationship (OR), habit plane (HP), and dislocation spacing, is successfully interpreted with one-step rotation from the Bain lattice relationship by applying a simplified invariant line (IL) analysis. It is proposed that the dislocation slipping direction in the matrix plays an important role in controlling the crystallography of precipitation.

RM-CLEAN: RM spectra cleaner

NASA Astrophysics Data System (ADS)

Heald, George

2017-08-01

RM-CLEAN reads in dirty Q and U cubes, generates rmtf based on the frequencies given in an ASCII file, and cleans the RM spectra following the algorithm given by Brentjens (2007). The output cubes contain the clean model components and the CLEANed RM spectra. The input cubes must be reordered with mode=312, and the output cubes will have the same ordering and thus must be reordered after being written to disk. RM-CLEAN runs as a MIRIAD (ascl:1106.007) task and a Python wrapper is included with the code.

Basic properties of lattices of cubes, algorithms for their construction, and application capabilities in discrete optimization

NASA Astrophysics Data System (ADS)

Khachaturov, R. V.

2015-01-01

The basic properties of a new type of lattices—a lattice of cubes—are described. It is shown that, with a suitable choice of union and intersection operations, the set of all subcubes of an N-cube forms a lattice, which is called a lattice of cubes. Algorithms for constructing such lattices are described, and the results produced by these algorithms in the case of lattices of various dimensions are illustrated. It is proved that a lattice of cubes is a lattice with supplements, which makes it possible to minimize and maximize supermodular functions on it. Examples of such functions are given. The possibility of applying previously developed efficient optimization algorithms to the formulation and solution of new classes of problems on lattices of cubes.

Design, Analysis and Testing of a PRSEUS Pressure Cube to Investigate Assembly Joints

NASA Technical Reports Server (NTRS)

Yovanof, Nicolette; Lovejoy, Andrew E.; Baraja, Jaime; Gould, Kevin

2012-01-01

Due to its potential to significantly increase fuel efficiency, the current focus of NASA's Environmentally Responsible Aviation Program is the hybrid wing body (HWB) aircraft. Due to the complex load condition that exists in HWB structure, as compared to traditional aircraft configurations, light-weight, cost-effective and manufacturable structural concepts are required to enable the HWB. The Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) concept is one such structural concept. A building block approach for technology development of the PRSEUS concept is being conducted. As part of this approach, a PRSEUS pressure cube was developed as a risk reduction test article to examine a new integral cap joint concept. This paper describes the design, analysis and testing of the PRSEUS pressure cube test article. The pressure cube was required to withstand a 2P, 18.4 psi, overpressure load requirement. The pristine pressure cube was tested to 2.2P with no catastrophic failure. After the addition of barely visible impact damage, the cube was pressure loaded to 48 psi where catastrophic failure occurred, meeting the scale-up requirement. Comparison of pretest and posttest analyses with the cube test response agree well, and indicate that current analysis methods can be used to accurately analyze PRSEUS structure for initial failure response.

Cube texture formation during the early stages of recrystallization of Al-1%wt.Mn and AA1050 aluminium alloys

NASA Astrophysics Data System (ADS)

Miszczyk, M. M.; Paul, H.

2015-08-01

The cube texture formation during primary recrystallization was analysed in plane strain deformed samples of a commercial AA1050 alloy and an Al-1%wt.Mn model alloy single crystal of the Goss{110}<001> orientation. The textures were measured with the use of X-ray diffraction and scanning electron microscopy equipped with an electron backscattered diffraction facility. After recrystallization of the Al-1%wt.Mn single crystal, the texture of the recrystallized grains was dominated by four variants of the S{123}<634> orientation. The cube grains were only sporadically detected by the SEM/EBSD system. Nevertheless, an increased density of <111> poles corresponding to the cube orientation was observed. The latter was connected with the superposition of four variants of the S{123}<634> orientation. This indicates that the cube texture after the recrystallization was a ‘compromise texture’. In the case of the recrystallized AA1050 alloy, the strong cube texture results from both the increased density of the particular <111> poles of the four variants of the S orientation and the ∼40°(∼< 111>)-type rotation. The first mechanism transforms the Sdef-oriented areas into Srex ones, whereas the second the near S-oriented, as-deformed areas into near cube-oriented grains.

