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.

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.

KSC-03PP-0146

NASA Technical Reports Server (NTRS)

2003-01-01

KENNEDY SPACE CENTER, FLA. - STS-107 David Brown chats with the Closeout Crew during final preparations of his launch and entry suit in the White Room. The environmentally controlled chamber is mated to Space Shuttle Columbia for entry into the Shuttle. The hatch is seen in the background right. STS-107 is a mission devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. The payload on Space Shuttle Columbia includes FREESTAR (Fast Reaction Experiments Enabling Science, Technology, Applications and Research) and the SHI Research Double Module (SHI/RDM), known as SPACEHAB. Experiments on the module range from material sciences to life sciences. Liftoff is scheduled for 10:39 a.m. EST.

KSC-03pp0146

NASA Image and Video Library

2003-01-16

KENNEDY SPACE CENTER, FLA. - STS-107 David Brown chats with the Closeout Crew during final preparations of his launch and entry suit in the White Room. The environmentally controlled chamber is mated to Space Shuttle Columbia for entry into the Shuttle. The hatch is seen in the background right. STS-107 is a mission devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. The payload on Space Shuttle Columbia includes FREESTAR (Fast Reaction Experiments Enabling Science, Technology, Applications and Research) and the SHI Research Double Module (SHI/RDM), known as SPACEHAB. Experiments on the module range from material sciences to life sciences. Liftoff is scheduled for 10:39 a.m. EST.

KSC-03pp0145

NASA Image and Video Library

2003-01-16

KENNEDY SPACE CENTER, FLA. - STS-107 Mission Specialist Laurel Clark waves to a camera out of view during final preparations of her launch and entry suit in the White Room. The environmentally controlled chamber is mated to Space Shuttle Columbia for entry into the Shuttle. The hatch is seen in the background right. STS-107 is a mission devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. The payload on Space Shuttle Columbia includes FREESTAR (Fast Reaction Experiments Enabling Science, Technology, Applications and Research) and the SHI Research Double Module (SHI/RDM), known as SPACEHAB. Experiments on the module range from material sciences to life sciences. Liftoff is scheduled for 10:39 a.m. EST.

76 FR 66690 - Solid Urea From the Russian Federation: Final Results of Antidumping Duty Administrative Review

Federal Register 2010, 2011, 2012, 2013, 2014

2011-10-27

...-Deposit Requirements The following cash-deposit requirements will be effective upon publication for all... Russian Federation. These cash-deposit requirements shall remain in effect until further notice... relevant entries during this review period. Failure to comply with this requirement could result in the...

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

NASA Technical Reports Server (NTRS)

Palaszewski, Bryan

2012-01-01

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

KSC-2009-2017

NASA Image and Video Library

2009-03-10

CAPE CANAVERAL, Fla. – In the Operations and Checkout Building at NASA's Kennedy Space Center in Florida, STS-119 Mission Specialist Richard Arnold gets help from a suit technician in the final fitting of his launch and entry suit. Arnold will be making his first shuttle flight. The 14-day mission is the 28th to the International Space Station and the 125th space shuttle flight. Discovery will deliver the final pair of power-generating solar array wings and the S6 truss segment. Installation of S6 will signal the station's readiness to house a six-member crew for conducting increased science. Liftoff of Discovery is scheduled for 9:20 p.m. EDT on March 11. Photo credit: NASA/Kim Shiflett

Navigation Strategy for the Mars 2001 Lander Mission

NASA Technical Reports Server (NTRS)

Mase, Robert A.; Spencer, David A.; Smith, John C.; Braun, Robert D.

2000-01-01

The Mars Surveyor Program (MSP) is an ongoing series of missions designed to robotically study, map and search for signs of life on the planet Mars. The MSP 2001 project will advance the effort by sending an orbiter, a lander and a rover to the red planet in the 2001 opportunity. Each vehicle will carry a science payload that will Investigate the Martian environment on both a global and on a local scale. Although this mission will not directly search for signs of life, or cache samples to be returned to Earth, it will demonstrate certain enabling technologies that will be utilized by the future Mars Sample Return missions. One technology that is needed for the Sample Return mission is the capability to place a vehicle on the surface within several kilometers of the targeted landing site. The MSP'01 Lander will take the first major step towards this type of precision landing at Mars. Significant reduction of the landed footprint will be achieved through two technology advances. The first, and most dramatic, is hypersonic aeromaneuvering; the second is improved approach navigation. As a result, the guided entry will produce in a footprint that is only tens of kilometers, which is an order of magnitude improvement over the Pathfinder and Mars Polar Lander ballistic entries. This reduction will significantly enhance scientific return by enabling the potential selection of otherwise unreachable landing sites with unique geologic interest and public appeal. A landed footprint reduction from hundreds to tens of kilometers is also a milestone on the path towards human exploration of Mars, where the desire is to place multiple vehicles within several hundred meters of the planned landing site. Hypersonic aeromaneuvering is an extension of the atmospheric flight goals of the previous landed missions, Pathfinder and Mars Polar Lander (MPL), that utilizes aerodynamic lift and an autonomous guidance algorithm while in the upper atmosphere. The onboard guidance algorithm will control the direction of the lift vector, via bank angle modulation, to keep the vehicle on the desired trajectory. While numerous autonomous guidance algorithms have been developed for use during hypersonic flight at Earth, this will be the first flight of an autonomously directed lifting entry vehicle at Mars. However, without sufficient control and knowledge of the atmospheric entry conditions, the guidance algorithm will not perform effectively. The goal of the interplanetary navigation strategy is to deliver the spacecraft to the desired entry condition with sufficient accuracy and knowledge to enable satisfactory guidance algorithm performance. Specifically, the entry flight path angle must not exceed 0.27 deg. to a 3 sigma confidence level. Entry errors will contribute directly to the size of the landed footprint and the most significant component is entry flight path angle. The size of the entry corridor is limited on the shallow side by integrated heating constraints, and on the steep side by deceleration (g-load) and terminal descent propellant. In order to meet this tight constraint it is necessary to place a targeting maneuver seven hours prior to the time of entry. At this time the trajectory knowledge will be quite accurate, and the effects of maneuver execution errors will be small. The drawback is that entry accuracy is dependent on the success of this final late maneuver. Because propulsive maneuvers are critical events, it is desirable to minimize their occurrence and provide the flight team with as much response time as possible in the event of a spacecraft fault. A mission critical maneuver at Entry - 7 hours does not provide much fault tolerance, and it is desirable to provide a strategy that minimizes reliance on this maneuver. This paper will focus on the Improvements in interplanetary navigation that will decrease entry errors and will reduce the landed footprint, even in the absence of aeromaneuvering. The easiest to take advantage of are Improvements In the knowledge of the Mars ephemeris and gravity field due to the MGS and MSP'98 missions. Improvements In data collection and reduction techniques such as "precislon ranging' and near-simultaneous tracking will also be utilized. In addition to precise trajectory control, a robust strategy for communications and flight operations must also be demonstrated. The result Is a navigation and communications strategy on approach that utilizes optimal maneuver placement to take advantage of trajectory knowledge, minimizes risk for the flight operations team, is responsive to spacecraft hardware limitations, and achieves the entry corridor. The MSP2001 mission Is managed at JPL under the auspices of the Mars Exploration Directorate. The spacecraft flight elements are built and managed by Lockheed-Martin Astronautics in Denver, Colorado.

