Managed Entry Agreements for Pharmaceuticals in the Context of Adaptive Pathways in Europe

PubMed Central

Bouvy, Jacoline C.; Sapede, Claudine; Garner, Sarah

2018-01-01

As per the EMA definition, adaptive pathways is a scientific concept for the development of medicines which seeks to facilitate patient access to promising medicines addressing high unmet need through a prospectively planned approach in a sustainable way. This review reports the findings of activities undertaken by the ADAPT-SMART consortium to identify enablers and explore the suitability of managed entry agreements for adaptive pathways products in Europe. We found that during 2006–2016 outcomes-based managed entry agreements were not commonly used for products with a conditional marketing authorization or authorized under exceptional circumstances. The barriers and enablers to develop workable managed entry agreements models for adaptive pathways products were discussed through interviews and a multi-stakeholder workshop with a number of recommendations made in this paper. PMID:29636692

Enabling Venus In-Situ Science - Deployable Entry System Technology, Adaptive Deployable Entry and Placement Technology (ADEPT): A Technology Development Project funded by Game Changing Development Program of the Space Technology Program

NASA Technical Reports Server (NTRS)

Wercinski, Paul F.; Venkatapathy, Ethiraj; Gage, Peter J.; Yount, Bryan C.; Prabhu, Dinesh K.; Smith, Brandon; Arnold, James O.; Makino, alberto; Peterson, Keith Hoppe; Chinnapongse, Ronald I.

2012-01-01

Venus is one of the important planetary destinations for scientific exploration, but: The combination of extreme entry environment coupled with extreme surface conditions have made mission planning and proposal efforts very challenging. We present an alternate, game-changing approach (ADEPT) where a novel entry system architecture enables more benign entry conditions and this allows for greater flexibility and lower risk in mission design

Promoting Parenting to Support Reintegrating Military Families: After Deployment, Adaptive Parenting Tools

PubMed Central

Gewirtz, Abigail H.; Pinna, Keri L. M.; Hanson, Sheila K.; Brockberg, Dustin

2014-01-01

The high operational tempo of the current conflicts and the unprecedented reliance on National Guard and Reserve forces highlights the need for services to promote reintegration efforts for those transitioning back to civilian family life. Despite evidence that parenting has significant influence on children’s functioning, and that parenting may be impaired during stressful family transitions, there is a dearth of empirically-supported psychological interventions tailored for military families reintegrating after deployment. This paper reports on the modification of an empirically-supported parenting intervention for families in which a parent has deployed to war. A theoretical rationale for addressing parenting during reintegration after deployment is discussed. We describe the intervention, After Deployment, Adaptive Parenting Tools (ADAPT), and report early feasibility and acceptability data from a randomized controlled effectiveness trial of ADAPT, a 14-week group-based, web-enhanced parenting training program. Among the first 42 families assigned to the intervention group, participation rates were high, and equal among mothers and fathers. Satisfaction was high across all fourteen sessions. Implications for psychological services to military families dealing with the deployment process are discussed. PMID:24564441

Promoting parenting to support reintegrating military families: after deployment, adaptive parenting tools.

PubMed

Gewirtz, Abigail H; Pinna, Keri L M; Hanson, Sheila K; Brockberg, Dustin

2014-02-01

The high operational tempo of the current conflicts and the unprecedented reliance on National Guard and Reserve forces highlights the need for services to promote reintegration efforts for those transitioning back to civilian family life. Despite evidence that parenting has significant influence on children's functioning, and that parenting may be impaired during stressful family transitions, there is a dearth of empirically supported psychological interventions tailored for military families reintegrating after deployment. This article reports on the modification of an empirically supported parenting intervention for families in which a parent has deployed to war. A theoretical rationale for addressing parenting during reintegration after deployment is discussed. We describe the intervention, After Deployment, Adaptive Parenting Tools (ADAPT), and report early feasibility and acceptability data from a randomized controlled effectiveness trial of ADAPT, a 14-week group-based, Web-enhanced parenting training program. Among the first 42 families assigned to the intervention group, participation rates were high, and equal among mothers and fathers. Satisfaction was high across all 14 sessions. Implications for psychological services to military families dealing with the deployment process are discussed. PsycINFO Database Record (c) 2014 APA, all rights reserved.

Progress in Payload Separation Risk Mitigation for a Deployable Venus Heat Shield

NASA Technical Reports Server (NTRS)

Smith, Brandon P.; Yount, Bryan C.; Venkatapathy, Ethiraj; Stern, Eric C.; Prabhu, Dinesh K.; Litton, Daniel K.

2013-01-01

A deployable decelerator known as the Adaptive Deployable Entry and Placement Technology (ADEPT) offers substantial science and mass savings for the Venus In Situ Explorer (VISE) mission. The lander and science payload must be separated from ADEPT during atmospheric entry. This paper presents a trade study of the separation system concept of operations and provides a conceptual design of the baseline: aft-separation with a subsonic parachute. Viability of the separation system depends on the vehicle's dynamic stability characteristics during deceleration from supersonic to subsonic speeds. A trajectory sensitivity study presented shows that pitch damping and Venusian winds drive stability prior to parachute deployment, while entry spin rate is not a driver of stability below Mach 5. Additionally, progress in free-flight CFD techniques capable of computing aerodynamic damping parameters is presented. Exploratory simulations of ADEPT at a constant speed of Mach number of 0.8 suggest the vehicle may have an oscillation limit cycle near 5 angle-of-attack. The proposed separation system conceptual design is thought to be viable.

Mechanically-Deployed Hypersonic Decelerator and Conformal Ablator Technologies for Mars Missions

NASA Technical Reports Server (NTRS)

Venkatapathy, Ethiraj; Wercinski, Paul F.; Beck, Robin A. S.; Hamm, Kenneth R.; Yount, Bryan C.; Makino, A.; Smith, B.; Gage, P.; Prabhu, D.

2012-01-01

The concept of a mechanically deployable hypersonic decelerator, developed initially for high mass (40 MT) human Mars missions, is currently funded by OCT for technology maturation. The ADEPT (Adaptive, Deployable Entry and Placement Technology) project has broad, game-changing applicability to in situ science missions to Venus, Mars, and the Outer Planets. Combined with maturation of conformal ablator technology (another current OCT investment), the two technologies provide unique low mass mission enabling capabilities otherwise not achievable by current rigid aeroshell or by inflatables. If this abstract is accepted, we will present results that illustrate the mission enabling capabilities of the mechanically deployable architecture for: (1) robotic Mars (Discovery or New Frontiers class) in the near term; (2) alternate approaches to landing MSL-class payloads, without the need for supersonic parachute or lifting entry, in the mid-term; and (3) Heavy mass and human missions to Mars in the long term.

Mechanically-Deployed Hypersonic Decelerator and Conformal Ablator Technologies for Mars Missions

NASA Technical Reports Server (NTRS)

Venkatapathy, E.; Wercinski, P.; Prabhu, D.

2012-01-01

The concept of a mechanically deployable hypersonic decelerator, developed initially for high mass (approximately 40 MT) human Mars missions, is currently funded by OCT for technology maturation. The ADEPT (Adaptive, Deployable Entry and Placement Technology) project has broad, game-changing applicability to in situ science missions to Venus, Mars, and the Outer Planets. Combined with maturation of conformal ablator technology (another current OCT investment), the two technologies provide unique low-mass mission enabling capabilities otherwise not achievable by current rigid aeroshell or by inflatables. If this abstract is accepted, we will present results that illustrate the mission enabling capabilities of the mechanically deployable architecture for: (1) robotic Mars (Discovery or New Frontiers class) in the near term (2) alternate approaches to landing MSL-class payloads, without the need for supersonic parachute or lifting entry, in the mid-term and (3) Heavy mass and human missions to Mars in the long term.

MSL EDL Entry Guidance using the Entry Terminal Point Controller

NASA Technical Reports Server (NTRS)

2006-01-01

The Mars Science Laboratory will be the first Mars mission to attempt a guided entry with the objective of safely delivering the entry vehicle to a survivable parachute deploy state within 10 km of the pre-designated landing site. The Entry Terminal Point Controller guidance algorithm is derived from the final phase Apollo Command Module guidance and, like Apollo, modulates the bank angle to control range based on deviations in range, altitude rate, and drag acceleration from a reference trajectory. For application to Mars landers which must make use of the tenuous Martian atmosphere, it is critical to balance the lift of the vehicle to minimize the range while still ensuring a safe deploy altitude. An overview of the process to generate optimized guidance settings is presented, discussing improvements made over the last four years. Performance tradeoffs between ellipse size and deploy altitude will be presented, along with imposed constraints of entry acceleration and heating. Performance sensitivities to the bank reversal deadbands, heading alignment, attitude initialization error, and atmospheric delivery errors are presented. Guidance settings for contingency operations, such as those appropriate for severe dust storm scenarios, are evaluated.

Guidance and Control Architecture Design and Demonstration for Low Ballistic Coefficient Atmospheric Entry

NASA Technical Reports Server (NTRS)

Swei, Sean

2014-01-01

We propose to develop a robust guidance and control system for the ADEPT (Adaptable Deployable Entry and Placement Technology) entry vehicle. A control-centric model of ADEPT will be developed to quantify the performance of candidate guidance and control architectures for both aerocapture and precision landing missions. The evaluation will be based on recent breakthroughs in constrained controllability/reachability analysis of control systems and constrained-based energy-minimum trajectory optimization for guidance development operating in complex environments.

Hypersonic entry vehicle state estimation using nonlinearity-based adaptive cubature Kalman filters

NASA Astrophysics Data System (ADS)

Sun, Tao; Xin, Ming

2017-05-01

Guidance, navigation, and control of a hypersonic vehicle landing on the Mars rely on precise state feedback information, which is obtained from state estimation. The high uncertainty and nonlinearity of the entry dynamics make the estimation a very challenging problem. In this paper, a new adaptive cubature Kalman filter is proposed for state trajectory estimation of a hypersonic entry vehicle. This new adaptive estimation strategy is based on the measure of nonlinearity of the stochastic system. According to the severity of nonlinearity along the trajectory, the high degree cubature rule or the conventional third degree cubature rule is adaptively used in the cubature Kalman filter. This strategy has the benefit of attaining higher estimation accuracy only when necessary without causing excessive computation load. The simulation results demonstrate that the proposed adaptive filter exhibits better performance than the conventional third-degree cubature Kalman filter while maintaining the same performance as the uniform high degree cubature Kalman filter but with lower computation complexity.

Investigation of Transonic Wake Dynamics for Mechanically Deployable Entry Systems

NASA Technical Reports Server (NTRS)

Stern, Eric; Barnhardt, Michael; Venkatapathy, Ethiraj; Candler, Graham; Prabhu, Dinesh

2012-01-01

A numerical investigation of transonic flow around a mechanically deployable entry system being considered for a robotic mission to Venus has been performed, and preliminary results are reported. The flow around a conceptual representation of the vehicle geometry was simulated at discrete points along a ballistic trajectory using Detached Eddy Simulation (DES). The trajectory points selected span the low supersonic to transonic regimes with freestream Mach numbers from 1:5 to 0:8, and freestream Reynolds numbers (based on diameter) between 2:09 x 10(exp 6) and 2:93 x 10(exp 6). Additionally, the Mach 0:8 case was simulated at angles of attack between 0 and 5 . Static aerodynamic coefficients obtained from the data show qualitative agreement with data from 70deg sphere-cone wind tunnel tests performed for the Viking program. Finally, the effect of choices of models and numerical algorithms is addressed by comparing the DES results to those using a Reynolds Averaged Navier-Stokes (RANS) model, as well as to results using a more dissipative numerical scheme.

Is Intelligent Speed Adaptation ready for deployment?

PubMed

Carsten, Oliver

2012-09-01

There have been 30 years of research on Intelligent Speed Adaptation (ISA), the in-vehicle system that is designed to promote compliance with speed limits. Extensive trials of ISA in real-world driving have shown that ISA can significantly reduce speeding, users have been found to have generally positive attitudes and at least some sections of the public have been shown to be willing to purchase ISA systems. Yet large-scale deployment of a system that could deliver huge accident reductions is still by no means guaranteed. Copyright © 2012. Published by Elsevier Ltd.

Mars entry guidance based on an adaptive reference drag profile

NASA Astrophysics Data System (ADS)

Liang, Zixuan; Duan, Guangfei; Ren, Zhang

2017-08-01

The conventional Mars entry tracks a fixed reference drag profile (FRDP). To improve the landing precision, a novel guidance approach that utilizes an adaptive reference drag profile (ARDP) is presented. The entry flight is divided into two phases. For each phase, a family of drag profiles corresponding to various trajectory lengths is planned. Two update windows are investigated for the reference drag profile. At each window, the ARDP is selected online from the profile database according to the actual range-to-go. The tracking law for the selected drag profile is designed based on the feedback linearization. Guidance approaches using the ARDP and the FRDP are then tested and compared. Simulation results demonstrate that the proposed ARDP approach achieves much higher guidance precision than the conventional FRDP approach.

LOFT. Containment building entry, an adapted use of TAN624, which ...

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

LOFT. Containment building entry, an adapted use of TAN-624, which originated as the mobile test building for the ANP program. Camera facing north. Note four-rail track entered building stack at right of view. Date: March 2004. INEEL negative no. HD-39-4-1 - Idaho National Engineering Laboratory, Test Area North, Scoville, Butte County, ID

Venus In Situ Explorer Mission design using a mechanically deployed aerodynamic decelerator

NASA Astrophysics Data System (ADS)

Smith, B.; Venkatapathy, E.; Wercinski, P.; Yount, B.; Prabhu, D.; Gage, P.; Glaze, L.; Baker, C.

The Venus In Situ Explorer (VISE) Mission addresses the highest priority science questions within the Venus community outlined in the National Research Council's Decadal Survey. The heritage Venus atmospheric entry system architecture, a 45° sphere-cone rigid aeroshell with a carbon phenolic thermal protection system, may no longer be the preferred entry system architecture compared to other viable alternatives being explored at NASA. A mechanically-deployed aerodynamic decelerator, known as the Adaptive Deployable Entry and Placement Technology (ADEPT), is an entry system alternative that can provide key operational benefits and risk reduction compared to a rigid aeroshell. This paper describes a mission feasibility study performed with the objectives of identifying potential adverse interactions with other mission elements and establishing requirements on decelerator performance. Feasibility is assessed through a launch-to-landing mission design study where the Venus Intrepid Tessera Lander (VITaL), a VISE science payload designed to inform the Decadal Survey results, is repackaged from a rigid aeroshell into the ADEPT decelerator. It is shown that ADEPT reduces the deceleration load on VITaL by an order of magnitude relative to a rigid aeroshell. The more benign entry environment opens up the VISE mission design environment for increased science return, reduced risk, and reduced cost. The ADEPT-VITAL mission concept of operations is presented and details of the entry vehicle structures and mechanisms are given. Finally, entry aerothermal analysis is presented that defines the operational requirements for a revolutionary structural-TPS material employed by ADEPT: three-dimensionally woven carbon cloth. Ongoing work to mitigate key risks identified in this feasibility study is presented.

Prenatal alcohol exposure, adaptive function, and entry into adult roles in a prospective study of young adults.

PubMed

Lynch, Mary Ellen; Kable, Julie A; Coles, Claire D

2015-01-01

Although many studies have demonstrated effects of prenatal alcohol exposure (PAE) on physical, cognitive, and behavioral development in children, few have focused on the long term effects on adults. In this study, data are presented on adaptive function and entry into adult roles in a community sample of young adults with PAE. The expectation was that prenatally exposed adults would show lower adaptive functioning and more difficulty with entry into adult roles than the non-exposed control group and that these effects would be related to the severity of PAE effects. The predominantly African-American, low income sample included adults with a wide range of prenatal exposure (n = 123) as well as control groups for socioeconomic (SES) (n =5 9) and disability (n = 54) status. The mothers of the alcohol-exposed and SES-control group participants were recruited before birth and offspring have been followed up periodically. The disability control group was recruited in adolescence. The adults were interviewed about adaptive function in day-to-day life and adult role entry. Collateral adults who were well-acquainted with each participant were interviewed concerning adaptive function. Results showed that adults who were dysmorphic and/or cognitively affected by PAE had difficulty with adaptive function and entry into adult roles. Males showing cognitive effects with no physical effects were the most severely affected. Results for exposed adults not showing physical or cognitive effects were similar to or more positive than those of the control group for most outcomes. PAE has long-term effects on adaptive outcomes in early adulthood. Additional research should focus on possible interventions at this transition and on factors contributing to the adjustment of the exposed, but unaffected participants. Copyright © 2015 Elsevier Inc. All rights reserved.

Aerocapture Inflatable Decelerator for Planetary Entry

NASA Technical Reports Server (NTRS)

Reza, Sajjad; Hund, Richard; Kustas, Frank; Willcockson, William; Songer, Jarvis; Brown, Glen

2007-01-01

Forward Attached Inflatable Decelerators, more commonly known as inflatable aeroshells, provide an effective, cost efficient means of decelerating spacecrafts by using atmospheric drag for aerocapture or planetary entry instead of conventional liquid propulsion deceleration systems. Entry into planetary atmospheres results in significant heating and aerodynamic pressures which stress aeroshell systems to their useful limits. Incorporation of lightweight inflatable decelerator surfaces with increased surface-area footprints provides the opportunity to reduce heat flux and induced temperatures, while increasing the payload mass fraction. Furthermore, inflatable aeroshell decelerators provide the needed deceleration at considerably higher altitudes and Mach numbers when compared with conventional rigid aeroshell entry systems. Inflatable aeroshells also provide for stowage in a compact space, with subsequent deployment of a large-area, lightweight heatshield to survive entry heating. Use of a deployable heatshield decelerator enables an increase in the spacecraft payload mass fraction and may eliminate the need for a spacecraft backshell.

Human Mars Entry, Descent and Landing Architectures Study Overview

NASA Technical Reports Server (NTRS)

Polsgrove, Tara T.; Dwyer Cianciolo, Alicia

2016-01-01

Landing humans on Mars will require entry, descent and landing (EDL) capability beyond the current state of the art. Nearly twenty times more delivered payload and an order of magnitude improvement in precision landing capability will be necessary. Several EDL technologies capable of meeting the human class payload delivery requirements are being considered. The EDL technologies considered include low lift-to-drag vehicles like Hypersonic Inflatable Aerodynamic Decelerators (HIAD), Adaptable Deployable Entry and Placement Technology (ADEPT), and mid range lift-to-drag vehicles like rigid aeroshell configurations. To better assess EDL technology options and sensitivities to future human mission design variations, a series of design studies has been conducted. The design studies incorporate EDL technologies with conceptual payload arrangements defined by the Evolvable Mars Campaign to evaluate the integrated system with higher fidelity than have been performed to date. This paper describes the results of the design studies for a lander design using the HIAD, ADEPT and rigid shell entry technologies and includes system and subsystem design details including mass and power estimates. This paper will review the point design for three entry configurations capable of delivering a 20 t human class payload to the surface of Mars.

An Adaptive Numeric Predictor-corrector Guidance Algorithm for Atmospheric Entry Vehicles. M.S. Thesis - MIT, Cambridge

NASA Technical Reports Server (NTRS)

Spratlin, Kenneth Milton

1987-01-01

An adaptive numeric predictor-corrector guidance is developed for atmospheric entry vehicles which utilize lift to achieve maximum footprint capability. Applicability of the guidance design to vehicles with a wide range of performance capabilities is desired so as to reduce the need for algorithm redesign with each new vehicle. Adaptability is desired to minimize mission-specific analysis and planning. The guidance algorithm motivation and design are presented. Performance is assessed for application of the algorithm to the NASA Entry Research Vehicle (ERV). The dispersions the guidance must be designed to handle are presented. The achievable operational footprint for expected worst-case dispersions is presented. The algorithm performs excellently for the expected dispersions and captures most of the achievable footprint.

Entry Dispersion Analysis for the Stardust Comet Sample Return Capsule

NASA Technical Reports Server (NTRS)

Desai, Prasun N.; Mitcheltree, Robert A.; Cheatwood, F. McNeil

1997-01-01

Stardust will be the first mission to return samples from beyond the Earth-Moon system. The sample return capsule, which is passively controlled during the fastest Earth entry ever, will land by parachute in Utah. The present study analyzes the entry, descent, and landing of the returning sample capsule. The effects of two aerodynamic instabilities are revealed (one in the high altitude free molecular regime and the other in the transonic/subsonic flow regime). These instabilities could lead to unacceptably large excursions in the angle-of-attack near peak heating and main parachute deployment, respectively. To reduce the excursions resulting from the high altitude instability, the entry spin rate of the capsule is increased. To stabilize the excursions from the transonic/subsonic instability, a drogue chute with deployment triggered by an accelerometer and timer is added prior to main parachute deployment. A Monte Carlo dispersion analysis of the modified entry (from which the impact of off-nominal conditions during the entry is ascertained) shows that the capsule attitude excursions near peak heating and drogue chute deployment are within Stardust program limits. Additionally, the size of the resulting 3-sigma landing ellipse is 83.5 km in downrange by 29.2 km in crossrange, which is within the Utah Test and Training Range boundaries.

Mars Exploration Rover Six-Degree-Of-Freedom Entry Trajectory Analysis

NASA Technical Reports Server (NTRS)

Desai, Prasun N.; Schoenenberger, Mark; Cheatwood, F. M.

2003-01-01

The Mars Exploration Rover mission will be the next opportunity for surface exploration of Mars in January 2004. Two rovers will be delivered to the surface of Mars using the same entry, descent, and landing scenario that was developed and successfully implemented by Mars Pathfinder. This investigation describes the trajectory analysis that was performed for the hypersonic portion of the MER entry. In this analysis, a six-degree-of-freedom trajectory simulation of the entry is performed to determine the entry characteristics of the capsules. In addition, a Monte Carlo analysis is also performed to statistically assess the robustness of the entry design to off-nominal conditions to assure that all entry requirements are satisfied. The results show that the attitude at peak heating and parachute deployment are well within entry limits. In addition, the parachute deployment dynamics pressure and Mach number are also well within the design requirements.

Entry Trajectory Issues for the Stardust Sample Return Capsule

NASA Technical Reports Server (NTRS)

Desai, Prasun N.; Mitcheltree, Robert A.; Cheatwood, F. McNeil

1999-01-01

The Stardust mission was successfully launched on February 7, 1999. It will be the first mission to return samples from a comet. The sample return capsule, which is passively controlled during the fastest Earth entry ever, will land by parachute in Utah. The present study describes the analysis of the entry, descent, and landing of the returning sample capsule utilizing the final, launch configuration capsule mass properties. The effects of two aerodynamic instabilities are revealed (one in the high altitude free molecular regime and the other in the transonic/subsonic flow regime). These instabilities could lead to unacceptably large excursions in the angle-of-attack near peak heating and main parachute deployment, respectively. To reduce the excursions resulting from the high altitude instability, the entry spin rate of the capsule is increased. To stabilize the excursions from the transonic/subsonic instability, a drogue chute with deployment triggered by a gravity-switch and timer is added prior to main parachute deployment. A Monte Carlo dispersion analysis of the modified entry (from which the impact of off-nominal conditions during the entry is ascertained) predicts that the capsule attitude excursions near peak heating and drogue chute deployment are within Stardust mission limits. Additionally, the size of the resulting 3-sigma landing ellipse is 60.8 km in downrange by 19.9 km in crossrange, which is within the Utah Test and Training Range boundaries.

Challenges to Computational Aerothermodynamic Simulation and Validation for Planetary Entry Vehicle Analysis

NASA Technical Reports Server (NTRS)

Gnoffo, Peter A.; Johnston, Christopher O.; Kleb, Bil

2010-01-01

Challenges to computational aerothermodynamic (CA) simulation and validation of hypersonic flow over planetary entry vehicles are discussed. Entry, descent, and landing (EDL) of high mass to Mars is a significant driver of new simulation requirements. These requirements include simulation of large deployable, flexible structures and interactions with reaction control system (RCS) and retro-thruster jets. Simulation of radiation and ablation coupled to the flow solver continues to be a high priority for planetary entry analyses, especially for return to Earth and outer planet missions. Three research areas addressing these challenges are emphasized. The first addresses the need to obtain accurate heating on unstructured tetrahedral grid systems to take advantage of flexibility in grid generation and grid adaptation. A multi-dimensional inviscid flux reconstruction algorithm is defined that is oriented with local flow topology as opposed to grid. The second addresses coupling of radiation and ablation to the hypersonic flow solver - flight- and ground-based data are used to provide limited validation of these multi-physics simulations. The third addresses the challenges of retro-propulsion simulation and the criticality of grid adaptation in this application. The evolution of CA to become a tool for innovation of EDL systems requires a successful resolution of these challenges.

Reconstruction of the Genesis Entry

NASA Technical Reports Server (NTRS)

Desai, Prasun N.; Qualls, Garry D.; Schoenenberger, Mark

2005-01-01

This paper provides an overview of the findings from a reconstruction analysis of the Genesis capsule entry. First, a comparison of the atmospheric properties (density and winds) encountered during the entry to the pre-entry profile is presented. The analysis that was performed on the video footage (obtained from the tracking stations at UTTR) during the descent is then described from which the Mach number at the onset of the capsule tumble was estimated following the failure of the drogue parachute deployment. Next, an assessment of the Genesis capsule aerodynamics that was extracted from the video footage is discussed, followed by a description of the capsule hypersonic attitude that must have occurred during the entry based on examination of the recovered capsule heatshield. Lastly, the entry trajectory reconstruction that was performed is presented.

Mission Sizing and Trade Studies for Low Ballistic Coefficient Entry Systems to Venus

NASA Technical Reports Server (NTRS)

Dutta, Soumyo; Smith, Brandon; Prabhu, Dinesh; Venkatapathy, Ethiraj

2012-01-01

The U.S and the U.S.S.R. have sent seventeen successful atmospheric entry missions to Venus. Past missions to Venus have utilized rigid aeroshell systems for entry. This rigid aeroshell paradigm sets performance limitations since the size of the entry vehicle is constrained by the fairing diameter of the launch vehicle. This has limited ballistic coefficients (beta) to well above 100 kg/m2 for the entry vehicles. In order to maximize the science payload and minimize the Thermal Protection System (TPS) mass, these missions have entered at very steep entry flight path angles (gamma). Due to Venus thick atmosphere and the steep-gamma, high- conditions, these entry vehicles have been exposed to very high heat flux, very high pressures and extreme decelerations (upwards of 100 g's). Deployable aeroshells avoid the launch vehicle fairing diameter constraint by expanding to a larger diameter after the launch. Due to the potentially larger wetted area, deployable aeroshells achieve lower ballistic coefficients (well below 100 kg/m2), and if they are flown at shallower flight path angles, the entry vehicle can access trajectories with far lower decelerations (50-60 g's), peak heat fluxes (400 W/cm2) and peak pressures. The structural and TPS mass of the shallow-gamma, low-beta deployables are lower than their steep-gamma, high-beta rigid aeroshell counterparts at larger diameters, contributing to lower areal densities and potentially higher payload mass fractions. For example, at large diameters, deployables may attain aeroshell areal densities of 10 kg/m2 as opposed to 50 kg/m2 for rigid aeroshells. However, the low-beta, shallow-gamma paradigm also raises issues, such as the possibility of skip-out during entry. The shallow-gamma could also increase the landing footprint of the vehicle. Furthermore, the deployable entry systems may be flexible, so there could be fluid-structure interaction, especially in the high altitude, low-density regimes. The need for precision in

Aerial Deployment and Inflation System for Mars Helium Balloons

NASA Technical Reports Server (NTRS)

Lachenmeler, Tim; Fairbrother, Debora; Shreves, Chris; Hall, Jeffery, L.; Kerzhanovich, Viktor V.; Pauken, Michael T.; Walsh, Gerald J.; White, Christopher V.

2009-01-01

A method is examined for safely deploying and inflating helium balloons for missions at Mars. The key for making it possible to deploy balloons that are light enough to be buoyant in the thin, Martian atmosphere is to mitigate the transient forces on the balloon that might tear it. A fully inflated Mars balloon has a diameter of 10 m, so it must be folded up for the trip to Mars, unfolded upon arrival, and then inflated with helium gas in the atmosphere. Safe entry into the Martian atmosphere requires the use of an aeroshell vehicle, which protects against severe heating and pressure loads associated with the hypersonic entry flight. Drag decelerates the aeroshell to supersonic speeds, then two parachutes deploy to slow the vehicle down to the needed safe speed of 25 to 35 m/s for balloon deployment. The parachute system descent dynamic pressure must be approximately 5 Pa or lower at an altitude of 4 km or more above the surface.

Orion Entry Display Feeder and Interactions with the Entry Monitor System

NASA Technical Reports Server (NTRS)

Baird, Darren; Bernatovich, Mike; Gillespie, Ellen; Kadwa, Binaifer; Matthews, Dave; Penny, Wes; Zak, Tim; Grant, Mike; Bihari, Brian

2010-01-01

The Orion spacecraft is designed to return astronauts to a landing within 10 km of the intended landing target from low Earth orbit, lunar direct-entry, and lunar skip-entry trajectories. Al pile the landing is nominally controlled autonomously, the crew can fly precision entries manually in the event of an anomaly. The onboard entry displays will be used by the crew to monitor and manually fly the entry, descent, and landing, while the Entry Monitor System (EMS) will be used to monitor the health and status of the onboard guidance and the trajectory. The entry displays are driven by the entry display feeder, part of the Entry Monitor System (EMS). The entry re-targeting module, also part of the EMS, provides all the data required to generate the capability footprint of the vehicle at any point in the trajectory, which is shown on the Primary Flight Display (PFD). It also provides caution and warning data and recommends the safest possible re-designated landing site when the nominal landing site is no longer within the capability of the vehicle. The PFD and the EMS allow the crew to manually fly an entry trajectory profile from entry interface until parachute deploy having the flexibility to manually steer the vehicle to a selected landing site that best satisfies the priorities of the crew. The entry display feeder provides data from the ENIS and other components of the GNC flight software to the displays at the proper rate and in the proper units. It also performs calculations that are specific to the entry displays and which are not made in any other component of the flight software. In some instances, it performs calculations identical to those performed by the onboard primary guidance algorithm to protect against a guidance system failure. These functions and the interactions between the entry display feeder and the other components of the EMS are described.

76 FR 60006 - Joint Europe Africa Deployment & Distribution Conference 2011: “Adapting To Challenge and Change”

Federal Register 2010, 2011, 2012, 2013, 2014

2011-09-28

... DEPARTMENT OF DEFENSE Office of the Secretary Joint Europe Africa Deployment & Distribution Conference 2011: ``Adapting To Challenge and Change'' AGENCY: United States Africa Command, Department of Defense (DoD). ACTION: Notice of conference. SUMMARY: This document announces that U.S. Africa Command...

Re-entry and reintegration: returning home after combat.

PubMed

Doyle, Michael E; Peterson, Kris A

2005-01-01

Soldier life exists on a continuum of readiness for deployment. Re-entry and reintegration-the return home and reunion with family and community-key the success of the deployment cycle. In current and projected future operations, the Army and society will both bear the burden of this re-entry and re-integration. Programs and procedures in place work towards improving communication, mitigating distress and resolving crises during reentry and reintegration. Key elements include: inclusion of families and communities early into the planning for reentry and reintegration; normalization (non-medicalization of distress); easy access to behavioral health professionals; and education of families on resources and benefits. Through broad collaboration, maximal benefit to the Soldier, family members and society be realized.

A Study of the Effects of Atmospheric Phenomena on Mars Science Laboratory Entry Performance

NASA Technical Reports Server (NTRS)

Cianciolo, Alicia D.; Way, David W.; Powell, Richard W.

2008-01-01

At Earth during entry the shuttle has experienced what has come to be known as potholes in the sky or regions of the atmosphere where the density changes suddenly. Because of the small data set of atmospheric information where the Mars Science Laboratory (MSL) parachute deploys, the purpose of this study is to examine the effect similar atmospheric pothole characteristics, should they exist at Mars, would have on MSL entry performance. The study considers the sensitivity of entry design metrics, including altitude and range error at parachute deploy and propellant use, to pothole like density and wind phenomena.

Pegasus XL CYGNSS Payload Adapter Installation to Deployment Mod

NASA Image and Video Library

2016-10-17

Technicians with Orbital ATK install the payload adapter to the deployment module that contains the micro satellites for NASA’s Cyclone Global Navigation Satellite System (CYGNSS) in Building 1555 at Vandenberg Air Force Base in California. CYGNSS is being prepared at Vandenberg, and then will be transported to NASA’s Kennedy Space Center in Florida aboard the Orbital ATK Pegasus XL rocket which will be attached to the Orbital ATK L-1011 carrier aircraft. CYGNSS will launch on the Pegasus XL rocket from the Skid Strip at Cape Canaveral Air Force Station. CYGNSS will make frequent and accurate measurements of ocean surface winds throughout the life cycle of tropical storms and hurricanes. The data that CYGNSS provides will enable scientists to probe key air-sea interaction processes that take place near the core of storms, which are rapidly changing and play a critical role in the beginning and intensification of hurricanes.

Mars Science Laboratory Entry Guidance Improvements for Mars 2018 (DRAFT)

NASA Technical Reports Server (NTRS)

Garcia-Llama, Eduardo; Winski, Richard G.; Shidner, Jeremy D.; Ivanov, Mark C.; Grover, Myron R.; Prakash, Ravi

2011-01-01

In 2011, the Mars Science Laboratory (MSL) will be launched in a mission to deliver the largest and most capable rover to date to the surface of Mars. A follow on MSL-derived mission, referred to as Mars 2018, is planned for 2018. Mars 2018 goals include performance enhancements of the Entry, Descent and Landing over that of its predecessor MSL mission of 2011. This paper will discuss the main elements of the modified 2018 EDL preliminary design that will increase performance on the entry phase of the mission. In particular, these elements will increase the parachute deploy altitude to allow for more time margin during the subsequent descent and landing phases and reduce the delivery ellipse size at parachute deploy through modifications in the entry reference trajectory design, guidance trigger logic design, and the effect of additional navigation hardware.

Study of advanced atmospheric entry systems for Mars

NASA Technical Reports Server (NTRS)

1978-01-01

Entry system designs are described for various advanced Mars missions including sample return, hard lander, and Mars airplane. The Mars exploration systems for sample return and the hard lander require decleration from direct approach entry velocities of about 6 km/s to terminal velocities consistent with surface landing requirements. The Mars airplane entry system is decelerated from orbit at 4.6 km/s to deployment near the surface. Mass performance characteristics of major elements of the Mass performance characteristics are estimated for the major elements of the required entry systems using Viking technology or logical extensions of technology in order to provide a common basis of comparison for the three entry modes mission mode approaches. The entry systems, although not optimized, are based on Viking designs and reflect current hardware performance capability and realistic mass relationships.

Orion Capsule Handling Qualities for Atmospheric Entry

NASA Technical Reports Server (NTRS)

Tigges, Michael A.; Bihari, Brian D.; Stephens, John-Paul; Vos, Gordon A.; Bilimoria, Karl D.; Mueller, Eric R.; Law, Howard G.; Johnson, Wyatt; Bailey, Randall E.; Jackson, Bruce

2011-01-01

Two piloted simulations were conducted at NASA's Johnson Space Center using the Cooper-Harper scale to study the handling qualities of the Orion Command Module capsule during atmospheric entry flight. The simulations were conducted using high fidelity 6-DOF simulators for Lunar Return Skip Entry and International Space Station Return Direct Entry flight using bank angle steering commands generated by either the Primary (PredGuid) or Backup (PLM) guidance algorithms. For both evaluations, manual control of bank angle began after descending through Entry Interface into the atmosphere until drogue chutes deployment. Pilots were able to use defined bank management and reversal criteria to accurately track the bank angle commands, and stay within flight performance metrics of landing accuracy, g-loads, and propellant consumption, suggesting that the pilotability of Orion under manual control is both achievable and provides adequate trajectory performance with acceptable levels of pilot effort. Another significant result of these analyses is the applicability of flying a complex entry task under high speed entry flight conditions relevant to the next generation Multi Purpose Crew Vehicle return from Mars and Near Earth Objects.

Deployable Aeroshell Flexible Thermal Protection System Testing

NASA Technical Reports Server (NTRS)

Hughes, Stephen J.; Ware, Joanne S.; DelCorso, Joseph A.; Lugo, Rafael A.

2009-01-01

Deployable aeroshells offer the promise of achieving larger aeroshell surface areas for entry vehicles than otherwise attainable without deployment. With the larger surface area comes the ability to decelerate high-mass entry vehicles at relatively low ballistic coefficients. However, for an aeroshell to perform even at the low ballistic coefficients attainable with deployable aeroshells, a flexible thermal protection system (TPS) is required that is capable of surviving reasonably high heat flux and durable enough to survive the rigors of construction handling, high density packing, deployment, aerodynamic loading and aerothermal heating. The Program for the Advancement of Inflatable Decelerators for Atmospheric Entry (PAIDAE) is tasked with developing the technologies required to increase the technology readiness level (TRL) of inflatable deployable aeroshells, and one of several of the technologies PAIDAE is developing for use on inflatable aeroshells is flexible TPS. Several flexible TPS layups were designed, based on commercially available materials, and tested in NASA Langley Research Center's 8 Foot High Temperature Tunnel (8ft HTT). The TPS layups were designed for, and tested at three different conditions that are representative of conditions seen in entry simulation analyses of inflatable aeroshell concepts. Two conditions were produced in a single run with a sting-mounted dual wedge test fixture. The dual wedge test fixture had one row of sample mounting locations (forward) at about half the running length of the top surface of the wedge. At about two thirds of the running length of the wedge, a second test surface drafted up at five degrees relative to the first test surface established the remaining running length of the wedge test fixture. A second row of sample mounting locations (aft) was positioned in the middle of the running length of the second test surface. Once the desired flow conditions were established in the test section the dual wedge

Technology Development for Deployable Aerodynamic Decelerators at Mars

NASA Technical Reports Server (NTRS)

Masciarelli, James P.

2002-01-01

Parachutes used for Mars landing missions are only certified for deployment at Mars behind blunt bodies flying at low angles of attack, Mach numbers up to 2.2, and dynamic pressures of up to 800 Pa. NASA is currently studying entry vehicle concepts for future robotic missions to Mars that would require parachutes to be deployed at higher Mach numbers and dynamic pressures. This paper demonstrates the need for expanding the parachute deployment envelope, and describes a three-phase technology development activity that has been initiated to address the need. The end result of the technology development program will be a aerodynamic decelerator system that can be deployed at Mach numbers of up to 3.1 and dynamic pressures of up to 1400 Pa.

Technology development for deployable aerodynamic decelerators at Mars

NASA Astrophysics Data System (ADS)

Masciarelli, James P.

2002-01-01

Parachutes used for Mars landing missions are only certified for deployment at Mars behind blunt bodies flying at low angles of attack, Mach numbers up to 2.2, and dynamic pressures of up to 800 Pa. NASA is currently studying entry vehicle concepts for future robotic missions to Mars that would require parachutes to be deployed at higher Mach numbers and dynamic pressures. This paper demonstrates the need for expanding the parachute deployment envelope, and describes a three-phase technology development activity that has been initiated to address the need. The end result of the technology development program will be a aerodynamic decelerator system that can be deployed at Mach numbers of up to 3.1 and dynamic pressures of up to 1400 Pa. .

Study and Development of a Sub-Orbital Re-Entry Demonstrator

NASA Astrophysics Data System (ADS)

Savino, R.

The Italian and European Space Agencies are supporting a research programme, developed in Campania region by a cluster of industries, research institutes and universities, on a low-cost re-entry capsule, able to return payloads from the ISS to Earth and/or to perform short-duration scientific missions in Low Earth Orbit (LEO). The ballistic capsule is characterized by a deployable, disposable "umbrella-like" heat shield that allows relatively small dimensions at launch and a sufficient exposed surface area in re-entry conditions, reducing the ballistic coefficient and leading to acceptable heat fluxes, mechanical loads and final descent velocity. ESA is supporting a preliminary study to develop a flight demonstrator of the capsule to be embarked as a secondary payload onboard a sub-orbital sounding rocket. The deployable thermal protection system concept may be applied to future science and robotic exploration mission requiring planetary entry and, possibly also to missions in the framework of Human Space flight, requiring planetary entry or re-entry. The technology offers also an interesting potential for aerobraking, aerocapture and for de-orbiting. This paper summarizes the results of these activities, which are being more and more refined as the work proceeds, including the definition and analysis of the mission scenario, the aerodynamic, aerothermodynamic, mechanical and structural analyses and the technical definition of avionics, instrumentation and main subsystems.

Mars Science Laboratory: Entry, Descent, and Landing System Performance

NASA Technical Reports Server (NTRS)

Way, David W.; Powell, Richard W.; Chen, Allen; SanMartin, A. Miguel; Burkhart, P. Daniel; Mendeck, Gavin F.

2007-01-01

In 2010, the Mars Science Laboratory (MSL) mission will pioneer the next generation of robotic Entry, Descent, and Landing (EDL) systems, by delivering the largest and most capable rover to date to the surface of Mars. To do so, MSL will fly a guided lifting entry at a lift-to-drag ratio in excess of that ever flown at Mars, deploy the largest parachute ever at Mars, and perform a novel Sky Crane maneuver. Through improved altitude capability, increased latitude coverage, and more accurate payload delivery, MSL is allowing the science community to consider the exploration of previously inaccessible regions of the planet. The MSL EDL system is a new EDL architecture based on Viking heritage technologies and designed to meet the challenges of landing increasing massive payloads on Mars. In accordance with level-1 requirements, the MSL EDL system is being designed to land an 850 kg rover to altitudes as high as 1 km above the Mars Orbiter Laser Altimeter defined areoid within 10 km of the desired landing site. Accordingly, MSL will enter the largest entry mass, fly the largest 70 degree sphere-cone aeroshell, generate the largest hypersonic lift-to-drag ratio, and deploy the largest Disk-Gap-Band supersonic parachute of any previous mission to Mars. Major EDL events include a hypersonic guided entry, supersonic parachute deploy and inflation, subsonic heatshield jettison, terminal descent sensor acquisition, powered descent initiation, sky crane terminal descent, rover touchdown detection, and descent stage flyaway. Key performance metrics, derived from level-1 requirements and tracked by the EDL design team to indicate performance capability and timeline margins, include altitude and range at parachute deploy, time on radar, and propellant use. The MSL EDL system, which will continue to develop over the next three years, will enable a notable extension in the advancement of Mars surface science by delivering more science capability than ever before to the surface of

Mars Science Laboratory: Entry, Descent, and Landing System Performance

NASA Technical Reports Server (NTRS)

Way, David W.; Powell, Richard W.; Chen, Allen; Steltzner, Adam D.; San Martin, Alejandro M.; Burkhart, Paul D.; mendeck, Gavin F.

2006-01-01

In 2010, the Mars Science Laboratory (MSL) mission will pioneer the next generation of robotic Entry, Descent, and Landing (EDL) systems, by delivering the largest and most capable rover to date to the surface of Mars. To do so, MSL will fly a guided lifting entry at a lift-to-drag ratio in excess of that ever flown at Mars, deploy the largest parachute ever at Mars, and perform a novel Sky Crane maneuver. Through improved altitude capability, increased latitude coverage, and more accurate payload delivery, MSL is allowing the science community to consider the exploration of previously inaccessible regions of the planet. The MSL EDL system is a new EDL architecture based on Viking heritage technologies and designed to meet the challenges of landing increasing massive payloads on Mars. In accordance with level-1 requirements, the MSL EDL system is being designed to land an 850 kg rover to altitudes as high as 1 km above the Mars Orbiter Laser Altimeter defined areoid within 10 km of the desired landing site. Accordingly, MSL will enter the largest entry mass, fly the largest 70 degree sphere-cone aeroshell, generate the largest hypersonic lift-to-drag ratio, and deploy the largest Disk-Gap-Band supersonic parachute of any previous mission to Mars. Major EDL events include a hypersonic guided entry, supersonic parachute deploy and inflation, subsonic heatshield jettison, terminal descent sensor acquisition, powered descent initiation, sky crane terminal descent, rover touchdown detection, and descent stage flyaway. Key performance metrics, derived from level-1 requirements and tracked by the EDL design team to indicate performance capability and timeline margins, include altitude and range at parachute deploy, time on radar, and propellant use. The MSL EDL system, which will continue to develop over the next three years, will enable a notable extension in the advancement of Mars surface science by delivering more science capability than ever before to the surface of

Entry Guidance for the 2011 Mars Science Laboratory Mission

NASA Technical Reports Server (NTRS)

Mendeck, Gavin F.; Craig, Lynn E.

2011-01-01

The 2011 Mars Science Laboratory will be the first Mars mission to attempt a guided entry to safely deliver the rover to a touchdown ellipse of 25 km x 20 km. The Entry Terminal Point Controller guidance algorithm is derived from the final phase Apollo Command Module guidance and, like Apollo, modulates the bank angle to control the range flown. For application to Mars landers which must make use of the tenuous Martian atmosphere, it is critical to balance the lift of the vehicle to minimize the range error while still ensuring a safe deploy altitude. An overview of the process to generate optimized guidance settings is presented, discussing improvements made over the last nine years. Key dispersions driving deploy ellipse and altitude performance are identified. Performance sensitivities including attitude initialization error and the velocity of transition from range control to heading alignment are presented.

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

A trajectory generation framework for modeling spacecraft entry in MDAO

NASA Astrophysics Data System (ADS)

D`Souza, Sarah N.; Sarigul-Klijn, Nesrin

2016-04-01

In this paper a novel trajectory generation framework was developed that optimizes trajectory event conditions for use in a Generalized Entry Guidance algorithm. The framework was developed to be adaptable via the use of high fidelity equations of motion and drag based analytical bank profiles. Within this framework, a novel technique was implemented that resolved the sensitivity of the bank profile to atmospheric non-linearities. The framework's adaptability was established by running two different entry bank conditions. Each case yielded a reference trajectory and set of transition event conditions that are flight feasible and implementable in a Generalized Entry Guidance algorithm.

Pre-deployment Heat Acclimatization Guidelines for Disaster Responders.

PubMed

Brearley, Matt B

2016-02-01

Minimal preparation time is a feature of responding to sudden onset disasters. While equipment and supplies are prepared for deployment at short notice, less is known of the physical preparation of medical responders. With many disaster-prone areas classified as tropical regions, there is potential for responders to endure a combination of high ambient temperatures and relative humidity during deployment. Heat acclimatization, defined as the physiological and perceptual adaptations to frequent elevations of core body temperature (Tc), is a key strategy to improve tolerance of hot conditions by medical responders. Pre-deployment heat acclimatization guidelines were developed based upon the duration of physical training and the subjective rate of perceived exertion (session RPE). An objective of individual training sessions was the perception of body temperature as warm to hot. The guidelines were implemented for Team Bravo (2nd rotation) of the Australian Medical Assistance Team (AusMAT) deployed to Tacloban, Philippines following Typhoon Haiyan in November 2013. The guidelines were distributed electronically five to seven days prior to deployment and were followed by a consultation. A group training session in hot conditions was undertaken prior to departure. The AusMAT responders to utilize the guidelines were based in cool or temperate climates that required extra layers of clothing, training during warmer parts of the days, or warm indoor conditions to achieve session objectives. Responders reported the guidelines were simple to use, applicable to their varied training regimens, and had improved their confidence to work in the heat despite not completing the entire 14 day period. The pre-deployment heat acclimatization guidelines provided AusMAT responders the ability to quantify their physical training and promoted physiological adaptations to maximize health, safety, and performance during deployment. While maintaining year-round heat acclimatization is

Mars entry-to-landing trajectory optimization and closed loop guidance

NASA Technical Reports Server (NTRS)

Ilgen, Marc R.; Manning, Raymund A.; Cruz, Manuel I.

1991-01-01

The guidance strategy of the Mars Rover Sample Return mission is presented in detail. Aeromaneuver versus aerobrake trades are examined, and an aerobrake analysis is presented which takes into account targeting, guidance, flight control, trajectory profile, delivery accuracy. An aeromaneuver analysis is given which includes the entry corridor, maneuver footprint, guidance, preentry phase, constant drag phase, equilibrium guide phase, variable drag phase, influence of trajectory profile on the entry flight loads, parachute deployment conditions and strategies, and landing accuracy. The Mars terminal descent phase is analyzed.

Determination of Barometric Altimeter Errors for the Orion Exploration Flight Test-1 Entry

NASA Technical Reports Server (NTRS)

Brown, Denise L.; Bunoz, Jean-Philippe; Gay, Robert

2012-01-01

The Exploration Flight Test 1 (EFT-1) mission is the unmanned flight test for the upcoming Multi-Purpose Crew Vehicle (MPCV). During entry, the EFT-1 vehicle will trigger several Landing and Recovery System (LRS) events, such as parachute deployment, based on on-board altitude information. The primary altitude source is the filtered navigation solution updated with GPS measurement data. The vehicle also has three barometric altimeters that will be used to measure atmospheric pressure during entry. In the event that GPS data is not available during entry, the altitude derived from the barometric altimeter pressure will be used to trigger chute deployment for the drogues and main parachutes. Therefore it is important to understand the impact of error sources on the pressure measured by the barometric altimeters and on the altitude derived from that pressure. The error sources for the barometric altimeters are not independent, and many error sources result in bias in a specific direction. Therefore conventional error budget methods could not be applied. Instead, high fidelity Monte-Carlo simulation was performed and error bounds were determined based on the results of this analysis. Aerodynamic errors were the largest single contributor to the error budget for the barometric altimeters. The large errors drove a change to the altitude trigger setpoint for FBC jettison deploy.

