Steel Spheres and Skydiver--Terminal Velocity

ERIC Educational Resources Information Center

Costa Leme, J.; Moura, C.; Costa, Cintia

2009-01-01

This paper describes the use of open source video analysis software in the study of the relationship between the velocity of falling objects and time. We discuss an experiment in which a steel sphere falls in a container filled with two immiscible liquids. The motion is similar to that of a skydiver falling through air.

Sphere forming method and apparatus

NASA Technical Reports Server (NTRS)

Youngberg, C. L.; Miller, C. G.; Stephens, J. B.; Finnerty, A. A. (Inventor)

1983-01-01

A system is provided for forming small accurately spherical objects. Preformed largely spherical objects are supported at the opening of a conduit on the update of hot gas emitted from the opening, so the object is in a molten state. The conduit is suddenly jerked away at a downward incline, to allow the molten object to drop in free fall, so that surface tension forms a precise sphere. The conduit portion that has the opening, lies in a moderate vacuum chamber, and the falling sphere passes through the chamber and through a briefly opened valve into a tall drop tower that contains a lower pressure, to allow the sphere to cool without deformation caused by falling through air.

Upper atmospheric planetary-wave and gravity-wave observations

NASA Technical Reports Server (NTRS)

Justus, C. G.; Woodrum, A.

1973-01-01

Previously collected data on atmospheric pressure, density, temperature and winds between 25 and 200 km from sources including Meteorological Rocket Network data, ROBIN falling sphere data, grenade release and pitot tube data, meteor winds, chemical release winds, satellite data, and others were analyzed by a daily-difference method, and results on the magnitude of atmospheric perturbations interpreted as gravity waves and planetary waves are presented. Traveling planetary-wave contributions in the 25-85 km range were found to have significant height and latitudinal variation. It was found that observed gravity-wave density perturbations and wind are related to one another in the manner predicted by gravity-wave theory. It was determined that, on the average, gravity-wave energy deposition or reflection occurs at all altitudes except the 55-75 km region of the mesosphere.

The DROPPS/MIDAS Campaign Neutral Atmosphere Measurements and the Occurrence of PMSE and NLC

NASA Technical Reports Server (NTRS)

Schmidlin, F. J.; Schauer, A. G.; Zukor, Dorothy J. (Technical Monitor)

2001-01-01

Measurements of the neutral atmosphere and their relationship to electrodynamic conditions in the mesosphere have been of interest for many years. Inflatable falling sphere measurements along with electrodynamic measurements were obtained in conjunction with the occurrence of PMSE and NLC during the DROPPS/MIDAS Campaign conducted in July 1999 from Andenes Rocket Range, Norway. The inflatable failing sphere measurements in conjunction with a PMSE event on 5-6 July and with a NLC event on 14 July are used to infer thermal advection and its influence on the clouds' maintenance. Hodograph analysis, an early tropospheric tool used by analyst and forecasters, will be used to determine the magnitude and direction of thermal advection from measured wind data. Analysis of the wind structure through the use of hodographs and some assumptions can determine thermal advection, wind shear, and possible vertical motion. Changes in the temperature structure between allied observations were subtle which may be explained by advection. Because of meteorological instabilities in the mesosphere it is possible that hodograph analysis may not fully work. It is our intention to show that such analysis has value and has a place in the mesosphere.

Sphere launcher

NASA Technical Reports Server (NTRS)

Reed, W. B.

1972-01-01

The sphere launcher was designed to eject a 200 lb, 15 in. diameter sphere from a space vehicle or missile, at a velocity of 58 ft/sec without imparting excessive lateral loads to the vehicle. This launching is accomplished with the vehicle operating in vacuum conditions and under a 9 g acceleration. Two principal elements are used: a high thrust, short burn time rocket motor and two snubbers for reducing the lateral loads to acceptable limits.

Leidenfrost vapour layer moderation of the drag crisis and trajectories of superhydrophobic and hydrophilic spheres falling in water.

PubMed

Vakarelski, Ivan U; Chan, Derek Y C; Thoroddsen, Sigurdur T

2014-08-21

We investigate the dynamic effects of a Leidenfrost vapour layer sustained on the surface of heated steel spheres during free fall in water. We find that a stable vapour layer sustained on the textured superhydrophobic surface of spheres falling through 95 °C water can reduce the hydrodynamic drag by up to 75% and stabilize the sphere trajectory for the Reynolds number between 10(4) and 10(6), spanning the drag crisis in the absence of the vapour layer. For hydrophilic spheres under the same conditions, the transition to drag reduction and trajectory stability occurs abruptly at a temperature different from the static Leidenfrost point. The observed drag reduction effects are attributed to the disruption of the viscous boundary layer by the vapour layer whose thickness depends on the water temperature. Both the drag reduction and the trajectory stabilization effects are expected to have significant implications for development of sustainable vapour layer based technologies.

Stratospheric aluminum oxide.

PubMed

Brownlee, D E; Ferry, G V; Tomandl, D

1976-03-26

Balloons and U-2 aircraft were used to collect micrometer-sized strato-spheric aerosols. It was discovered that for the past 6 years at least, aluminum oxide spheres have been the major stratospheric particulate in the size range 3 to 8 micrometers. The most probable source of the spheres is the exhaust from solid-fuel rockets.

Free-Flight Test of a Technique for Inflating an NASA 12-Foot-Diameter Sphere at High Altitudes

NASA Technical Reports Server (NTRS)

Kehlet, Alan B.; Patterson, Herbert G.

1959-01-01

A free-flight test has been conducted to check a technique for inflating an NASA 12-foot-diameter inflatable sphere at high altitudes. Flight records indicated that the nose section was successfully separated from the booster rocket, that the sphere was ejected, and that the nose section was jettisoned from the fully inflated sphere. On the basis of preflight and flight records, it is believed that the sphere was fully inflated by the time of peak altitude (239,000 feet). Calculations showed that during descent, jettison of the nose section occurred above an altitude of 150,000 feet. The inflatable sphere was estimated to start to deform during descent at an altitude of about 120,000 feet.

Aerodynamic Characteristics of a Model of an Inflatable-Sphere Launching Vehicle under Simulated Conditions of Mach Number and Altitude

NASA Technical Reports Server (NTRS)

Robinson, Ross B.; Morris, Odell A.

1960-01-01

An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the aerodynamic characteristics in pitch of a two-stage-rocket model configuration which simulated the last two stages of the launching vehicle for an inflatable sphere. Tests were made through an angle-of-attack range from -6 deg to 18 deg at dynamic pressures of 102 and 255 pounds per square foot with corresponding Mach numbers of 1.89 and 1.98 for the model both with and without a bumper arrangement designed to protect the rocket casing from the outer shell of the vehicle.

Experimental Evaluation of the Drag Coefficient of Water Rockets by a Simple Free-Fall Test

ERIC Educational Resources Information Center

Barrio-Perotti, R.; Blanco-Marigorta, E. Arguelles-Diaz, K.; Fernandez-Oro, J.

2009-01-01

The flight trajectory of a water rocket can be reasonably calculated if the magnitude of the drag coefficient is known. The experimental determination of this coefficient with enough precision is usually quite difficult, but in this paper we propose a simple free-fall experiment for undergraduate students to reasonably estimate the drag…

The Rocket Equation Improvement under ICF Implosion Experiment

NASA Astrophysics Data System (ADS)

Wang, Yanbin; Zheng, Zhijian

2013-10-01

The ICF explosion process has been studied in details. The rocket equation has been improved in explosive process by introducing the pressure parameter of fuel. Some methods could be drawn by the improved rocket equation. And the methods could be used to improve ICF target design, driving pulse design and experimental design. The First is to increase ablation pressure. The second is to decrease pressure of fuel. The third is to use larger diameter of target sphere. And the forth is to a shorten driving pulse.

Electrostatic demonstration of free-fall weightlessness

NASA Astrophysics Data System (ADS)

Balukovic, Jasmina; Slisko, Josip; Corona Cruz, Adrian

2015-05-01

The phenomena of free-fall weightlessness have been demonstrated to students for many years in a number of different ways. The essential basis of all these demonstrations is the fact that in free-falling, gravitationally accelerated systems, the weight force and weight-related forces (for example, friction and hydrostatic forces) disappear. In this article, an original electrostatic demonstration of weightlessness is presented. A charged balloon fixed at the opening of a plastic container cannot lift a light styrofoam sphere sitting on the bottom when the container is at rest. However, while the system is in free-fall, the sphere becomes weightless and the charged balloon is able to lift it electrostatically.

[REAL AND UNREAL BACKLASHES OF AEROSPACE ACTIVITY FOR THE HEALTH OF POPULATION RESIDING NEAR AREAS OF FALL OF BEING SEPARATED PARTS OF CARRIER ROCKETS].

PubMed

Meshkov, N A; Valtseva, E A; Kharlamova, E N; Kulikova, A Z

2015-01-01

Since the late 1990s, the ongoing debate about the consequences of the rocket-space activities for the health of people residing near areas offall ofseparatingfrom parts of rockets. Some scientists (Kolyado IB et al., 2001, 2013; Shoikhet YN et al., 2005, 2008; Skrebtsova NV 2005, 2006, Sidorov PI et al., 2007) argue that the main cause of morbidity is the effect of unsymmetrical dimethyl hydrazine (UDMH). However, environmentalists find it only in areas offalling fragments of separated parts of carrier rockets. Presented in the article data were obtained as a result of perennial epidemiological and hygienic research. There was performed a hygienic assessment of the content of chemical substances in water soil andfood, nutritional status and health risk near areas of the district of falling 310 and 326. There were studied conditions of work and the health of military personnel at the sites of storage of propellant components. The relationship between revealed diseases and UDMH was not established, but there was their causality due to the influence of environmental factors characteristic of territories and living conditions. In the settlements near the area of falling district 310 the share of extremely anxious persons was shown to be 1.8 times higher than in controls, which is caused by cases of falling fragments stages of carrier rockets in the territory of settlements.

Hero's Engine

NASA Technical Reports Server (NTRS)

2004-01-01

Legendary characters used the power of mythology to fly through the heavens. About 200 BC, a Greek inventor known as Hero of Alexandria came up with a new invention that depended on the mechanical interaction of heat and water. He invented a rocket-like device called an aeolipile. It used steam for propulsion. Hero mounted a sphere on top of a water kettle. A fire below the kettle turned the water into steam, and the gas traveled through the pipes to the sphere. Two L-shaped tubes on opposite sides of the sphere allowed the gas to escape, and in doing so gave a thrust to the sphere that caused it to rotate.

The middle atmosphere above Andoya Norway during the winter 1983/84 as derived from metrockets and OH nightglow observations

NASA Technical Reports Server (NTRS)

Meyer, W.; Gerndt, R.; Philbrick, C. R.; Schmidlin, F. J.

1985-01-01

A total of 110 wind measurements were performed in the middle atmosphere above Andoya (69N, 16E) during the MAP/WINE Campaign from December 2, 1983 to February 23, 1984 using 57 inflatable passive falling spheres, 33 datasondes, 18 foil clouds and 2 instrumented active spheres. Temperature profiles were derived from 42 falling spheres, 26 datasondes and 2 active spheres. Near-mesopause temperatures were determined from OH nightglow observations. Synthesized charts of the temperatures as well as the zonal and meridional wind components between 0 and 90 km altitudes are presented. The temperature measurements indicate the occurrence of several minor and one major stratospheric warming, the latter being observed over Andoya at the end of the launch series.

World Presidents Organization

NASA Technical Reports Server (NTRS)

2010-01-01

Members of the World Presidents' Organization enjoy exhibits at StenniSphere, the visitor center and museum at NASA's John C. Stennis Space Center during a Jan. 26 visit to the site. WPO members from several states spent the day touring Stennis facilities and learning about the work of the nation's premier rocket engine testing site. Exhibits enjoyed included a mockup of the International Space Station and the interactive Science on a Sphere globe.

Some Considerations Relating to Combustion in Rocket Motors

DTIC Science & Technology

1950-03-01

evaporation and chemical reaction. Even the separate processes of heat and mass transfer under varying conditions are too complex for adequate theoretical...treatment although with the aid of dimensional analysis and experiment useful relationships for the heat transfer to spheres and for the evaporation of...if they do not evaporate sufficiently rapidly they may be carriod out of the rocket in the gas stream with a consequent loss in performance. 4

Passive control of a falling sphere by elliptic-shaped appendages

NASA Astrophysics Data System (ADS)

Lācis, Uǧis; Olivieri, Stefano; Mazzino, Andrea; Bagheri, Shervin

2017-03-01

The majority of investigations characterizing the motion of single or multiple particles in fluid flows consider canonical body shapes, such as spheres, cylinders, discs, etc. However, protrusions on bodies—either surface imperfections or appendages that serve a function—are ubiquitous in both nature and applications. In this work, we characterize how the dynamics of a sphere with an axis-symmetric wake is modified in the presence of thin three-dimensional elliptic-shaped protrusions. By investigating a wide range of three-dimensional appendages with different aspect ratios and lengths, we clearly show that the sphere with an appendage may robustly undergo an inverted-pendulum-like (IPL) instability. This means that the position of the appendage placed behind the sphere and aligned with the free-stream direction is unstable, similar to how an inverted pendulum is unstable under gravity. Due to this instability, nontrivial forces are generated on the body, leading to turn and drift, if the body is free to fall under gravity. Moreover, we identify the aspect ratio and length of the appendage that induces the largest side force on the sphere, and therefore also the largest drift for a freely falling body. Finally, we explain the physical mechanisms behind these observations in the context of the IPL instability, i.e., the balance between surface area of the appendage exposed to reversed flow in the wake and the surface area of the appendage exposed to fast free-stream flow.

Optimum radars and filters for the passive sphere system

NASA Technical Reports Server (NTRS)

Luers, J. K.; Soltes, A.

1971-01-01

Studies have been conducted to determine the influence of the tracking radar and data reduction technique on the accuracy of the meteorological measurements made in the 30 to 100 kilometer altitude region by the ROBIN passive falling sphere. A survey of accuracy requirements was made of agencies interested in data from this region of the atmosphere. In light of these requirements, various types of radars were evaluated to determine the tracking system most applicable to the ROBIN, and methods were developed to compute the errors in wind and density that arise from noise errors in the radar supplied data. The effects of launch conditions on the measurements were also examined. Conclusions and recommendations have been made concerning the optimum tracking and data reduction techniques for the ROBIN falling sphere system.

Rheological Studies of Komatiite Liquids by In-Situ Falling Sphere Viscometry

NASA Astrophysics Data System (ADS)

O Dwyer, L.; Lesher, C. E.; Baxter, G.; Clark, A.; Fuss, T.; Tangeman, J.; Wang, Y.

2005-12-01

The rheological properties of komatiite liquids at high pressures and temperatures are being investigated by the in situ falling sphere technique, using the T-25 multianvil apparatus at the GSECARS 13 ID-D-D beamline at the Advanced Photon Source, ANL. The refractory and fluid nature of komatiite and other ultramafic liquids relevant to the Earth's deep interior, presents unique challenges for this approach. To reduce the density contrast between the melt and the marker sphere, and thus increase the Stoke's travel time, we have begun testing various composite spheres composed of refractory silicates and metals. Two successful custom designs are zirconia silicate mantled by Pt and Pt mantled by forsterite. These custom spheres contain sufficient Pt to absorb x-rays, while containing sufficient low-density refractory silicate so that marker sphere densities are in the range of 4-6 g/cc. These relatively more buoyant spheres increase travel time. These custom spheres, together with Re or Pt marker spheres, have been used to determine the viscosity of Gorgona anhydrous komatiite around 1600 ° C between 3.5 and 6 GPa. Initial experiments yield viscosities of 2.8 Pa s at 3.5 GPa, 5.3 Pa s at 4.6 GPa and 7.6 Pa s at 6 GPa. The observed positive pressure dependence of viscosity is consistent with recent results on pyrolite composition liquids and suggests that the activation volume for highly depolymerized melts will be positive for at least upper mantle conditions. The development of low-density, x-ray detectable marker spheres has applications in studies of melt density, whereby in situ detection of sink-float behavior during heating and compression cycles may be possible.

Structural Analysis and Testing of the Inflatable Re-entry Vehicle Experiment (IRVE)

NASA Technical Reports Server (NTRS)

Lindell, Michael C.; Hughes, Stephen J.; Dixon, Megan; Wiley, Cliff E.

2006-01-01

The Inflatable Re-entry Vehicle Experiment (IRVE) is a 3.0 meter, 60 degree half-angle sphere cone, inflatable aeroshell experiment designed to demonstrate various aspects of inflatable technology during Earth re-entry. IRVE will be launched on a Terrier-Improved Orion sounding rocket from NASA s Wallops Flight Facility in the fall of 2006 to an altitude of approximately 164 kilometers and re-enter the Earth s atmosphere. The experiment will demonstrate exo-atmospheric inflation, inflatable structure leak performance throughout the flight regime, structural integrity under aerodynamic pressure and associated deceleration loads, thermal protection system performance, and aerodynamic stability. Structural integrity and dynamic response of the inflatable will be monitored with photogrammetric measurements of the leeward side of the aeroshell during flight. Aerodynamic stability and drag performance will be verified with on-board inertial measurements and radar tracking from multiple ground radar stations. In addition to demonstrating inflatable technology, IRVE will help validate structural, aerothermal, and trajectory modeling and analysis techniques for the inflatable aeroshell system. This paper discusses the structural analysis and testing of the IRVE inflatable structure. Equations are presented for calculating fabric loads in sphere cone aeroshells, and finite element results are presented which validate the equations. Fabric material properties and testing are discussed along with aeroshell fabrication techniques. Stiffness and dynamics tests conducted on a small-scale development unit and a full-scale prototype unit are presented along with correlated finite element models to predict the in-flight fundamental mod

Effect of pressure on viscosity of liquid Fe-alloys up to 16 GPa

NASA Astrophysics Data System (ADS)

Terasaki, H.; Ohtani, E.; Suzuki, A.; Nishida, K.; Sakamaki, T.; Shindo, S.; Funakoshi, K.

2005-12-01

Viscosity of liquid Fe-alloy is closely related to a convection behavior of the Earth's liquid outer core and also time scale of planetary core formation. In previous studies, viscosity of liquid Fe-S has been measured up to 7 GPa using X-ray radiography falling sphere method [Terasaki et al. 2001]. However, some technical problems, such as chemical reaction between the metal marker sphere and the Fe-alloy sample and insufficient image recording time for less viscous material, have been suggested. In this study, we have measured the viscosity of Fe-S and Fe-C liquids without those problems by using novel techniques combined with in situ X-ray radiography falling sphere method and extended the pressure range to 16 GPa. Falling sphere viscometry was carried out under high pressure and temperature using high speed CCD camera with 1500 ton Kawai-type multi-anvil device at BL04B1, SPring-8 in Japan. Starting compositions of Fe-alloy were Fe78S22 and Fe86C14 which correspond to near eutectic compositions at the experimental pressures. Viscosity marker sphere, which was made of Re or Pt, was coated by alumina in order to prevent the reaction between the sphere and the Fe-alloy sample. Falling sphere images were obtained with recording rate of 50 - 125 frame/second. Viscosity of liquid Fe-S was measured up to 16.1 GPa and 1763 K. Measured viscosity coefficients were in the range of 8.8 - 9.2 mPa-s which indicates that the activation volume of viscous flow is approximately a half of the previous estimations (1.5 cm3/mol). Viscosity of liquid Fe-C was measured up to 5 GPa and 1843 K. Viscosity coefficients are 4.7 - 4.9 mPa-s. Activation volume of Fe-C liquid is estimated to be 0.8 cm3/mol. This pressure dependence is consistent with the result of Lucas (1964) measured at ambient pressure. Consequently, viscosity of Fe-alloy liquids are likely to stay small in the Earth's interior and there is no large difference in viscosity coefficient and activation volume between Fe-S and Fe-C eutectic liquids in the range of measurements.

Description and Flight Performance Results of the WASP Sounding Rocket

NASA Technical Reports Server (NTRS)

De Pauw, J. F.; Steffens, L. E.; Yuska, J. A.

1968-01-01

A general description of the design and construction of the WASP sounding rocket and of the performance of its first flight are presented. The purpose of the flight test was to place the 862-pound (391-kg) spacecraft above 250 000 feet (76.25 km) on free-fall trajectory for at least 6 minutes in order to study the effect of "weightlessness" on a slosh dynamics experiment. The WASP sounding rocket fulfilled its intended mission requirements. The sounding rocket approximately followed a nominal trajectory. The payload was in free fall above 250 000 feet (76.25 km) for 6.5 minutes and reached an apogee altitude of 134 nautical miles (248 km). Flight data including velocity, altitude, acceleration, roll rate, and angle of attack are discussed and compared to nominal performance calculations. The effect of residual burning of the second stage motor is analyzed. The flight vibration environment is presented and analyzed, including root mean square (RMS) and power spectral density analysis.

METHOD AND APPARATUS FOR DETERMINING CHARGED PARTICLE MOTION

DOEpatents

Kerns, Q.A.

1959-08-01

An analog system for determining the motion of charged particles in three dimensional electrical fields is described. A model electrode structure is formed and potentials are applied to the electrodes to provide an analog of the field which is to be studied. To simulate charged particles within the model, conducting spheres are placed at points from which particle motion is to be traced. To free the spheres from gravitational attraction in order that they will be electrostatically accelerated through the model, the apparatus is suspended and dropped. During the pericd that the model is dropping the spheres move through the electrcde structure with a motion corresponding to that of particles in the real system. The model is photographed in the course of falling so that the instantaneous position of the spheres within the simulated field at selected times may be observed and measured. The device thus gives data of particles in the real system. The model is photographed in the course of falling so that the instantaneous position of the spheres within the simulated field at selected times may be observed and measured. The device thus gives data which frequently can otherwise be obtained only with a digital computer.

Output-increasing, protective cover for a solar cell

DOEpatents

Hammerbacher, Milfred D.

1995-11-21

A flexible cover (14) for a flexible solar cell (12) protects the cell from the ambient and increases the cell's efficiency. The cell(12)includes silicon spheres (16) held in a flexible aluminum sheet matrix (20,22). The cover (14) is a flexible, protective layer (60) of light-transparent material having a relatively flat upper, free surface (64) and an irregular opposed surface (66). The irregular surface (66) includes first portions (68) which conform to the polar regions (31R) of the spheres (16) and second convex (72) or concave (90) portions (72 or 90) which define spaces (78) in conjunction with the reflective surface (20T) of one aluminum sheet (20). Without the cover (14) light (50) falling on the surface (20T) between the spheres (16) is wasted, that is, it does not fall on a sphere (16). The surfaces of the second portions are non-parallel to the direction of the otherwise wasted light (50), which fact, together with a selected relationship between the refractive indices of the cover and the spaces, result in sufficient diffraction of the otherwise wasted light (50) so that about 25% of it is reflected from the surface (20T) onto a sphere (16).

Experimental evaluation of the drag coefficient for smooth spheres by free fall experiments in old mines

NASA Astrophysics Data System (ADS)

Maroto, J. A.; Dueñas-Molina, J.; de Dios, J.

2005-05-01

Mines of Linares, Jaén, Spain, have been exploited from the age of the Phoenicians, Carthaginians and Romans. These silver and lead mines reached their maximum splendour at the end of the 19th century and at the beginning of the 20th century. Nevertheless, all the mining works finished in the 1970s and the diverse machinery was sold. Only the shafts remain since then which has now permitted carrying out interesting free fall experiments using smooth spheres of both cork and cast iron. The experiments were facilitated by the fact that the tubular shape of the shafts provides excellent transmission of sound, which made feasible the recording of the impact sound of the spheres with water at the bottom of the shafts at distances of up to 200 m. By using these experimental data, we have carried out an evaluation of the drag coefficient for the movement of smooth spheres through the air in the laminar regime with Reynolds number in the interval 103 to 2 × 105. This evaluation was in excellent agreement with the literature data. From the theoretical point of view, the analysis of the free fall movement includes a variety of concepts such as Newton's second law, the drag force, Archimedes principle and the velocity of sound, which makes these experiments very attractive for both physics teachers and physics students at university level. Finally, an easy experiment is proposed in this paper which has permitted an approximate evaluation of the drag coefficient for smooth spheres to be carried out in a laboratory environment.

Short and long periodic atmospheric variations between 25 and 200 km

NASA Technical Reports Server (NTRS)

Justus, C. G.; Woodrum, A.

1973-01-01

Previously collected data on atmospheric pressure, density, temperature and winds between 25 and 200 km from sources including Meteorological Rocket Network data, ROBIN falling sphere data, grenade release and pitot tube data, meteor winds, chemical release winds, satellite data, and others were analyzed by a daily difference method and results on the distribution statistics, magnitude, and spatial structure of gravity wave and planetary wave atmospheric variations are presented. Time structure of the gravity wave variations were determined by the analysis of residuals from harmonic analysis of time series data. Planetary wave contributions in the 25-85 km range were discovered and found to have significant height and latitudinal variation. Long period planetary waves, and seasonal variations were also computed by harmonic analysis. Revised height variations of the gravity wave contributions in the 25 to 85 km height range were computed. An engineering method and design values for gravity wave magnitudes and wave lengths are given to be used for such tasks as evaluating the effects on the dynamical heating, stability and control of spacecraft such as the space shuttle vehicle in launch or reentry trajectories.

Catcher’s Mitt Final Report

DTIC Science & Technology

2011-08-30

launch systems and procedures do not conform to and spacecraft (both satellites and rocket bodies) are not properly disposed of in accordance with...Concepts of this class include the use of whipple shields, aerogel panels or structures, large multi-hulled spheres, and layered open-cell foam

Catalytic, hollow, refractory spheres, conversions with them

NASA Technical Reports Server (NTRS)

Wang, Taylor G. (Inventor); Elleman, Daniel D. (Inventor); Lee, Mark C. (Inventor); Kendall, Jr., James M. (Inventor)

1989-01-01

Improved, heterogeneous, refractory catalysts are in the form of gas-impervious, hollow, thin-walled spheres (10) suitable formed of a shell (12) of refractory such as alumina having a cavity (14) containing a gas at a pressure greater than atmospheric pressure. The wall material may be itself catalytic or a catalytically active material coated onto the sphere as a layer (16), suitably platinum or iron, which may be further coated with a layer (18) of activator or promoter. The density of the spheres (30) can be uniformly controlled to a preselected value within .+-.10 percent of the density of the fluid reactant such that the spheres either remain suspended or slowly fall or rise through the liquid reactant.

Catalytic, hollow, refractory spheres

NASA Technical Reports Server (NTRS)

Wang, Taylor G. (Inventor); Elleman, Daniel D. (Inventor); Lee, Mark C. (Inventor); Kendall, Jr., James M. (Inventor)

1987-01-01

Improved, heterogeneous, refractory catalysts are in the form of gas-impervious, hollow, thin-walled spheres (10) suitable formed of a shell (12) of refractory such as alumina having a cavity (14) containing a gas at a pressure greater than atmospheric pressure. The wall material may be itself catalytic or a catalytically active material coated onto the sphere as a layer (16), suitably platinum or iron, which may be further coated with a layer (18) of activator or promoter. The density of the spheres (30) can be uniformly controlled to a preselected value within .+-.10 percent of the density of the fluid reactant such that the spheres either remain suspended or slowly fall or rise through the liquid reactant.

Catalytic hollow spheres

NASA Technical Reports Server (NTRS)

Wang, Taylor G. (Inventor); Elleman, Daniel D. (Inventor); Lee, Mark C. (Inventor); Kendall, Jr., James M. (Inventor)

1989-01-01

The improved, heterogeneous catalysts are in the form of gas-impervious, hollow, thin-walled spheres (10) suitably formed of a shell (12) of metal such as aluminum having a cavity (14) containing a gas at a pressure greater than atmospheric pressure. The wall material may be, itself, catalytic or the catalyst can be coated onto the sphere as a layer (16), suitably platinum or iron, which may be further coated with a layer (18) of activator or promoter. The density of the spheres (30) can be uniformly controlled to a preselected value within .+-.10 percent of the density of the fluid reactant such that the spheres either remain suspended or slowly fall or rise through the liquid reactant.

Catalytic hollow spheres

NASA Technical Reports Server (NTRS)

Wang, Taylor G. (Inventor); Elleman, Daniel D. (Inventor); Lee, Mark C. (Inventor); Kendall, Jr., James M. (Inventor)

1986-01-01

The improved, heterogeneous catalysts are in the form of gas-impervious, hollow, thin-walled spheres (10) suitably formed of a shell (12) of metal such as aluminum having a cavity (14) containing a gas at a pressure greater than atmospheric pressure. The wall material may be, itself, catalytic or the catalyst can be coated onto the sphere as a layer (16), suitably platinum or iron, which may be further coated with a layer (18) of activator or promoter. The density of the spheres (30) can be uniformly controlled to a preselected value within .+-.10 percent of the density of the fluid reactant such that the spheres either remain suspended or slowly fall or rise through the liquid reactant.

Performance prediction of a ducted rocket combustor

NASA Astrophysics Data System (ADS)

Stowe, Robert

2001-07-01

The ducted rocket is a supersonic flight propulsion system that takes the exhaust from a solid fuel gas generator, mixes it with air, and burns it to produce thrust. To develop such systems, the use of numerical models based on Computational Fluid Dynamics (CFD) is increasingly popular, but their application to reacting flow requires specific attention and validation. Through a careful examination of the governing equations and experimental measurements, a CFD-based method was developed to predict the performance of a ducted rocket combustor. It uses an equilibrium-chemistry Probability Density Function (PDF) combustion model, with a gaseous and a separate stream of 75 nm diameter carbon spheres to represent the fuel. After extensive validation with water tunnel and direct-connect combustion experiments over a wide range of geometries and test conditions, this CFD-based method was able to predict, within a good degree of accuracy, the combustion efficiency of a ducted rocket combustor.

Using EPSAT to analyze high power systems in the space environment. [Environment Power System Analysis Tool

NASA Technical Reports Server (NTRS)

Kuharski, Robert A.; Jongeward, Gary A.; Wilcox, Katherine G.; Rankin, Tom R.; Roche, James C.

1991-01-01

The authors review the Environment Power System Analysis Tool (EPSAT) design and demonstrate its capabilities by using it to address some questions that arose in designing the SPEAR III experiment. It is shown that that the rocket body cannot be driven to large positive voltages under the constraints of this experiment. Hence, attempts to measure the effects of a highly positive rocket body in the plasma environment should not be made in this experiment. It is determined that a hollow cathode will need to draw only about 50 mA to ground the rocket body. It is shown that a relatively small amount of gas needs to be released to induce a bulk breakdown near the rocket body, and this gas release should not discharge the sphere. Therefore, the experiment provides an excellent opportunity to study the neutralization of a differential charge.

Change in serum lipids after acute coronary syndromes: secondary analysis of SPACE ROCKET study data and a comparative literature review.

PubMed

Barth, Julian H; Jackson, Beryl M; Farrin, Amanda J; Efthymiou, Maria; Worthy, Gillian; Copeland, Joanne; Bailey, Kristian M; Romaine, Simon P R; Balmforth, Anthony J; McCormack, Terry; Whitehead, Andrew; Flather, Marcus D; Nixon, Jane; Hall, Alistair S

2010-10-01

It has long been an accepted belief that serum cholesterol significantly falls after myocardial infarction and that a return to pre-event levels takes approximately 3 months. The magnitude and clinical significance of this fall has recently been challenged. In the Secondary Prevention of Acute Coronary Events-Reduction Of Cholesterol to Key European Targets (SPACE ROCKET) trial, we measured serum lipids of individuals on day 1 and between days 2 and 4 after acute myocardial infarction (AMI). Second, we performed a thorough literature review and compared all studies reporting data on absolute changes in lipids immediately after AMI, using weighted means. Of 1263 SPACE ROCKET participants, 128 had paired lipid measurements where both samples had been measured using identical methods at baseline and on days 2-4 after AMI. The mean lowering in total cholesterol between day 1 and day 2-4 was 0.71 mmol/L (95% CI 0.58-0.84; P < 0.0001) and in triglycerides was 0.10 mmol/L (-0.14-0.33; P = 0.405). A total of 25 papers showing absolute lipid changes post-AMI were identified. The combined data demonstrated a mean fall in total cholesterol of 9% to 11% from baseline over days 3-14 post-AMI, whereas for triglycerides, there was a rise of 18% from baseline to between day 9 and 12 weeks. After a secondary analysis of SPACE ROCKET data and a comparison of previously published data, we report a 10% fall in total cholesterol after AMI-a difference that is of high clinical significance. Consequently, measurement of serum lipids in patients with AMI should be performed within the first hours after presentation.

Atmospheric scavenging of hydrochloric acid. [from rocket exhaust

NASA Technical Reports Server (NTRS)

Knutson, E. O.; Fenton, D. L.

1975-01-01

The scavenging of hydrogen chloride from a solid rocket exhaust cloud was investigated. Water drops were caused to fall through a confined exhaust cloud and then analyzed to determine the amount of HCl captured during fall. Bubblers were used to measure HCl concentration within the chamber. The measured chamber HCl concentration, together with the measured HCl deposition on the chamber walls, accounted for 81 to 94% of the theoretical HCl. It was found that the amount of HCl captured was approximately one-half of that predicted by the Frossling correlation. No effect of humidity was detected through a range of 69-98% R.H.. The scavenging of HCl from a solid rocket exhaust cloud was calculated using an idealized Kennedy Space Center rain cycle. Results indicate that this cycle would reduce the cloud HCl concentration to 20.6% if its value in the absence of rain.

Munitions Classification Library

DTIC Science & Technology

2016-04-04

F/B N N Practice Rockeye MK118 S Y Y N N U/P N N Practice 25-lb Mk76 B Y N N N F/B N N BDU-33 Practice Bomb 2.25-in SCAR Mk4 Mod0 R Y Y N N F/W Y N...Sphere SO N N N N Pristine Y Y steel 1 P = Projectile; G = Grenade; M = Mortar; R = Rocket; S = Submunition; B = Bomb ; RWH = Rocket Warhead; SO...many of the remaining outstanding desired items as possible and ranged in size from very small munitions (50 cal) all the way up to a 250-lb bomb

Simulations of two sedimenting-interacting spheres with different sizes and initial configurations using immersed boundary method

NASA Astrophysics Data System (ADS)

Liao, Chuan-Chieh; Hsiao, Wen-Wei; Lin, Ting-Yu; Lin, Chao-An

2015-06-01

Numerical investigations are carried out for the drafting, kissing and tumbling (DKT) phenomenon of two freely falling spheres within a long container by using an immersed-boundary method. The method is first validated with flows induced by a sphere settling under gravity in a small container for which experimental data are available. The hydrodynamic interactions of two spheres are then studied with different sizes and initial configurations. When a regular sphere is placed below the larger one, the duration of kissing decreases in pace with the increase in diameter ratio. On the other hand, the time duration of the kissing stage increases in tandem with the increase in diameter ratio as the large sphere is placed below the regular one, and there is no DKT interactions beyond threshold diameter ratio. Also, the gap between homogeneous spheres remains constant at the terminal velocity, whereas the gaps between the inhomogeneous spheres increase due to the differential terminal velocity.

Self-determined shapes and velocities of giant near-zero drag gas cavities

PubMed Central

Vakarelski, Ivan U.; Klaseboer, Evert; Jetly, Aditya; Mansoor, Mohammad M.; Aguirre-Pablo, Andres A.; Chan, Derek Y. C.; Thoroddsen, Sigurdur T.

2017-01-01

Minimizing the retarding force on a solid moving in liquid is the canonical problem in the quest for energy saving by friction and drag reduction. For an ideal object that cannot sustain any shear stress on its surface, theory predicts that drag force will fall to zero as its speed becomes large. However, experimental verification of this prediction has been challenging. We report the construction of a class of self-determined streamlined structures with this free-slip surface, made up of a teardrop-shaped giant gas cavity that completely encloses a metal sphere. This stable gas cavity is formed around the sphere as it plunges at a sufficiently high speed into the liquid in a deep tank, provided that the sphere is either heated initially to above the Leidenfrost temperature of the liquid or rendered superhydrophobic in water at room temperature. These sphere-in-cavity structures have residual drag coefficients that are typically less than 110 those of solid objects of the same dimensions, which indicates that they experienced very small drag forces. The self-determined shapes of the gas cavities are shown to be consistent with the Bernoulli equation of potential flow applied on the cavity surface. The cavity fall velocity is not arbitrary but is uniquely predicted by the sphere density and cavity volume, so larger cavities have higher characteristic velocities. PMID:28913434

Entry, Descent, and Landing With Propulsive Deceleration: Supersonic Retropropulsion Wind Tunnel Testing

NASA Technical Reports Server (NTRS)

Palaszewski, Bryan

2012-01-01

The future exploration of the Solar System will require innovations in transportation and the use of entry, descent, and landing (EDL) systems at many planetary landing sites. The cost of space missions has always been prohibitive, and using the natural planetary and planet s moons atmosphere for entry, descent, and landing can reduce the cost, mass, and complexity of these missions. This paper will describe some of the EDL ideas for planetary entry and survey the overall technologies for EDL that may be attractive for future Solar System missions. Future EDL systems may include an inflatable decelerator for the initial atmospheric entry and an additional supersonic retro-propulsion (SRP) rocket system for the final soft landing. As part of those efforts, NASA began to conduct experiments to gather the experimental data to make informed decisions on the "best" EDL options. A model of a three engine retro-propulsion configuration with a 2.5 in. diameter sphere-cone aeroshell model was tested in the NASA Glenn 1- by 1-Foot Supersonic Wind Tunnel (SWT). The testing was conducted to identify potential blockage issues in the tunnel, and visualize the rocket flow and shock interactions during supersonic and hypersonic entry conditions. Earlier experimental testing of a 70 Viking-like (sphere-cone) aeroshell was conducted as a baseline for testing of a supersonic retro-propulsion system. This baseline testing defined the flow field around the aeroshell and from this comparative baseline data, retro-propulsion options will be assessed. Images and analyses from the SWT testing with 300- and 500-psia rocket engine chamber pressures are presented here. The rocket engine flow was simulated with a non-combusting flow of air.

The importance of precision radar tracking data for the determination of density and winds from the high-altitude inflatable sphere

NASA Technical Reports Server (NTRS)

Schmidlin, F. J.; Michel, W. R.

1985-01-01

Analysis of inflatable sphere measurements obtained during the Energy Budget and MAP/WINE campaigns led to questions concerning the precision of the MPS-36 radar used for tracking the spheres; the compatibility of the sphere program with the MPS-36 radar tracking data; and the oversmoothing of derived parameters at high altitudes. Simulations, with winds having sinusoidal vertical wavelengths, were done with the sphere program (HIROBIN) to determine the resolving capability of various filters. It is concluded that given a precision radar and a perfectly performing sphere, the HIROBIN filters can be adjusted to provide small-scale perturbation information to 70 km (i.e., sinusoidal wavelengths of 2 km). It is recommended that the HIROBIN program be modified to enable it to use a variable length filter, that adjusts to fall velocity and accelerations to provide wind data with small perturbations.

Solid Rocket Booster Separation

NASA Technical Reports Server (NTRS)

1998-01-01

This Quick Time movie shows the Space Shuttle Solid Rocket Booster (SRB) separation from the external tank (ET). After separation, the boosters fall to the ocean from which they are retrieved and refurbished for reuse. The Shuttle's SRB's and solid rocket motors (SRM's) are the largest ever built and the first designed for refurbishment and reuse. Standing nearly 150-feet high, the twin boosters provide the majority of thrust for the first two minutes of flight, about 5.8 million pounds. That is equivalent to 44 million horsepower, or the combined power of 400,000 subcompact cars.

"Sphere" as a Gendered Space: Cognitive Linguistic Models of Conceptual Metaphor and Embodiment in Nineteenth-Century Women's Rights Discourse

ERIC Educational Resources Information Center

Smith, Carol Lynn Kay

2009-01-01

This study contributes an approach to understanding the cognitive models underlying rhetorical arguments about the "first wave" of women's rights discourse in the United States, which began to emerge more publically with the Seneca Falls convention in 1848 and started to gain momentum in 1851 and beyond. The usage of the lexical item "sphere" (in…

Kinetic Temperature and Carbon Dioxide from Broadband Infrared Limb Emission Measurements Taken from the TIMED/SABER Instrument

NASA Technical Reports Server (NTRS)

Mertens, Christopher J.; Russell III, James M.; Mlynczak, Martin G.; She, Chiao-Yao; Schmidlin, Francis J.; Goldberg, Richard A.; Lopez-Puertas, Manuel; Wintersteiner, Peter P.; Picard, Richard H.; Winick, Jeremy R.;

Location of space debris by infrasound

NASA Astrophysics Data System (ADS)

Asming, Vladimir; Vinogradov, Yuri

2013-04-01

After an exhausted stage has separated from a rocket it comes back to the dense atmosphere. It burns and divides into many pieces moving separately. Ballisticians can calculate an approximate trace of a falling stage and outline a supposed area where the debris can fall (target ellipse). Such ellipses are usually rather big in sizes (something like 60 x 100 km). For safety reasons all local inhabitants should be evacuated from a target area during rocket's launch. One of problems is that the ballistician can not compute the traces and areas exactly. There were many cases when debris had fallen outside the areas. Rescue teams must check such cases to make changes in rockets. The largest pieces can contain remains of toxic rocket fuel and therefore must be found and deactivated. That is why the problem of debris location is of significant importance for overland fall areas. It is more or less solved in Kazakhstan where large fragments of 1st stages can be seen in the Steppe but it is very difficult to find fragments of 2nd stages in Altai, Tomsk region and Komi republic (taiga, mountains, swamps). The rocket debris produces strong infrasonic shock waves during their reentry. Since 2009 the Kola Branch of Geophysical Survey of RAS participates in joint project with Khrunichev Space Center concerning with infrasound debris location. We have developed mobile infrasound arrays consisting of 3 microphones, analog-to-digit converter, GPS and notebook. The aperture is about 200 m, deployment time is less than 1 hour. Currently we have 4 such arrays, one of them is wireless and consists of 3 units comprising a microphone, GPS and radio-transmitter. We have made several field measurements by 3 or 4 such arrays placed around target ellipses of falling rocket stages in Kazakhstan ("Soyuz" rocket 1st stage), Altai and Tomsk region ("Proton" rocket 2nd stages). If was found that a typical 2nd stage divides into hundreds of pieces and each one generates a shock wave. This is a complicated problem to associate signals registered by different arrays. We developed an approach based on modeling of realistic fragment trajectories. We assume that until some time t0 all stage is moving along the predicted theoretical trajectory. At the time t0 (disintegration) the pieces receive different ballistic coefficients and random increments of velocity. We continue the trajectory (solving 2nd order differential equation) using the coordinates at t0 and velocities with random increments as initial conditions and with different ballistic coefficients. Thus we obtain a 'pipe' of trajectories each one can in principle occur in reality. For each trajectory of the pipe we compute theoretical times and azimuths of shock wave arrivals to the arrays. If they are in agreement with the measured arrivals we consider that the trajectory has occurred in reality and its end is the landing place of a rocket fragment. The experiment of "Soyuz" 1st stage location in Kazakhstan has shown that errors of such location are less than 2 km that is acceptable to use the method in practice.

SPHERES National Lab Facility

NASA Technical Reports Server (NTRS)

Benavides, Jose

2014-01-01

SPHERES is a facility of the ISS National Laboratory with three IVA nano-satellites designed and delivered by MIT to research estimation, control, and autonomy algorithms. Since Fall 2010, The SPHERES system is now operationally supported and managed by NASA Ames Research Center (ARC). A SPHERES Program Office was established and is located at NASA Ames Research Center. The SPHERES Program Office coordinates all SPHERES related research and STEM activities on-board the International Space Station (ISS), as well as, current and future payload development. By working aboard ISS under crew supervision, it provides a risk tolerant Test-bed Environment for Distributed Satellite Free-flying Control Algorithms. If anything goes wrong, reset and try again! NASA has made the capability available to other U.S. government agencies, schools, commercial companies and students to expand the pool of ideas for how to test and use these bowling ball-sized droids. For many of the researchers, SPHERES offers the only opportunity to do affordable on-orbit characterization of their technology in the microgravity environment. Future utilization of SPHERES as a facility will grow its capabilities as a platform for science, technology development, and education.

Magnetization of small iron-nickel spheres

NASA Technical Reports Server (NTRS)

Wasilewski, P.

1981-01-01

Magnetic properties of small iron-nickel alloy spheres, having compositions which cover the entire Fe-Ni binary, are presented. The spheres were formed during solidification in free fall following the melting of electropolished wires of appropriate composition. The spheres with Ni not greater than 25% acquired a martensitic thermal remanence while those with Ni not less than 30% acquired a thermoremanent magnetization. A magnetic remanence-composition diagram and a coercive force-composition diagram are constructed. Magnetic hysteresis loops and derived parameters demonstrate the difference between metal-bearing and oxide-bearing natural samples. The magnetic remanence varies as the sphere size in conjunction with the microstructure. These results help to explain why coercive force is generally low, remanent coercive force is generally high, and their ratio (R/C) is always large in fine metal dispersions, such as lunar samples and chondrite meteorites.

SPEAR-1: An experiment to measure current collection in the ionosphere by high voltage biased conductors

NASA Astrophysics Data System (ADS)

Raitt, W. John; Myers, Neil B.; Roberts, Jon A.; Thompson, D. C.

1990-12-01

An experiment is described in which a high electrical potential difference, up to 45 kV, was applied between deployed conducting spheres and a sounding rocket in the ionosphere. Measurements were made of the applied voltage and the resulting currents for each of 24 applications of different high potentials. In addition, diagnostic measurements of optical emissions in the vicinity of the spheres, energetic particle flow to the sounding rocket, dc electric field and wave data were made. The ambient plasma and neutral environments were measured by a Langmuir probe and a cold cathode neutral ionization gauge, respectively. The payload is described and examples of the measured current and voltage characteristics are presented. The characteristics of the measured currents are discussed in terms of the diagnostic measurements and the in-situ measurements of the vehicle environment. In general, it was found that the currents observed were at a level typical of magnetically limited currents from the ionospheric plasma for potentials less than 12 kV, and slightly higher for larger potentials. However, due to the failure to expose the plasma contactor, the vehicle sheath modified the sphere sheaths and made comparisons with the analytic models of Langmuir-Blodgett and Parker-Murphy less meaningful. Examples of localized enhancements of ambient gas density resulting from the operation of the attitude control system thrusters (cold nitrogen) were obtained. Current measurements and optical data indicated localized discharges due to enhanced gas density that reduced the vehicle-ionosphere impedance.

World Presidents Organization

NASA Technical Reports Server (NTRS)

2010-01-01

Members of the World Presidents' Organization take a try at 'piloting' a mock-up of the space shuttle cockpit during a Jan. 26 visit to StenniSphere, the museum and visitor center at NASA's John C. Stennis Space Center. WPO members from several states spent the day touring Stennis facilities and learning about the work of the nation's premier rocket engine testing site.

Phase diagram of heteronuclear Janus dumbbells

NASA Astrophysics Data System (ADS)

O'Toole, Patrick; Giacometti, Achille; Hudson, Toby

Using Aggregation-Volume-Bias Monte Carlo simulations along with Successive Umbrella Sampling and Histogram Re-weighting, we study the phase diagram of a system of dumbbells formed by two touching spheres having variable sizes, as well as different interaction properties. The first sphere ($h$) interacts with all other spheres belonging to different dumbbells with a hard-sphere potential. The second sphere ($s$) interacts via a square-well interaction with other $s$ spheres belonging to different dumbbells and with a hard-sphere potential with all remaining $h$ spheres. We focus on the region where the $s$ sphere is larger than the $h$ sphere, as measured by a parameter $1\\le \\alpha\\le 2 $ controlling the relative size of the two spheres. As $\\alpha \\to 2$ a simple fluid of square-well spheres is recovered, whereas $\\alpha \\to 1$ corresponds to the Janus dumbbell limit, where the $h$ and $s$ spheres have equal sizes. Many phase diagrams falling into three classes are observed, depending on the value of $\\alpha$. The $1.8 \\le \\alpha \\le 2$ is dominated by a gas-liquid phase separation very similar to that of a pure square-well fluid with varied critical temperature and density. When $1.3 \\le \\alpha \\le 1.8$ we find a progressive destabilization of the gas-liquid phase diagram by the onset of self-assembled structures, that eventually lead to a metastability of the gas-liquid transition below $\\alpha=1.2$.

Design and analysis of optical systems for the Stanford/MSFC Multi-Spectral Solar Telescope Array

NASA Astrophysics Data System (ADS)

Hadaway, James B.; Johnson, R. Barry; Hoover, Richard B.; Lindblom, Joakim F.; Walker, Arthur B. C., Jr.

1989-07-01

This paper reports on the design and the theoretical ray trace analysis of the optical systems which will comprise the primary imaging components for the Stanford/MSFC Multi-Spectral Solar Telescope Array (MSSTA). This instrument is being developed for ultra-high resolution investigations of the sun from a sounding rocket. Doubly reflecting systems of sphere-sphere, ellipsoid-sphere (Dall-Kirkham), paraboloid-hyperboloid (Cassegrain), and hyperboloid-hyperboloid (Ritchey-Chretien) configurations were analyzed. For these mirror systems, ray trace analysis was performed and through-focus spot diagrams, point spread function plots, and geometrical and diffraction MTFs were generated. The results of these studies are presented along with the parameters of the Ritchey-Chretien optical system selected for the MSSTA flight. The payload, which incorporates seven of these Ritchey-Chretien systems, is now being prepared for launch in late September 1989.

Design and analysis of optical systems for the Stanford/MSFC Multi-Spectral Solar Telescope Array

NASA Technical Reports Server (NTRS)

Hadaway, James B.; Johnson, R. Barry; Hoover, Richard B.; Lindblom, Joakim F.; Walker, Arthur B. C., Jr.

1989-01-01

This paper reports on the design and the theoretical ray trace analysis of the optical systems which will comprise the primary imaging components for the Stanford/MSFC Multi-Spectral Solar Telescope Array (MSSTA). This instrument is being developed for ultra-high resolution investigations of the sun from a sounding rocket. Doubly reflecting systems of sphere-sphere, ellipsoid-sphere (Dall-Kirkham), paraboloid-hyperboloid (Cassegrain), and hyperboloid-hyperboloid (Ritchey-Chretien) configurations were analyzed. For these mirror systems, ray trace analysis was performed and through-focus spot diagrams, point spread function plots, and geometrical and diffraction MTFs were generated. The results of these studies are presented along with the parameters of the Ritchey-Chretien optical system selected for the MSSTA flight. The payload, which incorporates seven of these Ritchey-Chretien systems, is now being prepared for launch in late September 1989.

Blast from the past

NASA Astrophysics Data System (ADS)

Carlowicz, Michael

1996-02-01

Forget dynamite or hydraulic and mechanical drills. Industrial and federal researchers have started boring holes with rocket fuel. In a cooperative arrangement between Sandia National Laboratory, Global Environmental Solutions, and Universal Tech Corp., scientists and engineers extracted fuel from 200 rocket motors and used it as a mining explosive. In a demonstration completed last fall, researchers used 4950 kg of solid rocket propellant to move more than 22,500 metric tons of rock from the Lone Star Quarry in Prairie, Oklahoma. They found that the fuel improved blast energy and detonation velocity over traditional explosives, and it required fewer drill holes.

Rolling and slipping down Galileo{close_quote}s inclined plane: Rhythms of the spheres

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

Crawford, F.S.

In ``Two New Sciences`` (TNS) Galileo presents a number of theorems and propositions for smooth solid spheres released from rest and rolling a distance {ital d} in time {ital t} down an incline of height {ital H} and length {ital L}. We collect and summarize his results in a single grand proportionality {ital P}: {ital d}{sub 1}/{ital d}{sub 2}=({ital t}{sup 2}{sub 1}/{ital t}{sup 2}{sub 2})({ital H}/{ital L}){sub 1}/({ital H}/{ital L}){sub 2}. ({ital P}) From TNS it is clear that what we call {ital P} is assumed by Galileo to hold for all inclinations including vertical free fall with {ital H}/{italmore » L}=1. But in TNS he describes only experiments with gentle inclinations {ital H}/{ital L}{lt}1/2. Indeed he cannot have performed the vertical free fall ({ital H}={ital L}) experiment, because we (moderns) know that as we increase {ital H}/{ital L}, {ital P} starts to break down when {ital H}/{ital L} exceeds about 0.5, because the sphere, which rolls without slipping for small {ital H}/{ital L}, starts to slip, whence {ital d} starts to exceed the predictions of {ital P}, becoming too large by a factor of 7/5 for vertical free fall at {ital H}/{ital L}=1. In 1973 Drake and in 1975 Drake and MacLachlan published their analysis of a previously unpublished experiment that Galileo performed that (without his realizing it) directly compared rolling without slipping to free fall. In the experiment, a sphere that has gained speed {ital v}{sub 1} while rolling down a gentle incline is deflected so as to be launched horizontally with speed {ital v}{sub 1} into a free fall orbit discovered by Galileo to be a parabola. The measured horizontal distance {ital X}{sub 2} traveled in this parabolic orbit (for a given vertical distance fallen to the floor) was smaller than he expected, by a factor 0.84. But that is exactly what we (moderns) expect, since we know that Galileo did not appreciate the difference between rolling without slipping, and slipping on a frictionless surface.« less

Cryo Tank Fill at Pad 39B

NASA Image and Video Library

2017-09-26

Several Praxair trucks begin to depart Launch Pad 39B at NASA's Kennedy Space Center in Florida, after offloading their loads of liquid oxygen, or LO2, one at a time into the giant storage sphere located at the northwest corner of the pad. The sphere was gradually chilled down from normal temperature to about negative 298 degrees Fahrenheit, during the first major integrated operation to prepare for the launch of the agency's Orion spacecraft atop the Space Launch System (SLS) rocket. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to pad B to support the launch of the SLS and Orion spacecraft for Exploration Mission-1, deep space missions and NASA’s journey to Mars.

Cryo Tank Fill at Pad 39B

NASA Image and Video Library

2017-09-26

Mist or vapor is visible as a Praxair truck slowly transfers its load of liquid oxygen, or LO2, into a giant storage sphere at the northwest corner of Launch Pad 39B at NASA's Kennedy Space Center in Florida. The sphere will gradually be chilled down from normal temperature to about negative 298 degrees Fahrenheit, during the first major integrated operation to prepare for the launch of the agency's Orion spacecraft atop the Space Launch System (SLS) rocket. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to pad B to support the launch of the SLS and Orion spacecraft for Exploration Mission-1, deep space missions and NASA’s journey to Mars.

Stennis' granddaughter visits Mississippi Facility

NASA Image and Video Library

2009-04-06

Jane Kenna of Atlanta, granddaughter of the late Sen. John C. Stennis, stands with her husband, John, near a bust of her grandfather displayed in StenniSphere, the visitor center at NASA's John C. Stennis Space Center. Kenna visited Stennis on April 6, her first trip to the rocket engine testing facility since the 1988 ceremony to rename the site in honor of Stennis.

World Presidents Organization

NASA Technical Reports Server (NTRS)

2010-01-01

Mississippi Gov. Haley Barbour speaks to members of the World Presidents' Organization during the group's visit to NASA's John C. Stennis Space Center on Jan. 26. WPO members from several states spent the day touring Stennis facilities and learning about the work of the nation's premier rocket engine testing site. Barbour visited with group members during a morning session in StenniSphere, the center's visitors center and museum.

World Presidents Organization

NASA Image and Video Library

2010-01-26

Mississippi Gov. Haley Barbour speaks to members of the World Presidents' Organization during the group's visit to NASA's John C. Stennis Space Center on Jan. 26. WPO members from several states spent the day touring Stennis facilities and learning about the work of the nation's premier rocket engine testing site. Barbour visited with group members during a morning session in StenniSphere, the center's visitors center and museum.

Circular Data Images for Directional Data

NASA Technical Reports Server (NTRS)

Morpet, William J.

2004-01-01

Directional data includes vectors, points on a unit sphere, axis orientation, angular direction, and circular or periodic data. The theoretical statistics for circular data (random points on a unit circle) or spherical data (random points on a unit sphere) are a recent development. An overview of existing graphical methods for the display of directional data is given. Cross-over occurs when periodic data are measured on a scale for the measurement of linear variables. For example, if angle is represented by a linear color gradient changing uniformly from dark blue at -180 degrees to bright red at +180 degrees, the color image will be discontinuous at +180 degrees and -180 degrees, which are the same location. The resultant color would depend on the direction of approach to the cross-over point. A new graphical method for imaging directional data is described, which affords high resolution without color discontinuity from "cross-over". It is called the circular data image. The circular data image uses a circular color scale in which colors repeat periodically. Some examples of the circular data image include direction of earth winds on a global scale, rocket motor internal flow, earth global magnetic field direction, and rocket motor nozzle vector direction vs. time.

Wind structure and variability in the middle atmosphere during the November 1980 energy budget campaign

NASA Technical Reports Server (NTRS)

Schmidlin, F. J.; Carlson, M.; Rees, D.; Offermann, D.; Philbrick, C. R.; Widdel, H. U.

1985-01-01

Between November 6 and December 1, 1980 series of rocket observations were obtained from two sites in northern Scandinavia (68 deg N) as part of the Energy Budget Campaign, revealing the presence of significant vertical and temporal changes in the wind structure. These changes coincided with different geomagnetic conditions, i.e. quiet and enhanced. Large amounts of rocket data were gathered from high latitudes over such a short interval of time. Prior to November 16 the meridional wind component above 60 km was found to be positive (southerly), while the magnitude of the zonal wind component incresed with altitude. After November 16 the meridional component became negative (northerly) and the magnitude of the zonal wind component was noted to decrease with altitude. Time-sections of the perturbations of the zonal wind show the presence of vertically propagating waves, which suggest gravity wave activity. These waves increase in length from 1 km near 30 km to over 12 km near 80 km. The observational techniques employed Andoya (69 deg N), Norway, and Esrange (67.9 deg N), Sweden, consisted of chaff foil, instrumented rigid spheres, chemical trails, inflatable spheres and parachutes.

Production of Space-rocket Technique: Psychological Factor

NASA Astrophysics Data System (ADS)

Vashchuk, S. P.; Sviderskiy, O. A.; Ezhova, O. N.; Rovenskaya, V. V.

2018-01-01

The article is devoted to the issues of studying the mental and physical condition of the shop workers who assemble carrier rockets and ways of processing their internal conflicts. It is shown that the complexity of the ongoing labor processes, the intensity of production activities and the responsibility for its end result lead to a high level of neurotic workers. The tendency to a long experience of a stressful situation helps them to increase the level of various forms of aggression and create a negative assessment of their official capabilities and successes. It is established that the duration of experiencing a stressful situation depends on coping strategies in the behavioral and emotional spheres.

Energy-Based Tetrahedron Sensor for High-Temperature, High-Pressure Environments

NASA Technical Reports Server (NTRS)

Gee, Kent L.; Sommerfeldt, Scott D.; Blotter, Jonathan D.