KSC-2009-2016

NASA Image and Video Library

2009-03-10

CAPE CANAVERAL, Fla. – In the Operations and Checkout Building at NASA's Kennedy Space Center in Florida, STS-119 Mission Specialist Steve Swanson has the final fitting of his launch and entry suit. Swanson is making his second shuttle flight. The 14-day mission is the 28th to the International Space Station and the 125th space shuttle flight. Discovery will deliver the final pair of power-generating solar array wings and the S6 truss segment. Installation of S6 will signal the station's readiness to house a six-member crew for conducting increased science. Liftoff of Discovery is scheduled for 9:20 p.m. EDT on March 11. Photo credit: NASA/Kim Shiflett

KSC-2009-2014

NASA Image and Video Library

2009-03-10

CAPE CANAVERAL, Fla. – In the Operations and Checkout Building at NASA's Kennedy Space Center in Florida, STS-119 Mission Specialist Koichi Wakata has a final fitting of his launch and entry suit. Wakata will remain on the station, replacing Expedition 18 Flight Engineer Sandra Magnus, who returns to Earth with the STS-119 crew. The 14-day mission is the 28th to the International Space Station and the 125th space shuttle flight. Discovery will deliver the final pair of power-generating solar array wings and the S6 truss segment. Installation of S6 will signal the station's readiness to house a six-member crew for conducting increased science. Liftoff of Discovery is scheduled for 9:20 p.m. EDT on March 11. Photo credit: NASA/Kim Shiflett

Thermal Protection of the Huygens Probe During Titan Entry: Last Questions

NASA Technical Reports Server (NTRS)

Bouilly, Jean-Marc

2005-01-01

CASSINI-HUYGENS mission is a cooperation between NASA and ESA, dedicated to the exploration of the Saturnian system. In the framework of this mission, the entry of the HUYGENS probe in the atmosphere of TITAN will be of major scientific interest. One of the essential points of the HUYGENS mission is therefore the good behavior of the thermal shield designed to maintain the aerodynamic shape and to protect the probe from excessive heating during the atmospheric entry on TITAN. The design and the qualification of this thermal shield were carried out between 1992 and 1995 (development phase). Currently, the final definition of mission parameters is being completed. As the performance of the thermal shield is one of all the parameters considered at system level, it is therefore necessary to reassess the thermal response of the TPS, taking into account some updated information that was not yet available during the development phase. After some recall of the results of 1992 to 1995, the paper will present a status of the current work on TPS.

Mars 2020 Entry, Descent and Landing Instrumentation 2 (MEDLI2)

NASA Technical Reports Server (NTRS)

Hwang, Helen H.; Bose, Deepak; White, Todd R.; Wright, Henry S.; Schoenenberger, Mark; Kuhl, Christopher A.; Trombetta, Dominic; Santos, Jose A.; Oishi, Tomomi; Karlgaard, Christopher D.;

76 FR 36089 - Circular Welded Non-Alloy Steel Pipe From the Republic of Korea: Final Results of the Antidumping...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-06-21

... Tube From Brazil, the Republic of Korea, Mexico, and Venezuela, 61 FR 11608 (March 21, 1996), pipe...) (``Assessment Policy Notice''). This clarification will apply to entries of subject merchandise during the... transaction. See Assessment Policy Notice for a full discussion of this clarification. Cash Deposit...

Which students will choose a career in psychiatry?

PubMed

Gowans, Margot C; Wright, Bruce J; Brenneis, Fraser R; Scott, Ian M

2011-10-01

In Canada, availability of and access to mental health professionals is limited. Only 6.6% of practising physicians are psychiatrists, a situation unlikely to improve in the foreseeable future. Identifying student characteristics present at medical school entry that predict a subsequent psychiatry residency choice could allow targeted recruiting or support to students early on in their careers, in turn creating a supply of psychiatry-oriented residency applicants. Between 2002 and 2004, data were collected from students in 15 Canadian medical school classes within 2 weeks of commencement of their medical studies. Surveys included questions on career preferences, attitudes, and demographics. Students were followed through to graduation and entry data linked anonymously with residency choice data. Logistic regression was used to identify early predictors of a psychiatry residency choice. Students (n = 1502) (77.4% of those eligible) contributed to the final analysis, with 5.3% naming psychiatry as their preferred residency career. When stated career interest in psychiatry at medical school entry was not included in a regression model, an exit career choice in psychiatry was predicted by a student's desire for prestige, lesser interest in medical compared with social problems, low hospital orientation, and not volunteering in sports. When an entry career interest in psychiatry was included in the model, this variable became the only predictor of an exit career choice in psychiatry. While experience and attitudes at medical school entry can predict whether students will chose a psychiatry career, the strongest predictor is an early career interest in psychiatry.