Reducing the burden of diarrhea among children under five years old: lessons learned from oral rehydration therapy corner program implementation in Northern Nigeria.

PubMed

Charyeva, Zulfiya; Cannon, Molly; Oguntunde, Olugbenga; Garba, Aminu Magashi; Sambisa, William; Bassi, Amos Paul; Ibrahim, Mohammed Auwal; Danladi, Saba'atu Elizabeth; Lawal, Nurudeen

2015-05-01

In Nigeria, diarrhea remains one of the leading causes of death among children under five years old. Oral Rehydration Therapy (ORT) corners were introduced to health facilities in Bauchi and Sokoto states to serve as points of treatment for sick children and equip caregivers with necessary skills in case management of diarrhea and diarrhea prevention. The operations research study examined the effect of facility-based ORT corners on caregivers' knowledge and skills in management of simple and moderate diarrhea at home, as well as caregivers' and service providers' perceived facilitators and barriers to utilization and delivering of ORT corner services. It also examined whether ORT activities were conducted according to the established protocols. This quantitative study relied on multiple sources of information to provide a complete picture of the current status of ORT corner services, namely surveys with ORT corner providers (N = 21), health facility providers (N = 23) and caregivers (N = 229), as well as a review of service statistics and health facility observations. Frequency distribution and binary analysis were conducted. The study revealed that ORT corner users were more knowledgeable in diarrhea prevention and management and demonstrated better skills for managing diarrhea at home than ORT corner non-users. However, the percentage of knowledgeable ORT users is not optimal, and providers need to continue to work toward improving such knowledge. ORT corner providers identified a lack of supplies as the major barrier for providing services. Furthermore, the study revealed a lack of information, education and communication materials, supportive supervision, and protocols and guidelines for delivering ORT corner services, as well as inadequate documentation of services provided at ORT corners. Recommendations for ORT corners program planners and implementers include ensuring all ORT corners have oral rehydration salt (ORS) packages and salt, sugar, and zinc tablets in stock, a secured commodity supply chain to avoid stockouts, and adequate policies and procedures in place.

Mission Control Center (MCC) View - Apollo 13 Splashdown - MSC

NASA Image and Video Library

1970-04-17

S70-35145 (17 April 1970) --- Overall view of Mission Operations Control Room in Mission Control Center at the Manned Spacecraft Center (MSC) during the ceremonies aboard the USS Iwo Jima, prime recovery ship for the Apollo 13 mission. Dr. Donald K. Slayton (in black shirt, left of center), director of Flight Crew Operations at MSC, and Chester M. Lee of the Apollo Program Directorate, Office of Manned Space Flight, NASA Headquarters, shake hands, while Dr. Rocco A. Petrone, Apollo program director, Office of Manned Space Flight, NASA Headquarters (standing, near Lee), watches the large screen showing astronaut James A. Lovell Jr., Apollo 13 commander, during the onboard ceremonies. In the foreground, Glynn S. Lunney (extreme left) and Eugene F. Kranz (smoking a cigar), two Apollo 13 flight directors, view the activity from their consoles.

KSC-2012-6141

NASA Image and Video Library

2012-11-03

CAPE CANAVERAL, Fla. – Kennedy Space Center Director Bob Cabana checks out an item available for auction at the Astronaut Scholarship Foundation's dinner at the Radisson Resort at the Port in Cape Canaveral celebrating the 40th anniversary of Apollo 17. The auction of space-related memorabilia was held with proceeds supporting college scholarships for students who exhibit imagination and exceptional performance in science, technology, engineering and math. The gala commemorating the anniversary of Apollo 17 included mission commander Eugene Cernan and other astronauts who flew Apollo missions. Launched Dec. 7, 1972, Cernan and lunar module pilot Harrison Schmitt landed in the moon's Taurus-Littrow highlands while command module pilot Ronald Evans remained in lunar orbit operating a scientific instrument module. For more information, visit http://www-pao.ksc.nasa.gov/history/apollo/apollo-17/apollo-17.htm Photo credit: NASA/Kim Shiflett

Lunar Shape via the Apollo Laser Altimeter.