2012-01-01

An acoustic energy-based probe has been developed that incorporates multiple acoustic sensing elements in order to obtain the acoustic pressure and three-dimensional acoustic particle velocity. With these quantities, the user can obtain various energy-based quantities, including acoustic energy density, acoustic intensity, and acoustic impedance. In this specific development, the probe has been designed to operate in an environment characterized by high temperatures and high pressures as is found in the close vicinity of rocket plumes. Given these capabilities, the probe is designed to be used to investigate the acoustic conditions within the plume of a rocket engine or jet engine to facilitate greater understanding of the noise generation mechanisms in those plumes. The probe features sensors mounted inside a solid sphere. The associated electronics for the probe are contained within the sphere and the associated handle for the probe. More importantly, the design of the probe has desirable properties that reduce the bias errors associated with determining the acoustic pressure and velocity using finite sum and difference techniques. The diameter of the probe dictates the lower and upper operating frequencies for the probe, where accurate measurements can be acquired. The current probe design implements a sphere diameter of 1 in. (2.5 cm), which limits the upper operating frequency to about 4.5 kHz. The sensors are operational up to much higher frequencies, and could be used to acquire pressure data at higher frequencies, but the energy-based measurements are limited to that upper frequency. Larger or smaller spherical probes could be designed to go to lower or higher frequency range

Entry, Descent, and Landing with Propulsive Deceleration: Supersonic Retropropulsion Wind Tunnel Testing and Shock Phenomena

NASA Technical Reports Server (NTRS)

Palaszewski, Bryan

2014-01-01

The future exploration of the Solar System will require innovations in transportation and the use of entry, descent, and landing (EDL) systems at many planetary landing sites. The cost of space missions has always been prohibitive, and using the natural planetary and planet's moon atmospheres for entry, and descent can reduce the cost, mass, and complexity of these missions. This paper will describe some of the EDL ideas for planetary entry and survey the overall technologies for EDL that may be attractive for future Solar System missions. Future EDL systems may include an inflatable decelerator for the initial atmospheric entry and an additional supersonic retropropulsion (SRP) rocket system for the final soft landing. A three engine retropropulsion configuration with a 2.5 in. diameter sphere-cone aeroshell model was tested in the NASA Glenn Research Center's 1- by 1-ft (1×1) Supersonic Wind Tunnel (SWT). The testing was conducted to identify potential blockage issues in the tunnel, and visualize the rocket flow and shock interactions during supersonic and hypersonic entry conditions. Earlier experimental testing of a 70deg Viking-like (sphere-cone) aeroshell was conducted as a baseline for testing of a SRP system. This baseline testing defined the flow field around the aeroshell and from this comparative baseline data, retropropulsion options will be assessed. Images and analyses from the SWT testing with 300- and 500-psia rocket engine chamber pressures are presented here. In addition, special topics of electromagnetic interference with retropropulsion induced shock waves and retropropulsion for Earth launched booster recovery are also addressed.

Entry, Descent, and Landing with Propulsive Deceleration: Supersonic Retropropulsion Wind Tunnel Testing and Shock Phenomena

NASA Technical Reports Server (NTRS)

Palaszewski, Bryan

2013-01-01

The future exploration of the Solar System will require innovations in transportation and the use of entry, descent, and landing (EDL) systems at many planetary landing sites. The cost of space missions has always been prohibitive, and using the natural planetary and planet's moon atmospheres for entry, and descent can reduce the cost, mass, and complexity of these missions. This paper will describe some of the EDL ideas for planetary entry and survey the overall technologies for EDL that may be attractive for future Solar System missions. Future EDL systems may include an inflatable decelerator for the initial atmospheric entry and an additional supersonic retro-propulsion (SRP) rocket system for the final soft landing. A three engine retro-propulsion configuration with a 2.5 inch diameter sphere-cone aeroshell model was tested in the NASA Glenn 1x1 Supersonic Wind Tunnel (SWT). The testing was conducted to identify potential blockage issues in the tunnel, and visualize the rocket flow and shock interactions during supersonic and hypersonic entry conditions. Earlier experimental testing of a 70 degree Viking-like (sphere-cone) aeroshell was conducted as a baseline for testing of a supersonic retro-propulsion system. This baseline testing defined the flow field around the aeroshell and from this comparative baseline data, retro-propulsion options will be assessed. Images and analyses from the SWT testing with 300- and 500-psia rocket engine chamber pressures are presented here. In addition, special topics of electromagnetic interference with retro-propulsion induced shock waves and retro-propulsion for Earth launched booster recovery are also addressed.

Experimental demonstration that a free-falling aerosol particle obeys a fluctuation theorem

NASA Astrophysics Data System (ADS)

Wong, Chun-Shang; Goree, J.; Gopalakrishnan, Ranganathan

2018-05-01

We investigate the fluctuating motion of an aerosol particle falling in air. Using a Millikan-like setup, we tracked a 1-μ m sphere falling at its terminal velocity. We observe occurrences of particles undergoing upward displacements against the force of gravity, so that negative work is done briefly. These negative-work events have a probability that is shown to obey the work fluctuation theorem. This experimental confirmation of the theorem's applicability to aerosols leads us to develop and demonstrate an application: an in situ measurement of an aerosol particle's mass.

Reconstruction of Attitude Dynamics of Free Falling Units

NASA Astrophysics Data System (ADS)

Yuan, Y.; Ivchenko, N.; Tibert, G.; Schlatter, N. M.

2015-09-01

Attitude reconstruction of a free falling sphere for the experiment Multiple Spheres for Characterization of Atmosphere Temperatures (MUSCAT) is studied in this paper. The attitude dynamics is modeled through Euler's rotational equations of motion. To estimate uncertain parameters in this model such as the matrix of inertia and the lever arm for the dynamic pressure with respect to the center of mass, the dynamics reconstruction can be formulated as an optimization problem. The goal is to minimize the deviation between the measurements and the propagation from the system equations. This approach was tested against a couple of flight data sets which correspond to different periods of time. The result is very reasonable compared to the laboratory test. The estimate can be improved further through allowing drag coefficients variable and taking advantage of measurements from a magnetometer in numerical calculation.

Environmental Impact Statement Space Shuttle Advanced Solid Rocket Motor Program

DTIC Science & Technology

1989-03-01

Space Shuttle solid rocket boosters are currently retrieved from the Atlantic Ocean after a launch and disassembled at KSC. It is assumed that the...testing is not anticipated to impact aquatic resources. The exhaust plume will be directed over the ocean , which has a high buffering capacity and mixing...approximately 30 miles. After being slowed by parachutes, the spent motors will fall into the ocean where they will be recovered and towed to a dock at

Development and Performance of a Filter Radiometer Monitor System for Integrating Sphere Sources

NASA Technical Reports Server (NTRS)

Ding, Leibo; Kowalewski, Matthew G.; Cooper, John W.; Smith, GIlbert R.; Barnes, Robert A.; Waluschka, Eugene; Butler, James J.

2011-01-01

The NASA Goddard Space Flight Center (GSFC) Radiometric Calibration Laboratory (RCL) maintains several large integrating sphere sources covering the visible to the shortwave infrared wavelength range. Two critical, functional requirements of an integrating sphere source are short and long-term operational stability and repeatability. Monitoring the source is essential in determining the origin of systemic errors, thus increasing confidence in source performance and quantifying repeatability. If monitor data falls outside the established parameters, this could be an indication that the source requires maintenance or re-calibration against the National Institute of Science and Technology (NIST) irradiance standard. The GSFC RCL has developed a Filter Radiometer Monitoring System (FRMS) to continuously monitor the performance of its integrating sphere calibration sources in the 400 to 2400nm region. Sphere output change mechanisms include lamp aging, coating (e.g. BaSO4) deterioration, and ambient water vapor level. The Filter Radiometer Monitor System (FRMS) wavelength bands are selected to quantify changes caused by these mechanisms. The FRMS design and operation are presented, as well as data from monitoring four of the RCL s integrating sphere sources.

Cryo Tank Fill at Pad 39B

NASA Image and Video Library

2017-09-26

NASA Launch Director Charlie Blackwell-Thompson, at left, arrives at Launch Pad 39B at NASA's Kennedy Space Center in Florida, to observe the first major tanking operation of liquid oxygen, or LO2, into the giant storage sphere at the northwest corner of the pad to prepare for the launch of the agency's Orion spacecraft atop the Space Launch System (SLS) rocket. During the operation, several Praxair trucks will slowly offload LO2 to gradually chill down the sphere from normal temperature to about negative 298 degrees Fahrenheit. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to pad B to support the launch of the SLS and Orion spacecraft for Exploration Mission-1, deep space missions and NASA’s journey to Mars.

Cryo Tank Fill at Pad 39B

NASA Image and Video Library

2017-09-26

A large plume of mist or vapor is visible as a Praxair truck slowly transfers its load of liquid oxygen, or LO2, into a giant storage sphere at the northwest corner of Launch Pad 39B at NASA's Kennedy Space Center in Florida. The sphere will gradually be chilled down from normal temperature to about negative 298 degrees Fahrenheit, during the first major integrated operation to prepare for the launch of the agency's Orion spacecraft atop the Space Launch System (SLS) rocket. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to pad B to support the launch of the SLS and Orion spacecraft for Exploration Mission-1, deep space missions and NASA’s journey to Mars.

Atmospheric pressure, density, temperature and wind variations between 50 and 200 km

NASA Technical Reports Server (NTRS)

Justus, C. G.; Woodrum, A.

1972-01-01

Data on atmospheric pressure, density, temperature and winds between 50 and 200 km were collected from sources including Meteorological Rocket Network data, ROBIN falling sphere data, grenade release and pitot tube data, meteor winds, chemical release winds, satellite data, and others. These data were analyzed by a daily difference method and results on the distribution statistics, magnitude, and spatial structure of the irregular atmospheric variations are presented. Time structures of the irregular variations were determined by the analysis of residuals from harmonic analysis of time series data. The observed height variations of irregular winds and densities are found to be in accord with a theoretical relation between these two quantities. The latitude variations (at 50 - 60 km height) show an increasing trend with latitude. A possible explanation of the unusually large irregular wind magnitudes of the White Sands MRN data is given in terms of mountain wave generation by the Sierra Nevada range about 1000 km west of White Sands. An analytical method is developed which, based on an analogy of the irregular motion field with axisymmetric turbulence, allows measured or model correlation or structure functions to be used to evaluate the effective frequency spectra of scalar and vector quantities of a spacecraft moving at any speed and at any trajectory elevation angle.

WOLF REXUS EXPERIMENT - European Planetary Science Congress

NASA Astrophysics Data System (ADS)

Buzdugan, A.

2017-09-01

WOLF experiment is developing a reaction wheel-based control system, effectively functioning as active nutation damper. One reaction wheel is used to reduce the undesirable lateral rates of spinning cylindrically symmetric free falling units, ejected from a sounding rocket. Once validated in REXUS flight, the concept and the design developed during WOLF experiment can be used for other application which require a flat spin of the free falling units.

ROCKET PORT CLOSURE

DOEpatents

Mattingly, J.T.

1963-02-12

This invention provides a simple pressure-actuated closure whereby windowless observation ports are opened to the atmosphere at preselected altitudes. The closure comprises a disk which seals a windowless observation port in rocket hull. An evacuated instrument compartment is affixed to the rocket hull adjacent the inner surface of the disk, while the outer disk surface is exposed to the atmosphere through which the rocket is traveling. The pressure differential between the evacuated instrument compartment and the relatively high pressure external atmosphere forces the disk against the edge of the observation port, thereby effecting a tight seai. The instrument compartment is evacuated to a pressure equal to the atmospheric pressure existing at the altitude at which it is desiretl that the closure should open. When the rocket reaches this preselected altitude, the inwardly directed atmospheric force on the disk is just equaled by the residual air pressure force within the instrument compartment. Consequently, the closure disk falls away and uncovers the open observation port. The separation of the disk from the rocket hull actuates a switch which energizes the mechanism of a detecting instrument disposed within the instrument compartment. (AE C)

Environmental dynamics at orbital altitudes

NASA Technical Reports Server (NTRS)

Karr, G. R.

1976-01-01

The influence of real satellite aerodynamics on the determination of upper atmospheric density was investigated. A method of analysis of satellite drag data is presented which includes the effect of satellite lift and the variation in aerodynamic properties around the orbit. The studies indicate that satellite lift may be responsible for the observed orbit precession rather than a super rotation of the upper atmosphere. The influence of simplifying assumptions concerning the aerodynamics of objects in falling sphere analysis were evaluated and an improved method of analysis was developed. Wind tunnel data was used to develop more accurate drag coefficient relationships for studying altitudes between 80 and 120 Km. The improved drag coefficient relationships revealed a considerable error in previous falling sphere drag interpretation. These data were reanalyzed using the more accurate relationships. Theoretical investigations of the drag coefficient in the very low speed ratio region were also conducted.

Solid-on-solid contact in a sphere-wall collision in a viscous fluid

NASA Astrophysics Data System (ADS)

Birwa, Sumit Kumar; Rajalakshmi, G.; Govindarajan, Rama; Menon, Narayanan

2018-04-01

We study experimentally the collision between a sphere falling through a viscous fluid and a solid plate below. It is known that there is a well-defined threshold Stokes number above which the sphere rebounds from such a collision. Our experiment tests for direct contact between the colliding bodies and, contrary to prior theoretical predictions, shows that solid-on-solid contact occurs even for Stokes numbers just above the threshold for rebounding. The dissipation is fluid dominated, though details of the contact mechanics depend on the surface and bulk properties of the solids. Our experiments and a model calculation indicate that mechanical contact between the two colliding objects is generic and will occur for any realistic surface roughness.

Can we obtain the coefficient of restitution from the sound of a bouncing ball?

NASA Astrophysics Data System (ADS)

Heckel, Michael; Glielmo, Aldo; Gunkelmann, Nina; Pöschel, Thorsten

2016-03-01

The coefficient of restitution may be determined from the sound signal emitted by a sphere bouncing repeatedly off the ground. Although there is a large number of publications exploiting this method, so far, there is no quantitative discussion of the error related to this type of measurement. Analyzing the main error sources, we find that even tiny deviations of the shape from the perfect sphere may lead to substantial errors that dominate the overall error of the measurement. Therefore, we come to the conclusion that the well-established method to measure the coefficient of restitution through the emitted sound is applicable only for the case of nearly perfect spheres. For larger falling height, air drag may lead to considerable error, too.

Cryo Tank Fill at Pad 39B

NASA Image and Video Library

2017-09-26

NASA Launch Director Charlie Blackwell-Thompson, center, talks to engineers at Launch Pad 39B at the agency's Kennedy Space Center in Florida. Blackwell-Thompson will observe the first major tanking operation of liquid oxygen, or LO2, into the giant storage sphere at the northwest corner of the pad to prepare for the launch of the agency's Orion spacecraft atop the Space Launch System (SLS) rocket. During the operation, several Praxair trucks will slowly offload LO2 to gradually chill down the sphere from normal temperature to about negative 298 degrees Fahrenheit. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to pad B to support the launch of the SLS and Orion spacecraft for Exploration Mission-1, deep space missions and NASA’s journey to Mars.

Cryo Tank Fill at Pad 39B

NASA Image and Video Library

2017-09-26

NASA Launch Director Charlie Blackwell-Thompson, at right, greets engineers and technicians at Launch Pad 39B at the agency's Kennedy Space Center in Florida. Blackwell-Thompson will observe the first major tanking operation of liquid oxygen, or LO2, into the giant storage sphere at the northwest corner of the pad to prepare for the launch of the agency's Orion spacecraft atop the Space Launch System (SLS) rocket. During the operation, several Praxair trucks will slowly offload LO2 to gradually chill down the sphere from normal temperature to about negative 298 degrees Fahrenheit. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to pad B to support the launch of the SLS and Orion spacecraft for Exploration Mission-1, deep space missions and NASA’s journey to Mars.

Cryo Tank Fill at Pad 39B

NASA Image and Video Library

2017-09-26

Several Praxair trucks carrying their loads of liquid oxygen, or LO2, have arrived at Launch Pad 39B at NASA's Kennedy Space Center in Florida. A mist is visible as LO2 is offloaded from one of the trucks into the giant storage sphere located at the northwest corner of the pad has begun. The sphere will gradually be chilled down from normal temperature to about negative 298 degrees Fahrenheit, during the first major integrated operation to prepare for the launch of the agency's Orion spacecraft atop the Space Launch System (SLS) rocket. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to pad B to support the launch of the SLS and Orion spacecraft for Exploration Mission-1, deep space missions and NASA’s journey to Mars.

Cryo Tank Fill at Pad 39B

NASA Image and Video Library

2017-09-26

Several Praxair trucks carrying their loads of liquid oxygen, or LO2, have arrived at Launch Pad 39B at NASA's Kennedy Space Center in Florida. The trucks will begin to offload the LO2 one at a time into the giant storage sphere located at the northwest corner of the pad. The sphere will gradually be chilled down from normal temperature to about negative 298 degrees Fahrenheit, during the first major integrated operation to prepare for the launch of the agency's Orion spacecraft atop the Space Launch System (SLS) rocket. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to pad B to support the launch of the SLS and Orion spacecraft for Exploration Mission-1, deep space missions and NASA’s journey to Mars.

Cryo Tank Fill at Pad 39B

NASA Image and Video Library

2017-09-26

Engineers watch as several Praxair trucks carrying their loads of liquid oxygen, or LO2, arrive at Launch Pad 39B at NASA's Kennedy Space Center in Florida. The trucks will offload the LO2 one at a time into the giant storage sphere located at the northwest corner of the pad. The sphere will gradually be chilled down from normal temperature to about negative 298 degrees Fahrenheit, during the first major integrated operation to prepare for the launch of the agency's Orion spacecraft atop the Space Launch System (SLS) rocket. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to pad B to support the launch of the SLS and Orion spacecraft for Exploration Mission-1, deep space missions and NASA’s journey to Mars.

Descent Stage of Mars Science Laboratory During Assembly

NASA Technical Reports Server (NTRS)

2008-01-01

This image from early October 2008 shows personnel working on the descent stage of NASA's Mars Science Laboratory inside the Spacecraft Assembly Facility at NASA's Jet Propulsion Laboratory, Pasadena, Calif.

The descent stage will provide rocket-powered deceleration for a phase of the arrival at Mars after the phases using the heat shield and parachute. When it nears the surface, the descent stage will lower the rover on a bridle the rest of the way to the ground. The larger three of the orange spheres in the descent stage are fuel tanks. The smaller two are tanks for pressurant gas used for pushing the fuel to the rocket engines.

JPL, a division of the California Institute of Technology, manages the Mars Science Laboratory Project for the NASA Science Mission Directorate, Washington.

Foam formation in low gravity

NASA Technical Reports Server (NTRS)

Wessling, Francis C.; Mcmanus, Samuel P.; Matthews, John; Patel, Darayas

1990-01-01

An apparatus that produced the first polyurethane foam in low gravity has been described. The chemicals were mixed together in an apparatus designed for operation in low gravity. Mixing was by means of stirring the chemicals with an electric motor and propeller in a mixing chamber. The apparatus was flown on Consort 1, the first low-gravity materials payload launched by a commercial rocket launch team. The sounding rocket flight produced over 7 min of low gravity during which a polyurethane spheroidal foam of approximately 2300 cu cm was formed. Photographs of the formation of the foam during the flight show the development of the spheroidal form. This begins as a small sphere and grows to approximately a 17-cm-diam spheroid. The apparatus will be flown again on subsequent low-gravity flights.

Unsteady sedimentation of a sphere in wormlike micellar fluids

NASA Astrophysics Data System (ADS)

Zhang, Yiran; Muller, Susan J.

2018-04-01

The unsteady sedimentation of a sphere in wormlike micellar fluids is studied experimentally through shear and extensional rheometry, sphere trajectory tracking, and particle image velocimetry. Unsteady sphere sedimentation characterized by fluctuations in the sphere settling velocity was observed for a range of sphere size and density in two non-shear-banding wormlike micellar solutions, a cetylpyridinium chloride (CpCl)-sodium salicylate (NaSal) solution and a cetyltrimethylammonium p-toluenesulfonate (CTAT)-NaCl solution. The onset of the transition from steady to unsteady sphere motion is characterized by an extensional Deborah number, D eext , defined locally in the negative wake of the falling sphere. This instability criterion is in agreement with previous findings by Mohammadigoushki and Muller [J. Rheol. 60, 587 (2016), 10.1122/1.4948800] in the wormlike micelle system of cetyltrimethylammonium bromide (CTAB) and NaSal, and appears to be universally valid independent of micelle chemistry or solution rheology (e.g., shear banding or not). Moreover, the frequency at which the sphere velocity fluctuates is found to be linearly correlated with an average shear Deborah number D es , which is a measure of the overall flow strength. This suggests that a constant critical strain is accumulated before the flow instability takes place in each velocity oscillation. The velocity fluctuations are found to become increasingly disordered with increasing elastic Mach number, M ae , indicating that the interactions between the flow instability and elastic wave propagation result in more chaotic velocity fluctuations.

Children enjoy visit to Stennis

NASA Image and Video Library

2010-07-27

About 200 children of employees at NASA's John C. Stennis Space Center visited the facility for annual Take Our Children to Work activities July 27. Participants enjoyed a windshield tour of the rocket engine test site and various demonstrations and presentations on such topics as cryogenics, the Gulf of Mexico oil spill, computer safety and robotics. They also had an opportunity to take photos at the astronaut suit exhibit and participate in StenniSphere activities.

Highlights of 2012 Fall Meeting

NASA Astrophysics Data System (ADS)

Finn, Carol

2013-01-01

This past December the streets of San Francisco, Calif., surrounding the Moscone Center were awash with a sea of Earth and space scientists attending the 45th consecutive AGU Fall Meeting, eager to share and expand their knowledge "for the benefit of humanity." As it has for many years, attendance at AGU's Fall Meeting—the largest gathering of Earth and space scientists in the world—continued to increase, this year passing the 24,000 mark. Attendees at the meeting, which took place on 3-7 December 2012, hailed from 97 countries; nearly 7000 of them were students. News from the Fall Meeting was carried in newspapers and on Web sites around the world, and the social media sphere lit up with talk of AGU and the Fall Meeting. It's even reported that for a short time we were a trending topic on Twitter.

Movements of a Sphere Moving Over Smooth and Rough Inclines

NASA Astrophysics Data System (ADS)

Jan, Chyan-Deng

1992-01-01

The steady movements of a sphere over a rough incline in air, and over smooth and rough inclines in a liquid were studied theoretically and experimentally. The principle of energy conservation was used to analyze the translation velocities, rolling resistances, and drag coefficients of a sphere moving over the inclines. The rolling resistance to the movement of a sphere from the rough incline was presumed to be caused by collisions and frictional slidings. A varnished wooden board was placed on the bottom of an experimental tilting flume to form a smooth incline and a layer of spheres identical to the sphere moving over them was placed on the smooth wooden board to form a rough incline. Spheres used in the experiments were glass spheres, steel spheres, and golf balls. Experiments show that a sphere moving over a rough incline with negligible fluid drag in air can reach a constant translation velocity. This constant velocity was found to be proportional to the bed inclination (between 11 ^circ and 21^circ) and the square root of the sphere's diameter, but seemingly independent of the sphere's specific gravity. Two empirical coefficients in the theoretical expression of the sphere's translation velocity were determined by experiments. The collision and friction parts of the shear stress exerted on the interface between the moving sphere and rough incline were determined. The ratio of collision to friction parts appears to increase with increase in the bed inclination. These two parts seem to be of the same order of magnitude. The rolling resistances and the relations between the drag coefficient and Reynolds number for a sphere moving over smooth and rough inclines in a liquid, such as water or salad oil, were determined by a regression analysis based on experimental data. It was found that the drag coefficient for a sphere over the rough incline is larger than that for a sphere over the smooth incline, and both of which are much larger than that for a sphere in free fall. The relative magnitudes of the shear stresses due to drag, collision, and friction were also determined in terms of the Reynolds number.

Public views evening engine test of a Space Shuttle Main Engine

NASA Image and Video Library

2001-04-21

Over the past year, more than 20,000 people came to Stennis Space Center to witness the 'shake, rattle and roar' of one of the world's most sophisticated engines. Stennis Space Center in south Mississippi is NASA's lead center for rocket propulsion testing. StenniSphere, the visitor center for Stennis Space Center, hosted more than 250,000 visitors in its first year of operation. Of those visitors, 26.4 percent were from Louisiana.

Origin of the moon - Capture by gas drag of the earth's primordial atmosphere

NASA Astrophysics Data System (ADS)

Nakazawa, K.; Komuro, T.; Hayashi, C.

1983-06-01

The novel lunar formation scenario proposed is an extension of planetary formation process studies suggesting that the earth originated in a gaseous solar nebula. Attention is given to a series of dynamical processes in which a low energy planetesimal is trapped within the terrestrial Hill sphere under circumstances in which the primordial atmosphere's gas density gradually decreases. An unbound planetesimal entering the Hill sphere would have had to dissipate its kinetic energy and then come into a bound orbit, before escaping from the Hill sphere, without falling onto the earth's surface. The kinetic energy dissipation condition is considered through the calculation of the solar gravity and atmospheric gas drag effects on the planetesimal's orbital motion. The result obtained shows that a low energy planetesimal of less than lunar mass can be trapped in the Hill sphere with a high probability, if it enters at those stages before atmospheric density has decreased to about 1/50th of the initial value.

Black Hole in 3-D

NASA Image and Video Library

1999-11-30

This three-dimensional illustration shows how the rotating space around a black hole twists up the magnetic field in the plasma falling toward the black hole. The black sphere at the center of the figure is the black hole itself. http://photojournal.jpl.nasa.gov/catalog/PIA04207

SLS Rocket Hardware Moved to NASA Marshall Stand for Upcoming Test Series (30-second timelapse)

NASA Image and Video Library

2016-10-13

A test version of the launch vehicle stage adapter (LVSA) for NASA’s new rocket, the Space Launch System, is moved to a 65-foot-tall test stand at the agency’s Marshall Space Flight Center in Huntsville, Alabama. The test version LVSA will be stacked with other test pieces of the upper part of the SLS rocket and pushed, pulled and twisted as part of an upcoming test series to ensure each structure can withstand the incredible stresses of launch. The LVSA joins the core stage simulator, which was loaded into the test stand Sept. 21. The other three qualification articles and the Orion simulator will complete the stack later this fall. SLS will be the world’s most powerful rocket, and with the Orion spacecraft, take astronauts to deep-space destinations, including the Journey to Mars. More information on the upcoming test series can be found here: http://go.nasa.gov/2dS8yXB

Multi-trait analysis of post-harvest storage in rocket salad (Diplotaxis tenuifolia) links sensorial, volatile and nutritional data.

PubMed

Spadafora, Natasha D; Amaro, Ana L; Pereira, Maria J; Müller, Carsten T; Pintado, Manuela; Rogers, Hilary J

2016-11-15

Rocket salad (Diplotaxis tenuifolia; wild rocket) is an important component of ready to eat salads providing a distinct peppery flavour and containing nutritionally relevant compounds. Quality deteriorates during post-harvest, in relation to time and storage temperature amongst other factors. Volatile organic compounds (VOCs) are easily measurable from rocket leaves and may provide useful quality indicators for e.g. changes in isothiocyanates derived from nutritionally important glucosinolates. VOC profiles discriminated storage temperatures (0, 5 and 10°C) and times (over 14days). More specifically, concentrations of aldehydes and isothiocyanates decreased with time paralleling a fall in vitamin C and a reduction in sensorial quality at the two higher temperatures. Sulphur containing compounds rise at later time-points and at higher temperatures coincident with an increase in microbial titre, mirroring a further drop in sensorial quality thus indicating their contribution to off-odours. Copyright © 2016 The Authors. Published by Elsevier Ltd.. All rights reserved.

KSC-03pd0250

NASA Image and Video Library

2003-01-16

KENNEDY SPACE CENTER, FLA. -- Approximately 33 seconds after T-0 and liftoff of Space Shuttle Columbia, several particles are observed falling away from the -Z portion of the LH solid rocket booster ETA ring. Particles were identified later as probably pieces of the instafoam closeout on the ETA ring.

Far-ultraviolet spectra and flux distributions of some Orion stars

NASA Technical Reports Server (NTRS)

Carruthers, G. R.; Heckathorn, H. M.; Opal, C. B.

1981-01-01

Far-ultraviolet (950-1800 A) spectra with about 2 A resolution were obtained of a number of stars in Orion during a sounding-rocket flight 1975 December 6. These spectra have been reduced to absolute flux distributions with the aid of preflight calibrations. The derived fluxes are in good agreement with model-atmosphere predictions and previous observations down to about 1200 A. In the 1200-1080 A range, the present results are in good agreement with model predictions but fall above the rocket measurements of Brune, Mount and Feldman. Below 1080 A, our measurements fall below the model predictions, reaching a deviation of a factor of 2 near 1010 A and a factor of 4 near 950 A. The present results are compared with those of Brune et al. via Copernicus U2 observations in this spectral range, and possible sources of discrepancies between the various observations and model-atmosphere predictions are discussed. Other aspects of the spectra, particularly with regard to spectral classification, are briefly discussed.

NASA Engineer Examines the Design of a Regeneratively-Cooled Rocket Engine

NASA Image and Video Library

1958-12-21

An engineer at the National Aeronautics and Space Administration (NASA) Lewis Research Center examines a drawing showing the assembly and details of a 20,000-pound thrust regeneratively cooled rocket engine. The engine was being designed for testing in Lewis’ new Rocket Engine Test Facility, which began operating in the fall of 1957. The facility was the largest high-energy test facility in the country that was capable of handling liquid hydrogen and other liquid chemical fuels. The facility’s use of subscale engines up to 20,000 pounds of thrust permitted a cost-effective method of testing engines under various conditions. The Rocket Engine Test Facility was critical to the development of the technology that led to the use of hydrogen as a rocket fuel and the development of lightweight, regeneratively-cooled, hydrogen-fueled rocket engines. Regeneratively-cooled engines use the cryogenic liquid hydrogen as both the propellant and the coolant to prevent the engine from burning up. The fuel was fed through rows of narrow tubes that surrounded the combustion chamber and nozzle before being ignited inside the combustion chamber. The tubes are visible in the liner sitting on the desk. At the time, Pratt and Whitney was designing a 20,000-pound thrust liquid-hydrogen rocket engine, the RL-10. Two RL-10s would be used to power the Centaur second-stage rocket in the 1960s. The successful development of the Centaur rocket and the upper stages of the Saturn V were largely credited to the work carried out Lewis.

Bubble nucleation and inflationary perturbations

NASA Astrophysics Data System (ADS)

Firouzjahi, Hassan; Jazayeri, Sadra; Karami, Asieh; Rostami, Tahereh

2017-12-01

In this work we study the imprints of bubble nucleation on primordial inflationary perturbations. We assume that the bubble is formed via the tunneling of a spectator field from the false vacuum of its potential to its true vacuum. We consider the configuration in which the observable CMB sphere is initially outside of the bubble. As the bubble expands, more and more regions of the exterior false vacuum, including our CMB sphere, fall into the interior of the bubble. The modes which leave the horizon during inflation at the time when the bubble wall collides with the observable CMB sphere are affected the most. The bubble wall induces non-trivial anisotropic and scale dependent corrections in the two point function of the curvature perturbation. The corrections in the curvature perturbation and the diagonal and off-diagonal elements of CMB power spectrum are estimated.

Beginnings of rocket development in the czech lands (Czechoslovakia)

NASA Astrophysics Data System (ADS)

Plavec, Michal

2011-11-01

Although the first references are from the 15th Century when both Hussites and crusaders are said to have used rockets during the Hussite Wars (also known as the Bohemian Wars) there is no strong evidence that rockets were actually used at that time. It is worth noting that Konrad Kyeser, who described several rockets in his Bellifortis manuscript written 1402-1405, served as advisor to Bohemian King Wenceslas IV. Rockets were in fact used as fireworks from the 16th century in noble circles. Some of these were built by Vavřinec Křička z Bitý\\vsky, who also published a book on fireworks, in which he described how to build rockets for firework displays. Czech soldiers were also involved in the creation of a rocket regiment in the Austrian (Austro-Hungarian) army in the first half of the 19th century. The pioneering era of modern rocket development began in the Czech lands during the 1920s. The first rockets were succesfully launched by Ludvík Očenášek in 1930 with one of them possibly reaching an altitude of 2000 metres. Vladimír Mandl, lawyer and author of the first book on the subject of space law, patented his project for a stage rocket (vysokostoupající raketa) in 1932, but this project never came to fruition. There were several factories during the so-called Protectorate of Bohemia and Moravia in 1939-1945, when the Czech lands were occupied by Nazi Germany, where parts for German Mark A-4/V-2 rockets were produced, but none of the Czech technicians or constructors were able to build an entire rocket. The main goal of the Czech aircraft industry after WW2 was to revive the stagnant aircraft industry. There was no place to create a rocket industry. Concerns about a rocket industry appeared at the end of the 1950s. The Political Board of the Central Committee of the Czechoslovak Communist Party started to study the possibilities of creating a rocket industry after the first flight into space and particularly after US nuclear weapons were based in Italy and West Germany in 1957 and 1959. The first project involved the meteorological rockets Sokol I and Sokol II in 1960, which were never completed, as the rocket industry came under the exclusive sphere of interest of the Soviet Union. In Czechoslovakia only a Rocket Research and Test Institute was created by the Czechoslovak Ministry of Defence in 1963. The first Czechoslovak rockets to find practical use were launched in 1965. This study has been created as a part of the scientific project: Výzkumný záměr MSM 0021620827 České země uprostřed Evropy v minulosti a dnes, blok V/d: Česká vysoko\\vskolská vzdělanost.

The steady and transient motion of a sphere through a viscoelastic fluid

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

Arigo, M.T.; McKinley, G.H.

1994-12-31

The settling motion of a sphere along the centerline of a cylindrical tube filled with a viscoelastic fluid is examined experimentally to quantify both the initial transient acceleration from rest and the ultimate steady state motion. A digital imaging system is used to determine the initial transient behavior of the sphere, and a laser Doppler velocimetry (LDV) system is used to independently measure the velocity of the fluid along the centerline of the cylinder as the sphere falls at its ultimate settling velocity. The motion of the sphere is a sensitive function of the dimensionless ratio of the sphere tomore » tube radii a/R and the dimensionless parameter called the Deborah number De. In this study, the authors extend the previous work of Becker et al. (1994), who examined a single ratio of a/R = 0.243, by considering a smaller aspect ratio of a/R = 0.121. Deborah numbers in the range 0.767 {le} De {le} 8.366 were obtained and experimental results who transient velocity over shoots of up to fifty percent of the final constant settling velocity at high De. comparison of the steady state velocity of the sphere in a non-Newtonian fluid to the theoretically-predicted stokes settling velocity reveals an initial drag reduction for low values of De followed by a drag enhancement at high De. LDV measurements in the viscoelastic fluid for both aspect ratios indicate a flow field in which the fore/aft symmetry is broken with the velocity profile in the wake of the sphere extending up to 50 radii behind the sphere at high De.« less

Stennis hosts Gulf Pine Council's NASA Brownie Day

NASA Image and Video Library

2007-10-13

Tori Williams, of Brownie Girl Scout Troop 313, builds her own `stomp rocket' with the help of adult chaperone Pamela Cottrell. The two, of Gulfport, participated in NASA Brownie Day on Oct. 13 at Stennis Space Center. They were among nearly 200 members of Brownie Girl Scout Troops within the Gulf Pines Council who took part in the day of educational activities at SSC. Brownie Day used NASA curriculum support materials to teach about the sun and its significance in our solar system. In addition to building and launching their own model rockets, the girls toured the center's portable Starlab planetarium; viewed demonstrations about living and working in space; played games of `Moon Phasers' that teach about the rotation of the moon around the earth; made bracelets with ultraviolet-sensitive beads; and other activities that celebrated Earth's very own star. They also toured StenniSphere and were able to earn their Earth and Sky and Space Explorer `Try-Its.'

Stennis hosts Gulf Pine Council's NASA Brownie Day

NASA Technical Reports Server (NTRS)

2007-01-01

Tori Williams, of Brownie Girl Scout Troop 313, builds her own `stomp rocket' with the help of adult chaperone Pamela Cottrell. The two, of Gulfport, participated in NASA Brownie Day on Oct. 13 at Stennis Space Center. They were among nearly 200 members of Brownie Girl Scout Troops within the Gulf Pines Council who took part in the day of educational activities at SSC. Brownie Day used NASA curriculum support materials to teach about the sun and its significance in our solar system. In addition to building and launching their own model rockets, the girls toured the center's portable Starlab planetarium; viewed demonstrations about living and working in space; played games of `Moon Phasers' that teach about the rotation of the moon around the earth; made bracelets with ultraviolet-sensitive beads; and other activities that celebrated Earth's very own star. They also toured StenniSphere and were able to earn their Earth and Sky and Space Explorer `Try-Its.'

Characterization of Air Emissions from Open Burning and Open Detonation of Gun Propellants and Ammunition

EPA Science Inventory

Emissions from open burning (OB) and open detonation (OD) of military ordnance and static fires (SF) of rocket motors were sampled in fall, 2013 at the Dundurn Depot (Saskatchewan, Canada). Emission sampling was conducted with an aerostat-lofted instrument package termed the “Fl...

Respiratory Home Health Care

MedlinePlus

... if it gets knocked over and damaged, the gas could escape, making the cylinder act like a rocket. If you have long tubing that lets you move about the house, warn visitors so they won’t trip on it. If you have a vessel of liquid oxygen, keep it upright. If it falls on ...

Stokes versus Basset: comparison of forces governing motion of small bodies with high acceleration

NASA Astrophysics Data System (ADS)

Krafcik, A.; Babinec, P.; Frollo, I.

2018-05-01

In this paper, the importance of the forces governing the motion of a millimetre-sized sphere in a viscous fluid has been examined. As has been shown previously, for spheres moving with a high initial acceleration, the Basset history force should be used, as well as the commonly used Stokes force. This paper introduces the concept of history forces, which are almost unknown to students despite their interesting mathematical structure and physical meaning, and shows the implementation of simple and efficient numerical methods as a MATLAB code to simulate the motion of a falling sphere. An important application of this code could be, for example, the simulation of microfluidic systems, where the external forces are very large and the relevant timescale is in the order of milliseconds to seconds, and therefore the Basset history force cannot be neglected.

On the Effect of Sphere-Overlap on Super Coarse-Grained Models of Protein Assemblies

NASA Astrophysics Data System (ADS)

Degiacomi, Matteo T.

2018-05-01

Ion mobility mass spectrometry (IM/MS) can provide structural information on intact protein complexes. Such data, including connectivity and collision cross sections (CCS) of assemblies' subunits, can in turn be used as a guide to produce representative super coarse-grained models. These models are constituted by ensembles of overlapping spheres, each representing a protein subunit. A model is considered plausible if the CCS and sphere-overlap levels of its subunits fall within predetermined confidence intervals. While the first is determined by experimental error, the latter is based on a statistical analysis on a range of protein dimers. Here, we first propose a new expression to describe the overlap between two spheres. Then we analyze the effect of specific overlap cutoff choices on the precision and accuracy of super coarse-grained models. Finally, we propose a method to determine overlap cutoff levels on a per-case scenario, based on collected CCS data, and show that it can be applied to the characterization of the assembly topology of symmetrical homo-multimers. [Figure not available: see fulltext.

ODERACS 2 White Spheres Optical Calibration Report

NASA Technical Reports Server (NTRS)

Culp, Robert D.; Gravseth, Ian; Gloor, Jason; Wantuch, Todd

1995-01-01

This report documents the status of the Orbital Debris Radar Calibration Spheres (ODERACS) 2 white spheres optical calibration study. The purpose of this study is to determine the spectral reflectivity and scattering characteristics in the visible wavelength region for the white spheres that were added to the project in the fall, 1994. Laboratory measurements were performed upon these objects and an analysis of the resulting data was conducted. These measurements are performed by illuminating the objects with a collimated beam of light and measuring the reflected light versus the phase angle. The phase angle is defined as the angle between the light source and the sensor, as viewed from the object. By measuring the reflected signal at the various phase angles, one is able to estimate the reflectance properties of the object. The methodology used in taking the measurements and reducing the data are presented. The results of this study will be used to support the calibration of ground-based optical instruments used in support of space debris research. Visible measurements will be made by the GEODDS, NASA and ILADOT telescopes.

Russian Education: A Revolution and Then a Fall

ERIC Educational Resources Information Center

Ismagilov, R. F.; Salnikov, P. P.; Ger, O. E.; Kaizer, A. G.

2016-01-01

The authors analyze the problems of the Russian education system and discuss their origins and causes, as well as their detrimental impact on all spheres of public life. After looking at some solutions and controversial reform measures, they describe the Russian and foreign experiences of implementing reforms in education. They weigh the pros and…

The University, Democracy and the Public Sphere

ERIC Educational Resources Information Center

Holmwood, John

2017-01-01

This article takes a historical approach to the rise and fall of the public university, relating its fate to specific developments in public policy. Particular attention will be paid to the United Kingdom since it has developed an explicit drive towards the marketization of higher education in the context of an earlier commitment to public higher…

[Stigmatisation and mental illness: medical workers, politics and journalists].

PubMed

Touzet, Patrick

2011-01-01

Stigmatisation of mental health patients results from our social representations. The destigmatisation for which medical workers aim towards falls within the political sphere of psychiatry. The other actors, journalists and politicians, also have an important role to play. They can strengthen stigmatisation when their personal interests go before their professional missions.

Integrated rheology model: Explosive Composition B-3

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

Davis, Stephen M.; Zerkle, David K.; Smilowitz, Laura B.

Composition B-3 (Comp B-3) is a high explosive formulation composed of 60/40wt% RDX (1,3,5-trinitroperhydro-1,3,5-triazine) /TNT (2,4,6 trinitrotoluene). Above approximately 78°C this formulation partially melts to form a multiphase system with solid RDX particles in a molten TNT matrix. This multiphase system presents a number of phenomena that influence its apparent viscosity. In an earlier study explosive Composition B-3 (Comp B-3, 60/40wt% RDX/TNT) was examined for evidence of yield stress using a non-isothermal falling ball viscometer and a yield stress model was proposed in this paper. An integrated viscosity model suitable for use in computational fluid dynamics (CFD) simulations is developedmore » to capture the transition from a heterogeneous solid to a Bingham viscoplastic fluid. This viscosity model is used to simulate the motion of imbedded spheres falling through molten Comp B-3. Finally, comparison of the simulations to physical tests show agreement between the positions predicted by the model and the measured locations of the spheres as a function of temperature between 90C and 165C.« less

Integrated rheology model: Explosive Composition B-3

DOE PAGES

Davis, Stephen M.; Zerkle, David K.; Smilowitz, Laura B.; ...

2018-03-20

Composition B-3 (Comp B-3) is a high explosive formulation composed of 60/40wt% RDX (1,3,5-trinitroperhydro-1,3,5-triazine) /TNT (2,4,6 trinitrotoluene). Above approximately 78°C this formulation partially melts to form a multiphase system with solid RDX particles in a molten TNT matrix. This multiphase system presents a number of phenomena that influence its apparent viscosity. In an earlier study explosive Composition B-3 (Comp B-3, 60/40wt% RDX/TNT) was examined for evidence of yield stress using a non-isothermal falling ball viscometer and a yield stress model was proposed in this paper. An integrated viscosity model suitable for use in computational fluid dynamics (CFD) simulations is developedmore » to capture the transition from a heterogeneous solid to a Bingham viscoplastic fluid. This viscosity model is used to simulate the motion of imbedded spheres falling through molten Comp B-3. Finally, comparison of the simulations to physical tests show agreement between the positions predicted by the model and the measured locations of the spheres as a function of temperature between 90C and 165C.« less

Safety First: Houston, We Have Liftoff!

ERIC Educational Resources Information Center

Roy, Ken

2014-01-01

A thrown basketball, a kicked football, an elastically launched catapult payload, and a free-falling solid fuel or pressurized gas-propelled rocket all have one thing in common. They are all projectiles familiar to elementary students. A projectile is an object thrown with an initial velocity and then allowed to move without thrust along its…

Soil factors of ecosystems' disturbance risk reduction under the impact of rocket fuel

NASA Astrophysics Data System (ADS)

Krechetov, Pavel; Koroleva, Tatyana; Sharapova, Anna; Chernitsova, Olga

2016-04-01

Environmental impacts occur at all stages of space rocket launch. One of the most dangerous consequences of a missile launch is pollution by components of rocket fuels ((unsymmetrical dimethylhydrazine (UDMH)). The areas subjected to falls of the used stages of carrier rockets launched from the Baikonur cosmodrome occupy thousands of square kilometers of different natural landscapes: from dry steppes of Kazakhstan to the taiga of West Siberia and mountains of the Altai-Sayany region. The study aims at assessing the environmental risk of adverse effects of rocket fuel on the soil. Experimental studies have been performed on soil and rock samples with specified parameters of the material composition. The effect of organic matter, acid-base properties, particle size distribution, and mineralogy on the decrease in the concentration of UDMH in equilibrium solutions has been studied. It has been found that the soil factors are arranged in the following series according to the effect on UDMH mobility: acid-base properties > organic matter content >clay fraction mineralogy > particle size distribution. The estimation of the rate of self-purification of contaminated soil is carried out. Experimental study of the behavior of UDMH in soil allowed to define a model for calculating critical loads of UDMH in terrestrial ecosystems.

ISAAC: A REXUS Student Experiment to Demonstrate an Ejection System with Predefined Direction

NASA Astrophysics Data System (ADS)

Balmer, G.; Berquand, A.; Company-Vallet, E.; Granberg, V.; Grigore, V.; Ivchenko, N.; Kevorkov, R.; Lundkvist, E.; Olentsenko, G.; Pacheco-Labrador, J.; Tibert, G.; Yuan, Y.

2015-09-01

ISAAC Infrared Spectroscopy to Analyse the middle Atmosphere Composition — was a student experiment launched from SSC's Esrange Space Centre, Sweden, on 29th May 2014, on board the sounding rocket REXUS 15 in the frame of the REXUS/BEXUS programme. The main focus of the experiment was to implement an ejection system for two large Free Falling Units (FFUs) (240 mm x 80 mm) to be ejected from a spinning rocket into a predefined direction. The system design relied on a spring-based ejection system. Sun and angular rate sensors were used to control and time the ejection. The flight data includes telemetry from the Rocket Mounted Unit (RMU), received and saved during flight, as well as video footage from the GoPro camera mounted inside the RMU and recovered after the flight. The FFUs' direction, speed and spin frequency as well as the rocket spin frequency were determined by analyzing the video footage. The FFU-Rocket-Sun angles were 64.3° and 104.3°, within the required margins of 90°+45°. The FFU speeds were 3.98 mIs and 3.74 mIs, lower than the expected 5± 1 mIs. The FFUs' spin frequencies were 1 .38 Hz and 1 .60 Hz, approximately half the rocket's spin frequency. The rocket spin rate slightly changed from 3. 163 Hz before the ejection to 3.1 17 Hz after the ejection of the two FFUs. The angular rate, sun sensor data and temperature on the inside of the rocket module skin were also recorded. The experiment design and results of the data analysis are presented in this paper.

BLUE-protocol and FALLS-protocol: two applications of lung ultrasound in the critically ill.

PubMed

Lichtenstein, Daniel A

2015-06-01

This review article describes two protocols adapted from lung ultrasound: the bedside lung ultrasound in emergency (BLUE)-protocol for the immediate diagnosis of acute respiratory failure and the fluid administration limited by lung sonography (FALLS)-protocol for the management of acute circulatory failure. These applications require the mastery of 10 signs indicating normal lung surface (bat sign, lung sliding, A-lines), pleural effusions (quad and sinusoid sign), lung consolidations (fractal and tissue-like sign), interstitial syndrome (lung rockets), and pneumothorax (stratosphere sign and the lung point). These signs have been assessed in adults, with diagnostic accuracies ranging from 90% to 100%, allowing consideration of ultrasound as a reasonable bedside gold standard. In the BLUE-protocol, profiles have been designed for the main diseases (pneumonia, congestive heart failure, COPD, asthma, pulmonary embolism, pneumothorax), with an accuracy > 90%. In the FALLS-protocol, the change from A-lines to lung rockets appears at a threshold of 18 mm Hg of pulmonary artery occlusion pressure, providing a direct biomarker of clinical volemia. The FALLS-protocol sequentially rules out obstructive, then cardiogenic, then hypovolemic shock for expediting the diagnosis of distributive (usually septic) shock. These applications can be done using simple grayscale machines and one microconvex probe suitable for the whole body. Lung ultrasound is a multifaceted tool also useful for decreasing radiation doses (of interest in neonates where the lung signatures are similar to those in adults), from ARDS to trauma management, and from ICUs to points of care. If done in suitable centers, training is the least of the limitations for making use of this kind of visual medicine.

Irreversible Local Markov Chains with Rapid Convergence towards Equilibrium.

PubMed

Kapfer, Sebastian C; Krauth, Werner

2017-12-15

We study the continuous one-dimensional hard-sphere model and present irreversible local Markov chains that mix on faster time scales than the reversible heat bath or Metropolis algorithms. The mixing time scales appear to fall into two distinct universality classes, both faster than for reversible local Markov chains. The event-chain algorithm, the infinitesimal limit of one of these Markov chains, belongs to the class presenting the fastest decay. For the lattice-gas limit of the hard-sphere model, reversible local Markov chains correspond to the symmetric simple exclusion process (SEP) with periodic boundary conditions. The two universality classes for irreversible Markov chains are realized by the totally asymmetric SEP (TASEP), and by a faster variant (lifted TASEP) that we propose here. We discuss how our irreversible hard-sphere Markov chains generalize to arbitrary repulsive pair interactions and carry over to higher dimensions through the concept of lifted Markov chains and the recently introduced factorized Metropolis acceptance rule.

Irreversible Local Markov Chains with Rapid Convergence towards Equilibrium

NASA Astrophysics Data System (ADS)

Kapfer, Sebastian C.; Krauth, Werner

2017-12-01

We study the continuous one-dimensional hard-sphere model and present irreversible local Markov chains that mix on faster time scales than the reversible heat bath or Metropolis algorithms. The mixing time scales appear to fall into two distinct universality classes, both faster than for reversible local Markov chains. The event-chain algorithm, the infinitesimal limit of one of these Markov chains, belongs to the class presenting the fastest decay. For the lattice-gas limit of the hard-sphere model, reversible local Markov chains correspond to the symmetric simple exclusion process (SEP) with periodic boundary conditions. The two universality classes for irreversible Markov chains are realized by the totally asymmetric SEP (TASEP), and by a faster variant (lifted TASEP) that we propose here. We discuss how our irreversible hard-sphere Markov chains generalize to arbitrary repulsive pair interactions and carry over to higher dimensions through the concept of lifted Markov chains and the recently introduced factorized Metropolis acceptance rule.

Carbide fuels for nuclear thermal propulsion

NASA Astrophysics Data System (ADS)

Matthews, R. B.; Blair, H. T.; Chidester, K. M.; Davidson, K. V.; Stark, W. E.; Storms, E. K.

1991-09-01

A renewed interest in manned exploration of space has revitalized interest in the potential for advancing nuclear rocket technology developed during the 1960's. Carbide fuel performance, melting point, stability, fabricability and compatibility are key technology issues for advanced Nuclear Thermal Propulsion reactors. The Rover fuels development ended with proven carbide fuel forms with demonstrated operating temperatures up to 2700 K for over 100 minutes. The next generation of nuclear rockets will start where the Rover technology ended, but with a more rigorous set of operating requirements including operating lifetime to 10 hours, operating temperatures greater that 3000 K, low fission product release, and compatibility. A brief overview of Rover/NERVA carbide fuel development is presented. A new fuel form with the highest potential combination of operating temperature and lifetime is proposed that consists of a coated uranium carbide fuel sphere with built-in porosity to contain fission products. The particles are dispersed in a fiber reinforced ZrC matrix to increase thermal shock resistance.

Conceptual design of an orbital debris collector

NASA Technical Reports Server (NTRS)

Odonoghue, Peter (Editor); Brenton, Brian; Chambers, Ernest; Schwind, Thomas; Swanhart, Christopher; Williams, Thomas

1991-01-01

The current Lower Earth Orbit (LEO) environment has become overly crowded with space debris. An evaluation of types of debris is presented in order to determine which debris poses the greatest threat to operation in space, and would therefore provide a feasible target for removal. A target meeting these functional requirements was found in the Cosmos C-1B Rocket Body. These launchers are spent space transporters which constitute a very grave risk of collision and fragmentation in LEO. The motion and physical characteristics of these rocket bodies have determined the most feasible method of removal. The proposed Orbital Debris Collector (ODC) device is designed to attach to the Orbital Maneuvering Vehicle (OMV), which provides all propulsion, tracking, and power systems. The OMV/ODC combination, the Rocket Body Retrieval Vehicle (RBRV), will match orbits with the rocket body, use a spin table to match the rotational motion of the debris, capture it, despin it, and remove it from orbit by allowing it to fall into the Earth's atmosphere. A disposal analysis is presented to show how the debris will be deorbited into the Earth's atmosphere. The conceptual means of operation of a sample mission is described.

The washout of combustion-generated hydrogen chloride. [rocket exhaust raindrop scavenging quantification

NASA Technical Reports Server (NTRS)

Fenton, D. L.; Purcell, R. Y.; Hrdina, D.; Knutson, E. O.

1980-01-01

The coefficient for the washout from a rocket exhaust cloud of HCl generated by the combustion of an ammonium perchlorate-based solid rocket propellant such as that to be used for the Space Shuttle Booster is determined. A mathematical model of HCl scavenging by rain is developed taking into account rain droplet size, fall velocity and concentration under various rain conditions, partitioning of exhaust HCl between liquid and gaseous phases, the tendency of HCl to promote water vapor condensation and the concentration and size of droplets within the exhaust cloud. The washout coefficient is calculated as a function of total cloud water content, total HCl content at 100% relative humidity, condensation nuclei concentration and rain intensity. The model predictions are compared with experimental results obtained in scavenging tests with solid rocket exhaust and raindrops of different sizes, and the large reduction in washout coefficient at high relative humidities predicted by the model is not observed. A washout coefficient equal to 0.0000512 times the -0.176 power of the mass concentration of HCl times the 0.773 power of the rainfall intensity is obtained from the experimental data.

Vertical Impact of a Sphere Falling into Water

ERIC Educational Resources Information Center

Cross, Rod

2016-01-01

The nature of the drag force on an object moving through a fluid is well documented and many experiments have been described to allow students to measure the force. For low speed flows the drag force is proportional to the velocity of the object, while at high flow speeds the drag force is proportional to the velocity squared. The basic physics…

Using the Atwood machine to study Stokes' law

NASA Astrophysics Data System (ADS)

Greenwood, Margaret Stautberg; Fazio, Frances; Russotto, Marie; Wilkosz, Aaron

1986-10-01

A sphere, on one side of an Atwood machine, is immersed in glycerin and permitted to fall. We timed the descent and measured the terminal speed. We varied the mass m2 on the other side of the Atwood machine and plotted a graph of the terminal speed versus mass m2. Both the slope and the intercept yield the viscosity.

SolSTUS: Solar Source Thermal Upper Stage

NASA Astrophysics Data System (ADS)

This paper was written by members of the Utah State University (USU) Space Systems Design class, fall quarter 1993. The class is funded by NASA and administered by the University Space Research Association (USRA). The focus of the class is to give students some experience in design of space systems and as a source of original ideas for NASA. This paper is a summary of the work done by members of the Space Systems Design class during the opening phase of the course. The class was divided into groups to work on different areas of the Solar Thermal Rocket (STR) booster in order to produce a design reference mission that would identify the key design issues. The design reference mission focused upon a small satellite mission to Mars. There are several critical components in a Solar Thermal Rocket. STR's produce a very low thrust, but have a high specific impulse, meaning that they take longer to reach the desired orbit, but use a lot less fuel in doing it. The complexity of the rocket is discussed in this paper. Some of the more critical design problems discussed are: (1) the structural and optical complexity of collecting and focusing sunlight onto a specific point, (2) long term storage of fuel (liquid hydrogen), (3) attitude control while thrusting in an elliptical orbit and orienting the mirrors to collect sunlight, and (4) power and communications for the rocket and it's internal systems. The design reference mission discussed here is a very general mission to Mars. A first order trajectory design has been done and a possible basic science payload for Mars has been suggested. This paper summarizes the design reference mission (DRM) formulated by the USU students during fall quarter and identifies major design challenges that will confront the design team during the next two quarters here at USU.

SolSTUS: Solar Source Thermal Upper Stage

NASA Technical Reports Server (NTRS)

1994-01-01

This paper was written by members of the Utah State University (USU) Space Systems Design class, fall quarter 1993. The class is funded by NASA and administered by the University Space Research Association (USRA). The focus of the class is to give students some experience in design of space systems and as a source of original ideas for NASA. This paper is a summary of the work done by members of the Space Systems Design class during the opening phase of the course. The class was divided into groups to work on different areas of the Solar Thermal Rocket (STR) booster in order to produce a design reference mission that would identify the key design issues. The design reference mission focused upon a small satellite mission to Mars. There are several critical components in a Solar Thermal Rocket. STR's produce a very low thrust, but have a high specific impulse, meaning that they take longer to reach the desired orbit, but use a lot less fuel in doing it. The complexity of the rocket is discussed in this paper. Some of the more critical design problems discussed are: (1) the structural and optical complexity of collecting and focusing sunlight onto a specific point, (2) long term storage of fuel (liquid hydrogen), (3) attitude control while thrusting in an elliptical orbit and orienting the mirrors to collect sunlight, and (4) power and communications for the rocket and it's internal systems. The design reference mission discussed here is a very general mission to Mars. A first order trajectory design has been done and a possible basic science payload for Mars has been suggested. This paper summarizes the design reference mission (DRM) formulated by the USU students during fall quarter and identifies major design challenges that will confront the design team during the next two quarters here at USU.

Watch 60-Seconds of Major SLS Hardware Being Moved and Put in the Test Stand at NASA Marshall

NASA Image and Video Library

2016-10-13

A test version of the launch vehicle stage adapter (LVSA) for NASA’s new rocket, the Space Launch System, is moved to a 65-foot-tall test stand at the agency’s Marshall Space Flight Center in Huntsville, Alabama. The test version LVSA will be stacked with other test pieces of the upper part of the SLS rocket and pushed, pulled and twisted as part of an upcoming test series to ensure each structure can withstand the incredible stresses of launch. The LVSA joins the core stage simulator, which was loaded into the test stand Sept. 21. The other three qualification articles and the Orion simulator will complete the stack later this fall. SLS will be the world’s most powerful rocket, and with the Orion spacecraft, take astronauts to deep-space destinations, including the Journey to Mars. More information on the upcoming test series can be found here: http://go.nasa.gov/2dS8yXB

Selection of artificial gravity by animals during suborbital rocket flights

NASA Technical Reports Server (NTRS)

Lange, K. O.; Belleville, R. E.; Clark, F. C.

1975-01-01

White rats selected preferred artificial gravity levels by locomotion in centrifuges consisting of two runways mounted in the nose of sounding rockets. Roll rate of the Aerobee 150A rocket was designed to produce an angular velocity of 45 rpm during 5 min of free-fall, providing a gravity range from 0.3 to 1.5 G depending on a subject's runway position. One animal was released at the high and one at the low gravity position in each flight. Animal positions were continuously recorded. Locomotion patterns during these flights were similar. All four animals explored the entire available G-range. One rat settled at 0.4 G after 2 min; the others crossed the 1-G location in progressively narrower excursions and were near earth gravity at the end of the test period. Tentatively, the data suggest that normal earth-reared rats select earth gravity when available magnitudes include values above and below 1 G. Modification of gravity preference by prolonged exposure to higher or lower levels remains a possibility.

A three-layer magnetic shielding for the MAIUS-1 mission on a sounding rocket

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

Kubelka-Lange, André, E-mail: andre.kubelka@zarm.uni-bremen.de; Herrmann, Sven; Grosse, Jens

Bose-Einstein-Condensates (BECs) can be used as a very sensitive tool for experiments on fundamental questions in physics like testing the equivalence principle using matter wave interferometry. Since the sensitivity of these experiments in ground-based environments is limited by the available free fall time, the QUANTUS project started to perform BEC interferometry experiments in micro-gravity. After successful campaigns in the drop tower, the next step is a space-borne experiment. The MAIUS-mission will be an atom-optical experiment that will show the feasibility of experiments with ultra-cold quantum gases in microgravity in a sounding rocket. The experiment will create a BEC of 10{supmore » 5} {sup 87}Rb-atoms in less than 5 s and will demonstrate application of basic atom interferometer techniques over a flight time of 6 min. The hardware is specifically designed to match the requirements of a sounding rocket mission. Special attention is thereby spent on the appropriate magnetic shielding from varying magnetic fields during the rocket flight, since the experiment procedures are very sensitive to external magnetic fields. A three-layer magnetic shielding provides a high shielding effectiveness factor of at least 1000 for an undisturbed operation of the experiment. The design of this magnetic shielding, the magnetic properties, simulations, and tests of its suitability for a sounding rocket flight are presented in this article.« less

A three-layer magnetic shielding for the MAIUS-1 mission on a sounding rocket.

