Small Body Science via Swarms of Nano-Satellites

NASA Astrophysics Data System (ADS)

Ernst, Sebastian M.; Lewis, John S.

2015-04-01

Imagine you had a fleet of nano-satellites deployed around an asteroid or comet, or directly on its surface. What things could you do with it that you could not do any other way? Missions which transport a number of small spacecraft and deploy it near small bodes, moons or planets are becoming ever more feasible and realistic. While constellations of nano-satellites already carry a significant weight in terrestrial remote sensing, the potential of similar concepts for planetary science missions has not yet been extensively explored. There have been proposals for such scenarios for the past decades, though only now is there the technology to make them happen. Multiple types of sensor networks can be deployed around planetary bodies or onto their surface while they can interact with each other if required. Furthermore, individual spacecraft become expendable. We wish to call attention to all the research in this field which has been conducted so far and inspire the planetary science community to further investigate the possibies of such mission architechtures.

Expendable oceanographic sensor apparatus

DOEpatents

McCoy, Kim O.; Downing, Jr., John P.; DeRoos, Bradley G.; Riches, Michael R.

1993-01-01

An expendable oceanographic sensor apparatus is deployed from an airplane or a ship to make oceanographic observations in a profile of the surface-to-ocean floor, while deployed on the floor, and then a second profile when returning to the ocean surface. The device then records surface conditions until on-board batteries fail. All data collected is stored and then transmitted from the surface to either a satellite or other receiving station. The apparatus is provided with an anchor that causes descent to the ocean floor and then permits ascent when the anchor is released. Anchor release is predetermined by the occurrence of a pre-programmed event.

Structural Analysis of Components of the Students for the Exploration and Development of Space Satellite (SEDSAT) for the Small Expendable Deployer System (SEDS) Project Office

NASA Technical Reports Server (NTRS)

Maddux, Gary A.

1998-01-01

During the time frame allocated by the delivery order, members of the UAH Applied Research Program, with the cooperation of representatives from NASA investigated and conducted stress analysis of the SEDSAT1 satellite. The main area of concern was with the design of the deployable 10 m antennas. The placement of the holes for the antenna door hinge pin was too close to the edge of the antenna canister. Because of the load placed on the hinge pin, the stress analysis of this area suggested that more space would be needed between the holes and the edge of the material. Due to other conflicts, SEDSATI was removed from flying on the space shuttle and moved to the Delta Launch Vehicle. This changed many of the design requirements for the mounting and deployment of the satellite that forced a new design for the satellite. Once this happened, the stress analysis became obsolete, and the task was concluded.

Analytical investigation of the dynamics of tethered constellations in Earth orbit, phase 2

NASA Technical Reports Server (NTRS)

Lorenzini, Enrico C.; Gullahorn, Gordon E.; Cosmo, Mario L.; Estes, Robert D.; Grossi, Mario D.

1994-01-01

This final report covers nine years of research on future tether applications and on the actual flights of the Small Expendable Deployment System (SEDS). Topics covered include: (1) a description of numerical codes used to simulate the orbital and attitude dynamics of tethered systems during station keeping and deployment maneuvers; (2) a comparison of various tethered system simulators; (3) dynamics analysis, conceptual design, potential applications and propagation of disturbances and isolation from noise of a variable gravity/microgravity laboratory tethered to the Space Station; (4) stability of a tethered space centrifuge; (5) various proposed two-dimensional tethered structures for low Earth orbit for use as planar array antennas; (6) tethered high gain antennas; (7) numerical calculation of the electromagnetic wave field on the Earth's surface on an electrodynamically tethered satellite; (8) reentry of tethered capsules; (9) deployment dynamics of SEDS-1; (10) analysis of SEDS-1 flight data; and (11) dynamics and control of SEDS-2.

JPSS-1 P-Pod Installation

NASA Image and Video Library

2017-10-31

At Vandenberg Air Force Base in California, a Poly Picosatellite Orbital Deployer, or P-POD, container is installed on the Joint Polar Satellite System-1, or JPSS-1, spacecraft. P-PODS are auxiliary payloads launched aboard NASA expendable launch vehicles carrying up to three small CubeSats. The small cube-shaped satellites are part of NASA’s Educational Launch of Nanosatellite, or ELaNa, missions. The small payloads are designed and built by students from high school-level classes up to college and university students. JPSS is the first in a series of four next-generation environmental satellites in a collaborative program between the NOAA and NASA. Liftoff from Vandenberg's Space Launch Compex-2 atop a United Launch Alliance Delta II rocket is scheduled for 1:47 a.m. PST (4:47 a.m. EST), on Nov. 14, 2017.

JPSS-1 P-Pod Installation

NASA Image and Video Library

2017-10-31

At Vandenberg Air Force Base in California, technicians and engineers prepare to install a Poly Picosatellite Orbital Deployer, or P-POD, container on the Joint Polar Satellite System-1, or JPSS-1, spacecraft. P-PODS are auxiliary payloads launched aboard NASA expendable launch vehicles carrying up to three small CubeSats. The small cube-shaped satellites are part of NASA’s Educational Launch of Nanosatellite, or ELaNa, missions. The small payloads are designed and built by students from high school-level classes up to college and university students. JPSS is the first in a series of four next-generation environmental satellites in a collaborative program between the NOAA and NASA. Liftoff from Vandenberg's Space Launch Compex-2 atop a United Launch Alliance Delta II rocket is scheduled for 1:47 a.m. PST (4:47 a.m. EST), on Nov. 14, 2017.

JPSS-1 P-Pod Installation

NASA Image and Video Library

2017-10-31

At Vandenberg Air Force Base in California, technicians and engineers prepare a Poly Picosatellite Orbital Deployer, or P-POD, container for installation on the Joint Polar Satellite System-1, or JPSS-1, spacecraft. P-PODS are auxiliary payloads launched aboard NASA expendable launch vehicles carrying up to three small CubeSats. The small cube-shaped satellites are part of NASA’s Educational Launch of Nanosatellite, or ELaNa, missions. The small payloads are designed and built by students from high school-level classes up to college and university students. JPSS is the first in a series of four next-generation environmental satellites in a collaborative program between the NOAA and NASA. Liftoff from Vandenberg's Space Launch Compex-2 atop a United Launch Alliance Delta II rocket is scheduled for 1:47 a.m. PST (4:47 a.m. EST), on Nov. 14, 2017.

Space Station Integrated Kinetic Launcher for Orbital Payload Systems (SSIKLOPS) - Cyclops

NASA Technical Reports Server (NTRS)

Smith, James P.; Lamb, Craig R.; Ballard, Perry G.

2013-01-01

Access to space for satellites in the 50-100 kg class is a challenge for the small satellite community. Rideshare opportunities are limited and costly, and the small sat must adhere to the primary payloads schedule and launch needs. Launching as an auxiliary payload on an Expendable Launch Vehicle presents many technical, environmental, and logistical challenges to the small satellite community. To assist the community in mitigating these challenges and in order to provide the community with greater access to space for 50-100 kg satellites, the NASA International Space Station (ISS) and Engineering communities in collaboration with the Department of Defense (DOD) Space Test Program (STP) is developing a dedicated 50-100 kg class ISS small satellite deployment system. The system, known as Cyclops, will utilize NASA's ISS resupply vehicles to launch small sats to the ISS in a controlled pressurized environment in soft stow bags. The satellites will then be processed through the ISS pressurized environment by the astronaut crew allowing satellite system diagnostics prior to orbit insertion. Orbit insertion is achieved through use of the Japan Aerospace Exploration Agency's Experiment Module Robotic Airlock (JEM Airlock) and one of the ISS Robotic Arms. Cyclops' initial satellite deployment demonstration of DOD STP's SpinSat and UT/TAMU's Lonestar satellites will be toward the end of 2013 or beginning of 2014. Cyclops will be housed on-board the ISS and used throughout its lifetime. The anatomy of Cyclops, its concept of operations for satellite deployment, and its satellite interfaces and requirements will be addressed further in this paper.

ProSEDS Telemetry System Utilization of GPS Position Data for Transmitter Cycling

NASA Technical Reports Server (NTRS)

Kennedy, Paul; Sims, Herb

2000-01-01

NASA Marshall Space Flight Center will launch the Propulsive Small Expendable Deployer System (ProSEDS) space experiment in late 2000. ProSEDS will demonstrate the use of an electrodynamic tether propulsion system and will utilize a conducting wire tether to generate limited spacecraft power. This paper will provide an overview of the ProSEDS mission and will discuss the design, development and test of the spacecraft telemetry system which utilizes a custom designed GPS subsystem to determine spacecraft position relative to ground station location and to control transmitter on/off cycling based on spacecraft state vector and ground station visibility.

Performance and safety testing of lithium batteries for the Expendable, Mobile, ASW Training Target (EMATT)

NASA Astrophysics Data System (ADS)

Hallal, P. B.; Bis, R. F.

1986-08-01

The developmental EMATT (expendable, mobile, ASW training target) may use a high-energy (lithium/sulfuryl chloride) battery system. Safety problems with the original battery cell design were experienced during early performance and safety testing. After redesign of the battery cell, performance and safety tests were made under specified abuse conditions, as well as under simulated launch conditions. The test results showed that the power system now meets all safety requirements, and that the EMATT vehicle is safe to deploy for its engineering development phase.

Space Station tethered waste disposal

NASA Technical Reports Server (NTRS)

Rupp, Charles C.

1988-01-01

The Shuttle Transportation System (STS) launches more payload to the Space Station than can be returned creating an accumulation of waste. Several methods of deorbiting the waste are compared including an OMV, solid rocket motors, and a tether system. The use of tethers is shown to offer the unique potential of having a net savings in STS launch requirement. Tether technology is being developed which can satisfy the deorbit requirements but additional effort is required in waste processing, packaging, and container design. The first step in developing this capability is already underway in the Small Expendable Deployer System program. A developmental flight test of a tether initiated recovery system is seen as the second step in the evolution of this capability.

A System of Systems Approach for Martian Exploration

NASA Astrophysics Data System (ADS)

Semrud, E. B.; Evans, B. W.; Fredericks, B.; Wells, D.

2012-06-01

A system of systems is designed for characterization of the Martian atmosphere and exploration of lava tubes in preparation for human colonization. Multiple expendable deployable sensor packages ensure mission success with a high level of redundancy.

Aerodynamic Characteristics and Glide-Back Performance of Langley Glide-Back Booster

NASA Technical Reports Server (NTRS)

Pamadi, Bandu N.; Covell, Peter F.; Tartabini, Paul V.; Murphy, Kelly J.

2004-01-01

NASA-Langley Research Center is conducting system level studies on an-house concept of a small launch vehicle to address NASA's needs for rapid deployment of small payloads to Low Earth Orbit. The vehicle concept is a three-stage system with a reusable first stage and expendable upper stages. The reusable first stage booster, which glides back to launch site after staging around Mach 3 is named the Langley Glide-Back Booster (LGBB). This paper discusses the aerodynamic characteristics of the LGBB from subsonic to supersonic speeds, development of the aerodynamic database and application of this database to evaluate the glide back performance of the LGBB. The aerodynamic database was assembled using a combination of wind tunnel test data and engineering level analysis. The glide back performance of the LGBB was evaluated using a trajectory optimization code and subject to constraints on angle of attack, dynamic pressure and normal acceleration.

Accelerated vehicle-to-infrastructure (V2I) safety applications : system requirements document : final.

DOT National Transportation Integrated Search

2001-05-01

The purpose of this working paper is to provide an estimate of the federal proportion of funds expended on intelligent transportation systems (ITS) infrastructure deployments for fiscal year (FY) 2000 using budget and planning data from state departm...

Biomechanics of an Expandable Lumbar Interbody Fusion Cage Deployed Through Transforaminal Approach

PubMed Central

Mica, Michael Conti; Voronov, Leonard I.; Carandang, Gerard; Havey, Robert M.; Wojewnik, Bartosz

2017-01-01

Introduction A novel expandable lumbar interbody fusion cage has been developed which allows for a broad endplate footprint similar to an anterior lumbar interbody fusion (ALIF); however, it is deployed from a minimally invasive transforaminal unilateral approach. The perceived benefit is a stable circumferential fusion from a single approach that maintains the anterior tension band of the anterior longitudinal ligament. The purpose of this biomechanics laboratory study was to evaluate the biomechanical stability of an expandable lumbar interbody cage inserted using a transforaminal approach and deployed in situ compared to a traditional lumbar interbody cage inserted using an anterior approach (control device). Methods Twelve cadaveric spine specimens (L1-L5) were tested intact and after implantation of both the control and experimental devices in two (L2-L3 and L3-L4) segments of each specimen; the assignments of the control and experimental devices to these segments were alternated. Effect of supplemental pedicle screw-rod stabilization was also assessed. Moments were applied to the specimens in flexion-extension (FE), lateral bending (LB), and axial rotation (AR). The effect of physiologic preload on construct stability was evaluated in FE. Segmental motions were measured using an optoelectronic motion measurement system. Results The deployable expendable TLIF cage and control devices significantly reduced FE motion with and without compressive preload when compared to the intact condition (p<0.05). Segmental motions in LB and AR were also significantly reduced with both devices (p<0.05). Under no preload, the deployable expendable TLIF cage construct resulted in significantly smaller FE motion compared to the control cage construct (p<0.01). Under all other testing modes (FE under 400N preload, LB, and AR) the postoperative motions of the two constructs did not differ statistically (p>0.05). Adding bilateral pedicle screws resulted in further reduction of ROM for all loading modes compared to intact condition, with no statistical difference between the two constructs (p>0.05). Conclusions The ability of the deployable expendable interbody cage in reducing segmental motions was equivalent to the control cage when used as a stand-alone construct and also when supplemented with bilateral pedicle screw-rod instrumentation. The larger footprint of the fully deployed TLIF cage combined with preservation of the anterior soft-tissue tension band may provide a better biomechanical fusion environment by combining the advantages of the traditional ALIF and TLIF approaches. PMID:29372129

Working paper : estimating the federal proportion of funds expended on ITS infrastructure for fiscal year 2000

DOT National Transportation Integrated Search

2000-01-01

In January 1996, Secretary Pena set a goal of deploying the integrated metropolitan Intelligent Transportation System (ITS) infrastructure in 75 of the nation's largest metropolitan areas by 2006. In 1997, the U.S. Department of Transportation initia...

Pathfinder

NASA Image and Video Library

2001-07-01

This photograph shows two Marshall Space Flight Center (MSFC) engineers, Mark Vaccaro (left) and Ken Welzyn, testing electrodynamic tethers in the MSFC Tether Winding and Spark Testing Facility. For 4 years, MSFC and industry partners have been developing the Propulsive Small Expendable Deployer System experiment, called ProSEDS. ProSEDS will test electrodynamic tether propulsion technology. Electrodynamic tethers are long, thin wires that collect electrical current when passing through a magnetic field. The tether works as a thruster as a magnetic field exerts a force on a current-carrying wire. Since electrodynamic tethers require no propellant, they could substantially reduce the weight of the spacecraft and provide a cost-effective method of reboosting spacecraft. The initial flight of ProSEDS is scheduled to fly aboard an Air Force Delta II rocket in the summer of 2002. In orbit, ProSEDS will deploy from a Delta II second stage. It will be a 3.1-mile (5 kilometer) long, ultrathin base-wire tether cornected with a 6.2-mile (10 kilometer) long non-conducting tether. This photograph shows Less Johnson, a scientist at MSFC, inspecting the nonconducting part of a tether as it exits a deployer similar to the one to be used in the ProSEDS experiment. The ProSEDS experiment is managed by the Space Transportation Directorate at MSFC.

Estimation of outgassing from an expended apogee motor and its effects on spacecraft surfaces

NASA Technical Reports Server (NTRS)

Scialdone, J. J.; Rogers, J. F.; Kruger, R.

1977-01-01

An experimental and theoretical investigation was carried out to evaluate the degradation of the solar cells and other sensitive surfaces of a spacecraft, resulting from the molecular outgassing of an expended solid propellant apogee motor. The motor, following its burnout, is retained by the spacecraft and is a source of gases and particulates which will be released mainly by the unburned propellant-to-casing insulation. The deployment of the solar array within a few minutes after the motor burn results in the interception and reflection to the surfaces of the spacecraft of the molecular outgassing and particulates. Various methods, based on some experimental data, were used to analytically assess the magnitude of the outgassing from the engine.

Pathfinder

NASA Image and Video Library

1999-03-01

NASA's Propulsive Small Expendable Deployer System experiment (ProSEDS) will demonstrate the use of an electrodynamic tether, basically a long, thin wire, for propulsion. An electrodynamic tether uses the same principles as electric motors in toys, appliances and computer disk drives, and generators in automobiles and power plants. When electrical current is flowing through the tether, a magnetic field is produced that pushes against the magnetic field of the Earth. For ProSEDS, the current in the tether results by virtue of the voltage generated when the tether moves through the Earth's magnetic field at more than 17,000 mph. This approach can produce drag thrust generating useable power. Since electrodynamic tethers require no propellant, they could substantially reduce the weight of the spacecraft and provide a cost-effective method of reboosting spacecraft. The initial flight of ProSEDS is scheduled to fly aboard an Air Force Delta II rocket in the summer of 2002. In orbit, ProSEDS will deploy from a Delta II second stage. It will be a 3.1-mile (5 kilometer) long, ultrathin base-wire cornected with a 6.2-mile (10 kilometer) long nonconducting tether. This photograph shows Less Johnson, a scientist at MSFC inspecting the nonconducting part of a tether as it exits a deployer similar to the one to be used in the ProSEDS experiment. The ProSEDS experiment is managed by the Space Transportation Directorate at MSFC.

14 CFR 420.19 - Launch site location review-general.

Code of Federal Regulations, 2011 CFR

2011-01-01

... nm orbit Weight class Small Medium Medium large Large 28 degrees inclination * ≤4400 >4400 to ≤11100.... Orbital expendable launch vehicles are further classified by weight class, based on the weight of payload... class of orbital expendable launch vehicles flown from a launch point, the applicant shall demonstrate...

Prospects for commercialization of SELV-based in-space operations

NASA Technical Reports Server (NTRS)

Katzberg, Stephen J. (Compiler); Garrison, James L., Jr. (Compiler)

1995-01-01

A workshop was hosted by the Langley Research Center as a part of an activity to assess the commercialization potential of Small Expendible Launch Vehicle-based in-space operations. Representatives of the space launch insurance industry, industrial consultants, producers of spacecraft, launch vehicle manufacturers, and government researchers constituted the participants. The workshop was broken into four sessions: Customers Small Expendible Launch Systems, Representative Missions, and Synthesis-Government role. This publication contains the presentation material, written synopses of the sessions, and conclusions developed at the workshop.

Manned systems utilization analysis (study 2.1). Volume 5: Program listing for the LOVES computer code

NASA Technical Reports Server (NTRS)

Wray, S. T., Jr.

1975-01-01

The LOVES computer code developed to investigate the concept of space servicing operational satellites as an alternative to replacing expendable satellites or returning satellites to earth for ground refurbishment is presented. In addition to having the capability to simulate the expendable satellite operation and the ground refurbished satellite operation, the program is designed to simulate the logistics of space servicing satellites using an upper stage vehicle and/or the earth to orbit shuttle. The program not only provides for the initial deployment of the satellite but also simulates the random failure and subsequent replacement of various equipment modules comprising the satellite. The program has been used primarily to conduct trade studies and/or parametric studies of various space program operational philosophies.

Deployment of 464XLAT (RFC6877) alongside IPv6-only CPU resources at WLCG sites

NASA Astrophysics Data System (ADS)

Froy, T. S.; Traynor, D. P.; Walker, C. J.

2017-10-01

IPv4 is now officially deprecated by the IETF. A significant amount of effort has already been expended by the HEPiX IPv6 Working Group on testing dual-stacked hosts and IPv6-only CPU resources. Dual-stack adds complexity and administrative overhead to sites that may already be starved of resource. This has resulted in a very slow uptake of IPv6 from WLCG sites. 464XLAT (RFC6877) is intended for IPv6 single-stack environments that require the ability to communicate with IPv4-only endpoints. This paper will present a deployment strategy for 464XLAT, operational experiences of using 464XLAT in production at a WLCG site and important information to consider prior to deploying 464XLAT.

Environmental Assessment for the Advanced Extremely High Frequency Satellite Beddown and Deployment Program

DTIC Science & Technology

2010-07-01

Final Environmental Assessment 22 Several invasive exotic plant species are also found on the station , particularly in disturbed areas such as...Department of Transportation EA Environmental Assessment Ec Debris Casualty Area EELV Evolved Expendable Launch Vehicle EIS Environmental Impact...Canaveral Air Force Station (CCAFS) in Florida (FL). This Environmental Assessment (EA) documents the results of a study of the potential

Pathfinder

NASA Image and Video Library

1999-03-25

Pictured is an artist's concept of NASA's Propulsive Small Expendable Deployer System experiment (ProSEDS). ProSEDS will demonstrate the use of an electrodynamic tether, basically a long, thin wire, for propulsion. An electrodynamic tether uses the same principles as electric motors in toys, appliances and computer disk drives, and generators in automobiles and power plants. When electrical current is flowing through the tether, a magnetic field is produced that pushes against the magnetic field of the Earth. For ProSEDS, the current in the tether results by virtue of the voltage generated when the tether moves through the Earth's magnetic field at more than 17,000 mph. This approach can produce drag thrust generating useable power. Since electrodynamic tethers require no propellant, they could substantially reduce the weight of the spacecraft and provide a cost-effective method of reboosting spacecraft. The initial flight of ProSEDS is scheduled to fly aboard an Air Force Delta II rocket in summer of 2002. In orbit, ProSEDS will deploy from a Delta II second stage. It will be a 3.1-mile (5 kilometer) long, ultrathin base-wire tether cornected with a 6.2-mile (10 kilometer) long nonconducting tether. The ProSEDS experiment is managed by the Space Transportation Directorate at the Marshall Space Flight Center.

Experience with integrally-cast compressor and turbine components for a small, low-cost, expendable-type turbojet engine

NASA Technical Reports Server (NTRS)

Dengler, R. P.

1975-01-01

Experiences with integrally-cast compressor and turbine components during fabrication and testing of four engine assemblies of a small (29 cm (11 1/2 in.) maximum diameter) experimental turbojet engine design for an expendable application are discussed. Various operations such as metal removal, welding, and re-shaping of these components were performed in preparation of full-scale engine tests. Engines with these components were operated for a total of 157 hours at engine speeds as high as 38,000 rpm and at turbine inlet temperatures as high as 1256 K (1800 F).

Air Deployable Underwater Glider and Buoy Development for Arctic and Oceanographic Sensing

NASA Astrophysics Data System (ADS)

Legnos, P. J.

2013-12-01

LBI developed under a NOAA SBIR the AXIB (Airborne eXpendable Ice Buoy). The initial buoy was developed to collect barometric pressure, air temperature two meters above the surface and sea surface or ice temperature. A number of these AXIBs have been successfully deployed in the Arctic and Antarctic. Currently we are in the process of integrating additional sensors to include an anemometer, thermistor chain and hydrophones. Further development is in process for the integration of solar and wind recharging systems and lower power sensors and processing LBI developed under an ONR SBIR Grant two Air Deployable Underwater Gliders. They are primarily designed for air deployment from Navy P-3 or P-8 Aircraft though easily deployed from other aircraft or helicopters. The A-size (4 7/8'dia. X 36' long) and the 12 ¾ (12 ¾' dia. X 9' 9' long). On the development side we are in the process of integrating sensors and enhancing the battery storage capacity. We anticipate a broad range of Oceanographic sensing missions for these Gliders.

Safety testing of lithium cells

NASA Technical Reports Server (NTRS)

Liberto, Nick

1991-01-01

Safety testing is intended to simulate, under laboratory conditions and controls, situations that will subject a cell to externally induced stress. The stresses can occur at any time during the useful life of the cell, from the time of manufacture until it is expended during mission deployment. Abuse testing can be divided into three major categories: Electrical, Mechanical, and Thermal. Although electrical abuses are generally found to occur during handling or deployment, Mechanical and Thermal stresses can be induced during transportation and storage. Therefore, it would be prudent to include predicted environmental exposure as part of the test plan. In the selection of a test program. specific test requirements should be tailored to meet the predicted mission requirements.

Safety testing of lithium cells

NASA Astrophysics Data System (ADS)

Liberto, Nick

1991-05-01

Safety testing is intended to simulate, under laboratory conditions and controls, situations that will subject a cell to externally induced stress. The stresses can occur at any time during the useful life of the cell, from the time of manufacture until it is expended during mission deployment. Abuse testing can be divided into three major categories: Electrical, Mechanical, and Thermal. Although electrical abuses are generally found to occur during handling or deployment, Mechanical and Thermal stresses can be induced during transportation and storage. Therefore, it would be prudent to include predicted environmental exposure as part of the test plan. In the selection of a test program. specific test requirements should be tailored to meet the predicted mission requirements.

The Design and Operation of a Slowfall AXCP (Air-Deployed Expendable Current Profiler).

DTIC Science & Technology

1988-05-01

Control Sensors pressure switch , P/N 607G6 .................................................... 13 Figure 8. Two-dimensional, free-body diagram of the...surface as well as a release mechanism. We then considered using an inexpensive pressure switch to trip the release mechanism. After a market survey...guillotine and pressure switch from the 250 to 300 psi pressure of seawater without resorting to a high precision 0-ring sealing system and pressure

Measurement of Near-Surface Salinity, Temperature and Directional Wave Spectra using a Novel Wave-Following, Lagrangian Surface Contact Buoy

NASA Astrophysics Data System (ADS)

Boyle, J. P.

2016-02-01

Results from a surface contact drifter buoy which measures near-surface conductivity ( 10 cm depth), sea state characteristics and near-surface water temperature ( 2 cm depth) are described. This light (< 750 gram), wave-following discus buoy platform has a hull diameter of 25 cm and a thickness of approximately 3 cm. The buoy is designed to allow for capsize events, but remains top up because it is ballasted for self-righting. It has a small above-surface profile and low windage, resulting in near-Lagrangian drift characteristics. It is autonomous, with low power requirements and solar panel battery recharging. Onboard sensors include an inductive toroidal conductivity probe for salinity measurement, a nine-degrees-of-freedom motion package for derivation of directional wave spectra and a thermocouple for water temperature measurement. Data retrieval for expendable, ocean-going operation uses an onboard Argos transmitter. Scientific results as well as data processing algorithms are presented from laboratory and field experiments which support qualification of buoy platform measurements. These include sensor calibration experiments, longer-term dock-side biofouling experiments during 2013-2014 and a series of short-duration ocean deployments in the Gulf Stream in 2014. In addition, a treatment method will be described which appears to minimize the effects of biofouling on the inductive conductivity probe when in coastal surface waters. Due to its low cost and ease of deployment, scores, perhaps hundreds of these novel instruments could be deployed from ships or aircraft during process studies or to provide surface validation for satellite-based measurements, particularly in high precipitation regions.

SPECS: Orbital debris removal

NASA Technical Reports Server (NTRS)

1991-01-01

The debris problem has reached a stage at which the risk to satellites and spacecraft has become substantial in low Earth orbit (LEO). This research discovered that small particles posed little threat to spacecraft because shielding can effectively prevent these particles from damaging the spacecraft. The research also showed that, even though collision with a large piece of debris could destroy the spacecraft, the large pieces of debris pose little danger because they can be tracked and the spacecraft can be maneuvered away from these pieces. Additionally, there are many current designs to capture and remove large debris particles from the space environment. From this analysis, it was decided to concentrate on the removal of medium-sized orbital debris, that is, those pieces ranging from 1 cm to 50 cm in size. The current design incorporates a transfer vehicle and a netting vehicle to capture the medium-sized debris. The system is based near an operational space station located at 28.5 deg inclination and 400 km altitude. The system uses ground-based tracking to determine the location of a satellite breakup or debris cloud. These data are uploaded to the transfer vehicle, which proceeds to rendezvous with the debris at a lower altitude parking orbit. Next, the netting vehicle is deployed, tracks the targeted debris, and captures it. After expending the available nets, the netting vehicle returns to the transfer vehicle for a new netting module and continues to capture more debris in the target area. Once all the netting modules are expended, the transfer vehicle returns to the space station's orbit where it is resupplied with new netting modules from a space shuttle load. The new modules are launched by the shuttle from the ground and the expended modules are taken back to Earth for removal of the captured debris, refueling, and repacking of the nets. Once the netting modules are refurbished, they are taken back into orbit for reuse. In a typical mission, the system has the ability to capture 50 pieces of orbital debris. One mission will take approximately six months and the system is designed to allow for a 30 deg inclination change on the outgoing and incoming trips of the transfer vehicle.

Altimeter and Oceanographic in Situ Measurements in the Area of the Greenland-Iceland-Norwegian Sea, 1987-1988

DTIC Science & Technology

1992-06-01

of CTD data; J. Boyd for collecting AXBT data; Steve Piacsek from SACLANTCEN for GDEM data and help in arrangement of Planet Cruise; P. Minnett from...FCTE ft OCT -992 00 "Orgsnrdl oontot4ns color platgs: All DTIC reproduot- Ions Will be In blaok and white* Pavel Pistek Ocean Sensing and Prediction...temperature-depth and thermistor chain data collected by the West German ship WFS Planet , airborne expendable bathythermograph data deployed by P-3

Studies of two phase flow

NASA Technical Reports Server (NTRS)

Witte, Larry C.

1994-01-01

The development of instrumentation for the support of research in two-phase flow in simulated microgravity conditions was performed. The funds were expended in the development of a technique for characterizing the motion and size distribution of small liquid droplets dispersed in a flowing gas. Phenomena like this occur in both microgravity and normal earth gravity situations inside of conduits that are carrying liquid-vapor mixtures at high flow rates. Some effort to develop a conductance probe for the measurement of liquid film thickness was also expended.

Countermeasure effectiveness against a man-portable air-defense system containing a two-color spinscan infrared seeker

NASA Astrophysics Data System (ADS)

Jackman, James; Richardson, Mark; Butters, Brian; Walmsley, Roy

2011-12-01

Man-portable air-defense (MANPAD) systems have developed sophisticated counter-countermeasures (CCM) to try and defeat any expendable countermeasure that is deployed by an aircraft. One of these is a seeker that is able to detect in two different parts of the electromagnetic spectrum. Termed two-color, the seeker can compare the emissions from the target and a countermeasure in different wavebands and reject the countermeasure. In this paper we describe the modeling process of a two-color infrared seeker using COUNTERSIM, a missile engagement and countermeasure software simulation tool. First, the simulations model a MANPAD with a two-color CCM which is fired against a fast jet model and a transport aircraft model releasing reactive countermeasures. This is then compared to when the aircraft releases countermeasures throughout an engagement up to the hit point to investigate the optimum flare firing time. The results show that the release time of expendable decoys as a countermeasure against a MANPAD with a two-color CCM is critical.

Flight mechanics applications for tethers in space: Cooperative Italian-US programs

NASA Technical Reports Server (NTRS)

Bevilacqua, Franco; Merlina, Pietro; Anderson, John L.

1990-01-01

Since the 1974 proposal by Giuseppe Colombo to fly a tethered subsatellite from the Shuttle Orbiter, the creative thinking of many scientists and engineers from Italy and U.S. has generated a broad range of potential tether applications in space. Many of these applications have promise for enabling innovative research and operational activities relating to flight mechanics in earth orbit and at suborbital altitudes. From a flight mechanics standpoint the most interesting of the currently proposed flight demonstrations are: the second Tethered Satellite System experiment which offers both the potential for aerothermodynamics and hypersonics research and for atmospheric science research; the Tethered Initiated Space Recovery System which would enable orbital deboost and recovery of a re-entry vehicle and waste removal from a space station; and the Tether Elevator/Crawler System which would provide a variable microgravity environment and space station center of mass management. The outer atmospheric and orbital flight mechanics characteristics of these proposed tether flight demonstrations are described. The second Tethered Satellite System mission will deploy the tethered satellite earthward and will bring it as low as 130 km from ground and thus into the transition region between the atmosphere (non-ionized) and the partially ionized ionosphere. The atmospheric flight mechanics of the tethered satellite is discussed and simulation results are presented. The Tether Initiated Space Recovery System experiment will demonstrate the ability of a simple tether system to deboost and recover a reentry vehicle. The main feature of this demonstration is the utilization of a Small Expendable Deployment System (SEDS) and the low-tension deployment assumed to separate the reentry vehicle from the Shuttle. This low-tension deployment maneuver is discussed and its criticalities are outlined. The Tether Elevator/Crawler System is a new space element able to move in a controlled way between the ends of a deployed tethered system. A Shuttle test of an Elevator model is planned to demonstrate the unique capability of this element as a microgravity facility and to test the transfer motion control. The basic dynamical features of the Elevator system are presented and a preliminary assessment of the Elevator-induced tether vibrations is discussed.

MARS PATHFINDER PYRO SYSTEMS SWITCHING ACTIVITY

NASA Technical Reports Server (NTRS)

1996-01-01

The Mars Pathfinder lander is subjected to a electrical and functional tests of its pyrotechic petal deployer system by Jet Propulsion Laboratory (JPL) engineers and technicians in KSC's Spacecraft Assembly and Encapsulation Facility (SAEF-2). In the background is the Pathfinder cruise stage, which the lander will be mated to once its functional tests are complete. The lander will remain attached to this stage during its six-to-seven-month journey to Mars. When the lander touches down on the surface of Mars next year, the pyrotechnic system will deploy its three petals open like a flower and allow the Sojourner autonomous rover to explore the Martian surface. The Mars Pathfinder is scheduled for launch aboard a Delta II expendable launch vehicle on Dec. 2, the beginning of a 24-day launch period. JPL is managing the Mars Pathfinder project for NASA.

The Deflection Plate Analyzer: A Technique for Space Plasma Measurements Under Highly Disturbed Conditions

NASA Technical Reports Server (NTRS)

Wright, Kenneth H., Jr.; Dutton, Ken; Martinez, Nelson; Smith, Dennis; Stone, Nobie H.

2004-01-01

A technique has been developed to measure the characteristics of space plasmas under highly disturbed conditions; e.g., non-Maxwellian plasmas with strong drifting populations and plasmas contaminated by spacecraft outgassing. The present method is an extension of the capabilities of the Differential Ion Flux Probe (DIFP) to include a mass measurement that does not include either high voltage or contamination sensitive devices such as channeltron electron multipliers or microchannel plates. This reduces the complexity and expense of instrument fabrication, testing, and integration of flight hardware as compared to classical mass analyzers. The new instrument design is called the Deflection Plate Analyzer (DPA) and can deconvolve multiple ion streams and analyze each stream for ion flux intensity (density), velocity (including direction of motion), mass, and temperature (or energy distribution). The basic functionality of the DPA is discussed. The performance characteristics of a flight instrument as built for an electrodynamic tether mission, the Propulsive Small Expendable Deployer System (ProSEDS), and the instrument s role in measuring key experimental conditions are also discussed.

MARS PATHFINDER CAMERA TEST IN SAEF-2

NASA Technical Reports Server (NTRS)

1996-01-01

In the Spacecraft Assembly and Encapsulation Facility-2 (SAEF-2), workers from the Jet Propulsion Laboratory (JPL) are conducting a systems test of the imager for the Mars Pathfinder. The imager (white and metallic cylindrical element close to hand of worker at left) is a specially designed camera featuring a stereo- imaging system with color capability provided by a set of selectable filters. It is mounted atop an extendable mast on the Pathfinder lander. Visible to the far left is the small rover which will be deployed from the lander to explore the Martian surface. Transmitting back to Earth images of the trail left by the rover will be one of the mission objectives for the imager. To the left of the worker standing near the imager is the mast for the low-gain antenna; the round high-gain antenna is to the right. Visible in the background is the cruise stage that will carry the Pathfinder on a direct trajectory to Mars. The Mars Pathfinder is one of two Mars-bound spacecraft slated for launch aboard Delta II expendable launch vehicles this year.

Imagining Sisyphus happy: DNA barcoding and the unnamed majority.

PubMed

Blaxter, Mark

2016-09-05

The vast majority of life on the Earth is physically small, and is classifiable as micro- or meiobiota. These organisms are numerically dominant and it is likely that they are also abundantly speciose. By contrast, the vast majority of taxonomic effort has been expended on 'charismatic megabionts': larger organisms where a wealth of morphology has facilitated Linnaean species definition. The hugely successful Linnaean project is unlikely to be extensible to the totality of approximately 10 million species in a reasonable time frame and thus alternative toolkits and methodologies need to be developed. One such toolkit is DNA barcoding, particularly in its metabarcoding or metagenetics mode, where organisms are identified purely by the presence of a diagnostic DNA sequence in samples that are not processed for morphological identification. Building on secure Linnaean foundations, classification of unknown (and unseen) organisms to molecular operational taxonomic units (MOTUs) and deployment of these MOTUs in biodiversity science promises a rewarding resolution to the Sisyphean task of naming all the world's species.This article is part of the themed issue 'From DNA barcodes to biomes'. © 2016 The Authors.

MARS PATHFINDER CAMERA TEST IN SAEF-2

NASA Technical Reports Server (NTRS)

1996-01-01

Jet Propulsion Laboratory (JPL) workers conduct a systems test of the Mars Pathfinder imager, installed atop the Pathfinder lander (with JPL insignia). The imager is the white cyclindrical structure close to the worker's gloved hand. At left is the small rover that will be deployed from the lander to explore the Martian surface. The rover is mounted on one of three petals that will be attached to the lander. The two-pronged mast extending upward from the lander is for the low-gain antenna. The imager is mounted on a mast that will be extended after the lander touches down on Mars, affording a better view of the area. The imager is a camera that will transmit images of the Martian surface as well as the trail left by the rover, helping researchers to better understand the composition of the soil. It also is equipped with selectable filters for gathering data about the atmosphere of the Red Planet. JPL manages the Mars Pathfinder project for NASA. The journey to Mars is scheduled to begin with liftoff Dec. 2 aboard a Delta II expendable launch vehicle.

The Deflection Plate Analyzer: A Technique for Space Plasma Measurements Under Highly Disturbed Conditions

NASA Technical Reports Server (NTRS)

Wright, Kenneth H., Jr.; Dutton, Ken; Martinez, Nelson; Smith, Dennis; Stone, Nobie H.

2003-01-01

A technique has been developed to measure the characteristics of space plasmas under highly disturbed conditions; e.g., non-Maxwellian plasmas with strong drifting populations and plasmas contaminated by spacecraft outgassing. The present method is an extension of the capabilities of the Differential Ion Flux Probe (DIFP) to include a mass measurement that does not include either high voltage or contamination sensitive devices such as channeltron electron multipliers or microchannel plates. This reduces the complexity and expense of instrument fabrication, testing, and integration of flight hardware as compared to classical mass analyzers. The new instrument design is called the Deflection Plate Analyzer (DPA) and can deconvolve multiple ion streams and analyze each stream for ion flux intensity (density), velocity (including direction of motion), mass, and temperature (or energy distribution). The basic functionality of the DPA is discussed. The performance characteristics of a flight instrument as built for an electrodynamic tether mission, the Propulsive Small Expendable Deployer System (ProSEDS), and the instrument s role in measuring key experimental conditions are also discussed.

New Generation Flask Sampling Technology Final Report

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

Smith, James R.

Scientists are turning their focus to the Arctic, site of one of the strongest climate change signals. A new generation of technologies is required to function within that harsh environment, chart evolution of its trace gases and provide new kinds of information for models of the atmosphere. Our response to the solicitation tracks how global atmospheric monitoring was launched more than a half century ago; namely, acquisition of discrete samples of air by flask and subsequent analysis in the laboratory. AOS is proposing to develop a new generation of flask sampling technology. It will enable the new Arctic programs tomore » begin with objective high density sampling of the atmosphere by UAS. The Phase I program will build the prototype flask technology and show that it can acquire and store mol fractions of CH4 and CO2 and value of δ13C with good fidelity. A CAD model will be produced for the entire platform including a package with 100 flasks and the airframe with auto-pilot, electronic propulsion and ground-to-air communications. A mobile flask analysis station will be prototyped in Phase I and designed to final form in Phase II. It expends very small sample per analysis and will interface directly to the flask package integrated permanently into the UAS fuselage. Commercial Applications and Other Benefits: • The New Generation Flask Sampling Technology able to provide a hundred or more samples of air per UAS mission. • A mobile analysis station expending far less sample than the existing ones and small enough to be stationed at the remote sites of Arctic operations. • A new form of validation for continuous trace gas observations from all platforms including the small UAS. • Further demonstration to potential customers of the AOS capabilities to invent, build, deploy and exploit entire platforms for observations of Earth’s atmosphere and ocean. Key Words: Flask Sampler, Mobile Analysis Station, Trace Gas, CO2, CH4, δC13, UAS, Baseline Airborne Observatory, Arctic, Climate Change. Summary for Members of Congress: The air, land and sea of the Arctic combine to produce a large climate change signal. AOS is proposing to develop unmanned airborne technologies able to begin prompt, objective observations of the signal’s atmospheric component.« less

Final design of a space debris removal system

NASA Technical Reports Server (NTRS)

Carlson, Erika; Casali, Steve; Chambers, Don; Geissler, Garner; Lalich, Andrew; Leipold, Manfred; Mach, Richard; Parry, John; Weems, Foley

1990-01-01

The objective is the removal of medium sized orbital debris in low Earth orbits. The design incorporates a transfer vehicle and a netting vehicle to capture the medium size debris. The system is based near an operational space station located at 28.5 degrees inclination and 400 km altitude. The system uses ground based tracking to determine the location of a satellite breakup or debris cloud. This data is unloaded to the transfer vehicle, and the transfer vehicle proceeds to rendezvous with the debris at a lower altitude parking orbit. Next, the netting vehicle is deployed, tracks the targeted debris, and captures it. After expending the available nets, the netting vehicle returns to the transfer vehicle for a new netting module and continues to capture more debris in the target area. Once all the netting modules are expended, the transfer vehicle returns to the space station's orbit, where it is resupplied with new netting modules from a space shuttle load. The new modules are launched by the shuttle from the ground, and the expended modules are taken back to Earth for removal of the captured debris, refueling, and repacking of the nets. Once the netting modules are refurbished, they are taken back into orbit for reuse. In a typical mission, the system has the ability to capture 50 pieces of orbital debris. One mission will take about six months. The system is designed to allow for a 30 degree inclination change on the outgoing and incoming trips of the transfer vehicle.

Final design of a space debris removal system

NASA Astrophysics Data System (ADS)

Carlson, Erika; Casali, Steve; Chambers, Don; Geissler, Garner; Lalich, Andrew; Leipold, Manfred; Mach, Richard; Parry, John; Weems, Foley

1990-12-01

The objective is the removal of medium sized orbital debris in low Earth orbits. The design incorporates a transfer vehicle and a netting vehicle to capture the medium size debris. The system is based near an operational space station located at 28.5 degrees inclination and 400 km altitude. The system uses ground based tracking to determine the location of a satellite breakup or debris cloud. This data is unloaded to the transfer vehicle, and the transfer vehicle proceeds to rendezvous with the debris at a lower altitude parking orbit. Next, the netting vehicle is deployed, tracks the targeted debris, and captures it. After expending the available nets, the netting vehicle returns to the transfer vehicle for a new netting module and continues to capture more debris in the target area. Once all the netting modules are expended, the transfer vehicle returns to the space station's orbit, where it is resupplied with new netting modules from a space shuttle load. The new modules are launched by the shuttle from the ground, and the expended modules are taken back to Earth for removal of the captured debris, refueling, and repacking of the nets. Once the netting modules are refurbished, they are taken back into orbit for reuse. In a typical mission, the system has the ability to capture 50 pieces of orbital debris. One mission will take about six months. The system is designed to allow for a 30 degree inclination change on the outgoing and incoming trips of the transfer vehicle.

Operations analysis (study 2.1): Payload designs for space servicing

NASA Technical Reports Server (NTRS)

Wolfe, R. R.

1974-01-01

Potential modes of operating in space in the space shuttle era are documented. The October 1973 NASA Mission Model provides a definition of various NASA and non-DOD automated payload configurations when employed in an expendable mode. The model also specifies a launch schedule for initial deployment of payloads as well as for subsequent replacements at periodic cycles. This model and its associated payload definitions serve as a foundation for the data presented in this report. The reference model has been revised to reflect automated space servicing of payloads as an operational concept instead of the existing expendable approach. The indication is that the bulk of a payload's subsystems and mission equipment require no support over the lifetime of the program. However, failure of a single unit could result in loss of the mission objectives. When space servicing is employed, the approach is to replace only that unit causing the anomaly. This concept affords an opportunity to standardize space replacable units, as well as to reduce the expense of logistics support, by allowing multiple servicing on any single upper stage/shuttle flight.

EELV Secondary Payload Adapter (ESPA)

NASA Astrophysics Data System (ADS)

Haskett, Scott A.; Weis, Steven C.; Doggrell, Leslie J.; Sciulli, Dino; Meink, Troy E.; Ganley, Jeff T.; Maly, Joseph R.; Jurisson, Karl

2000-11-01

Despite growing international interest in small satellites, high dedicated expendable launch vehicle costs and the lack of secondary launch opportunities continue to hinder the full exploitation of small satellite technology. In the United States, the Department of Defense (DoD), NASA, other government agencies, commercial companies, and many universities use small satellites to perform space experiments, demonstrate new technology, and test operational prototype hardware. In addition, the DoD continues to study the role of small satellites in fulfilling operational mission requirements. However, the US lacks sufficient small satellite launch capacity. Furthermore, US government agencies are restricted to the use of US launch vehicles, which eliminates many affordable launch opportunities. In an effort to increase the number of space experiments that can be flown with a small, fixed budget, the DoD Space Test Program (STP) has teamed with the Air Force Research Laboratory Space Vehicles Directorate (AFRL/VS) to develop a low-cost solution for the small satellite launch program. Our solution, which can be implemented on both Boeing and Lockheed-Martin Evolved Expendable Launch Vehicle-Medium (EELV-M) boosters, is called the EELV Secondary Payload Adaptor (ESPA). ESPA will increase the number of launch opportunities for 180kg-class (or smaller) satellites at prices highly competitive with other secondary launch services worldwide.

Novel Tools in Determining the Physiological Demands and Nutritional Practices of Ontario FireRangers during Fire Deployments

PubMed Central

Robertson, A. H.; Larivière, C.; Leduc, C. R.; McGillis, Z.; Eger, T.; Godwin, A.; Larivière, M.; Dorman, S. C.

2017-01-01

Introduction The seasonal profession of wildland fire fighting in Canada requires individuals to work in harsh environmental conditions that are physically demanding. The purpose of this study was to use novel technologies to evaluate the physiological demands and nutritional practices of Canadian FireRangers during fire deployments. Methods Participants (n = 21) from a northern Ontario Fire Base volunteered for this study and data collection occurred during the 2014 fire season and included Initial Attack (IA), Project Fire (P), and Fire Base (B) deployments. Deployment-specific energy demands and physiological responses were measured using heart-rate variability (HRV) monitoring devices (Zephyr BioHarness3 units). Food consumption behaviour and nutrient quantity and quality were captured using audio-video food logs on iPod Touches and analyzed by NutriBase Pro 11 software. Results Insufficient kilocalories were consumed relative to expenditure for all deployment types. Average daily kilocalories consumed: IA: 3758 (80% consumption rate); P: 2945±888.8; B: 2433±570.8. Average daily kilocalorie expenditure: IA: 4538±106.3; P: 4012±1164.8; B: 2842±649.9. The Average Macronutrient Distribution Range (AMDR) for protein was acceptable: 22–25% (across deployment types). Whereas the AMDR for fat and carbohydrates were high: 40–50%; and low: 27–37% respectively, across deployment types. Conclusions This study is the first to use the described methodology to simultaneously evaluate energy expenditures and nutritional practices in an occupational setting. The results support the use of HRV monitoring and video-food capture, in occupational field settings, to assess job demands. FireRangers expended the most energy during IA, and the least during B deployments. These results indicate the need to develop strategies centered on maintaining physical fitness and improving food practices. PMID:28107380

Novel Tools in Determining the Physiological Demands and Nutritional Practices of Ontario FireRangers during Fire Deployments.

PubMed

Robertson, A H; Larivière, C; Leduc, C R; McGillis, Z; Eger, T; Godwin, A; Larivière, M; Dorman, S C

2017-01-01

The seasonal profession of wildland fire fighting in Canada requires individuals to work in harsh environmental conditions that are physically demanding. The purpose of this study was to use novel technologies to evaluate the physiological demands and nutritional practices of Canadian FireRangers during fire deployments. Participants (n = 21) from a northern Ontario Fire Base volunteered for this study and data collection occurred during the 2014 fire season and included Initial Attack (IA), Project Fire (P), and Fire Base (B) deployments. Deployment-specific energy demands and physiological responses were measured using heart-rate variability (HRV) monitoring devices (Zephyr BioHarness3 units). Food consumption behaviour and nutrient quantity and quality were captured using audio-video food logs on iPod Touches and analyzed by NutriBase Pro 11 software. Insufficient kilocalories were consumed relative to expenditure for all deployment types. Average daily kilocalories consumed: IA: 3758 (80% consumption rate); P: 2945±888.8; B: 2433±570.8. Average daily kilocalorie expenditure: IA: 4538±106.3; P: 4012±1164.8; B: 2842±649.9. The Average Macronutrient Distribution Range (AMDR) for protein was acceptable: 22-25% (across deployment types). Whereas the AMDR for fat and carbohydrates were high: 40-50%; and low: 27-37% respectively, across deployment types. This study is the first to use the described methodology to simultaneously evaluate energy expenditures and nutritional practices in an occupational setting. The results support the use of HRV monitoring and video-food capture, in occupational field settings, to assess job demands. FireRangers expended the most energy during IA, and the least during B deployments. These results indicate the need to develop strategies centered on maintaining physical fitness and improving food practices.

Advanced Deployable Structural Systems for Small Satellites

NASA Technical Reports Server (NTRS)

Belvin, W. Keith; Straubel, Marco; Wilkie, W. Keats; Zander, Martin E.; Fernandez, Juan M.; Hillebrandt, Martin F.

2016-01-01

One of the key challenges for small satellites is packaging and reliable deployment of structural booms and arrays used for power, communication, and scientific instruments. The lack of reliable and efficient boom and membrane deployment concepts for small satellites is addressed in this work through a collaborative project between NASA and DLR. The paper provides a state of the art overview on existing spacecraft deployable appendages, the special requirements for small satellites, and initial concepts for deployable booms and arrays needed for various small satellite applications. The goal is to enhance deployable boom predictability and ground testability, develop designs that are tolerant of manufacturing imperfections, and incorporate simple and reliable deployment systems.

Exobiology in Earth orbit: The results of science workshops held at NASA, Ames Research Center

NASA Technical Reports Server (NTRS)

Defrees, D. (Editor); Brownlee, D. (Editor); Tarter, J. (Editor); Usher, D. (Editor); Irvine, W. (Editor); Klein, H. (Editor)

1989-01-01

The Workshops on Exobiology in Earth Orbit were held to explore concepts for orbital experiments of exobiological interest and make recommendations on which classes of experiments should be carried out. Various observational and experimental opportunities in Earth orbit are described including those associated with the Space Shuttle laboratories, spacecraft deployed from the Space Shuttle and expendable launch vehicles, the Space Station, and lunar bases. Specific science issues and technology needs are summarized. Finally, a list of recommended experiments in the areas of observational exobiology, cosmic dust collection, and in situ experiments is presented.

Can nurse practitioners and physicians beat parochialism into plowshares?

PubMed

Phillips, Robert L; Harper, Doreen C; Wakefield, Mary; Green, Larry A; Fryer, George E

2002-01-01

Nurse practitioners have evolved into a large and flexible workforce. Far too often, nurse practitioner and physician professional organizations do not work together but rather expend considerable effort jousting in policy arenas. Turf battles interfere with joint advocacy for needed health system change and delay development of interdisciplinary teams that could help patients. A combined, consistent effort is urgently needed for studying, training, and deploying a collaborative, integrated workforce aimed at improving the health care system of tomorrow. The country can ill afford doctors and nurses who ignore one another's capabilities and fail to maximize each other's contributions cost-effectively.

Electrical Power Systems for NASA's Space Transportation Program

NASA Technical Reports Server (NTRS)

Lollar, Louis F.; Maus, Louis C.

1998-01-01

Marshall Space Flight Center (MSFC) is the National Aeronautics and Space Administration's (NASA) lead center for space transportation systems development. These systems include earth to orbit launch vehicles, as well as vehicles for orbital transfer and deep space missions. The tasks for these systems include research, technology maturation, design, development, and integration of space transportation and propulsion systems. One of the key elements in any transportation system is the electrical power system (EPS). Every transportation system has to have some form of electrical power and the EPS for each of these systems tends to be as varied and unique as the missions they are supporting. The Preliminary Design Office (PD) at MSFC is tasked to perform feasibility analyses and preliminary design studies for new projects, particularly in the space transportation systems area. All major subsystems, including electrical power, are included in each of these studies. Three example systems being evaluated in PD at this time are the Liquid Fly Back Booster (LFBB) system, the Human Mission to Mars (HMM) study, and a tether based flight experiment called the Propulsive Small Expendable Deployer System (ProSEDS). These three systems are in various stages of definition in the study phase.

Small Portable Analyzer Diagnostic Equipment (SPADE) Program -- Diagnostic Software Validation

DTIC Science & Technology

1984-07-01

Electronic Equipment Electromagnetic Emission and Susceptibility Requirements for the Control of Electromagnetic Interference Electromagnetic...ONLY. ORIENTATION OF DEFECT LOOKING HHO QIlILL: t -ed’-o· Significant efforts were expended to simulate spalling failures associated with naturally

Seismic reading taken at MSC recording impact of Apollo 13 S-IVB with surface

NASA Technical Reports Server (NTRS)

1970-01-01

A seismic reading taken from instruments at the Manned Spacecraft Center (MSC) recording impact of the Apollo 13 S-IVB/Instrument Unit with lunar surface. The expended Saturn third stage and instrument unit impacted the lunar surface at 7:09 p.m., April 14, 1970. The location of the impact was 2.4 degrees south latitude and 27.9 degrees west longitude, about 76 nautical miles west-northwest of the Apollo 12 Lunar Surface Experiment package deployment site. The S-IVB/IU impact was picked up by the Passive Seismic Experiment, a component of the package and transmitted to instruments at the Mission Control Center.

Special investigation report: Commercial space launch incident, launch procedure anomaly orbital sciences corporation PEGASUS/SCD-1, 80 nautical miles east of Cape Canaveral, Florida, February 9, 1993

NASA Astrophysics Data System (ADS)

This report explains the procedural anomaly that occurred during the launch sequence of an Orbital Sciences Corporation Pegasus expendable launch vehicle, which was subsequently deployed successfully from an NB-52B airplane, on 9 Feb. 1993. The safety issues discussed in the report include command, control and communications responsibility, launch crew fatigue, launch interphone procedures, efficiency of launch constraints, and the lack of common launch documents. Safety recommendations concerning these issues were made to the Department of Transportation, the National Aeronautics and Space Administration, and the Orbital Sciences Corporation.

Special Investigation Report: Commercial Space Launch Incident, Launch Procedure Anomaly Orbital Sciences Corporation PEGASUS/SCD-1, 80 Nautical Miles East of Cape Canaveral, Florida, February 9, 1993

NASA Technical Reports Server (NTRS)

1993-01-01

This report explains the procedural anomaly that occurred during the launch sequence of an Orbital Sciences Corporation Pegasus expendable launch vehicle, which was subsequently deployed successfully from an NB-52B airplane, on 9 Feb. 1993. The safety issues discussed in the report include command, control and communications responsibility, launch crew fatigue, launch interphone procedures, efficiency of launch constraints, and the lack of common launch documents. Safety recommendations concerning these issues were made to the Department of Transportation, the National Aeronautics and Space Administration, and the Orbital Sciences Corporation.

Restartable solid motor stage for shuttle applications

NASA Technical Reports Server (NTRS)

Rohrbaugh, D. J.