PubMed

Sjogren, W L; Wollenhaupt, W R

1973-01-19

Data from the Apollo 15 and Apollo 16 laser altimeters reveal the first accurate elevation differences between distant features on both sides of the moon. The large far-side depression observed in the Apollo 15 data is not present in the Apollo 16 data. When the laser results are compared with elevations on maps from the Aeronautical Chart and Information Center, differences of 2 kilometers over a few hundred kilometers are detected in the Mare Nubium and Mare Tranquillitatis regions. The Apollo 16 data alone would put a 2-kilometer bulge toward the earth; however, the combined data are best fit by a sphere of radius 1737.7 kilometers. The offset of the center of gravity from the optical center is about 2 kilometers toward the earth and 1 kilometer eastward. The polar direction parameters are not well determined.

Organics in APOLLO Lunar Samples

NASA Technical Reports Server (NTRS)

Allen, C. C.; Allton, J. H.

2007-01-01

One of many unknowns prior to the Apollo landings concerned the possibility of life, its remains, or its organic precursors on the surface of the Moon. While the existence of lunar organisms was considered highly unlikely, a program of biological quarantine and testing for the astronauts, the Apollo Command Modules, and the lunar rock and soil samples, was instituted in the Lunar Receiving Laboratory (LRL). No conclusive evidence of lunar organisms, was detected and the quarantine program was ended after Apollo 14. Analyses for organic compounds were also con-ducted. Considerable effort was expended, during lunar surface operations and in the LRL, to minimize and quantify organic contamination. Post-Apollo curatorial operations and cleaning minimize contamination from particulates, oxygen, and water but no longer specifically address organic contamination. The organic compounds measured in Apollo samples are generally consistent with known sources of contamination.

Corner Store Inventories, Purchases, and Strategies for Intervention: A Review of the Literature.

PubMed

Langellier, Brent A; Garza, Jeremiah R; Prelip, Michael L; Glik, Deborah; Brookmeyer, Ron; Ortega, Alexander N

2013-01-01

An increasingly popular strategy to improving the food retail environment and promoting healthy eating in low-income and minority communities is the corner store conversion. This approach involves partnering with small 'corner' food stores to expand access to high-quality fruits, vegetables, and other healthy foods. We conducted a structured review of the literature to assess inventories and sales in corner stores, as well as to identify intervention strategies employed by corner store conversions. Our review returned eight descriptive studies that discussed corner store inventories and sales, as well as ten intervention studies discussing six unique corner store conversion interventions in the United States, the Marshall Islands, and Canada. Common intervention strategies included: 1) partnering with an existing store, 2) stocking healthy foods, and 3) social marketing and nutrition education. We summarize each strategy and review the effectiveness of overall corner store conversions at changing peoples' food purchasing, preparation, and consumption behaviors. Consumption of fresh, healthy, affordable foods could be improved by supporting existing retailers to expand their selection of healthy foods and promoting healthy eating at the neighborhood level. Additional corner store conversions should be conducted to determine the effectiveness and importance of specific intervention strategies.

Prime crew of Apollo/Saturn Mission 204 prepares for water egress training

NASA Image and Video Library

1966-10-27

S66-58501 (27 Oct. 1966) --- The prime crew of the first manned Apollo Space Flight, Apollo/Saturn (AS) mission 204, is suited up aboard the NASA Motor Vessel Retriever (MVR) in preparation for Apollo water egress training in the Gulf of Mexico. Left to right, are astronauts Edward H. White II, senior pilot; Virgil I. Grissom, command pilot; and Roger B. Chaffee, pilot.

Apollo 9 Lunar Module in lunar landing configuration

NASA Technical Reports Server (NTRS)

1969-01-01

View of the Apollo 9 Lunar Module, in a lunar landing configuration, as photographed form the Command/Service Module on the fifth day of the Apollo 9 earth-orbital mission. The landing gear on the 'Spider' has been deployed. Lunar surface probes (sensors) extend out from the landing gear foot pads. Inside the 'Spider' were Astronauts James A. McDivitt, Apollo 9 commander; and Russell L. Schweickart, lunar module pilot.

Vertical view of Apollo 16 landing site located Descartes area lunar nearside

NASA Technical Reports Server (NTRS)

1971-01-01

A vertical view of the Apollo 16 landing site located in the Descartes area lunar nearside. The overlay indicates the location of the proposed touchdown point for the Apollo 16 Lunar Module. Descartes is located west of the Sea of Nectar and southwest of the Sea of Tranquility. This photograph was taken with a 500mm lens camera from lunar orbit by the Apollo 14 crew.