PubMed

Kubelka-Lange, André; Herrmann, Sven; Grosse, Jens; Lämmerzahl, Claus; Rasel, Ernst M; Braxmaier, Claus

2016-06-01

Bose-Einstein-Condensates (BECs) can be used as a very sensitive tool for experiments on fundamental questions in physics like testing the equivalence principle using matter wave interferometry. Since the sensitivity of these experiments in ground-based environments is limited by the available free fall time, the QUANTUS project started to perform BEC interferometry experiments in micro-gravity. After successful campaigns in the drop tower, the next step is a space-borne experiment. The MAIUS-mission will be an atom-optical experiment that will show the feasibility of experiments with ultra-cold quantum gases in microgravity in a sounding rocket. The experiment will create a BEC of 10(5) (87)Rb-atoms in less than 5 s and will demonstrate application of basic atom interferometer techniques over a flight time of 6 min. The hardware is specifically designed to match the requirements of a sounding rocket mission. Special attention is thereby spent on the appropriate magnetic shielding from varying magnetic fields during the rocket flight, since the experiment procedures are very sensitive to external magnetic fields. A three-layer magnetic shielding provides a high shielding effectiveness factor of at least 1000 for an undisturbed operation of the experiment. The design of this magnetic shielding, the magnetic properties, simulations, and tests of its suitability for a sounding rocket flight are presented in this article.

On the backscatter of solar He II, 304 A radiation from interplanetary He/+/.

NASA Technical Reports Server (NTRS)

Paresce, F.; Bowyer, S.

1973-01-01

Backscatter of solar He II, 304 A radiation by interplanetary positive helium ions is shown to be insufficient to account for recent observations of this airglow radiation in the night sky at rocket altitudes. In fact, for most viewing directions, the expected intensities probably fall well below the sensitivity threshold of existing extreme ultraviolet instrumentation.

Early Rockets

NASA Image and Video Library

1943-01-01

In this photograph from the fall of 1943, German technicians wire vehicles for mobile V-2 batteries in an abandoned railroad turnel in the Rhineland. The team of German engineers and scientists who developed the V-2 came to the United States at the end of World War II and worked for the U. S. Army at Fort Bliss, Texas, and Redstone Arsenal in Huntsville, Alabama.

Density and Viscosity Measurement of Liquid FeS at High Pressure and High Temperature Using Synchrotron X-ray

NASA Astrophysics Data System (ADS)

Yu, T.; Long, H.; Young, C.; Wang, L.; Chen, J.

2005-12-01

From previous experimental and theoretical studies, sulfur has been considered one of the possible light elements in the core that might be responsible for the large density deficit when compared with the theoretical pure Fe core (Ganapathy and Anders, 1974; Ahrens and Jeanloz, 1987). Therefore, understanding the physical properties of liquid FeS will help us reveal the details of the Earth?|s core. This study focused on the liquid state of sulfur in iron due to sulfur?|s lack of amount in the mantle; easiness to alloy with iron; and the predicted 5 wt% ~10 wt% amount of this light element in the core (Ahrens, 1979; Sherman, 1997). Modern development of the multi-anvil high pressure apparatus limits the pressure range of the experiments (<30 GPa). It is somewhat low if comparing with the outer core pressure condition. Therefore, extrapolation of data derived at low pressure range to the condition of the outer core (>130 GPa) has to be applied, and may produce results that are far from the true numbers. However, at the point while the techniques are limited, studying the physical properties of the liquid-phase FeS at relatively low pressures still provides us a better picture of the physical behavior of the outer core comparing with data derived from solid state FeS experiments. Pervious studies on the viscosity of the Fe-FeS system (LeBlanc and Secco, 1996; Dobson et al., 2000; Urakawa et al., 2001; Secco et al., 2002) have presented different values of viscosity numbers with a maximum difference of two orders of magnitude. We have conducted the density measurements of liquid FeS (~36 wt% of S) up to 5.6 GPa in pressure and 1673K in temperature using the in-situ synchrotron-source x-ray absorption setup at Beamline X17B2, NSLS. The viscosity measurements were conducted by the x-ray radiograph technique combined with the falling sphere method. The falling sphere method applied at the experiment is suitable for liquids with viscosities between 10-3 Pa-s and 105 Pa-s (LeBlanc et al., 1999). We used tungsten spheres in our viscosity measurement experiments. We analyzed the sphere falling motion in the sample chamber at high pressure and high temperature. And by applying our density compression curve of liquid FeS to the Stokes?| viscometry method, we were able to derive the viscosity of liquid FeS.

Measuring the Drag Force on a Falling Ball

ERIC Educational Resources Information Center

Cross, Rod; Lindsey, Crawford

2014-01-01

The effect of the aerodynamic drag force on an object in flight is well known and has been described in this and other journals many times. At speeds less than about 1 m/s, the drag force on a sphere is proportional to the speed and is given by Stokes' law. At higher speeds, the drag force is proportional to the velocity squared and is…

Random sphere packing model of heterogeneous propellants

NASA Astrophysics Data System (ADS)

Kochevets, Sergei Victorovich

It is well recognized that combustion of heterogeneous propellants is strongly dependent on the propellant morphology. Recent developments in computing systems make it possible to start three-dimensional modeling of heterogeneous propellant combustion. A key component of such large scale computations is a realistic model of industrial propellants which retains the true morphology---a goal never achieved before. The research presented develops the Random Sphere Packing Model of heterogeneous propellants and generates numerical samples of actual industrial propellants. This is done by developing a sphere packing algorithm which randomly packs a large number of spheres with a polydisperse size distribution within a rectangular domain. First, the packing code is developed, optimized for performance, and parallelized using the OpenMP shared memory architecture. Second, the morphology and packing fraction of two simple cases of unimodal and bimodal packs are investigated computationally and analytically. It is shown that both the Loose Random Packing and Dense Random Packing limits are not well defined and the growth rate of the spheres is identified as the key parameter controlling the efficiency of the packing. For a properly chosen growth rate, computational results are found to be in excellent agreement with experimental data. Third, two strategies are developed to define numerical samples of polydisperse heterogeneous propellants: the Deterministic Strategy and the Random Selection Strategy. Using these strategies, numerical samples of industrial propellants are generated. The packing fraction is investigated and it is shown that the experimental values of the packing fraction can be achieved computationally. It is strongly believed that this Random Sphere Packing Model of propellants is a major step forward in the realistic computational modeling of heterogeneous propellant of combustion. In addition, a method of analysis of the morphology of heterogeneous propellants is developed which uses the concept of multi-point correlation functions. A set of intrinsic length scales of local density fluctuations in random heterogeneous propellants is identified by performing a Monte-Carlo study of the correlation functions. This method of analysis shows great promise for understanding the origins of the combustion instability of heterogeneous propellants, and is believed to become a valuable tool for the development of safe and reliable rocket engines.

Population annealing simulations of a binary hard-sphere mixture

NASA Astrophysics Data System (ADS)

Callaham, Jared; Machta, Jonathan

2017-06-01

Population annealing is a sequential Monte Carlo scheme well suited to simulating equilibrium states of systems with rough free energy landscapes. Here we use population annealing to study a binary mixture of hard spheres. Population annealing is a parallel version of simulated annealing with an extra resampling step that ensures that a population of replicas of the system represents the equilibrium ensemble at every packing fraction in an annealing schedule. The algorithm and its equilibration properties are described, and results are presented for a glass-forming fluid composed of a 50/50 mixture of hard spheres with diameter ratio of 1.4:1. For this system, we obtain precise results for the equation of state in the glassy regime up to packing fractions φ ≈0.60 and study deviations from the Boublik-Mansoori-Carnahan-Starling-Leland equation of state. For higher packing fractions, the algorithm falls out of equilibrium and a free volume fit predicts jamming at packing fraction φ ≈0.667 . We conclude that population annealing is an effective tool for studying equilibrium glassy fluids and the jamming transition.

Strategic Studies Quarterly. Volume 9, Number 3. Fall 2015

DTIC Science & Technology

2015-01-01

leaders doing what they can to better inform civilians to minimize the number of times civilian leaders might be wrong? Golby proposes a "new framework...but they have a clear responsibility to communicate their expertise and advice candidly during policy deliberations. The effective development of...there may not always be a clear distinction between political and military spheres. Political leaders of- ten depend on information they obtain from

A Conventional Flexible Response Strategy for the Western Pacific

DTIC Science & Technology

2015-04-15

Finlandized,“ falling into Beijing’s sphere of influence. Whichever combination of balancing and bandwagoning strategies by regional states occurs...stakes that exist in many possible conflicts with China. US responses must be credible reactions to provocations if they are to be effective ...hold major US air bases in Guam and Okinawa at risk through heavy missile barrages will make air-based power projection less effective .39 These

Investigation of Slosh Dynamics on Flight and Ground Platforms

NASA Astrophysics Data System (ADS)

Vergalla, Michael; Zhou, Ran

The slosh dynamics in cryogenic fuel tanks under microgravity is a problem that severely affects the reliability of spacecraft launching. To investigate slosh dynamics and their effects on space vehicle dynamics three levels of testing are presently in progress. Platforms include a 3-DOF ground testing table, parabolic flights, sounding rockets and finally the International Space Station. Ground tests provide an economically viable platform for investigating rotational, translational, and coupled feed-back modes due to repeatable CNC motions. The parabolic flight campaign has conducted four successful flights aboard multiple aircraft using static and tethered slosh packages. Using the PANTHER II student designed rocket, a slosh package was launched as a payload. Finally with collaboration between Florida Institute of Technology and Massachusetts Institute of Technology SPHERES project, two test sessions investigating feedback using partially and fully filled propellant tanks have been completed aboard the In-ternational Space Station. Motion data from all tests will be input to in house Dynamic Mesh Model to further establish confidence in the versatility and accuracy of the method. The results show that it is necessary to construct additional hardware for slosh studies.

A preliminary analysis of low frequency pressure oscillations in hybrid rocket motors

NASA Technical Reports Server (NTRS)

Jenkins, Rhonald M.

1994-01-01

Past research with hybrid rockets has suggested that certain motor operating conditions are conducive to the formation of pressure oscillations, or flow instabilities, within the motor combustion chamber. These combustion-related vibrations or pressure oscillations may be encountered in virtually any type of rocket motor and typically fall into three frequency ranges: low frequency oscillations (0-300 Hz); intermediate frequency oscillations (400-1000 Hz); and high frequency oscillations (greater than 1000 Hz). In general, combustion instability is characterized by organized pressure oscillations occurring at well-defined intervals with pressure peaks that may maintain themselves, grow, or die out. Usually, such peaks exceed +/- 5% of the mean chamber pressure. For hybrid motors, these oscillations have been observed to grow to a limiting amplitude which may be dependent on factors such as fuel characteristics, oxidizer injector characteristics, average chamber pressure, oxidizer mass flux, combustion chamber length, and grain geometry. The approach taken in the present analysis is to develop a modified chamber length, L, instability theory which accounts for the relationship between pressure and oxidizer to fuel concentration ratio in the motor.

Launch Vehicle Stage Adapter from Start to Stack

NASA Image and Video Library

2016-10-16

See how a test version of the launch vehicle stage adapter (LVSA) for NASA's new rocket, the Space Launch System, is designed, built and stacked in a test stand at the agency's Marshall Space Flight Center in Huntsville, Alabama. The LVSA was moved to a 65-foot-tall test stand Oct. 12 at Marshall. The test version LVSA will be stacked with other test pieces of the upper part of the SLS rocket and pushed, pulled and twisted as part of an upcoming test series to ensure each structure can withstand the incredible stresses of launch. The LVSA joins the core stage simulator, which was loaded into the test stand Sept. 21. The other three qualification articles and the Orion simulator will complete the stack later this fall. Testing is scheduled to begin in early 2017. SLS will be the world’s most powerful rocket, and with the Orion spacecraft, take astronauts to deep-space destinations, including the Journey to Mars. More information on the upcoming test series can be found here: http://go.nasa.gov/2dS8yXB

Japanese H-IIA rocket

NASA Image and Video Library

2013-11-14

The Japanese H-IIA rocket will be launching the GPM Core Observatory into orbit in 2014. Credit: JAXA The Global Precipitation Measurement (GPM) mission is an international partnership co-led by NASA and the Japan Aerospace Exploration Agency (JAXA) that will provide next-generation global observations of precipitation from space. GPM will study global rain, snow and ice to better understand our climate, weather, and hydrometeorological processes. As of Novermber 2013 the GPM Core Observatory is in the final stages of testing at NASA Goddard Space Flight Center. The satellite will be flown to Japan in the fall of 2013 and launched into orbit on an HII-A rocket in early 2014. For more on the GPM mission, visit gpm.gsfc.nasa.gov/. NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

Rocket Design for the Future

NASA Technical Reports Server (NTRS)

Follett, William W.; Rajagopal, Raj

2001-01-01

The focus of the AA MDO team is to reduce product development cost through the capture and automation of best design and analysis practices and through increasing the availability of low-cost, high-fidelity analysis. Implementation of robust designs reduces costs associated with the Test-Fall-Fix cycle. RD is currently focusing on several technologies to improve the design process, including optimization and robust design, expert and rule-based systems, and collaborative technologies.

Testing of a Liquid Oxygen/Liquid Methane Reaction Control Thruster in a New Altitude Rocket Engine Test Facility

NASA Technical Reports Server (NTRS)

Meyer, Michael L.; Arrington, Lynn A.; Kleinhenz, Julie E.; Marshall, William M.

2012-01-01

A relocated rocket engine test facility, the Altitude Combustion Stand (ACS), was activated in 2009 at the NASA Glenn Research Center. This facility has the capability to test with a variety of propellants and up to a thrust level of 2000 lbf (8.9 kN) with precise measurement of propellant conditions, propellant flow rates, thrust and altitude conditions. These measurements enable accurate determination of a thruster and/or nozzle s altitude performance for both technology development and flight qualification purposes. In addition the facility was designed to enable efficient test operations to control costs for technology and advanced development projects. A liquid oxygen-liquid methane technology development test program was conducted in the ACS from the fall of 2009 to the fall of 2010. Three test phases were conducted investigating different operational modes and in addition, the project required the complexity of controlling propellant inlet temperatures over an extremely wide range. Despite the challenges of a unique propellant (liquid methane) and wide operating conditions, the facility performed well and delivered up to 24 hot fire tests in a single test day. The resulting data validated the feasibility of utilizing this propellant combination for future deep space applications.

Electromagnetic braking revisited with a magnetic point dipole model

NASA Astrophysics Data System (ADS)

Land, Sara; McGuire, Patrick; Bumb, Nikhil; Mann, Brian P.; Yellen, Benjamin B.

2016-04-01

A theoretical model is developed to predict the trajectory of magnetized spheres falling through a copper pipe. The derive magnetic point dipole model agrees well with the experimental trajectories for NdFeB spherical magnets of varying diameter, which are embedded inside 3D printed shells with fixed outer dimensions. This demonstration of electrodynamic phenomena and Lenz's law serves as a good laboratory exercise for physics, electromagnetics, and dynamics classes at the undergraduate level.

Cryo Tank Fill at Pad 39B

NASA Image and Video Library

2017-09-26

Several Praxair trucks carrying their loads of liquid oxygen, or LO2, arrive at Launch Pad 39B at NASA's Kennedy Space Center in Florida. The trucks will offload LO2 slowly into a giant storage sphere located at the northwest corner of the pad to gradually chill it down from normal temperature to about negative 298 degrees Fahrenheit, during the first major integrated operation to prepare for the launch of the agency's Orion spacecraft atop the Space Launch System (SLS) rocket. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to pad B to support the launch of the SLS and Orion spacecraft for Exploration Mission-1, deep space missions and NASA’s journey to Mars.

[Lifting the curtain on improvisation as a method].

PubMed

Tortonèse, Michèle; Chalancon, Benoît; Gauthier, Benjamin; Magny, Florian

2014-01-01

On the care stage, all the actors are active. One comes to lay down their suffering, the other has a dutyto consider their pain. The caregiver must play a role in stage managing the patient from the moment he or she remains anchored in reality and in the present moment. Beyond listening to the delusional speech, beyond containment and the effort of establishing communication, the nursing care of delusional patients falls within the sphere of negotiation.

The Infrared Handbook

DTIC Science & Technology

1978-01-01

wavelength, infrared range, SW1R, from 1.6 to 5.6 jum and in the long wavelength infrared, LWIR , from 7.0 to 23.0 fun. Figure 3-87 shows a profile of...si n n Wavelength (M ra) Fig. 3-86. Sample spectrum scan (vertical) from a LWIR spectrometer aboard a Black Brant rocket flown from Poker Flat...radiation of a finite cross-section. Laser, lidar, or search-light probes fall into this category. Because of the nonuniform illumination of the

Theoretical and experimental studies of atmospheric structure and dynamics, using high altitude chemical release, Radio meteor, and meteorological rocket network and other data

NASA Technical Reports Server (NTRS)

Edwards, H. D.

1976-01-01

Data collected by the Georgia Tech Radio Meteor Wind Facility during the fall and winter of 1975 are analyzed indicating a relationship between lower thermospheric circulation at mid latitudes and polar stratospheric dynamics. Techniques of measurement of mixing processes in the upper atmosphere and the interpretation of those measurements are described along with a diffusion simulation program based on the Global Reference Atmosphere program.

On the Concentration Gradient across a Spherical Source Washed by Slow Flow

PubMed Central

Jaffe, Lionel

1965-01-01

A model has been numerically analyzed to help interpret the orienting effects of flow upon cells. The model is a sphere steadily and uniformly emitting a diffusible stuff into a medium otherwise free of it and moving past with Stokes flow. Its properties depend primarily upon the Peclet number, Pe, equal to a · v∞/D, i.e., the sphere's radius, a, times the free stream speed, v∞, over the stuff's diffusion constant, D. As Pe rises, and washing becomes more effective, the average surface concentration, C̄s a falls (Figs. 2 and 5) and the residual material becomes relatively concentrated on the sphere's lee pole (Figs. 2 and 4). Specifically, as Pe rises from 0.1 to 1, the relative concentration gradient, G, rises from 0.7 to 5.0 per cent and to the point where it is rising at about 8 per cent per decade; by Pe 1000, G = 22.1 per cent. From Pe 1 through 1000, G/(1 - C̄s a), or the gradient per concentration deficiency remains at about 26 per cent suggesting that G approaches a ceiling of about 26 per cent. Also from Pe 1 through 1000, the average mass transfer co-efficient nearly equals that previously calculated for spheres maintaining constant surface concentration instead of flux. The complete differential equation without approximations, the Gauss-Seidel method, and an approximation for the outer boundary condition were used. PMID:14268954

Replacement of Ablators with Phase-Change Material for Thermal Protection of STS Elements

NASA Technical Reports Server (NTRS)

Kaul, Raj K.; Stuckey, Irvin; Munafo, Paul M. (Technical Monitor)

2002-01-01

As part of the research and development program to develop new Thermal Protection System (TPS) materials for aerospace applications at NASA's Marshall Space Flight Center (MSFC), an experimental study was conducted on a new concept for a non-ablative TPS material. Potential loss of TPS material and ablation by-products from the External Tank (ET) or Solid Rocket Booster (SRB) during Shuttle flight with the related Orbiter tile damage necessitates development of a non-ablative thermal protection system. The new Thermal Management Coating (TMC) consists of phase-change material encapsulated in micro spheres and a two-part resin system to adhere the coating to the structure material. The TMC uses a phase-change material to dissipate the heat produced during supersonic flight rather than an ablative material. This new material absorbs energy as it goes through a phase change during the heating portion of the flight profile and then the energy is slowly released as the phase-change material cools and returns to its solid state inside the micro spheres. The coating was subjected to different test conditions simulating design flight environments at the NASA/MSFC Improved Hot Gas Facility (IHGF) to study its performance.

Experimental Investigation of the Viscosity of Iron-rich Silicate Melts under Pressure

NASA Astrophysics Data System (ADS)

Edwards, P. M.; Lesher, C. E.; Pommier, A.; O'Dwyer Brown, L.

2017-12-01

The transport properties of silicate melts govern diffusive flow of momentum, heat, and mass in the interior of terrestrial planets. In particular, constraining melt viscosity is critical for dynamic modeling of igneous processes and is thus key to our understanding of magma convection and mixing, melt migration in the mantle, and crystal-liquid fractionation. Among the different constituents of silicate melts, iron is of significant importance as it highly influences some of their properties, such as surface tension, compressibility, and density. We present an experimental study of the viscosity of natural and synthetic iron-rich silicate melts under pressure. In situ falling-sphere measurements of viscosity have been conducted on hedenbergite (CaFeSi2O6) and iron-rich peridotite melts from 1 to 7 GPa and at temperatures between 1750 and 2100 K, using the multi-anvil apparatus at the GSECARS beamline at the Advanced Photon Source, Argonne National Lab. We used double reservoir capsules, with the bottom reservoir containing the sample, while a more refractory material is placed in the upper reservoir (e.g., diopside, enstatite, forsterite). This configuration allows the fall of two rhenium spheres across the sample at different temperatures. Melt viscosity is calculated using Stokes' law and the terminal velocity of the spheres. We observe that melt viscosity slightly decreases with increasing temperature and increasing pressure: for instance, the viscosity of the hedenbergite melt decreases from 1.26 Pa•s to 0.43 Pa•s over the 1 - 3.5 GPa pressure range and between 1820 and 1930 K. Our experimental data are used to develop a viscosity model of iron-rich silicate melts under pressure. Results will be compared with previous viscosity works on iron-free and iron-bearing silicate liquids in order to discuss the effect of iron on melt viscosity and structure at pressure and temperature conditions relevant to terrestrial mantles.

Rocket and laboratory studies in astronomy

NASA Technical Reports Server (NTRS)

Feldman, P. D.

1993-01-01

This report covers the period from September 1, 1992 to August 31, 1993. During the reporting period we launched the Faint Object Telescope to measure absolute fluxes of two hot dwarf stars in the spectral range below 1200 A. Although all systems worked normally, a higher than anticipated pressure in the detector led to ion-feedback that masked the useable data from the source. We have identified the source of the problem and are preparing for a reflight in the Fall of 1993. Our laboratory program for the evaluation of the ultraviolet performance of charge-coupled-detector (CCD) arrays continued with the aim of including a UV-sensitive CCD in a payload to be flown in 1994, and we have begun the assembly of this payload. Work has continued on the analysis of data from previous rocket experiments and from the UVX experiment which flew on STS-61C in January 1986.

KSC-2011-1457

NASA Image and Video Library

2011-02-15

VANDENBERG AIR FORCE BASE, Calif. -- On Space Launch Complex 576-E at Vandenberg Air Force Base in California, Orbital Sciences workers prepare NASA's Glory upper stack for attachment to the Taurus XL rocket's Stage 0. The upper stack consists of Stages 1, 2 and 3 of the Taurus as well as the encapsulated Glory spacecraft. Workers put the non-flight environmental shield over the fairing prior to assembly. A portion of the umbilical tower is attached to the upper stack which falls away from the spacecraft during liftoff. The Orbital Sciences Taurus XL rocket will launch Glory into low Earth orbit. Once Glory reaches orbit, it will collect data on the properties of aerosols and black carbon. It also will help scientists understand how the sun's irradiance affects Earth's climate. Launch is scheduled for 5:09 a.m. EST Feb. 23. For information, visit www.nasa.gov/glory. Photo credit: NASA/Randy Beaudoin, VAFB

KSC-2011-6091

NASA Image and Video Library

2011-08-03

CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, cleanup of Launch Pad 39B is in progress beside the pad's flame trench. The trench is 450 feet long, 58 feet wide and 42 feet deep with an inner inverted V-shaped steel flame deflector. Sand, reinforcing steel and large wooden mats were placed over the pad's concrete surfaces during deconstruction to protect them from falling debris. In the distance is the 525-foot-tall Vehicle Assembly Building. In 2009, the structure at the pad was no longer needed for NASA's Space Shuttle Program, so it is being restructured for future use. The new design will feature a "clean pad" for rockets to come with their own launcher, making it more versatile for a number of rockets and spacecraft. The lightning protection system, consisting of three lightning towers and a wire catenary system, will remain. For information on NASA's future plans, visit http://www.nasa.gov/exploration. Photo credit: NASA/Kim Shiflett

KSC-2011-6090

NASA Image and Video Library

2011-08-03

CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, cleanup of Launch Pad 39B is in progress beside the pad's flame trench. The trench is 450 feet long, 58 feet wide and 42 feet deep with an inner inverted V-shaped steel flame deflector. Sand, reinforcing steel and large wooden mats were placed over the pad's concrete surfaces during deconstruction to protect them from falling debris. In 2009, the structure at the pad was no longer needed for NASA's Space Shuttle Program, so it is being restructured for future use. The new design will feature a "clean pad" for rockets to come with their own launcher, making it more versatile for a number of rockets and spacecraft. The lightning protection system, consisting of three lightning towers and a wire catenary system, will remain. For information on NASA's future plans, visit http://www.nasa.gov/exploration. Photo credit: NASA/Kim Shiflett

KSC-2011-6088

NASA Image and Video Library

2011-08-03

CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, cleanup of Launch Pad 39B is in progress beside the pad's flame trench. The trench is 450 feet long, 58 feet wide and 42 feet deep with an inner inverted V-shaped steel flame deflector. Sand, reinforcing steel and large wooden mats were placed over the pad's concrete surfaces during deconstruction to protect them from falling debris. In the distance is the 525-foot-tall Vehicle Assembly Building. In 2009, the structure at the pad was no longer needed for NASA's Space Shuttle Program, so it is being restructured for future use. The new design will feature a "clean pad" for rockets to come with their own launcher, making it more versatile for a number of rockets and spacecraft. The lightning protection system, consisting of three lightning towers and a wire catenary system, will remain. For information on NASA's future plans, visit http://www.nasa.gov/exploration. Photo credit: NASA/Kim Shiflett

KSC-2011-6089

NASA Image and Video Library

2011-08-03

CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, cleanup of Launch Pad 39B is in progress beside the pad's flame trench. The trench is 450 feet long, 58 feet wide and 42 feet deep with an inner inverted V-shaped steel flame deflector. Sand, reinforcing steel and large wooden mats were placed over the pad's concrete surfaces during deconstruction to protect them from falling debris. In the distance is the 525-foot-tall Vehicle Assembly Building. In 2009, the structure at the pad was no longer needed for NASA's Space Shuttle Program, so it is being restructured for future use. The new design will feature a "clean pad" for rockets to come with their own launcher, making it more versatile for a number of rockets and spacecraft. The lightning protection system, consisting of three lightning towers and a wire catenary system, will remain. For information on NASA's future plans, visit http://www.nasa.gov/exploration. Photo credit: NASA/Kim Shiflett

Plasma properties of hot coronal loops utilizing coordinated SMM and solar research rocket observations

NASA Technical Reports Server (NTRS)

Moses, J. Daniel

1989-01-01

Three improvements in photographic x-ray imaging techniques for solar astronomy are presented. The testing and calibration of a new film processor was conducted; the resulting product will allow photometric development of sounding rocket flight film immediately upon recovery at the missile range. Two fine grained photographic films were calibrated and flight tested to provide alternative detector choices when the need for high resolution is greater than the need for high sensitivity. An analysis technique used to obtain the characteristic curve directly from photographs of UV solar spectra were applied to the analysis of soft x-ray photographic images. The resulting procedure provides a more complete and straightforward determination of the parameters describing the x-ray characteristic curve than previous techniques. These improvements fall into the category of refinements instead of revolutions, indicating the fundamental suitability of the photographic process for x-ray imaging in solar astronomy.

Monitoring Direct Effects of Delta, Atlas, and Titan Launches from Cape Canaveral Air Station

NASA Technical Reports Server (NTRS)

Schmalzer, Paul A.; Boyle, Shannon R.; Hall, Patrice; Oddy, Donna M.; Hensley, Melissa A.; Stolen, Eric D.; Duncan, Brean W.

1998-01-01

Launches of Delta, Atlas, and Titan rockets from Cape Canaveral Air Station (CCAS) have potential environmental effects that could arise from direct impacts of the launch exhaust (e.g., blast, heat), deposition of exhaust products of the solid rocket motors (hydrogen chloride, aluminum oxide), or other effects such as noise. Here we: 1) review previous reports, environmental assessments, and environmental impact statements for Delta, Atlas, and Titan vehicles and pad areas to clarity the magnitude of potential impacts; 2) summarize observed effects of 15 Delta, 22 Atlas, and 8 Titan launches; and 3) develop a spatial database of the distribution of effects from individual launches and cumulative effects of launches. The review of previous studies indicated that impacts from these launches can occur from the launch exhaust heat, deposition of exhaust products from the solid rocket motors, and noise. The principal effluents from solid rocket motors are hydrogen chloride (HCl), aluminum oxide (Al2O3), water (H2O), hydrogen (H2), carbon monoxide (CO), and carbon dioxide (CO2). The exhaust plume interacts with the launch complex structure and water deluge system to generate a launch cloud. Fall out or rain out of material from this cloud can produce localized effects from acid or particulate deposition. Delta, Atlas, and Titan launch vehicles differ in the number and size of solid rocket boosters and in the amount of deluge water used. All are smaller and use less water than the Space Shuttle. Acid deposition can cause damage to plants and animals exposed to it, acidify surface water and soil, and cause long-term changes to community composition and structure from repeated exposure. The magnitude of these effects depends on the intensity and frequency of acid deposition.

Numerical and experimental capabilities for studying rocket plume-regolith interactions

NASA Astrophysics Data System (ADS)

White, C.; Scanlon, T. J.; Merrifield, J. A.; Kontis, K.; Langener, T.; Alves, J.

2016-11-01

Soft landings on extra-terrestrial airless bodies will be required for future sample return missions, such as the Phobos Sample Return (PhSR). PhSR is a candidate mission of ESA's Mars Robotic Exploration Preparation (MREP-2) Programme. Its main objective is to acquire and return a sample from the Martian moon Phobos, after a scientific characterisation phase of the moon and of the landing site. If a rocket is used to slow down the spacecraft to a vertical descent velocity that it will be able to free-fall from, care has to be taken to ensure that the rocket exhaust does not contaminate the surface regolith that is to be collected, and that the rocket does not cause unacceptable levels of erosion to the surface, which could jeopardise the mission. In addition to the work being done in the scope of PhSR, the European Space Agency is funding an experimental facility for investigating these nozzle expansion problems; the current progress of this is described. To support this work, an uncoupled hybrid computational fluid dynamics-direct simulation Monte Carlo method is developed and used to simulate the exhaust of a mono-propellant rocket above the surface of an airless body. The pressure, shear stress, and heat flux at the surface are compared to an analytical free-molecul solution to determine the altitude above which the free-molecular solution is suffcient for predicting these properties. The pressures match well as low as 15 m above the surface, but the heat flux and shear stress are not in agreement until an altitude of 40 m. A new adsorption/desorption boundary condition for the direct simulation Monte Carlo code has also been developed for future use in in-depth contamination studies.

High Power Dye Lasers

DTIC Science & Technology

1975-09-30

sphere is greatly reduced when compared to the axial flow dye cell. This is because the focusing optics can only direct light from a limited angle into...Distribution in Flashlamp . . . „ [ [ TTIH Flashlamp Cooling and Thermal Limits [ [ [ ii~ik Optical Characteristics ’,,: •*••••••••••• il-ib...Tracing Program e Dye Pumping System Laser Tests ! 1 i * * TTT’I Laser Output Fall Off !!!.’!!!" ’ TTT’H Single Shot Optical Distortion TTT’I

Russian Meteorological and Geophysical Rockets of New Generation

NASA Astrophysics Data System (ADS)

Yushkov, V.; Gvozdev, Yu.; Lykov, A.; Shershakov, V.; Ivanov, V.; Pozin, A.; Afanasenkov, A.; Savenkov, Yu.; Kuznetsov, V.

2015-09-01

To study the process in the middle and upper atmosphere, ionosphere and near-Earth space, as well as to monitor the geophysical environment in Russian Federal Service for Hydrology and Environmental Monitoring (ROSHYDROMET) the development of new generation of meteorological and geophysical rockets has been completed. The modern geophysical research rocket system MR-30 was created in Research and Production Association RPA "Typhoon". The basis of the complex MR-30 is a new geophysical sounding rocket MN-300 with solid propellant, Rocket launch takes place at an angle of 70º to 90º from the launcher, which is a farm with a guide rail type required for imparting initial rotation rocket. The Rocket is spin stabilized with a spin rate between 5 and 7 Hz. Launch weight is 1564 kg, and the mass of the payload of 50 to 150 kg. MR-300 is capable of lifting up to 300 km, while the area of dispersion points for booster falling is an ellipse with parameters 37x 60 km. The payload of the rocket MN-300 consists of two sections: a sealed, located below the instrument compartment, and not sealed, under the fairing. Block of scientific equipment is formed on the platform in a modular layout. This makes it possible to solve a wide range of tasks and conduct research and testing technologies using a unique environment of space, as well as to conduct technological experiments testing and research systems and spacecraft equipment. New Russian rocket system MERA (MEteorological Rocket for Atmospheric Research) belongs to so called "dart" technique that provide lifting of small scientific payload up to altitude 100 km and descending with parachute. It was developed at Central Aerological Observatory jointly with State Unitary Enterprise Instrument Design Bureau. The booster provides a very rapid acceleration to about Mach 5. After the burning phase of the buster the dart is separated and continues ballistic flight for about 2 minutes. The dart carries the instrument payload+ parachute and an ejection charge, but does not include additional propellant. Time to apogee is 151 seconds. Launch weight is 67 kg. Payload is 54 mm dia. x 400 mm long with max payload weight 2-3 kg. Initial acceleration (vertical): 200g's (up). GPS/GLONASS position system with be used for tracking the payload. 30 channel telemetry system will provide data transition. Temperature, pressure, wind, electron density will be measured during the ascent (from 60 km) and descent lags as a basic atmospheric parameters. Portable rocket system MERA can be widely used in the frame of international collaboration. The main technical specifications of MERA and MN-300 are described and results of test flights are presented.

Project Summaries, 1989 - 1990

NASA Technical Reports Server (NTRS)

1990-01-01

Student designs summarized here include two undergraduate space designs and five graduate space designs from fall 1989, plus four undergraduate space designs and four undergraduate aircraft designs from spring 1990. Progress in a number of programs is described. The Geostationary Satellite Servicing Facility, the Lunar Farside Observatory and Science Base, the Texas Educational Satellite, an asteroid rendezvous vehicle, a Titan probe, a subsystems commonality assessment for lunar/Mars landers, a nuclear-thermal rocket propelled Earth-Mars vehicle, and a comprehensive orbital debris management program are among the topics discussed.

Cryo Tank Fill at Pad 39B

NASA Image and Video Library

2017-09-26

Praxair trucks carrying their loads of liquid oxygen, or LO2, are on their way to Launch Pad 39B at NASA's Kennedy Space Center in Florida. The trucks will offload LO2 slowly into a giant storage sphere located at the northwest corner of the pad to gradually chill it down from normal temperature to about negative 298 degrees Fahrenheit, during the first major integrated operation to prepare for the launch of the agency's Orion spacecraft atop the Space Launch System (SLS) rocket. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to pad B to support the launch of the SLS and Orion spacecraft for Exploration Mission-1, deep space missions and NASA’s journey to Mars.

Cryo Tank Fill at Pad 39B

NASA Image and Video Library

2017-09-26

One of several Praxair trucks carrying its load of liquid oxygen, or LO2, is in route to Launch Pad 39B at NASA's Kennedy Space Center in Florida. The truck will offload LO2 slowly into a giant storage sphere located at the northwest corner of the pad to gradually chill it down from normal temperature to about negative 298 degrees Fahrenheit, during the first major integrated operation to prepare for the launch of the agency's Orion spacecraft atop the Space Launch System (SLS) rocket. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to pad B to support the launch of the SLS and Orion spacecraft for Exploration Mission-1, deep space missions and NASA’s journey to Mars.

Cryo Tank Fill at Pad 39B

NASA Image and Video Library

2017-09-26

Several Praxair trucks carrying their loads of liquid oxygen, or LO2, have arrived at Launch Pad 39B at NASA's Kennedy Space Center in Florida. The trucks will offload LO2 slowly into a giant storage sphere located at the northwest corner of the pad to gradually chill it down from normal temperature to about negative 298 degrees Fahrenheit, during the first major integrated operation to prepare for the launch of the agency's Orion spacecraft atop the Space Launch System (SLS) rocket. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to pad B to support the launch of the SLS and Orion spacecraft for Exploration Mission-1, deep space missions and NASA’s journey to Mars.

Experimental study of oblique impact between dry spheres and liquid layers

NASA Astrophysics Data System (ADS)

Ma, Jiliang; Liu, Daoyin; Chen, Xiaoping

2013-09-01

Liquid addition is common in industrial fluidization-based processes. A detailed understanding of collision mechanics of particles with liquid layers is helpful to optimize these processes. The normal impact with liquid has been studied extensively; however, the studies on oblique impact with liquid are scarce. In this work, experiments are conducted to trace Al2O3 spheres obliquely impacting on a surface covered by liquid layers, in which the free-fall spheres are disturbed initially by a horizontal gas flow. The oblique impact exhibits different rebound behaviors from normal collision due to the occurrence of strong rotation. The normal and tangential restitution coefficients (en and et) and liquid bridge rupture time (trup) are analyzed. With increase in liquid layer thickness and viscosity, en and et decline, and trup increases. With increase in tangential velocity, et decreases first and then increases, whereas en remains nearly unchanged, and trup decreases constantly. A modified Stokes number is proposed to further explore the relation between restitution coefficients and the impact parameters. Finally, an analysis of energy dissipation shows that the contact deformation and liquid phase are the two main sources of total energy dissipation. Unexpectedly, the dissipative energy caused by the liquid phase is independent of tangential velocity.

KSC-02pd2057

NASA Image and Video Library

2002-10-25

KENNEDY SPACE CENTER, FLA. - At NASA's Space Launch Complex 2 (SLC-2), Vandenberg Air Force Base, Calif., the launch tower has been rolled back to reveal a Delta II rocket with its solid rocket boosters attached. The rocket will carry the ICESat and CHIPSat satellites into Earth orbits. The Ice, Cloud, and Land Elevation Satellite, or ICESat, is a 661-pound satellite known as Geoscience Laser Altimeter System (GLAS) that will revolutionize our understanding of ice and its role in global climate change and how we protect and understand our home planet. It will help scientists determine if the global sea level is rising or falling. It will look at the ice sheets that blanket the Earth's poles to see if they are growing or shrinking. It will assist in developing an understanding of how changes in the Earth's atmosphere and climate effect polar ice masses and global sea level. The Cosmic Hot Interstellar Plasma Spectrometer, or CHIPSat, a suitcase-size 131-pound satellite, will provide invaluable information into the origin, physical processes and properties of the hot gas contained in the interstellar medium. This can provide important clues about the formation and evolution of galaxies since the interstellar medium literally contains the seeds of future stars. The Delta II launch is scheduled for Jan. 11, 2003, between 4:45 p.m. - 5:30 p.m. PST.

KSC-02pd2049

NASA Image and Video Library

2002-10-24

KENNEDY SPACE CENTER, FLA. - On the launch tower on NASA's Space Launch Complex 2 (SLC-2), Vandenberg Air Force Base, Calif., a solid rocket booster is lifted into an upright position beside the Delta II rocket to which it will be attached. The rocket will carry the ICESat and CHIPSat satellites into Earth orbits. ICESat is a 661-pound satellite known as Geoscience Laser Altimeter System (GLAS) that will revolutionize our understanding of ice and its role in global climate change and how we protect and understand our home planet. It will help scientists determine if the global sea level is rising or falling. It will look at the ice sheets that blanket the Earth's poles to see if they are growing or shrinking. It will assist in developing an understanding of how changes in the Earth's atmosphere and climate effect polar ice masses and global sea level. CHIPSat, a suitcase-size 131-pound satellite, will provide invaluable information into the origin, physical processes and properties of the hot gas contained in the interstellar medium. This can provide important clues about the formation and evolution of galaxies since the interstellar medium literally contains the seeds of future stars. The Delta II launch is scheduled for Jan. 11 between 4:45 p.m. - 5:30 p.m. PST.

KSC-02pd2048

NASA Image and Video Library

2002-10-24

KENNEDY SPACE CENTER, FLA. - On the launch tower on NASA's Space Launch Complex 2 (SLC-2), Vandenberg Air Force Base, Calif., a solid rocket booster is lifted into an upright position as preparations continue to mate it to a Delta II rocket. The rocket will carry the ICESat and CHIPSat satellites into Earth orbits. ICESat is a 661-pound satellite known as Geoscience Laser Altimeter System (GLAS) that will revolutionize our understanding of ice and its role in global climate change and how we protect and understand our home planet. It will help scientists determine if the global sea level is rising or falling. It will look at the ice sheets that blanket the Earth's poles to see if they are growing or shrinking. It will assist in developing an understanding of how changes in the Earth's atmosphere and climate effect polar ice masses and global sea level. CHIPSat, a suitcase-size 131-pound satellite, will provide invaluable information into the origin, physical processes and properties of the hot gas contained in the interstellar medium. This can provide important clues about the formation and evolution of galaxies since the interstellar medium literally contains the seeds of future stars. The Delta II launch is scheduled for Jan. 11 between 4:45 p.m. - 5:30 p.m. PST.

KSC-02pd2047

NASA Image and Video Library

2002-10-24

KENNEDY SPACE CENTER, FLA. - On the launch tower on NASA's Space Launch Complex 2 (SLC-2), Vandenberg Air Force Base, Calif., a solid rocket booster is lifted into an upright position for mating to a Delta II rocket. The rocket will carry the ICESat and CHIPSat satellites into Earth orbits. ICESat is a 661-pound satellite known as Geoscience Laser Altimeter System (GLAS) that will revolutionize our understanding of ice and its role in global climate change and how we protect and understand our home planet. It will help scientists determine if the global sea level is rising or falling. It will look at the ice sheets that blanket the Earth's poles to see if they are growing or shrinking. It will assist in developing an understanding of how changes in the Earth's atmosphere and climate effect polar ice masses and global sea level. CHIPSat, a suitcase-size 131-pound satellite, will provide invaluable information into the origin, physical processes and properties of the hot gas contained in the interstellar medium. This can provide important clues about the formation and evolution of galaxies since the interstellar medium literally contains the seeds of future stars. The Delta II launch is scheduled for Jan. 11 between 4:45 p.m. - 5:30 p.m. PST.

Gravity Modeling for Variable Fidelity Environments

NASA Technical Reports Server (NTRS)

Madden, Michael M.

2006-01-01

Aerospace simulations can model worlds, such as the Earth, with differing levels of fidelity. The simulation may represent the world as a plane, a sphere, an ellipsoid, or a high-order closed surface. The world may or may not rotate. The user may select lower fidelity models based on computational limits, a need for simplified analysis, or comparison to other data. However, the user will also wish to retain a close semblance of behavior to the real world. The effects of gravity on objects are an important component of modeling real-world behavior. Engineers generally equate the term gravity with the observed free-fall acceleration. However, free-fall acceleration is not equal to all observers. To observers on the sur-face of a rotating world, free-fall acceleration is the sum of gravitational attraction and the centrifugal acceleration due to the world's rotation. On the other hand, free-fall acceleration equals gravitational attraction to an observer in inertial space. Surface-observed simulations (e.g. aircraft), which use non-rotating world models, may choose to model observed free fall acceleration as the gravity term; such a model actually combines gravitational at-traction with centrifugal acceleration due to the Earth s rotation. However, this modeling choice invites confusion as one evolves the simulation to higher fidelity world models or adds inertial observers. Care must be taken to model gravity in concert with the world model to avoid denigrating the fidelity of modeling observed free fall. The paper will go into greater depth on gravity modeling and the physical disparities and synergies that arise when coupling specific gravity models with world models.

THE FREE-FALL TIME OF FINITE SHEETS AND FILAMENTS

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

Toala, Jesus A.; Vazquez-Semadeni, Enrique; Gomez, Gilberto C.

2012-01-10

Molecular clouds often exhibit filamentary or sheet-like shapes. We compute the free-fall time ({tau}{sub ff}) for finite, uniform, self-gravitating circular sheets and filamentary clouds of small but finite thickness, so that their volume density {rho} can still be defined. We find that, for thin sheets, the free-fall time is larger than that of a uniform sphere with the same volume density by a factor proportional to {radical}A, where the aspect ratio A is given by A = R/h, R being the sheet's radius and h is its thickness. For filamentary clouds, the aspect ratio is defined as A=L/R, where Lmore » is the filament's half-length and R is its (small) radius, and the modification factor is more complicated, although in the limit of large A it again reduces to nearly {radical}A. We propose that our result for filamentary shapes naturally explains the ubiquitous configuration of clumps fed by filaments observed in the densest structures of molecular clouds. Also, the longer free-fall times for non-spherical geometries in general may contribute toward partially alleviating the 'star formation conundrum', namely, the star formation rate in the Galaxy appears to be proceeding in a timescale much larger than the total molecular mass in the Galaxy divided by its typical free-fall time. If molecular clouds are in general formed by thin sheets and long filaments, then their relevant free-fall time may have been systematically underestimated, possibly by factors of up to one order of magnitude.« less

Standard Reference Material (SRM 1990) for Single Crystal Diffractometer Alignment

USGS Publications Warehouse

Wong-Ng, W.; Siegrist, T.; DeTitta, G.T.; Finger, L.W.; Evans, H.T.; Gabe, E.J.; Enright, G.D.; Armstrong, J.T.; Levenson, M.; Cook, L.P.; Hubbard, C.R.

2001-01-01

An international project was successfully completed which involved two major undertakings: (1) a round-robin to demonstrate the viability of the selected standard and (2) the certification of the lattice parameters of the SRM 1990, a Standard Reference Material?? for single crystal diffractometer alignment. This SRM is a set of ???3500 units of Cr-doped Al2O3, or ruby spheres [(0 420.011 mole fraction % Cr (expanded uncertainty)]. The round-robin consisted of determination of lattice parameters of a pair of crystals' the ruby sphere as a standard, and a zeolite reference to serve as an unknown. Fifty pairs of crystals were dispatched from Hauptman-Woodward Medical Research Institute to volunteers in x-ray laboratories world-wide. A total of 45 sets of data was received from 32 laboratories. The mean unit cell parameters of the ruby spheres was found to be a=4.7608 A?? ?? 0.0062 A??, and c=12.9979 A?? ?? 0.020 A?? (95 % intervals of the laboratory means). The source of errors of outlier data was identified. The SRM project involved the certification of lattice parameters using four well-aligned single crystal diffractometers at (Bell Laboratories) Lucent Technologies and at NRC of Canada (39 ruby spheres), the quantification of the Cr content using a combined microprobe and SEM/EDS technique, and the evaluation of the mosaicity of the ruby spheres using a double-crystal spectrometry method. A confirmation of the lattice parameters was also conducted using a Guinier-Ha??gg camera. Systematic corrections of thermal expansion and refraction corrections were applied. These rubies_ are rhombohedral, with space group R3c. The certified mean unit cell parameters are a=4.76080 ?? 0.00029 A??, and c=12 99568 A?? ?? 0.00087 A?? (expanded uncertainty). These certified lattice parameters fall well within the results of those obtained from the international round-robin study. The Guinier-Ha??gg transmission measurements on five samples of powdered rubies (a=4.7610 A?? ?? 0.0013 A??, and c=12.9954 A?? ?? 0.0034 A??) agreed well with the values obtained from the single crystal spheres.

Standard Reference Material (SRM 1990) For Single Crystal Diffractometer Alignment

PubMed Central

Wong-Ng, W.; Siegrist, T.; DeTitta, G. T.; Finger, L. W.; Evans, H. T.; Gabe, E. J.; Enright, G. D.; Armstrong, J. T.; Levenson, M.; Cook, L. P.; Hubbard, C. R.

2001-01-01

An international project was successfully completed which involved two major undertakings: (1) a round-robin to demonstrate the viability of the selected standard and (2) the certification of the lattice parameters of the SRM 1990, a Standard Reference Material® for single crystal diffractometer alignment. This SRM is a set of ≈3500 units of Cr-doped Al2O3, or ruby spheres [(0.420.011 mole fraction % Cr (expanded uncertainty)]. The round-robin consisted of determination of lattice parameters of a pair of crystals: the ruby sphere as a standard, and a zeolite reference to serve as an unknown. Fifty pairs of crystals were dispatched from Hauptman-Woodward Medical Research Institute to volunteers in x-ray laboratories world-wide. A total of 45 sets of data was received from 32 laboratories. The mean unit cell parameters of the ruby spheres was found to be a=4.7608 ű0.0062 Å, and c=12.9979 ű0.020 Å (95 % intervals of the laboratory means). The source of errors of outlier data was identified. The SRM project involved the certification of lattice parameters using four well-aligned single crystal diffractometers at (Bell Laboratories) Lucent Technologies and at NRC of Canada (39 ruby spheres), the quantification of the Cr content using a combined microprobe and SEM/EDS technique, and the evaluation of the mosaicity of the ruby spheres using a double-crystal spectrometry method. A confirmation of the lattice parameters was also conducted using a Guinier-Hägg camera. Systematic corrections of thermal expansion and refraction corrections were applied. These rubies– are rhombohedral, with space group R3¯c. The certified mean unit cell parameters are a=4.76080±0.00029 Å, and c=12.99568 ű0.00087 Å (expanded uncertainty). These certified lattice parameters fall well within the results of those obtained from the international round-robin study. The Guinier-Hägg transmission measurements on five samples of powdered rubies (a=4.7610 ű0.0013 Å, and c = 12.9954 ű0.0034 Å) agreed well with the values obtained from the single crystal spheres. PMID:27500067

Hydrometeor Size Distribution Measurements by Imaging the Attenuation of a Laser Spot

NASA Technical Reports Server (NTRS)

Lane, John

2013-01-01

The optical extinction of a laser due to scattering of particles is a well-known phenomenon. In a laboratory environment, this physical principle is known as the Beer-Lambert law, and is often used to measure the concentration of scattering particles in a fluid or gas. This method has been experimentally shown to be a usable means to measure the dust density from a rocket plume interaction with the lunar surface. Using the same principles and experimental arrangement, this technique can be applied to hydrometeor size distributions, and for launch-pad operations, specifically as a passive hail detection and measurement system. Calibration of a hail monitoring system is a difficult process. In the past, it has required comparison to another means of measuring hydrometeor size and density. Using a technique recently developed for estimating the density of surface dust dispersed during a rocket landing, measuring the extinction of a laser passing through hail (or dust in the rocket case) yields an estimate of the second moment of the particle cloud, and hydrometeor size distribution in the terrestrial meteorological case. With the exception of disdrometers, instruments that measure rain and hail fall make indirect measurements of the drop-size distribution. Instruments that scatter microwaves off of hydrometeors, such as the WSR-88D (Weather Surveillance Radar 88 Doppler), vertical wind profilers, and microwave disdrometers, measure the sixth moment of the drop size distribution (DSD). By projecting a laser onto a target, changes in brightness of the laser spot against the target background during rain and hail yield a measurement of the DSD's second moment by way of the Beer-Lambert law. In order to detect the laser attenuation within the 8-bit resolution of most camera image arrays, a minimum path length is required. Depending on the intensity of the hail fall rate for moderate to heavy rainfall, a laser path length of 100 m is sufficient to measure variations in optical extinction using a digital camera. For hail fall only, the laser path may be shorter because of greater scattering due to the properties of hailstones versus raindrops. A photodetector may replace the camera in automated installations. Laser-based rain and hail measurement systems are available, but they are based on measuring the interruption of a thin laser beam, thus counting individual hydrometeors. These systems are true disdrometers since they also measure size and velocity. The method reported here is a simple method, requiring far less processing, but it is not a disdrometer.

On the reduction of splash-back

NASA Astrophysics Data System (ADS)

Dickerson, Andrew; Stephen, Jeremy

2017-11-01

The reduction of splash height following the impact of a solid body on a liquid surface is relevant to multiple sectors including military missile entry, industrial processing, and visits to public restrooms. While most studies have viewed splashes in the context of control of impactor shape and surface properties, we here consider the effects of splash height following modification of a liquid surface by surfactants and thin fabrics. Smooth, hydrophilic, free-falling spheres are allowed to impact a quiescent liquid surface of modified surface conditions while filmed with a high-speed camera. We measure splash heights and cavity depths formed by impacting spheres across Froude numbers 3 - 6.5. As expected, lowering the surface tension of the liquid increased splash height with respect to pure water. The introduction of fabric to the surface has an more unpredictable effect. With respect to unaltered impact conditions, ample inclusion of fabric on the surface reduces splash height, while a meager amount of fabric amplifies splashing due to the augmentation of cavity formation preceding a Worthington jet.

NASA Engineer and Technician Instrument Zero Gravity Spheres

NASA Image and Video Library

1961-08-21

An engineer and technician at the National Aeronautics and Space Administration (NASA) Lewis Research Center install the instrumentation on spherical fuel tanks for an investigation of the behavior of liquids in microgravity. Lewis researchers were undertaking a broad effort to study the heat transfer properties of high energy propellants such as liquid hydrogen in microgravity. In the center’s 2.2-Second Drop Tower they investigated the wetting characteristics of liquid and the liquid-vapor configurations, and predicted the equilibrium state in microgravity conditions. Lewis was also conducting a series microgravity investigations which launched 9-inch diameter spherical dewars, seen here, on an Aerobee sounding rocket. A camera inside the rocket filmed the liquid hydrogen’s behavior during its 4 to 7 minutes of freefall. The researchers concluded, however, that they needed to extend the weightlessness period to obtain better results. So they designed an experiment to be launched on an Atlas missile that would provide 21 minutes of weightlessness. The experiment was flight qualified at Lewis. The 36-percent full liquid hydrogen stainless steel dewar was launched on the Atlas on February 25, 1964. The instrumentation measured temperature, pressure, vacuum, and liquid level. Temperature instrumentation indicated wall drying during the freefall. The resultant pressure-rise characteristics were similar to those used for the normal-gravity test.

Filament wound data base development, revision 1

NASA Technical Reports Server (NTRS)

Sharp, R. Scott; Braddock, William F.

1985-01-01

The objective was to update the present Space Shuttle Solid Rocket Booster (SRB) baseline reentry aerodynamic data base and to develop a new reentry data base for the filament wound case SRB along with individual protuberance increments. Lockheed's procedures for performing these tasks are discussed. Free fall of the SRBs after separation from the Space Shuttle Launch Vehicle is completely uncontrolled. However, the SRBs must decelerate to a velocity and attitude that is suitable for parachute deployment. To determine the SRB reentry trajectory parameters, including the rate of deceleration and attitude history during free-fall, engineers at Marshall Space Flight Center are using a six-degree-of-freedom computer program to predict dynamic behavior. Static stability aerodynamic coefficients are part of the information required for input into this computer program. Lockheed analyzed the existing reentry aerodynamic data tape (Data Tape 5) for the current steel case SRB. This analysis resulted in the development of Data Tape 7.

Microinstabilities in the Gasdynamic Mirror Propulsion System

NASA Technical Reports Server (NTRS)

Emrich, William

2005-01-01

The gasdynamic mirror has been proposed as a concept which could form the basis of a highly efficient fusion rocket engine. Gasdynamic mirrors differ from most other mirror type plasma confinement schemes in that they have much larger aspect ratios and operate at somewhat higher plasma densities. There are several types of instabilities which are known to plague mirror type confinement schemes. These instabilities fall into two general classes. One class of instability is the Magnetohydrodynamic or MHD instability which induces gross distortions in the plasma geometry. The other class of instability is the "loss cone" microinstability which leads to general plasma turbulence. The "loss cone" microinstability is caused by velocity space asymmetries resulting from the loss of plasma having constituent particle velocities within the angle of the magnetic mirror "loss cone." These instabilities generally manifest themselves in high temperature, moderately dense plasmas. The present study indicates that a GDM configured as a rocket engine might operate in a plasma regime where microinstabilities could potentially be significant.

Microinstabilities in the Gasdynamic Mirror Propulsion System

NASA Technical Reports Server (NTRS)

Emrich, William

2005-01-01

The gasdynamic mirror has been proposed as a concept which could form the basis of a highly efficient fusion rocket engine. Gasdynamic mirrors differ from most other mirror type plasma confinement schemes in that they have much larger aspect ratios and operate at somewhat higher plasma densities. There are several types of instabilities which are known to plague mirror type confinement schemes. These instabilities fall into two general classes. One class of instability is the Magnetohdrodynamic or MHD instability which induces gross distortions in the plasma geometry. The other class of instability is the "loss cone" microinstability which leads to general plasma turbulence. The "loss cone" microinstability is caused by velocity space asymmetries resulting from the loss of plasma having constituent particle velocities within the angle of the magnetic mirror "loss cone." These instabilities generally manifest themselves in high temperature, moderately dense plasmas. The present study indicates that a GDM configured as a rocket engine might operate in a plasma regine where microinstabilities could potentially be significant.

KSC-03pd0069

NASA Image and Video Library

2003-01-12

VANDENBERG AFB, Calif. -- A Boeing Delta II rocket soars above the clouds here today at Vandenberg AFB, Calif. The NASA payloads aboard the rocket are the ICESat, an Ice Cloud and land Elevation Satellite, and CHIPSat, a Cosmic Hot Interstellar Plasma Spectrometer. ICESat, a 661-pound satellite, is a benchmark satellite for the Earth Observing System that will help scientists determine if the global sea level is rising or falling. It will observe the ice sheets that blanket the Earth’s poles to determine if they are growing or shrinking. It will assist in developing an understanding of how changes in the Earth’s atmosphere and climate affect polar ice masses and global sea level. The Geoscience Laser Altimeter System is the sole instrument on the satellite. CHIPSat, a suitcase-size 131-pound satellite, will provide information about the origin, physical processes and properties of the hot gas contained in the interstellar medium. This launch marks the first Delta from Vandenberg this year. (USAF photo by: SSgt. Lee A Osberry Jr.)

KSC-03pd0068

NASA Image and Video Library

2003-01-12

VANDENBERG AFB, Calif. -- A Boeing Delta II rocket soars above the clouds here today at Vandenberg AFB, Calif. The NASA payload aboard the rocket are the ICESat, an Ice Cloud and land Elevation Satellite, and CHIPSat, a Cosmic Hot Interstellar Plasma Spectrometer. ICESat, a 661-pound satellite, is a benchmark satellite for the Earth Observing System that will help scientists determine if the global sea level is rising or falling. It will observe the ice sheets that blanket the Earth’s poles to determine if they are growing or shrinking. It will assist in developing an understanding of how changes in the Earth’s atmosphere and climate affect polar ice masses and global sea level. The Geoscience Laser Altimeter System is the sole instrument on the satellite. CHIPSat, a suitcase-size 131-pound satellite, will provide information about the origin, physical processes and properties of the hot gas contained in the interstellar medium. This launch marks the first Delta from Vandenberg this year. (USAF photo by: SSgt Lee A Osberry Jr.)

Use of System Safety Risk Assessments for the Space Shuttle Reusable Solid Rocket Motor (RSRM)

NASA Technical Reports Server (NTRS)

Greenhalgh, Phillip O.; McCool, Alex (Technical Monitor)

2001-01-01

This paper discusses the System Safety approach used to assess risk for the Space Shuttle Reusable Solid Rocket Motor (RSRM). Previous to the first RSRM flight in the fall of 1988, all systems were analyzed extensively to assure that hazards were identified, assessed and that the baseline risk was understood and appropriately communicated. Since the original RSRM baseline was established, Thiokol and NASA have implemented a number of initiatives that have further improved the RSRM. The robust design, completion of rigorous testing and flight success of the RSRM has resulted in a wise reluctance to make changes. One of the primary assessments required to accompany the documentation of each proposed change and aid in the decision making process is a risk assessment. Documentation supporting proposed changes, including the risk assessments from System Safety, are reviewed and assessed by Thiokol and NASA technical management. After thorough consideration, approved changes are implemented adding improvements to and reducing risk of the Space Shuttle RSRM.

APES: Acute Precipitating Electron Spectrometer - A High Time Resolution Monodirectional Magnetic Deflection Electron Spectrometer

NASA Technical Reports Server (NTRS)

Michell, R. G.; Samara, M.; Grubbs, G., II; Ogasawara, K.; Miller, G.; Trevino, J. A.; Webster, J.; Stange, J.