1973-01-01

The application of restartable solid motor stages to shuttle missions has been shown to provide a viable supplement to the shuttle program. Restartable solid motors in the 3000 pound class provide a small expendable transfer stage that reduces the demand on the shuttle for the lower energy missions. Shuttle operational requirements and preliminary performance data provided an input for defining design features required for restartable solid motor applications. These data provided a basis for a configuration definition that is compatible with shuttle operations. Mission by mission analysis showed the impact on a NASA supplied mission model. The results showed a 15% reduction in the number of shuttle flights required. In addition the amount of shuttle capability used to complete the mission objectives was significantly reduced. For example, in the 1979 missions there was a 62% reduction in shuttle capability used. The study also showed that the solid motor could provide a supplement to the TUG that would allow TUGS to be used in a recoverable rather than an expendable mode. The study shows a 71% reduction in the number of TUGs that would be expended.

Solidifying Small Satellite Access to Orbit via the International Space Station (ISS): Cyclops' Deployment of the Lonestar SmallSat from the ISS

NASA Technical Reports Server (NTRS)

Hershey, Matthew P.; Newswander, Daniel R.; Evernden, Brent A.

2016-01-01

On January 29, 2016, the Space Station Integrated Kinetic Launcher for Orbital Payload Systems (SSIKLOPS), known as "Cyclops" to the International Space Station (ISS) community, deployed Lonestar from the ISS. The deployment of Lonestar, a collaboration between Texas A&M University and the University of Texas at Austin, continued to showcase the simplicity and reliability of the Cyclops deployment system. Cyclops, a NASA-developed, dedicated 10-100 kg class ISS SmallSat deployment system, utilizes the Japanese airlock and robotic systems to seamlessly insert SmallSats into orbit. This paper will illustrate Cyclops' successful deployment of Lonestar from the ISS as well as outline its concept of operations, interfaces, requirements, and processes.

Professional Learning for Distributed Leadership: Primary Headteachers' Perspectives

ERIC Educational Resources Information Center

Torrance, Deirdre

2015-01-01

This article draws from a small-scale study of headteachers motivated to positively impact on the quality of pupil experience by involving all staff in a distributed perspective on leadership. Each headteacher perceived leadership as involving learned processes requiring support and experience, expending considerable effort in providing a fertile…

13 CFR 119.18 - What are the restrictions against lobbying?

Code of Federal Regulations, 2010 CFR

2010-01-01

... lobbying? 119.18 Section 119.18 Business Credit and Assistance SMALL BUSINESS ADMINISTRATION PROGRAM FOR...? No assistance made available under the PRIME program may be expended by a grantee or subgrantee to... employee of a Federal, State, or local government in connection with its participation in the program. ...

Recruiting Trends, 2008-2009

ERIC Educational Resources Information Center

Collegiate Employment Research Institute (NJ3), 2009

2009-01-01

This paper presents the recruiting trends for 2008-2009. This year's report is based on 945 respondents, including 57 K-12 schools. The researchers continued their focus on fast-growth small companies and expended most of their energy in retaining their sample distribution, knowing that the prevailing economic situation would reduce responses.…

Physical oceanographic data from the OTEC Punta Tuna, Puerto Rico Site, September 1979-June 1980

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

Frye, D.; Davison, A.; Leavitt, K.

1981-01-01

The first results of an oceanographic measurement program being conducted off the southeast corner of Puerto Rico are presented. The study site is a proposed OTEC site and is located about 20 km off Punta Tuna. The objectives of the measurement program are to document the physical oceanography of the site as related to the engineering and environmental factors involved in OTEC design and operation. Oceanographic measurements include: (1) a subsurface mooring instrumented with five current, temperature, and pressure recorders; and (2) quarterly hydrographic cruises to measure salinity, temperature, and depth profiles on a grid of 33 stations in themore » vicinity of the mooring site. The first cruise, conducted between 16 and 21 June 1980, included the initial mooring deployment and a CTD (conductivity, temperature, and depth) and XBT (expendable bathythermograph) survey. The CTD/XBT measurements are presented. Also included are results of in situ current, temperature, and pressure measurements made during two previous programs. In September 1979, Coastal Marine Research (CMR) deployed a mooring at approximately the same site as the present mooring. Results from three of these instruments are included. The Naval Underwater Systems Center deployed a mooring at this site in February 1979 and partial results from one instrument on this mooring are also presented. (WHK)« less

SEDS1 mission software verification using a signal simulator

NASA Technical Reports Server (NTRS)

Pierson, William E.

1992-01-01

The first flight of the Small Expendable Deployer System (SEDS1) is schedule to fly as the secondary payload of a Delta 2 in March, 1993. The objective of the SEDS1 mission is to collect data to validate the concept of tethered satellite systems and to verify computer simulations used to predict their behavior. SEDS1 will deploy a 50 lb. instrumented satellite as an end mass using a 20 km tether. Langley Research Center is providing the end mass instrumentation, while the Marshall Space Flight Center is designing and building the deployer. The objective of the experiment is to test the SEDS design concept by demonstrating that the system will satisfactorily deploy the full 20 km tether without stopping prematurely, come to a smooth stop on the application of a brake, and cut the tether at the proper time after it swings to the local vertical. Also, SEDS1 will collect data which will be used to test the accuracy of tether dynamics models used to stimulate this type of deployment. The experiment will last about 1.5 hours and complete approximately 1.5 orbits. Radar tracking of the Delta II and end mass is planned. In addition, the SEDS1 on-board computer will continuously record, store, and transmit mission data over the Delta II S-band telemetry system. The Data System will count tether windings as the tether unwinds, log the times of each turn and other mission events, monitor tether tension, and record the temperature of system components. A summary of the measurements taken during the SEDS1 are shown. The Data System will also control the tether brake and cutter mechanisms. Preliminary versions of two major sections of the flight software, the data telemetry modules and the data collection modules, were developed and tested under the 1990 NASA/ASEE Summer Faculty Fellowship Program. To facilitate the debugging of these software modules, a prototype SEDS Data System was programmed to simulate turn count signals. During the 1991 summer program, the concept of simulating signals produced by the SEDS electronics systems and circuits was expanded and more precisely defined. During the 1992 summer program, the SEDS signal simulator was programmed to test the requirements of the SEDS Mission software, and this simulator will be used in the formal verification of the SEDS Mission Software. The formal test procedures specification was written which incorporates the use of the signal simulator to test the SEDS Mission Software and which incorporates procedures for testing the other major component of the SEDS software, the Monitor Software.

Artist's Concept of X-37 Re-entry

NASA Technical Reports Server (NTRS)

1999-01-01

Pictured is an artist's concept of the experimental X-37 Reusable Launch Vehicle re-entering Earth`s atmosphere. NASA and the Boeing Company entered a cooperative agreement to develop and fly a new experimental space plane called the X-37 that would be ferried into orbit to test new technologies. The reusable space plane incorporated technologies aimed at significantly cutting the cost of space flight. The X-37 would be carried into orbit by the Space Shuttle or be launched by an expendable rocket. After the X-37 was deployed, it would remain in orbit up to 21 days, performing a variety of experiments before re-entering the Earth's atmosphere and landing. The X-37 program was discontinued in 2003.

Advanced Concept

NASA Image and Video Library

1999-08-13

Pictured is an artist's concept of the experimental X-37 Reusable Launch Vehicle re-entering Earth‘s atmosphere. NASA and the Boeing Company entered a cooperative agreement to develop and fly a new experimental space plane called the X-37 that would be ferried into orbit to test new technologies. The reusable space plane incorporated technologies aimed at significantly cutting the cost of space flight. The X-37 would be carried into orbit by the Space Shuttle or be launched by an expendable rocket. After the X-37 was deployed, it would remain in orbit up to 21 days, performing a variety of experiments before re-entering the Earth's atmosphere and landing. The X-37 program was discontinued in 2003.

Space shuttle program. Expendable second stage reusable space shuttle booster. Volume 2: Technical summary. Book 2: Expendable second stage vehicle definition

NASA Technical Reports Server (NTRS)

1971-01-01

A definition of the expendable second stage for use with the reusable space shuttle booster is presented. The subjects discussed are: (1) expendable second stage design, (2) structural subsystem, (3) propulsion subsystem, (4) avionics subsystems, (5) recovery and deorbit subsystem, and (6) expendable second stage vehicle installation, assembly, and checkout.

The K-1 Active Dispenser for Orbit Transfer

NASA Astrophysics Data System (ADS)

Lai, G.; Cochran, D.; Curtis, R.

2002-01-01

Kistler Aerospace Corporation is building the K-1, the world's first fully reusable launch vehicle. The two-stage K- 1 is designed primarily to service the market for low-earth orbit (LEO) missions, due to Kistler's need to recover both stages. For customers requiring payload delivery to high-energy orbits, Kistler can outfit the payload with a K- 1 Active Dispenser (an expendable third stage). The K-1 second stage will deploy the Active Dispenser mated with its payload into a 200 km circular LEO parking orbit. From this orbit, the Active Dispenser would use its own propulsion to place its payload into the final desired drop-off orbit or earth-escape trajectory. This approach allows Kistler to combine the low-cost launch services offered by the reusable two-stage K-1 with the versatility of a restartable, expendable upper stage. Enhanced with an Active Dispenser, the K-1 will be capable of delivering 1,500 kg to a geosynchronous transfer orbit or up to approximately 1,000 kg into a Mars rendezvous trajectory. The list price of a K-1 Active Dispenser launch is 25 million (plus the price of mission unique integration services) significantly less than the price of any launch vehicle service in the world with comparable capability.

Comparative evaluation of existing expendable upper stages for space shuttle

NASA Technical Reports Server (NTRS)

Weyers, V. J.; Sagerman, G. D.; Borsody, J.; Lubick, R. J.

1974-01-01

The use of existing expendable upper stages in the space shuttle during its early years of operation is evaluated. The Burner 2, Scout, Delta, Agena, Transtage, and Centaur were each studied under contract by their respective manufacturers to determine the extent and cost of the minimum modifications necessary to integrate the stage with the shuttle orbiter. A comparative economic analysis of thirty-five different families of these stages is discussed. Results show that the overall transportation system cost differences between many of the families are quite small. However, by considering several factors in addition to cost, it is possible to select one family as being representative of the capability of the minimum modification existing stage approach. The selected family meets all of the specified mission requirements during the early years of shuttle operation.

Miniature Free-Flying Magnetometer Utilizing System-On-A-Chip Technology

NASA Technical Reports Server (NTRS)

Eyre, F. B.; Blaes, B. R.

2001-01-01

Four Free-Flying Magnetometers (FFMs), developed at the Jet Propulsion Laboratory (JPL) for the Enstrophy mission, were successfully deployed from the payload of a sounding rocket launched from Poker Flats, Alaska on February 11, 1999. The FFMs functioned successfully by synchronously measuring the vector magnetic field at 4 points separate from the payload and at relative distances up to 3 km, and communicated their data, in bursts, to the ground. This is the first time synchronized in-situ multipoint measurements of the Earth's magnetic field utilizing miniature spin-stabilized "sensorcraft" have been performed. The data they provided have enabled, for the first time, the direct measure of field-aligned current density and are enabling new science by determining the fine-scale structure of the currents in the Earth's ionosphere involved in the production of aurora. These proof-of-concept "hockey puck" (80 mm diameter, 38 mm height, 250 gram mass) FFMs were built using off-the-shelf commercial, industrial, and military grade surface-mount electronic components. Radiation-hard electronics was not required for the Enstrophy mission's short sub-orbital flight. The successful design, implementation, and flight demonstration of this 1st generation FFM design has provided a solid base for further development of a 2nd generation FFM design for planetary science applications. A reliable ultra-miniature radiation-hard 2nd-generation FFM utilizing System-On-A-Chip (SOAC) technologies is proposed. This design would be targeted for long-term planetary missions to investigate magnetospheric field configurations in regions having small-scale structure and to separate spatial and temporal variations. A fleet of short-lived (expendable) FFMs would be deployed into a targeted region to gather multiprobe vector magnetic field data. The FFMs would be ejected from a parent spacecraft at a speed of a few m/sec and would cover spatial volumes of order tens of kilometers for times of order one hour. The parent spacecraft would carry a sufficient number of FFMs for multiple deployments. Additional information is contained in the original extended abstract.

48 CFR 1819.7209 - Credit agreements.

Code of Federal Regulations, 2010 CFR

2010-10-01

... ADMINISTRATION SOCIOECONOMIC PROGRAMS SMALL BUSINESS PROGRAMS NASA Mentor-Protégé Program 1819.7209 Credit agreements. (a) The credit permits the mentor to include the cost it expends on a mentor-protégé agreement as... Plan. The following provisions apply to all credit mentor-protégé agreements: (1) Developmental...

14 CFR 420.19 - Launch site location review-general.

Code of Federal Regulations, 2010 CFR

2010-01-01

... site, at least one type of expendable or reusable launch vehicle can be flown from the launch point... × 10−6). (2) Types of launch vehicles include orbital expendable launch vehicles, guided sub-orbital expendable launch vehicles, unguided sub-orbital expendable launch vehicles, and reusable launch vehicles...

24 CFR 84.35 - Supplies and other expendable property.

Code of Federal Regulations, 2010 CFR

2010-04-01

... 24 Housing and Urban Development 1 2010-04-01 2010-04-01 false Supplies and other expendable... Standards § 84.35 Supplies and other expendable property. (a) Title to supplies and other expendable property shall vest in the recipient upon acquisition. If there is a residual inventory of unused supplies...

Defense Science Board 1996 Summer Study Task Force On Tactics and Technology for 21st Century Military Superiority. Volume 2, Part 1. Supporting Materials

DTIC Science & Technology

1996-10-01

systems currently headed for deployment ( BIDS is highlighted in the chart) to widely dispersed microsensors on micro, autonomous platforms. Small room... Small , Rapidly Deployable Forces" Joe Polito, Dan Rondeau, Sandia National Laboratory V.2. "Robotic Concepts for Small Rapidly Deployable Forces" V-7...Robert Palmquist, Jill Fahrenholtz, Richard Wheeler, Sandia National Laboratory V.3. "Potential for Distributed Ground Sensors in Support of Small Unit V

Preliminary design method for deployable spacecraft beams

NASA Technical Reports Server (NTRS)

Mikulas, Martin M., Jr.; Cassapakis, Costas

1995-01-01

There is currently considerable interest in low-cost, lightweight, compactly packageable deployable elements for various future missions involving small spacecraft. These elements must also have a simple and reliable deployment scheme and possess zero or very small free-play. Although most small spacecraft do not experience large disturbances, very low stiffness appendages or free-play can couple with even small disturbances and lead to unacceptably large attitude errors which may involve the introduction of a flexible-body control system. A class of structures referred to as 'rigidized structures' offers significant promise in providing deployable elements that will meet these needs for small spacecraft. The purpose of this paper is to introduce several rigidizable concepts and to develop a design methodology which permits a rational comparison of these elements to be made with alternate concepts.

DCBRP: a deterministic chain-based routing protocol for wireless sensor networks.

PubMed

Marhoon, Haydar Abdulameer; Mahmuddin, M; Nor, Shahrudin Awang

2016-01-01

Wireless sensor networks (WSNs) are a promising area for both researchers and industry because of their various applications The sensor node expends the majority of its energy on communication with other nodes. Therefore, the routing protocol plays an important role in delivering network data while minimizing energy consumption as much as possible. The chain-based routing approach is superior to other approaches. However, chain-based routing protocols still expend substantial energy in the Chain Head (CH) node. In addition, these protocols also have the bottleneck issues. A novel routing protocol which is Deterministic Chain-Based Routing Protocol (DCBRP). DCBRP consists of three mechanisms: Backbone Construction Mechanism, Chain Head Selection (CHS), and the Next Hop Connection Mechanism. The CHS mechanism is presented in detail, and it is evaluated through comparison with the CCM and TSCP using an ns-3 simulator. It show that DCBRP outperforms both CCM and TSCP in terms of end-to-end delay by 19.3 and 65%, respectively, CH energy consumption by 18.3 and 23.0%, respectively, overall energy consumption by 23.7 and 31.4%, respectively, network lifetime by 22 and 38%, respectively, and the energy*delay metric by 44.85 and 77.54%, respectively. DCBRP can be used in any deterministic node deployment applications, such as smart cities or smart agriculture, to reduce energy depletion and prolong the lifetimes of WSNs.

JEMRMS Small Satellite Deployment Observation

NASA Image and Video Library

2012-10-04

ISS033-E-009334 (4 Oct. 2012) --- Several tiny satellites are featured in this image photographed by an Expedition 33 crew member on the International Space Station. The satellites were released outside the Kibo laboratory using a Small Satellite Orbital Deployer attached to the Japanese module’s robotic arm on Oct. 4, 2012. Japan Aerospace Exploration Agency astronaut Aki Hoshide, flight engineer, set up the satellite deployment gear inside the lab and placed it in the Kibo airlock. The Japanese robotic arm then grappled the deployment system and its satellites from the airlock for deployment.

JEMRMS Small Satellite Deployment Observation

NASA Image and Video Library

2012-10-04

ISS033-E-009458 (4 Oct. 2012) --- Several tiny satellites are featured in this image photographed by an Expedition 33 crew member on the International Space Station. The satellites were released outside the Kibo laboratory using a Small Satellite Orbital Deployer attached to the Japanese module’s robotic arm on Oct. 4, 2012. Japan Aerospace Exploration Agency astronaut Aki Hoshide, flight engineer, set up the satellite deployment gear inside the lab and placed it in the Kibo airlock. The Japanese robotic arm then grappled the deployment system and its satellites from the airlock for deployment.

Small Hydropower Development in Rwanda: Trends, Opportunities and Challenges

NASA Astrophysics Data System (ADS)

Geoffrey, Gasore; Zimmerle, Daniel; Ntagwirumugara, Etienne

2018-04-01

The Rift Valley region of Sub-Saharan Africa represents a promising area for the development of small (<5MW) hydropower resources. This study compiles data from government and UN agency reports to analyze different development outlooks. The study found that there has been a rapid deployment of small hydropower in the last 10 years. From the current total deployed small hydro of 47.5 MW, 16.5MW (35%) were deployed from 1957 to 1984 while the remaining 31 MW (65%) were deployed from 2007 to 2017. While all systems constructed prior to 1985 are grid-connected, one third of the 24 facilities constructed after 2007 are connected to off-grid systems. The study provides an overview of the economic incentives for developing small hydropower systems in Rwanda and the potential contribution of that development to Rwanda’s electrification goals.

Small satellite generic bus structure

NASA Astrophysics Data System (ADS)

Fiore, John N.; Summers, George D.

1993-02-01

A 'Smallsat' generic structure has been developed for LEO and expendable launch vehicles. The structure makes extensive use of Al-alloy honeycomb-stabilized panels in order to satisfy stiffness, weight, strength and thermal stability requirements in the LEO environment, in conjunction with discrete applications of multilayered insulation blankets and silverized Teflon radiators. The Smallsat structure is ideally suited for assembly-line manufacturing and storage until required.

Infantry Small-Unit Mountain Operations

DTIC Science & Technology

2011-02-01

expended to traverse it.  Unique sustainment solutions. Sustainment in a mountain environment is a challenging and time-consuming process . Terrain...a particular environment during the intelligence preparation of the battlefield (IPB) process and provide the analysis to the company. The IPB...consists of a four-step process that includes—  Defining the operational environment.  Describing environmental effects on operations.  Evaluating the

A modular design for rapid-response telecoms and navigation missions

NASA Astrophysics Data System (ADS)

Davies, P.; Liddle, D.; Buckley, John; Sweeting, M.; Roussel-Dupre, Diane; Caffrey, Michael

2004-11-01

Surrey Satellite Technology Ltd and Los Alamos National Laboratory are together building the Cibola Flight Experiment (CFESat), a mission with the aim of flight-proving a reconfigurable processor payload intended for a Low Earth Orbit system. The mission will survey portions of the VHF and UHF radio spectra. The satellite will be launched by the Space Test Program in September 2006 on the USAF Evolved Expendable Launch Vehicle (EELV) using the EELV's Secondary Payload Adapter (ESPA) that allows up to six small satellites to be launched as "piggyback" passengers with larger spacecraft. The payload is based on networks of reprogrammable, Field Programmable Gate Arrays (FPGAs) to process the received signals for ionospheric and lightning studies. The objective is to validate the on-orbit use of commercial, reconfigurable FPGA technology utilizing several different single-event upset mitigation schemes. It will also detect and measure impulsive events that occur in a complex background. SSTL's satellite platform is based on a new, ESPA- compatible, structure housing subsystems and equipments with proven flight heritage from SSTL's disaster monitoring constellation (DMC) and the Topsat mission satellite due for launch in 2005. The structure is mechanically quite complex for a microsatellite having both deployed solar panels and a pair of long booms as part of the payload. The satellite design is highly constrained by the mass and volume requirements of the EELV/EPSA.

Deployable Mini-Payload Missions Enabled by Small Radioisotope Power Systems (RPSs)

NASA Technical Reports Server (NTRS)

Abelson, Robert D.; Satter, Celeste M.

2005-01-01

Deployable mini-payloads are envisioned as small, simple, standalone instruments that could be deployed from a mother vehicle such as a rover or the proposed Jupiter Icy Moons Orbiter to key points of interest within the solar system. Used in conjunction with a small radioisotope power system (RPS), these payloads could potentially be used for long-duration science missions or as positional beacons for rovers or other spacecraft. The RPS power source would be suitable for deployable mini-payload missions that would take place anywhere there is limited, intermittent, or no solar insolation. This paper introduces two such concepts: (1) a seismic monitoring station deployed by a rover or aerobot, and (2) a passive fields and particles station delivered by a mother spacecraft to Jupiter.

KSC-97PC903

NASA Image and Video Library

1997-05-17

Environmental Health Specialist Jamie A. Keeley, of EG&G Florida Inc., uses an ion chamber dose rate meter to measure radiation levels in one of three radioisotope thermoelectric generators (RTGs) that will provide electrical power to the Cassini spacecraft on its mission to explore the Saturnian system. The three RTGs and one spare are being tested and mointored in the Radioisotope Thermoelectric Generator Storage Building in the KSC's Industrial Area. The RTGs use heat from the natural decay of plutonium to generate electric power. RTGs enable spacecraft to operate far from the Sun where solar power systems are not feasible. The RTGs on Cassini are of the same design as those flying on the already deployed Galileo and Ulysses spacecraft. The Cassini mission is targeted for an Oct. 6 launch aboard a Titan IVB/Centaur expendable launch vehicle.

MARS PATHFINDER CAMERA TEST IN SAEF-2

NASA Technical Reports Server (NTRS)

1996-01-01

In the Spacecraft Assembly and Encapsulation Facility-2 (SAEF-2), workers from the Jet Propulsion Laboratory (JPL) are conducting a systems test of the imager for the Mars Pathfinder. Mounted on the Pathfinder lander, the imager (the white cylindrical element the worker is touching) is a specially designed camera featuring a stereo-imaging system with color capability provided by a set of selectable filters. It is mounted on an extendable mast that will pop up after the lander touches down on the Martian surface. The imager will transmit images of the terrain, allowing engineers back on Earth to survey the landing site before the Pathfinder rover is deployed to explore the area. The Mars Pathfinder is scheduled for launch aboard a Delta II expendable launch vehicle on Dec. 2. JPL manages the Pathfinder project for NASA.

Early Program Development

NASA Image and Video Library

1996-06-20

Engineers at one of MSFC's vacuum chambers begin testing a microthruster model. The purpose of these tests are to collect sufficient data that will enabe NASA to develop microthrusters that will move the Space Shuttle, a future space station, or any other space related vehicle with the least amount of expended energy. When something is sent into outer space, the forces that try to pull it back to Earth (gravity) are very small so that it only requires a very small force to move very large objects. In space, a force equal to a paperclip can move an object as large as a car. Microthrusters are used to produce these small forces.

Small Cube Satellite Deploy

NASA Image and Video Library

2013-11-19

ISS038-E-003874 (19 Nov. 2013) --- Three nanosatellites, known as Cubesats, are deployed from a Small Satellite Orbital Deployer (SSOD) attached to the Kibo laboratory's robotic arm at 7:10 a.m. (EST) on Nov. 19, 2013. Japan Aerospace Exploration Agency astronaut Koichi Wakata, Expedition 38 flight engineer, monitored the satellite deployment while operating the Japanese robotic arm from inside Kibo. The Cubesats were delivered to the International Space Station Aug. 9, aboard Japan's fourth H-II Transfer Vehicle, Kounotori-4.

Expendable second stage reusable space shuttle booster. Volume 2: Technical summary. Book 3: Booster vehicle modifications and ground systems definition

NASA Technical Reports Server (NTRS)

1972-01-01

A definition of the expendable second stage and space shuttle booster separation system is presented. Modifications required on the reusable booster for expendable second stage/payload flight and the ground systems needed to operate the expendable second stage in conjuction with the space shuttle booster are described. The safety, reliability, and quality assurance program is explained. Launch complex operations and services are analyzed.

Small Cube Satellite Deploy

NASA Image and Video Library

2013-11-19

ISS038-E-003870 (19 Nov. 2013) --- Three nanosatellites, known as Cubesats, are deployed from a Small Satellite Orbital Deployer (SSOD) attached to the Kibo laboratory’s robotic arm at 7:10 a.m. (EST) on Nov. 19, 2013. Japan Aerospace Exploration Agency astronaut Koichi Wakata, Expedition 38 flight engineer, monitored the satellite deployment while operating the Japanese robotic arm from inside Kibo. The Cubesats were delivered to the International Space Station Aug. 9, aboard Japan’s fourth H-II Transfer Vehicle, Kounotori-4.

Small Cube Satellite Deploy

NASA Image and Video Library

2013-11-19

ISS038-E-003869 (19 Nov. 2013) --- Three nanosatellites, known as Cubesats, are deployed from a Small Satellite Orbital Deployer (SSOD) attached to the Kibo laboratory’s robotic arm at 7:10 a.m. (EST) on Nov. 19, 2013. Japan Aerospace Exploration Agency astronaut Koichi Wakata, Expedition 38 flight engineer, monitored the satellite deployment while operating the Japanese robotic arm from inside Kibo. The Cubesats were delivered to the International Space Station Aug. 9, aboard Japan’s fourth H-II Transfer Vehicle, Kounotori-4.

Small Cube Satellite Deploy

NASA Image and Video Library

2013-11-19

ISS038-E-003871 (19 Nov. 2013) --- Three nanosatellites, known as Cubesats, are deployed from a Small Satellite Orbital Deployer (SSOD) attached to the Kibo laboratory’s robotic arm at 7:10 a.m. (EST) on Nov. 19, 2013. Japan Aerospace Exploration Agency astronaut Koichi Wakata, Expedition 38 flight engineer, monitored the satellite deployment while operating the Japanese robotic arm from inside Kibo. The Cubesats were delivered to the International Space Station Aug. 9, aboard Japan’s fourth H-II Transfer Vehicle, Kounotori-4.

Small Cube Satellite Deploy

NASA Image and Video Library

2013-11-19

ISS038-E-003872 (19 Nov. 2013) --- Three nanosatellites, known as Cubesats, are deployed from a Small Satellite Orbital Deployer (SSOD) attached to the Kibo laboratory’s robotic arm at 7:10 a.m. (EST) on Nov. 19, 2013. Japan Aerospace Exploration Agency astronaut Koichi Wakata, Expedition 38 flight engineer, monitored the satellite deployment while operating the Japanese robotic arm from inside Kibo. The Cubesats were delivered to the International Space Station Aug. 9, aboard Japan’s fourth H-II Transfer Vehicle, Kounotori-4.

NASA Headquarters/Kennedy Space Center: Organization and Small Spacecraft Launch Services

NASA Technical Reports Server (NTRS)

Sierra, Albert; Beddel, Darren

1999-01-01

The objectives of the Kennedy Space Center's (KSC) Expendable Launch Vehicles (ELV) Program are to provide safe, reliable, cost effective ELV launches, maximize customer satisfaction, and perform advanced payload processing capability development. Details are given on the ELV program organization, products and services, foreign launch vehicle policy, how to get a NASA launch service, and some of the recent NASA payloads.

Next generation sensing platforms for extended deployments in large-scale, multidisciplinary, adaptive sampling and observational networks

NASA Astrophysics Data System (ADS)

Cross, J. N.; Meinig, C.; Mordy, C. W.; Lawrence-Slavas, N.; Cokelet, E. D.; Jenkins, R.; Tabisola, H. M.; Stabeno, P. J.

2016-12-01

New autonomous sensors have dramatically increased the resolution and accuracy of oceanographic data collection, enabling rapid sampling over extremely fine scales. Innovative new autonomous platofrms like floats, gliders, drones, and crawling moorings leverage the full potential of these new sensors by extending spatiotemporal reach across varied environments. During 2015 and 2016, The Innovative Technology for Arctic Exploration Program at the Pacific Marine Environmental Laboratory tested several new types of fully autonomous platforms with increased speed, durability, and power and payload capacity designed to deliver cutting-edge ecosystem assessment sensors to remote or inaccessible environments. The Expendable Ice-Tracking (EXIT) gloat developed by the NOAA Pacific Marine Environmental Laboratory (PMEL) is moored near bottom during the ice-free season and released on an autonomous timer beneath the ice during the following winter. The float collects a rapid profile during ascent, and continues to collect critical, poorly-accessible under-ice data until melt, when data is transmitted via satellite. The autonomous Oculus sub-surface glider developed by the University of Washington and PMEL has a large power and payload capacity and an enhanced buoyancy engine. This 'coastal truck' is designed for the rapid water column ascent required by optical imaging systems. The Saildrone is a solar and wind powered ocean unmanned surface vessel (USV) developed by Saildrone, Inc. in partnership with PMEL. This large-payload (200 lbs), fast (1-7 kts), durable (46 kts winds) platform was equipped with 15 sensors designed for ecosystem assessment during 2016, including passive and active acoustic systems specially redesigned for autonomous vehicle deployments. The senors deployed on these platforms achieved rigorous accuracy and precision standards. These innovative platforms provide new sampling capabilities and cost efficiencies in high-resolution sensor deployment, including reconnaissance for annual fisheries and marine mammal surveys; better linkages between sustained observing platforms; and adaptive deployments that can easily target anomalies as they arise.

An opportunity cost model of subjective effort and task performance

PubMed Central

Kurzban, Robert; Duckworth, Angela; Kable, Joseph W.; Myers, Justus

2013-01-01

Why does performing certain tasks cause the aversive experience of mental effort and concomitant deterioration in task performance? One explanation posits a physical resource that is depleted over time. We propose an alternate explanation that centers on mental representations of the costs and benefits associated with task performance. Specifically, certain computational mechanisms, especially those associated with executive function, can be deployed for only a limited number of simultaneous tasks at any given moment. Consequently, the deployment of these computational mechanisms carries an opportunity cost – that is, the next-best use to which these systems might be put. We argue that the phenomenology of effort can be understood as the felt output of these cost/benefit computations. In turn, the subjective experience of effort motivates reduced deployment of these computational mechanisms in the service of the present task. These opportunity cost representations, then, together with other cost/benefit calculations, determine effort expended and, everything else equal, result in performance reductions. In making our case for this position, we review alternate explanations both for the phenomenology of effort associated with these tasks and for performance reductions over time. Likewise, we review the broad range of relevant empirical results from across subdisciplines, especially psychology and neuroscience. We hope that our proposal will help to build links among the diverse fields that have been addressing similar questions from different perspectives, and we emphasize ways in which alternate models might be empirically distinguished. PMID:24304775

Nano Entry System for CubeSat-Class Payloads Project (Nano-ADEPT)

NASA Technical Reports Server (NTRS)

Smith, Brandon Patrick

2014-01-01

This project is developing a mechanically deployed system through a mission application study, deployment/ejection testing, and wind tunnel testing. Adaptable Deployable Entry and Placement Technology (ADEPT) has been under development at NASA since 2011. Nano-ADEPT is the application of this revolutionary entry technology for small spacecraft. The unique capability of ADEPT for small science payloads comes from its ability to stow within a slender volume and deploy passively to achieve a mass-efficient drag surface with a high heat rate capability. Near-term applications for this technology include return of small science payloads or CubeSat technology from Low Earth Orbit (LEO) and delivery of secondary payloads to the surface of Mars.

Prefrontal Cortical Inactivations Decrease Willingness to Expend Cognitive Effort on a Rodent Cost/Benefit Decision-Making Task.

PubMed

Hosking, Jay G; Cocker, Paul J; Winstanley, Catharine A

2016-04-01

Personal success often necessitates expending greater effort for greater reward but, equally important, also requires judicious use of our limited cognitive resources (e.g., attention). Previous animal models have shown that the prelimbic (PL) and infralimbic (IL) regions of the prefrontal cortex (PFC) are not involved in (physical) effort-based choice, whereas human studies have demonstrated PFC contributions to (mental) effort. Here, we utilize the rat Cognitive Effort Task (rCET) to probe PFC's role in effort-based decision making. In the rCET, animals can choose either an easy trial, where the attentional demand is low but the reward (sugar) is small or a difficult trial on which both the attentional demand and reward are greater. Temporary inactivation of PL and IL decreased all animals' willingness to expend mental effort and increased animals' distractibility; PL inactivations more substantially affected performance (i.e., attention), whereas IL inactivations increased motor impulsivity. These data imply that the PFC contributes to attentional resources, and when these resources are diminished, animals shift their choice (via other brain regions) accordingly. Thus, one novel therapeutic approach to deficits in effort expenditure may be to focus on the resources that such decision making requires, rather than the decision-making process per se. © The Author 2015. Published by Oxford University Press. All rights reserved. For Permissions, please e-mail: journals.permissions@oup.com.

Lessons learned from and the future for NASA's Small Explorer Program

NASA Technical Reports Server (NTRS)

Newton, George P.

1991-01-01

NASA started the Small Explorer Program to provide space scientists with an opportunity to conduct space science research in the Explorer Program using scientific payloads launched on small-class expendable launch vehicles. A series of small payload, scientific missions was envisioned that could be launched at the rate of one to two missions per year. Three missions were selected in April 1989: Solar Anomalous and Magnetospheric Particle Explorer, Fast Auroral Snapshot Explorer, and Sub-millimeter Wave Astronomy. These missions are planned for launch in June 1992, September 1994 and June 1995, respectively. At a program level, this paper presents the history, objectives, status, and lessons learned which may be applicable to similar programs, and discusses future program plans.

Paving the Way for Small Satellite Access to Orbit: Cyclops' Deployment of SpinSat, the Largest Satellite Ever Deployed from the International Space Station

NASA Technical Reports Server (NTRS)

Hershey, Matthew P.; Newswander, Daniel R.; Smith, James P.; Lamb, Craig R.; Ballard, Perry G.

2015-01-01

The Space Station Integrated Kinetic Launcher for Orbital Payload Systems (SSIKLOPS), known as "Cyclops" to the International Space Station (ISS) community, successfully deployed the largest satellite ever (SpinSat) from the ISS on November 28, 2014. Cyclops, a collaboration between the NASA ISS Program, NASA Johnson Space Center Engineering, and Department of Defense Space Test Program (DoD STP) communities, is a dedicated 10-100 kg class ISS small satellite deployment system. This paper will showcase the successful deployment of SpinSat from the ISS. It will also outline the concept of operations, interfaces, requirements, and processes for satellites to utilize the Cyclops satellite deployment system.

Deployment of Mobile Learning Course Materials to Android Powered Mobile Devices

ERIC Educational Resources Information Center

Chao, Lee

2012-01-01

The objective of this article is to facilitate mobile teaching and learning by providing an alternative course material deployment method. This article suggests a course material deployment platform for small universities or individual instructors. Different from traditional course material deployment methods, the method discussed deploys course…

Three small deployed satellites

NASA Image and Video Library

2012-10-04

ISS033-E-009282 (4 Oct. 2012) --- Several tiny satellites are featured in this image photographed by an Expedition 33 crew member on the International Space Station. The satellites were released outside the Kibo laboratory using a Small Satellite Orbital Deployer attached to the Japanese module’s robotic arm on Oct. 4, 2012. Japan Aerospace Exploration Agency astronaut Aki Hoshide, flight engineer, set up the satellite deployment gear inside the lab and placed it in the Kibo airlock. The Japanese robotic arm then grappled the deployment system and its satellites from the airlock for deployment. Earth’s horizon and the blackness of space provide the backdrop for the scene.

JEMRMS Small Satellite Deployment Observation

NASA Image and Video Library

2012-10-04

ISS033-E-009315 (4 Oct. 2012) --- Several tiny satellites are featured in this image photographed by an Expedition 33 crew member on the International Space Station. The satellites were released outside the Kibo laboratory using a Small Satellite Orbital Deployer attached to the Japanese module’s robotic arm on Oct. 4, 2012. Japan Aerospace Exploration Agency astronaut Aki Hoshide, flight engineer, set up the satellite deployment gear inside the lab and placed it in the Kibo airlock. The Japanese robotic arm then grappled the deployment system and its satellites from the airlock for deployment. A blue and white part of Earth provides the backdrop for the scene.

Reagentless chemiluminescence-based fiber optic sensors for regenerative life support in space

NASA Astrophysics Data System (ADS)

Atwater, James E.; Akse, James R.; DeHart, Jeffrey; Wheeler, Richard R., Jr.

1995-04-01

The initial feasibility demonstration of a reagentless chemiluminescence based fiber optic sensor technology for use in advanced regenerative life support applications in space and planetary outposts is described. The primary constraints for extraterrestrial deployment of any technology are compatibility with microgravity and hypogravity environments; minimal size, weight, and power consumption; and minimal use of expendables due to the great expense and difficulty inherent to resupply logistics. In the current research, we report the integration of solid state flow through modules for the production of aqueous phase reagents into an integrated system for the detection of important analytes by chemiluminescence, with fiber optic light transmission. By minimizing the need for resupply expendables, the use of solid phase modules makes complex chemical detection schemes practical. For the proof of concept, hydrogen peroxide and glucose were chosen as analytes. The reaction is catalyzed by glucose oxidase, an immobilized enzyme. The aqueous phase chemistry required for sensor operation is implemented using solid phase modules which adjust the pH of the influent stream, catalyze the oxidation of analyte, and provide the controlled addition of the luminophore to the flowing aqueous stream. Precise control of the pH has proven essential for the long-term sustained release of the luminophore. Electrocatalysis is achieved using a controlled potential across gold mesh and gold foil electrodes which undergo periodic polarity reversals. The development and initial characterization of performance of the reagentless fiber optic chemiluminescence sensors are presented in this paper.

76 FR 52694 - National Environmental Policy Act: Launch of NASA Routine Payloads on Expendable Launch Vehicles

Federal Register 2010, 2011, 2012, 2013, 2014

2011-08-23

...: Launch of NASA Routine Payloads on Expendable Launch Vehicles AGENCY: National Aeronautics and Space Administration (NASA). ACTION: Notice of availability and request for comments on the draft environmental assessment (``Draft EA'') for launch of NASA routine payloads on expendable launch vehicles. SUMMARY...

7 CFR 3019.35 - Supplies and other expendable property.

Code of Federal Regulations, 2010 CFR

2010-01-01

... of unused supplies exceeding $5000 in total aggregate value upon termination or completion of the... 7 Agriculture 15 2010-01-01 2010-01-01 false Supplies and other expendable property. 3019.35... Requirements Property Standards § 3019.35 Supplies and other expendable property. (a) Title to supplies and...

Small, low-cost, expendable turbojet engine. 1: Design, fabrication, and preliminary testing

NASA Technical Reports Server (NTRS)

Dengler, R. P.; Macioce, L. E.

1976-01-01

A small experimental axial-flow turbojet engine in the 2,669-Newton (600-lbf) thrust class was designed, fabricated, and tested to demonstrate the feasibility of several low-cost concepts. Design simplicity was stressed in order to reduce the number of components and machining operations. Four engines were built and tested for a total of 157 hours. Engine testing was conducted at both sea-level static and simulated flight conditions for engine speeds as high as 38,000 rpm and turbine-inlet temperatures as high as 1,255 K (1,800 F).

To amend title 49, United States Code, to require that not less than 10 percent of the amounts made available for certain high-speed rail projects be expended through small business concerns owned and controlled by socially and economically disadvantaged individuals, and for other purposes.

THOMAS, 111th Congress

Rep. Moore, Gwen [D-WI-4

2010-04-13

House - 04/14/2010 Referred to the Subcommittee on Railroads, Pipelines, and Hazardous Materials. (All Actions) Tracker: This bill has the status IntroducedHere are the steps for Status of Legislation:

To amend title 49, United States Code, to require that not less than 10 percent of the amounts made available for certain high-speed rail projects be expended through small business concerns owned and controlled by socially and economically disadvantaged individuals, and for other purposes.

THOMAS, 112th Congress

Rep. Moore, Gwen [D-WI-4

2011-09-20

House - 09/21/2011 Referred to the Subcommittee on Railroads, Pipelines, and Hazardous Materials. (All Actions) Tracker: This bill has the status IntroducedHere are the steps for Status of Legislation:

Design and Early In-flight Performance of the Tropical Rainfall Measuring Mission (TRMM) Power Subsystem

NASA Technical Reports Server (NTRS)

Moran, Vickie Eakin; Flatley, Thomas P.; Shue, John; Gaddy, Edward M.; Manzer, Dominic; Hicks, Edward

1998-01-01

Maryland built the spacecraft in-house with four U.S. instruments and one Japanese instrument, the first space flown Precipitation Radar (PR). The TRMM Observatory was successfully launched from Tanegashima Space Center in Japan on an H-2 Expendable Launch Vehicle on November 27, 1997. This paper presents an overview of the TRMM Power System including its design, testing, and in flight performance for the first 70 days. Finally, key lessons learned are presented. The TRMM power system consists of an 18.1 square meter deployed solar array fabricated by TRW with Tecstar GaAs/Ge cells, two (2) Hughes 50 Ampere-Hour (Ah) Super NiCd' batteries, each with 22 Eagle-Picher cells, and three (3) electronics boxes designed to provide power regulation, battery charge control, and command and telemetry interface.

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

Naskar, Amit K.; Keum, Jong K.; Boeman, Raymond G.

Over the past several decades, the automotive industry has expended significant effort to develop lightweight parts from new easy-to-process polymeric nanocomposites. These materials have been particularly attractive because they can increase fuel efficiency and reduce greenhouse gas emissions. However, attempts to reinforce soft matrices by nanoscale reinforcing agents at commercially deployable scales have been only sporadically successful to date. This situation is due primarily to the lack of fundamental understanding of how multiscale interfacial interactions and the resultant structures affect the properties of polymer nanocomposites. In this paper, we critically evaluate the state of the art in the field andmore » propose a possible path that may help to overcome these barriers. Finally, only once we achieve a deeper understanding of the structure–properties relationship of polymer matrix nanocomposites will we be able to develop novel structural nanocomposites with enhanced mechanical properties for automotive applications.« less

Three small deployed satellites

NASA Image and Video Library

2012-10-04

ISS033-E-009286 (4 Oct. 2012) --- Several tiny satellites are featured in this image photographed by an Expedition 33 crew member on the International Space Station. The satellites were released outside the Kibo laboratory using a Small Satellite Orbital Deployer attached to the Japanese module’s robotic arm on Oct. 4, 2012. Japan Aerospace Exploration Agency astronaut Aki Hoshide, flight engineer, set up the satellite deployment gear inside the lab and placed it in the Kibo airlock. The Japanese robotic arm then grappled the deployment system and its satellites from the airlock for deployment. A portion of the station’s solar array panels and a blue and white part of Earth provide the backdrop for the scene.

Three small deployed satellites

NASA Image and Video Library

2012-10-04

ISS033-E-009285 (4 Oct. 2012) --- Several tiny satellites are featured in this image photographed by an Expedition 33 crew member on the International Space Station. The satellites were released outside the Kibo laboratory using a Small Satellite Orbital Deployer attached to the Japanese module’s robotic arm on Oct. 4, 2012. Japan Aerospace Exploration Agency astronaut Aki Hoshide, flight engineer, set up the satellite deployment gear inside the lab and placed it in the Kibo airlock. The Japanese robotic arm then grappled the deployment system and its satellites from the airlock for deployment. A portion of the station’s solar array panels and a blue and white part of Earth provide the backdrop for the scene.

SCORPIUS, A New Generation of Responsive, Low Cost Expendable Launch Vehicles

NASA Astrophysics Data System (ADS)

Conger, R. E.; Chakroborty, S. P.; Wertz, J. R.

2002-01-01

The Scorpius vehicle family extends from one and two stage sub-orbital vehicles for target and science applications to small, medium and heavy lift orbital vehicles. These new liquid fueled vehicles have LEO and GTO capabilities. Microcosm and the Scorpius Space Launch Company (SSLC) are well into the development of this all-new generation of expendable launch vehicles to support commercial and government missions. This paper presents the projected performance of the family of vehicles, status of the development program and projected launch service prices. The paper will discuss the new low cost ablative engines and low cost pressure-fed LOX/Jet-A propulsion systems. Schedules, payload volumes, dispensers, attach fittings, and planned dual manifest capabilities will be presented. The unique configuration of the wide base first stage allows fairings that may extend beyond the current 4-meters. The Scorpius family is designed to facilitate encapsulated payloads and launch-on-demand. The implications of these new operational procedures will be addressed, including the techniques that will be used to drive down the cost of access to space while improving reliability. The Scorpius family of low cost vehicles addresses the full range of payloads from 700 lbs. in the Sprite Mini-Lift to over 50,000 lbs. to LEO in the Heavy-Lift, and over 18,000 lbs. to GTO. Two sub-orbital vehicles have been developed and successfully launched, with the latest vehicle (SR-XM) launched in March of 2001 from White Sands Missile Range. Development of the family of vehicles commenced in 1993 under contracts with the Air Force Research Laboratory Space Vehicle Directorate after a number of years of independent studies and system engineering. The Sprite Mini-Lift Small Expendable Launch Vehicle (SELV) that utilizes the SR-XM technologies is planned for an initial launch in mid 2005 with larger, scaled-up vehicles to follow.

Advanced Deployable Shell-Based Composite Booms for Small Satellite Structural Applications Including Solar Sails

NASA Technical Reports Server (NTRS)

Fernandez, Juan M.

2017-01-01

State of the art deployable structures are mainly being designed for medium to large size satellites. The lack of reliable deployable structural systems for low cost, small volume, rideshare-class spacecraft severely constrains the potential for using small satellite platforms for affordable deep space science and exploration precursor missions that could be realized with solar sails. There is thus a need for reliable, lightweight, high packaging efficiency deployable booms that can serve as the supporting structure for a wide range of small satellite systems including solar sails for propulsion. The National Air and Space Administration (NASA) is currently investing in the development of a new class of advanced deployable shell-based composite booms to support future deep space small satellite missions using solar sails. The concepts are being designed to: meet the unique requirements of small satellites, maximize ground testability, permit the use of low-cost manufacturing processes that will benefit scalability, be scalable for use as elements of hierarchical structures (e.g. trusses), allow long duration storage, have high deployment reliability, and have controlled deployment behavior and predictable deployed dynamics. This paper will present the various rollable boom concepts that are being developed for 5-20 m class size deployable structures that include solar sails with the so-called High Strain Composites (HSC) materials. The deployable composite booms to be presented are being developed to expand the portfolio of available rollable booms for small satellites and maximize their length for a given packaged volume. Given that solar sails are a great example of volume and mass optimization, the booms were designed to comply with nominal solar sail system requirements for 6U CubeSats, which are a good compromise between those of smaller form factors (1U, 2U and 3U CubeSats) and larger ones (12 U and 27 U future CubeSats, and ESPA-class microsatellites). Solar sail missions for such composite boom systems are already under consideration and development at NASA, as well as mission studies that will benefit from planned scaled-up versions of the composite boom technologies to be introduced. The paper presents ongoing research and development of thin-shell rollable composite booms designed under the particular stringent and challenging system requirements of relatively large solar sails housed on small satellites. These requirements will be derived and listed. Several new boom concepts are proposed and other existing ones are improved upon using thin-ply composite materials to yield unprecedented compact deployable structures. Some of these booms are shown in Fig. 1. For every boom to be introduced the scalable fabrication process developed to keep the overall boom system cost down will be shown. Finally, the initial results of purposely designed boom structural characterization test methods with gravity off-loading will be presented to compare their structural performance under expected and general load cases.

43 CFR 12.935 - Supplies and other expendable property.

Code of Federal Regulations, 2010 CFR

2010-10-01

... of unused supplies exceeding $5,000 in total aggregate value upon termination or completion of the... 43 Public Lands: Interior 1 2010-10-01 2010-10-01 false Supplies and other expendable property. 12... Organizations Post-Award Requirements § 12.935 Supplies and other expendable property. (a) Title to supplies and...

29 CFR 99.205 - Basis for determining Federal awards expended.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 29 Labor 1 2010-07-01 2010-07-01 true Basis for determining Federal awards expended. 99.205 Section 99.205 Labor Office of the Secretary of Labor AUDITS OF STATES, LOCAL GOVERNMENTS, AND NON-PROFIT ORGANIZATIONS Audits § 99.205 Basis for determining Federal awards expended. (a) Determining Federal awards...

48 CFR 1828.371 - Clauses for cross-waivers of liability for Space Shuttle services, Expendable Launch Vehicle (ELV...

Code of Federal Regulations, 2011 CFR

2011-10-01

... of liability for Space Shuttle services, Expendable Launch Vehicle (ELV) launches, and Space Station... of liability for Space Shuttle services, Expendable Launch Vehicle (ELV) launches, and Space Station activities. (a) In agreements covering Space Shuttle services, certain ELV launches, and Space Station...

48 CFR 1828.371 - Clauses for cross-waivers of liability for Space Shuttle services, Expendable Launch Vehicle (ELV...

Code of Federal Regulations, 2010 CFR

2010-10-01

... of liability for Space Shuttle services, Expendable Launch Vehicle (ELV) launches, and Space Station... of liability for Space Shuttle services, Expendable Launch Vehicle (ELV) launches, and Space Station activities. (a) In agreements covering Space Shuttle services, certain ELV launches, and Space Station...

Processing Depth, Elaboration of Encoding, Memory Stores, and Expended Processing Capacity.

ERIC Educational Resources Information Center

Eysenck, Michael W.; Eysenck, M. Christine

1979-01-01

The effects of several factors on expended processing capacity were measured. Expended processing capacity was greater when information was retrieved from secondary memory than from primary memory, when processing was of a deep, semantic nature than when it was shallow and physical, and when processing was more elaborate. (Author/GDC)

Knowledge Creation and Deployment in the Small, but Growing, Enterprise and the Psychological Contract

ERIC Educational Resources Information Center

Leach, Tony

2010-01-01

This paper contains an account of a small scale investigation into the usefulness of the concepts of the learning organisation and organisational learning when seeking to describe the processes of knowledge creation and deployment within the small, but growing, enterprise (SME). A review of the literature reveals a concern that the relationship…

Small Space Launch: Origins & Challenges

NASA Astrophysics Data System (ADS)

Freeman, T.; Delarosa, J.

2010-09-01

The United States Space Situational Awareness capability continues to be a key element in obtaining and maintaining the high ground in space. Space Situational Awareness satellites are critical enablers for integrated air, ground and sea operations, and play an essential role in fighting and winning conflicts. The United States leads the world space community in spacecraft payload systems from the component level into spacecraft, and in the development of constellations of spacecraft. In the area of launch systems that support Space Situational Awareness, despite the recent development of small launch vehicles, the United States launch capability is dominated by an old, unresponsive and relatively expensive set of launchers in the Expandable, Expendable Launch Vehicles (EELV) platforms; Delta IV and Atlas V. The United States directed Air Force Space Command to develop the capability for operationally responsive access to space and use of space to support national security, including the ability to provide critical space capabilities in the event of a failure of launch or on-orbit capabilities. On 1 Aug 06, Air Force Space Command activated the Space Development & Test Wing (SDTW) to perform development, test and evaluation of Air Force space systems and to execute advanced space deployment and demonstration projects to exploit new concepts and technologies, and rapidly migrate capabilities to the warfighter. The SDTW charged the Launch Test Squadron (LTS) with the mission to develop the capability of small space launch, supporting government research and development space launches and missile defense target missions, with operationally responsive spacelift for Low-Earth-Orbit Space Situational Awareness assets as a future mission. This new mission created new challenges for LTS. The LTS mission tenets of developing space launches and missile defense target vehicles were an evolution from the squadrons previous mission of providing sounding rockets under the Rocket Sounding Launch Program (RSLP). The new mission tenets include shortened operational response periods criteria for the warfighter, while reducing the life-cycle development, production and launch costs of space launch systems. This presentation will focus on the technical challenges in transforming and integrating space launch vehicles and space craft vehicles for small space launch missions.

Small-scale nuclear reactors for remote military operations: opportunities and challenges

DTIC Science & Technology

2015-08-25

study – Report was published in March 2011  CNA study identified challenges to deploy small modular reactors (SMRs) at a base – Identified First-of...forward operating bases. The availability of deployable, cost-effective, regulated, and secure small modular reactors with a modest output electrical...defense committees on the challenges, operational requirements, constraints, cost, and life cycle analysis for a small modular reactor of less than 10

Energy dissipation in substorms

NASA Technical Reports Server (NTRS)

Weiss, Loretta A.; Reiff, P. H.; Moses, J. J.; Heelis, R. A.; Moore, B. D.

1992-01-01

The energy dissipated by substorms manifested in several ways is discussed: the Joule dissipation in the ionosphere; the energization of the ring current by the injection of plasma sheet particles; auroral election and ion acceleration; plasmoid ejection; and plasma sheet ion heating during the recovery phase. For each of these energy dissipation mechanisms, a 'rule of thumb' formula is given, and a typical dissipation rate and total energy expenditure is estimated. The total energy dissipated as Joule heat (approximately) 2 x 10(exp 15) is found about twice the ring current injection term, and may be even larger if small scale effects are included. The energy expended in auroral electron precipitation, on the other hand, is smaller than the Joule heating by a factor of five. The energy expended in refilling and heating the plasma sheets is estimated to be approximately 5 x 10(exp 14)J, while the energy lost due to plasmoid ejection is between (approximately) (10 exp 13)(exp 14)J.

NanoRacks CubeSat Deployment

NASA Image and Video Library

2015-02-27

ISS042E290579 (02/27/2015) --- On Feb. 27 2015, a series of CubeSats, small experimental satellites, were deployed via a special device mounted on the Japanese Experiment Module (JEM) Remote Manipulator System (JEMRMS). Deployed satellites included twelve Dove sats, one TechEdSat-4, one GEARRSat, one LambdaSat, one MicroMas. These satellites perform a variety of functions from capturing new Earth imagery, to using microwave scanners to create 3D images of hurricanes, to even developing new methods for returning science samples back to Earth from space. The small satellites were deployed through the first week in March.

Histological Diagnoses of Military Personnel Undergoing Lung Biopsy After Deployment to Southwest Asia.

PubMed

Madar, Cristian S; Lewin-Smith, Michael R; Franks, Teri J; Harley, Russell A; Klaric, John S; Morris, Michael J

2017-08-01

The current understanding of associations between lung disease and military deployment to Southwest Asia, including Iraq and Afghanistan, is both controversial and limited. We sought to clarify the relation between military deployment and biopsy-proven lung disease. Retrospective data were analyzed for military personnel with non-neoplastic lung biopsies evaluated at the Armed Forces Institute of Pathology or Joint Pathology Center (January 2005 to December 2012). Of 391 subjects, 137 (35.0%) had deployed to Southwest Asia prior to biopsy. Compared to non-deployed subjects, those deployed were younger (median age 37 vs. 51 years) with higher representation of African Americans (30.0 vs. 16.9%). Deployed patients were more likely diagnosed with non-necrotizing granulomas (OR 2.4). Non-deployed subjects had higher frequency of idiopathic interstitial pneumonias, particularly organizing pneumonia. Prevalence of small airways diseases including constrictive bronchiolitis was low. This study provides a broader understanding of diversity of biopsy-proven non-neoplastic lung disease as it relates to military deployment to Southwest Asia and importantly did not show an increased prevalence of small airway disease to include constrictive bronchiolitis.

Portable Hydraulic Powerpack

NASA Technical Reports Server (NTRS)

Anderson, L. A.; Henry, R. L.; Fedor, O. H.; Owens, L. J.