KSC-2009-2018

NASA Image and Video Library

2009-03-10

CAPE CANAVERAL, Fla. – In the Operations and Checkout Building at NASA's Kennedy Space Center in Florida, STS-119 Mission Specialist John Phillips has a final fitting of his launch and entry suit and the helmet. Phillips is making his third shuttle flight. The 14-day mission is the 28th to the International Space Station and the 125th space shuttle flight. Discovery will deliver the final pair of power-generating solar array wings and the S6 truss segment. Installation of S6 will signal the station's readiness to house a six-member crew for conducting increased science. Liftoff of Discovery is scheduled for 9:20 p.m. EDT on March 11. Photo credit: NASA/Kim Shiflett

KSC-2009-2013

NASA Image and Video Library

2009-03-10

CAPE CANAVERAL, Fla. – – In the Operations and Checkout Building at NASA's Kennedy Space Center in Florida, STS-119 Mission Specialist Joseph Acaba has a final fitting of his launch and entry suit. Acaba is making his first shuttle flight. The 14-day mission is the 28th to the International Space Station and the 125th space shuttle flight. Discovery will deliver the final pair of power-generating solar array wings and the S6 truss segment. Installation of S6 will signal the station's readiness to house a six-member crew for conducting increased science. Liftoff of Discovery is scheduled for 9:20 p.m. EDT on March 11. Photo credit: NASA/Kim Shiflett

KSC-2009-2012

NASA Image and Video Library

2009-03-10

CAPE CANAVERAL, Fla. – In the Operations and Checkout Building at NASA's Kennedy Space Center in Florida, STS-119 Mission Specialist Richard Arnold signals he is ready for launch during the final fitting of his launch and entry suit. Arnold is making his first shuttle flight. The 14-day mission is the 28th to the International Space Station and the 125th space shuttle flight. Discovery will deliver the final pair of power-generating solar array wings and the S6 truss segment. Installation of S6 will signal the station's readiness to house a six-member crew for conducting increased science. Liftoff of Discovery is scheduled for 9:20 p.m. EDT on March 11. Photo credit: NASA/Kim Shiflett

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.

2011 Mars Science Laboratory Launch Period Design

NASA Technical Reports Server (NTRS)

Abilleira, Fernando

2011-01-01

The Mars Science Laboratory mission, set to launch in the fall of 2011, has the primary objective of landing the most advanced rover to date to the surface of Mars to assess whether Mars ever was, or still is today, able to sustain carbon-based life. Arriving at Mars in August 2012, the Mars Science Laboratory will also demonstrate the ability to deliver large payloads to the surface of Mars, land more accurately (than previous missions) in a 20-km by 25-km ellipse, and traverse up to 20 km. Following guided entry and parachute deployment, the spacecraft will descend on a parachute and a Powered Descent Vehicle to safely land the rover on the surface of Mars. The launch/arrival strategy is driven by several key requirements, which include: launch vehicle capability, atmosphere-relative entry speed, communications coverage during Entry, Descent and Landing, latitude accessibility, and dust storm season avoidance. Notable among these requirements is maintaining a telecommunications link from atmospheric entry to landing plus one minute, via a Direct-To-Earth X-band link and via orbital assets using an UHF link, to ensure that any failure during Entry, Descent and Landing can be reconstructed in case of a mission anomaly. Due to concerns related to the lifetime of the relay orbiters, two additional launch/arrival strategies have been developed to improve Entry, Descent, and Landing communications. This paper discusses the final launch/arrival strategy selected prior to the launch period down-selection that is scheduled to occur in August 2011. It is also important to note that this paper is an update to Ref. 1 in that it includes two new Type 1 launch periods and drops the Type 2 launch period that is no longer considered.

The graduate entry generation: a qualitative study exploring the factors influencing the career expectations and aspirations of a graduating cohort of graduate entry dental students in one London institution

PubMed Central

2011-01-01

Background Dentistry in the UK has a number of new graduate-entry programmes. The aim of the study was to explore the motivation, career expectations and experiences of final year students who chose to pursue a dental career through the graduate entry programme route in one institution; and to explore if, and how, their intended career expectations and aspirations were informed by this choice. Method In-depth interviews of 14 graduate entry students in their final year of study. Data were transcribed verbatim and analysed using framework analysis. Results There were three categories of factors influencing students' choice to study dentistry through graduate entry: 'push', 'pull' and 'mediating'. Mediating factors related to students' personal concerns and circumstances, whereas push and pull factors related to features of their previous and future careers and wider social factors. Routes to Graduate Entry study comprised: 'early career changers', 'established career changers' and those pursuing 'routes to specialisation'. These routes also influenced the students' practice of dentistry, as students integrated skills in their dental studies, and encountered new challenges. Factors which students believed would influence their future careers included: vocational training; opportunities for specialisation or developing special interests and policy-related issues, together with wider professional and social concerns. The graduate entry programme was considered 'hard work' but a quick route to a professional career which had much to offer. Students' felt more could have been made of their pre-dental studies and/or experience during the programme. Factors perceived as influencing students' future contribution to dentistry included personal and social influences. Overall there was strong support for the values of the NHS and 'giving back' to the system in their future career. Conclusion Graduate entry students appear to be motivated to enter dentistry by a range of factors which suit their preferences and circumstances. They generally embrace the programme enthusiastically and seek to serve within healthcare, largely in the public sector. These students, who carry wider responsibilities, bring knowledge, skills and experience to dentistry which could be harnessed further during the programme. The findings suggest that graduate entry students, facilitated by varied career options, will contribute to an engaged workforce. PMID:21942994

The graduate entry generation: a qualitative study exploring the factors influencing the career expectations and aspirations of a graduating cohort of graduate entry dental students in one London institution.

PubMed

Newton, Paul; Cabot, Lyndon; Wilson, Nairn H F; Gallagher, Jennifer E

2011-09-24

Dentistry in the UK has a number of new graduate-entry programmes. The aim of the study was to explore the motivation, career expectations and experiences of final year students who chose to pursue a dental career through the graduate entry programme route in one institution; and to explore if, and how, their intended career expectations and aspirations were informed by this choice. In-depth interviews of 14 graduate entry students in their final year of study. Data were transcribed verbatim and analysed using framework analysis. There were three categories of factors influencing students' choice to study dentistry through graduate entry: 'push', 'pull' and 'mediating'. Mediating factors related to students' personal concerns and circumstances, whereas push and pull factors related to features of their previous and future careers and wider social factors. Routes to Graduate Entry study comprised: 'early career changers', 'established career changers' and those pursuing 'routes to specialisation'. These routes also influenced the students' practice of dentistry, as students integrated skills in their dental studies, and encountered new challenges.Factors which students believed would influence their future careers included: vocational training; opportunities for specialisation or developing special interests and policy-related issues, together with wider professional and social concerns.The graduate entry programme was considered 'hard work' but a quick route to a professional career which had much to offer. Students' felt more could have been made of their pre-dental studies and/or experience during the programme. Factors perceived as influencing students' future contribution to dentistry included personal and social influences. Overall there was strong support for the values of the NHS and 'giving back' to the system in their future career. Graduate entry students appear to be motivated to enter dentistry by a range of factors which suit their preferences and circumstances. They generally embrace the programme enthusiastically and seek to serve within healthcare, largely in the public sector. These students, who carry wider responsibilities, bring knowledge, skills and experience to dentistry which could be harnessed further during the programme. The findings suggest that graduate entry students, facilitated by varied career options, will contribute to an engaged workforce. © 2011 Newton et al; licensee BioMed Central Ltd.