PredGuid+A: Orion Entry Guidance Modified for Aerocapture

NASA Technical Reports Server (NTRS)

Lafleur, Jarret

2013-01-01

PredGuid+A software was developed to enable a unique numerical predictor-corrector aerocapture guidance capability that builds on heritage Orion entry guidance algorithms. The software can be used for both planetary entry and aerocapture applications. Furthermore, PredGuid+A implements a new Delta-V minimization guidance option that can take the place of traditional targeting guidance and can result in substantial propellant savings. PredGuid+A allows the user to set a mode flag and input a target orbit's apoapsis and periapsis. Using bank angle control, the guidance will then guide the vehicle to the appropriate post-aerocapture orbit using one of two algorithms: Apoapsis Targeting or Delta-V Minimization (as chosen by the user). Recently, the PredGuid guidance algorithm was adapted for use in skip-entry scenarios for NASA's Orion multi-purpose crew vehicle (MPCV). To leverage flight heritage, most of Orion's entry guidance routines are adapted from the Apollo program.

Avionics architecture studies for the entry research vehicle

NASA Technical Reports Server (NTRS)

Dzwonczyk, M. J.; Mckinney, M. F.; Adams, S. J.; Gauthier, R. J.

1989-01-01

This report is the culmination of a year-long investigation of the avionics architecture for NASA's Entry Research Vehicle (ERV). The Entry Research Vehicle is conceived to be an unmanned, autonomous spacecraft to be deployed from the Shuttle. It will perform various aerodynamic and propulsive maneuvers in orbit and land at Edwards AFB after a 5 to 10 hour mission. The design and analysis of the vehicle's avionics architecture are detailed here. The architecture consists of a central triply redundant ultra-reliable fault tolerant processor attached to three replicated and distributed MIL-STD-1553 buses for input and output. The reliability analysis is detailed here. The architecture was found to be sufficiently reliable for the ERV mission plan.

The Lilongwe Central Hospital Patient Management Information System: A Success in Computer-Based Order Entry Where One Might Least Expect It

PubMed Central

GP, Douglas; RA, Deula; SE, Connor

2003-01-01

Computer-based order entry is a powerful tool for enhancing patient care. A pilot project in the pediatric department of the Lilongwe Central Hospital (LCH) in Malawi, Africa has demonstrated that computer-based order entry (COE): 1) can be successfully deployed and adopted in resource-poor settings, 2) can be built, deployed and sustained at relatively low cost and with local resources, and 3) has a greater potential to improve patient care in developing than in developed countries. PMID:14728338

Venus entry probe technology reference mission

NASA Astrophysics Data System (ADS)

van den Berg, M. L.; Falkner, P.; Atzei, A. C.; Phipps, A.; Mieremet, A.; Kraft, S.; Peacock, A.

The Venus Entry Probe is one of ESA's Technology Reference Missions (TRM). TRMs are model science-driven missions that are, although not part of the ESA science programme, able to provide focus to future technology requirements. This is accomplished through the study of several technologically demanding and scientifically meaningful mission concepts, which are strategically chosen to address diverse technological issues. The TRMs complement ESA's current mission specific development programme and allow the ESA Science Directorate to strategically plan the development of technologies that will enable potential future scientific missions. Key technological objectives for future planetary exploration include the use of small orbiters and in-situ probes with highly miniaturized and highly integrated payload suites. The low resource, and therefore low cost, spacecraft allow for a phased strategic approach to planetary exploration. The aim of the Venus Entry Probe TRM (VEP) is to study approaches for low cost in-situ exploration of the Venusian atmosphere. The mission profile consists of two minisats. The first satellite enters low Venus orbit. This satellite contains a highly integrated remote sensing payload suite primarily dedicated to support the in-situ atmospheric measurements of the aerobot. The second minisat enters deep elliptical orbit, deploys the aerobot, and subsequently operates as a data relay, data processing and overall resource allocation satellite. The micro-aerobot consists of a long-duration balloon that will analyze the Venusian middle cloud layer at an altitude of ˜ 55 km, where the environment is relatively benign (T = 20 C and p = 0.45 bars). The balloon will deploy a swarm of active ballast probes, which determine vertical profiles of selected properties of the lower atmosphere. In this presentation, the mission objectives and profile of the Venus Entry Probe TRM will be given as well as the key technological challenges.

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

, 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.

On the Use of a Range Trigger for the Mars Science Laboratory Entry Descent and Landing

NASA Technical Reports Server (NTRS)

Way, David W.

2011-01-01

In 2012, during the Entry, Descent, and Landing (EDL) of the Mars Science Laboratory (MSL) entry vehicle, a 21.5 m Viking-heritage, Disk-Gap-Band, supersonic parachute will be deployed at approximately Mach 2. The baseline algorithm for commanding this parachute deployment is a navigated planet-relative velocity trigger. This paper compares the performance of an alternative range-to-go trigger (sometimes referred to as Smart Chute ), which can significantly reduce the landing footprint size. Numerical Monte Carlo results, predicted by the POST2 MSL POST End-to-End EDL simulation, are corroborated and explained by applying propagation of uncertainty methods to develop an analytic estimate for the standard deviation of Mach number. A negative correlation is shown to exist between the standard deviations of wind velocity and the planet-relative velocity at parachute deploy, which mitigates the Mach number rise in the case of the range trigger.

Helping military families through the deployment process: Strategies to support parenting

PubMed Central

Gewirtz, Abigail H.; Erbes, Christopher R.; Polusny, Melissa A.; Forgatch, Marion S.; DeGarmo, David S.

2011-01-01

Recent studies have highlighted the impact of deployment on military families and children and the corresponding need for interventions to support them. Historically, however, little emphasis has been placed on family-based interventions in general, and parenting interventions in particular, with returning service members. This paper provides an overview of research on the associations between combat deployment, parental adjustment of service members and spouses, parenting impairments, and children’s adjustment problems, and provides a social interaction learning framework for research and practice to support parenting among military families affected by a parent’s deployment. We then describe the Parent Management Training-Oregon model (PMTO™), a family of interventions that improves parenting practices and child adjustment in highly stressed families, and briefly present work on an adaptation of PMTO for use in military families (After Deployment: Adaptive Parenting Tools, or ADAPT). The article concludes with PMTO-based recommendations for clinicians providing parenting support to military families. PMID:21841889

Motivationally Significant Stimuli Show Visual Prior Entry: Evidence for Attentional Capture

ERIC Educational Resources Information Center

West, Greg L.; Anderson, Adam A. K.; Pratt, Jay

2009-01-01

Previous studies that have found attentional capture effects for stimuli of motivational significance do not directly measure initial attentional deployment, leaving it unclear to what extent these items produce attentional capture. Visual prior entry, as measured by temporal order judgments (TOJs), rests on the premise that allocated attention…

Disturbance observer based model predictive control for accurate atmospheric entry of spacecraft

NASA Astrophysics Data System (ADS)

Wu, Chao; Yang, Jun; Li, Shihua; Li, Qi; Guo, Lei

2018-05-01

Facing the complex aerodynamic environment of Mars atmosphere, a composite atmospheric entry trajectory tracking strategy is investigated in this paper. External disturbances, initial states uncertainties and aerodynamic parameters uncertainties are the main problems. The composite strategy is designed to solve these problems and improve the accuracy of Mars atmospheric entry. This strategy includes a model predictive control for optimized trajectory tracking performance, as well as a disturbance observer based feedforward compensation for external disturbances and uncertainties attenuation. 500-run Monte Carlo simulations show that the proposed composite control scheme achieves more precise Mars atmospheric entry (3.8 km parachute deployment point distribution error) than the baseline control scheme (8.4 km) and integral control scheme (5.8 km).

Improving the Quality of Evidence-Based Writing Entries in Electronic Portfolios

ERIC Educational Resources Information Center

Denton, David W.

2012-01-01

The problem investigated in this study was whether entries written to an electronic portfolio by preservice teachers improved in quality after an intervention was deployed. The study also compared portfolio metadata to writing quality scores to determine whether there was a relationship. Participants included a convenience sample of 11…

Trading Robustness Requirements in Mars Entry Trajectory Design

NASA Technical Reports Server (NTRS)

Lafleur, Jarret M.

2009-01-01

One of the most important metrics characterizing an atmospheric entry trajectory in preliminary design is the size of its predicted landing ellipse. Often, requirements for this ellipse are set early in design and significantly influence both the expected scientific return from a particular mission and the cost of development. Requirements typically specify a certain probability level (6-level) for the prescribed ellipse, and frequently this latter requirement is taken at 36. However, searches for the justification of 36 as a robustness requirement suggest it is an empirical rule of thumb borrowed from non-aerospace fields. This paper presents an investigation into the sensitivity of trajectory performance to varying robustness (6-level) requirements. The treatment of robustness as a distinct objective is discussed, and an analysis framework is presented involving the manipulation of design variables to effect trades between performance and robustness objectives. The scenario for which this method is illustrated is the ballistic entry of an MSL-class Mars entry vehicle. Here, the design variable is entry flight path angle, and objectives are parachute deploy altitude performance and error ellipse robustness. Resulting plots show the sensitivities between these objectives and trends in the entry flight path angles required to design to these objectives. Relevance to the trajectory designer is discussed, as are potential steps for further development and use of this type of analysis.

Airborne Observation of the Hayabusa Sample Return Capsule Re-Entry

NASA Technical Reports Server (NTRS)

Grinstead, Jay H.; Jenniskens, Peter; Cassell, Alan M.; Albers, James; Winter, Michael W.

2011-01-01

NASA Ames Research Center and the SETI Institute collaborated on an effort to observe the Earth re-entry of the Japan Aerospace Exploration Agency's Hayabusa sample return capsule. Hayabusa was an asteroid exploration mission that retrieved a sample from the near-Earth asteroid Itokawa. Its sample return capsule re-entered over the Woomera Prohibited Area in southern Australia on June 13, 2010. Being only the third sample return mission following NASA's Genesis and Stardust missions, Hayabusa's return was a rare opportunity to collect aerothermal data from an atmospheric entry capsule returning at superorbital speeds. NASA deployed its DC-8 airborne laboratory and a team of international researchers to Australia for the re-entry. For approximately 70 seconds, spectroscopic and radiometric imaging instruments acquired images and spectra of the capsule, its wake, and destructive re-entry of the spacecraft bus. Once calibrated, spectra of the capsule will be interpreted to yield data for comparison with and validation of high fidelity and engineering simulation tools used for design and development of future atmospheric entry system technologies. A brief summary of the Hayabusa mission, the preflight preparations and observation mission planning, mission execution, and preliminary spectral data are documented.

Smart Book Charts

NASA Technical Reports Server (NTRS)

Chinnapongse, Ronald L.

2015-01-01

Smart book charts for TPSM: Heatshield for Extreme Entry Environment Technology (HEEET), Conformal Ablative TPS (CA-TPS), 3D Woven Multifunctional Ablative TPS (3D MAT), and Adaptable, Deployable, Entry and Placement Technology (ADEPT).

Aerothermodynamic environment for a Titan probe with deployable decelerator

NASA Technical Reports Server (NTRS)

Green, M. J.; Swenson, B. L.; Balakrishnan, A.

1985-01-01

It is pointed out that further exploration of Titan, Saturn's largest moon, is of current interest to the scientific community, particularly from the standpoint of the organic chemical evolution of its atmosphere. For a suitable study of this Saturnian satellite, a mission involving a Titan atmospheric entry probe is to be conducted. The probe is to employ a deployable decelerator with the aim to allow scientific measurements in the haze layer. The present investigation is concerned with an assessment of the aerothermodynamic environment for the considered probe during its hypervelocity, low-Reynolds-number entry. Attention is given to the employed computational method, the Titan probe configuration, the Titan probe trajectory, the viscous-layer regime of the aerothermodynamic environment, and the incipient merged-layer regime.

Assessment of the Reconstructed Aerodynamics of the Mars Science Laboratory Entry Vehicle

NASA Technical Reports Server (NTRS)

Schoenenberger, Mark; Van Norman, John W.; Dyakonov, Artem A.; Karlgaard, Christopher D.; Way, David W.; Kutty, Prasad

2013-01-01

On August 5, 2012, the Mars Science Laboratory entry vehicle successfully entered Mars atmosphere, flying a guided entry until parachute deploy. The Curiosity rover landed safely in Gale crater upon completion of the Entry Descent and Landing sequence. This paper compares the aerodynamics of the entry capsule extracted from onboard flight data, including Inertial Measurement Unit (IMU) accelerometer and rate gyro information, and heatshield surface pressure measurements. From the onboard data, static force and moment data has been extracted. This data is compared to preflight predictions. The information collected by MSL represents the most complete set of information collected during Mars entry to date. It allows the separation of aerodynamic performance from atmospheric conditions. The comparisons show the MSL aerodynamic characteristics have been identified and resolved to an accuracy better than the aerodynamic database uncertainties used in preflight simulations. A number of small anomalies have been identified and are discussed. This data will help revise aerodynamic databases for future missions and will guide computational fluid dynamics (CFD) development to improved prediction codes.

Deployment, Mental Health Problems, Suicidality, and Use of Mental Health Services Among Military Personnel.

PubMed

Chu, Carol; Stanley, Ian H; Hom, Melanie A; Lim, Ingrid C; Joiner, Thomas E

2016-01-01

Following deployment, soldiers may struggle to cope with the after-effects of combat service and experience increased suicidality. Therefore, connection to mental health services is vital. Research regarding the relationship between deployment, suicidality, and mental health connections has been equivocal, with some studies finding a link between deployment history and mental health outcomes, and others not. The purpose of this study was to examine the effects of military deployment on mental health and service utilization outcomes using a longitudinal design. Deployment history, mental health visits, symptoms of suicidality, and various mental health outcomes were assessed in a sample of 1,566 Army recruiters at study entry and 18-months follow-up. Deployment history was positively associated with mental health visits, number of major depressive episodes, and acquired capability for suicide at baseline; however, no significant relationship between deployment, mental health visits, and any other suicide or mental health-related outcomes emerged at baseline or follow-up. Findings suggest a disconnection from mental health services among military personnel. Implications for treatment and suicide prevention efforts among military personnel are discussed.

School re-entry of the pediatric heart transplant recipient.

PubMed

Weil, Constance M; Rodgers, S; Rubovits, S

2006-12-01

Pediatric cardiac transplant has become increasingly frequent in the last decade and survival rates have improved remarkably. Outcome research on this population suggests that the majority of children have the capacity for healthy adaptation although 25-40% have been shown to have some type of psychiatric difficulties. As school plays a major role in these children's lives, early intervention and close liaison with schools is indicated to reduce psychological morbidity, enhance adaptation within the school environment and enhance overall adjustment. This paper proposes a model for a school re-entry program for this population. The school re-entry program is aimed at children who are undergoing cardiac transplant and will be entering or re-entering the school system. They may range in academic age from preschool to college level and have been attending private or public schools with placements in regular education programs, regular education programs with resource support, special education programs, and alternative school programs. Others may not have been attending school because of the severity of their medical condition and have been receiving in-home tutoring. Each child is offered school re-entry assistance by a multi-disciplinary team composed of members from the Cardiology Transplant Service. The re-entry program includes cognitive and psychosocial assessment, liaison with the child's school pre- and post-transplant, academic planning and provision of academic, emotional, and behavioral support before, during, and immediately after transplant, a school re-entry visit, and an ongoing school consultation. The goal is to address issues necessary for a successful school re-entry including appropriate academic placement and support, psychosocial adjustment, education of school personnel and ongoing health needs of the student. The next step is to formally evaluate the efficacy of this program in successful school re-entry.

Development of Test Article Building Block (TABB) for deployable platform systems

NASA Technical Reports Server (NTRS)

Greenberg, H. S.; Barbour, R. T.

1984-01-01

The concept of a Test Article Building Block (TABB) is described. The TABB is a ground test article that is representative of a future building block that can be used to construct LEO and GEO deployable space platforms for communications and scientific payloads. This building block contains a main housing within which the entire structure, utilities, and deployment/retraction mechanism are stowed during launch. The end adapter secures the foregoing components to the housing during launch. The main housing and adapter provide the necessary building-block-to-building-block attachments for automatically deployable platforms. Removal from the shuttle cargo bay can be accomplished with the remote manipulator system (RMS) and/or the handling and positioning aid (HAPA). In this concept, all the electrical connections are in place prior to launch with automatic latches for payload attachment provided on either the end adapters or housings. The housings also can contain orbiter docking ports for payload installation and maintenance.

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.

Flexible Robotic Entry Device for nuclear materials production reactor

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

Heckendorn, F.M.

1988-01-01

The Savannah River Laboratory (SRL) has developed and is implementing a Flexible Robotic Entry Device (FRED) for the nuclear materials production reactors at the Savannah River Plant (SRP). FRED is designed for rapid deployment into confinement areas of operating reactors to assess unknown conditions. A unique ''smart tether'' method has been incorporated into FRED for simultaneous bidirectional transmission of multiple video/audio/control/power signals over a single coaxial cable. 3 figs.

On-Board Entry Trajectory Planning Expanded to Sub-orbital Flight

NASA Technical Reports Server (NTRS)

Lu, Ping; Shen, Zuojun

2003-01-01

A methodology for on-board planning of sub-orbital entry trajectories is developed. The algorithm is able to generate in a time frame consistent with on-board environment a three-degree-of-freedom (3DOF) feasible entry trajectory, given the boundary conditions and vehicle modeling. This trajectory is then tracked by feedback guidance laws which issue guidance commands. The current trajectory planning algorithm complements the recently developed method for on-board 3DOF entry trajectory generation for orbital missions, and provides full-envelope autonomous adaptive entry guidance capability. The algorithm is validated and verified by extensive high fidelity simulations using a sub-orbital reusable launch vehicle model and difficult mission scenarios including failures and aborts.

Handling Qualities of a Capsule Spacecraft During Atmospheric Entry

NASA Technical Reports Server (NTRS)

Bilimoria, Karl D.; Mueller, Eric R.

2010-01-01

A piloted simulation was conducted to study handling qualities for capsule spacecraft entering the Earth s atmosphere. Eight evaluation pilots, including six pilot astronauts, provided Cooper-Harper ratings, workload ratings, and qualitative comments. The simulation began after descending through the atmospheric entry interface point and continued until the drogue parachutes deployed. There were two categories of piloting tasks, both of which required bank angle control. In one task category, the pilot followed a closed-loop bank angle command computed by the backup guidance system to manage g-loads during entry. In the other task category, the pilot used intuitive rules to determine the desired bank angle independently, based on an open-loop schedule of vertical speed, Mach, and total energy specified at several range-to-target gates along the entry trajectory. Pilots were able to accurately track the bank angle guidance commands and steered the capsule toward the recovery site with essentially the same range error as the benchmark autopilot trajectory albeit with substantially higher propellant usage, and the handling qualities for this task were satisfactory. Another key result was that the complex piloting task of atmospheric entry could be performed satisfactorily, even in the presence of large dispersions, by controlling bank angle to follow a simple open-loop schedule.

Parachute Swivel Mechanism for planetary entry

NASA Technical Reports Server (NTRS)

Birner, R.; Kaese, J.; Koller, F.; Muehlner, E.; Luhmann, H.-J.

1993-01-01

A parachute swivel mechanism (PSM) for planetary entry missions such as a Mars probe (MARSNET) or return of cometary material samples (ROSETTA mission) has been developed. The purpose of the PSM is to decouple the spin of the probe from the parachute, with low friction torque, during both the deployment and descent phases. Critical requirements are high shock loads, low friction, low temperatures, and several years of storage in the deep space environment (during the cruise phase of the probe, prior to operation). The design uses a main thrust ball bearing to cope with the load requirement and a smaller thrust ball bearing for guiding of the shaft. Except for use on the Viking and Galileo swivels, it appears that this type of bearing has very rarely been employed in space mechanisms, so that little is known of its friction behavior with dry lubrication. A slip ring assembly allows the transfer of electrical power for post-reefing of the parachute. A test program has been conducted covering the environmental conditions of Mars entry and Earth reentry. This paper describes requirement constraints, model missions of planetary entries, a bearing trade-off, analyses performed, design details, the lubrication system, and test results (friction torque versus load/spin rate). In addition, the design of the test rig is addressed.

Flight Mechanics of the Entry, Descent and Landing of the ExoMars Mission

NASA Technical Reports Server (NTRS)

HayaRamos, Rodrigo; Boneti, Davide

2007-01-01

ExoMars is ESA's current mission to planet Mars. A high mobility rover and a fixed station will be deployed on the surface of Mars. This paper regards the flight mechanics of the Entry, Descent and Landing (EDL) phases used for the mission analysis and design of the Baseline and back-up scenarios of the mission. The EDL concept is based on a ballistic entry, followed by a descent under parachutes and inflatable devices (airbags) for landing. The mission analysis and design is driven by the flexibility in terms of landing site, arrival dates and the very stringent requirement in terms of landing accuracy. The challenging requirements currently imposed to the mission need innovative analysis and design techniques to support system design trade-offs to cope with the variability in entry conditions. The concept of the Global Entry Corridor has been conceived, designed, implemented and successfully validated as a key tool to provide a global picture of the mission capabilities in terms of landing site reachability.

Development of Inflatable Entry Systems Technologies

NASA Technical Reports Server (NTRS)

Player, Charles J.; Cheatwood, F. McNeil; Corliss, James

2005-01-01

Achieving the objectives of NASA s Vision for Space Exploration will require the development of new technologies, which will in turn require higher fidelity modeling and analysis techniques, and innovative testing capabilities. Development of entry systems technologies can be especially difficult due to the lack of facilities and resources available to test these new technologies in mission relevant environments. This paper discusses the technology development process to bring inflatable aeroshell technology from Technology Readiness Level 2 (TRL-2) to TRL-7. This paper focuses mainly on two projects: Inflatable Reentry Vehicle Experiment (IRVE), and Inflatable Aeroshell and Thermal Protection System Development (IATD). The objectives of IRVE are to conduct an inflatable aeroshell flight test that demonstrates exoatmospheric deployment and inflation, reentry survivability and stability, and predictable drag performance. IATD will continue the development of the technology by conducting exploration specific trade studies and feeding forward those results into three more flight tests. Through an examination of these projects, and other potential projects, this paper discusses some of the risks, issues, and unexpected benefits associated with the development of inflatable entry systems technology.

Mars Pathfinder Atmospheric Entry Navigation Operations

NASA Technical Reports Server (NTRS)

Braun, R. D.; Spencer, D. A.; Kallemeyn, P. H.; Vaughan, R. M.

1997-01-01

On July 4, 1997, after traveling close to 500 million km, the Pathfinder spacecraft successfully completed entry, descent, and landing, coming to rest on the surface of Mars just 27 km from its target point. In the present paper, the atmospheric entry and approach navigation activities required in support of this mission are discussed. In particular, the flight software parameter update and landing site prediction analyses performed by the Pathfinder operations navigation team are described. A suite of simulation tools developed during Pathfinder's design cycle, but extendible to Pathfinder operations, are also presented. Data regarding the accuracy of the primary parachute deployment algorithm is extracted from the Pathfinder flight data, demonstrating that this algorithm performed as predicted. The increased probability of mission success through the software parameter update process is discussed. This paper also demonstrates the importance of modeling atmospheric flight uncertainties in the estimation of an accurate landing site. With these atmospheric effects included, the final landed ellipse prediction differs from the post-flight determined landing site by less then 0.5 km in downtrack.

Post-Flight EDL Entry Guidance Performance of the 2011 Mars Science Laboratory Mission

NASA Technical Reports Server (NTRS)

Mendeck, Gavin F.; McGrew, Lynn Craig

2012-01-01

The 2011 Mars Science Laboratory was the first successful Mars mission to attempt a guided entry which safely delivered the rover to a final position approximately 2 km from its target within a touchdown ellipse of 19.1 km x 6.9 km. The Entry Terminal Point Controller guidance algorithm is derived from the final phase Apollo Command Module guidance and, like Apollo, modulates the bank angle to control the range flown. For application to Mars landers which must make use of the tenuous Martian atmosphere, it is critical to balance the lift of the vehicle to minimize the range error while still ensuring a safe deploy altitude. An overview of the process to generate optimized guidance settings is presented, discussing improvements made over the last nine years. Key dispersions driving deploy ellipse and altitude performance are identified. Performance sensitivities including attitude initialization error and the velocity of transition from range control to heading alignment are presented. Just prior to the entry and landing of MSL in August 2012, the EDL team examined minute tuning of the reference trajectory for the selected landing site, analyzed whether adjustment of bank reversal deadbands were necessary, the heading alignment velocity trigger was in union with other parameters to balance the EDL risks, and the vertical L/D command limits. This paper details a preliminary postflight assessment of the telemetry and trajectory reconstruction that is being performed, and updates the information presented in the former paper Entry Guidance for the 2011 Mars Science Laboratory Mission (AIAA Atmospheric Flight Mechanics Conference; 8-11 Aug. 2011; Portland, OR; United States)

Combined Structural and Trajectory Control of Variable-Geometry Planetary Entry Systems

NASA Technical Reports Server (NTRS)

Quadrelli, Marco B.; Pellegrino, Sergio; Kwok, Kawai

2011-01-01

Some of the key challenges of planetary entry are to dissipate the large kinetic energy of the entry vehicle and to land with precision. Past missions to Mars were based on unguided entry, where entry vehicles carried payloads of less than 0.6 T and landed within 100 km of the designated target. The Mars Science Laboratory (MSL) is expected to carry a mass of almost 1 T to within 20 km of the target site. Guided lifting entry is needed to meet these higher deceleration and targeting demands. If the aerodynamic characteristics of the decelerator are variable during flight, more trajectory options are possible, and can be tailored to specific mission requirements. In addition to the entry trajectory modulation, having variable aerodynamic properties will also favor maneuvering of the vehicle prior to descent. For proper supersonic parachute deployment, the vehicle needs to turn to a lower angle of attack. One approach to entry trajectory improvement and angle of attack control is to embed a variable geometry decelerator in the design of the vehicle. Variation in geometry enables the vehicle to adjust its aerodynamic performance continuously without additional fuel cost because only electric power is needed for actuating the mechanisms that control the shape change. Novel structural and control concepts have been developed that enable the decelerator to undergo variation in geometry. Changing the aerodynamic characteristics of a flight vehicle by active means can potentially provide a mechanically simple, affordable, and enabling solution for entry, descent, and landing across a wide range of mission types, sample capture and return, and reentry to Earth, Titan, Venus, or Mars. Unguided ballistic entry is not sufficient to meet this more stringent deceleration, heating, and targeting demands. Two structural concepts for implementing the cone angle variation, a segmented shell, and a corrugated shell, have been presented.

Entry vehicle performance analysis and atmospheric guidance algorithm for precision landing on Mars. M.S. Thesis - Massachusetts Inst. of Technology

NASA Technical Reports Server (NTRS)

Dieriam, Todd A.

1990-01-01

Future missions to Mars may require pin-point landing precision, possibly on the order of tens of meters. The ability to reach a target while meeting a dynamic pressure constraint to ensure safe parachute deployment is complicated at Mars by low atmospheric density, high atmospheric uncertainty, and the desire to employ only bank angle control. The vehicle aerodynamic performance requirements and guidance necessary for 0.5 to 1.5 lift drag ratio vehicle to maximize the achievable footprint while meeting the constraints are examined. A parametric study of the various factors related to entry vehicle performance in the Mars environment is undertaken to develop general vehicle aerodynamic design requirements. The combination of low lift drag ratio and low atmospheric density at Mars result in a large phugoid motion involving the dynamic pressure which complicates trajectory control. Vehicle ballistic coefficient is demonstrated to be the predominant characteristic affecting final dynamic pressure. Additionally, a speed brake is shown to be ineffective at reducing the final dynamic pressure. An adaptive precision entry atmospheric guidance scheme is presented. The guidance uses a numeric predictor-corrector algorithm to control downrange, an azimuth controller to govern crossrange, and analytic control law to reduce the final dynamic pressure. Guidance performance is tested against a variety of dispersions, and the results from selected tests are presented. Precision entry using bank angle control only is demonstrated to be feasible at Mars.

Entry Descent and Landing Workshop Proceedings. Volume 1; Inflatable Reentry Vehicle Experiment-3 (IRVE-3) Project Overview & Instrumentation

NASA Technical Reports Server (NTRS)

Dillman, Robert

2015-01-01

Entry mass at Mars is limited by the payload size that can be carried by a rigid capsule that can fit inside the launch vehicle fairing. Landing altitude at Mars is limited by ballistic coefficient (mass per area) of entry body. Inflatable technologies allow payload to use full diameter of launch fairing, and deploy larger aeroshell before atmospheric interface, landing more payload at a higher altitude. Also useful for return of large payloads from Low Earth Orbit (LEO).

Orion Entry Flight Control Stability and Performance

NASA Technical Reports Server (NTRS)

Strahan, Alan L.; Loe, Greg R.; Seiler, Pete

2007-01-01

The Orion Spacecraft will be required to perform entry and landing functions for both Low Earth Orbit (LEO) and Lunar return missions, utilizing only the Command Module (CM) with its unique systems and GN&C design. This paper presents the current CM Flight Control System (FCS) design to support entry and landing, with a focus on analyses that have supported its development to date. The CM FCS will have to provide for spacecraft stability and control while following guidance or manual commands during exo-atmospheric flight, after Service Module separation, translational powered flight required of the CM, atmospheric flight supporting both direct entry and skip trajectories down to drogue chute deploy, and during roll attitude reorientation just prior to touchdown. Various studies and analyses have been performed or are on-going supporting an overall FCS design with reasonably sized Reaction Control System (RCS) jets, that minimizes fuel usage, that provides appropriate command following but with reasonable stability and control margin. Results from these efforts to date are included, with particular attention on design issues that have emerged, such as the struggle to accommodate sub-sonic pitch and yaw control without using excessively large jets that could have a detrimental impact on vehicle weight. Apollo, with a similar shape, struggled with this issue as well. Outstanding CM FCS related design and analysis issues, planned for future effort, are also briefly be discussed.

An adaptive signal-processing approach to online adaptive tutoring.

PubMed

Bergeron, Bryan; Cline, Andrew

2011-01-01

Conventional intelligent or adaptive tutoring online systems rely on domain-specific models of learner behavior based on rules, deep domain knowledge, and other resource-intensive methods. We have developed and studied a domain-independent methodology of adaptive tutoring based on domain-independent signal-processing approaches that obviate the need for the construction of explicit expert and student models. A key advantage of our method over conventional approaches is a lower barrier to entry for educators who want to develop adaptive online learning materials.

System definition study of deployable, non-metallic space structures

NASA Technical Reports Server (NTRS)

Stimler, F. J.

1984-01-01

The state of the art for nonmetallic materials and fabrication techniques suitable for future space structures are summarized. Typical subsystems and systems of interest to the space community that are reviewed include: (1) inflatable/rigidized space hangar; (2) flexible/storable acoustic barrier; (3) deployable fabric bulkhead in a space habitat; (4) extendible tunnel for soft docking; (5) deployable space recovery/re-entry systems for personnel or materials; (6) a manned habitat for a space station; (7) storage enclosures external to the space station habitat; (8) attachable work stations; and (9) safe haven structures. Performance parameters examined include micrometeoroid protection; leakage rate prediction and control; rigidization of flexible structures in the space environment; flammability and offgassing; lifetime for nonmetallic materials; crack propagation prevention; and the effects of atomic oxygen and space debris. An expandable airlock for shuttle flight experiments and potential tethered experiments from shuttle are discussed.

Aerodynamic Challenges for the Mars Science Laboratory Entry, Descent and Landing

NASA Technical Reports Server (NTRS)

Schoenenberger, Mark; Dyakonov, Artem; Buning, Pieter; Scallion, William; Norman, John Van

2009-01-01

An overview of several important aerodynamics challenges new to the Mars Science Laboratory (MSL) entry vehicle are presented. The MSL entry capsule is a 70 degree sphere cone-based on the original Mars Viking entry capsule. Due to payload and landing accuracy requirements, MSL will be flying at the highest lift-to-drag ratio of any capsule sent to Mars (L/D = 0.24). The capsule will also be flying a guided entry, performing bank maneuvers, a first for Mars entry. The system's mechanical design and increased performance requirements require an expansion of the MSL flight envelope beyond those of historical missions. In certain areas, the experience gained by Viking and other recent Mars missions can no longer be claimed as heritage information. New analysis and testing is re1quired to ensure the safe flight of the MSL entry vehicle. The challenge topics include: hypersonic gas chemistry and laminar-versus-turbulent flow effects on trim angle, a general risk assessment of flying at greater angles-of-attack than Viking, quantifying the aerodynamic interactions induced by a new reaction control system and a risk assessment of recontact of a series of masses jettisoned prior to parachute deploy. An overview of the analysis and tests being conducted to understand and reduce risk in each of these areas is presented. The need for proper modeling and implementation of uncertainties for use in trajectory simulation has resulted in a revision of prior models and additional analysis for the MSL entry vehicle. The six degree-of-freedom uncertainty model and new analysis to quantify roll torque dispersions are presented.

Overview of the Phoenix Entry, Descent and Landing System Architecture

NASA Technical Reports Server (NTRS)

Grover, Myron R., III; Cichy, Benjamin D.; Desai, Prasun N.

2008-01-01

NASA s Phoenix Mars Lander began its journey to Mars from Cape Canaveral, Florida in August 2007, but its journey to the launch pad began many years earlier in 1997 as NASA s Mars Surveyor Program 2001 Lander. In the intervening years, the entry, descent and landing (EDL) system architecture went through a series of changes, resulting in the system flown to the surface of Mars on May 25th, 2008. Some changes, such as entry velocity and landing site elevation, were the result of differences in mission design. Other changes, including the removal of hypersonic guidance, the reformulation of the parachute deployment algorithm, and the addition of the backshell avoidance maneuver, were driven by constant efforts to augment system robustness. An overview of the Phoenix EDL system architecture is presented along with rationales driving these architectural changes.

ADEPT Heat Shield Testing

NASA Image and Video Library

2015-10-16

NASA is developing the next generation of heat shield to enable astronauts to go to Mars and other deep space destinations. Called the Adaptive Deployable Entry and Placement Technology or ADEPT, the heat shield is mechanically deployable and uses a flexible woven carbon fabric as its skin. Recently, engineers successfully completed a series of tests in the Ames Arc Jet facility. Other tests conducted in wind tunnels at Ames demonstrated that the ADEPT materials and system perform well under planetary re-entry conditions.

Very Low Head Turbine Deployment in Canada

NASA Astrophysics Data System (ADS)

Kemp, P.; Williams, C.; Sasseville, Remi; Anderson, N.

2014-03-01

The Very Low Head (VLH) turbine is a recent turbine technology developed in Europe for low head sites in the 1.4 - 4.2 m range. The VLH turbine is primarily targeted for installation at existing hydraulic structures to provide a low impact, low cost, yet highly efficient solution. Over 35 VLH turbines have been successfully installed in Europe and the first VLH deployment for North America is underway at Wasdell Falls in Ontario, Canada. Deployment opportunities abound in Canada with an estimated 80,000 existing structures within North America for possible low-head hydro development. There are several new considerations and challenges for the deployment of the VLH turbine technology in Canada in adapting to the hydraulic, environmental, electrical and social requirements. Several studies were completed to determine suitable approaches and design modifications to mitigate risk and confirm turbine performance. Diverse types of existing weirs and spillways pose certain hydraulic design challenges. Physical and numerical modelling of the VLH deployment alternatives provided for performance optimization. For this application, studies characterizing the influence of upstream obstacles using water tunnel model testing as well as full-scale prototype flow dynamics testing were completed. A Cold Climate Adaptation Package (CCA) was developed to allow year-round turbine operation in ice covered rivers. The CCA package facilitates turbine extraction and accommodates ice forces, frazil ice, ad-freezing and cold temperatures that are not present at the European sites. The Permanent Magnet Generator (PMG) presents some unique challenges in meeting Canadian utility interconnection requirements. Specific attention to the frequency driver control and protection requirements resulted in a driver design with greater over-voltage capability for the PMG as well as other key attributes. Environmental studies in Europe included fish friendliness testing comprised of multiple in

Deployable Crew Quarters

NASA Technical Reports Server (NTRS)

Izenson, Michael G.; Chen, Weibo

2008-01-01

The deployable crew quarters (DCQ) have been designed for the International Space Station (ISS). Each DCQ would be a relatively inexpensive, deployable boxlike structure that is designed to fit in a rack bay. It is to be occupied by one crewmember to provide privacy and sleeping functions for the crew. A DCQ comprises mostly hard panels, made of a lightweight honeycomb or matrix/fiber material, attached to each other by cloth hinges. Both faces of each panel are covered with a layer of Nomex cloth and noise-suppression material to provide noise isolation from ISS. On Earth, the unit is folded flat and attached to a rigid pallet for transport to the ISS. On the ISS, crewmembers unfold the unit and install it in place, attaching it to ISS structural members by use of soft cords (which also help to isolate noise and vibration). A few hard pieces of equipment (principally, a ventilator and a smoke detector) are shipped separately and installed in the DCQ unit by use of a system of holes, slots, and quarter-turn fasteners. Full-scale tests showed that the time required to install a DCQ unit amounts to tens of minutes. The basic DCQ design could be adapted to terrestrial applications to satisfy requirements for rapid deployable emergency shelters that would be lightweight, portable, and quickly erected. The Temporary Early Sleep Station (TeSS) currently on-orbit is a spin-off of the DCQ.

Mechanism of HSV infection through soluble adapter-mediated virus bridging to the EGF receptor

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

Nakano, Kenji, E-mail: kenakano@med.kyushu-u.ac.j; Kobayashi, Masatoshi; Nakamura, Kei-ichiro

2011-04-25

Herpes simplex virus entry into cells requires the binding of envelope glycoprotein D (gD) to an entry receptor. Depending on the cell, entry occurs by different mechanisms, including fusion at the cell surface or endocytosis. Here we examined the entry mechanism through a non-HSV receptor mediated by a soluble bi-specific adapter protein composed of recognition elements for gD and the EGF receptor (EGFR). Virus entered into endosomes using either EGF or an EGFR-specific single chain antibody (scFv) for receptor recognition. Infection was less efficient with the EGF adapter which could be attributed to its weaker binding to a viral gD.more » Infection mediated by the scFv adapter was pH sensitive, indicating that gD-EGFR bridging alone was insufficient for capsid release from endosomes. We also show that the scFv adapter enhanced infection of EGFR-expressing tumor tissue in vivo. Our results indicate that adapters may retarget HSV infection without drastically changing the entry mechanism.« less

Associations of contextual risk and protective factors with fathers’ parenting practices in the post-deployment environment

PubMed Central

Davis, Laurel; Hanson, Sheila K.; Zamir, Osnat; Gewirtz, Abigail H.; DeGarmo, David S.

2015-01-01

Deployment separation and reunifications are salient contexts that directly impact effective family functioning and parenting for military fathers. Yet, we know very little about determinants of post-deployed father involvement and effective parenting. The present study examined hypothesized risk and protective factors of observed parenting for 282 post-deployed fathers who served in the Army National Guard/Reserves. Pre-intervention data were employed from fathers participating in the After Deployment, Adaptive Parenting Tools (ADAPT) randomized control trial. Parenting practices were obtained from direct observation of father-child interaction and included measures of problem solving, harsh discipline, positive involvement, encouragement, and monitoring. Risk factors included combat exposure, negative life events, months deployed, and PTSD symptoms. Protective factors included education, income, dyadic adjustment, and social support. Results of a structural equation model predicting an effective parenting construct indicated that months deployed, income, and father age were most related to observed parenting, explaining 16% of the variance. We are aware of no other study utilizing direct parent-child observations of father’s parenting skills following overseas deployment. Implications for practice and preventive intervention are discussed. PMID:26213794

Terminal altitude maximization for Mars entry considering uncertainties

NASA Astrophysics Data System (ADS)

Cui, Pingyuan; Zhao, Zeduan; Yu, Zhengshi; Dai, Juan

2018-04-01

Uncertainties present in the Mars atmospheric entry process may cause state deviations from the nominal designed values, which will lead to unexpected performance degradation if the trajectory is designed merely based on the deterministic dynamic model. In this paper, a linear covariance based entry trajectory optimization method is proposed considering the uncertainties presenting in the initial states and parameters. By extending the elements of the state covariance matrix as augmented states, the statistical behavior of the trajectory is captured to reformulate the performance metrics and path constraints. The optimization problem is solved by the GPOPS-II toolbox in MATLAB environment. Monte Carlo simulations are also conducted to demonstrate the capability of the proposed method. Primary trading performances between the nominal deployment altitude and its dispersion can be observed by modulating the weights on the dispersion penalty, and a compromised result referring to maximizing the 3σ lower bound of the terminal altitude is achieved. The resulting path constraints also show better satisfaction in a disturbed environment compared with the nominal situation.

Adaptation Scolaire: Bibliographie annotee (Scholastic Adaptation: Annotated Bibliography).

ERIC Educational Resources Information Center

Alberta Dept. of Education, Edmonton. Language Services Branch.

This annotated bibliography on resources concerning scholastic adaptation for students with exceptionalities was based on information collected by the Alberta Ministry of Education (Candada) from publishing houses and university presses. From the 350 submissions received, the 42 entries in this bibliography represent the materials chosen as the…

A tape-spring hexapod for deployable telescopes: dynamics

NASA Astrophysics Data System (ADS)

Blanchard, L.; Aridon, G.; Falzon, F.; Rémond, D.; Dufour, R.

2017-11-01

An hexapod based telescope concept whose legs are deployable has been investigated in order to stow the secondary mirror during launch and to self-deploy it in orbit The main advantages of this concept are: a reduced volume for launch with high reduction of passive stability requirements, mass and inertia reduction inducing an agility gain. The positioning errors are corrected thanks to the vertical displacement of the hexapod feet and the final optical performance is reached thanks to adaptive optics. The paper presents the first steps towards the optimal design of a breadboard and the method developed to model the dynamic behaviour of such a structure with highly deformed flexible elements and validated with the results of sine vibration testing of the hexapod. The following part deals with the evaluation of its deployment and correction capabilities.

Development of Thermal Protection Materials for Future Mars Entry, Descent and Landing Systems

NASA Technical Reports Server (NTRS)

Cassell, Alan M.; Beck, Robin A. S.; Arnold, James O.; Hwang, Helen; Wright, Michael J.; Szalai, Christine E.; Blosser, Max; Poteet, Carl C.

2010-01-01

Entry Systems will play a crucial role as NASA develops the technologies required for Human Mars Exploration. The Exploration Technology Development Program Office established the Entry, Descent and Landing (EDL) Technology Development Project to develop Thermal Protection System (TPS) materials for insertion into future Mars Entry Systems. An assessment of current entry system technologies identified significant opportunity to improve the current state of the art in thermal protection materials in order to enable landing of heavy mass (40 mT) payloads. To accomplish this goal, the EDL Project has outlined a framework to define, develop and model the thermal protection system material concepts required to allow for the human exploration of Mars via aerocapture followed by entry. Two primary classes of ablative materials are being developed: rigid and flexible. The rigid ablatives will be applied to the acreage of a 10x30 m rigid mid L/D Aeroshell to endure the dual pulse heating (peak approx.500 W/sq cm). Likewise, flexible ablative materials are being developed for 20-30 m diameter deployable aerodynamic decelerator entry systems that could endure dual pulse heating (peak aprrox.120 W/sq cm). A technology Roadmap is presented that will be used for facilitating the maturation of both the rigid and flexible ablative materials through application of decision metrics (requirements, key performance parameters, TRL definitions, and evaluation criteria) used to assess and advance the various candidate TPS material technologies.

Development of the Aquarius Antenna Deployment Mechanisms and Spring/Damper Actuator

NASA Technical Reports Server (NTRS)

Johnson, Joel A.

2008-01-01

The Aquarius Instrument s large radar reflector dish needed to be stowed for launch, and then deployed on-orbit. The Deployment Subsystem consisted of a cantilevered boom structure and two single-axis hinge mechanisms to accurately deploy and position the reflector dish relative to the radar feed horns. The cantilevered design demanded high stiffness and accuracy from the deployment mechanism at the root of the boom. A preload-generating end-of-travel latch was also required. To largely eliminate the need for control systems, each deployment mechanism was actuated by a passive spring motor with viscous-fluid damping. Tough requirements and adaptation of a heritage actuator to the new application resulted in numerous challenges. Fabrication, assembly, and testing encountered additional problems, though ultimately the system was demonstrated very successfully. This paper revisits the development to highlight which design concepts worked and the many important lessons learned.

Archaeal viruses at the cell envelope: entry and egress

PubMed Central

Quemin, Emmanuelle R. J.; Quax, Tessa E. F.

2015-01-01

The cell envelope represents the main line of host defense that viruses encounter on their way from one cell to another. The cytoplasmic membrane in general is a physical barrier that needs to be crossed both upon viral entry and exit. Therefore, viruses from the three domains of life employ a wide range of strategies for perforation of the cell membrane, each adapted to the cell surface environment of their host. Here, we review recent insights on entry and egress mechanisms of viruses infecting archaea. Due to the unique nature of the archaeal cell envelope, these particular viruses exhibit novel and unexpected mechanisms to traverse the cellular membrane. PMID:26097469

5. PORTICO AND ENTRY DETAIL, SOUTH (FRONT) ELEVATION. This entry ...

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

5. PORTICO AND ENTRY DETAIL, SOUTH (FRONT) ELEVATION. This entry replaces original twin entries to southeast and southwest rooms from portico, and was installed when south entry hall was built. - Oak Island (House), County Road 768 vicinity, Edisto Island, Charleston County, SC

Taking it to the streets: delivering on deployment.

PubMed

Carr, Dafna; Welch, Vickie; Fabik, Trish; Hirji, Nadir; O'Connor, Casey

2009-01-01

From inception to deployment, the Wait Time Information System (WTIS) project faced significant challenges associated with time, scope and complexity. It involved not only the creation and deployment of two large-scale province-wide systems (the WTIS and Ontario's Client Registry/Enterprise Master Patient Index) within aggressive time frames, but also the active engagement of 82 Ontario hospitals, scores of healthcare leaders and several thousand clinicians who would eventually be using the new technology and its data. The provincial WTIS project team (see Figure 1) also had to be able to adapt and evolve their planning in an environment that was changing day-by-day. This article looks at the factors that allowed the team to take the WTIS out to the field and shares the approach, processes and tools used to deploy this complex and ambitious information management and information technology (IM/IT) initiative.

Regular Deployment of Wireless Sensors to Achieve Connectivity and Information Coverage

PubMed Central

Cheng, Wei; Li, Yong; Jiang, Yi; Yin, Xipeng

2016-01-01

Coverage and connectivity are two of the most critical research subjects in WSNs, while regular deterministic deployment is an important deployment strategy and results in some pattern-based lattice WSNs. Some studies of optimal regular deployment for generic values of rc/rs were shown recently. However, most of these deployments are subject to a disk sensing model, and cannot take advantage of data fusion. Meanwhile some other studies adapt detection techniques and data fusion to sensing coverage to enhance the deployment scheme. In this paper, we provide some results on optimal regular deployment patterns to achieve information coverage and connectivity as a variety of rc/rs, which are all based on data fusion by sensor collaboration, and propose a novel data fusion strategy for deployment patterns. At first the relation between variety of rc/rs and density of sensors needed to achieve information coverage and connectivity is derived in closed form for regular pattern-based lattice WSNs. Then a dual triangular pattern deployment based on our novel data fusion strategy is proposed, which can utilize collaborative data fusion more efficiently. The strip-based deployment is also extended to a new pattern to achieve information coverage and connectivity, and its characteristics are deduced in closed form. Some discussions and simulations are given to show the efficiency of all deployment patterns, including previous patterns and the proposed patterns, to help developers make more impactful WSN deployment decisions. PMID:27529246

Intelligent transportation systems for work zones : deployment benefits and lessons learned

DOT National Transportation Integrated Search

2000-12-01

This paper presents what has been learned in four principal areas of arterial management: 1) adaptive control strategies; 2) advanced traveler information systems; 3) automated enforcement; and 4) integration. The levels of deployment, benefits, depl...

Comparative Analysis of Host Cell Entry of Ebola Virus From Sierra Leone, 2014, and Zaire, 1976.