1986-01-01

Rechargeable hydraulic powerpack functions as lightweight, compact source of mechanical energy. Self-contained hydraulic powerpack derives energy from solid chemical charge. Combustion of charge initiated by small hammer, and revolving feeder replaces charges expended. Combustion gases cool during expansion in turbine and not too hot for release to atmosphere. Unit has applications driving wheelchairs and operating drills, winches, and other equipment in remote areas. Also replaces electric motors and internal-combustion engines as source of power in explosive atmospheres.

An agronomic field-scale sensor network for monitoring soil water and temperature variation

NASA Astrophysics Data System (ADS)

Brown, D. J.; Gasch, C.; Brooks, E. S.; Huggins, D. R.; Campbell, C. S.; Cobos, D. R.

2014-12-01

Environmental sensor networks have been deployed in a variety of contexts to monitor plant, air, water and soil properties. To date, there have been relatively few such networks deployed to monitor dynamic soil properties in cropped fields. Here we report on experience with a distributed soil sensor network that has been deployed for seven years in a research farm with ongoing agronomic field operations. The Washington State University R. J. Cook Agronomy Farm (CAF), Pullman, WA, USA has recently been designated a United States Department of Agriculture (USDA) Long-Term Agro-Ecosystem Research (LTAR) site. In 2007, 12 geo-referenced locations at CAF were instrumented, then in 2009 this network was expended to 42 locations distributed across the 37-ha farm. At each of this locations, Decagon 5TE probes (Decagon Devices Inc., Pullman, WA, USA) were installed at five depths (30, 60, 90, 120, and 150 cm), with temperature and volumetric soil moisture content recorded hourly. Initially, data loggers were wirelessly connected to a data station that could be accessed through a cell connection, but due to the logistics of agronomic field operations, we later buried the dataloggers at each site and now periodically download data via local radio transmission. In this presentation, we share our experience with the installation, maintenance, calibration and data processing associated with an agronomic soil monitoring network. We also present highlights of data derived from this network, including seasonal fluctuations of soil temperature and volumetric water content at each depth, and how these measurements are influenced by crop type, soil properties, landscape position, and precipitation events.

45 CFR 264.80 - If a Territory receives Matching Grant funds, what funds must it expend?

Code of Federal Regulations, 2010 CFR

2010-10-01

... funds must it expend? 264.80 Section 264.80 Public Welfare Regulations Relating to Public Welfare OFFICE... Levels of the Territories? § 264.80 If a Territory receives Matching Grant funds, what funds must it expend? (a) If a Territory receives Matching Grant funds under section 1108(b) of the Act, it must: (1...

Initial development of a laser altimeter

NASA Astrophysics Data System (ADS)

Gilio, J. P.

1985-09-01

A design study was carried out of a small, expendable, self-contained laser altimeter for overwater operation at low altitude. A .904 micrometer Gallium Arsenide laser was used to build a prototype transmitter/ receiver at a cost of less than $600 and small enough to fit inside a 5 inch diameter cylinder, 5 inches long. Tests at a height of 120 feet above the surface of a lake resulted in a signal-to-noise ratio of 6, and validated the trade-off equation used in this study. A second test model, with design improvements incorporated, is predicted to yield a SNR of over 20 for an altitude of 150 meters.

Polymer matrix nanocomposites for automotive structural components

DOE PAGES

Naskar, Amit K.; Keum, Jong K.; Boeman, Raymond G.

2016-12-06

Over the past several decades, the automotive industry has expended significant effort to develop lightweight parts from new easy-to-process polymeric nanocomposites. These materials have been particularly attractive because they can increase fuel efficiency and reduce greenhouse gas emissions. However, attempts to reinforce soft matrices by nanoscale reinforcing agents at commercially deployable scales have been only sporadically successful to date. This situation is due primarily to the lack of fundamental understanding of how multiscale interfacial interactions and the resultant structures affect the properties of polymer nanocomposites. In this paper, we critically evaluate the state of the art in the field andmore » propose a possible path that may help to overcome these barriers. Finally, only once we achieve a deeper understanding of the structure–properties relationship of polymer matrix nanocomposites will we be able to develop novel structural nanocomposites with enhanced mechanical properties for automotive applications.« less

Polymer matrix nanocomposites for automotive structural components

NASA Astrophysics Data System (ADS)

Naskar, Amit K.; Keum, Jong K.; Boeman, Raymond G.

2016-12-01

Over the past several decades, the automotive industry has expended significant effort to develop lightweight parts from new easy-to-process polymeric nanocomposites. These materials have been particularly attractive because they can increase fuel efficiency and reduce greenhouse gas emissions. However, attempts to reinforce soft matrices by nanoscale reinforcing agents at commercially deployable scales have been only sporadically successful to date. This situation is due primarily to the lack of fundamental understanding of how multiscale interfacial interactions and the resultant structures affect the properties of polymer nanocomposites. In this Perspective, we critically evaluate the state of the art in the field and propose a possible path that may help to overcome these barriers. Only once we achieve a deeper understanding of the structure-properties relationship of polymer matrix nanocomposites will we be able to develop novel structural nanocomposites with enhanced mechanical properties for automotive applications.

Polymer matrix nanocomposites for automotive structural components.

PubMed

Naskar, Amit K; Keum, Jong K; Boeman, Raymond G

2016-12-06

Over the past several decades, the automotive industry has expended significant effort to develop lightweight parts from new easy-to-process polymeric nanocomposites. These materials have been particularly attractive because they can increase fuel efficiency and reduce greenhouse gas emissions. However, attempts to reinforce soft matrices by nanoscale reinforcing agents at commercially deployable scales have been only sporadically successful to date. This situation is due primarily to the lack of fundamental understanding of how multiscale interfacial interactions and the resultant structures affect the properties of polymer nanocomposites. In this Perspective, we critically evaluate the state of the art in the field and propose a possible path that may help to overcome these barriers. Only once we achieve a deeper understanding of the structure-properties relationship of polymer matrix nanocomposites will we be able to develop novel structural nanocomposites with enhanced mechanical properties for automotive applications.

Oceanographic Measurements Program Review.

DTIC Science & Technology

1982-03-01

prototype Advanced Microstructure Profiler (AMP) was completed and the unit was operationally tested in local waters (Lake Washington and Puget Sound ...Expendables ....... ............. ..21 A.W. Green The Developent of an Air-Launched ................ 25 Expendable Sound Velocimeter (AXSV); R. Bixby...8217., ,? , .’,*, ;; .,’...; "’ . :" .* " . .. ". ;’ - ~ ~ ~ ~ ’ V’ 7T W, V a .. -- THE DEVELOPMENT OF AN AIR-LAUNCHED EXPENDABLE SOUND VELOCIMETER (AXSV) Richard Bixby

Expendable second stage reusable space shuttle booster. Volume 4: Detail mass properties data

NASA Technical Reports Server (NTRS)

1971-01-01

Mass properties data are presented to describe the characteristics of an expendable second stage with a reusable space shuttle booster. The final mass characteristics of the vehicle configurations for three specified payloads are presented in terms of weight, center of gravity, and mass moments of inertia. Three basic subjects are the integrated vehicle system, the expendable second stage, and the booster modifications.

45 CFR 263.1 - How much State money must a State expend annually to meet the basic MOE requirement?

Code of Federal Regulations, 2010 CFR

2010-10-01

... 45 Public Welfare 2 2010-10-01 2010-10-01 false How much State money must a State expend annually... State's Maintenance of Effort? § 263.1 How much State money must a State expend annually to meet the... historic State expenditures. (2) However, if a State meets the minimum work participation rate requirements...

77 FR 30518 - Support of Deployment of Prototype Small Modular Reactors at the Savannah River Site

Federal Register 2010, 2011, 2012, 2013, 2014

2012-05-23

... DEPARTMENT OF ENERGY Support of Deployment of Prototype Small Modular Reactors at the Savannah River Site AGENCY: Savannah River Operations Office, Department of Energy (DOE). ACTION: Notice of availability. SUMMARY: DOE-Savannah River Operations Office (SR), in conjunction with the Savannah River...

Expendable vs reusable propulsion systems cost sensitivity

NASA Technical Reports Server (NTRS)

Hamaker, Joseph W.; Dodd, Glenn R.

1989-01-01

One of the key trade studies that must be considered when studying any new space transportation hardware is whether to go reusable or expendable. An analysis is presented here for such a trade relative to a proposed Liquid Rocket Booster which is being studied at MSFC. The assumptions or inputs to the trade were developed and integrated into a model that compares the Life-Cycle Costs of both a reusable LRB and an expendable LRB. Sensitivities were run by varying the input variables to see their effect on total cost. In addition a Monte-Carlo simulation was run to determine the amount of cost risk that may be involved in a decision to reuse or expend.

Demonstrations of Deployable Systems for Robotic Precursor Missions

NASA Technical Reports Server (NTRS)

Dervan, J.; Johnson, L.; Lockett, T.; Carr, J.; Boyd, D.

2017-01-01

NASA is developing thin-film based, deployable propulsion, power, and communication systems for small spacecraft that serve as enabling technologies for exploration of the solar system. By leveraging recent advancements in thin films, photovoltaics, deployment systems, and miniaturized electronics, new mission-level capabilities will be demonstrated aboard small spacecraft enabling a new generation of frequent, inexpensive, and highly capable robotic precursor missions with goals extensible to future human exploration. Specifically, thin-film technologies are allowing the development and use of solar sails for propulsion, small, lightweight photovoltaics for power, and omnidirectional antennas for communication as demonstrated by recent advances on the Near Earth Asteroid (NEA) Scout and Lightweight Integrated Solar Array and anTenna (LISA-T) projects.

In-Vacuum Photogrammetry of a Ten-Meter Square Solar Sail

NASA Technical Reports Server (NTRS)

Pappa, Richard S.; Jones, Thomas W.; Lunsford, Charles B.; Meyer, Christopher G.

2006-01-01

Solar sailing is a promising, future in-space propulsion method that uses the small force of reflecting sunlight to accelerate a large, reflective membrane without expendable propellants. One of two solar sail configurations under development by NASA is a striped net approach by L'Garde, Inc. This design uses four inflatably deployed, lightweight booms supporting a network of thin strings onto which four quadrants of ultrathin aluminized membranes are attached. The NASA Langley Research Center (LaRC) provided both experimental and analytical support to L'Garde for validating the structural characteristics of this unique, ultralightweight spacecraft concept. One of LaRC's responsibilities was to develop and apply photogrammetric methods to measure sail shape. The deployed shape provides important information for validating the accuracy of finite-element modeling techniques. Photogrammetry is the science and art of calculating 3D coordinates of targets or other distinguishing features on structures using images. A minimum of two camera views of each target is required for 3D determination, but having four or more camera views is preferable for improved reliability and accuracy. Using retroreflective circular targets typically provides the highest measurement accuracy and automation. References 3 and 4 provide details of photogrammetry technology, and reference 5 discusses previous experiences with photogrammetry for measuring gossamer spacecraft structures such as solar sails. This paper discusses the experimental techniques used to measure a L Garde 10-m solar sail test in vacuum with photogrammetry. The test was conducted at the NASA-Glenn Space Power Facility (SPF) located at Plum Brook Station in Sandusky, Ohio. The SPF is the largest vacuum chamber in the United States, measuring 30 m in diameter by 37 m in height. High vacuum levels (10(exp -6) torr) can be maintained inside the chamber, and cold environments (-195 C) are possible using variable-geometry cryogenic cold walls. This test used a vacuum level of approximately 1 torr (sufficient for structural static/dynamic characterization) and instead of using the cryogenic cold walls, used local LN2 cold plates underneath each of the four cold-rigidizable solar sail booms instead.

Small Cube Satellite Deploy

NASA Image and Video Library

2013-11-19

ISS038-E-003876 (19 Nov. 2013) --- Three nanosatellites, known as Cubesats, are featured in this image photographed by an Expedition 38 crew member on the International Space Station. The satellites were released outside the Kibo laboratory using a Small Satellite Orbital Deployer attached to the Japanese module's robotic arm on Nov. 19, 2013. Japan Aerospace Exploration Agency astronaut Koichi Wakata, flight engineer, monitored the satellite deployment while operating the Japanese robotic arm from inside Kibo. The Cubesats were delivered to the International Space Station Aug. 9, aboard Japan’s fourth H-II Transfer Vehicle, Kounotori-4.

Small Spacecraft Active Thermal Control: Micro-Vascular Composites Enable Small Satellite Cooling

NASA Technical Reports Server (NTRS)

Ghosh, Alexander

2016-01-01

The Small Spacecraft Integrated Power System with Active Thermal Control project endeavors to achieve active thermal control for small spacecraft in a practical and lightweight structure by circulating a coolant through embedded micro-vascular channels in deployable composite panels. Typically, small spacecraft rely on small body mounted passive radiators to discard heat. This limits cooling capacity and leads to the necessity to design for limited mission operations. These restrictions severely limit the ability of the system to dissipate large amounts of heat from radios, propulsion systems, etc. An actively pumped cooling system combined with a large deployable radiator brings two key advantages over the state of the art for small spacecraft: capacity and flexibility. The use of a large deployable radiator increases the surface area of the spacecraft and allows the radiation surface to be pointed in a direction allowing the most cooling, drastically increasing cooling capacity. With active coolant circulation, throttling of the coolant flow can enable high heat transfer rates during periods of increased heat load, or isolate the radiator during periods of low heat dissipation.

Applicability and Performance Benefits of XD (Tradename) Titanium Aluminides to Expendable Gas Turbine Engines

DTIC Science & Technology

1993-08-01

analysis A dynamic analysis was conducted on the blades and splitters. The existing design for the compressor was used and XD® titanium aluminide property...AD-A272 998 ARMY RESEARCH LABORATORY Applicability and Performance Benefits of XD® Titanium Aluminides to Expendable Gas Turbine Engines Pamela...Benefits of XD® Contract # Titanium Aluminides to Expendable Gas Turbine DAAL04-91-C-0034 Fnginpq 6. AUTHOR(S) Pamela Sadler, K. Sharvan Kumar, John A. S

NanoRacks CubeSat Deployment

NASA Image and Video Library

2014-02-11

ISS038-E-044916 (11 Feb. 2014) --- A set of NanoRacks CubeSats is photographed by an Expedition 38 crew member after the deployment by the Small Satellite Orbital Deployer (SSOD). The CubeSats program contains a variety of experiments such as Earth observations and advanced electronics testing.

Changes in water quality in agricultural catchments after deployment of wastewater treatment plant.

PubMed

Langhammer, Jakub; Rödlová, Sylva

2013-12-01

Insufficient wastewater remediation in small communities and nonpoint source pollution are the key factors in determining the water quality of small streams in an agricultural landscape. Despite the current extensive construction of municipal wastewater treatment facilities in small communities, the level of organic substances and nutrients in the recipient catchments has not decreased in many areas. This paper analyzes the changes in the water quality of the small streams after the deployment of wastewater treatment plants that were designed to address sources of pollution from small municipalities. The analysis is based on the results from a water quality monitoring network in the small watersheds in the Czech Republic. Five rural catchments with one dominant municipal pollution source, where a wastewater treatment plant was deployed during the monitoring period, were selected according to a predefined set of criteria, from a series of 317 profiles. Basic water quality indicators were selected for the assessment: O₂, BOD-5, COD, TOC, conductivity, NH₄-N, NO₂-N, NO₃-N, PT, and PO₄-P. Results of the analysis showed that the simple deployment of the water treatment facilities at these streams often did not lead to a reduction of contamination in the streams. The expected post-deployment changes, namely, a significant and permanent reduction of stream contamination, occurred only in one catchment, whereas in the remainder of the catchments, only marginal changes or even increased concentrations of the contaminants were detected. As the critical factors that determined the efficiency of wastewater treatment were studied, the need for the consideration of the local conditions during the design of the facility, particularly regarding the size of the catchments, initial level of contamination, proper system of operation, and process optimization of the treatment facility, emerged as the important factor.

Seismic Oceanography in the Tyrrhenian Sea: Thermohaline Staircases, Eddies, and Internal Waves

NASA Astrophysics Data System (ADS)

Buffett, G. G.; Krahmann, G.; Klaeschen, D.; Schroeder, K.; Sallarès, V.; Papenberg, C.; Ranero, C. R.; Zitellini, N.

2017-11-01

We use seismic oceanography to document and analyze oceanic thermohaline fine structure across the Tyrrhenian Sea. Multichannel seismic (MCS) reflection data were acquired during the MEDiterranean OCcidental survey in April-May 2010. We deployed along-track expendable bathythermograph probes simultaneous with MCS acquisition. At nearby locations we gathered conductivity-temperature-depth data. An autonomous glider survey added in situ measurements of oceanic properties. The seismic reflectivity clearly delineates thermohaline fine structure in the upper 2,000 m of the water column, indicating the interfaces between Atlantic Water/Winter Intermediate Water, Levantine Intermediate Water, and Tyrrhenian Deep Water. We observe the Northern Tyrrhenian Anticyclone, a near-surface mesoscale eddy, plus laterally and vertically extensive thermohaline staircases. Using MCS, we are able to fully image the anticyclone to a depth of 800 m and to confirm the horizontal continuity of the thermohaline staircases of more than 200 km. The staircases show the clearest step-like gradients in the center of the basin while they become more diffuse toward the periphery and bottom, where impedance gradients become too small to be detected by MCS. We quantify the internal wave field and find it to be weak in the region of the eddy and in the center of the staircases, while it is stronger near the coastlines. Our results indicate this is because of the influence of the boundary currents, which disrupt the formation of staircases by preventing diffusive convection. In the interior of the basin, the staircases are clearer and the internal wave field weaker, suggesting that other mixing processes such as double diffusion prevail.

Deployment and retraction of a cable-driven solar array: Testing and simulation

NASA Technical Reports Server (NTRS)

Kumar, P.; Pellegrino, S.

1995-01-01

The paper investigates three critical areas in cable-driven rigid-panel solar arrays: First, the variation of deployment and retraction cable tensions due to friction at the hinges; Second, the change in deployment dynamics associated with different deployment histories; Third, the relationship between the level of pre-tension in the closed contact loops and the synchronization of deployment. A small scale model array has been made and tested, and its behavior has been compared to numerical simulations.

Space platform expendables resupply concept definition study. Volume 1: Executive summary

NASA Technical Reports Server (NTRS)

1984-01-01

NASA has recognized that the capability for remote resupply of space platform expendable fluids will help transition space utilization into a new era of operational efficiency and cost/effectiveness. The emerging Orbital Maneuvering System (OMV) in conjunction with an expendables resupply module will introduce the capability for fluid resupply enabling satellite lifetime extension at locations beyond the range of the Orbiter. This report summarizes a Phase A study of a remote resupply module for the OMV. Volume 1 is the executive summary.

Space platform expendables resupply concept definition study

NASA Technical Reports Server (NTRS)

1985-01-01

NASA has recognized that the capability for remote resupply of space platform expendable fluids will help transition space utilization into a new era of operational efficiency and cost/effectiveness. The emerging Orbital Maneuvering System (OMV) in conjunction with an expendables resupply module will introduce the capability for fluid resupply enabling satellite lifetime extension at locations beyond the range of the Orbiter. This report summarizes a supplemental study to the original Phase A study and is presented as addenda to that study.

Space platform expendables resupply concept definition study, volume 2

NASA Technical Reports Server (NTRS)

1984-01-01

NASA has recognized that the capability for remote resupply of space platform expendable fluids will help transition space utilization into a new era of operational efficiency and cost/effectiveness. The emerging Orbital Maneuvering System (OMV) in conjunction with an expendables resupply module will introduce the capability for fluid resupply enabling satellite lifetime extension at locations beyond the range of the Orbiter. This report summarizes a Phase A study of a remote resupply module for the OMV. Volume 2 represents study results.

Expendable Second Stage Reusable Space Shuttle Booster. Volume 9; Preliminary System Specification

NASA Technical Reports Server (NTRS)

1971-01-01

The specification for establishing the requirements for the system performance, design, development, and ground and flight operations of the expendable second stage on a reusable space shuttle booster system is presented. The basic specification is that the system shall be capable of placing payloads in excess of 100,000 pounds into earth orbit. In addition, the expendable second stage provides a multimission, economical, large capability system suitable for a variety of space missions in the 1980 time period.

Parachute deploy/Release mechanism

NASA Technical Reports Server (NTRS)

Robelen, D. B.

1979-01-01

Mechanism operated by signals from single radio-control channel deploy and releases small drogue parachute from flying aircraft. Technique has uses in industrial process control and in recreational hobby applications.

An ARM Mobile Facility Designed for Marine Deployments

NASA Astrophysics Data System (ADS)

Wiscombe, W. J.

2007-05-01

The U.S. Dept. of Energy's ARM (Atmospheric Radiation Measurements) Program is designing a Mobile Facility exclusively for marine deployments. This marine facility is patterned after ARM's land Mobile Facility, which had its inaugural deployment at Point Reyes, California, in 2005, followed by deployments to Niger in 2006 and Germany in 2007 (ongoing), and a planned deployment to China in 2008. These facilities are primarily intended for the study of clouds, radiation, aerosols, and surface processes with a goal to include these processes accurately in climate models. They are preferably embedded within larger field campaigns which provide context. They carry extensive instrumentation (in several large containers) including: cloud radar, lidar, microwave radiometers, infrared spectrometers, broadband and narrowband radiometers, sonde-launching facilities, extensive surface aerosol measurements, sky imagers, and surface latent and sensible heat flux devices. ARM's Mobile Facilities are designed for 6-10 month deployments in order to capture climatically-relevant datasets. They are available to any scientist, U.S. or international, who wishes to submit a proposal during the annual Spring call. The marine facility will be adapted to, and ruggedized for, the harsh marine environment and will add a scanning two-frequency radar, a boundary-layer wind profiler, a shortwave spectrometer, and aerosol instrumentation adapted to typical marine aerosols like sea salt. Plans also include the use of roving small UAVs, automated small boats, and undersea autonomous vehicles in order to address the point-to-area-average problem which is so crucial for informing climate models. Initial deployments are planned for small islands in climatically- interesting cloud regimes, followed by deployments on oceanic platforms (like decommissioned oil rigs and the quasi-permanent platform of this session's title) and eventually on large ships like car carriers plying routine routes.

Multi-CubeSat Deployment Strategies: How Different Satellite Deployment Schemes Affect Satellite Separation and Detection for Various Types of Constellations and Missions

DTIC Science & Technology

2016-03-24

2009.1 107 of the 158 satellites launched are operated by commercial entities.1 In early 2015, SpaceX and OneWeb each announced their plans to deploy...very large constellations of small satellites ( SpaceX – 4025, OneWeb – 648).1 Each of the OneWeb satellites is planned to weigh around 150 kg,12...while SpaceX expects their satellites to weigh several hundred kilograms each.13 Clearly, the growth in the use of small satellites is causing, and will

Aircraft Surveys of the Beaufort Sea Seasonal Ice Zone

NASA Astrophysics Data System (ADS)

Morison, J.

2016-02-01

The Seasonal Ice Zone Reconnaissance Surveys (SIZRS) is a program of repeated ocean, ice, and atmospheric measurements across the Beaufort-Chukchi sea seasonal sea ice zone (SIZ) utilizing US Coast Guard Arctic Domain Awareness (ADA) flights of opportunity. The SIZ is the region between maximum winter sea ice extent and minimum summer sea ice extent. As such, it contains the full range of positions of the marginal ice zone (MIZ) where sea ice interacts with open water. The increasing size and changing air-ice-ocean properties of the SIZ are central to recent reductions in Arctic sea ice extent. The changes in the interplay among the atmosphere, ice, and ocean require a systematic SIZ observational effort of coordinated atmosphere, ice, and ocean observations covering up to interannual time-scales, Therefore, every year beginning in late Spring and continuing to early Fall, SIZRS makes monthly flights across the Beaufort Sea SIZ aboard Coast Guard C-130H aircraft from USCG Air Station Kodiak dropping Aircraft eXpendable CTDs (AXCTD) and Aircraft eXpendable Current Profilers (AXCP) for profiles of ocean temperature, salinity and shear, dropsondes for atmospheric temperature, humidity, and velocity profiles, and buoys for atmosphere and upper ocean time series. Enroute measurements include IR imaging, radiometer and lidar measurements of the sea surface and cloud tops. SIZRS also cooperates with the International Arctic Buoy Program for buoy deployments and with the NOAA Earth System Research Laboratory atmospheric chemistry sampling program on board the aircraft. Since 2012, SIZRS has found that even as SIZ extent, ice character, and atmospheric forcing varies year-to-year, the pattern of ocean freshening and radiative warming south of the ice edge is consistent. The experimental approach, observations and extensions to other projects will be discussed.

s98e09732

NASA Image and Video Library

1998-11-01

S98-E-09732 (Nov. 1998) --- Closeup view of part of the antenna system for the Teleoperator Control System (TORU) manual docking system on Zarya. This photograph was taken prior to Zarya's deployment. Recent activities showed an indication of a possible failure to deploy of two small antennae elements in the TORU. Accompanying image shows pre-flight closeout closeup image of the second small element.

An Agile Methodology for Implementing Service-Oriented Architecture in Small and Medium Sized Organizations

ERIC Educational Resources Information Center

Laidlaw, Gregory

2013-01-01

The purpose of this study is to evaluate the use of Lean/Agile principles, using action research to develop and deploy new technology for Small and Medium sized enterprises. The research case was conducted at the Lapeer County Sheriff's Department and involves the initial deployment of a Service Oriented Architecture to alleviate the data…

Historical problem areas: Lessons learned for expendable and reusable vehicle propulsion systems

NASA Technical Reports Server (NTRS)

Fester, Dale A.

1991-01-01

The following subject areas are covered: expendable launch vehicle lessons learned, upper stage/transfer vehicle lessons learned, shuttle systems - reuse, and reusable system issues and lessons learned.

Deployable Propulsion, Power and Communications Systems for Solar System Exploration

NASA Technical Reports Server (NTRS)

Johnson, L.; Carr, J.; Boyd, D.

2017-01-01

NASA is developing thin-film based, deployable propulsion, power, and communication systems for small spacecraft that could provide a revolutionary new capability allowing small spacecraft exploration of the solar system. By leveraging recent advancements in thin films, photovoltaics, and miniaturized electronics, new mission-level capabilities will be enabled aboard lower-cost small spacecraft instead of their more expensive, traditional counterparts, enabling a new generation of frequent, inexpensive deep space missions. Specifically, thin-film technologies are allowing the development and use of solar sails for propulsion, small, lightweight photovoltaics for power, and omnidirectional antennas for communication.

ESPA: EELV secondary payload adapter with whole-spacecraft isolation for primary and secondary payloads

NASA Astrophysics Data System (ADS)

Maly, Joseph R.; Haskett, Scott A.; Wilke, Paul S.; Fowler, E. C.; Sciulli, Dino; Meink, Troy E.

2000-04-01

ESPA, the Secondary Payload Adapter for Evolved Expendable Launch Vehicles, addresses two of the major problems currently facing the launch industry: the vibration environment of launch vehicles, and the high cost of putting satellites into orbit. (1) During the 1990s, billions of dollars have been lost due to satellite malfunctions, resulting in total or partial mission failure, which can be directly attributed to vibration loads experienced by payloads during launch. Flight data from several recent launches have shown that whole- spacecraft launch isolation is an excellent solution to this problem. (2) Despite growing worldwide interest in small satellites, launch costs continue to hinder the full exploitation of small satellite technology. Many small satellite users are faced with shrinking budgets, limiting the scope of what can be considered an 'affordable' launch opportunity.

Occupational dreams, choices and aspirations: adolescents' entrepreneurial prospects and orientations.

PubMed

Schmitt-Rodermund, Eva; Vondracek, Fred W

2002-02-01

The present study examined possible early antecedents of entrepreneurship of 14-17-year-old 10th grade students (n=320). We hypothesized that Entrepreneurial Orientation (interest and self-efficacy), together with Willingness to Expend Effort, would be an important predictor of an adolescent's Entrepreneurial Prospects, i.e. prospects of becoming self-employed in the future. Furthermore, personality and the model of self-employed family were expected to predict the level of Entrepreneurial Orientation. The same relationships were investigated separately for students who were more or less willing to expend effort. Among students more willing to expend effort, levels of Entrepreneurial Orientation were higher for those who were conscientious, self-efficient, open to new experiences, and low in agreeableness. Among students less willing to expend effort, a high need for social recognition predicted higher levels of Entrepreneurial Orientation. In addition, parents' model for them was connected with lower levels of Entrepreneurial Orientation. A moderating effect of Willingness to Expend Effort was supported by the results for parents' model and need for social recognition. Copyright 2002 Published by Elsevier Science Ltd on behalf of The Association for Professionals in Services for Adolescents.

Cycom 977-2 Composite Material: Impact Test Results (workshop presentation)

NASA Technical Reports Server (NTRS)

Engle, Carl; Herald, Stephen; Watkins, Casey

2005-01-01

Contents include the following: Ambient (13A) tests of Cycom 977-2 impact characteristics by the Brucenton and statistical method at MSFC and WSTF. Repeat (13A) tests of tested Cycom from phase I at MSFC to expended testing statistical database. Conduct high-pressure tests (13B) in liquid oxygen (LOX) and GOX at MSFC and WSTF to determine Cycom reaction characteristics and batch effect. Conduct expended ambient (13A) LOX test at MSFC and high-pressure (13B) testing to determine pressure effects in LOX. Expend 13B GOX database.

41 CFR 101-26.103-2 - Restriction on personal convenience items.

Code of Federal Regulations, 2012 CFR

2012-07-01

... funds may be expended for pictures, objects of art, plants, or flowers (both artificial and real), or... expended for pictures, objects of art, plants, flowers (both artificial and real), or any other similar...

41 CFR 101-26.103-2 - Restriction on personal convenience items.

Code of Federal Regulations, 2011 CFR

2011-07-01

... funds may be expended for pictures, objects of art, plants, or flowers (both artificial and real), or... expended for pictures, objects of art, plants, flowers (both artificial and real), or any other similar...

41 CFR 101-26.103-2 - Restriction on personal convenience items.

Code of Federal Regulations, 2013 CFR

2013-07-01

... funds may be expended for pictures, objects of art, plants, or flowers (both artificial and real), or... expended for pictures, objects of art, plants, flowers (both artificial and real), or any other similar...

41 CFR 101-26.103-2 - Restriction on personal convenience items.

Code of Federal Regulations, 2014 CFR

2014-07-01

... funds may be expended for pictures, objects of art, plants, or flowers (both artificial and real), or... expended for pictures, objects of art, plants, flowers (both artificial and real), or any other similar...

41 CFR 101-26.103-2 - Restriction on personal convenience items.

Code of Federal Regulations, 2010 CFR

2010-07-01

... funds may be expended for pictures, objects of art, plants, or flowers (both artificial and real), or... expended for pictures, objects of art, plants, flowers (both artificial and real), or any other similar...

VOLTTRON™: Tech-to-Market Best-Practices Guide for Small- and Medium-Sized Commercial Buildings

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

Cort, Katherine A.; Haack, Jereme N.; Katipamula, Srinivas

VOLTTRON™ is an open-source distributed control and sensing platform developed by Pacific Northwest National Laboratory for the U.S. Department of Energy. It was developed to be used by the Office of Energy Efficiency and Renewable Energy to support transactive controls research and deployment activities. VOLTTRON is designed to be an overarching integration platform that could be used to bring together vendors, users, and developers and enable rapid application development and testing. The platform is designed to support modern control strategies, including the use of agent- and transaction-based controls. It also is designed to support the management of a wide rangemore » of applications, including heating, ventilation, and air-conditioning systems; electric vehicles; and distributed-energy and whole-building loads. This report was completed as part of the Building Technologies Office’s Technology-to-Market Initiative for VOLTTRON’s Market Validation and Business Case Development efforts. The report provides technology-to-market guidance and best practices related to VOLTTRON platform deployments and commercialization activities for use by entities serving small- and medium-sized commercial buildings. The report characterizes the platform ecosystem within the small- and medium-sized commercial building market and articulates the value proposition of VOLTTRON for three core participants in this ecosystem: 1) platform owners/adopters, 2) app developers, and 3) end-users. The report also identifies key market drivers and opportunities for open platform deployments in the small- and medium-sized commercial building market. Possible pathways to the market are described—laboratory testing to market adoption to commercialization. We also identify and address various technical and market barriers that could hinder deployment of VOLTTRON. Finally, we provide “best practice” tech-to-market guidance for building energy-related deployment efforts serving small- and medium-sized commercial buildings.« less

SmallSat Spinning Lander with a Raman Spectrometer Payload for Future Ocean Worlds Exploration Missions

NASA Technical Reports Server (NTRS)

Ridenoure, R.; Angel, S. M.; Aslam, S.; Gorius, N.; Hewagama, T.; Nixon, C. A.; Sharma, S.

2017-01-01

We describe an Evolved Expendable Launch Vehicle Secondary Payload Adapter (ESPA)-class SmallSat spinning lander concept for the exploration of Europa or other Ocean World surfaces to ascertain the potential for life. The spinning lander will be ejected from an ESPA ring from an orbiting or flyby spacecraft and will carry on-board a standoff remote Spatial Heterodyne Raman spectrometer (SHRS) and a time resolved laser induced fluorescence spectrograph (TR-LIFS), and once landed and stationary the instruments will make surface chemical measurements. The SHRS and TR-LIFS have no moving parts have minimal mass and power requirements and will be able to characterize the surface and near-surface chemistry, including complex organic chemistry to constrain the ocean composition.

SmallSat Spinning Lander with a Raman Spectrometer Payload for Future Ocean Worlds Exploration Missions

NASA Astrophysics Data System (ADS)

Ridenoure, R.; Angel, S. M.; Aslam, S.; Gorius, N.; Hewagama, T.; Nixon, C. A.; Sharma, S.

2017-09-01

We describe an Evolved Expendable Launch Vehicle Secondary Payload Adapter (ESPA)-class SmallSat spinning lander concept for the exploration of Europa or other Ocean World surfaces to ascertain the potential for life. The spinning lander will be ejected from an ESPA ring from an orbiting or flyby spacecraft and will carry on-board a standoff remote Spatial Heterodyne Raman spectrometer (SHRS) and a time resolved laser induced fluorescence spectrograph (TR-LIFS), and once landed and stationary the instruments will make surface chemical measurements. The SHRS and TR-LIFS have no moving parts have minimal mass and power requirements and will be able to characterize the surface and near-surface chemistry, including complex organic chemistry to constrain the ocean composition.

Space Science

NASA Image and Video Library

1996-12-04

The Mars Pathfinder began the journey to Mars with liftoff atop a Delta II expendable launch vehicle from launch Complex 17B on Cape Canaveral Air Station. The Mars Pathfinder traveled on a direct trajectory to Mars, and arrived there in July 1997. Mars Pathfinder sent a lander and small robotic rover, Sojourner, to the surface of Mars. The primary objective of the mission was to demonstrate a low-cost way of delivering a science package to the surface of Mars using a direct entry, descent and landing with the aid of small rocket engines, a parachute, airbags and other techniques. In addition, landers and rovers of the future will share the heritage of Mars Pathfinder designs and technologies first tested in this mission. Pathfinder also collected invaluable data about the Martian surface.

NanoRacks CubeSat Deployment

NASA Image and Video Library

2014-02-11

ISS038-E-044887 (11 Feb. 2014) --- The Small Satellite Orbital Deployer (SSOD), in the grasp of the Kibo laboratory robotic arm, is photographed by an Expedition 38 crew member on the International Space Station as it deploys a set of NanoRacks CubeSats. The CubeSats program contains a variety of experiments such as Earth observations and advanced electronics testing.

NanoRacks CubeSat Deployment

NASA Image and Video Library

2014-02-11

ISS038-E-044889 (11 Feb. 2014) --- The Small Satellite Orbital Deployer (SSOD), in the grasp of the Kibo laboratory robotic arm, is photographed by an Expedition 38 crew member on the International Space Station as it deploys a set of NanoRacks CubeSats. The CubeSats program contains a variety of experiments such as Earth observations and advanced electronics testing.

NanoRacks CubeSat Deployment

NASA Image and Video Library

2014-02-11

ISS038-E-044890 (11 Feb. 2014) --- The Small Satellite Orbital Deployer (SSOD), in the grasp of the Kibo laboratory robotic arm, is photographed by an Expedition 38 crew member on the International Space Station as it deploys a set of NanoRacks CubeSats. The CubeSats program contains a variety of experiments such as Earth observations and advanced electronics testing.

Lightweight Solar Power for Small Satellites

NASA Technical Reports Server (NTRS)

Nabors, Sammy A.

2015-01-01

The innovation targets small satellites or CubeSats for which conventional deployable arrays are not feasible due to their size, weight and complexity. This novel solar cell array includes a thin and flexible photovoltaic cell applied to an inflatable structure to create a high surface area array for collecting solar energy in a lightweight, simple and deployable structure. The inflatable array, with its high functional surface area, eliminates the need and the mechanisms required to point the system toward the sun. The power density achievable in these small arrays is similar to that of conventional high-power deployable/pointable arrays used on large satellites or space vehicles. Although inflatable solar arrays have been previously considered by others, the arrays involved the use of traditional rigid solar cells. Researchers are currently working with thin film photovoltaics from various suppliers so that the NASA innovation is not limited to any particular solar cell technology. NASA has built prototypes and tested functionality before and after inflation. As shown in the current-voltage currents below, deployment does not damage the cell performance.

Origami-inspired, on-demand deployable and collapsible mechanical metamaterials with tunable stiffness

NASA Astrophysics Data System (ADS)

Zhai, Zirui; Wang, Yong; Jiang, Hanqing

2018-03-01

Origami has been employed to build deployable mechanical metamaterials through folding and unfolding along the crease lines. Deployable metamaterials are usually flexible, particularly along their deploying and collapsing directions, which unfortunately in many cases leads to an unstable deployed state, i.e., small perturbations may collapse the structure along the same deployment path. Here we create an origami-inspired mechanical metamaterial with on-demand deployability and selective collapsibility through energy analysis. This metamaterial has autonomous deployability from the collapsed state and can be selectively collapsed along two different paths, embodying low stiffness for one path and substantially high stiffness for another path. The created mechanical metamaterial yields load-bearing capability in the deployed direction while possessing great deployability and collapsibility. The principle in this work can be utilized to design and create versatile origami-inspired mechanical metamaterials that can find many applications.

Origami-inspired, on-demand deployable and collapsible mechanical metamaterials with tunable stiffness.

PubMed

Zhai, Zirui; Wang, Yong; Jiang, Hanqing

2018-02-27

Origami has been employed to build deployable mechanical metamaterials through folding and unfolding along the crease lines. Deployable metamaterials are usually flexible, particularly along their deploying and collapsing directions, which unfortunately in many cases leads to an unstable deployed state, i.e., small perturbations may collapse the structure along the same deployment path. Here we create an origami-inspired mechanical metamaterial with on-demand deployability and selective collapsibility through energy analysis. This metamaterial has autonomous deployability from the collapsed state and can be selectively collapsed along two different paths, embodying low stiffness for one path and substantially high stiffness for another path. The created mechanical metamaterial yields load-bearing capability in the deployed direction while possessing great deployability and collapsibility. The principle in this work can be utilized to design and create versatile origami-inspired mechanical metamaterials that can find many applications. Copyright © 2018 the Author(s). Published by PNAS.

Origami-inspired, on-demand deployable and collapsible mechanical metamaterials with tunable stiffness

PubMed Central

Zhai, Zirui; Wang, Yong

2018-01-01

Origami has been employed to build deployable mechanical metamaterials through folding and unfolding along the crease lines. Deployable metamaterials are usually flexible, particularly along their deploying and collapsing directions, which unfortunately in many cases leads to an unstable deployed state, i.e., small perturbations may collapse the structure along the same deployment path. Here we create an origami-inspired mechanical metamaterial with on-demand deployability and selective collapsibility through energy analysis. This metamaterial has autonomous deployability from the collapsed state and can be selectively collapsed along two different paths, embodying low stiffness for one path and substantially high stiffness for another path. The created mechanical metamaterial yields load-bearing capability in the deployed direction while possessing great deployability and collapsibility. The principle in this work can be utilized to design and create versatile origami-inspired mechanical metamaterials that can find many applications. PMID:29440441

Baseline spacecraft and mission design for the SP-100 flight experiment

NASA Technical Reports Server (NTRS)

Deininger, William D.; Vondra, Robert J.

1989-01-01

The design and performance of a spacecraft employing arcjet nuclear electric propulsion, suitable for use in the SP-100 Space Reactor Power System (SRPS) Flight Experiment, are outlined. The vehicle design is based on a 93 kWe ammonia arcjet system operating at an experimentally-measured specific impulse of 1030 s and an efficiency of 42 percent. The arcjet/gimbal assemblies, power conditioning subsystem, propellant feed system, propulsion system thermal control, spacecraft diagnostic instrumentation, and the telemetry requirements are described. A 100 kWe SRPS is assumed. The total spacecraft mass is baselined at 5675 kg excluding the propellant and propellant feed system. Four mission scenarios are described which are capable of demonstrating the full capability of the SRPS. The missions considered include spacecraft deployment to possible surveillance platform orbits, a spacecraft storage mission and an orbit raising round trip corresponding to possible orbit transfer vehicle missions. Launches from Kennedy Space Center using the Titan IV expendable launch vehicle are assumed.

Mammalian energetics. Instantaneous energetics of puma kills reveal advantage of felid sneak attacks.

PubMed

Williams, Terrie M; Wolfe, Lisa; Davis, Tracy; Kendall, Traci; Richter, Beau; Wang, Yiwei; Bryce, Caleb; Elkaim, Gabriel Hugh; Wilmers, Christopher C

2014-10-03

Pumas (Puma concolor) live in diverse, often rugged, complex habitats. The energy they expend for hunting must account for this complexity but is difficult to measure for this and other large, cryptic carnivores. We developed and deployed a physiological SMART (species movement, acceleration, and radio tracking) collar that used accelerometry to continuously monitor energetics, movements, and behavior of free-ranging pumas. This felid species displayed marked individuality in predatory activities, ranging from low-cost sit-and-wait behaviors to constant movements with energetic costs averaging 2.3 times those predicted for running mammals. Pumas reduce these costs by remaining cryptic and precisely matching maximum pouncing force (overall dynamic body acceleration = 5.3 to 16.1g) to prey size. Such instantaneous energetics help to explain why most felids stalk and pounce, and their analysis represents a powerful approach for accurately forecasting resource demands required for survival by large, mobile predators. Copyright © 2014, American Association for the Advancement of Science.

KSC-10941f07

NASA Image and Video Library

1997-05-27

Jet Propulsion Laboratory (JPL) technicians finish mounting a thermal model of a radioisotope thermoelectric generator (RTG) on the installation cart which will be used to install the RTG in the Cassini spacecraft at Level 14 of Space Launch Complex 40, Cape Canaveral Air Station. The technicians use the thermal model to practice installation procedures. The three actual RTGs which will provide electrical power to Cassini on its 6.7-mile trip to the Saturnian system, and during its four-year mission at Saturn, are being tested and monitored in the Radioisotope Thermoelectric Generator Storage Building in KSC's Industrial Area. The RTGs use heat from the natural decay of plutonium to generate electric power. RTGs enable spacecraft to operate far from the Sun where solar power systems are not feasible. The RTGs on Cassini are of the same design as those flying on the already deployed Galileo and Ulysses spacecraft. The Cassini mission is targeted for an October 6 launch aboard a Titan IVB/Centaur expendable launch vehicle. Cassini is built and managed for NASA by JPL

Initiation of small-satellite formations via satellite ejector

NASA Astrophysics Data System (ADS)

McMullen, Matthew G

Small satellites can be constructed at a fraction of the cost of a full-size satellite. One full-size satellite can be replaced with a multitude of small satellites, offering expanded area coverage through formation flight. However, the shortcoming to the smaller size is usually a lack of thrusting capabilities. Furthermore, current designs for small satellite deployment mechanisms are only capable of love deployment velocities (on the order of meters per second). Motivated to address this shortcoming, a conceived satellite ejector would offer a significant orbit change by ejecting the satellite at higher deployment velocities (125-200 m/s). Focusing on the applications of the ejector, it is sought to bridge the gap in prior research by offering a method to initiate formation flight. As a precursor to the initiation, the desired orbit properties to initiate the formation are specified in terms of spacing and velocity change vector. From this, a systematic method is developed to find the relationship among velocity change vector, the desired orbit's orientation, and the spacing required to initiate the formation.

J-SSOD 4 Mission

NASA Image and Video Library

2015-09-17

ISS045E014236 (09/17/2015) – A Japanese Small Satellite is deployed from outside the Japanese Experiment Module on Sept. 17, 2015. Two satellites were sent into Earth orbit by the Small Satellite Orbital Deployer. The first satellite is designed to observe the Ultraviolet (UV) spectrum during the Orionid meteor shower in October. The second satellite, sponsored by the University of Brasilia and the Brazilian government, focuses on meteorological data collection.

Increased Small-World Network Topology Following Deployment-Acquired Traumatic Brain Injury Associated with the Development of Post-Traumatic Stress Disorder.

PubMed

Rowland, Jared A; Stapleton-Kotloski, Jennifer R; Dobbins, Dorothy L; Rogers, Emily; Godwin, Dwayne W; Taber, Katherine H

2018-05-01

Cross-sectional and longitudinal studies in active duty and veteran cohorts have both demonstrated that deployment-acquired traumatic brain injury (TBI) is an independent risk factor for developing post-traumatic stress disorder (PTSD), beyond confounds such as combat exposure, physical injury, predeployment TBI, and pre-deployment psychiatric symptoms. This study investigated how resting-state brain networks differ between individuals who developed PTSD and those who did not following deployment-acquired TBI. Participants included postdeployment veterans with deployment-acquired TBI history both with and without current PTSD diagnosis. Graph metrics, including small-worldness, clustering coefficient, and modularity, were calculated from individually constructed whole-brain networks based on 5-min eyes-open resting-state magnetoencephalography (MEG) recordings. Analyses were adjusted for age and premorbid IQ. Results demonstrated that participants with current PTSD displayed higher levels of small-worldness, F(1,12) = 5.364, p < 0.039, partial eta squared = 0.309, and Cohen's d = 0.972, and clustering coefficient, F(1, 12) = 12.204, p < 0.004, partial eta squared = 0.504, and Cohen's d = 0.905, than participants without current PTSD. There were no between-group differences in modularity or the number of modules present. These findings are consistent with a hyperconnectivity hypothesis of the effect of TBI history on functional networks rather than a disconnection hypothesis, demonstrating increased levels of clustering coefficient rather than a decrease as might be expected; however, these results do not account for potential changes in brain structure. These results demonstrate the potential pathological sequelae of changes in functional brain networks following deployment-acquired TBI and represent potential neurobiological changes associated with deployment-acquired TBI that may increase the risk of subsequently developing PTSD.

[The use of the new loads of expendable medical supplies by the medical service of the Armed Forces].

PubMed

Miroshnichenko, Iu V; Bunin, S A; Grebeniuk, A N; Kononov, V N; Sidorov, D A

2014-09-01

The new loads of expendable medical supplies adopted by the Armed Forces of the Russian Federation and included into regulating documents are the most important elements of the authorized equipment system. Nine loads of expendable medical supplies, combined into two classification groups, are provided for the medical service. The use of these loads improves the effectiveness of medical supply for all stages of medical evacuation, medical continuity during medical and evacuation procedures and allows to deliver medical aid to patients on the basis of modern and innovative medical technologies.

Efficient structures for geosynchronous spacecraft solar arrays. Phase 1, 2 and 3

NASA Astrophysics Data System (ADS)

Adams, L. R.; Hedgepeth, J. M.

1981-09-01

Structural concepts for deploying and supporting lightweight solar-array blankets for geosynchronous electrical power are evaluated. It is recommended that the STACBEAM solar-array system should be the object of further study and detailed evaluation. The STACBEAM system provides high stiffness at low mass, and with the use of a low mass deployment mechanism, full structural properties can be maintained throughout deployment. The stowed volume of the STACBEAM is acceptably small, and its linear deployment characteristic allows periodic attachments to the solar-array blanket to be established in the stowed configuration and maintained during deployment.

Efficient structures for geosynchronous spacecraft solar arrays. Phase 1, 2 and 3

NASA Technical Reports Server (NTRS)

Adams, L. R.; Hedgepeth, J. M.

1981-01-01

Structural concepts for deploying and supporting lightweight solar-array blankets for geosynchronous electrical power are evaluated. It is recommended that the STACBEAM solar-array system should be the object of further study and detailed evaluation. The STACBEAM system provides high stiffness at low mass, and with the use of a low mass deployment mechanism, full structural properties can be maintained throughout deployment. The stowed volume of the STACBEAM is acceptably small, and its linear deployment characteristic allows periodic attachments to the solar-array blanket to be established in the stowed configuration and maintained during deployment.

NanoRacks CubeSat Deployment

NASA Image and Video Library

2014-02-11

ISS038-E-044883 (11 Feb. 2014) --- The Small Satellite Orbital Deployer (SSOD), in the grasp of the Kibo laboratory robotic arm, is photographed by an Expedition 38 crew member on the International Space Station as it begins the deployment of a set of NanoRacks CubeSats. The CubeSats program contains a variety of experiments such as Earth observations and advanced electronics testing.

NanoRacks CubeSat Deployment

NASA Image and Video Library

2014-02-11

ISS038-E-044994 (11 Feb. 2014) --- The Small Satellite Orbital Deployer (SSOD), in the grasp of the Kibo laboratory robotic arm, is photographed by an Expedition 38 crew member on the International Space Station prior to the deployment of a set of NanoRacks CubeSats. The CubeSats program contains a variety of experiments such as Earth observations and advanced electronics testing.

Development of a Deployable Nonmetallic Boom for Reconfigurable Systems of Small Spacecraft

NASA Technical Reports Server (NTRS)

Rehnmark, Fredrik; Pryor, Mark; Holmes, Buck; Schaechter, David; Pedreiro, Nelson; Carrington, Connie

2007-01-01

In 2005, NASA commenced Phase 1 of the Modular Reconfigurable High Energy Technology Demonstrator (MRHE) program to investigate reconfigurable systems of small spacecraft. During that year, Lockheed Martin's Advanced Technology Center (ATC) led an accelerated effort to develop a 1-g MRHE concept demonstration featuring robotic spacecraft simulators equipped with docking mechanisms and deployable booms. The deployable boom built for MRHE was the result of a joint effort in which ATK was primarily responsible for developing and fabricating the Collapsible Rollable Tube (CRT patent pending) boom while Lockheed Martin designed and built the motorized Boom Deployment Mechanism (BDM) under a concurrent but separate IR&D program. Tight coordination was necessary to meet testbed integration and functionality requirements. This paper provides an overview of the CRT boom and BDM designs and presents preliminary results of integration and testing to support the MRHE demonstration.

Observed ocean thermal response to Hurricanes Gustav and Ike

NASA Astrophysics Data System (ADS)

Meyers, Patrick C.; Shay, Lynn K.; Brewster, Jodi K.; Jaimes, Benjamin

2016-01-01

The 2008 Atlantic hurricane season featured two hurricanes, Gustav and Ike, crossing the Gulf of Mexico (GOM) within a 2 week period. Over 400 airborne expendable bathythermographs (AXBTs) were deployed in a GOM field campaign before, during, and after the passage of Gustav and Ike to measure the evolving upper ocean thermal structure. AXBT and drifter deployments specifically targeted the Loop Current (LC) complex, which was undergoing an eddy-shedding event during the field campaign. Hurricane Gustav forced a 50 m deepening of the ocean mixed layer (OML), dramatically altering the prestorm ocean conditions for Hurricane Ike. Wind-forced entrainment of colder thermocline water into the OML caused sea surface temperatures to cool by over 5°C in GOM common water, but only 1-2°C in the LC complex. Ekman pumping and a near-inertial wake were identified by fluctuations in the 20°C isotherm field observed by AXBTs and drifters following Hurricane Ike. Satellite estimates of the 20° and 26°C isotherm depths and ocean heat content were derived using a two-layer model driven by sea surface height anomalies. Generally, the satellite estimates correctly characterized prestorm conditions, but the two-layer model inherently could not resolve wind-forced mixing of the OML. This study highlights the importance of a coordinated satellite and in situ measurement strategy to accurately characterize the ocean state before, during, and after hurricane passage, particularly in the case of two consecutive storms traveling through the same domain.

Simple, Robust Cryogenic Propellant Depot for Near Term Applications

NASA Technical Reports Server (NTRS)

McLean, Christopher; Pitchford, Brian; Mustafi, Shuvo; Wollen, Mark; Walls, Laurie; Schmidt, Jeff

2011-01-01

The ability to refuel cryogenic propulsion stages on-orbit provides an innovative paradigm shift for space transportation supporting National Aeronautics and Space Administration s (NASA) Exploration program as well as deep space robotic, national security and commercial missions. Refueling enables large beyond low Earth orbit (LEO) missions without requiring super heavy lift vehicles that must continuously grow to support increasing mission demands as America s exploration transitions from early Lagrange point missions to near Earth objects (NEO), the lunar surface and eventually Mars. Earth-to-orbit launch can be optimized to provide competitive, cost-effective solutions that allow sustained exploration. This paper describes an experimental platform developed to demonstrate the major technologies required for fuel depot technology. This test bed is capable of transferring residual liquid hydrogen (LH2) or liquid oxygen (LO2) from a Centaur upper stage, and storage in a secondary tank for up to one year on-orbit. A dedicated, flight heritage spacecraft bus is attached to an Evolved Expendable Launch Vehicle (EELV) Secondary Payload Adapter (ESPA) ring supporting experiments and data collection. This platform can be deployed as early as Q1 2013. The propellant depot design described in this paper can be deployed affordably this decade supporting missions to Earth-Moon Lagrange points and lunar fly by. The same depot concept can be scaled up to support more demanding missions and launch capabilities. The enabling depot design features, technologies and concept of operations are described.

Advanced Commercial Buildings Initiative Final Report

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

Roberts, Sydney G.

The Southface Advanced Commercial Buildings Initiative has developed solutions to overcome market barriers to energy reductions in small commercial buildings by building on the success of four local and Southeast regional energy efficiency deployment programs. These programs address a variety of small commercial building types, efficiency levels, owners, facility manager skills and needs for financing. The deployment programs also reach critical private sector, utility, nonprofit and government submarkets, and have strong potential to be replicated at scale. During the grant period, 200 small commercial buildings participated in Southface-sponsored energy upgrade programs, saving 166,736,703 kBtu of source energy.

The U.S. Evolved Expendable Launch Vehicle (EELV) programs : Quarterly Launch Report : special report

DOT National Transportation Integrated Search

1997-01-01

The Evolved Expendable Launch Vehicle (EELV) Program is a Department of Defense technology-development program managed by the Air Force. The program is intended to produce an improved launch vehicle family for government use. The EELV will replace th...

Overview of Advanced Space Propulsion Activities in the Space Environmental Effects Team at MSFC

NASA Technical Reports Server (NTRS)

Edwards, David; Carruth, Ralph; Vaughn, Jason; Schneider, Todd; Kamenetzky, Rachel; Gray, Perry

2000-01-01

Exploration of our solar system, and beyond, requires spacecraft velocities beyond our current technological level. Technologies addressing this limitation are numerous. The Space Environmental Effects (SEE) Team at the Marshall Space Flight Center (MSFC) is focused on three discipline areas of advanced propulsion; Tethers, Beamed Energy, and Plasma. This presentation will give an overview of advanced propulsion related activities in the Space Environmental Effects Team at MSFC. Advancements in the application of tethers for spacecraft propulsion were made while developing the Propulsive Small Expendable Deployer System (ProSEDS). New tether materials were developed to meet the specifications of the ProSEDS mission and new techniques had to be developed to test and characterize these tethers. Plasma contactors were developed, tested and modified to meet new requirements. Follow-on activities in tether propulsion include the Air-SEDS activity. Beamed energy activities initiated with an experimental investigation to quantify the momentum transfer subsequent to high power, 5J, ablative laser interaction with materials. The next step with this experimental investigation is to quantify non-ablative photon momentum transfer. This step was started last year and will be used to characterize the efficiency of solar sail materials before and after exposure to Space Environmental Effects (SEE). Our focus with plasma, for propulsion, concentrates on optimizing energy deposition into a magnetically confined plasma and integration of measurement techniques for determining plasma parameters. Plasma confinement is accomplished with the Marshall Magnetic Mirror (M3) device. Initial energy coupling experiments will consist of injecting a 50 amp electron beam into a target plasma. Measurements of plasma temperature and density will be used to determine the effect of changes in magnetic field structure, beam current, and gas species. Experimental observations will be compared to predictions from computer modeling.