2016-01-01

We present a description of the Acute Precipitating Electron Spectrometer (APES) that was designed and built for the Ground-to-Rocket Electron Electrodynamics Correlative Experiment (GREECE) auroral sounding rocket mission. The purpose was to measure the precipitating electron spectrum with high time resolution, on the order of milliseconds. The trade-off made in order to achieve high time resolution was to limit the aperture to only one look direction. The energy selection was done by using a permanent magnet to separate the incoming electrons, such that the different energies would fall onto different regions of the microchannel plate and therefore be detected by different anodes. A rectangular microchannel plate (MCP) was used (15 mm x 100 mm), and there was a total of 50 discrete anodes under the MCP, each one 15 mm x 1.5 mm, with a 0.5 mm spacing between anodes. The target energy range of APES was 200 eV to 30 keV.

Using the Flow-3D General Moving Object Model to Simulate Coupled Liquid Slosh - Container Dynamics on the SPHERES Slosh Experiment: Aboard the International Space Station

NASA Technical Reports Server (NTRS)

Schulman, Richard; Kirk, Daniel; Marsell, Brandon; Roth, Jacob; Schallhorn, Paul

2013-01-01

The SPHERES Slosh Experiment (SSE) is a free floating experimental platform developed for the acquisition of long duration liquid slosh data aboard the International Space Station (ISS). The data sets collected will be used to benchmark numerical models to aid in the design of rocket and spacecraft propulsion systems. Utilizing two SPHERES Satellites, the experiment will be moved through different maneuvers designed to induce liquid slosh in the experiment's internal tank. The SSE has a total of twenty-four thrusters to move the experiment. In order to design slosh generating maneuvers, a parametric study with three maneuvers types was conducted using the General Moving Object (GMO) model in Flow-30. The three types of maneuvers are a translation maneuver, a rotation maneuver and a combined rotation translation maneuver. The effectiveness of each maneuver to generate slosh is determined by the deviation of the experiment's trajectory as compared to a dry mass trajectory. To fully capture the effect of liquid re-distribution on experiment trajectory, each thruster is modeled as an independent force point in the Flow-3D simulation. This is accomplished by modifying the total number of independent forces in the GMO model from the standard five to twenty-four. Results demonstrate that the most effective slosh generating maneuvers for all motions occurs when SSE thrusters are producing the highest changes in SSE acceleration. The results also demonstrate that several centimeters of trajectory deviation between the dry and slosh cases occur during the maneuvers; while these deviations seem small, they are measureable by SSE instrumentation.

KSC-00pp1570

NASA Image and Video Library

2000-09-08

KENNEDY SPACE CENTER, Fla. -- A perfect on-time launch for Atlantis as it rockets toward space on mission STS-106. Liftoff occurred at 8:45:47 a.m. EDT. On the 11-day mission to the International Space Station, the seven-member crew will perform support tasks on orbit, transfer supplies and prepare the living quarters in the newly arrived Zvezda Service Module. The first long-duration crew, dubbed “Expedition One,” is due to arrive at the Station in late fall. Landing of Atlantis is targeted for 4:45 a.m. EDT on Sept. 19

Moon (Form-Origin)

NASA Astrophysics Data System (ADS)

Tsiapas, Elias

2016-04-01

When the Earth was formed, it was in a state of burning heat. As time went by, temperature on the planet's surface was falling due to radiation and heat transfer, and various components (crusts) began taking solid form at the Earth's poles. The formation of crusts took place at the Earth's poles, because the stirring of burning and fluid masses on the surface of the Earth was significantly slighter there than it was on the equator. Due to centrifugal force and Coriolis Effect, these solid masses headed towards the equator; those originating from the North Pole followed a south-western course, while those originating from the South Pole followed a north-western course and there they rotated from west to east at a lower speed than the underlying burning and liquid earth, because of their lower initial linear velocity, their solid state and inertia. Because inertia is proportional to mass, the initially larger solid body swept all new solid ones, incorporating them to its western side. The density of the new solid masses was higher, because the components on the surface would freeze and solidify first, before the underlying thicker components. As a result, the western side of the initial islet of solid rocks submerged, while the east side elevated. . As a result of the above, this initial islet began to spin in reverse, and after taking on the shape of a sphere, it formed the "heart" of the Moon. The Moon-sphere, rolling on the equator, would sink the solid rocks that continued to descend from the Earth's poles. The sinking rocks partially melted because of higher temperatures in the greater depths that the Moon descended to, while part of the rocks' mass bonded with the Moon and also served as a heat-insulating material, preventing the descended side of the sphere from melting. Combined with the Earth's liquid mass that covered its emerging eastern surface, new sphere-shaped shells were created, with increased density and very powerful structural cohesion. During the above mentioned process, the thick clouds surrounding Earth-Moon were causing heavy storms and on the outer surface of the rolling Moon, wherever small cavities - or pockets - existed, these would fill up with water. Then, due to the Moon's changing tilt, these pockets were sealed by sediments and as a result, small water tanks are scattered on the successive layers of the Moon, from its centre to its surface. . As this sphere (the Moon) continued to grow, the Earth-Moon system was displaying a double-planet image. The Moon's reverse rolling velocity increased according to the increase of its mass and volume. As the temperature on the surface of the Earth continued to fall, a larger number of bigger sized solid masses were descending from the poles towards the equator, and the Moon could no longer aggregate them. The gathering and interference of solid rocks of great mass acted as the catapult on which the Moon bounced off the Earth and was put into orbit around it.

Moon (Form-Origin)

NASA Astrophysics Data System (ADS)

Tsiapas, Elias; Soumelidou, Despina; Tsiapas, Christos

2017-04-01

When the Earth was formed, it was in a state of burning heat. As time went by, temperature on the planet's surface was falling due to radiation and heat transfer, and various components (crusts) began taking solid form at the Earth's poles. The formation of crusts took place at the Earth's poles, because the stirring of burning and fluid masses on the surface of the Earth was significantly slighter there than it was on the equator. Due to centrifugal force and Coriolis Effect, these solid masses headed towards the equator; those originating from the North Pole followed a south-western course, while those originating from the South Pole followed a north-western course and there they rotated from west to east at a lower speed than the underlying burning and liquid earth, because of their lower initial linear velocity, their solid state and inertia. Because inertia is proportional to mass, the initially larger solid body swept all new solid ones, incorporating them to its western side. The density of the new solid masses was higher, because the components on the surface would freeze and solidify first, before the underlying thicker components. As a result, the western side of the initial islet of solid rocks submerged, while the east side elevated. . As a result of the above, this initial islet began to spin in reverse, and after taking on the shape of a sphere, it formed the "heart" of the Moon. The Moon-sphere, rolling on the equator, would sink the solid rocks that continued to descend from the Earth's poles. The sinking rocks partially melted because of higher temperatures in the greater depths that the Moon descended to, while part of the rocks' mass bonded with the Moon and also served as a heat-insulating material, preventing the descended side of the sphere from melting. Combined with the Earth's liquid mass that covered its emerging eastern surface, new sphere-shaped shells were created, with increased density and very powerful structural cohesion. During the above mentioned process, the thick clouds surrounding Earth-Moon were causing heavy storms and on the outer surface of the rolling Moon, wherever small cavities - or pockets - existed, these would fill up with water. Then, due to the Moon's changing tilt, these pockets were sealed by sediments and as a result, small water tanks are scattered on the successive layers of the Moon, from its centre to its surface. . As this sphere (the Moon) continued to grow, the Earth-Moon system was displaying a double-planet image. The Moon's reverse rolling velocity increased according to the increase of its mass and volume. As the temperature on the surface of the Earth continued to fall, a larger number of bigger sized solid masses were descending from the poles towards the equator, and the Moon could no longer aggregate them. The gathering and interference of solid rocks of great mass acted as the catapult on which the Moon bounced off the Earth and was put into orbit around it.

Moon (Form-Origin)

NASA Astrophysics Data System (ADS)

Tsiapas, Elias

2015-04-01

When the Earth was formed, it was in a state of burning heat. As time went by, temperature on the planet's surface was falling due to radiation and heat transfer, and various components (crusts) began taking solid form at the Earth's poles. The formation of crusts took place at the Earth's poles, because the stirring of burning and fluid masses on the surface of the Earth was significantly slighter there than it was on the equator. Due to centrifugal force and Coriolis Effect, these solid masses headed towards the equator; those originating from the North Pole followed a south-western course, while those originating from the South Pole followed a north-western course and there they rotated from west to east at a lower speed than the underlying burning and liquid earth, because of their lower initial linear velocity, their solid state and inertia. Because inertia is proportional to mass, the initially larger solid body swept all new solid ones, incorporating them to its western side. The density of the new solid masses was higher, because the components on the surface would freeze and solidify first, before the underlying thicker components. As a result, the western side of the initial islet of solid rocks submerged, while the east side elevated. . As a result of the above, this initial islet began to spin in reverse, and after taking on the shape of a sphere, it formed the "heart" of the Moon. The Moon-sphere, rolling on the equator, would sink the solid rocks that continued to descend from the Earth's poles. The sinking rocks partially melted because of higher temperatures in the greater depths that the Moon descended to, while part of the rocks' mass bonded with the Moon and also served as a heat-insulating material, preventing the descended side of the sphere from melting. Combined with the Earth's liquid mass that covered its emerging eastern surface, new sphere-shaped shells were created, with increased density and very powerful structural cohesion. During the above mentioned process, the thick clouds surrounding Earth-Moon were causing heavy storms and on the outer surface of the rolling Moon, wherever small cavities - or pockets - existed, these would fill up with water. Then, due to the Moon's changing tilt, these pockets were sealed by sediments and as a result, small water tanks are scattered on the successive layers of the Moon, from its centre to its surface. . As this sphere (the Moon) continued to grow, the Earth-Moon system was displaying a double-planet image. The Moon's reverse rolling velocity increased according to the increase of its mass and volume. As the temperature on the surface of the Earth continued to fall, a larger number of bigger sized solid masses were descending from the poles towards the equator, and the Moon could no longer aggregate them. The gathering and interference of solid rocks of great mass acted as the catapult on which the Moon bounced off the Earth and was put into orbit around it.

Moon (Form-Origin)

NASA Astrophysics Data System (ADS)

Tsiapas, Elias

2014-05-01

When the Earth was formed, it was in a state of burning heat. As time went by, temperature on the planet's surface was falling due to radiation and heat transfer, and various components (crusts) began taking solid form at the Earth's poles. The formation of crusts took place at the Earth's poles, because the stirring of burning and fluid masses on the surface of the Earth was significantly slighter there than it was on the equator. Due to centrifugal force and Coriolis Effect, these solid masses headed towards the equator; those originating from the North Pole followed a south-western course, while those originating from the South Pole followed a north-western course and there they rotated from west to east at a lower speed than the underlying burning and liquid earth, because of their lower initial linear velocity, their solid state and inertia. Because inertia is proportional to mass, the initially larger solid body swept all new solid ones, incorporating them to its western side. The density of the new solid masses was higher, because the components on the surface would freeze and solidify first, before the underlying thicker components. As a result, the western side of the initial islet of solid rocks submerged, while the east side elevated. . As a result of the above, this initial islet began to spin in reverse, and after taking on the shape of a sphere, it formed the "heart" of the Moon. The Moon-sphere, rolling on the equator, would sink the solid rocks that continued to descend from the Earth's poles. The sinking rocks partially melted because of higher temperatures in the greater depths that the Moon descended to, while part of the rocks' mass bonded with the Moon and also served as a heat-insulating material, preventing the descended side of the sphere from melting. Combined with the Earth's liquid mass that covered its emerging eastern surface, new sphere-shaped shells were created, with increased density and very powerful structural cohesion. During the above mentioned process, the thick clouds surrounding Earth-Moon were causing heavy storms and on the outer surface of the rolling Moon, wherever small cavities - or pockets - existed, these would fill up with water. Then, due to the Moon's changing tilt, these pockets were sealed by sediments and as a result, small water tanks are scattered on the successive layers of the Moon, from its centre to its surface. . As this sphere (the Moon) continued to grow, the Earth-Moon system was displaying a double-planet image. The Moon's reverse rolling velocity increased according to the increase of its mass and volume. As the temperature on the surface of the Earth continued to fall, a larger number of bigger sized solid masses were descending from the poles towards the equator, and the Moon could no longer aggregate them. The gathering and interference of solid rocks of great mass acted as the catapult on which the Moon bounced off the Earth and was put into orbit around it..

Fuzzy spaces topology change and BH thermodynamics

NASA Astrophysics Data System (ADS)

Silva, C. A. S.; Landim, R. R.

2014-03-01

What is the ultimate fate of something that falls into a black hole? From this question arises one of the most intricate problems of modern theoretical physics: the black hole information loss paradox. Bekenstein and Hawking have been shown that the entropy in a black hole is proportional to the surface area of its event horizon, which should be quantized in a multiple of the Planck area. This led G.'t Hooft and L. Susskind to propose the holographic principle which states that all the information inside the black hole can be stored on its event horizon. From this results, one may think if the solution to the information paradox could lies in the quantum properties of the black hole horizon. One way to quantize the event horizon is to see it as a fuzzy sphere, which posses a closed relation with Hopf algebras. This relation makes possible a topology change process where a fuzzy sphere splits in two others. In this work it will be shown that, if one quantize the black hole event horizon as a fuzzy sphere taking into account its quantum symmetry properties, a topology change process to black holes can be defined without break unitarity or locality, and we can obtain a possible solution to the information paradox. Moreover, we show that this model can explain the origin of the black hole entropy, and why black holes obey a generalized second law of thermodynamics.

Three-dimensional Reconstruction of Block Shape Irregularity and its Effects on Block Impacts Using an Energy-Based Approach

NASA Astrophysics Data System (ADS)

Zhang, Yulong; Liu, Zaobao; Shi, Chong; Shao, Jianfu

2018-04-01

This study is devoted to three-dimensional modeling of small falling rocks in block impact analysis in energy view using the particle flow method. The restitution coefficient of rockfall collision is introduced from the energy consumption mechanism to describe rockfall-impacting properties. Three-dimensional reconstruction of falling block is conducted with the help of spherical harmonic functions that have satisfactory mathematical properties such as orthogonality and rotation invariance. Numerical modeling of the block impact to the bedrock is analyzed with both the sphere-simplified model and the 3D reconstructed model. Comparisons of the obtained results suggest that the 3D reconstructed model is advantageous in considering the combination effects of rockfall velocity and rotations during colliding process. Verification of the modeling is carried out with the results obtained from other experiments. In addition, the effects of rockfall morphology, surface characteristics, velocity, and volume, colliding damping and relative angle are investigated. A three-dimensional reconstruction modulus of falling blocks is to be developed and incorporated into the rockfall simulation tools in order to extend the modeling results at block scale to slope scale.

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.

Selection of artificial gravity by animals during suborbital rocket flights.

PubMed

Lange, K O; Belleville, R E; Clark, F C

1975-06-01

White rats selected preferred artificial gravity levels by locomotion in centrifuges consisting of two runways mounted in the nose of sounding rockets. Roll rate of the Aerobee 150A rocket was designed to produce an angular velocity of 45 r.p.m. during 5 min of free-fall, providing a gravity range range from 0.3 to 1.5 G depending on a subject's runway position. One animal was released at the high and one at the low gravity position in each flight. Animal positions were continuously recorded. Flight subjects were selected from about 100 trained animals adapted to the simulated launch environment for several months. In two flights excessive rollrates produced gravity ranges above the designed limits. In two other flights the desired range was produced. Locomotion patterns during these flights were similar. All four animals explored the entire available G-range. One rat settled at 0.4 G after 2 min; the others crossed the 1-G location in progressively narrower excursions and were near earth gravity at the end of the test period. Data were more varible than in laboratory tests above 1 G and the observation periods were necessarily few and short. Tentatively, however, the data suggest that normal earth-reared rats select earth gravity when available magnitudes include values above and below 1 B. Modification of gravity preference by prolonged exposure to higher or lower levels remains a possibility.

Capabilities and constraints of NASA's ground-based reduced gravity facilities

NASA Technical Reports Server (NTRS)

Lekan, Jack; Neumann, Eric S.; Sotos, Raymond G.

1993-01-01

The ground-based reduced gravity facilities of NASA have been utilized to support numerous investigations addressing various processes and phenomina in several disciplines for the past 30 years. These facilities, which include drop towers, drop tubes, aircraft, and sounding rockets are able to provide a low gravity environment (gravitational levels that range from 10(exp -2)g to 10(exp -6)g) by creating a free fall or semi-free fall condition where the force of gravity on an experiment is offset by its linear acceleration during the 'fall' (drop or parabola). The low gravity condition obtained on the ground is the same as that of an orbiting spacecraft which is in a state of perpetual free fall. The gravitational levels and associated duration times associated with the full spectrum of reduced gravity facilities including spaced-based facilities are summarized. Even though ground-based facilities offer a relatively short experiment time, this available test time has been found to be sufficient to advance the scientific understanding of many phenomena and to provide meaningful hardware tests during the flight experiment development process. Also, since experiments can be quickly repeated in these facilities, multistep phenomena that have longer characteristic times associated with them can sometimes be examined in a step-by-step process. There is a large body of literature which has reported the study results achieved through using reduced-gravity data obtained from the facilities.

A US History of Airbreathing/Rocket Combined-Cycle (RBCC) Propulsion for Powering Future Aerospace Transports, with a Look Ahead to the Year 2020

NASA Technical Reports Server (NTRS)

Escher, William J. D.

1999-01-01

A technohistorical and forward-planning overview of U.S. developments in combined airbreathing/rocket propulsion for advanced aerospace vehicle applications is presented. Such system approaches fall into one of two categories: (1) Combination propulsion systems (separate, non-interacting engines installed), and (2) Combined-Cycle systems. The latter, and main subject, comprises a large family of closely integrated engine types, made up of both airbreathing and rocket derived subsystem hardware. A single vehicle-integrated, multimode engine results, one capable of operating efficiently over a very wide speed and altitude range, atmospherically and in space. While numerous combination propulsion systems have reached operational flight service, combined-cycle propulsion development, initiated ca. 1960, remains at the subscale ground-test engine level of development. However, going beyond combination systems, combined-cycle propulsion potentially offers a compelling set of new and unique capabilities. These capabilities are seen as enabling ones for the evolution of Spaceliner class aerospace transportation systems. The following combined-cycle hypersonic engine developments are reviewed: (1) RENE (rocket engine nozzle ejector), (2) Cryojet and LACE, (3) Ejector Ramjet and its derivatives, (4) the seminal NASA NAS7-377 study, (5) Air Force/Marquardt Hypersonic Ramjet, (6) Air Force/Lockheed-Marquardt Incremental Scramjet flight-test project, (7) NASA/Garrett Hypersonic Research Engine (HRE), (8) National Aero-Space Plane (NASP), (9) all past projects; and such current and planned efforts as (10) the NASA ASTP-ART RBCC project, (11) joint CIAM/NASA DNSCRAM flight test,(12) Hyper-X, (13) Trailblazer,( 14) W-Vehicle and (15) Spaceliner 100. Forward planning programmatic incentives, and the estimated timing for an operational Spaceliner powered by combined-cycle engines are discussed.

Charge and energy spectra of particles with E from 0.2 to 30 MeV/nuc in the January 25, 1971 solar flare.

NASA Technical Reports Server (NTRS)

Price, P. B.; Sullivan, J. D.

1972-01-01

Tracks of 1000 solar particles with charge Z not less than 10 and tracks of about 150 particles with Z equal to 8 have been analyzed in a stack of plastic detectors exposed in a rocket during the solar flare of Jan. 25, 1971. The energy spectra peak at about 1.5 MeV/nuc, with the flux falling to zero at about 0.4 MeV/nuc. Fe, Si, and O appear to have similar energy spectra for energies between 2 and 12 MeV/nuc.

KSC-2010-4635

NASA Image and Video Library

2010-09-10

CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, construction crews lay sand, reinforcing steel and large wooden mats under the rotating service structure (RSS) of Launch Pad 39B to protect the structure's concrete from falling debris during deconstruction. Starting in 2009, the structure at the pad was no longer needed for NASA's Space Shuttle Program, so it is being restructured for future use. The new design will feature a "clean pad" for rockets to come with their own launcher, making it more versatile for a number of vehicles. For information on NASA's future plans, visit www.nasa.gov. Photo credit: NASA/Jim Grossmann

KSC-2011-6158

NASA Image and Video Library

2011-08-03

CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, cleanup of Launch Pad 39B is in progress. Sand, reinforcing steel and large wooden mats were placed over the pad's concrete surfaces during deconstruction to protect them from falling debris. In 2009, the structure at the pad was no longer needed for NASA's Space Shuttle Program, so it is being restructured for future use. The new design will feature a "clean pad" for rockets to come with their own launcher, making it more versatile for a number of vehicles. For information on NASA's future plans, visit http://www.nasa.gov/exploration. Photo credit: NASA/Kim Shiflett

KSC-2010-4636

NASA Image and Video Library

2010-09-10

CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, construction crews lay sand, reinforcing steel and large wooden mats under the rotating service structure (RSS) of Launch Pad 39B to protect the structure's concrete from falling debris during deconstruction. Starting in 2009, the structure at the pad was no longer needed for NASA's Space Shuttle Program, so it is being restructured for future use. The new design will feature a "clean pad" for rockets to come with their own launcher, making it more versatile for a number of vehicles. For information on NASA's future plans, visit www.nasa.gov. Photo credit: NASA/Jim Grossmann

KSC-2010-4634

NASA Image and Video Library

2010-09-10

CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, construction crews lay sand, reinforcing steel and large wooden mats under the rotating service structure (RSS) of Launch Pad 39B to protect the structure's concrete from falling debris during deconstruction. Starting in 2009, the structure at the pad was no longer needed for NASA's Space Shuttle Program, so it is being restructured for future use. The new design will feature a "clean pad" for rockets to come with their own launcher, making it more versatile for a number of vehicles. For information on NASA's future plans, visit www.nasa.gov. Photo credit: NASA/Jim Grossmann

KSC-00pd1262

NASA Image and Video Library

2000-09-08

KENNEDY SPACE CENTER, Fla. -- Columns of flame spew from the solid rocket boosters hurling Space Shuttle Atlantis toward space on mission STS-106. The on-time liftoff occurred at 8:45:47 a.m. EDT for the start of an 11-day mission to the International Space Station. While on board, the seven-member crew will perform support tasks, transfer supplies and prepare the living quarters in the newly arrived Zvezda Service Module. The first long-duration crew, dubbed “Expedition One,” is due to arrive at the Station in late fall. Landing of Atlantis is targeted for 4:45 a.m. EDT on Sept. 19

KSC00pd1262

NASA Image and Video Library

2000-09-08

KENNEDY SPACE CENTER, Fla. -- Columns of flame spew from the solid rocket boosters hurling Space Shuttle Atlantis toward space on mission STS-106. The on-time liftoff occurred at 8:45:47 a.m. EDT for the start of an 11-day mission to the International Space Station. While on board, the seven-member crew will perform support tasks, transfer supplies and prepare the living quarters in the newly arrived Zvezda Service Module. The first long-duration crew, dubbed “Expedition One,” is due to arrive at the Station in late fall. Landing of Atlantis is targeted for 4:45 a.m. EDT on Sept. 19

Solvent as electron donor: Donor/acceptor electronic coupling is a dynamical variable

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

Castner, E.W. Jr.; Kennedy, D.; Cave, R.J.

2000-04-06

The authors combine analysis of measurements by femtosecond optical spectroscopy, computer simulations, and the generalized Mulliken-Hush (GMH) theory in the study of electron-transfer reactions and electron donor-acceptor interactions. The study focus is on ultrafast photoinduced electron-transfer reactions from aromatic amine solvent donors to excited-state acceptors. The experimental results from femtosecond dynamical measurements fall into three categories: six coumarin acceptors reductively quenched by N,N-dimethylaniline (DMA), eight electron-donating amine solvents reductively quenching coumarin 152 (7-(dimethylamino)-4-(trifluoromethyl)-coumarin), and reductive quenching dynamics of two coumarins by DMA as a function of dilution in the nonreactive solvents toluene and chlorobenzene. Applying a combination of molecular dynamicsmore » trajectories, semiempirical quantum mechanical calculations (of the relevant adiabatic electronic states), and GMH theory to the C152/DMA photoreaction, the authors calculate the electron donor/acceptor interaction parameter H{sub DA} at various time frames, H{sub DA} is strongly modulated by both inner-sphere and outer-sphere nuclear dynamics, leading us to conclude that H{sub DA} must be considered as a dynamical variable.« less

Percolation study for the capillary ascent of a liquid through a granular soil

NASA Astrophysics Data System (ADS)

Cárdenas-Barrantes, Manuel Antonio; Muñoz, José Daniel; Araujo, Nuno Machado

2017-06-01

Capillary rise plays a crucial role in the construction of road embankments in flood zones, where hydrophobic compounds are added to the soil to suppress the rising of water and avoid possible damage of the pavement. Water rises through liquid bridges, menisci and trimers, whose width and connectivity depends on the maximal half-length λ of the capillary bridges among grains. Low λs generate a disconnect structure, with small clusters everywhere. On the contrary, for high λ, create a percolating cluster of trimers and enclosed volumes that form a natural path for capillary rise. Hereby, we study the percolation transition of this geometric structure as a function of λ on a granular media of monodisperse spheres in a random close packing. We determine both the percolating threshold λc = (0.049 ± 0.004)R (with R the radius of the granular spheres), and the critical exponent of the correlation length v = 0.830 ± 0.051, suggesting that the percolation transition falls into the universality class of ordinary percolation.

Glass shell manufacturing in space

NASA Technical Reports Server (NTRS)

Downs, R. L.; Ebner, M. A.; Nolen, R. L., Jr.

1981-01-01

Highly-uniform, hollow glass spheres (shells), which are used for inertial confinement fusion targets, were formed from metal-organic gel powder feedstock in a vertical furnace. As a result of the rapid pyrolysis caused by the furnace, the gel is transformed to a shell in five distinct stages: (a) surface closure of the porous gel; (b) generation of a closed-cell foam structure in the gel; (c) spheridization of the gel and further expansion of the foam; (d) coalescence of the closed-cell foam to a single-void shell; and (e) fining of the glass shell. The heat transfer from the furnace to the falling gel particle was modeled to determine the effective heating rate of the gel. The model predicts the temperature history for a particle as a function of mass, dimensions, specific heat, and absorptance as well as furnace temperature profile and thermal conductivity of the furnace gas. A model was developed that predicts the gravity-induced degradation of shell concentricity in falling molten shells as a function of shell characteristics and time.

Apparatus for the production of gel beads containing a biocatalyst

DOEpatents

Scott, C.D.; Scott, T.C.; Davison, B.H.

1998-03-19

An apparatus is described for the large-scale and continuous production of gel beads containing a biocatalyst. The apparatus is a columnar system based on the chemical cross-linking of hydrocolloidal gels that contain and immobilize a biocatalyst, the biocatalyst being a microorganism or an enzyme. Hydrocolloidal gels, such as alginate, carrageenan, and a mixture of bone gelatin and modified alginate, provide immobilization matrices that can be used to entrap and retain the biocatalyst while allowing effective contact with substrates and release of products. Such immobilized biocatalysts are generally formulated into small spheres or beads that have high concentrations of the biocatalyst within the gel matrix. The columnar system includes a gel dispersion nozzle submerged in a heated non-interacting liquid, typically an organic liquid, that is immiscible with water to allow efficient formation of spherical gel droplets, the non-interacting liquid having a specific gravity that is less than water so that the gel droplets will fall through the liquid by the force of gravity. The heated non-interacting liquid is in direct contact with a chilled upflowing non-interacting liquid that will provide sufficient residence time for the gel droplets as they fall through the liquid so that they will be cooled below the gelling temperature and form solid spheres. The upflowing non-interacting liquid is in direct contact with an upflowing temperature-controlled aqueous solution containing the necessary chemicals for cross-linking or fixing of the gel beads to add the necessary stability. The flow rates of the two liquid streams can be varied to control the proper residence time in each liquid section to accommodate the production of gel beads of differing settling velocities. A valve is provided for continuous removal of the stabilized gel beads from the bottom of the column. 1 fig.

Apparatus and method for the production of gel beads containing a biocatalyst

DOEpatents

Scott, Charles D.; Scott, Timothy C.; Davison, Brian H.

1998-01-01

An apparatus and method for the large-scale and continuous production of gel beads containing a biocatalyst. The apparatus is a columnar system based on the chemical cross-linking of hydrocolloidal gels that contain and immobilize a biocatalyst, the biocatalyst being a microorganism or an enzyme. Hydrocolloidal gels, such as alginate, carrageenan, and a mixture of bone gelatin and modified alginate, provide immobilization matrices that can be used to entrap and retain the biocatalyst while allowing effective contact with substrates and release of products. Such immobilized biocatalysts are generally formulated into small spheres or beads that have high concentrations of the biocatalyst within the gel matrix. The columnar system includes a gel dispersion nozzle submerged in a heated non-interacting liquid, typically an organic liquid, that is immiscible with water to allow efficient formation of spherical gel droplets, the non-interacting liquid having a specific gravity that is less than water so that the gel droplets will fall through the liquid by the force of gravity. The heated non-interacting liquid is in direct contact with a chilled upflowing non-interacting liquid that will provide sufficient residence time for the gel droplets as they fall through the liquid so that they will be cooled below the gelling temperature and form solid spheres. The upflowing non-interacting liquid is in direct contact with an upflowing temperature-controlled aqueous solution containing the necessary chemicals for cross-linking or fixing of the gel beads to add the necessary stability. The flow rates of the two liquid streams can be varied to control the proper residence time in each liquid section to accommodate the production of gel beads of differing settling velocities. A valve is provided for continuous removal of the stabilized gel beads from the bottom of the column.

Apparatus for the production of gel beads containing a biocatalyst

DOEpatents

Scott, Charles D.; Scott, Timothy C.; Davison, Brian H.

1998-01-01

An apparatus for the large-scale and continuous production of gel beads containing a biocatalyst. The apparatus is a columnar system based on the chemical cross-linking of hydrocolloidal gels that contain and immobilize a biocatalyst, the biocatalyst being a microorganism or an enzyme. Hydrocolloidal gels, such as alginate, carrageenan, and a mixture of bone gelatin and modified alginate, provide immobilization matrices that can be used to entrap and retain the biocatalyst while allowing effective contact with substrates and release of products. Such immobilized biocatalysts are generally formulated into small spheres or beads that have high concentrations of the biocatalyst within the gel matrix. The columnar system includes a gel dispersion nozzle submerged in a heated non-interacting liquid, typically an organic liquid, that is immiscible with water to allow efficient formation of spherical gel droplets, the non-interacting liquid having a specific gravity that is less than water so that the gel droplets will fall through the liquid by the force of gravity. The heated non-interacting liquid is in direct contact with a chilled upflowing non-interacting liquid that will provide sufficient residence time for the gel droplets as they fall through the liquid so that they will be cooled below the gelling temperature and form solid spheres. The upflowing non-interacting liquid is in direct contact with an upflowing temperature-controlled aqueous solution containing the necessary chemicals for cross-linking or fixing of the gel beads to add the necessary stability. The flow rates of the two liquid streams can be varied to control the proper residence time in each liquid section to accommodate the production of gel beads of differing settling velocities. A valve is provided for continuous removal of the stabilized gel beads from the bottom of the column.

Objective assessment of gender roles: Gender Roles Test (GRT-36).

PubMed

Fernández, Juan; Quiroga, M Angeles; del Olmo, Isabel; Aróztegui, Javier; Martín, Arantxa

2011-11-01

This study was designed to develop a computerized test to assess gender roles. This test is presented as a decision-making task to mask its purpose. Each item displays a picture representing an activity and a brief sentence that describes it. Participants have to choose the most suitable sex to perform each activity: man or woman. The test (Gender Roles Test, GRT-36) consists of 36 items/activities. The program registers both the choices made and their response times (RTs). Responses are considered as stereotyped when the chosen sex fits stereotyped roles and non-stereotyped when the chosen sex does not fit stereotyped roles. Individual means (RTs) were computed for stereotyped and non-stereotyped responses, differentiating between domestic and work spheres. A "D" score, reflecting the strength of association between activities and sex, was calculated for each sphere and sex. The study incorporated 78 participants (69% women and 31% men) ranging from 19 to 59 years old. The results show that: (a) reading speed does not explain the variability in the RTs; (b) RTs show good internal consistency; (c) RTs are shorter for stereotyped than for neutral stimuli; (d) RTs are shorter for stereotyped than for non-stereotyped responses. Intended goals are supported by obtained results. Scores provided by the task facilitate both group and individual detailed analysis of gender role, differentiating the gender role assigned to men from that assigned to women, at the domestic and work spheres. Obtained data fall within the scope of the genderology and their implications are discussed.

Waves generated in the vicinity of an argon plasma gun in the ionosphere

NASA Technical Reports Server (NTRS)

Cahill, L. J., Jr.; Arnoldy, R. L.; Lysak, R. L.; Peria, W.; Lynch, K. A.

1993-01-01

Wave and particle observations were made in the close vicinity of an argon plasma gun carned to over 600 km altitude on a sounding rocket. The gun was carned on a subpayload, separated from the main payload early in the flight. Twelve-second argon ion ejections were energized alternately with a peak energy of 100 or 200 eV. They produced waves, with multiple harmonics, in the range of ion cyclotron waves, 10 to 1000 Hz at rocket altitudes. Many of these waves could not be identified as corresponding to the cyclotron frequencies of any of the ions, argon or ambient, known to be present. In addition, the wave frequencies were observed to rise and fall and to change abruptly during a 12-s gun operation. The wave amplitudes, near a few hundred Hertz, were of the order of O. 1 V/m. Some of the waves may be ion-ion hybrid waves. Changes in ion populations were observed at the main payload and at the subpayload during gun operations. A gun-related, field-aligned, electron population also appeared.

Waves generated in the vicinity of an argon plasma gun in the ionosphere

NASA Astrophysics Data System (ADS)

Cahill, L. J., Jr.; Arnoldy, R. L.; Lysak, R. L.; Peria, W.; Lynch, K. A.

1993-06-01

Wave and particle observations were made in the close vicinity of an argon plasma gun carned to over 600 km altitude on a sounding rocket. The gun was carned on a subpayload, separated from the main payload early in the flight. Twelve-second argon ion ejections were energized alternately with a peak energy of 100 or 200 eV. They produced waves, with multiple harmonics, in the range of ion cyclotron waves, 10 to 1000 Hz at rocket altitudes. Many of these waves could not be identified as corresponding to the cyclotron frequencies of any of the ions, argon or ambient, known to be present. In addition, the wave frequencies were observed to rise and fall and to change abruptly during a 12-s gun operation. The wave amplitudes, near a few hundred Hertz, were of the order of O. 1 V/m. Some of the waves may be ion-ion hybrid waves. Changes in ion populations were observed at the main payload and at the subpayload during gun operations. A gun-related, field-aligned, electron population also appeared.

Species and temperature measurement in H2/O2 rocket flow fields by means of Raman scattering diagnostics

NASA Technical Reports Server (NTRS)

De Groot, Wim A.; Weiss, Jonathan M.

1992-01-01

Validation of CFD codes developed for prediction and evaluation of rocket performance is hampered by a lack of experimental data. Nonintrusive laser based diagnostics are needed to provide spatially and temporally resolved gas dynamic and fluid dynamic measurements. This paper reports the first nonintrusive temperature and species measurements in the plume of a 110 N gaseous hydrogen/oxygen thruster at and below ambient pressures, obtained with spontaneous Raman spectroscopy. Measurements at 10 mm downstream of the exit plane are compared with predictions from a numerical solution of the axisymmetric Navier-Stokes and species transport equations with chemical kinetics, which fully model the combustor-nozzle-plume flowfield. The experimentally determined oxygen number density at the centerline at 10 mm downstream of the exit plane is four times that predicted by the model. The experimental number density data fall between those numerically predicted for the exit and 10 mm downstream planes in both magnitude and radial gradient. The predicted temperature levels are within 10 to 15 percent of measured values.

History of Chandra X-Ray Observatory

NASA Image and Video Library

1999-01-01

In this photograph, the Chandra X-Ray Observatory (CXO) was installed and mated to the Inertial Upper Stage (IUS) inside the Shuttle Columbia's cargo bay at the Kennedy Space Center. The CXO will help astronomers world-wide better understand the structure and evolution of the universe by studying powerful sources of x-rays such as exploding stars, matter falling into black holes, and other exotic celestial objects. X-ray astronomy can only be done from space because Earth's atmosphere blocks x-rays from reaching the surface. The Observatory provides images that are 50 times more detailed than previous x-ray missions. At more than 45 feet in length and weighing more than 5 tons, the CXO was carried into low-Earth orbit by the Space Shuttle Columbia (STS-93 mission) on July 22, 1999. The Observatory was deployed from the Shuttle's cargo bay at 155 miles above the Earth. Two firings of an attached IUS rocket, and several firings of its own onboard rocket motors, after separating from the IUS, placed the Observatory into its working orbit. The IUS is a solid rocket used to place spacecraft into orbit or boost them away from the Earth on interplanetary missions. Since its first use by NASA in 1983, the IUS has supported a variety of important missions, such as the Tracking and Data Relay Satellite, Galileo spacecraft, Magellan spacecraft, and Ulysses spacecraft. The IUS was built by the Boeing Aerospace Co., at Seattle, Washington and managed by the Marshall Space Flight Center.

Summary of PhysPAG Activity

NASA Astrophysics Data System (ADS)

Nousek, John A.

2014-01-01

The Physics of the Cosmos Program Analysis Group (PhysPAG) is responsible for solicitiing and coordinating community input for the development and execution of NASA's Physics of the Cosmos (PCOS) program. In this session I will report on the activity of the PhysPAG, and solicit community involvement in the process of defining PCOS objectives, planning SMD architecture, and prioritizing PCOS activities. I will also report on the activities of the PhysPAG Executive Committee, which include the chairs of the Science Analysis Groups/ Science Interest Groups which fall under the PhysPAG sphere of interest. Time at the end of the presentation willl be reserved for questions and discussion from the community.

Atopic Dermatitis (Eczema): An Appraisal

PubMed Central

Hudson, Arthur L.

1962-01-01

Atopic (spontaneous) allergies and nonatopic (induced) allergies are often confused. The meaning of these terms is definite, but the occurrence of either (in a given individual) may depend upon his autonomic nervous system control. The evidence that allergens produce the cutaneous changes in atopic dermatitis is flimsy, and neurodermatitis would be a more appropriate term since the entity falls into that pattern of skin changes. Treatment carried out, from infancy sometimes to old age, consists of careful management of the patient in the physical and emotional spheres, avoidance of external irritation and the use of a multiplicity of anti-pruritic, anti-inflammatory and sedative agents. PMID:13955448

Going Above & Beyond: Astronomy as the Public’s Gateway to Science

NASA Astrophysics Data System (ADS)

Rehnberg, Morgan

2015-11-01

Many of the world’s most pressing scientific issues fall outside the purview of astronomy. Climate change, vaccination, genetic modification, and other similar topics are embroiled in the trenches of an ideological war in the public sphere, which creates a sometimes-insurmountable obstacle to discussion. This talk will describe a show series developed at Fiske Planetarium that uses the public’s remarkable appetite for space content as a means for engaging indirectly with these contentious topics. It also promotes the planetarium as a place for interdisciplinary learning and offers the opportunity for the broader population to engage with young scientists in a different light.

Transport properties of nonelectrolyte mixtures. IX. Viscosity coefficients for acetonitrile and for three mixtures of toluene+acetonitrile from 25 to 100°c at pressures up to 500 MPa

NASA Astrophysics Data System (ADS)

Dymond, J. H.; Awan, M. A.; Glen, N. F.; Isdale, J. D.

1991-05-01

A two-coil self-centering falling-body viscometer has been used to measure viscosity coefficients for acetonitrile and three binary mixtures of toluene+ acetonitrile at 25, 50, 75, and 100°C and pressures up to 500 MPa. The results for acetonitrile can be interpreted by an approach based on hard-sphere theory, with a roughness factor of 1.46. The binary-mixture data are well represented by the Grunberg and Nissan equation with a mixing parameter which is pressure and temperature dependent but composition independent.

Novel Techniques for High Pressure Falling Sphere Viscosimetry under Simulated Earth's Mantle Conditions

NASA Astrophysics Data System (ADS)

Mueller, H. J.; Beckmann, F.; Dobson, D. P.; Hunt, S. A.; Secco, R.; Lauterjung, J.; Lathe, C.

2014-12-01

Viscosity data of melts measured under in situ high pressure conditions are crucial for the understanding of Earth's lower mantle and the interior of terrestrial and extrasolar Super-Earth planets. We report recent technical advances and techniques enabling falling sphere viscosity measurements in single- and double-stage DIA-type multi-anvil apparatus. For the experiments we used presses with a maximum load of 250 tons and 1750 tons. We anticipate that our system will enable viscosity measurements up to the maximum pressure for non-diamond anvils, i.e. pressures up to some 30 GPa. For the development of the new set ups the deformation of the cell assemblies were analyzed by X-ray absorption tomography at beamline W II at DESY/HASYLAB after the high pressure runs. These analysis gave considerable insights into strategies for improving the cell assembly with the result that the optimized assemblies could be used at much higher pressures without blow-outs. We think this approach is much faster and more beneficial than the classical way of trial and error. Additionally to prevent high pressure blow outs the task was to make the whole melting chamber accessible for the high pressure X-radiography system up to the maximum pressures. This way the accuracy and reliability of the measurements can be improved. For this goal we used X-ray transparent cBN-anvils at the single-stage DIA large volume press. Because this material is recently not available for the cube size of 32 mm this aproach did not work for the double-stage DIA. As a very useful and economical alternative we used slotted carbide anvils filled with fired pyrophyllite bars. To improve the frame quality of the platinum spheres taken by the CCD-camera the energy of the monochromatic X-rays had to be increased to 100 keV. The resulting ascent of scattered radiation required a new design of the X-radiography unit. Our results are demonstrated with viscosity measurements following Stokes law by evaluation of X-radiography sequences taken by a CCD-camera at pressures of 5 GPa as well as 10 GPa and temperatures of 1890 K. As the first result we could increase the maximum pressure range of published viscosity measurements with dacite melts by almost factor 1.5 (see Tinker et al., 2004).

Computer simulation of supersonic rarefied gas flow in the transition region, about a spherical probe; a Monte Carlo approach with application to rocket-borne ion probe experiments

NASA Technical Reports Server (NTRS)

Horton, B. E.; Bowhill, S. A.

1971-01-01

This report describes a Monte Carlo simulation of transition flow around a sphere. Conditions for the simulation correspond to neutral monatomic molecules at two altitudes (70 and 75 km) in the D region of the ionosphere. Results are presented in the form of density contours, velocity vector plots and density, velocity and temperature profiles for the two altitudes. Contours and density profiles are related to independent Monte Carlo and experimental studies, and drag coefficients are calculated and compared with available experimental data. The small computer used is a PDP-15 with 16 K of core, and a typical run for 75 km requires five iterations, each taking five hours. The results are recorded on DECTAPE to be printed when required, and the program provides error estimates for any flow field parameter.

Leadership in Space: Selected Speeches of NASA Administrator Michael Griffin, May 2005 - October 2008

NASA Technical Reports Server (NTRS)

Griffin, Michael

2008-01-01

Speech topics include: Leadership in Space; Space Exploration: Real and Acceptable Reasons; Why Explore Space?; Space Exploration: Filling up the Canvas; Continuing the Voyage: The Spirit of Endeavour; Incorporating Space into Our Economic Sphere of Influence; The Role of Space Exploration in the Global Economy; Partnership in Space Activities; International Space Cooperation; National Strategy and the Civil Space Program; What the Hubble Space Telescope Teaches Us about Ourselves; The Rocket Team; NASA's Direction; Science and NASA; Science Priorities and Program Management; NASA and the Commercial Space Industry; NASA and the Business of Space; American Competitiveness: NASA's Role & Everyone's Responsibility; Space Exploration: A Frontier for American Collaboration; The Next Generation of Engineers; System Engineering and the "Two Cultures" of Engineering; Generalship of Engineering; NASA and Engineering Integrity; The Constellation Architecture; Then and Now: Fifty Years in Space; The Reality of Tomorrow; and Human Space Exploration: The Next 50 Years.

On Modeling Air/Space-Borne Radar Returns in the Melting Layer

NASA Technical Reports Server (NTRS)

Liao, Liang; Meneghini, Robert

2005-01-01

The bright band is the enhanced radar echo associated with the melting of hydrometeors in stratiform rain where the melting process usually occurs below 0 C isotherm over a distance of about 500m. To simulate this radar signature, a scattering model of melting snow is proposed in which the fractional water content is prescribed as a function of the radius of a spherical mixed- phase particle consisting of air, ice and water. The model is based on the observation that melting starts at the surface of the particle and then gradually develops towards the center. To compute the scattering parameters of a non-uniform melting particle, the particle is modeled as a sphere represented by a collection of 64(exp 3) cubic cells of identical size where the probability of water at any cell is prescribed as a function of the radius. The internal field of the particle, used for deriving the effective dielectric constant, is computed by the Conjugate Gradient and Fast Fourier Transform (CGFFT) numerical methods. To make computations of the scattering parameters more efficient, a multi-layer stratified-sphere scattering model is introduced after demonstrating that the scattering parameters of the non-uniformly melting particle can be accurately reproduced by the stratified sphere. In conjunction with a melting layer model that describes the melting fractions and fall velocities of hydrometeors as a function of the distance from the 0 C isotherm, the stratified-sphere model is used to simulate the radar bright band profiles. These simulated profiles are shown to compare well with measurements from the Precipitation Radar (PR) aboard the Tropical Rainfall Measuring Mission (TRMM) satellite and a dual-wavelength airborne radar. The results suggest that the proposed model of a melting snow particle may be useful in studying the characteristics of the bright-band in particular and mixed- phase hydrometeors in general.

Computer simulations of liquid crystals: Defects, deformations and dynamics

NASA Astrophysics Data System (ADS)

Billeter, Jeffrey Lee

1999-11-01

Computer simulations play an increasingly important role in investigating fundamental issues in the physics of liquid crystals. Presented here are the results of three projects which utilize the unique power of simulations to probe questions which neither theory nor experiment can adequately answer. Throughout, we use the (generalized) Gay-Berne model, a widely-used phenomenological potential which captures the essential features of the anisotropic mesogen shapes and interactions. First, we used a Molecular Dynamics simulation with 65536 Gay-Berne particles to study the behaviors of topological defects in a quench from the isotropic to the nematic phase. Twist disclination loops were the dominant defects, and we saw evidence for dynamical scaling. We observed the loops separating, combining and collapsing, and we also observed numerous non-singular type-1 lines which appeared to be intimately involved with many of the loop processes. Second, we used a Molecular Dynamics simulation of a sphere embedded in a system of 2048 Gay-Berne particles to study the effects of radial anchoring of the molecules at the sphere's surface. A saturn ring defect configuration was observed, and the ring caused a driven sphere (modelling the falling ball experiment) to experience an increased resistance as it moved through the nematic. Deviations from a linear relationship between the driving force and the terminal speed are attributed to distortions of the saturn ring which we observed. The existence of the saturn ring confirms theoretical predictions for small spheres. Finally, we constructed a model for wedge-shaped molecules and used a linear response approach in a Monte Carlo simulation to investigate the flexoelectric behavior of a system of 256 such wedges. Novel potential models as well as novel analytical and visualization techniques were developed for these projects. Once again, the emphasis throughout was to investigate questions which simulations alone can adequately answer.

Torsional Alfvén Waves in a Dipolar Magnetic Field

NASA Astrophysics Data System (ADS)

Nataf, H. C.; Tigrine, Z.; Cardin, P.; Schaeffer, N.

2017-12-01

The discovery of torsional Alfvén waves in the Earth's core (Gillet et al, 2010) is a strong motivation for investigating the properties of these waves. Here, we report on the first experimental study of such waves. Alfvén waves are difficult to excite and observe in liquid metals because of their high magnetic diffusivity. Nevertheless, we obtained clear signatures of such diffusive waves in our DTS experiment. In this setup, some 40 liters of liquid sodium are contained between a ro = 210 mm-radius stainless steel outer shell, and a ri = 74 mm-radius copper inner sphere. Both spherical boundaries can rotate independently around a common vertical axis. The inner sphere shells a strong permanent magnet, which produces a nearly dipolar magnetic field whose intensity falls from 175 mT at ri to 8 mT at ro in the equatorial plane. We excite Alfvén waves in the liquid sodium by applying a sudden jerk of the inner sphere. To study the effect of global rotation, which leads to the formation of geostrophic torsional Alfvén waves, we spin the experiment at rotation rates fo = fi up to 15 Hz. The Alfvén wave produces a clear azimuthal magnetic signal on magnetometers installed in a sleeve inside the fluid. We also probe the associated azimuthal velocity field using ultrasound Doppler velocimetry. Electric potentials at the surface of the outer sphere turn out to be very revealing as well. In parallel, we use the XSHELLS magnetohydrodynamics spherical code to model torsional Alfvén waves in the experimental conditions, and beyond. We explore both linear and non-linear regimes. We observe a strong excitation of inertial waves in the equatorial plane, where the wave transits from a region of strong magnetic field to a region dominated by rotation (see figure of meridian map of azimuthal velocity). These novel observations should help deciphering the dynamics of Alfvén waves in planetary cores.

Hyperfine coupling constants on inner-sphere water molecules of Gd(III)-based MRI contrast agents.

PubMed

Esteban-Gómez, David; de Blas, Andrés; Rodríguez-Blas, Teresa; Helm, Lothar; Platas-Iglesias, Carlos

2012-11-12

Herein we present a theoretical investigation of the hyperfine coupling constants (HFCCs) on the inner-sphere water molecules of [Gd(H(2)O)(8)](3+) and different Gd(III)-based magnetic resonance imaging contrast agents such as [Gd(DOTA)(H(2)O)](-), [Gd(DTPA)(H(2)O)](2-), [Gd(DTPA-BMA)(H(2)O)] and [Gd(HP-DO3A)(H(2)O)]. DFT calculations performed on the [Gd(H(2)O)(8)](3+) model system show that both hybrid-GGA functionals (BH&HLYP, B3PW91 and PBE1PBE) and the hybrid meta-GGA functional TPSSh provide (17)O HFCCs in close agreement with the experimental data. The use of all-electron relativistic approaches based on the DKH2 approximation and the use of relativistic effective core potentials (RECP) provide results of essentially the same quality. The accurate calculation of HFCCs on the [Gd(DOTA)(H(2)O)](-), [Gd(DTPA)(H(2)O)](2-), [Gd(DTPA-BMA)(H(2)O)] and [Gd(HP-DO3A)(H(2)O)] complexes requires an adequate description of solvent effects. This was achieved by using a mixed cluster/continuum approach that includes explicitly two second-sphere water molecules. The calculated isotropic (17)O HFCCs (A(iso)) fall within the range 0.40-0.56 MHz, and show deviations from the corresponding experimental values typically lower than 0.05 MHz. The A(iso) values are significantly affected by the distance between the oxygen atom of the coordinated water molecule and the Gd(III) ion, as well as by the orientation of the water molecule plane with respect to the Gd-O vector. (1)H HFCCs of coordinated water molecules and (17)O HFCCs of second-sphere water molecules take values close to zero. Copyright © 2012 WILEY-VCH Verlag GmbH & Co. KGaA, Weinheim.

SpaceX leading investigation of mishap on This Week @NASA – July 3, 2015

NASA Image and Video Library

2015-07-03

SpaceX, with Federal Aviation Administration oversight, is leading the investigation of what caused the June 28 mishap shortly after the company’s Falcon 9 rocket and Dragon cargo spacecraft launched from Cape Canaveral Air Force Station in Florida. The flight was SpaceX’s seventh contracted resupply mission to the International Space Station. Although important supplies and cargo were lost aboard the Dragon, the station crew has sufficient supplies into the Fall. Also, Progress on crew access tower at Cape, New Horizons’ final flight path, Forever Remembered exhibit, Health and Safety Fair and NASA Week and the Essence Festival!

STS-121/Discovery: Imagery Quick-Look Briefing

NASA Technical Reports Server (NTRS)

2006-01-01

Kyle Herring (NASA Public Affairs) introduced Wayne Hale (Space Shuttle Program Manager) who stated that the imagery for the Space shuttle external tank showed the tank performed very well. Image analysis showed small pieces of foam falling off the rocket booster and external tank. There was no risk involved in these minor incidents. Statistical models were built to assist in risk analysis. The orbiter performed excellently. Wayne also provided some close-up pictures of small pieces of foam separating from the external tank during launching. He said the crew will also perform a 100% inspection of the heat shield. This flight showed great improvement over previous flights.

Auroral-particle precipitation and trapping caused by electrostatic double layers in the ionosphere.

PubMed

Albert, R D; Lindstrom, P J

1970-12-25

Interpretation of high-resolution angular distribution measurements of the primary auroral electron flux detected by a rocket probe launched into a visible aurora from Fort Churchill in the fall of 1966 leads to the following conclusions. The auroral electron flux is nearly monoenergetic and has a quasi-trapped as well as a precipitating component. The quasi-trapped flux appears to be limited to a region defined by magnetic-mirror points and multiple electrostatic double layers in the ionosphere. The electrostatic field of the double-layer distribution enhances the aurora by lowering the magnetic-mirror points and supplying energy to the primary auroral electrons.

KSC-00pp1267

NASA Image and Video Library

2000-09-08

KENNEDY SPACE CENTER, Fla. -- Space Shuttle Atlantis appears to burst forth from a cocoon of smoke as it rockets toward space on mission STS-106. The perfect on-time liftoff of Atlantis occurred at 8:45:47 a.m. EDT. On the 11-day mission to the International Space Station, the seven-member crew will perform support tasks on orbit, transfer supplies and prepare the living quarters in the newly arrived Zvezda Service Module. The first long-duration crew, dubbed “Expedition One,” is due to arrive at the Station in late fall. Landing of Atlantis is targeted for 4:45 a.m. EDT on Sept. 19

KSC-00pd1263

NASA Image and Video Library

2000-09-08

KENNEDY SPACE CENTER, Fla. -- Filling the ground with billows of smoke and steam created by the flaming solid rocket boosters, Space Shuttle Atlantis speeds toward space on mission STS-106. The perfect on-time liftoff occurred at 8:45:47 a.m. EDT. On the 11-day mission to the International Space Station, the seven-member crew will perform support tasks on orbit, transfer supplies and prepare the living quarters in the newly arrived Zvezda Service Module. The first long-duration crew, dubbed “Expedition One,” is due to arrive at the Station in late fall. Landing of Atlantis is targeted for 4:45 a.m. EDT on Sept. 19

Protective factors and predictors of vulnerability to chronic stress: a comparative study of 4 communities after 7 years of continuous rocket fire.

PubMed

Gelkopf, Marc; Berger, Rony; Bleich, Avraham; Silver, Roxane Cohen

2012-03-01

Many communities across the world are chronically exposed to extreme violence. Responses of residents from a city and rural community in Southern Israel, both exposed to 7 years of daily mortar fire, were compared to residents from demographically, socio-economically and geographically comparable non-exposed control samples to examine protective factors and predictors of vulnerability to chronic war-related attacks. Samples from a highly exposed city (Sderot) and a highly exposed rural community region (Otef Aza), along with a demographically comparable comparison non-exposed city (Ofakim) and non-exposed rural community region (Hevel Lachish), were obtained in 2007 using Random Digit Dialing. In total, 740 individuals (81.8% participation rate) were interviewed about trauma exposure, mental health, functioning and health care utilization. In the highly exposed city of Sderot, 97.8% of residents had been in close proximity to falling rockets; in the highly exposed rural community region of Otef Aza, 95.5% were similarly exposed. Despite exposure to chronic rocket attacks, residents of Otef Aza evidenced little symptomatology: only one person (1.5%) reported symptoms consistent with probable posttraumatic stress disorder (PTSD) and functioning levels did not differ from those of non-exposed communities. In contrast, posttraumatic stress (PTS), distress, functional impairment and health care utilization were substantially higher in the highly exposed city of Sderot than the other three communities. Lack of resources was associated with increased vulnerability among city residents; predictors of PTS across all samples included being female, older, directly exposed to rockets, history of trauma, suffering economic loss, and lacking social support. Increased community solidarity, sense of belonging and confidence in authorities may have served a protective function for residents of rural communities, despite the chronic attacks to which they were exposed. Copyright © 2011 Elsevier Ltd. All rights reserved.

The construction of combinatorial manifolds with prescribed sets of links of vertices

NASA Astrophysics Data System (ADS)

Gaifullin, A. A.

2008-10-01

To every oriented closed combinatorial manifold we assign the set (with repetitions) of isomorphism classes of links of its vertices. The resulting transformation \\mathcal{L} is the main object of study in this paper. We pose an inversion problem for \\mathcal{L} and show that this problem is closely related to Steenrod's problem on the realization of cycles and to the Rokhlin-Schwartz-Thom construction of combinatorial Pontryagin classes. We obtain a necessary condition for a set of isomorphism classes of combinatorial spheres to belong to the image of \\mathcal{L}. (Sets satisfying this condition are said to be balanced.) We give an explicit construction showing that every balanced set of isomorphism classes of combinatorial spheres falls into the image of \\mathcal{L} after passing to a multiple set and adding several pairs of the form (Z,-Z), where -Z is the sphere Z with the orientation reversed. Given any singular simplicial cycle \\xi of a space X, this construction enables us to find explicitly a combinatorial manifold M and a map \\varphi\\colon M\\to X such that \\varphi_* \\lbrack M \\rbrack =r[\\xi] for some positive integer r. The construction is based on resolving singularities of \\xi. We give applications of the main construction to cobordisms of manifolds with singularities and cobordisms of simple cells. In particular, we prove that every rational additive invariant of cobordisms of manifolds with singularities admits a local formula. Another application is the construction of explicit (though inefficient) local combinatorial formulae for polynomials in the rational Pontryagin classes of combinatorial manifolds.

Energy and pitch angle-dispersed auroral electrons suggesting a time-variable, inverted-V potential structure

NASA Astrophysics Data System (ADS)

Arnoldy, R. L.; Lynch, K. A.; Austin, J. B.; Kintner, P. M.

1999-10-01

High temporal resolution electron detectors aboard the PHAZE II rocket flight have shown that the energy-dispersed, field-aligned bursts (FABs) are time coincident with pitch angle-dispersed electrons having energies at the maximum voltage of the inverted-V potential. This modulation of the energetic inverted-V electrons is superimposed upon an energy-diffused background resulting in a peak-to-valley ratio of ~2 for the pitch angle-dispersed electrons. Since the characteristic energy of the FABs, the order of an eV, is considerably less than that of the plasma sheet electrons (the order of a keV) presumably falling through the inverted-V potential to create the discrete aurora, the modulation mechanism has to be independent of the electron temperature. The mechanism must accelerate the cold electrons over a range of energies from the inverted-V energy down to a few tens of eV. It must do this at the same time it is creating a population of hot, pitch angle-dispersed electrons at the inverted-V energy. Both the energy dispersion of the FABs and the pitch angle dispersion of the inverted-V electrons can be used to determine a source height assuming both populations start from the same source region at the same time. These calculations give source heights between 3500 and 5300 km for various events and disagreement between the two methods the order of 20%, which is within the rather substantial error limits of both calculations. A simple mechanism of providing a common start time for both populations of electrons would be a turning on/off of a spatially limited (vertically), inverted-V potential. The energy-dispersed FABs can be reconstructed at rocket altitudes if one assumes that cold electrons are accelerated to an energy determined by how much of the inverted-V potential they fall through when it is turned on. Similarly, the pitch angle-dispersed, inverted-V electrons can be modeled at rocket altitudes if one assumes that the plasma sheet electrons falling through the entire potential drop all start to do so at the same time when the potential is turned on. The FABs seem to fluctuate at either ~10 Hz or near 100 Hz. An important constraint of the on/off mechanism is whether cold electrons (1 eV) can fill the inverted-V volume during the off cycle. The maximum vertical height of the 10 kV potential region for the 10 Hz events would be the order of 100 and 10 km for the 100 Hz events. To get 10 kV, these heights require parallel electric fields of 0.1 and 1 V/m respectively for the 10 and 100 Hz events assuming that the filling is along B from below the inverted-V potential. Alternative mechanisms are also discussed in the light of the data presented.