PubMed

Hofmann-Winkler, Heike; Gnirß, Kerstin; Wrensch, Florian; Pöhlmann, Stefan

2015-10-01

The ongoing Ebola virus (EBOV) disease (EVD) epidemic in Western Africa is the largest EVD outbreak recorded to date and requires the rapid development and deployment of antiviral measures. The viral glycoprotein (GP) facilitates host cell entry and, jointly with cellular interaction partners, constitutes a potential target for antiviral intervention. However, it is unknown whether the GPs of the currently and previously circulating EBOVs use the same mechanisms for cellular entry and are thus susceptible to inhibition by the same antivirals and cellular defenses. Here, we show that the GPs of the EBOVs circulating in 1976 and 2014 transduce the same spectrum of target cells, use the same cellular factors for host cell entry, and are comparably susceptible to blockade by antiviral interferon-induced transmembrane proteins and neutralizing antibody KZ52. Thus, the viruses responsible for the ongoing EVD epidemic should be fully susceptible to established antiviral strategies targeting GP and cellular entry factors. © The Author 2015. Published by Oxford University Press on behalf of the Infectious Diseases Society of America.

Parallel, Gradient-Based Anisotropic Mesh Adaptation for Re-entry Vehicle Configurations

NASA Technical Reports Server (NTRS)

Bibb, Karen L.; Gnoffo, Peter A.; Park, Michael A.; Jones, William T.

2006-01-01

Two gradient-based adaptation methodologies have been implemented into the Fun3d refine GridEx infrastructure. A spring-analogy adaptation which provides for nodal movement to cluster mesh nodes in the vicinity of strong shocks has been extended for general use within Fun3d, and is demonstrated for a 70 sphere cone at Mach 2. A more general feature-based adaptation metric has been developed for use with the adaptation mechanics available in Fun3d, and is applicable to any unstructured, tetrahedral, flow solver. The basic functionality of general adaptation is explored through a case of flow over the forebody of a 70 sphere cone at Mach 6. A practical application of Mach 10 flow over an Apollo capsule, computed with the Felisa flow solver, is given to compare the adaptive mesh refinement with uniform mesh refinement. The examples of the paper demonstrate that the gradient-based adaptation capability as implemented can give an improvement in solution quality.

Flexible robotic entry device for a nuclear materials production reactor

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

Heckendorn, F.M. II

1988-01-01

The Savannah River Laboratory has developed and is implementing a flexible robotic entry device (FRED) for the nuclear materials production reactors now operating at the Savannah River Plant (SRP). FRED is designed for rapid deployment into confinement areas of operating reactors to assess unknown conditions. A unique smart tether method has been incorporated into FRED for simultaneous bidirectional transmission of multiple video/audio/control/power signals over a single coaxial cable. This system makes it possible to use FRED under all operating and standby conditions, including those where radio/microwave transmissions are not possible or permitted, and increases the quantity of data available.

Disposable telemetry cable deployment system

DOEpatents

Holcomb, David Joseph

2000-01-01

A disposable telemetry cable deployment system for facilitating information retrieval while drilling a well includes a cable spool adapted for insertion into a drill string and an unarmored fiber optic cable spooled onto the spool cable and having a downhole end and a stinger end. Connected to the cable spool is a rigid stinger which extends through a kelly of the drilling apparatus. A data transmission device for transmitting data to a data acquisition system is disposed either within or on the upper end of the rigid stinger.

Solar Adaptive Optics.

PubMed

Rimmele, Thomas R; Marino, Jose

Adaptive optics (AO) has become an indispensable tool at ground-based solar telescopes. AO enables the ground-based observer to overcome the adverse effects of atmospheric seeing and obtain diffraction limited observations. Over the last decade adaptive optics systems have been deployed at major ground-based solar telescopes and revitalized ground-based solar astronomy. The relatively small aperture of solar telescopes and the bright source make solar AO possible for visible wavelengths where the majority of solar observations are still performed. Solar AO systems enable diffraction limited observations of the Sun for a significant fraction of the available observing time at ground-based solar telescopes, which often have a larger aperture than equivalent space based observatories, such as HINODE. New ground breaking scientific results have been achieved with solar adaptive optics and this trend continues. New large aperture telescopes are currently being deployed or are under construction. With the aid of solar AO these telescopes will obtain observations of the highly structured and dynamic solar atmosphere with unprecedented resolution. This paper reviews solar adaptive optics techniques and summarizes the recent progress in the field of solar adaptive optics. An outlook to future solar AO developments, including a discussion of Multi-Conjugate AO (MCAO) and Ground-Layer AO (GLAO) will be given. Supplementary material is available for this article at 10.12942/lrsp-2011-2.

Analysis of spacecraft entry into Mars atmosphere

NASA Astrophysics Data System (ADS)

Nakajima, Ken; Nagano, Koutarou

1991-07-01

The effects on a spacecraft body while entering the Martian atmosphere and the resulting design constraints are analyzed. The analyses are conducted using the Viking entry phase restriction conditions and a Mars atmosphere model. Results from analysis conducted by the Program to Optimize Simulated Trajectories (POST) are described. Results obtained from the analysis are as follows: (1) flight times depend greatly on lift-to-drag ratio and less on ballistic coefficients; (2) terminal landing speeds depend greatly on ballistic coefficients and less on lift-to-drag ratios; (3) the dependence of the flight path angles on ballistic coefficients is slightly larger than their dependence on lift-to-drag ratios; (4) as the ballistic coefficients become smaller and the lift-to-drag ratios become larger, the deceleration at high altitude becomes larger; (5) small ballistic coefficients and low lift-to-drag ratios are required to meet the constraints of Mach number at parachute deployment and deployment altitude; and (6) heating rates at stagnation points are dependent on ballistic coefficients. It is presumed that the aerodynamic characteristics will be 0.2 for the lift-to-drag ratio and 75 kg/sq m for the ballistic coefficient for the case of a Mars landing using capsules similar to those used in the Viking program.

Heart rate variability: Pre-deployment predictor of post-deployment PTSD symptoms

PubMed Central

Pyne, Jeffrey M.; Constans, Joseph I.; Wiederhold, Mark D.; Gibson, Douglas P.; Kimbrell, Timothy; Kramer, Teresa L.; Pitcock, Jeffery A.; Han, Xiaotong; Williams, D. Keith; Chartrand, Don; Gevirtz, Richard N.; Spira, James; Wiederhold, Brenda K.; McCraty, Rollin; McCune, Thomas R.

2017-01-01

Heart rate variability is a physiological measure associated with autonomic nervous system activity. This study hypothesized that lower pre-deployment HRV would be associated with higher post-deployment post-traumatic stress disorder (PTSD) symptoms. Three-hundred-forty-three Army National Guard soldiers enrolled in the Warriors Achieving Resilience (WAR) study were analyzed. The primary outcome was PTSD symptom severity using the PTSD Checklist – Military version (PCL) measured at baseline, 3- and 12-month post-deployment. Heart rate variability predictor variables included: high frequency power (HF) and standard deviation of the normal cardiac inter-beat interval (SDNN). Generalized linear mixed models revealed that the pre-deployment PCL*ln(HF) interaction term was significant (p < 0.0001). Pre-deployment SDNN was not a significant predictor of post-deployment PCL. Covariates included age, pre-deployment PCL, race/ethnicity, marital status, tobacco use, childhood abuse, pre-deployment traumatic brain injury, and previous combat zone deployment. Pre-deployment heart rate variability predicts post-deployment PTSD symptoms in the context of higher pre-deployment PCL scores. PMID:27773678

Influence of seasonal cycles in Martian atmosphere on entry, descent and landing sequence

NASA Astrophysics Data System (ADS)

Marčeta, Dušan; Šegan, Stevo; Rašuo, Boško

2014-05-01

The phenomena like high eccentricity of Martian orbit, obliquity of the orbital plane and close alignment of the winter solstice and the orbital perihelion, separately or together can significantly alter not only the level of some Martian atmospheric parameters but also the characteristics of its diurnal and seasonal cycle. Considering that entry, descent and landing (EDL) sequence is mainly driven by the density profile of the atmosphere and aerodynamic characteristic of the entry vehicle. We have performed the analysis of the influence of the seasonal cycles of the atmospheric parameters on EDL profiles by using Mars Global Reference Atmospheric Model (Mars-GRAM). Since the height of the deployment of the parachute and the time passed from the deployment to propulsion firing (descent time) are of crucial importance for safe landing and the achievable landing site elevation we paid special attention to the influence of the areocentric longitude of the Sun (Ls) on these variables. We have found that these variables have periodic variability with respect to Ls and can be very well approximated with a sine wave function whose mean value depends only on the landing site elevation while the amplitudes and phases depend only on the landing site latitude. The amplitudes exhibit behavior which is symmetric with respect to the latitude but the symmetry is shifted from the equator to the northern mid-tropics. We have also noticed that the strong temperature inversions which are usual for middle and higher northern latitudes while Mars is around its orbital perihelion significantly alter the descent time without influencing the height of the parachute deployment. At last, we applied our model to determine the dependence of the accessible landing region on Ls and found that this region reaches maximum when Mars is around the orbital perihelion and can vary 50° in latitude throughout the Martian year.

USDOT guidance summary for connected vehicle deployments : application deployment.

DOT National Transportation Integrated Search

2016-07-01

This document provides guidance material in regards to the Application Deployment Plan for the CV Pilots DeploymentConcept Development Phase. Methods for application deployment are discussed with definitions for the successfulmanagement of each aspec...

A Cross-site Qualitative Study of Physician Order Entry

PubMed Central

Ash, Joan S.; Gorman, Paul N.; Lavelle, Mary; Payne, Thomas H.; Massaro, Thomas A.; Frantz, Gerri L.; Lyman, Jason A.

2003-01-01

Objective: To describe the perceptions of diverse professionals involved in computerized physician order entry (POE) at sites where POE has been successfully implemented and to identify differences between teaching and nonteaching hospitals. Design: A multidisciplinary team used observation, focus groups, and interviews with clinical, administrative, and information technology staff to gather data at three sites. Field notes and transcripts were coded using an inductive approach to identify patterns and themes in the data. Measurements: Patterns and themes concerning perceptions of POE were identified. Results: Four high-level themes were identified: (1) organizational issues such as collaboration, pride, culture, power, politics, and control; (2) clinical and professional issues involving adaptation to local practices, preferences, and policies; (3) technical/implementation issues, including usability, time, training and support; and (4) issues related to the organization of information and knowledge, such as system rigidity and integration. Relevant differences between teaching and nonteaching hospitals include extent of collaboration, staff longevity, and organizational missions. Conclusion: An organizational culture characterized by collaboration and trust and an ongoing process that includes active clinician engagement in adaptation of the technology were important elements in successful implementation of physician order entry at the institutions that we studied. PMID:12595408

USDOT guidance summary for connected vehicle deployments : deployment outreach.

DOT National Transportation Integrated Search

2016-07-01

This document provides guidance material in regards to the outreach activities in the CV Pilot Deployment ConceptDevelopment Phase and deployment outreach plan in the Deployment Phases. This guidance provides keyrequirements and references in develop...

Direct-to-Earth Communications with Mars Science Laboratory During Entry, Descent, and Landing

NASA Technical Reports Server (NTRS)

Soriano, Melissa; Finley, Susan; Fort, David; Schratz, Brian; Ilott, Peter; Mukai, Ryan; Estabrook, Polly; Oudrhiri, Kamal; Kahan, Daniel; Satorius, Edgar

2013-01-01

Mars Science Laboratory (MSL) undergoes extreme heating and acceleration during Entry, Descent, and Landing (EDL) on Mars. Unknown dynamics lead to large Doppler shifts, making communication challenging. During EDL, a special form of Multiple Frequency Shift Keying (MFSK) communication is used for Direct-To-Earth (DTE) communication. The X-band signal is received by the Deep Space Network (DSN) at the Canberra Deep Space Communication complex, then down-converted, digitized, and recorded by open-loop Radio Science Receivers (RSR), and decoded in real-time by the EDL Data Analysis (EDA) System. The EDA uses lock states with configurable Fast Fourier Transforms to acquire and track the signal. RSR configuration and channel allocation is shown. Testing prior to EDL is discussed including software simulations, test bed runs with MSL flight hardware, and the in-flight end-to-end test. EDA configuration parameters and signal dynamics during pre-entry, entry, and parachute deployment are analyzed. RSR and EDA performance during MSL EDL is evaluated, including performance using a single 70-meter DSN antenna and an array of two 34-meter DSN antennas as a back up to the 70-meter antenna.

Adaptation of a web-based, open source electronic medical record system platform to support a large study of tuberculosis epidemiology

PubMed Central

2012-01-01

Background In 2006, we were funded by the US National Institutes of Health to implement a study of tuberculosis epidemiology in Peru. The study required a secure information system to manage data from a target goal of 16,000 subjects who needed to be followed for at least one year. With previous experience in the development and deployment of web-based medical record systems for TB treatment in Peru, we chose to use the OpenMRS open source electronic medical record system platform to develop the study information system. Supported by a core technical and management team and a large and growing worldwide community, OpenMRS is now being used in more than 40 developing countries. We adapted the OpenMRS platform to better support foreign languages. We added a new module to support double data entry, linkage to an existing laboratory information system, automatic upload of GPS data from handheld devices, and better security and auditing of data changes. We added new reports for study managers, and developed data extraction tools for research staff and statisticians. Further adaptation to handle direct entry of laboratory data occurred after the study was launched. Results Data collection in the OpenMRS system began in September 2009. By August 2011 a total of 9,256 participants had been enrolled, 102,274 forms and 13,829 laboratory results had been entered, and there were 208 users. The system is now entirely supported by the Peruvian study staff and programmers. Conclusions The information system served the study objectives well despite requiring some significant adaptations mid-stream. OpenMRS has more tools and capabilities than it did in 2008, and requires less adaptations for future projects. OpenMRS can be an effective research data system in resource poor environments, especially for organizations using or considering it for clinical care as well as research. PMID:23131180

Post-deployment Mental Health in Reserve and National Guard Service Members: Deploying With or Without One's Unit and Deployment Preparedness.

PubMed

Ursano, Robert J; Wang, Jing; Fullerton, Carol S; Ramsawh, Holly; Gifford, Robert K; Russell, Dale; Cohen, Gregory H; Sampson, Laura; Galea, Sandro

2018-01-01

Given the greater prevalence of post-deployment mental health concerns among reservists, the higher likelihood of deploying without their regular unit, and potentially lower rates of deployment preparedness, we examined associations between deploying with or without one's regular unit (individual augmentee status, IAS), deployment preparedness, and mental health problems including post-traumatic stress disorder (PTSD), depression (MDD), and binge drinking in a nationally representative sample of Reserve Component (RC) Army and Marine-enlisted males (n = 705). A series of multivariate regressions examined the association of mental health with IAS and deployment preparedness, adjusting for demographics. To examine whether deployment preparedness varied by IAS, an IAS × deployment preparedness interaction was included. In an adjusted model, being an individual augmentee and low deployment preparedness were associated with any mental health problem (screening positive for PTSD, MDD, binge drinking, or any combination of the three). There was a significant IAS × deployment preparedness interaction. Mental health problems did not vary by preparedness among individual augmentees. Participants deploying with regular units with low-medium preparedness had greater risk for mental health problems (odds ratio [OR] = 3.69, 95% confidence interval [CI] = 1.78-7.62 and OR = 2.29, 95% CI = 1.12-4.71), than those with high preparedness. RC-enlisted male personnel who deployed without their regular unit were five times more likely to have a mental health problem, and were 61% more likely to report binge drinking. Additionally, those with lower levels of deployment preparedness were up to three times more likely to have a mental health problem and up to six times more likely to report PTSD. The current investigation found that both IAS and deployment preparedness were associated with negative mental health outcomes in a large representative sample of previously deployed RC

The Mars Science Laboratory (MSL) Entry, Descent And Landing Instrumentation (MEDLI): Hardware Performance and Data Reconstruction

NASA Technical Reports Server (NTRS)

Little, Alan; Bose, Deepak; Karlgaard, Chris; Munk, Michelle; Kuhl, Chris; Schoenenberger, Mark; Antill, Chuck; Verhappen, Ron; Kutty, Prasad; White, Todd

2013-01-01

The Mars Science Laboratory (MSL) Entry, Descent and Landing Instrumentation (MEDLI) hardware was a first-of-its-kind sensor system that gathered temperature and pressure readings on the MSL heatshield during Mars entry on August 6, 2012. MEDLI began as challenging instrumentation problem, and has been a model of collaboration across multiple NASA organizations. After the culmination of almost 6 years of effort, the sensors performed extremely well, collecting data from before atmospheric interface through parachute deploy. This paper will summarize the history of the MEDLI project and hardware development, including key lessons learned that can apply to future instrumentation efforts. MEDLI returned an unprecedented amount of high-quality engineering data from a Mars entry vehicle. We will present the performance of the 3 sensor types: pressure, temperature, and isotherm tracking, as well as the performance of the custom-built sensor support electronics. A key component throughout the MEDLI project has been the ground testing and analysis effort required to understand the returned flight data. Although data analysis is ongoing through 2013, this paper will reveal some of the early findings on the aerothermodynamic environment that MSL encountered at Mars, the response of the heatshield material to that heating environment, and the aerodynamic performance of the entry vehicle. The MEDLI data results promise to challenge our engineering assumptions and revolutionize the way we account for margins in entry vehicle design.

Medical student satisfaction, coping and burnout in direct-entry versus graduate-entry programmes.

PubMed

DeWitt, Dawn; Canny, Benedict J; Nitzberg, Michael; Choudri, Jennifer; Porter, Sarah

2016-06-01

There is ongoing debate regarding the optimal length of medical training, with concern about the cost of prolonged training. Two simultaneous tracks currently exist in Australia: direct entry from high school and graduate entry for students with a bachelor degree. Medical schools are switching to graduate entry based on maturity, academic preparedness and career-choice surety. We tested the assumption that graduate entry is better by exploring student preferences, coping, burnout, empathy and alcohol use. From a potential pool of 2188 participants, enrolled at five Australian medical schools, a convenience sample of 688 (31%) first and second year students completed a survey in the middle of the academic year. Participants answered questions about demographics, satisfaction and coping and completed three validated instruments. Over 90% of students preferred their own entry-type, though more graduate-entry students were satisfied with their programme (82.4% versus 65.3%, p < 0.001). There was no difference between graduate-entry and direct-entry students in self-reported coping or in the proportion of students meeting criteria for burnout (50.7% versus 51.2%). Direct-entry students rated significantly higher for empathy (concern, p = 0.022; personal distress, p = 0.031). Graduate-entry students reported significantly more alcohol use and hazardous drinking (30.0% versus 22.8%; p = 0.017). Our multi-institution data confirm that students are generally satisfied with their choice of entry pathway and do not confirm significant psychosocial benefits of graduate entry. Overall, our data suggest that direct-entry students cope with the workload and psychosocial challenges of medical school, in the first 2 years, as well as graduate-entry students. Burnout and alcohol use should be addressed in both pathways. Despite studies showing similar academic outcomes, and higher total costs, more programmes in Australia are becoming graduate entry. Further research on

Event detection for car park entries by video-surveillance

NASA Astrophysics Data System (ADS)

Coquin, Didier; Tailland, Johan; Cintract, Michel

2007-10-01

Intelligent surveillance has become an important research issue due to the high cost and low efficiency of human supervisors, and machine intelligence is required to provide a solution for automated event detection. In this paper we describe a real-time system that has been used for detecting car park entries, using an adaptive background learning algorithm and two indicators representing activity and identity to overcome the difficulty of tracking objects.

Entry Atmospheric Flight Control Authority Impacts on GN and C and Trajectory Performance for Orion Exploration Flight Test 1

NASA Technical Reports Server (NTRS)

McNamara, Luke W.

2012-01-01

One of the key design objectives of NASA's Orion Exploration Flight Test 1 (EFT-1) is to execute a guided entry trajectory demonstrating GN&C capability. The focus of this paper is the ight control authority of the vehicle throughout the atmospheric entry ight to the target landing site and its impacts on GN&C, parachute deployment, and integrated performance. The vehicle's attitude control authority is obtained from thrusting 12 Re- action Control System (RCS) engines, with four engines to control yaw, four engines to control pitch, and four engines to control roll. The static and dynamic stability derivatives of the vehicle are determined to assess the inherent aerodynamic stability. The aerodynamic moments at various locations in the entry trajectory are calculated and compared to the available torque provided by the RCS system. Interaction between the vehicle's RCS engine plumes and the aerodynamic conditions are considered to assess thruster effectiveness. This document presents an assessment of Orion's ight control authority and its effectiveness in controlling the vehicle during critical events in the atmospheric entry trajectory.

TQM and lean strategy deployment in Italian hospitals.

PubMed

Chiarini, Andrea; Baccarani, Claudio

2016-10-03

Purpose This paper aims to contribute to the debate concerning total quality management (TQM)-Lean strategy in public healthcare by analyzing the deployment path for implementation, the possible benefits that can be achieved and the encountered pitfalls. Design/methodology/approach Three case studies are drawn from three large Italian hospitals with more than 500 beds each and structured with many departments. The hospitals are located in Tuscany, Italy. These three hospitals have embraced TQM and Lean, starting from strategic objectives and their deployment. At the same time, they have also implemented many TQM-Lean tools. The case studies are based on interviews held with four managers in each of these three public hospitals. Findings Results from the interviews show that there is a specific deployment path for TQM-Lean implementation. The hospitals have also achieved benefits linked to patient satisfaction and improved organizational performances. Problems related to organizational and cultural issues, such as senior managers' commitment, staff management, manufacturing culture and tools adaptation, could affect the benefits. Research limitations/implications The research has been carried out in just three Italian public hospitals. Hence, similar investigations could be managed in other countries. Researchers could also use a larger sample and investigate these issues by means of quantitative inquiry. Practical implications Practitioners could try to apply the deployment path revealed by these case studies in other public and private hospitals. Originality/value The results of this research show that there is a specific, new deployment path for implementing TQM-Lean strategy in some public hospitals.

Connected Vehicle Pilot Deployment Program phase 1 : application deployment plan : New York City : final application deployment plan.

DOT National Transportation Integrated Search

2016-08-04

This document is the Task 7 Application Deployment Plan deliverable for the New York City Connected Vehicle Pilot Deployment. It describes the process that the deployment team will follow to acquire and test the connected vehicle safety applications....

Adaptive Technologies for Training and Education

ERIC Educational Resources Information Center

Durlach, Paula J., Ed; Lesgold, Alan M., Ed.

2012-01-01

This edited volume provides an overview of the latest advancements in adaptive training technology. Intelligent tutoring has been deployed for well-defined and relatively static educational domains such as algebra and geometry. However, this adaptive approach to computer-based training has yet to come into wider usage for domains that are less…

Adaptability, Engagement and Academic Achievement at University

ERIC Educational Resources Information Center

Collie, Rebecca J.; Holliman, Andrew J.; Martin, Andrew J.

2017-01-01

University entry is a time of great change for students. The extent to which students are able to effectively navigate such change likely has an impact on their success in university. In the current study, we examined this by way of adaptability, the extent to which students' adaptability is associated with their behavioural engagement at…

Cell Surface THY-1 Contributes to Human Cytomegalovirus Entry via a Macropinocytosis-Like Process

PubMed Central

Li, Qingxue; Fischer, Elizabeth

2016-01-01

ABSTRACT Previously we showed that THY-1 has a critical role in the initial stage of infection of certain cell types with human cytomegalovirus (HCMV) and that THY-1 is important for HCMV-mediated activation of phosphatidylinositol 3-kinase (PI3K)/Akt during virus entry. THY-1 is known to interact with integrins and is a major cargo protein of clathrin-independent endocytic vesicles. Since macropinocytosis involves integrin signaling, is PI3K/Akt dependent, and is a clathrin-independent endocytic process, we determined whether THY-1 has a role in HCMV entry by macropinocytosis. Using electron microscopy in two cell lines that support HCMV infection in a THY-1-dependent manner, we found that HCMV enters these cells by a macropinocytosis-like process. THY-1 associated with HCMV virions on the cell surface and colocalized with virus inside macropinosomes. 5-(N-Ethyl-N-isopropyl)amiloride (EIPA) and soluble THY-1 blocked HCMV infection in the cell lines by ≥80% and 60%, respectively. HCMV entry into the cells triggered increased influx of extracellular fluid, a marker of macropinocytosis, and this increased fluid uptake was inhibited by EIPA and by soluble THY-1. Blocking actin depolymerization, Na+/H+ exchange, PI3K, and Pak1 kinase, which are critical for macropinocytosis, impaired HCMV infection. Neither internalized HCMV virions nor THY-1 in virus-infected cells colocalized with transferrin as determined by confocal microscopy, indicating that clathrin-mediated endocytosis was not involved in THY-1-associated virus entry. These results suggest that HCMV has adapted to utilize THY-1, a cargo protein of clathrin-independent endocytotic vesicles, to facilitate efficient entry into certain cell types by a macropinocytosis-like process. IMPORTANCE Human cytomegalovirus (HCMV) infects over half of the population and is the most common infectious cause of birth defects. The virus is the most important infection occurring in transplant recipients. The mechanism of how

Quantum connectivity optimization algorithms for entanglement source deployment in a quantum multi-hop network

NASA Astrophysics Data System (ADS)

Zou, Zhen-Zhen; Yu, Xu-Tao; Zhang, Zai-Chen

2018-04-01

At first, the entanglement source deployment problem is studied in a quantum multi-hop network, which has a significant influence on quantum connectivity. Two optimization algorithms are introduced with limited entanglement sources in this paper. A deployment algorithm based on node position (DNP) improves connectivity by guaranteeing that all overlapping areas of the distribution ranges of the entanglement sources contain nodes. In addition, a deployment algorithm based on an improved genetic algorithm (DIGA) is implemented by dividing the region into grids. From the simulation results, DNP and DIGA improve quantum connectivity by 213.73% and 248.83% compared to random deployment, respectively, and the latter performs better in terms of connectivity. However, DNP is more flexible and adaptive to change, as it stops running when all nodes are covered.

A Prospective Study of Acute Diarrhea in a Cohort of United States Military Personnel on Deployment to the Multinational Force and Observers, Sinai, Egypt

PubMed Central

Riddle, Mark S.; Rockabrand, David M.; Schlett, Carey; Monteville, Marshall R.; Frenck, Robert W.; Romine, Marcy; Ahmed, Salwa F.; Sanders, John W.

2011-01-01

To better understand the epidemiology of diarrhea in deployed personnel to the Middle East, a prospective cohort study of travelers' diarrhea (TD) was conducted between May 2004 and January 2005 at the Multinational Force and Observers (MFO) camp in the southern Sinai. A baseline entry questionnaire and stool specimen was provided on study entry, and volunteers were followed every 6 weeks. Of 211 volunteers, 145 (68.7%) completed one or more follow-up visits. In total, 416 follow-up surveys were completed, which described an overall incidence of 25.2 episodes per 100 person months (95% confidence interval = 21.2–30.0). Additionally, stools were collected in 72 of 77 diarrhea-associated clinic visits, with bacterial pathogens most commonly isolated (enterotoxigenic Escherichia coli in 30 [42%] samples and Campylobacter jejuni in 7 [10%] samples) Despite modern preventive methods, diarrhea is still a common problem for deployed US military personnel in Egypt, frequently resulting in diminished ability to work. PMID:21212203

Pre-deployment Year Mental Health Diagnoses and Treatment in Deployed Army Women

PubMed Central

Adams, Rachel Sayko; Mohr, Beth A.; Jeffery, Diana D.; Funk, Wendy; Williams, Thomas V.; Larson, Mary Jo

2016-01-01

We estimated the prevalence of select mental health diagnoses (MHDX) and mental health treatment (MHT), and identified characteristics associated with MHT during the pre-deployment year (365 days before deployment) in active duty Army women (N = 14,633) who returned from Iraq or Afghanistan deployments in FY2010. Pre-deployment year prevalence estimates were: 26.2 % for any select MHDX and 18.1 % for any MHT. Army women who had physical injuries since FY2002 or any behavioral health treatment between FY2002 and the pre-deployment year had increased odds of pre-deployment year MHT. During the pre-deployment year, a substantial percentage of Army women had MHDX and at least one MHT encounter or stay. Future research should determine if pre-deployment MHDX among Army women reflect vulnerability to future MHDX, or if pre-deployment MHT results in protection from chronic symptoms. PMID:27368233

Pre-deployment Year Mental Health Diagnoses and Treatment in Deployed Army Women.

PubMed

Wooten, Nikki R; Adams, Rachel Sayko; Mohr, Beth A; Jeffery, Diana D; Funk, Wendy; Williams, Thomas V; Larson, Mary Jo

2017-07-01

We estimated the prevalence of select mental health diagnoses (MHDX) and mental health treatment (MHT), and identified characteristics associated with MHT during the pre-deployment year (365 days before deployment) in active duty Army women (N = 14,633) who returned from Iraq or Afghanistan deployments in FY2010. Pre-deployment year prevalence estimates were: 26.2 % for any select MHDX and 18.1 % for any MHT. Army women who had physical injuries since FY2002 or any behavioral health treatment between FY2002 and the pre-deployment year had increased odds of pre-deployment year MHT. During the pre-deployment year, a substantial percentage of Army women had MHDX and at least one MHT encounter or stay. Future research should determine if pre-deployment MHDX among Army women reflect vulnerability to future MHDX, or if pre-deployment MHT results in protection from chronic symptoms.

Preparedness Evaluation of French Military Orthopedic Surgeons Before Deployment.

PubMed

Choufani, Camille; Barbier, Olivier; Mayet, Aurélie; Rigal, Sylvain; Mathieu, Laurent

2018-06-13

A deployed military orthopedic surgeon is a trauma surgeon working in austere conditions. The first aim of this study was to analyze the current activity of French military orthopedic surgeons in the field and to identify the differences of the combat zone with their daily practice. The second aim was to assess the adequacy of the preparedness they received before their deployment and to identify additional needs that could be addressed in future training. An evaluation survey was sent to all French military orthopedic surgeons deployed in theaters of operations between 2004 and 2014. An analogic visual scale of 10 was used to evaluate their surgical activity abroad and prior training. A total of 55 surgeons, with a median deployment number of 7, were included in this study after they answered the survey. Debridement and external fixation were the most common orthopedic procedures. The practice of general surgery was mostly concerned with vascular and abdominal injuries as part of damage control procedures. Median scores were ranked at seven for surgical preparedness, five for physical readiness, and three for mental preparedness. There was a significant inverse relationship between the number of missions performed and the evaluation of surgical preparedness. The higher they perceived their mental preparedness, the better they estimated their surgical preparedness. In the French Army, deployed orthopedic surgeons perform general surgical activity. Their initial training must be adapted to this constraint and enhanced by continuing medical education.

Design of Measure and Control System for Precision Pesticide Deploying Dynamic Simulating Device

NASA Astrophysics Data System (ADS)

Liang, Yong; Liu, Pingzeng; Wang, Lu; Liu, Jiping; Wang, Lang; Han, Lei; Yang, Xinxin

A measure and control system for precision deploying pesticide simulating equipment is designed in order to study pesticide deployment technology. The system can simulate every state of practical pesticide deployment, and carry through precise, simultaneous measure to every factor affecting pesticide deployment effects. The hardware and software incorporates a structural design of modularization. The system is divided into many different function modules of hardware and software, and exploder corresponding modules. The modules’ interfaces are uniformly defined, which is convenient for module connection, enhancement of system’s universality, explodes efficiency and systemic reliability, and make the program’s characteristics easily extended and easy maintained. Some relevant hardware and software modules can be adapted to other measures and control systems easily. The paper introduces the design of special numeric control system, the main module of information acquisition system and the speed acquisition module in order to explain the design process of the module.

ENTRY ON SOUTHEAST SIDE (WILLISTON AVENUE ENTRY), VIEW FACING NORTHWEST. ...

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

ENTRY ON SOUTHEAST SIDE (WILLISTON AVENUE ENTRY), VIEW FACING NORTHWEST. - Schofield Barracks Military Reservation, Quadrangle I Administration Building, Williston Avenue between Wright-Smith & Reilly Avenues, Wahiawa, Honolulu County, HI

Entry at Venus

NASA Technical Reports Server (NTRS)

Venkatapathy, Ethiraj; Smith, Brandon

2016-01-01

This is lecture to be given at the IPPW 2016, as part of the 2 day course on Short Course on Destination Venus: Science, Technology and Mission Architectures. The attached presentation material is intended to be introduction to entry aspects of Venus in-situ robotic missions. The presentation introduces the audience to the aerodynamic and aerothermodynamic aspects as well as the loads, both aero and thermal, generated during entry. The course touches upon the system design aspects such as TPS design and both high and low ballistic coefficient entry system concepts that allow the science payload to be protected from the extreme entry environment and yet meet the mission objectives.

Titan Explorer Entry, Descent and Landing Trajectory Design

NASA Technical Reports Server (NTRS)

Fisher, Jody L.; Lindberg, Robert E.; Lockwood, Mary Kae

2006-01-01

The Titan Explorer mission concept includes an orbiter, entry probe and inflatable airship designed to take remote and in-situ measurements of Titan's atmosphere. A modified entry, descent and landing trajectory at Titan that incorporates mid-air airship inflation (under a parachute) and separation is developed and examined for Titan Explorer. The feasibility of mid-air inflation and deployment of an airship under a parachute is determined by implementing and validating an airship buoyancy and inflation model in the trajectory simulation program, Program to Optimize Simulated Trajectories II (POST2). A nominal POST2 trajectory simulation case study is generated which examines different descent scenarios by varying airship inflation duration, orientation, and separation. The buoyancy model incorporation into POST2 is new to the software and may be used in future trajectory simulations. Each case from the nominal POST2 trajectory case study simulates a successful separation between the parachute and airship systems with sufficient velocity change as to alter their paths to avoid collision throughout their descent. The airship and heatshield also separate acceptably with a minimum distance of separation from the parachute system of 1.5 km. This analysis shows the feasibility of airship inflation on a parachute for different orientations, airship separation at various inflation times, and preparation for level-flight at Titan.

Deployable antenna

NASA Technical Reports Server (NTRS)

Fink, Patrick W. (Inventor); Dobbins, Justin A. (Inventor); Lin, Greg Y. (Inventor); Chu, Andrew W. (Inventor); Scully, Robert C. (Inventor)

2006-01-01

A deployable antenna and method for using wherein the deployable antenna comprises a collapsible membrane having at least one radiating element for transmitting electromagnetic waves, receiving electromagnetic waves, or both.

Family adjustment of deployed and non-deployed mothers in families with a parent deployed to Iraq or Afghanistan

PubMed Central

Gewirtz, Abigail H.; McMorris, Barbara J.; Hanson, Sheila; Davis, Laurel

2014-01-01

Almost nothing is known about the family and individual adjustment of military mothers who have deployed to the conflicts in Iraq or Afghanistan (Operations Iraqi and Enduring Freedom, and Operation New Dawn; OIF, OEF, OND), constituting a gap in psychologists’ knowledge about how best to help this population. We report baseline data on maternal, child, parenting, and couple adjustment for mothers in 181 families in which a parent deployed to OIF/OEF/OND. Among this sample, 34 mothers had deployed at least once, and 147 mothers had experienced the deployment of a male spouse/partner. Mothers completed self-report questionnaires assessing past year adverse life events, war experiences (for deployed mothers only), posttraumatic stress disorder (PTSD) and depression symptoms, difficulties in emotion regulation, parenting, couple adjustment, and child functioning. Mothers who had deployed reported greater distress than non-deployed mothers (higher scores on measures of PTSD and depression symptoms), and slightly more past year adverse events. A moderate number of war experiences (combat and post-battle aftermath events) were reported, consistent with previous studies of women in current and prior conflicts. However, no differences were found between the two groups on measures of couple adjustment, parenting, or child functioning. Results are discussed in terms of the dearth of knowledge about deployed mothers, and implications for psychologists serving military families. PMID:25663739

INTERIOR OF ENTRY HALLWAY AND STEEL ENTRY DOOR ON SOUTH ...

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

INTERIOR OF ENTRY HALLWAY AND STEEL ENTRY DOOR ON SOUTH SIDE, VIEW FACING NORTHEAST. - Naval Air Station Barbers Point, Telephone Exchange, Coral Sea Road north of Bismarck Sea Road, Ewa, Honolulu County, HI

Key Attributes of a Successful Physician Order Entry System Implementation in a Multi-hospital Environment

PubMed Central

Ahmad, Asif; Teater, Phyllis; Bentley, Thomas D.; Kuehn, Lynn; Kumar, Rajee R.; Thomas, Andrew; Mekhjian, Hagop S.

2002-01-01

The benefits of computerized physician order entry have been widely recognized, although few institutions have successfully installed these systems. Obstacles to successful implementation are organizational as well as technical. In the spring of 2000, following a 4-year period of planning and customization, a 9-month pilot project, and a 14-month hiatus for year 2000, the Ohio State University Health System extensively implemented physician order entry across inpatient units. Implementation for specialty and community services is targeted for completion in 2002. On implemented units, all orders are processed through the system, with 80 percent being entered by physicians and the rest by nursing or other licensed care providers. The system is deployable across diverse clinical environments, focused on physicians as the primary users, and accepted by clinicians. These are the three criteria by which the authors measured the success of their implementation. They believe that the availability of specialty-specific order sets, the engagement of physician leadership, and a large-scale system implementation were key strategic factors that enabled physician-users to accept a physician order entry system despite significant changes in workflow. PMID:11751800

Self-Deployable Membrane Structures

NASA Technical Reports Server (NTRS)

Sokolowski, Witold M.; Willis, Paul B.; Tan, Seng C.

2010-01-01

Currently existing approaches for deployment of large, ultra-lightweight gossamer structures in space rely typically upon electromechanical mechanisms and mechanically expandable or inflatable booms for deployment and to maintain them in a fully deployed, operational configuration. These support structures, with the associated deployment mechanisms, launch restraints, inflation systems, and controls, can comprise more than 90 percent of the total mass budget. In addition, they significantly increase the stowage volume, cost, and complexity. A CHEM (cold hibernated elastic memory) membrane structure without any deployable mechanism and support booms/structure is deployed by using shape memory and elastic recovery. The use of CHEM micro-foams reinforced with carbon nanotubes is considered for thin-membrane structure applications. In this advanced structural concept, the CHEM membrane structure is warmed up to allow packaging and stowing prior to launch, and then cooled to induce hibernation of the internal restoring forces. In space, the membrane remembers its original shape and size when warmed up. After the internal restoring forces deploy the structure, it is then cooled to achieve rigidization. For this type of structure, the solar radiation could be utilized as the heat energy used for deployment and space ambient temperature for rigidization. The overall simplicity of the CHEM self-deployable membrane is one of its greatest assets. In present approaches to space-deployable structures, the stow age and deployment are difficult and challenging, and introduce a significant risk, heavy mass, and high cost. Simple procedures provided by CHEM membrane greatly simplify the overall end-to-end process for designing, fabricating, deploying, and rigidizing large structures. The CHEM membrane avoids the complexities associated with other methods for deploying and rigidizing structures by eliminating deployable booms, deployment mechanisms, and inflation and control systems

Deployment of community health workers across rural sub-Saharan Africa: financial considerations and operational assumptions.

PubMed

McCord, Gordon C; Liu, Anne; Singh, Prabhjot

2013-04-01

To provide cost guidance for developing a locally adaptable and nationally scalable community health worker (CHW) system within primary-health-care systems in sub-Saharan Africa. The yearly costs of training, equipping and deploying CHWs throughout rural sub-Saharan Africa were calculated using data from the literature and from the Millennium Villages Project. Model assumptions were such as to allow national governments to adapt the CHW subsystem to national needs and to deploy an average of 1 CHW per 650 rural inhabitants by 2015. The CHW subsystem described was costed by employing geographic information system (GIS) data on population, urban extents, national and subnational disease prevalence, and unit costs (from the field for wages and commodities). The model is easily replicable and configurable. Countries can adapt it to local prices, wages, population density and disease burdens in different geographic areas. The average annual cost of deploying CHWs to service the entire sub-Saharan African rural population by 2015 would be approximately 2.6 billion (i.e. 2600 million) United States dollars (US$). This sum, to be covered both by national governments and by donor partners, translates into US$ 6.86 per year per inhabitant covered by the CHW subsystem and into US$ 2.72 per year per inhabitant. Alternatively, it would take an annual average of US$ 3750 to train, equip and support each CHW. Comprehensive CHW subsystems can be deployed across sub-Saharan Africa at cost that is modest compared with the projected costs of the primary-health-care system. Given their documented successes, they offer a strong complement to facility-based care in rural African settings.

Deployment of community health workers across rural sub-Saharan Africa: financial considerations and operational assumptions

PubMed Central

McCord, Gordon C; Liu, Anne

2013-01-01

Abstract Objective To provide cost guidance for developing a locally adaptable and nationally scalable community health worker (CHW) system within primary-health-care systems in sub-Saharan Africa. Methods The yearly costs of training, equipping and deploying CHWs throughout rural sub-Saharan Africa were calculated using data from the literature and from the Millennium Villages Project. Model assumptions were such as to allow national governments to adapt the CHW subsystem to national needs and to deploy an average of 1 CHW per 650 rural inhabitants by 2015. The CHW subsystem described was costed by employing geographic information system (GIS) data on population, urban extents, national and subnational disease prevalence, and unit costs (from the field for wages and commodities). The model is easily replicable and configurable. Countries can adapt it to local prices, wages, population density and disease burdens in different geographic areas. Findings The average annual cost of deploying CHWs to service the entire sub-Saharan African rural population by 2015 would be approximately 2.6 billion (i.e. 2600 million) United States dollars (US$). This sum, to be covered both by national governments and by donor partners, translates into US$ 6.86 per year per inhabitant covered by the CHW subsystem and into US$ 2.72 per year per inhabitant. Alternatively, it would take an annual average of US$ 3750 to train, equip and support each CHW. Conclusion Comprehensive CHW subsystems can be deployed across sub-Saharan Africa at cost that is modest compared with the projected costs of the primary-health-care system. Given their documented successes, they offer a strong complement to facility-based care in rural African settings. PMID:23599547

Analytic Guidance for the First Entry in a Skip Atmospheric Entry

NASA Technical Reports Server (NTRS)

Garcia-Llama, Eduardo

2007-01-01

This paper presents an analytic method to generate a reference drag trajectory for the first entry portion of a skip atmospheric entry. The drag reference, expressed as a polynomial function of the velocity, will meet the conditions necessary to fit the requirements of the complete entry phase. The generic method proposed to generate the drag reference profile is further simplified by thinking of the drag and the velocity as density and cumulative distribution functions respectively. With this notion it will be shown that the reference drag profile can be obtained by solving a linear algebraic system of equations. The resulting drag profile is flown using the feedback linearization method of differential geometric control as guidance law with the error dynamics of a second order homogeneous equation in the form of a damped oscillator. This approach was first proposed as a revisited version of the Space Shuttle Orbiter entry guidance. However, this paper will show that it can be used to fly the first entry in a skip entry trajectory. In doing so, the gains in the error dynamics will be changed at a certain point along the trajectory to improve the tracking performance.

The role of digital data entry in participatory environmental monitoring.

PubMed

Brammer, Jeremy R; Brunet, Nicolas D; Burton, A Cole; Cuerrier, Alain; Danielsen, Finn; Dewan, Kanwaljeet; Herrmann, Thora Martina; Jackson, Micha V; Kennett, Rod; Larocque, Guillaume; Mulrennan, Monica; Pratihast, Arun Kumar; Saint-Arnaud, Marie; Scott, Colin; Humphries, Murray M

2016-12-01

Many argue that monitoring conducted exclusively by scientists is insufficient to address ongoing environmental challenges. One solution entails the use of mobile digital devices in participatory monitoring (PM) programs. But how digital data entry affects programs with varying levels of stakeholder participation, from nonscientists collecting field data to nonscientists administering every step of a monitoring program, remains unclear. We reviewed the successes, in terms of management interventions and sustainability, of 107 monitoring programs described in the literature (hereafter programs) and compared these with case studies from our PM experiences in Australia, Canada, Ethiopia, Ghana, Greenland, and Vietnam (hereafter cases). Our literature review showed that participatory programs were less likely to use digital devices, and 2 of our 3 more participatory cases were also slow to adopt digital data entry. Programs that were participatory and used digital devices were more likely to report management actions, which was consistent with cases in Ethiopia, Greenland, and Australia. Programs engaging volunteers were more frequently reported as ongoing, but those involving digital data entry were less often sustained when data collectors were volunteers. For the Vietnamese and Canadian cases, sustainability was undermined by a mismatch in stakeholder objectives. In the Ghanaian case, complex field protocols diminished monitoring sustainability. Innovative technologies attract interest, but the foundation of effective participatory adaptive monitoring depends more on collaboratively defined questions, objectives, conceptual models, and monitoring approaches. When this foundation is built through effective partnerships, digital data entry can enable the collection of more data of higher quality. Without this foundation, or when implemented ineffectively or unnecessarily, digital data entry can be an additional expense that distracts from core monitoring objectives

9. FIRST FLOOR, ENTRY HALL, LOOKING SOUTHWEST TOWARDS FRONT ENTRY ...

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

9. FIRST FLOOR, ENTRY HALL, LOOKING SOUTHWEST TOWARDS FRONT ENTRY WITH OPEN DOORWAY TO WINDER STAIRWAY ON RIGHT - Open Gate Farm, House, Ridge Road, 1 mile East of Elephant Road, Perkasie, Bucks County, PA

Deployment simulation of a deployable reflector for earth science application

NASA Astrophysics Data System (ADS)

Wang, Xiaokai; Fang, Houfei; Cai, Bei; Ma, Xiaofei

2015-10-01

A novel mission concept namely NEXRAD-In-Space (NIS) has been developed for monitoring hurricanes, cyclones and other severe storms from a geostationary orbit. It requires a space deployable 35-meter diameter Ka-band (35 GHz) reflector. NIS can measure hurricane precipitation intensity, dynamics and its life cycle. These information is necessary for predicting the track, intensity, rain rate and hurricane-induced floods. To meet the requirements of the radar system, a Membrane Shell Reflector Segment (MSRS) reflector technology has been developed and several technologies have been evaluated. However, the deployment analysis of this large size and high-precision reflector has not been investigated. For a pre-studies, a scaled tetrahedral truss reflector with spring driving deployment system has been made and tested, deployment dynamics analysis of this scaled reflector has been performed using ADAMS to understand its deployment dynamic behaviors. Eliminating the redundant constraints in the reflector system with a large number of moving parts is a challenging issue. A primitive joint and flexible struts were introduced to the analytical model and they can effectively eliminate over constraints of the model. By using a high-speed camera and a force transducer, a deployment experiment of a single-bay tetrahedral module has been conducted. With the tested results, an optimization process has been performed by using the parameter optimization module of ADAMS to obtain the parameters of the analytical model. These parameters were incorporated to the analytical model of the whole reflector. It is observed from the analysis results that the deployment process of the reflector with a fixed boundary experiences three stages. These stages are rapid deployment stage, slow deployment stage and impact stage. The insight of the force peak distributions of the reflector can help the optimization design of the structure.

Pre-deployment dissociation and personality as risk factors for post-deployment post-traumatic stress disorder in Danish soldiers deployed to Afghanistan

PubMed Central

Ponce de León, Beatriz; Andersen, Søren; Karstoft, Karen-Inge; Elklit, Ask

2018-01-01

ABSTRACT Objective: This study investigated whether pre-deployment dissociation was associated with previously identified post-traumatic stress disorder (PTSD) symptom trajectories from before to 2.5 years after military deployment. Furthermore, it examined whether the tendency to dissociate, pre-deployment personality factors, conceptualized by the Big Five model, and previous trauma represented independent risk factors for post-deployment PTSD symptoms. Method: This prospective study included the entire team of 743 soldiers from the Danish Contingent of the International Security Assistance Force 7 deployed to Afghanistan in 2009. Data consisted of self-report measures and were collected six times: before deployment; during deployment; and 1–3 weeks, 2 months, 7 months and 2.5 years after homecoming. Results: The findings indicate significant associations between pre-deployment dissociation and six PTSD trajectories (p < 0.001, η2 = 0.120). Based on mean differences in dissociation for the six trajectories, two main groups emerged: a group with high dissociation scores at pre-deployment, which had moderate PTSD symptom levels at pre-deployment and fluctuated over time; and a group with low dissociation scores at pre-deployment, which had low initial PTSD symptom levels and diverged over time. Our study also confirmed previous findings of a positive association between neuroticism and dissociation (r = 0.31, p < 0.001). This suggests that negative emotionality may be a vulnerability that enhances dissociative experiences, although a causal link cannot be concluded from the findings. Finally, pre-deployment dissociation, pre-deployment neuroticism and a history of traumatic events, as independent factors, were significant predictors of post-deployment PTSD (p < 0.001, R2 = 0.158). Conclusions: The study emphasizes the multiplicity of factors involved in the development of PTSD, and group differences in dissociative symptoms support the

Shuttle program. MCC Level C formulation requirements: Entry guidance and entry autopilot

NASA Technical Reports Server (NTRS)

Harpold, J. C.; Hill, O.

1980-01-01

A set of preliminary entry guidance and autopilot software formulations is presented for use in the Mission Control Center (MCC) entry processor. These software formulations meet all level B requirements. Revision 2 incorporates the modifications required to functionally simulate optimal TAEM targeting capability (OTT). Implementation of this logic in the MCC must be coordinated with flight software OTT implementation and MCC TAEM guidance OTT. The entry guidance logic is based on the Orbiter avionics entry guidance software. This MCC requirements document contains a definition of coordinate systems, a list of parameter definitions for the software formulations, a description of the entry guidance detailed formulation requirements, a description of the detailed autopilot formulation requirements, a description of the targeting routine, and a set of formulation flow charts.