Autonomous Adaptive Low-Power Instrument Platform (AAL-PIP) for remote high latitude geospace data collection

NASA Astrophysics Data System (ADS)

Clauer, C. R.; Kim, H.; Deshpande, K.; Xu, Z.; Weimer, D.; Musko, S.; Crowley, G.; Fish, C.; Nealy, R.; Humphreys, T. E.; Bhatti, J. A.; Ridley, A. J.

2014-06-01

We present the development considerations and design for ground based instrumentation that is being deployed on the East Antarctic Plateau along a 40° magnetic meridian chain to investigate interhemispheric magnetically conjugate geomagnetic coupling and other space weather related phenomena. The stations are magnetically conjugate to geomagnetic stations along the west coast of Greenland. The autonomous adaptive low-power instrument platforms being deployed in the Antarctic are designed to operate unattended in remote locations for at least 5 years. They utilize solar power and AGM storage batteries for power, two-way Iridium satellite communication for data acquisition and program/operation modification, support fluxgate and induction magnetometers as well as dual-frequency gps receiver and an HF radio experiment. Size and weight considerations are considered to enable deployment by a small team using small aircraft. Considerable experience has been gained in the development and deployment of remote polar instrumentation that is reflected in the present generation of instrumentation discussed here. We conclude with the lessons learned from our experience in the design, deployment and operation of remote polar instrumentation.

An autonomous adaptive low-power instrument platform (AAL-PIP) for remote high-latitude geospace data collection

NASA Astrophysics Data System (ADS)

Clauer, C. R.; Kim, H.; Deshpande, K.; Xu, Z.; Weimer, D.; Musko, S.; Crowley, G.; Fish, C.; Nealy, R.; Humphreys, T. E.; Bhatti, J. A.; Ridley, A. J.

2014-10-01

We present the development considerations and design for ground-based instrumentation that is being deployed on the East Antarctic Plateau along a 40° magnetic meridian chain to investigate interhemispheric magnetically conjugate geomagnetic coupling and other space-weather-related phenomena. The stations are magnetically conjugate to geomagnetic stations along the west coast of Greenland. The autonomous adaptive low-power instrument platforms being deployed in the Antarctic are designed to operate unattended in remote locations for at least 5 years. They utilize solar power and AGM storage batteries for power, two-way Iridium satellite communication for data acquisition and program/operation modification, support fluxgate and induction magnetometers as well as a dual-frequency GPS receiver and a high-frequency (HF) radio experiment. Size and weight considerations are considered to enable deployment by a small team using small aircraft. Considerable experience has been gained in the development and deployment of remote polar instrumentation that is reflected in the present generation of instrumentation discussed here. We conclude with the lessons learned from our experience in the design, deployment and operation of remote polar instrumentation.

U.S. Service Member Deployment in Response to the Ebola Crisis: The Psychological Perspective.

PubMed

Sipos, Maurice L; Kim, Paul Y; Thomas, Stephen J; Adler, Amy B

2018-03-01

In the fall of 2014, the United States and other nations responded to the worst outbreak of the Ebola virus disease in history. As part of this effort, U.S. service members deployed to West Africa to support a spectrum of activities that did not involve direct patient care. Although previous studies identified the psychological impact of responding to an outbreak, these studies were limited to retrospective data, small sample sizes, and medical personnel. The goals of the present study were to (a) document the mental health and well-being of troops deploying in response to an infectious disease outbreak; (b) identify their stressors, attitudes toward deployment, and health risk concerns; and (c) understand the role of combat experience in adjusting to these types of missions. Study participants at both pre- and during deployment were active duty U.S. soldiers in a combat aviation battalion from a large U.S. military installation. U.S. soldiers were surveyed (n = 251) 3 wk before deploying to Liberia (October 2014) and surveyed again during their deployment (February 2015; n = 173). Participants were primarily male (86.1%), junior ranking (56.0%), and just over half had previous combat deployment experience (51.2%). Surveys were anonymous and not linked to one another over time. Overall rates of mental health problems were low (2.4% at pre-deployment and 5.8% during deployment), whereas sleep problems were reported by 4.9% at pre-deployment and 12% during deployment. At pre-deployment, top stressors focused on health threats; fewer stressors were reported during deployment. Soldiers were relatively less concerned about contracting Ebola than other more prevalent diseases. Soldiers with combat experience reported more somatic and sleep problems at pre-deployment than those without previous combat experience. There were no significant differences during deployment between those with and without previous combat experience. Overall, a small proportion of respondents reported significant rates of mental health problems. In contrast, sleep problems were reported by 12% during deployment. In terms of attitudes toward the mission, the vast majority reported that they knew what to do to protect themselves from disease and that they understood the potential risk involved. The study also confirmed previous findings that soldiers with previous combat experience had more somatic symptoms at pre-deployment than those without, although this distinction appeared limited to the pre-deployment phase. Results can be used to address anxiety by personnel during pre-deployment and to inform leadership preparing personnel to deploy in response to future infectious disease outbreaks.

CUBES Project Support

NASA Technical Reports Server (NTRS)

Jenkins, Kenneth T., Jr.

2012-01-01

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

SSOD on JEM RMS

NASA Image and Video Library

2012-10-04

ISS033-E-009269 (4 Oct. 2012) --- A Small Satellite Orbital Deployer (SSOD) attached to the Japanese module’s robotic arm is featured in this image photographed by an Expedition 33 crew member on the International Space Station. Several tiny satellites were released outside the Kibo laboratory using the SSOD on Oct. 4, 2012. Japan Aerospace Exploration Agency astronaut Aki Hoshide, flight engineer, set up the satellite deployment gear inside the lab and placed it in the Kibo airlock. The Japanese robotic arm then grappled the deployment system and its satellites from the airlock for deployment.

20 CFR 437.20 - Standards for financial management systems.

Code of Federal Regulations, 2010 CFR

2010-04-01

... 20 Employees' Benefits 2 2010-04-01 2010-04-01 false Standards for financial management systems... Financial Administration § 437.20 Standards for financial management systems. (a) A State must expend and account for grant funds in accordance with State laws and procedures for expending and accounting for its...

77 FR 11418 - Airworthiness Directives; Various Transport Category Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-02-27

... oxygen generators in the lavatories until the generator oxygen supply is expended, or removing the oxygen generator(s); and, for each chemical oxygen generator, after the generator is expended (or removed... Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: Deliver to Mail...

77 FR 38000 - Airworthiness Directives; Various Transport Category Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-06-26

... generators in the lavatories until the generator oxygen supply is expended, or removing the oxygen generator(s); and, for each chemical oxygen generator, after the generator is expended (or removed), removing... AD was prompted by reports that the current design of the oxygen generators presents a hazard that...

Toward understanding the ecological impact of transportation corridors

Treesearch

Victoria J. Bennett; Winston P. Smith; Matthew G. Betts

2011-01-01

Transportation corridors (notably roads) affect wildlife habitat, populations, and entire ecosystems. Considerable effort has been expended to quantify direct effects of roads on wildlife populations and ecological communities and processes. Much less effort has been expended toward quantifying indirect effects. In this report, we provide a comprehensive review of road...

10 CFR 600.135 - Supplies and other expendable property.

Code of Federal Regulations, 2010 CFR

2010-01-01

... acquisition. If there is a residual inventory of unused supplies exceeding $5000 in total aggregate value upon... 10 Energy 4 2010-01-01 2010-01-01 false Supplies and other expendable property. 600.135 Section... Education, Hospitals, and Other Nonprofit Organizations Post-Award Requirements § 600.135 Supplies and other...

45 CFR 2543.35 - Supplies and other expendable property.

Code of Federal Regulations, 2010 CFR

2010-10-01

... acquisition. If there is a residual inventory of unused supplies exceeding $5,000 in total aggregate value... 45 Public Welfare 4 2010-10-01 2010-10-01 false Supplies and other expendable property. 2543.35... OTHER NON-PROFIT ORGANIZATIONS Post-Award Requirements Property Standards § 2543.35 Supplies and other...

49 CFR 110.70 - Financial administration.

Code of Federal Regulations, 2010 CFR

2010-10-01

... 49 Transportation 2 2010-10-01 2010-10-01 false Financial administration. 110.70 Section 110.70... PUBLIC SECTOR TRAINING AND PLANNING GRANTS § 110.70 Financial administration. (a) A State must expend and account for grant funds in accordance with State laws and procedures for expending and accounting for its...

29 CFR 778.217 - Reimbursement for expenses.

Code of Federal Regulations, 2011 CFR

2011-07-01

... expended by an employee in purchasing supplies, tools, materials, or equipment on behalf of his employer... approximate amount expended by an employee, who is traveling “over the road” on his employer's business, for... expenses, such as taxicab fares, incurred while traveling on the employer's business. (4) “Supper money”, a...

Upper Ocean Momentum Response to Hurricane Forcing

NASA Astrophysics Data System (ADS)

Shay, L. K.; Jaimes de la Cruz, B.; Uhlhorn, E.

2016-02-01

The oceanic velocity response of the Loop Current (LC) and its complex warm and cold eddy field to hurricanes is critical to evaluate coupled operational forecast models. Direct velocity measurements of ocean current (including temperature and salinity) fields during hurricanes are needed to understand these complex interaction processes. As part of NOAA Intensity Forecasting Experiments, airborne expendable bathythermographs (AXBT), Conductivity-Temperature-Depth (AXCTD), and Current Profilers (AXCP) probes have been deployed in several major hurricanes from the NOAA research aircraft over the Gulf. Over the last decade, profilers were deployed in Isidore and Lili, Katrina and Rita, Gustav and Ike and Isaac-all of which interacted with the LC and warm eddy field. Central to these interactions under hurricane forcing is the level of sea surface cooling (typically about 1oC) induced by the wind-forced current response in the LC complex. Vertical current shear and instability (e.g., Richardson number) at the base of the oceanic mixed layer is often arrested by the strong upper ocean currents associated with the LC of 1 to 1.5 m s-1. By contrast, the SST cooling response often exceeds 3.5 to 4oC away from the LC complex in the Gulf Common Water. A second aspect of the interaction between the surface wind field and the LC is that the vorticity of the background flows (based on altimetry) enhances upwelling and downwelling processes by projecting onto the wind stress. This process modulates vertical mixing process at depth by keeping the Richardson numbers above criticality. Thus, the ocean cooling is less in the LC complex allowing for a higher and more sustained enthalpy flux as determined from global positioning system sondes deployed in these storms. This level of cooling (or lack thereof) in the LC complex significant impacts hurricane intensity that often reaches severe status which affects offshore structures and coastal communities at landfall in the northern Gulf of Mexico.

Small aperture seismic arrays for studying planetary interiors and seismicity

NASA Astrophysics Data System (ADS)

Schmerr, N. C.; Lekic, V.; Fouch, M. J.; Panning, M. P.; Siegler, M.; Weber, R. C.

2017-12-01

Seismic arrays are a powerful tool for understanding the interior structure and seismicity across objects in the Solar System. Given the operational constraints of ground-based lander investigations, a small aperture seismic array can provide many of the benefits of a larger-scale network, but does not necessitate a global deployment of instrumentation. Here we define a small aperture array as a deployment of multiple seismometers, with a separation between instruments of 1-1000 meters. For example, small aperture seismic arrays have been deployed on the Moon during the Apollo program, the Active Seismic Experiments of Apollo 14 and 16, and the Lunar Seismic Profiling Experiment deployed by the Apollo 17 astronauts. Both were high frequency geophone arrays with spacing of 50 meters that provided information on the layering and velocity structure of the uppermost kilometer of the lunar crust. Ideally such arrays would consist of instruments that are 3-axis short period or broadband seismometers. The instruments must have a sampling rate and frequency range sensitivity capable of distinguishing between waves arriving at each station in the array. Both terrestrial analogs and the data retrieved from the Apollo arrays demonstrate the efficacy of this approach. Future opportunities exist for deployment of seismic arrays on Europa, asteroids, and other objects throughout the Solar System. Here we will present both observational data and 3-D synthetic modeling results that reveal the sensing requirements and the primary advantages of a small aperture seismic array over single station approach. For example, at the smallest apertures of < 1 m, we constrain that sampling rates must exceed 500 Hz and instrument sensitivity must extend to 100 Hz or greater. Such advantages include the improved ability to resolve the location of the sources near the array through detection of backazimuth and differential timing between stations, determination of the small-scale structure (layering, scattering bodies, density and velocity variations) in the vicinity of the array, as well as the ability to improve the signal to noise ratio of distant body waves by additive methods such as stacking and velocity-slowness analysis. These results will inform future missions on the surfaces of objects throughout the Solar System.

Enhancing the NASA Expendable Launch Vehicle Payload Safety Review Process Through Program Activities

NASA Technical Reports Server (NTRS)

Palo, Thomas E.

2007-01-01

The safety review process for NASA spacecraft flown on Expendable Launch Vehicles (ELVs) has been guided by NASA-STD 8719.8, Expendable Launch Vehicle Payload Safety Review Process Standard. The standard focused primarily on the safety approval required to begin pre-launch processing at the launch site. Subsequent changes in the contractual, technical, and operational aspects of payload processing, combined with lessons-learned supported a need for the reassessment of the standard. This has resulted in the formation of a NASA ELV Payload Safety Program. This program has been working to address the programmatic issues that will enhance and supplement the existing process, while continuing to ensure the safety of ELV payload activities.

Small Projects Rapid Integration and Test Environment (SPRITE): Application for Increasing Robutness

NASA Technical Reports Server (NTRS)

Lee, Ashley; Rakoczy, John; Heather, Daniel; Sanders, Devon

2013-01-01

Over the past few years interest in the development and use of small satellites has rapidly gained momentum with universities, commercial, and government organizations. In a few years we may see networked clusters of dozens or even hundreds of small, cheap, easily replaceable satellites working together in place of the large, expensive and difficult-to-replace satellites now in orbit. Standards based satellite buses and deployment mechanisms, such as the CubeSat and Poly Pico-satellite Orbital Deployer (P-POD), have stimulated growth in this area. The use of small satellites is also proving to be a cost effective capability in many areas traditionally dominated by large satellites, though many challenges remain. Currently many of these small satellites undergo very little testing prior to flight. As these small satellites move from technology demonstration and student projects toward more complex operational assets, it is expected that the standards for verification and validation will increase.

Deployment Mechanism for the Space Technology 5 Micro Satellite

NASA Technical Reports Server (NTRS)

Rossoni, Peter; Cooperrider, Caner; Durback, Gerard

2004-01-01

Space Technology 5 (ST5) is a technology mission that will send three spin-stabilized, 25-kg satellites into a highly elliptical Earth orbit. Each of these satellites must be deployed separately from the same launch vehicle with a spin rate of 3.4 rads (32.4 rpm). Because of the satellite's small size and the requirement to achieve its mission spin rate on deploy, typical spin table, pyrotechnic deployment devices or spin up thrusters could not be used. Instead, this new mechanism design employs a "Frisbee" spin up strategy with a shape memory alloy actuated Pinpuller to deploy each satellite. The mechanism has undergone several design and test iterations and has been successfully qualified for flight.

Deployment Mechanism for the Space Technology 5 Micro Satellite

NASA Technical Reports Server (NTRS)

Rossoni, Peter; Cooperrider, Caner; Durback, Gerard

2004-01-01

Space Technology 5 (ST5) is a technology mission that will send three spin-stabilized, 25-kg satellites into a highly elliptical Earth orbit. Each of these satellites must be deployed separately from the same launch vehicle with a spin rate of 3.4 rad/s (32.4 rpm). Because of the satellite's small size and the requirement to achieve its mission spin rate on deploy, typical spin table, pyrotechnic deployment devices or spin up thrusters could not be used. Instead, this new mechanism design employs a 'Frisbee' spin up strategy with a shape memory alloy actuated Pinpuller to deploy each satellite. The mechanism has undergone several design and test iterations and has been successfully qualified for flight.

ADEPT - A Mechanically Deployable Entry System Technology in Development at NASA

NASA Technical Reports Server (NTRS)

Venkatapathy, Ethiraj; Wercinski, Paul; Cassell, Alan; Smith, Brandon; Yount, Bryan

2016-01-01

The proposed presentation will give an overview of a mechanically deployable entry system concept development with a comprehensive summary of the ground tests and design development completed to-date, and current plans for a small-scale flight test in the near future.

76 FR 72218 - National Environmental Policy Act; NASA Routine Payloads on Expendable Launch Vehicles

Federal Register 2010, 2011, 2012, 2013, 2014

2011-11-22

...; NASA Routine Payloads on Expendable Launch Vehicles AGENCY: National Aeronautics and Space... (CEQ) Regulations for Implementing the Procedural Provisions of NEPA (40 CFR parts 1500-1508), and NASA policy and procedures (14 CFR part 1216 subpart 1216.3), NASA has made a Finding of No Significant Impact...

21 CFR 1403.20 - Standards for financial management systems.

Code of Federal Regulations, 2010 CFR

2010-04-01

... 21 Food and Drugs 9 2010-04-01 2010-04-01 false Standards for financial management systems. 1403... Financial Administration § 1403.20 Standards for financial management systems. (a) A State must expend and account for grant funds in accordance with State laws and procedures for expending and accounting for its...

System Level Aerothermal Testing for the Adaptive Deployable Entry and Placement Technology (ADEPT)

NASA Technical Reports Server (NTRS)

Cassell, Alan; Gorbunov, Sergey; Yount, Bryan; Prabhu, Dinesh; de Jong, Maxim; Boghozian, Tane; Hui, Frank; Chen, Y.-K.; Kruger, Carl; Poteet, Carl;

Modelling of energy expended by free swimming spermatozoa in temperature-dependent viscous semen.

PubMed

Foo, Jong Yong Abdiel

2010-01-01

Derived models of fertilization kinetics have relied upon estimates of the swimming velocity of spermatozoa from the insemination site to a fallopian tube. However, limited derivations are available describing the probability and energy expended when spermatozoa collide with one another. An analytic approach of spermatozoon motion in a linear viscoelastic fluid is adopted to simplify the derivation. The complex kinematics of motion of an inextensible flagellum is modelled as planar flagellar wave of small amplitude. In humans, a temperature difference is expected between the cooler tubal isthmus and the warmer tubal ampulla. Thus, fluidic characteristics of semen such as viscosity can vary along the female reproductive tract. The results suggest that the probability of spermatozoa colliding in relatively lower viscous semen increases by 64.87% for a 0.5 degrees C surge in temperature. Moreover, this increases for a denser concentration of spermatozoa due to the limited semen volume available to manoeuvre. In addition, the propulsive forces and shear stress were 39.35% lower in less viscous semen due to an increase in temperature of only 0.5 degrees C. Hence, the described derivations herein can assist in the understanding of work done by a normal motile spermatozoon in a pool of semen.

Design and Qualification of a SmallSat Stepper Motor Driver, Flight Results On-Board the Yes2 Satellite

NASA Astrophysics Data System (ADS)

Graczyk, R.; Kruijff, M.; Spiliotopoulos, I.

2008-08-01

Drivers for stepper motors are a commonly required critical technology for small satellites. This paper highlights the stepper driver design, test, and mission performance for the second Young Engineers' Satellite (YES2). The unit integrates the required digital and power parts and was developed with generic low-cost satellite applications in mind. One of the key mechanisms in YES2 is a friction brake containing a stepper motor which is in turn controlled by a stepper driver. The friction brake was used to control the deployment speed such that the tether deployed according to a pre-described two-stage trajectory. The stepper driver was itself commanded by an on-board computer that used tether deployment data as input and provided the new required position of the brake as output. The stepper driver design was driven by the requirements of a low cost yet reliable redundant design, use of a micro-controller and software commonly known to students, very small dimension, good thermal behavior and capable of delivering high torque at high efficiency. The work followed as much as possible ESA's design standards and was qualified by electromagnetic compatibility, thermal vacuum and shaker tests. It was functionally tested in real-time ground tether deployments. Mission data shows the stepper driver performed well in flight.

Vehicle safety : technologies, challenges, and research and development expenditures for advanced air bags

DOT National Transportation Integrated Search

2001-06-01

One hundred seventy five fatalities - primarily children and small women - have been attributed to the deployment of an air bag in relatively low-speed crashes as of April 2001. Advanced air bag systems tailor the deployment of the bags to the charac...

Tony Jimenez | NREL

Science.gov Websites

pre-feasibility analysis; wind data analysis; the small wind turbine certification process; economic Regional Test Center effort, analysis of the potential economic impact of large-scale MHK deployment off pre-feasibility analysis. Tony is an engineer officer in the Army Reserve. He has deployed twice

NanoRacks CubeSat Deployment

NASA Image and Video Library

2014-02-11

ISS038-E-045009 (11 Feb. 2014) --- The Small Satellite Orbital Deployer (SSOD), in the grasp of the Kibo laboratory robotic arm, is photographed by an Expedition 38 crew member on the International Space Station as it deploys a set of NanoRacks CubeSats. The CubeSats program contains a variety of experiments such as Earth observations and advanced electronics testing. Station solar array panels, Earth's horizon and the blackness of space provide the backdrop for the scene.

Small Project Rapid Integration and Test Environment (SPRITE) An Innovation Space for Small Projects Design, Development, Integration, and Test

NASA Technical Reports Server (NTRS)

Lee, Ashley; Rackoczy, John; Heater, Daniel; Sanders, Devon; Tashakkor, Scott

2013-01-01

Over the past few years interest in the development and use of small satellites has rapidly gained momentum with universities, commercial, and government organizations. In a few years we may see networked clusters of dozens or even hundreds of small, cheap, easily replaceable satellites working together in place of the large, expensive and difficult-to-replace satellites now in orbit. Standards based satellite buses and deployment mechanisms, such as the CubeSat and Poly Pico-satellite Orbital Deployer (P-POD), have stimulated growth in this area. The use of small satellites is also proving to be a cost effective capability in many areas traditionally dominated by large satellites, though many challenges remain. Currently many of these small satellites undergo very little testing prior to flight. As these small satellites move from technology demonstration and student projects toward more complex operational assets, it is expected that the standards for verification and validation will increase.

Long-Term Observations of Ocean Biogeochemistry with Nitrate and Oxygen Sensors in Apex Profiling Floats

NASA Astrophysics Data System (ADS)

Johnson, K. S.; Coletti, L.; Jannasch, H.; Martz, T.; Swift, D.; Riser, S.

2008-12-01

Long-term, autonomous observations of ocean biogeochemical cycles are now feasible with chemical sensors in profiling floats. These sensors will enable decadal-scale observations of trends in global ocean biogeochemical cycles. Here, we focus on measurements on nitrate and dissolved oxygen. The ISUS (In Situ Ultraviolet Spectrophotometer) optical nitrate sensor has been adapted to operate in a Webb Research, Apex profiling float. The Apex float is of the type used in the Argo array and is designed for multi-year, expendable deployments in the ocean. Floats park at 1000 m depth and make 60 nitrate and oxygen measurements at depth intervals ranging from 50 m below 400 m to 5 m in the upper 100 m as they profile to the surface. All data are transmitted to shore using the Iridium telemetry system and they are available on the Internet in near-real time. Floats equipped with ISUS and an Aanderaa oxygen sensor are capable of making 280 vertical profiles from 1000 m. At a 5 day cycle time, the floats should have nearly a four year endurance. Three floats have now been deployed at the Hawaii Ocean Time series station (HOT), Ocean Station Papa (OSP) in the Gulf of Alaska and at 50 South, 30 East in the Southern Ocean. Two additional floats are designated for deployment at the Bermuda Atlantic Time Series station (BATS) and in the Drake Passage. The HOT float has made 56 profiles over 260 days and should continue operating for 3 more years. Nitrate concentrations are in excellent agreement with the long-term mean observed at HOT. No significant long-term drift in sensor response has occurred. A variety of features have been observed in the HOT nitrate data that are linked to contemporaneous changes in oxygen production and mesoscale dynamics. The impacts of these features will be briefly described. The Southern Ocean float has operated for 200 days and is now observing reinjection of nitrate into surface waters as winter mixing occurs(surface nitrate > 24 micromolar). We expect that the OSP and Southern Ocean floats will provide a quantitative measurement of the timing and magnitude of the spring bloom via the drawdown of surface nitrate. We are funded through NSF and NOPP to continue float deployments at HOT, BATS, OSP and the Southern Ocean for the next 3 years and to refine the sensor so it can be offered as a commercial option for all float users. New sensors in development for float deployments include a stable ISFET pH sensor.

Seasonal Ice Zone Reconnaissance Surveys Coordination

DTIC Science & Technology

2016-03-30

sea surface temperature (SST), sea level atmospheric pressure ( SLP ), and velocity (Steele), and dropsonde measurements of atmospheric properties...aircraft), cloud top/base heights UpTempO buoys for understanding and prediction…. Steele UpTempO buoy drops for SLP , SST, SSS, & surface velocity...reflectance, skin temperature, visible imagery AXCTD= Air Expendable CTD, AXCP= Air Expendable Current Profiler, SLP = Sea Level atmospheric

77 FR 9701 - Agency Information Collection Activities; Submission for OMB Emergency Review: Comment Request...

Federal Register 2010, 2011, 2012, 2013, 2014

2012-02-17

... delivery of services, reduce improper payments, and improve tax operations. These funds were transferred to... but not expended to date, as well as the goods and services obtained from the funds expended. Amount of obligated by unexpended funds, as well as the goods and services expected to be obtained from the...

Storytelling as Research/Research as Storytelling

ERIC Educational Resources Information Center

Lewis, Patrick J.

2011-01-01

If story is central to human meaning why, in the research world, is there not more storytelling? Walter Benjamin (1973) noted that, "a story is different. It does not expend itself. It preserves and concentrates its strength and is capable of releasing it even after a long time" (p. 90). How might research not expend itself, but preserve and…

Microchemical Analysis Of Space Operation Debris

NASA Technical Reports Server (NTRS)

Cummings, Virginia J.; Kim, Hae Soo

1995-01-01

Report discusses techniques used in analyzing debris relative to space shuttle operations. Debris collected from space shuttle, expendable launch vehicles, payloads carried by space shuttle, and payloads carried by expendable launch vehicles. Optical microscopy, scanning electron microscopy with energy-dispersive spectrometry, analytical electron microscopy with wavelength-dispersive spectrometry, and X-ray diffraction chosen as techniques used in examining samples of debris.

Intelligent Network Flow Optimization (INFLO) prototype : Seattle small-scale demonstration report.

DOT National Transportation Integrated Search

2015-05-01

This report describes the performance and results of the INFLO Prototype Small-Scale Demonstration. The purpose of the Small-Scale Demonstration was to deploy the INFLO Prototype System to demonstrate its functionality and performance in an operation...

Investigation of Propulsion System Requirements for Spartan Lite

NASA Technical Reports Server (NTRS)

Urban, Mike; Gruner, Timothy; Morrissey, James; Sneiderman, Gary

1998-01-01

This paper discusses the (chemical or electric) propulsion system requirements necessary to increase the Spartan Lite science mission lifetime to over a year. Spartan Lite is an extremely low-cost (less than 10 M) spacecraft bus being developed at the NASA Goddard Space Flight Center to accommodate sounding rocket class (40 W, 45 kg, 35 cm dia by 1 m length) payloads. While Spartan Lite is compatible with expendable launch vehicles, most missions are expected to be tertiary payloads deployed by. the Space Shuttle. To achieve a one year or longer mission life from typical Shuttle orbits, some form of propulsion system is required. Chemical propulsion systems (characterized by high thrust impulsive maneuvers) and electrical propulsion systems (characterized by low-thrust long duration maneuvers and the additional requirement for electrical power) are discussed. The performance of the Spartan Lite attitude control system in the presence of large disturbance torques is evaluated using the Trectops(Tm) dynamic simulator. This paper discusses the performance goals and resource constraints for candidate Spartan Lite propulsion systems and uses them to specify quantitative requirements against which the systems are evaluated.

Report of the Committee on the Space Station of the National Research Council

NASA Technical Reports Server (NTRS)

1987-01-01

The Space Station Program will be the most ambitious space project the nation has ever undertaken; will require tens of billions of dollars; and will entwine for many years the space program with those of international partners. It must have enduring stable support across administrations, and the support must be generous. The current Space Shuttle is barely adequate for the limited purpose of deploying the Space Station, and it is inadequate to meet broader national needs in space. The Committee recommends in the strongest terms that the Shuttle be upgraded with new improved solid rocket motors, that it be supplemented with expendable launch vehicles, and that a heavy lift launch vehicle be developed for use in the latter half of the 1990s. The Committee strongly recommends that NASA prepare a new Space Station Program cost estimate in conjunction with the Program Requirements Review scheduled for early next year by NASA. The exercise should address the full range of uncertainties in the current Program, some of which are discussed in the report.

ANTS/PAM: Future Exploration of the Asteroid Belt

NASA Astrophysics Data System (ADS)

Clark, P. E.; Curtis, S. A.; Rilee, M. L.; Cheung, C. Y.

2004-05-01

The Autonomous Nano-Technology Swarm (ANTS) is applied to the Prospecting Asteroid Mission (PAM) concept, as part of a NASA RASC study. The ANTS architecture is inspired by success of social insect colonies, based on the division of labor within the colonies: 1) within their specialties, individual specialists generally outperform general-ists, and 2) with sufficiently efficient social interaction and coordination, the group of specialists generally outper-forms the group of generalists. ANTS as applied to PAM involves a thousand individual specialist `sciencecraft', one subswarm per target, in an environment where detection and tracking of irregular, infrequent targets is a major chal-lenge. Workers, carry and operate eight to nine different scientific instruments, including spectrometers, ranging and radio science devices, imagers. The remaining specialists, Messenger/Rulers, provide communication and coordina-tion. The non-expendable propulsion system is based on autonomously deployable and configurable solar sails, a system suitable to a low gravity environment. The design of the neural basis function requires a minimum of 4 or 5 specialists for collective decision making. Allowing for ten instrument specialist teams and compensating for antici-pated high attrition, we calculate an initial minimum of 100 per subswarm should allow characterization of hundreds of asteroids. The difficulty in observing irregular, rapidly moving, poorly illuminated objects is largely overcome by the ANT sciencecraft capability to optimize conditions for each instrument. Components are composed of carbon nanotubules reversibly deployable from NEMS nodes, allowing 100 times decrease in packaging volume. 1000 smart 10 centimeter, 1 kg cubic boxes create a 1000 kg 1 meter cube.

New computer and communications environments for light armored vehicles

NASA Astrophysics Data System (ADS)

Rapanotti, John L.; Palmarini, Marc; Dumont, Marc

2002-08-01

Light Armoured Vehicles (LAVs) are being developed to meet the modern requirements of rapid deployment and operations other than war. To achieve these requirements, passive armour is minimized and survivability depends more on sensors, computers and countermeasures to detect and avoid threats. The performance, reliability, and ultimately the cost of these components, will be determined by the trends in computing and communications. These trends and the potential impact on DAS (Defensive Aids Suite) development were investigated and are reported in this paper. Vehicle performance is affected by communication with other vehicles and other ISTAR (Intelligence, Surveillance, Target Acquisition and Reconnaissance) battlefield assets. This investigation includes the networking technology Jini developed by SUN Microsystems, which can be used to interface the vehicle to the ISTAR network. VxWorks by Wind River Systems, is a real time operating system designed for military systems and compatible with Jini. Other technologies affecting computer hardware development include, dynamic reconfiguration, hot swap, alternate pathing, CompactPCI, and Fiber Channel serial communication. To achieve the necessary performance at reasonable cost, and over the long service life of the vehicle, a DAS should have two essential features. A fitted for, but not fitted with approach will provide the necessary rapid deployment without a need to equip the entire fleet. With an expected vehicle service life of 50 years, 5-year technology upgrades can be used to maintain vehicle performance over the entire service life. A federation of modules instead of integrated fused sensors will provide the capability for incremental upgrades and mission configurability. A plug and play capability can be used for both hardware and expendables.

Mars pathfinder Rover egress deployable ramp assembly

NASA Technical Reports Server (NTRS)

Spence, Brian R.; Sword, Lee F.

1996-01-01

The Mars Pathfinder Program is a NASA Discovery Mission, led by the Jet Propulsion Laboratory, to launch and place a small planetary Rover for exploration on the Martian surface. To enable safe and successful egress of the Rover vehicle from the spacecraft, a pair of flight-qualified, deployable ramp assemblies have been developed. This paper focuses on the unique, lightweight deployable ramp assemblies. A brief mission overview and key design requirements are discussed. Design and development activities leading to qualification and flight systems are presented.

1. Air-Sea and Lateral Exchange Processes in East Indian Coastal Current off Sri Lanka 2. ASIRI: Remote Sensing of Atmospheric Waves and Instabilities (RAWI)

DTIC Science & Technology

2014-09-30

second project, collaboration is sought with institutions in Seychelles and Singapore for atmospheric deployments. In all cases, the project expects to...suite of atmospheric instruments in the coasts of three IO island nations, Sri Lanka, Seychelles and Singapore to capture small-scale events pertinent...necessary for the deployments are being developed in Sri Lanka. The nature of the deployments in Seychelles and Singapore do not require additional

Comprehension and Time Expended for a Doctoral Student with a Learning Disability when Reading with and without an Accommodation

ERIC Educational Resources Information Center

Tanners, Adam; McDougall, Dennis; Skouge, Jim; Narkon, Drue

2012-01-01

The purpose of this alternating treatment, single-case research study was to compare reading comprehension and time expended reading, of a doctoral student with learning disabilities, under two reading conditions. In condition one, the student used a self-discovered accommodation, that is, listening, on an iPod, to an audiobook version…

A Respirometric Technique to Evaluate Velopharyngeal Function in Speakers with Cleft Palate, with and without Prostheses.

ERIC Educational Resources Information Center

Gilbert, Harvey R.; Ferrand, Carole T.

1987-01-01

Respirometric quotients (RQ), the ratio of oral air volume expended to total volume expended, were obtained from the productions of oral and nasal airflow of 10 speakers with cleft palate, with and without their prosthetic appliances, and 10 normal speakers. Cleft palate speakers without their appliances exhibited the lowest RQ values. (Author/DB)

Effort-Based Decision-Making in Schizophrenia.

PubMed

Culbreth, Adam J; Moran, Erin K; Barch, Deanna M

2018-08-01

Motivational impairment has long been associated with schizophrenia but the underlying mechanisms are not clearly understood. Recently, a small but growing literature has suggested that aberrant effort-based decision-making may be a potential contributory mechanism for motivational impairments in psychosis. Specifically, multiple reports have consistently demonstrated that individuals with schizophrenia are less willing than healthy controls to expend effort to obtain rewards. Further, this effort-based decision-making deficit has been shown to correlate with severity of negative symptoms and level of functioning, in many but not all studies. In the current review, we summarize this literature and discuss several factors that may underlie aberrant effort-based decision-making in schizophrenia.

Expendable bubble tiltmeter for geophysical monitoring

USGS Publications Warehouse

Westphal, J.A.; Carr, M.A.; Miller, W.F.; Dzurisin, D.

1983-01-01

An unusually rugged highly sensitive and inexpensive bubble tiltmeter has been designed, tested, and built in quantity. These tiltmeters are presently used on two volcanoes and an Alaskan glacier, where they continuously monitor surface tilts of geological interest. This paper discusses the mechanical, thermal, and electric details of the meter, and illustrates its performance characteristics in both large (>10-4 radian) and small (<10-6 radian) tilt environments. The meter's ultimate sensitivity is better than 2??10-8 radians rms for short periods (hours), and its useful dynamic range is greater than 10 4. Included is a short description of field use of the instrument for volcano monitoring.

Small nonnative fishes as predators of larval razorback suckers

USGS Publications Warehouse

Carpenter, J.; Mueller, G.A.

2008-01-01

The razorback sucker (Xyrauchen texanus), an endangered big-river fish of the Colorado River basin, has demonstrated no sustainable recruitment in 4 decades, despite presence of spawning adults and larvae. Lack of adequate recruitment has been attributed to several factors, including predation by nonnative fishes. Substantial funding and effort has been expended on mechanically removing nonnative game fishes, typically targeting large predators. As a result, abundance of larger predators has declined, but the abundance of small nonnative fishes has increased in some areas. We conducted laboratory experiments to determine if small nonnative fishes would consume larval razorback suckers. We tested adults of three small species (threadfin shad, Dorosoma petenense; red shiner, Cyprinella lutrensis; fathead minnow, Pimephales promelas) and juveniles of six larger species (common carp, Cyprinus carpio; yellow bullhead, Ameiurus natalis; channel catfish, Ictalurus punctatus; rainbow trout, Oncorhynchus mykiss; green sunfish, Lepomis cyanellus; bluegill, L. macrochirus). These nonnative fishes span a broad ecological range and are abundant within the historical range of the razorback sucker. All nine species fed on larval razorback suckers (total length, 9-16 mm). Our results suggest that predation by small nonnative fishes could be responsible for limiting recovery of this endangered species.

Low-Cost Phased Array Antenna for Sounding Rockets, Missiles, and Expendable Launch Vehicles

NASA Technical Reports Server (NTRS)

Mullinix, Daniel; Hall, Kenneth; Smith, Bruce; Corbin, Brian

2012-01-01

A low-cost beamformer phased array antenna has been developed for expendable launch vehicles, rockets, and missiles. It utilizes a conformal array antenna of ring or individual radiators (design varies depending on application) that is designed to be fed by the recently developed hybrid electrical/mechanical (vendor-supplied) phased array beamformer. The combination of these new array antennas and the hybrid beamformer results in a conformal phased array antenna that has significantly higher gain than traditional omni antennas, and costs an order of magnitude or more less than traditional phased array designs. Existing omnidirectional antennas for sounding rockets, missiles, and expendable launch vehicles (ELVs) do not have sufficient gain to support the required communication data rates via the space network. Missiles and smaller ELVs are often stabilized in flight by a fast (i.e. 4 Hz) roll rate. This fast roll rate, combined with vehicle attitude changes, greatly increases the complexity of the high-gain antenna beam-tracking problem. Phased arrays for larger ELVs with roll control are prohibitively expensive. Prior techniques involved a traditional fully electronic phased array solution, combined with highly complex and very fast inertial measurement unit phased array beamformers. The functional operation of this phased array is substantially different from traditional phased arrays in that it uses a hybrid electrical/mechanical beamformer that creates the relative time delays for steering the antenna beam via a small physical movement of variable delay lines. This movement is controlled via an innovative antenna control unit that accesses an internal measurement unit for vehicle attitude information, computes a beam-pointing angle to the target, then points the beam via a stepper motor controller. The stepper motor on the beamformer controls the beamformer variable delay lines that apply the appropriate time delays to the individual array elements to properly steer the beam. The array of phased ring radiators is unique in that it provides improved gain for a small rocket or missile that uses spin stabilization for stability. The antenna pattern created is symmetric about the roll axis (like an omnidirectional wraparound), and is thus capable of providing continuous coverage that is compatible with very fast spinning rockets. For larger ELVs with roll control, a linear array of elements can be used for the 1D scanned beamformer and phased array, or a 2D scanned beamformer can be used with an NxN element array.

Energy Efficiency Challenges of 5G Small Cell Networks.

PubMed

Ge, Xiaohu; Yang, Jing; Gharavi, Hamid; Sun, Yang

2017-05-01

The deployment of a large number of small cells poses new challenges to energy efficiency, which has often been ignored in fifth generation (5G) cellular networks. While massive multiple-input multiple outputs (MIMO) will reduce the transmission power at the expense of higher computational cost, the question remains as to which computation or transmission power is more important in the energy efficiency of 5G small cell networks. Thus, the main objective in this paper is to investigate the computation power based on the Landauer principle. Simulation results reveal that more than 50% of the energy is consumed by the computation power at 5G small cell base stations (BSs). Moreover, the computation power of 5G small cell BS can approach 800 watt when the massive MIMO (e.g., 128 antennas) is deployed to transmit high volume traffic. This clearly indicates that computation power optimization can play a major role in the energy efficiency of small cell networks.

Energy Efficiency Challenges of 5G Small Cell Networks

PubMed Central

Ge, Xiaohu; Yang, Jing; Gharavi, Hamid; Sun, Yang

2017-01-01

The deployment of a large number of small cells poses new challenges to energy efficiency, which has often been ignored in fifth generation (5G) cellular networks. While massive multiple-input multiple outputs (MIMO) will reduce the transmission power at the expense of higher computational cost, the question remains as to which computation or transmission power is more important in the energy efficiency of 5G small cell networks. Thus, the main objective in this paper is to investigate the computation power based on the Landauer principle. Simulation results reveal that more than 50% of the energy is consumed by the computation power at 5G small cell base stations (BSs). Moreover, the computation power of 5G small cell BS can approach 800 watt when the massive MIMO (e.g., 128 antennas) is deployed to transmit high volume traffic. This clearly indicates that computation power optimization can play a major role in the energy efficiency of small cell networks. PMID:28757670

Economics of the solid rocket booster for space shuttle

NASA Technical Reports Server (NTRS)

Rice, W. C.

1979-01-01

The paper examines economics of the solid rocket booster for the Space Shuttle. Costs have been held down by adapting existing technology to the 146 in. SRB selected, with NASA reducing the cost of expendables and reusing the expensive nonexpendable hardware. Drop tests of Titan III motor cases and nozzles proved that boosters can survive water impact at vertical velocities of 100 ft/sec so that SRB components can be reused. The cost of expendables was minimized by selecting proven propellants, insulation, and nozzle ablatives of known costs; the propellant has the lowest available cost formulation, and low cost ablatives, such as pitch carbon fibers, will be used when available. Thus, the use of proven technology and low cost expendables will make the SRB an economical booster for the Space Shuttle.

Integrated operations/payloads/fleet analysis. Volume 2: Payloads

NASA Technical Reports Server (NTRS)

1971-01-01

The payloads for NASA and non-NASA missions of the integrated fleet are analyzed to generate payload data for the capture and cost analyses for the period 1979 to 1990. Most of the effort is on earth satellites, probes, and planetary missions because of the space shuttle's ability to retrieve payloads for repair, overhaul, and maintenance. Four types of payloads are considered: current expendable payload; current reusable payload; low cost expendable payload, (satellite to be used with expendable launch vehicles); and low cost reusable payload (satellite to be used with the space shuttle/space tug system). Payload weight analysis, structural sizing analysis, and the influence of mean mission duration on program cost are also discussed. The payload data were computerized, and printouts of the data for payloads for each program or mission are included.

Lightweight, Self-Deployable Wheels

NASA Technical Reports Server (NTRS)

Chmielewski, Artur; Sokolowski, Witold; Rand, Peter

2003-01-01

Ultra-lightweight, self-deployable wheels made of polymer foams have been demonstrated. These wheels are an addition to the roster of cold hibernated elastic memory (CHEM) structural applications. Intended originally for use on nanorovers (very small planetary-exploration robotic vehicles), CHEM wheels could also be used for many commercial applications, such as in toys. The CHEM concept was reported in "Cold Hibernated Elastic Memory (CHEM) Expandable Structures" (NPO-20394), NASA Tech Briefs, Vol. 23, No. 2 (February 1999), page 56. To recapitulate: A CHEM structure is fabricated from a shape-memory polymer (SMP) foam. The structure is compressed to a very small volume while in its rubbery state above its glass-transition temperature (Tg). Once compressed, the structure can be cooled below Tg to its glassy state. As long as the temperature remains

Swedish Defence Acquisition Transformation: A Research Agenda

DTIC Science & Technology

2015-05-13

presentation • A small country perspective • The swinging pendulum : “From preparedness to deployment to preparedness?” – or “from national defence to PSOs to...history of war The swinging (political) pendulum • A. 200 years of peace – Standing in preparedness • B. Post Cold War – Deployed on PSOs • C

Near-Earth Asteroid Solar Sail Test Deployment

NASA Image and Video Library

2018-06-28

NASA's Near-Earth Asteroid Scout, a small satellite the size of a shoebox designed to study asteroids close to Earth, performed a deployment test June 28 of the solar sail that will launch on Exploration Mission-1. The test was performed in an indoor clean room at the NeXolve facility in Huntsville, Alabama.

Recent developments in deployment analysis simulation using a multi-body computer code

NASA Technical Reports Server (NTRS)

Housner, Jerrold M.

1989-01-01

Deployment is a candidate mode for construction of structural space systems components. By its very nature, deployment is a dynamic event, often involving large angle unfolding of flexible beam members. Validation of proposed designs and conceptual deployment mechanisms is enhanced through analysis. Analysis may be used to determine member loads thus helping to establish deployment rates and deployment control requirements for a given concept. Futhermore, member flexibility, joint free-play, manufacturing tolerances, and imperfections can affect the reliability of deployment. Analyses which include these effects can aid in reducing risks associated with a particular concept. Ground tests which can play a similar role to that of analyses are difficult and expensive to perform. Suspension systems just for vibration ground tests of large space structures in a 1 g environment present many challenges. Suspension of a structure which spatially expands is even more challenging. Analysis validation through experimental confirmation on relatively small simple models would permit analytical extrapolation to larger more complex space structures.

Letter to the Editor : Rapidly-deployed small tent hospitals: lessons from the earthquake in Haiti.

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

Rosen, Y.; Gurman , P.; Verna, E.

2012-06-01

The damage to medical facilities resulting form the January 2010 earthquake in haiti necessitated the establishment of field tent hospitals. Much of the local medical infrastructure was destroyed or limited operationally when the Fast Israel Rescue and Search Team (FIRST) arrived in Haiti shortly after the January 2010 earthquake. The FIRST deployed small tent hospitals in Port-au-Prince and in 11 remote areas outside of the city. Each tent was set up in less than a half hour. The tents were staffed with an orthopedic surgeon, gynecologists, primary care and emergency care physicians, a physician with previous experience in tropical medicine,more » nurses, paramedics, medics, and psychologists. The rapidly deployable and temporary nature of the effort allowed the team to treat and educate, as well as provide supplies for, thousands of refugees throughout Haiti. In addition, a local Haitian physician and his team created a small tent hospital to serve the Petion Refugee Camp and its environs. FIRST personnel also took shifts at this hospital.« less

Expendable launch vehicle propulsion

NASA Technical Reports Server (NTRS)

Fuller, Paul N.

1991-01-01

The current status is reviewed of the U.S. Expendable Launch Vehicle (ELV) fleet, the international competition, and the propulsion technology of both domestic and foreign ELVs. The ELV propulsion technology areas where research, development, and demonstration are most needed are identified. These propulsion technology recommendations are based on the work performed by the Commercial Space Transportation Advisory Committee (COMSTAC), an industry panel established by the Dept. of Transportation.

The October 1973 expendable launch vehicle traffic model, revision 2

NASA Technical Reports Server (NTRS)

1974-01-01

Traffic model data for current expendable launch vehicles (assuming no space shuttle) for calendar years 1980 through 1991 are presented along with some supporting and summary data. This model was based on a payload program equivalent in scientific return to the October 1973 NASA Payload Model, the NASA estimated non NASA/non DoD Payload Model, and the 1971 DoD Mission Model.

Seasonal Ice Zone Reconnaissance Surveys Coordination

DTIC Science & Technology

2014-09-30

profiler (AXCP) ocean velocity shear (Morison), UpTempO buoy measurements of sea surface temperature (SST), sea level atmospheric pressure ( SLP ), and...and prediction…. Steele UpTempO buoy drops for SLP , SST, SSS, & surface velocity Visible and Thermal Images of the SIZ from the Coast Guard...Expendable CTD, AXCP= Air Expendable Current Profiler, SLP = Sea Level atmospheric Pressure, SST= Seas Surface Temperature, A/C= aircraft, SIC=Sea Ice

Evaluating the Effort Expended to Understand Speech in Noise Using a Dual-Task Paradigm: The Effects of Providing Visual Speech Cues

ERIC Educational Resources Information Center

Fraser, Sarah; Gagne, Jean-Pierre; Alepins, Majolaine; Dubois, Pascale

2010-01-01

Purpose: Using a dual-task paradigm, 2 experiments (Experiments 1 and 2) were conducted to assess differences in the amount of listening effort expended to understand speech in noise in audiovisual (AV) and audio-only (A-only) modalities. Experiment 1 had equivalent noise levels in both modalities, and Experiment 2 equated speech recognition…

New life for expendable launchers

NASA Astrophysics Data System (ADS)

Lopez, Ramon L.; Waskul, Greg

The U.S. commercial expendable launch vehicle (ELV) industry is examined. The use of Titan, Delta, Atlas-Centaur, and Liberty boosters to launch domestic and foreign commercial payloads is analyzed. The ELV commercialization agreement which explains the division of liability between the parties is described. Consideration is given to the competition to the U.S. industry from Europe's Ariane, China's Long March, and the Soviet Proton launchers.

42 CFR 137.110 - May a Self-Governance Tribe retain and expend any program income earned pursuant to a compact and...

Code of Federal Regulations, 2013 CFR

2013-10-01

... 42 Public Health 1 2013-10-01 2013-10-01 false May a Self-Governance Tribe retain and expend any... HEALTH AND HUMAN SERVICES TRIBAL SELF-GOVERNANCE Funding Program Income § 137.110 May a Self-Governance... Medicare, Medicaid, or other program income earned by a Self-Governance Tribe shall be treated as...

42 CFR 137.110 - May a Self-Governance Tribe retain and expend any program income earned pursuant to a compact and...

Code of Federal Regulations, 2011 CFR

2011-10-01

... 42 Public Health 1 2011-10-01 2011-10-01 false May a Self-Governance Tribe retain and expend any... HEALTH AND HUMAN SERVICES TRIBAL SELF-GOVERNANCE Funding Program Income § 137.110 May a Self-Governance... Medicare, Medicaid, or other program income earned by a Self-Governance Tribe shall be treated as...

42 CFR 137.110 - May a Self-Governance Tribe retain and expend any program income earned pursuant to a compact and...

Code of Federal Regulations, 2010 CFR

2010-10-01

... 42 Public Health 1 2010-10-01 2010-10-01 false May a Self-Governance Tribe retain and expend any... HEALTH AND HUMAN SERVICES TRIBAL SELF-GOVERNANCE Funding Program Income § 137.110 May a Self-Governance... Medicare, Medicaid, or other program income earned by a Self-Governance Tribe shall be treated as...

42 CFR 137.110 - May a Self-Governance Tribe retain and expend any program income earned pursuant to a compact and...

Code of Federal Regulations, 2012 CFR

2012-10-01

... 42 Public Health 1 2012-10-01 2012-10-01 false May a Self-Governance Tribe retain and expend any... HEALTH AND HUMAN SERVICES TRIBAL SELF-GOVERNANCE Funding Program Income § 137.110 May a Self-Governance... Medicare, Medicaid, or other program income earned by a Self-Governance Tribe shall be treated as...

42 CFR 137.110 - May a Self-Governance Tribe retain and expend any program income earned pursuant to a compact and...

Code of Federal Regulations, 2014 CFR

2014-10-01

... 42 Public Health 1 2014-10-01 2014-10-01 false May a Self-Governance Tribe retain and expend any... HEALTH AND HUMAN SERVICES TRIBAL SELF-GOVERNANCE Funding Program Income § 137.110 May a Self-Governance... Medicare, Medicaid, or other program income earned by a Self-Governance Tribe shall be treated as...

Low-cost management aspects for developing, producing and operating future space transportation systems

NASA Astrophysics Data System (ADS)

Goehlich, Robert A.; Rücker, Udo

2005-01-01

It is believed that a potential means for further significant reduction of the recurrent launch cost, which results also in a stimulation of launch rates of small satellites, is to make the launcher reusable, to increase its reliability and to make it suitable for new markets such as mass space tourism. Therefore, not only launching small satellites with expendable rockets on non-regular flights but also with reusable rockets on regular flights should be considered for the long term. However, developing, producing and operating reusable rockets require a fundamental change in the current "business as usual" philosophy. Under current conditions, it might not be possible to develop, to produce or to operate a reusable vehicle fleet economically. The favorite philosophy is based on "smart business" processes adapted by the authors using cost engineering techniques. In the following paper, major strategies for reducing costs are discussed, which are applied for a representative program proposal.

A small spacecraft for multipoint measurement of ionospheric plasma.

PubMed

Roberts, T M; Lynch, K A; Clayton, R E; Weiss, J; Hampton, D L

2017-07-01

Measurement of ionospheric plasma is often performed by a single in situ device or remotely using cameras and radar. This article describes a small, low-resource, deployed spacecraft used as part of a local, multipoint measurement network. A B-field aligned sounding rocket ejects four of these spin-stabilized spacecraft in a cross pattern. In this application, each spacecraft carries two retarding potential analyzers which are used to determine plasma density, flow, and ion temperature. An inertial measurement unit and a light-emitting diode array are used to determine the position and orientation of the devices after deployment. The design of this spacecraft is first described, and then results from a recent test flight are discussed. This flight demonstrated the successful operation of the deployment mechanism and telemetry systems, provided some preliminary plasma measurements in a simple mid-latitude environment, and revealed several design issues.

A small spacecraft for multipoint measurement of ionospheric plasma

NASA Astrophysics Data System (ADS)

Roberts, T. M.; Lynch, K. A.; Clayton, R. E.; Weiss, J.; Hampton, D. L.

2017-07-01

Measurement of ionospheric plasma is often performed by a single in situ device or remotely using cameras and radar. This article describes a small, low-resource, deployed spacecraft used as part of a local, multipoint measurement network. A B-field aligned sounding rocket ejects four of these spin-stabilized spacecraft in a cross pattern. In this application, each spacecraft carries two retarding potential analyzers which are used to determine plasma density, flow, and ion temperature. An inertial measurement unit and a light-emitting diode array are used to determine the position and orientation of the devices after deployment. The design of this spacecraft is first described, and then results from a recent test flight are discussed. This flight demonstrated the successful operation of the deployment mechanism and telemetry systems, provided some preliminary plasma measurements in a simple mid-latitude environment, and revealed several design issues.

Xatcobeo: Small Mechanisms for CubeSat Satellites - Antenna and Solar Array Deployment

NASA Technical Reports Server (NTRS)

EncinasPlaza, Jose Miguel; VilanVilan, Jose Antonio; AquadoAgelet, Fernando; BrandiaranMancheno, Javier; LopezEstevez, Miguel; MartinezFernandez, Cesar; SarmientoAres, Fany

2010-01-01

The Xatcobeo project, which includes the mechanisms dealt with here, is principally a university project to design and construct a CubeSat 1U-type satellite. This work describes the design and operational features of the system for antenna storage and deployment, and the design and simulations of the solar array deployment system. It explains the various problems faced and solutions adopted, with a view to providing valid data for any other applications that could find them useful, be they of a similar nature or not.

Methodology for Variable Fidelity Multistage Optimization under Uncertainty

DTIC Science & Technology

2011-03-31

problem selected for the application of the new optimization methodology is a Single Stage To Orbit ( SSTO ) expendable launch vehicle (ELV). Three...the primary exercise of the variable fidelity optimization portion of the code. SSTO vehicles have been discussed almost exclusively in the context...of reusable launch vehicles (RLV). There is very little discussion in recent literature of SSTO designs which are expendable. In the light of the

Mission Design for NASA's Inner Heliospheric Sentinels and ESA's Solar Orbiter Missions

NASA Technical Reports Server (NTRS)

Downing, John; Folta, David; Marr, Greg; Rodriquez-Canabal, Jose; Conde, Rich; Guo, Yanping; Kelley, Jeff; Kirby, Karen

2007-01-01

This paper will document the mission design and mission analysis performed for NASA's Inner Heliospheric Sentinels (IHS) and ESA's Solar Orbiter (SolO) missions, which were conceived to be launched on separate expendable launch vehicles. This paper will also document recent efforts to analyze the possibility of launching the Inner Heliospheric Sentinels and Solar Orbiter missions using a single expendable launch vehicle, nominally an Atlas V 551.