The Fall in Older Adults: Physical and Cognitive Problems.

PubMed

Laurence, Bernard Demanze; Michel, Lacour

2017-01-01

The aging of posture and balance function alters the quality of life in older people and causes serious problems in terms of public health and socio-economic costs for our modern societies. This article reviews the various causes of imbalance and dizziness in the elderly, and considers how to prevent falls, and how to rehabilitate a faller subject in order to regain a good quality of life. Two effective ways of intervention are discussed, emphasizing the crucial role of physical activity and cognitive stimulation, classic or using the latest technical advances in virtual reality and video games. Fall in the elderly result from aging mechanisms acting on both the sensorimotor and cognitive spheres. The structural and functional integrity of the peripheral sensory receptors and the musculoskeletal system deteriorate with age. The brain ages and the executive functions, memory, learning, cortical processing of information, sharing of attentional resources and concentration, are modified in the elderly. Psychological affective factors such as depression, anxiety and stress contribute also to speed up the sensorimotor and cognitive decline. The rehabilitation of the postural balance in the elderly must take into account all of these components. The aging of the population and the increased of lifespan are a challenge for our modern societies regarding the major health and socio-economic questions they raise. The fall in the elderly being one of the dramatic consequences of the aging equilibration function, it is therefore imperative to develop rehabilitation procedures of balance. Copyright© Bentham Science Publishers; For any queries, please email at epub@benthamscience.org.

Ares I-X: On the Threshold of Exploration

NASA Technical Reports Server (NTRS)

Davis, Stephan R.; Askins, Bruce

2009-01-01

Ares I-X, the first flight of the Ares I crew launch vehicle, is less than a year from launch. Ares I-X will test the flight characteristics of Ares I from liftoff to first stage separation and recovery. The flight also will demonstrate the computer hardware and software (avionics) needed to control the vehicle; deploy the parachutes that allow the first stage booster to land in the ocean safely; measure and control how much the rocket rolls during flight; test and measure the effects of first stage separation; and develop and try out new ground handling and rocket stacking procedures in the Vehicle Assembly Building (VAB) and first stage recovery procedures at Kennedy Space Center (KSC) in Florida. All Ares I-X major elements have completed their critical design reviews, and are nearing final fabrication. The first stage--four-segment solid rocket booster from the Space Shuttle inventory--incorporates new simulated forward structures to match the Ares I five-segment booster. The upper stage, Orion crew module, and launch abort system will comprise simulator hardware that incorporates developmental flight instrumentation for essential data collection during the mission. The upper stage simulator consists of smaller cylindrical segments, which were transported to KSC in fall 2008. The crew module and launch abort system simulator were shipped in December 2008. The first stage hardware, active roll control system (RoCS), and avionics components will be delivered to KSC in 2009. This paper will provide detailed statuses of the Ares I-X hardware elements as NASA's Constellation Program prepares for this first flight of a new exploration era in the summer of 2009.

KSC-02pd2030

NASA Image and Video Library

2002-10-23

KENNEDY SPACE CENTER, FLA. - The first stage of a Delta II rocket arrives at NASA's Space Launch Complex 2 (SLC-2) at Vandenberg Air Force Base, Calif. The rocket will carry the ICESat and CHIPSat satellites into Earth orbits. ICESat is a 661-pound satellite known as Geoscience Laser Altimeter System (GLAS) that will revolutionize our understanding of ice and its role in global climate change and how we protect and understand our home planet. It will help scientists determine if the global sea level is rising or falling. It will look at the ice sheets that blanket the Earth's poles to see if they are growing or shrinking. It will assist in developing an understanding of how changes in the Earth's atmosphere and climate effect polar ice masses and global sea level. CHIPSat, a suitcase-size 131-pound satellite, will provide invaluable information into the origin, physical processes and properties of the hot gas contained in the interstellar medium. This can provide important clues about the formation and evolution of galaxies since the interstellar medium literally contains the seeds of future stars. The Delta II launch is scheduled for Jan. 11 between 4:45 p.m. - 5:30 p.m. PST.

KSC-02pd2032

NASA Image and Video Library

2002-10-23

KENNEDY SPACE CENTER, FLA. - Workers at NASA's Space Launch Complex 2 (SLC-2) at Vandenberg Air Force Base, Calif., watch as the first stage of the Delta II rocket is raised to a vertical position. The rocket will carry the ICESat and CHIPSat satellites into Earth orbits. ICESat is a 661-pound satellite known as Geoscience Laser Altimeter System (GLAS) that will revolutionize our understanding of ice and its role in global climate change and how we protect and understand our home planet. It will help scientists determine if the global sea level is rising or falling. It will look at the ice sheets that blanket the Earth's poles to see if they are growing or shrinking. It will assist in developing an understanding of how changes in the Earth's atmosphere and climate effect polar ice masses and global sea level. CHIPSat, a suitcase-size 131-pound satellite, will provide invaluable information into the origin, physical processes and properties of the hot gas contained in the interstellar medium. This can provide important clues about the formation and evolution of galaxies since the interstellar medium literally contains the seeds of future stars. The Delta II launch is scheduled for Jan. 11 between 4:45 p.m. - 5:30 p.m. PST.

KSC-02pd2046

NASA Image and Video Library

2002-10-23

KENNEDY SPACE CENTER, FLA. - On the launch tower on NASA's Space Launch Complex 2 (SLC-2), Vandenberg Air Force Base, Calif., the second stage of a Delta II rocket sits mated with the first stage. The rocket will carry the ICESat and CHIPSat satellites into Earth orbits. ICESat is a 661-pound satellite known as Geoscience Laser Altimeter System (GLAS) that will revolutionize our understanding of ice and its role in global climate change and how we protect and understand our home planet. It will help scientists determine if the global sea level is rising or falling. It will look at the ice sheets that blanket the Earth's poles to see if they are growing or shrinking. It will assist in developing an understanding of how changes in the Earth's atmosphere and climate effect polar ice masses and global sea level. CHIPSat, a suitcase-size 131-pound satellite, will provide invaluable information into the origin, physical processes and properties of the hot gas contained in the interstellar medium. This can provide important clues about the formation and evolution of galaxies since the interstellar medium literally contains the seeds of future stars. The Delta II launch is scheduled for Jan. 11 between 4:45 p.m. - 5:30 p.m. PST.

KSC-02pd2036

NASA Image and Video Library

2002-10-23

KENNEDY SPACE CENTER, FLA. - The first stage of the Delta II rocket is ready to be lifted up the tower on NASA's Space Launch Complex 2 (SLC-2), Vandenberg Air Force Base, Calif. The rocket will carry the ICESat and CHIPSat satellites into Earth orbits. ICESat is a 661-pound satellite known as Geoscience Laser Altimeter System (GLAS) that will revolutionize our understanding of ice and its role in global climate change and how we protect and understand our home planet. It will help scientists determine if the global sea level is rising or falling. It will look at the ice sheets that blanket the Earth's poles to see if they are growing or shrinking. It will assist in developing an understanding of how changes in the Earth's atmosphere and climate effect polar ice masses and global sea level. CHIPSat, a suitcase-size 131-pound satellite, will provide invaluable information into the origin, physical processes and properties of the hot gas contained in the interstellar medium. This can provide important clues about the formation and evolution of galaxies since the interstellar medium literally contains the seeds of future stars. The Delta II launch is scheduled for Jan. 11 between 4:45 p.m. - 5:30 p.m. PST.

KSC-02pd2038

NASA Image and Video Library

2002-10-23

KENNEDY SPACE CENTER, FLA. - The interstage of the Delta II rocket arrives at NASA's Space Launch Complex 2 (SLC-2), Vandenberg Air Force Base, Calif. The rocket will carry the ICESat and CHIPSat satellites into Earth orbits. ICESat is a 661-pound satellite known as Geoscience Laser Altimeter System (GLAS) that will revolutionize our understanding of ice and its role in global climate change and how we protect and understand our home planet. It will help scientists determine if the global sea level is rising or falling. It will look at the ice sheets that blanket the Earth's poles to see if they are growing or shrinking. It will assist in developing an understanding of how changes in the Earth's atmosphere and climate effect polar ice masses and global sea level. CHIPSat, a suitcase-size 131-pound satellite, will provide invaluable information into the origin, physical processes and properties of the hot gas contained in the interstellar medium. This can provide important clues about the formation and evolution of galaxies since the interstellar medium literally contains the seeds of future stars. The Delta II launch is scheduled for Jan. 11 between 4:45 p.m. - 5:30 p.m. PST.

KSC-02pd2037

NASA Image and Video Library

2002-10-23

KENNEDY SPACE CENTER, FLA. - The first stage of the Delta II rocket is moved into place in the tower on NASA's Space Launch Complex 2 (SLC-2), Vandenberg Air Force Base, Calif. The rocket will carry the ICESat and CHIPSat satellites into Earth orbits. ICESat is a 661-pound satellite known as Geoscience Laser Altimeter System (GLAS) that will revolutionize our understanding of ice and its role in global climate change and how we protect and understand our home planet. It will help scientists determine if the global sea level is rising or falling. It will look at the ice sheets that blanket the Earth's poles to see if they are growing or shrinking. It will assist in developing an understanding of how changes in the Earth's atmosphere and climate effect polar ice masses and global sea level. CHIPSat, a suitcase-size 131-pound satellite, will provide invaluable information into the origin, physical processes and properties of the hot gas contained in the interstellar medium. This can provide important clues about the formation and evolution of galaxies since the interstellar medium literally contains the seeds of future stars. The Delta II launch is scheduled for Jan. 11 between 4:45 p.m. - 5:30 p.m. PST.

KSC-02pd2033

NASA Image and Video Library

2002-10-23

KENNEDY SPACE CENTER, FLA. - The first stage of the Delta II rocket is raised to a vertical position at NASA's Space Launch Complex 2 (SLC-2) at Vandenberg Air Force Base, Calif. The rocket will carry the ICESat and CHIPSat satellites into Earth orbits. ICESat is a 661-pound satellite known as Geoscience Laser Altimeter System (GLAS) that will revolutionize our understanding of ice and its role in global climate change and how we protect and understand our home planet. It will help scientists determine if the global sea level is rising or falling. It will look at the ice sheets that blanket the Earth's poles to see if they are growing or shrinking. It will assist in developing an understanding of how changes in the Earth's atmosphere and climate effect polar ice masses and global sea level. CHIPSat, a suitcase-size 131-pound satellite, will provide invaluable information into the origin, physical processes and properties of the hot gas contained in the interstellar medium. This can provide important clues about the formation and evolution of galaxies since the interstellar medium literally contains the seeds of future stars. The Delta II launch is scheduled for Jan. 11 between 4:45 p.m. - 5:30 p.m. PST.

KSC-02pd2044

NASA Image and Video Library

2002-10-23

KENNEDY SPACE CENTER, FLA. - Workers on the launch tower on NASA's Space Launch Complex 2 (SLC-2), Vandenberg Air Force Base, Calif., help guide the interstage of the Delta II rocket toward the first stage. The rocket will carry the ICESat and CHIPSat satellites into Earth orbits. ICESat is a 661-pound satellite known as Geoscience Laser Altimeter System (GLAS) that will revolutionize our understanding of ice and its role in global climate change and how we protect and understand our home planet. It will help scientists determine if the global sea level is rising or falling. It will look at the ice sheets that blanket the Earth's poles to see if they are growing or shrinking. It will assist in developing an understanding of how changes in the Earth's atmosphere and climate effect polar ice masses and global sea level. CHIPSat, a suitcase-size 131-pound satellite, will provide invaluable information into the origin, physical processes and properties of the hot gas contained in the interstellar medium. This can provide important clues about the formation and evolution of galaxies since the interstellar medium literally contains the seeds of future stars. The Delta II launch is scheduled for Jan. 11 between 4:45 p.m. - 5:30 p.m. PST.

Development and Validation of a Computational Model for Predicting the Behavior of Plumes from Large Solid Rocket Motors

NASA Technical Reports Server (NTRS)

Wells, Jason E.; Black, David L.; Taylor, Casey L.

2013-01-01

Exhaust plumes from large solid rocket motors fired at ATK's Promontory test site carry particulates to high altitudes and typically produce deposits that fall on regions downwind of the test area. As populations and communities near the test facility grow, ATK has become increasingly concerned about the impact of motor testing on those surrounding communities. To assess the potential impact of motor testing on the community and to identify feasible mitigation strategies, it is essential to have a tool capable of predicting plume behavior downrange of the test stand. A software package, called PlumeTracker, has been developed and validated at ATK for this purpose. The code is a point model that offers a time-dependent, physics-based description of plume transport and precipitation. The code can utilize either measured or forecasted weather data to generate plume predictions. Next-Generation Radar (NEXRAD) data and field observations from twenty-three historical motor test fires at Promontory were collected to test the predictive capability of PlumeTracker. Model predictions for plume trajectories and deposition fields were found to correlate well with the collected dataset.

Partial gravity reaction experiment sysytem on graund using multi-Copter

NASA Astrophysics Data System (ADS)

Hasegawa, Katsuya; Maeda, Naoko

2016-07-01

In order to enable further space exploration into the space, Moon, Mars, and other planets, it is essential to understand the physiological response to low gravity environments. However, We made low gravity environment for studies using the satellite parabolic flight and drop tower. It is very expensive experiment that low gravity physiological response. Because, it requires rockets and airplanes and dedicated Tower, low gravity conditions test have not been conducted sufficiently due to the extraordinary high cost for conducting experiments. The study present is to develop the radio-controlled multicopter system that is used for the controlled falling flight vehicle (not free fall). During the controlled falling, the payload is exposed to a certain level of low gravity. 1) G profile: low gravity from 0 g to 1 g that will last approximately 5seconds, 50 kg. 2) Supply limited imaging techniques, high-speed or normal video and X ray images. 3) Wireless transmission of up to 64 channels of analog and digital signals. This vehicle is designed for experimentation on various model organisms, from cells to animals and plants. The multicopter flight system enables conducting experiments in low gravity conditions with less than 1% of the budget for spaceflight or parabolic flights. Experiment is possible to perform repeated many times in one day. We can expect reproducible results from many repeated trials at the lowest cost.

STS-45 external tank (ET) falls back to Earth after jettisoning from OV-104

NASA Image and Video Library

1992-03-24

STS045-71-001 (24 March 1992) --- This 70mm photograph of the external fuel tank (ET) for STS-45 was photographed 4 1/2 minutes after having been jettisoned from Space Shuttle Atlantis. The excellent view of the starboard side of the ET shows both top and bottom attach points to the two solid rocket boosters (SRB). NASA engineers studying the STS-45 onboard photography deem the visible burn scars, caused by the SRBs, to be normal. The long thin pipe visible is the liquid oxygen line. At the bottom end of the large tank, both the liquid oxygen (nearest camera) and liquid hydrogen orbiter-to-ET attach hardware can be seen.

KSC-2010-4941

NASA Image and Video Library

2010-09-30

CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, the rotating service structure (RSS) on Launch Pad 39B is being dismantled. Sand, reinforcing steel and large wooden mats were put down under the RSS to protect the structure's concrete from falling debris during deconstruction. Starting in 2009, the structure at the pad was no longer needed for NASA's Space Shuttle Program, so it is being restructured for future use. The new design will feature a "clean pad" for rockets to come with their own launcher, making it more versatile for a number of vehicles. The new lightning protection system, consisting of three lightning towers and a wire catenary system will remain. Photo credit: NASA/Jim Grossmann

KSC-2010-4942

NASA Image and Video Library

2010-09-30

CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, crews are dismantling the rotating service structure (RSS) on Launch Pad 39B. Sand, reinforcing steel and large wooden mats were put down under the RSS to protect the structure's concrete from falling debris during deconstruction. Starting in 2009, the structure at the pad was no longer needed for NASA's Space Shuttle Program, so it is being restructured for future use. The new design will feature a "clean pad" for rockets to come with their own launcher, making it more versatile for a number of vehicles. The new lightning protection system, consisting of three lightning towers and a wire catenary system will remain. Photo credit: NASA/Jim Grossmann

KSC-2010-4946

NASA Image and Video Library

2010-09-30

CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, crews are dismantling the rotating service structure (RSS) on Launch Pad 39B. Sand, reinforcing steel and large wooden mats were put down under the RSS to protect the structure's concrete from falling debris during deconstruction. Starting in 2009, the structure at the pad was no longer needed for NASA's Space Shuttle Program, so it is being restructured for future use. The new design will feature a "clean pad" for rockets to come with their own launcher, making it more versatile for a number of vehicles. The new lightning protection system, consisting of three lightning towers and a wire catenary system will remain. Photo credit: NASA/Jim Grossmann

KSC-2010-4944

NASA Image and Video Library

2010-09-30

CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, crews are dismantling the rotating service structure (RSS) on Launch Pad 39B. Sand, reinforcing steel and large wooden mats were put down under the RSS to protect the structure's concrete from falling debris during deconstruction. Starting in 2009, the structure at the pad was no longer needed for NASA's Space Shuttle Program, so it is being restructured for future use. The new design will feature a "clean pad" for rockets to come with their own launcher, making it more versatile for a number of vehicles. The new lightning protection system, consisting of three lightning towers and a wire catenary system will remain. Photo credit: NASA/Jim Grossmann

KSC-2010-4943

NASA Image and Video Library

2010-09-30

CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, the rotating service structure (RSS) on Launch Pad 39B is being dismantled. Sand, reinforcing steel and large wooden mats were put down under the RSS to protect the structure's concrete from falling debris during deconstruction. Starting in 2009, the structure at the pad was no longer needed for NASA's Space Shuttle Program, so it is being restructured for future use. The new design will feature a "clean pad" for rockets to come with their own launcher, making it more versatile for a number of vehicles. The new lightning protection system, consisting of three lightning towers and a wire catenary system will remain. Photo credit: NASA/Jim Grossmann

KSC-2010-4945

NASA Image and Video Library

2010-09-30

CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, the rotating service structure (RSS) on Launch Pad 39B is being dismantled. Sand, reinforcing steel and large wooden mats were put down under the RSS to protect the structure's concrete from falling debris during deconstruction. Starting in 2009, the structure at the pad was no longer needed for NASA's Space Shuttle Program, so it is being restructured for future use. The new design will feature a "clean pad" for rockets to come with their own launcher, making it more versatile for a number of vehicles. The new lightning protection system, consisting of three lightning towers and a wire catenary system will remain. Photo credit: NASA/Jim Grossmann

KSC-2010-4987

NASA Image and Video Library

2010-10-04

CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, crews continue dismantling the rotating service structure (RSS) on Launch Pad 39B. Sand, reinforcing steel and large wooden mats were put down under the RSS to protect the structure's concrete from falling debris during deconstruction. Starting in 2009, the structure at the pad was no longer needed for NASA's Space Shuttle Program, so it is being restructured for future use. The new design will feature a "clean pad" for rockets to come with their own launcher, making it more versatile for a number of vehicles. The new lightning protection system, consisting of three lightning towers and a wire catenary system will remain. Photo credit: NASA/Jack Pfaller

KSC-00pp1270

NASA Image and Video Library

2000-09-08

KENNEDY SPACE CENTER, Fla. -- Space Shuttle Atlantis’s solid rocket boosters trail brilliant flames that light up the clouds of smoke and steam and reflect in the waters Launch Pad 39B at launch. The perfect on-time liftoff of Atlantis on mission STS-106 occurred at 8:45:47 a.m. EDT. On the 11-day mission to the International Space Station, the seven-member crew will perform support tasks on orbit, transfer supplies and prepare the living quarters in the newly arrived Zvezda Service Module. The first long-duration crew, dubbed “Expedition One,” is due to arrive at the Station in late fall. Landing of Atlantis is targeted for 4:45 a.m. EDT on Sept. 19

KSC-00pp1269

NASA Image and Video Library

2000-09-08

KENNEDY SPACE CENTER, Fla. -- The waters near Launch Pad 39B reflect the brilliant red-orange flames from the solid rocket boosters as Space Shuttle Atlantis lifts off on mission STS-106 to the International Space Station. The perfect on-time launch occurred at 8:45:47 a.m. EDT. On the 11-day mission to the Station, the seven-member crew will perform support tasks on orbit, transfer supplies and prepare the living quarters in the newly arrived Zvezda Service Module. The first long-duration crew, dubbed “Expedition One,” is due to arrive at the Station in late fall. Landing of Atlantis is targeted for 4:45 a.m. EDT on Sept. 19.

KSC-00pp1265

NASA Image and Video Library

2000-09-08

KENNEDY SPACE CENTER, Fla. -- Bare branches frame the liftoff of Space Shuttle Atlantis on mission STS-106 to the International Space Station. Billows of smoke and steam are illuminated by the flames of the solid rocket boosters. The perfect on-time liftoff of Atlantis occurred at 8:45:47 a.m. EDT. On the 11-day mission to the International Space Station, the seven-member crew will perform support tasks on orbit, transfer supplies and prepare the living quarters in the newly arrived Zvezda Service Module. The first long-duration crew, dubbed “Expedition One,” is due to arrive at the Station in late fall. Landing of Atlantis is targeted for 4:45 a.m. EDT on Sept. 19

Apparatus and method for the production of gel beads containing a biocatalyst

DOEpatents

Scott, C.D.; Scott, T.C.; Davison, B.H.

1998-01-27

An apparatus and method are disclosed for the large-scale and continuous production of gel beads containing a biocatalyst. The apparatus is a columnar system based on the chemical cross-linking of hydrocolloidal gels that contain and immobilize a biocatalyst, the biocatalyst being a microorganism or an enzyme. Hydrocolloidal gels, such as alginate, carrageenan, and a mixture of bone gelatin and modified alginate, provide immobilization matrices that can be used to entrap and retain the biocatalyst while allowing effective contact with substrates and release of products. Such immobilized biocatalysts are generally formulated into small spheres or beads that have high concentrations of the biocatalyst within the gel matrix. The columnar system includes a gel dispersion nozzle submerged in a heated non-interacting liquid, typically an organic liquid, that is immiscible with water to allow efficient formation of spherical gel droplets, the non-interacting liquid having a specific gravity that is less than water so that the gel droplets will fall through the liquid by the force of gravity. The heated non-interacting liquid is in direct contact with a chilled upflowing non-interacting liquid that will provide sufficient residence time for the gel droplets as they fall through the liquid so that they will be cooled below the gelling temperature and form solid spheres. The upflowing non-interacting liquid is in direct contact with an upflowing temperature-controlled aqueous solution containing the necessary chemicals for cross-linking or fixing of the gel beads to add the necessary stability. The flow rates of the two liquid streams can be varied to control the proper residence time in each liquid section to accommodate the production of gel beads of differing settling velocities. A valve is provided for continuous removal of the stabilized gel beads from the bottom of the column. 1 fig.

A Physical Model to Determine Snowfall over Land by Microwave Radiometry

NASA Technical Reports Server (NTRS)

Skofronick-Jackson, G.; Kim, M.-J.; Weinman, J. A.; Chang, D.-E.

2003-01-01

Because microwave brightness temperatures emitted by snow covered surfaces are highly variable, snowfall above such surfaces is difficult to observe using window channels that occur at low frequencies (v less than 100 GHz). Furthermore, at frequencies v less than or equal to 37 GHz, sensitivity to liquid hydrometeors is dominant. These problems are mitigated at high frequencies (v greater than 100 GHz) where water vapor screens the surface emission and sensitivity to frozen hydrometeors is significant. However the scattering effect of snowfall in the atmosphere at those higher frequencies is also impacted by water vapor in the upper atmosphere. This work describes the methodology and results of physically-based retrievals of snow falling over land surfaces. The theory of scattering by randomly oriented dry snow particles at high microwave frequencies appears to be better described by regarding snow as a concatenation of equivalent ice spheres rather than as a sphere with the effective dielectric constant of an air-ice mixture. An equivalent sphere snow scattering model was validated against high frequency attenuation measurements. Satellite-based high frequency observations from an Advanced Microwave Sounding Unit (AMSU-B) instrument during the March 5-6, 2001 New England blizzard were used to retrieve snowfall over land. Vertical distributions of snow, temperature and relative humidity profiles were derived from the Pennsylvania State University-National Center for Atmospheric Research (PSU-NCAR) fifth-generation Mesoscale Model (MM5). Those data were applied and modified in a radiative transfer model that derived brightness temperatures consistent with the AMSU-B observations. The retrieved snowfall distribution was validated with radar reflectivity measurements obtained from the National Oceanic and Atmospheric Administration (NOAA) National Weather Service (NWS) ground-based radar network.

Darwinian Controversies: An Historiographical Recounting

NASA Astrophysics Data System (ADS)

Depew, David J.

2010-05-01

This essay reviews key controversies in the history of the Darwinian research tradition: the Wilberforce-Huxley debate in 1860, early twentieth-century debates about the heritability of acquired characteristics and the consistency of Mendelian genetics with natural selection; the 1925 Scopes trial about teaching evolution; tensions about race, culture, and eugenics at the 1959 centenary celebration Darwin’s Origin of Species; adaptationism and its critics in the Sociobiology debate of 1970s and, more recently, Evolutionary Psychology; and current disputes about Intelligent Design. These controversies, I argue, are etched into public memory because they occur at the emotionally charged boundaries between public-political, technical-scientific, and personal-religious spheres of discourse. Over most of them falls the shadow of eugenics. The main lesson is that the history of Darwinism cannot be told except by showing the mutual influence of the different norms of discourse that obtain in the personal, technical, and public spheres. Nor can evolutionary biology successfully be taught to citizens and citizens-to-be until the fractious intersections between spheres of discourse have been made explicit. In the course of showing why, I take rival evolutionary approaches to be dynamical historical research traditions rather than static theories. Accordingly, I distinguish Darwin’s version of Darwinism from its later transformations. I pay special attention to the role Darwin assigned to development in evolution, which was marginalized by twentieth-century population genetical Darwinism, but has recently resurfaced in new forms. I also show how the disputed phrases “survival of the fittest” and “social Darwinism” have shaped personal anxieties about “Darwinism,” have provoked public opposition to teaching evolution in public schools, and have cast a shadow over efforts to effectively communicate to the public largely successful technical efforts to make evolutionary inquiry into a science.

3D shape of asteroid (6) Hebe from VLT/SPHERE imaging: Implications for the origin of ordinary H chondrites

NASA Astrophysics Data System (ADS)

Marsset, M.; Carry, B.; Dumas, C.; Hanuš, J.; Viikinkoski, M.; Vernazza, P.; Müller, T. G.; Delbo, M.; Jehin, E.; Gillon, M.; Grice, J.; Yang, B.; Fusco, T.; Berthier, J.; Sonnett, S.; Kugel, F.; Caron, J.; Behrend, R.

2017-08-01

Context. The high-angular-resolution capability of the new-generation ground-based adaptive-optics camera SPHERE at ESO VLT allows us to assess, for the very first time, the cratering record of medium-sized (D 100-200 km) asteroids from the ground, opening the prospect of a new era of investigation of the asteroid belt's collisional history. Aims: We investigate here the collisional history of asteroid (6) Hebe and challenge the idea that Hebe may be the parent body of ordinary H chondrites, the most common type of meteorites found on Earth ( 34% of the falls). Methods: We observed Hebe with SPHERE as part of the science verification of the instrument. Combined with earlier adaptive-optics images and optical light curves, we model the spin and three-dimensional (3D) shape of Hebe and check the consistency of the derived model against available stellar occultations and thermal measurements. Results: Our 3D shape model fits the images with sub-pixel residuals and the light curves to 0.02 mag. The rotation period (7.274 47 h), spin (ECJ2000 λ, β of 343°, +47°), and volume-equivalent diameter (193 ± 6 km) are consistent with previous determinations and thermophysical modeling. Hebe's inferred density is 3.48 ± 0.64 g cm-3, in agreement with an intact interior based on its H-chondrite composition. Using the 3D shape model to derive the volume of the largest depression (likely impact crater), it appears that the latter is significantly smaller than the total volume of close-by S-type H-chondrite-like asteroid families. Conclusions: Our results imply that (6) Hebe is not the most likely source of H chondrites. Over the coming years, our team will collect similar high-precision shape measurements with VLT/SPHERE for 40 asteroids covering the main compositional classes, thus providing an unprecedented dataset to investigate the origin and collisional evolution of the asteroid belt. Based on observations made with ESO Telescopes at the La Silla Paranal Observatory under programme ID 60.A-9379 and 086.C-0785.

STS-60 Space Shuttle mission report

NASA Technical Reports Server (NTRS)

Fricke, Robert W., Jr.

1994-01-01

The STS-60 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Redesigned Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the sixtieth flight of the Space Shuttle Program and eighteenth flight of the Orbiter vehicle Discovery (OV-103). In addition to the Orbiter, the flight vehicle consisted of an ET designated at ET-61 (Block 10); three SSME's which were designated as serial numbers 2012, 2034, and 2032 in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-062. The RSRM's that were installed in each SRB were designated as 360L035A (lightweight) for the left SRB, and 360Q035B (quarterweight) for the right SRB. This STS-60 Space Shuttle Program Mission Report fulfills the Space Shuttle Program requirement as documented in NSTS 07700, Volume VIII, Appendix E. That document requires that each major organizational element supporting the Program report the results of its hardware evaluation and mission performance plus identify all related in-flight anomalies. The primary objectives of the STS-60 mission were to deploy and retrieve the Wake Shield Facility-1 (WSF-1), and to activate the Spacehab-2 payload and perform on-orbit experiments. Secondary objectives of this flight were to activate and command the Capillary Pumped Loop/Orbital Debris Radar Calibration Spheres/Breman Satellite Experiment/Getaway Special (GAS) Bridge Assembly (CAPL/ODERACS/BREMSAT/GBA) payload, the Auroral Photography Experiment-B (APE-B), and the Shuttle Amateur Radio Experiment-II (SAREX-II).

Formation of Ordered Arrays of Proteins on Surfaces

NASA Technical Reports Server (NTRS)

Lenhoff, A. M.

1996-01-01

Van der Waals (dispersion) forces contribute to interactions of proteins with other molecules or with surfaces, but because of the structural complexity of protein molecules, the magnitude of these effects is usually estimated based on idealized models of the molecular geometry, e.g., spheres or spheroids. The calculations reported here seek to account for both the geometric irregularity of protein molecules and the material properties of the interacting media. While the latter are found to fall in the generally accepted range, the molecular shape is shown to cause the magnitudes of the interactions to differ significantly from those calculated using idealized models, with important consequences. First, the roughness of the molecular surface leads to much lower average interaction energies for both protein-protein and protein-surface cases relative to calculations in which the protein molecule is approximated as a sphere. These results indicate that a form of steric stabilization may be an important effect in protein solutions. Underlying this behavior is appreciable orientational dependence, one reflection of which is that molecules of complementary shape are found to exhibit very strong attractive dispersion interactions. Although this has been widely discussed previously in the context of molecular recognition processes, the broader implications of these phenomena may also be important at larger molecular separations, e.g., in the dynamics of aggregation, precipitation and crystal growth.

The policy of import substitution as the basis for economic security and well-being of society

NASA Astrophysics Data System (ADS)

Makasheva, Yu S.; Makasheva, N. P.; Gromova, A. S.; Andreeva, N. V.; Ishtunov, S. A.

2016-09-01

The study presents the analysis of import substitution opportunities on separate branches of economic activity, preceding the realization of import substitution policy with the aim to support national economic security, which is essential for the contemporary society welfare insurance. Currently, social well-being is considered to be the reflection of economic activity, the instrument of state influence on the society, as well as an indicator of the social security system. Due to the fact that Russia is integrated into the world economy, the foreign-economic policy currently is playing an important role in the development of national security and the state's interest to the spheres of economy considering external and internal threats. Decline in external economic conditions may result in serious consequences for the functioning and development of the country as well as for the trade and investment activities, which will further lead to the decline in export, withdrawal of capital, recession of industrial production, trade and investment sphere, fall of GDP and living standards. Thus, considering the current state of instability in the world economy and the growing political tension in relation to Russian Federation, the measures to increase economic security in the country should be taken. The policy of import substitution is considered to be one of the major solutions nowadays.

Van der Waals Interactions Involving Proteins

NASA Technical Reports Server (NTRS)

Roth, Charles M.; Neal, Brian L.; Lenhoff, Abraham M.

1996-01-01

Van der Waals (dispersion) forces contribute to interactions of proteins with other molecules or with surfaces, but because of the structural complexity of protein molecules, the magnitude of these effects is usually estimated based on idealized models of the molecular geometry, e.g., spheres or spheroids. The calculations reported here seek to account for both the geometric irregularity of protein molecules and the material properties of the interacting media. Whereas the latter are found to fall in the generally accepted range, the molecular shape is shown to cause the magnitudes of the interactions to differ significantly from those calculated using idealized models. with important consequences. First, the roughness of the molecular surface leads to much lower average interaction energies for both protein-protein and protein-surface cases relative to calculations in which the protein molecule is approximated as a sphere. These results indicate that a form of steric stabilization may be an important effect in protein solutions. Underlying this behavior is appreciable orientational dependence, one reflection of which is that molecules of complementary shape are found to exhibit very strong attractive dispersion interactions. Although this has been widely discussed previously in the context of molecular recognition processes, the broader implications of these phenomena may also be important at larger molecular separations, e.g., in the dynamics of aggregation, precipitation, and crystal growth.

Active experiments in space; Proceedings of the Topical Meeting of the Interdisciplinary Scientific Commission D (Meeting D3) of the COSPAR 28th Plenary Meeting, The Hague, Netherlands, June 25-July 6, 1990

NASA Astrophysics Data System (ADS)

Torbert, R.

1992-12-01

The present volume on active experiments in space discusses dynamic trapping of electrons in the Porcupine ionospheric ion beam experiment, plasma wave observations during electron gun experiments on ISEE-1, spatial coherence and electromagnetic wave generation during electron beam experiments in space, and recent experimental measurements of space platform charging at LEO altitudes. Attention is given to high voltage spheres in an unmagnetized plasma, energetic ion emission for active spacecraft control, the collective gyration of a heavy ion cloud in a magnetized plasma, and remote sensing of artificial luminous clouds by lidars. Topics addressed include modulation of the background flux of energetic particles by artificial injection, wave measurements in active experiments on plasma beam injection, field formation around negatively biased solar arrays in the LEO-plasma, and the registration of ELF waves in rocket-satellite experiments with plasma injection.

Ariel 6 measurements of ultra-heavy cosmic ray fluxes in the region 34 or = Z or = 48

NASA Technical Reports Server (NTRS)

Fowler, P. H.; Masheder, M. R. W.; Moses, R. T.; Walker, R. N. F.; Worley, A.; Gay, A. M.

1985-01-01

The Ariel VI satellite was launched by NASA on a Scout rocket on 3rd June 1979 from Wallops Island, Virginia, USA, into a near circular 625 km orbit inclined at 55 deg. It carried a spherical cosmic ray detector designed by a group from Bristol University. A spherical aluminum vessel of diameter 75 cm contains a gas scintillation mixture and a thin spherical shell of Pilot 425 plastic, and forms a single optical cavity viewed by 16 photomultipliers. Particle tracks through the detector may be characterized by their impact parameter p and by whether or not they pass through the cup of plastic scintillator placed between the sphere and the spacecraft body (referred to below as the Anti-Coincidence Detector or ACD). Individual particle charges are determined by separately measuring the gas scintillation and the Cerenkov emission from the plastic shell. This is possible because of the quite different distribution in time of these emissions.

KSC01padig279

NASA Image and Video Library

2001-09-29

KODIAK ISLAND, Alaska -- A Lockheed Martin Athena I launch vehicle rockets off the launch pad at Kodiak Launch Complex (KSC) with the Kodiak Star spacecraft on board. Liftoff occurred at 10:40 p.m. EDT, Sept. 29. The Kodiak Star payload consists of four satellites: PICOSat, PCSat, Sapphire and Starshine 3. Starshine is sponsored by NASA. The 200-pound sphere will be used by students to study orbital decay. The other three satellites, also on educational missions, are sponsored by the department of defense. PICOSat is a technology demonstration satellite with four experiments on board. PCSat was designed by midshipmen at the U.S. Naval Academy, and will become part of the amateur radio community's automatic position reporting system. Sapphire is a micro-satellite built by students at Stanford University and Washington University - St. Louis to test infrared sensors for space use. KLC is the newest commercial launch complex in the United States, ideal for launch payloads requiring low-Earth polar or sun-synchronous orbits

Wind structure and small-scale wind variability in the stratosphere and mesosphere during the November 1980 Energy Budget Campaign

NASA Technical Reports Server (NTRS)

Schmidlin, F. J.; Carlson, M.; Rees, D.; Offermann, D.; Philbrick, C. R.; Widdel, H. U.

1982-01-01

Rocket observations made from two sites in northern Scandinavia between November 6 and December 1, 1980, as part of the Energy Budget Campaign are discussed. It was found that significant vertical and temporal changes in the wind structure were present and that they coincided with different geomagnetic conditions, that is, quiet and enhanced. Before November 16, the meridional wind component above 60 km was found to be positive (southerly), whereas the magnitude of the zonal wind component increased with altitude. After November 16 the meridional component became negative (northerly), and the magnitude of the zonal wind component was observed to decrease with altitude. Time sections of the perturbations of the zonal wind reveal the presence of vertically propagating waves, suggesting gravity wave activity. The waves are found to increase in wavelength from 3-4 km near 40 km to more than 12 km near 80 km. The observational techniques made use of chaff foil, chemical trails, inflatable spheres, and parachutes.

Development of an Integrated Data Acquisition System for a Small Flight Probe

NASA Technical Reports Server (NTRS)

Swanson, Gregory T.; Empey, Daniel M.; Skokova, Kristina A.; Venkatapathy, Ethiraj

2012-01-01

In support of the SPRITE concept, an integrated data acquisition system has been developed and fabricated for preliminary testing. The data acquisition system has been designed to condition traditional thermal protection system sensors, store their data to an on-board memory card, and in parallel, telemeter to an external system. In the fall of 2010, this system was integrated into a 14 in. diameter, 45 degree sphere cone probe instrumented with thermal protection system sensors. This system was then tested at the NASA Ames Research Center Aerodynamic Heating Facility's arc jet at approximately 170 W/sq. cm. The first test in December 2010 highlighted hardware design issues that were redesigned and implemented leading to a successful test in February 2011.

Advanced Power and Propulsion: Insuring Human Survival and Productivity in Deep Space Missions

NASA Technical Reports Server (NTRS)

Chang-Diaz, Franklin R.

2001-01-01

Dr. Chang-Diaz gave an intriguing presentation of his research in advanced rocket propulsion and its relevance for planning and executing crewed deep space explorations. Though not necessarily exclusively Martian, his thrust looks critically at future Mars missions. Initially Dr. Chang-Diaz showed the time constraints of Mars missions due to orbital mechanics and our present chemically powered rocket technology. Since essentially all the energy required to place current generation spacecraft into a Martian trajectory must be expended in the early minutes of a flight, most of such a mission is spent in free-fall drift, captive to the gravitational forces among Earth, the Sun, and Mars. The simple physics of such chemically powered missions requires nearly a year in transit for each direction of a Mars mission. And the optimal orientations of Earth and Mars for rendezvous require further time on or around Mars to await return. These extensions of mission duration place any crew under a three-fold jeopardy: (1) physiological deconditioning (which in some aspects is still unknown and unpreventable), (2) psychological stress, and (3) ionizing radiation. This latter risk is due to exposure of crew members for extended time to the highly unpredictable and potentially lethal radiations of open space. Any gains in shortening mission duration would reap equivalent or greater benefits for these crew concerns. Dr. Chang-Diaz has applied his training and expertise (Ph.D. from Massachusetts Institute of Technology in applied plasma physics) toward development of continuous rocket propulsion which would offer great time advantages in travel, and also more launch options than are now available. He clearly explained the enormous gains from a relatively low thrust accelerative force applied essentially continuously versus the high, but short-lived propulsion of present chemical rockets. In fact, such spacecraft could be powered throughout the mission, accelerating to approximately the midpoint and decelerating during the latter half. This would not only provide some level of gravity (acceleration) throughout the mission but also allow very high velocities to be achieved, thus saving many months of travel time. In proposing the design of such a spacecraft propulsion system, Dr. Chang-Diaz was quick to acknowledge the need for a large power source, which undoubtedly must be nuclear fueled at the solar distances involved. He calls his system the Variable Specific Impulse Magnetoplasma Rocket (VASIMR). The other major ingredient is a mass (deuterium, which could also function as a radiation shield for crews) for energizing into the ultra hot, high velocity exhaust plasma. He foresees models now functional in the laboratory soon to be tested in space. In fact, some of these concepts have already been tried there. His optimism and determination would have operational rockets in the next decades.

Turbopump options for nuclear thermal rockets

NASA Astrophysics Data System (ADS)

Bissell, W. R.; Gunn, S. V.

1992-07-01

Several turbopump options for delivering liquid nitrogen to nuclear thermal rocket (NTR) engines were evaluated and compared. Axial and centrifugal flow pumps were optimized, with and without boost pumps, utilizing current design criteria within the latest turbopump technology limits. Two possible NTR design points were used, a modest pump pressure rise of 1,743 psia and a relatively higher pump pressure rise of 4,480 psia. Both engines utilized the expander cycle to maximize engine performance for the long duration mission. Pump suction performance was evaluated. Turbopumps with conventional cavitating inducers were compared with zero NPSH (saturated liquid in the tanks) pumps over a range of tank saturation pressures, with and without boost pumps. Results indicate that zero NSPH pumps at high tank vapor pressures, 60 psia, are very similar to those with the finite NPSHs. At low vapor pressures efficiencies fall and turbine pressure ratios increase leading to decreased engine chamber pressures and or increased pump pressure discharges and attendant high-pressure component weights. It may be concluded that zero tank NSPH capabilities can be obtained with little penalty to the engine systems but boost pumps are needed if tank vapor pressure drops below 30 psia. Axial pumps have slight advantages in weight and chamber pressure capability while centrifugal pumps have a greater operating range.

KSC-05PD-0028

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. Tugboats maneuver the barge carrying the newly redesigned External Tank, designated for use on Return to Flight mission STS-114, toward the dock at the Launch Complex 39 Area Turn Basin at Kennedy. The barge arrived after an approximately 900-mile journey at sea from the Michoud Assembly Facility in New Orleans. It left the facility Dec. 31 on the Pegasus, NASAs specially designed barge, towed by Solid Rocket Booster retrieval ship Liberty Star. At Port Canaveral, the barge was then hooked up to the tugs for the last part of the journey. Next, the External Tank will be off-loaded from the barge and transported to the Vehicle Assembly Building for its final checkout and mating to the twin Solid Rocket Boosters and orbiter Discovery. NASA and Lockheed Martin Corp. spent nearly two years modifying the 15-story, bronze-colored tank to make it safer for liftoff. Among dozens of changes is a redesigned forward bipod fitting -- a design that meets the recommendation of the Columbia Accident Investigation Board to reduce the risk to the Space Shuttle from falling debris during ascent. STS-114 is targeted for a launch opportunity beginning in May. The seven-member Discovery crew will fly to the International Space Station primarily to test and evaluate new procedures for flight safety, including Space Shuttle inspection and repair techniques.

KSC-02pd2042

NASA Image and Video Library

2002-10-23

KENNEDY SPACE CENTER, FLA. - Workers on the launch tower on NASA's Space Launch Complex 2 (SLC-2), Vandenberg Air Force Base, Calif., watch as the interstage of the Delta II rocket is lifted to a level where it can be mated with the first stage. The rocket will carry the ICESat and CHIPSat satellites into Earth orbits. ICESat is a 661-pound satellite known as Geoscience Laser Altimeter System (GLAS) that will revolutionize our understanding of ice and its role in global climate change and how we protect and understand our home planet. It will help scientists determine if the global sea level is rising or falling. It will look at the ice sheets that blanket the Earth's poles to see if they are growing or shrinking. It will assist in developing an understanding of how changes in the Earth's atmosphere and climate effect polar ice masses and global sea level. CHIPSat, a suitcase-size 131-pound satellite, will provide invaluable information into the origin, physical processes and properties of the hot gas contained in the interstellar medium. This can provide important clues about the formation and evolution of galaxies since the interstellar medium literally contains the seeds of future stars. The Delta II launch is scheduled for Jan. 11 between 4:45 p.m. - 5:30 p.m. PST.

KSC-02pd2060

NASA Image and Video Library

2002-10-25

KENNEDY SPACE CENTER, FLA. - A second stage is lifted at NASA's Space Launch Complex 2 (SLC-2) at Vandenberg Air Force Base, Calif., for placement atop a Delta II rocket. The rocket will carry the ICESat and CHIPSat satellites into Earth orbits. The Ice, Cloud, and Land Elevation Satellite, or ICESat, is a 661-pound satellite carrying the Geoscience Laser Altimeter System (GLAS) that will revolutionize our understanding of ice and its role in global climate change and how we protect and understand our home planet. It will help scientists determine if the global sea level is rising or falling. It will look at the ice sheets that blanket the Earth's poles to see if they are growing or shrinking. It will assist in developing an understanding of how changes in the Earth's atmosphere and climate effect polar ice masses and global sea level. The Cosmic Hot Interstellar Plasma Spectrometer, or CHIPSat, a suitcase-size 131-pound satellite, will provide invaluable information into the origin, physical processes and properties of the hot gas contained in the interstellar medium. This can provide important clues about the formation and evolution of galaxies since the interstellar medium literally contains the seeds of future stars. The Delta II launch is scheduled for Jan. 11, 2003, between 4:45 p.m. - 5:30 p.m. PST.

KSC-02pd2041

NASA Image and Video Library

2002-10-23

KENNEDY SPACE CENTER, FLA. - The interstage of the Delta II rocket is lifted up the launch tower on NASA's Space Launch Complex 2 (SLC-2), Vandenberg Air Force Base, Calif. The interstage will eventually house the second stage and will be mated with the first stage. The rocket will carry the ICESat and CHIPSat satellites into Earth orbits. ICESat is a 661-pound satellite known as Geoscience Laser Altimeter System (GLAS) that will revolutionize our understanding of ice and its role in global climate change and how we protect and understand our home planet. It will help scientists determine if the global sea level is rising or falling. It will look at the ice sheets that blanket the Earth's poles to see if they are growing or shrinking. It will assist in developing an understanding of how changes in the Earth's atmosphere and climate effect polar ice masses and global sea level. CHIPSat, a suitcase-size 131-pound satellite, will provide invaluable information into the origin, physical processes and properties of the hot gas contained in the interstellar medium. This can provide important clues about the formation and evolution of galaxies since the interstellar medium literally contains the seeds of future stars. The Delta II launch is scheduled for Jan. 11 between 4:45 p.m. - 5:30 p.m. PST.

KSC-02pd2061

NASA Image and Video Library

2002-10-25

KENNEDY SPACE CENTER, FLA. - A second stage is lifted into place at NASA's Space Launch Complex 2 (SLC-2) at Vandenberg Air Force Base, Calif., atop a Delta II rocket. The rocket will carry the ICESat and CHIPSat satellites into Earth orbits. The Ice, Cloud, and Land Elevation Satellite, or ICESat, is a 661-pound satellite carrying the Geoscience Laser Altimeter System (GLAS) that will revolutionize our understanding of ice and its role in global climate change and how we protect and understand our home planet. It will help scientists determine if the global sea level is rising or falling. It will look at the ice sheets that blanket the Earth's poles to see if they are growing or shrinking. It will assist in developing an understanding of how changes in the Earth's atmosphere and climate effect polar ice masses and global sea level. The Cosmic Hot Interstellar Plasma Spectrometer, or CHIPSat, a suitcase-size 131-pound satellite, will provide invaluable information into the origin, physical processes and properties of the hot gas contained in the interstellar medium. This can provide important clues about the formation and evolution of galaxies since the interstellar medium literally contains the seeds of future stars. The Delta II launch is scheduled for Jan. 11, 2003, between 4:45 p.m. - 5:30 p.m. PST.

KSC-02pd2045

NASA Image and Video Library

2002-10-23

KENNEDY SPACE CENTER, FLA. - Workers on the launch tower on NASA's Space Launch Complex 2 (SLC-2), Vandenberg Air Force Base, Calif., help guide the interstage of the Delta II rocket into position for mating with the first stage. The rocket will carry the ICESat and CHIPSat satellites into Earth orbits. ICESat is a 661-pound satellite known as Geoscience Laser Altimeter System (GLAS) that will revolutionize our understanding of ice and its role in global climate change and how we protect and understand our home planet. It will help scientists determine if the global sea level is rising or falling. It will look at the ice sheets that blanket the Earth's poles to see if they are growing or shrinking. It will assist in developing an understanding of how changes in the Earth's atmosphere and climate effect polar ice masses and global sea level. CHIPSat, a suitcase-size 131-pound satellite, will provide invaluable information into the origin, physical processes and properties of the hot gas contained in the interstellar medium. This can provide important clues about the formation and evolution of galaxies since the interstellar medium literally contains the seeds of future stars. The Delta II launch is scheduled for Jan. 11 between 4:45 p.m. - 5:30 p.m. PST.

KSC-02pd2031

NASA Image and Video Library

2002-10-23

KENNEDY SPACE CENTER, FLA. - The first stage of the Delta II rocket is in the process of being raised to a vertical position on NASA's Space Launch Complex 2 (SLC-2) at Vandenberg Air Force Base, Calif. The rocket will carry the ICESat and CHIPSat satellites into Earth orbits. ICESat is a 661-pound satellite known as Geoscience Laser Altimeter System (GLAS) that will revolutionize our understanding of ice and its role in global climate change and how we protect and understand our home planet. It will help scientists determine if the global sea level is rising or falling. It will look at the ice sheets that blanket the Earth's poles to see if they are growing or shrinking. It will assist in developing an understanding of how changes in the Earth's atmosphere and climate effect polar ice masses and global sea level. CHIPSat, a suitcase-size 131-pound satellite, will provide invaluable information into the origin, physical processes and properties of the hot gas contained in the interstellar medium. This can provide important clues about the formation and evolution of galaxies since the interstellar medium literally contains the seeds of future stars. The Delta II launch is scheduled for Jan. 11 between 4:45 p.m. - 5:30 p.m. PST.

KSC-02pd2039

NASA Image and Video Library

2002-10-23

KENNEDY SPACE CENTER, FLA. - On NASA's Space Launch Complex 2 (SLC-2), Vandenberg Air Force Base, Calif., the interstage of the Delta II rocket is ready to be lifted up the tower for mating with the first stage (seen behind it). The rocket will carry the ICESat and CHIPSat satellites into Earth orbits. ICESat is a 661-pound satellite known as Geoscience Laser Altimeter System (GLAS) that will revolutionize our understanding of ice and its role in global climate change and how we protect and understand our home planet. It will help scientists determine if the global sea level is rising or falling. It will look at the ice sheets that blanket the Earth's poles to see if they are growing or shrinking. It will assist in developing an understanding of how changes in the Earth's atmosphere and climate effect polar ice masses and global sea level. CHIPSat, a suitcase-size 131-pound satellite, will provide invaluable information into the origin, physical processes and properties of the hot gas contained in the interstellar medium. This can provide important clues about the formation and evolution of galaxies since the interstellar medium literally contains the seeds of future stars. The Delta II launch is scheduled for Jan. 11 between 4:45 p.m. - 5:30 p.m. PST.

KSC-02pd2059

NASA Image and Video Library

2002-10-25

KENNEDY SPACE CENTER, FLA. - A second stage is lifted at NASA's Space Launch Complex 2 (SLC-2) at Vandenberg Air Force Base, Calif., for placement on a Delta II rocket The rocket will carry the ICESat and CHIPSat satellites into Earth orbits. The Ice, Cloud, and Land Elevation Satellite, or ICESat, is a 661-pound satellite carrying the Geoscience Laser Altimeter System (GLAS) that will revolutionize our understanding of ice and its role in global climate change and how we protect and understand our home planet. It will help scientists determine if the global sea level is rising or falling. It will look at the ice sheets that blanket the Earth's poles to see if they are growing or shrinking. It will assist in developing an understanding of how changes in the Earth's atmosphere and climate effect polar ice masses and global sea level. The Cosmic Hot Interstellar Plasma Spectrometer, or CHIPSat, a suitcase-size 131-pound satellite, will provide invaluable information into the origin, physical processes and properties of the hot gas contained in the interstellar medium. This can provide important clues about the formation and evolution of galaxies since the interstellar medium literally contains the seeds of future stars. The Delta II launch is scheduled for Jan. 11, 2003, between 4:45 p.m. - 5:30 p.m. PST.

KSC-02pd2043

NASA Image and Video Library

2002-10-23

KENNEDY SPACE CENTER, FLA. - Workers on the launch tower on NASA's Space Launch Complex 2 (SLC-2), Vandenberg Air Force Base, Calif., help guide the interstage of the Delta II rocket into position for mating with the first stage. The rocket will carry the ICESat and CHIPSat satellites into Earth orbits. ICESat is a 661-pound satellite known as Geoscience Laser Altimeter System (GLAS) that will revolutionize our understanding of ice and its role in global climate change and how we protect and understand our home planet. It will help scientists determine if the global sea level is rising or falling. It will look at the ice sheets that blanket the Earth's poles to see if they are growing or shrinking. It will assist in developing an understanding of how changes in the Earth's atmosphere and climate effect polar ice masses and global sea level. CHIPSat, a suitcase-size 131-pound satellite, will provide invaluable information into the origin, physical processes and properties of the hot gas contained in the interstellar medium. This can provide important clues about the formation and evolution of galaxies since the interstellar medium literally contains the seeds of future stars. The Delta II launch is scheduled for Jan. 11 between 4:45 p.m. - 5:30 p.m. PST.

KSC-02pd2062

NASA Image and Video Library

2002-10-25

KENNEDY SPACE CENTER, FLA. - A second stage is inserted into an interstage atop a Delta II rocket at NASA's Space Launch Complex 2 (SLC-2) at Vandenberg Air Force Base, Calif. The rocket will carry the ICESat and CHIPSat satellites into Earth orbits. The Ice, Cloud, and Land Elevation Satellite, or ICESat, is a 661-pound satellite carrying the Geoscience Laser Altimeter System (GLAS) that will revolutionize our understanding of ice and its role in global climate change and how we protect and understand our home planet. It will help scientists determine if the global sea level is rising or falling. It will look at the ice sheets that blanket the Earth's poles to see if they are growing or shrinking. It will assist in developing an understanding of how changes in the Earth's atmosphere and climate effect polar ice masses and global sea level. The Cosmic Hot Interstellar Plasma Spectrometer, or CHIPSat, a suitcase-size 131-pound satellite, will provide invaluable information into the origin, physical processes and properties of the hot gas contained in the interstellar medium. This can provide important clues about the formation and evolution of galaxies since the interstellar medium literally contains the seeds of future stars. The Delta II launch is scheduled for Jan. 11, 2003, between 4:45 p.m. - 5:30 p.m. PST.

KSC-02pd2035

NASA Image and Video Library

2002-10-23

KENNEDY SPACE CENTER, FLA. - With the transporter moved from below, the first stage of the Delta II rocket is suspended in air waiting to be lifted up the tower on NASA's Space Launch Complex 2 (SLC-2), Vandenberg Air Force Base, Calif. The rocket will carry the ICESat and CHIPSat satellites into Earth orbits. ICESat is a 661-pound satellite known as Geoscience Laser Altimeter System (GLAS) that will revolutionize our understanding of ice and its role in global climate change and how we protect and understand our home planet. It will help scientists determine if the global sea level is rising or falling. It will look at the ice sheets that blanket the Earth's poles to see if they are growing or shrinking. It will assist in developing an understanding of how changes in the Earth's atmosphere and climate effect polar ice masses and global sea level. CHIPSat, a suitcase-size 131-pound satellite, will provide invaluable information into the origin, physical processes and properties of the hot gas contained in the interstellar medium. This can provide important clues about the formation and evolution of galaxies since the interstellar medium literally contains the seeds of future stars. The Delta II launch is scheduled for Jan. 11 between 4:45 p.m. - 5:30 p.m. PST.

KSC-02pd2058

NASA Image and Video Library

2002-10-25

KENNEDY SPACE CENTER, FLA. - The second stage arrives at NASA's Space Launch Complex 2 (SLC-2) at Vandenberg Air Force Base, Calif., for placement on a Delta II rocket The rocket will carry the ICESat and CHIPSat satellites into Earth orbits. The Ice, Cloud, and Land Elevation Satellite, or ICESat, is a 661-pound satellite carrying the Geoscience Laser Altimeter System (GLAS) that will revolutionize our understanding of ice and its role in global climate change and how we protect and understand our home planet. It will help scientists determine if the global sea level is rising or falling. It will look at the ice sheets that blanket the Earth's poles to see if they are growing or shrinking. It will assist in developing an understanding of how changes in the Earth's atmosphere and climate effect polar ice masses and global sea level. The Cosmic Hot Interstellar Plasma Spectrometer, or CHIPSat, a suitcase-size 131-pound satellite, will provide invaluable information into the origin, physical processes and properties of the hot gas contained in the interstellar medium. This can provide important clues about the formation and evolution of galaxies since the interstellar medium literally contains the seeds of future stars. The Delta II launch is scheduled for Jan. 11, 2003, between 4:45 p.m. - 5:30 p.m. PST.

KSC-02pd2034

NASA Image and Video Library

2002-10-23

KENNEDY SPACE CENTER, FLA. - Workers check the lower end of the first stage of the Delta II rocket before it is lifted up the tower on NASA's Space Launch Complex 2 (SLC-2), Vandenberg Air Force Base, Calif. The rocket will carry the ICESat and CHIPSat satellites into Earth orbits. ICESat is a 661-pound satellite known as Geoscience Laser Altimeter System (GLAS) that will revolutionize our understanding of ice and its role in global climate change and how we protect and understand our home planet. It will help scientists determine if the global sea level is rising or falling. It will look at the ice sheets that blanket the Earth's poles to see if they are growing or shrinking. It will assist in developing an understanding of how changes in the Earth's atmosphere and climate effect polar ice masses and global sea level. CHIPSat, a suitcase-size 131-pound satellite, will provide invaluable information into the origin, physical processes and properties of the hot gas contained in the interstellar medium. This can provide important clues about the formation and evolution of galaxies since the interstellar medium literally contains the seeds of future stars. The Delta II launch is scheduled for Jan. 11 between 4:45 p.m. - 5:30 p.m. PST.

KSC-02pd2063

NASA Image and Video Library

2002-10-25

KENNEDY SPACE CENTER, FLA. - A second stage is inserted and secured into an interstage atop a Delta II rocket at NASA's Space Launch Complex 2 (SLC-2) at Vandenberg Air Force Base, Calif. The rocket will carry the ICESat and CHIPSat satellites into Earth orbits. The Ice, Cloud, and Land Elevation Satellite, or ICESat, is a 661-pound satellite carrying the Geoscience Laser Altimeter System (GLAS) that will revolutionize our understanding of ice and its role in global climate change and how we protect and understand our home planet. It will help scientists determine if the global sea level is rising or falling. It will look at the ice sheets that blanket the Earth's poles to see if they are growing or shrinking. It will assist in developing an understanding of how changes in the Earth's atmosphere and climate effect polar ice masses and global sea level. The Cosmic Hot Interstellar Plasma Spectrometer, or CHIPSat, a suitcase-size 131-pound satellite, will provide invaluable information into the origin, physical processes and properties of the hot gas contained in the interstellar medium. This can provide important clues about the formation and evolution of galaxies since the interstellar medium literally contains the seeds of future stars. The Delta II launch is scheduled for Jan. 11, 2003, between 4:45 p.m. - 5:30 p.m. PST.

Species and temperature measurement in H2/O2 rocket flow fields by means of Raman scattering diagnostics

NASA Technical Reports Server (NTRS)

Degroot, Wim A.; Weiss, Jonathan M.