Overview of the Mars Science Laboratory Parachute Decelerator Subsystem

NASA Technical Reports Server (NTRS)

Sengupta, Anita; Steltzner, Adam; Witkowski, Al; Rowan, Jerry; Cruz, Juan

2007-01-01

In 2010 the Mars Science Laboratory (MSL) mission will deliver NASA's largest and most capable rover to the surface of Mars. MSL will explore previously unattainable landing sites due to the implementation of a high precision Entry, Descent, and Landing (EDL) system. The parachute decelerator subsystem (PDS) is an integral prat of the EDL system, providing a mass and volume efficient some of aerodynamic drag to decelerate the entry vehicle from Mach 2 to subsonic speeds prior to final propulsive descent to the sutface. The PDS for MSL is a mortar deployed 19.7m Viking type Disk-Gap-Band (DGB) parachute; chosen to meet the EDL timeline requirements and to utilize the heritage parachute systems from Viking, Mars Pathfinder, Mars Exploration Rover, and Phoenix NASA Mars Lander Programs. The preliminary design of the parachute soft goods including materials selection, stress analysis, fabrication approach, and development testing will be discussed. The preliminary design of mortar deployment system including mortar system sizing and performance predictions, gas generator design, and development mortar testing will also be presented.

KSC-00pp1567

NASA Image and Video Library

2000-10-11

STS-92 Pilot Pamela Ann Melroy has a final check on her launch and entry suit in the White Room before entering Discovery. The White Room is an environmentally controlled area at the end of the Orbiter Access Arm that provides entry to the orbiter as well as emergency egress if needed. The arm remains in the extended position until 7 minutes 24 seconds before launch. Melroy and the rest of the crew are undertaking the fifth flight to the International Space Station for construction. Discovery carries a payload that includes the Integrated Truss Structure Z-1, first of 10 trusses that will form the backbone of the Space Station, and the third Pressurized Mating Adapter that will provide a Shuttle docking port for solar array installation on the sixth Station flight and Lab installation on the seventh Station flight. The mission includes four spacewalks for the construction activities. Discovery’s landing is expected Oct. 22 at 2:10 p.m. EDT

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...

Mars Exploration Rover Entry, Descent, and Landing: A Thermal Perspective

NASA Technical Reports Server (NTRS)

Tsuyuki, Glenn T.; Sunada, Eric T.; Novak, Keith S.; Kinsella, Gary M.; Phillip, Charles J.

2005-01-01

Perhaps the most challenging mission phase for the Mars Exploration Rovers was the Entry, Descent, and Landing (EDL). During this phase, the entry vehicle attached to its cruise stage was transformed into a stowed tetrahedral Lander that was surrounded by inflated airbags through a series of complex events. There was only one opportunity to successfully execute an automated command sequence without any possible ground intervention. The success of EDL was reliant upon the system thermal design: 1) to thermally condition EDL hardware from cruise storage temperatures to operating temperature ranges; 2) to maintain the Rover electronics within operating temperature ranges without the benefit of the cruise single phase cooling loop, which had been evacuated in preparation for EDL; and 3) to maintain the cruise stage propulsion components for the critical turn to entry attitude. Since the EDL architecture was inherited from Mars Pathfinder (MPF), the initial EDL thermal design would be inherited from MPF. However, hardware and implementation differences from MPF ultimately changed the MPF inheritance approach for the EDL thermal design. With the lack of full inheritance, the verification and validation of the EDL thermal design took on increased significance. This paper will summarize the verification and validation approach for the EDL thermal design along with applicable system level thermal testing results as well as appropriate thermal analyses. In addition, the lessons learned during the system-level testing will be discussed. Finally, the in-flight EDL experiences of both MER-A and -B missions (Spirit and Opportunity, respectively) will be presented, demonstrated how lessons learned from Spirit were applied to Opportunity.

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.

NASA Announces Contest to Name X-Ray Observatory

NASA Astrophysics Data System (ADS)

1998-04-01

NASA is searching for a new name for the Advanced X-ray Astrophysics Facility (AXAF), currently scheduled for launch Dec. 3, 1998, from the Space Shuttle Columbia. AXAF is the third of NASA's Great Observatories, after the Hubble Space Telescope and the Compton Gamma Ray Observatory. Once in orbit around Earth, it will explore hot, turbulent regions in the universe where X-rays are produced. Dr. Alan Bunner, director of NASA's Structure and Evolution of the universe science program, will announce April 18 at the National Science Teacher's Association meeting in Las Vegas, NV, the start of a contest, open to people worldwide, to find a new name for the observatory. Entries should contain the name of a person (not living), place, or thing from history, mythology, or fiction. Contestants should describe in a few sentences why this choice would be a good name for AXAF. The name must not have been used before on space missions by NASA or other organizations or countries. The grand prize will be a trip to NASA's Kennedy Space Center in Cape Canaveral, FL, to see the launch of the satellite aboard the Space Shuttle. Ten runner-up prizes will be awarded and all entrants will receive an AXAF poster. The grand prize is sponsored by TRW Inc., AXAF's prime contractor. The AXAF Science Center in Cambridge, MA, will run the contest for NASA. NASA will announce the final selection of the winning name later this year. Entries also can be mailed to: AXAF Contest, AXAF Science Center, Office of Education and Public Outreach, 60 Garden Street, MS 83, Cambridge, MA 02138. Mailed entries must be postmarked no later than June 30, 1998. All entries must state a name for the mission, along with the reason the name would make a good choice. The observatory, now in the final stages of assembly and testing at TRW's facility in Redondo Beach, CA, is more than 45 feet long and weighs 10,500 pounds. AXAF is the largest and most powerful X-ray observatory ever constructed, and its images will be more than ten times sharper than any previous X-ray telescope. This focusing power of the telescope is equivalent to the ability to read a newspaper at a distance of half a mile. Cosmic X-rays are produced by violent events, such as when stars explode or galaxies collide. X-rays also are emitted by matter heated to many millions of degrees as it swirls toward a black hole. The only way to observe these and other extremely hot astronomical sources is with a space-based X-ray telescope. Editor's Note (Dec 21, 1998): How the Chandra X-ray Observatory got its name: See the details of the contest and winning essays and the press release.