Work stressors, depressive symptoms and sleep quality among US Navy members: a parallel process latent growth modelling approach across deployment.

PubMed

Bravo, Adrian J; Kelley, Michelle L; Swinkels, Cindy M; Ulmer, Christi S

2017-11-03

The present study examined whether work stressors contribute to sleep problems and depressive symptoms over the course of deployment (i.e. pre-deployment, post-deployment and 6-month reintegration) among US Navy members. Specifically, we examined whether depressive symptoms or sleep quality mediate the relationships between work stressors and these outcomes. Participants were 101 US Navy members who experienced an 8-month deployment after Operational Enduring Freedom/Operation Iraqi Freedom. Using piecewise latent growth models, we found that increased work stressors were linked to increased depressive symptoms and decreased sleep quality across all three deployment stages. Further, increases in work stressors from pre- to post-deployment contributed to poorer sleep quality post-deployment via increasing depressive symptoms. Moreover, sleep quality mediated the association between increases in work stressors and increases in depressive symptoms from pre- to post-deployment. These effects were maintained from post-deployment through the 6-month reintegration. Although preliminary, our results suggest that changes in work stressors may have small, but significant implications for both depressive symptoms and quality of sleep over time, and a bi-directional relationship persists between sleep quality and depression across deployment. Strategies that target both stress and sleep could address both precipitating and perpetuating factors that affect sleep and depressive symptoms. © 2017 European Sleep Research Society.

Novel techniques and insights into the deployment of pop-up satellite archival tags on a small-bodied deep-water chondrichthyan

NASA Astrophysics Data System (ADS)

Shipley, Oliver N.; Howey, Lucy A.; Tolentino, Emily R.; Jordan, Lance K. B.; Brooks, Edward J.

2017-01-01

Acquiring movement data for small-bodied, deep-water chondrichthyans is challenged by extreme effects of capture and handling stress, and post-release predation, however, it is urgently required to examine important fisheries interactions and assess the ecological role of these species within deep-water food webs. Here we suggest a novel release-cage mechanism to deploy pop-up satellite archival tags, as well as present vertical habitat data for a data-deficient, small-bodied, deep-water bycatch species, the Cuban dogfish (Squalus cubensis). Data were gathered from seven of eight High Rate X-Tags deployed on mature Cuban dogfish in the Exuma Sound, The Bahamas. Recovery periods appeared variable between individuals and are likely driven by capture-and-handling stress and tag burden. Application of the cross-correlation function to time-series depth and temperature data indicated three of the seven individuals suffered mortality through predation, which occurred during daytime, and suggests Cuban dogfish may constitute a proportion of deep-water apex predator diet in the Exuma Sound. Two animals were successfully released via a novel release-cage mechanism and displayed either no, or rapid (<15 mins) vertically stationary recovery periods and were not consumed by predators; data for these individuals were recorded for the entire deployment duration (14 days). Vertical habitat data suggests Cuban dogfish are diel-vertical migrators, similar to other deep-water taxa, and exhibit a relatively broad temperature and depth range, which may be driven by preference for specific bathymetric structures. These techniques provide an important first step into acquiring and presenting vertical habitat data for small-bodied, deep-water chondrichthyans, which can be directly applied to fisheries and ecosystem-based management approaches.

Evaluating the Cost, Safety, and Proliferation Risks of Small Floating Nuclear Reactors.

PubMed

Ford, Michael J; Abdulla, Ahmed; Morgan, M Granger

2017-11-01

It is hard to see how our energy system can be decarbonized if the world abandons nuclear power, but equally hard to introduce the technology in nonnuclear energy states. This is especially true in countries with limited technical, institutional, and regulatory capabilities, where safety and proliferation concerns are acute. Given the need to achieve serious emissions mitigation by mid-century, and the multidecadal effort required to develop robust nuclear governance institutions, we must look to other models that might facilitate nuclear plant deployment while mitigating the technology's risks. One such deployment paradigm is the build-own-operate-return model. Because returning small land-based reactors containing spent fuel is infeasible, we evaluate the cost, safety, and proliferation risks of a system in which small modular reactors are manufactured in a factory, and then deployed to a customer nation on a floating platform. This floating small modular reactor would be owned and operated by a single entity and returned unopened to the developed state for refueling. We developed a decision model that allows for a comparison of floating and land-based alternatives considering key International Atomic Energy Agency plant-siting criteria. Abandoning onsite refueling is beneficial, and floating reactors built in a central facility can potentially reduce the risk of cost overruns and the consequences of accidents. However, if the floating platform must be built to military-grade specifications, then the cost would be much higher than a land-based system. The analysis tool presented is flexible, and can assist planners in determining the scope of risks and uncertainty associated with different deployment options. © 2017 Society for Risk Analysis.

Energy performance assessment of virtualization technologies using small environmental monitoring sensors.

PubMed

Liu, Lu; Masfary, Osama; Antonopoulos, Nick

2012-01-01

The increasing trends of electrical consumption within data centres are a growing concern for business owners as they are quickly becoming a large fraction of the total cost of ownership. Ultra small sensors could be deployed within a data centre to monitor environmental factors to lower the electrical costs and improve the energy efficiency. Since servers and air conditioners represent the top users of electrical power in the data centre, this research sets out to explore methods from each subsystem of the data centre as part of an overall energy efficient solution. In this paper, we investigate the current trends of Green IT awareness and how the deployment of small environmental sensors and Site Infrastructure equipment optimization techniques which can offer a solution to a global issue by reducing carbon emissions.

Polycyclic Aromatic Hydrocarbons and Polychlorinated Dibenzo-p-Dioxins/Dibenzofurans in Microliter Samples of Human Serum as Exposure Indicators

PubMed Central

Xia, Xiaoyan; Carroll-Haddad, Alesia; Brown, Nicole; Utell, Mark J.; Mallon, Timothy; Hopke, Philip K.

2016-01-01

Objective The objectives were: 1) measure polycyclic aromatic hydrocarbons (PAHs), polychlorinated dibenzo-p-dioxins (PCDDs) and dibenzofurans (PCDFs) in 100 μL of human serum and 2) assess PAH and PCDD/PCDF as markers of burn pit exposures during military deployments. Methods PAHs and PCDDs/PCDFs were analyzed in 100μL serum samples collected pre- and post-deployment from 200 persons deployed to Iraq or Afghanistan (CASE); 200 persons not deployed (CONTROL) with GC/MS. Results Naphthalene was found in ~83% of the samples and was statistically different between post-deployment CASE personnel and pre-deployment. 1,2,3,4,6,7,8-Heptachlorodibenzo-p-dioxin, Octachlorodibenzo-p-dioxin, 1,2,3,7,8,9-Hexachlorodibenzofuran, and 1,2,3,4,6,7,8-Heptachlorodibenzofuran were found in ~38% of samples. Concentrations were significantly different between CASE and CONTROL and between pre- and post-deployment samples. Conclusions PAH and PCDD/PCDF in serum can serve as exposure markers and measurements in small volumes is feasible for quantifying exposure to burn pits. PMID:27501107

Applications of Dynamic Deployment of Services in Industrial Automation

NASA Astrophysics Data System (ADS)

Candido, Gonçalo; Barata, José; Jammes, François; Colombo, Armando W.

Service-oriented Architecture (SOA) is becoming a de facto paradigm for business and enterprise integration. SOA is expanding into several domains of application envisioning a unified solution suitable across all different layers of an enterprise infrastructure. The application of SOA based on open web standards can significantly enhance the interoperability and openness of those devices. By embedding a dynamical deployment service even into small field de- vices, it would be either possible to allow machine builders to place built- in services and still allow the integrator to deploy on-the-run the services that best fit his current application. This approach allows the developer to keep his own preferred development language, but still deliver a SOA- compliant application. A dynamic deployment service is envisaged as a fundamental framework to support more complex applications, reducing deployment delays, while increasing overall system agility. As use-case scenario, a dynamic deployment service was implemented over DPWS and WS-Management specifications allowing designing and programming an automation application using IEC61131 languages, and deploying these components as web services into devices.

The opearation and scientific data of MINERVA rover in Hayabusa mission

NASA Astrophysics Data System (ADS)

Yoshimitsu, T.; Kubota, T.; Nakatani, I.

section Introduction The asteroid explorer Hayabusa operated by Institute of Space and Astronautical Science ISAS JAXA made a rendezvous with the target asteroid Itokawa in September 2005 after more than two years interplanetary cruise since the launch in 2003 The spacecraft precisely observed the target from the vicinity of the asteroid for two months and then tried to land on the surface in order to get some fragments which will be brought back to the Earth The authors installed a experimental small rover named MINERVA into the spacecraft It was supposed to make a surface exploration after having been deployed onto the surface MINERVA is the smallest spacecraft with a weight of 591 g and a dimension of about 10 cm in size In this small body it is equipped with a moving ability over the micro-gravity environment on the asteroid and a few scientific instruments cameras and thermometers to characterize the surface MINERVA was deployed in November 2005 but it could not reach at the asteroid because the deployment was not done at the good timing Thus it became a artificial solar satellite and the surface exploration was not conducted It survived at least for 18 hours after the deployment while the obtained data were transmitted to the Earth via the mother spacecraft This paper describes the operation and the possible science from the obtained data by MINERVA section Deployment MINERVA was deployed in November 12 2005 by sending a command from the Earth when the rehearsal operation of the touchdown was in

Deployable Soft Composite Structures.

PubMed

Wang, Wei; Rodrigue, Hugo; Ahn, Sung-Hoon

2016-02-19

Deployable structure composed of smart materials based actuators can reconcile its inherently conflicting requirements of low mass, good shape adaptability, and high load-bearing capability. This work describes the fabrication of deployable structures using smart soft composite actuators combining a soft matrix with variable stiffness properties and hinge-like movement through a rigid skeleton. The hinge actuator has the advantage of being simple to fabricate, inexpensive, lightweight and simple to actuate. This basic actuator can then be used to form modules capable of different types of deformations, which can then be assembled into deployable structures. The design of deployable structures is based on three principles: design of basic hinge actuators, assembly of modules and assembly of modules into large-scale deployable structures. Various deployable structures such as a segmented triangular mast, a planar structure comprised of single-loop hexagonal modules and a ring structure comprised of single-loop quadrilateral modules were designed and fabricated to verify this approach. Finally, a prototype for a deployable mirror was developed by attaching a foldable reflective membrane to the designed ring structure and its functionality was tested by using it to reflect sunlight onto to a small-scale solar panel.

Deployable Soft Composite Structures

PubMed Central

Wang, Wei; Rodrigue, Hugo; Ahn, Sung-Hoon

2016-01-01

Deployable structure composed of smart materials based actuators can reconcile its inherently conflicting requirements of low mass, good shape adaptability, and high load-bearing capability. This work describes the fabrication of deployable structures using smart soft composite actuators combining a soft matrix with variable stiffness properties and hinge-like movement through a rigid skeleton. The hinge actuator has the advantage of being simple to fabricate, inexpensive, lightweight and simple to actuate. This basic actuator can then be used to form modules capable of different types of deformations, which can then be assembled into deployable structures. The design of deployable structures is based on three principles: design of basic hinge actuators, assembly of modules and assembly of modules into large-scale deployable structures. Various deployable structures such as a segmented triangular mast, a planar structure comprised of single-loop hexagonal modules and a ring structure comprised of single-loop quadrilateral modules were designed and fabricated to verify this approach. Finally, a prototype for a deployable mirror was developed by attaching a foldable reflective membrane to the designed ring structure and its functionality was tested by using it to reflect sunlight onto to a small-scale solar panel. PMID:26892762

PANSAT satellite deployment from STS-95 Discovery's payload bay

NASA Image and Video Library

1998-10-30

STS095-E-5040 (30 Oct. 1998) --- PANSAT, a nonrecoverable satellite developed by the Naval Postgraduate School (NPS) in Monterey, California, is deployed from the cargo bay of the Earth-orbiting Space Shuttle Discovery. The small ball-shaped payload is basically a tiny telecommunications satellite. The photo was recorded with an electronic still camera (ESC) at 1:49:13 GMT, Oct. 30.

Flat-plate solar array project. Volume 5: Process development

NASA Technical Reports Server (NTRS)

Gallagher, B.; Alexander, P.; Burger, D.

1986-01-01

The goal of the Process Development Area, as part of the Flat-Plate Solar Array (FSA) Project, was to develop and demonstrate solar cell fabrication and module assembly process technologies required to meet the cost, lifetime, production capacity, and performance goals of the FSA Project. R&D efforts expended by Government, Industry, and Universities in developing processes capable of meeting the projects goals during volume production conditions are summarized. The cost goals allocated for processing were demonstrated by small volume quantities that were extrapolated by cost analysis to large volume production. To provide proper focus and coverage of the process development effort, four separate technology sections are discussed: surface preparation, junction formation, metallization, and module assembly.

45 CFR 264.50 - What happens if, in a fiscal year, a State does not expend, with its own funds, an amount equal...

Code of Federal Regulations, 2014 CFR

2014-10-01

... 45 Public Welfare 2 2014-10-01 2012-10-01 true What happens if, in a fiscal year, a State does not expend, with its own funds, an amount equal to the reduction to the adjusted SFAG resulting from a penalty? 264.50 Section 264.50 Public Welfare Regulations Relating to Public Welfare OFFICE OF FAMILY ASSISTANCE (ASSISTANCE PROGRAMS), ADMINISTRATIO...

45 CFR 264.50 - What happens if, in a fiscal year, a State does not expend, with its own funds, an amount equal...

Code of Federal Regulations, 2010 CFR

2010-10-01

... 45 Public Welfare 2 2010-10-01 2010-10-01 false What happens if, in a fiscal year, a State does not expend, with its own funds, an amount equal to the reduction to the adjusted SFAG resulting from a penalty? 264.50 Section 264.50 Public Welfare Regulations Relating to Public Welfare OFFICE OF FAMILY ASSISTANCE (ASSISTANCE PROGRAMS),...

45 CFR 264.50 - What happens if, in a fiscal year, a State does not expend, with its own funds, an amount equal...

Code of Federal Regulations, 2011 CFR

2011-10-01

... 45 Public Welfare 2 2011-10-01 2011-10-01 false What happens if, in a fiscal year, a State does not expend, with its own funds, an amount equal to the reduction to the adjusted SFAG resulting from a penalty? 264.50 Section 264.50 Public Welfare Regulations Relating to Public Welfare OFFICE OF FAMILY ASSISTANCE (ASSISTANCE PROGRAMS),...

45 CFR 264.50 - What happens if, in a fiscal year, a State does not expend, with its own funds, an amount equal...

Code of Federal Regulations, 2013 CFR

2013-10-01

... 45 Public Welfare 2 2013-10-01 2012-10-01 true What happens if, in a fiscal year, a State does not expend, with its own funds, an amount equal to the reduction to the adjusted SFAG resulting from a penalty? 264.50 Section 264.50 Public Welfare Regulations Relating to Public Welfare OFFICE OF FAMILY ASSISTANCE (ASSISTANCE PROGRAMS), ADMINISTRATIO...

45 CFR 264.50 - What happens if, in a fiscal year, a State does not expend, with its own funds, an amount equal...

Code of Federal Regulations, 2012 CFR

2012-10-01

... 45 Public Welfare 2 2012-10-01 2012-10-01 false What happens if, in a fiscal year, a State does not expend, with its own funds, an amount equal to the reduction to the adjusted SFAG resulting from a penalty? 264.50 Section 264.50 Public Welfare Regulations Relating to Public Welfare OFFICE OF FAMILY ASSISTANCE (ASSISTANCE PROGRAMS),...

On the biomechanical analysis of the calories expended in a straight boxing jab

PubMed Central

2017-01-01

Boxing and related sports activities have become a standard workout regime at many fitness studios worldwide. Oftentimes, people are interested in the calories expended during these workouts. This note focuses on determining the calories in a boxer's jab, using kinematic vector-loop relations and basic work–energy principles. Numerical simulations are undertaken to illustrate the basic model. Multi-limb extensions of the model are also discussed. PMID:28404871

Wii Tennis Play for Low-Income African American Adolescents’ Energy Expenditure

PubMed Central

Staiano, Amanda E.; Calvert, Sandra L.

2013-01-01

Exergames, which are video games that require gross motor activity, are popular activities that produce energy expenditure. Seventy-four low-income African American 12- to 18-year-old adolescents were randomly assigned to a 30-minute condition: 1) solitary Wii tennis exergame play against virtual peers; 2) social Wii tennis exergame play against a real peer; or 3) control group with sedentary computer activity. Adolescents were tested for caloric expenditure after exposure to treatment conditions as well as on a tennis court using Actical accelerometers. Adolescents who played the social exergame against a peer expended significantly more energy than those who played alone. Both exergame groups expended more energy than the control group. Adolescents who played the social exergame also expended comparable calories to actual tennis court play during a simulated lesson. Exergames, then, could promote physical activity, thereby becoming a tool to combat the obesity crisis that is affecting many youth. PMID:24058381

Space platform expendables resupply concept definition study. Volume 3: Work breakdown structure and work breakdown structure dictionary

NASA Technical Reports Server (NTRS)

1984-01-01

The work breakdown structure (WBS) for the Space Platform Expendables Resupply Concept Definition Study is described. The WBS consists of a list of WBS elements, a dictionary of element definitions, and an element logic diagram. The list and logic diagram identify the interrelationships of the elements. The dictionary defines the types of work that may be represented by or be classified under each specific element. The Space Platform Expendable Resupply WBS was selected mainly to support the program planning, scheduling, and costing performed in the programmatics task (task 3). The WBS is neither a statement-of-work nor a work authorization document. Rather, it is a framework around which to define requirements, plan effort, assign responsibilities, allocate and control resources, and report progress, expenditures, technical performance, and schedule performance. The WBS element definitions are independent of make-or-buy decisions, organizational structure, and activity locations unless exceptions are specifically stated.

Deployment Experiences, Social Support, and Mental Health: Comparison of Black, White, and Hispanic U.S. Veterans Deployed to Afghanistan and Iraq.

PubMed

Muralidharan, Anjana; Austern, David; Hack, Samantha; Vogt, Dawne

2016-06-01

Compared to their White counterparts, Black and Hispanic Vietnam-era, male, combat veterans in the United States have experienced discrimination and increased trauma exposure during deployment and exhibited higher rates of postdeployment mental health disorders. The present study examined differences in deployment experiences and postdeployment mental health among male and female Black, Hispanic, and White veterans deployed in support of Operation Enduring Freedom in Afghanistan and Operation Iraqi Freedom in Iraq. Data were drawn from a national survey of veterans (N = 924) who had returned from deployment within the last 2 years. Ethnoracial minority veterans were compared to White veterans of the same gender on deployment experiences and postdeployment mental health. The majority of comparisons did not show significant differences; however, several small group differences did emerge (.02 < η(2) < .04). Ethnoracial minority veterans reported greater perceived threat in the warzone and more family-related concerns and stressors during deployment than White veterans of the same gender. Minority female veterans reported higher levels of postdeployment symptoms of anxiety than their White counterparts, which were accounted for by differences in deployment experience. These differences call for ongoing monitoring. Copyright © 2016 International Society for Traumatic Stress Studies.

Results of a NASA Kennedy Space Center Earned Value Management Pilot Project

NASA Technical Reports Server (NTRS)

Delgado, Hector N.; Rhodeside, Glenn R.

2004-01-01

The Earn Value Management Pilot provided a tremendous amount of data on the strengths and weaknesses of the new financial system, the ability to support EVM from many viewpoints, the lack of tools for small to medium projects implementing EVM, and the training and environment necessary to successfully deploy EVM to all projects. This data along with other pilots will prove invaluable. Deploying EVM should not be taken lightly - a full assessment of capabilities and supporting infrastructure should be done prior to any deployment, and some very basic questions should be asked. For instance, will sufficient training be provided? Can the project managers readily and easily obtain all the necessary data? If EVM is to thrive in all projects regardless of cost, the transition should be as seamless as possible, minimizing cost and effort, and with the end user in mind. In setting up an EVM implementation, the question, "How does the project manager benefit from this process?" must remain at the forefront. Further research in this area is needed to answer the question,"Is EVM cost effective in small projects?" The authors welcome knowledge sharing with other organizations that are striving to gain the benefits of EVM on small projects.

Arctic (and Antarctic) Observing Experiment - an Assessment of Methods to Measure Temperature over Polar Environments

NASA Astrophysics Data System (ADS)

Rigor, I. G.; Clemente-Colon, P.; Nghiem, S. V.; Hall, D. K.; Woods, J. E.; Henderson, G. R.; Zook, J.; Marshall, C.; Gallage, C.

2014-12-01

The Arctic environment has been undergoing profound changes; the most visible is the dramatic decrease in Arctic sea ice extent (SIE). These changes pose a challenge to our ability to measure surface temperature across the Polar Regions. Traditionally, the International Arctic Buoy Programme (IABP) and International Programme for Antarctic Buoys (IPAB) have measured surface air temperature (SAT) at 2-m height, which minimizes the ambiguity of measurements near of the surface. Specifically, is the temperature sensor measuring open water, snow, sea ice, or air? But now, with the dramatic decrease in Arctic SIE, increase in open water during summer, and the frailty of the younger sea ice pack, the IABP has had to deploy and develop new instruments to measure temperature. These instruments include Surface Velocity Program (SVP) buoys, which are commonly deployed on the world's ice-free oceans and typically measure sea surface temperature (SST), and the new robust Airborne eXpendable Ice Beacons (AXIB), which measure both SST and SAT. "Best Practice" requires that these instruments are inter-compared, and early results showing differences in collocated temperature measurements of over 2°C prompted the establishment of the IABP Arctic Observing Experiment (AOX) buoy test site at the US Department of Energy (DOE) Atmospheric Radiation Measurement (ARM) site in Barrow, Alaska. Preliminary results showed that the color of the hull of SVP buoys introduces a bias due to solar heating of the buoy. Since then, we have recommended that buoys should be painted white to reduce biases in temperature measurements due to different colors of the buoys deployed in different regions of the Arctic or the Antarctic. Measurements of SAT are more robust, but some of the temperature shields are susceptible to frosting. During our presentation we will provide an intercomparison of the temperature measurements at the AOX test site (i.e. high quality DOE/ARM observations compared with unattended buoy measurements, and satellite retrievals). We will also show how these data may be used to improve our record of temperature over polar environments.

Space Situational Awareness of Large Numbers of Payloads From a Single Deployment

NASA Astrophysics Data System (ADS)

Segerman, A.; Byers, J.; Emmert, J.; Nicholas, A.

2014-09-01

The nearly simultaneous deployment of a large number of payloads from a single vehicle presents a new challenge for space object catalog maintenance and space situational awareness (SSA). Following two cubesat deployments last November, it took five weeks to catalog the resulting 64 orbits. The upcoming Kicksat mission will present an even greater SSA challenge, with its deployment of 128 chip-sized picosats. Although all of these deployments are in short-lived orbits, future deployments will inevitably occur at higher altitudes, with a longer term threat of collision with active spacecraft. With such deployments, individual scientific payload operators require rapid precise knowledge of their satellites' locations. Following the first November launch, the cataloguing did not initially associate a payload with each orbit, leaving this to the satellite operators. For short duration missions, the time required to identify an experiment's specific orbit may easily be a large fraction of the spacecraft's lifetime. For a Kicksat-type deployment, present tracking cannot collect enough observations to catalog each small object. The current approach is to treat the chip cloud as a single catalog object. However, the cloud dissipates into multiple subclouds and, ultimately, tiny groups of untrackable chips. One response to this challenge may be to mandate installation of a transponder on each spacecraft. Directional transponder transmission detections could be used as angle observations for orbit cataloguing. Of course, such an approach would only be employable with cooperative spacecraft. In other cases, a probabilistic association approach may be useful, with the goal being to establish the probability of an element being at a given point in space. This would permit more reliable assessment of the probability of collision of active spacecraft with any cloud element. This paper surveys the cataloguing challenges presented by large scale deployments of small spacecraft, examining current methods. Potential new approaches are discussed, including simulations to evaluate their utility. Acknowledgement: This work was supported by the Office of the Assistant Secretary of Defense for R&E, via the Data-to-Decisions program.

Mechanisms of Günther Tulip filter tilting during transfemoral placement.

PubMed

Matsui, Y; Horikawa, M; Ohta, K; Jahangiri Noudeh, Y; Kaufman, J A; Farsad, K

The purpose of this study was to characterize the mechanisms of Günther Tulip filter (GTF) tilting during transfemoral placement in an experimental model with further validation in a clinical series. In an experimental study, 120 GTF placements in an inferior vena cava (IVC) model were performed using 6 configurations of pre-deployment filter position. The angle between the pre-deployment filter axis and IVC axis, and the proximity of the constrained filter legs to IVC wall prior to deployment were evaluated. The association of those pre-deployment factors with post-deployment filter tilting was analyzed. The association noted in the experimental study was then evaluated in a retrospective clinical series of 21 patients. In the experimental study, there was a significant association between the pre-deployment angle and post-deployment filter tilting (P<0.0001). With a low pre-deployment angle (≤5°), a significant association was noted between filter tilting and the proximity of the constrained filter legs to the far IVC wall (P=0.001). In a retrospective clinical study, a significant association between the pre-deployment angle and post-deployment filter tilting was also noted with a linear regression model (P=0.026). Significant association of the pre-deployment angle with post-deployment GTF tilting was shown in both the experimental and clinical studies. The experimental study also showed that proximity of filter legs is relevant when pre-deployment angle is small. Addressing these factors may result in a lower incidence of filter tilting. Copyright © 2017 Editions françaises de radiologie. Published by Elsevier Masson SAS. All rights reserved.

Deployable Propulsion and Power Systems for Solar System Exploration

NASA Technical Reports Server (NTRS)

Johnson, Les; Carr, John

2017-01-01

NASA is developing thin-film based, deployable propulsion, power and communication systems for small spacecraft that could provide a revolutionary new capability allowing small spacecraft exploration of the solar system. The Near Earth Asteroid (NEA) Scout reconnaissance mission will demonstrate solar sail propulsion on a 6U CubeSat interplanetary spacecraft and lay the groundwork for their future use in deep space science and exploration missions. Solar sails use sunlight to propel vehicles through space by reflecting solar photons from a large, mirror-like sail made of a lightweight, highly reflective material. This continuous photon pressure provides propellantless thrust, allowing for very high delta V maneuvers on long-duration, deep space exploration. Since reflected light produces thrust, solar sails require no onboard propellant. The Lightweight Integrated Solar Array and Transceiver (LISA-T) is a launch stowed, orbit deployed array on which thin-film photovoltaic and antenna elements are embedded. Inherently, small satellites are limited in surface area, volume, and mass allocation; driving competition between power, communications, and GN&C (guidance navigation and control) subsystems. This restricts payload capability and limits the value of these low-cost satellites. LISA-T is addressing this issue, deploying large-area arrays from a reduced volume and mass envelope - greatly enhancing power generation and communications capabilities of small spacecraft. The NEA Scout mission, funded by NASA's Advanced Exploration Systems Program and managed by NASA MSFC, will use the solar sail as its primary propulsion system, allowing it to survey and image one or more NEA's of interest for possible future human exploration. NEA Scout uses a 6U cubesat (to be provided by NASA's Jet Propulsion Laboratory), an 86 sq m solar sail and will weigh less than 12 kilograms. NEA Scout will be launched on the first flight of the Space Launch System in 2018. Similar in concept to the NEA Scout solar sail, the LISA-T array is designed to fit into a very small volume and provide abundant power and omnidirectional communications in just about any deployment configuration. The technology is being proposed for flight validation as early as 2019 in a low earth orbit demonstration using a 3U cubesat, of which less than 1U will be devoted to the LISA-T power and propulsion system. By leveraging recent advancements in thin films, photovoltaics and miniaturized electronics, new mission-level capabilities will be enabled aboard lower-cost small spacecraft instead of their more expensive, traditional counterparts, enabling a new generation of frequent, inexpensive deep space missions.

Rule-Based vs. Behavior-Based Self-Deployment for Mobile Wireless Sensor Networks

PubMed Central

Urdiales, Cristina; Aguilera, Francisco; González-Parada, Eva; Cano-García, Jose; Sandoval, Francisco

2016-01-01

In mobile wireless sensor networks (MWSN), nodes are allowed to move autonomously for deployment. This process is meant: (i) to achieve good coverage; and (ii) to distribute the communication load as homogeneously as possible. Rather than optimizing deployment, reactive algorithms are based on a set of rules or behaviors, so nodes can determine when to move. This paper presents an experimental evaluation of both reactive deployment approaches: rule-based and behavior-based ones. Specifically, we compare a backbone dispersion algorithm with a social potential fields algorithm. Most tests are done under simulation for a large number of nodes in environments with and without obstacles. Results are validated using a small robot network in the real world. Our results show that behavior-based deployment tends to provide better coverage and communication balance, especially for a large number of nodes in areas with obstacles. PMID:27399709

Link-quality measurement and reporting in wireless sensor networks.

PubMed

Chehri, Abdellah; Jeon, Gwanggil; Choi, Byoungjo

2013-03-04

Wireless Sensor networks (WSNs) are created by small hardware devices that possess the necessary functionalities to measure and exchange a variety of environmental data in their deployment setting. In this paper, we discuss the experiments in deploying a testbed as a first step towards creating a fully functional heterogeneous wireless network-based underground monitoring system. The system is mainly composed of mobile and static ZigBee nodes, which are deployed on the underground mine galleries for measuring ambient temperature. In addition, we describe the measured results of link characteristics such as received signal strength, latency and throughput for different scenarios.

Link-Quality Measurement and Reporting in Wireless Sensor Networks

PubMed Central

Chehri, Abdellah; Jeon, Gwanggil; Choi, Byoungjo

2013-01-01

Wireless Sensor networks (WSNs) are created by small hardware devices that possess the necessary functionalities to measure and exchange a variety of environmental data in their deployment setting. In this paper, we discuss the experiments in deploying a testbed as a first step towards creating a fully functional heterogeneous wireless network-based underground monitoring system. The system is mainly composed of mobile and static ZigBee nodes, which are deployed on the underground mine galleries for measuring ambient temperature. In addition, we describe the measured results of link characteristics such as received signal strength, latency and throughput for different scenarios. PMID:23459389

On the biomechanical analysis of the calories expended in a straight boxing jab.

PubMed

Zohdi, T I

2017-04-01

Boxing and related sports activities have become a standard workout regime at many fitness studios worldwide. Oftentimes, people are interested in the calories expended during these workouts. This note focuses on determining the calories in a boxer's jab, using kinematic vector-loop relations and basic work-energy principles. Numerical simulations are undertaken to illustrate the basic model. Multi-limb extensions of the model are also discussed. © 2017 The Author(s).

Confronting Emergent Nuclear-Armed Regional Adversaries: Prospects for Neutralization, Strategies for Escalation Management

DTIC Science & Technology

2015-01-01

might find multiple ways to blur the nuclear threshold if pushed to acts of desperation. Instead of expending all of its weapons in one suicidal ...the temptation (and any allied pressure) to punish the enemy or add demands that would significantly exceed the status quo ante bellum. Ultimately...multiple options at their disposal if pushed to acts of desperation. Instead of expending all of their weapons in one suicidal spasm, a savvy

Payload Performance Analysis for a Reusable Two-Stage-to-Orbit Vehicle

NASA Technical Reports Server (NTRS)

Tartabini, Paul V.; Beaty, James R.; Lepsch, Roger A.; Gilbert, Michael G.

2015-01-01

This paper investigates a unique approach in the development of a reusable launch vehicle where, instead of designing the vehicle to be reusable from its inception, as was done for the Space Shuttle, an expendable two stage launch vehicle is evolved over time into a reusable launch vehicle. To accomplish this objective, each stage is made reusable by adding the systems necessary to perform functions such as thermal protection and landing, without significantly altering the primary subsystems and outer mold line of the original expendable vehicle. In addition, some of the propellant normally used for ascent is used instead for additional propulsive maneuvers after staging in order to return both stages to the launch site, keep loads within acceptable limits and perform a soft landing. This paper presents a performance analysis that was performed to investigate the feasibility of this approach by quantifying the reduction in payload capability of the original expendable launch vehicle after accounting for the mass additions, trajectory changes and increased propellant requirements necessary for reusability. Results show that it is feasible to return both stages to the launch site with a positive payload capability equal to approximately 50 percent of an equivalent expendable launch vehicle. Further discussion examines the ability to return a crew/cargo capsule to the launch site and presents technical challenges that would have to be overcome.

Electromagnetic Simulations for an Axisymmetric Gregorian Reflector System for a Space Deployed Inflatable Antenna

DTIC Science & Technology

2016-01-22

Q. J. Wei, S. Pan, S. Mohan, and S. Seager, Inflatable antenna for CubeSat : fabrication, deployment and results of experimental tests, 2014 IEEE...Aerospace Conference, pp. 1- 12. [8] A. Babuscia, T. Choi, C. Lee, and K-M. Cheung, Inflatable antennas and arrays for interplanetary communication using CubeSats and SmallSats, 2015 IEEE Aerospace Conference, pp. 1-9.

Distributed sensor network for local-area atmospheric modeling

NASA Astrophysics Data System (ADS)

French, Patrick D.; Lovell, John S.; Seaman, Nelson L.

2003-09-01

In the event of a Weapons of Mass Destruction (WMD) chemical or radiological release, quick identification of the nature and source of the release can support efforts to warn, protect and evacuate threatened populations downwind; mitigate the release; provide more accurate plume forecasting; and collect critical transient evidence to help identify the perpetrator(s). Although there are systems available to assist in tracking a WMD release and then predicting where a plume may be traveling, there are no reliable systems available to determine the source location of that release. This would typically require the timely deployment of a remote sensing capability, a grid of expendable air samplers, or a surface sampling plan if the plume has dissipated. Each of these typical solutions has major drawbacks (i.e.: excessive cost, technical feasibility, duration to accomplish, etc...). This paper presents data to support the use of existing rapid-response meteorological modeling coupled with existing transport and diffusion modeling along with a prototype cost-effective situational awareness monitor which would reduce the sensor network requirements while still accomplishing the overall mission of having a 95% probability in converging on a source location within 100 meters.

Employees lower Cassini's upper experiment module and base onto a work stand in the PHSF

NASA Technical Reports Server (NTRS)

1997-01-01

Employees in the Payload Hazardous Servicing Facility (PHSF) lower the upper experiment module and base of the Cassini orbiter onto a work stand during prelaunch processing, testing and integration work in that facility. The Cassini orbiter and Huygens probe being processed at KSC are the two primary components of the Cassini spacecraft, which will be launched on a Titan IVB/Centaur expendable launch vehicle from Cape Canaveral Air Station. Cassini will explore Saturn, its rings and moons for four years. The Huygens probe, designed and developed for the European Space Agency (ESA), will be deployed from the orbiter to study the clouds, atmosphere and surface of Saturn's largest moon, Titan. The orbiter was designed and assembled at NASA's Jet Propulsion Laboratory in California. Following postflight inspections, integration of the 12 science instruments not already installed on the orbiter will be completed. Then, the parabolic high-gain antenna and the propulsion module will be mated to the orbiter, followed by the Huygens probe, which will complete spacecraft integration. The Cassini mission is targeted for an Oct. 6 launch to begin its 6.7-year journey to the Saturnian system. Arrival at the planet is expected to occur around July 1, 2004.

KSC-97pc679

NASA Image and Video Library

1997-04-21

Workers prepare to tow away the large container with the Cassini orbiter from KSC’s Shuttle Landing Facility. The orbiter just arrived on the U.S. Air Force C-17 air cargo plane, shown here, from Edwards Air Force Base, California. The orbiter and the Huygens probe already being processed at KSC are the two primary components of the Cassini spacecraft, which will be launched on a Titan IVB/Centaur expendable launch vehicle from Cape Canaveral Air Station. Cassini will explore Saturn, its rings and moons for four years. The Huygens probe, designed and developed for the European Space Agency (ESA), will be deployed from the orbiter to study the clouds, atmosphere and surface of Saturn’s largest moon, Titan. The orbiter was designed and assembled at NASA’s Jet Propulsion Laboratory in California. Following postflight inspections, integration of the 12 science instruments not already installed on the orbiter will be completed. Then, the parabolic high-gain antenna and the propulsion module will be mated to the orbiter, followed by the Huygens probe, which will complete spacecraft integration. The Cassini mission is targeted for an Oct. 6 launch to begin its 6.7-year journey to the Saturnian system. Arrival at the planet is expected to occur around July 1, 2004

KSC-97pc729

NASA Image and Video Library

1997-04-22

An employee in the Payload Hazardous Servicing Facility (PHSF) sews thermal insulation material on the front heat shield of the Huygens probe during prelaunch processing testing and integration in that facility, with the probe’s back cover in the background. The Huygens probe and the Cassini orbiter being processed at KSC are the two primary components of the Cassini spacecraft, which will be launched on a Titan IVB/Centaur expendable launch vehicle from Cape Canaveral Air Station. Cassini will explore Saturn, its rings and moons for four years. The Huygens probe, designed and developed for the European Space Agency (ESA), will be deployed from the orbiter to study the clouds, atmosphere and surface of Saturn’s largest moon, Titan. The orbiter was designed and assembled at NASA’s Jet Propulsion Laboratory in California. Following postflight inspections, integration of the 12 science instruments not already installed on the orbiter will be completed. Then, the parabolic high-gain antenna and the propulsion module will be mated to the orbiter, followed by the Huygens probe, which will complete spacecraft integration. The Cassini mission is targeted for an Oct. 6 launch to begin its 6.7-year journey to the Saturnian system. Arrival at the planet is expected to occur around July 1, 2004

KSC-97pc677

NASA Image and Video Library

1997-04-21

Workers begin unloading the Cassini orbiter from a U.S. Air Force C-17 air cargo plane after its arrival at KSC’s Shuttle Landing Facility from Edwards Air Force Base, California. The orbiter and the Huygens probe already being processed at KSC are the two primary components of the Cassini spacecraft, which will be launched on a Titan IVB/Centaur expendable launch vehicle from Cape Canaveral Air Station. Cassini will explore Saturn, its rings and moons for four years. The Huygens probe, designed and developed for the European Space Agency (ESA), will be deployed from the orbiter to study the clouds, atmosphere and surface of Saturn’s largest moon, Titan. The orbiter was designed and assembled at NASA’s Jet Propulsion Laboratory in California. Following postflight inspections, integration of the 12 science instruments not already installed on the orbiter will be completed. Then, the parabolic high-gain antenna and the propulsion module will be mated to the orbiter, followed by the Huygens probe, which will complete spacecraft integration. The Cassini mission is targeted for an Oct. 6 launch to begin its 6.7-year journey to the Saturnian system. Arrival at the planet is expected to occur around July 1, 2004

Energy Performance Assessment of Virtualization Technologies Using Small Environmental Monitoring Sensors

PubMed Central

Liu, Lu; Masfary, Osama; Antonopoulos, Nick

2012-01-01

The increasing trends of electrical consumption within data centres are a growing concern for business owners as they are quickly becoming a large fraction of the total cost of ownership. Ultra small sensors could be deployed within a data centre to monitor environmental factors to lower the electrical costs and improve the energy efficiency. Since servers and air conditioners represent the top users of electrical power in the data centre, this research sets out to explore methods from each subsystem of the data centre as part of an overall energy efficient solution. In this paper, we investigate the current trends of Green IT awareness and how the deployment of small environmental sensors and Site Infrastructure equipment optimization techniques which can offer a solution to a global issue by reducing carbon emissions. PMID:22778660

Update on Progress of Space Station Integrated Kinetic Launcher for Orbital Payload Systems (SSIKLOPS) - Cyclops

NASA Technical Reports Server (NTRS)

Newswander, Daniel; Smith, James P.; Lamb, Craig R.; Ballard, Perry G.

2014-01-01

The Space Station Integrated Kinetic Launcher for Orbital Payload Systems (SSIKLOPS), known as "Cyclops" to the International Space Station (ISS) community, was introduced last August (2013) during Technical Session V: From Earth to Orbit of the 27th Annual AIAA/USU Conference on Small Satellites. Cyclops is a collaboration between the NASA ISS Program, NASA Johnson Space Center Engineering, and Department of Defense (DoD) Space Test Program (STP) communities to develop a dedicated 50-100 kg class ISS small satellite deployment system. This paper will address the progress of Cyclops through its fabrication, assembly, flight certification, and on-orbit demonstration phases. It will also go into more detail regarding its anatomy, its satellite deployment concept of operations, and its satellite interfaces and requirements. Cyclops is manifested to fly on Space-X 4 which is currently scheduled in July 2014 with its initial satellite deployment demonstration of DoD STP's SpinSat and UT/TAMU's Lonestar satellites being late summer or fall of 2014.

E-Government Attempts in Small Island Developing States: The Rate of Corruption with Virtualization.

PubMed

Sari, Arif

2017-12-01

In recent years, many Small Island Developing State (SIDS) governments have worked to increase openness and transparency of their transactions as a means to enhance efficiency and reduce corruption in their economies. In order to achieve a cost-effective and efficient strategy to implement a transparent government, Information Communication Technologies offer an opportunity of virtualization by deploying e-government services to promote transparency, accountability and consistency in the public sector and to minimize corruption. This paper explores the potential impact of government virtualization by SIDS and against corruption by comparing the corruption perception index (CPI) rates of 15 SIDS countries. The CPI relates to the degree by which corruption is perceived to exist among public officials and politicians by business people and country analysts. In order to reveal the long-term impact of virtual deployment and its consequences on corruption, an in-depth case analysis based on the CPI index rates was conducted on the deployment of the e-government system in Cyprus.

Activity Behaviours in Lean and Morbidly Obese Pregnant Women.

PubMed

Fazzi, Caterina; Mohd-Shukri, Nor; Denison, Fiona C; Saunders, David H; Norman, Jane E; Reynolds, Rebecca M

2018-05-17

Interventions to increase physical activity in pregnancy are challenging for morbidly obese women. Targeting sedentary behaviours may be a suitable alternative to increase energy expenditure. We aimed to determine total energy expenditure, and energy expended in sedentary activities in morbidly obese and lean pregnant women. We administered the Pregnancy Physical Activity Questionnaire PPAQ (non-objective) and the Actical accelerometer (objective) to morbidly obese (BMI≥40kg/m²) and lean (BMI≤25Kg/M²) pregnant women recruited in early (<24 weeks), and late (≥24 weeks) gestation. Data are mean (SD). Morbidly obese pregnant women reported expending significantly more energy per day in early (n=140 vs 109; 3198.4 (1847.1) vs 1972.3 (10284.8) Kcal/day, p<0.0001) and late (n=104 vs 64; 3078.2 (1356.5) vs 1947.5 (652.0) Kcal/day, p<0.0001) pregnancy, and expended significantly more energy in sedentary activities, in early (816.1 (423.5) vs 540.1 (244.9) Kcal/day, p<0.0001) and late (881.6 (455.4) vs 581.1 (248.5) Kcal/day, p<0.0001) pregnancy, than lean pregnant women. No differences were observed in the proportion of energy expended sedentary between lean and morbidly obese pregnant women. The greater total energy expenditure in morbidly obese pregnant women was corroborated by Actical accelerometer in early (n=14 per group, obese 1167.7 (313.6) Kcal; lean 781.1 (210.1) Kcal, p<0.05), and in late (n=14 per group, obese 1223.6 (351.5) Kcal; lean 893.7 (175.9) Kcal, p<0.05) pregnancy. In conclusion, non-objective and objective measures showed morbidly obese pregnant women expended more energy per day than lean pregnant. Further studies are needed to determine whether sedentary behaviours are a suitable target for intervention in morbidly obese pregnancy. This article is protected by copyright. All rights reserved. This article is protected by copyright. All rights reserved.

When exercise does not pay: Counterproductive effects of impending exercise on energy intake among restrained eaters.

PubMed

Sim, Aaron Y; Lee, Li Ling; Cheon, Bobby K

2018-04-01

Evidence suggests people may overestimate the effectiveness of future positive behaviour, leading to counterproductive behaviours in the present. Applied to weight-management, we hypothesize that inaccurate expectations about impending exercise may impede weight management by promoting overconsumption prior to exercise. This study aimed to determine how expectations about impending exercise and its potential ability to expend energy may influence i) energy intake before exercise and ii) overall energy balance (energy intake minus energy expended via exercise). Using a randomised, counterbalanced design, 21 inactive, overweight males, following a baseline session, completed two experimental trials: i) ad-libitum snack meal (potato-crisps) followed by an exercise session (SE) and ii) ad-libitum snack meal only (SO). There was no main effect of condition (SE vs. SO) on ad-libitum snack intake (p = .917). However, after accounting for dietary restraint (covariate), a difference in snack intake between SE and SO was revealed (p = .050). Specifically, participants who scored higher in dietary restraint consumed more in the SE (vs. SO) session (162 ± 359 kcal more) compared with participants who scored lower in dietary restraint (89 ± 135 kcal less). Among restrained eaters, the relative (net) energy consumed after accounting for energy expended from exercise in SE was not different from the energy consumed in the SO condition, suggesting that energy expended via exercise in SE does not appear to negate extra energy consumed in this condition compared with SO. Of interest, desire to eat and prospective food consumption ratings at the start of the trial were greater (p ≤ .029) in SE compared with SO. Findings suggest that restrained-eaters are at risk of adopting compensatory eating behaviour that may impede negative energy balance typically resulting from exercise (i.e. expending insufficient energy to negate compensatory energy intake). Copyright © 2017 Elsevier Ltd. All rights reserved.

Relay NBS Graft with the Plus Delivery System to Improve Deployment in Aortic Arch with Small Radius Curve

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

Ferro, Carlo; Rossi, Umberto G., E-mail: urossi76@hotmail.com; Seitun, Sara

The purpose of this report is to describe deployment of the Relay NBS Thoracic Stent Graft with the Plus Delivery System (Bolton Medical, Sunrise, FL) in a flexible resin arch model with a 15-mm radius curve as well as our preliminary clinical results. The Relay NBS graft with the Plus Delivery System was evaluated by way of bench testing, which was performed with stent grafts with diameters ranging from 24 to 46 mm and lengths ranging from 100 to 250 mm in flexible resin arch models with a 15-mm arch radius of curvature. The deployment sequence was analyzed. The Relaymore » NBS graft with the Plus Delivery System was deployed in two patients, respectively, having a 6.5-cm penetrating aortic ulcer of the proximal third of the descending thoracic aorta and a DeBakey type-I aortic dissection with chronic false lumen dilatation after surgery due to an entry site at the distal thoracic aorta. Bench tests showed proper conformation and apposition of the Relay NBS graft with the Plus Delivery System in the flexible resin model. This stent graft was deployed successfully into the two patients with a correct orientation of the first stent and without early or late complications. The Relay NBS graft with the Plus Delivery System ensures an optimal conformation and apposition of the first stent in the aortic arch with a small radius of curvature.« less

Community Air Sensor Network (CAIRSENSE) Project: Lower Cost, Continuous Ambient Monitoring Methods

EPA Science Inventory

Advances in air pollution sensor technology have enabled the development of small and low cost systems to measure outdoor air pollution. The deployment of numerous sensors across a small geographic area would have potential benefits to supplement existing monitoring networks and ...

Electromagnetic panel deployment and retraction using the geomagnetic field in LEO satellite missions

NASA Astrophysics Data System (ADS)

Inamori, Takaya; Sugawara, Yoshiki; Satou, Yasutaka

2015-12-01

Increasingly, spacecraft are installed with large-area structures that are extended and deployed post-launch. These extensible structures have been applied in several missions for power generation, thermal radiation, and solar propulsion. Here, we propose a deployment and retraction method using the electromagnetic force generated when the geomagnetic field interacts with electric current flowing on extensible panels. The panels are installed on a satellite in low Earth orbit. Specifically, electrical wires placed on the extensible panels generate magnetic moments, which interfere with the geomagnetic field. The resulting repulsive and retraction forces enable panel deployment and retraction. In the proposed method, a satellite realizes structural deployment using simple electrical wires. Furthermore, the satellite can achieve not only deployment but also retraction for avoiding damage from space debris and for agile attitude maneuvers. Moreover, because the proposed method realizes quasi-static deployment and the retraction of panels by electromagnetic forces, low impulsive force is exerted on fragile panels. The electrical wires can also be used to detect the panel deployment and retraction and generate a large magnetic moment for attitude control. The proposed method was assessed in numerical simulations based on multibody dynamics. Simulation results shows that a small cubic satellite with a wire current of 25 AT deployed 4 panels (20 cm × 20 cm) in 500 s and retracted 4 panels in 100 s.

Entrainment and mixing of shelf/slope waters in the near-surface Gulf Stream

NASA Astrophysics Data System (ADS)

Lillibridge, J. L., III; Hitchcock, G.; Rossby, T.; Lessard, E.; Mork, M.; Golmen, L.

1990-08-01

An interdisciplinary study of the entrainment of shelf and slope waters in the Gulf Stream front was undertaken in October 1985 northeast of Cape Hatteras. Fifteen hydrographic transects of the Gulf Stream front and of the shelf water intrusion known as Ford water were completed in 2 1/2 days with a towed undulating profiler, the SeaSoar, equipped with a conductivity-temperature-depth probe and a fluorometer. Upstream sections within 50 km of the shelf break show entrainment of surface and subsurface waters along the northern edge of the high-velocity Gulf Stream. The low-salinity core, first observed at 70 m, is subducted to >100 m. The subsurface Ford water is also at a maximum in chlorophyll, fluorescence, and dissolved oxygen and contains a distinct diatom assemblage of nearshore species. Productivity rates in the Ford water may be equivalent to those in slope waters. Expendable current profilers yield an estimated transport for subsurface shelf waters of 1 to 5×105 m3 s-1 and indicate that vertical shear at the depth of maximum static stability is typically 2×10-2 s-1. A bulk Richardson number is estimated over vertical scales of several meters by combining SeaSoar density profiles with velocity shear from concurrent expendable current profiler deployments. The minimum values are generally >1, and only infrequently are they at or below the 0.25 threshold for shear instability. The presence of double-diffusive processes around the low-salinity core of Ford water is indicated by elevated conductivity Cox numbers. The stability parameter "Turner angle" shows that low-salinity Ford water and its associated T-S property front are sites of double-diffusive mixing, given general agreement between the distributions of Turner angle and Cox number. We conclude that double-diffusive processes are more important than shear flow instability in governing cross-isopycnal mixing. However, downstream transit times are so swift that no measurable change or decay occurs in the Ford water. This explains the occurrence of distinct shelf water phytoplankton species within the low-salinity waters downstream of Cape Hatteras.

Dimensions of operational stress and forms of unacceptable risk taking with small arms and munitions.

PubMed

Ben-Shalom, Uzi

2015-01-01

Accidents with small arms and munitions during deployment is a significant safety concern for leaders and safety specialists in combat units. Operational stress may lead to forms of unacceptable risk taking with small arms that may underlie some of these accidents. The present research studied the correlation between two dimensions of operational stress, two forms of risk taking with small arms among combat unit soldiers and possible mediators. The dimensions of operational threat, negative affect and personality profile from the EPQ-R-S were predictors; "exaggerated preparedness" and "risky games with small arms and munitions" were dependent variables; safety climate of the platoon served as a mediator variable. The participants were 461 compulsory service combat soldiers in 31 companies. This field study was conducted during period of top security alert. The results reveal that perceived threat is indeed correlated with exaggerated operational preparedness whereas general emotional state was correlated with risky games with small arms. Safety climate mediated only the correlation between general emotional state and risky games with small arms and munitions. Preparedness and risky games were predicted by the interaction of Psychoticism and the Lie Scale from the EPQ-R-S. The results may enhance the efforts in reducing risk taking and prevention of accidents with small arms and munitions during and following deployment.

Heart rate and estimated energy expenditure of flapping and gliding in black-browed albatrosses.

PubMed

Sakamoto, Kentaro Q; Takahashi, Akinori; Iwata, Takashi; Yamamoto, Takashi; Yamamoto, Maki; Trathan, Philip N

2013-08-15

Albatrosses are known to expend only a small amount of energy during flight. The low energy cost of albatross flight has been attributed to energy-efficient gliding (soaring) with sporadic flapping, although little is known about how much time and energy albatrosses expend in flapping versus gliding during cruising flight. Here, we examined the heart rates (used as an instantaneous index of energy expenditure) and flapping activities of free-ranging black-browed albatrosses (Thalassarche melanophrys) to estimate the energy cost of flapping as well as time spent in flapping activities. The heart rate of albatrosses during flight (144 beats min(-1)) was similar to that while sitting on the water (150 beats min(-1)). In contrast, heart rate was much higher during takeoff and landing (ca. 200 beats min(-1)). Heart rate during cruising flight was linearly correlated with the number of wing flaps per minute, suggesting an extra energy burden of flapping. Albatrosses spend only 4.6±1.4% of their time flapping during cruising flight, which was significantly lower than during and shortly after takeoff (9.8±3.5%). Flapping activity, which amounted to just 4.6% of the time in flight, accounted for 13.3% of the total energy expenditure during cruising flight. These results support the idea that albatrosses achieve energy-efficient flight by reducing the time spent in flapping activity, which is associated with high energy expenditure.

Value Focused Thinking Approach Using Multivariate Validation for Junior Enlisted Performance Reporting in the United States Air Force

DTIC Science & Technology

2014-03-22

consideration for enlisted airmen, has largely become a non factor due to over-inflated scores, with other factors such as specialty knowledge test scores, time...appraisal. Secondly, an Artificial Neural Network (ANN) classifier will be applied to the large sample data to confirm that the values solicited to...jobs, employees make themselves vulnerable to the organization when they expend effort. If extra effort is expended to reduce errors or defects, or

Visible and Thermal Imaging of Sea Ice and Open Water from Coast Guard Arctic Domain Awareness Flights

DTIC Science & Technology

2014-09-30

dropsondes, micro- aircraft), cloud top/base heights Arctic Ocean Surface Temperature project Steele Buoy drops for SLP , SST, SSS, & surface velocity...Colón & Vancas (NIC) Drop buoys for SLP , temperature and surface velocity Waves & Fetch in the MIZ Thompson SWIFTS buoys measuring wave energy...Expendable CTD, AXCP= Air Expendable Current Profiler, SLP = Sea Level atmospheric Pressure, SST= Seas Surface Temperature, A/C= aircraft, FSD= Floe Size Distribution, SIC=Sea Ice Concentration

25 CFR 514.14 - What happens if a tribe overpays its fees or if the Commission does not expend the full amount of...

Code of Federal Regulations, 2013 CFR

2013-04-01

... 25 Indians 2 2013-04-01 2013-04-01 false What happens if a tribe overpays its fees or if the Commission does not expend the full amount of fees collected in a fiscal year? 514.14 Section 514.14 Indians NATIONAL INDIAN GAMING COMMISSION, DEPARTMENT OF THE INTERIOR GENERAL PROVISIONS FEES § 514.14 What happens if a tribe overpays its fees or if th...

25 CFR 514.14 - What happens if a tribe overpays its fees or if the Commission does not expend the full amount of...

Code of Federal Regulations, 2014 CFR

2014-04-01

... 25 Indians 2 2014-04-01 2014-04-01 false What happens if a tribe overpays its fees or if the Commission does not expend the full amount of fees collected in a fiscal year? 514.14 Section 514.14 Indians NATIONAL INDIAN GAMING COMMISSION, DEPARTMENT OF THE INTERIOR GENERAL PROVISIONS FEES § 514.14 What happens if a tribe overpays its fees or if th...

30 Brigade Combat Teams: Is the Army too Small

DTIC Science & Technology

2016-12-01

are described in Table 3. Each entity travels through five servers.  Deploy: This server represents the time it takes to deploy from home station...estimated to average 1 hour per response, including the time for reviewing instruction, searching existing data sources, gathering and maintaining...ABSTRACT (maximum 200 words) The purpose of this thesis is to determine the impact of a contingency operation on Army dwell time . The Department of

Fit to Fight: Admin or Ethos? Embedding Fitness in Air Force Culture

DTIC Science & Technology

2009-02-12

including decreased levels of anxiety , depression , fatigue, and confusion, and improved memory and cognition.7 Maj Denise Hollywood highlighted...Ballaro also found a strong “statistically significant relationship between individuals who returned . . . early [from deployment] due to illness or...injuries and individuals who did not exercise while deployed.” Granted, sample size was small, but of the 89 early returners, 62--or 70 percent--did

Occupational therapists as dog handlers: the collective experience with animal-assisted therapy in Iraq.