Technology transfer for adaptation

NASA Astrophysics Data System (ADS)

Biagini, Bonizella; Kuhl, Laura; Gallagher, Kelly Sims; Ortiz, Claudia

2014-09-01

Technology alone will not be able to solve adaptation challenges, but it is likely to play an important role. As a result of the role of technology in adaptation and the importance of international collaboration for climate change, technology transfer for adaptation is a critical but understudied issue. Through an analysis of Global Environment Facility-managed adaptation projects, we find there is significantly more technology transfer occurring in adaptation projects than might be expected given the pessimistic rhetoric surrounding technology transfer for adaptation. Most projects focused on demonstration and early deployment/niche formation for existing technologies rather than earlier stages of innovation, which is understandable considering the pilot nature of the projects. Key challenges for the transfer process, including technology selection and appropriateness under climate change, markets and access to technology, and diffusion strategies are discussed in more detail.

Planetary/DOD entry technology flight experiments. Volume 2: Planetary entry flight experiments

NASA Technical Reports Server (NTRS)

Christensen, H. E.; Krieger, R. J.; Mcneilly, W. R.; Vetter, H. C.

1976-01-01

The technical feasibility of launching a high speed, earth entry vehicle from the space shuttle to advance technology for the exploration of the outer planets' atmospheres was established. Disciplines of thermodynamics, orbital mechanics, aerodynamics propulsion, structures, design, electronics and system integration focused on the goal of producing outer planet environments on a probe shaped vehicle during an earth entry. Major aspects of analysis and vehicle design studied include: planetary environments, earth entry environment capability, mission maneuvers, capabilities of shuttle upper stages, a comparison of earth entry planetary environments, experiment design and vehicle design.

Adapting to Environmental Jolts.

ERIC Educational Resources Information Center

Meyer, Alan D.

1982-01-01

Examines the reactions of three San Francisco (California) hospitals to the 1975 doctors' strike. Analyzes the anticipatory, responsive, and readjustment phases of the hospitals' adaptations in terms of each hospital's previous market strategy, organizational structure and ideology, and deployment of slack resources, including financial, human,…

Texting while driving: is speech-based text entry less risky than handheld text entry?

PubMed

He, J; Chaparro, A; Nguyen, B; Burge, R J; Crandall, J; Chaparro, B; Ni, R; Cao, S

2014-11-01

Research indicates that using a cell phone to talk or text while maneuvering a vehicle impairs driving performance. However, few published studies directly compare the distracting effects of texting using a hands-free (i.e., speech-based interface) versus handheld cell phone, which is an important issue for legislation, automotive interface design and driving safety training. This study compared the effect of speech-based versus handheld text entries on simulated driving performance by asking participants to perform a car following task while controlling the duration of a secondary text-entry task. Results showed that both speech-based and handheld text entries impaired driving performance relative to the drive-only condition by causing more variation in speed and lane position. Handheld text entry also increased the brake response time and increased variation in headway distance. Text entry using a speech-based cell phone was less detrimental to driving performance than handheld text entry. Nevertheless, the speech-based text entry task still significantly impaired driving compared to the drive-only condition. These results suggest that speech-based text entry disrupts driving, but reduces the level of performance interference compared to text entry with a handheld device. In addition, the difference in the distraction effect caused by speech-based and handheld text entry is not simply due to the difference in task duration. Copyright © 2014 Elsevier Ltd. All rights reserved.

Cross-Cultural Competency Adaptability of Dental Hygiene Educators in Entry Level Dental Hygiene Programs

ERIC Educational Resources Information Center

Engeswick, Lynnette Marie

2011-01-01

This study was conducted to discover the extent dental hygiene educators in 25 entry-level dental hygiene programs from the Upper Midwest demonstrate Emotional Resilience, Flexibility and Openness, Perceptual Acuity, and Personal Autonomy as they relate to their level of education and multicultural experiences. An additional purpose was to examine…

Feasibility study of low angle planetary entry. [probe design for Jovian entry

NASA Technical Reports Server (NTRS)

Defrees, R. E.

1975-01-01

The feasibility of a Jovian entry by a probe originally designed for Saturn and Uranus entries is examined. An entry probe is described which is capable of release near an outer planet's sphere of influence and descent to a predetermined target entry point in the planet's atmosphere. The probe is designed so as to survive the trapped particle radiation belts and an entry heating pulse. Data is gathered and relayed to an overflying spacecraft bus during descent. Probe variations for two similar missions are described. In the first flyby of Jupiter by a Pioneer spacecraft launched during the 1979 opportunity is examined parametrically. In the second mission an orbiter based on Pioneer and launched in 1980 is defined in specific terms. The differences rest in the science payloads and directly affected wiring and electronics packages.

10. FIRST FLOOR, ENTRY HALL, LOOKING SOUTHWEST TOWARDS FRONT ENTRY ...

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

10. FIRST FLOOR, ENTRY HALL, LOOKING SOUTHWEST TOWARDS FRONT ENTRY WITH DOOR PARTIALLY CLOSED TO SHOWS ITS RAISED PANEL CONSTRUCTION AND STRAP HINGES - Open Gate Farm, House, Ridge Road, 1 mile East of Elephant Road, Perkasie, Bucks County, PA

A high throughput Cre–lox activated viral membrane fusion assay identifies pharmacological inhibitors of HIV entry

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

Esposito, Anthony M.; Cheung, Pamela; Swartz, Talia H.

Enveloped virus entry occurs when viral and cellular membranes fuse releasing particle contents into the target cell. Human immunodeficiency virus (HIV) entry occurs by cell-free virus or virus transferred between infected and uninfected cells through structures called virological synapses. We developed a high-throughput cell-based assay to identify small molecule inhibitors of cell-free or virological synapse-mediated entry. An HIV clone carrying Cre recombinase as a Gag-internal gene fusion releases active Cre into cells upon viral entry activating a recombinatorial gene switch changing dsRed to GFP-expression. A screen of a 1998 known-biological profile small molecule library identified pharmacological HIV entry inhibitors thatmore » block both cell-free and cell-to-cell infection. Many top hits were noted as HIV inhibitors in prior studies, but not previously recognized as entry antagonists. Modest therapeutic indices for simvastatin and nigericin were observed in confirmatory HIV infection assays. This robust assay is adaptable to study HIV and heterologous viral pseudotypes. - Highlights: • Cre recombinase viral fusion assay screens cell-free or cell–cell entry inhibitors. • This Gag-iCre based assay is specific for the entry step of HIV replication. • Screened a library of known pharmacologic compounds for HIV fusion antagonists. • Many top hits were previously noted as HIV inhibitors, but here are classified as entry antagonists. Many top hits were previously noted as HIV inhibitors, but not as entry antagonists. • The assay is compatible with pseudotyping with HIV and heterologous viruses.« less

Interior view of west end entry showing entry hallway and ...

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

Interior view of west end entry showing entry hallway and double-door frame, view facing south - U.S. Naval Base, Pearl Harbor, Administration Annex, Near Russell Avenue (previously Avenue E), between of Facility Nos. 1C & 1E , Pearl City, Honolulu County, HI

Deployable wing model considering structural flexibility and aerodynamic unsteadiness for deployment system design

NASA Astrophysics Data System (ADS)

Otsuka, Keisuke; Wang, Yinan; Makihara, Kanjuro

2017-11-01

In future, wings will be deployed in the span direction during flight. The deployment system improves flight ability and saves storage space in the airplane. For the safe design of the wing, the deployment motion needs to be simulated. In the simulation, the structural flexibility and aerodynamic unsteadiness should be considered because they may lead to undesirable phenomena such as a residual vibration after the deployment or a flutter during the deployment. In this study, the deployment motion is simulated in the time domain by using a nonlinear folding wing model based on multibody dynamics, absolute nodal coordinate formulation, and two-dimensional aerodynamics with strip theory. We investigate the effect of the structural flexibility and aerodynamic unsteadiness on the time-domain deployment simulation.

Development of a Mars Airplane Entry, Descent, and Flight Trajectory

NASA Technical Reports Server (NTRS)

Murray, James E.; Tartabini, Paul V.

2001-01-01

An entry, descent, and flight (EDF) trajectory profile for a Mars airplane mission is defined as consisting of the following elements: ballistic entry of an aeroshell; supersonic deployment of a decelerator parachute; subsonic release of a heat shield; release, unfolding, and orientation of an airplane to flight attitude; and execution of a pull up maneuver to achieve trimmed, horizontal flight. Using the Program to Optimize Simulated Trajectories (POST) a trajectory optimization problem was formulated. Model data representative of a specific Mars airplane configuration, current models of the Mars surface topography and atmosphere, and current estimates of the interplanetary trajectory, were incorporated into the analysis. The goal is to develop an EDF trajectory to maximize the surface-relative altitude of the airplane at the end of a pull up maneuver, while subject to the mission design constraints. The trajectory performance was evaluated for three potential mission sites and was found to be site-sensitive. The trajectory performance, examined for sensitivity to a number of design and constraint variables, was found to be most sensitive to airplane mass, aerodynamic performance characteristics, and the pull up Mach constraint. Based on the results of this sensitivity study, an airplane-drag optimized trajectory was developed that showed a significant performance improvement.

Inhibitors of SARS-CoV Entry - Identification using an Internally-Controlled Dual Envelope Pseudovirion Assay

PubMed Central

Zhou, Yanchen; Agudelo, Juliet; Lu, Kai; Goetz, David H.; Hansell, Elizabeth; Chen, Yen Ting; Roush, William R.; McKerrow, James; Craik, Charles S.; Amberg, Sean M.; Simmons, Graham

2011-01-01

Severe acute respiratory syndrome-associated coronavirus (SARS-CoV) emerged as the causal agent of an endemic atypical pneumonia, infecting thousands of people worldwide. Although a number of promising potential vaccines and therapeutic agents for SARS-CoV have been described, no effective antiviral drug against SARS-CoV is currently available. The intricate, sequential nature of the viral entry process provides multiple valid targets for drug development. Here, we describe a rapid and safe cell-based high-throughput screening system, Dual Envelope Pseudovirion (DEP) Assay, for specifically screening inhibitors of viral entry. The assay system employs a novel dual envelope strategy, using lentiviral pseudovirions as targets whose entry is driven by the SARS-CoV Spike glycoprotein. A second, unrelated viral envelope is used as an internal control to reduce the number of false positives. As an example of the power of this assay a class of inhibitors is reported with the potential to inhibit SARS-CoV at two steps of the replication cycle, viral entry and particle assembly. This assay system can be easily adapted to screen entry inhibitors against other viruses with the careful selection of matching partner virus envelopes. PMID:21820471

Trajectory optimization study of a lifting body re-entry vehicle for medium to intermediate range applications

NASA Astrophysics Data System (ADS)

Rizvi, S. Tauqeer ul Islam; Linshu, He; ur Rehman, Tawfiq; Rafique, Amer Farhan

2012-11-01

A numerical optimization study of lifting body re-entry vehicles is presented for nominal as well as shallow entry conditions for Medium and Intermediate Range applications. Due to the stringent requirement of a high degree of accuracy for conventional vehicles, lifting re-entry can be used to attain the impact at the desired terminal flight path angle and speed and thus can potentially improve accuracy of the re-entry vehicle. The re-entry of a medium range and intermediate range vehicles is characterized by very high negative flight path angle and low re-entry speed as compared to a maneuverable re-entry vehicle or a common aero vehicle intended for an intercontinental range. Highly negative flight path angles at the re-entry impose high dynamic pressure as well as heat loads on the vehicle. The trajectory studies are carried out to maximize the cross range of the re-entry vehicle while imposing a maximum dynamic pressure constraint of 350 KPa with a 3 MW/m2 heat rate limit. The maximum normal acceleration and the total heat load experienced by the vehicle at the stagnation point during the maneuver have been computed for the vehicle for possible future conceptual design studies. It has been found that cross range capability of up to 35 km can be achieved with a lifting-body design within the heat rate and the dynamic pressure boundary at normal entry conditions. For shallow entry angle of -20 degree and intermediate ranges a cross range capability of up to 250 km can be attained for a lifting body design with less than 10 percent loss in overall range. The normal acceleration also remains within limits. The lifting-body results have also been compared with wing-body results at shallow entry condition. An hp-adaptive pseudo-spectral method has been used for constrained trajectory optimization.

19 CFR 132.24 - Entry.

Code of Federal Regulations, 2011 CFR

2011-04-01

... 19 Customs Duties 1 2011-04-01 2011-04-01 false Entry. 132.24 Section 132.24 Customs Duties U.S. CUSTOMS AND BORDER PROTECTION, DEPARTMENT OF HOMELAND SECURITY; DEPARTMENT OF THE TREASURY QUOTAS Mail Importation of Absolute Quota Merchandise § 132.24 Entry. Unless a formal entry or entry by appraisement is...

19 CFR 132.24 - Entry.

Code of Federal Regulations, 2010 CFR

2010-04-01

... 19 Customs Duties 1 2010-04-01 2010-04-01 false Entry. 132.24 Section 132.24 Customs Duties U.S. CUSTOMS AND BORDER PROTECTION, DEPARTMENT OF HOMELAND SECURITY; DEPARTMENT OF THE TREASURY QUOTAS Mail Importation of Absolute Quota Merchandise § 132.24 Entry. Unless a formal entry or entry by appraisement is...

19 CFR 142.16 - Entry summary documentation.

Code of Federal Regulations, 2010 CFR

2010-04-01

... 19 Customs Duties 2 2010-04-01 2010-04-01 false Entry summary documentation. 142.16 Section 142.16... TREASURY (CONTINUED) ENTRY PROCESS Entry Summary Documentation § 142.16 Entry summary documentation. (a) Entry summary not filed at time of entry. When the entry documentation is filed before the entry summary...

A Light-Weight Inflatable Hypersonic Drag Device for Planetary Entry

NASA Technical Reports Server (NTRS)

McRonald, Angus D.

1995-01-01

The author has analyzed the use of a light-weight inflatable hypersonic drag device, called a ballute, (balloon + parachute) for flight in planetary atmospheres, for entry, aerocapture, and aerobraking. Studies to date include missions to Mars, Venus, Earth, Saturn, Titan, Neptune and Pluto. Data on a Pluto lander and a Mars orbiter will be presented to illustrate the concept. The main advantage of using a ballute is that aero deceleration and heating in atmospheric entry occurs at much smaller atmospheric density with a ballute than without it. For example, if a ballute has a diameter 10 times as large as the spacecraft, for unchanged total mass, entry speed and entry angle,the atmospheric density at peak convective heating is reduced by a factor of 100, reducing the peak heating by a factor of 10 for the spacecraft, and a factor of about 30 for the ballute. Consequently the entry payload (lander, orbiter, etc) is subject to much less heating, requires a much reduced thermal protection system (possibly only an MLI blanket), and the spacecraft design is therefore relatively unchanged from its vacuum counterpart. The heat flux on the ballute is small enough to be radiated at temperatures below 800 K or so. Also, the heating may be reduced further because the ballute enters at a more shallow angle, even allowing for the increased delivery angle error. Added advantages are a smaller mass ratio of entry system to total entry mass, and freedom from the low-density and transonic instability problems that conventional rigid entry bodies suffer, since the vehicle attitude is determined by the ballute, usually released at continuum conditions (hypersonic for an orbiter, and subsonic for a lander). Also, for a lander the range from entry to touchdown is less, offering a smaller footprint. The ballute derives an entry corridor for aerocapture by entering on a path that would lead to landing, and releasing the ballute adaptively, responding to measured deceleration, at a speed

A Light-Weight Inflatable Hypersonic Drag Device for Planetary Entry

NASA Technical Reports Server (NTRS)

McRonald, Angus D.

2000-01-01

The author has analyzed the use of a light-weight inflatable hypersonic drag device, called a ballute, for flight in planetary atmospheres, for entry, aerocapture, and aerobraking. Studies to date include Mars, Venus, Earth, Saturn, Titan, Neptune and Pluto, and data on a Pluto lander and a Mars orbiter will be presented to illustrate the concept. The main advantage of using a ballute is that aero, deceleration and heating in atmospheric entry occurs at much smaller atmospheric density with a ballute than without it. For example, if a ballute has a diameter 10 times as large as the spacecraft, for unchanged total mass, entry speed and entry angle,the atmospheric density at peak convective heating is reduced by a factor of 100, reducing the heating by a factor of 10 for the spacecraft and a factor of 30 for the ballute. Consequently the entry payload (lander, orbiter, etc) is subject to much less heating, requires a much reduced thermal. protection system (possibly only an MLI blanket), and the spacecraft design is therefore relatively unchanged from its vacuum counterpart. The heat flux on the ballute is small enough to be radiated at temperatures below 800 K or so. Also, the heating may be reduced further because the ballute enters at a more shallow angle, even allowing for the increased delivery angle error. Added advantages are less mass ratio of entry system to total entry mass, and freedom from the low-density and transonic instability problems that conventional rigid entry bodies suffer, since the vehicle attitude is determined by the ballute, usually released at continuum conditions (hypersonic for an orbiter, and subsonic for a lander). Also, for a lander the range from entry to touchdown is less, offering a smaller footprint. The ballute derives an entry corridor for aerocapture by entering on a path that would lead to landing, and releasing the ballute adaptively, responding to measured deceleration, at a speed computed to achieve the desired orbiter exit

Enhanced attention amplifies face adaptation.

PubMed

Rhodes, Gillian; Jeffery, Linda; Evangelista, Emma; Ewing, Louise; Peters, Marianne; Taylor, Libby

2011-08-15

Perceptual adaptation not only produces striking perceptual aftereffects, but also enhances coding efficiency and discrimination by calibrating coding mechanisms to prevailing inputs. Attention to simple stimuli increases adaptation, potentially enhancing its functional benefits. Here we show that attention also increases adaptation to faces. In Experiment 1, face identity aftereffects increased when attention to adapting faces was increased using a change detection task. In Experiment 2, figural (distortion) face aftereffects increased when attention was increased using a snap game (detecting immediate repeats) during adaptation. Both were large effects. Contributions of low-level adaptation were reduced using free viewing (both experiments) and a size change between adapt and test faces (Experiment 2). We suggest that attention may enhance adaptation throughout the entire cortical visual pathway, with functional benefits well beyond the immediate advantages of selective processing of potentially important stimuli. These results highlight the potential to facilitate adaptive updating of face-coding mechanisms by strategic deployment of attentional resources. Copyright © 2011 Elsevier Ltd. All rights reserved.

Evaluation of a family-centered prevention intervention for military children and families facing wartime deployments.

PubMed

Lester, Patricia; Saltzman, William R; Woodward, Kirsten; Glover, Dorie; Leskin, Gregory A; Bursch, Brenda; Pynoos, Robert; Beardslee, William

2012-03-01

We evaluated the Families OverComing Under Stress program, which provides resiliency training designed to enhance family psychological health in US military families affected by combat- and deployment-related stress. We performed a secondary analysis of Families OverComing Under Stress program evaluation data that was collected between July 2008 and February 2010 at 11 military installations in the United States and Japan. We present data at baseline for 488 unique families (742 parents and 873 children) and pre-post outcomes for 331 families. Family members reported high levels of satisfaction with the program and positive impact on parent-child indicators. Psychological distress levels were elevated for service members, civilian parents, and children at program entry compared with community norms. Change scores showed significant improvements across all measures for service member and civilian parents and their children (P < .001). Evaluation data provided preliminary support for a strength-based, trauma-informed military family prevention program to promote resiliency and mitigate the impact of wartime deployment stress.

Orion Entry Monitor

NASA Technical Reports Server (NTRS)

Smith, Kelly M.

2016-01-01

NASA is scheduled to launch the Orion spacecraft atop the Space Launch System on Exploration Mission 1 in late 2018. When Orion returns from its lunar sortie, it will encounter Earth's atmosphere with speeds in excess of 11 kilometers per second, and Orion will attempt its first precision-guided skip entry. A suite of flight software algorithms collectively called the Entry Monitor has been developed in order to enhance crew situational awareness and enable high levels of onboard autonomy. The Entry Monitor determines the vehicle capability footprint in real-time, provides manual piloting cues, evaluates landing target feasibility, predicts the ballistic instantaneous impact point, and provides intelligent recommendations for alternative landing sites if the primary landing site is not achievable. The primary engineering challenges of the Entry Monitor is in the algorithmic implementation in making a highly reliable, efficient set of algorithms suitable for onboard applications.

Drag De-Orbit Device: A New Standard Re-Entry Actuator for CubeSats

NASA Technical Reports Server (NTRS)

Guglielmo, David; Omar, Sanny; Bevilacqua, Riccardo

2017-01-01

With the advent of CubeSats, research in Low Earth Orbit (LEO) becomes possible for universities and small research groups. Only a handful of launch sites can be used, due to geographical and political restrictions. As a result, common orbits in LEO are becoming crowded due to the additional launches made possible by low-cost access to space. CubeSat design principles require a maximum of a 25-year orbital lifetime in an effort to reduce the total number of spacecraft in orbit at any time. Additionally, since debris may survive re-entry, it is ideal to de-orbit spacecraft over unpopulated areas to prevent casualties. The Drag Deorbit Device (D3) is a self-contained targeted re-entry subsystem intended for CubeSats. By varying the cross-wind area, the atmospheric drag can be varied in such a way as to produce desired maneuvers. The D3 is intended to be used to remove spacecraft from orbit to reach a desired target interface point. Additionally, attitude stabilization is performed by the D3 prior to deployment and can replace a traditional ADACS on many missions.This paper presents the hardware used in the D3 and operation details. Four stepper-driven, repeatedly retractable booms are used to modify the cross-wind area of the D3 and attached spacecraft. Five magnetorquers (solenoids) over three axes are used to damp rotational velocity. This system is expected to be used to improve mission flexibility and allow additional launches by reducing the orbital lifetime of spacecraft.The D3 can be used to effect a re-entry to any target interface point, with the orbital inclination limiting the maximum latitude. In the chance that the main spacecraft fails, a timer will automatically deploy the booms fully, ensuring the spacecraft will at the minimum reenter the atmosphere in the minimum possible time, although not necessarily at the desired target interface point. Although this does not reduce the risk of casualties, the 25-year lifetime limit is still respected, allowing

Determination of Barometric Altimeter Errors for the Orion Exploration Flight Test-1 Entry

NASA Technical Reports Server (NTRS)

Brown, Denise L.; Munoz, Jean-Philippe; Gay, Robert

2011-01-01

The EFT-1 mission is the unmanned flight test for the upcoming Multi-Purpose Crew Vehicle (MPCV). During entry, the EFT-1 vehicle will trigger several Landing and Recovery System (LRS) events, such as parachute deployment, based on onboard altitude information. The primary altitude source is the filtered navigation solution updated with GPS measurement data. The vehicle also has three barometric altimeters that will be used to measure atmospheric pressure during entry. In the event that GPS data is not available during entry, the altitude derived from the barometric altimeter pressure will be used to trigger chute deployment for the drogues and main parachutes. Therefore it is important to understand the impact of error sources on the pressure measured by the barometric altimeters and on the altitude derived from that pressure. There are four primary error sources impacting the sensed pressure: sensor errors, Analog to Digital conversion errors, aerodynamic errors, and atmosphere modeling errors. This last error source is induced by the conversion from pressure to altitude in the vehicle flight software, which requires an atmosphere model such as the US Standard 1976 Atmosphere model. There are several secondary error sources as well, such as waves, tides, and latencies in data transmission. Typically, for error budget calculations it is assumed that all error sources are independent, normally distributed variables. Thus, the initial approach to developing the EFT-1 barometric altimeter altitude error budget was to create an itemized error budget under these assumptions. This budget was to be verified by simulation using high fidelity models of the vehicle hardware and software. The simulation barometric altimeter model includes hardware error sources and a data-driven model of the aerodynamic errors expected to impact the pressure in the midbay compartment in which the sensors are located. The aerodynamic model includes the pressure difference between the midbay

Side-Branch and Coaxial Intravascular Ultrasound Guided Wire Re-Entry after Failed Retrograde Approach of Chronic Total Occlusion Intervention.

PubMed

Chou, Ruey-Hsing; Lai, Chih-Hung; Lu, Tse-Min

2016-05-01

Intravascular ultrasound (IVUS) can provide valuable information during the intervention of difficult chronic total occlusion (CTO) lesion. Stumpless CTO lesions with an adjacent side branch are associated with a significantly lower success rate because the proper entry point is not always clearly identified and the guidewires easily slip into the side branch. Herein we presented a case of a stumpless middle left circumflex (LCX) artery CTO lesion with auto-collateral from obtuse marginal branch. Initially, we positioned the IVUS into the side-branch to find the entry point of LCX-CTO lesion. However, the punctured wire went into the false lumen. A retrograde approach was tried but later failed. Therefore, we used IVUS to find the entry point where the true lumen transited to the false lumen, and used a stiff guidewire to puncture the entry point. After we confirmed with IVUS that the whole guidewire was in the true lumen, we deployed 3 drug-eluting stents. The final angiogram showed TIMI 3 flow with preservation of all side branches. The patient was angina-free during the 6-month follow-up. By presenting this case, we have demonstrated the application of both side-branch and coaxial IVUS-guided recanalization technique in the stumpless CTO lesion.

Deployment Pulmonary Health

DTIC Science & Technology

2015-02-11

A similar risk-based approach may be appropriate for deploying military personnel. e) If DoD were to consider implementing a large- scale pre...quality of existing spirometry programs prior to considering a larger scale pre-deployment effort. Identifying an accelerated decrease in spirometry...baseline spirometry on a wider scale . e) Conduct pre-deployment baseline spirometry if there is a significant risk of exposure to a pulmonary hazard based

Atmospheric Entry Studies for Venus Missions: 45 Sphere-Cone Rigid Aeroshells and Ballistic Entries

NASA Technical Reports Server (NTRS)

Prabhu, Dinesh K.; Spilker, Thomas R.; Allen, Gary A., Jr.; Hwang, Helen H.; Cappuccio, Gelsomina; Moses, Robert W.

2013-01-01

The present study considers direct ballistic entries into the atmosphere of Venus using a 45deg sphere-cone rigid aeroshell, a legacy shape that has been used successfully in the past in the Pioneer Venus Multiprobe Mission. For a number of entry mass and heatshield diameter combinations (i.e., various ballistic coefficients) and entry velocities, the trajectory space in terms of entry flight path angles between skip out and -30deg is explored with a 3DoF trajectory code, TRAJ. From these trajectories, the viable entry flight path angle space is determined through the use of mechanical and thermal performance limits on the thermal protection material and science payload; the thermal protection material of choice is entry-grade carbon phenolic, for which a material thermal response model is available. For mechanical performance, a 200 g limit is placed on the peak deceleration load experienced by the science instruments, and 10 bar is assumed as the pressure limit for entry-grade carbon-phenolic material. For thermal performance, inflection points in the total heat load distribution are used as cut off criteria. Analysis of the results shows the existence of a range of critical ballistic coefficients beyond which the steepest possible entries are determined by the pressure limit of the material rather than the deceleration load limit.

Aerodynamic Coefficients from Aeroballistic Range Testing of Deployed- and Stowed-SIAD SFDT Models

NASA Technical Reports Server (NTRS)

Wilder, Michael C.; Brown, Jeffrey D.; Bogdanoff, David W.; Yates, Leslie A.; Dyakonov, Artem A.; Clark, Ian G.; Grinstead, Jay H.

2017-01-01

This report documents a ballistic-range test campaign conducted in 2012 in order to estimate the aerodynamic stability characteristics of two configurations of the Supersonic Flight Dynamics Test (SFDT) vehicle prior to its initial flight in 2014. The SFDT vehicle was a test bed for demonstrating several new aerodynamic decelerator technologies then being developed under the Low-Density Supersonic Decelerator (LDSD) Project. Of particular interest here is the Supersonic Inflatable Aerodynamic Decelerator (SIAD), an inflatable attached torus used to increase the drag surface area of an entry vehicle during the supersonic portion of the entry trajectory. Two model configurations were tested in the ballistic range: one representing the SFDT vehicle prior to deployment of the SIAD, and the other representing the nominal shape with the SIAD inflated. Both models were fabricated from solid metal, and therefore, the effects of the flexibility of the inflatable decelerator were not considered. The test conditions were chosen to match, as close as possible, the Mach number, Reynolds number, and motion dynamics expected for the SFDT vehicle in flight, both with the SIAD stowed and deployed. For SFDT models with the SIAD stowed, 12 shots were performed covering a Mach number range of 3.2 to 3.7. For models representing the deployed SIAD, 37 shots were performed over a Mach number range of 2.0 to 3.8. Pitch oscillation amplitudes covered a range from 0.7 to 20.6 degrees RMS. Portions of this report (data analysis approach, aerodynamic modeling, and resulting aerodynamic coefficients) were originally published as an internal LDSD Project report [1] in 2012. In addition, this report provides a description of the test design approach, the test facility, and experimental procedures. Estimated non-linear aerodynamic coefficients, including pitch damping, for both model configurations are reported, and the shot-by-shot trajectory measurements, plotted in comparison with calculated

Identification of a D-amino acid decapeptide HIV-1 entry inhibitor

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

Boggiano, Cesar; Jiang Shibo; Lu Hong

2006-09-08

Entry of human immunodeficiency virus type 1 (HIV-1) virion into host cells involves three major steps, each being a potential target for the development of entry inhibitors: gp120 binding to CD4, gp120-CD4 complex interacting with a coreceptor, and gp41 refolding to form a six-helix bundle. Using a D-amino acid decapeptide combinatorial library, we identified peptide DC13 as having potent HIV-1 fusion inhibitory activity, and effectively inhibiting infection by several laboratory-adapted and primary HIV-1 strains. While DC13 did not block binding of gp120 to CD4, nor disrupt the gp41 six-helix bundle formation, it effectively blocked the binding of an anti-CXCR4 monoclonalmore » antibody and chemokine SDF-1{alpha} to CXCR4-expressing cells. However, because R5-using primary viruses were also neutralized, the antiviral activity of DC13 implies additional mode(s) of action. These results suggest that DC13 is a useful HIV-1 coreceptor antagonist for CXCR4 and, due to its biostability and simplicity, may be of value for developing a new class of HIV-1 entry inhibitors.« less

Titan Lifting Entry & Atmospheric Flight (T-LEAF) Science Mission

NASA Astrophysics Data System (ADS)

Lee, G.; Sen, B.; Ross, F.; Sokol, D.

2016-12-01

Northrop Grumman has been developing the Titan Lifting Entry & Atmospheric Flight (T-LEAF) sky rover to roam the lower atmosphere and observe at close quarters the lakes and plains of Saturn's ocean moon, Titan. T-LEAF also supports surface exploration and science by providing precision delivery of in-situ instruments to the surface of Titan. T-LEAF is a highly maneuverable sky rover and its aerodynamic shape (i.e., a flying wing) does not restrict it to following prevailing wind patterns on Titan, but allows mission operators to chart its course. This freedom of mobility allows T-LEAF to follow the shorelines of Titan's methane lakes, for example, or to target very specific surface locations. We will present a straw man concept of T-LEAF, including size, mass, power, on-board science payloads and measurement, and surface science dropsonde deployment CONOPS. We will discuss the various science instruments and their vehicle level impacts, such as meteorological and electric field sensors, acoustic sensors for measuring shallow depths, multi-spectral imagers, high definition cameras and surface science dropsondes. The stability of T-LEAF and its long residence time on Titan will provide for time to perform a large aerial survey of select prime surface targets deployment of dropsondes at selected locations surface measurements that are coordinated with on-board remote measurements communication relay capabilities to orbiter (or Earth). In this context, we will specifically focus upon key factors impacting the design and performance of T-LEAF science: science payload accommodation, constraints and opportunities characteristics of flight, payload deployment and measurement CONOPS in the Titan atmosphere. This presentation will show how these factors provide constraints as well as enable opportunities for novel long duration scientific studies of Titan's surface.

The Successful Deployment of a New Sub-Seafloor Observatory

NASA Astrophysics Data System (ADS)

Lado Insua, T.; Moran, K.; Kulin, I.; Farrington, S.; Newman, J. B.; Riedel, M.; Iturrino, G. J.; Masterson, W. A.; Furman, C. R.; Klaus, A.; Storms, M.; Attryde, J.; Hetmaniak, C.; Huey, D.

2013-12-01

The Simple Cabled Instrument for Measuring Parameters In-Situ (SCIMPI) is a new ocean observatory instrument designed to study dynamic processes in the sub-seafloor. The first SCIMPI prototype comprises nine modules that collect time series measurements of temperature, pressure and electrical resistivity of sediments at pre-selected depths below seafloor. These modules are joined in an array by flexible cables. Floats are attached to the cables of the system to keep the cabling taught against the weight of a sinker bar at the bottom of the string. The system was designed for deployment through drillpipe using D/V JOIDES Resolution. SCIMPI is designed for sediments that will collapse around the observatory after deployment. After five years in development, SCIMPI was successfully deployed within the NEPTUNE Canada observatory in May 2013. The IODP Expedition 341S took place on the Cascadia Margin. The deployment Site U1416 is within an active gas hydrate vent field. Spacing of SCIMPI modules was tailored to measure parameters in the accreted sediment and above and below the Bottom Simulating Reflector (BSR). The location of the modules was dimensioned based on a multivariate analysis of physical properties derived from IODP boreholes located nearby. Members of the SCIMPI team, science party, technical support, crew and participants of the School of Rock assembled the instrument on deck during the days leading up to the deployment. During deployment, SCIMPI was connected to the Multi-Function-Telemetry-Module (from LDEO) and was lowered through drillpipe on the wireline logging cable. SCIMPI communicated data to a shipboard computer until its release, providing assurance that measurements were active on all sensors. The observatory was released with the Electronic Release System (ERS) and the drillpipe was pulled out of the borehole. A camera system was used to check on the installation immediately after deployment. An Ocean Networks Canada expedition revisited the

19 CFR 141.61 - Completion of entry and entry summary documentation.

Code of Federal Regulations, 2010 CFR

2010-04-01

... on CBP Form 7501. (e) Statistical information—(1) Information required on entry summary or withdrawal... a separate statistical reporting number, the applicable information required by the General Statistical Notes, Harmonized Tariff Schedule of the United States (HTSUS), must be shown on the entry summary...

Adaptive Signal Timing Comparison Between the InSync and QuicTrac Adaptive Signal Systems Installed in Colorado

DOT National Transportation Integrated Search

2012-07-01

The FHWAs Every Day Counts (EDC) initiative identifies adaptive signal control as a tool for local agencies to deploy : innovation. In an effort to achieve the goals of the EDC initiative, the traffic sections of the Colorado Department of : Trans...

Inflatable re-entry shield ready for test in space

NASA Astrophysics Data System (ADS)

2000-02-01

The Russian spacecraft Mars'96 for instance, which was launched in November 1996 but failed to reach its nominal orbit, carried two modules designed to land on that planet's surface. For the last part of the mission, an Inflatable Re-Entry and Descent Technology (IRDT) had been deployed. The main components of this system were an aerobraking and thermally protective shell, a densely packed inflating material and a pressurisation system. This technology is now considered applicable to other re-entry scenarios such as payload recovery from the International Space Station, planetary landers for science missions and atmospheric research. A demonstration mission on 9/10 February 2000 will evaluate the performance of this new technology before it is offered to potential users. A Russian Soyuz/Fregat launcher, lifting off from the Kazakh steppe near Baikonur, will provide a low-cost flight opportunity for the test vehicle, which is equipped with the inflatable heat shield and a sensor package developed by DaimlerChrysler Aerospace (DASA). After four orbits around the Earth, the test vehicle will be powered by the launcher's upper stage to re-enter the atmosphere for a landing the next day about 1800 km north-west of the launch site. During the mission, a number of technical parameters such as pressure, temperature and deceleration will be monitored and the inflation of the re-entry/descent structure observed. "From this novel technology, we are expecting a major breakthrough, to make re-entry of small payloads more and more reliable, simpler and less costly than traditional systems", explains Dieter Kassing, ESA's IRDT project manager. One of the main instruments on board the test vehicle is a sensor device developed by the University of Stuttgart for the determination of oxygen partial pressure in low Earth orbit and during re-entry. The scientific/technical investigations will be led by Dr. Ulrich Schoettle (Stuttgart University). Lionel Marraffa (ESA) will lead the

Shape Morphing Adaptive Radiator Technology (SMART) Updates to Techport Entry

NASA Technical Reports Server (NTRS)

Erickson, Lisa; Bertagne, Christopher; Hartl, Darren; Witcomb, John; Cognata, Thomas

2017-01-01

The Shape-Morphing Adaptive Radiator Technology (SMART) project builds off the FY16 research effort that developed a flexible composite radiator panel and demonstrated its ability to actuate from SMA's attached to it. The proposed FY17 Shape-Morphing Adaptive Radiator Technology (SMART) project's goal is to 1) develop a practical radiator design with shape memory alloys (SMAs) bonded to the radiator's panel, and 2) build a multi-panel radiator prototype for subsequent system level thermal vacuum tests. The morphing radiator employs SMA materials to passively change its shape to adapt its rate of heat rejection to vehicle requirements. Conceptually, the radiator panel has a naturally closed position (like a cylinder) in a cold environment. Whenever the radiator's temperature gradually rises, SMA's affixed to the face sheet will pull the face sheet open a commensurate amount - increasing the radiators view to space and causing it to reject more heat. In a vehicle, the radiator's variable heat rejection capabilities would reduce the number of additional heat rejection devices in a vehicle's thermal control system. This technology aims to help achieve the required maximum to minimum heat rejection ratio required for manned space vehicles to adopt a lighter, simpler, single loop thermal control architecture (ATCS). Single loop architectures are viewed as an attractive means to reduce mass and complexity over traditional dual-loop solutions. However, fluids generally considered safe enough to flow within crewed cabins (e.g. propylene glycol-water mixtures) have much higher freezing points and viscosities than those used in the external sides of dual loop ATCSs (e.g. Ammonia and HFE7000).

Towards deployable meta-implants.

PubMed

Bobbert, F S L; Janbaz, S; Zadpoor, A A

2018-06-07

Meta-biomaterials exhibit unprecedented or rare combinations of properties not usually found in nature. Such unusual mechanical, mass transport, and biological properties could be used to develop novel categories of orthopedic implants with superior performance, otherwise known as meta-implants. Here, we use bi-stable elements working on the basis of snap-through instability to design deployable meta-implants. Deployable meta-implants are compact in their retracted state, allowing them to be brought to the surgical site with minimum invasiveness. Once in place, they are deployed to take their full-size load-bearing shape. We designed five types of meta-implants by arranging bi-stable elements in such a way to obtain a radially-deployable structure, three types of auxetic structures, and an axially-deployable structure. The intermediate stable conditions ( i.e. multi-stability features), deployment force, and stiffness of the meta-implants were found to be strongly dependent on the geometrical parameters of the bi-stable elements as well as on their arrangement.

ADAPTATION TO POVERTY IN LONG-RUN PANEL DATA

PubMed Central

Clark, Andrew E.; D’Ambrosio, Conchita; Ghislandi, Simone

2017-01-01

We consider the link between poverty and subjective well-being and focus in particular on potential adaptation to poverty. We use panel data on almost 54,000 individuals living in Germany from 1985 to 2012 to show, first, that life satisfaction falls with both the incidence and intensity of contemporaneous poverty. We then reveal that there is little evidence of adaptation within a poverty spell: poverty starts bad and stays bad in terms of subjective well-being. We cannot identify any cause of poverty entry that explains the overall lack of poverty adaptation. PMID:28690342

Entry, Descent, and Landing Communications for the 2011 Mars Science Laboratory

NASA Technical Reports Server (NTRS)

Abilleira, Fernando; Shidner, Jeremy D.

2012-01-01

The Mars Science Laboratory (MSL), established as the most advanced rover to land on the surface of Mars to date, launched on November 26th, 2011 and arrived to the Martian Gale Crater during the night of August 5th, 2012 (PDT). MSL will investigate whether the landing region was ever suitable to support carbon-based life, and examine rocks, soil, and the atmosphere with a sophisticated suite of tools. This paper addresses the flight system requirement by which the vehicle transmitted indications of the following events using both X-band tones and UHF telemetry to allow identification of probable root causes should a mission anomaly have occurred: Heat-Rejection System (HRS) venting, completion of the cruise stage separation, turn to entry attitude, atmospheric deceleration, bank angle reversal commanded, parachute deployment, heatshield separation, radar ground acquisition, powered descent initiation, rover separation from the descent stage, and rover release. During Entry, Descent, and Landing (EDL), the flight system transmitted a UHF telemetry stream adequate to determine the state of the spacecraft (including the presence of faults) at 8 kbps initiating from cruise stage separation through at least one minute after positive indication of rover release on the surface of Mars. The flight system also transmitted X-band semaphore tones from Entry to Landing plus one minute although since MSL was occulted, as predicted, by Mars as seen from the Earth, Direct-To-Earth (DTE) communications were interrupted at approximately is approx. 5 min after Entry ( approximately 130 prior to Landing). The primary data return paths were through the Deep Space Network (DSN) for DTE and the existing Mars network of orbiting assets for UHF, which included the Mars Reconnaissance Orbiter (MRO), Mars Odyssey (ODY), and Mars Express (MEX) elements. These orbiters recorded the telemetry data stream and returned it back to Earth via the DSN. The paper also discusses the total power

Lunar Entry Downmode Options for Orion

NASA Technical Reports Server (NTRS)

Smith, Kelly; Rea, Jeremy

2016-01-01

Traditional ballistic entry does not scale well to higher energy entry trajectories. Clutch algorithm is a two-stage approach with the capture stage and load relief stage. Clutch may offer expansion of the operational entry corridor. Clutch is a candidate solution for Exploration Mission-2's degraded entry mode.

19 CFR 191.143 - Drawback entry.

Code of Federal Regulations, 2010 CFR

2010-04-01

... (CONTINUED) DRAWBACK Foreign-Built Jet Aircraft Engines Processed in the United States § 191.143 Drawback entry. (a) Filing of entry. Drawback entries covering these foreign-built jet aircraft engines shall be filed on Customs Form 7551, modified to show that the entry covers jet aircraft engines processed under...

19 CFR 191.143 - Drawback entry.

Code of Federal Regulations, 2011 CFR

2011-04-01

... (CONTINUED) DRAWBACK Foreign-Built Jet Aircraft Engines Processed in the United States § 191.143 Drawback entry. (a) Filing of entry. Drawback entries covering these foreign-built jet aircraft engines shall be filed on Customs Form 7551, modified to show that the entry covers jet aircraft engines processed under...

Evaluation of Mars Entry Reconstructured Trajectories Based on Hypothetical 'Quick-Look' Entry Navigation Data

NASA Technical Reports Server (NTRS)

Pastor, P. Rick; Bishop, Robert H.; Striepe, Scott A.

2000-01-01

A first order simulation analysis of the navigation accuracy expected from various Navigation Quick-Look data sets is performed. Here quick-look navigation data are observations obtained by hypothetical telemetried data transmitted on the fly during a Mars probe's atmospheric entry. In this simulation study, navigation data consists of 3-axis accelerometer sensor and attitude information data. Three entry vehicle guidance types are studied: I. a Maneuvering entry vehicle (as with Mars 01 guidance where angle of attack and bank angle are controlled); II. Zero angle-of-attack controlled entry vehicle (as with Mars 98); and III. Ballistic, or spin stabilized entry vehicle (as with Mars Pathfinder);. For each type, sensitivity to progressively under sampled navigation data and inclusion of sensor errors are characterized. Attempts to mitigate the reconstructed trajectory errors, including smoothing, interpolation and changing integrator characteristics are also studied.

Advertising and generic market entry.

PubMed

Königbauer, Ingrid

2007-03-01

The effect of purely persuasive advertising on generic market entry and social welfare is analysed. An incumbent has the possibility to invest in advertising which affects the prescribing physician's perceived relative qualities of the brand-name and the generic version of the drug. Advertising creates product differentiation and can induce generic market entry which is deterred without differentiation due to strong Bertrand competition. However, over-investment in advertising can deter generic market entry under certain conditions and reduces welfare as compared to accommodated market entry.

Umbilical Deployment Device

NASA Technical Reports Server (NTRS)

Shafer, Michael W.; Gallon, John C.; Rivellini, Tommaso P.

2011-01-01

The landing scheme for NASA's next-generation Mars rover will encompass a novel landing technique (see figure). The rover will be lowered from a rocket-powered descent stage and then placed onto the surface while hanging from three bridles. Communication between the rover and descent stage will be maintained through an electrical umbilical cable, which will be deployed in parallel with structural bridles. The -inch (13-mm) umbilical cable contains a Kevlar rope core, around which wires are wrapped to create a cable. This cable is helically coiled between two concentric truncated cones. It is deployed by pulling one end of the cable from the cone. A retractable mechanism maintains tension on the cable after deployment. A break-tie tethers the umbilical end attached to the rover even after the cable is cut after touchdown. This break-tie allows the descent stage to develop some velocity away from the rover prior to the cable releasing from the rover deck, then breaks away once the cable is fully extended. The descent stage pulls the cable up so that recontact is not made. The packaging and deployment technique can store a long length of cable in a relatively small volume while maintaining compliance with the minimum bend radius requirement for the cable being deployed. While the packaging technique could be implemented without the use of break-ties, they were needed in this design due to the vibratory environment and the retraction required by the cable. The break-ties used created a series of load-spikes in the deployment signature. The load spikes during the deployment of the initial three coils of umbilical showed no increase between the different temperature trials. The cold deployment did show an increased load requirement for cable extraction in the region where no break-ties were used. This increase in cable drag was superimposed on the loads required to rupture the last set of break-ties, and as such, these loads saw significant increase when compared to

Cassini/Huygens Probe Entry, Descent, and Landing (EDL) at Titan Independent Technical Assessment

NASA Technical Reports Server (NTRS)

Powell, Richard W.; Lockwood, Mary Kae; Cruz, Juan R.; Striepe, Scott A.; Sutton, Kenneth; Fisher, Jody; Takashima, Naruhisa T.; Justus, Jere; Keller, Vernon W.; Bose, Deepak;

A fault-tolerant avionics suite for an entry research vehicle

NASA Technical Reports Server (NTRS)

Dzwonczyk, Mark; Stone, Howard

1988-01-01

A highly-reliable avionics suite has been designed for an Entry Research Vehicle. The autonomous spacecraft would be deployed from the Space Shuttle Orbiter and perform a variety of aerodynamic and propulsive maneuvers which may be required for future space transportation system vehicles. The flight electronics consist of a central fault-tolerant processor, which is resilient to all first failures, reliably cross-strapped to redundant and distributed sets of sensors and effectors. This paper describes the preliminary design and analysis of the architecture which resulted from a fifteen month study by the Charles Stark Draper Laboratory for the NASA Langley Research Center. After a brief introduction to the design task, the architecture of the central flight computer and its interface to the vehicle are discussed. Following this, the method and results of the baseline reliability study for the avionic suite are presented.

A fault-tolerant avionics suite for an entry research vehicle

NASA Astrophysics Data System (ADS)

Dzwonczyk, Mark; Stone, Howard

A highly-reliable avionics suite has been designed for an Entry Research Vehicle. The autonomous spacecraft would be deployed from the Space Shuttle Orbiter and perform a variety of aerodynamic and propulsive maneuvers which may be required for future space transportation system vehicles. The flight electronics consist of a central fault-tolerant processor, which is resilient to all first failures, reliably cross-strapped to redundant and distributed sets of sensors and effectors. This paper describes the preliminary design and analysis of the architecture which resulted from a fifteen month study by the Charles Stark Draper Laboratory for the NASA Langley Research Center. After a brief introduction to the design task, the architecture of the central flight computer and its interface to the vehicle are discussed. Following this, the method and results of the baseline reliability study for the avionic suite are presented.

Potentially modifiable pre-, peri-, and postdeployment characteristics associated with deployment-related posttraumatic stress disorder among ohio army national guard soldiers.

PubMed

Goldmann, Emily; Calabrese, Joseph R; Prescott, Marta R; Tamburrino, Marijo; Liberzon, Israel; Slembarski, Renee; Shirley, Edwin; Fine, Thomas; Goto, Toyomi; Wilson, Kimberly; Ganocy, Stephen; Chan, Philip; Serrano, Mary Beth; Sizemore, James; Galea, Sandro

2012-02-01

To evaluate potentially modifiable deployment characteristics-- predeployment preparedness, unit support during deployment, and postdeployment support-that may be associated with deployment-related posttraumatic stress disorder (PTSD). We recruited a sample of 2616 Ohio Army National Guard (OHARNG) soldiers and conducted structured interviews to assess traumatic event exposure and PTSD related to the soldiers' most recent deployment, consistent with DSM-IV criteria. We assessed preparedness, unit support, and postdeployment support by using multimeasure scales adapted from the Deployment Risk and Resilience Survey. The prevalence of deployment-related PTSD was 9.6%. In adjusted logistic models, high levels of all three deployment characteristics (compared with low) were independently associated with lower odds of PTSD. When we evaluated the influence of combinations of deployment characteristics on the development of PTSD, we found that postdeployment support was an essential factor in the prevention of PTSD. Results show that factors throughout the life course of deployment-in particular, postdeployment support-may influence the development of PTSD. These results suggest that the development of suitable postdeployment support opportunities may be centrally important in mitigating the psychological consequences of war. Copyright © 2012 Elsevier Inc. All rights reserved.