KSC-2009-2015

NASA Image and Video Library

2009-03-10

CAPE CANAVERAL, Fla. – In the Operations and Checkout Building at NASA's Kennedy Space Center in Florida, STS-119 Mission Specialist Koichi Wakata puts on his helmet as part of the final fitting of his launch and entry suit. Wakata is making his third shuttle flight. He will remain on the station, replacing Expedition 18 Flight Engineer Sandra Magnus, who returns to Earth with the STS-119 crew. The 14-day mission is the 28th to the International Space Station and the 125th space shuttle flight. Discovery will deliver the final pair of power-generating solar array wings and the S6 truss segment. Installation of S6 will signal the station's readiness to house a six-member crew for conducting increased science. Liftoff of Discovery is scheduled for 9:20 p.m. EDT on March 11. Photo credit: NASA/Kim Shiflett

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 integrity when exposed to a relevant dynamic pressure and aerodynamic stability of the inflatable system. Structural integrity and structural response of the inflatable will be verified with photogrammetric measurements of the back side of the aeroshell in flight. Aerodynamic stability as well as drag performance will be verified with on board inertial measurements and radar tracking from multiple ground radar stations. The experiment will yield valuable information about zero-g vacuum deployment dynamics of the flexible inflatable structure with both inertial and photographic measurements. In addition to demonstrating inflatable technology, IRVE will validate structural, aerothermal, and trajectory modeling techniques for the inflatable. Structural response determined from photogrammetrics will validate structural models, skin temperature measurements and additional in-depth temperature measurements will validate material thermal performance models, and on board inertial measurements along with radar tracking from multiple ground radar stations will validate trajectory simulation models.

Final Report: Update of the Glossary of Meteorology, September 1, 1994 - August 3, 1999

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

American Meteorological Society

2000-01-24

The American Meteorological Society has updated the Glossary of Meteorology from the first addition which was published in 1959. The second edition contains over 12,000 entries in meteorology and related fields. The glossary will be made available in both book and CD-ROM formats. DOE was one of six federal agencies that provided support for this project.

Navigation Challenges of the Mars Phoenix Lander Mission

NASA Technical Reports Server (NTRS)

Portock, Brian M.; Kruizinga, Gerhard; Bonfiglio, Eugene; Raofi, Behzad; Ryne, Mark

2008-01-01

The Mars Phoenix Lander mission was launched on August 4th, 2007. To land safely at the desired landing location on the Mars surface, the spacecraft trajectory had to be controlled to a set of stringent atmospheric entry and landing conditions. The landing location needed to be controlled to an elliptical area with dimensions of 100km by 20km. The two corresponding critical components of the atmospheric entry conditions are the entry flight path angle (target: -13.0 deg +/-0.21 deg) and the entry time (within +/-30 seconds). The purpose of this paper is to describe the navigation strategies used to overcome the challenges posed during spacecraft operations, which included an attitude control thruster calibration campaign, a trajectory control strategy, and a trajectory reconstruction strategy. Overcoming the navigation challenges resulted in final Mars atmospheric entry conditions just 0.007 deg off in entry flight path angle and 14.9 sec early in entry time. These entry dispersions in addition to the entry, descent, and landing trajectory dispersion through the atmosphere, lead to a final landing location just 7 km away from the desired landing target.

STS-82 Mission Specialist Steven L. Smith Suit Up

NASA Technical Reports Server (NTRS)

1997-01-01

STS-82 Mission Specialist Steven L. Smith gives a ''';thumbs up'''; while donning his launch and entry suit in the Operations and Checkout Building. A suit technician stands ready to assist with final adjustments. This is Smith''';s second space flight. He and the six other crew members will depart shortly for Launch Pad 39A, where the Space Shuttle Discovery awaits liftoff on a 10-day mission to service the orbiting Hubble Space Telescope (HST). This will be the second HST servicing mission. Four back-to-back spacewalks are planned.

15 CFR 301.7 - Final disposition of an application.

Code of Federal Regulations, 2012 CFR

2012-01-01

... (Continued) INTERNATIONAL TRADE ADMINISTRATION, DEPARTMENT OF COMMERCE MISCELLANEOUS REGULATIONS INSTRUMENTS AND APPARATUS FOR EDUCATIONAL AND SCIENTIFIC INSTITUTIONS § 301.7 Final disposition of an application... not been advised of the port of entry of the instrument, or if entry has not been made when the...

15 CFR 301.7 - Final disposition of an application.

Code of Federal Regulations, 2011 CFR

2011-01-01

... (Continued) INTERNATIONAL TRADE ADMINISTRATION, DEPARTMENT OF COMMERCE MISCELLANEOUS REGULATIONS INSTRUMENTS AND APPARATUS FOR EDUCATIONAL AND SCIENTIFIC INSTITUTIONS § 301.7 Final disposition of an application... not been advised of the port of entry of the instrument, or if entry has not been made when the...

15 CFR 301.7 - Final disposition of an application.

Code of Federal Regulations, 2010 CFR

2010-01-01

... (Continued) INTERNATIONAL TRADE ADMINISTRATION, DEPARTMENT OF COMMERCE MISCELLANEOUS REGULATIONS INSTRUMENTS AND APPARATUS FOR EDUCATIONAL AND SCIENTIFIC INSTITUTIONS § 301.7 Final disposition of an application... not been advised of the port of entry of the instrument, or if entry has not been made when the...

15 CFR 301.7 - Final disposition of an application.

Code of Federal Regulations, 2014 CFR

2014-01-01

... (Continued) INTERNATIONAL TRADE ADMINISTRATION, DEPARTMENT OF COMMERCE MISCELLANEOUS REGULATIONS INSTRUMENTS AND APPARATUS FOR EDUCATIONAL AND SCIENTIFIC INSTITUTIONS § 301.7 Final disposition of an application... not been advised of the port of entry of the instrument, or if entry has not been made when the...

15 CFR 301.7 - Final disposition of an application.

Code of Federal Regulations, 2013 CFR

2013-01-01

... (Continued) INTERNATIONAL TRADE ADMINISTRATION, DEPARTMENT OF COMMERCE MISCELLANEOUS REGULATIONS INSTRUMENTS AND APPARATUS FOR EDUCATIONAL AND SCIENTIFIC INSTITUTIONS § 301.7 Final disposition of an application... not been advised of the port of entry of the instrument, or if entry has not been made when the...