View of Apollo 17 lunar rock sample no. 72415,0

NASA Image and Video Library

1972-01-18

S73-16198 (December 1972) --- A close-up view of Apollo 17 lunar sample number 72415,0 which was brought back from the Taurus-Littrow landing site by the Apollo 17 crewmen. This sample is a brecciated dunite clast weighing a little over 32 grams (about 1.14 ounces). This sample was collected at station 2 (South Massif) during the second Apollo 17 extravehicular activity (EVA).

Apollo experience report: Mission planning for lunar module descent and ascent

NASA Technical Reports Server (NTRS)

Bennett, F. V.

1972-01-01

The premission planning, the real-time situation, and the postflight analysis for the Apollo 11 lunar descent and ascent are described. A comparison between premission planning and actual results is included. A navigation correction capability, developed from Apollo 11 postflight analysis was used successfully on Apollo 12 to provide the first pinpoint landing. An experience summary, which illustrates typical problems encountered by the mission planners, is also included.

Crew Members - First Manned Apollo Flight - Unmanned Mission Launch - Cape

NASA Image and Video Library

1968-01-22

S68-18700 (22 Jan. 1968) --- Two prime crew members of the first manned Apollo space flight were present at Cape Kennedy for the launch of the Apollo V (LM-1/Saturn 204) unmanned space mission. On left is astronaut Walter M. Schirra Jr.; and on right is astronaut R. Walter Cunningham. In background is the Apollo V stack at Launch Complex 37 ready for launch.

Saturn Apollo Program

NASA Image and Video Library

1975-07-01

SA-210 Apollo-Soyuz Test Project (ASTP) awaits the launch scheduled on July 15, 1975 on the launch pad at the Kennedy Space Center, the ASTP mission with astronauts Thomas Stafford, Vance Brand, and Donald "Deke" Slayton. The Saturn IB, developed under the direction of the Marshall Space Flight Center (MSFC), launched five manned Earth-orbital missions between 1968 and 1975: Apollo 7, Skylab 2, Skylab 3, Skylab 4, and the Apollo-Soyuz Test Project .

A multifunctional solar panel antenna for cube satellites

NASA Astrophysics Data System (ADS)

Fawole, Olutosin C.

The basic cube satellite (CubeSat) is a modern small satellite that has a standard size of about one liter (the 1U CubeSat). Three 1U CubeSats could be stacked to form a 3U CubeSat. Their low-cost, short development time, and ease of deployment make CubeSats popular for space research, geographical information gathering, and communication applications. An antenna is a key part of the CubeSat communication subsystem. Traditionally, antennas used on CubeSats are wrapped-up wire dipole antennas, which are deployed after satellite launch. Another antenna type used on CubeSats is the patch antenna. In addition to their low gain and efficiency, deployable dipole antennas may also fail to deploy on satellite launch. On the other hand, a solid patch antenna will compete for space with solar cells when placed on a CubeSat face, interfering with satellite power generation. Slot antennas are promising alternatives to dipole and patch antennas on CubeSats. When excited, a thin slot aperture etched on a conductive sheet (ground plane) is an efficient bidirectional radiator. This open slot antenna can be backed by a reflector or cavity for unidirectional radiation, and solar cells can be placed in spaces on the ground plane not occupied by the slot. The large surface areas of 3U CubeSats can be exploited for a multifunctional antenna by integrating multiple thin slot radiators, which are backed by a thin cavity on the CubeSat surfaces. Solar cells can then be integrated on the antenna surface. Polarization diversity and frequency diversity improve the overall performance of a communication system. Having a single radiating structure that could provide these diversities is desired. It has been demonstrated that when a probe excites a square cavity with two unequal length crossed-slots, the differential radiation from the two slots combines in the far-field to yield circular polarization. In addition, it has been shown that two equal-length proximal slots, when both fed with a stripline, resonate at a frequency due to their original lengths, and also resonate at a lower frequency due to mutual coupling between the slots, leading to a dual-band operation. The multifunctional antenna designs presented are harmonizations and extensions of these two independent works. In the multifunctional antenna designs presented, multiple slots were etched on a 83 mm x 340 mm two-layer shallow cavity. The slots were laid out on the cavity such when the cavity was excited by a probe at a particular point, the differential radiation from the slots would combine in the far-field to yield Left-Handed Circular Polarization (LHCP). Furthermore, when the cavity was excited by another probe at an opposite point, the slots would produce Right-Handed Circular Polarization (RHCP). In addition, as forethought, these slots were laid out on the cavity such that some slots were close together enough to give Linearly Polarized (LP) dual-band operation when fed with a stripline. This antenna was designed and optimized via computer simulations, fabricated using Printed Circuit Board (PCB) technology, and characterized using a Vector Network Analyzer (VNA) and NSI Far Field Systems.