Comparison of Two Entry Methods for Laparoscopic Port Entry: Technical Point of View

PubMed Central

Toro, Adriana; Mannino, Maurizio; Cappello, Giovanni; Di Stefano, Andrea; Di Carlo, Isidoro

2012-01-01

Laparoscopic entry is a blind procedure and it often represents a problem for all the related complications. In the last three decades, rapid advances in laparoscopic surgery have made it an invaluable part of general surgery, but there remains no clear consensus on an optimal method of entry into the peritoneal cavity. The aim of this paper is to focus on the evolution of two used methods of entry into the peritoneal cavity in laparoscopic surgery. PMID:22761542

Orion Entry Handling Qualities Assessments

NASA Technical Reports Server (NTRS)

Bihari, B.; Tiggers, M.; Strahan, A.; Gonzalez, R.; Sullivan, K.; Stephens, J. P.; Hart, J.; Law, H., III; Bilimoria, K.; Bailey, R.

2011-01-01

The Orion Command Module (CM) is a capsule designed to bring crew back from the International Space Station (ISS), the moon and beyond. The atmospheric entry portion of the flight is deigned to be flown in autopilot mode for nominal situations. However, there exists the possibility for the crew to take over manual control in off-nominal situations. In these instances, the spacecraft must meet specific handling qualities criteria. To address these criteria two separate assessments of the Orion CM s entry Handling Qualities (HQ) were conducted at NASA s Johnson Space Center (JSC) using the Cooper-Harper scale (Cooper & Harper, 1969). These assessments were conducted in the summers of 2008 and 2010 using the Advanced NASA Technology Architecture for Exploration Studies (ANTARES) six degree of freedom, high fidelity Guidance, Navigation, and Control (GN&C) simulation. This paper will address the specifics of the handling qualities criteria, the vehicle configuration, the scenarios flown, the simulation background and setup, crew interfaces and displays, piloting techniques, ratings and crew comments, pre- and post-fight briefings, lessons learned and changes made to improve the overall system performance. The data collection tools, methods, data reduction and output reports will also be discussed. The objective of the 2008 entry HQ assessment was to evaluate the handling qualities of the CM during a lunar skip return. A lunar skip entry case was selected because it was considered the most demanding of all bank control scenarios. Even though skip entry is not planned to be flown manually, it was hypothesized that if a pilot could fly the harder skip entry case, then they could also fly a simpler loads managed or ballistic (constant bank rate command) entry scenario. In addition, with the evaluation set-up of multiple tasks within the entry case, handling qualities ratings collected in the evaluation could be used to assess other scenarios such as the constant bank angle

Deployable Temporary Shelter

NASA Technical Reports Server (NTRS)

Shaffer, Joe R.; Headley, David E.

1993-01-01

Compact storable components expand to create large shelter. Fully deployed structure provides large, unobstructed bay. Deployed trusses support wall and roof blankets. Provides temporary cover for vehicles, people, and materials. Terrestrial version used as garage, hangar, or large tent.

Safer laparoscopic trocar entry: it's all about pressure.

PubMed

Tsaltas, Jim; Pearce, Scott; Lawrence, Anthony; Meads, Alan; Mezzatesta, Joseph; Nicolson, Scott

2004-08-01

This prospective observational study aimed to assess the feasibility of adapting peritoneal hyperdistention to 25 mmHg during laparoscopy in an Australian hospital environment. A total of 1150 consecutive diagnostic or operative laparoscopies were performed. All cases were monitored for early detection of untoward physiological changes. All patients had Veress needle insufflation with distension to 25 mmHg prior to insertion of the primary trocar. No patients experienced any surgical entry complications or adverse clinical effects noted during anaesthetic. The aim of the current study is to assess the feasibility and safety of increasing the peritoneal insufflation pressure to 25 mmHg for primary trocar insertion.

Deployment-related Respiratory Issues.

PubMed

Morris, Michael J; Rawlins, Frederic A; Forbes, Damon A; Skabelund, Andrew J; Lucero, Pedro F

2016-01-01

Military deployment to Southwest Asia since 2003 in support of Operations Enduring Freedom/Iraqi Freedom/New Dawn has presented unique challenges from a pulmonary perspective. Various airborne hazards in the deployed environment include suspended geologic dusts, burn pit smoke, vehicle exhaust emissions, industrial air pollution, and isolated exposure incidents. These exposures may give rise to both acute respiratory symptoms and in some instances development of chronic lung disease. While increased respiratory symptoms during deployment are well documented, there is limited data on whether inhalation of airborne particulate matter is causally related to an increase in either common or unique pulmonary diseases. While disease processes such as acute eosinophilic pneumonia and exacerbation of preexisting asthma have been adequately documented, there is significant controversy surrounding the potential effects of deployment exposures and development of rare pulmonary disorders such as constrictive bronchiolitis. The role of smoking and related disorders has yet to be defined. This article presents the current evidence for deployment-related respiratory symptoms and ongoing Department of Defense studies. Further, it also provides general recommendations for evaluating pulmonary health in the deployed military population.

Distraction during Deployment: Marital Relationship Associations with Spillover for Deployed Army Soldiers

PubMed Central

Carter, S. P.; Loew, B.; Allen, E. S.; Osborne, L.; Stanley, S. M.; Markman, H. J.

2015-01-01

Military spouses often have concerns regarding the impact of their communication on soldiers during deployment. However, literature is mixed regarding how communication between soldiers and spouses may impact soldiers’ self-reported work functioning during deployment, suggesting the need to evaluate moderating factors. In the current study, three relationship factors (marital satisfaction, conflictual communication, and proportion of conversation focused on problems) were tested as moderators of communication frequency and negative marriage-to-work spillover for soldiers. Whereas the three relationship factors were independently related to negative spillover, none significantly moderated the relationship between communication frequency and spillover. The overall pattern of results suggests that (a) lower marital satisfaction, a focus on problems during communication, and conflictual communication are each strongly linked to spillover for deployed soldiers, and (b) military couples may be self-restricting deployment communication frequency when experiencing less marital satisfaction and higher rates of negative communication. Implications for communication during deployment are discussed. PMID:26236093

Deployment hinge using wraparound strips

NASA Technical Reports Server (NTRS)

Blanc, Eric

1992-01-01

Aerospatiale developed a new appendage deployment concept called AMEDE (French acronym for improvement of deployment mechanisms) with a view toward increased simplicity and functional reliability. This new concept, applicable to the deployment of any type of spaceborne appendage (in particular to solar arrays), enables deployment without synchronization or speed regulation devices. On the other hand, it requires the use of hinges with low driving or resistive torques. The AMEDE concept is compared with the conventional deployment concept. The conceptual and functional principles for the ADELE hinge are presented, as well as the hinges' main characteristics. The development status of both the AMEDE concept and the ADELE (French acronym for deployment hinge using wraparound strips) hinge are addressed.

27. View of entry door to vestibule to MWOC entry ...

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

27. View of entry door to vestibule to MWOC entry door in transmitter building no. 102 (note coded key pad to left and intercom phone on left) and door to the central systems monitor room (CSMR) to right (out of sight). - Clear Air Force Station, Ballistic Missile Early Warning System Site II, One mile west of mile marker 293.5 on Parks Highway, 5 miles southwest of Anderson, Anderson, Denali Borough, AK

Deployment Health

DTIC Science & Technology

2006-08-11

thermo luminescent dosimeter ( TLD badge)) are required for performing specific tasks in a safe manner while deployed, personnel must be trained on the...monitoring devices (e.g., thermo luminescent dosimeter ( TLD badge)) as required by occupational specialty of personnel. (E4.A1.1.5.) 5.5.8 X X...assigned, attached, on temporary duty, or temporary additional duty to deployed units. Report the data electronically to the DMDC (at the SECRET level

Evaluation of a Family-Centered Prevention Intervention for Military Children and Families Facing Wartime Deployments

PubMed Central

Saltzman, William R.; Woodward, Kirsten; Glover, Dorie; Leskin, Gregory A.; Bursch, Brenda; Pynoos, Robert; Beardslee, William

2012-01-01

Objectives. We evaluated the Families OverComing Under Stress program, which provides resiliency training designed to enhance family psychological health in US military families affected by combat- and deployment-related stress. Methods. We performed a secondary analysis of Families OverComing Under Stress program evaluation data that was collected between July 2008 and February 2010 at 11 military installations in the United States and Japan. We present data at baseline for 488 unique families (742 parents and 873 children) and pre–post outcomes for 331 families. Results. Family members reported high levels of satisfaction with the program and positive impact on parent–child indicators. Psychological distress levels were elevated for service members, civilian parents, and children at program entry compared with community norms. Change scores showed significant improvements across all measures for service member and civilian parents and their children (P < .001). Conclusions. Evaluation data provided preliminary support for a strength-based, trauma-informed military family prevention program to promote resiliency and mitigate the impact of wartime deployment stress. PMID:22033756

19 CFR 142.11 - Entry summary form.

Code of Federal Regulations, 2010 CFR

2010-04-01

... 19 Customs Duties 2 2010-04-01 2010-04-01 false Entry summary form. 142.11 Section 142.11 Customs... (CONTINUED) ENTRY PROCESS Entry Summary Documentation § 142.11 Entry summary form. (a) Customs Form 7501. The entry summary shall be on Customs Form 7501 unless a different form is prescribed elsewhere in this...

Optimal firm growth under the threat of entry

PubMed Central

Kort, Peter M.; Wrzaczek, Stefan

2015-01-01

The paper studies the incumbent-entrant problem in a fully dynamic setting. We find that under an open-loop information structure the incumbent anticipates entry by overinvesting, whereas in the Markov perfect equilibrium the incumbent slightly underinvests in the period before the entry. The entry cost level where entry accommodation passes into entry deterrence is lower in the Markov perfect equilibrium. Further we find that the incumbent’s capital stock level needed to deter entry is hump shaped as a function of the entry time, whereas the corresponding entry cost, where the entrant is indifferent between entry and non-entry, is U-shaped. PMID:26435573

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.

Entry and Exit.

DTIC Science & Technology

1987-03-01

1. Introduction R Analyses of industrial competition have attained a new vigor with the application of game -theoretic methods. The process of... competition is represented in models that reflect genuine struggles for entry, market power, and continuing survival. Dynamics and informational effects are...presents a few of the models developed recently to study competitive processes that affect a firm’s entry into a market , and the decision to exit. The

Demographic and academic-related differences between standard-entry and graduate-entry nursing students: a prospective correlational survey.

PubMed

Everett, Bronwyn; Salamonson, Yenna; Trajkovski, Suza; Fernandez, Ritin

2013-07-01

Students who enroll in graduate-entry nursing programs are described as more highly motivated, scoring higher in most learning strategies, and achieving greater academic success than standard-entry nursing students. A prospective correlational design was used to compare the demographic and academic-related characteristics of standard-entry and graduate-entry nursing students in their first year of study. Between 2007 and 2011, students enrolled in the Bachelor of Nursing, Standard Entry and the Bachelor Nursing, Graduate Entry at a large Australian university were surveyed in the first year of their program. Data included English-language usage and time spent in paid work, as well as four dimensions of Pintrich's Motivated Strategies for Learning Questionnaire. Survey data was linked to students' academic grades at the end of the semester. A total of 730 students completed the survey and consented to collection of their academic grades. Graduate-entry students were more likely to be older (28.6 vs. 24.3 years, P < 0.001), and there was a higher percentage of males (25.2% vs. 15.9%, P = 0.003). Although no difference was identified between groups for use of Extrinsic Goal Orientation as a learning strategy, the graduate-entry students were more likely to identify Peer Learning, Help Seeking and Critical Thinking as strategies for learning than the standard-entry students (P < 0.001). Further, while this group of students achieved a higher mean GPA (4.8 vs. 4.0, P < 0.001) compared to the standard-entry students, regression analyses revealed that in both groups, lower levels of English-language proficiency and increased time spent in paid work were predictors of poorer academic performance. Similar to US-based studies, demographic and academic-related differences were identified between standard-entry and graduate-entry nursing students. However, the study also highlights lower levels of English-language proficiency and increased time spent in paid work negatively

31 CFR 363.201 - What other regulations govern book-entry marketable book-entry Treasury bills, notes, and bonds?

Code of Federal Regulations, 2010 CFR

2010-07-01

... 31 Money and Finance: Treasury 2 2010-07-01 2010-07-01 false What other regulations govern book-entry marketable book-entry Treasury bills, notes, and bonds? 363.201 Section 363.201 Money and Finance... Securities § 363.201 What other regulations govern book-entry marketable book-entry Treasury bills, notes...

31 CFR 363.201 - What other regulations govern book-entry marketable book-entry Treasury bills, notes, and bonds?

Code of Federal Regulations, 2012 CFR

2012-07-01

... 31 Money and Finance:Treasury 2 2012-07-01 2012-07-01 false What other regulations govern book-entry marketable book-entry Treasury bills, notes, and bonds? 363.201 Section 363.201 Money and Finance... Securities § 363.201 What other regulations govern book-entry marketable book-entry Treasury bills, notes...

31 CFR 363.201 - What other regulations govern book-entry marketable book-entry Treasury bills, notes, and bonds?

Code of Federal Regulations, 2014 CFR

2014-07-01

... 31 Money and Finance: Treasury 2 2014-07-01 2014-07-01 false What other regulations govern book-entry marketable book-entry Treasury bills, notes, and bonds? 363.201 Section 363.201 Money and Finance... Securities § 363.201 What other regulations govern book-entry marketable book-entry Treasury bills, notes...

31 CFR 363.201 - What other regulations govern book-entry marketable book-entry Treasury bills, notes, and bonds?

Code of Federal Regulations, 2011 CFR

2011-07-01

... 31 Money and Finance:Treasury 2 2011-07-01 2011-07-01 false What other regulations govern book-entry marketable book-entry Treasury bills, notes, and bonds? 363.201 Section 363.201 Money and Finance... Securities § 363.201 What other regulations govern book-entry marketable book-entry Treasury bills, notes...

31 CFR 363.201 - What other regulations govern book-entry marketable book-entry Treasury bills, notes, and bonds?

Code of Federal Regulations, 2013 CFR

2013-07-01

... 31 Money and Finance:Treasury 2 2013-07-01 2013-07-01 false What other regulations govern book-entry marketable book-entry Treasury bills, notes, and bonds? 363.201 Section 363.201 Money and Finance... Securities § 363.201 What other regulations govern book-entry marketable book-entry Treasury bills, notes...

Tera-OP Reliable Intelligently Adaptive Processing System (TRIPS) Implementation

DTIC Science & Technology

2008-09-01

38 6.8 Instruction Scheduling ...39 6.8.1 Spatial Path Scheduling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39 6.8.2...oblivious scheduling for rapid application prototyping and deployment, environmental adaptivity for resilience in hostile environments, and dynamic

High-acceleration cable deployment

NASA Technical Reports Server (NTRS)

Barns, C. E.; Canning, T. N.; Gin, B.; King, R. W.; Murphy, J. P.

1980-01-01

Prototype high-acceleration umbilical-cable deployment allows electrical communication between above-ground instrumentation and ballistic projectile below surface. Cable deployment is made up of forebody and afterbody. Foreboy can be separated from afterbody by rocket, or they can be fired as unit at target that stops afterbody on impact (forebody would continue, deploying cable). Similar design could be used in study of sea ice and in other surface-penetration studies.

A Model for Designing Adaptive Laboratory Evolution Experiments.

PubMed

LaCroix, Ryan A; Palsson, Bernhard O; Feist, Adam M

2017-04-15

The occurrence of mutations is a cornerstone of the evolutionary theory of adaptation, capitalizing on the rare chance that a mutation confers a fitness benefit. Natural selection is increasingly being leveraged in laboratory settings for industrial and basic science applications. Despite increasing deployment, there are no standardized procedures available for designing and performing adaptive laboratory evolution (ALE) experiments. Thus, there is a need to optimize the experimental design, specifically for determining when to consider an experiment complete and for balancing outcomes with available resources (i.e., laboratory supplies, personnel, and time). To design and to better understand ALE experiments, a simulator, ALEsim, was developed, validated, and applied to the optimization of ALE experiments. The effects of various passage sizes were experimentally determined and subsequently evaluated with ALEsim, to explain differences in experimental outcomes. Furthermore, a beneficial mutation rate of 10 -6.9 to 10 -8.4 mutations per cell division was derived. A retrospective analysis of ALE experiments revealed that passage sizes typically employed in serial passage batch culture ALE experiments led to inefficient production and fixation of beneficial mutations. ALEsim and the results described here will aid in the design of ALE experiments to fit the exact needs of a project while taking into account the resources required and will lower the barriers to entry for this experimental technique. IMPORTANCE ALE is a widely used scientific technique to increase scientific understanding, as well as to create industrially relevant organisms. The manner in which ALE experiments are conducted is highly manual and uniform, with little optimization for efficiency. Such inefficiencies result in suboptimal experiments that can take multiple months to complete. With the availability of automation and computer simulations, we can now perform these experiments in an optimized

Gender differences in the effects of deployment-related stressors and pre-deployment risk factors on the development of PTSD symptoms in National Guard Soldiers deployed to Iraq and Afghanistan.

PubMed

Polusny, Melissa A; Kumpula, Mandy J; Meis, Laura A; Erbes, Christopher R; Arbisi, Paul A; Murdoch, Maureen; Thuras, Paul; Kehle-Forbes, Shannon M; Johnson, Alexandria K

2014-02-01

Although women in the military are exposed to combat and its aftermath, little is known about whether combat as well as pre-deployment risk/protective factors differentially predict post-deployment PTSD symptoms among women compared to men. The current study assesses the influence of combat-related stressors and pre-deployment risk/protective factors on women's risk of developing PTSD symptoms following deployment relative to men's risk. Participants were 801 US National Guard Soldiers (712 men, 89 women) deployed to Iraq or Afghanistan who completed measures of potential risk/protective factors and PTSD symptoms one month before deployment (Time 1) and measures of deployment-related stressors and PTSD symptoms about 2-3 months after returning from deployment (Time 2). Men reported greater exposure to combat situations than women, while women reported greater sexual stressors during deployment than men. Exposure to the aftermath of combat (e.g., witnessing injured/dying people) did not differ by gender. At Time 2, women reported more severe PTSD symptoms and higher rates of probable PTSD than did men. Gender remained a predictor of higher PTSD symptoms after accounting for pre-deployment symptoms, prior interpersonal victimization, and combat related stressors. Gender moderated the association between several risk factors (combat-related stressors, prior interpersonal victimization, lack of unit support and pre-deployment concerns about life/family disruptions) and post-deployment PTSD symptoms. Elevated PTSD symptoms among female service members were not explained simply by gender differences in pre-deployment or deployment-related risk factors. Combat related stressors, prior interpersonal victimization, and pre-deployment concerns about life and family disruptions during deployment were differentially associated with greater post-deployment PTSD symptoms for women than men. Copyright © 2013 The Authors. Published by Elsevier Ltd.. All rights reserved.

Deployable geodesic truss structure

NASA Technical Reports Server (NTRS)

Mikulas, Martin M., Jr. (Inventor); Rhodes, Marvin D. (Inventor); Simonton, J. Wayne (Inventor)

1987-01-01

A deployable geodesic truss structure which can be deployed from a stowed state to an erected state is described. The truss structure includes a series of bays, each bay having sets of battens connected by longitudinal cross members which give the bay its axial and torsional stiffness. The cross members are hinged at their mid point by a joint so that the cross members are foldable for deployment or collapsing. The bays are deployed and stabilized by actuator means connected between the mid point joints of the cross members. Hinged longerons may be provided to also connect the sets of battens and to collapse for stowing with the rest of the truss structure.

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.

Nanosatellite Launch Adapter System (NLAS)

NASA Technical Reports Server (NTRS)

Chartres, James; Cappuccio, Gelsomina

2015-01-01

The Nanosatellite Launch Adapter System (NLAS) was developed to increase access to space while simplifying the integration process of miniature satellites, called nanosats or CubeSats, onto launch vehicles. A standard CubeSat measures about 10 cm square, and is referred to as a 1-unit (1U) CubeSat. A single NLAS provides the capability to deploy 24U of CubeSats. The system is designed to accommodate satellites measuring 1U, 1.5U, 2U, 3U and 6U sizes for deployment into orbit. The NLAS may be configured for use on different launch vehicles. The system also enables flight demonstrations of new technologies in the space environment.

Relationship of Service Members’ Deployment Trauma, PTSD Symptoms and Experiential Avoidance to Postdeployment Family Reengagement

PubMed Central

Brockman, Callie; Snyder, James; Gewirtz, Abigail; Gird, Suzanne R.; Quattlebaum, Jamie; Schmidt, Nicole; Pauldine, Michael R.; Elish, Katie; Schrepferman, Lynn; Hayes, Charles; Zettle, Robert; DeGarmo, David

2016-01-01

This research examined whether military service members’ deployment-related trauma exposure, PTSD symptoms and experiential avoidance are associated with their observed levels of positive social engagement, social withdrawal, reactivity-coercion, and distress avoidance during postdeployment family interaction. Self reports of deployment related trauma, postdeployment PTSD symptoms and experiential avoidance were collected from 184 men who were deployed to the Middle East conflicts, were partnered, and had a child between 4 and 13 years of age. Video samples of parent-child and partner problem solving and conversations about deployment issues were collected, and were rated by trained observers to assess service members’ positive engagement, social withdrawal, reactivity-coercion, and distress avoidance, as well as spouse and child negative affect and behavior. Service members’ experiential avoidance was reliably associated with less of observed positive engagement and more observed withdrawal and distress avoidance after controlling for spouse and child negative affect and behavior during ongoing interaction. Service members’ experiential avoidance also diminished significant associations between service members’ PTSD symptoms and their observed behavior. The results are discussed in terms of how service members’ psychological acceptance promotes family resilience and adaption to the multiple contextual challenges and role transitions associated with military deployment. Implications for parenting and marital interventions are described. PMID:26437144

Relationship of service members' deployment trauma, PTSD symptoms, and experiential avoidance to postdeployment family reengagement.

PubMed

Brockman, Callie; Snyder, James; Gewirtz, Abigail; Gird, Suzanne R; Quattlebaum, Jamie; Schmidt, Nicole; Pauldine, Michael R; Elish, Katie; Schrepferman, Lynn; Hayes, Charles; Zettle, Robert; DeGarmo, David

2016-02-01

This research examined whether military service members' deployment-related trauma exposure, posttraumatic stress disorder (PTSD) symptoms, and experiential avoidance are associated with their observed levels of positive social engagement, social withdrawal, reactivity-coercion, and distress avoidance during postdeployment family interaction. Self reports of deployment related trauma, postdeployment PTSD symptoms, and experiential avoidance were collected from 184 men who were deployed to the Middle East conflicts, were partnered, and had a child between 4 and 13 years of age. Video samples of parent-child and partner problem solving and conversations about deployment issues were collected, and were rated by trained observers to assess service members' positive engagement, social withdrawal, reactivity-coercion, and distress avoidance, as well as spouse and child negative affect and behavior. Service members' experiential avoidance was reliably associated with less observed positive engagement and more observed withdrawal and distress avoidance after controlling for spouse and child negative affect and behavior during ongoing interaction. Service members' experiential avoidance also diminished significant associations between service members' PTSD symptoms and their observed behavior. The results are discussed in terms of how service members' psychological acceptance promotes family resilience and adaption to the multiple contextual challenges and role transitions associated with military deployment. Implications for parenting and marital interventions are described. (c) 2016 APA, all rights reserved).

Orbiter entry aerothermodynamics

NASA Technical Reports Server (NTRS)

Ried, R. C.

1985-01-01

The challenge in the definition of the entry aerothermodynamic environment arising from the challenge of a reliable and reusable Orbiter is reviewed in light of the existing technology. Select problems pertinent to the orbiter development are discussed with reference to comprehensive treatments. These problems include boundary layer transition, leeward-side heating, shock/shock interaction scaling, tile gap heating, and nonequilibrium effects such as surface catalysis. Sample measurements obtained from test flights of the Orbiter are presented with comparison to preflight expectations. Numerical and wind tunnel simulations gave efficient information for defining the entry environment and an adequate level of preflight confidence. The high quality flight data provide an opportunity to refine the operational capability of the orbiter and serve as a benchmark both for the development of aerothermodynamic technology and for use in meeting future entry heating challenges.

Novel Visual Sensor Coverage and Deployment in Time Aware PTZ Wireless Visual Sensor Networks.

PubMed

Yap, Florence G H; Yen, Hong-Hsu

2016-12-30

In this paper, we consider the visual sensor deployment algorithm in Pan-Tilt-Zoom (PTZ) Wireless Visual Sensor Networks (WVSNs). With PTZ capability, a sensor's visual coverage can be extended to reduce the number of visual sensors that need to be deployed. The coverage zone of a visual sensor in PTZ WVSN is composed of two regions, a Direct Coverage Region (DCR) and a PTZ Coverage Region (PTZCR). In the PTZCR, a visual sensor needs a mechanical pan-tilt-zoom operation to cover an object. This mechanical operation can take seconds, so the sensor might not be able to adjust the camera in time to capture the visual data. In this paper, for the first time, we study this PTZ time-aware PTZ WVSN deployment problem. We formulate this PTZ time-aware PTZ WVSN deployment problem as an optimization problem where the objective is to minimize the total visual sensor deployment cost so that each area is either covered in the DCR or in the PTZCR while considering the PTZ time constraint. The proposed Time Aware Coverage Zone (TACZ) model successfully captures the PTZ visual sensor coverage in terms of camera focal range, angle span zone coverage and camera PTZ time. Then a novel heuristic, called Time Aware Deployment with PTZ camera (TADPTZ) algorithm, is proposed to solve the problem. From our computational experiments, we found out that TACZ model outperforms the existing M coverage model under all network scenarios. In addition, as compared to the optimal solutions, the TACZ model is scalable and adaptable to the different PTZ time requirements when deploying large PTZ WVSNs.

Novel Visual Sensor Coverage and Deployment in Time Aware PTZ Wireless Visual Sensor Networks

PubMed Central

Yap, Florence G. H.; Yen, Hong-Hsu

2016-01-01

In this paper, we consider the visual sensor deployment algorithm in Pan-Tilt-Zoom (PTZ) Wireless Visual Sensor Networks (WVSNs). With PTZ capability, a sensor’s visual coverage can be extended to reduce the number of visual sensors that need to be deployed. The coverage zone of a visual sensor in PTZ WVSN is composed of two regions, a Direct Coverage Region (DCR) and a PTZ Coverage Region (PTZCR). In the PTZCR, a visual sensor needs a mechanical pan-tilt-zoom operation to cover an object. This mechanical operation can take seconds, so the sensor might not be able to adjust the camera in time to capture the visual data. In this paper, for the first time, we study this PTZ time-aware PTZ WVSN deployment problem. We formulate this PTZ time-aware PTZ WVSN deployment problem as an optimization problem where the objective is to minimize the total visual sensor deployment cost so that each area is either covered in the DCR or in the PTZCR while considering the PTZ time constraint. The proposed Time Aware Coverage Zone (TACZ) model successfully captures the PTZ visual sensor coverage in terms of camera focal range, angle span zone coverage and camera PTZ time. Then a novel heuristic, called Time Aware Deployment with PTZ camera (TADPTZ) algorithm, is proposed to solve the problem. From our computational experiments, we found out that TACZ model outperforms the existing M coverage model under all network scenarios. In addition, as compared to the optimal solutions, the TACZ model is scalable and adaptable to the different PTZ time requirements when deploying large PTZ WVSNs. PMID:28042829

Vibration Control of Deployable Astromast Boom: Preliminary Experiments

NASA Technical Reports Server (NTRS)

Swaminadham, M.; Hamilton, David A.

1994-01-01

This paper deals with the dynamic characterization of a flexible aerospace solar boom. The modeling issues and sine dwell vibration testing to determine natural frequencies and mode shapes of a continuous-longer on deployable ASTROMAST lattice boom are discussed. The details of the proof-of-concept piezoelectric active vibration experiments on a simple cantilever beam to control its vibrations are presented. The control parameters like voltage to the controller crystal and its location are investigated, to determine the effectiveness of control element to suppress selected resonant vibrations of the test specimen. Details of this experiment and plans for its future adaptation to the prototype structure are also discussed.

Inflatable Re-Entry Vehicle Experiment (IRVE) Design Overview

NASA Technical Reports Server (NTRS)

Hughes, Stephen J.; Dillman, Robert A.; Starr, Brett R.; Stephan, Ryan A.; Lindell, Michael C.; Player, Charles J.; Cheatwood, F. McNeil

2005-01-01

Inflatable aeroshells offer several advantages over traditional rigid aeroshells for atmospheric entry. Inflatables offer increased payload volume fraction of the launch vehicle shroud and the possibility to deliver more payload mass to the surface for equivalent trajectory constraints. An inflatable s diameter is not constrained by the launch vehicle shroud. The resultant larger drag area can provide deceleration equivalent to a rigid system at higher atmospheric altitudes, thus offering access to higher landing sites. When stowed for launch and cruise, inflatable aeroshells allow access to the payload after the vehicle is integrated for launch and offer direct access to vehicle structure for structural attachment with the launch vehicle. They also offer an opportunity to eliminate system duplication between the cruise stage and entry vehicle. There are however several potential technical challenges for inflatable aeroshells. First and foremost is the fact that they are flexible structures. That flexibility could lead to unpredictable drag performance or an aerostructural dynamic instability. In addition, durability of large inflatable structures may limit their application. They are susceptible to puncture, a potentially catastrophic insult, from many possible sources. Finally, aerothermal heating during planetary entry poses a significant challenge to a thin membrane. NASA Langley Research Center and NASA's Wallops Flight Facility are jointly developing inflatable aeroshell technology for use on future NASA missions. The technology will be demonstrated in the Inflatable Re-entry Vehicle Experiment (IRVE). This paper will detail the development of the initial IRVE inflatable system to be launched on a Terrier/Orion sounding rocket in the fourth quarter of CY2005. The experiment will demonstrate achievable packaging efficiency of the inflatable aeroshell for launch, inflation, leak performance of the inflatable system throughout the flight regime, structural

Tether Deployer And Brake

NASA Technical Reports Server (NTRS)

Carroll, Joseph A.; Alexander, Charles M.

1993-01-01

Design concept promises speed, control, and reliability. Scheme for deploying tether provides for fast, free, and snagless payout and fast, dependable braking. Developed for small, expendable tethers in outer space, scheme also useful in laying transoceanic cables, deploying guidance wires to torpedoes and missiles, paying out rescue lines from ship to ship via rockets, deploying antenna wires, releasing communication and power cables to sonobuoys and expendable bathythermographs, and in reeling out lines from fishing rods.

Athletic Training Students With Disabilities: A Survey of Entry-Level Education Programs

PubMed Central

Newsham, Katherine R

2006-01-01

Context: The Rehabilitation Act of 1973 and the Americans with Disabilities Act of 1990 created and expanded protection for people with disabilities. Objective: To identify the proportion of students with disabilities enrolled in entry-level athletic training education programs (ATEPs), to examine the nature of the disabilities reported by these students, and to assess the number of ATEPs with policies (beyond technical standards) for admitting students with disabilities. Design: I distributed a survey via e-mail and the US Postal Service. The survey instrument was adapted from a tool used in similar research on medical education programs. Setting: Entry-level ATEPs. Patients or Other Participants: The survey was distributed to program directors at 292 Commission on Accreditation of Allied Health Education Program–accredited entry-level ATEPs. Main Outcome Measure(s): Using frequency analysis, I determined the rate at which students with disabilities enrolled in entry-level ATEPs and the types of disabilities represented. Disabilities represented in the study were related to learning, auditory, visual, emotional, orthopaedic, mobility, and motor skill impairments. Results: Of the 283 surveys delivered, 105 (37%) were completed and returned. A total of 70% of respondents reported enrollment of students with disabilities in their ATEPs. The number of students with disabilities in entry-level ATEPs increased during the 4-year period of this study, and the proportion of students with disabilities has also increased annually (from 1.8% to 2.6%). The most common type of impairment was a learning disability, accounting for more than 80% of all disabilities reported. Fewer than 10% of the ATEPs had a specific enrollment policy for students with disabilities. Conclusions: The number of students with disabilities in entry-level ATEPs is increasing, yet this figure is well below the 9% reported for the general student population. Most institutions rely on technical

Diving, Jumping and Drinking: instabilities during water entry and exit

NASA Astrophysics Data System (ADS)

Jung, Sunghwan

2017-11-01

All organisms interact with fluids in one way or another, and some have presumably adapted their behaviors or features in response to fluid-mechanical forces. Particularly, fluid forces are of great importance when organisms or their body parts move in and out of water. In this talk, I will discuss three problems in which fluid mechanics principles affect form and function of animals. The first problem is how several seabirds (e.g. Gannets and Boobies) dive into water at up to 24 m/s without any injuries. This study examines the effects of their beak shape and dense feathers during water entry to reduce or spread the impact force on the body. The second problem is how animals jump out of water, from plankton to whales. Some aquatic animals generate enough force to exit the water surface as an effective method of capturing prey or escaping from predators. Finally, I will discuss about lapping animals (e.g. dog and cat) as a combined water entry and exit. During the tongue-lapping, associated fluid forces and pinch-off instability will be discussed.

Preventing re-entry to foster care.

PubMed

Carnochan, Sarah; Rizik-Baer, Daniel; Austin, Michael J

2013-01-01

Re-entry to foster care generally refers to circumstances in which children who have been discharged from foster care to be reunified with their family of origin, adopted, or provided kinship guardianship are returned to foster care. In the context of the federal performance measurement system, re-entry refers specifically to a return to foster care following an unsuccessful reunification. The federal Children and Family Services Review measures re-entry to foster care with a single indicator, called the permanency of reunification indicator, one of four indicators comprising the reunification composite measure. This review focuses on research related to the re-entry indicator, including the characteristics of children, caregivers and families, as well as case and child welfare services that are associated with a higher or lower risk of re-entry to foster care. Promising post-reunification services designed to prevent re-entry to foster care are described.

Poliovirus Cell Entry: Common Structural Themes in Viral Cell Entry Pathways

PubMed Central

Hogle, James M.

2006-01-01

Structural studies of polio- and closely related viruses have provided a series of snapshots along their cell entry pathways. Based on the structures and related kinetic, biochemical, and genetic studies, we have proposed a model for the cell entry pathway for polio- and closely related viruses. In this model a maturation cleavage of a capsid protein precursor locks the virus in a metastable state, and the receptor acts like a transition-state catalyst to overcome an energy barrier and release the mature virion from the metastable state. This initiates a series of conformational changes that allow the virus to attach to membranes, form a pore, and finally release its RNA genome into the cytoplasm. This model has striking parallels with emerging models for the maturation and cell entry of more complex enveloped viruses such as influenza virus and HIV. PMID:12142481

Orion Exploration Flight Test-1 Contingency Drogue Deploy Velocity Trigger

NASA Technical Reports Server (NTRS)

Gay, Robert S.; Stochowiak, Susan; Smith, Kelly

2013-01-01

As a backup to the GPS-aided Kalman filter and the Barometric altimeter, an "adjusted" velocity trigger is used during entry to trigger the chain of events that leads to drogue chute deploy for the Orion Multi-Purpose Crew Vehicle (MPCV) Exploration Flight Test-1 (EFT-1). Even though this scenario is multiple failures deep, the Orion Guidance, Navigation, and Control (GN&C) software makes use of a clever technique that was taken from the Mars Science Laboratory (MSL) program, which recently successfully landing the Curiosity rover on Mars. MSL used this technique to jettison the heat shield at the proper time during descent. Originally, Orion use the un-adjusted navigated velocity, but the removal of the Star Tracker to save costs for EFT-1, increased attitude errors which increased inertial propagation errors to the point where the un-adjusted velocity caused altitude dispersions at drogue deploy to be too large. Thus, to reduce dispersions, the velocity vector is projected onto a "reference" vector that represents the nominal "truth" vector at the desired point in the trajectory. Because the navigation errors are largely perpendicular to the truth vector, this projection significantly reduces dispersions in the velocity magnitude. This paper will detail the evolution of this trigger method for the Orion project and cover the various methods tested to determine the reference "truth" vector; and at what point in the trajectory it should be computed.

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

Critical Spacecraft-to-Earth Communications for Mars Exploration Rover (MER) entry, descent and landing

NASA Technical Reports Server (NTRS)

Hurd, William J.; Estabrook, Polly; Racho, Caroline S.; Satorius, Edgar H.

2002-01-01

For planetary lander missions, the most challenging phase of the spacecraft to ground communications is during the entry, descent, and landing (EDL). As each 2003 Mars Exploration Rover (MER) enters the Martian atmosphere, it slows dramatically. The extreme acceleration and jerk cause extreme Doppler dynamics on the X-band signal received on Earth. When the vehicle slows sufficiently, the parachute is deployed, causing almost a step in deceleration. After parachute deployment, the lander is lowered beneath the parachute on a bridle. The swinging motion of the lander imparts high Doppler dynamics on the signal and causes the received signal strength to vary widely, due to changing antenna pointing angles. All this time, the vehicle transmits important health and status information that is especially critical if the landing is not successful. Even using the largest Deep Space Network antennas, the weak signal and high dynamics render it impossible to conduct reliable phase coherent communications. Therefore, a specialized form of frequency-shift-keying will be used. This paper describes the EDL scenario, the signal conditions, the methods used to detect and frequency-track the carrier and to detect the data modulation, and the resulting performance estimates.

Lifting Entry & Atmospheric Flight (LEAF) System Concept Applications at Solar System Bodies With an Atmosphere

NASA Astrophysics Data System (ADS)

Lee, Greg; Polidan, Ronald; Ross, Floyd; Sokol, Daniel; Warwick, Steve

2015-11-01

Northrop Grumman and L’Garde have continued the development of a hypersonic entry, semi-buoyant, maneuverable platform capable of performing long-duration (months to a year) in situ and remote measurements at any solar system body that possesses an atmosphere.The Lifting Entry & Atmospheric Flight (LEAF) family of vehicles achieves this capability by using a semi-buoyant, ultra-low ballistic coefficient vehicle whose lifting entry allows it to enter the atmosphere without an aeroshell. The mass savings realized by eliminating the heavy aeroshell allows significantly more payload to be accommodated by the platform for additional science collection and return.In this presentation, we discuss the application of the LEAF system at various solar system bodies: Venus, Titan, Mars, and Earth. We present the key differences in platform design as well as operational differences required by the various target environments. The Venus implementation includes propulsive capability to reach higher altitudes during the day and achieves full buoyancy in the mid-cloud layer of Venus’ atmosphere at night.Titan also offers an attractive operating environment, allowing LEAF designs that can target low or medium altitude operations, also with propulsive capabilities to roam within each altitude regime. The Mars version is a glider that descends gradually, allowing targeted delivery of payloads to the surface or high resolution surface imaging. Finally, an Earth version could remain in orbit in a stowed state until activated, allowing rapid response type deployments to any region of the globe.

19 CFR 122.42 - Aircraft entry.

Code of Federal Regulations, 2010 CFR

2010-04-01

... 19 Customs Duties 1 2010-04-01 2010-04-01 false Aircraft entry. 122.42 Section 122.42 Customs Duties U.S. CUSTOMS AND BORDER PROTECTION, DEPARTMENT OF HOMELAND SECURITY; DEPARTMENT OF THE TREASURY AIR COMMERCE REGULATIONS Aircraft Entry and Entry Documents; Electronic Manifest Requirements for...

Automated entry technologies for confined space work activities: A survey.

PubMed

Botti, Lucia; Ferrari, Emilio; Mora, Cristina

2017-04-01

Work in confined spaces poses a significant risk to workers and rescuers involved in the emergency response when an accident occurs. Despite several standards and regulations define the safety requirements for such activities, injuries, and fatalities still occur. Furthermore, the on-site inspections after accidents often reveal that both employers and employees fail to implement safe entry procedures. Removing the risk is possible by avoiding the worker entry, but many activities require the presence of the operator inside the confined space to perform manual tasks. The following study investigates the available technologies for hazardous confined space work activities, e.g., cleaning, inspecting, and maintenance tasks. The aim is to provide a systematic review of the automated solutions for high-risk activities in confined spaces, considering the non-man entry as the most effective confined space safety strategy. Second, this survey aims to provide suggestions for future research addressing the design of new technologies. The survey consists of about 60 papers concerning innovative technologies for confined space work activities. The document review shows that several solutions have been developed and automation can replace the workers for a limited number of hazardous tasks. Several activities still require the manual intervention due to the complex characteristics of confined spaces, e.g., to remove the remains of the automatic cleaning process from the bottom of a tank. The results show that available technologies require more flexibility to adapt to such occupational environments and further research is needed.

19 CFR 144.41 - Entry for rewarehouse.

Code of Federal Regulations, 2012 CFR

2012-04-01

... 19 Customs Duties 2 2012-04-01 2012-04-01 false Entry for rewarehouse. 144.41 Section 144.41 Customs Duties U.S. CUSTOMS AND BORDER PROTECTION, DEPARTMENT OF HOMELAND SECURITY; DEPARTMENT OF THE TREASURY (CONTINUED) WAREHOUSE AND REWAREHOUSE ENTRIES AND WITHDRAWALS Rewarehouse Entries § 144.41 Entry for rewarehouse. (a) Applicability. When...

19 CFR 144.41 - Entry for rewarehouse.

Code of Federal Regulations, 2014 CFR

2014-04-01

... 19 Customs Duties 2 2014-04-01 2014-04-01 false Entry for rewarehouse. 144.41 Section 144.41 Customs Duties U.S. CUSTOMS AND BORDER PROTECTION, DEPARTMENT OF HOMELAND SECURITY; DEPARTMENT OF THE TREASURY (CONTINUED) WAREHOUSE AND REWAREHOUSE ENTRIES AND WITHDRAWALS Rewarehouse Entries § 144.41 Entry for rewarehouse. (a) Applicability. When...

19 CFR 144.41 - Entry for rewarehouse.

Code of Federal Regulations, 2011 CFR

2011-04-01

... 19 Customs Duties 2 2011-04-01 2011-04-01 false Entry for rewarehouse. 144.41 Section 144.41 Customs Duties U.S. CUSTOMS AND BORDER PROTECTION, DEPARTMENT OF HOMELAND SECURITY; DEPARTMENT OF THE TREASURY (CONTINUED) WAREHOUSE AND REWAREHOUSE ENTRIES AND WITHDRAWALS Rewarehouse Entries § 144.41 Entry for rewarehouse. (a) Applicability. When...

19 CFR 144.41 - Entry for rewarehouse.

Code of Federal Regulations, 2010 CFR

2010-04-01

... 19 Customs Duties 2 2010-04-01 2010-04-01 false Entry for rewarehouse. 144.41 Section 144.41 Customs Duties U.S. CUSTOMS AND BORDER PROTECTION, DEPARTMENT OF HOMELAND SECURITY; DEPARTMENT OF THE TREASURY (CONTINUED) WAREHOUSE AND REWAREHOUSE ENTRIES AND WITHDRAWALS Rewarehouse Entries § 144.41 Entry for rewarehouse. (a) Applicability. When...

19 CFR 144.41 - Entry for rewarehouse.

Code of Federal Regulations, 2013 CFR

2013-04-01

... 19 Customs Duties 2 2013-04-01 2013-04-01 false Entry for rewarehouse. 144.41 Section 144.41 Customs Duties U.S. CUSTOMS AND BORDER PROTECTION, DEPARTMENT OF HOMELAND SECURITY; DEPARTMENT OF THE TREASURY (CONTINUED) WAREHOUSE AND REWAREHOUSE ENTRIES AND WITHDRAWALS Rewarehouse Entries § 144.41 Entry for rewarehouse. (a) Applicability. When...

10 CFR 1048.3 - Unauthorized entry.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 10 Energy 4 2010-01-01 2010-01-01 false Unauthorized entry. 1048.3 Section 1048.3 Energy DEPARTMENT OF ENERGY (GENERAL PROVISIONS) TRESPASSING ON STRATEGIC PETROLEUM RESERVE FACILITIES AND OTHER PROPERTY § 1048.3 Unauthorized entry. Unauthorized entry into or upon an SPR facility or real property...

10 CFR 1048.3 - Unauthorized entry.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 10 Energy 4 2011-01-01 2011-01-01 false Unauthorized entry. 1048.3 Section 1048.3 Energy DEPARTMENT OF ENERGY (GENERAL PROVISIONS) TRESPASSING ON STRATEGIC PETROLEUM RESERVE FACILITIES AND OTHER PROPERTY § 1048.3 Unauthorized entry. Unauthorized entry into or upon an SPR facility or real property...

10 CFR 1048.3 - Unauthorized entry.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 10 Energy 4 2012-01-01 2012-01-01 false Unauthorized entry. 1048.3 Section 1048.3 Energy DEPARTMENT OF ENERGY (GENERAL PROVISIONS) TRESPASSING ON STRATEGIC PETROLEUM RESERVE FACILITIES AND OTHER PROPERTY § 1048.3 Unauthorized entry. Unauthorized entry into or upon an SPR facility or real property...

10 CFR 1048.3 - Unauthorized entry.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 10 Energy 4 2014-01-01 2014-01-01 false Unauthorized entry. 1048.3 Section 1048.3 Energy DEPARTMENT OF ENERGY (GENERAL PROVISIONS) TRESPASSING ON STRATEGIC PETROLEUM RESERVE FACILITIES AND OTHER PROPERTY § 1048.3 Unauthorized entry. Unauthorized entry into or upon an SPR facility or real property...

10 CFR 1048.3 - Unauthorized entry.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 10 Energy 4 2013-01-01 2013-01-01 false Unauthorized entry. 1048.3 Section 1048.3 Energy DEPARTMENT OF ENERGY (GENERAL PROVISIONS) TRESPASSING ON STRATEGIC PETROLEUM RESERVE FACILITIES AND OTHER PROPERTY § 1048.3 Unauthorized entry. Unauthorized entry into or upon an SPR facility or real property...

32 CFR 763.4 - Entry restrictions.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 32 National Defense 5 2010-07-01 2010-07-01 false Entry restrictions. 763.4 Section 763.4 National Defense Department of Defense (Continued) DEPARTMENT OF THE NAVY ISLANDS UNDER NAVY JURISDICTION RULES GOVERNING PUBLIC ACCESS Entry Regulations for Kaho'olawe Island, Hawaii § 763.4 Entry restrictions. (a...

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.

Atmospheric Entry Studies for Venus Missions: 45 deg Sphere-Cone Rigid Aeroshells and Ballistic Entries

NASA Technical Reports Server (NTRS)

Prabu, Dinesh K.; Allen, Gary A., Jr.; Cappuccio, Gelsomina; Spilker, Thomas R.; Hwang, Helen H.; Moses, Robert W.

2013-01-01

The present study considers ballistic entries into the atmosphere of Venus using a 45deg sphere-cone rigid aeroshell, a legacy shape that has been used successfully in the past in the Pioneer Venus Multiprobe Mission. For a number of entry mass and capsule diameter combinations (i.e., various ballistic coefficients) and entry velocities, the trajectory space in terms of entry flight path angles between skip out and -30 is explored with a 3DOF trajectory code, TRAJ. Assuming that the thermal protection material of choice is carbon phenolic of flight heritage, the entry flight path angle space is constrained a posteriori by the mechanical and thermal performance parameters of the material. For mechanical performance, a 200 g limit is placed on the peak deceleration load and 10 bar is assumed as the limit for heritage carbon-phenolic material. It is shown that both constraints cannot be active simultaneously. For thermal performance, a heat flux 2.5 kW/sq cm is utilized as a threshold below which the heritage carbon phenolic is considered mass inefficient. Using these constraints, viable entry flight path angle corridors are determined. Analysis of the results also hints at the existence of a range of "critical" ballistic coefficients beyond which the steepest possible entries are determined by the pressure limit of 10 bar. The results are verified against known performance of the various probes used in the Pioneer Venus mission. It is anticipated that the results presented here will serve as a baseline in the development of a new class of ablative materials for future Venus missions.

Attacking 22 entries in rugby union: running demands and differences between successful and unsuccessful entries.

PubMed

Tierney, P; Tobin, D P; Blake, C; Delahunt, E

2017-12-01

Global Positioning System (GPS) technology is commonly utilized in team sports, including rugby union. It has been used to describe the average running demands of rugby union. This has afforded an enhanced understanding of the physical fitness requirements for players. However, research in team sports has suggested that training players relative to average demands may underprepare them for certain scenarios within the game. To date, no research has investigated the running demands of attacking 22 entries in rugby union. Additionally, no research has been undertaken to determine whether differences exist in the running intensity of successful and unsuccessful attacking 22 entries in rugby union. The first aim of this study was to describe the running intensity of attacking 22 entries. The second aim of this study was to investigate whether differences exist in the running intensity of successful and unsuccessful attacking 22 entries. Running intensity was measured using meters per minute (m min -1 ) for (a) total distance, (b) running distance, (c) high-speed running distance, and (d) very high-speed running distance. This study provides normative data for the running intensity of attacking 22 entries in rugby union. Forwards achieved greater high-speed running intensity in successful (3.6 m min -1 ) compared to unsuccessful (1.8 m min -1 ) attacking 22 entries. Forwards should try and achieve greater high-speed running intensity in attacking 22 entries to increase the likelihood of successful outcomes during this period of gameplay. © 2016 John Wiley & Sons A/S. Published by John Wiley & Sons Ltd.