KSC-01pp1255

NASA Image and Video Library

2001-07-08

KENNEDY SPACE CENTER, Fla. -- STS-104 Mission Specialist Janet Lynn Kavandi arrives at the KSC Shuttle Landing Facility to make final preparations for launch of Space Shuttle Atlantis July 12. The mission is the 10th assembly flight to the International Space Station and carries the Joint Airlock Module, which will become the primary path for spacewalk entry and departure using both U.S. spacesuits and the Russian Orlan spacesuit for EVA activity

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

NASA Technical Reports Server (NTRS)

Mendeck, Gavin F.; McGrew, Lynn Craig

2013-01-01

The 2011 Mars Science Laboratory was the first Mars guided entry which safely delivered the rover to a landing 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. The guided entry performed as designed without any significant exceptions. The Curiosity rover was delivered about 2.2 km from the expected touchdown. This miss distance is attributed to little time to correct the downrange drift from the final bank reversal and a suspected tailwind during heading alignment. The successful guided entry for the Mars Science Laboratory lays the foundation for future Mars missions to improve upon.

A Common Probe Design for Multiple Planetary Destinations

NASA Technical Reports Server (NTRS)

Hwang, H. H.; Allen, G. A., Jr.; Alunni, A. I.; Amato, M. J.; Atkinson, D. H.; Bienstock, B. J.; Cruz, J. R.; Dillman, R. A.; Cianciolo, A. D.; Elliott, J. O.;

KSC-07pd3531

NASA Image and Video Library

2007-12-03

KENNEDY SPACE CENTER, FLA. -- STS-122 Mission Specialist Stanley Love dons his launch and entry suit for a final fitting before space shuttle Atlantis' launch scheduled for 4:31 p.m. EST on Dec. 6. Love will make his first shuttle flight. Atlantis will carry the Columbus Lab, Europe’s largest contribution to the construction of the International Space Station. It will support scientific and technological research in a microgravity environment. Columbus, a program of ESA, is a multifunctional, pressurized laboratory that will be permanently attached to Node 2 of the space station to carry out experiments in materials science, fluid physics and biosciences, as well as to perform a number of technological applications. Photo credit: NASA/Kim Shiflett

Doppler Data and Density Profile from Cassini Saturn Atmospheric Entry

NASA Astrophysics Data System (ADS)

Wong, M.; Boone, D.; Roth, D. C.

2017-12-01

After thirteen years of surveying the Saturnian system and providing a multitude of ground-breaking science data, the Cassini spacecraft will perform its final act on September 15, 2017 when it plunges into Saturn's upper atmosphere. This `close contact' with uncharted territory will deliver sets of data about Saturn that were not previously obtainable. In addition to new information obtained from various science instruments onboard, the doppler signal, primarily used for navigation purposes throughout the tour, will in this circumstance furnish a glimpse of the atmospheric density along Cassini's path through the upper atmosphere. In this talk we will discuss preliminary results from our analysis of the doppler data and its implication on the atmospheric density.

KSC-07pd3536

NASA Image and Video Library

2007-12-03

KENNEDY SPACE CENTER, FLA. -- STS-122 Mission Specialist Rex Walheim checks the helmet to his launch and entry suit for a final fitting before space shuttle Atlantis' launch scheduled for 4:31 p.m. EST on Dec. 6. Walheim will make his second shuttle flight. Atlantis will carry the Columbus Lab, Europe’s largest contribution to the construction of the International Space Station. It will support scientific and technological research in a microgravity environment. Columbus, a program of ESA, is a multifunctional, pressurized laboratory that will be permanently attached to Node 2 of the space station to carry out experiments in materials science, fluid physics and biosciences, as well as to perform a number of technological applications. Photo credit: NASA/Kim Shiflett

KSC-07pd3533

NASA Image and Video Library

2007-12-03

KENNEDY SPACE CENTER, FLA. -- STS-122 Mission Specialist Rex Walheim checks the helmet to his launch and entry suit for a final fitting before space shuttle Atlantis' launch scheduled for 4:31 p.m. EST on Dec. 6. Walheim will make his second shuttle flight. Atlantis will carry the Columbus Lab, Europe’s largest contribution to the construction of the International Space Station. It will support scientific and technological research in a microgravity environment. Columbus, a program of ESA, is a multifunctional, pressurized laboratory that will be permanently attached to Node 2 of the space station to carry out experiments in materials science, fluid physics and biosciences, as well as to perform a number of technological applications. Photo credit: NASA/Kim Shiflett

KSC-07pd3535

NASA Image and Video Library

2007-12-03

KENNEDY SPACE CENTER, FLA. -- STS-122 Mission Specialist Leland Melvin dons his launch and entry suit for a final fitting before space shuttle Atlantis' launch scheduled for 4:31 p.m. EST on Dec. 6. Melvin will make his first shuttle flight. Atlantis will carry the Columbus Lab, Europe’s largest contribution to the construction of the International Space Station. It will support scientific and technological research in a microgravity environment. Columbus, a program of ESA, is a multifunctional, pressurized laboratory that will be permanently attached to Node 2 of the space station to carry out experiments in materials science, fluid physics and biosciences, as well as to perform a number of technological applications. Photo credit: NASA/Kim Shiflett

PRN 95-3: Reduction of Worker protection Standard (WPS) Interim Restricted Entry Intervals (REIS) for Certain Low Risk Pesticides

EPA Pesticide Factsheets

On January 11, 1995, EPA published a draft policy on Reduced Restricted Entry Intervals for Certain Pesticides, in the Federal Register. The final policy was published in the Federal Register on May 3, 1995. This Notice contains the final policy.

77 FR 60917 - Trinexapac-ethyl; Pesticide Tolerances

Federal Register 2010, 2011, 2012, 2013, 2014

2012-10-05

... ``hog, meat by-products'' in order to correct inadvertent errors in the final rule tolerance table for...'' is revised to ``hog, meat by-products.'' V. Statutory and Executive Order Reviews This final rule... alphabetical order an entry for ``Hog, meat by-products''. 0 iii. Revising the entries for ``Wheat, forage...

STS-84 Commander Charles Precourt suits up

NASA Technical Reports Server (NTRS)

1997-01-01

STS-84 Commander Charles J. Precourt adjusts the helmet of his launch and entry suit during final prelaunch preparations in the Operations and Checkout Building. This is Precourts third space flight, but his first as commander. Precourt and six other crew members will depart shortly for Launch Pad 39A, where the Space Shuttle Atlantis awaits liftoff during an approximate 7-minute launch window which opens at about 4:08 a.m. This will be the sixth docking of the Space Shuttle with the Russian Space Station Mir. The exact liftoff time will be determined about 90 minutes prior to launch, based on the most current location of Mir.