PubMed

Fike, Lorie; Najera, Cecilia; Dougherty, David

2012-01-01

The first pair of US Army animal-assisted therapy (AAT) dogs deployed to Iraq in December 2007 with the 85th Medical Detachment Combat and Operational Stress Control unit. As of this writing, 6 dogs have deployed to Iraq and Afghanistan, offering Soldiers a small reminder of home. Army occupational therapists led the way in this endeavor as primary handlers; the path has been rocky but ultimately rewarding. This article depicts how occupational therapists used AAT and animal-assisted activities to help Soldiers cope with the stressors of living in a deployed environment. Challenges and lessons-learned, including anecdotal examples, are discussed.

Space research - At a crossroads

NASA Technical Reports Server (NTRS)

Mcdonald, Frank B.

1987-01-01

Efforts which must be expended if U.S. space research is to regain vitality in the next few years are discussed. Small-scale programs are the cornerstone for big science projects, giving both researchers and students a chance to practice the development of space missions and hardware and identify promising goals for larger projects. Small projects can be carried aloft by balloons, sounding rockets, the Shuttle and ELVs. It is recommended that NASA continue the development of remote sensing systems, and join with other government agencies to fund space-based materials science, space biology and medical research. Increased international cooperation in space projects is necessary for affording moderate to large scale missions, for political reasons, and to maximize available space resources. Finally, the establishment and funding of long-range goals in space, particularly the development of the infrastructure and technologies for the exploration and colonization of the planets, must be viewed as the normal outgrowth of the capabilities being developed for LEO operations.

A robust quantitative near infrared modeling approach for blend monitoring.

PubMed

Mohan, Shikhar; Momose, Wataru; Katz, Jeffrey M; Hossain, Md Nayeem; Velez, Natasha; Drennen, James K; Anderson, Carl A

2018-01-30

This study demonstrates a material sparing Near-Infrared modeling approach for powder blend monitoring. In this new approach, gram scale powder mixtures are subjected to compression loads to simulate the effect of scale using an Instron universal testing system. Models prepared by the new method development approach (small-scale method) and by a traditional method development (blender-scale method) were compared by simultaneously monitoring a 1kg batch size blend run. Both models demonstrated similar model performance. The small-scale method strategy significantly reduces the total resources expended to develop Near-Infrared calibration models for on-line blend monitoring. Further, this development approach does not require the actual equipment (i.e., blender) to which the method will be applied, only a similar optical interface. Thus, a robust on-line blend monitoring method can be fully developed before any large-scale blending experiment is viable, allowing the blend method to be used during scale-up and blend development trials. Copyright © 2017. Published by Elsevier B.V.

Mars Sample Return and Flight Test of a Small Bimodal Nuclear Rocket and ISRU Plant

NASA Technical Reports Server (NTRS)

George, Jeffrey A.; Wolinsky, Jason J.; Bilyeu, Michael B.; Scott, John H.

2014-01-01

A combined Nuclear Thermal Rocket (NTR) flight test and Mars Sample Return mission (MSR) is explored as a means of "jump-starting" NTR development. Development of a small-scale engine with relevant fuel and performance could more affordably and quickly "pathfind" the way to larger scale engines. A flight test with subsequent inflight postirradiation evaluation may also be more affordable and expedient compared to ground testing and associated facilities and approvals. Mission trades and a reference scenario based upon a single expendable launch vehicle (ELV) are discussed. A novel "single stack" spacecraft/lander/ascent vehicle concept is described configured around a "top-mounted" downward firing NTR, reusable common tank, and "bottom-mount" bus, payload and landing gear. Requirements for a hypothetical NTR engine are described that would be capable of direct thermal propulsion with either hydrogen or methane propellant, and modest electrical power generation during cruise and Mars surface insitu resource utilization (ISRU) propellant production.

Experienced and Anticipated Pride and Shame as Predictors of Goal-Directed Behavior.

PubMed

Gilchrist, Jenna D; Conroy, David E; Sabiston, Catherine M

2017-12-01

This study examined how experienced and anticipated pride and shame were related to time spent training and effort expended toward training the following week. Participants (N = 158, 76% women; M age  = 35.51, SD = 10.29 years) training for a marathon/half-marathon completed a weekly online questionnaire for 5 weeks leading up to a race. In the multilevel models, time spent training was positively predicted by race proximity, age, and effort expended that week. Effort expended toward training was predicted by the current week's effort, the amount of time spent training that week, and was greater for participants who usually reported experiencing more pride than others. Neither anticipated pride or shame predicted time or effort, nor did experienced shame. The findings indicate that it is functional to foster high levels of pride when training for a long-distance race. Further work is needed to ascertain the relationship between anticipated emotions on goal-directed behavior.

Injury Patterns Sustained in Fatal Motor Vehicle Collisions with Driver's Third-Generation Airbag Deployment.

PubMed

Kuk, Mariya; Shkrum, Michael J

2018-05-01

The Office of the Chief Coroner for Ontario database for 2011-2012 was used to compare fatal injury patterns in drivers whose third-generation airbags deployed compared to first- and second-generation airbag deployments and airbag nondeployments with and without seatbelt use. There were 110 frontal and offset frontal crashes analyzed. The small sample size meant that the odds of craniocerebral, cervical spinal, thoracic, and abdominal injuries were not statistically different for airbag generation, deployment status, and seatbelt use; however, the risk of fatal thoracic injuries in third- and second-generation cases was increased. Seatbelt usage in third- and second-generation deployment cases reduced the risk of all injuries except abdominal trauma. High severity impacts and occupant compartment intrusion were frequently observed. The analyses in this retrospective study were challenged by data that were not collated in a standardized way and were limited in details about scene, vehicle, and driver variables. © 2017 American Academy of Forensic Sciences.

PANSAT satellite deployment from STS-95 Discovery's payload bay

NASA Image and Video Library

1998-10-30

STS095-E-5041 (30 Oct. 1998) --- PANSAT, a nonrecoverable satellite developed by the Naval Postgraduate School (NPS) in Monterey, California, is silhouetted against a sunglint effect on ocean waters below, following its deployment from the cargo bay of the Earth-orbiting Space Shuttle Discovery. The small ball-shaped payload is basically a tiny telecommunications satellite. The photo was recorded with an electronic still camera (ESC) at 1:49:33 GMT, Oct. 30.

Deployment Threats to Rapid Deployment Forces

DTIC Science & Technology

1982-12-01

may take two weeks. The same process occurs in people who move rapidly from a time zone in which they are well-adapted to a time zone that is hours...travel is a complex process involving change and transition. Some of these changes are small and apparently insignificant, others loom large in their... process of depart- ing is not innocuous. It must be viewed as a personsal transition that may have a significant potential for stress production

Trillium Horizon, A Small Portable Observatory Grade Seismometer For Direct Bury And Vault Use

NASA Astrophysics Data System (ADS)

Moores, A.; Parker, T.; Bainbridge, G.

2017-12-01

As of August 2017 almost 5 years of data have been collected from broadband seismic sensors designed for direct burial applications. These first posthole instruments have been deployed in a wide range of extremely challenging environments such as dynamic ice and snow environments, extreme wet and dry conditions in soils of high clay content, and steep creeping terrain. In all use cases the direct burial approach has consistently provided high quality data when compared to shallow vault installations. In this presentation we extract and analyze operational performance data, including tilt information from mass position time series recorded at direct burial installations and at temporary shallow vault deployments. This data shows that while higher tilt tolerance is required for data quality outcome certainty in some installations, the majority of installations can be addressed by a smaller instrument with a narrower tilt range hence reducing size and cost. The lessons learned from this real world field data have guided the development of a new smaller, less expensive instrument, Trillium Horizon.Based on this analysis and and user feedback from many direct burial deployments, the Trillium Horizon seismometer has been developed as a simple versatile instrument to span the majority of deployment scenarios and specific use cases including shallow direct bury deployments, traditional piers, and problematic wet vault installs. With its small size, robust waterproof case and connector, +/-1.5° tilt range, dual-purpose cable, and accessories for both posthole and vault installation, Trillium Horizon is optimized for usability as well as performance.

Safety Testing of Lithium (Sulfur Dioxide) Battery for Expendable, Mobile, ASW Training Target (EMATT)

DTIC Science & Technology

1988-12-01

Projict (0704.0115), YlissiengtOn, DC ;(1503. 1. AGENCY USE ONLY (Leave blank) 2. REPORT DATE 3. REOTTYPE AN) DATES COVERED 4. TITLE AND SUBTITLE 1...EXPENDABLE, MOBILE, ASW TRAINING TARGET (EMATT) 1-1 NSWC TR 88-254 The EMATT unit was first designed to use a lithium/sulfuryl chloride (Li/SO2 CI 2 ) "DD...in Table 3-1. Short Circuit Test The battery was shorted by the use of a remotely controlled relay. The relay, rated at 100 amp 250V, was employed

Final Report

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

Segre, Carlo, Ph.D.

2005-03-30

In December of 2004, upon hearing of the DOE decision to terminate this grant, a no-cost extension was requested to allow us to expend residual funds from the 2004 calendar year. These funds have been used to support MR-CAT staff as we transition to other funding. As of this writing, the funds have been expended. Over the past four years of DOE operations funding, MR-CAT has become one of the most productive sectors at the Advanced Photon Source. This report will list the overall accomplishments of the collaboration during the time of DOE funding.

Development and parametric evaluation of the prototype 2 and 3 flash evaporators

NASA Technical Reports Server (NTRS)

Hixon, C. W.; Dietz, J. B.

1975-01-01

Development of the Prototype 2 and 3 flash evaporator heat sinks which vaporize an expendable fluid to cool a heat transport fluid loop is reported. The units utilize Freon 21 as the heat transport fluid and water as the expendable fluid to meet the projected performance requirements of the space shuttle for both on-orbit and ascent/reentry operations. The evaporant is pulse-sprayed by on-off control onto heat transfer surfaces containing the transport fluid and exhausted to the vacuum environment through fixed area exhaust ducts.

NASA work unit system users manual

NASA Technical Reports Server (NTRS)

1972-01-01

The NASA Work Unit System is a management information system for research tasks (i.e., work units) performed under NASA grants and contracts. It supplies profiles to indicate how much effort is being expended to what types of research, where the effort is being expended, and how funds are being distributed. The user obtains information by entering requests on the keyboard of a time-sharing terminal. Responses are received as video displays or typed messages at the terminal, or as lists printed in the computer room for subsequent delivery by messenger.

On Efficient Deployment of Wireless Sensors for Coverage and Connectivity in Constrained 3D Space.

PubMed

Wu, Chase Q; Wang, Li

2017-10-10

Sensor networks have been used in a rapidly increasing number of applications in many fields. This work generalizes a sensor deployment problem to place a minimum set of wireless sensors at candidate locations in constrained 3D space to k -cover a given set of target objects. By exhausting the combinations of discreteness/continuousness constraints on either sensor locations or target objects, we formulate four classes of sensor deployment problems in 3D space: deploy sensors at Discrete/Continuous Locations (D/CL) to cover Discrete/Continuous Targets (D/CT). We begin with the design of an approximate algorithm for DLDT and then reduce DLCT, CLDT, and CLCT to DLDT by discretizing continuous sensor locations or target objects into a set of divisions without sacrificing sensing precision. Furthermore, we consider a connected version of each problem where the deployed sensors must form a connected network, and design an approximation algorithm to minimize the number of deployed sensors with connectivity guarantee. For performance comparison, we design and implement an optimal solution and a genetic algorithm (GA)-based approach. Extensive simulation results show that the proposed deployment algorithms consistently outperform the GA-based heuristic and achieve a close-to-optimal performance in small-scale problem instances and a significantly superior overall performance than the theoretical upper bound.

Stent deployment protocol for optimized real-time visualization during endovascular neurosurgery.

PubMed

Silva, Michael A; See, Alfred P; Dasenbrock, Hormuzdiyar H; Ashour, Ramsey; Khandelwal, Priyank; Patel, Nirav J; Frerichs, Kai U; Aziz-Sultan, Mohammad A

2017-05-01

Successful application of endovascular neurosurgery depends on high-quality imaging to define the pathology and the devices as they are being deployed. This is especially challenging in the treatment of complex cases, particularly in proximity to the skull base or in patients who have undergone prior endovascular treatment. The authors sought to optimize real-time image guidance using a simple algorithm that can be applied to any existing fluoroscopy system. Exposure management (exposure level, pulse management) and image post-processing parameters (edge enhancement) were modified from traditional fluoroscopy to improve visualization of device position and material density during deployment. Examples include the deployment of coils in small aneurysms, coils in giant aneurysms, the Pipeline embolization device (PED), the Woven EndoBridge (WEB) device, and carotid artery stents. The authors report on the development of the protocol and their experience using representative cases. The stent deployment protocol is an image capture and post-processing algorithm that can be applied to existing fluoroscopy systems to improve real-time visualization of device deployment without hardware modifications. Improved image guidance facilitates aneurysm coil packing and proper positioning and deployment of carotid artery stents, flow diverters, and the WEB device, especially in the context of complex anatomy and an obscured field of view.

Design and Analysis of Cost-Efficient Sensor Deployment for Tracking Small UAS with Agent-Based Modeling.

PubMed

Shin, Sangmi; Park, Seongha; Kim, Yongho; Matson, Eric T

2016-04-22

Recently, commercial unmanned aerial systems (UAS) have gained popularity. However, these UAS are potential threats to people in terms of safety in public places, such as public parks or stadiums. To reduce such threats, we consider a design, modeling, and evaluation of a cost-efficient sensor system that detects and tracks small UAS. In this research, we focus on discovering the best sensor deployments by simulating different types and numbers of sensors in a designated area, which provide reasonable detection rates at low costs. Also, the system should cover the crowded areas more thoroughly than vacant areas to reduce direct threats to people underneath. This research study utilized the Agent-Based Modeling (ABM) technique to model a system consisting of independent and heterogeneous agents that interact with each other. Our previous work presented the ability to apply ABM to analyze the sensor configurations with two types of radars in terms of cost-efficiency. The results from the ABM simulation provide a list of candidate configurations and deployments that can be referred to for applications in the real world environment.

Design and Analysis of Cost-Efficient Sensor Deployment for Tracking Small UAS with Agent-Based Modeling

PubMed Central

Shin, Sangmi; Park, Seongha; Kim, Yongho; Matson, Eric T.

2016-01-01

Recently, commercial unmanned aerial systems (UAS) have gained popularity. However, these UAS are potential threats to people in terms of safety in public places, such as public parks or stadiums. To reduce such threats, we consider a design, modeling, and evaluation of a cost-efficient sensor system that detects and tracks small UAS. In this research, we focus on discovering the best sensor deployments by simulating different types and numbers of sensors in a designated area, which provide reasonable detection rates at low costs. Also, the system should cover the crowded areas more thoroughly than vacant areas to reduce direct threats to people underneath. This research study utilized the Agent-Based Modeling (ABM) technique to model a system consisting of independent and heterogeneous agents that interact with each other. Our previous work presented the ability to apply ABM to analyze the sensor configurations with two types of radars in terms of cost-efficiency. The results from the ABM simulation provide a list of candidate configurations and deployments that can be referred to for applications in the real world environment. PMID:27110790

Ultrasonic vibration double scratch morphology and scratching force of BK7 glass

NASA Astrophysics Data System (ADS)

Wang, Chu; Wang, Hongxiang; Liu, Junliang; Gao, Shi

2018-03-01

In this paper, the damage morphology and scratching force of BK7 glass components were analyzed by ultrasonic vibration double-scratch test. The results showed that there was surface damage caused by plastic flow and brittle fracture during the scratching process, and the scratching depth and the distance between the two scratches had effect on the propagation and overlapping of lateral cracks. When the scratching depth was small, the jagged scratch was produced on the surface, and accompanied by a small amount of tiny pieces of debris off. With the increase in scratching depth, the lateral cracks caused by scratching overlapped and expended to form a mesh sheet, and then fell off from the surface. When the scratching distance was small, the interaction of the cracks caused large slice of material to fall off. With the increase in scratching distance, the area between the two scratches was not easy to occur the overlapping of the lateral cracks. In addition, with the increase of the scratching depth, the scratching force showed a gradual increase trend, and the scratching force of the second scratch would increase with the scratching distance.

Small molecule inhibition of fibroblast growth factor receptors in cancer.

PubMed

Liang, Guang; Chen, Gaozhi; Wei, Xiaoyan; Zhao, Yunjie; Li, Xiaokun

2013-10-01

Fibroblast growth factors (FGFs) signal through FGF receptors (FGFRs), which are a sub-family of the superfamily of receptor tyrosine kinases, to regulate human development and metabolism. Uncontrolled FGF signaling is responsible for diverse array of developmental disorders, most notably skeletal syndromes due to FGFR gain-of-function mutations. Studies in the last few years have provided significant evidence for the importance of FGF signaling in the pathogenesis of diverse cancers, including endometrial and bladder cancers. FGFs are both potent mitogenic and angiogenic factors and can contribute to carcinogenesis by stimulating cell proliferation and tumor angiogenesis. Gene knockout and pharmacological inhibition of FGFRs in in vivo and in vitro models validate FGFRs as a target for cancer treatment. Considerable efforts are being expended to develop specific, small-molecule inhibitors for treating FGFR-driven cancers. Recent reviews on the FGF/FGFR system have focused primarily on signaling, pathophysiology, and functions in cancer. In this article, we review the key roles of FGFR in cancer, provide an update on the status of clinical trials with small-molecule FGFR inhibitors, and discuss how the current structural data on FGFR kinases guide the design and characterization of new FGFR inhibitors. Copyright © 2013 Elsevier Ltd. All rights reserved.

Engineering design, stress and thermal analysis, and documentation for SATS program

NASA Technical Reports Server (NTRS)

1973-01-01

An in-depth analysis and mechanical design of the solar array stowage and deployment arrangements for use in Small Applications Technology Satellite spacecraft is presented. Alternate approaches for the major elements of work are developed and evaluated. Elements include array stowage and deployment arrangements, the spacecraft and array behavior in the spacecraft despin mode, and the design of the main hinge and segment hinge assemblies. Feasibility calculations are performed and the preferred approach is identified.

Challenges to deployment of twenty-first century nuclear reactor systems

PubMed Central

2017-01-01

The science and engineering of materials have always been fundamental to the success of nuclear power to date. They are also the key to the successful deployment and operation of a new generation of nuclear reactor systems and their associated fuel cycles. This article reflects on some of the historical issues, the challenges still prevalent today and the requirement for significant ongoing materials R&D and discusses the potential role of small modular reactors. PMID:28293142

Ames Infusion Stories for NASA Annual Technology Report: Nano Entry System for CubeSat-Class Payloads

NASA Technical Reports Server (NTRS)

Smith, Brandon; Jan, Darrell Leslie; Venkatapathy, Etiraj

2015-01-01

The Nano Entry System for CubeSat-Class Payloads led to the development of the Nano-Adaptable Deployable Entry and Placement Technology ("Nano-ADEPT"). Nano-ADEPT is a mechanically deployed entry, descent, and landing (EDL) system that stows during launch and cruise (like an umbrella) and serves as both heat shield and primary structure during EDL. It is especially designed for small spacecraft where volume is a limiting constraint.

Challenges to deployment of twenty-first century nuclear reactor systems.

PubMed

Ion, Sue

2017-02-01

The science and engineering of materials have always been fundamental to the success of nuclear power to date. They are also the key to the successful deployment and operation of a new generation of nuclear reactor systems and their associated fuel cycles. This article reflects on some of the historical issues, the challenges still prevalent today and the requirement for significant ongoing materials R&D and discusses the potential role of small modular reactors.

Analysis of the Flight Motions of a Small Deployable Glider Configuration

NASA Technical Reports Server (NTRS)

Coe, Paul L., Jr.

1975-01-01

An investigation was conducted at the request of the U.S. Air Force Avionics Laboratory to analyze the flight characteristics of a small uncontrolled glider with folding wings. The study consisted of wind-tunnel tests of an actual glider and a theoretical analysis of the performance, stability, and trimmability of the configuration.

Rural ITS toolbox and deployment plan for Regions 2, 6, 7 and 9 : ITS toolbox for rural and small urban areas

DOT National Transportation Integrated Search

1998-12-01

As a part of the Small Urban and Rural ITS Study it conducted in 4 of its more rural regions, the New York State Department of Transportation has developed a compendium of systems, devices and strategies that can enhance safety, provide information, ...

Geosynchronous earth orbit/low earth orbit space object inspection and debris disposal: A preliminary analysis using a carrier satellite with deployable small satellites

NASA Astrophysics Data System (ADS)

Crockett, Derick

Detailed observations of geosynchronous satellites from earth are very limited. To better inspect these high altitude satellites, the use of small, refuelable satellites is proposed. The small satellites are stationed on a carrier platform in an orbit near the population of geosynchronous satellites. A carrier platform equipped with deployable, refuelable SmallSats is a viable option to inspect geosynchronous satellites. The propellant requirement to transfer to a targeted geosynchronous satellite, perform a proximity inspection mission, and transfer back to the carrier platform in a nearby orbit is determined. Convex optimization and traditional optimization techniques are explored, determining minimum propellant trajectories. Propellant is measured by the total required change in velocity, delta-v. The trajectories were modeled in a relative reference frame using the Clohessy-Wiltshire equations. Mass estimations for the carrier platform and the SmallSat were determined by using the rocket equation. The mass estimates were compared to the mass of a single, non-refuelable satellite performing the same geosynchronous satellite inspection missions. From the minimum delta-v trajectories and the mass analysis, it is determined that using refuelable SmallSats and a carrier platform in a nearby orbit can be more efficient than using a single non-refuelable satellite to perform multiple geosynchronous satellite inspections.

A stowing and deployment strategy for large membrane space systems on the example of Gossamer-1

NASA Astrophysics Data System (ADS)

Seefeldt, Patric

2017-09-01

Deployment systems for innovative space applications such as solar sails require a technique for a controlled and autonomous deployment in space. The deployment process has a strong impact on the mechanism and structural design and sizing. On the example of the design implemented in the Gossamer-1 project of the German Aerospace Center (DLR), such a stowing and deployment process is analyzed. It is based on a combination of zig-zag folding and coiling of triangular sail segments spanned between crossed booms. The deployment geometry and forces introduced by the mechanism considered are explored in order to reveal how the loads are transferred through the membranes to structural components such as the booms. The folding geometry and force progressions are described by function compositions of an inverse trigonometric function with the considered trigonometric function itself. If these functions are evaluated over several periods of the trigonometric function, a non-smooth oscillating curve occurs. Depending on the trigonometric function, these are often vividly described as zig-zag or sawtooth functions. The developed functions are applied to the Gossamer-1 design. The deployment geometry reveals a tendency that the loads are transferred along the catheti of the sail segments and therefore mainly along the boom axes. The load introduced by the spool deployment mechanism is described. By combining the deployment geometry with that load, a prediction of the deployment load progression is achieved. The mathematical description of the stowing and deployment geometry, as well as the forces inflicted by the mechanism provides an understanding of how exactly the membrane deploys and through which edges the deployment forces are transferred. The mathematical analysis also gives an impression of sensitive parameters that could be influenced by manufacturing tolerances or unsymmetrical deployment of the sail segments. While the mathematical model was applied on the design of the Gossamer-1 hardware, it allows an analysis of other geometries. This is of particular interest as Gossamer-1 investigated deployment technology on a relatively small scale of 5m × 5m , while the currently considered solar sail missions require sails that are about one order of magnitude bigger.

Deployment and evaluation of a dual-sensor autofocusing method for on-machine measurement of patterns of small holes on freeform surfaces.

PubMed

Chen, Xiaomei; Longstaff, Andrew; Fletcher, Simon; Myers, Alan

2014-04-01

This paper presents and evaluates an active dual-sensor autofocusing system that combines an optical vision sensor and a tactile probe for autofocusing on arrays of small holes on freeform surfaces. The system has been tested on a two-axis test rig and then integrated onto a three-axis computer numerical control (CNC) milling machine, where the aim is to rapidly and controllably measure the hole position errors while the part is still on the machine. The principle of operation is for the tactile probe to locate the nominal positions of holes, and the optical vision sensor follows to focus and capture the images of the holes. The images are then processed to provide hole position measurement. In this paper, the autofocusing deviations are analyzed. First, the deviations caused by the geometric errors of the axes on which the dual-sensor unit is deployed are estimated to be 11 μm when deployed on a test rig and 7 μm on the CNC machine tool. Subsequently, the autofocusing deviations caused by the interaction of the tactile probe, surface, and small hole are mathematically analyzed and evaluated. The deviations are a result of the tactile probe radius, the curvatures at the positions where small holes are drilled on the freeform surface, and the effect of the position error of the hole on focusing. An example case study is provided for the measurement of a pattern of small holes on an elliptical cylinder on the two machines. The absolute sum of the autofocusing deviations is 118 μm on the test rig and 144 μm on the machine tool. This is much less than the 500 μm depth of field of the optical microscope. Therefore, the method is capable of capturing a group of clear images of the small holes on this workpiece for either implementation.

The effect of temperature and body weight on the routine metabolic rate and postprandial metabolic response in mulloway, Argyrosomus japonicus.

PubMed

Pirozzi, Igor; Booth, Mark A

2009-09-01

Specific dynamic action (SDA) is the energy expended on the physiological processes associated with meal digestion and is strongly influenced by the characteristics of the meal and the body weight (BW) and temperature of the organism. This study assessed the effects of temperature and body weight on the routine metabolic rate (RMR) and postprandial metabolic response in mulloway, Argyrosomus japonicus. RMR and SDA were established at 3 temperatures (14, 20 and 26 degrees C). 5 size classes of mulloway ranging from 60 g to 1.14 kg were used to establish RMR with 3 of the 5 size classes (60, 120 and 240 g) used to establish SDA. The effect of body size on the mass-specific RMR (mg O(2) kg(-1) h(-1)) varied significantly depending on the temperature; there was a greater relative increase in the mass-specific RMR for smaller mulloway with increasing temperature. No statistical differences were found between the mass exponent (b) values at each temperature when tested against H(0): b=0.8. The gross RMR of mulloway (mg O(2) fish(-1) h(-1)) can be described as function of temperature (T; 14-26 degrees C) as: (0.0195T-0.0454)BW(g)(0.8) and the mass-specific RMR (mg O(2) kg(-1) h(-1)) can be described as: (21.042T-74.867)BW(g)(-0.2). Both SDA duration and time to peak SDA were influenced by temperature and body weight; SDA duration occurred within 41-89 h and peak time occurred within 17-38 h of feeding. The effect of body size on peak metabolic rate varied significantly depending on temperature, generally increasing with temperature and decreasing with increasing body size. Peak gross oxygen consumption (MO(2): mg O(2) fish(-1) h(-1)) scaled allometrically with BW. Temperature, but not body size, significantly affected SDA scope, although the difference was numerically small. There was a trend for MO(2) above RMR over the SDA period to increase with temperature; however, this was not statistically significant. The average proportion of energy expended over the SDA period (SDA coefficient) ranged from approximately 7-13% of the total DE intake while the proportion of total energy expended on SDA above RMR ranged from approximately 16-27%.

Improving Attachments of Remotely-Deployed Dorsal Fin-Mounted Tags: Tissue Structure, Hydrodynamics, in situ Performance, and Tagged-Animal Follow-up

DTIC Science & Technology

2014-09-30

TERM GOALS We recently developed small satellite-linked telemetry tags that are anchored with small attachment darts to the dorsal fins of small ...monitor the movements of numerous species not previously accessible because they were too large or difficult to capture safely, but too small for tags...cetaceans that provides the data needed to answer critical conservation and management questions without an adverse effect on the tagged animal. Therefore

A Freezable Heat Exchanger for Space Suit Radiator Systems

NASA Technical Reports Server (NTRS)

Nabity, James A.; Mason, Georgia R.; Copeland, Robert J.; Trevino, Luis a.

2008-01-01

During an ExtraVehicular Activity (EVA), both the heat generated by the astronaut s metabolism and that produced by the Portable Life Support System (PLSS) must be rejected to space. The heat sources include the heat of adsorption of metabolic CO2, the heat of condensation of water, the heat removed from the body by the liquid cooling garment and the load from the electrical components. Although the sublimator hardware to reject this load weighs only 1.58 kg (3.48 lbm), an additional 3.6 kg (8 lbm) of water are loaded into the unit, most of which is sublimated and lost to space, thus becoming the single largest expendable during an eight-hour EVA. Using a radiator to reject heat from the astronaut during an EVA can reduce the amount of expendable water consumed in the sublimator. Radiators have no moving parts and are thus highly reliable. Past freezable radiators have been too heavy, but the weight can be greatly reduced by placing a small and freeze tolerant heat exchanger between the astronaut and radiator, instead of making the very large radiator freeze tolerant. Therefore, the key technological innovation to improve space suit radiator performance was the development of a lightweight and freezable heat exchanger that accommodates the variable heat load generated by the astronaut. Herein, we present the heat transfer performance of a newly designed heat exchanger that endured several freeze / thaw cycles without any apparent damage. The heat exchanger was also able to continuously turn down or turn up the heat rejection to follow the variable load.

KSC-97pc402

NASA Image and Video Library

1997-03-06

Workers take off the protective covering on the propulsion module for the Cassini spacecraft after uncrating the module at KSC's Spacecraft Assembly and Encapsulation Facility-2 (SAEF-2). The extended journey of 6.7 years to Saturn and the 4-year mission for Cassini once it gets there will require the spacecraft to carry a large amount of propellant for inflight trajectory-correction maneuvers and attitude control, particularly during the science observations. The propulsion module has redundant 445-newton main engines that burn nitrogen tetraoxide and monomethyl-hydrazine for main propulsion and 16 smaller 1-newton engines that burn hydrazine to control attitude and to correct small deviations from the spacecraft flight path. Cassini will be launched on a Titan IVB/Centaur expendable launch vehicle. Liftoff is targeted for October 6 from Launch Complex 40, Cape Canaveral Air Station

A Time History of Control Operation of a C-54 Airplane in Blind Landing Approaches

NASA Technical Reports Server (NTRS)

Talmage, Donald B.

1947-01-01

Tests were made with a C-54 airplane in which airline pilots made several blind approaches to determine whether any special flying techniques were used in blind landings and whether any special handling-qualities requirements would have to be formulated because of such special techniques. It was found that the airplane was flown at all times in the normal manner; that is, all turns were banked turns that were nearly coordinated by use of the rudder so that the sideslip was held close to zero. The pilot expended considerable physical work in continually moving the controls but this wake was due in part to the large friction in the three control systems. The actual control deflections used were small compared to the maximum deflections available.

Study on the three-station typical network deployments of workspace Measurement and Positioning System

NASA Astrophysics Data System (ADS)

Xiong, Zhi; Zhu, J. G.; Xue, B.; Ye, Sh. H.; Xiong, Y.

2013-10-01

As a novel network coordinate measurement system based on multi-directional positioning, workspace Measurement and Positioning System (wMPS) has outstanding advantages of good parallelism, wide measurement range and high measurement accuracy, which makes it to be the research hotspots and important development direction in the field of large-scale measurement. Since station deployment has a significant impact on the measurement range and accuracy, and also restricts the use-cost, the optimization method of station deployment was researched in this paper. Firstly, positioning error model was established. Then focusing on the small network consisted of three stations, the typical deployments and error distribution characteristics were studied. Finally, through measuring the simulated fuselage using typical deployments at the industrial spot and comparing the results with Laser Tracker, some conclusions are obtained. The comparison results show that under existing prototype conditions, I_3 typical deployment of which three stations are distributed in a straight line has an average error of 0.30 mm and the maximum error is 0.50 mm in the range of 12 m. Meanwhile, C_3 typical deployment of which three stations are uniformly distributed in the half-circumference of an circle has an average error of 0.17 mm and the maximum error is 0.28 mm. Obviously, C_3 typical deployment has a higher control effect on precision than I_3 type. The research work provides effective theoretical support for global measurement network optimization in the future work.

Advancements of the Lightweight Integrated Solar Array and Transceiver (LISA-T) Small Spacecraft System

NASA Technical Reports Server (NTRS)

Lockett, Tiffany Russell; Martinez, Armando; Boyd, Darren; SanSouice, Michael; Farmer, Brandon; Schneider, Todd; Laue, Greg; Fabisinski, Leo; Johnson, Les; Carr, John A.

2015-01-01

This paper describes recent advancements of the Lightweight Integrated Solar Array and Transceiver (LISA-T) currently being developed at NASA's Marshall Space Flight Center. The LISA-T array comprises a launch stowed, orbit deployed structure on which thin-film photovoltaic (PV) and antenna devices are embedded. The system provides significant electrical power generation at low weights, high stowage efficiency, and without the need for solar tracking. Leveraging high-volume terrestrial-market PVs also gives the potential for lower array costs. LISA-T is addressing the power starvation epidemic currently seen by many small-scale satellites while also enabling the application of deployable antenna arrays. Herein, an overview of the system and its applications are presented alongside sub-system development progress and environmental testing plans.

Advancements of the Lightweight Integrated Solar Array and Transceiver (LISA-T) Small Spacecraft System

NASA Technical Reports Server (NTRS)

Russell, Tiffany; Martinez, Armando; Boyd, Darren; SanSoucie, Michael; Farmer, Brandon; Schneider, Todd; Fabisinski, Leo; Johnson, Les; Carr, John A.

2015-01-01

This paper describes recent advancements of the Lightweight Integrated Solar Array and Transceiver (LISA-T) currently being developed at NASA's Marshall Space Flight Center. The LISA-T array comprises a launch stowed, orbit deployed structure on which thin-film photovoltaic (PV) and antenna devices are embedded. The system provides significant electrical power generation at low weights, high stowage efficiency, and without the need for solar tracking. Leveraging high-volume terrestrial-market PVs also gives the potential for lower array costs. LISA-T is addressing the power starvation epidemic currently seen by many small-scale satellites while also enabling the application of deployable antenna arrays. Herein, an overview of the system and its applications are presented alongside sub-system development progress and environmental testing plans/initial results.

Feasibility for Orbital Life Extension of a CubeSat in the Lower Thermosphere

NASA Technical Reports Server (NTRS)

Blandino, John J.; Martinez-Baquero, Nicolas; Demetriou, Michael A.; Gatsonis, Nikolaos A.; Paschalidis, Nicholas

2016-01-01

Orbital flight of CubeSats at altitudes between 150 and 250 km has the potential to enable a new class of scientific, commercial, and defense-related missions. A study is presented to demonstrate the feasibility of extending the orbital lifetime of a CubeSat in a 210 km orbit. Propulsion consists of an electrospray thruster operating at a 2 W, 0.175 mN thrust, and an specific impulse (Isp) of 500 s. The mission consists of two phases. In phase 1, the CubeSat is deployed from a 414 km orbit and uses the thruster to deorbit to the target altitude of 210 km. In phase 2, the propulsion system is used to extend the mission lifetime until propellant is fully expended. A control algorithm based on maintaining a target orbital energy is presented that uses an extended Kalman filter to generate estimates of the orbital dynamic state, which are periodically updated by Global Positioning System measurements. For phase 1, the spacecraft requires 25.21 days to descend from 414 to 210 km, corresponding to a delta V = 96.25 m/s and a propellant consumption of 77.8 g. Phase 2 lasts 57.83 days, corresponding to a delta V = 119.15 m/s, during which the remaining 94.2 g of propellant are consumed.

An employee sews thermal insulation material on the front heat shield of the Huygens probe in the PH

NASA Technical Reports Server (NTRS)

1997-01-01

An employee in the Payload Hazardous Servicing Facility (PHSF) sews thermal insulation material on the front heat shield of the Huygens probe during prelaunch processing testing and integration in that facility, with the probe's back cover in the background. The Huygens probe and the Cassini orbiter being processed at KSC are the two primary components of the Cassini spacecraft, which will be launched on a Titan IVB/Centaur expendable launch vehicle from Cape Canaveral Air Station. Cassini will explore Saturn, its rings and moons for four years. The Huygens probe, designed and developed for the European Space Agency (ESA), will be deployed from the orbiter to study the clouds, atmosphere and surface of Saturn's largest moon, Titan. The orbiter was designed and assembled at NASA's Jet Propulsion Laboratory in California. Following postflight inspections, integration of the 12 science instruments not already installed on the orbiter will be completed. Then, the parabolic high-gain antenna and the propulsion module will be mated to the orbiter, followed by the Huygens probe, which will complete spacecraft integration. The Cassini mission is targeted for an Oct. 6 launch to begin its 6.7-year journey to the Saturnian system. Arrival at the planet is expected to occur around July 1, 2004.

An employee sews thermal insulation material on the back cover and heat shield of the Huygens probe

NASA Technical Reports Server (NTRS)

1997-01-01

An employee in the Payload Hazardous Servicing Facility (PHSF) sews thermal insulation material on the back cover and heat shield of the Huygens probe during prelaunch processing, testing and integration in that facility. The Huygens probe and the Cassini orbiter being processed at KSC are the two primary components of the Cassini spacecraft, which will be launched on a Titan IVB/Centaur expendable launch vehicle from Cape Canaveral Air Station. Cassini will explore Saturn, its rings and moons for four years. The Huygens probe, designed and developed for the European Space Agency (ESA), will be deployed from the orbiter to study the clouds, atmosphere and surface of Saturn's largest moon, Titan. The orbiter was designed and assembled at NASA's Jet Propulsion Laboratory in California. Following postflight inspections, integration of the 12 science instruments not already installed on the orbiter will be completed. Then, the parabolic high-gain antenna and the propulsion module will be mated to the orbiter, followed by the Huygens probe, which will complete spacecraft integration. The Cassini mission is targeted for an Oct. 6 launch to begin its 6.7-year journey to the Saturnian system. Arrival at the planet is expected to occur around July 1, 2004.

An employee works on the top side of the experiment platform for the Huygens probe in the PHSF

NASA Technical Reports Server (NTRS)

1997-01-01

An employee in the Payload Hazardous Servicing Facility (PHSF) works on the top side of the experiment platform for the Huygens probe that will accompany the Cassini orbiter to Saturn during prelaunch processing, testing and integration in that facility. The Huygens probe and the Cassini orbiter being processed at KSC are the two primary components of the Cassini spacecraft, which will be launched on a Titan IVB/Centaur expendable launch vehicle from Cape Canaveral Air Station. Cassini will explore Saturn, its rings and moons for four years. The Huygens probe, designed and developed for the European Space Agency (ESA), will be deployed from the orbiter to study the clouds, atmosphere and surface of Saturn's largest moon, Titan. The orbiter was designed and assembled at NASA's Jet Propulsion Laboratory in California. Following postflight inspections, integration of the 12 science instruments not already installed on the orbiter will be completed. Then, the parabolic high-gain antenna and the propulsion module will be mated to the orbiter, followed by the Huygens probe, which will complete spacecraft integration. The Cassini mission is targeted for an Oct. 6 launch to begin its 6.7-year journey to the Saturnian system. Arrival at the planet is expected to occur around July 1, 2004.

KSC-97pc678

NASA Image and Video Library

1997-04-21

Workers offload the shipping container with the Cassini orbiter from what looks like a giant shark mouth, but is really an Air Force C-17 air cargo plane which just landed at KSC’s Shuttle Landing Facility from Edwards Air Force Base, California. The orbiter and the Huygens probe already being processed at KSC are the two primary components of the Cassini spacecraft, which will be launched on a Titan IVB/Centaur expendable launch vehicle from Cape Canaveral Air Station. Cassini will explore Saturn, its rings and moons for four years. The Huygens probe, designed and developed for the European Space Agency (ESA), will be deployed from the orbiter to study the clouds, atmosphere and surface of Saturn’s largest moon, Titan. The orbiter was designed and assembled at NASA’s Jet Propulsion Laboratory in California. Following postflight inspections, integration of the 12 science instruments not already installed on the orbiter will be completed. Then, the parabolic high-gain antenna and the propulsion module will be mated to the orbiter, followed by the Huygens probe, which will complete spacecraft integration. The Cassini mission is targeted for an Oct. 6 launch to begin its 6.7-year journey to the Saturnian system. Arrival at the planet is expected to occur around July 1, 2004

KSC-97pc680

NASA Image and Video Library

1997-04-21

Workers prepare to move the shipping container with the Cassini orbiter inside the Payload Hazardous Servicing Facility (PHSF) for prelaunch processing, testing and integration. The orbiter arrived at KSC’s Shuttle Landing Facility in a U.S. Air Force C-17 air cargo plane from Edwards Air Force Base, California. The orbiter and the Huygens probe already being processed at KSC are the two primary components of the Cassini spacecraft, which will be launched on a Titan IVB/Centaur expendable launch vehicle from Cape Canaveral Air Station. Cassini will explore Saturn, its rings and moons for four years. The Huygens probe, designed and developed for the European Space Agency (ESA), will be deployed from the orbiter to study the clouds, atmosphere and surface of Saturn’s largest moon, Titan. The orbiter was designed and assembled at NASA’s Jet Propulsion Laboratory in California. Following postflight inspections, integration of the 12 science instruments not already installed on the orbiter will be completed. Then, the parabolic high-gain antenna and the propulsion module will be mated to the orbiter, followed by the Huygens probe, which will complete spacecraft integration. The Cassini mission is targeted for an Oct. 6 launch to begin its 6.7-year journey to the Saturnian system. Arrival at the planet is expected to occur around July 1, 2004

KSC-97pc682

NASA Image and Video Library

1997-04-21

Workers prepare to move the shipping container with the Cassini orbiter inside the Payload Hazardous Servicing Facility (PHSF) for prelaunch processing, testing and integration. The orbiter arrived at KSC’s Shuttle Landing Facility in a U.S. Air Force C-17 air cargo plane from Edwards Air Force Base, California. The orbiter and the Huygens probe already being processed at KSC are the two primary components of the Cassini spacecraft, which will be launched on a Titan IVB/Centaur expendable launch vehicle from Cape Canaveral Air Station. Cassini will explore Saturn, its rings and moons for four years. The Huygens probe, designed and developed for the European Space Agency (ESA), will be deployed from the orbiter to study the clouds, atmosphere and surface of Saturn’s largest moon, Titan. The orbiter was designed and assembled at NASA’s Jet Propulsion Laboratory in California. Following postflight inspections, integration of the 12 science instruments not already installed on the orbiter will be completed. Then, the parabolic high-gain antenna and the propulsion module will be mated to the orbiter, followed by the Huygens probe, which will complete spacecraft integration. The Cassini mission is targeted for an Oct. 6 launch to begin its 6.7-year journey to the Saturnian system. Arrival at the planet is expected to occur around July 1, 2004

KSC-97pc681

NASA Image and Video Library

1997-04-21

Workers prepare to move the shipping container with the Cassini orbiter inside the Payload Hazardous Servicing Facility (PHSF) for prelaunch processing, testing and integration. The orbiter arrived at KSC’s Shuttle Landing Facility in a U.S. Air Force C-17 air cargo plane from Edwards Air Force Base, California. The orbiter and the Huygens probe already being processed at KSC are the two primary components of the Cassini spacecraft, which will be launched on a Titan IVB/Centaur expendable launch vehicle from Cape Canaveral Air Station. Cassini will explore Saturn, its rings and moons for four years. The Huygens probe, designed and developed for the European Space Agency (ESA), will be deployed from the orbiter to study the clouds, atmosphere and surface of Saturn’s largest moon, Titan. The orbiter was designed and assembled at NASA’s Jet Propulsion Laboratory in California. Following postflight inspections, integration of the 12 science instruments not already installed on the orbiter will be completed. Then, the parabolic high-gain antenna and the propulsion module will be mated to the orbiter, followed by the Huygens probe, which will complete spacecraft integration. The Cassini mission is targeted for an Oct. 6 launch to begin its 6.7-year journey to the Saturnian system. Arrival at the planet is expected to occur around July 1, 2004

Cassini orbiter arrives at SLF

NASA Technical Reports Server (NTRS)

1997-01-01

Workers offload the shipping container with the Cassini orbiter from what looks like a giant shark mouth, but is really an Air Force C-17 air cargo plane which just landed at KSC's Shuttle Landing Facility from Edwards Air Force Base, California. The orbiter and the Huygens probe already being processed at KSC are the two primary components of the Cassini spacecraft, which will be launched on a Titan IVB/Centaur expendable launch vehicle from Cape Canaveral Air Station. Cassini will explore Saturn, its rings and moons for four years. The Huygens probe, designed and developed for the European Space Agency (ESA), will be deployed from the orbiter to study the clouds, atmosphere and surface of Saturn's largest moon, Titan. The orbiter was designed and assembled at NASA's Jet Propulsion Laboratory in California. Following postflight inspections, integration of the 12 science instruments not already installed on the orbiter will be completed. Then, the parabolic high-gain antenna and the propulsion module will be mated to the orbiter, followed by the Huygens probe, which will complete spacecraft integration. The Cassini mission is targeted for an Oct. 6 launch to begin its 6.7-year journey to the Saturnian system. Arrival at the planet is expected to occur around July 1, 2004.

Cassini orbiter arrives at SLF

NASA Technical Reports Server (NTRS)

1997-01-01

Workers prepare to tow away the large container with the Cassini orbiter from KSC's Shuttle Landing Facility. The orbiter just arrived on the U.S. Air Force C-17 air cargo plane, shown here, from Edwards Air Force Base, California. The orbiter and the Huygens probe already being processed at KSC are the two primary components of the Cassini spacecraft, which will be launched on a Titan IVB/Centaur expendable launch vehicle from Cape Canaveral Air Station. Cassini will explore Saturn, its rings and moons for four years. The Huygens probe, designed and developed for the European Space Agency (ESA), will be deployed from the orbiter to study the clouds, atmosphere and surface of Saturn's largest moon, Titan. The orbiter was designed and assembled at NASA's Jet Propulsion Laboratory in California. Following postflight inspections, integration of the 12 science instruments not already installed on the orbiter will be completed. Then, the parabolic high-gain antenna and the propulsion module will be mated to the orbiter, followed by the Huygens probe, which will complete spacecraft integration. The Cassini mission is targeted for an Oct. 6 launch to begin its 6.7-year journey to the Saturnian system. Arrival at the planet is expected to occur around July 1, 2004.

The Effect of Personnel Stability on Organizational Performance: Do Battalions with Stable Command Groups Achieve Higher Training Proficiency at the National Training Center?

DTIC Science & Technology

2008-01-01

Graduate School and the students they work with on a routine basis. All three of my committee members have been superb mentors in helping me develop the...Deployable” and “Individual Replacement Induced Non-Deployable.” Wartime non-deployable status is provided to soldiers who are unavailable due to medical ...responder medical tasks, mastery of communication systems, and basic reporting requirements. The unit can progress to small-unit level collective training

Quality Function Deployment for Large Systems

NASA Technical Reports Server (NTRS)

Dean, Edwin B.

1992-01-01

Quality Function Deployment (QFD) is typically applied to small subsystems. This paper describes efforts to extend QFD to large scale systems. It links QFD to the system engineering process, the concurrent engineering process, the robust design process, and the costing process. The effect is to generate a tightly linked project management process of high dimensionality which flushes out issues early to provide a high quality, low cost, and, hence, competitive product. A pre-QFD matrix linking customers to customer desires is described.

The NASA Lewis Research Center's Expendable Launch Vehicle Program: An Economic Impact Study

NASA Technical Reports Server (NTRS)

Austrian, Ziona

1996-01-01

This study investigates the economic impact of the Lewis Research Center's (LeRC) Expendable Launch Vehicle Program (ELVP) on Northeast Ohio's economy. It was conducted by The Urban Center's Economic Development Program in Cleveland State University's Levin College of Urban Affairs. The study measures ELVP's direct impact on the local economy in terms of jobs, output, payroll, and taxes, as well as the indirect impact of these economic activities when they "ripple" throughout the economy. The study uses regional economic multipliers based on input-output models to estimate the effect of ELVP spending on the Northeast Ohio economy.

The NASA Lewis Research Center's Expendable Launch Vehicle Program: An Economic Impact Study

NASA Technical Reports Server (NTRS)

Austrian, Ziona

1996-01-01

This study investigates the economic impact of the Lewis Research Center's (LeRC) Expendable Launch Vehicle Program (ELVP) on Northeast Ohio's economy. It was conducted by The Urban Center's Economic Development Program in Cleveland State University's Levin College of Urban Affairs. The study measures ELVP's direct impact on the local economy in terms of jobs, output, payroll, and taxes, as well as the indirect impact of these economic activities when they 'ripple' throughout the economy. The study uses regional economic multipliers based on input-output models to estimate the effect of ELVP spending on the Northeast Ohio economy.

Environmental impact statement for the Kennedy Space Center, 1978 - 1979 revision

NASA Technical Reports Server (NTRS)

1979-01-01

The ongoing operation of KSC for expendable launch vehicles and automated spacecraft, continued development of facility capabilities, and the approved follow-on operations of the Space Transportation System and associated payloads are described. Emphasis is placed on the expendable launch vehicle and space shuttle traffic projected as of January, 1979. The maximum potential effect on the environment is addressed. Site specific environmental effects are summarized. It is indicated that all potential impacts will be localized, of short duration, controllable, and of minimum severity. The impact on land use, air and water quality, weather, and noise effects is covered.

Production of porous coating on a prosthesis

DOEpatents

Sump, Kenneth R.

1987-01-01

Preselected surface areas of a prosthesis are covered by a blend of matching primary metallic particles and expendable particles. The particles are compressed and heated to assure that deformation and metallurgical bonding occurs between them and between the primary particles and the surface boundaries of the prosthesis. Porosity is achieved by removal of the expendable material. The result is a coating including discrete bonded particles separated by a network of interconnected voids presenting a homogeneous porous coating about the substrate. It has strength suitable for bone implant usage without intermediate adhesives, and adequate porosity to promote subsequent bone ingrowth.

Comments on the commercialization of expendable launch vehicles

NASA Technical Reports Server (NTRS)

Trilling, D. R.

1984-01-01

The President's national space policy encourages private sector investment and involvement in civil space activities. Last November, the President designated the Department of Transportation as lead agency for the commercialization of expendable launch vehicles. This presents a substantial challenge to the United States Government, since the guidelines and requirements that are set now will have great influence on whether American firms can become a viable competitive industry in the world launch market. There is a dual need to protect public safety and free the private sector launch industry from needless regulatory barriers so that it can grow and prosper.

An efficient genetic algorithm for maximum coverage deployment in wireless sensor networks.

PubMed

Yoon, Yourim; Kim, Yong-Hyuk

2013-10-01

Sensor networks have a lot of applications such as battlefield surveillance, environmental monitoring, and industrial diagnostics. Coverage is one of the most important performance metrics for sensor networks since it reflects how well a sensor field is monitored. In this paper, we introduce the maximum coverage deployment problem in wireless sensor networks and analyze the properties of the problem and its solution space. Random deployment is the simplest way to deploy sensor nodes but may cause unbalanced deployment and therefore, we need a more intelligent way for sensor deployment. We found that the phenotype space of the problem is a quotient space of the genotype space in a mathematical view. Based on this property, we propose an efficient genetic algorithm using a novel normalization method. A Monte Carlo method is adopted to design an efficient evaluation function, and its computation time is decreased without loss of solution quality using a method that starts from a small number of random samples and gradually increases the number for subsequent generations. The proposed genetic algorithms could be further improved by combining with a well-designed local search. The performance of the proposed genetic algorithm is shown by a comparative experimental study. When compared with random deployment and existing methods, our genetic algorithm was not only about twice faster, but also showed significant performance improvement in quality.

Community Air Sensor Network (CAIRSENSE) project: Evaluation of low-cost sensor performance in a suburban environment in the southeastern United States

EPA Science Inventory

Advances in air pollution sensor technology have enabled the development of small and low cost systems to measure outdoor air pollution. The deployment of a large number of sensors across a small geographic area would have potential benefits to supplement traditional monitoring n...

Maghemite decorated with ultra-small palladium nanoparticles (γ-Fe2O3–Pd): applications in the Heck–Mizoroki olefination, Suzuki reaction and allylic oxidation of alkenes

EPA Science Inventory

A nanocatalyst comprising ultra-small Pd/PdO nanoparticles (<5 nm) supported on maghemite was prepared by a co-precipitation protocol using inexpensive raw materials and was deployed successfully in various significant synthetic transformations, namely the Heck–Mizoroki olefinati...

USE OF A RHODE ISLAND SALT POND BY JUVENILE WINTER FLOUNDER, PSEUDOPLEURONECTES AMERICANUS

EPA Science Inventory

We used a 1.75 m2 drop ring sampler in June and July of 2000 to quantify populations of juvenile flatfishes and other small nekton in Ninigret Pond, Rhode Island. The drop sampler was deployed in approximately 1 m of water from a boom mounted on the bow of a small boat. Abundance...

The Lightweight Integrated Solar Array and anTenna (LISA-T) Big Power for Small Spacecraft

NASA Technical Reports Server (NTRS)

Johnson, Les; Carr, John A.; Boyd, Darren

2017-01-01

NASA is developing a space power system using lightweight, flexible photovoltaic devices originally developed for use here on Earth to provide low cost power for spacecraft. The Lightweight Integrated Solar Array and anTenna (LISA-T) is a launch stowed, orbit deployed array on which thin-film photovoltaic and antenna elements are embedded. The LISA-T system is deployable, building upon NASA's expertise in developing thin-film deployable solar sails such the one being developed for the Near Earth Asteroid Scout project which will fly in 2018. One of the biggest challenges for the NEA Scout, and most other spacecraft, is power. There simply isn't enough of it available, thus limiting the range of operation of the spacecraft from the Sun (due to the small surface area available for using solar cells), the range of operation from the Earth (low available power with inherently small antenna sizes tightly constrain the bandwidth for communication), and the science (you can only power so many instruments with limited power). The LISA-T has the potential to mitigate each of these limitations, especially for small spacecraft. Inherently, small satellites are limited in surface area, volume, and mass allocation; driving competition between their need for power and robust communications with the requirements of the science or engineering payload they are developed to fly. LISA-T is addressing this issue, deploying large-area arrays from a reduced volume and mass envelope - greatly enhancing power generation and communications capabilities of small spacecraft and CubeSats. The problem is that these CubeSats can usually only generate between 7W and 50W of power. The power that can be generated by the LISA-T ranges from tens of watts to several hundred watts, at a much higher mass and stowage efficiency. A matrix of options are in development, including planar (pointed) and omnidirectional (non-pointed) arrays. The former is seeking the highest performance possible while the latter is seeking GN&C simplicity. Options for leveraging both high performance, 'typical cost' triple junction thin-film solar cells as well as moderate performance, low cost cells are being developed. Alongside, UHF (ultrahigh frequency), S-band, and X-band antennas are being integrated into the array to move their space claim away from the spacecraft and open the door for more capable multi-element antenna designs such as those needed for spherical coverage and electronically steered phase arrays.

Extracting ballistic forensic intelligence: microstamped firearms deliver data for illegal firearm traffic mapping: technology, implementation, and applications

NASA Astrophysics Data System (ADS)

Ohar, Orest P.; Lizotte, Todd E.

2009-08-01

Over the years law enforcement has become increasingly complex, driving a need for a better level of organization of knowledge within policing. The use of COMPSTAT or other Geospatial Information Systems (GIS) for crime mapping and analysis has provided opportunities for careful analysis of crime trends. By identifying hotspots within communities, data collected and entered into these systems can be analyzed to determine how, when and where law enforcement assets can be deployed efficiently. This paper will introduce in detail, a powerful new law enforcement and forensic investigative technology called Intentional Firearm Microstamping (IFM). Once embedded and deployed into firearms, IFM will provide data for identifying and tracking the sources of illegally trafficked firearms within the borders of the United States and across the border with Mexico. Intentional Firearm Microstamping is a micro code technology that leverages a laser based micromachining process to form optimally located, microscopic "intentional structures and marks" on components within a firearm. Thus when the firearm is fired, these IFM structures transfer an identifying tracking code onto the expended cartridge that is ejected from the firearm. Intentional Firearm Microstamped structures are laser micromachined alpha numeric and encoded geometric tracking numbers, linked to the serial number of the firearm. IFM codes can be extracted quickly and used without the need to recover the firearm. Furthermore, through the process of extraction, IFM codes can be quantitatively verified to a higher level of certainty as compared to traditional forensic matching techniques. IFM provides critical intelligence capable of identifying straw purchasers, trafficking routes and networks across state borders and can be used on firearms illegally exported across international borders. This paper will outline IFM applications for supporting intelligence led policing initiatives, IFM implementation strategies, describe the how IFM overcomes the firearms stochastic properties and explain the code extraction technologies that can be used by forensic investigators and discuss the applications where the extracted data will benefit geospatial information systems for forensic intelligence benefit.