19 CFR 142.44 - Entry number range.

Code of Federal Regulations, 2013 CFR

2013-04-01

... 19 Customs Duties 2 2013-04-01 2013-04-01 false Entry number range. 142.44 Section 142.44 Customs... (CONTINUED) ENTRY PROCESS Line Release § 142.44 Entry number range. After an application for Line Release has received final approval, filers must provide the port director, in writing, with a range of entry numbers...

Deployable reflector structure

NASA Technical Reports Server (NTRS)

Mikulas, Martin, Jr. (Inventor); Hoberman, Charles (Inventor)

1993-01-01

A deployable reflector structure is presented. The structure has a number of movable reflector panels pivotably supported on rigid arms. Several such arms are pivotably connected to a central structure. The arm can move in starburst fashion from a packaged stage, where all arms are vertical, to a deployed stage, where all arms are horizontal. All of the movable reflector panels are maintained at a predetermined angle to an axis of the reflector structure when the arms are pivoted. The reflector panels are stacked tightly on top of each other in the packaged state of the reflector structure. Simple mechanisms are used for avoiding interference between panels on different arms in the packaged stage and for fitting the movable panels together like tiles in the deployed stage.

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.

Deployment dynamics and control of large-scale flexible solar array system with deployable mast

NASA Astrophysics Data System (ADS)

Li, Hai-Quan; Liu, Xiao-Feng; Guo, Shao-Jing; Cai, Guo-Ping

2016-10-01

In this paper, deployment dynamics and control of large-scale flexible solar array system with deployable mast are investigated. The adopted solar array system is introduced firstly, including system configuration, deployable mast and solar arrays with several mechanisms. Then dynamic equation of the solar array system is established by the Jourdain velocity variation principle and a method for dynamics with topology changes is introduced. In addition, a PD controller with disturbance estimation is designed to eliminate the drift of spacecraft mainbody. Finally the validity of the dynamic model is verified through a comparison with ADAMS software and the deployment process and dynamic behavior of the system are studied in detail. Simulation results indicate that the proposed model is effective to describe the deployment dynamics of the large-scale flexible solar arrays and the proposed controller is practical to eliminate the drift of spacecraft mainbody.

Abusive Relationship and Its Associated Factors Between Deployed and Un-Deployed Veterans in College.

PubMed

Min, Hosik

2018-03-01

This study is to examine the effect of student veteran status on abusive relationships, namely, emotional, physical, and sexual abuse. In addition, this study divided student veterans into two groups, deployed and un-deployed veterans, to see whether two groups demonstrate different results on abusive relationships. Logistic regression models were employed as a statistical strategy using the 2011-2014 American College Health Association National College Health Assessment II (ACHA-NCHA-II) data. The results found that deployed veterans were more likely to experience physical abuse, while un-deployed veterans were more likely to experience emotional abuse. Student veterans did not show any significant relationship with sexual abuse regardless deployment experience. It would be appropriate to consider the results of this study to address abusive relationships among student veterans, which help them to not only adjust college life but also succeed in careers and have healthy family relationships.

The unfolded protein response in a pair of sensory neurons promotes entry of C. elegans into dauer diapause.

PubMed

Kulalert, Warakorn; Kim, Dennis H

2013-12-16

In response to unfavorable environmental conditions such as starvation, crowding, and elevated temperature, Caenorhabditis elegans larvae enter an alternative developmental stage known as dauer, which is characterized by adaptive changes in stress resistance and metabolism. The genetic dissection of the molecular mechanisms of the C. elegans dauer developmental decision has defined evolutionarily conserved signaling pathways of organismal neuroendocrine physiology. Here, we have identified a mechanism by which a dominant mutation in a neuronal insulin gene, daf-28(sa191), causes constitutive entry into dauer diapause. We demonstrate that expression of the mutant DAF-28 insulin peptide results in endoplasmic reticulum (ER) stress in the ASI pair of chemosensory neurons. The neuronal ER stress does not compromise cellular survival but activates PEK-1, the C. elegans ortholog of the mammalian eIF2α kinase PERK, which in turn phosphorylates Ser49 of eIF2α, specifically in the ASI neuron pair, to promote entry into dauer diapause. Our data establish a novel role for ER stress and the unfolded protein response (UPR) in promoting entry into dauer diapause and suggest that, in addition to cell-autonomous activities in the maintenance of ER homeostasis, the UPR may act in a non-cell-autonomous manner to promote organismal adaptation to stress during larval development. Copyright © 2013 Elsevier Ltd. All rights reserved.

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.

The ESA/NASA Multi-Aircraft ATV-1 Re-Entry Campaign: Analysis of Airborne Intensified Video Observations from the NASA/JSC Experiment

NASA Technical Reports Server (NTRS)

Barker, Ed; Maley, Paul; Mulrooney, Mark; Beaulieu, Kevin

2009-01-01

In September 2008, a joint ESA/NASA multi-instrument airborne observing campaign was conducted over the Southern Pacific ocean. The objective was the acquisition of data to support detailed atmospheric re-entry analysis for the first flight of the European Automated Transfer Vehicle (ATV)-1. Skilled observers were deployed aboard two aircraft which were flown at 12.8 km altitude within visible range of the ATV-1 re-entry zone. The observers operated a suite of instruments with low-light-level detection sensitivity including still cameras, high speed and 30 fps video cameras, and spectrographs. The collected data has provided valuable information regarding the dynamic time evolution of the ATV-1 re-entry fragmentation. Specifically, the data has satisfied the primary mission objective of recording the explosion of ATV-1's primary fuel tank and thereby validating predictions regarding the tanks demise and the altitude of its occurrence. Furthermore, the data contains the brightness and trajectories of several hundred ATV-1 fragments. It is the analysis of these properties, as recorded by the particular instrument set sponsored by NASA/Johnson Space Center, which we present here.

What pre-deployment and early post-deployment factors predict health function after combat deployment?: a prospective longitudinal study of Operation Enduring Freedom (OEF)/Operation Iraqi Freedom (OIF) soldiers

PubMed Central

2013-01-01

Background Physical and mental function are strong indicators of disability and mortality. OEF/OIF Veterans returning from deployment have been found to have poorer function than soldiers who have not deployed; however the reasons for this are unknown. Methods A prospective cohort of 790 soldiers was assessed both pre- and immediately after deployment to determine predictors of physical and mental function after war. Results On average, OEF/OIF Veterans showed significant declines in both physical (t=6.65, p<.0001) and mental function (t=7.11, p<.0001). After controlling for pre-deployment function, poorer physical function after deployment was associated with older age, more physical symptoms, blunted systolic blood pressure reactivity and being injured. After controlling for pre-deployment function, poorer mental function after deployment was associated with younger age, lower social desirability, lower social support, greater physical symptoms and greater PTSD symptoms. Conclusions Combat deployment was associated with an immediate decline in both mental and physical function. The relationship of combat deployment to function is complex and influenced by demographic, psychosocial, physiological and experiential factors. Social support and physical symptoms emerged as potentially modifiable factors. PMID:23631419

Deployment Mechanism for Thermal Pointing System

NASA Technical Reports Server (NTRS)

Koski, Kraig

2014-01-01

The Deployment Mechanism for the Total and Spectral Solar Irradiance Sensor (TSIS) is responsible for bringing the Thermal Pointing System (TPS) from its stowed, launch locked position to the on-orbit deployed, operational position. The Deployment Mechanism also provides structural support for the TSIS optical bench and two-axis gimbal. An engineering model of the Deployment Mechanism has been environmentally qualified and life tested. This paper will give an overview of the TSIS mission and then describe the development, design, and testing of the Deployment Mechanism.

Deployable antenna kinematics using tensegrity structure design

NASA Astrophysics Data System (ADS)

Knight, Byron Franklin

With vast changes in spacecraft development over the last decade, a new, cheaper approach was needed for deployable kinematic systems such as parabolic antenna reflectors. Historically, these mesh-surface reflectors have resembled folded umbrellas, with incremental redesigns utilized to save packaging size. These systems are typically over-constrained designs, the assumption being that high reliability necessary for space operations requires this level of conservatism. But with the rapid commercialization of space, smaller launch platforms and satellite buses have demanded much higher efficiency from all space equipment than can be achieved through this incremental approach. This work applies an approach called tensegrity to deployable antenna development. Kenneth Snelson, a student of R. Buckminster Fuller, invented Tensegrity structures in 1948. Such structures use a minimum number of compression members (struts); stability is maintain using tension members (ties). The novelty introduced in this work is that the ties are elastic, allowing the struts to extend or contract, and in this way changing the surface of the antenna. Previously, the University of Florida developed an approach to quantify the stability and motion of parallel manipulators. This approach was applied to deployable, tensegrity, antenna structures. Based on the kinematic analyses for the 3-3 (octahedron) and 4-4 (square anti-prism) structures, the 6-6 (hexagonal anti-prism) analysis was completed which establishes usable structural parameters. The primary objective for this work was to prove the stability of this class of deployable structures, and their potential application to space structures. The secondary objective is to define special motions for tensegrity antennas, to meet the subsystem design requirements, such as addressing multiple antenna-feed locations. This work combines the historical experiences of the artist (Snelson), the mathematician (Ball), and the space systems engineer

Meteor Entry and Breakup Based on Evolution of NASAs Entry Capsule Design Tools

NASA Technical Reports Server (NTRS)

Prabku, Dinesh K.; Saunders, D.; Stern, E.; Chen, Y.-K.; Allen, G.; Agrawal, P.; Jaffe, R.; White, S.; Tauber, M.; Bauschlicher, C.;

Lateral Coherence and Mixing in the Coastal Ocean: Adaptive Sampling using Gliders

DTIC Science & Technology

2012-09-30

Adaptive Sampling using Gliders R. Kipp Shearman Jonathan D. Nash James N. Moum John A. Barth College of Oceanic & Atmospheric Sciences Oregon State...persistent on O (3 day) timescales, so are ideally suited to be adaptively sampled by autonomous gliders that actively report both turbulent and...plan to deploy 4 AUV gliders to perform intensive, adaptive surveys. Newly-enhanced to measure turbulent mixing, water-column currents and dye

Lateral Coherence and Mixing in the Coastal Ocean: Adaptive Sampling using Gliders

DTIC Science & Technology

2011-09-30

Coherence and Mixing in the Coastal Ocean: Adaptive Sampling using Gliders R. Kipp Shearman Jonathan D. Nash James N. Moum John A. Barth College of...These structures evolve yet are often persistent on O (3 day) timescales, so are ideally suited to be adaptively sampled by autonomous gliders that...processes driving lateral dispersion, we plan to deploy 4 AUV gliders to perform intensive, adaptive surveys. Newly-enhanced to measure turbulent mixing

Cross Deployment Networking and Systematic Performance Analysis of Underwater Wireless Sensor Networks.

PubMed

Wei, Zhengxian; Song, Min; Yin, Guisheng; Wang, Hongbin; Ma, Xuefei; Song, Houbing

2017-07-12

Underwater wireless sensor networks (UWSNs) have become a new hot research area. However, due to the work dynamics and harsh ocean environment, how to obtain an UWSN with the best systematic performance while deploying as few sensor nodes as possible and setting up self-adaptive networking is an urgent problem that needs to be solved. Consequently, sensor deployment, networking, and performance calculation of UWSNs are challenging issues, hence the study in this paper centers on this topic and three relevant methods and models are put forward. Firstly, the normal body-centered cubic lattice to cross body-centered cubic lattice (CBCL) has been improved, and a deployment process and topology generation method are built. Then most importantly, a cross deployment networking method (CDNM) for UWSNs suitable for the underwater environment is proposed. Furthermore, a systematic quar-performance calculation model (SQPCM) is proposed from an integrated perspective, in which the systematic performance of a UWSN includes coverage, connectivity, durability and rapid-reactivity. Besides, measurement models are established based on the relationship between systematic performance and influencing parameters. Finally, the influencing parameters are divided into three types, namely, constraint parameters, device performance and networking parameters. Based on these, a networking parameters adjustment method (NPAM) for optimized systematic performance of UWSNs has been presented. The simulation results demonstrate that the approach proposed in this paper is feasible and efficient in networking and performance calculation of UWSNs.

Cross Deployment Networking and Systematic Performance Analysis of Underwater Wireless Sensor Networks

PubMed Central

Wei, Zhengxian; Song, Min; Yin, Guisheng; Wang, Hongbin; Ma, Xuefei

2017-01-01

Underwater wireless sensor networks (UWSNs) have become a new hot research area. However, due to the work dynamics and harsh ocean environment, how to obtain an UWSN with the best systematic performance while deploying as few sensor nodes as possible and setting up self-adaptive networking is an urgent problem that needs to be solved. Consequently, sensor deployment, networking, and performance calculation of UWSNs are challenging issues, hence the study in this paper centers on this topic and three relevant methods and models are put forward. Firstly, the normal body-centered cubic lattice to cross body-centered cubic lattice (CBCL) has been improved, and a deployment process and topology generation method are built. Then most importantly, a cross deployment networking method (CDNM) for UWSNs suitable for the underwater environment is proposed. Furthermore, a systematic quar-performance calculation model (SQPCM) is proposed from an integrated perspective, in which the systematic performance of a UWSN includes coverage, connectivity, durability and rapid-reactivity. Besides, measurement models are established based on the relationship between systematic performance and influencing parameters. Finally, the influencing parameters are divided into three types, namely, constraint parameters, device performance and networking parameters. Based on these, a networking parameters adjustment method (NPAM) for optimized systematic performance of UWSNs has been presented. The simulation results demonstrate that the approach proposed in this paper is feasible and efficient in networking and performance calculation of UWSNs. PMID:28704959

Forebody and base region real gas flow in severe planetary entry by a factored implicit numerical method. II - Equilibrium reactive gas

NASA Technical Reports Server (NTRS)

Davy, W. C.; Green, M. J.; Lombard, C. K.

1981-01-01

The factored-implicit, gas-dynamic algorithm has been adapted to the numerical simulation of equilibrium reactive flows. Changes required in the perfect gas version of the algorithm are developed, and the method of coupling gas-dynamic and chemistry variables is discussed. A flow-field solution that approximates a Jovian entry case was obtained by this method and compared with the same solution obtained by HYVIS, a computer program much used for the study of planetary entry. Comparison of surface pressure distribution and stagnation line shock-layer profiles indicates that the two solutions agree well.

Abort-once-around entry corridor analysis program document

NASA Technical Reports Server (NTRS)

Kyle, H. C.

1975-01-01

The abort once around entry target corridor analysis program (ABECAP) was studied. The allowable range of flight path angles at entry interface for acceptable entry trajectories from a shuttle abort once around (AOA) situation was established. The solutions thus determined may be shown as corridor plots of entry interface flight path angle versus range from entry interface (EI) to the target.

Atmospheric Entry Studies for Uranus

NASA Astrophysics Data System (ADS)

Agrawal, P.; Allen, G. A.; Hwang, H. H.; Marley, M. S.; McGuire, M. K.; Garcia, J. A.; Sklyanskiy, E.; Huynh, L. C.; Moses, R. W.

2014-06-01

To better understand the technology requirements for a Uranus atmospheric entry probe, an internal NASA study funded by ISPT program was conducted. The talk describes two different approaches to the planet: 1) direct ballistic entry and 2) Aerocapture.

Entry decisions in the generic pharmaceutical industry.

PubMed

Morton, F M

1999-01-01

Data on all generic drug entries in the period 1984-1994 are used to estimate which markets heterogeneous potential entrants will decide to enter. I find that organizational experience predicts entry. Firms tend to enter markets with supply and demand characteristics similar to the firm's existing drugs. Larger revenue markets, markets with more hospital sales, and products that treat chronic conditions attract more entry. The simultaneous nature of entry leads to an additional interpretation: specialization is profitable because of the severe risk to profits when a market is "overentered." However, I am unable to make any conclusions about the efficiency of entry decisions.

Sodium entry through endothelial store-operated calcium entry channels: regulation by Orai1

PubMed Central

Xu, Ningyong; Cioffi, Donna L.; Alexeyev, Mikhail; Rich, Thomas C.

2014-01-01

Orai1 interacts with transient receptor potential protein of the canonical subfamily (TRPC4) and contributes to calcium selectivity of the endothelial cell store-operated calcium entry current (ISOC). Orai1 silencing increases sodium permeability and decreases membrane-associated calcium, although it is not known whether Orai1 is an important determinant of cytosolic sodium transitions. We test the hypothesis that, upon activation of store-operated calcium entry channels, Orai1 is a critical determinant of cytosolic sodium transitions. Activation of store-operated calcium entry channels transiently increased cytosolic calcium and sodium, characteristic of release from an intracellular store. The sodium response occurred more abruptly and returned to baseline more rapidly than did the transient calcium rise. Extracellular choline substitution for sodium did not inhibit the response, although 2-aminoethoxydiphenyl borate and YM-58483 reduced it by ∼50%. After this transient response, cytosolic sodium continued to increase due to influx through activated store-operated calcium entry channels. The magnitude of this sustained increase in cytosolic sodium was greater when experiments were conducted in low extracellular calcium and when Orai1 expression was silenced; these two interventions were not additive, suggesting a common mechanism. 2-Aminoethoxydiphenyl borate and YM-58483 inhibited the sustained increase in cytosolic sodium, only in the presence of Orai1. These studies demonstrate that sodium permeates activated store-operated calcium entry channels, resulting in an increase in cytosolic sodium; the magnitude of this response is determined by Orai1. PMID:25428882

Deployable System for Crash-Load Attenuation

NASA Technical Reports Server (NTRS)

Kellas, Sotiris; Jackson, Karen E.

2007-01-01

An externally deployable honeycomb structure is investigated with respect to crash energy management for light aircraft. The new concept utilizes an expandable honeycomb-like structure to absorb impact energy by crushing. Distinguished by flexible hinges between cell wall junctions that enable effortless deployment, the new energy absorber offers most of the desirable features of an external airbag system without the limitations of poor shear stability, system complexity, and timing sensitivity. Like conventional honeycomb, once expanded, the energy absorber is transformed into a crush efficient and stable cellular structure. Other advantages, afforded by the flexible hinge feature, include a variety of deployment options such as linear, radial, and/or hybrid deployment methods. Radial deployment is utilized when omnidirectional cushioning is required. Linear deployment offers better efficiency, which is preferred when the impact orientation is known in advance. Several energy absorbers utilizing different deployment modes could also be combined to optimize overall performance and/or improve system reliability as outlined in the paper. Results from a series of component and full scale demonstration tests are presented as well as typical deployment techniques and mechanisms. LS-DYNA analytical simulations of selected tests are also presented.

ESA Venus Entry Probe Study

NASA Technical Reports Server (NTRS)

vandenBerg, M. L.; Falkner, P.; Phipps, A.; Underwood, J. C.; Lingard, J. S.; Moorhouse, J.; Kraft, S.; Peacock, A.

2005-01-01

The Venus Entry Probe is one of ESA s Technology Reference Studies (TRS). The purpose of the Technology Reference Studies is to provide a focus for the development of strategically important technologies that are of likely relevance for future scientific missions. The aim of the Venus Entry Probe TRS is to study approaches for low cost in-situ exploration of Venus and other planetary bodies with a significant atmosphere. In this paper, the mission objectives and an outline of the mission concept of the Venus Entry Probe TRS are presented.

Connected vehicle pilot deployment program phase 1, deployment outreach plan -- New York City.

DOT National Transportation Integrated Search

2016-07-19

This document is a high level plan that describes the Outreach Plan for the New York City Connected Vehicle Pilot Deployment. The plan defines the communications strategy for the CV Pilot Deployment; identifies roles and responsibilities of persons t...

In vivo deployment of mechanically adaptive nanocomposites for intracortical microelectrodes

PubMed Central

Harris, J P; Hess, A E; Rowan, S J; Weder, C; Zorman, C A; Tyler, D J; Capadona, J R

2012-01-01

We recently introduced a series of stimuli-responsive, mechanically-adaptive polymer nanocomposites. Here, we report the first application of these bio-inspired materials as substrates for intracortical microelectrodes. Our hypothesis is that the ideal electrode should be initially stiff to facilitate minimal trauma during insertion into the cortex, yet becomes mechanically compliant to match the stiffness of the brain tissue and minimize forces exerted on the tissue, attenuating inflammation. Microprobes created from mechanically reinforced nanocomposites demonstrated a significant advantage compared to model microprobes composed of neat polymer only. The nanocomposite microprobes exhibit a higher storage modulus (E’ = ~5 GPa) than the neat polymer microprobes (E’ = ~2 GPa) and could sustain higher loads (~17 mN), facilitating penetration through the pia mater and insertion into the cerebral cortex of a rat. In contrast, the neat polymer microprobes mechanically failed under lower loads (~7 mN) before they were capable of inserting into cortical tissue. Further, we demonstrated the material’s ability to morph while in the rat cortex to more closely match the mechanical properties of the cortical tissue. Nanocomposite microprobes that were implanted into the rat cortex for up to 8 weeks demonstrated increased cell density at the microelectrode-tissue interface and a lack of tissue necrosis or excessive gliosis. This body of work introduces our nanocomposite-based microprobes as adaptive substrates for intracortical microelectrodes and potentially other biomedical applications. PMID:21654037

Mobile Adaptive Communication Support for Vocabulary Acquisition

ERIC Educational Resources Information Center

Epp, Carrie Demmans

2014-01-01

This work explores the use of an adaptive mobile tool for language learning. A school-based deployment study showed that the tool supported learning. A second study is being conducted in informal learning environments. Current work focuses on building models that increase our understanding of the relationship between application usage and learning.

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.

An experimental SMI adaptive antenna array simulator for weak interfering signals

NASA Technical Reports Server (NTRS)

Dilsavor, Ronald S.; Gupta, Inder J.

1991-01-01

An experimental sample matrix inversion (SMI) adaptive antenna array for suppressing weak interfering signals is described. The experimental adaptive array uses a modified SMI algorithm to increase the interference suppression. In the modified SMI algorithm, the sample covariance matrix is redefined to reduce the effect of thermal noise on the weights of an adaptive array. This is accomplished by subtracting a fraction of the smallest eigenvalue of the original covariance matrix from its diagonal entries. The test results obtained using the experimental system are compared with theoretical results. The two show a good agreement.

Mining Deployment Optimization

NASA Astrophysics Data System (ADS)

Čech, Jozef

2016-09-01

The deployment problem, researched primarily in the military sector, is emerging in some other industries, mining included. The principal decision is how to deploy some activities in space and time to achieve desired outcome while complying with certain requirements or limits. Requirements and limits are on the side constraints, while minimizing costs or maximizing some benefits are on the side of objectives. A model with application to mining of polymetallic deposit is presented. To obtain quick and immediate decision solutions for a mining engineer with experimental possibilities is the main intention of a computer-based tool. The task is to determine strategic deployment of mining activities on a deposit, meeting planned output from the mine and at the same time complying with limited reserves and haulage capacities. Priorities and benefits can be formulated by the planner.

Six-degree-of-freedom guidance and control-entry analysis of the HL-20

NASA Technical Reports Server (NTRS)

Powell, Richard W.

1993-01-01

The ability of the HL-20 lifting body to fly has been evaluated for an automated entry from atmospheric interface to landing. This evaluation was required to demonstrate that not only successful touchdown conditions would be possible for this low lift-to-drag-ratio vehicle, but also the vehicle would not exceed its design dynamic pressure limit of 400 psf during entry. This dynamic pressure constraint limit, coupled with limited available pitch-control authority at low supersonic speeds, restricts the available maneuvering capability for the HL-20 to acquire the runway. One result of this analysis was that this restrictive maneuvering capability does not allow the use of a model-following atmospheric entry-guidance algorithm, such as that used by the Space Shuttle, but instead requires a more adaptable guidance algorithm. Therefore, for this analysis, a predictor-corrector guidance algorithm was developed that would provide successful touchdown conditions while not violating the dynamic pressure constraint. A flight-control system was designed and incorporated, along with the predictor-corrector guidance algorithm, into a six-DOF simulation. which showed that the HL-20 remained controllable and could reach the landing site and execute a successful landing under all off-nominal conditions simulated.

An Experimental Trial of Adaptive Programming in Drug Court: Outcomes at 6, 12 and 18 Months.

PubMed

Marlowe, Douglas B; Festinger, David S; Dugosh, Karen L; Benasutti, Kathleen M; Fox, Gloria; Harron, Ashley

2014-06-01

Test whether an adaptive program improves outcomes in drug court by adjusting the schedule of court hearings and clinical case-management sessions pursuant to a priori performance criteria. Consenting participants in a misdemeanor drug court were randomly assigned to the adaptive program (n = 62) or to a baseline-matching condition (n = 63) in which they attended court hearings based on the results of a criminal risk assessment. Outcome measures were re-arrest rates at 18 months post-entry to the drug court and urine drug test results and structured interview results at 6 and 12 months post-entry. Although previously published analyses revealed significantly fewer positive drug tests for participants in the adaptive condition during the first 18 weeks of drug court, current analyses indicate the effects converged during the ensuing year. Between-group differences in new arrest rates, urine drug test results and self-reported psychosocial problems were small and non-statistically significant at 6, 12 and 18 months post-entry. A non-significant trend (p = .10) suggests there may have been a small residual impact (Cramer's ν = .15) on new misdemeanor arrests after 18 months. Adaptive programming shows promise for enhancing short-term outcomes in drug courts; however, additional efforts are needed to extend the effects beyond the first 4 to 6 months of enrollment.

Novel Insights into Cell Entry of Emerging Human Pathogenic Arenaviruses.

PubMed

Fedeli, Chiara; Moreno, Héctor; Kunz, Stefan

2018-06-22

Viral hemorrhagic fevers caused by emerging RNA viruses of the Arenavirus family are among the most devastating human diseases. Climate change, global trade, and increasing urbanization promote the emergence and re-emergence of these human pathogenic viruses. Emerging pathogenic arenaviruses are of zoonotic origin and reservoir-to-human transmission is crucial for spillover into human populations. Host cell attachment and entry are the first and most fundamental steps of every virus infection and represent major barriers for zoonotic transmission. During host cell invasion, viruses critically depend on cellular factors, including receptors, co-receptors, and regulatory proteins of endocytosis. An in-depth understanding of the complex interaction of a virus with cellular factors implicated in host cell entry is therefore crucial to predict the risk of zoonotic transmission, define the tissue tropism, and assess disease potential. Over the past years, investigation of the molecular and cellular mechanisms underlying host cell invasion of human pathogenic arenaviruses uncovered remarkable viral strategies and provided novel insights into viral adaptation and virus-host co-evolution that will be covered in the present review. Copyright © 2018. Published by Elsevier Ltd.

EDITORIAL Wireless sensor networks: design for real-life deployment and deployment experiences Wireless sensor networks: design for real-life deployment and deployment experiences

NASA Astrophysics Data System (ADS)

Gaura, Elena; Roedig, Utz; Brusey, James

2010-12-01

Wireless sensor networks (WSNs) are among the most promising technologies of the new millennium. The opportunities afforded by being able to program networks of small, lightweight, low-power, computation- and bandwidth-limited nodes have attracted a large community of researchers and developers. However, the unique set of capabilities offered by the technology produces an exciting but complex design space, which is often difficult to negotiate in an application context. Deploying sensing physical environments produces its own set of challenges, and can push systems into failure modes, thus revealing problems that can be difficult to discover or reproduce in simulation or the laboratory. Sustained efforts in the area of wireless networked sensing over the last 15 years have resulted in a large number of theoretical developments, substantial practical achievements, and a wealth of lessons for the future. It is clear that in order to bridge the gap between (on the one hand) visions of very large scale, autonomous, randomly deployed networks and (on the other) the actual performance of fielded systems, we need to view deployment as an essential component in the process of developing sensor networks: a process that includes hardware and software solutions that serve specific applications and end-user needs. Incorporating deployment into the design process reveals a new and different set of requirements and considerations, whose solutions require innovative thinking, multidisciplinary teams and strong involvement from end-user communities. This special feature uncovers and documents some of the hurdles encountered and solutions offered by experimental scientists when deploying and evaluating wireless sensor networks in situ, in a variety of well specified application scenarios. The papers specifically address issues of generic importance for WSN system designers: (i) data quality, (ii) communications availability and quality, (iii) alternative, low-energy sensing

Dynamic analysis of the deployment for mesh reflector deployable antennas with the cable-net structure

NASA Astrophysics Data System (ADS)

Zhang, Yiqun; Li, Na; Yang, Guigeng; Ru, Wenrui

2017-02-01

This paper presents a dynamic analysis approach for the composite structure of a deployable truss and cable-net system. An Elastic Catenary Element is adopted to model the slack/tensioned cables. Then, from the energy standpoint, the kinetic energy, elasticity-potential energy and geopotential energy of the cable-net structure and deployable truss are derived. Thus, the flexible multi-body dynamic model of the deployable antenna is built based on the Lagrange equation. The effect of the cable-net tension on the antenna truss is discussed and compared with previous publications and a dynamic deployment analysis is performed. Both the simulation and experimental results verify the validity of the method presented.

Anomalistic Disturbance Torques during the Entry Phase of the Mars Exploration Rover Missions: A Telemetry and Mars-Surface Investigation

NASA Technical Reports Server (NTRS)

Tolson, Robert H.; Willcockson, William H.; Desai, Prasun N.; Thomas, Paige

2006-01-01

Shortly after landing on Mars, post-flight analysis of the "Spirit" entry data suggested that the vehicle experienced large, anomalistic oscillations in angle-of-attack starting at about M=6. Similar analysis for "Opportunity " found even larger oscillations starting immediately after maximum dynamic pressure at M=14. Where angles-of-attack of 1-2 degrees were expected from maximum dynamic pressure to drogue deployment, the reconstructions suggested 4 to 9 degrees. The next Mars lander, 2007 Phoenix project, was concerned enough to recommend further exploration of the anomalies. Detailed analysis of "Opportunity" data found significant anomalies in the hypersonic aerodynamic torques. The analysis showed that these torques were essentially fixed in the spinning vehicle. Nearly a year after landing, the "Oportunity" rover took pictures of its aeroshell on the surface, which showed that portions of the aeroshell thermal blanket assembly still remained. This blanket assembly was supposed to burn off very early in the entry. An analysis of the aeroshell photographs led to an estimate of the aerodynamic torques that the remnants could have produced. A comparison of two estimates of the aerodynamic torque perturbations (one extracted from telemetry data and the other from Mars surface photographs) showed exceptional agreement. Trajectory simulations using a simple data derived torque perturbation model provided rigid body motions similar to that observed during the "Opportunity" entry. Therefore, the case of the anomalistic attitude behavior for the "Opportunity" EDL is now considered closed and a suggestion is put forth that a similar event occurred for the "Spirit" entry as well.

31 CFR 357.0 - Book-entry systems.

Code of Federal Regulations, 2014 CFR

2014-07-01

... General Information § 357.0 Book-entry systems. (a) Treasury securities. Treasury securities are...-entry system is the book-entry system in which Treasury securities are held in a tiered system through securities intermediaries such as financial institutions or brokerage firms. A Treasury security is...

31 CFR 357.0 - Book-entry systems.

Code of Federal Regulations, 2012 CFR

2012-07-01

... General Information § 357.0 Book-entry systems. (a) Treasury securities. Treasury securities are...-entry system is the book-entry system in which Treasury securities are held in a tiered system through securities intermediaries such as financial institutions or brokerage firms. A Treasury security is...

31 CFR 357.0 - Book-entry systems.

Code of Federal Regulations, 2011 CFR

2011-07-01

... General Information § 357.0 Book-entry systems. (a) Treasury securities. Treasury securities are...-entry system is the book-entry system in which Treasury securities are held in a tiered system through securities intermediaries such as financial institutions or brokerage firms. A Treasury security is...

31 CFR 357.0 - Book-entry systems.

Code of Federal Regulations, 2013 CFR

2013-07-01

... General Information § 357.0 Book-entry systems. (a) Treasury securities. Treasury securities are...-entry system is the book-entry system in which Treasury securities are held in a tiered system through securities intermediaries such as financial institutions or brokerage firms. A Treasury security is...

Design and deploying study of a new petal-type deployable solid surface antenna

NASA Astrophysics Data System (ADS)

Huang, He; Guan, Fu-Ling; Pan, Liang-Lai; Xu, Yan

2018-07-01

Deployable solid surface reflector is still one of the most important ways to fulfill the ultra-high-accuracy and ultra-large-aperture reflector antennas. However the drawback of integrate stiffness is still a main problem for solid surface reflectors in the former research. To figure out this problem, a New Petal-type Deployable Solid Surface Antenna (NPDSSA) is developed in this study. A kind of drag springs are applied as linkages with adjacent petals to improve the integrate rigidity. The structural design is introduced and the geometric parameters are analyzed to find their effects on the rotation and package capacities. The software simulations and laboratory model tests are conducted to verify the deploying process of NPDSSA. Two models are employed to study the property of linkage butts and drag springs. It is indicated that model NPDSSA with the application of linkage butts and drag springs has better integrality and stability during the deploying. Finally it is concluded that NPDSSA is feasible for space applications.

Deployment Simulation of Ultra-Lightweight Inflatable Structures

NASA Technical Reports Server (NTRS)

Wang, John T.; Johnson, Arthur R.

2002-01-01

Dynamic deployment analyses of folded inflatable tubes are conducted to investigate modeling issues related to the deployment of solar sail booms. The analyses are necessary because ground tests include gravity effects and may poorly represent deployment in space. A control volume approach, available in the LS-DYNA nonlinear dynamic finite element code, and the ideal gas law are used to simulate the dynamic inflation deployment process. Three deployment issues are investigated for a tube packaged in a Z-fold configuration. The issues are the effect of the rate of inflation, the effect of residual air, and the effect of gravity. The results of the deployment analyses reveal that the time and amount of inflation gas required to achieve a full deployment are related to these issues.

7 CFR 319.24-5 - Condition of entry.

Code of Federal Regulations, 2011 CFR

2011-01-01

... SERVICE, DEPARTMENT OF AGRICULTURE FOREIGN QUARANTINE NOTICES Corn Diseases Regulations Governing Entry of Indian Corn Or Maize § 319.24-5 Condition of entry. The corn shall not be removed from the port of entry... Quarantine Programs, that the corn has been properly sterilized and released for entry without further...

7 CFR 319.24-5 - Condition of entry.

Code of Federal Regulations, 2010 CFR

2010-01-01

... SERVICE, DEPARTMENT OF AGRICULTURE FOREIGN QUARANTINE NOTICES Corn Diseases Regulations Governing Entry of Indian Corn Or Maize § 319.24-5 Condition of entry. The corn shall not be removed from the port of entry... Quarantine Programs, that the corn has been properly sterilized and released for entry without further...

19 CFR 143.35 - Procedure for electronic entry summary.

Code of Federal Regulations, 2011 CFR

2011-04-01

... 19 Customs Duties 2 2011-04-01 2011-04-01 false Procedure for electronic entry summary. 143.35...; DEPARTMENT OF THE TREASURY (CONTINUED) SPECIAL ENTRY PROCEDURES Electronic Entry Filing § 143.35 Procedure for electronic entry summary. In order to obtain entry summary processing electronically, the filer...

19 CFR 143.35 - Procedure for electronic entry summary.

Code of Federal Regulations, 2010 CFR

2010-04-01

... 19 Customs Duties 2 2010-04-01 2010-04-01 false Procedure for electronic entry summary. 143.35...; DEPARTMENT OF THE TREASURY (CONTINUED) SPECIAL ENTRY PROCEDURES Electronic Entry Filing § 143.35 Procedure for electronic entry summary. In order to obtain entry summary processing electronically, the filer...

19 CFR 143.35 - Procedure for electronic entry summary.

Code of Federal Regulations, 2012 CFR

2012-04-01

... 19 Customs Duties 2 2012-04-01 2012-04-01 false Procedure for electronic entry summary. 143.35...; DEPARTMENT OF THE TREASURY (CONTINUED) SPECIAL ENTRY PROCEDURES Electronic Entry Filing § 143.35 Procedure for electronic entry summary. In order to obtain entry summary processing electronically, the filer...

The impact of antecedent trauma exposure and mental health symptoms on the post-deployment mental health of Afghanistan-deployed Australian troops.

PubMed

Searle, Amelia K; Van Hooff, Miranda; Lawrence-Wood, Ellie R; Grace, Blair S; Saccone, Elizabeth J; Davy, Carol P; Lorimer, Michelle; McFarlane, Alexander C

2017-10-01

Both traumatic deployment experiences and antecedent traumas increase personnel's risk of developing PTSD and depression. However, only cross-sectional studies have assessed whether antecedent trauma moderates stress reactions to deployment experiences. This study prospectively examines whether antecedent trauma moderates the association between deployment trauma and post-deployment PTSD and depressive symptoms after accounting for antecedent mental health problems, in a large Australian Defence Force (ADF) sample. In the ADF Middle East Area of Operations Prospective Study, currently-serving military personnel deployed to Afghanistan across 2010-2012 (n = 1122) completed self-reported measures at pre-deployment and post-deployment. Within multivariable regressions, associations between deployment trauma and PTSD and depressive symptoms at post-deployment were stronger for personnel with greater antecedent trauma. However, once adjusting for antecedent mental health problems, these significant interaction effects disappeared. Instead, deployment-related trauma and antecedent mental health problems showed direct associations with post-deployment mental health problems. Antecedent trauma was also indirectly associated with post-deployment mental health problems through antecedent mental health problems. Similar associations were seen with prior combat exposure as a moderator. Antecedent and deployment trauma were reported retrospectively. Self-reports may also suffer from social desirability bias, especially at pre-deployment. Our main effects results support the pervasive and cumulative negative effect of trauma on military personnel, regardless of its source. While antecedent trauma does not amplify personnel's psychological response to deployment trauma, it is indirectly associated with increased post-deployment mental health problems. Antecedent mental health should be considered within pre-deployment prevention programs, and deployment-trauma within post

Numerical Skip-Entry Guidance

NASA Technical Reports Server (NTRS)

Tigges, Michael; Crull, Timothy; Rea, Jeremy; Johnson, Wyatt

2006-01-01

This paper assesses a preliminary guidance and targeting strategy for accomplishing Skip-Entry (SE) flight during a lunar return-capsule entry flight. One of the primary benefits of flying a SE trajectory is to provide the crew with continuous Continental United States (CONUS) landing site access throughout the lunar month. Without a SE capability, the capsule must land either in water or at one of several distributed land sites in the Southern Hemisphere for a significant portion of a lunar month using a landing and recovery scenario similar to that employed during the Apollo program. With a SE trajectory, the capsule can land either in water at a site in proximity to CONUS or at one of several distributed landing sites within CONUS, thereby simplifying the operational requirements for crew retrieval and vehicle recovery, and possibly enabling a high degree of vehicle reusability. Note that a SE capability does not require that the vehicle land on land. A SE capability enables a longer-range flight than a direct-entry flight, which permits the vehicle to land at a much greater distance from the Entry Interface (EI) point. This does not exclude using this approach to push the landing point to a water location in proximity of CONUS and utilizing water or airborne recovery forces.

Competitive Swarm Optimizer Based Gateway Deployment Algorithm in Cyber-Physical Systems

PubMed Central

Huang, Shuqiang; Tao, Ming

2017-01-01

Wireless sensor network topology optimization is a highly important issue, and topology control through node selection can improve the efficiency of data forwarding, while saving energy and prolonging lifetime of the network. To address the problem of connecting a wireless sensor network to the Internet in cyber-physical systems, here we propose a geometric gateway deployment based on a competitive swarm optimizer algorithm. The particle swarm optimization (PSO) algorithm has a continuous search feature in the solution space, which makes it suitable for finding the geometric center of gateway deployment; however, its search mechanism is limited to the individual optimum (pbest) and the population optimum (gbest); thus, it easily falls into local optima. In order to improve the particle search mechanism and enhance the search efficiency of the algorithm, we introduce a new competitive swarm optimizer (CSO) algorithm. The CSO search algorithm is based on an inter-particle competition mechanism and can effectively avoid trapping of the population falling into a local optimum. With the improvement of an adaptive opposition-based search and its ability to dynamically parameter adjustments, this algorithm can maintain the diversity of the entire swarm to solve geometric K-center gateway deployment problems. The simulation results show that this CSO algorithm has a good global explorative ability as well as convergence speed and can improve the network quality of service (QoS) level of cyber-physical systems by obtaining a minimum network coverage radius. We also find that the CSO algorithm is more stable, robust and effective in solving the problem of geometric gateway deployment as compared to the PSO or Kmedoids algorithms. PMID:28117735

Competitive Swarm Optimizer Based Gateway Deployment Algorithm in Cyber-Physical Systems.

PubMed

Huang, Shuqiang; Tao, Ming

2017-01-22

Wireless sensor network topology optimization is a highly important issue, and topology control through node selection can improve the efficiency of data forwarding, while saving energy and prolonging lifetime of the network. To address the problem of connecting a wireless sensor network to the Internet in cyber-physical systems, here we propose a geometric gateway deployment based on a competitive swarm optimizer algorithm. The particle swarm optimization (PSO) algorithm has a continuous search feature in the solution space, which makes it suitable for finding the geometric center of gateway deployment; however, its search mechanism is limited to the individual optimum (pbest) and the population optimum (gbest); thus, it easily falls into local optima. In order to improve the particle search mechanism and enhance the search efficiency of the algorithm, we introduce a new competitive swarm optimizer (CSO) algorithm. The CSO search algorithm is based on an inter-particle competition mechanism and can effectively avoid trapping of the population falling into a local optimum. With the improvement of an adaptive opposition-based search and its ability to dynamically parameter adjustments, this algorithm can maintain the diversity of the entire swarm to solve geometric K -center gateway deployment problems. The simulation results show that this CSO algorithm has a good global explorative ability as well as convergence speed and can improve the network quality of service (QoS) level of cyber-physical systems by obtaining a minimum network coverage radius. We also find that the CSO algorithm is more stable, robust and effective in solving the problem of geometric gateway deployment as compared to the PSO or Kmedoids algorithms.

5-Beam ADCP Deployment Strategy Considerations

NASA Astrophysics Data System (ADS)

Moore, T.; Savidge, D. K.; Gargett, A.

2016-02-01

With the increasing availability of 5 beam ADCPs and expanding opportunities for their deployment within both observatory and dedicated process study settings, refinements in deployment strategies are needed.Measuring vertical velocities directly with a vertically oriented acoustic beam requires that the instrument be stably mounted and leveled within fractions of a degree. Leveled shallow water deployments to date have utilized divers to jet pipes into the sand for stability, manually mount the instruments on the pipes, and level them. Leveling has been guided by the deployed instrument's pitch and roll output, available in real-time because of the observatory settings in which the deployments occurred. To expand the range of feasible deployments to deeper, perhaps non-real-time capable settings, alternatives to diver deployment and leveling must be considered. To determine stability requirements, mooring motion (heading, pitch and roll) has been sampled at 1Hz by gimballed ADCPs at a range of instrument deployment depths, and in shrouded and unshrouded cages. Conditions under which ADCP cages resting on the bottom experience significant shifts in tilt, roll or heading are assessed using co-located wind and wave measurements. The accuracy of estimating vertical velocities using all five beams relative to a well leveled vertical single beam is assessed from archived high frequency five beam data, to explore whether easing the leveling requirement is feasible.

50 CFR 679.83 - Rockfish Program entry level fishery.

Code of Federal Regulations, 2010 CFR

2010-10-01

... 50 Wildlife and Fisheries 9 2010-10-01 2010-10-01 false Rockfish Program entry level fishery. 679... ALASKA Rockfish Program § 679.83 Rockfish Program entry level fishery. (a) Rockfish entry level fishery—(1) General. A rockfish entry level harvester and rockfish entry level processor may participate in...

21 CFR 1316.05 - Entry.

Code of Federal Regulations, 2010 CFR

2010-04-01

... 21 Food and Drugs 9 2010-04-01 2010-04-01 false Entry. 1316.05 Section 1316.05 Food and Drugs DRUG ENFORCEMENT ADMINISTRATION, DEPARTMENT OF JUSTICE ADMINISTRATIVE FUNCTIONS, PRACTICES, AND PROCEDURES Administrative Inspections § 1316.05 Entry. An inspection shall be carried out by an inspector. Any such...

19 CFR 151.41 - Information on entry summary.

Code of Federal Regulations, 2010 CFR

2010-04-01

... 19 Customs Duties 2 2010-04-01 2010-04-01 false Information on entry summary. 151.41 Section 151... Products § 151.41 Information on entry summary. On the entry summary for petroleum or petroleum products in.... If the exact volumetric quantity cannot be determined in advance, the entry summary may be made for...

Comparing post-deployment mental health services utilization in soldiers deployed to Balkan, Iraq and Afghanistan.

PubMed

Madsen, T; Sadowa Vedtofte, M; Nordentoft, M; Ravnborg Nissen, L; Bo Andersen, S

2017-06-01

Insight on how different missions have impacted rates of mental health service (MHS) utilization is unexplored. We compared postdeployment MHS utilization in a national cohort of first-time deployed to missions in Balkan, Iraq, and Afghanistan respectively. A prospective national cohort study of 13 246 first-time deployed in the period 1996 through 2012 to missions in Balkan area, Iraq, or Afghanistan respectively. Soldiers 'MHS utilization was also compared with a 5:1 sex-, age-, and calendar year-matched never-deployed background population. Postdeployment utilization of MHS was retrieved from national coverage registers. Using Cox survival analyses, participants were followed and compared with regard to receiving three different types of psychiatric services: (i) admission to psychiatric hospital, (ii) psychiatric outpatient contact, and (iii) prescriptions of psychotropics. Utilizing of psychiatric outpatient services and psychotropics was significantly higher in first-time deployed to Iraq and Afghanistan compared with deployed to Balkan. However, the rate of postdeployment admission to psychiatric hospital did not differ between missions. Postdeployment rates of psychiatric admission and psychiatric outpatient treatment were significantly higher in Afghanistan-deployed personnel compared with the background population. Utilization of MHS differed significantly between mission areas and was highest after the latest mission to Afghanistan. © 2017 John Wiley & Sons A/S. Published by John Wiley & Sons Ltd.

19 CFR 143.23 - Form of entry.

Code of Federal Regulations, 2010 CFR

2010-04-01

... (CONTINUED) SPECIAL ENTRY PROCEDURES Informal Entry § 143.23 Form of entry. Except for the types of... upper right hand corner. (g) Merchandise, regardless of value, which is imported for noncommercial... credit, Customs Form 7501, annotated “informal entry” in the upper right hand corner, and Customs Form...

Graphite/epoxy composite adapters for the Space Shuttle/Centaur vehicle

NASA Technical Reports Server (NTRS)

Kasper, Harold J.; Ring, Darryl S.

1990-01-01

The decision to launch various NASA satellite and Air Force spacecraft from the Space Shuttle created the need for a high-energy upper stage capable of being deployed from the cargo bay. Two redesigned versions of the Centaur vehicle which employed a graphite/epoxy composite material for the forward and aft adapters were selected. Since this was the first time a graphite/epoxy material was used for Centaur major structural components, the development of the adapters was a major effort. An overview of the composite adapter designs, subcomponent design evaluation test results, and composite adapter test results from a full-scale vehicle structural test is presented.

32 CFR 770.57 - Entry procedures.

Code of Federal Regulations, 2013 CFR

2013-07-01

... ACCESS TO PARTICULAR INSTALLATIONS Entry Regulations for Portsmouth Naval Shipyard, Portsmouth, New Hampshire § 770.57 Entry procedures. (a) Any person or group desiring the advance consent of the Commander...

32 CFR 770.57 - Entry procedures.

Code of Federal Regulations, 2014 CFR

2014-07-01

... ACCESS TO PARTICULAR INSTALLATIONS Entry Regulations for Portsmouth Naval Shipyard, Portsmouth, New Hampshire § 770.57 Entry procedures. (a) Any person or group desiring the advance consent of the Commander...

32 CFR 770.57 - Entry procedures.

Code of Federal Regulations, 2012 CFR

2012-07-01

... ACCESS TO PARTICULAR INSTALLATIONS Entry Regulations for Portsmouth Naval Shipyard, Portsmouth, New Hampshire § 770.57 Entry procedures. (a) Any person or group desiring the advance consent of the Commander...

32 CFR 770.57 - Entry procedures.

Code of Federal Regulations, 2011 CFR

2011-07-01

... ACCESS TO PARTICULAR INSTALLATIONS Entry Regulations for Portsmouth Naval Shipyard, Portsmouth, New Hampshire § 770.57 Entry procedures. (a) Any person or group desiring the advance consent of the Commander...