An Entry Flight Controls Analysis for a Reusable Launch Vehicle

NASA Technical Reports Server (NTRS)

Calhoun, Philip

2000-01-01

The NASA Langley Research Center has been performing studies to address the feasibility of various single-stage to orbit concepts for use by NASA and the commercial launch industry to provide a lower cost access to space. Some work on the conceptual design of a typical lifting body concept vehicle, designated VentureStar(sup TM) has been conducted in cooperation with the Lockheed Martin Skunk Works. This paper will address the results of a preliminary flight controls assessment of this vehicle concept during the atmospheric entry phase of flight. The work includes control analysis from hypersonic flight at the atmospheric entry through supersonic speeds to final approach and landing at subsonic conditions. The requirements of the flight control effectors are determined over the full range of entry vehicle Mach number conditions. The analysis was performed for a typical maximum crossrange entry trajectory utilizing angle of attack to limit entry heating and providing for energy management, and bank angle to modulation of the lift vector to provide downrange and crossrange capability to fly the vehicle to a specified landing site. Sensitivity of the vehicle open and closed loop characteristics to CG location, control surface mixing strategy and wind gusts are included in the results. An alternative control surface mixing strategy utilizing a reverse aileron technique demonstrated a significant reduction in RCS torque and fuel required to perform bank maneuvers during entry. The results of the control analysis revealed challenges for an early vehicle configuration in the areas of hypersonic pitch trim and subsonic longitudinal controllability.

STS-92 MS Wakata gets suit checked in the White Room before launch

NASA Technical Reports Server (NTRS)

2000-01-01

STS-92 Mission Specialist Koichi Wakata of Japan gets a final check of his launch and entry suit in the White Room before entering Discovery. The White Room is an environmentally controlled area at the end of the Orbiter Access Arm that provides entry to the orbiter as well as emergency egress if needed. The arm remains in the extended position until 7 minutes 24 seconds before launch. Wakata and the rest of the crew are making the fifth flight to the International Space Station for construction. Discovery carries a payload that includes the Integrated Truss Structure Z-1, first of 10 trusses that will form the backbone of the Space Station, and the third Pressurized Mating Adapter that will provide a Shuttle docking port for solar array installation on the sixth Station flight and Lab installation on the seventh Station flight. The mission includes four spacewalks for the construction activities. Discovery's landing is expected Oct. 22 at 2:10 p.m. EDT.

STS-92 Pilot Melroy gets suit checked in the White Room before launch

NASA Technical Reports Server (NTRS)

2000-01-01

STS-92 Pilot Pamela Ann Melroy has a final check on her launch and entry suit in the White Room before entering Discovery. The White Room is an environmentally controlled area at the end of the Orbiter Access Arm that provides entry to the orbiter as well as emergency egress if needed. The arm remains in the extended position until 7 minutes 24 seconds before launch. Melroy and the rest of the crew are undertaking the fifth flight to the International Space Station for construction. Discovery carries a payload that includes the Integrated Truss Structure Z-1, first of 10 trusses that will form the backbone of the Space Station, and the third Pressurized Mating Adapter that will provide a Shuttle docking port for solar array installation on the sixth Station flight and Lab installation on the seventh Station flight. The mission includes four spacewalks for the construction activities. Discovery's landing is expected Oct. 22 at 2:10 p.m. EDT.

KSC-00pp1564

NASA Image and Video Library

2000-10-11

STS-92 Mission Specialist Koichi Wakata of Japan gets a final check of his launch and entry suit in the White Room before entering Discovery. The White Room is an environmentally controlled area at the end of the Orbiter Access Arm that provides entry to the orbiter as well as emergency egress if needed. The arm remains in the extended position until 7 minutes 24 seconds before launch. Wakata and the rest of the crew are making the fifth flight to the International Space Station for construction. Discovery carries a payload that includes the Integrated Truss Structure Z-1, first of 10 trusses that will form the backbone of the Space Station, and the third Pressurized Mating Adapter that will provide a Shuttle docking port for solar array installation on the sixth Station flight and Lab installation on the seventh Station flight. The mission includes four spacewalks for the construction activities. Discovery’s landing is expected Oct. 22 at 2:10 p.m. EDT

KSC-00pp1565

NASA Image and Video Library

2000-10-11

STS-92 Mission Specialist Michael E. Lopez-Alegria gets a final check of his launch and entry suit in the White Room before entering Discovery. The White Room is an environmentally controlled area at the end of the Orbiter Access Arm that provides entry to the orbiter as well as emergency egress if needed. The arm remains in the extended position until 7 minutes 24 seconds before launch. Lopez-Alegria and the rest of the crew are undertaking the fifth flight to the International Space Station for construction. Discovery carries a payload that includes the Integrated Truss Structure Z-1, first of 10 trusses that will form the backbone of the Space Station, and the third Pressurized Mating Adapter that will provide a Shuttle docking port for solar array installation on the sixth Station flight and Lab installation on the seventh Station flight. The mission includes four spacewalks for the construction activities. Discovery’s landing is expected Oct. 22 at 2:10 p.m. EDT

STS-92 MS Lopez-Alegria gets suit checked in the White Room before launch

NASA Technical Reports Server (NTRS)

2000-01-01

STS-92 Mission Specialist Michael E. Lopez-Alegria gets a final check of his launch and entry suit in the White Room before entering Discovery. The White Room is an environmentally controlled area at the end of the Orbiter Access Arm that provides entry to the orbiter as well as emergency egress if needed. The arm remains in the extended position until 7 minutes 24 seconds before launch. Lopez-Alegria and the rest of the crew are undertaking the fifth flight to the International Space Station for construction. Discovery carries a payload that includes the Integrated Truss Structure Z-1, first of 10 trusses that will form the backbone of the Space Station, and the third Pressurized Mating Adapter that will provide a Shuttle docking port for solar array installation on the sixth Station flight and Lab installation on the seventh Station flight. The mission includes four spacewalks for the construction activities. Discovery's landing is expected Oct. 22 at 2:10 p.m. EDT.