Simultaneous Deep-Ocean Operations With Autonomous and Remotely Operated Vehicles

NASA Astrophysics Data System (ADS)

Yoerger, D. R.; Bowen, A. D.; Bradley, A. M.

2005-12-01

The complimentary capabilities of autonomous and remotely vehicles can be obtained more efficiently if two or more vehicles can be deployed simultaneously from a single vessel. Simultaneous operations make better use of ship time and personnel. However, such operations require specific technical capabilities and careful scheduling. We recently demonstrated several key capabilities on the VISIONS05 cruise to the Juan de Fuca Ridge, where the Autonomous Benthic Explorer (ABE) and the ROV Jason 2 were operated simultaneously. The cruise featured complex ROV operations ranging from servicing seismic instruments, water sampling, drilling, and installation of in-situ experiments. The AUV provided detailed near-bottom bathymetry of the Endeavour segment while concurrently providing a cable route survey for a primary Canadian Neptune node. To meet these goals, we had to operate both vehicles at the same time. In previous efforts, we have operated ABE in a coordinated fashion with either the submersible Alvin or Jason 2. But the vehicles were either deployed sequentially or they were operated in separate acoustic transponder nets with the restriction that the vessel recover the AUV within a reasonable period after it reached the surface to avoid loss of the AUV. During the VISIONS05 cruise, we operated both vehicles at the same time and demonstrated several key capabilities to make simultaneous operations more efficient. These include the ability of the AUV to anchor to the seafloor after its batteries were expended or if a fault occurred, allowing complex ROV operations to run to completion without the constraint of retrieving the AUV at a specific time. The anchoring system allowed the vehicle to rest near the seafloor on a short mooring in a low power state. The AUV returned to the surface either through an acoustic command from the vessel or when a preassigned time was reached. We also tested an experimental acoustic beacon system that can allow multiple vehicles to determine their position without interfering with each other.

Manta A New BroadBand OBS

NASA Astrophysics Data System (ADS)

Hello, Y.; Yegikyan, M.; Charvis, P.; Philippe, O.

2017-12-01

Manta is a new BroadBand OBS developed at Geoazur and commercialized by Osean. The design is inspired by 3-years autonomy MUG-OBS a Multiparameter Ocean Bottom System which carry a lot of sort of sensor types. As Mug-OBS, Manta-OBS rated 6000m is designed to resist a trawling. All the components are non corrosive such polyethylene, titanium and buoyancy is ensured by syntactic foam. Equipped in standard version with a Trillium compact OBS Manta has an autonomy of 18 months, but can accept on its 4 input channels any kind of signal as low as from an hydrophone or larger from other type of a seismometer or accelerometer. Tri-axial geophones unit (2 Hz or 4.5 Hz ) can replace the seismometer and will expend the lifespan for the instrument. The seismometer is encapsulated in a central well established by four panels of the main structure to protect it from sea current convection and is decoupled from main chassis. An health bulletin is recoverable by acoustic any time to facilitate the installation and during a visit when instrument is deployed. Main parameters for acquisition can be changed by acoustics command from surface at any time. Once at the bottom, release for the main sensor installation is programmed on a timer but controlled by the tilt of the OBS. If the tilt is too important based on programmed limits, sensor will not released automatically, but this can be forced by acoustic command after returning the tilt informations to the boat operator. Manta is equipped with flash light and AIS system for easy location at recovery, and can also send it's position by Iridium satellite in case of an unexpected ascent such caused by a possible trawling if deployed in shallow water. Clock drift calculation is automatically made against GPS time signal once the OBS return at the surface. The recovery of the OBS is initiated by an acoustic command. These new features made Manta a very versatile instrument for monitoring earthquakes.

Photovoltaic Power System and Power Distribution Demonstration for the Desert RATS Program

NASA Technical Reports Server (NTRS)

Colozza, Anthony; Jakupca, Ian; Mintz, Toby; Herlacher, Mike; Hussey, Sam

2012-01-01

A stand alone, mobile photovoltaic power system along with a cable deployment system was designed and constructed to take part in the Desert Research And Technology Studies (RATS) lunar surface human interaction evaluation program at Cinder Lake, Arizona. The power system consisted of a photovoltaic array/battery system. It is capable of providing 1 kW of electrical power. The system outputs were 48 V DC, 110 V AC, and 220 V AC. A cable reel with 200 m of power cable was used to provide power from the trailer to a remote location. The cable reel was installed on a small trailer. The reel was powered to provide low to no tension deployment of the cable. The cable was connected to the 220 V AC output of the power system trailer. The power was then converted back to 110 V AC on the cable deployment trailer for use at the remote site. The Scout lunar rover demonstration vehicle was used to tow the cable trailer and deploy the power cable. This deployment was performed under a number of operational scenarios, manned operation, remote operation and tele-robotically. Once deployed, the cable was used to provide power, from the power system trailer, to run various operational tasks at the remote location.

A Depth-Adjustment Deployment Algorithm Based on Two-Dimensional Convex Hull and Spanning Tree for Underwater Wireless Sensor Networks.

PubMed

Jiang, Peng; Liu, Shuai; Liu, Jun; Wu, Feng; Zhang, Le

2016-07-14

Most of the existing node depth-adjustment deployment algorithms for underwater wireless sensor networks (UWSNs) just consider how to optimize network coverage and connectivity rate. However, these literatures don't discuss full network connectivity, while optimization of network energy efficiency and network reliability are vital topics for UWSN deployment. Therefore, in this study, a depth-adjustment deployment algorithm based on two-dimensional (2D) convex hull and spanning tree (NDACS) for UWSNs is proposed. First, the proposed algorithm uses the geometric characteristics of a 2D convex hull and empty circle to find the optimal location of a sleep node and activate it, minimizes the network coverage overlaps of the 2D plane, and then increases the coverage rate until the first layer coverage threshold is reached. Second, the sink node acts as a root node of all active nodes on the 2D convex hull and then forms a small spanning tree gradually. Finally, the depth-adjustment strategy based on time marker is used to achieve the three-dimensional overall network deployment. Compared with existing depth-adjustment deployment algorithms, the simulation results show that the NDACS algorithm can maintain full network connectivity with high network coverage rate, as well as improved network average node degree, thus increasing network reliability.

A Depth-Adjustment Deployment Algorithm Based on Two-Dimensional Convex Hull and Spanning Tree for Underwater Wireless Sensor Networks

PubMed Central

Jiang, Peng; Liu, Shuai; Liu, Jun; Wu, Feng; Zhang, Le

2016-01-01

Most of the existing node depth-adjustment deployment algorithms for underwater wireless sensor networks (UWSNs) just consider how to optimize network coverage and connectivity rate. However, these literatures don’t discuss full network connectivity, while optimization of network energy efficiency and network reliability are vital topics for UWSN deployment. Therefore, in this study, a depth-adjustment deployment algorithm based on two-dimensional (2D) convex hull and spanning tree (NDACS) for UWSNs is proposed. First, the proposed algorithm uses the geometric characteristics of a 2D convex hull and empty circle to find the optimal location of a sleep node and activate it, minimizes the network coverage overlaps of the 2D plane, and then increases the coverage rate until the first layer coverage threshold is reached. Second, the sink node acts as a root node of all active nodes on the 2D convex hull and then forms a small spanning tree gradually. Finally, the depth-adjustment strategy based on time marker is used to achieve the three-dimensional overall network deployment. Compared with existing depth-adjustment deployment algorithms, the simulation results show that the NDACS algorithm can maintain full network connectivity with high network coverage rate, as well as improved network average node degree, thus increasing network reliability. PMID:27428970

Deployment Methods for an Origami-Inspired Rigid-Foldable Array

NASA Technical Reports Server (NTRS)

Zirbel, Shannon A.; Trease, Brian P.; Magleby, Spencer P.; Howell, Larry L.

2014-01-01

The purpose of this work is to evaluate several deployment methods for an origami-inspired solar array at two size scales: 25-meter array and CubeSat array. The array enables rigid panel deployment and introduces new concepts for actuating CubeSat deployables. The design for the array was inspired by the origami flasher model (Lang, 1997; Shafer, 2001). Figure 1 shows the array prototyped from Garolite and Kapton film at the CubeSat scale. Prior work demonstrated that rigid panels like solar cells could successfully be folded into the final stowed configuration without requiring the panels to flex (Zirbel, Lang, Thomson, & al., 2013). The design of the array is novel and enables efficient use of space. The array can be wrapped around the central bus of the spacecraft in the case of the large array, or can accommodate storage of a small instrument payload in the case of the CubeSat array. The radial symmetry of this array around the spacecraft is ideally suited for spacecraft that need to spin. This work focuses on several actuation methods for a one-time deployment of the array. The array is launched in its stowed configuration and it will be deployed when it is in space. Concepts for both passive and active actuation were considered.

An innovative deployable solar panel system for Cubesats

NASA Astrophysics Data System (ADS)

Santoni, Fabio; Piergentili, Fabrizio; Donati, Serena; Perelli, Massimo; Negri, Andrea; Marino, Michele

2014-02-01

One of the main Cubesat bus limitations is the available on-board power. The maximum power obtained using body mounted solar panels and advanced triple junction solar cells on a triple unit Cubesat is typically less than 10 W. The Cubesat performance and the mission scenario opened to these small satellite systems could be greatly enhanced by an increase of the available power. This paper describes the design and realization of a modular deployable solar panel system for Cubesats, consisting of a modular hinge and spring system that can be potentially used on-board single (1U), double(2U), triple (3U) and six units (6U) Cubesats. The size of each solar panels is the size of a lateral Cubesat surface. The system developed is the basis for a SADA (Solar Array Drive Assembly), in which a maneuvering capability is added to the deployed solar array in order to follow the apparent motion of the sun. The system design trade-off is discussed, comparing different deployment concepts and architectures, leading to the final selection for the modular design. A prototype of the system has been realized for a 3U Cubesat, consisting of two deployable solar panel systems, made of three solar panels each, for a total of six deployed solar panels. The deployment system is based on a plastic fiber wire and thermal cutters, guaranteeing a suitable level of reliability. A test-bed for the solar panel deployment testing has been developed, supporting the solar array during deployment reproducing the dynamical situation in orbit. The results of the deployment system testing are discussed, including the design and realization of the test-bed, the mechanical stress given to the solar cells by the deployment accelerations and the overall system performance. The maximum power delivered by the system is about 50.4 W BOL, greatly enhancing the present Cubesat solar array performance.

Values of Deploying a Compact Polarimetric Radar to Monitor Extreme Precipitation in a Mountainous Area: Mineral County, Colorado

NASA Astrophysics Data System (ADS)

Cheong, B. L.; Kirstetter, P. E.; Yu, T. Y.; Busto, J.; Speeze, T.; Dennis, J.

2015-12-01

Precipitation in mountainous regions can trigger flash floods and landslides especially in areas affected by wildfire. Because of the small space-time scales required for observation, they remain poorly observed. A light-weighted X-band polarimetric radar can rapidly respond to the situation and provide continuous rainfall information with high resolution for flood forecast and emergency management. A preliminary assessment of added values to the operational practice in Mineral county, Colorado was performed in Fall 2014 and Summer 2015 with a transportable polarimetric radar deployed at the Lobo Overlook. This region is one of the numerous areas in the Rocky Mountains where the WSR-88D network does not provide sufficient weather coverage due to blockages, and the limitations have impeded forecasters and local emergency managers from making accurate predictions and issuing weather warnings. High resolution observations were collected to document the precipitation characteristics and demonstrate the added values of deploying a small weather radar in such context. The analysis of the detailed vertical structure of precipitation explain the decreased signal sampled by the operational radars. The specific microphysics analyzed though polarimetry suggest that the operational Z-R relationships may not be appropriate to monitor severe weather over this wildfire affected region. Collaboration with the local emergency managers and the National Weather Service shows the critical value of deploying mobile, polarimetric and unmanned radars in complex terrain. Several selected cases are provided in this paper for illustration.

A Lightweight, Precision-Deployable, Optical Bench for High Energy Astrophysics Missions

NASA Astrophysics Data System (ADS)

Danner, Rolf; Dailey, D.; Lillie, C.

2011-09-01

The small angle of total reflection for X-rays, forcing grazing incidence optics with large collecting areas to long focal lengths, has been a fundamental barrier to the advancement of high-energy astrophysics. Design teams around the world have long recognized that a significant increase in effective area beyond Chandra and XMM-Newton requires either a deployable optical bench or separate X-ray optics and instrument module on formation flying spacecraft. Here, we show that we have in hand the components for a lightweight, precision-deployable optical bench that, through its inherent design features, is the affordable path to the next generation of imaging high-energy astrophysics missions. We present our plans for a full-scale engineering model of a deployable optical bench for Explorer-class missions. We intend to use this test article to raise the technology readiness level (TRL) of the tensegrity truss for a lightweight, precision-deployable optical bench for high-energy astrophysics missions from TRL 3 to TRL 5 through a set of four well-defined technology milestones. The milestones cover the architecture's ability to deploy and control the focal point, characterize the deployed dynamics, determine long-term stability, and verify the stowed load capability. Our plan is based on detailed design and analysis work and the construction of a first prototype by our team. Building on our prior analysis and the high TRL of the architecture components we are ready to move on to the next step. The key elements to do this affordably are two existing, fully characterized, flight-quality, deployable booms. After integrating them into the test article, we will demonstrate that our architecture meets the deployment accuracy, adjustability, and stability requirements. The same test article can be used to further raise the TRL in the future.

Bioinformatics Pipelines for Targeted Resequencing and Whole-Exome Sequencing of Human and Mouse Genomes: A Virtual Appliance Approach for Instant Deployment

PubMed Central

Saeed, Isaam; Wong, Stephen Q.; Mar, Victoria; Goode, David L.; Caramia, Franco; Doig, Ken; Ryland, Georgina L.; Thompson, Ella R.; Hunter, Sally M.; Halgamuge, Saman K.; Ellul, Jason; Dobrovic, Alexander; Campbell, Ian G.; Papenfuss, Anthony T.; McArthur, Grant A.; Tothill, Richard W.

2014-01-01

Targeted resequencing by massively parallel sequencing has become an effective and affordable way to survey small to large portions of the genome for genetic variation. Despite the rapid development in open source software for analysis of such data, the practical implementation of these tools through construction of sequencing analysis pipelines still remains a challenging and laborious activity, and a major hurdle for many small research and clinical laboratories. We developed TREVA (Targeted REsequencing Virtual Appliance), making pre-built pipelines immediately available as a virtual appliance. Based on virtual machine technologies, TREVA is a solution for rapid and efficient deployment of complex bioinformatics pipelines to laboratories of all sizes, enabling reproducible results. The analyses that are supported in TREVA include: somatic and germline single-nucleotide and insertion/deletion variant calling, copy number analysis, and cohort-based analyses such as pathway and significantly mutated genes analyses. TREVA is flexible and easy to use, and can be customised by Linux-based extensions if required. TREVA can also be deployed on the cloud (cloud computing), enabling instant access without investment overheads for additional hardware. TREVA is available at http://bioinformatics.petermac.org/treva/. PMID:24752294

Maximizing photovoltaic power generation of a space-dart configured satellite

NASA Astrophysics Data System (ADS)

Lee, Dae Young; Cutler, James W.; Mancewicz, Joe; Ridley, Aaron J.

2015-06-01

Many small satellites are power constrained due to their minimal solar panel area and the eclipse environment of low-Earth orbit. As with larger satellites, these small satellites, including CubeSats, use deployable power arrays to increase power production. This presents a design opportunity to develop various objective functions related to energy management and methods for optimizing these functions over a satellite design. A novel power generation model was created, and a simulation system was developed to evaluate various objective functions describing energy management for complex satellite designs. The model uses a spacecraft-body-fixed spherical coordinate system to analyze the complex geometry of a satellite's self-induced shadowing with computation provided by the Open Graphics Library. As an example design problem, a CubeSat configured as a space-dart with four deployable panels is optimized. Due to the fast computation speed of the solution, an exhaustive search over the design space is used to find the solar panel deployment angles which maximize total power generation. Simulation results are presented for a variety of orbit scenarios. The method is extendable to a variety of complex satellite geometries and power generation systems.

Development of a Solar Array Drive Assembly for CubeSat

NASA Technical Reports Server (NTRS)

Passaretti, Mike; Hayes, Ron

2010-01-01

Small satellites and in particular CubeSats, have increasingly become more viable as platforms for payloads typically requiring much larger bus structures. As advances in technology make payloads and instruments for space missions smaller, lighter and more power efficient, a niche market is emerging from the university community to perform rapidly developed, low-cost missions on very small spacecraft - micro, nano, and picosatellites. In just the last few years, imaging, biological and new technology demonstration missions have been either proposed or have flown using variations of the CubeSat structure as a basis. As these missions have become more complex, and the CubeSat standard has increased in both size (number of cubes) and mass, available power has become an issue. Body-mounted solar cells provide a minimal amount of power; deployable arrays improve on that baseline but are still limited. To truly achieve maximum power, deployed tracked arrays are necessary. To this end, Honeybee Robotics Spacecraft Mechanisms Corporation, along with MMA of Nederland Colorado, has developed a solar array drive assembly (SADA) and deployable solar arrays specifically for CubeSat missions. In this paper, we discuss the development of the SADA.

Surface Control of Cold Hibernated Elastic Memory Self-Deployable Structure

NASA Technical Reports Server (NTRS)

Sokolowski, Witold M.; Ghaffarian, Reza

2006-01-01

A new class of simple, reliable, lightweight, low packaging volume and cost, self-deployable structures has been developed for use in space and commercial applications. This technology called 'cold hibernated elastic memory' (CHEM) utilizes shape memory polymers (SMP)in open cellular (foam) structure or sandwich structures made of shape memory polymer foam cores and polymeric composite skins. Some of many potential CHEM space applications require a high precision deployment and surface accuracy during operation. However, a CHEM structure could be slightly distorted by the thermo-mechanical processing as well as by thermal space environment Therefore, the sensor system is desirable to monitor and correct the potential surface imperfection. During these studies, the surface control of CHEM smart structures was demonstrated using a Macro-Fiber Composite (MFC) actuator developed by the NASA LaRC and US Army ARL. The test results indicate that the MFC actuator performed well before and after processing cycles. It reduced some residue compressive strain that in turn corrected very small shape distortion after each processing cycle. The integrated precision strain gages were detecting only a small flat shape imperfection indicating a good recoverability of original shape of the CHEM test structure.

The Case for Small Spacecraft: An Integrated Perspective on Electric Propulsion

DTIC Science & Technology

1995-01-01

microsatellite classes (termed small saellites for the remaining por-tion of this paper). A -large body -of information has been generated over the past...there is a growing market for small satellite propulsion. This year several flight es:eriments and commercial systems will deploy with electtric ...determined from equation 7. Cd is the drag coefficient, which is generally on the order of one[ 2], and we will assume to be 2.2. Although it neglects lateral

Intelligent Transportation Systems Early Deployment Planning for a Small Region

DOT National Transportation Integrated Search

1999-01-01

Strategic planning for intelligent transportation systems (ITS) in : smaller metropolitan areas presents a number of difficulties. Awareness of and : experience with the use of electronics and communications systems among : transportation syst...

Tim Reber | NREL

Science.gov Websites

also leads the Sustainable Energy for Remote Indonesian Grids program, with the aim to increase deployment of clean energy in small, remote grids across Indonesia. Prior to joining NREL, Tim worked as a

Micro-sensors for in-situ meteorological measurements

NASA Technical Reports Server (NTRS)

Crisp, David; Kaiser, William J.; Vanzandt, Thomas R.; Tillman, James E.

1993-01-01

Improved in-situ meteorological measurements are needed for monitoring the weather and climate of the terrestrial and Martian atmospheres. We have initiated a program to assess the feasibility and utility of micro-sensors for precise in-situ meteorological measurements in these environments. Sensors are being developed for measuring pressure, temperature, wind velocity, humidity, and aerosol amounts. Silicon micro-machining and large scale integration technologies are being used to make sensors that are small, rugged, lightweight, and require very little power. Our long-term goal is to develop very accurate miniaturized sensors that can be incorporated into complete instrument packages or 'micro weather stations,' and deployed on a variety of platforms. If conventional commercially available silicon production techniques can be used to fabricate these sensor packages, it will eventually be possible to mass-produce them at low cost. For studies of the Earth's troposphere and stratosphere, they could be deployed on aircraft, dropsondes, radiosondes, or autonomous surface stations at remote sites. Improved sensor accuracy and reduced sensor cost are the primary challenges for these applications. For studies of the Martian atmosphere, these sensor packages could be incorporated into the small entry probes and surface landers that are being planned for the Mars Environmental SURvey (MESUR) Mission. That decade-long program will deploy a global network of small stations on the Martian surface for monitoring meteorological and geological processes. Low mass, low power, durability, large dynamic range and calibration stability are the principal challenges for this application. Our progress on each of these sensor types is presented.

Belonging protects against postdeployment depression in military personnel.

PubMed

Bryan, Craig J; Heron, Elizabeth A

2015-05-01

Depression among U.S. military personnel has received relatively little empirical attention compared to posttraumatic stress disorder, despite evidence that depression is associated with poor psychosocial outcomes and increased suicide risk. Even less is known about factors that protect against depression in military populations. A sample of 168 active duty Air Force convoy operators completed self-report measures of depression, posttraumatic stress, and sense of "belonging" before deploying to Iraq, and again at 1, 3, 6, and 12 months following their return. Linear growth modeling was used to test the associations of the variables over time. Mean depression scores remained low and stable across the deployment and 12-month follow-up period. Increased depression severity was significantly associated with low belonging (P < .001) and with posttraumatic stress symptoms (P < .001) at every time point. Relatively small, predominantly male sample utilizing self-report methods. A sense of belongingness may protect service members from depression at all stages of the deployment cycle, from predeployment preparations through deployment and postdeployment adjustment. © 2015 Wiley Periodicals, Inc.

Advanced Regenerative Environmental Control and Life Support Systems: Air and Water Regeneration

NASA Technical Reports Server (NTRS)

Schubert, F. H.; Wynveen, R. A.; Quattrone, P. D.

1985-01-01

Extended manned space missions will require regenerative life support techniques. Past manned missions used nonregenerative expendables, except for a molecular sieve based carbon dioxide removal system aboard Skylab. The resupply penalties associated with expendables becomes prohibitive as crew size and mission duration increase. The Space Station scheduled to be operational in the 1990's is based on a crew of four to sixteen and a resupply period of 90 days or greater. It will be the first major spacecraft to employ regenerable techniques for life support. The techniques to be used in the requirements for the space station are addressed.

Communication analysis for the expendable explorer spacecraft

NASA Technical Reports Server (NTRS)

1990-01-01

This report provides the results of communication analysis for the baseline and enhanced performance spacecraft designs proposed for Expendable Explorer Spacecraft (EES) series of missions. Five classes of orbits (Geosynchronous, Circular-28 degree inclination, Polar-90 degree inclination, Sunsynchronous-97 degree inclination, Molniya orbit) and a set of candidate instrument payloads provided by the ESS Study Manager were used to formulate the basis for the ESS Communications Study. The study was performed to assess the feasibility of using Space Network or ground stations for supporting the communications, tracking and data handling of the candidate instruments that are proposed to be launched into the desired orbit.

Cognitive capacity limitations and Need for Cognition differentially predict reward-induced cognitive effort expenditure.

PubMed

Sandra, Dasha A; Otto, A Ross

2018-03-01

While psychological, economic, and neuroscientific accounts of behavior broadly maintain that people minimize expenditure of cognitive effort, empirical work reveals how reward incentives can mobilize increased cognitive effort expenditure. Recent theories posit that the decision to expend effort is governed, in part, by a cost-benefit tradeoff whereby the potential benefits of mental effort can offset the perceived costs of effort exertion. Taking an individual differences approach, the present study examined whether one's executive function capacity, as measured by Stroop interference, predicts the extent to which reward incentives reduce switch costs in a task-switching paradigm, which indexes additional expenditure of cognitive effort. In accordance with the predictions of a cost-benefit account of effort, we found that a low executive function capacity-and, relatedly, a low intrinsic motivation to expend effort (measured by Need for Cognition)-predicted larger increase in cognitive effort expenditure in response to monetary reward incentives, while individuals with greater executive function capacity-and greater intrinsic motivation to expend effort-were less responsive to reward incentives. These findings suggest that an individual's cost-benefit tradeoff is constrained by the perceived costs of exerting cognitive effort. Copyright © 2017 Elsevier B.V. All rights reserved.

The commercial implications of the EELV program

NASA Astrophysics Data System (ADS)

Sasso, Steven E.

1998-01-01

There have been several studies over the past 15 years intended to define and develop a space launch system that would meet future needs of the United States Government (USG). While these past studies (Advanced Launch System, National Launch System, Spacelifter, etc) yielded valuable data, none were carried to fruition. Overriding issues included high development cost, changing requirements, and uncertainty in the mission model, as well lack of a clear direction for where this nation should be headed. In 1995, the Air Force embarked on the Evolved Expendable Launch Vehicle (EELV) program as a way of defining and developing the next-generation expendable launch system. This time groundrules for this effort were clearly defined-the program relied on the use of evolving a system rather than developing a high-technology solution to reduce development cost, and the commercial market was factored in as a way of reducing cost to the USG. The EELV program is nearing the engineering manufacturing development (EMD) phase by mid-1998 with first flight planned for early 2001. This paper describes the planned Lockheed Martin EELV program and its ability to utilize the commercial market to benefit the USG in its need to develop the next-generation expendable launch vehicle.

Swarms of small earthquakes on Marapi Volcano, West Sumatra, Indonesia: are these precursors to explosion event?

NASA Astrophysics Data System (ADS)

Hidayat, D.; Patria, C.; Adi, S.; Gunawan, H.; Taisne, B.; Nurfiani, D.; Tan, C. T.

2016-12-01

Marapi Volcano's activity is characterized by Strombolian to small Vulcanian explosions with occasional VEI 2 producing tephra and pyroclastic flows. Currently in collaboration between Earth Observatory of Singapore (EOS) and Centre for Volcanology and Geological Hazard Mitigation (CVGHM) the volcano is seismically monitored with 7 broadband stations, and 2 short-period stations. In addition, we deployed 2 tiltmeters and an experimental soil CO2 sensor. These stations are telemetered by 5.8GHz radio to Marapi Observatory Post where data are archived and displayed for Marapi observers for their daily volcano activity monitoring work. We also archive the data in the EOS and CVGHM main offices. Data are being utilized by volcano scientists of CVGHM and researchers in both institutes as well as university students in and around them. We presented seismic earthquake sequences (swarm) prior to small explosion on Marapi in July 2016. These earthquakes are small, better identified after the deployment of seismic stations at summit, and located at depths < 1km near the volcano active vents. Similar swarms occurred prior to small explosions of Marapi. We also presented VLP-LP signals associated with an explosion which can be explained as volumetric change of sub-vertical crack at depth similar to the occurrence of small earthquake swarms. Our study attempt to understand the state of the volcano based on monitoring data and enable us to better estimate the hazards associated with future small explosions or eruptions.

Enabling Science and Deep Space Exploration through Space Launch System (LSL) Secondary Payload Opportunities

NASA Technical Reports Server (NTRS)

Singer, Jody; Pelfrey, Joseph; Norris, George

2016-01-01

For the first time in almost 40 years, a NASA human-rated launch vehicle has completed its Critical Design Review (CDR). By reaching this milestone, NASA's Space Launch System (SLS) and Orion spacecraft are on the path to launch a new era of deep space exploration. NASA is making investments to expand science and exploration capability of the SLS by developing the capability to deploy small satellites during the trans-lunar phase of the mission trajectory. Exploration Mission 1 (EM-1), currently planned for launch no earlier than July 2018, will be the first mission to carry such payloads on the SLS. The EM-1 launch will include thirteen 6U Cubesat small satellites that will be deployed beyond low earth orbit. By providing an earth-escape trajectory, opportunities are created for advancement of small satellite subsystems, including deep space communications and in-space propulsion. This SLS capability also creates low-cost options for addressing existing Agency strategic knowledge gaps and affordable science missions. A new approach to payload integration and mission assurance is needed to ensure safety of the vehicle, while also maintaining reasonable costs for the small payload developer teams. SLS EM-1 will provide the framework and serve as a test flight, not only for vehicle systems, but also payload accommodations, ground processing, and on-orbit operations. Through developing the requirements and integration processes for EM-1, NASA is outlining the framework for the evolved configuration of secondary payloads on SLS Block upgrades. The lessons learned from the EM-1 mission will be applied to processes and products developed for future block upgrades. In the heavy-lift configuration of SLS, payload accommodations will increase for secondary opportunities including small satellites larger than the traditional Cubesat class payload. The payload mission concept of operations, proposed payload capacity of SLS, and the payload requirements for launch and deployment will be described to provide potential payload users an understanding of this unique exploration capability.

Evaluating IPv6 Adoption in the Internet

NASA Astrophysics Data System (ADS)

Colitti, Lorenzo; Gunderson, Steinar H.; Kline, Erik; Refice, Tiziana

As IPv4 address space approaches exhaustion, large networks are deploying IPv6 or preparing for deployment. However, there is little data available about the quantity and quality of IPv6 connectivity. We describe a methodology to measure IPv6 adoption from the perspective of a Web site operator and to evaluate the impact that adding IPv6 to a Web site will have on its users. We apply our methodology to the Google Web site and present results collected over the last year. Our data show that IPv6 adoption, while growing significantly, is still low, varies considerably by country, and is heavily influenced by a small number of large deployments. We find that native IPv6 latency is comparable to IPv4 and provide statistics on IPv6 transition mechanisms used.

Preliminary results from DIMES: Dispersion in the ACC

NASA Astrophysics Data System (ADS)

Balwada, D.; Speer, K.; LaCasce, J. H.; Owens, B.

2012-04-01

The Diapycnal and Isopynal Mixing Experiment in the Southern Ocean (DIMES) is a CLIVAR process study designed to study mixing in the Antarctic Circumpolar Current. The experiment includes tracer release, float, and small-scale turbulence components. This presentation will report on some results of the float component, from floats deployed across the ACC in the Southeast Pacific Ocean. These are the first subsurface Lagrangian trajectories from the ACC. Floats were deployed to follow approximately a constant density surface for a period of 1-3 years. To help aid the experimental results virtual floats were advected using AVISO data and basic statistics were derived from both deployed and virtual float trajectories. Experimental design, initial results, comparison to virtual floats and single particle and relative dispersion calculations will be presented.

FLUIDIC: Metal Air Recharged

ScienceCinema

Friesen, Cody

2018-02-14

Fluidic, with the help of ARPA-E funding, has developed and deployed the world's first proven high cycle life metal air battery. Metal air technology, often used in smaller scale devices like hearing aids, has the lowest cost per electron of any rechargeable battery storage in existence. Deploying these batteries for grid reliability is competitive with pumped hydro installations while having the advantages of a small footprint. Fluidic's battery technology allows utilities and other end users to store intermittent energy generated from solar and wind, as well as maintain reliable electrical delivery during power outages. The batteries are manufactured in the US and currently deployed to customers in emerging markets for cell tower reliability. As they continue to add customers, they've gained experience and real world data that will soon be leveraged for US grid reliability.

Estimating Turbulent Surface Fluxes from Small Unmanned Aircraft: Evaluation of Current Abilities

NASA Astrophysics Data System (ADS)

de Boer, G.; Lawrence, D.; Elston, J.; Cassano, J. J.; Mack, J.; Wildmann, N.; Nigro, M. A.; Ivey, M.; Wolfe, D. E.; Muschinski, A.

2014-12-01

Heat transfer between the atmosphere and Earth's surface represents a key component to understanding Earth energy balance, making it important in understanding and simulating climate. Arguably, the oceanic air-sea interface and Polar sea-ice-air interface are amongst the most challenging in which to measure these fluxes. This difficulty results partially from challenges associated with infrastructure deployment on these surfaces and partially from an inability to obtain spatially representative values over a potentially inhomogeneous surface. Traditionally sensible (temperature) and latent (moisture) fluxes are estimated using one of several techniques. A preferred method involves eddy-correlation where cross-correlation between anomalies in vertical motion (w) and temperature (T) or moisture (q) is used to estimate heat transfer. High-frequency measurements of these quantities can be derived using tower-mounted instrumentation. Such systems have historically been deployed over land surfaces or on ships and buoys to calculate fluxes at the air-land or air-sea interface, but such deployments are expensive and challenging to execute, resulting in a lack of spatially diverse measurements. A second ("bulk") technique involves the observation of horizontal windspeed, temperature and moisture at a given altitude over an extended time period in order to estimate the surface fluxes. Small Unmanned Aircraft Systems (sUAS) represent a unique platform from which to derive these fluxes. These sUAS can be small ( 1 m), lightweight ( 700 g), low cost ( $2000) and relatively easy to deploy to remote locations and over inhomogeneous surfaces. We will give an overview of the ability of sUAS to provide measurements necessary for estimating surface turbulent fluxes. This discussion is based on flights in the vicinity of the 1000 ft. Boulder Atmospheric Observatory (BAO) tower, and over the US Department of Energy facility at Oliktok Point, Alaska. We will present initial comparisons between UAS-derived turbulent fluxes and those derived from tower-based instrumentation and discuss differences in the context of sensor technology and flight patterns employed to collect data.

Lightweight GPS-tags, one giant leap for wildlife tracking? An assessment approach.

PubMed

Recio, Mariano R; Mathieu, Renaud; Denys, Paul; Sirguey, Pascal; Seddon, Philip J

2011-01-01

Recent technological improvements have made possible the development of lightweight GPS-tagging devices suitable to track medium-to-small sized animals. However, current inferences concerning GPS performance are based on heavier designs, suitable only for large mammals. Lightweight GPS-units are deployed close to the ground, on species selecting micro-topographical features and with different behavioural patterns in comparison to larger mammal species. We assessed the effects of vegetation, topography, motion, and behaviour on the fix success rate for lightweight GPS-collar across a range of natural environments, and at the scale of perception of feral cats (Felis catus). Units deployed at 20 cm above the ground in sites of varied vegetation and topography showed that trees (native forest) and shrub cover had the largest influence on fix success rate (89% on average); whereas tree cover, sky availability, number of satellites and horizontal dilution of position (HDOP) were the main variables affecting location error (±39.5 m and ±27.6 m before and after filtering outlier fixes). Tests on HDOP or number of satellites-based screening methods to remove inaccurate locations achieved only a small reduction of error and discarded many accurate locations. Mobility tests were used to simulate cats' motion, revealing a slightly lower performance as compared to the fixed sites. GPS-collars deployed on 43 cats showed no difference in fix success rate by sex or season. Overall, fix success rate and location error values were within the range of previous tests carried out with collars designed for larger species. Lightweight GPS-tags are a suitable method to track medium to small size species, hence increasing the range of opportunities for spatial ecology research. However, the effects of vegetation, topography and behaviour on location error and fix success rate need to be evaluated prior to deployment, for the particular study species and their habitats.

Application of powder metallurgy techniques for the development of non-toxic ammunition. Final CRADA report

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

Lowden, R.; Kelly, R.

1997-05-30

The purpose of the Cooperative Research and Development Agreement (CRADA) between Martin Marietta Energy Systems, Inc., and Delta Frangible Ammunition (DFA), was to identify and evaluate composite materials for the development of small arms ammunition. Currently available small arms ammunition utilizes lead as the major component of the projectile. The introduction of lead into the environment by these projectiles when they are expended is a rapidly increasing environmental problem. At certain levels, lead is a toxic metal to the environment and a continual health and safety concern for firearm users as well as those who must conduct lead recovery operationsmore » from the environment. DFA is a leading supplier of high-density mixtures, which will be used to replace lead-based ammunition in specific applications. Current non-lead ammunition has several limitations that prevent it from replacing lead-based ammunition in many applications (such as applications that require ballistics, weapon recoil, and weapon function identical to that of lead-based ammunition). The purpose of the CRADA was to perform the research and development to identify cost-effective materials to be used in small arms ammunition that eventually will be used in commercially viable, environmentally conscious, non-lead, frangible and/or non-frangible, ammunition.« less

Wastewater infrastructure for small cities in an urbanizing world: integrating protection of human health and the environment with resource recovery and food security.

PubMed

Verbyla, Matthew E; Oakley, Stewart M; Mihelcic, James R

2013-04-16

The majority of population growth in developing countries will occur in small cities closely linked to agricultural zones, with poor access to water and sanitation. Wastewater management priorities in these regions will be different from those in larger cities and developed countries. Two wastewater treatment systems in Bolivia, one with an upflow anaerobic sludge blanket (UASB) reactor and polishing ponds, the other with three stabilization ponds, are assessed to determine their resource recovery potential. The UASB reactor produces biogas with 500-650 MJ per day. In six months, both systems discharge wastewater with the same mass of nutrients as fertilizers used to produce crops containing 10-75 days' worth of the recommended food energy intake for each person using the system. Both systems also discharge detectable levels of helminth eggs, Giardia cysts, and Cryptosporidium oocysts, but the UASB reactor system discharges higher concentrations, implying limited reuse potential. From a regional management standpoint, small cities should not expend resources to treat wastewater to levels suitable for discharge into surface waters. Rather, they should focus on removing pathogens to reclaim water and nutrients. Biogas recovery may be a priority that should be subservient to water and nutrient recovery in these settings.

Biomimetic Models for An Ecological Approach to Massively-Deployed Sensor Networks

NASA Technical Reports Server (NTRS)

Jones, Kennie H.; Lodding, Kenneth N.; Olariu, Stephan; Wilson, Larry; Xin, Chunsheng

2005-01-01

Promises of ubiquitous control of the physical environment by massively-deployed wireless sensor networks open avenues for new applications that will redefine the way we live and work. Due to small size and low cost of sensor devices, visionaries promise systems enabled by deployment of massive numbers of sensors ubiquitous throughout our environment working in concert. Recent research has concentrated on developing techniques for performing relatively simple tasks with minimal energy expense, assuming some form of centralized control. Unfortunately, centralized control is not conducive to parallel activities and does not scale to massive size networks. Execution of simple tasks in sparse networks will not lead to the sophisticated applications predicted. We propose a new way of looking at massively-deployed sensor networks, motivated by lessons learned from the way biological ecosystems are organized. We demonstrate that in such a model, fully distributed data aggregation can be performed in a scalable fashion in massively deployed sensor networks, where motes operate on local information, making local decisions that are aggregated across the network to achieve globally-meaningful effects. We show that such architectures may be used to facilitate communication and synchronization in a fault-tolerant manner, while balancing workload and required energy expenditure throughout the network.

PERCEPT: indoor navigation for the blind and visually impaired.

PubMed

Ganz, Aura; Gandhi, Siddhesh Rajan; Schafer, James; Singh, Tushar; Puleo, Elaine; Mullett, Gary; Wilson, Carole

2011-01-01

In order to enhance the perception of indoor and unfamiliar environments for the blind and visually-impaired, we introduce the PERCEPT system that supports a number of unique features such as: a) Low deployment and maintenance cost; b) Scalability, i.e. we can deploy the system in very large buildings; c) An on-demand system that does not overwhelm the user, as it offers small amounts of information on demand; and d) Portability and ease-of-use, i.e., the custom handheld device carried by the user is compact and instructions are received audibly.

Instrumentation for detailed bridge-scour measurements

USGS Publications Warehouse

Landers, Mark N.; Mueller, David S.; Trent, Roy E.; ,

1993-01-01

A portable instrumentation system is being developed to obtain channel bathymetry during floods for detailed bridge-scour measurements. Portable scour measuring systems have four components: sounding instrument, horizontal positioning instrument, deployment mechanisms, and data storage device. The sounding instrument will be a digital fathometer. Horizontal position will be measured using a range-azimuth based hydrographic survey system. The deployment mechanism designed for this system is a remote-controlled boat using a small waterplane area, twin-hull design. An on-board computer and radio will monitor the vessel instrumentation, record measured data, and telemeter data to shore.

A deployable .015 inch diameter wire antenna

NASA Technical Reports Server (NTRS)

Dibiasi, L.

1979-01-01

This mechanism was developed to dispense a small diameter wire which serves as a receiving antenna for electric field measurements on an Earth orbiting satellite. The antenna is deployed radially from a spinning satellite. A brushless dc motor drives a storage spool to dispense the wire at a controlled rate. Centrifugal force, acting on a mass attached to the end of the wire, keeps the wire in the radial position. The mechanism design, testing, and performance characteristics are discussed. Finally, operational data of the mechanism while in orbit are presented.

Assessment Of The Aerodynamic And Aerothermodynamic Performance Of The USV-3 High-Lift Re-Entry Vehicle

NASA Astrophysics Data System (ADS)

Pezzella, Giuseppe; Richiello, Camillo; Russo, Gennaro

2011-05-01

This paper deals with the aerodynamic and aerothermodynamic trade-off analysis carried out with the aim to design a hypersonic flying test bed (FTB), namely USV3. Such vehicle will have to be launched with a small expendable launcher and shall re-enter the Earth atmosphere allowing to perform several experiments on critical re-entry phenomena. The demonstrator under study is a re-entry space glider characterized by a relatively simple vehicle architecture able to validate hypersonic aerothermodynamic design database and passenger experiments, including thermal shield and hot structures. Then, a summary review of the aerodynamic characteristics of two FTB concepts, compliant with a phase-A design level, has been provided hereinafter. Indeed, several design results, based both on engineering approach and computational fluid dynamics, are reported and discussed in the paper.

Image-based ranging and guidance for rotorcraft

NASA Technical Reports Server (NTRS)

Menon, P. K. A.

1991-01-01

This report documents the research carried out under NASA Cooperative Agreement No. NCC2-575 during the period Oct. 1988 - Dec. 1991. Primary emphasis of this effort was on the development of vision based navigation methods for rotorcraft nap-of-the-earth flight regime. A family of field-based ranging algorithms were developed during this research period. These ranging schemes are capable of handling both stereo and motion image sequences, and permits both translational and rotational camera motion. The algorithms require minimal computational effort and appear to be implementable in real time. A series of papers were presented on these ranging schemes, some of which are included in this report. A small part of the research effort was expended on synthesizing a rotorcraft guidance law that directly uses the vision-based ranging data. This work is discussed in the last section.

Technology Demonstration Missions

NASA Technical Reports Server (NTRS)

McDougal, John; French, Raymond; Adams-Fogle, Beth; Stephens, Karen

2015-01-01

Technology Demonstration Missions (TDM) is in its third year of execution, being initiated in 2010 and baselined in January of 2012. There are 11 projects that NASA Marshall Space Flight Center (MSFC) has contributed to or led: (1) Evolvable Cryogenics (eCryo): Cyrogenic Propellant Storage and Transfer Engineering Development Unit (EDU), a proof of manufacturability effort, used to enhance knowledge and technology related to handling cryogenic propellants, specifically liquid hydrogen. (2) Composites for Exploration Upper Stage (CEUS): Design, build, test, and address flight certification of a large composite shell suitable for the second stage of the Space Launch System (SLS). (3) Deep Space Atomic Clock (DSAC): Spaceflight to demo small, low-mass atomic clock that can provide unprecedented stability for deep space navigation. (4) Green Propellant Infusion Mission (GPIM): Demo of high-performance, green propellant propulsion system suitable for Evolved Expendable Launch Vehicle (EELV) Secondary Payload Adapter (ESPA)-class spacecraft. (5) Human Exploration Telerobotics (HET): Demonstrating how telerobotics, remote control of a variety of robotic systems, can take routine, highly repetitive, dangerous or long-duration tasks out of human hands. (6) Laser Communication Relay Demo (LCRD): Demo to advance optical communications technology toward infusion into deep space and near Earth operational systems, while growing the capabilities of industry sources. (7) Low Density Supersonic Decelerator (LDSD): Demo new supersonic inflatable decelerator and parachute technologies to enable Mars landings of larger payloads with greater precision at a wider range of altitudes. (8) Mars Science Laboratory (MSL) Entry Descent & Landing Instrumentation (MEDLI): Demo of embedded sensors embedded in the MSL heat shield, designed to record the heat and atmospheric pressure experienced during the spacecraft's high-speed, hot entry in the Martian atmosphere. (9) Solar Electric Propulsion (SEP): 50-kW class spacecraft that uses flexible blanket solar arrays for power generation and an electric propulsion system that delivers payload from low-Earth orbit to higher orbits. (10) Solar Sail Demonstration (SSD): Demo to validate sail deployment techniques for solar sails that are propelled by the pressure of sunlight. (11) Terrestrial HIAD Orbit Reentry (THOR): Demo of a 3.7-m Hypersonic Inflatable Aerodynamic Decelerator (HIAD) entry vehicle to test second generation aerothermal performance and modeling.

Multiyear ice transport and small scale sea ice deformation near the Alaska coast measured by air-deployable Ice Trackers

NASA Astrophysics Data System (ADS)

Mahoney, A. R.; Kasper, J.; Winsor, P.

2015-12-01

Highly complex patterns of ice motion and deformation were captured by fifteen satellite-telemetered GPS buoys (known as Ice Trackers) deployed near Barrow, Alaska, in spring 2015. Two pentagonal clusters of buoys were deployed on pack ice by helicopter in the Beaufort Sea between 20 and 80 km offshore. During deployment, ice motion in the study region was effectively zero, but two days later the buoys captured a rapid transport event in which multiyear ice from the Beaufort Sea was flushed into the Chukchi Sea. During this event, westward ice motion began in the Chukchi Sea and propagated eastward. This created new openings in the ice and led to rapid elongation of the clusters as the westernmost buoys accelerated away from their neighbors to the east. The buoys tracked ice velocities of over 1.5 ms-1, with fastest motion occurring closest to the coast indicating strong current shear. Three days later, ice motion reversed and the two clusters became intermingled, rendering divergence calculations based on the area enclosed by clusters invalid. The data show no detectable difference in velocity between first year and multiyear ice floes, but Lagrangian timeseries of SAR imagery centered on each buoy show that first year ice underwent significant small-scale deformation during the event. The five remaining buoys were deployed by local residents on prominent ridges embedded in the landfast ice within 16 km of Barrow in order to track the fate of such features after they detached from the coast. Break-up of the landfast ice took place over a period of several days and, although the buoys each initially followed a similar eastward trajectory around Point Barrow into the Beaufort Sea, they rapidly dispersed over an area more than 50 km across. With rapid environmental and socio-economic change in the Arctic, understanding the complexity of nearshore ice motion is increasingly important for predict future changes in the ice and the tracking ice-related hazards contaminants entrained in the ice. This work demonstrates the ability of low-cost easily-deployable Ice Trackers to generate to generate data of both scientific and operational value.

Reconnaissance and Autonomy for Small Robots (RASR)

DTIC Science & Technology

2012-06-29

The Reconnaissance and Autonomy for Small Robots (RASR) team developed a system for the coordination of groups of unmanned ground vehicles (UGVs...development of a system that used 1) a relevant deployable platform; 2) a minimum set of relatively inexpensive navigation and LADAR sensors; 3) an...expandable and modular control system with innovative software algorithms to minimize computing footprint; and that minimized 4) required communications

The DSI small satellite launcher

NASA Technical Reports Server (NTRS)

Nichols, S.; Gibbons, D.; Wise, J.; Nguyen, D.

1992-01-01

A new launcher has been developed by DSI, that is compatible with the GAS canisters. It has the proven capability to deploy a satellite from an orbiting Shuttle that is 18 inches in diameter, 31 inches long, and weighing 190 pounds. These DSI Launchers were used aboard the Discovery (STS-39) in May 1991 as part of the Infrared Background Signature Survey (IBSS) to deploy three small satellites known as Chemical Release Observation (CRO) satellites A, B, and C. Because the satellites contained hazardous liquids (MMH, UDMH, and MON-10) and were launched from GAS Cylinders without motorized doors, the launchers were required to pass NASA Shuttle Payload safety and verification requirements. Some of the more interesting components of the design were the V-band retention and separation mechanism, the separation springs, and the launcher electronics which provided a properly inhibited release sequence operated through the Small Payload Accommodations Switch Panel (SPASP) on board the Orbiter. The original plan for this launcher was to use a motorized door. The launcher electronics, therefore has the capability to be modified to accommodate the door, if desired.

The COWVR Mission: Demonstrating Small Satellite Capability to Fill the Looming Gap in Microwave Radiometer Coverage

NASA Astrophysics Data System (ADS)

Brown, S. T.; Focardi, P.; Kitiyakara, A.; Maiwald, F.; Milligan, L.; Montes, O.; Padmanabhan, S.; Redick, R.; Russell, D.

2017-12-01

Passive microwave radiometer systems have been providing important Earth observations for over 30 years, including by not limited to surface wind vector, atmospheric and surface temperature, water vapor, clouds, precipitation, snow and sea ice. These data are critical for weather forecasting and the longevity of the record, along with careful calibration, has also enabled the extraction of climate records. But the future of these systems, conically scanning systems in particular, is uncertain. These sensors are have typically been developed at high cost and deployed on large spacecraft. A solution may lie in smaller, lower-cost but equally capable sensors manifested on free-flying small-satellites which can open the door to new possibilities and an avenue for sustainable passive microwave observation. Among the possibilities are deployment in constellations to shorten revisit time to improve weather forecasting or routine deployment of single sensors over time to ensure an unbroken long duration climate record. The Compact Ocean Wind Vector Radiometer (COWVR) mission, formally the US Air Force ORS-6 mission, will demonstrate a new generation conically scanning passive microwave radiometer on a small satellite. COWVR is an 18-34 GHz fully polarimetric radiometer with a 75cm aperture designed to provide measurements of ocean vector winds with an accuracy that meets or exceeds that provided by WindSat in all non-precipitating conditions, but using a simpler design which has both performance and cost advantages. This paper will give an overview of the COWVR instrument and mission and its performance estimated from pre-launch calibration data. While the COWVR mission is a focused technology demonstration mission, the sensor design is scalable to a much broader frequency range while retaining its low-cost advantage. We will describe extensions of the COWVR design that have been developed and the capabilities of such systems when deployed in a constellation scenario or climate monitoring scenario. We will also describe deployable reflector technologies being developed at JPL to enable large apertures (>2-meter) to stow inside an ESPA volume (<80cm) and be suitable for operation from 6-200 GHz. This removes any limitations on the spatial resolution of the sensor, even when launched as a ESPA secondary payload.

Lessons Learned in the Development of Gamma-Rover (GRover) Inspection Device

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

Valdez, Patrick LJ; Alzheimer, James M.; Catalan, Michael A.

2006-02-11

The Gamma-Rover (GRover) is an electrically powered crawler designed to visually inspect and characterize the radiological conditions within the B-Cell and D-Cell ventilation ducting in support of the Hanford Site’s 324 Building Stabilization/Deactivation Project. Due to the bid opening of the Department of Energy’s River Corridor Project prior to deployment, GRover has not yet been deployed. The delay in deployment has allowed the designers to develop lessons learned from the original development in order to propose improvements when the system is deployed in the future. Gamma field information is detected with a pair of Eberline DA1-8/RMS systems. One system ismore » mounted directly on the crawler, while the second is mounted on the deployment platform. Four web cameras on a pair of CAT-5e/USB channels provide video feedback from both the crawler and the deployment platform. The drive system was designed to overcome a potentially difficult path of the duct, which included three ninety-degree bends. Mockups of the duct bends yielded high friction on the tether, and a drive system to overcome this friction was especially difficult to design into such a small package. Deployment was to be performed during a routine air filter change-out. As such, a specialized deployment platform was designed to pass through the existing filter housing. GRover would be required to be staged within the hot cell prior to the filter change-out and could therefore be dosed in excess of 8 hours. Thus, the platform also had to protect the electronics from radiation damage for an extended period of time.« less

Evaluation of Speed Control Signs for Small Rural Towns

DOT National Transportation Integrated Search

2006-04-14

This report presents the results of the national evaluation of the Sacramento-Watt Avenue Transit Signal Priority Project, a cooperative project between Sacramento County and the Sacramento Regional Transit District (RT) to deploy transit signal prio...

Planning for intelligent transportation systems in small urban areas.

DOT National Transportation Integrated Search

1997-01-01

Intelligent transportation systems (ITS) has been a primary program focus of the U.S. Department of Transportation since its origination in the Intermodal Surface Transportation Efficiency Act of 1991. The federal ITS program funded early deployment ...

A system concept for gradual deployment of geostationary lightsats

NASA Astrophysics Data System (ADS)

Peters, Graham C.; Garry, James R. C.

1993-10-01

Small satellites provide an attractive option for developing countries wishing to own and operate a satellite for the first time. It is proposed that space segment capacity could be built-up in response to increasing traffic requirements by launching small satellites at intervals into a single orbital slot to form a cluster. This paper, which results from an ESA study, reviews the various system aspects which must be considered and develops a suitable approach for multi-satellite deployment and collocation. Particular attention is paid to the system and payload configuration required to achieve effective mutual sparing between the satellites' payloads as the constellation is expanded. Mission and operational aspects are examined to obtain an acceptable risk of collisions between the satellites in a single orbit slot. The complexity and cost of operations are investigated to obtain the optimum size of satellite required to satisfy different demand requirements taken from real market scenarios.

Wireless Sensor Networks for Oceanographic Monitoring: A Systematic Review

PubMed Central

Albaladejo, Cristina; Sánchez, Pedro; Iborra, Andrés; Soto, Fulgencio; López, Juan A.; Torres, Roque

2010-01-01

Monitoring of the marine environment has come to be a field of scientific interest in the last ten years. The instruments used in this work have ranged from small-scale sensor networks to complex observation systems. Among small-scale networks, Wireless Sensor Networks (WSNs) are a highly attractive solution in that they are easy to deploy, operate and dismantle and are relatively inexpensive. The aim of this paper is to identify, appraise, select and synthesize all high quality research evidence relevant to the use of WSNs in oceanographic monitoring. The literature is systematically reviewed to offer an overview of the present state of this field of study and identify the principal resources that have been used to implement networks of this kind. Finally, this article details the challenges and difficulties that have to be overcome if these networks are to be successfully deployed. PMID:22163583

A large-aperture low-cost hydrophone array for tracking whales from small boats.

PubMed

Miller, B; Dawson, S

2009-11-01

A passive sonar array designed for tracking diving sperm whales in three dimensions from a single small vessel is presented, and the advantages and limitations of operating this array from a 6 m boat are described. The system consists of four free floating buoys, each with a hydrophone, built-in recorder, and global positioning system receiver (GPS), and one vertical stereo hydrophone array deployed from the boat. Array recordings are post-processed onshore to obtain diving profiles of vocalizing sperm whales. Recordings are synchronized using a GPS timing pulse recorded onto each track. Sensitivity analysis based on hyperbolic localization methods is used to obtain probability distributions for the whale's three-dimensional location for vocalizations received by at least four hydrophones. These localizations are compared to those obtained via isodiachronic sequential bound estimation. Results from deployment of the system around a sperm whale in the Kaikoura Canyon in New Zealand are shown.

Emergent Adaptive Noise Reduction from Communal Cooperation of Sensor Grid

NASA Technical Reports Server (NTRS)

Jones, Kennie H.; Jones, Michael G.; Nark, Douglas M.; Lodding, Kenneth N.