Modelling multi-rotor UAVs swarm deployment using virtual pheromones

PubMed Central

Pujol, Mar; Rizo, Ramón; Rizo, Carlos

2018-01-01

In this work, a swarm behaviour for multi-rotor Unmanned Aerial Vehicles (UAVs) deployment will be presented. The main contribution of this behaviour is the use of a virtual device for quantitative sematectonic stigmergy providing more adaptable behaviours in complex environments. It is a fault tolerant highly robust behaviour that does not require prior information of the area to be covered, or to assume the existence of any kind of information signals (GPS, mobile communication networks …), taking into account the specific features of UAVs. This behaviour will be oriented towards emergency tasks. Their main goal will be to cover an area of the environment for later creating an ad-hoc communication network, that can be used to establish communications inside this zone. Although there are several papers on robotic deployment it is more difficult to find applications with UAV systems, mainly because of the existence of various problems that must be overcome including limitations in available sensory and on-board processing capabilities and low flight endurance. In addition, those behaviours designed for UAVs often have significant limitations on their ability to be used in real tasks, because they assume specific features, not easily applicable in a general way. Firstly, in this article the characteristics of the simulation environment will be presented. Secondly, a microscopic model for deployment and creation of ad-hoc networks, that implicitly includes stigmergy features, will be shown. Then, the overall swarm behaviour will be modeled, providing a macroscopic model of this behaviour. This model can accurately predict the number of agents needed to cover an area as well as the time required for the deployment process. An experimental analysis through simulation will be carried out in order to verify our models. In this analysis the influence of both the complexity of the environment and the stigmergy system will be discussed, given the data obtained in the

ROBOTICS IN HAZARDOUS ENVIRONMENTS - REAL DEPLOYMENTS BY THE SAVANNAH RIVER NATIONAL LABORATORY

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

Kriikku, E.; Tibrea, S.; Nance, T.

The Research & Development Engineering (R&DE) section in the Savannah River National Laboratory (SRNL) engineers, integrates, tests, and supports deployment of custom robotics, systems, and tools for use in radioactive, hazardous, or inaccessible environments. Mechanical and electrical engineers, computer control professionals, specialists, machinists, welders, electricians, and mechanics adapt and integrate commercially available technology with in-house designs, to meet the needs of Savannah River Site (SRS), Department of Energy (DOE), and other governmental agency customers. This paper discusses five R&DE robotic and remote system projects.

76 FR 8294 - Technical Correction: Completion of Entry and Entry Summary-Declaration of Value; Correction

Federal Register 2010, 2011, 2012, 2013, 2014

2011-02-14

... DEPARTMENT OF HOMELAND SECURITY U. S. Customs and Border Protection 19 CFR Part 141 [USCBP-2008-0062; CBP Dec. 10-34] RIN 1515-AD61 (Formerly 1505-AB96) Technical Correction: Completion of Entry and Entry Summary-- Declaration of Value; Correction AGENCY: Customs and Border Protection, Department of...

Development and modeling of self-deployable structures

NASA Astrophysics Data System (ADS)

Neogi, Depankar

Deployable space structures are prefabricated structures which can be transformed from a closed, compact configuration to a predetermined expanded form in which they are stable and can bear loads. The present research effort investigates a new family of deployable structures, called the Self-Deployable Structures (SDS). Unlike other deployable structures, which have rigid members, the SDS members are flexible while the connecting joints are rigid. The joints store the predefined geometry of the deployed structure in the collapsed state. The SDS is stress-free in both deployed and collapsed configurations and results in a self-standing structure which acquires its structural properties after a chemical reaction. Reliability of deployment is one of the most important features of the SDS, since it does not rely on mechanisms that can lock during deployment. The unit building block of these structures is the self-deployable structural element (SDSE). Several SDSE members can be linked to generate a complex building block such as a triangular or a tetrahedral structure. Different SDSE and SDS concepts are investigated in the research work, and the performance of SDS's are experimentally and theoretically explored. Triangular and tetrahedral prototype SDS have been developed and presented. Theoretical efforts include modeling the behavior of 2-dimensional SDSs. Using this design tool, engineers can study the effects of different packing configurations and deployment sequence; and perform optimization on the collapsed state of a structure with different external constraints. The model also predicts if any lockup or entanglement occurs during deployment.

32 CFR 770.39 - Entry procedures.

Code of Federal Regulations, 2010 CFR

2010-07-01

... ACCESS TO PARTICULAR INSTALLATIONS Entry Regulations for Naval Installations and Property in Puerto Rico... entry upon any U.S. Naval installation or property in Puerto Rico from the Commanding Officer of the...

32 CFR 770.39 - Entry procedures.

Code of Federal Regulations, 2011 CFR

2011-07-01

... ACCESS TO PARTICULAR INSTALLATIONS Entry Regulations for Naval Installations and Property in Puerto Rico... entry upon any U.S. Naval installation or property in Puerto Rico from the Commanding Officer of the...

Reported stressors and health care needs of active duty Navy personnel during three phases of deployment in support of the war in Iraq.

PubMed

McNulty, Peggy Anne Fisher

2005-06-01

Literature has generously documented the stress of military members and their families during deployments in noncombat periods. Deployment has been shown to increase the needs of family members for health care, both physical and psychological. The purpose of this study was to describe the health care needs and perceived stressors of active duty members deployed to Iraq during the predeployment, mid-deployment, and postdeployment phases. Active duty Navy service members deployed on three aircraft carriers during Operation Enduring Freedom and Operation Iraqi Freedom in 2002-2003 were randomly selected to participate in an anonymous study that evaluated member well-being, adaptation, coping, anxiety, stress, and health care needs during three phases of deployment. Data were obtained from 474 Navy members in predeployment, 445 in mid-deployment, and 276 in postdeployment. Logistic regression analyses indicated that many variables predicted extreme anxiety during deployment, including mid-deployment phase, age of under 25 years, being childless, nonattendance at church, being enlisted, zero- or one-deployment history; no high school education, and being currently in counseling. Active duty members in all phases of deployment had equally disturbing levels of anxiety. All phases reported suicidal ideation at alarming rates (2.4% in predeployment, 4.9% in mid-deployment, and 3% in postdeployment). This study sheds new light on the stressors and subsequent health care needs of active duty members on carriers during war and provides valuable information for the prevention of high-risk anxieties and subsequent health risks for all service members during similar deployments.

30 CFR 842.13 - Right of entry.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 30 Mineral Resources 3 2010-07-01 2010-07-01 false Right of entry. 842.13 Section 842.13 Mineral... INSPECTION AND ENFORCEMENT PROCEDURES FEDERAL INSPECTIONS AND MONITORING § 842.13 Right of entry. (a) Each... right of entry to, upon, and through any coal exploration or surface coal mining and reclamation...

30 CFR 721.12 - Right of entry.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 30 Mineral Resources 3 2010-07-01 2010-07-01 false Right of entry. 721.12 Section 721.12 Mineral... REGULATIONS FEDERAL INSPECTIONS § 721.12 Right of entry. (a) Authorized representatives of the Secretary..., shall have the right of entry to, upon, or through any surface coal mining and reclamation operations or...

31 CFR 357.0 - Book-entry systems.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 31 Money and Finance: Treasury 2 2010-07-01 2010-07-01 false Book-entry systems. 357.0 Section 357..., DEPARTMENT OF THE TREASURY BUREAU OF THE PUBLIC DEBT REGULATIONS GOVERNING BOOK-ENTRY TREASURY BONDS, NOTES AND BILLS HELD IN LEGACY TREASURY DIRECT General Information § 357.0 Book-entry systems. (a) Treasury...

Deployable M-braced truss structure

NASA Technical Reports Server (NTRS)

Mikulas, M. M., Jr. (Inventor); Rhodes, M. D. (Inventor)

1986-01-01

A deployable M-braced truss structure, efficiently packaged into a compact stowed position and expandable to an operative position at the use site is described. The M-braced configuration effectively separates tension compression and shear in the structure and permits efficient structural design. Both diagonals and longerons telescope from an M-braced base unit and deploy either pneumatically, mechanically by springs or cables, or by powered reciprocating mechanisms. Upon full deployment, the diagonals and longerons lock into place with a simple latch mechanism.

The development of a complementary expendable launch vehicle interface for an STS deployable payload

NASA Astrophysics Data System (ADS)

Eubanks, Ed; Gibb, John

1990-04-01

The development is described of an interface, the Titan Payload Adapter (TPA), between a Space Transportation System (STS) deployable payload and an expendable launch vehicle (ELV). Separate ascent and separation constraint systems allow a payload with integral trunnions to retain its originally designed, boost-phase load structure, yet also allow the expendable booster vehicle to separate from the payload via retro-rockets. Design requirements as well as development problems and their solutions are discussed.

The development of a complementary expendable launch vehicle interface for an STS deployable payload

NASA Technical Reports Server (NTRS)

Eubanks, ED; Gibb, John

1990-01-01

The development is described of an interface, the Titan Payload Adapter (TPA), between a Space Transportation System (STS) deployable payload and an expendable launch vehicle (ELV). Separate ascent and separation constraint systems allow a payload with integral trunnions to retain its originally designed, boost-phase load structure, yet also allow the expendable booster vehicle to separate from the payload via retro-rockets. Design requirements as well as development problems and their solutions are discussed.

Connected Vehicle Pilot Deployment Program phase I : comprehensive Pilot Deployment Plan : Tampa Hillsborough Expressway Authority (THEA) : final report.

DOT National Transportation Integrated Search

2016-07-01

The Tampa Hillsborough Expressway Authority (THEA) Connected Vehicle (CV) Pilot Deployment Program is part of a national effort to advance CV technologies by deploying, demonstrating, testing and offering lessons learned for future deployers. The THE...

Adaptive Clinical Trials: Advantages and Disadvantages of Various Adaptive Design Elements.

PubMed

Korn, Edward L; Freidlin, Boris

2017-06-01

There is a wide range of adaptive elements of clinical trial design (some old and some new), with differing advantages and disadvantages. Classical interim monitoring, which adapts the design based on early evidence of superiority or futility of a treatment arm, has long been known to be extremely useful. A more recent application of interim monitoring is in the use of phase II/III designs, which can be very effective (especially in the setting of multiple experimental treatments and a reliable intermediate end point) but do have the cost of having to commit earlier to the phase III question than if separate phase II and phase III trials were performed. Outcome-adaptive randomization is an older technique that has recently regained attention; it increases trial complexity and duration without offering substantial benefits to the patients in the trial. The use of adaptive trials with biomarkers is new and has great potential for efficiently identifying patients who will be helped most by specific treatments. Master protocols in which trial arms and treatment questions are added to an ongoing trial can be especially efficient in the biomarker setting, where patients are screened for entry into different subtrials based on evolving knowledge about targeted therapies. A discussion of three recent adaptive clinical trials (BATTLE-2, I-SPY 2, and FOCUS4) highlights the issues. Published by Oxford University Press 2017. This work is written by US Government employees and is in the public domain in the US.

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.

Visualization of Flow Separation Around an Atmospheric Entry Capsule at Low-Subsonic Mach Number Using Background-Oriented Schlieren (BOS)

NASA Technical Reports Server (NTRS)

Mizukaki, Toshiharu; Borg, Stephen E.; Danehy, Paul M.; Murman, Scott M.

2014-01-01

This paper presents the results of visualization of separated flow around a generic entry capsule that resembles the Apollo Command Module (CM) and the Orion Multi-Purpose Crew Vehicle (MPCV). The model was tested at flow speeds up to Mach 0.4 at a single angle of attack of 28 degrees. For manned spacecraft using capsule-shaped vehicles, certain flight operations such as emergency abort maneuvers soon after launch and flight just prior to parachute deployment during the final stages of entry, the command module may fly at low Mach number. Under these flow conditions, the separated flow generated from the heat-shield surface on both windward and leeward sides of the capsule dominates the wake flow downstream of the capsule. In this paper, flow visualization of the separated flow was conducted using the background-oriented schlieren (BOS) method, which has the capability of visualizing significantly separated wake flows without the particle seeding required by other techniques. Experimental results herein show that BOS has detection capability of density changes on the order of 10(sup-5).

Entry Guidance for the Reusable Launch Vehicle

NASA Technical Reports Server (NTRS)

Lu, Ping

1999-01-01

The X-33 Advanced Technology Demonstrator is a half-scale prototype developed to test the key technologies needed for a full-scale single-stage reusable launch vehicle (RLV). The X-33 is a suborbital vehicle that will be launched vertically, and land horizontally. The goals of this research were to develop an alternate entry guidance scheme for the X-33 in parallel to the actual X-33 entry guidance algorithms, provide comparative and complementary study, and identify potential new ways to improve entry guidance performance. Toward these goals, the nominal entry trajectory is defined by a piecewise linear drag-acceleration-versus-energy profile, which is in turn obtained by the solution of a semi-analytical parameter optimization problem. The closed-loop guidance is accomplished by tracking the nominal drag profile with primarily bank-angle modulation on-board. The bank-angle is commanded by a single full-envelope nonlinear trajectory control law. Near the end of the entry flight, the guidance logic is switched to heading control in order to meet strict conditions at the terminal area energy management interface. Two methods, one on ground-track control and the other on heading control, were proposed and examined for this phase of entry guidance where lateral control is emphasized. Trajectory dispersion studies were performed to evaluate the effectiveness of the entry guidance algorithms against a number of uncertainties including those in propulsion system, atmospheric properties, winds, aerodynamics, and propellant loading. Finally, a new trajectory-regulation method is introduced at the end as a promising precision entry guidance method. The guidance principle is very different and preliminary application in X-33 entry guidance simulation showed high precision that is difficult to achieve by existing methods.

Nipah virus entry can occur by macropinocytosis

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

Pernet, Olivier; Pohl, Christine; Ainouze, Michelle

2009-12-20

Nipah virus (NiV) is a zoonotic biosafety level 4 paramyxovirus that emerged recently in Asia with high mortality in man. NiV is a member, with Hendra virus (HeV), of the Henipavirus genus in the Paramyxoviridae family. Although NiV entry, like that of other paramyxoviruses, is believed to occur via pH-independent fusion with the host cell's plasma membrane we present evidence that entry can occur by an endocytic pathway. The NiV receptor ephrinB2 has receptor kinase activity and we find that ephrinB2's cytoplasmic domain is required for entry but is dispensable for post-entry viral spread. The mutation of a single tyrosinemore » residue (Y304F) in ephrinB2's cytoplasmic tail abrogates NiV entry. Moreover, our results show that NiV entry is inhibited by constructions and drugs specific for the endocytic pathway of macropinocytosis. Our findings could potentially permit the rapid development of novel low-cost antiviral treatments not only for NiV but also HeV.« less

Evolved atmospheric entry corridor with safety factor

NASA Astrophysics Data System (ADS)

Liang, Zixuan; Ren, Zhang; Li, Qingdong

2018-02-01

Atmospheric entry corridors are established in previous research based on the equilibrium glide condition which assumes the flight-path angle to be zero. To get a better understanding of the highly constrained entry flight, an evolved entry corridor that considers the exact flight-path angle is developed in this study. Firstly, the conventional corridor in the altitude vs. velocity plane is extended into a three-dimensional one in the space of altitude, velocity, and flight-path angle. The three-dimensional corridor is generated by a series of constraint boxes. Then, based on a simple mapping method, an evolved two-dimensional entry corridor with safety factor is obtained. The safety factor is defined to describe the flexibility of the flight-path angle for a state within the corridor. Finally, the evolved entry corridor is simulated for the Space Shuttle and the Common Aero Vehicle (CAV) to demonstrate the effectiveness of the corridor generation approach. Compared with the conventional corridor, the evolved corridor is much wider and provides additional information. Therefore, the evolved corridor would benefit more to the entry trajectory design and analysis.

32 CFR 770.38 - Entry restrictions.

Code of Federal Regulations, 2010 CFR

2010-07-01

... in Puerto Rico § 770.38 Entry restrictions. Except for duly authorized military personnel and... duties, entry upon any U.S. Navy installation or property in Puerto Rico at anytime, by any person for...

32 CFR 770.38 - Entry restrictions.

Code of Federal Regulations, 2011 CFR

2011-07-01

... in Puerto Rico § 770.38 Entry restrictions. Except for duly authorized military personnel and... duties, entry upon any U.S. Navy installation or property in Puerto Rico at anytime, by any person for...

Expectations among the elderly about nursing home entry.

PubMed

Lindrooth, R C; Hoerger, T J; Norton, E C

2000-12-01

To assess whether the covariates that explain expectations of nursing home entry are consistent with the characteristics of those who enter nursing homes. Waves 1 and 2 of the Assets and Health Dynamics Among the Oldest Old (AHEAD) survey. We model expectations about nursing home entry as a function of expectations about leaving a bequest, living at least ten years, health condition, and other observed characteristics. We use an instrumental variables and generalized least squares (IV-GLS) method based on Hausman and Taylor (1981) to obtain more efficient estimates than fixed effects, without the restrictive assumptions of random effects. Expectations about nursing home entry are reasonably close to the actual probability of nursing home entry. Most of the variables that affect actual entry also have significant effects on expectations about entry. Medicaid subsidies for nursing home care may have little effect on expectations about nursing home entry; individuals in the lowest asset quartile, who are most likely to receive these subsidies, report probabilities not significantly different from those in other quartiles. Application of the IV-GLS approach is supported by a series of specification tests. We find that expectations about future nursing home entry are consistent with the characteristics of actual entrants. Underestimation of risk of nursing home entry as a reason for low levels of long-term care insurance is not supported by this analysis.

Design of Adaptive Policy Pathways under Deep Uncertainties

NASA Astrophysics Data System (ADS)

Babovic, Vladan

2013-04-01

The design of large-scale engineering and infrastructural systems today is growing in complexity. Designers need to consider sociotechnical uncertainties, intricacies, and processes in the long- term strategic deployment and operations of these systems. In this context, water and spatial management is increasingly challenged not only by climate-associated changes such as sea level rise and increased spatio-temporal variability of precipitation, but also by pressures due to population growth and particularly accelerating rate of urbanisation. Furthermore, high investment costs and long term-nature of water-related infrastructure projects requires long-term planning perspective, sometimes extending over many decades. Adaptation to such changes is not only determined by what is known or anticipated at present, but also by what will be experienced and learned as the future unfolds, as well as by policy responses to social and water events. As a result, a pathway emerges. Instead of responding to 'surprises' and making decisions on ad hoc basis, exploring adaptation pathways into the future provide indispensable support in water management decision-making. In this contribution, a structured approach for designing a dynamic adaptive policy based on the concepts of adaptive policy making and adaptation pathways is introduced. Such an approach provides flexibility which allows change over time in response to how the future unfolds, what is learned about the system, and changes in societal preferences. The introduced flexibility provides means for dealing with complexities of adaptation under deep uncertainties. It enables engineering systems to change in the face of uncertainty to reduce impacts from downside scenarios while capitalizing on upside opportunities. This contribution presents comprehensive framework for development and deployment of adaptive policy pathway framework, and demonstrates its performance under deep uncertainties on a case study related to urban

9 CFR 98.9 - Embryos refused entry.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 9 Animals and Animal Products 1 2012-01-01 2012-01-01 false Embryos refused entry. 98.9 Section 98... EMBRYOS AND ANIMAL SEMEN Ruminant and Swine Embryos from Regions Free of Rinderpest and Foot-and-Mouth Disease; and Embryos of Horses and Asses § 98.9 Embryos refused entry. Any embryo refused entry into the...

9 CFR 98.9 - Embryos refused entry.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 9 Animals and Animal Products 1 2014-01-01 2014-01-01 false Embryos refused entry. 98.9 Section 98... EMBRYOS AND ANIMAL SEMEN Ruminant and Swine Embryos from Regions Free of Rinderpest and Foot-and-Mouth Disease; and Embryos of Horses and Asses § 98.9 Embryos refused entry. Any embryo refused entry into the...

9 CFR 98.9 - Embryos refused entry.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 9 Animals and Animal Products 1 2013-01-01 2013-01-01 false Embryos refused entry. 98.9 Section 98... EMBRYOS AND ANIMAL SEMEN Ruminant and Swine Embryos from Regions Free of Rinderpest and Foot-and-Mouth Disease; and Embryos of Horses and Asses § 98.9 Embryos refused entry. Any embryo refused entry into the...

9 CFR 98.9 - Embryos refused entry.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 9 Animals and Animal Products 1 2010-01-01 2010-01-01 false Embryos refused entry. 98.9 Section 98... EMBRYOS AND ANIMAL SEMEN Ruminant and Swine Embryos from Regions Free of Rinderpest and Foot-and-Mouth Disease; and Embryos of Horses and Asses § 98.9 Embryos refused entry. Any embryo refused entry into the...

9 CFR 98.9 - Embryos refused entry.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 9 Animals and Animal Products 1 2011-01-01 2011-01-01 false Embryos refused entry. 98.9 Section 98... EMBRYOS AND ANIMAL SEMEN Ruminant and Swine Embryos from Regions Free of Rinderpest and Foot-and-Mouth Disease; and Embryos of Horses and Asses § 98.9 Embryos refused entry. Any embryo refused entry into the...

Teaching Composition to Re-Entry Students

ERIC Educational Resources Information Center

Foulkes, Natalie; Taines, Beatrice

1978-01-01

Describes the Women's Re-Entry Program at Diablo Valley College which uses structured teaching methods to alleviate the two principal weaknesses found in English compositions written by re-entry women, vagueness and lack of organization. (TP)

Equilibrium radiative heating tables for Earth entry

NASA Astrophysics Data System (ADS)

Sutton, Kenneth; Hartung, Lin C.

1990-05-01

The recent resurgence of interest in blunt-body atmospheric entry for applications such as aeroassisted orbital transfer and planetary return has engendered a corresponding revival of interest in radiative heating. Radiative heating may be of importance in these blunt-body flows because of the highly energetic shock layer around the blunt nose. Sutton developed an inviscid, stagnation point, radiation coupled flow field code for investigating blunt-body atmospheric entry. The method has been compared with ground-based and flight data, and reasonable agreement has been found. To provide information for entry body studies in support of lunar and Mars return scenarios of interest in the 1970's, the code was exercised over a matrix of Earth entry conditions. Recently, this matrix was extended slightly to reflect entry vehicle designs of current interest. Complete results are presented.

Alphavirus entry into host cells.

PubMed

Vancini, Ricardo; Hernandez, Raquel; Brown, Dennis

2015-01-01

Viruses have evolved to exploit the vast complexity of cellular processes for their success within the host cell. The entry mechanisms of enveloped viruses (viruses with a surrounding outer lipid bilayer membrane) are usually classified as being either endocytotic or fusogenic. Different mechanisms have been proposed for Alphavirus entry and genome delivery. Indirect observations led to a general belief that enveloped viruses can infect cells either by protein-assisted fusion with the plasma membrane in a pH-independent manner or by endocytosis and fusion with the endocytic vacuole in a low-pH environment. The mechanism of Alphavirus penetration has been recently revisited using direct observation of the processes by electron microscopy under conditions of different temperatures and time progression. Under conditions nonpermissive for endocytosis or any vesicular transport, events occur which allow the entry of the virus genome into the cells. When drug inhibitors of cellular functions are used to prevent entry, only ionophores are found to significantly inhibit RNA delivery. Arboviruses are agents of significant human and animal disease; therefore, strategies to control infections are needed and include development of compounds which will block critical steps in the early infection events. It appears that current evidence points to an entry mechanism, in which alphaviruses infect cells by direct penetration of cell plasma membranes through a pore structure formed by virus and, possibly, host proteins. © 2015 Elsevier Inc. All rights reserved.

Adaptive Management of Computing and Network Resources for Spacecraft Systems

NASA Technical Reports Server (NTRS)

Pfarr, Barbara; Welch, Lonnie R.; Detter, Ryan; Tjaden, Brett; Huh, Eui-Nam; Szczur, Martha R. (Technical Monitor)

2000-01-01

It is likely that NASA's future spacecraft systems will consist of distributed processes which will handle dynamically varying workloads in response to perceived scientific events, the spacecraft environment, spacecraft anomalies and user commands. Since all situations and possible uses of sensors cannot be anticipated during pre-deployment phases, an approach for dynamically adapting the allocation of distributed computational and communication resources is needed. To address this, we are evolving the DeSiDeRaTa adaptive resource management approach to enable reconfigurable ground and space information systems. The DeSiDeRaTa approach embodies a set of middleware mechanisms for adapting resource allocations, and a framework for reasoning about the real-time performance of distributed application systems. The framework and middleware will be extended to accommodate (1) the dynamic aspects of intra-constellation network topologies, and (2) the complete real-time path from the instrument to the user. We are developing a ground-based testbed that will enable NASA to perform early evaluation of adaptive resource management techniques without the expense of first deploying them in space. The benefits of the proposed effort are numerous, including the ability to use sensors in new ways not anticipated at design time; the production of information technology that ties the sensor web together; the accommodation of greater numbers of missions with fewer resources; and the opportunity to leverage the DeSiDeRaTa project's expertise, infrastructure and models for adaptive resource management for distributed real-time systems.

Aeroelastic characteristics of a rapid prototype multi-material wind tunnel model of a mechanically deployable aerodynamic decelerator

NASA Astrophysics Data System (ADS)

Raskin, Boris

Scaled wind tunnel models are necessary for the development of aircraft and spacecraft to simulate aerodynamic behavior. This allows for testing multiple iterations of a design before more expensive full-scale aircraft and spacecraft are built. However, the cost of building wind tunnel models can still be high because they normally require costly subtractive manufacturing processes, such as machining, which can be time consuming and laborious due to the complex surfaces of aerodynamic models. Rapid prototyping, commonly known as 3D printing, can be utilized to save on wind tunnel model manufacturing costs. A rapid prototype multi-material wind tunnel model was manufactured for this thesis to investigate the possibility of using PolyJet 3D printing to create a model that exhibits aeroelastic behavior. The model is of NASA's Adaptable Deployable entry and Placement (ADEPT) aerodynamic decelerator, used to decelerate a spacecraft during reentry into a planet's atmosphere. It is a 60° cone with a spherically blunted nose that consists of a 12 flexible panels supported by a rigid structure of nose, ribs, and rim. The novel rapid prototype multi-material model was instrumented and tested in two flow conditions. Quantitative comparisons were made of the average forces and dynamic forces on the model, demonstrating that the model matched expected behavior for average drag, but not Strouhal number, indicating that there was no aeroelastic behavior in this particular case. It was also noted that the dynamic properties (e.g., resonant frequency) associated with the mounting scheme are very important and may dominate the measured dynamic response.

Deployable video conference table

NASA Technical Reports Server (NTRS)

Cohen, Marc M. (Inventor); Lissol, Peter (Inventor)

1993-01-01

A deployable table is presented. The table is stowed in and deployed from a storage compartment based upon a non-self rigidizing, 4-hinge, arch support structure that folds upon itself to stow and that expands to deploy. The work surfaces bypass each other above and below to allow the deployment mechanism to operate. This assembly includes the following: first and second primary pivot hinges placed at the opposite ends of the storage compartment; first and second lateral frame members with proximal ends connected to the first and second pivot hinges; a medial frame member offset from and pivotally connected to distal ends of the first and second members through third and fourth medial pivot hinges; and left-side, right-side, and middle trays connected respectively to the first, second, and third frame members and being foldable into and out of the storage compartment by articulation of the first, second, third, and fourth joints. At least one of the third and fourth joints are locked to set the first, second, and third frame members in a desired angular orientation with respect to each other.

Non-traditional Infrasound Deployment

NASA Astrophysics Data System (ADS)

McKenna, M. H.; McComas, S.; Simpson, C. P.; Diaz-Alvarez, H.; Costley, R. D.; Hayward, C.; Golden, P.; Endress, A.

2017-12-01

Historically, infrasound arrays have been deployed in rural environments where anthropological noise sources are limited. As interest in monitoring low energy sources at local distances grows in the infrasound community, it will be vital to understand how to monitor infrasound sources in an urban environment. Arrays deployed in urban centers have to overcome the decreased signal-to-noise ratio and reduced amount of real estate available to deploy an array. To advance the understanding of monitoring infrasound sources in urban environments, local and regional infrasound arrays were deployed on building rooftops on the campus at Southern Methodist University (SMU), and data were collected for one seasonal cycle. The data were evaluated for structural source signals (continuous-wave packets), and when a signal was identified, the back azimuth to the source was determined through frequency-wavenumber analysis. This information was used to identify hypothesized structural sources; these sources were verified through direct measurement and dynamic structural analysis modeling. In addition to the rooftop arrays, a camouflaged infrasound sensor was installed on the SMU campus and evaluated to determine its effectiveness for wind noise reduction. Permission to publish was granted by Director, Geotechnical and Structures Laboratory.

Adaptive Immunity to Fungi

PubMed Central

Wüthrich, Marcel; Deepe, George S.; Klein, Bruce

2013-01-01

Only a handful of the more than 100,000 fungal species on our planet cause disease in humans, yet the number of life-threatening fungal infections in patients has recently skyrocketed as a result of advances in medical care that often suppress immunity intensely. This emerging crisis has created pressing needs to clarify immune defense mechanisms against fungi, with the ultimate goal of therapeutic applications. Herein, we describe recent insights in understanding the mammalian immune defenses deployed against pathogenic fungi. The review focuses on adaptive immune responses to the major medically important fungi and emphasizes how dendritic cells and subsets in various anatomic compartments respond to fungi, recognize their molecular patterns, and signal responses that nurture and shape the differentiation of T cell subsets and B cells. Also emphasized is how the latter deploy effector and regulatory mechanisms that eliminate these nasty invaders while also constraining collateral damage to vital tissue. PMID:22224780

Fathering after military deployment: parenting challenges and goals of fathers of young children.

PubMed

Walsh, Tova B; Dayton, Carolyn J; Erwin, Michael S; Muzik, Maria; Busuito, Alexandra; Rosenblum, Katherine L

2014-02-01

Although often eagerly anticipated, reunification after deployment poses challenges for families, including adjusting to the parent-soldier's return, re-establishing roles and routines, and the potentially necessary accommodation to combat-related injuries or psychological effects. Fourteen male service members, previously deployed to a combat zone, parent to at least one child under seven years of age, were interviewed about their relationships with their young children. Principles of grounded theory guided data analysis to identify key themes related to parenting young children after deployment. Participants reported significant levels of parenting stress and identified specific challenges, including difficulty reconnecting with children, adapting expectations from military to family life, and coparenting. Fathers acknowledged regret about missing an important period in their child's development and indicated a strong desire to improve their parenting skills. They described a need for support in expressing emotions, nurturing, and managing their tempers. Results affirm the need for support to military families during reintegration and demonstrate that military fathers are receptive to opportunities to engage in parenting interventions. Helping fathers understand their children's behavior in the context of age-typical responses to separation and reunion may help them to renew parent-child relationships and reengage in optimal parenting of their young children.

Decision-making tool for applying adaptive traffic control systems : final report.

DOT National Transportation Integrated Search

2016-03-01

Adaptive traffic signal control technologies have been increasingly deployed in real world situations. The objective of this project was to develop a decision-making tool to guide traffic engineers and decision-makers who must decide whether or not a...

Expectations among the elderly about nursing home entry.

PubMed Central

Lindrooth, R C; Hoerger, T J; Norton, E C

2000-01-01

OBJECTIVE: To assess whether the covariates that explain expectations of nursing home entry are consistent with the characteristics of those who enter nursing homes. DATA SOURCES: Waves 1 and 2 of the Assets and Health Dynamics Among the Oldest Old (AHEAD) survey. STUDY DESIGN: We model expectations about nursing home entry as a function of expectations about leaving a bequest, living at least ten years, health condition, and other observed characteristics. We use an instrumental variables and generalized least squares (IV-GLS) method based on Hausman and Taylor (1981) to obtain more efficient estimates than fixed effects, without the restrictive assumptions of random effects. PRINCIPAL FINDINGS: Expectations about nursing home entry are reasonably close to the actual probability of nursing home entry. Most of the variables that affect actual entry also have significant effects on expectations about entry. Medicaid subsidies for nursing home care may have little effect on expectations about nursing home entry; individuals in the lowest asset quartile, who are most likely to receive these subsidies, report probabilities not significantly different from those in other quartiles. Application of the IV-GLS approach is supported by a series of specification tests. CONCLUSIONS: We find that expectations about future nursing home entry are consistent with the characteristics of actual entrants. Underestimation of risk of nursing home entry as a reason for low levels of long-term care insurance is not supported by this analysis. PMID:11130816

Ethernet access network based on free-space optic deployment technology

NASA Astrophysics Data System (ADS)

Gebhart, Michael; Leitgeb, Erich; Birnbacher, Ulla; Schrotter, Peter

2004-06-01

The satisfaction of all communication needs from single households and business companies over a single access infrastructure is probably the most challenging topic in communications technology today. But even though the so-called "Last Mile Access Bottleneck" is well known since more than ten years and many distribution technologies have been tried out, the optimal solution has not yet been found and paying commercial access networks offering all service classes are still rare today. Conventional services like telephone, radio and TV, as well as new and emerging services like email, web browsing, online-gaming, video conferences, business data transfer or external data storage can all be transmitted over the well known and cost effective Ethernet networking protocol standard. Key requirements for the deployment technology driven by the different services are high data rates to the single customer, security, moderate deployment costs and good scalability to number and density of users, quick and flexible deployment without legal impediments and high availability, referring to the properties of optical and wireless communication. We demonstrate all elements of an Ethernet Access Network based on Free Space Optic distribution technology. Main physical parts are Central Office, Distribution Network and Customer Equipment. Transmission of different services, as well as configuration, service upgrades and remote control of the network are handled by networking features over one FSO connection. All parts of the network are proven, the latest commercially available technology. The set up is flexible and can be adapted to any more specific need if required.

The actin cytoskeleton in store-mediated calcium entry

PubMed Central

Rosado, Juan A; Sage, Stewart O

2000-01-01

Store-mediated Ca2+ entry is the main pathway for Ca2+ influx in platelets and many other cells. Several hypotheses have considered both direct and indirect coupling mechanisms between the endoplasmic reticulum and the plasma membrane. Here we pay particular attention to new insights into the regulation of store-mediated Ca2+ entry: the role of the cytoskeleton in a secretion-like coupling model. In this model, Ca2+ entry may be mediated by a reversible trafficking and coupling of the endoplasmic reticulum with the plasma membrane, that shows close parallels to the events mediating secretion. As with secretion, the actin cytoskeleton plays an inhibitory role in the activation of Ca2+ entry by preventing the approach and coupling of the endoplasmic reticulum with the plasma membrane, making cytoskeletal remodelling a key event in the activation of Ca2+ entry. We also review recent advances investigating the regulation of store-mediated Ca2+ entry by small GTPases and phosphoinositides, which might be involved in the store-mediated Ca2+ entry pathway through roles in the remodelling of the cytoskeleton. PMID:10896713

Robustness via Run-Time Adaptation of Contingent Plans

NASA Technical Reports Server (NTRS)

Bresina, John L.; Washington, Richard; Norvig, Peter (Technical Monitor)

2000-01-01

In this paper, we discuss our approach to making the behavior of planetary rovers more robust for the purpose of increased productivity. Due to the inherent uncertainty in rover exploration, the traditional approach to rover control is conservative, limiting the autonomous operation of the rover and sacrificing performance for safety. Our objective is to increase the science productivity possible within a single uplink by allowing the rover's behavior to be specified with flexible, contingent plans and by employing dynamic plan adaptation during execution. We have deployed a system exhibiting flexible, contingent execution; this paper concentrates on our ongoing efforts on plan adaptation, Plans can be revised in two ways: plan steps may be deleted, with execution continuing with the plan suffix; and the current plan may be merged with an "alternate plan" from an on-board library. The plan revision action is chosen to maximize the expected utility of the plan. Plan merging and action deletion constitute a more conservative general-purpose planning system; in return, our approach is more efficient and more easily verified, two important criteria for deployed rovers.

Satellite Re-entry Modeling and Uncertainty Quantification

NASA Astrophysics Data System (ADS)

Horsley, M.

2012-09-01

LEO trajectory modeling is a fundamental aerospace capability and has applications in many areas of aerospace, such as maneuver planning, sensor scheduling, re-entry prediction, collision avoidance, risk analysis, and formation flying. Somewhat surprisingly, modeling the trajectory of an object in low Earth orbit is still a challenging task. This is primarily due to the large uncertainty in the upper atmospheric density, about 15-20% (1-sigma) for most thermosphere models. Other contributions come from our inability to precisely model future solar and geomagnetic activities, the potentially unknown shape, material construction and attitude history of the satellite, and intermittent, noisy tracking data. Current methods to predict a satellite's re-entry trajectory typically involve making a single prediction, with the uncertainty dealt with in an ad-hoc manner, usually based on past experience. However, due to the extreme speed of a LEO satellite, even small uncertainties in the re-entry time translate into a very large uncertainty in the location of the re-entry event. Currently, most methods simply update the re-entry estimate on a regular basis. This results in a wide range of estimates that are literally spread over the entire globe. With no understanding of the underlying distribution of potential impact points, the sequence of impact points predicted by the current methodology are largely useless until just a few hours before re-entry. This paper will discuss the development of a set of the High Performance Computing (HPC)-based capabilities to support near real-time quantification of the uncertainty inherent in uncontrolled satellite re-entries. An appropriate management of the uncertainties is essential for a rigorous treatment of the re-entry/LEO trajectory problem. The development of HPC-based tools for re-entry analysis is important as it will allow a rigorous and robust approach to risk assessment by decision makers in an operational setting. Uncertainty

Stability and Change in the Cognitive and Adaptive Behaviour Scores of Preschoolers with Autism Spectrum Disorder

ERIC Educational Resources Information Center

Flanagan, Helen E.; Smith, Isabel M.; Vaillancourt, Tracy; Duku, Eric; Szatmari, Peter; Bryson, Susan; Fombonne, Eric; Mirenda, Pat; Roberts, Wendy; Volden, Joanne; Waddell, Charlotte; Zwaigenbaum, Lonnie; Bennett, Teresa; Elsabbagh, Mayada; Georgiades, Stelios

2015-01-01

We examined the stability of cognitive and adaptive behaviour standard scores in children with autism spectrum disorder (ASD) between diagnosis and school entry approximately age 6. IQ increased 18 points in 2-year-olds, 12 points in 3-year-olds, and 9 points in 4-year-olds (N = 281). Adaptive behaviour scores increased 4 points across age groups…

Cigarette smoking and military deployment: a prospective evaluation.

PubMed

Smith, Besa; Ryan, Margaret A K; Wingard, Deborah L; Patterson, Thomas L; Slymen, Donald J; Macera, Caroline A

2008-12-01

The stress of military deployment may compound occupational stress experienced in the military and manifest in maladaptive coping behaviors such as cigarette smoking. The current study describes new smoking among never-smokers, smoking recidivism among past smokers, and change in daily smoking among smokers in relation to military deployment. The Millennium Cohort is a 21-year longitudinal study. The current analysis utilized participants (N=48,304) who submitted baseline data (July 2001-June 2003) before the current conflicts in Iraq and Afghanistan and follow-up data (June 2004-January 2006) on health measures. New smoking was identified among baseline never-smokers, smoking recidivism among baseline past smokers, and increased or decreased daily smoking among baseline smokers. Analyses were conducted March 2007-April 2007. Among never-smokers, smoking initiation was identified in 1.3% of nondeployers and 2.3% of deployers. Among past smokers, smoking resumption occurred in 28.7% of nondeployers and 39.4% of those who deployed. Smoking increased 44% among nondeployers and 57% among deployers. Those who deployed and reported combat exposures were at 1.6 times greater odds of initiating smoking among baseline never-smokers (95% CI=1.2, 2.3) and at 1.3 times greater odds of resuming smoking among baseline past smokers when compared to those who did not report combat exposures. Other deployment factors independently associated with postdeployment smoking recidivism included deploying for >9 months and deploying multiple times. Among those who smoked at baseline, deployment was not associated with changes in daily amount smoked. Military deployment is associated with smoking initiation and, more strongly, with smoking recidivism, particularly among those with prolonged deployments, multiple deployments, or combat exposures. Prevention programs should focus on the prevention of smoking relapse during or after deployment.

Commercial vehicle information systems and networks (CVISN) deployment program : benefits of CVISN level 1 deployment

DOT National Transportation Integrated Search

2001-09-05

In Transportation Equity Act for the 21st Century (TEA-21), Congress established a goal to complete Commercial Vehicle Information Systems and Networks (CVISN) deployment in a majority of states by September 30, 2003. Through the CVISN Deployment Pro...

Deployment-related mental disorders among Canadian Forces personnel deployed in support of the mission in Afghanistan, 2001–2008

PubMed Central

Boulos, David; Zamorski, Mark A.

2013-01-01

Background: The conflict in Afghanistan has exposed more Canadian Forces personnel to a greater degree of adversity than at any time in recent memory. We determined the incidence of Afghanistan deployment–related mental disorders and associated risk factors among personnel previously deployed in support of this mission. Methods: The study population consisted of 30 513 Canadian Forces personnel who began a deployment in support of the mission in Afghanistan before Jan. 1, 2009. The primary outcome was a mental disorder perceived by a Canadian Forces clinician to be related to the Afghanistan deployment. Data on diagnoses and perceptions were abstracted from medical records of a stratified random sample of 2014 personnel. Sample design weights were used in all analyses to generate descriptive statistics for the entire study population. Results: Over a median follow-up of 1364 days, 13.5% (95% confidence interval [CI] 12.1%–14.8%) of the study population had a mental disorder that was attributed to the Afghanistan deployment. Posttraumatic stress disorder was the most common diagnosis (in 8.0%, 95% CI 7.0%–9.0%, of personnel). Deployment to higher-threat locations, service in the Canadian Army and lower rank were independent risk factors associated with an Afghanistan-related diagnosis (e.g., hazard ratio for deployment to Kandahar Province 5.6, 95% CI 2.6–12.5, relative to deployment to the United Arab Emirates). In contrast, sex, Reserve Forces status, multiple deployments and deployment length were not independent risk factors. Interpretation: An important minority of Canadian Forces personnel deployed in support of the Afghanistan mission had a diagnosis of a mental disorder perceived to be related to the deployment. Determining long-term outcomes is an important next step. PMID:23820441

Self-deploying photovoltaic power system

NASA Technical Reports Server (NTRS)

Colozza, Anthony J. (Inventor)

1993-01-01

A lightweight flexible photovoltaic (PV) blanket is attached to a support structure of initially stowed telescoping members. The deployment mechanism comprises a series of extendable and rotatable columns. As these columns are extended the PV blanket is deployed to its proper configuration.

Rapidly Deployed Modular Telemetry System

NASA Technical Reports Server (NTRS)

Varnavas, Kosta A. (Inventor); Sims, William Herbert, III (Inventor)

2013-01-01

The present invention is a telemetry system, and more specifically is a rapidly deployed modular telemetry apparatus which utilizes of SDR technology and the FPGA programming capability to reduce the number of hardware components and programming required to deploy a telemetry system.

Hybrid Deployable Foam Antennas and Reflectors

NASA Technical Reports Server (NTRS)

Rivellini, Tommaso; Willis, Paul; Hodges, Richard; Spitz, Suzanne

2006-01-01

Hybrid deployable radio antennas and reflectors of a proposed type would feature rigid narrower apertures plus wider adjoining apertures comprising reflective surfaces supported by open-cell polymeric foam structures (see figure). The open-cell foam structure of such an antenna would be compressed for compact stowage during transport. To initiate deployment of the antenna, the foam structure would simply be released from its stowage mechanical restraint. The elasticity of the foam would drive the expansion of the foam structure to its full size and shape. There are several alternatives for fabricating a reflective surface supported by a polymeric foam structure. One approach would be to coat the foam with a metal. Another approach would be to attach a metal film or a metal-coated polymeric membrane to the foam. Yet another approach would be to attach a metal mesh to the foam. The hybrid antenna design and deployment concept as proposed offers significant advantages over other concepts for deployable antennas: 1) In the unlikely event of failure to deploy, the rigid narrow portion of the antenna would still function, providing a minimum level of assured performance. In contrast, most other concepts for deploying a large antenna from compact stowage are of an "all or nothing" nature: the antenna is not useful at all until and unless it is fully deployed. 2) Stowage and deployment would not depend on complex mechanisms or actuators, nor would it involve the use of inflatable structures. Therefore, relative to antennas deployed by use of mechanisms, actuators, or inflation systems, this antenna could be lighter, cheaper, amenable to stowage in a smaller volume, and more reliable. An open-cell polymeric (e.g., polyurethane) foam offers several advantages for use as a compressible/expandable structural material to support a large antenna or reflector aperture. A few of these advantages are the following: 3) The open cellular structure is amenable to compression to a very

Adapting an existing visualization application for browser-based deployment: A case study from the Tropical Rainfall Measuring Mission

NASA Astrophysics Data System (ADS)

Kelley, Owen A.

2013-02-01

THOR, the Tool for High-resolution Observation Review, is a data viewer for the Tropical Rainfall Measuring Mission (TRMM) and the upcoming Global Precipitation Measurement (GPM) mission. THOR began as a desktop application, but now it can be accessed with a web browser, making THOR one of the first online tools for visualizing TRMM satellite data (http://pps.gsfc.nasa.gov/thor). In this effort, the reuse of the existing visualization code was maximized and the complexity of new code was minimized by avoiding unnecessary functionality, frameworks, or libraries. The simplicity of this approach makes it potentially attractive to researchers wishing to adapt their visualization applications for online deployment. To enable THOR to run within a web browser, three new pieces of code are written. First, the graphical user interface (GUI) of the desktop application is translated into HTML, JavaScript, and CSS. Second, a simple communication mechanism is developed over HTTP. Third, a virtual GUI is created on the server that interfaces with the image-generating routines of the existing desktop application so that these routines do not need to be modified for online use. While the basic functionality of THOR is now available online, prototyping is ongoing for enhanced 3D imaging and other aspects of both THOR Desktop and THOR Online. Because TRMM data products are complex and periodically reprocessed with improved algorithms, having a tool such as THOR is important to analysts at the Precipitation Processing System where the algorithms are tested and the products generated, stored, and distributed. Researchers also have found THOR useful for taking a first look at individual files before writing their own software to perform specialized calculations and analyses.

Connected Vehicle Pilot Deployment Program phase 1 : deployment readiness summary : New York City : final report.

DOT National Transportation Integrated Search

2016-09-09

This document describes the Deployment Readiness Summary for the New York City (NYC) Connected Vehicle Pilot Deployment (CVPD) Project. It demonstrates the completion of Task 1-12 deliverables of Phase 1 by the NYC team. The document also addresses h...

Passive Earth Entry Vehicle Landing Test

NASA Technical Reports Server (NTRS)

Kellas, Sotiris

2017-01-01

Two full-scale passive Earth Entry Vehicles (EEV) with realistic structure, surrogate sample container, and surrogate Thermal Protection System (TPS) were built at NASA Langley Research Center (LaRC) and tested at the Utah Test and Training Range (UTTR). The main test objective was to demonstrate structural integrity and investigate possible impact response deviations of the realistic vehicle as compared to rigid penetrometer responses. With the exception of the surrogate TPS and minor structural differences in the back shell construction, the two test vehicles were identical in geometry and both utilized the Integrated Composite Stiffener Structure (ICoSS) structural concept in the forward shell. The ICoSS concept is a lightweight and highly adaptable composite concept developed at NASA LaRC specifically for entry vehicle TPS carrier structures. The instrumented test vehicles were released from a helicopter approximately 400 m above ground. The drop height was selected such that at least 98% of the vehicles terminal velocity would be achieved. While drop tests of spherical penetrometers and a low fidelity aerodynamic EEV model were conducted at UTTR in 1998 and 2000, this was the first time a passive EEV with flight-like structure, surrogate TPS, and sample container was tested at UTTR for the purpose of complete structural system validation. Test results showed that at a landing vertical speed of approximately 30 m/s, the test vehicle maintained structural integrity and enough rigidity to penetrate the sandy clay surface thus attenuating the landing load, as measured at the vehicle CG, to less than 600 g. This measured deceleration was found to be in family with rigid penetrometer test data from the 1998 and 2000 test campaigns. Design implications of vehicle structure/soil interaction with respect to sample container and sample survivability are briefly discussed.

Ebola virus host cell entry.

PubMed

Sakurai, Yasuteru

2015-01-01

Ebola virus is an enveloped virus with filamentous structure and causes a severe hemorrhagic fever in human and nonhuman primates. Host cell entry is the first essential step in the viral life cycle, which has been extensively studied as one of the therapeutic targets. A virus factor of cell entry is a surface glycoprotein (GP), which is an only essential viral protein in the step, as well as the unique particle structure. The virus also interacts with a lot of host factors to successfully enter host cells. Ebola virus at first binds to cell surface proteins and internalizes into cells, followed by trafficking through endosomal vesicles to intracellular acidic compartments. There, host proteases process GPs, which can interact with an intracellular receptor. Then, under an appropriate circumstance, viral and endosomal membranes are fused, which is enhanced by major structural changes of GPs, to complete host cell entry. Recently the basic research of Ebola virus infection mechanism has markedly progressed, largely contributed by identification of host factors and detailed structural analyses of GPs. This article highlights the mechanism of Ebola virus host cell entry, including recent findings.