1992-01-01

Validation of Computational Fluid Dynamics (CFD) codes developed for prediction and evaluation of rocket performance is hampered by a lack of experimental data. Non-intrusive laser based diagnostics are needed to provide spatially and temporally resolved gas dynamic and fluid dynamic measurements. This paper reports the first non-intrusive temperature and species measurements in the plume of a 110 N gaseous hydrogen/oxygen thruster at and below ambient pressures, obtained with spontaneous Raman spectroscopy. Measurements at 10 mm downstream of the exit plane are compared with predictions from a numerical solution of the axisymmetric Navier-Stokes and species transport equations with chemical kinetics, which fully model the combustor-nozzle-plume flowfield. The experimentally determined oxygen number density at the centerline at 10 mm downstream of the exit plane is four times that predicted by the model. The experimental number density data fall between those numerically predicted for the exit and 10 mm downstream planes in both magnitude and radial gradient. The predicted temperature levels are within 10 to 15 percent of measured values. Some of the discrepancies between experimental data and predictions result from not modeling the three dimensional core flow injection mixing process, facility back pressure effects, and possible diffuser-thruster interactions.

Is the Sky Really Falling? An Overview of Orbital Debris

NASA Technical Reports Server (NTRS)

Hull, Scott M.

2015-01-01

Orbital debris has been a prominent topic for a while, even before the movie Gravity came out. An anti-satellite test and a collision with an operational satellite both produced large highly-publicized debris clouds within recent years. While large objects like abandoned satellites and rocket bodies may be the most recognizable and identifiable concerns, a majority of the daily threat comes from the much more numerous smaller particles. In fact, small particle penetration continues to rank among the leading risks for manned space missions to the International Space Station and beyond. How much 'stuff' is up there, where did it come from, what harm can it do, and what is being done about it? These questions and more will be discussed.

KSC-2010-4984

NASA Image and Video Library

2010-10-04

CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, this image shows the progress of the rotating service structure (RSS) on Launch Pad 39B as it is being dismantled. Sand, reinforcing steel and large wooden mats were put down under the RSS to protect the structure's concrete from falling debris during deconstruction. Starting in 2009, the structure at the pad was no longer needed for NASA's Space Shuttle Program, so it is being restructured for future use. The new design will feature a "clean pad" for rockets to come with their own launcher, making it more versatile for a number of vehicles. The new lightning protection system, consisting of three lightning towers and a wire catenary system will remain. Photo credit: NASA/Jack Pfaller

KSC-2010-4988

NASA Image and Video Library

2010-10-04

CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, this long range view shows the progress of the rotating service structure (RSS) on Launch Pad 39B as it is being dismantled. Sand, reinforcing steel and large wooden mats were put down under the RSS to protect the structure's concrete from falling debris during deconstruction. Starting in 2009, the structure at the pad was no longer needed for NASA's Space Shuttle Program, so it is being restructured for future use. The new design will feature a "clean pad" for rockets to come with their own launcher, making it more versatile for a number of vehicles. The new lightning protection system, consisting of three lightning towers and a wire catenary system will remain. Photo credit: NASA/Jack Pfaller

KSC-2010-4986

NASA Image and Video Library

2010-10-04

CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, this image shows the progress of the rotating service structure (RSS) on Launch Pad 39B as it is being dismantled. Sand, reinforcing steel and large wooden mats were put down under the RSS to protect the structure's concrete from falling debris during deconstruction. Starting in 2009, the structure at the pad was no longer needed for NASA's Space Shuttle Program, so it is being restructured for future use. The new design will feature a "clean pad" for rockets to come with their own launcher, making it more versatile for a number of vehicles. The new lightning protection system, consisting of three lightning towers and a wire catenary system will remain. Photo credit: NASA/Jack Pfaller

Description of the three axis low-g accelerometer package

NASA Technical Reports Server (NTRS)

Amalavage, A. J.; Fikes, E. H.; Berry, E. H.

1978-01-01

The three axis low-g accelerometer package designed for use on the Space Processing Application Rocket (SPAR) Program is described. The package consists of the following major sections: (1) three Kearfott model 2412 accelerometers mounted in an orthogonal triad configuration on a temperature controlled, thermally isolated cube, (2) the accelerometer servoelectronics (printed circuit cards PC-6 through PC-12), and (3) the signal conditioner (printed circuit cards PC-15 and PC-16). The measurement range is 0 + or - 0.031 g with a quantization of 1.1 x 10 to the 7th power g. The package was flown successfully on six SPAR launches with the Black Brant booster. These flights provide approximately 300 s of free fall or zero-g environment.

The relativistic gravity train

NASA Astrophysics Data System (ADS)

Seel, Max

2018-05-01

The gravity train that takes 42.2 min from any point A to any other point B that is connected by a straight-line tunnel through Earth has captured the imagination more than most other applications in calculus or introductory physics courses. Brachystochron and, most recently, nonlinear density solutions have been discussed. Here relativistic corrections are presented. It is discussed how the corrections affect the time to fall through Earth, the Sun, a white dwarf, a neutron star, and—the ultimate limit—the difference in time measured by a moving, a stationary and the fiducial observer at infinity if the density of the sphere approaches the density of a black hole. The relativistic gravity train can serve as a problem with approximate and exact analytic solutions and as numerical exercise in any introductory course on relativity.

Sexually transmitted infections in Estonia.

PubMed

Põder, A; Bingham, J S

1999-10-01

Estonia, one of the Baltic countries, regained its independence in 1991, after the collapse of the USSR. This process led to great changes in every sphere of life--in politics, in the economy and in medicine. The service providing care for sexually transmitted infections (STIs) was involved in the process of these changes, too. However, freedom was followed not only by great happiness, but also by social destabilization and transformation of the old moral norms, the most evident features of which were the dramatic rise in crime, a sexual revolution and public prostitution. These 2 great simultaneous transformations in the STI care system and public mores led to the rapid increase of STIs in Estonia in the first half of the 1990s. Now some stabilization, and even a fall in incidence has occurred.

Neoliberal Optimism: Applying Market Techniques to Global Health.

PubMed

Mei, Yuyang

2017-01-01

Global health and neoliberalism are becoming increasingly intertwined as organizations utilize markets and profit motives to solve the traditional problems of poverty and population health. I use field work conducted over 14 months in a global health technology company to explore how the promise of neoliberalism re-envisions humanitarian efforts. In this company's vaccine refrigerator project, staff members expect their investors and their market to allow them to achieve scale and develop accountability to their users in developing countries. However, the translation of neoliberal techniques to the global health sphere falls short of the ideal, as profits are meager and purchasing power remains with donor organizations. The continued optimism in market principles amidst such a non-ideal market reveals the tenacious ideological commitment to neoliberalism in these global health projects.

High-precision Non-Contact Measurement of Creep of Ultra-High Temperature Materials for Aerospace

NASA Technical Reports Server (NTRS)

Rogers, Jan R.; Hyers, Robert

2008-01-01

For high-temperature applications (greater than 2,000 C) such as solid rocket motors, hypersonic aircraft, nuclear electric/thermal propulsion for spacecraft, and more efficient jet engines, creep becomes one of the most important design factors to be considered. Conventional creep-testing methods, where the specimen and test apparatus are in contact with each other, are limited to temperatures approximately 1,700 C. Development of alloys for higher-temperature applications is limited by the availability of testing methods at temperatures above 2000 C. Development of alloys for applications requiring a long service life at temperatures as low as 1500 C, such as the next generation of jet turbine superalloys, is limited by the difficulty of accelerated testing at temperatures above 1700 C. For these reasons, a new, non-contact creep-measurement technique is needed for higher temperature applications. A new non-contact method for creep measurements of ultra-high-temperature metals and ceramics has been developed and validated. Using the electrostatic levitation (ESL) facility at NASA Marshall Space Flight Center, a spherical sample is rotated quickly enough to cause creep deformation due to centrifugal acceleration. Very accurate measurement of the deformed shape through digital image analysis allows the stress exponent n to be determined very precisely from a single test, rather than from numerous conventional tests. Validation tests on single-crystal niobium spheres showed excellent agreement with conventional tests at 1985 C; however the non-contact method provides much greater precision while using only about 40 milligrams of material. This method is being applied to materials including metals and ceramics for non-eroding throats in solid rockets and next-generation superalloys for turbine engines. Recent advances in the method and the current state of these new measurements will be presented.

Analysis of International Space Station Materials on MISSE-3 and MISSE-4

NASA Technical Reports Server (NTRS)

Finckenor, Miria M.; Golden, Johnny L.; O'Rourke, Mary Jane

2008-01-01

For high-temperature applications (> 2,000 C) such as solid rocket motors, hypersonic aircraft, nuclear electric/thermal propulsion for spacecraft, and more efficient jet engines, creep becomes one of the most important design factors to be considered. Conventional creep-testing methods, where the specimen and test apparatus are in contact with each other, are limited to temperatures 1,700 deg. C. Development of alloys for higher-temperature applications is limited by the availability of testing methods at temperatures above 2000 C. Development of alloys for applications requiring a long service life at temperatures as low as 1500 C, such as the next generation of jet turbine superalloys, is limited by the difficulty of accelerated testing at temperatures above 1700 0c. For these reasons, a new, non-contact creep-measurement technique is needed for higher temperature applications. A new non-contact method for creep measurements of ultra-high-temperature metals and ceramics has been developed and validated. Using the electrostatic levitation (ESL) facility at NASA Marshall Space Flight Center, a spherical sample is rotated quickly enough to cause creep deformation due to centrifugal acceleration. Very accurate measurement of the deformed shape through digital image analysis allows the stress exponent n to be determined very precisely from a single test, rather than from numerous conventional tests. Validation tests on single-crystal niobium spheres showed excellent agreement with conventional tests at 1985 C; however the non-contact method provides much greater precision while using only about 40 milligrams of material. This method is being applied to materials including metals and ceramics for noneroding throats in solid rockets and next-generation superalloys for turbine engines. Recent advances in the method and the current state of these new measurements will be presented.

Orbital Debris and NASA's Measurement Program

NASA Astrophysics Data System (ADS)

Africano, J. L.; Stansbery, E. G.

2002-05-01

Since the launch of Sputnik in 1957, the number of manmade objects in orbit around the Earth has dramatically increased. The United States Space Surveillance Network (SSN) tracks and maintains orbits on over nine thousand objects down to a limiting diameter of about ten centimeters. Unfortunately, active spacecraft are only a small percentage ( ~ 7%) of this population. The rest of the population is orbital debris or ``space junk" consisting of expended rocket bodies, dead payloads, bits and pieces from satellite launches, and fragments from satellite breakups. The number of these smaller orbital debris objects increases rapidly with decreasing size. It is estimated that there are at least 130,000 orbital debris objects between one and ten centimeters in diameter. Most objects smaller than 10 centimeters go untracked! As the orbital debris population grows, the risk to other orbiting objects, most importantly manned space vehicles, of a collision with a piece of debris also grows. The kinetic energy of a solid 1 cm aluminum sphere traveling at an orbital velocity of 10 km/sec is equivalent to a 400 lb. safe traveling at 60 mph. Fortunately, the volume of space in which the orbiting population resides is large, collisions are infrequent, but they do occur. The Space Shuttle often returns to earth with its windshield pocked with small pits or craters caused by collisions with very small, sub-millimeter-size pieces of debris (paint flakes, particles from solid rocket exhaust, etc.), and micrometeoroids. To get a more complete picture of the orbital-debris environment, NASA has been using both radar and optical techniques to monitor the orbital debris environment. This paper gives an overview of the orbital debris environment and NASA's measurement program.

Cryo-braking using penetrators for enhanced capabilities for the potential landing of payloads on icy solar system objects

NASA Astrophysics Data System (ADS)

Winglee, R. M.; Robinson, T.; Danner, M.; Koch, J.

2018-03-01

The icy moons of Jupiter and Saturn are important astrobiology targets. Access to the surface of these worlds is made difficult by the high ΔV requirements which is typically in the hypervelocity range. Passive braking systems cannot be used due to the lack of an atmosphere, and active braking by rockets significantly adds to the missions costs. This paper demonstrates that a two-stage landing system can overcome these problems and provide significant improvements in the payload fraction that can be landed The first stage involves a hypervelocity impactor which is designed to penetrate to a depth of a few tens of meters. This interaction is the cryo-breaking component and is examined through laboratory experiments, empirical relations and modeling. The resultant ice-particle cloud creates a transient artificial atmosphere that can be used to enable passive braking of the second stage payload dd, with a substantially higher mass payload fraction than possible with a rocket landing system. It is shown that a hollow cylinder design for the impactor can more efficiently eject the material upwards in a solid cone of ice particles relative to solid impactors such as spheres or spikes. The ejected mass is shown to be of the order of 103 to 104 times the mass of the impactor. The modeling indicates that a 10 kg payload with a braking system of 3 m2 (i.e. an areal density of 0.3 kg/m2) is sufficient to allow the landing of the payload with the deceleration limited to less than 2000 g's. Modern electronics can withstand this deceleration and as such the system provides an important alternative to landing payloads on icy solar system objects.

STS-63 Space Shuttle report

NASA Technical Reports Server (NTRS)

Fricke, Robert W., Jr.

1995-01-01

The STS-63 Space Shuttle Program Mission Report summarizes the Payload activities and provides detailed data on the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Reusable Solid Rocket Motor (RSRM), and the Space Shuttle Main Engine (SSME) systems performance during this sixty-seventh flight of the Space Shuttle Program, the forty-second since the return to flight, and twentieth flight of the Orbiter vehicle Discovery (OV-103). In addition to the OV-103 Orbiter vehicle, the flight vehicle consisted of an ET that was designated ET-68; three SSME's that were designated 2035, 2109, and 2029 in positions 1, 2, and 3, respectively; and two SRB's that were designated BI-070. The RSRM's that were an integral part of the SRB's were designated 360Q042A for the left SRB and 360L042B for the right SRB. The STS-63 mission was planned as an 8-day duration mission with two contingency days available for weather avoidance or Orbiter contingency operations. The primary objectives of the STS-63 mission were to perform the Mir rendezvous operations, accomplish the Spacehab-3 experiments, and deploy and retrieve the Shuttle Pointed Autonomous Research Tool for Astronomy-204 (SPARTAN-204) payload. The secondary objectives were to perform the Cryogenic Systems Experiment (CSE)/Shuttle Glo-2 Experiment (GLO-2) Payload (CGP)/Orbital Debris Radar Calibration Spheres (ODERACS-2) (CGP/ODERACS-2) payload objectives, the Solid Surface Combustion Experiment (SSCE), and the Air Force Maui Optical Site Calibration Tests (AMOS). The objectives of the Mir rendezvous/flyby were to verify flight techniques, communication and navigation-aid sensor interfaces, and engineering analyses associated with Shuttle/Mir proximity operations in preparation for the STS-71 docking mission.

Instrumentation development for space debris optical observation system in Indonesia: Preliminary results

NASA Astrophysics Data System (ADS)

Dani, Tiar; Rachman, Abdul; Priyatikanto, Rhorom; Religia, Bahar

2015-09-01

An increasing number of space junk in orbit has raised their chances to fall in Indonesian region. So far, three debris of rocket bodies have been found in Bengkulu, Gorontalo and Lampung. LAPAN has successfully developed software for monitoring space debris that passes over Indonesia with an altitude below 200 km. To support the software-based system, the hardware-based system has been developed based on optical instruments. The system has been under development in early 2014 which consist of two systems: the telescopic system and wide field system. The telescopic system uses CCD cameras and a reflecting telescope with relatively high sensitivity. Wide field system uses DSLR cameras, binoculars and a combination of CCD with DSLR Lens. Methods and preliminary results of the systems will be presented.

KSC-08pd3742

NASA Image and Video Library

2008-11-19

CAPE CANAVERAL, Fla. – At the Parachute Refurbishment Facility at NASA's Kennedy Space Center in Florida, workers begin hanging the parachutes recovered from sea after the launch of space shuttle Endeavour on the STS-126 mission onto a monorail system. The parachutes are used to slow the descent of the solid rocket boosters that are jettisoned during liftoff. The monorail will transport each parachute into a 30,000-gallon washer and a huge dryer heated with 140-degree air at 13,000 cubic feet per minute One pilot, one drogue and three main canopies per booster slow the booster’s fall from about 360 mph to 50 mph. After the chutes are cleaned and repaired, they must be carefully packed into their bags so they will deploy correctly the next time they are used. Photo credit: NASA/Jim Grossmann

KSC-08pd3743

NASA Image and Video Library

2008-11-19

CAPE CANAVERAL, Fla. – At the Parachute Refurbishment Facility at NASA's Kennedy Space Center in Florida, workers begin hanging the parachutes recovered from sea after the launch of space shuttle Endeavour on the STS-126 mission onto a monorail system. The parachutes are used to slow the descent of the solid rocket boosters that are jettisoned during liftoff. The monorail will transport each parachute into a 30,000-gallon washer and a huge dryer heated with 140-degree air at 13,000 cubic feet per minute. One pilot, one drogue and three main canopies per booster slow the booster’s fall from about 360 mph to 50 mph. After the chutes are cleaned and repaired, they must be carefully packed into their bags so they will deploy correctly the next time they are used. Photo credit: NASA/Jim Grossmann

KSC-08pd3740

NASA Image and Video Library

2008-11-19

CAPE CANAVERAL, Fla. – Parachutes recovered from sea after the launch of space shuttle Endeavour on the STS-126 mission are suspended from a hanging monorail system at the Parachute Refurbishment Facility at NASA's Kennedy Space Center in Florida. The parachutes are used to slow the descent of the solid rocket boosters that are jettisoned during liftoff. The monorail will transport each parachute into a 30,000-gallon washer and a huge dryer heated with 140-degree air at 13,000 cubic feet per minute. One pilot, one drogue and three main canopies per booster slow the booster’s fall from about 360 mph to 50 mph. After the chutes are cleaned and repaired, they must be carefully packed into their bags so they will deploy correctly the next time they are used. Photo credit: NASA/Jim Grossmann

KSC-08pd3747

NASA Image and Video Library

2008-11-19

CAPE CANAVERAL, Fla. – At the Parachute Refurbishment Facility at NASA's Kennedy Space Center in Florida, the parachutes recovered from sea after the launch of space shuttle Endeavour on the STS-126 mission are moved through the 30,000-gallon washer. The parachutes are used to slow the descent of the solid rocket boosters that are jettisoned during liftoff. After washing, the monorail will move the parachutes into a huge dryer heated with 140-degree air at 13,000 cubic feet per minute. One pilot, one drogue and three main canopies per booster slow the booster’s fall from about 360 mph to 50 mph. After the chutes are cleaned and repaired, they must be carefully packed into their bags so they will deploy correctly the next time they are used. Photo credit: NASA/Jim Grossmann

Siena, 1794: History's Most Consequential Meteorite Fall

NASA Astrophysics Data System (ADS)

Marvin, U. B.

1995-09-01

In the mythos of meteoritics, the fall of stones at L'Aigle in Normandy at 1 p. m. on April 26, 1803, is commonly regarded as the event that turned skeptics into believers and opened the way for the new science. A strong case can be made, however, that the fall of stones at Siena at 7:00 p.m. on June 16, 1794, established the authenticity of meteorite falls and set in motion the reexaminations of entrenched beliefs that led to the founding of the new science. The Siena fall was heralded by the appearance of an extraordinarily high, dark cloud emitting smoke, sparks like rockets, and bolts of unusually slow-moving red lightning. With a tremendous explosion a shower of stones, ranging in weight from a few milligrams to 3 kg, fell southeast of Siena. This was the first meteorite fall to occur in the vicinity of a sizeable European city and the first to be witnessed by so many people, including English visitors, that the fall of the stones from the sky could not be denied. It also was the first fall to be seriously investigated by scholars, at several universities in Italy, who collected eye-witness reports and specimens and formulated hypotheses of origin. Their task was greatly complicated by the timing of the fall which occurred 18 hours after Mt. Vesuvius sprang into full eruption. Some believed that the two events were entirely coincidental; others thought that the stones either were ejecta from the volcano (which lay about 320 km to the southeast of Siena) or had consolidated in the fiery masses of dust and ash expelled by the mountain. No explanations seemed entirely satisfactory, but, in an age when the very possibility of falling stones had been decisively ruled out by savants of the Enlightenment, the well-observed fall at Siena opened a new dialog on this subject. The Siena fall occurred only two months after the publication in Riga and Leipzig of Ernst F. F. Chladni's book On the Origin of Ironmasses in which he concluded from historical records that fragments of iron and stone fall do, indeed, fall from sky. News traveled so slowly in the 18th century that Chladni's book received negative reviews in Germany throughout 1794 and much of 1795 before the first notice of the Siena fall appeared in a Berlin paper in 1796. The same amount of time passed before Chladni's book reached England, but the groundwork for a more tolerant reception of it in that country was laid by travelers returning from Italy in 1794 with their descriptions and their specimens from Siena (including bogus "fallen stones" fabricated for the tourist market). Widespread interest was aroused in 1795 when the Royal Society published an account of the eruption of Mt. Vesuvius by Sir William Hamilton, the English Ambassador at Naples, who included a short discussion of the Siena stones and their possible link with the volcano. Hamilton's article carried the story of the Siena fall to France and Germany. The case for fallen stones was further strengthened when a 56-pound stone fell at 3:30 p.m. on December 13th, 1795, at Wold Cottage in Yorkshire. Early in 1796, Edward King, a Fellow of the Royal Society, published the first book in English on fallen stones. In it, he focused primarily on the Siena event but just as he was finishing his text he received a copy of Chladni's book and quoted from it extensively. King's 36-page book was widely read. It received some bad reviews in England but it immediately prompted one reader to report the fall of a stone [apparently a genuine meteorite] at Pettiswood, Ireland. He had withheld his story for 17 years for fear of ridicule. Now, the climate of opinion had changed and meteoritics already was becoming a new branch of science.

KSC-05PD-0027

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. The barge carrying the newly redesigned External Tank, designated for use on Return to Flight mission STS-114, is towed toward the Launch Complex 39 Area Turn Basin at Kennedy. At left is the Vehicle Assembly Building. The barge arrived after an approximately 900-mile journey at sea from the Michoud Assembly Facility in New Orleans. It left the facility Dec. 31 on the Pegasus, NASAs specially designed barge, towed by Solid Rocket Booster retrieval ship Liberty Star. At Port Canaveral, the barge was then hooked up to the tugs for the last part of the journey. Next, the External Tank will be off- loaded from the barge and transported to the Vehicle Assembly Building for its final checkout and mating to the twin Solid Rocket Boosters and orbiter Discovery. NASA and Lockheed Martin Corp. spent nearly two years modifying the 15-story, bronze- colored tank to make it safer for liftoff. Among dozens of changes is a redesigned forward bipod fitting -- a design that meets the recommendation of the Columbia Accident Investigation Board to reduce the risk to the Space Shuttle from falling debris during ascent. STS-114 is targeted for a launch opportunity beginning in May. The seven-member Discovery crew will fly to the International Space Station primarily to test and evaluate new procedures for flight safety, including Space Shuttle inspection and repair techniques.

KSC-05PD-0031

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. The barge carrying the newly redesigned External Tank (ET), designated for use on Return to Flight mission STS-114, is finally docked at the Launch Complex 39 Area Turn Basin. The ET can be seen inside the barge. The External Tank arrived safely early this morning at Port Canaveral, Fla., after an approximately 900-mile journey at sea. It departed from the Michoud Assembly Facility in New Orleans Dec. 31 and was transported on the Pegasus, NASAs specially designed barge, pulled by Solid Rocket Booster retrieval ship Liberty Star. At the port, the barge was then hooked up to the tugs for the last part of the journey. Next, the External Tank will be off-loaded from the barge and transported to the Vehicle Assembly Building for its final checkout and mating to the twin Solid Rocket Boosters and orbiter Discovery. NASA and Lockheed Martin Corp. spent nearly two years modifying the 15-story, bronze-colored tank to make it safer for liftoff. Among dozens of changes is a redesigned forward bipod fitting -- a design that meets the recommendation of the Columbia Accident Investigation Board to reduce the risk to the Space Shuttle from falling debris during ascent. STS-114 is targeted for a launch opportunity beginning in May. The seven-member Discovery crew will fly to the International Space Station primarily to test and evaluate new procedures for flight safety, including Space Shuttle inspection and repair techniques.

KSC-05PD-0026

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. The tugboat towing the barge carrying the newly redesigned External Tank, designated for use on Return to Flight mission STS-114, passes through a drawbridge on its voyage to the Launch Complex 39 Area Turn Basin at Kennedy. The barge arrived after an approximately 900-mile journey at sea from the Michoud Assembly Facility in New Orleans. It left the facility Dec. 31 on the Pegasus, NASAs specially designed barge, towed by Solid Rocket Booster retrieval ship Liberty Star. At Port Canaveral, the barge was then hooked up to the tugs for the last part of the journey to the Launch Complex 39 Area Turn Basin at Kennedy. Next, the External Tank will be off-loaded from the barge and transported to the Vehicle Assembly Building for its final checkout and mating to the twin Solid Rocket Boosters and orbiter Discovery. NASA and Lockheed Martin Corp. spent nearly two years modifying the 15-story, bronze-colored tank to make it safer for liftoff. Among dozens of changes is a redesigned forward bipod fitting -- a design that meets the recommendation of the Columbia Accident Investigation Board to reduce the risk to the Space Shuttle from falling debris during ascent. STS-114 is targeted for a launch opportunity beginning in May. The seven- member Discovery crew will fly to the International Space Station primarily to test and evaluate new procedures for flight safety, including Space Shuttle inspection and repair techniques.

KSC-05PD-0024

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. The barge carrying the newly redesigned External Tank, designated for use on Return to Flight mission STS-114, passes cruise ships as it enters Port Canaveral, Fla. The barge arrived after an approximately 900-mile journey at sea from the Michoud Assembly Facility in New Orleans. It left the facility Dec. 31 on the Pegasus, NASAs specially designed barge, towed by Solid Rocket Booster retrieval ship Liberty Star. At Port Canaveral, the barge was then hooked up to the tugs for the last part of the journey to the Launch Complex 39 Area Turn Basin at Kennedy. Next, the External Tank will be off-loaded from the barge and transported to the Vehicle Assembly Building for its final checkout and mating to the twin Solid Rocket Boosters and orbiter Discovery. NASA and Lockheed Martin Corp. spent nearly two years modifying the 15-story, bronze-colored tank to make it safer for liftoff. Among dozens of changes is a redesigned forward bipod fitting -- a design that meets the recommendation of the Columbia Accident Investigation Board to reduce the risk to the Space Shuttle from falling debris during ascent. STS-114 is targeted for a launch opportunity beginning in May. The seven-member Discovery crew will fly to the International Space Station primarily to test and evaluate new procedures for flight safety, including Space Shuttle inspection and repair techniques.

KSC-05PD-0025

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. A tugboat tows the barge carrying the newly redesigned External Tank, designated for use on Return to Flight mission STS-114, to the dock at the Launch Complex 39 Area Turn Basin at Kennedy. The barge arrived after an approximately 900-mile journey at sea from the Michoud Assembly Facility in New Orleans. It left the facility Dec. 31 on the Pegasus, NASAs specially designed barge, towed by Solid Rocket Booster retrieval ship Liberty Star. At Port Canaveral, the barge was then hooked up to the tugs for the last part of the journey to the Launch Complex 39 Area Turn Basin at Kennedy. Next, the External Tank will be off-loaded from the barge and transported to the Vehicle Assembly Building for its final checkout and mating to the twin Solid Rocket Boosters and orbiter Discovery. NASA and Lockheed Martin Corp. spent nearly two years modifying the 15-story, bronze-colored tank to make it safer for liftoff. Among dozens of changes is a redesigned forward bipod fitting -- a design that meets the recommendation of the Columbia Accident Investigation Board to reduce the risk to the Space Shuttle from falling debris during ascent. STS-114 is targeted for a launch opportunity beginning in May. The seven-member Discovery crew will fly to the International Space Station primarily to test and evaluate new procedures for flight safety, including Space Shuttle inspection and repair techniques.

Characterization of Air Emissions from Open Burning and ...

EPA Pesticide Factsheets

Emissions from open burning (OB) and open detonation (OD) of military ordnance and static fires (SF) of rocket motors were sampled in fall, 2013 at the Dundurn Depot (Saskatchewan, Canada). Emission sampling was conducted with an aerostat-lofted instrument package termed the “Flyer” that was maneuvered into the downwind plumes. Forty-nine OB events, 94 OD events, and 16 SF on four propellants types (Triple base, 105 M1, 155 M4A2 white bag, and 155 M6 red bag), two smokes (HC grenade and red phosphorus), five explosive types (Trigran, C4, ANFO, ANFO+HC grenade, and ANFO+Flare), and two rocket motors types (CVR-7 and MK 58) resulted in emission factors for particulate matter (PM), carbon dioxide (CO2), carbon monoxide (CO), methane (CH4), volatile organic compounds (VOCs), chlorine species (HCl, chloride, chlorate, perchlorate), polychlorinated dibenzodioxins and polychlorinated dibenzofurans (PCDDs/PCDFs) and PM-based metals. These data provide Canada and the United States with additional air emissions data to support health risk assessments and permitting for safe treatment of military ordnance by OB/OD/SF. In addition, the data will be used to conduct air dispersion modelling assessing the impact of treatment of various ordnance on the air quality, to support mandatory reporting requirements of the Canadian Environmental Protection Act (CEPA), the National Pollutant Release Inventory (NPRI), and to update the Canadian Ammunition Chemical Database.Result

KSC-02pd2040

NASA Image and Video Library

2002-10-23

KENNEDY SPACE CENTER, FLA. - Workers at the base of the launch tower on NASA's Space Launch Complex 2 (SLC-2), Vandenberg Air Force Base, Calif., watch as the interstage of the Delta II rocket is lifted up the tower. The interstage will eventually house the second stage and will be mated with the first stage. The rocket will carry the ICESat and CHIPSat satellites into Earth orbits. ICESat is a 661-pound satellite known as Geoscience Laser Altimeter System (GLAS) that will revolutionize our understanding of ice and its role in global climate change and how we protect and understand our home planet. It will help scientists determine if the global sea level is rising or falling. It will look at the ice sheets that blanket the Earth's poles to see if they are growing or shrinking. It will assist in developing an understanding of how changes in the Earth's atmosphere and climate effect polar ice masses and global sea level. CHIPSat, a suitcase-size 131-pound satellite, will provide invaluable information into the origin, physical processes and properties of the hot gas contained in the interstellar medium. This can provide important clues about the formation and evolution of galaxies since the interstellar medium literally contains the seeds of future stars. The Delta II launch is scheduled for Jan. 11 between 4:45 p.m. - 5:30 p.m. PST.

Excellence of numerical differentiation method in calculating the coefficients of high temperature series expansion of the free energy and convergence problem of the expansion

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

Zhou, S., E-mail: chixiayzsq@yahoo.com; Solana, J. R.

2014-12-28

In this paper, it is shown that the numerical differentiation method in performing the coupling parameter series expansion [S. Zhou, J. Chem. Phys. 125, 144518 (2006); AIP Adv. 1, 040703 (2011)] excels at calculating the coefficients a{sub i} of hard sphere high temperature series expansion (HS-HTSE) of the free energy. Both canonical ensemble and isothermal-isobaric ensemble Monte Carlo simulations for fluid interacting through a hard sphere attractive Yukawa (HSAY) potential with extremely short ranges and at very low temperatures are performed, and the resulting two sets of data of thermodynamic properties are in excellent agreement with each other, and wellmore » qualified to be used for assessing convergence of the HS-HTSE for the HSAY fluid. Results of valuation are that (i) by referring to the results of a hard sphere square well fluid [S. Zhou, J. Chem. Phys. 139, 124111 (2013)], it is found that existence of partial sum limit of the high temperature series expansion series and consistency between the limit value and the true solution depend on both the potential shapes and temperatures considered. (ii) For the extremely short range HSAY potential, the HS-HTSE coefficients a{sub i} falls rapidly with the order i, and the HS-HTSE converges from fourth order; however, it does not converge exactly to the true solution at reduced temperatures lower than 0.5, wherein difference between the partial sum limit of the HS-HTSE series and the simulation result tends to become more evident. Something worth mentioning is that before the convergence order is reached, the preceding truncation is always improved by the succeeding one, and the fourth- and higher-order truncations give the most dependable and qualitatively always correct thermodynamic results for the HSAY fluid even at low reduced temperatures to 0.25.« less

Numerical Study of Motion of Falling Conical Graupel

NASA Astrophysics Data System (ADS)

Chueh, Chih-Che; Wang, Pao K.; Hashino, Tempei

2018-01-01

In the present study, the attitudes of freely-falling conical graupel with a realistic range of densities are investigated numerically by solving the transient Navier-Stokes equations and the body dynamics equations representing the 6-degrees-of-freedom motion. This framework allows us to determine the position and orientation of the graupel in response to the hydrodynamic force of the flow fields. The results show more significant horizontal movements than those cases with a fixed bulk density of ice assumed in our previous study. This is because the real graupel particles possess the density less than the bulk density of ice, which, in turn, leads to a relatively small mass and a relatively small set of moments of inertia. We demonstrate that, with the six degrees of freedom considered together, when Reynolds number is small, a typical damped oscillation occurs, whereas when Reynolds number is high, amplifying oscillation may occur which leads to more complicated and unpredictable flying attitudes such as tumbling. The drag coefficients obtained in the present study agree with the previous studies and can be approximated by that of spheres of the same Reynolds numbers. We also show that conical graupel can perform significant horizontal translations which can be on the order of 1 km in 1 h.

Numerical simulation of a sphere moving down an incline with identical spheres placed equally apart

USGS Publications Warehouse

Ling, Chi-Hai; Jan, Chyan-Deng; Chen, Cheng-lung; Shen, Hsieh Wen

1992-01-01

This paper describes a numerical study of an elastic sphere moving down an incline with a string of identical spheres placed equally apart. Two momentum equations and a moment equation formulated for the moving sphere are solved numerically for the instantaneous velocity of the moving sphere on an incline with different angles of inclination. Input parameters for numerical simulation include the properties of the sphere (the radius, density, Poison's ratio, and Young's Modulus of elasticity), the coefficient of friction between the spheres, and a damping coefficient of the spheres during collision.

Rocket propulsion elements - An introduction to the engineering of rockets (6th revised and enlarged edition)

NASA Astrophysics Data System (ADS)

Sutton, George P.

The subject of rocket propulsion is treated with emphasis on the basic technology, performance, and design rationale. Attention is given to definitions and fundamentals, nozzle theory and thermodynamic relations, heat transfer, flight performance, chemical rocket propellant performance analysis, and liquid propellant rocket engine fundamentals. The discussion also covers solid propellant rocket fundamentals, hybrid propellant rockets, thrust vector control, selection of rocket propulsion systems, electric propulsion, and rocket testing.

14 CFR 101.25 - Operating limitations for Class 2-High Power Rockets and Class 3-Advanced High Power Rockets.

Code of Federal Regulations, 2013 CFR

2013-01-01

... Power Rockets and Class 3-Advanced High Power Rockets. 101.25 Section 101.25 Aeronautics and Space... OPERATING RULES MOORED BALLOONS, KITES, AMATEUR ROCKETS AND UNMANNED FREE BALLOONS Amateur Rockets § 101.25 Operating limitations for Class 2-High Power Rockets and Class 3-Advanced High Power Rockets. When operating...

14 CFR 101.25 - Operating limitations for Class 2-High Power Rockets and Class 3-Advanced High Power Rockets.

Code of Federal Regulations, 2012 CFR

2012-01-01

... Power Rockets and Class 3-Advanced High Power Rockets. 101.25 Section 101.25 Aeronautics and Space... OPERATING RULES MOORED BALLOONS, KITES, AMATEUR ROCKETS AND UNMANNED FREE BALLOONS Amateur Rockets § 101.25 Operating limitations for Class 2-High Power Rockets and Class 3-Advanced High Power Rockets. When operating...

14 CFR 101.25 - Operating limitations for Class 2-High Power Rockets and Class 3-Advanced High Power Rockets.

Code of Federal Regulations, 2014 CFR

2014-01-01

... Power Rockets and Class 3-Advanced High Power Rockets. 101.25 Section 101.25 Aeronautics and Space... OPERATING RULES MOORED BALLOONS, KITES, AMATEUR ROCKETS AND UNMANNED FREE BALLOONS Amateur Rockets § 101.25 Operating limitations for Class 2-High Power Rockets and Class 3-Advanced High Power Rockets. When operating...

14 CFR 101.25 - Operating limitations for Class 2-High Power Rockets and Class 3-Advanced High Power Rockets.

Code of Federal Regulations, 2010 CFR

2010-01-01

... Power Rockets and Class 3-Advanced High Power Rockets. 101.25 Section 101.25 Aeronautics and Space... OPERATING RULES MOORED BALLOONS, KITES, AMATEUR ROCKETS AND UNMANNED FREE BALLOONS Amateur Rockets § 101.25 Operating limitations for Class 2-High Power Rockets and Class 3-Advanced High Power Rockets. When operating...

14 CFR 101.25 - Operating limitations for Class 2-High Power Rockets and Class 3-Advanced High Power Rockets.

Code of Federal Regulations, 2011 CFR

2011-01-01

... Power Rockets and Class 3-Advanced High Power Rockets. 101.25 Section 101.25 Aeronautics and Space... OPERATING RULES MOORED BALLOONS, KITES, AMATEUR ROCKETS AND UNMANNED FREE BALLOONS Amateur Rockets § 101.25 Operating limitations for Class 2-High Power Rockets and Class 3-Advanced High Power Rockets. When operating...

Evaluation of the Effect of Exhausts from Liquid and Solid Rockets on Ozone Layer

NASA Astrophysics Data System (ADS)

Yamagiwa, Yoshiki; Ishimaki, Tetsuya

This paper reports the analytical results of the influences of solid rocket and liquid rocket exhausts on ozone layer. It is worried about that the exhausts from solid propellant rockets cause the ozone depletion in the ozone layer. Some researchers try to develop the analytical model of ozone depletion by rocket exhausts to understand its physical phenomena and to find the effective design of rocket to minimize its effect. However, these models do not include the exhausts from liquid rocket although there are many cases to use solid rocket boosters with a liquid rocket at the same time in practical situations. We constructed combined analytical model include the solid rocket exhausts and liquid rocket exhausts to analyze their effects. From the analytical results, we find that the exhausts from liquid rocket suppress the ozone depletion by solid rocket exhausts.

Effect of the magnetic field on measurements of the electron density and temperature by cylindrical probes in the Earth's ionosphere

NASA Astrophysics Data System (ADS)

Gubsky, V. F.

2009-12-01

In the 1960s and 1970s, quite simply produced cylindrical Langmuir probes were used in the USSR both on satellites (Kosmos-378, Intercosmos-2, -4, -8, -10, -19) and to measure the electron density and temperature on vertical launched rockets (Vertical’-4, -6, -10) within the Intercosmos program. These measurements were first made at middle latitudes. With increasing inclination of the orbits of launched satellites (satellites had no stabilization), falling sections were sometimes observed on probe characteristics in the electron saturation region. The Intercosmos-Bulgaria-1300 satellite, which was stabilized along three axes and was equipped with a cylindrical probe whose longitudinal axis was always directed downward to the Earth, was launched in 1981. This satellite allowed definite conclusions on the effect of the geomagnetic field on the form of the probe characteristic and, hence, on the determination of the electron density and temperature. Probe characteristics with falling sections are presented. These measurements are compared with those performed in a laboratory plasma. The appearance of negative sections on the probe characteristics is shown to be due to the effect of the geomagnetic field. The degree of this effect depends both on the electron density and temperature and on the probe voltage.

Space Shuttle Projects

NASA Image and Video Library

1989-03-01

This STS-29 mission onboard photo depicts the External Tank (ET) falling toward the ocean after separation from the Shuttle orbiter Discovery. The giant cylinder, higher than a 15-story building, with a length of 154-feet (47-meters) and a diameter of 27,5-feet (8.4-meters), is the largest single piece of the Space Shuttle. During launch, the ET also acts as a backbone for the orbiter and solid rocket boosters. In separate, internal pressurized tank sections, the ET holds the liquid hydrogen fuel and liquid oxygen oxidizer for the Shuttle's three main engines. During launch, the ET feeds the fuel under pressure through 17-inch (43.2-centimeter) ducts which branch off into smaller lines that feed directly into the main engines. Some 64,000 gallons (242,260 liters) of fuel are consumed by the main engines each minute. Machined from aluminum alloys, the Space Shuttle's ET is the only part of the launch vehicle that currently is not reused. After its 526,000 gallons (1,991,071 liters) of propellants are consumed during the first 8.5 minutes of flight, it is jettisoned from the orbiter and breaks up in the upper atmosphere, its pieces falling into remote ocean waters. The Marshall Space Flight Center was responsible for developing the ET.

Static measurement of the thickness of the ablative coating of the solid rocket boosters

NASA Technical Reports Server (NTRS)

Harrison, Harry C.

1996-01-01

The Solid Rocket Boosters (SRB's) used to launch the Space Shuttle are coated with a layer of ablative material to prevent thermal damage when they reenter the earth's atmosphere. The coating consists of a mixture of cork, glass, and resin. A new coating (Marshall Convergent Coating, MCC-2) was recently developed that is environmentally complaint. The coating must meet certain minimum thickness standards in order to protect the SRB. The coating is applied by a robot controlled nozzle that moves from the bottom to top, as the rocket part rotates on a table. Several coats are applied, building up to the desired thickness. Inspectors do a limited amount of destructive 'wet' testing. This involves an inspector inserting a rod in the wet coating and removing the rod. This results in a hole that, of course, must be patched later. The material is cured and the thickness is measured. There is no real-time feedback as the coating is being applied. Although this might seem like the best way to control thickness, the problems with 'blowback' (reflected material covering the sensor) are formidable, and have not been solved. After the thermal coating is applied, a protective top coat is applied. The SRB part is then placed in a oven and baked to harden the surface. The operations personnel then measure the thickness of the layer using the Kaman 7200 Displacement Measuring System. The probe is placed on the surface. One person (the inspector) reads the instrument, while another(the technician) records the thickness. Measurements are taken at one foot intervals. After the measurements are taken, the number of low readings is tabulated. If more than 10 percent of the points fall below the minimum value, there is a design review, and the part may be stripped of coating, and a new coating is applied. There is no other analysis.

Space Shuttle Transportation (Roll-Out) Loads Diagnostics

NASA Technical Reports Server (NTRS)

Elliott, Kenny B.; Buehrle, Ralph D.; James, George H.; Richart, Jene A.

2005-01-01

The Space Transportation System (STS) consists of three primary components; an Orbiter Vehicle, an External Fuel Tank, and two Solid Rocket Boosters. The Orbiter Vehicle and Solid Rocket Boosters are reusable components, and as such, they are susceptible to durability issues. Recently, the fatigue load spectra for these components have been updated to include load histories acquired during the rollout phase of the STS processing for flight. Using traditional program life assessment techniques, the incorporation of these "rollout" loads produced unacceptable life estimates for certain Orbiter structural members. As a result, the Space Shuttle System Engineering and Integration Office has initiated a program to re-assess the method used for developing the "rollout" loads and performing the life assessments. In the fall of 2003 a set of tests were preformed to provide information to either validate existing load spectra estimation techniques or generate new load spectra estimation methods. Acceleration and strain data were collected from two rollouts of a partial-stack configuration of the Space Shuttle. The partial stack configuration consists of two Solid Rocket Boosters tied together at the upper External Tank attachment locations mounted on the Mobile Launch Platform carried by a Crawler Transporter (CT). In the current analysis, the data collected from this test is examined for consistency in speed, surface condition effects, and the characterization of the forcing function. It is observed that the speed of the CT is relatively stable. The dynamic response acceleration of the partial-stack is slightly sensitive to the surface condition of the road used for transport, and the dynamic response acceleration of the partial-stack generally increases as the transport speed increases. However, the speed sensitivity is dependent on the measurement location. Finally, the character of the forcing function is narrow-banded with the primary drivers being harmonics of two CT speed dependent excitations. One source is an excitation due to the CT treads striking the road surface, and the second is unknown.

Models for the Immediate Environment of Ions in Aqueous Solutions of Neodymium Chloride

NASA Astrophysics Data System (ADS)

Smirnov, P. R.; Grechin, O. V.

2018-01-01

Radial distribution functions of neodymium chloride aqueous solutions in a wide range of concentrations under ambient conditions are calculated from experimental data obtained earlier via X-ray diffraction analysis. Different models of the structural organization of the system are developed. The optimum versions are determined by calculating theoretical functions for each model and comparing their fit to the experimental functions. Such quantitative characteristics of the immediate environment of Nd3+ and Cl- ions as coordination numbers, interparticle distances, and varieties of ion pairs are determined. It is shown that the average number of water molecules in the first coordination sphere of the cation falls from 9 to 6.2 as the concentration rises. The structure of the systems over the whole range of concentrations is determined by ion associates of the noncontact type.

Water Surface Impact and Ricochet of Deformable Elastomeric Spheres

NASA Astrophysics Data System (ADS)

Hurd, Randy C.

Soft and deformable silicone rubber spheres ricochet from a water surface when rigid spheres and disks (or skipping stones) cannot. This dissertation investigates why these objects are able to skip so successfully. High speed cameras allow us to see that these unique spheres deform significantly as they impact the water surface, flattening into pancake-like shapes with greater area. Though the water entry behavior of deformable spheres deviates from that of rigid spheres, our research shows that if this deformation is accounted for, their behavior can be predicted from previously established methods. Soft spheres skip more easily because they deform significantly when impacting the water surface. We present a diagram which enables the prediction of a ricochet from sphere impact conditions such as speed and angle. Experiments and mathematical representations of the sphere skipping both show that these deformable spheres skip more readily because deformation momentarily increases sphere area and produces an attack angle with the water which is favorable to skipping. Predictions from our mathematical representation of sphere skipping agree strongly with observations from experiments. Even when a sphere was allowed to skip multiple times in the laboratory, the mathematical predictions show good agreement with measured impact conditions through subsequent skipping events. While studying multiple impact events in an outdoor setting, we discovered a previously unidentified means of skipping, which is unique to deformable spheres. This new skipping occurs when a relatively soft sphere first hits the water at a high speed and low impact angle and the sphere begins to rotate very quickly. This quick rotation causes the sphere to stretch into a shape similar to an American football and maintain this shape while it spins. The sphere is observed to move nearly parallel with the water surface with the tips of this "football" dipping into the water as it rotates and the sides passing just over the surface. This sequence of rapid impact events give the impression that the sphere is walking across the water surface.

Collinear swimmer propelling a cargo sphere at low Reynolds number.

PubMed

Felderhof, B U

2014-11-01

The swimming velocity and rate of dissipation of a linear chain consisting of two or three little spheres and a big sphere is studied on the basis of low Reynolds number hydrodynamics. The big sphere is treated as a passive cargo, driven by the tail of little spheres via hydrodynamic and direct elastic interaction. The fundamental solution of Stokes equations in the presence of a sphere with a no-slip boundary condition, as derived by Oseen, is used to model the hydrodynamic interactions between the big sphere and the little spheres.

Computer modeling of current collection by the CHARGE-2 mother payload

NASA Technical Reports Server (NTRS)

Mandell, M. J.; Lilley, J. R., Jr.; Katz, I.; Neubert, T.; Myers, Neil B.

1990-01-01

The three-dimensional computer codes NASCAP/LEO and POLAR have been used to calculate current collection by the mother payload of the CHARGE-2 rocket under conditions of positive and negative potential up to several hundred volts. For negative bias (ion collection), the calculations lie about 25 percent above the data, indicating that the ions were less dense, colder, or heavier than the input parameters. For positive bias (electron collection), NASCAP/LEO and POLAR calculations show similar agreement with the measurements at the highest altitudes. This agreement indicates that the current is classically magnetically limited, even during electron beam emission. However, the calculated values fall well below the data at lower altitudes. It is suggested that beam-plasma-neutral interactions are responsible for the high values of collected current at altitudes below 240 km.

Solidification of Undercooled Melts of Al-Based Alloys on Earth and in Space

NASA Astrophysics Data System (ADS)

Herlach, Dieter M.; Burggraf, Stefan; Galenko, Peter; Gandin, Charles-André; Garcia-Escorial, Asuncion; Henein, Hani; Karrasch, Christian; Mullis, Andrew; Rettenmayr, Markus; Valloton, Jonas

2017-08-01

Containerless processing of droplets and drops by atomization and electromagnetic levitation are applied to undercool metallic melts and alloys prior to solidification. Heterogeneous nucleation on crucible walls is completely avoided giving access to large undercoolings. Experiments are performed both under terrestrial (1 g) conditions and in reduced gravity ( µg) as well. Microgravity conditions are realized by the free fall of small droplets during atomization of a spray of droplets, individual drops in a drop tube and by electromagnetic levitation of drops during parabolic flights, sounding rocket missions, and using the electro-magnetic levitator multi-user facility on board the International Space Station. The comparison of both sets of experiments in 1 g and µg leads to an estimation of the influence of forced convection on dendrite growth kinetics and microstructure evolution.

Motion Simulator

NASA Technical Reports Server (NTRS)

1993-01-01

MOOG, Inc. supplies hydraulic actuators for the Space Shuttle. When MOOG learned NASA was interested in electric actuators for possible future use, the company designed them with assistance from Marshall Space Flight Center. They also decided to pursue the system's commercial potential. This led to partnership with InterActive Simulation, Inc. for production of cabin flight simulators for museums, expositions, etc. The resulting products, the Magic Motion Simulator 30 Series, are the first electric powered simulators. Movements are computer-guided, including free fall to heighten the sense of moving through space. A projection system provides visual effects, and the 11 speakers of a digital laser based sound system add to the realism. The electric actuators are easier to install, have lower operating costs, noise, heat and staff requirements. The U.S. Space & Rocket Center and several other organizations have purchased the simulators.

KSC-08pd3746

NASA Image and Video Library

2008-11-19

CAPE CANAVERAL, Fla. – At the Parachute Refurbishment Facility at NASA's Kennedy Space Center in Florida, a worker checks the parachute lines, recovered from sea after the launch of space shuttle Endeavour on the STS-126 mission, as they move into the 30,000-gallon washer. The parachutes are used to slow the descent of the solid rocket boosters that are jettisoned during liftoff. After washing, the monorail will move the parachutes into a huge dryer heated with 140-degree air at 13,000 cubic feet per minute. One pilot, one drogue and three main canopies per booster slow the booster’s fall from about 360 mph to 50 mph. After the chutes are cleaned and repaired, they must be carefully packed into their bags so they will deploy correctly the next time they are used. Photo credit: NASA/Jim Grossmann

KSC-08pd3748

NASA Image and Video Library

2008-11-19

CAPE CANAVERAL, Fla. – At the Parachute Refurbishment Facility at NASA's Kennedy Space Center in Florida, another parachute recovered from sea after the launch of space shuttle Endeavour on the STS-126 mission is unwound from a large turnstile. After their recovery, the parachutes are untangled, hung on a monorail system and transported into a 30,000-gallon washer and a huge dryer heated with 140-degree air at 13,000 cubic feet per minute. The parachutes are used to slow the descent of the solid rocket boosters that are jettisoned during liftoff. One pilot, one drogue and three main canopies per booster slow the booster’s fall from about 360 mph to 50 mph. After the chutes are cleaned and repaired, they must be carefully packed into their bags so they will deploy correctly the next time they are used. Photo credit: NASA/Jim Grossmann

KSC-08pd3745

NASA Image and Video Library

2008-11-19

CAPE CANAVERAL, Fla. – At the Parachute Refurbishment Facility at NASA's Kennedy Space Center in Florida, a worker checks the parachute lines suspended from the monorail system. The parachutes were recovered from sea after the launch of space shuttle Endeavour on the STS-126 mission The parachutes are used to slow the descent of the solid rocket boosters that are jettisoned during liftoff. The monorail will transport each parachute into a 30,000-gallon washer and a huge dryer heated with 140-degree air at 13,000 cubic feet per minute. One pilot, one drogue and three main canopies per booster slow the booster’s fall from about 360 mph to 50 mph. After the chutes are cleaned and repaired, they must be carefully packed into their bags so they will deploy correctly the next time they are used. Photo credit: NASA/Jim Grossmann

Stem/progenitor cells derived from the cochlear sensory epithelium give rise to spheres with distinct morphologies and features.

PubMed

Diensthuber, Marc; Oshima, Kazuo; Heller, Stefan

2009-06-01

Nonmammalian vertebrates regenerate lost sensory hair cells by means of asymmetric division of supporting cells. Inner ear or lateral line supporting cells in birds, amphibians, and fish consequently serve as bona fide stem cells resulting in high regenerative capacity of hair cell-bearing organs. Hair cell regeneration does not happen in the mammalian cochlea, but cells with proliferative capacity can be isolated from the neonatal cochlea. These cells have the ability to form clonal floating colonies, so-called spheres, when cultured in nonadherent conditions. We noticed that the sphere population derived from mouse cochlear sensory epithelium cells was heterogeneous, consisting of morphologically distinct sphere types, hereby classified as solid, transitional, and hollow. Cochlear sensory epithelium-derived stem/progenitor cells initially give rise to small solid spheres, which subsequently transition into hollow spheres, a change that is accompanied by epithelial differentiation of the majority of sphere cells. Only solid spheres, and to a lesser extent, transitional spheres, appeared to harbor self-renewing stem cells, whereas hollow spheres could not be consistently propagated. Solid spheres contained significantly more rapidly cycling Pax-2-expressing presumptive otic progenitor cells than hollow spheres. Islet-1, which becomes upregulated in nascent sensory patches, was also more abundant in solid than in hollow spheres. Likewise, hair cell-like cells, characterized by the expression of multiple hair cell markers, differentiated in significantly higher numbers in cell populations derived from solid spheres. We conclude that cochlear sensory epithelium cell populations initially give rise to small solid spheres that have self-renewing capacity before they subsequently convert into hollow spheres, a process that is accompanied by loss of stemness and reduced ability to spontaneously give rise to hair cell-like cells. Solid spheres might, therefore, represent the most suitable sphere type for cell-based assays or animal model transplantation studies aimed at development of cell replacement therapies.

Measurement of the Casimir Force between Two Spheres

NASA Astrophysics Data System (ADS)

Garrett, Joseph L.; Somers, David A. T.; Munday, Jeremy N.

2018-01-01

Complex interaction geometries offer a unique opportunity to modify the strength and sign of the Casimir force. However, measurements have traditionally been limited to sphere-plate or plate-plate configurations. Prior attempts to extend measurements to different geometries relied on either nanofabrication techniques that are limited to only a few materials or slight modifications of the sphere-plate geometry due to alignment difficulties of more intricate configurations. Here, we overcome this obstacle to present measurements of the Casimir force between two gold spheres using an atomic force microscope. Force measurements are alternated with topographical scans in the x -y plane to maintain alignment of the two spheres to within approximately 400 nm (˜1 % of the sphere radii). Our experimental results are consistent with Lifshitz's theory using the proximity force approximation (PFA), and corrections to the PFA are bounded using nine sphere-sphere and three sphere-plate measurements with spheres of varying radii.

Viscous constraints on predator:food size ratios in microscale feeding

NASA Astrophysics Data System (ADS)

Jabbarzadeh, Mehdi; Fu, Henry

2014-11-01

Small organisms such as protists or copepods may try to capture food by manipulating food with cilia, limbs, or feeding appendages. At these small scales, viscous flow may complicate the ability of a feeding appendage to closely approach a food particle. As a simplified but tractable model of such feeding approach, we consider the problem of two spheres approaching in a Stokes fluid. The first ``feeding'' sphere, which represents a body part or feeding appendage, is pushed with a constant force towards a force-free ``food'' sphere. When the feeding sphere reaches within a cutoff distance of the food sphere we assume that nonhydrodynamic interactions lead to capture. We examine approach for a range of size ratios between the feeding and food sphere. To investigate the approach efficiency, we examine the time required for the feeding sphere to capture the food sphere, as well as how far the feeding sphere must move before it captures the food sphere. We also examine the effect of varying the cutoff distance for capture. We find that hydrodynamic interactions strongly affect the results when the size of the spheres is comparable. We describe what relative sizes between feeding sphere and food particles may be most effective for food capture.

Possibilities of Architectural Lighting to Create New Style

NASA Astrophysics Data System (ADS)

Chudinova, V. G.; Bokova, O. R.

2017-11-01

The article presents the argumentation of the provision on the style-forming potential of the lighting design the sphere of which is interpreted in a wide range of genres. The area of the intersection of form-building technological and artistic aspects lies in the field of ecology which includes not only energy saving, but also the well-being of the human and the society. The theory and practice of designing the night-time image of architectural ensembles, buildings and landscapes develops much slower than the implementation of light solutions in the advertising industry. In most cases, the possibilities of lighting design are used only in the field of decorative lighting despite their huge aesthetic potential and rapidly improving technologies. The request for innovation and uniqueness usually arises on the basis of image and political ambitions of large corporations or for the positioning of powerful brands. The success of such projects becomes a driver for both creation and promotion of innovative solutions. However, in a broader scientific sense, not only the design of artificial light systems but also the optimization of the daylight usage falls into the sphere lighting design. The need for the new methods of architectural shaping is dictated by the need to introduce in the building of resource-saving lighting technologies, ecological infrastructure including alternative energy sources. The article gives the examples of different lighting design genres supplemented with illustrations. The conclusions concern the prospective directions and tasks of scientific research in the field of lighting design.

High temperature insulation for ceramic matrix composites

DOEpatents

Merrill, Gary B.; Morrison, Jay Alan

2001-01-01

A ceramic composition is provided to insulate ceramic matrix composites under high temperature, high heat flux environments. The composition comprises a plurality of hollow oxide-based spheres of various dimensions, a phosphate binder, and at least one oxide filler powder, whereby the phosphate binder partially fills gaps between the spheres and the filler powders. The spheres are situated in the phosphate binder and the filler powders such that each sphere is in contact with at least one other sphere. The spheres may be any combination of Mullite spheres, Alumina spheres, or stabilized Zirconia spheres. The filler powder may be any combination of Alumina, Mullite, Ceria, or Hafnia. Preferably, the phosphate binder is Aluminum Ortho-Phosphate. A method of manufacturing the ceramic insulating composition and its application to CMC substrates are also provided.

High temperature insulation for ceramic matrix composites

DOEpatents

Merrill, Gary B.; Morrison, Jay Alan

2000-01-01

A ceramic composition is provided to insulate ceramic matrix composites under high temperature, high heat flux environments. The composite comprises a plurality of hollow oxide-based spheres of varios dimentions, a phosphate binder, and at least one oxide filler powder, whereby the phosphate binder partially fills gaps between the spheres and the filler powders. The spheres are situated in the phosphate binder and the filler powders such that each sphere is in contact with at least one other sphere. The spheres may be any combination of Mullite spheres, Alumina spheres, or stabilized Zirconia spheres. The filler powder may be any combination of Alumina, Mullite, Ceria, or Hafnia. Preferably, the phosphate binder is Aluminum Ortho-Phosphate. A method of manufacturing the ceramic insulating composition and its application to CMC substates are also provided.

High temperature insulation for ceramic matrix composites

DOEpatents

Merrill, Gary B.; Morrison, Jay Alan

2004-01-13

A ceramic composition is provided to insulate ceramic matrix composites under high temperature, high heat flux environments. The composition comprises a plurality of hollow oxide-based spheres of various dimensions, a phosphate binder, and at least one oxide filler powder, whereby the phosphate binder partially fills gaps between the spheres and the filler powders. The spheres are situated in the phosphate binder and the filler powders such that each sphere is in contact with at least one other sphere. The spheres may be any combination of Mullite spheres, Alumina spheres, or stabilized Zirconia spheres. The filler powder may be any combination of Alumina, Mullite, Ceria, or Hafnia. Preferably, the phosphate binder is Aluminum Ortho-Phosphate. A method of manufacturing the ceramic insulating composition and its application to CMC substrates are also provided.

Air-Powered Rockets.

ERIC Educational Resources Information Center

Rodriguez, Charley; Raynovic, Jim

This document describes methods for designing and building two types of rockets--rockets from paper and rockets from bottles. Devices used for measuring the heights that the rockets obtain are also discussed. (KHR)

Engineers demonstrate the pocket rocket

NASA Technical Reports Server (NTRS)

1996-01-01

Part of Stennis Space Center's mission with its traveling exhibits is to educate the younger generation on how propulsion systems work. A popular tool is the 'pocket rocket,' which demonstrates how a hybrid rocket works. A hybrid rocket is a cross breed between a solid fuel rocket and a liquid fuel rocket.