49 CFR 231.29 - Road locomotives with corner stairways.

Code of Federal Regulations, 2011 CFR

2011-10-01

... ADMINISTRATION, DEPARTMENT OF TRANSPORTATION RAILROAD SAFETY APPLIANCE STANDARDS § 231.29 Road locomotives with corner stairways. After September 30, 1979, road locomotives with corner stairway openings must be... 49 Transportation 4 2011-10-01 2011-10-01 false Road locomotives with corner stairways. 231.29...

49 CFR 231.29 - Road locomotives with corner stairways.

Code of Federal Regulations, 2010 CFR

2010-10-01

... ADMINISTRATION, DEPARTMENT OF TRANSPORTATION RAILROAD SAFETY APPLIANCE STANDARDS § 231.29 Road locomotives with corner stairways. After September 30, 1979, road locomotives with corner stairway openings must be... 49 Transportation 4 2010-10-01 2010-10-01 false Road locomotives with corner stairways. 231.29...

Finite element model study of the effect of corner rounding on detectability of corner cracks using bolt hole eddy current

NASA Astrophysics Data System (ADS)

Underhill, P. R.; Krause, T. W.

2017-02-01

Recent work has shown that the detectability of corner cracks in bolt-holes is compromised when rounding of corners arises, as might occur during bolt-hole removal. Probability of Detection (POD) studies normally require a large number of samples of both fatigue cracks and electric discharge machined notches. In the particular instance of rounding of bolt-hole corners the generation of such a large set of samples representing the full spectrum of potential rounding would be prohibitive. In this paper, the application of Finite Element Method (FEM) modeling is used to supplement the study of detection of cracks forming at the rounded corners of bolt-holes. FEM models show that rounding of the corner of the bolt-hole reduces the size of the response to a corner crack to a greater extent than can be accounted for by loss of crack area. This reduced sensitivity can be ascribed to a lower concentration of eddy currents at the rounded corner surface and greater lift-off of pick-up coils relative to that of a straight-edge corner. A rounding with a radius of 0.4 mm (.016 inch) showed a 20% reduction in the strength of the crack signal. Assuming linearity of the crack signal with crack size, this would suggest an increase in the minimum detectable size by 25%.

Apollo Lunar Sample Integration into Google Moon: A New Approach to Digitization

NASA Technical Reports Server (NTRS)

Dawson, Melissa D.; Todd, nancy S.; Lofgren, Gary E.

2011-01-01

The Google Moon Apollo Lunar Sample Data Integration project is part of a larger, LASER-funded 4-year lunar rock photo restoration project by NASA s Acquisition and Curation Office [1]. The objective of this project is to enhance the Apollo mission data already available on Google Moon with information about the lunar samples collected during the Apollo missions. To this end, we have combined rock sample data from various sources, including Curation databases, mission documentation and lunar sample catalogs, with newly available digital photography of rock samples to create a user-friendly, interactive tool for learning about the Apollo Moon samples

Flight feeding systems design and evaluation. [the Apollo inflight menu design

NASA Technical Reports Server (NTRS)

Huber, C. S.

1973-01-01

The Apollo flight menu design is fully recounted for Apollo missions 7 through 17, to show modifications that were introduced to the Apollo food system, to document the range of menus and nutritional quality, and to describe packaging and preparation procedures for each class of food item. Papers concerning the Apollo 14 food system, and nutrition systems for pressure suits are included, and the following special topics are treated in depth: (1) food handling procedures; (2) modification of the physical properties of freeze dried rice; (3) stabilization of aerospace food waste; and (4) identification and quantitation of hexadecanal and octadecanal in broiler muscle phospholipids.