Deployable Debris Shields For Space Station

NASA Technical Reports Server (NTRS)

Christiansen, Eric L.; Cour-Palais, Burton G.; Crews, Jeanne

1993-01-01

Multilayer shields made of lightweight sheet materials deployed from proposed Space Station Freedom for additional protection against orbiting debris. Deployment mechanism attached at each location on exterior where extra protection needed. Equipment withdraws layer of material from storage in manner similar to unfurling sail or extending window shade. Number of layers deployed depends on required degree of protection, and could be as large as five.

Accommodating Thickness in Origami-Based Deployable Arrays

NASA Technical Reports Server (NTRS)

Zirbel, Shannon A.; Magleby, Spencer P.; Howell, Larry L.; Lang, Robert J.; Thomson, Mark W.; Sigel, Deborah A.; Walkemeyer, Phillip E.; Trease, Brian P.

2013-01-01

The purpose of this work is to create deployment systems with a large ratio of stowed-to-deployed diameter. Deployment from a compact form to a final flat state can be achieved through origami-inspired folding of panels. There are many models capable of this motion when folded in a material with negligible thickness; however, when the application requires the folding of thick, rigid panels, attention must be paid to the effect of material thickness not only on the final folded state, but also during the folding motion (i.e., the panels must not be required to flex to attain the final folded form). The objective is to develop new methods for deployment from a compact folded form to a large circular array (or other final form). This paper describes a mathematical model for modifying the pattern to accommodate material thickness in the context of the design, modeling, and testing of a deployable system inspired by an origami six-sided flasher model. The model is demonstrated in hardware as a 1/20th scale prototype of a deployable solar array for space applications. The resulting prototype has a ratio of stowed-to-deployed diameter of 9.2 (or 1.25 m deployed outer diameter to 0.136 m stowed outer diameter).

Mid-L/D Lifting Body Entry Demise Analysis

NASA Technical Reports Server (NTRS)

Ling, Lisa

2017-01-01

The mid-lift-to-drag ratio (mid-L/D) lifting body is a fully autonomous spacecraft under design at NASA for enabling a rapid return of scientific payloads from the International Space Station (ISS). For contingency planning and risk assessment for the Earth-return trajectory, an entry demise analysis was performed to examine three potential failure scenarios: (1) nominal entry interface conditions with loss of control, (2) controlled entry at maximum flight path angle, and (3) controlled entry at minimum flight path angle. The objectives of the analysis were to predict the spacecraft breakup sequence and timeline, determine debris survival, and calculate the debris dispersion footprint. Sensitivity analysis was also performed to determine the effect of the initial pitch rate on the spacecraft stability and breakup during the entry. This report describes the mid-L/D lifting body and presents the results of the entry demise and sensitivity analyses.

Omaha Metropolitan Area, ITS Early Deployment Planning Study, Strategic Deployment Plan, Appendices E: Deployment Scenarios, F: Project Descriptions, G: Support Technologies, H: Cost Estimate Assumptions

DOT National Transportation Integrated Search

1995-12-15

THE OBJECTIVE OF THE OMAHA INTELLIGENT TRANSPORTATION (ITS) EARLY DEPLOYMENT STUDY IS TO DEVELOP A STRATEGIC PLAN FOR THE DEPLOYMENT OF ITS TECHNOLOGIES IN THE OMAHA METROPOLITAN AREA. THE PLAN WILL IDENTIFY THE ITS USER SERVICES THAT WILL BE MOST BE...

Supporting Knowledge Transfer in IS Deployment Projects

NASA Astrophysics Data System (ADS)

Schönström, Mikael

To deploy new information systems is an expensive and complex task, and does seldom result in successful usage where the system adds strategic value to the firm (e.g. Sharma et al. 2003). It has been argued that innovation diffusion is a knowledge integration problem (Newell et al. 2000). Knowledge about business processes, deployment processes, information systems and technology are needed in a large-scale deployment of a corporate IS. These deployments can therefore to a large extent be argued to be a knowledge management (KM) problem. An effective deployment requires that knowledge about the system is effectively transferred to the target organization (Ko et al. 2005).

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.

Pay attention to reflux/feed entry design

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

Fleming, B.; Martin, G.R.; Hartman, E.L.

1996-01-01

Trays generally are forgiving pieces of equipment and can conceal the effects of poorly designed feed and reflux entries. When one tries to push a tower to its hydraulic limit, however, poor entry design can penalize the performance of the trays and result in a lower final capacity. Normally, new towers are not as susceptible to entry design problems as ones being revamped. This is because new towers usually have some degree of capacity oversizing.Standard design practices used for new columns having spare capacity, though, may not be suitable for revamped towers. In this article, the authors detail the basicmore » principles of reflux and feed entry design, good practices to follow, and poor practices to avoid. They also include a case study of a large-diameter light hydrocarbon splitter revamped with high capacity trays to illustrate the potential pitfalls associated with incorrectly designed reflux and feed entry arrangements.« less

New Graduate Entry: Students' Transition to an Adapted Physical Education Graduate Program

ERIC Educational Resources Information Center

Sato, Takahiro; Samalot-Rivera, Amaury; Kozub, Francis M.

2016-01-01

The purpose of this study was to describe and explain master of arts students' academic and social experiences during the transition to an adapted physical education (APE) graduate program. In this study, we used the theory of transition, which allowed us to understand students' transition to graduate studies and to assist them in connecting to…

Preentry communications study. Outer planets atmospheric entry probe

NASA Technical Reports Server (NTRS)

Hinrichs, C. A.

1976-01-01

A pre-entry communications study is presented for a relay link between a Jupiter entry probe and a spacecraft in hyperbolic orbit. Two generic communications links of interest are described: a pre-entry link to a spun spacecraft antenna, and a pre-entry link to a despun spacecraft antenna. The propagation environment of Jupiter is defined. Although this is one of the least well known features of Jupiter, enough information exists to reasonably establish bounds on the performance of a communications link. Within these bounds, optimal carrier frequencies are defined. The next step is to identify optimal relative geometries between the probe and the spacecraft. Optimal trajectories are established for both spun and despun spacecraft antennas. Given the optimal carrier frequencies, and the optimal trajectories, the data carrying capacities of the pre-entry links are defined. The impact of incorporating pre-entry communications into a basic post entry probe is then assessed. This assessment covers the disciplines of thermal control, power source, mass properties and design layout. A conceptual design is developed of an electronically despun antenna for use on a Pioneer class of spacecraft.

19 CFR 10.31 - Entry; bond.

Code of Federal Regulations, 2011 CFR

2011-04-01

... for sound or television broadcasting, cinematographic equipment, articles imported for sports purposes... ARTICLES CONDITIONALLY FREE, SUBJECT TO A REDUCED RATE, ETC. General Provisions Temporary Importations Under Bond § 10.31 Entry; bond. (a)(1) Entry of articles brought into the United States temporarily and...

Apollo experience report: Mission planning for Apollo entry

NASA Technical Reports Server (NTRS)

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

1972-01-01

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

Users speak out on technology deployment

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

Peters, Mark; Prochaska, Marty; Cromer, Paul

2001-02-25

This report summarizes user feedback data collected during a recent Accelerated Site Technology Deployment (ASTD) project: the Fluor Fernald ASTD Technology Deployment Project from May, 1999 through September, 2000. The main goal of the ASTD project was to use the ''Fernald approach'' to expedite the deployment of new or innovative technologies with superior safety, cost, and/or productivity benefits to Department of Energy (DOE) facilities. The Fernald approach targets technology end-users and their managers and directly involves them with hands-on demonstrations of new or innovative technologies during technology transfer sessions. The two technologies deployed through this project were the Personal Icemore » Cooling System (PICS) and the oxy-gasoline torch. Participants of technology transfer sessions were requested to complete feedback surveys. Surveys evaluated the effectiveness of the Fernald approach to technology deployment and assessed the responsiveness of employees to new technologies. This report presents the results of those surveys.« less

Deployer Performance Results for the TSS-1 Mission

NASA Technical Reports Server (NTRS)

Marshall, Leland S.; Geiger, Ronald V.

1995-01-01

Performance of the Tethered Satellite System (TSS) Deployer during the STS-46 mission (July and August 1992) is analyzed in terms of hardware operation at the component and system level. Although only a limited deployment of the satellite was achieved (256 meters vs 20 kilometers planned), the mission served to verify the basic capability of the Deployer to release, control and retrieve a tethered satellite. - Deployer operational flexibility that was demonstrated during the flight is also addressed. Martin Marietta was the prime contractor for the development of the Deployer, under management of the NASA George C. Marshall Space Flight Center (MSFC). The satellite was provided by Alenia, Torino, Italy under contract to the Agencia Spaziale Italiana (ASI). Proper operation of the avionics components and the majority of mechanisms was observed during the flight. System operations driven by control laws for the deployment and retrieval of the satellite were also successful for the limited deployment distance. Anomalies included separation problems for one of the two umbilical connectors between the Deployer and satellite, tether jamming (at initial Satellite fly-away and at a deployment distance of 224 meters), and a mechanical interference which prevented tether deployment beyond 256 meters. The Deployer was used in several off-nominal conditions to respond to these anomalies, which ultimately enabled a successful satellite retrieval and preservation of hardware integrity for a future re-flight. The paper begins with an introduction defining the significance of the TSS-1 mission. The body of the paper is divided into four major sections: (1) Description of Deployer System and Components, (2) Deployer Components/Systems Demonstrating Successful Operation, (3) Hardware Anomalies and Operational Responses, and (4) Design Modifications for the TSS-1R Re-flight Mission. Conclusions from the TSS-1 mission, including lessons learned are presented at the end of the

Parental Incarceration, Transnational Migration, and Military Deployment: Family Process Mechanisms of Youth Adjustment to Temporary Parent Absence

PubMed Central

Rodriguez, Aubrey J.; Margolin, Gayla

2015-01-01

The temporary absence of a parent (e.g., due to incarceration, migration, or military deployment) is experienced by many youth and can have profound effects. Available research within these disparate literatures primarily has catalogued contextual and individual variables that influence youth adaptation, which are integrated and summarized here. In addition, we present a systematic review of proximal family process mechanisms by which youth and their family members adapt to periods of temporary parent absence. This systematic review across the different types of parent absence produced four themes: communication among family members, parenting characteristics during absence, negotiation of decision-making power and authority, and shifts in family roles. By juxtaposing the three types of temporary parent absence, we aim to bridge the separate research silos of parent absence due to incarceration, deployment, and migration, and to bring wide-ranging characteristics and processes of temporary parent-absent families into sharper focus. The review highlights possibilities for fuller integration of these literatures, and emphasizes the clinical value of considering these types of experiences from a family and relational perspective, rather than an individual coping perspective. PMID:25304163

Generic Entry, Reformulations, and Promotion of SSRIs

PubMed Central

Donohue, Julie M.; Koss, Catherine; Berndt, Ernst R.; Frank, Richard G.

2009-01-01

Background Previous research has shown that a manufacturer’s promotional strategy for a brand-name drug is typically affected by generic entry. However, little is known about how newer strategies to extend patent life, including product reformulation introduction or obtaining approval to market for additional clinical indications, influence promotion. Objective To examine the relationship between promotional expenditures, generic entry, reformulation entry, and new indication approval. Study Design/Setting We used quarterly data on national product-level promotional spending (including expenditures for physician detailing and direct-to-consumer advertising (DTCA), and the retail value of free samples distributed in physician offices) for selective serotonin reuptake inhibitors (SSRIs) over the period 1997 through 2004. We estimated econometric models of detailing, DTCA, and total quarterly promotional expenditures as a function of the timing of generic entry, entry of new product formulations, and Food and Drug Administration (FDA) approval for new clinical indications for existing medications in the SSRI class. Main Outcome Measure Expenditures by pharmaceutical manufacturers for promotion of antidepressant medications. Results Over the period 1997–2004, there was considerable variation in the composition of promotional expenditures across the SSRIs. Promotional expenditures for the original brand molecule decreased dramatically when a reformulation of the molecule was introduced. Promotional spending (both total and detailing alone) for a specific molecule was generally lower after generic entry than before, although the effect of generic entry on promotional spending appears to be closely linked with the choice of product reformulation strategy pursued by the manufacturer. Detailing expenditures for Paxil were increased after the manufacturer received FDA approval to market the drug for generalized anxiety disorder (GAD), while the likelihood of DTCA outlays

9 CFR 93.806 - Animals refused entry.

Code of Federal Regulations, 2014 CFR

2014-01-01

... FOR MEANS OF CONVEYANCE AND SHIPPING CONTAINERS Elephants, Hippopotami, Rhinoceroses, and Tapirs § 93.806 Animals refused entry. Any elephant, hippopotamus, rhinoceros, or tapir refused entry into the...

9 CFR 93.806 - Animals refused entry.

Code of Federal Regulations, 2011 CFR

2011-01-01

... FOR MEANS OF CONVEYANCE AND SHIPPING CONTAINERS Elephants, Hippopotami, Rhinoceroses, and Tapirs § 93.806 Animals refused entry. Any elephant, hippopotamus, rhinoceros, or tapir refused entry into the...

9 CFR 93.806 - Animals refused entry.

Code of Federal Regulations, 2010 CFR

2010-01-01

... FOR MEANS OF CONVEYANCE AND SHIPPING CONTAINERS Elephants, Hippopotami, Rhinoceroses, and Tapirs § 93.806 Animals refused entry. Any elephant, hippopotamus, rhinoceros, or tapir refused entry into the...

9 CFR 93.806 - Animals refused entry.

Code of Federal Regulations, 2013 CFR

2013-01-01

... FOR MEANS OF CONVEYANCE AND SHIPPING CONTAINERS Elephants, Hippopotami, Rhinoceroses, and Tapirs § 93.806 Animals refused entry. Any elephant, hippopotamus, rhinoceros, or tapir refused entry into the...

9 CFR 93.806 - Animals refused entry.

Code of Federal Regulations, 2012 CFR

2012-01-01

... FOR MEANS OF CONVEYANCE AND SHIPPING CONTAINERS Elephants, Hippopotami, Rhinoceroses, and Tapirs § 93.806 Animals refused entry. Any elephant, hippopotamus, rhinoceros, or tapir refused entry into the...

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.

Analytic Development of a Reference Profile for the First Entry in a Skip Atmospheric Entry

NASA Technical Reports Server (NTRS)

Garcia-Llama, Eduardo

2010-01-01

This note shows that a feasible reference drag profile for the first entry portion of a skip entry can be generated as a polynomial expression of the velocity. The coefficients of that polynomial are found through the resolution of a system composed of m + 1 equations, where m is the degree of the drag polynomial. It has been shown that a minimum of five equations (m = 4) are required to establish the range and the initial and final conditions on velocity and flight path angle. It has been shown that at least one constraint on the trajectory can be imposed through the addition of one extra equation in the system, which must be accompanied by the increase in the degree of the drag polynomial. In order to simplify the resolution of the system of equations, the drag was considered as being a probability density function of the velocity, with the velocity as a distribution function of the drag. Combining this notion with the introduction of empirically derived constants, it has been shown that the system of equations required to generate the drag profile can be successfully reduced to a system of linear algebraic equations. For completeness, the resulting drag profiles have been flown using the feedback linearization method of differential geometric control as a guidance law with the error dynamics of a second order homogeneous equation in the form of a damped oscillator. Satisfactory results were achieved when the gains in the error dynamics were changed at a certain point along the trajectory that is dependent on the velocity and the curvature of the drag as a function of the velocity. Future work should study the capacity to update the drag profile in flight when dispersions are introduced. Also, future studies should attempt to link the first entry, as presented and controlled in this note, with a more standard control concept for the second entry, such as the Apollo entry guidance, to try to assess the overall skip entry performance. A guidance law that includes

Physics-Based Modeling of Meteor Entry and Breakup

NASA Technical Reports Server (NTRS)

Prabhu, Dinesh K.; Agrawal, Parul; Allen, Gary A., Jr.; Bauschlicher, Charles W., Jr.; Brandis, Aaron M.; Chen, Yih-Kang; Jaffe, Richard L.; Palmer, Grant E.; Saunders, David A.; Stern, Eric C.;

Physics-Based Modeling of Meteor Entry and Breakup

NASA Technical Reports Server (NTRS)

Prabhu, Dinesh K.; Agrawal, Parul; Allen, Gary A., Jr.; Bauschlicher, Charles W., Jr.; Brandis, Aaron M.; Chen, Yih-Kanq; Jaffe, Richard L.; Palmer, Grant E.; Saunders, David A.; Stern, Eric C.;

A module concept for a cable-mesh deployable antenna

NASA Technical Reports Server (NTRS)

Meguro, Akira

1993-01-01

This paper describes the design, manufacture, and deployment tests of a modular mesh deployable antenna. Reaction forces and moments created by a mesh and cable network are estimated using CASA. Deployment analysis is carried out using DADS. Three types of deployable antenna modules are developed and fabricated. Their design approach and deployment characteristics are also presented. Ground deployment tests are performed to verify design criteria.

19 CFR 141.18 - Entry by nonresident corporation.

Code of Federal Regulations, 2010 CFR

2010-04-01

... 19 Customs Duties 2 2010-04-01 2010-04-01 false Entry by nonresident corporation. 141.18 Section....18 Entry by nonresident corporation. A nonresident corporation (i.e., one which is not incorporated... entry is located who is authorized to accept service of process against that corporation or, in the case...

19 CFR 141.18 - Entry by nonresident corporation.

Code of Federal Regulations, 2011 CFR

2011-04-01

... 19 Customs Duties 2 2011-04-01 2011-04-01 false Entry by nonresident corporation. 141.18 Section....18 Entry by nonresident corporation. A nonresident corporation (i.e., one which is not incorporated... entry is located who is authorized to accept service of process against that corporation or, in the case...

19 CFR 141.18 - Entry by nonresident corporation.

Code of Federal Regulations, 2013 CFR

2013-04-01

... 19 Customs Duties 2 2013-04-01 2013-04-01 false Entry by nonresident corporation. 141.18 Section....18 Entry by nonresident corporation. A nonresident corporation (i.e., one which is not incorporated... entry is located who is authorized to accept service of process against that corporation or, in the case...

19 CFR 141.18 - Entry by nonresident corporation.

Code of Federal Regulations, 2012 CFR

2012-04-01

... 19 Customs Duties 2 2012-04-01 2012-04-01 false Entry by nonresident corporation. 141.18 Section....18 Entry by nonresident corporation. A nonresident corporation (i.e., one which is not incorporated... entry is located who is authorized to accept service of process against that corporation or, in the case...

19 CFR 141.18 - Entry by nonresident corporation.

Code of Federal Regulations, 2014 CFR

2014-04-01

... 19 Customs Duties 2 2014-04-01 2014-04-01 false Entry by nonresident corporation. 141.18 Section....18 Entry by nonresident corporation. A nonresident corporation (i.e., one which is not incorporated... entry is located who is authorized to accept service of process against that corporation or, in the case...

31 CFR 337.6 - Conversions to book-entry.

Code of Federal Regulations, 2014 CFR

2014-07-01

... 31 Money and Finance: Treasury 2 2014-07-01 2014-07-01 false Conversions to book-entry. 337.6... FEDERAL HOUSING ADMINISTRATION DEBENTURES Certificated Debentures § 337.6 Conversions to book-entry. Upon implementation of the book-entry debenture system, to be announced in advance by separate public notice, all new...

31 CFR 337.6 - Conversions to book-entry.

Code of Federal Regulations, 2011 CFR

2011-07-01

... 31 Money and Finance:Treasury 2 2011-07-01 2011-07-01 false Conversions to book-entry. 337.6... HOUSING ADMINISTRATION DEBENTURES Certificated Debentures § 337.6 Conversions to book-entry. Upon implementation of the book-entry debenture system, to be announced in advance by separate public notice, all new...

31 CFR 337.6 - Conversions to book-entry.

Code of Federal Regulations, 2012 CFR

2012-07-01

... 31 Money and Finance:Treasury 2 2012-07-01 2012-07-01 false Conversions to book-entry. 337.6... HOUSING ADMINISTRATION DEBENTURES Certificated Debentures § 337.6 Conversions to book-entry. Upon implementation of the book-entry debenture system, to be announced in advance by separate public notice, all new...

31 CFR 337.6 - Conversions to book-entry.

Code of Federal Regulations, 2013 CFR

2013-07-01

... 31 Money and Finance:Treasury 2 2013-07-01 2013-07-01 false Conversions to book-entry. 337.6... HOUSING ADMINISTRATION DEBENTURES Certificated Debentures § 337.6 Conversions to book-entry. Upon implementation of the book-entry debenture system, to be announced in advance by separate public notice, all new...

31 CFR 337.6 - Conversions to book-entry.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 31 Money and Finance: Treasury 2 2010-07-01 2010-07-01 false Conversions to book-entry. 337.6... HOUSING ADMINISTRATION DEBENTURES Certificated Debentures § 337.6 Conversions to book-entry. Upon implementation of the book-entry debenture system, to be announced in advance by separate public notice, all new...

Six pitfalls in firewall deployment

NASA Astrophysics Data System (ADS)

Wilner, Bruce

1996-03-01

This note describes six key pitfalls in the deployment of popular commercial firewalls. The term `deployment' is intended to include the architecture of the firewall software itself, the integration of the firewall with the operating system platform, and the interconnection of the complete hardware/software combination within its target environment. After reviewing the evolution of Internet firewalls against the backdrop of classical trusted systems development, specific flaws and oversights in the familiar commercial deployments are analyzed in some detail. While significantly costlier solutions are available that address some of these problems, the analysis is applicable to the overwhelming majority of firewalls in use at both commercial and Government installations.

A Deployable Primary Mirror for Space Telescopes

NASA Technical Reports Server (NTRS)

Lake, Mark S.; Phelps, James E.; Dyer, Jack E.; Caudle, David A.; Tam, Anthony; Escobedo, Javier; Kasl, Eldon P.

1999-01-01

NASA Langley Research Center, Composite Optics, Inc., and Nyma/ADF have developed jointly a deployable primary mirror for space telescopes that combines over five years of research on deployment of optical-precision structures and over ten years of development of fabrication techniques for optical-precision composite mirror panels and structures. The deployable mirror is directly applicable to a broad class of non-imaging "lidar" (light direction a nd ranging) telescopes whose figure-error requirements are in the range of one to ten microns RMS. Furthermore, the mirror design can be readily modified to accommodate imaging-quality reflector panels and active panel-alignment control mechanisms for application to imaging telescopes. The present paper: 1) describes the deployable mirror concept; 2) explains the status of the mirror development; and 3) provides some technical specifications for a 2.55- m-diameter, proof-of-concept mirror. Keywords: precision deployment, hinge joint, latch joint, deployable structures, fabrication, space telescopes, optical instruments, microdynamics.

A Comparison of Two Skip Entry Guidance Algorithms

NASA Technical Reports Server (NTRS)

Rea, Jeremy R.; Putnam, Zachary R.

2007-01-01

The Orion capsule vehicle will have a Lift-to-Drag ratio (L/D) of 0.3-0.35. For an Apollo-like direct entry into the Earth's atmosphere from a lunar return trajectory, this L/D will give the vehicle a maximum range of about 2500 nm and a maximum crossrange of 216 nm. In order to y longer ranges, the vehicle lift must be used to loft the trajectory such that the aerodynamic forces are decreased. A Skip-Trajectory results if the vehicle leaves the sensible atmosphere and a second entry occurs downrange of the atmospheric exit point. The Orion capsule is required to have landing site access (either on land or in water) inside the Continental United States (CONUS) for lunar returns anytime during the lunar month. This requirement means the vehicle must be capable of flying ranges of at least 5500 nm. For the L/D of the vehicle, this is only possible with the use of a guided Skip-Trajectory. A skip entry guidance algorithm is necessary to achieve this requirement. Two skip entry guidance algorithms have been developed: the Numerical Skip Entry Guidance (NSEG) algorithm was developed at NASA/JSC and PredGuid was developed at Draper Laboratory. A comparison of these two algorithms will be presented in this paper. Each algorithm has been implemented in a high-fidelity, 6 degree-of-freedom simulation called the Advanced NASA Technology Architecture for Exploration Studies (ANTARES). NASA and Draper engineers have completed several monte carlo analyses in order to compare the performance of each algorithm in various stress states. Each algorithm has been tested for entry-to-target ranges to include direct entries and skip entries of varying length. Dispersions have been included on the initial entry interface state, vehicle mass properties, vehicle aerodynamics, atmosphere, and Reaction Control System (RCS). Performance criteria include miss distance to the target, RCS fuel usage, maximum g-loads and heat rates for the first and second entry, total heat load, and control

30 CFR 75.326 - Mean entry air velocity.

Code of Federal Regulations, 2014 CFR

2014-07-01

... 30 Mineral Resources 1 2014-07-01 2014-07-01 false Mean entry air velocity. 75.326 Section 75.326... MANDATORY SAFETY STANDARDS-UNDERGROUND COAL MINES Ventilation § 75.326 Mean entry air velocity. In exhausting face ventilation systems, the mean entry air velocity shall be at least 60 feet per minute...

30 CFR 75.326 - Mean entry air velocity.

Code of Federal Regulations, 2012 CFR

2012-07-01

... 30 Mineral Resources 1 2012-07-01 2012-07-01 false Mean entry air velocity. 75.326 Section 75.326... MANDATORY SAFETY STANDARDS-UNDERGROUND COAL MINES Ventilation § 75.326 Mean entry air velocity. In exhausting face ventilation systems, the mean entry air velocity shall be at least 60 feet per minute...

GPM Solar Array Gravity Negated Deployment Testing

NASA Technical Reports Server (NTRS)

Penn, Jonathan; Johnson, Chris; Lewis, Jesse; Dear, Trevin; Stewart, Alphonso

2014-01-01

NASA Goddard Space Flight Center (GSFC) successfully developed a g-negation support system for use on the solar arrays of the Global Precipitation Measurement (GPM) Satellite. This system provides full deployment capability at the subsystem and observatory levels. In addition, the system provides capability for deployed configuration first mode frequency verification testing. The system consists of air pads, a support structure, an air supply, and support tables. The g-negation support system was used to support all deployment activities for flight solar array deployment testing.

Valine entry into rat brain after diet-induced changes in plasma amino acids

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

Tews, J.K.; Greenwood, J.; Pratt, O.E.

1987-01-01

Passage of amino acids across the blood-brain barrier is assumed to be modified by amino acid composition of the blood. To gain a better understanding of the effects of protein intake on brain amino acid uptake, the authors examined associations among diet, plasma amino acid patterns, and the rate of entry of valine into the brain. Rats were fed diets containing 6, 18, or 50% casein before receiving one meal of a diet containing 0, 6, 18, or 50% casein. After 4-7 h, they were anesthetized and infused intravenously with (/sup 14/C)valine for 5 min before plasma and brain samplesmore » were taken for determination of radioactivity and content of individual amino acids. As protein content of the meal was increased from 0 to 50% casein, plasma and brain concentrations of valine and most other large neutral amino acid (LNAA) increased severalfold; also the ratio of (/sup 14/C)valine in brain to that in plasma decreased by >50%, and the rate of valine entry into the brain increased 3.5-fold. The increase in valine flux slowed as plasma levels of LNAA, competitors for valine transport, increased. The results were far more dependent on protein content of the final meal than on that of the adaptation diet; thus changes in protein intake, as reflected in altered plasma amino acid patterns, markedly altered valine entry into the brain.« less

32 CFR 763.5 - Entry procedures.

Code of Federal Regulations, 2010 CFR

2010-07-01

... GOVERNING PUBLIC ACCESS Entry Regulations for Kaho'olawe Island, Hawaii § 763.5 Entry procedures. (a) It is... Harbor, Hawaii 96860, at least 15 days prior to the access requested, providing therein confirmed access... proscribed by either Federal law or the State of Hawaii Penal Code, as incorporated under the Federal...

Small expendable deployer system measurement analysis

NASA Technical Reports Server (NTRS)

Carrington, Connie K.

1988-01-01

The first on-orbit experiment of the Small Expendable Deployer System (SEDS) for tethered satellites will collect telemetry data for tether length, rate of deployment, and tether tension. The post-flight analysis will use this data to reconstruct the deployment history and determine dynamic characteristics such as tether shape and payload position. Linearized observability analysis has determined that these measurements are adequate to define states for a two-mass tether model, and two state estimators were written.

DESIGN: a program to create data entry programs

Treesearch

J. Michael Wuerth; David R. Weise

1994-01-01

Scientific data entry can be an exacting process. The specific information needs change from investigation to investigation. A computer program to design custom data screens is described. The program, DESIGN, generates the necessary C programming language source code to create a basic data entry program. Data entry screens can contain multiple nested screens. Users can...

1994 Entry-Level Athletic Training Salaries

PubMed Central

Moss, Crayton L.

1996-01-01

In this study, I examined salaries for entry-level positions in athletic training during the year 1994. An entry-level position was defined as a position to be filled with an athletic trainer certified by the NATA, with no full-time paid employment experience. According to the “Placement Vacancy Notice” (NATA, Dallas, TX) and “BYLINE” (Athletic Trainer Services, Inc, Mt Pleasant, MI), there were 432 entry-level vacancies in hospital/clinics, college/universities, and high school settings. A total of 271 surveys (63%) were returned. Overall, beginning salaries for entry-level athletic training positions were $23,228 (±$3,177) for a bachelor's degree and $25,362 (±$3,883) for a master's degree. A stipend ($4,216 ± $2,039) was included in 86% of the high school positions. The term of contract for high school was usually a 10-month position (10.0 ± .9 months), hospital/clinic, 12-months (11.7 ± .7 months), while the college/university varied from 9 to 12 months (10.5 ± 1.2 months). Also included in the study was fringe benefit information: pension (other than Social Security), life, medical, dental, and vision insurance. Continued studies are recommended to establish salary norms and trends for entry-level positions so that athletic trainers will understand what monetary compensation to expect for their services. PMID:16558367

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 deploy) to its original size and shape. Once thus deployed, the CHEM structure can be rigidified by cooling below Tg to the glassy state. The structure could be subsequently reheated above Tg and recompacted. The compaction/deployment/rigidification cycle could be repeated as many times as needed.

Methods and Apparatus for Deployable Swirl Vanes

NASA Technical Reports Server (NTRS)

Shah, Parthiv N. (Inventor)

2017-01-01

An aircraft control structure for drag management includes a nozzle structure configured to exhaust a swirling fluid stream. A plurality of swirl vanes are positioned within the nozzle structure, and an actuation subsystem is configured to cause the plurality of swirl vanes to move from a deployed state to a non-deployed state. In the non-deployed state, the plurality of swirl vanes are substantially flush with the inner surface of the nozzle structure. In the deployed state, the plurality of swirl vanes produce the swirling fluid stream.

46 CFR 147A.25 - Entry.

Code of Federal Regulations, 2012 CFR

2012-10-01

... 46 Shipping 5 2012-10-01 2012-10-01 false Entry. 147A.25 Section 147A.25 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) DANGEROUS CARGOES INTERIM REGULATIONS FOR SHIPBOARD FUMIGATION During Fumigation § 147A.25 Entry. (a) No person may enter the spaces that immediately adjoin the space...

46 CFR 147A.25 - Entry.

Code of Federal Regulations, 2013 CFR

2013-10-01

... 46 Shipping 5 2013-10-01 2013-10-01 false Entry. 147A.25 Section 147A.25 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) DANGEROUS CARGOES INTERIM REGULATIONS FOR SHIPBOARD FUMIGATION During Fumigation § 147A.25 Entry. (a) No person may enter the spaces that immediately adjoin the space...

46 CFR 147A.25 - Entry.

Code of Federal Regulations, 2014 CFR

2014-10-01

... 46 Shipping 5 2014-10-01 2014-10-01 false Entry. 147A.25 Section 147A.25 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) DANGEROUS CARGOES INTERIM REGULATIONS FOR SHIPBOARD FUMIGATION During Fumigation § 147A.25 Entry. (a) No person may enter the spaces that immediately adjoin the space...

Re-Entry: Managing Cross-Cultural Transitions.

ERIC Educational Resources Information Center

Adler, Nancy J.

1981-01-01

Studied the re-entry process of corporate and governmental employees (N=200) returning to Canada after working overseas. Research found re-entry into the original culture was a more difficult transition than moving to the foreign culture. Home-country managers tended to exhibit xenophobia in assessing the potential and actual effectiveness of…

46 CFR 147A.25 - Entry.

Code of Federal Regulations, 2010 CFR

2010-10-01

... During Fumigation § 147A.25 Entry. (a) No person may enter the spaces that immediately adjoin the space that is fumigated during fumigation unless entry is for emergency purposes or the space is tested and declared safe for human occupancy by a marine chemist or other qualified person and is inspected under...

46 CFR 147A.25 - Entry.

Code of Federal Regulations, 2011 CFR

2011-10-01

... During Fumigation § 147A.25 Entry. (a) No person may enter the spaces that immediately adjoin the space that is fumigated during fumigation unless entry is for emergency purposes or the space is tested and declared safe for human occupancy by a marine chemist or other qualified person and is inspected under...

Rover deployment system for lunar landing mission

NASA Astrophysics Data System (ADS)

Sutoh, Masataku; Hoshino, Takeshi; Wakabayashi, Sachiko

2017-09-01

For lunar surface exploration, a deployment system is necessary to allow a rover to leave the lander. The system should be as lightweight as possible and stored retracted when launched. In this paper, two types of retractable deployment systems for lunar landing missions, telescopic- and fold-type ramps, are discussed. In the telescopic-type system, a ramp is stored with the sections overlapping and slides out during deployment. In the fold-type system, it is stored folded and unfolds for the deployment. For the development of these ramps, a design concept study and structural analysis were conducted first. Subsequently, ramp deployment and rover release tests were performed using the developed ramp prototypes. Through these tests, the validity of their design concepts and functions have been confirmed. In the rover release test, it was observed that the developed lightweight ramp was sufficiently strong for a 50-kg rover to descend. This result suggests that this ramp system is suitable for the deployment of a 300-kg-class rover on the Moon, where the gravity is about one-sixth that on Earth. The lightweight and sturdy ramp developed in this study will contribute to both safe rover deployment and increase of lander/rover payload.

Adjustable Bracket For Entry Of Welding Wire

NASA Technical Reports Server (NTRS)

Gilbert, Jeffrey L.; Gutow, David A.

1993-01-01

Wire-entry bracket on welding torch in robotic welding system provides for adjustment of angle of entry of welding wire over range of plus or minus 30 degrees from nominal entry angle. Wire positioned so it does not hide weld joint in view of through-the-torch computer-vision system part of robot-controlling and -monitoring system. Swiveling bracket also used on nonvision torch on which wire-feed-through tube interferes with workpiece. Angle simply changed to one giving sufficient clearance.

19 CFR 142.3a - Entry numbers.

Code of Federal Regulations, 2013 CFR

2013-04-01

...) Format. The following format, including hyphens, must be used when showing the entry number: XXX-NNNNNNN-N XXX represents an entry filer code assigned by CBP, NNNNNNN is a unique number which is assigned...

19 CFR 142.3a - Entry numbers.

Code of Federal Regulations, 2014 CFR

2014-04-01

...) Format. The following format, including hyphens, must be used when showing the entry number: XXX-NNNNNNN-N XXX represents an entry filer code assigned by CBP, NNNNNNN is a unique number which is assigned...

19 CFR 142.3a - Entry numbers.

Code of Federal Regulations, 2011 CFR

2011-04-01

...) Format. The following format, including hyphens, must be used when showing the entry number: XXX-NNNNNNN-N XXX represents an entry filer code assigned by CBP, NNNNNNN is a unique number which is assigned...

19 CFR 142.3a - Entry numbers.

Code of Federal Regulations, 2012 CFR

2012-04-01

...) Format. The following format, including hyphens, must be used when showing the entry number: XXX-NNNNNNN-N XXX represents an entry filer code assigned by CBP, NNNNNNN is a unique number which is assigned...

19 CFR 142.3a - Entry numbers.

Code of Federal Regulations, 2010 CFR

2010-04-01

...) Format. The following format, including hyphens, must be used when showing the entry number: XXX-NNNNNNN-N XXX represents an entry filer code assigned by CBP, NNNNNNN is a unique number which is assigned...

Gerst depressurized Kibo for Cubesat deployment

NASA Image and Video Library

2014-08-18

ISS040-E-096126 (18 Aug. 2014) --- In the International Space Station?s Kibo laboratory, European Space Agency astronaut Alexander Gerst, Expedition 40 flight engineer, depressurizes the Kibo airlock in preparation for a series of NanoRacks CubeSat miniature satellite deployments. The first two pairs of nanosatellites are scheduled for deployment on Aug. 19. The Planet Labs Dove satellites that were carried to the station aboard the Orbital Sciences Cygnus commercial cargo craft are being deployed between Aug. 19 and Aug. 25.

Gerst depressurized Kibo for Cubesat deployment

NASA Image and Video Library

2014-08-18

ISS040-E-096122 (18 Aug. 2014) --- In the International Space Station?s Kibo laboratory, European Space Agency astronaut Alexander Gerst, Expedition 40 flight engineer, depressurizes the Kibo airlock in preparation for a series of NanoRacks CubeSat miniature satellite deployments. The first two pairs of nanosatellites are scheduled for deployment on Aug. 19. The Planet Labs Dove satellites that were carried to the station aboard the Orbital Sciences Cygnus commercial cargo craft are being deployed between Aug. 19 and Aug. 25.

Injuries before and after deployments to Afghanistan and Iraq.

PubMed

Knapik, J J; Spiess, A; Grier, T; Sharp, M A; Lester, M E; Marin, R; Jones, B H

2012-06-01

To examine outpatient injuries before and after deployments of elements of the 10th Mountain Division to Afghanistan (n = 505 men) and the 1st Cavalry Division to Iraq (n = 3242 men). Observational. The military units provided a list of deployed soldiers, and soldiers' outpatient medical encounters were obtained from the Defense Medical Surveillance System. Cumulative injury incidence was examined for two consecutive 90-day periods before the deployments (Periods 1-2) and two consecutive 90-day periods after the deployments (Periods 3-4). Both groups showed post-deployment increases in the overall incidence of injury (Afghanistan group = 14.1%, 14.1%, 16.4, 23.4%; Iraq Group = 15.1%, 12.4%, 35.4%, 43.4%; Periods 1-4, respectively). Soldiers with pre-deployment injuries were 1.4-3.0 times more likely to experience post-deployment injuries. This study found a post-deployment increase in the incidence of outpatient injury. Also, soldiers with pre-deployment injuries were more likely to experience post-deployment injuries. Published by Elsevier Ltd.

Overview of entry risk predictions

NASA Astrophysics Data System (ADS)

Mrozinski, R.; Mendeck, G.; Cutri-Kohart, R.

Risk to people on the ground from uncontrolled entries of spacecraft is a primary concern when analyzing end-of-life disposal options for satellites. Countries must balance this risk with the need to mitigate an exponentially growing space debris population. Currently the United States does this via guidelines that call for a satellite to be disposed of in a controlled manner if an uncontrolled entry would be too risky to people on the ground. This risk is measured by a quantity called "casualty expectation", or E , where casualty expectation is defined as the expectedc number of people suffering death or injury due to a spacecraft entry event. If Ec exceeds 1 in 10,000, U. S. guidelines state that the entry should be controlled rather than uncontrolled. Since this guideline can have serious impacts on the cost, lifetime, and even the mission and functionality of a satellite, it is critical that this quantity be estimated well, and decision makers understand all assumptions and limitations inherent in the resulting value. This paper discusses several issues regarding estimates of casualty expectation, beginning with an overview of relevant United States policies and guidelines. The equation the space industry typically uses to estimate casualty expectation is presented, along with a look at the sensitivity of the results to the typical assumptions, models, and initial condition uncertainties. Differences in these modeling issues with respect to launch failure Ec estimates are included in the discussion. An alternate quantity to assess risks due to spacecraft entries is introduced. "Probability of casualty", or Pc , is defined as the probability of one or more instances of people suffering death or injury due to a spacecraft entry event. The equation to estimate Pc is derived, where the same assumptions, modeling, and initial condition issues for Ec apply. Several examples are then given of both Ec and Pc estimate calculations. Due to the difficult issues in

Shuttle launched flight tests - Supporting technology for planetary entry missions

NASA Technical Reports Server (NTRS)

Vetter, H. C.; Mcneilly, W. R.; Siemers, P. M., III; Nachtsheim, P. R.

1975-01-01

The feasibility of conducting Space Shuttle-launched earth entry flight tests to enhance the technology base for second generation planetary entry missions is examined. Outer planet entry environments are reviewed, translated into earth entry requirements and used to establish entry test system design and cost characteristics. Entry speeds up to those needed to simulate radiative heating levels of more than 30 kW/sq cm are shown to be possible. A standardized recoverable test bed concept is described that is capable of accommodating a wide range of entry technology experiments. The economic advantage of shared Shuttle launches are shown to be achievable through a test system configured to the volume constraints of a single Spacelab pallet using existing propulsion components.

Physics-Based Modeling of Meteor Entry and Breakup

NASA Technical Reports Server (NTRS)

Prabhu, Dinesh K.; Agrawal, Parul; Allen, Gary A.; Brandis, Aaron M.; Chen, Yih-Kanq; Jaffe, Richard L.; Saunders, David A.; Stern, Eric C.; Tauber, Michael E.; Venkatapathy, Ethiraj

2015-01-01

A new research effort at NASA Ames Research Center has been initiated in Planetary Defense, which integrates the disciplines of planetary science, atmospheric entry physics, and physics-based risk assessment. This paper describes work within the new program and is focused on meteor entry and breakup. Over the last six decades significant effort was expended in the US and in Europe to understand meteor entry including ablation, fragmentation and airburst (if any) for various types of meteors ranging from stony to iron spectral types. These efforts have produced primarily empirical mathematical models based on observations. Weaknesses of these models, apart from their empiricism, are reliance on idealized shapes (spheres, cylinders, etc.) and simplified models for thermal response of meteoritic materials to aerodynamic and radiative heating. Furthermore, the fragmentation and energy release of meteors (airburst) is poorly understood. On the other hand, flight of human-made atmospheric entry capsules is well understood. The capsules and their requisite heatshields are designed and margined to survive entry. However, the highest speed Earth entry for capsules is less than 13 km/s (Stardust). Furthermore, Earth entry capsules have never exceeded diameters of 5 m, nor have their peak aerothermal environments exceeded 0.3 atm and 1 kW/cm2. The aims of the current work are: (i) to define the aerothermal environments for objects with entry velocities from 13 to greater than 20 km/s; (ii) to explore various hypotheses of fragmentation and airburst of stony meteors in the near term; (iii) to explore the possibility of performing relevant ground-based tests to verify candidate hypotheses; and (iv) to quantify the energy released in airbursts. The results of the new simulations will be used to anchor said risk assessment analyses. With these aims in mind, state-of-the-art entry capsule design tools are being extended for meteor entries. We describe: (i) applications of current

The Propulsive Small Expendable Deployer System (ProSEDS)

NASA Technical Reports Server (NTRS)

Lorenzini, Enrico C.; Cosmo, Mario L.; Estes, Robert D.; Sanmartin, Juan; Pelaez, Jesus; Ruiz, Manuel

2003-01-01

This Final Report covers the following main topics: 1) Brief Description of ProSEDS; 2) Mission Analysis; 3) Dynamics Reference Mission; 4) Dynamics Stability; 5) Deployment Control; 6) Updated System Performance; 7) Updated Mission Analysis; 8) Updated Dynamics Reference Mission; 9) Updated Deployment Control Profiles and Simulations; 10) Updated Reference Mission; 11) Evaluation of Power Delivered by the Tether; 12) Deployment Control Profile Ref. #78 and Simulations; 13) Kalman Filters for Mission Estimation; 14) Analysis/Estimation of Deployment Flight Data; 15) Comparison of ED Tethers and Electrical Thrusters; 16) Dynamics Analysis for Mission Starting at a Lower Altitude; 17) Deployment Performance at a Lower Altitude; 18) Satellite Orbit after a Tether Cut; 19) Deployment with Shorter Dyneema Tether Length; 20) Interactive Software for ED Tethers.

Deployment and Adverse Pregnancy Outcomes: Primary Findings and Methodological Considerations.

PubMed

Katon, Jodie; Cypel, Yasmin; Raza, Mubashra; Zephyrin, Laurie; Reiber, Gayle; Yano, Elizabeth M; Barth, Shannon; Schneiderman, Aaron

2017-02-01

Objective To characterize the pregnancy outcomes of women Operation Enduring Freedom/Operation Iraqi Freedom (OEF/OIF) Veterans including prevalence of preterm delivery, low birth weight, and macrosomia, and to highlight methodological limitations that can impact findings. Methods A retrospective cohort study was conducted starting in 2014 analyzing data from the 2009 to 2011 National Health Study for a New Generation of US Veterans, which sampled Veterans deployed and not deployed to OIF/OEF. All pregnancies resulting in a live birth were included, and categorized as occurring among non-deployers, before deployment, during deployment, or after deployment. Outcomes included preterm birth, low birth weight, and macrosomia. The association of deployment with selected outcomes was estimated using separate general estimating equations to account for lack of outcome independence among women contributing multiple pregnancies. Adjustment variables included maternal age at outcome, and race/ethnicity. Results There were 2276 live births (191 preterm births, 153 low birth weight infants, and 272 macrosomic infants). Compared with pregnancies before deployment, pregnancies among non-deployers and those after deployment appeared to have greater risk of preterm birth [non-deployers: odds ratio (OR) = 2.16, 95 % confidence interval (CI) 1.25, 3.72; after deployment: OR = 1.90, 95 % CI 0.90, 4.02]. A similar pattern was observed for low birth weight. No association of deployment with macrosomia was detected. Discussion Compared with non-deployers, those who eventually deploy appear to have better pregnancy outcomes prior to deployment, but this advantage is no longer apparent after deployment. Non-deployers may not be an appropriate reference group to study the putative health impacts of deployment on pregnancy outcomes.

AASHTO connected vehicle infrastructure deployment analysis.

DOT National Transportation Integrated Search

2011-06-17

This report describes a deployment scenario for Connected Vehicle infrastructure by state and local transportation agencies, together with a series of strategies and actions to be performed by AASHTO to support application development and deployment.

Effects of open-entry spike-bull, limited-entry branched-bull harvesting on elk composition in Washington

USGS Publications Warehouse

Bender, L.C.; Fowler, P.E.; Bernatowicz, J.A.; Musser, J.L.; Stream, L.E.

2002-01-01

The Washington Department of Fish and Wildlife implemented an open-entry spike-bull, limited-entry branched-bull elk (Cervus elaphus) harvest strategy in the Blue Mountains (1989), Yakima (1994), and Colockum (1994) herd areas of Washington state with goals of increasing numbers of adult bulls to increase breeding efficiency and possibly calf recruitment. Numbers of total bulls/100 cows (x??=5.4) and branched bulls/100 cows (x??=5.3) increased with the change in harvest strategy, while yearling bulls/100 cows remained unchanged; calves/100 cows declined (x??=-8.6). Calves/100 cows were always negatively correlated with both total bulls/100 cows and branched bulls/100 cows in each area; correlations were significant in 5 of 9 comparisons with total-bull ratios and 5 of 9 comparisons with branched-bull ratios. Open-entry spike-bull, limited-entry branched-bull harvesting can be used to increase total-bull and branched-bulls ratios in hunted elk populations. However, the increased ratios of bulls and branched bulls were unimportant in influencing calf recruitment, likely because of the importance of female condition on production and survival of young.

Newberry Seismic Deployment Fieldwork Report

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

Wang, J; Templeton, D C

2012-03-21

This report summarizes the seismic deployment of Lawrence Livermore National Laboratory (LLNL) Geotech GS-13 short-period seismometers at the Newberry Enhanced Geothermal System (EGS) Demonstration site located in Central Oregon. This Department of Energy (DOE) demonstration project is managed by AltaRock Energy Inc. AltaRock Energy had previously deployed Geospace GS-11D geophones at the Newberry EGS Demonstration site, however the quality of the seismic data was somewhat low. The purpose of the LLNL deployment was to install more sensitive sensors which would record higher quality seismic data for use in future seismic studies, such as ambient noise correlation, matched field processing earthquakemore » detection studies, and general EGS microearthquake studies. For the LLNL deployment, seven three-component seismic stations were installed around the proposed AltaRock Energy stimulation well. The LLNL seismic sensors were connected to AltaRock Energy Gueralp CMG-DM24 digitizers, which are powered by AltaRock Energy solar panels and batteries. The deployment took four days in two phases. In phase I, the sites were identified, a cavity approximately 3 feet deep was dug and a flat concrete pad oriented to true North was made for each site. In phase II, we installed three single component GS-13 seismometers at each site, quality controlled the data to ensure that each station was recording data properly, and filled in each cavity with native soil.« less

ITS strategic deployment plan : executive summary

DOT National Transportation Integrated Search

1997-02-27

The Salt Lake Valley ITS Early Deployment Planning Study-Phase II prepared the framework to deploy candidate Intelligent Transportation System (ITS) projects that address Salt Lake Valleys transportation needs. A planning process was used that inc...

On-Board Generation of Three-Dimensional Constrained Entry Trajectories