Advanced Tactical Booster Technologies: Applications for Long-Range Rocket Systems

DTIC Science & Technology

2016-09-07

Applications for Long-Range Rocket Systems 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR(S) Matthew McKinna, Jason Mossman 5d...technology advantages currently under development for tactical rocket motors which have direct application to land-based long-range rocket systems...increased rocket payload capacity, improved rocket range or increased rocket loadout from the volumetrically constrained environment of a land-based

High-speed schlieren imaging of rocket exhaust plumes

NASA Astrophysics Data System (ADS)

Coultas-McKenney, Caralyn; Winter, Kyle; Hargather, Michael

2016-11-01

Experiments are conducted to examine the exhaust of a variety of rocket engines. The rocket engines are mounted in a schlieren system to allow high-speed imaging of the engine exhaust during startup, steady state, and shutdown. A variety of rocket engines are explored including a research-scale liquid rocket engine, consumer/amateur solid rocket motors, and water bottle rockets. Comparisons of the exhaust characteristics, thrust and cost for this range of rockets is presented. The variety of nozzle designs, target functions, and propellant type provides unique variations in the schlieren imaging.

Electromagnetic Energy Localization and Characterization of Composites

DTIC Science & Technology

2013-01-01

polyhedrons ), and [39] (spheres and a complex yet symmetric structure). With time-domain EM analysis, regular shapes, such as cubes, spheres, and regular...spheres), [40] (spheres, crosses, cylinders, and polyhedrons ), and [41] (spheres and cylinders); and 3-D random mixtures using a frequency-domain finite...element method [42] ( polyhedrons ), and [43], [44] (spheres). Such steady-state analyses are limited as they, for example, do not capture temporal

On use of hybrid rocket propulsion for suborbital vehicles

NASA Astrophysics Data System (ADS)

Okninski, Adam

2018-04-01

While the majority of operating suborbital rockets use solid rocket propulsion, recent advancements in the field of hybrid rocket motors lead to renewed interest in their use in sounding rockets. This paper presents results of optimisation of sounding rockets using hybrid propulsion. An overview of vehicles under development during the last decade, as well as heritage systems is provided. Different propellant combinations are discussed and their performance assessment is given. While Liquid Oxygen, Nitrous Oxide and Nitric Acid have been widely tested with various solid fuels in flight, Hydrogen Peroxide remains an oxidiser with very limited sounding rocket applications. The benefits of hybrid propulsion for sounding rockets are given. In case of hybrid rocket motors the thrust curve can be optimised for each flight, using a flow regulator, depending on the payload and mission. Results of studies concerning the optimal burn duration and nozzle selection are given. Specific considerations are provided for the Polish ILR-33 "Amber" sounding rocket. Low regression rates, which up to date were viewed as a drawback of hybrid propulsion may be used to the benefit of maximising rocket performance if small solid rocket boosters are used during the initial flight period. While increased interest in hybrid propulsion is present, no up-to-date reference concerning use of hybrid rocket propulsion for sounding rockets is available. The ultimate goal of the paper is to provide insight into the sensitivity of different design parameters on performance of hybrid sounding rockets and delve into the potential and challenges of using hybrid rocket technology for expendable suborbital applications.

Two-Dimensional Motions of Rockets

ERIC Educational Resources Information Center

Kang, Yoonhwan; Bae, Saebyok

2007-01-01

We analyse the two-dimensional motions of the rockets for various types of rocket thrusts, the air friction and the gravitation by using a suitable representation of the rocket equation and the numerical calculation. The slope shapes of the rocket trajectories are discussed for the three types of rocket engines. Unlike the projectile motions, the…

History of Solid Rockets

NASA Technical Reports Server (NTRS)

Green, Rebecca

2017-01-01

Solid rockets are of interest to the space program because they are commonly used as boosters that provide the additional thrust needed for the space launch vehicle to escape the gravitational pull of the Earth. Larger, more advanced solid rockets allow for space launch vehicles with larger payload capacities, enabling mankind to reach new depths of space. This presentation will discuss, in detail, the history of solid rockets. The history begins with the invention and origin of the solid rocket, and then goes into the early uses and design of the solid rocket. The evolution of solid rockets is depicted by a description of how solid rockets changed and improved and how they were used throughout the 16th, 17th, 18th, and 19th centuries. Modern uses of the solid rocket include the Solid Rocket Boosters (SRBs) on the Space Shuttle and the solid rockets used on current space launch vehicles. The functions and design of the SRB and the advancements in solid rocket technology since the use of the SRB are discussed as well. Common failure modes and design difficulties are discussed as well.

Terminal energy distribution of blast waves from bursting spheres

NASA Technical Reports Server (NTRS)

Adamczyk, A. A.; Strehlow, R. A.

1977-01-01

The calculation results for the total energy delivered to the surroundings by the burst of an idealized massless sphere containing an ideal gas are presented. The logic development of various formulas for sphere energy is also presented. For all types of sphere bursts the fraction of the total initial energy available in the sphere that is delivered to the surroundings is shown to lie between that delivered for the constant pressure addition of energy to a source region and that delivered by isentropic expansion of the sphere. The relative value of E sub/Q increases at fixed sphere pressure/surrounding pressure as sphere temperature increases because the velocity of sound increases.

Development of Mechanics in Support of Rocket Technology in Ukraine

NASA Astrophysics Data System (ADS)

Prisnyakov, Vladimir

2003-06-01

The paper analyzes the advances of mechanics made in Ukraine in resolving various problems of space and rocket technology such as dynamics and strength of rockets and rocket engines, rockets of different purpose, electric rocket engines, and nonstationary processes in various systems of rockets accompanied by phase transitions of working media. Achievements in research on the effect of vibrations and gravitational fields on the behavior of space-rocket systems are also addressed. Results obtained in investigating the reliability and structural strength durability conditions for nuclear installations, solid- and liquid-propellant engines, and heat pipes are presented

NASA sounding rockets, 1958 - 1968: A historical summary

NASA Technical Reports Server (NTRS)

Corliss, W. R.

1971-01-01

The development and use of sounding rockets is traced from the Wac Corporal through the present generation of rockets. The Goddard Space Flight Center Sounding Rocket Program is discussed, and the use of sounding rockets during the IGY and the 1960's is described. Advantages of sounding rockets are identified as their simplicity and payload simplicity, low costs, payload recoverability, geographic flexibility, and temporal flexibility. The disadvantages are restricted time of observation, localized coverage, and payload limitations. Descriptions of major sounding rockets, trends in vehicle usage, and a compendium of NASA sounding rocket firings are also included.

Design of a Six Degree of Freedom Thrust Sensor for a Hybrid Rocket

NASA Astrophysics Data System (ADS)

McGehee, Tripp

2005-03-01

A hybrid rocket is composed of a solid fuel and a separate liquid or gaseous oxidizer. These rockets may be throttled like liquid rockets, are safer than solid rockets, and are much less complex than liquid rockets. However, hybrid rockets produce thrust oscillations that are not practical for large scale use. A lab scale hybrid rocket at the University of Arkansas at Little Rock (UALR) Hybrid Rocket Facility is used to develop sensors to measure physical properties of hybrid rockets. Research is currently being conducted to design a six degree of freedom force sensor to measure the thrust and torque in all three spatial dimensions. The current design mounts the rocket in a rigid cage and connects the cage to a solid table by six sensor legs. The legs utilize strain gauges and a Wheatstone bridge to produce a voltage proportional to the force on the leg. A detailed description of the cage design and the design process will be given.

Congreve Rockets

NASA Technical Reports Server (NTRS)

2004-01-01

The British fired Congreve rockets against the United States in the War of 1812. As a result Francis Scott Key coined the phrase the 'rocket's red glare.' Congreve had used a 16-foot guide stick to help stabilize his rocket. William Hale, another British inventor, invented the stickless rocket in 1846. The U.S. Army used the Hale rocket more than 100 years ago in the war with Mexico. Rockets were also used to a limited extent by both sides in the American Civil War.

Early Rockets

NASA Image and Video Library

2004-04-15

The British fired Congreve rockets against the United States in the War of 1812. As a result Francis Scott Key coined the phrase the "rocket's red glare." Congreve had used a 16-foot guide stick to help stabilize his rocket. William Hale, another British inventor, invented the stickless rocket in 1846. The U.S. Army used the Hale rocket more than 100 years ago in the war with Mexico. Rockets were also used to a limited extent by both sides in the American Civil War.

KSC-05PD-0022

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. A tugboat maneuvers the barge carrying the newly redesigned External Tank (ET), designated for use on Return to Flight mission STS-114, toward the dock at the Launch Complex 39 Area Turn Basin. The ET can be seen inside the barge. The External Tank arrived safely early this morning at Port Canaveral, Fla., after an approximately 900-mile journey at sea. It departed from the Michoud Assembly Facility in New Orleans Dec. 31 and was transported on the Pegasus, NASAs specially designed barge, pulled by Solid Rocket Booster retrieval ship Liberty Star. At the port, the barge was then hooked up to the tugs for the last part of the journey to the Turn Basin. Next, the External Tank will be off-loaded from the barge and transported to the Vehicle Assembly Building for its final checkout and mating to the twin Solid Rocket Boosters and orbiter Discovery. NASA and Lockheed Martin Corp. spent nearly two years modifying the 15-story, bronze-colored tank to make it safer for liftoff. Among dozens of changes is a redesigned forward bipod fitting -- a design that meets the recommendation of the Columbia Accident Investigation Board to reduce the risk to the Space Shuttle from falling debris during ascent. STS-114 is targeted for a launch opportunity beginning in May. The seven-member Discovery crew will fly to the International Space Station primarily to test and evaluate new procedures for flight safety, including Space Shuttle inspection and repair techniques.

KSC-05PD-0020

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. The newly redesigned External Tank, designated for use on Return to Flight mission STS-114, moves slowly toward its destination, the dock at the Launch Complex 39 Area Turn Basin, propelled by two tugboats. At left in the background is Launch Pad 39A. The External Tank arrived safely early this morning at Port Canaveral, Fla., after an approximately 900-mile journey at sea. It departed from the Michoud Assembly Facility in New Orleans Dec. 31 and was transported on the Pegasus, NASAs specially designed barge, pulled by Solid Rocket Booster retrieval ship Liberty Star. At the port, the barge was then hooked up to the tugs for the last part of the journey to the Turn Basin. Next, the External Tank will be off-loaded from the barge and transported to the Vehicle Assembly Building for its final checkout and mating to the twin Solid Rocket Boosters and orbiter Discovery. NASA and Lockheed Martin Corp. spent nearly two years modifying the 15-story, bronze-colored tank to make it safer for liftoff. Among dozens of changes is a redesigned forward bipod fitting -- a design that meets the recommendation of the Columbia Accident Investigation Board to reduce the risk to the Space Shuttle from falling debris during ascent. STS-114 is targeted for a launch opportunity beginning in May. The seven-member Discovery crew will fly to the International Space Station primarily to test and evaluate new procedures for flight safety, including Space Shuttle inspection and repair techniques.

KSC-05PD-0023

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. Tugboats maneuver the barge carrying the newly redesigned External Tank (ET), designated for use on Return to Flight mission STS-114, closer to the dock at the Launch Complex 39 Area Turn Basin. The ET can be seen inside the barge. The External Tank arrived safely early this morning at Port Canaveral, Fla., after an approximately 900-mile journey at sea. It departed from the Michoud Assembly Facility in New Orleans Dec. 31 and was transported on the Pegasus, NASAs specially designed barge, pulled by Solid Rocket Booster retrieval ship Liberty Star. At the port, the barge was then hooked up to the tugs for the last part of the journey to the Turn Basin. Next, the External Tank will be off-loaded from the barge and transported to the Vehicle Assembly Building for its final checkout and mating to the twin Solid Rocket Boosters and orbiter Discovery. NASA and Lockheed Martin Corp. spent nearly two years modifying the 15-story, bronze-colored tank to make it safer for liftoff. Among dozens of changes is a redesigned forward bipod fitting -- a design that meets the recommendation of the Columbia Accident Investigation Board to reduce the risk to the Space Shuttle from falling debris during ascent. STS-114 is targeted for a launch opportunity beginning in May. The seven- member Discovery crew will fly to the International Space Station primarily to test and evaluate new procedures for flight safety, including Space Shuttle inspection and repair techniques.

KSC-05PD-0030

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. Tugboats maneuver the barge carrying the newly redesigned External Tank (ET), designated for use on Return to Flight mission STS-114, closer to the dock at the Launch Complex 39 Area Turn Basin. The ET can be seen inside the barge. The External Tank arrived safely early this morning at Port Canaveral, Fla., after an approximately 900-mile journey at sea. It departed from the Michoud Assembly Facility in New Orleans Dec. 31 and was transported on the Pegasus, NASAs specially designed barge, pulled by Solid Rocket Booster retrieval ship Liberty Star. At the port, the barge was then hooked up to the tugs for the last part of the journey. Next, the External Tank will be off-loaded from the barge and transported to the Vehicle Assembly Building for its final checkout and mating to the twin Solid Rocket Boosters and orbiter Discovery. NASA and Lockheed Martin Corp. spent nearly two years modifying the 15-story, bronze-colored tank to make it safer for liftoff. Among dozens of changes is a redesigned forward bipod fitting -- a design that meets the recommendation of the Columbia Accident Investigation Board to reduce the risk to the Space Shuttle from falling debris during ascent. STS-114 is targeted for a launch opportunity beginning in May. The seven-member Discovery crew will fly to the International Space Station primarily to test and evaluate new procedures for flight safety, including Space Shuttle inspection and repair techniques.

KSC-05PD-0021

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. The newly redesigned External Tank, designated for use on Return to Flight mission STS-114, moves slowly toward its destination, the dock at the Launch Complex 39 Area Turn Basin, propelled by two tugboats. At left in the background is Launch Pad 39A. The External Tank arrived safely early this morning at Port Canaveral, Fla., after an approximately 900-mile journey at sea. It departed from the Michoud Assembly Facility in New Orleans Dec. 31 and was transported on the Pegasus, NASAs specially designed barge, pulled by Solid Rocket Booster retrieval ship Liberty Star. At the port, the barge was then hooked up to the tugs for the last part of the journey to the Turn Basin. Next, the External Tank will be off-loaded from the barge and transported to the Vehicle Assembly Building for its final checkout and mating to the twin Solid Rocket Boosters and orbiter Discovery. NASA and Lockheed Martin Corp. spent nearly two years modifying the 15-story, bronze-colored tank to make it safer for liftoff. Among dozens of changes is a redesigned forward bipod fitting -- a design that meets the recommendation of the Columbia Accident Investigation Board to reduce the risk to the Space Shuttle from falling debris during ascent. STS-114 is targeted for a launch opportunity beginning in May. The seven-member Discovery crew will fly to the International Space Station primarily to test and evaluate new procedures for flight safety, including Space Shuttle inspection and repair techniques.

KSC-05PD-0029

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. Tugboats maneuver the barge carrying the newly redesigned External Tank (ET), designated for use on Return to Flight mission STS-114, closer to the dock at the Launch Complex 39 Area Turn Basin. The ET can be seen inside the barge. The External Tank arrived safely early this morning at Port Canaveral, Fla., after an approximately 900-mile journey at sea. It departed from the Michoud Assembly Facility in New Orleans Dec. 31 and was transported on the Pegasus, NASAs specially designed barge, pulled by Solid Rocket Booster retrieval ship Liberty Star. At the port, the barge was then hooked up to the tugs for the last part of the journey to the Turn Basin. Next, the External Tank will be off-loaded from the barge and transported to the Vehicle Assembly Building for its final checkout and mating to the twin Solid Rocket Boosters and orbiter Discovery. NASA and Lockheed Martin Corp. spent nearly two years modifying the 15-story, bronze-colored tank to make it safer for liftoff. Among dozens of changes is a redesigned forward bipod fitting -- a design that meets the recommendation of the Columbia Accident Investigation Board to reduce the risk to the Space Shuttle from falling debris during ascent. STS-114 is targeted for a launch opportunity beginning in May. The seven- member Discovery crew will fly to the International Space Station primarily to test and evaluate new procedures for flight safety, including Space Shuttle inspection and repair techniques.

History of Solid Rockets

NASA Technical Reports Server (NTRS)

Green, Becky; Hales, Christy

2017-01-01

Solid rockets were created by accident and their design and uses have evolved over time. Solid rockets are more simple and reliable than liquid rockets, but they have reduced performance capability. All solid rockets have a similar set of failure modes.

Template method synthesis of mesoporous carbon spheres and its applications as supercapacitors.

PubMed

Wilgosz, Karolina; Chen, Xuecheng; Kierzek, Krzysztof; Machnikowski, Jacek; Kalenczuk, Ryszard J; Mijowska, Ewa

2012-05-29

Mesoporous carbon spheres (MCS) have been fabricated from structured mesoporous silica sphere using chemical vapor deposition (CVD) with ethylene as a carbon feedstock. The mesoporous carbon spheres have a high specific surface area of 666.8 m2/g and good electrochemical properties. The mechanism of formation mesoporous carbon spheres (carbon spheres) is investigated. The important thing is a surfactant hexadecyl trimethyl ammonium bromide (CTAB), which accelerates the process of carbon deposition. An additional advantage of this surfactant is an increase the yield of product. These mesoporous carbon spheres, which have good electrochemical properties is suitable for supercapacitors.

Template method synthesis of mesoporous carbon spheres and its applications as supercapacitors

NASA Astrophysics Data System (ADS)

Wilgosz, Karolina; Chen, Xuecheng; Kierzek, Krzysztof; Machnikowski, Jacek; Kalenczuk, Ryszard J.; Mijowska, Ewa

2012-05-01

Mesoporous carbon spheres (MCS) have been fabricated from structured mesoporous silica sphere using chemical vapor deposition (CVD) with ethylene as a carbon feedstock. The mesoporous carbon spheres have a high specific surface area of 666.8 m2/g and good electrochemical properties. The mechanism of formation mesoporous carbon spheres (carbon spheres) is investigated. The important thing is a surfactant hexadecyl trimethyl ammonium bromide (CTAB), which accelerates the process of carbon deposition. An additional advantage of this surfactant is an increase the yield of product. These mesoporous carbon spheres, which have good electrochemical properties is suitable for supercapacitors.

Anti-gravity device

NASA Technical Reports Server (NTRS)

Palsingh, S. (Inventor)

1975-01-01

An educational toy useful in demonstrating fundamental concepts regarding the laws of gravity is described. The device comprises a sphere 10 of radius r resting on top of sphere 12 of radius R. The center of gravity of sphere 10 is displaced from its geometrical center by distance D. The dimensions are so related that D((R+r)/r) is greater than r. With the center of gravity of sphere 10 lying on a vertical line, the device is in equilibrium. When sphere 10 is rolled on the surface of sphere 12 it will return to its equilibrium position upon release. This creates an illusion that sphere 10 is defying the laws of gravity. In reality, due to the above noted relationship of D, R, and r, the center of gravity of sphere 10 rises from its equilibrium position as it rolls a short distance up or down the surface of sphere 12.

Formation of giant H II regions following supernova explosions

NASA Technical Reports Server (NTRS)

Sartori, L.

1971-01-01

The principal optical properties of type I supernovae are summarized. These include the light curve and the spectrum. The spectra consist of broad bands with very little continuum. According to the theory presented, the observed light is principally fluorescence, excited in the medium surrounding the supernova by ultraviolet radiation originating from the explosion. It is proposed that the spectrum that impinges on the fluorescent medium while emission is taking place must fall abruptly across the Lyman edge of He II. Such a filtering action is plausibly provided by a much denser internal region, rich in helium, immediately surrounding the exploding object. This will form a Stromgren sphere during the time the intense UV pulse is passing through it. The dense region also slows down the photons below the edge by Thomson scattering, thereby spreading out the UV pulse in time. Various proposed mechanisms for the production of ionization in the Gum nebula are discussed.

Negative vortices: The formation of vortex rings with reversed rotation in viscoelastic liquids

NASA Astrophysics Data System (ADS)

Palacios-Morales, Carlos; Barbosa, Christophe; Solorio, Francisco; Zenit, Roberto

2015-05-01

The formation process of vortex rings in a viscoelastic liquid is studied experimentally considering a piston-cylinder arrangement. Initially, a vortex ring begins to form as fluid is injected from the cylinder into the tank in a manner similar to that observed for Newtonian liquids. For later times, when the piston ceases its motion, the flow changes dramatically. A secondary vortex with reversed spinning direction appears and grows to be as large in size as the original one. The formation process is studied by contrasting the evolution with that obtained for Newtonian liquids with equivalent Reynolds numbers and stroke ratios. We argue that the reversing flow, or negative vortex, results from the combined action of shear and extension rates produced during the vortex formation, in a process similar to that observed behind ascending bubbles and falling spheres in viscoelastic media.

A New Standard for Assessing the Performance of High Contrast Imaging Systems

NASA Astrophysics Data System (ADS)

Jensen-Clem, Rebecca; Mawet, Dimitri; Gomez Gonzalez, Carlos A.; Absil, Olivier; Belikov, Ruslan; Currie, Thayne; Kenworthy, Matthew A.; Marois, Christian; Mazoyer, Johan; Ruane, Garreth; Tanner, Angelle; Cantalloube, Faustine

2018-01-01

As planning for the next generation of high contrast imaging instruments (e.g., WFIRST, HabEx, and LUVOIR, TMT-PFI, EELT-EPICS) matures and second-generation ground-based extreme adaptive optics facilities (e.g., VLT-SPHERE, Gemini-GPI) finish their principal surveys, it is imperative that the performance of different designs, post-processing algorithms, observing strategies, and survey results be compared in a consistent, statistically robust framework. In this paper, we argue that the current industry standard for such comparisons—the contrast curve—falls short of this mandate. We propose a new figure of merit, the “performance map,” that incorporates three fundamental concepts in signal detection theory: the true positive fraction, the false positive fraction, and the detection threshold. By supplying a theoretical basis and recipe for generating the performance map, we hope to encourage the widespread adoption of this new metric across subfields in exoplanet imaging.

Shape and symmetry of heptacoordinate transition-metal complexes: structural trends.

PubMed

Casanova, David; Alemany, Pere; Bofill, Josep M; Alvarez, Santiago

2003-03-17

The stereochemistries of heptacoordinate transition-metal complexes are analyzed by using continuous symmetry and shape measures of their coordination spheres. The distribution of heptacoordination through the transition-metal series is presented based on structural database searches including organometallic and Werner-type molecular complexes, metalloproteins, and extended solids. The most common polyhedron seems to be the pentagonal bipyramid, while different preferences are found for specific families of compounds, as in the complexes with three or four carbonyl or phosphine ligands, which prefer the capped octahedron or the capped trigonal prism rather than the pentagonal bipyramid. The symmetry maps for heptacoordination are presented and shown to be helpful for detecting stereochemical trends. The maximal symmetry interconversion pathways between the three most common polyhedra are defined in terms of symmetry constants and a large number of experimental structures are seen to fall along those paths.

Production and characterization of pure cryogenic inertial fusion targets

NASA Astrophysics Data System (ADS)

Boyd, B. A.; Kamerman, G. W.

An experimental cryogenic inertial fusion target generator and two optical techniques for automated target inspection are described. The generator produces 100 microns diameter solid hydrogen spheres at a rate compatible with fueling requirements of conceptual inertial fusion power plants. A jet of liquified hydrogen is disrupted into droplets by an ultrasonically excited nozzle. The droplets solidify into microspheres while falling through a chamber maintained below the hydrogen triple point pressure. Stable operation of the generator has been demonstrated for up to three hours. The optical inspection techniques are computer aided photomicrography and coarse diffraction pattern analysis (CDPA). The photomicrography system uses a conventional microscope coupled to a computer by a solid state camera and digital image memory. The computer enhances the stored image and performs feature extraction to determine pellet parameters. The CDPA technique uses Fourier transform optics and a special detector array to perform optical processing of a target image.

Computing the apparent centroid of radar targets

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

Lee, C.E.

1996-12-31

A high-frequency multibounce radar scattering code was used as a simulation platform for demonstrating an algorithm to compute the ARC of specific radar targets. To illustrate this simulation process, several targets models were used. Simulation results for a sphere model were used to determine the errors of approximation associated with the simulation; verifying the process. The severity of glint induced tracking errors was also illustrated using a model of an F-15 aircraft. It was shown, in a deterministic manner, that the ARC of a target can fall well outside its physical extent. Finally, the apparent radar centroid simulation based onmore » a ray casting procedure is well suited for use on most massively parallel computing platforms and could lead to the development of a near real-time radar tracking simulation for applications such as endgame fuzing, survivability, and vulnerability analyses using specific radar targets and fuze algorithms.« less

Numerical simulation of divergent rocket-based-combined-cycle performances under the flight condition of Mach 3

NASA Astrophysics Data System (ADS)

Cui, Peng; Xu, WanWu; Li, Qinglian

2018-01-01

Currently, the upper operating limit of the turbine engine is Mach 2+, and the lower limit of the dual-mode scramjet is Mach 4. Therefore no single power systems can operate within the range between Mach 2 + and Mach 4. By using ejector rockets, Rocket-based-combined-cycle can work well in the above scope. As the key component of Rocket-based-combined-cycle, the ejector rocket has significant influence on Rocket-based-combined-cycle performance. Research on the influence of rocket parameters on Rocket-based-combined-cycle in the speed range of Mach 2 + to Mach 4 is scarce. In the present study, influences of Mach number and total pressure of the ejector rocket on Rocket-based-combined-cycle were analyzed numerically. Due to the significant effects of the flight conditions and the Rocket-based-combined-cycle configuration on Rocket-based-combined-cycle performances, flight altitude, flight Mach number, and divergence ratio were also considered. The simulation results indicate that matching lower altitude with higher flight Mach numbers can increase Rocket-based-combined-cycle thrust. For another thing, with an increase of the divergent ratio, the effect of the divergent configuration will strengthen and there is a limit on the divergent ratio. When the divergent ratio is greater than the limit, the effect of divergent configuration will gradually exceed that of combustion on supersonic flows. Further increases in the divergent ratio will decrease Rocket-based-combined-cycle thrust.

Shape Universality Classes in the Random Sequential Adsorption of Nonspherical Particles

NASA Astrophysics Data System (ADS)

Baule, Adrian

2017-07-01

Random sequential adsorption (RSA) of particles of a particular shape is used in a large variety of contexts to model particle aggregation and jamming. A key feature of these models is the observed algebraic time dependence of the asymptotic jamming coverage ˜t-ν as t →∞ . However, the exact value of the exponent ν is not known apart from the simplest case of the RSA of monodisperse spheres adsorbed on a line (Renyi's seminal "car parking problem"), where ν =1 can be derived analytically. Empirical simulation studies have conjectured on a case-by-case basis that for general nonspherical particles, ν =1 /(d +d ˜ ), where d denotes the dimension of the domain, and d ˜ the number of orientational degrees of freedom of a particle. Here, we solve this long-standing problem analytically for the d =1 case—the "Paris car parking problem." We prove, in particular, that the scaling exponent depends on the particle shape, contrary to the original conjecture and, remarkably, falls into two universality classes: (i) ν =1 /(1 +d ˜ /2 ) for shapes with a smooth contact distance, e.g., ellipsoids, and (ii) ν =1 /(1 +d ˜ ) for shapes with a singular contact distance, e.g., spherocylinders and polyhedra. The exact solution explains, in particular, why many empirically observed scalings fall in between these two limits.

Hybrid Rocket Propulsion for Sounding Rocket Applications

NASA Technical Reports Server (NTRS)

1991-01-01

A discussion of the H-225K hybrid rocket motor, produced by the American Rocket Company, is given. The H-225K motor is presented in terms of the following topics: (1) hybrid rocket fundamentals; (2) hybrid characteristics; and (3) hybrid advantages.

An Unusual Rolling-Sphere Phenomenon.

ERIC Educational Resources Information Center

Cromer, Alan

1996-01-01

Discusses the theory behind a study of motion where a hollow plastic sphere racing against a steel sphere in two parallel sections of inclined channeling always reaches the bottom first; once on the floor, however, the steel sphere travels faster, speeding past the plastic sphere when both are about one meter from the base of the track. (JRH)

Porous Ceramic Spheres From Cation Exchange Beads

NASA Technical Reports Server (NTRS)

Dynys, Fred

2005-01-01

This document is a slide presentation that examines the use of a simple templating process to produce hollow ceramic spheres with a pore size of 1 to 10 microns. Using ion exchange process it was determined that the method produces porous ceramic spheres with a unique structure: (i.e., inner sphere surrounded by an outer sphere.)

Early Rockets

NASA Image and Video Library

1940-01-01

The Hermes A-1 rocket was designed by the U. S. Army after capturing the V-2 rocket from the German army at the conclusion of the Second World War. The Hermes A-1 is a modified V-2 rocket; it utilized the German aerodynamic configuration; however, internally it was a completely new design. This rocket was the first designed by the German Rocket Team at Redstone Arsenal in Huntsville, AL.

Finite-size radiation force correction for inviscid spheres in standing waves.

PubMed

Marston, Philip L

2017-09-01

Yosioka and Kawasima gave a widely used approximation for the acoustic radiation force on small liquid spheres surrounded by an immiscible liquid in 1955. Considering the liquids to be inviscid with negligible thermal dissipation, in their approximation the force on the sphere is proportional to the sphere's volume and the levitation position in a vertical standing wave becomes independent of the size. The analysis given here introduces a small correction term proportional to the square of the sphere's radius relative to the aforementioned small-sphere force. The significance of this term also depends on the relative density and sound velocity of the sphere. The improved approximation is supported by comparison with the exact partial-wave-series based radiation force for ideal fluid spheres in ideal fluids.

21 CFR 866.4830 - Rocket immunoelectro-phoresis equipment.

Code of Federal Regulations, 2010 CFR

2010-04-01

... 21 Food and Drugs 8 2010-04-01 2010-04-01 false Rocket immunoelectro-phoresis equipment. 866.4830... § 866.4830 Rocket immunoelectro-phoresis equipment. (a) Identification. Rocket immunoelectrophoresis... called rocket immunoelectrophoresis. In this procedure, an electric current causes the protein in...

21 CFR 866.4830 - Rocket immunoelectro-phoresis equipment.

Code of Federal Regulations, 2011 CFR

2011-04-01

... 21 Food and Drugs 8 2011-04-01 2011-04-01 false Rocket immunoelectro-phoresis equipment. 866.4830... § 866.4830 Rocket immunoelectro-phoresis equipment. (a) Identification. Rocket immunoelectrophoresis... called rocket immunoelectrophoresis. In this procedure, an electric current causes the protein in...

21 CFR 866.4830 - Rocket immunoelectro-phoresis equipment.

Code of Federal Regulations, 2012 CFR

2012-04-01

... 21 Food and Drugs 8 2012-04-01 2012-04-01 false Rocket immunoelectro-phoresis equipment. 866.4830... § 866.4830 Rocket immunoelectro-phoresis equipment. (a) Identification. Rocket immunoelectrophoresis... called rocket immunoelectrophoresis. In this procedure, an electric current causes the protein in...

21 CFR 866.4830 - Rocket immunoelectro-phoresis equipment.

Code of Federal Regulations, 2014 CFR

2014-04-01

... 21 Food and Drugs 8 2014-04-01 2014-04-01 false Rocket immunoelectro-phoresis equipment. 866.4830... § 866.4830 Rocket immunoelectro-phoresis equipment. (a) Identification. Rocket immunoelectrophoresis... called rocket immunoelectrophoresis. In this procedure, an electric current causes the protein in...

21 CFR 866.4830 - Rocket immunoelectro-phoresis equipment.

Code of Federal Regulations, 2013 CFR

2013-04-01

... 21 Food and Drugs 8 2013-04-01 2013-04-01 false Rocket immunoelectro-phoresis equipment. 866.4830... § 866.4830 Rocket immunoelectro-phoresis equipment. (a) Identification. Rocket immunoelectrophoresis... called rocket immunoelectrophoresis. In this procedure, an electric current causes the protein in...

Template method synthesis of mesoporous carbon spheres and its applications as supercapacitors

PubMed Central

2012-01-01

Mesoporous carbon spheres (MCS) have been fabricated from structured mesoporous silica sphere using chemical vapor deposition (CVD) with ethylene as a carbon feedstock. The mesoporous carbon spheres have a high specific surface area of 666.8 m2/g and good electrochemical properties. The mechanism of formation mesoporous carbon spheres (carbon spheres) is investigated. The important thing is a surfactant hexadecyl trimethyl ammonium bromide (CTAB), which accelerates the process of carbon deposition. An additional advantage of this surfactant is an increase the yield of product. These mesoporous carbon spheres, which have good electrochemical properties is suitable for supercapacitors. PMID:22643113

Dispersivity of Bidisperse Packings of Spheres and Evidence for Distinct Random Structures

NASA Astrophysics Data System (ADS)

Scheven, U. M.

2018-05-01

The intrinsic longitudinal and transverse dispersivity of bidisperse random packings of spheres with size ratio 5 ∶1 was determined by pulsed field gradient nuclear magnetic resonance, in the dilute regime where small spheres occupy between 0% and 5% of the packings' volume. Small spheres plugging pores systematically raise the mechanical transverse and longitudinal dispersivity above that of reference packings of monodisperse spheres. NMR-derived porosities, widths of velocity distributions, and dispersivities reveal distinct states of structural disorder above and below a relative sphere concentration n /N =1 , where n and N are the number densities of small and large spheres.

STS-29 Discovery, OV-103, external tank (ET) separation

NASA Image and Video Library

1989-03-13

STS029-72-059 (13 March 1989) --- This 70mm photograph, taken by Astronaut James P. Bagian 16 minutes and 7 seconds after liftoff of Discovery, shows the external fuel tank (ET) against the background of Earth. The tank is falling away from the orbiter following ET separation. The left side shows the burn scar above the solid rocket booster (SRB) forward attach point. The burn is caused by the forward SRB separation motors firing during SRB separation. Post 51-L analysis of the thermal and pressure effects of the separation motor exhaust plume indicate that the scarring is not a safety hazard. However, photographs such as this one were requested for additional missions in order to document the phenomenon and corroborate this conclusion. The photo was made at 15:13:07 GMT, March 13, 1989. It was among the visuals used by the crew at its Mar. 28, 1989 post-flight press conference.

Environmental effects and large space systems

NASA Technical Reports Server (NTRS)

Garrett, H. B.

1981-01-01

When planning large scale operations in space, environmental impact must be considered in addition to radiation, spacecraft charging, contamination, high power and size. Pollution of the atmosphere and space is caused by rocket effluents and by photoelectrons generated by sunlight falling on satellite surfaces even light pollution may result (the SPS may reflect so much light as to be a nuisance to astronomers). Large (100 Km 2) structures also will absorb the high energy particles that impinge on them. Altogether, these effects may drastically alter the Earth's magnetosphere. It is not clear if these alterations will in any way affect the Earth's surface climate. Large structures will also generate large plasma wakes and waves which may cause interference with communications to the vehicle. A high energy, microwave beam from the SPS will cause ionospheric turbulence, affecting UHF and VHF communications. Although none of these effects may ultimately prove critical, they must be considered in the design of large structures.

Whistler mode plasma waves observed on Electron Echo 2

NASA Technical Reports Server (NTRS)

Monson, S. J.; Kellogg, P. J.; Cartwright, D. G.

1976-01-01

Observations of whistler-mode waves associated with beams of electrons injected into the ionosphere are reported. The measurements are from the plasma-wave experiments carried on the Electron Echo 2 sounding rocket launched on September 24, 1972. Over 2000 electron injections were made with durations of 8 ms and 64 ms and pitch angles from 0 to 180 deg. The electric field receivers carried on the ejected nose cone observed strong whistler waves in the range from less than 100 kHz up to the electron cyclotron frequency of 1400 kHz. The whistler characteristics fall into four distinct types depending on pitch angle and gun energy. Both frequency and amplitude showed strong dependence on time from the start of the pulse and pitch angle. Cases of enhancement at the leading edge of a gun pulse, growth during a pulse, and echoes after the end of a pulse were all observed.

Space processing experimental apparatus - A survey

NASA Technical Reports Server (NTRS)

Siebel, M. P.

1977-01-01

The processing of materials in a low-g environment was started approximately 10 years ago. This article surveys the apparatus developed during that period. A low-g environment occurs naturally in a free-flying spacecraft (e.g., in manned flights such as Apollo, Skylab, and ASTP); low-g conditions also occur in other free-falling bodies such as sounding rockets and drop tower capsules. Apparatus has been developed for all these craft. Most of the apparatus described serves to melt and resolidify materials in low g; the material may be contained or, by virtue of the environment, freely floating. Other apparatus for separation of intimately mixed components or species is also described. A general conclusion is drawn that the apparatus addresses only a few of the possibilities available, is still at the experimental stage, and is of laboratory scale. It is predicted that processes showing promise will be scaled up to derive economic advantages in the Shuttle era of space flight.

Experiments on the properties of superfluid helium in zero gravity

NASA Technical Reports Server (NTRS)

Mason, P.; Collins, D.; Petrac, D.; Yang, L.; Edeskuty, F.; Williamson, K.

1976-01-01

The paper describes a research program designed to study the behavior of superfluid liquid helium in low and zero gravity in order to determine the properties which are critically important to its use as a stored cryogen for cooling scientific instruments aboard spacecraft for periods up to several months. The experiment program consists of a series of flights of an experiment package on a free-fall trajectory both on an aircraft and on a rocket. The objectives are to study thickness of thin films of helium as a function of acceleration, heat transfer in thin films, heat transfer across copper-liquid helium interfaces, fluid dynamics of bulk helium in high and low accelerations and under various conditions of rotations, alternate methods of separation of liquid and vapor phases and of efficient venting of the vapor, and undesirable thermomechanical oscillations in the vent pipes. Preliminary results from aircraft tests are discussed.

KSC-08pd3744

NASA Image and Video Library

2008-11-19

CAPE CANAVERAL, Fla. – At the Parachute Refurbishment Facility at NASA's Kennedy Space Center in Florida, workers place rods under the lines of the parachutes recovered from sea after the launch of space shuttle Endeavour on the STS-126 mission to hang them on a monorail system. Behind them, the parachutes are suspended from the monorail. The parachutes are used to slow the descent of the solid rocket boosters that are jettisoned during liftoff. The monorail will transport each parachute into a 30,000-gallon washer and a huge dryer heated with 140-degree air at 13,000 cubic feet per minute. One pilot, one drogue and three main canopies per booster slow the booster’s fall from about 360 mph to 50 mph. After the chutes are cleaned and repaired, they must be carefully packed into their bags so they will deploy correctly the next time they are used. Photo credit: NASA/Jim Grossmann

KSC-08pd3739

NASA Image and Video Library

2008-11-19

CAPE CANAVERAL, Fla. – Parachutes recovered from sea after the launch of space shuttle Endeavour on the STS-126 mission are stretched out at the Parachute Refurbishment Facility at NASA's Kennedy Space Center in Florida to detangle them. The parachutes are used to slow the descent of the solid rocket boosters that are jettisoned during liftoff. After the chutes are returned to the facility following launch, a hanging monorail system is used to transport each parachute into a 30,000-gallon washer and then into a huge dryer heated with 140-de¬gree air at 13,000 cubic feet per minute. One pilot, one drogue and three main canopies per booster slow the booster’s fall from about 360 mph to 50 mph. After the chutes are cleaned and repaired, they must be care¬fully packed into their bags so they will deploy correctly the next time they are used. Photo credit: NASA/Jim Grossmann

Early Rockets

NASA Image and Video Library

2004-04-15

Sir William Congreve developed a rocket with a range of about 9,000 feet. The incendiary rocket used black powder, an iron case, and a 16-foot guide stick. In 1806, British used Congreve rockets to attack Napoleon's headquarters in France. In 1807, Congreve directed a rocket attack against Copenhagen.

Design considerations for a pressure-driven multi-stage rocket

NASA Astrophysics Data System (ADS)

Sauerwein, Steven Craig

2002-01-01

The purpose of this study was to examine the feasibility of using propellant tank pressurization to eliminate the use of high-pressure turbopumps in multi-stage liquid-fueled satellite launchers. Several new technologies were examined to reduce the mass of such a rocket. Composite materials have a greater strength-to-weight ratio than metals and can be used to reduce the weight of rocket propellant tanks and structure. Catalytically combined hydrogen and oxygen can be used to heat pressurization gas, greatly reducing the amount of gas required. Ablatively cooled rocket engines can reduce the complexity and cost of the rocket. Methods were derived to estimate the mass of the various rocket components. These included a method to calculate the amount of gas needed to pressurize a propellant tank by modeling the behavior of the pressurization gas as the liquid propellant flows out of the tank. A way to estimate the mass and size of a ablatively cooled composite cased rocket engine. And a method to model the flight of such a rocket through the atmosphere in conjunction with optimization of the rockets trajectory. The results show that while a liquid propellant rocket using tank pressurization are larger than solid propellant rockets and turbopump driven liquid propellant rockets, they are not impractically large.

Biomolecule-assisted construction of cadmium sulfide hollow spheres with structure-dependent photocatalytic activity.

PubMed

Wei, Chengzhen; Zang, Wenzhe; Yin, Jingzhou; Lu, Qingyi; Chen, Qun; Liu, Rongmei; Gao, Feng

2013-02-25

In this study, we report the synthesis of monodispersive solid and hollow CdS spheres with structure-dependent photocatalytic abilities for dye photodegradation. The monodispersive CdS nanospheres were constructed with the assistance of the soulcarboxymthyi chitosan biopolymer under hydrothermal conditions. The solid CdS spheres were corroded by ammonia to form hollow CdS nanospheres through a dissolution-reprecipitation mechanism. Their visible-light photocatalytic activities were investigated, and the results show that both the solid and the hollow CdS spheres have visible-light photocatalytic abilities for the photodegradation of dyes. The photocatalytic properties of the CdS spheres were demonstrated to be structure dependent. Although the nanoparticles comprising the hollow spheres have larger sizes than those comprising the solid spheres, the hollow CdS spheres have better photocatalytic performances than the solid CdS spheres, which can be attributed to the special hollow structure. Copyright © 2013 WILEY-VCH Verlag GmbH & Co. KGaA, Weinheim.

Microwave-Assisted Solvothermal Synthesis of VO2 Hollow Spheres and Their Conversion into V2O5 Hollow Spheres with Improved Lithium Storage Capability.

PubMed

Pan, Jing; Zhong, Li; Li, Ming; Luo, Yuanyuan; Li, Guanghai

2016-01-22

Monodispersed hierarchically structured V2O5 hollow spheres were successfully obtained from orthorhombic VO2 hollow spheres, which are in turn synthesized by a simple template-free microwave-assisted solvothermal method. The structural evolution of VO2 hollow spheres has been studied and explained by a chemically induced self-transformation process. The reaction time and water content in the reaction solution have a great influence on the morphology and phase structure of the resulting products in the solvothermal reaction. The diameter of the VO2 hollow spheres can be regulated simply by changing vanadium ion content in the reaction solution. The VO2 hollow spheres can be transformed into V2O5 hollow spheres with nearly no morphological change by annealing in air. The nanorods composed of V2O5 hollow spheres have an average length of about 70 nm and width of about 19 nm. When used as a cathode material for lithium-ion batteries, the V2O5 hollow spheres display a diameter-dependent electrochemical performance, and the 440 nm hollow spheres show the highest specific discharge capacity of 377.5 mAhg(-1) at a current density of 50 mAg(-1) , and are better than the corresponding solid spheres and nanorod assemblies. © 2016 WILEY-VCH Verlag GmbH & Co. KGaA, Weinheim.

Triassico: A Sphere Positioning System for Surface Studies with IBA Techniques

NASA Astrophysics Data System (ADS)

Fontana, Cristiano L.; Doyle, Barney L.

We propose here a novel device, called the Triassico, to microscopically study the entire surface of millimeter-sized spheres. The sphere dimensions can be as small as 1 mm, and the upper limit defined only by the power and by the mechanical characteristics of the motors used. Three motorized driving rods are arranged so an equilateral triangle is formed by the rod's axes, on such a triangle the sphere sits. Movement is achieved by rotating the rods with precise relative speeds and by exploiting the friction between the sphere and the rods surfaces. The sphere can be held in place by gravity or by an opposing trio of rods. By rotating the rods with specific relative angular velocities, a net torque can be exerted on the sphere which then rotates. No repositioning of the sphere or of the motors is needed to cover the full surface with the investigating tools. An algorithm was developed to position the sphere at any arbitrary polar and azimuthal angle. The algorithm minimizes the number of rotations needed by the rods, in order to efficiently select a particular position on the sphere surface. A prototype Triassico was developed for the National Ignition Facility, of the Lawrence Livermore National Laboratory (Livermore, California, USA), as a sphere manipulation apparatus for ion microbeam analysis at Sandia National Laboratories (Albuquerque, NM, USA) of Xe-doped DT inertial confinement fusion fuel spheres. Other applications span from samples orientation, ball bearing manufacturing, or jewelry.

Swapping Rocks: Ejection and Exchange of Surface Material Among the Terrestrial Planets

NASA Astrophysics Data System (ADS)

Melosh, H. J.; Tonks, W. B.

1993-07-01

The discovery of meteorites originating from both the Moon and Mars has led to the realization that major impacts can eject material from planetary-sized objects. Although there is not yet any direct proof, there appears to be no reason why such impacts cannot eject material from the surfaces of Earth and Venus as well. Because of this possibility, and in view of the implications of such exchange for biological evolution, we examined the orbital evolution and ultimate fate of ejecta from each of the terrestrial planets. This work employed an Opik-type orbital evolution model in which both planets and ejected particles follow elliptical orbits about the Sun, with uniformly precessing arguments of perihelion and ascending nodes. An encounter takes place when the particle passes within the sphere of influence of the planet. When this occurs, the encounter is treated as a two-body scattering event, with a randomly chosen impact parameter within the sphere of influence. If the impact parameter is less than the planet's radius, an impact is scored. Otherwise, the scattered particle either takes up a new Keplerian orbit or is ejected from the solar system. We incorporated several different space erosion models and examined the full matrix of possible outcomes of ejection from each planet in random directions with velocities at great distance from the planet of 0.5, 2.5, and 5.0 km/s. Each run analyzed the evolution of 5000 particles to achieve sufficient statistical resolution. Both the ultimate fate and median transit times of particles was recorded. The results show very little dependence on velocity of ejection. Mercury ejecta is nearly all reaccreted by Mercury or eroded in space--very little ever evolves to cross the orbits of the other planets (a few percent impact Venus). The median time between ejection and reimpact is about 30 m.y. for all erosion models. Venus ejecta is mostly reaccreted by Venus, but a significant fraction (about 30%) falls on the Earth with a median transit time of 12 m.y. Of the remainder, a few percent strike Mars and a larger fraction (about 20%) are ejected from the solar system by Jupiter. Earth ejecta is also mainly reaccreted by the Earth, but about 30% strike Venus within 15 m.y. and 5% strike Mars within 150 m.y. Again, about 20% of Earth ejecta is thrown out of the solar system by Jupiter. Mars ejecta is more equitably distributed: Nearly equal fractions fall on Earth and Venus, slightly more are accreted to Mars, and a few percent strike Mercury. About 20% of Mars ejecta is thrown out of the solar system by Jupiter. The larger terrestrial planets, Venus and Earth, thus readily exchange ejecta. Mars ejecta largely falls on Venus and Earth, but Mars only receives a small fraction of their ejecta. A substantial fraction of ejecta from all the terrestrial planets (except Mercury) is thrown out of the solar system by Jupiter, a fact that may have some implications for the panspermia mechanism of spreading life through the galaxy. From the standpoint of collecting meteorites on Earth, in addition to martian and lunar meteorites, we should expect someday to find meteorites from Earth itself (Earth rocks that have spent a median time of 5 m.y. in space before falling again on the Earth) and from Venus.

Indians Repulse British With Rocket

NASA Technical Reports Server (NTRS)

2004-01-01

During the early introduction of rockets to Europe, they were used only as weapons. Enemy troops in India repulsed the British with rockets. Later, in Britain, Sir William Congreve developed a rocket that could fire to about 9,000 feet. The British fired Congreve rockets against the United States in the War of 1812.

World Data Center A (rockets and satellites) catalogue of data. Volume 1, part A: Sounding rockets

NASA Technical Reports Server (NTRS)

1972-01-01

A cumulative listing of all scientifically successful rockets that have been identified from various sources is presented. The listing starts with the V-2 rocket launched on 7 March 1947 and contains all rockets identified up to 31 December 1971.

16 CFR 1507.10 - Rockets with sticks.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 16 Commercial Practices 2 2011-01-01 2011-01-01 false Rockets with sticks. 1507.10 Section 1507.10... FIREWORKS DEVICES § 1507.10 Rockets with sticks. Rockets with sticks (including skyrockets and bottle rockets) shall utilize a straight and rigid stick to provide a direct and stable flight. Such sticks shall...

Early Rockets

NASA Image and Video Library

2004-04-15

During the early introduction of rockets to Europe, they were used only as weapons. Enemy troops in India repulsed the British with rockets. Later, in Britain, Sir William Congreve developed a rocket that could fire to about 9,000 feet. The British fired Congreve rockets against the United States in the War of 1812.

16 CFR 1507.10 - Rockets with sticks.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 16 Commercial Practices 2 2012-01-01 2012-01-01 false Rockets with sticks. 1507.10 Section 1507.10... FIREWORKS DEVICES § 1507.10 Rockets with sticks. Rockets with sticks (including skyrockets and bottle rockets) shall utilize a straight and rigid stick to provide a direct and stable flight. Such sticks shall...

16 CFR 1507.10 - Rockets with sticks.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 16 Commercial Practices 2 2010-01-01 2010-01-01 false Rockets with sticks. 1507.10 Section 1507.10... FIREWORKS DEVICES § 1507.10 Rockets with sticks. Rockets with sticks (including skyrockets and bottle rockets) shall utilize a straight and rigid stick to provide a direct and stable flight. Such sticks shall...

16 CFR 1507.10 - Rockets with sticks.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 16 Commercial Practices 2 2014-01-01 2014-01-01 false Rockets with sticks. 1507.10 Section 1507.10... FIREWORKS DEVICES § 1507.10 Rockets with sticks. Rockets with sticks (including skyrockets and bottle rockets) shall utilize a straight and rigid stick to provide a direct and stable flight. Such sticks shall...

Early Rockets

NASA Image and Video Library

2004-04-15

Goddard rocket with four rocket motors. This rocket attained an altitude of 200 feet in a flight, November 1936, at Roswell, New Mexico. From 1930 to 1941, Dr. Goddard made substantial progress in the development of progressively larger rockets which attained altitudes of 2400 meters, and refined his equipment for guidance and control, his techniques of welding, and his insulation, pumps, and other associated equipment. In many respects, Dr. Goddard laid the essential foundations of practical rocket technology

Collaborative Sounding Rocket launch in Alaska and Development of Hybrid Rockets

NASA Astrophysics Data System (ADS)

Ono, Tomohisa; Tsutsumi, Akimasa; Ito, Toshiyuki; Kan, Yuji; Tohyama, Fumio; Nakashino, Kyouichi; Hawkins, Joseph

Tokai University student rocket project (TSRP) was established in 1995 for a purpose of the space science and engineering hands-on education, consisting of two space programs; the one is sounding rocket experiment collaboration with University of Alaska Fairbanks and the other is development and launch of small hybrid rockets. In January of 2000 and March 2002, two collaborative sounding rockets were successfully launched at Poker Flat Research Range in Alaska. In 2001, the first Tokai hybrid rocket was successfully launched at Alaska. After that, 11 hybrid rockets were launched to the level of 180-1,000 m high at Hokkaido and Akita in Japan. Currently, Tokai students design and build all parts of the rockets. In addition, they are running the organization and development of the project under the tight budget control. This program has proven to be very effective in providing students with practical, real-engineering design experience and this program also allows students to participate in all phases of a sounding rocket mission. Also students learn scientific, engineering subjects, public affairs and system management through experiences of cooperative teamwork. In this report, we summarize the TSRP's hybrid rocket program and discuss the effectiveness of the program in terms of educational aspects.

Focused RBCC Experiments: Two-Rocket Configuration Experiments and Hydrocarbon/Oxygen Rocket Ejector Experiments

NASA Technical Reports Server (NTRS)

Santoro, Robert J.; Pal, Sibtosh

2003-01-01

This addendum report documents the results of two additional efforts for the Rocket Based Combined Cycle (RBCC) rocket-ejector mode research work carried out at the Penn State Propulsion Engineering Research Center in support of NASA s technology development efforts for enabling 3 d generation Reusable Launch Vehicles (RLV). The tasks reported here build on an earlier NASA MSFC funded research program on rocket ejector investigations. The first task investigated the improvements of a gaseous hydrogen/oxygen twin thruster RBCC rocket ejector system over a single rocket system. The second task investigated the performance of a hydrocarbon (liquid JP-7)/gaseous oxygen single thruster rocket-ejector system. To gain a systematic understanding of the rocket-ejector s internal fluid mechanic/combustion phenomena, experiments were conducted with both direct-connect and sea-level static diffusion and afterburning (DAB) configurations for a range of rocket operating conditions. For all experimental conditions, overall system performance was obtained through global measurements of wall static pressure profiles, heat flux profiles and engine thrust. Detailed mixing and combustion information was obtained through Raman spectroscopy measurements of major species (gaseous oxygen, hydrogen, nitrogen and water vapor) for the gaseous hydrogen/oxygen rocket ejector experiments.

Porous Si spheres encapsulated in carbon shells with enhanced anodic performance in lithium-ion batteries

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

Wang, Hui; Wu, Ping, E-mail: zjuwuping@njnu.edu.cn; Shi, Huimin

2014-07-01

Highlights: • In situ magnesiothermic reduction route for the formation of porous Si@C spheres. • Unique microstructural characteristics of both porous sphere and carbon matrix. • Enhanced anodic performance in term of cycling stability for lithium-ion batteries. - Abstract: A novel type of porous Si–C micro/nano-hybrids, i.e., porous Si spheres encapsulated in carbon shells (porous Si@C spheres), has been constructed through the pyrolysis of polyvinylidene fluoride (PVDF) and subsequent magnesiothermic reduction methodology by using SiO{sub 2} spheres as precursors. The as-synthesized porous Si@C spheres have been applied as anode materials for lithium-ion batteries (LIBs), and exhibit enhanced anodic performance inmore » term of cycling stability compared with bare Si spheres. For example, the porous Si@C spheres are able to exhibit a high reversible capacity of 900.0 mA h g{sup −1} after 20 cycles at a current density of 0.05 C (1 C = 4200 mA g{sup −1}), which is much higher than that of bare Si spheres (430.7 mA h g{sup −1})« less

One Dimensional Analysis Model of a Condensing Spray Chamber Including Rocket Exhaust Using SINDA/FLUINT and CEA

NASA Technical Reports Server (NTRS)

Sakowski, Barbara; Edwards, Daryl; Dickens, Kevin

2014-01-01

Modeling droplet condensation via CFD codes can be very tedious, time consuming, and inaccurate. CFD codes may be tedious and time consuming in terms of using Lagrangian particle tracking approaches or particle sizing bins. Also since many codes ignore conduction through the droplet and or the degradating effect of heat and mass transfer if noncondensible species are present, the solutions may be inaccurate. The modeling of a condensing spray chamber where the significant size of the water droplets and the time and distance these droplets take to fall, can make the effect of droplet conduction a physical factor that needs to be considered in the model. Furthermore the presence of even a relatively small amount of noncondensible has been shown to reduce the amount of condensation [Ref 1]. It is desirable then to create a modeling tool that addresses these issues. The path taken to create such a tool is illustrated. The application of this tool and subsequent results are based on the spray chamber in the Spacecraft Propulsion Research Facility (B2) located at NASA's Plum Brook Station that tested an RL-10 engine. The platform upon which the condensation physics is modeled is SINDAFLUINT. The use of SINDAFLUINT enables the ability to model various aspects of the entire testing facility, including the rocket exhaust duct flow and heat transfer to the exhaust duct wall. The ejector pumping system of the spray chamber is also easily implemented via SINDAFLUINT. The goal is to create a transient one dimensional flow and heat transfer model beginning at the rocket, continuing through the condensing spray chamber, and finally ending with the ejector pumping system. However the model of the condensing spray chamber may be run independently of the rocket and ejector systems detail, with only appropriate mass flow boundary conditions placed at the entrance and exit of the condensing spray chamber model. The model of the condensing spray chamber takes into account droplet conduction as well as the degrading effect of mass and heat transfer due to the presence of noncondensibles. The one dimension model of the condensing spray chamber makes no presupposition on the pressure profile within the chamber, allowing the implemented droplet physics of heat and mass transfer coupled to the SINDAFLUINT solver to determine a transient pressure profile of the condensing spray chamber. Model results compare well to the RL-10 engine pressure test data.

Vertical Spin Tunnel Testing and Stability Analysis of Multi-Mission Earth Entry Vehicles

NASA Technical Reports Server (NTRS)

Glaab, Louis J.; Morelli, Eugene A.; Fremaux, C. Michael; Bean, Jacob

2014-01-01

Multi-Mission Earth Entry Vehicles (MMEEVs) are blunt-body vehicles designed with the purpose of transporting payloads from space to the surface of the Earth. To achieve high reliability and minimum weight, MMEEVs avoid using limited-reliability systems, such as parachutes, retro-rockets, and reaction control systems and rely on the natural aerodynamic stability of the vehicle throughout the Entry, Descent, and Landing phases of flight. Testing in NASA Langley's 20-FT Vertical Spin Tunnel (20-FT VST), dynamically-scaled MMEEV models was conducted to improve subsonic aerodynamic models and validate stability criteria for this class of vehicle. This report documents the resulting data from VST testing for an array of 60-deg sphere-cone MMEEVs. Model configurations included were 1.2 meter, and 1.8 meter designs. The addition of a backshell extender, which provided a 150% increase in backshell diameter for the 1.2 meter design, provided a third test configuration. Center of Gravity limits were established for all MMEEV configurations. An application of System Identification (SID) techniques was performed to determine the aerodynamic coefficients in order to provide databases for subsequent 6-degree-of-freedom simulations.

Comparison of NiS2 and α-NiS hollow spheres for supercapacitors, non-enzymatic glucose sensors and water treatment.

PubMed

Wei, Chengzhen; Cheng, Cheng; Cheng, Yanyan; Wang, Yan; Xu, Yazhou; Du, Weimin; Pang, Huan

2015-10-21

NiS2 hollow spheres are successfully prepared by a one-step template free method. Meanwhile, α-NiS hollow spheres can also be synthesized via the calcination of the pre-obtained NiS2 hollow spheres at 400 °C for 1 h in air. The electrochemical performances of the as-prepared NiS2 and α-NiS hollow sphere products are evaluated. When used for supercapacitors, compared with NiS2 hollow spheres, the α-NiS hollow sphere electrode shows a large specific capacitance of 717.3 F g(-1) at 0.6 A g(-1) and a good cycle life. Furthermore, NiS2 and α-NiS hollow spheres are successfully applied to fabricate non-enzymatic glucose sensors. In particular, the α-NiS hollow spheres exhibit good catalytic activity for the oxidation of glucose, a fast amperometric response time of less than 5 s, and the detection limit is estimated to be 0.08 μM. More importantly, compared with other normally co-existing interfering species, such as ascorbic acid, uric acid and dopamine, the electrode modified with α-NiS hollow spheres shows good selectivity. Moreover, the α-NiS hollow spheres also present good capacity to remove Congo red organic pollutants from wastewater by their surface adsorption ability.