2010-01-01

In the last decade, the realization of small, inexpensive, and powerful devices with sensors, computers, and wireless communication has promised the development of massive sized sensor networks with dense deployments over large areas capable of high fidelity situational assessments. However, most management models have been based on centralized control and research has concentrated on methods for passing data from sensor devices to the central controller. Most implementations have been small but, as it is not scalable, this methodology is insufficient for massive deployments. Here, a specific application of a large sensor network for adaptive noise reduction demonstrates a new paradigm where communities of sensor/computer devices assess local conditions and make local decisions from which emerges a global behaviour. This approach obviates many of the problems of centralized control as it is not prone to single point of failure and is more scalable, efficient, robust, and fault tolerant

In situ Volcanic Plume Monitoring with small Unmanned Aerial Systems for Cal/Val of Satellite Remote Sensing Data: CARTA-UAV 2013 Mission (Invited)

NASA Astrophysics Data System (ADS)

Diaz, J. A.; Pieri, D. C.; Bland, G.; Fladeland, M. M.

2013-12-01

The development of small unmanned aerial systems (sUAS) with a variety of sensor packages, enables in situ and proximal remote sensing measurements of volcanic plumes. Using Costa Rican volcanoes as a Natural Laboratory, the University of Costa Rica as host institution, in collaboration with four NASA centers, have started an initiative to develop low-cost, field-deployable airborne platforms to perform volcanic gas & ash plume research, and in-situ volcanic monitoring in general, in conjunction with orbital assets and state-of-the-art models of plume transport and composition. Several gas sensors have been deployed into the active plume of Turrialba Volcano including a miniature mass spectrometer, and an electrochemical SO2 sensor system with temperature, pressure, relative humidity, and GPS sensors. Several different airborne platforms such as manned research aircraft, unmanned aerial vehicles, tethered balloons, as well as man-portable in-situ ground truth systems are being used for this research. Remote sensing data is also collected from the ASTER and OMI spaceborne instruments and compared with in situ data. The CARTA-UAV 2013 Mission deployment and follow up measurements successfully demonstrated a path to study and visualize gaseous volcanic emissions using mass spectrometer and gas sensor based instrumentation in harsh environment conditions to correlate in situ ground/airborne data with remote sensing satellite data for calibration and validation purposes. The deployment of such technology improves on our current capabilities to detect, analyze, monitor, model, and predict hazards presented to aircraft by volcanogenic ash clouds from active and impending volcanic eruptions.

The Lightweight Integrated Solar Array and anTenna (LISA-T) - Big Power for Small Spacecraft

NASA Technical Reports Server (NTRS)

Johnson, Les; Carr, John; Boyd, Darren

2017-01-01

NASA is developing a space power system using lightweight, flexible photovoltaic devices originally developed for use here on Earth to provide low cost power for spacecraft. The Lightweight Integrated Solar Array and anTenna (LISA-T) is a launch-stowed, orbit-deployed array on which thin-film photovoltaic and antenna elements are embedded. The LISA-T system is deployable, building upon NASA's expertise in developing thin-film deployable solar sails such the one being developed for the Near Earth Asteroid Scout project which will fly in 2018. One of the biggest challenges for the NEA Scout, and most other spacecraft, is power. There simply isn't enough of it available, thus limiting the range of operation of the spacecraft from the Sun (due to the small surface area available for using solar cells), the range of operation from the Earth (low available power with inherently small antenna sizes tightly constrain the bandwidth for communication), and the science (you can only power so many instruments with limited power). The LISA-T has the potential to mitigate each of these limitations. Inherently, small satellites are limited in surface area, volume, and mass allocation; driving competition between their need for power and robust communications with the requirements of the science or engineering payload they are developed to fly. LISA-T is addressing this issue, deploying large-area arrays from a reduced volume and mass envelope - greatly enhancing power generation and communications capabilities of small spacecraft and CubeSats. The problem is that these CubeSats can usually only generate between 7 watts and 50 watts of power. The power that can be generated by the LISA-T ranges from tens of watts to several hundred watts. A matrix of options are in development, including planar (pointed) and omnidirectional (non-pointed) arrays. The former is seeking the highest performance possible while the latter is seeking GN&C (Guidance, Navigation and Control) simplicity. In both cases, power generation ranges from tens of watts to several hundred with an expected specific power greater than 250 watts per kilogram and a stowed power density greater than 200 kilowatts per cubic meter. Options for leveraging both high performance, 'typical cost' triple junction thin-film solar cells as well as moderate performance, low cost cells are being developed. Alongside, both UHF (ultra high frequency) and S-band antennas are being integrated into the array to move their space claim away from the spacecraft and open the door for omnidirectional communications and electronically steered phase arrays.

Study of extraterrestrial disposal of radioactive wastes. Part 1: Space transportation and destination considerations for extraterrestrial disposal of radioactive wastes. [feasibility of using space shuttle

NASA Technical Reports Server (NTRS)

Thompson, R. L.; Ramler, J. R.; Stevenson, S. M.

1974-01-01

A feasibility study of extraterrestrial disposal of radioactive waste is reported. This report covers the initial work done on only one part of the NASA study, that evaluates and compares possible space destinations and space transportation systems. The currently planned space shuttle was found to be more cost effective than current expendable launch vehicles by about a factor of 2. The space shuttle requires a third stage to perform the waste disposal missions. Depending on the particular mission, this third stage could be either a reusable space tug or an expendable stage such as a Centaur.

Assessment of candidate-expendable launch vehicles for large payloads

NASA Technical Reports Server (NTRS)

1984-01-01

In recent years the U.S. Air Force and NASA conducted design studies of 3 expendable launch vehicle configurations that could serve as a backup to the space shuttle--the Titan 34D7/Centaur, the Atlas II/Centaur, and the shuttle-derived SRB-X--as well as studies of advanced shuttle-derived launch vehicles with much larger payload capabilities than the shuttle. The 3 candidate complementary launch vehicles are judged to be roughly equivalent in cost, development time, reliability, and payload-to-orbit performance. Advanced shuttle-derived vehicles are considered viable candidates to meet future heavy lift launch requirements; however, they do not appear likely to result in significant reduction in cost-per-pound to orbit.

Space shuttle phase B extension, volume 1

NASA Technical Reports Server (NTRS)

1971-01-01

In order to define a system which would significantly reduce payload delivery costs, activities were extended to modifications of the reusable space shuttle design concept. Considered were systems using orbiters with external propellant tanks and an interim expendable booster which allowed phased development of the usable orbiter and booster. Analyzed were: Merits of internal and external propellant tanks and the impact of external LH2 compared to L02 and LH2; impact of cargo bay size; impact abort; merit of expendable booster options; and merit of a phased development program. Studies showed that external L02/LH2 and the continued use of the J-2S engine on the orbiter reduced program cost and risk.

Practice brief. Securing wireless technology for healthcare.

PubMed

Retterer, John; Casto, Brian W

2004-05-01

Wireless networking can be a very complex science, requiring an understanding of physics and the electromagnetic spectrum. While the radio theory behind the technology can be challenging, a basic understanding of wireless networking can be sufficient for small-scale deployment. Numerous security mechanisms are available to wireless technologies, making it practical, scalable, and affordable for healthcare organizations. The decision on the selected security model should take into account the needs for additional server hardware and administrative costs. Where wide area network connections exist between cooperative organizations, deployment of a distributed security model can be considered to reduce administrative overhead. The wireless approach chosen should be dynamic and concentrate on the organization's specific environmental needs. Aspects of organizational mission, operations, service level, and budget allotment as well as an organization's risk tolerance are all part of the balance in the decision to deploy wireless technology.

A Causal Role for the Cortical Frontal Eye Fields in Microsaccade Deployment

PubMed Central

Dash, Suryadeep; Lomber, Stephen G.

2016-01-01

Microsaccades aid vision by helping to strategically sample visual scenes. Despite the importance of these small eye movements, no cortical area has ever been implicated in their generation. Here, we used unilateral and bilateral reversible inactivation of the frontal eye fields (FEF) to identify a cortical drive for microsaccades. Unexpectedly, FEF inactivation altered microsaccade metrics and kinematics. Such inactivation also impaired microsaccade deployment following peripheral cue onset, regardless of cue side or inactivation configuration. Our results demonstrate that the FEF provides critical top-down drive for microsaccade generation, particularly during the recovery of microsaccades after disruption by sensory transients. Our results constitute the first direct evidence, to our knowledge, for the contribution of any cortical area to microsaccade generation, and they provide a possible substrate for how cognitive processes can influence the strategic deployment of microsaccades. PMID:27509130

A Causal Role for the Cortical Frontal Eye Fields in Microsaccade Deployment.

PubMed

Peel, Tyler R; Hafed, Ziad M; Dash, Suryadeep; Lomber, Stephen G; Corneil, Brian D

2016-08-01

Microsaccades aid vision by helping to strategically sample visual scenes. Despite the importance of these small eye movements, no cortical area has ever been implicated in their generation. Here, we used unilateral and bilateral reversible inactivation of the frontal eye fields (FEF) to identify a cortical drive for microsaccades. Unexpectedly, FEF inactivation altered microsaccade metrics and kinematics. Such inactivation also impaired microsaccade deployment following peripheral cue onset, regardless of cue side or inactivation configuration. Our results demonstrate that the FEF provides critical top-down drive for microsaccade generation, particularly during the recovery of microsaccades after disruption by sensory transients. Our results constitute the first direct evidence, to our knowledge, for the contribution of any cortical area to microsaccade generation, and they provide a possible substrate for how cognitive processes can influence the strategic deployment of microsaccades.

Nanosail-D: The Small Satellite That Could!

NASA Technical Reports Server (NTRS)

Alhorn, Dean C.; Casas, Joseph P.; Agasid, Elwood F.; Adams, Charles L.; Laue, Greg; Kitts, Christopher; O'Brien, Sue

2011-01-01

Three years from its initial design review, NanoSail-D successfully deployed its sail on January 20th, 2011. It became the first solar sail vehicle to orbit the earth and the second sail ever unfurled in space. The NanoSail-D mission had two main objectives: eject a nanosatellite from a microsatellite; deploy its sail from a highly compacted volume and low mass system to validate large structure deployment and potential de-orbit technologies. These objectives were successfully achieved and the de-orbit analysis is in process. This paper presents an overview of the NanoSail-D project and insights into how potential setbacks were overcome. Many lessons have been learned during these past three years and are discussed in light of the phenomenal success and interest that this small satellite has generated. NanoSail-D was jointly designed and built by NASA's Marshall Space Flight Center and NASA's Ames Research Center. ManTech/NeXolve Corporation also provided key sail design support. The NanoSail-D experiment is managed by Marshall and jointly sponsored by the Army Space and Missile Defense Command, the Von Braun Center for Science and Innovation and Dynetics Inc. Ground operations support was provided by Santa Clara University, with radio beacon packets received from amateur operators around the world.

Strong seasonality of Bonamia sp. infection and induced Crassostrea ariakensis mortality in Bogue and Masonboro Sounds, North Carolina, USA.

PubMed

Carnegie, Ryan B; Stokes, Nancy A; Audemard, Corinne; Bishop, Melanie J; Wilbur, Ami E; Alphin, Troy D; Posey, Martin H; Peterson, Charles H; Burreson, Eugene M

2008-07-01

Asian oyster Crassostrea ariakensis is being considered for introduction to Atlantic coastal waters of the USA. Successful aquaculture of this species will depend partly on mitigating impacts by Bonamia sp., a parasite that has caused high C. ariakensis mortality south of Virginia. To better understand the biology of this parasite and identify strategies for management, we evaluated its seasonal pattern of infection in C. ariakensis at two North Carolina, USA, locations in 2005. Small (<50 mm) triploid C. ariakensis were deployed to upwellers on Bogue Sound in late spring (May), summer (July), early fall (September), late fall (November), and early winter (December) 2005; and two field sites on Masonboro Sound in September 2005. Oyster growth and mortality were evaluated biweekly at Bogue Sound, and weekly at Masonboro, with Bonamia sp. prevalence evaluated using parasite-specific PCR. We used histology to confirm infections in PCR-positive oysters. Bonamia sp. appeared in the late spring Bogue Sound deployment when temperatures approached 25 degrees C, six weeks post-deployment. Summer- and early fall-deployed oysters displayed Bonamia sp. infections after 3-4 weeks. Bonamia sp. prevalences were 75% in Bogue Sound, and 60% in Masonboro. While oyster mortality reached 100% in late spring and summer deployments, early fall deployments showed reduced (17-82%) mortality. Late fall and early winter deployments, made at temperatures <20 degrees C, developed no Bonamia sp. infections at all. Seasonal Bonamia sp. cycling, therefore, is influenced greatly by temperature. Avoiding peak seasonal Bonamia sp. activity will be essential for culturing C. ariakensis in Bonamia sp.-enzootic waters.

Investigation of hydrophobic contaminants in an urban slough system using passive sampling - Insights from sampling rate calculations

USGS Publications Warehouse

McCarthy, K.

2008-01-01

Semipermeable membrane devices (SPMDs) were deployed in the Columbia Slough, near Portland, Oregon, on three separate occasions to measure the spatial and seasonal distribution of dissolved polycyclic aromatic hydrocarbons (PAHs) and organochlorine compounds (OCs) in the slough. Concentrations of PAHs and OCs in SPMDs showed spatial and seasonal differences among sites and indicated that unusually high flows in the spring of 2006 diluted the concentrations of many of the target contaminants. However, the same PAHs - pyrene, fluoranthene, and the alkylated homologues of phenanthrene, anthracene, and fluorene - and OCs - polychlorinated biphenyls, pentachloroanisole, chlorpyrifos, dieldrin, and the metabolites of dichlorodiphenyltrichloroethane (DDT) - predominated throughout the system during all three deployment periods. The data suggest that storm washoff may be a predominant source of PAHs in the slough but that OCs are ubiquitous, entering the slough by a variety of pathways. Comparison of SPMDs deployed on the stream bed with SPMDs deployed in the overlying water column suggests that even for the very hydrophobic compounds investigated, bed sediments may not be a predominant source in this system. Perdeuterated phenanthrene (phenanthrene-d10). spiked at a rate of 2 ??g per SPMD, was shown to be a reliable performance reference compound (PRC) under the conditions of these deployments. Post-deployment concentrations of the PRC revealed differences in sampling conditions among sites and between seasons, but indicate that for SPMDs deployed throughout the main slough channel, differences in sampling rates were small enough to make site-to-site comparisons of SPMD concentrations straightforward. ?? Springer Science+Business Media B.V. 2007.

50 CFR 600.503 - Vessel and gear identification.

Code of Federal Regulations, 2010 CFR

2010-10-01

... the air. (2) The operator of each FFV not assigned an IRCS, such as a small trawler associated with a... deployed longlines, strings of traps or pots, and gillnets are marked at the surface at each terminal end...

50 CFR 600.503 - Vessel and gear identification.

Code of Federal Regulations, 2011 CFR

2011-10-01

... the air. (2) The operator of each FFV not assigned an IRCS, such as a small trawler associated with a... deployed longlines, strings of traps or pots, and gillnets are marked at the surface at each terminal end...

NETL Crosscutting Research Video Series – LIBSense™ Sensor

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

Bhatt, Chet

NETL’s LIBSense™ Sensor is a small optical sensing device that can be used to detect elements in downhole applications. Since the sensor is an all-optical device and uses no electronics, it can be deployed into extreme environments.

Online transit trip planner for small agencies using Google Transit : final deployment package.

DOT National Transportation Integrated Search

2011-09-01

Google Transit is a public transportation trip planner that enables travelers to obtain information regarding available transit services between a : given origin and given destination. While transit agencies can publish their service information onto...

Embedded Volttron specification - benchmarking small footprint compute device for Volttron

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

Sanyal, Jibonananda; Fugate, David L.; Woodworth, Ken

An embedded system is a small footprint computing unit that typically serves a specific purpose closely associated with measurements and control of hardware devices. These units are designed for reasonable durability and operations in a wide range of operating conditions. Some embedded systems support real-time operations and can demonstrate high levels of reliability. Many have failsafe mechanisms built to handle graceful shutdown of the device in exception conditions. The available memory, processing power, and network connectivity of these devices are limited due to the nature of their specific-purpose design and intended application. Industry practice is to carefully design the softwaremore » for the available hardware capability to suit desired deployment needs. Volttron is an open source agent development and deployment platform designed to enable researchers to interact with devices and appliances without having to write drivers themselves. Hosting Volttron on small footprint embeddable devices enables its demonstration for embedded use. This report details the steps required and the experience in setting up and running Volttron applications on three small footprint devices: the Intel Next Unit of Computing (NUC), the Raspberry Pi 2, and the BeagleBone Black. In addition, the report also details preliminary investigation of the execution performance of Volttron on these devices.« less

Dissociable contributions of anterior cingulate cortex and basolateral amygdala on a rodent cost/benefit decision-making task of cognitive effort.

PubMed

Hosking, Jay G; Cocker, Paul J; Winstanley, Catharine A

2014-06-01

Personal success often requires the choice to expend greater effort for larger rewards, and deficits in such effortful decision making accompany a number of illnesses including depression, schizophrenia, and attention-deficit/hyperactivity disorder. Animal models have implicated brain regions such as the basolateral amygdala (BLA) and anterior cingulate cortex (ACC) in physical effort-based choice, but disentangling the unique contributions of these two regions has proven difficult, and effort demands in industrialized society are predominantly cognitive in nature. Here we utilize the rodent cognitive effort task (rCET), a modification of the five-choice serial reaction-time task, wherein animals can choose to expend greater visuospatial attention to obtain larger sucrose rewards. Temporary inactivation (via baclofen-muscimol) of BLA and ACC showed dissociable effects: BLA inactivation caused hard-working rats to 'slack off' and 'slacker' rats to work harder, whereas ACC inactivation caused all animals to reduce willingness to expend mental effort. Furthermore, BLA inactivation increased the time needed to make choices, whereas ACC inactivation increased motor impulsivity. These data illuminate unique contributions of BLA and ACC to effort-based decision making, and imply overlapping yet distinct circuitry for cognitive vs physical effort. Our understanding of effortful decision making may therefore require expanding our models beyond purely physical costs.

Neural substrates of the impaired effort expenditure decision making in schizophrenia.

PubMed

Huang, Jia; Yang, Xin-Hua; Lan, Yong; Zhu, Cui-Ying; Liu, Xiao-Qun; Wang, Ye-Fei; Cheung, Eric F C; Xie, Guang-Rong; Chan, Raymond C K

2016-09-01

Unwillingness to expend more effort to pursue high value rewards has been associated with motivational anhedonia in schizophrenia (SCZ) and abnormal dopamine activity in the nucleus accumbens (NAcc). The authors hypothesized that dysfunction of the NAcc and the associated forebrain regions are involved in the impaired effort expenditure decision-making of SCZ. A 2 (reward magnitude: low vs. high) × 3 (probability: 20% vs. 50% vs. 80%) event-related fMRI design in the effort-expenditure for reward task (EEfRT) was used to examine the neural response of 23 SCZ patients and 23 demographically matched control participants when the participants made effort expenditure decisions to pursue uncertain rewards. SCZ patients were significantly less likely to expend high level of effort in the medium (50%) and high (80%) probability conditions than healthy controls. The neural response in the NAcc, the posterior cingulate gyrus and the left medial frontal gyrus in SCZ patients were weaker than healthy controls and did not linearly increase with an increase in reward magnitude and probability. Moreover, NAcc activity was positively correlated with the willingness to expend high-level effort and concrete consummatory pleasure experience. NAcc and posterior cingulate dysfunctions in SCZ patients may be involved in their impaired effort expenditure decision-making. (PsycINFO Database Record (c) 2016 APA, all rights reserved).

Technical Challenges and Lessons from the Migration of the GLOBE Data and Information System to Utilize Cloud Computing Service

NASA Technical Reports Server (NTRS)

Moses, John F.; Memarsadeghi, Nargess; Overoye, David; Littlefield, Brain

2017-01-01

The Global Learning and Observation to Benefit the Environment (GLOBE) Data and Information System supports an international science and education program with capabilities to accept local environment observations, archive, display and visualize them along with global satellite observations. Since its inception twenty years ago, the Web and database system has been upgraded periodically to accommodate the changes in technology and the steady growth of GLOBEs education community and collection of observations. Recently, near the end-of-life of the system hardware, new commercial computer platform options were explored and a decision made to utilize Cloud services. Now the GLOBE DIS has been fully deployed and maintained using Amazon Cloud services for over two years now. This paper reviews the early risks, actual challenges, and some unexpected findings as a result of the GLOBE DIS migration. We describe the plans, cost drivers and estimates, highlight adjustments that were made and suggest improvements. We present the trade studies for provisioning, for load balancing, networks, processing, storage, as well as production, staging and backup systems. We outline the migration teams skills and required level of effort for transition, and resulting changes in the overall maintenance and operations activities. Examples include incremental adjustments to processing capacity and frequency of backups, and efforts previously expended on hardware maintenance that were refocused onto application-specific enhancements.

Technical Challenges and Lessons from the Migration of the GLOBE Data and Information System to Utilize Cloud Computing Service

NASA Technical Reports Server (NTRS)

Moses, John F.; Memarsadeghi, Nargess; Overoye, David; Littlefield, Bryan

2016-01-01

The Global Learning and Observation to Benefit the Environment (GLOBE) Data and Information System supports an international science and education program with capabilities to accept local environment observations, archive, display and visualize them along with global satellite observations. Since its inception twenty years ago, the Web and database system has been upgraded periodically to accommodate the changes in technology and the steady growth of GLOBEs education community and collection of observations. Recently, near the end-of-life of the system hardware, new commercial computer platform options were explored and a decision made to utilize Cloud services. Now the GLOBE DIS has been fully deployed and maintained using Amazon Cloud services for over two years now. This paper reviews the early risks, actual challenges, and some unexpected findings as a result of the GLOBE DIS migration. We describe the plans, cost drivers and estimates, highlight adjustments that were made and suggest improvements. We present the trade studies for provisioning, for load balancing, networks, processing, storage, as well as production, staging and backup systems. We outline the migration teams skills and required level of effort for transition, and resulting changes in the overall maintenance and operations activities. Examples include incremental adjustments to processing capacity and frequency of backups, and efforts previously expended on hardware maintenance that were refocused onto application-specific enhancements.

What Are Punishment and Reputation for?

PubMed Central

Krasnow, Max M.; Cosmides, Leda; Pedersen, Eric J.; Tooby, John

2012-01-01

Why did punishment and the use of reputation evolve in humans? According to one family of theories, they evolved to support the maintenance of cooperative group norms; according to another, they evolved to enhance personal gains from cooperation. Current behavioral data are consistent with both hypotheses (and both selection pressures could have shaped human cooperative psychology). However, these hypotheses lead to sharply divergent behavioral predictions in circumstances that have not yet been tested. Here we report results testing these rival predictions. In every test where social exchange theory and group norm maintenance theory made different predictions, subject behavior violated the predictions of group norm maintenance theory and matched those of social exchange theory. Subjects do not direct punishment toward those with reputations for norm violation per se; instead, they use reputation self-beneficially, as a cue to lower the risk that they personally will experience losses from defection. More tellingly, subjects direct their cooperative efforts preferentially towards defectors they have punished and away from those they haven’t punished; they avoid expending punitive effort on reforming defectors who only pose a risk to others. These results are not consistent with the hypothesis that the psychology of punishment evolved to uphold group norms. The circumstances in which punishment is deployed and withheld–its circuit logic–support the hypothesis that it is generated by psychological mechanisms that evolved to benefit the punisher, by allowing him to bargain for better treatment. PMID:23049833

What are punishment and reputation for?

PubMed

Krasnow, Max M; Cosmides, Leda; Pedersen, Eric J; Tooby, John

2012-01-01

Why did punishment and the use of reputation evolve in humans? According to one family of theories, they evolved to support the maintenance of cooperative group norms; according to another, they evolved to enhance personal gains from cooperation. Current behavioral data are consistent with both hypotheses (and both selection pressures could have shaped human cooperative psychology). However, these hypotheses lead to sharply divergent behavioral predictions in circumstances that have not yet been tested. Here we report results testing these rival predictions. In every test where social exchange theory and group norm maintenance theory made different predictions, subject behavior violated the predictions of group norm maintenance theory and matched those of social exchange theory. Subjects do not direct punishment toward those with reputations for norm violation per se; instead, they use reputation self-beneficially, as a cue to lower the risk that they personally will experience losses from defection. More tellingly, subjects direct their cooperative efforts preferentially towards defectors they have punished and away from those they haven't punished; they avoid expending punitive effort on reforming defectors who only pose a risk to others. These results are not consistent with the hypothesis that the psychology of punishment evolved to uphold group norms. The circumstances in which punishment is deployed and withheld-its circuit logic-support the hypothesis that it is generated by psychological mechanisms that evolved to benefit the punisher, by allowing him to bargain for better treatment.

Patient credentialing as a population health management strategy: a diabetes case study.

PubMed

Watson, Lindsay L; Bluml, Benjamin M; Skoufalos, Alexandria

2015-06-01

When given the opportunity to become actively involved in the decision-making process, patients can positively impact their health outcomes. Understanding how to empower patients to become informed consumers of health care services is an important strategy for addressing disparities and variability in care. Patient credentialing identifies people who have a certain diagnosis and have achieved certain levels of competency in understanding and managing their disease. Patient credentialing was developed to meet 3 core purposes: (1) enhance patient engagement by increasing personal accountability for health outcomes, (2) create a mass customization strategy for providers to deliver high-quality, patient-centered collaborative care, and (3) provide payers with a foundation for properly aligning health benefit incentives. The Patient Self-Management Credential for Diabetes, a first-of-its-kind, psychometrically validated tool, has been deployed within 3 practice-based research initiatives as a component of innovative diabetes care. Results from these projects show improved clinical outcomes, reduced health care costs, and a relationship between credential achievement levels and clinical markers of diabetes. Implementing patient credentialing as part of collaborative care delivered within various settings across the health care system may be an effective way to reduce disparities, improve access to care and appropriate treatments, incentivize patient engagement in managing their health, and expend time and resources in a customized way to meet individual needs.

Cassini orbiter is moved to PHSF after arriving at SLF

NASA Technical Reports Server (NTRS)

1997-01-01

Workers prepare to move the shipping container with the Cassini orbiter inside the Payload Hazardous Servicing Facility (PHSF) for prelaunch processing, testing and integration. The orbiter arrived at KSC's Shuttle Landing Facility in a U.S. Air Force C-17 air cargo plane from Edwards Air Force Base, California. The orbiter and the Huygens probe already being processed at KSC are the two primary components of the Cassini spacecraft, which will be launched on a Titan IVB/Centaur expendable launch vehicle from Cape Canaveral Air Station. Cassini will explore Saturn, its rings and moons for four years. The Huygens probe, designed and developed for the European Space Agency (ESA), will be deployed from the orbiter to study the clouds, atmosphere and surface of Saturn's largest moon, Titan. The orbiter was designed and assembled at NASA's Jet Propulsion Laboratory in California. Following postflight inspections, integration of the 12 science instruments not already installed on the orbiter will be completed. Then, the parabolic high-gain antenna and the propulsion module will be mated to the orbiter, followed by the Huygens probe, which will complete spacecraft integration. The Cassini mission is targeted for an Oct. 6 launch to begin its 6.7-year journey to the Saturnian system. Arrival at the planet is expected to occur around July 1, 2004.

Technical Challenges and Lessons from the Migration of the GLOBE Data and Information System to Utilize Cloud Computing Service

NASA Astrophysics Data System (ADS)

Moses, J. F.; Memarsadeghi, N.; Overoye, D.; Littlefield, B.

2016-12-01

The Global Learning and Observation to Benefit the Environment (GLOBE) Data and Information System supports an international science and education program with capabilities to accept local environment observations, archive, display and visualize them along with global satellite observations. Since its inception twenty years ago, the Web and database system has been upgraded periodically to accommodate the changes in technology and the steady growth of GLOBE's education community and collection of observations. Recently, near the end-of-life of the system hardware, new commercial computer platform options were explored and a decision made to utilize Cloud services. Now the GLOBE DIS has been fully deployed and maintained using Amazon Cloud services for over two years now. This paper reviews the early risks, actual challenges, and some unexpected findings as a result of the GLOBE DIS migration. We describe the plans, cost drivers and estimates, highlight adjustments that were made and suggest improvements. We present the trade studies for provisioning, for load balancing, networks, processing , storage, as well as production, staging and backup systems. We outline the migration team's skills and required level of effort for transition, and resulting changes in the overall maintenance and operations activities. Examples include incremental adjustments to processing capacity and frequency of backups, and efforts previously expended on hardware maintenance that were refocused onto application-specific enhancements.

Differential Brain Activation to Angry Faces by Elite Warfighters: Neural Processing Evidence for Enhanced Threat Detection

PubMed Central

Paulus, Martin P.; Simmons, Alan N.; Fitzpatrick, Summer N.; Potterat, Eric G.; Van Orden, Karl F.; Bauman, James; Swain, Judith L.

2010-01-01

Background Little is known about the neural basis of elite performers and their optimal performance in extreme environments. The purpose of this study was to examine brain processing differences between elite warfighters and comparison subjects in brain structures that are important for emotion processing and interoception. Methodology/Principal Findings Navy Sea, Air, and Land Forces (SEALs) while off duty (n = 11) were compared with n = 23 healthy male volunteers while performing a simple emotion face-processing task during functional magnetic resonance imaging. Irrespective of the target emotion, elite warfighters relative to comparison subjects showed relatively greater right-sided insula, but attenuated left-sided insula, activation. Navy SEALs showed selectively greater activation to angry target faces relative to fearful or happy target faces bilaterally in the insula. This was not accounted for by contrasting positive versus negative emotions. Finally, these individuals also showed slower response latencies to fearful and happy target faces than did comparison subjects. Conclusions/Significance These findings support the hypothesis that elite warfighters deploy greater processing resources toward potential threat-related facial expressions and reduced processing resources to non-threat-related facial expressions. Moreover, rather than expending more effort in general, elite warfighters show more focused neural and performance tuning. In other words, greater neural processing resources are directed toward threat stimuli and processing resources are conserved when facing a nonthreat stimulus situation. PMID:20418943

Remote patient management: technology-enabled innovation and evolving business models for chronic disease care.

PubMed

Coye, Molly Joel; Haselkorn, Ateret; DeMello, Steven

2009-01-01

Remote patient management (RPM) is a transformative technology that improves chronic care management while reducing net spending for chronic disease. Broadly deployed within the Veterans Health Administration and in many small trials elsewhere, RPM has been shown to support patient self-management, shift responsibilities to non-clinical providers, and reduce the use of emergency department and hospital services. Because transformative technologies offer major opportunities to advance national goals of improved quality and efficiency in health care, it is important to understand their evolution, the experiences of early adopters, and the business models that may support their deployment.

Two-stage optics - High-acuity performance from low-acuity optical systems

NASA Technical Reports Server (NTRS)

Meinel, Aden B.; Meinel, Marjorie P.

1992-01-01

The concept of two-stage optics, developed under a program to enhance the performance, lower the cost, and increase the reliability of the 20-m Large Deployable Telescope, is examined. The concept permits the large primary mirror to remain as deployed or as space-assembled, with phasing and subsequent control of the system done by a small fully assembled optical active element placed at an exit pupil. The technique is being applied to correction of the fabrication/testing error in the Hubble Space Telescope primary mirror. The advantages offered by this concept for very large space telescopes are discussed.

2014 Summer Series - Ethiraj Venkatapathy - Mary Poppins Approach to Human Mars Mission Entry, Descent and Landing

NASA Image and Video Library

2014-06-17

NASA is investing in a number of technologies to extend Entry, Descent and Landing (EDL) capabilities to enable Human Missions to Mars. These technologies will also enable robotic Science missions. Human missions will require landing payloads of 10?s of metric tons, not possible with today's technology. Decelerating from entry speeds around 15,000 miles per hour to landing in a matter of minutes will require very large drag or deceleration. The one way to achieve required deceleration is to deploy a large surface that can be stowed during launch and deployed prior to entry. This talk will highlight a simple concept similar to an umbrella. Though the concept is simple, the size required for human Mars missions and the heating encountered during entry are significant challenges. The mechanically deployable system can also enable robotic science missions to Venus and is also equally applicable for bringing back cube-satellites and other small payloads. The scalable concept called Adaptive Deployable Entry and Placement Technology (ADEPT) is under development and is the focus of this talk.

Evaluation of Methods for In-Situ Calibration of Field-Deployable Microphone Phased Arrays

NASA Technical Reports Server (NTRS)

Humphreys, William M.; Lockard, David P.; Khorrami, Mehdi R.; Culliton, William G.; McSwain, Robert G.

2017-01-01

Current field-deployable microphone phased arrays for aeroacoustic flight testing require the placement of hundreds of individual sensors over a large area. Depending on the duration of the test campaign, the microphones may be required to stay deployed at the testing site for weeks or even months. This presents a challenge in regards to tracking the response (i.e., sensitivity) of the individual sensors as a function of time in order to evaluate the health of the array. To address this challenge, two different methods for in-situ tracking of microphone responses are described. The first relies on the use of an aerial sound source attached as a payload on a hovering small Unmanned Aerial System (sUAS) vehicle. The second relies on the use of individually excited ground-based sound sources strategically placed throughout the array pattern. Testing of the two methods was performed in microphone array deployments conducted at Fort A.P. Hill in 2015 and at Edwards Air Force Base in 2016. The results indicate that the drift in individual sensor responses can be tracked reasonably well using both methods. Thus, in-situ response tracking methods are useful as a diagnostic tool for monitoring the health of a phased array during long duration deployments.

Calibration procedure for Slocum glider deployed optical instruments.

PubMed

Cetinić, Ivona; Toro-Farmer, Gerardo; Ragan, Matthew; Oberg, Carl; Jones, Burton H

2009-08-31

Recent developments in the field of the autonomous underwater vehicles allow the wide usage of these platforms as part of scientific experiments, monitoring campaigns and more. The vehicles are often equipped with sensors measuring temperature, conductivity, chlorophyll a fluorescence (Chl a), colored dissolved organic matter (CDOM) fluorescence, phycoerithrin (PE) fluorescence and spectral volume scattering function at 117 degrees, providing users with high resolution, real time data. However, calibration of these instruments can be problematic. Most in situ calibrations are performed by deploying complementary instrument packages or water samplers in the proximity of the glider. Laboratory calibrations of the mounted sensors are difficult due to the placement of the instruments within the body of the vehicle. For the laboratory calibrations of the Slocum glider instruments we developed a small calibration chamber where we can perform precise calibrations of the optical instruments aboard our glider, as well as sensors from other deployment platforms. These procedures enable us to obtain pre- and post-deployment calibrations for optical fluorescence instruments, which may differ due to the biofouling and other physical damage that can occur during long-term glider deployments. We found that biofouling caused significant changes in the calibration scaling factors of fluorescent sensors, suggesting the need for consistent and repetitive calibrations for gliders as proposed in this paper.

Water-Energy Correlations: Analysis of Water Technologies, Processes and Systems in Rural and Urban India

NASA Astrophysics Data System (ADS)

Murumkar, A. R.; Gupta, S.; Kaurwar, A.; Satankar, R. K.; Mounish, N. K.; Pitta, D. S.; Virat, J.; Kumar, G.; Hatte, S.; Tripathi, R. S.; Shedekar, V.; George, K. J.; Plappally, A. K.

2015-12-01

In India, the present value of water, both potable and not potable, bears no relation to the energy of water production. However, electrical energy spent on ground water extraction alone is equivalent to the nation's hydroelectric capacity of 40.1 GWh. Likewise, desalinating 1m3 water of the Bay of Bengal would save three times the energy for potable ground water extraction along the coast of the Bay. It is estimated that every second woman in rural India expends 0.98 kWhe/m3/d for bringing water for household needs. Yet, the water-energy nexus remains to be a topic which is gravely ignored. This is largely caused by factors such as lack of awareness, defective public policies, and intrusive cultural practices. Furthermore, there are instances of unceasing dereliction towards water management and maintenance of the sparsely distributed water and waste water treatment plants across the country. This pollutes the local water across India apart from other geogenic impurities. Additionally, product aesthetics and deceptive advertisements take advantage of the abulia generated by users' ignorance of technical specifications of water technologies and processes in mismanagement of water use. Accordingly, urban residents are tempted to expend on energy intensive water technologies at end use. This worsens the water-energy equation at urban households. Cooking procedures play a significant role in determining the energy expended on water at households. The paper also evaluates total energy expense involved in cultivating some major Kharif and Rabi crops. Manual and traditional agricultural practices are more prominent than mechanized and novel agricultural techniques. The specific energy consumption estimate for different water technologies will help optimize energy expended on water in its life cycles. The implication of the present study of water-energy correlation will help plan and extend water management infrastructure at different locations across India.

Physical activity and risk of ischemic stroke in the Northern Manhattan Study

PubMed Central

Willey, J Z.; Moon, Y P.; Paik, M C.; Boden-Albala, B; Sacco, R L.; Elkind, M S.V.

2009-01-01

Background: It is controversial whether physical activity is protective against first stroke among older persons. We sought to examine whether physical activity, as measured by intensity of exercise and energy expended, is protective against ischemic stroke. Methods: The Northern Manhattan Study is a prospective cohort study in older, urban-dwelling, multiethnic, stroke-free individuals. Baseline measures of leisure-time physical activity were collected via in-person questionnaires. Cox proportional hazards models were constructed to examine whether energy expended and intensity of physical activity were associated with the risk of incident ischemic stroke. Results: Physical inactivity was present in 40.5% of the cohort. Over a median follow-up of 9.1 years, there were 238 incident ischemic strokes. Moderate- to heavy-intensity physical activity was associated with a lower risk of ischemic stroke (adjusted hazard ratio [HR] 0.65, 95% confidence interval [0.44–0.98]). Engaging in any physical activity vs none (adjusted HR 1.16, 95% CI 0.88–1.51) and energy expended in kcal/wk (adjusted HR per 500-unit increase 1.01, 95% CI 0.99–1.03) were not associated with ischemic stroke risk. There was an interaction of sex with intensity of physical activity (p = 0.04), such that moderate to heavy activity was protective against ischemic stroke in men (adjusted HR 0.37, 95% CI 0.18–0.78), but not in women (adjusted HR 0.92, 95% CI 0.57–1.50). Conclusions: Moderate- to heavy-intensity physical activity, but not energy expended, is protective against risk of ischemic stroke independent of other stroke risk factors in men in our cohort. Engaging in moderate to heavy physical activities may be an important component of primary prevention strategies aimed at reducing stroke risk. GLOSSARY CI = confidence interval; HR = hazard ratio; MET = metabolic equivalents. PMID:19933979

Workers take off the protective covering on Cassini's propulsion module in SAEF-2

NASA Technical Reports Server (NTRS)

1997-01-01

Workers take off the protective covering on the propulsion module for the Cassini spacecraft after uncrating the module at KSC's Spacecraft Assembly and Encapsulation Facility-2 (SAEF-2). The extended journey of 6.7 years to Saturn and the 4-year mission for Cassini once it gets there will require the spacecraft to carry a large amount of propellant for inflight trajectory- correction maneuvers and attitude control, particularly during the science observations. The propulsion module has redundant 445-newton main engines that burn nitrogen tetraoxide and monomethyl-hydrazine for main propulsion and 16 smaller 1-newton engines that burn hydrazine to control attitude and to correct small deviations from the spacecraft flight path. Cassini will be launched on a Titan IVB/Centaur expendable launch vehicle. Liftoff is targeted for October 6 from Launch Complex 40, Cape Canaveral Air Station.

A conceptual design for the attitude control and determination system for the Magnetosphere Imager spacecraft

NASA Technical Reports Server (NTRS)

Polites, M. E.; Carrington, C. K.

1995-01-01

This paper presents a conceptual design for the attitude control and determination (ACAD) system for the Magnetosphere Imager (Ml) spacecraft. The MI is a small spin-stabilized spacecraft that has been proposed for launch on a Taurus-S expendable launch vehicle into a highly-ellipdcal polar Earth orbit. Presently, launch is projected for 1999. The paper describes the MI mission and ACAD requirements and then proposes an ACAD system for meeting these requirements. The proposed design is low-power, low-mass, very simple conceptually, highly passive, and consistent with the overall MI design philosophy, which is faster-better-cheaper. Still, the MI ACAD system is extremely robust and can handle a number of unexpected, adverse situations on orbit without impacting the mission as a whole. Simulation results are presented that support the soundness of the design approach.

Materials samples face rigors of space.

PubMed

Flinn, Edward D

2002-07-01

The Materials International Space Station Experiment (MISSE) is described. This project is designed to conduct long duration materials tests on samples attached to the ISS. A batch of 750 material samples were delivered on STS-105 and attached to the ISS airlock. They will be exposed to the space environment for 18 months and are slated to return on STS-114. A second batch of 750 samples is being prepared. The experiment containers were used originally for the Mir Environmental Effects Payload, which tested a variety of substances, including some slated for use on the ISS. Researchers are particularly interested in the effects of atomic oxygen on the samples. Some samples are being tested to determine their use in radiation protection. As part of the MISSE project, ultrathin tether materials are being tested for use on the Propulsive Small Expendable Depoloyer System (ProSEDS), which will use a tether system to change a satellite's orbital altitude.

Iridium-coated rhenium thrusters by CVD

NASA Technical Reports Server (NTRS)

Harding, J. T.; Kazaroff, J. M.; Appel, M. A.

1989-01-01

Operation of spacecraft thrusters at increased temperature reduces propellant requirements. Inasmuch as propellant comprises the bulk of a satellite's mass, even a small percentage reduction makes possible a significant enhancement of the mission in terms of increased payload. Because of its excellent high temperature strength, rhenium is often the structural material of choice. It can be fabricated into free-standing shapes by chemical vapor deposition (CVD) onto an expendable mandrel. What rhenium lacks is oxidation resistance, but this can be provided by a coating of iridium, also by CVD. This paper describes the process used by Ultramet to fabricate 22-N (5-lbf) and, more recently, 445-N (100-lbf) Ir/Re thrusters; characterizes the CVD-deposited materials; and summarizes the materials effects of firing these thrusters. Optimal propellant mixture ratios can be employed because the materials withstand an oxidizing environment up to the melting temperature of iridium, 2400 C (4350 F).

Iridium-coated rhenium thrusters by CVD

NASA Technical Reports Server (NTRS)

Harding, John T.; Kazaroff, John M.; Appel, Marshall A.

1988-01-01

Operation of spacecraft thrusters at increased temperature reduces propellant requirements. Inasmuch as propellant comprises the bulk of a satellite's mass, even a small percentage reduction makes possible a significant enhancement of the mission in terms of increased payload. Because of its excellent high temperature strength, rhenium is often the structural material of choice. It can be fabricated into free-standing shapes by chemical vapor deposition (CVD) onto an expendable mandrel. What rhenium lacks is oxidation resistance, but this can be provided by a coating of iridium, also by CVD. This paper describes the process used by Ultramet to fabricate 22-N (5-lbf) and, more recently, 445-N (100-lbf) Ir/Re thrusters; characterizes the CVD-deposited materials; and summarizes the materials effects of firing these thrusters. Optimal propellant mixture ratios can be employed because the materials withstand an oxidizing environment up to the meltimg temperature of iridium, 2400 C (4350 F).

ED15-0249-032

NASA Image and Video Library

2015-08-13

NASA’s Global Hawk aircraft deploys a dropsonde during a test flight over the Dryden Aeronautical Test Range in August 2015. The small, tube-shaped sensor will transmit data on temperature, humidity, and wind speed, which will be used to help improve weather model forecasts

NETL Crosscutting Research Video Series – LIBSense™ Sensor (Short Version)

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

None

NETL’s LIBSense™ Sensor is a small optical sensing device that can be used to detect elements in downhole applications. Since the sensor is an all-optical device and uses no electronics, it can be deployed into extreme environments.

Sandia National Laboratories: Working with Sandia: Small Business

Science.gov Websites

Programs Nuclear Weapons About Nuclear Weapons Safety & Security Weapons Science & Technology Robotics R&D 100 Awards Laboratory Directed Research & Development Technology Deployment Centers Audit Sandia's Economic Impact Licensing & Technology Transfer Browse Technology Portfolios

Engineering Model Propellant Feed System Development for an Iodine Hall Thruster Demonstration Mission

NASA Technical Reports Server (NTRS)

Polzin, Kurt A.

2016-01-01

CUBESATS are relatively new spacecraft platforms that are typically deployed from a launch vehicle as a secondary payload, providing low-cost access to space for a wide range of end-users. These satellites are comprised of building blocks having dimensions of 10x10x10 cu cm and a mass of 1.33 kg (a 1-U size). While providing low-cost access to space, a major operational limitation is the lack of a propulsion system that can fit within a CubeSat and is capable of executing high (Delta)v maneuvers. This makes it difficult to use CubeSats on missions requiring certain types of maneuvers (i.e. formation flying, spacecraft rendezvous). Recently, work has been performed investigating the use of iodine as a propellant for Hall-effect thrusters (HETs) 2 that could subsequently be used to provide a high specific impulse path to CubeSat propulsion. 3, 4 Iodine stores as a dense solid at very low pressures, making it acceptable as a propellant on a secondary payload. It has exceptionally high ?Isp (density times specific impulse), making it an enabling technology for small satellite near-term applications and providing the potential for systems-level advantages over mid-term high power electric propulsion options. Iodine flow can also be thermally regulated, subliming at relatively low temperature (< 100 C) to yield I2 vapor at or below 50 torr. At low power, the measured performance of an iodine-fed HET is very similar to that of a state-of-the-art xenon-fed thruster. Just as importantly, the current-voltage discharge characteristics of low power iodine-fed and xenon-fed thrusters are remarkably similar, potentially reducing development and qualifications costs by making it possible to use an already-qualified xenon-HET PPU in an iodine-fed system. Finally, a cold surface can be installed in a vacuum test chamber on which expended iodine propellant can deposit. In addition, the temperature doesn't have to be extremely cold to maintain a low vapor pressure in the vacuum chamber (it is under 10(exp -6) torr at -75 C), making it possible to 'cryopump' the propellant with lower-cost recirculating refrigerant-based systems as opposed to using liquid nitrogen or low temperature gaseous helium cryopanels. In the present paper, we describe the design and testing of the engineering model propellant feed system for iSAT (see Fig. 1). The feed system is based around an iodine propellant reservoir and two proportional control valves (PFCVs) that meter the iodine flow to the cathode and anode. The flow is split upstream of the PFCVs to both components can be fed from a common reservoir. Testing of the reservoir is reported to demonstrate that the design is capable of delivering the required propellant flow rates to operate the thruster. The tubing and reservoir are fabricated from hastelloy to resist corrosion by the heated gaseous iodine propellant. The reservoir, tubing, and PFCVs are heated to ensure the sublimed propellant will not re-deposit within the feed system. Heating is accomplished through a number of individual zones to control the overall power expended on heating the system and insulation is employed to minimize the amount of power used to heat the system prior to thruster operation.

Evaluation of Trap Designs and Deployment Strategies for Capturing Halyomorpha halys (Hemiptera: Pentatomidae)

PubMed Central

Morrison, William R.; Cullum, John P.; Leskey, Tracy C.

2015-01-01

Halyomorpha halys (Stål) is an invasive pest that attacks numerous crops. For growers to make informed management decisions against H. halys, an effective monitoring tool must be in place. We evaluated various trap designs baited with the two-component aggregation pheromone of H. halys and synergist and deployed in commercial apple orchards. We compared our current experimental standard trap, a black plywood pyramid trap 1.22 m in height deployed between border row apple trees with other trap designs for two growing seasons. These included a black lightweight coroplast pyramid trap of similar dimension, a smaller (29 cm) pyramid trap also ground deployed, a smaller limb-attached pyramid trap, a smaller pyramid trap hanging from a horizontal branch, and a semipyramid design known as the Rescue trap. We found that the coroplast pyramid was the most sensitive, capturing more adults than all other trap designs including our experimental standard. Smaller pyramid traps performed equally in adult captures to our experimental standard, though nymphal captures were statistically lower for the hanging traps. Experimental standard plywood and coroplast pyramid trap correlations were strong, suggesting that standard plywood pyramid traps could be replaced with lighter, cheaper coroplast pyramid traps. Strong correlations with small ground- and limb-deployed pyramid traps also suggest that these designs offer promise as well. Growers may be able to adopt alternative trap designs that are cheaper, lighter, and easier to deploy to monitor H. halys in orchards without a significant loss in sensitivity. PMID:26470309

Attitude stability of a spinning spacecraft during appendage deployment/retraction

NASA Technical Reports Server (NTRS)

Fitz-Coy, Norman; Fullerton, Wayne

1994-01-01

The work presented is motivated by the need for a national satellite rescue policy, not the ad hoc policy now in place. In studying different approaches for a national policy, the issue of capture and stabilization of a tumbling spacecraft must be addressed. For a rescue mission involving a tumbling spacecraft, it may be advantageous to have a rescue vehicle which is compact and 'rigid' during the rendezvous/capture phase. After capture, passive stabilization techniques could be utilized as an efficient means of detumbling the resulting system (i.e., both the rescue vehicle and captures spacecraft). Since the rescue vehicle is initially compact and 'rigid,' significant passive stabilization through energy dissipation can only be achieved through the deployment of flexible appendages. Once stabilization is accomplished, retraction of the appendages before maneuvering the system to its final destination may also prove advantageous. It is therefore of paramount interest that we study the effect of appendage deployment/retraction on the attitude stability of a spacecraft. Particular interest should be paid to appendage retraction, since if this process is destabilizing, passive stabilization as proposed may not be useful. Over the past three decades, it has been an 'on-again-off-again affair' with the problem of spacecraft appendage deployment. In most instances, these studies have been numerical simulations of specific spacecraft configurations for which there were specific concerns. The primary focus of these studies was the behavior of the appendage during deployment; the effects of appendage retraction was considered only in one of these studies. What is missing in the literature is a thorough study of the effects of appendage deployment/retraction on the attitude stability of a spacecraft. This paper presents a rigorous analysis of the stability of a spinning spacecraft during the deployment or the retraction of an appendage. The analysis is simplified such that meaningful insights into the problem can be inferred; it is not overly simplified such that critical dynamical behavior is neglected. The system is analyzed assuming that the spacecraft hub is rigid. The appendage deployment mechanism is modeled as a point mass on a massless rod whose length undergoes prescribed changes. Simplified flexibility effects of the appendage are included. The system is examined for stability by linearizing the equations in terms of small deviations from steady, noninterfering coning motion. Routh's procedure for analyzing small deviations from steady motion in dynamical systems is utilized in the analysis. The system of equations are nondimensionalized to facilitate parametric studies. The results are presented in terms of a reduced number of nondimensional parameters so that some general conclusions may be drawn. Verification of the linear analysis is presented through numerical simulations of the complete nonlinear, nonautonomous, coupled equations.

Wind Power Today and Tomorrow

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

Not Available

Wind Power Today and Tomorrow is an annual publication that provides an overview of the wind research conducted under the U.S. Department of Energy's Wind and Hydropower Technologies Program. The purpose of Wind Power Today and Tomorrow is to show how DOE supports wind turbine research and deployment in hopes of furthering the advancement of wind technologies that produce clean, low-cost, reliable energy. Content objectives include: educate readers about the advantages and potential for widespread deployment of wind energy; explain the program's objectives and goals; describe the program's accomplishments in research and application; examine the barriers to widespread deployment; describemore » the benefits of continued research and development; facilitate technology transfer; and attract cooperative wind energy projects with industry. This 2003 edition of the program overview also includes discussions about wind industry growth in 2003, how DOE is taking advantage of low wind speed region s through advancing technology, and distributed applications for small wind turbines.« less

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

Scribner, R.A.

Sea-launched cruise missiles (SLCMs) present some particularly striking problems for both national security and arms control. These small, dual-purpose, difficult to detect weapons present some formidable challenges for verification in any scheme that attempts to limit rather than eliminate them. Conventionally armed SLCMs offer to the navies of both superpowers important offensive and defensive capabilities. Nuclear armed, long-range, land-attack SLCMs, on the other hand, seem to pose destabilizing threats and otherwise have questionable value, despite strong US support for extensive deployment of them. If these weapons are not constrained, their deployment could circumvent gains which might be made in agreementsmore » directly reducing of strategic nuclear weapons. This paper reviews the technology and planned deployments of SLCMs, the verification schemes which have been discussed and are being investigated to try to deal with the problem, and examines the proposed need for and possible uses of SLCMs. It presents an overview of the problem technically, militarily, and politically.« less

Advanced Opto-Electronics (LIDAR and Microsensor Development)

NASA Technical Reports Server (NTRS)

Vanderbilt, Vern C. (Technical Monitor); Spangler, Lee H.

2005-01-01

Our overall intent in this aspect of the project were to establish a collaborative effort between several departments at Montana State University for developing advanced optoelectronic technology for advancing the state-of-the-art in optical remote sensing of the environment. Our particular focus was on development of small systems that can eventually be used in a wide variety of applications that might include ground-, air-, and space deployments, possibly in sensor networks. Specific objectives were to: 1) Build a field-deployable direct-detection lidar system for use in measurements of clouds, aerosols, fish, and vegetation; 2) Develop a breadboard prototype water vapor differential absorption lidar (DIAL) system based on highly stable, tunable diode laser technology developed previously at MSU. We accomplished both primary objectives of this project, in developing a field-deployable direct-detection lidar and a breadboard prototype of a water vapor DIAL system. Paper summarizes each of these accomplishments.

The October 1973 NASA mission model analysis and economic assessment

NASA Technical Reports Server (NTRS)

1974-01-01

Results are presented of the 1973 NASA Mission Model Analysis. The purpose was to obtain an economic assessment of using the Shuttle to accommodate the payloads and requirements as identified by the NASA Program Offices and the DoD. The 1973 Payload Model represents a baseline candidate set of future payloads which can be used as a reference base for planning purposes. The cost of implementing these payload programs utilizing the capabilities of the shuttle system is analyzed and compared with the cost of conducting the same payload effort using expendable launch vehicles. There is a net benefit of 14.1 billion dollars as a result of using the shuttle during the 12-year period as compared to using an expendable launch vehicle fleet.

Space Tug systems study. Volume 2: Compendium

NASA Technical Reports Server (NTRS)

1974-01-01

Possible storable propellant configurations and program plans are evaluated for the space tug. Alternatives examined include: use of existing expendable stages modified for use with shuttle, followed by a space tug at a later date; use of a modified growth version of existing expendable stages for greater performance and potential reuse, followed by a space tug at a later date; use of a low development cost, reusable, interim space tug available at shuttle initial operational capability (IOC) that could be evolved to greater system capabilities at a later date; and use a direct developed tug with maximum potential to be available at some specified time after space shuttle IOC. The capability options were narrowed down to three final options for detailed program definition.

Dry ice blasting

NASA Astrophysics Data System (ADS)

Lonergan, Jeffrey M.

1992-04-01

As legal and societal pressures against the use of hazardous waste generating materials has increased, so has the motivation to find safe, effective, and permanent replacements. Dry ice blasting is a technology which uses CO2 pellets as a blasting medium. The use of CO2 for cleaning and stripping operations offers potential for significant environmental, safety, and productivity improvements over grit blasting, plastic media blasting, and chemical solvent cleaning. Because CO2 pellets break up and sublime upon impact, there is no expended media to dispose of. Unlike grit or plastic media blasting which produce large quantities of expended media, the only waste produced by CO2 blasting is the material removed. The quantity of hazardous waste produced, and thus the cost of hazardous waste disposal is significantly reduced.

Virtual Observer Controller (VOC) for Small Unit Infantry Laser Simulation Training

DTIC Science & Technology

2007-04-01

per-seat license when deployed. As a result, ViaVoice was abandoned early in development. Next, the SPHINX engine from Carnegie Mellon University was...examined. Sphinx is Java-based software, providing cross-platform functionality, and it is also free, open-source software. Software developers at...IST had experience using SPHINX , so it was initially selected it to be the VOC speech engine. After implementing a small portion of the VOC grammar

Are Ripples a Sign of Water?

NASA Technical Reports Server (NTRS)

2004-01-01

Scientists are investigating the ripples and textures seen in this 4-panel mosaic image, taken by the microscopic imager on the instrument deployment device or 'robotic arm' of NASA's Mars Exploration Rover Opportunity. The images were taken from 'Panoramic Position 2' on the southeast side of the rim of 'Endurance' Crater. This small set of nearly 150 images was acquired to examine small-scale ripple patterns suggestive of past aqueous processes on Mars.