Interaction of a shock wave with multiple spheres suspended in different arrangements

NASA Astrophysics Data System (ADS)

Zhang, Li-Te; Sui, Zhen-Zhen; Shi, Hong-Hui

2018-03-01

In this study, the unsteady drag force, Fd, drag coefficient, Cd, and the relevant dynamic behaviors of waves caused by the interaction between a planar incident shock wave and a multi-sphere model are investigated by using imbedded accelerometers and a high-speed Schlieren system. The shock wave is produced in a horizontal 200 mm inner diameter circular shock tube with a 2000 mm × 200 mm × 200 mm transparent test section. The time history of Cd is obtained based on band-block and low-pass Fast Fourier Transformation filtering combined with Savitzky-Golay polynomial smoothing for the measured acceleration. The effects of shock Mach number, Ms, geometry of multi-sphere model, nondimensional distance between sphere centers, H, and channel blockage are analyzed. We find that all time histories of Cd have a similar double-peak shaped main structure. It is due to wave reflection, diffraction, interference, and convergence at different positions of the spheres. The peak Fd increases, whereas the peak Cd decreases monotonically with increasing Ms. The increase of shock strength due to shock focusing by upstream spheres increases the peak Fd of downstream spheres. Both the increase in sphere number and the decrease in distance between spheres promote wave interference between neighboring spheres. As long as the wave interference times are shorter than the peak times, the peak Fd and Cd are higher compared to a single sphere.

STS-53 Space Shuttle mission report

NASA Technical Reports Server (NTRS)

Fricke, Robert W., Jr.

1993-01-01

The STS-53 Space Shuttle Program Mission Report provides a summary of the Orbiter, External Tank (ET), Solid Rocket Booster/Redesigned Solid Rocket Motor (SRB/RSRM), and the Space Shuttle Main Engine (SSME) subsystems performance during the fifty-second flight of the Space Shuttle Program, and the fifteenth flight of the Orbiter vehicle Discovery (OV-103). In addition to the Orbiter, the flight vehicle consisted of an ET, which was designated as ET-49/LWT-42; three SSME's, which were serial numbers 2024, 2012, and 2017 in positions 1, 2, and 3, respectively; and two SRB's, which were designated BI-055. The lightweight RSRM's that were installed in each SRB were designated 360L028A for the left SRB, and 360L028B for the right SRB. The primary objective of this flight was to successfully deploy the Department of Defense 1 (DOD-1) payload. The secondary objectives of this flight were to perform the operations required by the Glow Experiment/Cryogenic Heat Pipe Experiment Payload (GCP); the Hand-Held, Earth-Oriented, Real-Time, Cooperative, User-Friendly, Location-Targeting and Environmental System (HERCULES); the Space Tissue Loss (STL); the Battlefield Laser Acquisition Sensor Test (BLAST); the Radiation Monitoring Equipment-III (RME-III); the Microcapsules in Space-1 (MIS-1); the Visual Function Tester-2 (VFT-2); the Cosmic Radiation Effects and Activation Monitor (CREAM); the Clouds Logic to Optimize Use of Defense Systems-1A (CLOUDS-1A); the Fluids Acquisition and Resupply Experiment (FARE); and the Orbital Debris Radar Calibration Spheres (ODERACS). In addition to presenting a summary of subsystem performance, this report also discusses each Orbiter, ET, SSME, SRB, and RSRM in-flight anomaly in the applicable section of the report. Listed in the discussion of each anomaly is the officially assigned tracking number as published by each Project Office in their respective Problem Tracking List. All times given in this report are in Greenwich mean time (G.m.t.) as well as mission elapsed time (MET).

STS-53 Space Shuttle mission report

NASA Astrophysics Data System (ADS)

Fricke, Robert W., Jr.

1993-02-01

The STS-53 Space Shuttle Program Mission Report provides a summary of the Orbiter, External Tank (ET), Solid Rocket Booster/Redesigned Solid Rocket Motor (SRB/RSRM), and the Space Shuttle Main Engine (SSME) subsystems performance during the fifty-second flight of the Space Shuttle Program, and the fifteenth flight of the Orbiter vehicle Discovery (OV-103). In addition to the Orbiter, the flight vehicle consisted of an ET, which was designated as ET-49/LWT-42; three SSME's, which were serial numbers 2024, 2012, and 2017 in positions 1, 2, and 3, respectively; and two SRB's, which were designated BI-055. The lightweight RSRM's that were installed in each SRB were designated 360L028A for the left SRB, and 360L028B for the right SRB. The primary objective of this flight was to successfully deploy the Department of Defense 1 (DOD-1) payload. The secondary objectives of this flight were to perform the operations required by the Glow Experiment/Cryogenic Heat Pipe Experiment Payload (GCP); the Hand-Held, Earth-Oriented, Real-Time, Cooperative, User-Friendly, Location-Targeting and Environmental System (HERCULES); the Space Tissue Loss (STL); the Battlefield Laser Acquisition Sensor Test (BLAST); the Radiation Monitoring Equipment-III (RME-III); the Microcapsules in Space-1 (MIS-1); the Visual Function Tester-2 (VFT-2); the Cosmic Radiation Effects and Activation Monitor (CREAM); the Clouds Logic to Optimize Use of Defense Systems-1A (CLOUDS-1A); the Fluids Acquisition and Resupply Experiment (FARE); and the Orbital Debris Radar Calibration Spheres (ODERACS). In addition to presenting a summary of subsystem performance, this report also discusses each Orbiter, ET, SSME, SRB, and RSRM in-flight anomaly in the applicable section of the report. Listed in the discussion of each anomaly is the officially assigned tracking number as published by each Project Office in their respective Problem Tracking List. All times given in this report are in Greenwich mean time (G.m.t.) as well as mission elapsed time (MET).

Critical Review of the Navy Space Cadre

DTIC Science & Technology

2014-06-01

SPACE PROGRAM Following World War II, Army and Navy researchers divided captured German V-2 rocket components to rebuild V-2 rockets and eventually...develop the first American rockets .19 The Navy began launching space probes on V-2 rockets in 1946, including from the deck of USS Midway (CVB-41) in...1947.20 But the dwindling supply of V-2 rockets motivated the Navy to develop its own rockets . The Aerobee and Viking, would form a solid foundation

Dr. Robert H. Goddard and His Rocket

NASA Technical Reports Server (NTRS)

2004-01-01

Goddard rocket with four rocket motors. This rocket attained an altitude of 200 feet in a flight, November 1936, at Roswell, New Mexico. From 1930 to 1941, Dr. Goddard made substantial progress in the development of progressively larger rockets which attained altitudes of 2400 meters, and refined his equipment for guidance and control, his techniques of welding, and his insulation, pumps, and other associated equipment. In many respects, Dr. Goddard laid the essential foundations of practical rocket technology

KENNEDY SPACE CENTER, FLA. - The Rocket Garden at the KSC Visitor Complex features eight authentic rockets from the past, including a Mercury-Atlas rocket. The garden also features a climb-in Mercury, Gemino and Apollo capsule replicas, seating pods and informative graphic elements.

NASA Image and Video Library

2003-07-22

KENNEDY SPACE CENTER, FLA. - The Rocket Garden at the KSC Visitor Complex features eight authentic rockets from the past, including a Mercury-Atlas rocket. The garden also features a climb-in Mercury, Gemino and Apollo capsule replicas, seating pods and informative graphic elements.

DataRocket: Interactive Visualisation of Data Structures

NASA Astrophysics Data System (ADS)

Parkes, Steve; Ramsay, Craig

2010-08-01

CodeRocket is a software engineering tool that provides cognitive support to the software engineer for reasoning about a method or procedure and for documenting the resulting code [1]. DataRocket is a software engineering tool designed to support visualisation and reasoning about program data structures. DataRocket is part of the CodeRocket family of software tools developed by Rapid Quality Systems [2] a spin-out company from the Space Technology Centre at the University of Dundee. CodeRocket and DataRocket integrate seamlessly with existing architectural design and coding tools and provide extensive documentation with little or no effort on behalf of the software engineer. Comprehensive, abstract, detailed design documentation is available early on in a project so that it can be used for design reviews with project managers and non expert stakeholders. Code and documentation remain fully synchronised even when changes are implemented in the code without reference to the existing documentation. At the end of a project the press of a button suffices to produce the detailed design document. Existing legacy code can be easily imported into CodeRocket and DataRocket to reverse engineer detailed design documentation making legacy code more manageable and adding substantially to its value. This paper introduces CodeRocket. It then explains the rationale for DataRocket and describes the key features of this new tool. Finally the major benefits of DataRocket for different stakeholders are considered.

Development of a 12-Thrust Chamber Kerosene /Oxygen Primary Rocket Sub-System for an Early (1964) Air-Augmented Rocket Ground-Test System

NASA Technical Reports Server (NTRS)

Pryor, D.; Hyde, E. H.; Escher, W. J. D.

1999-01-01

Airbreathing/Rocket combined-cycle, and specifically rocket-based combined- cycle (RBCC), propulsion systems, typically employ an internal engine flow-path installed primary rocket subsystem. To achieve acceptably short mixing lengths in effecting the "air augmentation" process, a large rocket-exhaust/air interfacial mixing surface is needed. This leads, in some engine design concepts, to a "cluster" of small rocket units, suitably arrayed in the flowpath. To support an early (1964) subscale ground-test of a specific RBCC concept, such a 12-rocket cluster was developed by NASA's Marshall Space Flight Center (MSFC). The small primary rockets used in the cluster assembly were modified versions of an existing small kerosene/oxygen water-cooled rocket engine unit routinely tested at MSFC. Following individual thrust-chamber tests and overall subsystem qualification testing, the cluster assembly was installed at the U. S. Air Force's Arnold Engineering Development Center (AEDC) for RBCC systems testing. (The results of the special air-augmented rocket testing are not covered here.) While this project was eventually successfully completed, a number of hardware integration problems were met, leading to catastrophic thrust chamber failures. The principal "lessons learned" in conducting this early primary rocket subsystem experimental effort are documented here as a basic knowledge-base contribution for the benefit of today's RBCC research and development community.

The effect of disorder of small spheres on the photonic properties of the inverse binary NaCl-like structure

NASA Astrophysics Data System (ADS)

Pattabhiraman, Harini; Dijkstra, Marjolein

2017-09-01

Inverse opal structures are experimentally realisable photonic band gap materials. They suffer from the drawback of possessing band gaps that are extremely susceptible to structural disorders. A binary colloidal NaCl lattice, which is also experimentally realisable, is a promising alternative to these opals. In this work, we systematically analyse the effect of structural disorder of the small spheres on the photonic properties of an inverse binary NaCl lattice with a size ratio of 0.30 between the small and large spheres. The types of structural disorders studied include the position of the small spheres in the octahedral void of the large spheres, polydispersity in size of the small spheres, and the fraction of small spheres in the crystal. We find a low susceptibility of the band gap of the inverse NaCl lattice to the disorder of the small spheres.

Identification of tumor-initiating cells derived from two canine rhabdomyosarcoma cell lines

PubMed Central

KISHIMOTO, Takuya Evan; YASHIMA, Shoko; NAKAHIRA, Rei; ONOZAWA, Eri; AZAKAMI, Daigo; UJIKE, Makoto; OCHIAI, Kazuhiko; ISHIWATA, Toshiyuki; TAKAHASHI, Kimimasa; MICHISHITA, Masaki

2017-01-01

Cancer stem cells or tumor-initiating cells (TICs) are a small subpopulation of cells that have the capacity to self-renew, differentiate and initiate tumors. These cells may function in tumor initiation, aggression and recurrence. Whether spheres derived from canine rhabdomyosarcoma cells have stem cell-like properties is unclear. We induced sphere formation in the canine rhabdomyosarcoma cell lines, CMS-C and CMS-J, and characterized the spheres in vitro and in vivo. Sphere-forming cells were more resistant to vincristine, mitoxantrone and doxorubicin than adherent cells. Xenograft transplantation demonstrated that 1 × 103 sphere-forming cells derived from CMS-C were sufficient for tumor formation. The sphere assay showed that the sphere-forming cells were present in these tumors. These results suggest that the spheres derived from canine rhabdomyosarcoma cells may possess characteristics of TICs. This study provides the foundation for elucidating the contribution of TICs to rhabdomyosarcoma tumorigenesis. PMID:28529244

Identification of tumor-initiating cells derived from two canine rhabdomyosarcoma cell lines.

PubMed

Kishimoto, Takuya Evan; Yashima, Shoko; Nakahira, Rei; Onozawa, Eri; Azakami, Daigo; Ujike, Makoto; Ochiai, Kazuhiko; Ishiwata, Toshiyuki; Takahashi, Kimimasa; Michishita, Masaki

2017-07-07

Cancer stem cells or tumor-initiating cells (TICs) are a small subpopulation of cells that have the capacity to self-renew, differentiate and initiate tumors. These cells may function in tumor initiation, aggression and recurrence. Whether spheres derived from canine rhabdomyosarcoma cells have stem cell-like properties is unclear. We induced sphere formation in the canine rhabdomyosarcoma cell lines, CMS-C and CMS-J, and characterized the spheres in vitro and in vivo. Sphere-forming cells were more resistant to vincristine, mitoxantrone and doxorubicin than adherent cells. Xenograft transplantation demonstrated that 1 × 10 3 sphere-forming cells derived from CMS-C were sufficient for tumor formation. The sphere assay showed that the sphere-forming cells were present in these tumors. These results suggest that the spheres derived from canine rhabdomyosarcoma cells may possess characteristics of TICs. This study provides the foundation for elucidating the contribution of TICs to rhabdomyosarcoma tumorigenesis.

Specific surface area of overlapping spheres in the presence of obstructions

NASA Astrophysics Data System (ADS)

Jenkins, D. R.

2013-02-01

This study considers the random placement of uniform sized spheres, which may overlap, in the presence of another set of randomly placed (hard) spheres, which do not overlap. The overlapping spheres do not intersect the hard spheres. It is shown that the specific surface area of the collection of overlapping spheres is affected by the hard spheres, such that there is a minimum in the specific surface area as a function of the relative size of the two sets of spheres. The occurrence of the minimum is explained in terms of the break-up of pore connectivity. The configuration can be considered to be a simple model of the structure of a porous composite material. In particular, the overlapping particles represent voids while the hard particles represent fillers. Example materials are pervious concrete, metallurgical coke, ice cream, and polymer composites. We also show how the material properties of such composites are affected by the void structure.

Specific surface area of overlapping spheres in the presence of obstructions.

PubMed

Jenkins, D R

2013-02-21

This study considers the random placement of uniform sized spheres, which may overlap, in the presence of another set of randomly placed (hard) spheres, which do not overlap. The overlapping spheres do not intersect the hard spheres. It is shown that the specific surface area of the collection of overlapping spheres is affected by the hard spheres, such that there is a minimum in the specific surface area as a function of the relative size of the two sets of spheres. The occurrence of the minimum is explained in terms of the break-up of pore connectivity. The configuration can be considered to be a simple model of the structure of a porous composite material. In particular, the overlapping particles represent voids while the hard particles represent fillers. Example materials are pervious concrete, metallurgical coke, ice cream, and polymer composites. We also show how the material properties of such composites are affected by the void structure.

Generating perfect fluid spheres in general relativity

NASA Astrophysics Data System (ADS)

Boonserm, Petarpa; Visser, Matt; Weinfurtner, Silke

2005-06-01

Ever since Karl Schwarzschild’s 1916 discovery of the spacetime geometry describing the interior of a particular idealized general relativistic star—a static spherically symmetric blob of fluid with position-independent density—the general relativity community has continued to devote considerable time and energy to understanding the general-relativistic static perfect fluid sphere. Over the last 90 years a tangle of specific perfect fluid spheres has been discovered, with most of these specific examples seemingly independent from each other. To bring some order to this collection, in this article we develop several new transformation theorems that map perfect fluid spheres into perfect fluid spheres. These transformation theorems sometimes lead to unexpected connections between previously known perfect fluid spheres, sometimes lead to new previously unknown perfect fluid spheres, and in general can be used to develop a systematic way of classifying the set of all perfect fluid spheres.

In vitro and in vivo study of the application of volvox spheres to co-culture vehicles in liver tissue engineering.

PubMed

Chang, Siou Han; Huang, Han Hsiang; Kang, Pei Leun; Wu, Yu Chian; Chang, Ming-Huang; Kuo, Shyh Ming

2017-11-01

Volvox sphere is a biomimetic concept of a natural Volvox, wherein a large outer sphere contains smaller inner spheres, which can encapsulate cells and provide a double-layer three-dimensional environment for culturing cells. This study simultaneously encapsulated rat mesenchymal stem cells (MSCs) and AML12 hepatocytes in volvox spheres and extensively evaluated the effects of various culturing modes on cell functions and fates. The results showed that compared with a static flask culture, MSCs encapsulated in volvox spheres differentiated into hepatocyte-like cells with a 2-fold increase in albumin (ALB) expression and a 2.5-fold increase in cytokeratin 18 expression in a dynamic bioreactor. Moreover, the restorative effects of volvox spheres encapsulating cells on retrorsine-exposed CCl 4 -induced liver injuries in rats were evaluated. The data presented significant reductions in AST and ALT levels after the implantation of volvox spheres encapsulating both MSCs and AML12 hepatocytes in vivo. In contrast to the negative control group, histopathological analysis demonstrated liver repair and formation of the new liver tissue in groups implanted with volvox spheres containing cells. These results demonstrate that liver cells implanted with volvox spheres encapsulating both MSCs and AML12 hepatocytes promote liver repair and liver tissue regeneration in liver failure caused by necrotizing agents such as retrorsine and CCl 4 . Hence, volvox spheres encapsulating MSCs and liver cells can be a promising and clinically effective therapy for liver injury. In this study, we used a volvox sphere, which is a unique design that mimics the natural Volvox, that consists of a large outer sphere that contains smaller inner spheres, which provide a three-dimensional environment to culture cells. The purpose of this study is to co-culture mesenchymal stem cells (MSCs) and AML12 liver cells in volvox spheres and evaluate two different culture methods, dynamic bioreactor and static culture flask,on the cultured cells. In addition, we aimed to evaluate the restorative effects of volvox spheres encapsulating MSCs and/or AML12 liver cells on rats with retrorsine-exposed CCl 4 -induced liver injuries. The results showed that MSCs encapsulated in volvox spheres differentiated into hepatocyte-like cells with a 2-fold increase in albumin expression and a 2.5-fold increase in cytokeratin 18 expression ina dynamic bioreactor. Moreover, the data presented significant reductions in AST and ALT levels after the implantation of volvox spheres encapsulating both MSCs and AML12 hepatocytes in vivo. In contrast to the negative control group, histopathological analysis demonstrated liver repair and formation of new liver tissue in groups implanted with volvox spheres containing cells. These results demonstrate that liver cells implanted with volvox spheres encapsulating both MSCs and AML12 hepatocytes promote liver repair and liver tissue regeneration in liver failure caused by necrotizing agents such as retrorsine and CCl 4 . Hence, volvox spheres encapsulating MSCs and liver cells can be a promising and clinically effective therapy for liver injury. Copyright © 2017 Acta Materialia Inc. Published by Elsevier Ltd. All rights reserved.

On the history of the development of solid-propellant rockets in the Soviet Union

NASA Technical Reports Server (NTRS)

Pobedonostsev, Y. A.

1977-01-01

Pre-World War II Soviet solid-propellant rocket technology is reviewed. Research and development regarding solid composite preparations of pyroxyline TNT powder is described, as well as early work on rocket loading calculations, problems of flight stability, and aircraft rocket launching and ground rocket launching capabilities.

40 CFR 61.43 - Emission testing-rocket firing or propellant disposal.

Code of Federal Regulations, 2014 CFR

2014-07-01

... 40 Protection of Environment 9 2014-07-01 2014-07-01 false Emission testing-rocket firing or... Standard for Beryllium Rocket Motor Firing § 61.43 Emission testing—rocket firing or propellant disposal. (a) Ambient air concentrations shall be measured during and after firing of a rocket motor or...

46 CFR 160.040-4 - Equipment for impulse-projected rocket type line-throwing appliance.

Code of Federal Regulations, 2013 CFR

2013-10-01

... 46 Shipping 6 2013-10-01 2013-10-01 false Equipment for impulse-projected rocket type line...-Throwing Appliance, Impulse-Projected Rocket Type (and Equipment) § 160.040-4 Equipment for impulse-projected rocket type line-throwing appliance. (a) Four rocket projectiles, each complete with bridle and...

40 CFR 61.43 - Emission testing-rocket firing or propellant disposal.

Code of Federal Regulations, 2013 CFR

2013-07-01

... 40 Protection of Environment 9 2013-07-01 2013-07-01 false Emission testing-rocket firing or... Standard for Beryllium Rocket Motor Firing § 61.43 Emission testing—rocket firing or propellant disposal. (a) Ambient air concentrations shall be measured during and after firing of a rocket motor or...

46 CFR 160.040-4 - Equipment for impulse-projected rocket type line-throwing appliance.

Code of Federal Regulations, 2012 CFR

2012-10-01

... 46 Shipping 6 2012-10-01 2012-10-01 false Equipment for impulse-projected rocket type line...-Throwing Appliance, Impulse-Projected Rocket Type (and Equipment) § 160.040-4 Equipment for impulse-projected rocket type line-throwing appliance. (a) Four rocket projectiles, each complete with bridle and...

46 CFR 160.040-4 - Equipment for impulse-projected rocket type line-throwing appliance.

Code of Federal Regulations, 2014 CFR

2014-10-01

... 46 Shipping 6 2014-10-01 2014-10-01 false Equipment for impulse-projected rocket type line...-Throwing Appliance, Impulse-Projected Rocket Type (and Equipment) § 160.040-4 Equipment for impulse-projected rocket type line-throwing appliance. (a) Four rocket projectiles, each complete with bridle and...

40 CFR 61.43 - Emission testing-rocket firing or propellant disposal.

Code of Federal Regulations, 2011 CFR

2011-07-01

... 40 Protection of Environment 8 2011-07-01 2011-07-01 false Emission testing-rocket firing or... Standard for Beryllium Rocket Motor Firing § 61.43 Emission testing—rocket firing or propellant disposal. (a) Ambient air concentrations shall be measured during and after firing of a rocket motor or...

46 CFR 160.040-4 - Equipment for impulse-projected rocket type line-throwing appliance.

Code of Federal Regulations, 2010 CFR

2010-10-01

... 46 Shipping 6 2010-10-01 2010-10-01 false Equipment for impulse-projected rocket type line...-Throwing Appliance, Impulse-Projected Rocket Type (and Equipment) § 160.040-4 Equipment for impulse-projected rocket type line-throwing appliance. (a) Four rocket projectiles, each complete with bridle and...

16 CFR § 1507.10 - Rockets with sticks.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 16 Commercial Practices 2 2013-01-01 2013-01-01 false Rockets with sticks. § 1507.10 Section Â... REGULATIONS FIREWORKS DEVICES § 1507.10 Rockets with sticks. Rockets with sticks (including skyrockets and bottle rockets) shall utilize a straight and rigid stick to provide a direct and stable flight. Such...

40 CFR 61.43 - Emission testing-rocket firing or propellant disposal.

Code of Federal Regulations, 2012 CFR

2012-07-01

... 40 Protection of Environment 9 2012-07-01 2012-07-01 false Emission testing-rocket firing or... Standard for Beryllium Rocket Motor Firing § 61.43 Emission testing—rocket firing or propellant disposal. (a) Ambient air concentrations shall be measured during and after firing of a rocket motor or...

40 CFR 61.43 - Emission testing-rocket firing or propellant disposal.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 40 Protection of Environment 8 2010-07-01 2010-07-01 false Emission testing-rocket firing or... Standard for Beryllium Rocket Motor Firing § 61.43 Emission testing—rocket firing or propellant disposal. (a) Ambient air concentrations shall be measured during and after firing of a rocket motor or...

46 CFR 160.040-4 - Equipment for impulse-projected rocket type line-throwing appliance.

Code of Federal Regulations, 2011 CFR

2011-10-01

... 46 Shipping 6 2011-10-01 2011-10-01 false Equipment for impulse-projected rocket type line...-Throwing Appliance, Impulse-Projected Rocket Type (and Equipment) § 160.040-4 Equipment for impulse-projected rocket type line-throwing appliance. (a) Four rocket projectiles, each complete with bridle and...

Design of Force Sensor Leg for a Rocket Thrust Detector

NASA Astrophysics Data System (ADS)

Woten, Douglas; McGehee, Tripp; Wright, Anne

2005-03-01

A hybrid rocket is composed of a solid fuel and a separate liquid or gaseous oxidizer. These rockets may be throttled like liquid rockets, are safer than solid rockets, and are much less complex than liquid rockets. However, hybrid rockets produce thrust oscillations that are not practical for large scale use. A lab scale hybrid rocket at the University of Arkansas at Little Rock (UALR) Hybrid Rocket Facility is used to develop sensors to measure physical properties of hybrid rockets. Research is currently being conducted to design a six degree of freedom force sensor to measure the thrust and torque in all three spacial dimensions. The detector design uses six force sensor legs. Each leg utilizes strain gauges and a Wheatstone bridge to produce a voltage propotional to the force on the leg. The leg was designed using the CAD software ProEngineer and ProMechanica. Computer models of the strains on the single leg will be presented. A prototype leg was built and was tested in an INSTRON and results will be presented.

If Only Newton Had a Rocket.

ERIC Educational Resources Information Center

Hammock, Frank M.

1988-01-01

Shows how model rocketry can be included in physics curricula. Describes rocket construction, a rocket guide sheet, calculations and launch teams. Discusses the relationships of basic mechanics with rockets. (CW)

Carrier rockets

NASA Astrophysics Data System (ADS)

Aleksandrov, V. A.; Vladimirov, V. V.; Dmitriev, R. D.; Osipov, S. O.

This book takes into consideration domestic and foreign developments related to launch vehicles. General information concerning launch vehicle systems is presented, taking into account details of rocket structure, basic design considerations, and a number of specific Soviet and American launch vehicles. The basic theory of reaction propulsion is discussed, giving attention to physical foundations, the various types of forces acting on a rocket in flight, basic parameters characterizing rocket motion, the effectiveness of various approaches to obtain the desired velocity, and rocket propellants. Basic questions concerning the classification of launch vehicles are considered along with construction and design considerations, aspects of vehicle control, reliability, construction technology, and details of structural design. Attention is also given to details of rocket motor design, the basic systems of the carrier rocket, and questions of carrier rocket development.

High Energy Density Additives for Hybrid Fuel Rockets to Improve Performance and Enhance Safety

NASA Technical Reports Server (NTRS)

Jaffe, Richard L.

2014-01-01

We propose a conceptual study of prototype strained hydrocarbon molecules as high energy density additives for hybrid rocket fuels to boost the performance of these rockets without compromising safety and reliability. Use of these additives could extend the range of applications for which hybrid rockets become an attractive alternative to conventional solid or liquid fuel rockets. The objectives of the study were to confirm and quantify the high enthalpy of these strained molecules and to assess improvement in rocket performance that would be expected if these additives were blended with conventional fuels. We confirmed the chemical properties (including enthalpy) of these additives. However, the predicted improvement in rocket performance was too small to make this a useful strategy for boosting hybrid rocket performance.

Rocket center Peenemünde — Personal memories

NASA Astrophysics Data System (ADS)

Dannenberg, Konrad; Stuhlinger, Ernst

Von Braun built his first rockets as a young teenager. At 14, he started making plans for rockets for human travel to the Moon and Mars. The German Army began a rocket program in 1929. Two years later, Colonel (later General) Becker contacted von Braun who experimented with rockets in Berlin, gave him a contract in 1932, and, jointly with the Air Force, in 1936 built the rocket center Peenemünde where von Braun and his team developed the A-4 (V-2) rocket under Army auspices, while the Air Force developed the V-1 (buzz bomb), wire-guided bombs, and rocket planes. Albert Speer, impressed by the work of the rocketeers, allowed a modest growth of the Peenemünde project; this brought Dannenberg to the von Braun team in 1940. Hitler did not believe in rockets; he ignored the A-4 project until 1942 when he began to support it, expecting that it could turn the fortunes of war for him. He drastically increased the Peenemünde work force and allowed the transfer of soldiers from the front to Peenemünde; that was when Stuhlinger, in 1943, came to Peenemünde as a Pfc.-Ph.D. Later that year, Himmler wrenched the authority over A-4 production out of the Army's hands, put it under his command, and forced production of the immature rocket at Mittelwerk, and its military deployment against targets in France, Belgium, and England. Throughout the development of the A-4 rocket, von Braun was the undisputed leader of the project. Although still immature by the end of the war, the A-4 had proceeded to a status which made it the first successful long-range precision rocket, the prototype for a large number of military rockets built by numerous nations after the war, and for space rockets that launched satellites and traveled to the Moon and the planets.

Sphericity determination using resonant ultrasound spectroscopy

DOEpatents

Dixon, Raymond D.; Migliori, Albert; Visscher, William M.

1994-01-01

A method is provided for grading production quantities of spherical objects, such as roller balls for bearings. A resonant ultrasound spectrum (RUS) is generated for each spherical object and a set of degenerate sphere-resonance frequencies is identified. From the degenerate sphere-resonance frequencies and known relationships between degenerate sphere-resonance frequencies and Poisson's ratio, a Poisson's ratio can be determined, along with a "best" spherical diameter, to form spherical parameters for the sphere. From the RUS, fine-structure resonant frequency spectra are identified for each degenerate sphere-resonance frequency previously selected. From each fine-structure spectrum and associated sphere parameter values an asphericity value is determined. The asphericity value can then be compared with predetermined values to provide a measure for accepting or rejecting the sphere.

Sphericity determination using resonant ultrasound spectroscopy

DOEpatents

Dixon, R.D.; Migliori, A.; Visscher, W.M.

1994-10-18

A method is provided for grading production quantities of spherical objects, such as roller balls for bearings. A resonant ultrasound spectrum (RUS) is generated for each spherical object and a set of degenerate sphere-resonance frequencies is identified. From the degenerate sphere-resonance frequencies and known relationships between degenerate sphere-resonance frequencies and Poisson's ratio, a Poisson's ratio can be determined, along with a 'best' spherical diameter, to form spherical parameters for the sphere. From the RUS, fine-structure resonant frequency spectra are identified for each degenerate sphere-resonance frequency previously selected. From each fine-structure spectrum and associated sphere parameter values an asphericity value is determined. The asphericity value can then be compared with predetermined values to provide a measure for accepting or rejecting the sphere. 14 figs.

Rocket Science 101 Interactive Educational Program

NASA Technical Reports Server (NTRS)

Armstrong, Dennis; Funkhouse, Deborah; DiMarzio, Donald

2007-01-01

To better educate the public on the basic design of NASA s current mission rockets, Rocket Science 101 software has been developed as an interactive program designed to retain a user s attention and to teach about basic rocket parts. This program also has helped to expand NASA's presence on the Web regarding educating the public about the Agency s goals and accomplishments. The software was designed using Macromedia s Flash 8. It allows the user to select which type of rocket they want to learn about, interact with the basic parts, assemble the parts to create the whole rocket, and then review the basic flight profile of the rocket they have built.

From the Peenemuende 'Aggregates' to the American moon rocket - The development of the Saturn V Apollo rocket by Werner von Braun's team based on the Peenemuende concept

NASA Astrophysics Data System (ADS)

Reisig, G. H. R.

The origin of active space flight and the important role played in it by the innovations made in the Peenemuende rocket program are discussed. The rocket development carried out by the Werner von Braun team is chronologically recalled. The A4 rocket and its aerodynamic configuration are discussed, including the ballistic demands on its configuration, the development of the Peenemuende supersonic wind tunnel, and the pretesting of the A4 configuration using the A5 rocket. Rocket development in the U.S. from the Redstone to the Saturn is reviewed.

Design and Testing of a Liquid Nitrous Oxide and Ethanol Fueled Rocket Engine

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

Youngblood, Stewart

A small-scale, bi-propellant, liquid fueled rocket engine and supporting test infrastructure were designed and constructed at the Energetic Materials Research and Testing Center (EMRTC). This facility was used to evaluate liquid nitrous oxide and ethanol as potential rocket propellants. Thrust and pressure measurements along with high-speed digital imaging of the rocket exhaust plume were made. This experimental data was used for validation of a computational model developed of the rocket engine tested. The developed computational model was utilized to analyze rocket engine performance across a range of operating pressures, fuel-oxidizer mixture ratios, and outlet nozzle configurations. A comparative study ofmore » the modeling of a liquid rocket engine was performed using NASA CEA and Cantera, an opensource equilibrium code capable of being interfaced with MATLAB. One goal of this modeling was to demonstrate the ability of Cantera to accurately model the basic chemical equilibrium, thermodynamics, and transport properties for varied fuel and oxidizer operating conditions. Once validated for basic equilibrium, an expanded MATLAB code, referencing Cantera, was advanced beyond CEAs capabilities to predict rocket engine performance as a function of supplied propellant flow rate and rocket engine nozzle dimensions. Cantera was found to comparable favorably to CEA for making equilibrium calculations, supporting its use as an alternative to CEA. The developed rocket engine performs as predicted, demonstrating the developedMATLAB rocket engine model was successful in predicting real world rocket engine performance. Finally, nitrous oxide and ethanol were shown to perform well as rocket propellants, with specific impulses experimentally recorded in the range of 250 to 260 seconds.« less

Lung ultrasound in the critically ill.

PubMed

Lichtenstein, Daniel A

2014-01-09

Lung ultrasound is a basic application of critical ultrasound, defined as a loop associating urgent diagnoses with immediate therapeutic decisions. It requires the mastery of ten signs: the bat sign (pleural line), lung sliding (yielding seashore sign), the A-line (horizontal artifact), the quad sign, and sinusoid sign indicating pleural effusion, the fractal, and tissue-like sign indicating lung consolidation, the B-line, and lung rockets indicating interstitial syndrome, abolished lung sliding with the stratosphere sign suggesting pneumothorax, and the lung point indicating pneumothorax. Two more signs, the lung pulse and the dynamic air bronchogram, are used to distinguish atelectasis from pneumonia. All of these disorders were assessed using CT as the "gold standard" with sensitivity and specificity ranging from 90% to 100%, allowing ultrasound to be considered as a reasonable bedside "gold standard" in the critically ill. The BLUE-protocol is a fast protocol (<3 minutes), which allows diagnosis of acute respiratory failure. It includes a venous analysis done in appropriate cases. Pulmonary edema, pulmonary embolism, pneumonia, chronic obstructive pulmonary disease, asthma, and pneumothorax yield specific profiles. Pulmonary edema, e.g., yields anterior lung rockets associated with lung sliding, making the "B-profile." The FALLS-protocol adapts the BLUE-protocol to acute circulatory failure. It makes sequential search for obstructive, cardiogenic, hypovolemic, and distributive shock using simple real-time echocardiography (right ventricle dilatation, pericardial effusion), then lung ultrasound for assessing a direct parameter of clinical volemia: the apparition of B-lines, schematically, is considered as the endpoint for fluid therapy. Other aims of lung ultrasound are decreasing medical irradiation: the LUCIFLR program (most CTs in ARDS or trauma can be postponed), a use in traumatology, intensive care unit, neonates (the signs are the same than in adults), many disciplines (pulmonology, cardiology…), austere countries, and a help in any procedure (thoracentesis). A 1992, cost-effective gray-scale unit, without Doppler, and a microconvex probe are efficient. Lung ultrasound is a holistic discipline for many reasons (e.g., one probe, perfect for the lung, is able to scan the whole-body). Its integration can provide a new definition of priorities. The BLUE-protocol and FALLS-protocol allow simplification of expert echocardiography, a clear advantage when correct cardiac windows are missing.

Lung ultrasound in the critically ill

PubMed Central

2014-01-01

Lung ultrasound is a basic application of critical ultrasound, defined as a loop associating urgent diagnoses with immediate therapeutic decisions. It requires the mastery of ten signs: the bat sign (pleural line), lung sliding (yielding seashore sign), the A-line (horizontal artifact), the quad sign, and sinusoid sign indicating pleural effusion, the fractal, and tissue-like sign indicating lung consolidation, the B-line, and lung rockets indicating interstitial syndrome, abolished lung sliding with the stratosphere sign suggesting pneumothorax, and the lung point indicating pneumothorax. Two more signs, the lung pulse and the dynamic air bronchogram, are used to distinguish atelectasis from pneumonia. All of these disorders were assessed using CT as the “gold standard” with sensitivity and specificity ranging from 90% to 100%, allowing ultrasound to be considered as a reasonable bedside “gold standard” in the critically ill. The BLUE-protocol is a fast protocol (<3 minutes), which allows diagnosis of acute respiratory failure. It includes a venous analysis done in appropriate cases. Pulmonary edema, pulmonary embolism, pneumonia, chronic obstructive pulmonary disease, asthma, and pneumothorax yield specific profiles. Pulmonary edema, e.g., yields anterior lung rockets associated with lung sliding, making the “B-profile.” The FALLS-protocol adapts the BLUE-protocol to acute circulatory failure. It makes sequential search for obstructive, cardiogenic, hypovolemic, and distributive shock using simple real-time echocardiography (right ventricle dilatation, pericardial effusion), then lung ultrasound for assessing a direct parameter of clinical volemia: the apparition of B-lines, schematically, is considered as the endpoint for fluid therapy. Other aims of lung ultrasound are decreasing medical irradiation: the LUCIFLR program (most CTs in ARDS or trauma can be postponed), a use in traumatology, intensive care unit, neonates (the signs are the same than in adults), many disciplines (pulmonology, cardiology…), austere countries, and a help in any procedure (thoracentesis). A 1992, cost-effective gray-scale unit, without Doppler, and a microconvex probe are efficient. Lung ultrasound is a holistic discipline for many reasons (e.g., one probe, perfect for the lung, is able to scan the whole-body). Its integration can provide a new definition of priorities. The BLUE-protocol and FALLS-protocol allow simplification of expert echocardiography, a clear advantage when correct cardiac windows are missing. PMID:24401163

Hypothetical Dark Matter/axion Rockets:. Dark Matter in Terms of Space Physics Propulsion

NASA Astrophysics Data System (ADS)

Beckwith, A.

2010-12-01

Current proposed photon rocket designs include the Nuclear Photonic Rocket and the Antimatter Photonic Rocket (proposed by Eugen Sanger in the 1950s, as reported by Ref. 1). This paper examines the feasibility of improving the thrust of photon-driven ramjet propulsion by using DM rocket propulsion. The open question is: would a heavy WIMP, if converted to photons, upgrade the power (thrust) of a photon rocket drive, to make interstellar travel a feasible proposition?

Trong Bui, NASA Dryden's principal investigator for the aerospike rocket tests, with one of two rockets flown in the first tests.

NASA Image and Video Library

2004-12-09

Trong Bui, NASA Dryden's principal investigator for the aerospike rocket tests, holds the first of two 10-ft. long rockets that were flown at speeds up to Mach 1.5, the first known supersonic tests of rockets with aerospike nozzles. The goals of the flight research project were to obtain aerospike rocket nozzle performance data in flight and to investigate the effects of transonic flow and transient flight conditions on aerospike nozzle performance.

40. HISTORIC VIEW LOOKING WEST AT THE TEST STAND. NOTE ...

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

40. HISTORIC VIEW LOOKING WEST AT THE TEST STAND. NOTE THE LOAD CELL APPARATUS LOCATED ABOVE THE ROCKET. THE SPACE BETWEEN THE BOTTOM OF THE LOAD CELL APPARATUS AND THE TOP OF THE ROCKET IS THE DIFFERENCE IN SIZE BETWEEN THE REDSTONE ROCKET AND ITS DECEDENT THE JUPITER C ROCKET. THE GAP IS FILLED WITH A SPACER WHEN THEY TEST A REDSTONE ROCKET. - Marshall Space Flight Center, Redstone Rocket (Missile) Test Stand, Dodd Road, Huntsville, Madison County, AL

Micro-Rockets for the Classroom.

ERIC Educational Resources Information Center

Huebner, Jay S.; Fletcher, Alice S.; Cato, Julia A.; Barrett, Jennifer A.

1999-01-01

Compares micro-rockets to commercial models and water rockets. Finds that micro-rockets are more advantageous because they are constructed with inexpensive and readily available materials and can be safely launched indoors. (CCM)

Another Look at Rocket Thrust

ERIC Educational Resources Information Center

Hester, Brooke; Burris, Jennifer

2012-01-01

Rocket propulsion is often introduced as an example of Newton's third law. The rocket exerts a force on the exhaust gas being ejected; the gas exerts an equal and opposite force--the thrust--on the rocket. Equivalently, in the absence of a net external force, the total momentum of the system, rocket plus ejected gas, remains constant. The law of…

Sphere based fluid systems

NASA Technical Reports Server (NTRS)

Elleman, Daniel D. (Inventor); Wang, Taylor G. (Inventor)

1989-01-01

Systems are described for using multiple closely-packed spheres. In one system for passing fluid, a multiplicity of spheres lie within a container, with all of the spheres having the same outside diameter and with the spheres being closely nested in one another to create multiple interstitial passages of a known size and configuration and smooth walls. The container has an inlet and outlet for passing fluid through the interstitial passages formed between the nested spheres. The small interstitial passages can be used to filter out material, especially biological material such as cells in a fluid, where the cells can be easily destroyed if passed across sharp edges. The outer surface of the spheres can contain a material that absorbs a constitutent in the flowing fluid, such as a particular contamination gas, or can contain a catalyst to chemically react the fluid passing therethrough, the use of multiple small spheres assuring a large area of contact of these surfaces of the spheres with the fluid. In a system for storing and releasing a fluid such as hydrogen as a fuel, the spheres can include a hollow shell containing the fluid to be stored, and located within a compressable container that can be compressed to break the shells and release the stored fluid.

Establishment of prostate cancer spheres from a prostate cancer cell line after phenethyl isothiocyanate treatment and discovery of androgen-dependent reversible differentiation between sphere and neuroendocrine cells.

PubMed

Chen, Yamei; Cang, Shundong; Han, Liying; Liu, Christina; Yang, Patrick; Solangi, Zeeshan; Lu, Quanyi; Liu, Delong; Chiao, J W

2016-05-03

Prostate cancer can transform from androgen-responsive to an androgen-independent phenotype. The mechanism responsible for the transformation remains unclear. We studied the effects of an epigenetic modulator, phenethyl isothiocyanate (PEITC), on the androgen-responsive LNCaP cells. After treatment with PEITC, floating spheres were formed with characteristics of prostate cancer stem cells (PCSC). These spheres were capable of self-renewal in media with and without androgen. They have been maintained in both types of media as long term cultures. Upon androgen deprivation, the adherent spheres differentiated to neuroendocrine cells (NEC) with decreased proliferation, expression of androgen receptor, and PSA. NEC reverse differentiated to spheres when androgen was replenished. The sphere cells expressed surface marker CD44 and had enhanced histone H3K4 acetylation, DNMT1 down-regulation and GSTP1 activation. We hypothesize that PEITC-mediated alteration in epigenomics of LNCaP cells may give rise to sphere cells, whereas reversible androgenomic alterations govern the shuttling between sphere PCSC and progeny NEC. Our findings identify unrecognized properties of prostate cancer sphere cells with multi-potential plasticity. This system will facilitate development of novel therapeutic agents and allow further exploration into epigenomics and androgenomics governing the transformation to hormone refractory prostate cancer.

A non-traditional fluid problem: transition between theoretical models from Stokes’ to turbulent flow

NASA Astrophysics Data System (ADS)

Salomone, Horacio D.; Olivieri, Néstor A.; Véliz, Maximiliano E.; Raviola, Lisandro A.

2018-05-01

In the context of fluid mechanics courses, it is customary to consider the problem of a sphere falling under the action of gravity inside a viscous fluid. Under suitable assumptions, this phenomenon can be modelled using Stokes’ law and is routinely reproduced in teaching laboratories to determine terminal velocities and fluid viscosities. In many cases, however, the measured physical quantities show important deviations with respect to the predictions deduced from the simple Stokes’ model, and the causes of these apparent ‘anomalies’ (for example, whether the flow is laminar or turbulent) are seldom discussed in the classroom. On the other hand, there are various variable-mass problems that students tackle during elementary mechanics courses and which are discussed in many textbooks. In this work, we combine both kinds of problems and analyse—both theoretically and experimentally—the evolution of a system composed of a sphere pulled by a chain of variable length inside a tube filled with water. We investigate the effects of different forces acting on the system such as weight, buoyancy, viscous friction and drag force. By means of a sequence of mathematical models of increasing complexity, we obtain a progressive fit that accounts for the experimental data. The contrast between the various models exposes the strengths and weaknessess of each one. The proposed experience can be useful for integrating concepts of elementary mechanics and fluids, and is suitable as laboratory practice, stressing the importance of the experimental validation of theoretical models and showing the model-building processes in a didactic framework.

The ultimate limits of the relativistic rocket equation. The Planck photon rocket

NASA Astrophysics Data System (ADS)

Haug, Espen Gaarder

2017-07-01

In this paper we look at the ultimate limits of a photon propulsion rocket. The maximum velocity for a photon propulsion rocket is just below the speed of light and is a function of the reduced Compton wavelength of the heaviest subatomic particles in the rocket. We are basically combining the relativistic rocket equation with Haug's new insight on the maximum velocity for anything with rest mass. An interesting new finding is that in order to accelerate any subatomic "fundamental" particle to its maximum velocity, the particle rocket basically needs two Planck masses of initial load. This might sound illogical until one understands that subatomic particles with different masses have different maximum velocities. This can be generalized to large rockets and gives us the maximum theoretical velocity of a fully-efficient and ideal rocket. Further, no additional fuel is needed to accelerate a Planck mass particle to its maximum velocity; this also might sound absurd, but it has a very simple and logical solution that is explained in this paper.

Focused Experimental and Analytical Studies of the RBCC Rocket-Ejector

NASA Technical Reports Server (NTRS)

Lehman, M.; Pal, S.; Schwes, D.; Chen, J. D.; Santoro, R. J.

1999-01-01

The rocket-ejector mode of a Rocket Based Combined Cycle Engine (RBCC) was studied through a joint experimental/analytical approach. A two-dimensional variable geometry rocket-ejector system with enhanced optical access was designed and fabricated for experimentation. The rocket-ejector system utilizes a single two-dimensional gaseous oxygen/gaseous hydrogen rocket as the ejector. To gain a systematic understanding of the rocket ejector's internal fluid mechanic/combustion phenomena, experiments were conducted with both direct-connect and sea-level static configurations for a range of rocket operating conditions Overall system performance was obtained through Global measurements of wall static pressure profiles, heat flux profiles and engine thrust, whereas detailed mixing and combustion information was obtained through Raman spectroscopy measurements of major species (gaseous oxygen, hydrogen. nitrogen and water vapor). These experimental efforts were complemented by Computational Fluid Dynamic (CFD) flowfield analyses.

Diagnosis of a Poorly Performing Liquid Hydrogen Bulk Storage Sphere

NASA Technical Reports Server (NTRS)

Krenn, Angela G.

2011-01-01

There are two 850,000 gallon Liquid Hydrogen (LH2) storage spheres used to support the Space Shuttle Program; one residing at Launch Pad A and the other at Launch Pad B. The LH2 Sphere at Pad B has had a high boiloff rate since being brought into service in the 1960's. The daily commodity loss was estimated to be approximately double that of the Pad A sphere, and well above the minimum required by the sphere's specification. Additionally, after being re-painted in the late 1990's a "cold spot" appeared on the outer sphere which resulted in a poor paint bond, and mold formation. Thermography was used to characterize the area, and the boiloff rate was continually evaluated. All evidence suggested that the high boiloff rate was caused by an excessive heat leak into the inner sphere due to an insulation void in the annulus. Pad B was recently taken out of Space Shuttle program service which provided a unique opportunity to diagnose the sphere's poor performance. The sphere was drained and inerted, and then opened from the annular relief device on the top where a series of boroscoping operations were accomplished. Boroscoping revealed a large Perlite insulation void in the region of the sphere where the cold spot was apparent. Perlite was then trucked in and off-loaded into the annular void region until the annulus was full. The sphere has not yet been brought back into service.

Cavitation and radicals drive the sonochemical synthesis of functional polymer spheres

DOE PAGES

Narayanan, Badri; Deshmukh, Sanket A.; Shrestha, Lok Kumar; ...

2016-07-25

Sonochemical synthesis can lead to a dramatic increase in the kinetics of formation of polymer spheres (templates for carbon spheres) compared to the modified Stober silica method applied to produce analogous polymer spheres. Reactive molecular dynamics simulations of the sonochemical process indicate a significantly enhanced rate of polymer sphere formation starting from resorcinol and formaldehyde precursors. The associated chemical reaction kinetics enhancement due to sonication is postulated to arise from the localized lowering of atomic densities, localized heating, and generation of radicals due to cavitation collapse in aqueous systems. This dramatic increase in reaction rates translates into enhanced nucleation andmore » growth of the polymer spheres. Finally, the results are of broad significance to understanding mechanisms of sonication induced synthesis as well as technologies utilizing polymers spheres.« less

Cavitation and radicals drive the sonochemical synthesis of functional polymer spheres

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

Narayanan, Badri, E-mail: bnarayanan@anl.gov; Deshmukh, Sanket A.; Sankaranarayanan, Subramanian K. R. S., E-mail: ssankaranarayanan@anl.gov

2016-07-25

Sonochemical synthesis can lead to a dramatic increase in the kinetics of formation of polymer spheres (templates for carbon spheres) compared to the modified Stöber silica method applied to produce analogous polymer spheres. Reactive molecular dynamics simulations of the sonochemical process indicate a significantly enhanced rate of polymer sphere formation starting from resorcinol and formaldehyde precursors. The associated chemical reaction kinetics enhancement due to sonication is postulated to arise from the localized lowering of atomic densities, localized heating, and generation of radicals due to cavitation collapse in aqueous systems. This dramatic increase in reaction rates translates into enhanced nucleation andmore » growth of the polymer spheres. The results are of broad significance to understanding mechanisms of sonication induced synthesis as well as technologies utilizing polymers spheres.« less

Future space transport

NASA Technical Reports Server (NTRS)

Grishin, S. D.; Chekalin, S. V.

1984-01-01

Prospects for the mastery of space and the basic problems which must be solved in developing systems for both manned and cargo spacecraft are examined. The achievements and flaws of rocket boosters are discussed as well as the use of reusable spacecraft. The need for orbiting satellite solar power plants and related astrionics for active control of large space structures for space stations and colonies in an age of space industrialization is demonstrated. Various forms of spacecraft propulsion are described including liquid propellant rocket engines, nuclear reactors, thermonuclear rocket engines, electrorocket engines, electromagnetic engines, magnetic gas dynamic generators, electromagnetic mass accelerators (rail guns), laser rocket engines, pulse nuclear rocket engines, ramjet thermonuclear rocket engines, and photon rockets. The possibilities of interstellar flight are assessed.

Preliminary study of a hydrogen peroxide rocket for use in moving source jet noise tests

NASA Technical Reports Server (NTRS)

Plencner, R. M.

1977-01-01

A preliminary investigation was made of using a hydrogen peroxide rocket to obtain pure moving source jet noise data. The thermodynamic cycle of the rocket was analyzed. It was found that the thermodynamic exhaust properties of the rocket could be made to match those of typical advanced commercial supersonic transport engines. The rocket thruster was then considered in combination with a streamlined ground car for moving source jet noise experiments. When a nonthrottlable hydrogen peroxide rocket was used to accelerate the vehicle, propellant masses and/or acceleration distances became too large. However, when a throttlable rocket or an auxiliary system was used to accelerate the vehicle, reasonable propellant masses could be obtained.

Effect of vaginal spheres and pelvic floor muscle training in women with urinary incontinence: a randomized, controlled trial.

PubMed

Porta-Roda, Oriol; Vara-Paniagua, Jesús; Díaz-López, Miguel A; Sobrado-Lozano, Pilar; Simó-González, Marta; Díaz-Bellido, Paloma; Reula-Blasco, María C; Muñoz-Garrido, Francisco

2015-08-01

To compare the efficacy and safety of Kegel exercises performed with or without, vaginal spheres as treatment for women with urinary incontinence. Multicentre parallel-group, open, randomized controlled trial. Women were allocated to either a pelvic floor muscle-training program consisting of Kegel exercises performed twice daily, 5 days/week at home, over 6 months with vaginal spheres, or to the same program without spheres. The primary endpoint was women's report of urinary incontinence at 6 months using the International Consultation on Incontinence Questionnaire-Short Form (ICIQ-UI-SF). Secondary outcome measures were the 1 hr pad-test, King's Health Questionnaire (KHQ) and a five-point Likert scale for subjective evaluation. Adherence was measured with the Morisky-Green test. Thirty-seven women were randomized to the spheres group and 33 to the control group. The primary endpoint was evaluated in 65 women (35 in the spheres group vs. 30 controls). ICIQ-UI-SF results improved significantly at 1-month follow-up in the spheres group (P < 0.01) and at 6 months in the controls. The 1 hr pad-test improved in the spheres group but not in the control group. No significant differences were found in the KHQ results or in the subjective evaluation of efficacy and safety. Adherence was higher in the spheres group but differences were not significant. Mild transient side effects were reported in four patients in the spheres group and one in the control group. Both treatments improved urinary incontinence but women who performed the exercises with vaginal spheres showed an earlier improvement. Vaginal spheres were well tolerated and safe. © 2014 Wiley Periodicals, Inc.

Improving of Hybrid Rocket Engine on the Basis of Optimizing Design Fuel Grain

NASA Astrophysics Data System (ADS)

Oriekov, K. M.; Ushkin, M. P.

2015-09-01

This article examines the processes intrachamber in hybrid rocket engine (HRE) and the comparative assessment of the use of solid rocket motors (SRM) and HRE for meteorological rockets with a mass of payload of the 364 kg. Results of the research showed the possibility of a significant increase in the ballistic effectiveness of meteorological rocket.

33 CFR 334.1290 - In Bering Sea, Shemya Island Area, Alaska; meteorological rocket launching facility, Alaskan Air...

Code of Federal Regulations, 2010 CFR

2010-07-01

..., Alaska; meteorological rocket launching facility, Alaskan Air Command, U.S. Air Force. 334.1290 Section...; meteorological rocket launching facility, Alaskan Air Command, U.S. Air Force. (a) The danger zone. An arc of a...) Rockets will normally be launched one each day Monday through Friday between 9 a.m. and 3 p.m. Rocket...

33 CFR 334.1290 - In Bering Sea, Shemya Island Area, Alaska; meteorological rocket launching facility, Alaskan Air...

Code of Federal Regulations, 2011 CFR

2011-07-01

..., Alaska; meteorological rocket launching facility, Alaskan Air Command, U.S. Air Force. 334.1290 Section...; meteorological rocket launching facility, Alaskan Air Command, U.S. Air Force. (a) The danger zone. An arc of a...) Rockets will normally be launched one each day Monday through Friday between 9 a.m. and 3 p.m. Rocket...

33 CFR 334.1290 - In Bering Sea, Shemya Island Area, Alaska; meteorological rocket launching facility, Alaskan Air...

Code of Federal Regulations, 2014 CFR

2014-07-01

..., Alaska; meteorological rocket launching facility, Alaskan Air Command, U.S. Air Force. 334.1290 Section...; meteorological rocket launching facility, Alaskan Air Command, U.S. Air Force. (a) The danger zone. An arc of a...) Rockets will normally be launched one each day Monday through Friday between 9 a.m. and 3 p.m. Rocket...

33 CFR 334.1290 - In Bering Sea, Shemya Island Area, Alaska; meteorological rocket launching facility, Alaskan Air...

Code of Federal Regulations, 2013 CFR

2013-07-01

..., Alaska; meteorological rocket launching facility, Alaskan Air Command, U.S. Air Force. 334.1290 Section...; meteorological rocket launching facility, Alaskan Air Command, U.S. Air Force. (a) The danger zone. An arc of a...) Rockets will normally be launched one each day Monday through Friday between 9 a.m. and 3 p.m. Rocket...

33 CFR 334.1290 - In Bering Sea, Shemya Island Area, Alaska; meteorological rocket launching facility, Alaskan Air...

Code of Federal Regulations, 2012 CFR

2012-07-01

..., Alaska; meteorological rocket launching facility, Alaskan Air Command, U.S. Air Force. 334.1290 Section...; meteorological rocket launching facility, Alaskan Air Command, U.S. Air Force. (a) The danger zone. An arc of a...) Rockets will normally be launched one each day Monday through Friday between 9 a.m. and 3 p.m. Rocket...

Filter Bed of Packed Spheres

NASA Technical Reports Server (NTRS)

Elleman, D. D.; Wang, T. G.

1986-01-01

Spheres sized and treated for desired sieve properties. Filter constructed from densely packed spheres restrained by screens. Hollow gas-filled plastic or metal spheres normally used. Manufactured within one percent or better diameter tolerance. Normally, all spheres in filter of same nominal diameter. Filter used as sieve to pass only particles smaller than given size or to retain particles larger than that size. Options available under filter concept make it easy to design for specific applications.

Measurements of temperature profiles at the exit of small rockets.

PubMed

Griggs, M; Harshbarger, F C

1966-02-01

The sodium line reversal technique was used to determine the reversal temperature profile across the exit of small rockets. Measurements were made on one 73-kg thrust rocket, and two 23-kg thrust rockets with different injectors. The large rocket showed little variation of reversal temperature across the plume. However, the 23-kg rockets both showed a large decrease of reversal temperature from the axis to the edge of the plume. In addition, the sodium line reversal technique of temperature measurement was compared with an infrared technique developed in these laboratories.

Early Rockets

NASA Image and Video Library

2004-04-15

During the 19th century, rocket enthusiasts and inventors began to appear in almost every country. Some people thought these early rocket pioneers were geniuses, and others thought they were crazy. Claude Ruggieri, an Italian living in Paris, apparently rocketed small animals into space as early as 1806. The payloads were recovered by parachute. As depicted here by artist Larry Toschik, French authorities were not always impressed with rocket research. They halted Ruggieri's plans to launch a small boy using a rocket cluster. (Reproduced from a drawing by Larry Toschik and presented here courtesy of the artist and Motorola Inc.)

Forming MOFs into spheres by use of molecular gastronomy methods.

PubMed

Spjelkavik, Aud I; Aarti; Divekar, Swapnil; Didriksen, Terje; Blom, Richard

2014-07-14

A novel method utilizing hydrocolloids to prepare nicely shaped spheres of metal-organic frameworks (MOFs) has been developed. Microcrystalline CPO-27-Ni particles are dispersed in either alginate or chitosan solutions, which are added dropwise to solutions containing, respectively, either divalent group 2 cations or base that act as gelling agents. Well-shaped spheres are immediately formed, which can be dried into spheres containing mainly MOF (>95 wt %). The spheronizing procedures have been optimized with respect to maximum specific surface area, shape, and particle density of the final sphere. At optimal conditions, well-shaped 2.5-3.5 mm diameter CPO-27-Ni spheres with weight-specific surface areas <10 % lower than the nonformulated CPO-27-Ni precursor, and having sphere densities in the range 0.8 to 0.9 g cm(-3) and particle crushing strengths above 20 N, can be obtained. The spheres are well suited for use in fixed-bed catalytic or adsorption processes. © 2014 WILEY-VCH Verlag GmbH & Co. KGaA, Weinheim.

iSAP: Interactive Sparse Astronomical Data Analysis Packages

NASA Astrophysics Data System (ADS)

Fourt, O.; Starck, J.-L.; Sureau, F.; Bobin, J.; Moudden, Y.; Abrial, P.; Schmitt, J.

2013-03-01

iSAP consists of three programs, written in IDL, which together are useful for spherical data analysis. MR/S (MultiResolution on the Sphere) contains routines for wavelet, ridgelet and curvelet transform on the sphere, and applications such denoising on the sphere using wavelets and/or curvelets, Gaussianity tests and Independent Component Analysis on the Sphere. MR/S has been designed for the PLANCK project, but can be used for many other applications. SparsePol (Polarized Spherical Wavelets and Curvelets) has routines for polarized wavelet, polarized ridgelet and polarized curvelet transform on the sphere, and applications such denoising on the sphere using wavelets and/or curvelets, Gaussianity tests and blind source separation on the Sphere. SparsePol has been designed for the PLANCK project. MS-VSTS (Multi-Scale Variance Stabilizing Transform on the Sphere), designed initially for the FERMI project, is useful for spherical mono-channel and multi-channel data analysis when the data are contaminated by a Poisson noise. It contains routines for wavelet/curvelet denoising, wavelet deconvolution, multichannel wavelet denoising and deconvolution.