Guidance/Navigation Requirements Study Final Report. Volume III. Appendices

DTIC Science & Technology

1978-04-30

shown Figure G-2. The free-flight simulation program FFSIM uses quaternions to calculate the body attitude as a function of time. To calculate the...the lack of open-loop damping, the existence of a feedback controller which will stabilize the closed-loon system depends upon the satisfaction of a...re-entry vehicle has dynamic pecularitles which tend to discourage the use of "linear-quadratic" feedback regulators in guidance. The disadvantageous

Barratt on middeck

NASA Image and Video Library

2011-02-24

S133-E-005034 (24 Feb. 2011) --- Astronaut Michael Barratt, STS-133 mission specialist, is seen on the middeck of the space shuttle Discovery soon after reaching Earth orbit on flight day one. Barratt is preparing to stow his launch and entry escape suit, which will be called upon again in a week and a half from now when Discovery comes back to Earth for the final time. Photo credit: NASA or National Aeronautics and Space Administration

Mode of Entry as a Predictor of Success in Final Year Bachelor of Education Degree Examinations in Universities in Ekiti and Ondo States, Nigeria

ERIC Educational Resources Information Center

Adeyemi, T. O.

2009-01-01

This paper investigates the mode of entry as a predictor of success in final year bachelor of education degree examinations in universities in Ekiti and Ondo States, Nigeria. As an ex-post facto and correlational research, the study population comprised all the 1810 final year 400 level students in the two universities offering education courses,…

ELROI Extremely Low Resource Optical Identifier. A license plate for your satellite, and more.

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

Palmer, David

ELROI (Extremely Low Resource Optical Identifier) is a license plate for your satellite; a small tag that flashes an optical identification code that can be read by a small telescope on the ground. The final version of the tag will be the size of a thick postage stamp and fully autonomous: you can attach it to everything that goes into space, including small cubesats and inert debris like rocket stages, and it will keep blinking even after the satellite is shut down, reliably identifying the object from launch until re-entry.

Communications Blackout Predictions for Atmospheric Entry of Mars Science Laboratory

NASA Technical Reports Server (NTRS)

Morabito, David D.; Edquist, Karl

2005-01-01

The Mars Science Laboratory (MSL) is expected to be a long-range, long-duration science laboratory rover on the Martian surface. MSL will provide a significant milestone that paves the way for future landed missions to Mars. NASA is studying options to launch MSL as early as 2009. MSL will be the first mission to demonstrate the new technology of 'smart landers', which include precision landing and hazard avoidance in order to -land at scientifically interesting sites that would otherwise be unreachable. There are three elements to the spacecraft; carrier (cruise stage), entry vehicle, and rover. The rover will have an X-band direct-to-Earth (DTE) link as well as a UHF proximity link. There is also a possibility of an X-band proximity link. Given the importance of collecting critical event telemetry data during atmospheric entry, it is important to understand the ability of a signal link to be maintained, especially during the period near peak convective heating. The received telemetry during entry (or played back later) will allow for the performance of the Entry-Descent-Landing technologies to be assessed. These technologies include guided entry for precision landing, hazard avoidance, a new sky-crane landing system and powered descent. MSL will undergo an entry profile that may result in a potential communications blackout caused by ionized plasma for short periods near peak heating. The vehicle will use UHF and possibly X-band during the entry phase. The purpose of this report is to quantify or bound the likelihood of any such blackout at UHF frequencies (401 MHz) and X-band frequencies (8.4 GHz). Two entry trajectory scenarios were evaluated: a stressful entry trajectory to quantify an upper-bound for any possible blackout period, and a nominal likely trajectory to quantify likelihood of blackout for such cases.

77 FR 41973 - Record of Decision for the Entry Control Reconfiguration and Base Perimeter Fence Relocation in...

Federal Register 2010, 2011, 2012, 2013, 2014

2012-07-17

... Reconfiguration and Base Perimeter Fence Relocation in area A Wright-Patterson AF Base, Ohio, Final Environmental..., 2012, the United States Air Force signed the ROD for the Entry Control Reconfiguration and Base Perimeter Fence Relocation in Area A Wright-Patterson Air Force Base (WPAFB), Ohio Final Environmental...

Entry-to-practice public health nursing competencies: A Delphi method and knowledge translation strategy.

PubMed

Schofield, Ruth; Chircop, Andrea; Baker, Cynthia; Dietrich Leurer, Marie; Duncan, Susan; Wotton, Donalda

2018-06-01

Sustaining and strengthening nurses 'contributions to public and population health in the 21st century depends in part on nursing education. Clearly articulated entry-to-practice competencies will contribute to the capacity of undergraduate nursing education programs to prepare graduates to promote local, national and global population health. The Canadian Association of Schools of Nursing created the Public Health Task Force to develop consensus on core, national entry-to-practice competencies in public health nursing for undergraduate nursing students and to support these competencies with corresponding online teaching strategies. Delphi approach. Nurses with public health experience in education and practice, and representatives from other public health professional organizations across Canada. The three-phased competency development included: 1) an environmental scan; 2) an iterative process to draft competencies; and 3) a modified Delphi process to confirm the final competency framework using face to face consultations and a survey. The knowledge translation strategy involved soliciting submissions of teaching strategies for peer-review and subsequent inclusion in an interactive online resource. 242 public health educators and practitioners participated in the consensus consultation. The final document outlined five competency statements with 19 accompanying indicators. A total of 123 teaching strategies were submitted for the online resource, of which 50 were accepted as exemplary teaching strategies. This competency development process can provide guidance for the development of competencies in other countries, thus strengthening public health nursing education globally. The decision to intentionally level the competencies to entry-to-practice, as opposed to an advanced level, enhanced their application to undergraduate nursing education. The development of the additional inventory of teaching strategies created a sustainable innovative resource for public health nursing educators and practitioners world-wide to support the adoption of entry-to-practice public health nursing competencies. Crown Copyright © 2018. Published by Elsevier Ltd. All rights reserved.

KSC-07pd3532

NASA Image and Video Library

2007-12-03

KENNEDY SPACE CENTER, FLA. -- STS-122 Mission Specialist Hans Schlegel checks the helmet to his launch and entry suit for a final fitting before space shuttle Atlantis' launch scheduled for 4:31 p.m. EST on Dec. 6. Schlegel, who represents the European Space Agency, will make his second shuttle flight. Atlantis will carry the Columbus Lab, Europe’s largest contribution to the construction of the International Space Station. It will support scientific and technological research in a microgravity environment. Columbus, a program of ESA, is a multifunctional, pressurized laboratory that will be permanently attached to Node 2 of the space station to carry out experiments in materials science, fluid physics and biosciences, as well as to perform a number of technological applications. Photo credit: NASA/Kim Shiflett

KSC-07pd3530

NASA Image and Video Library

2007-12-03

KENNEDY SPACE CENTER, FLA. -- STS-122 Mission Specialist Hans Schlegel dons his launch and entry suit for a final fitting before space shuttle Atlantis' launch scheduled for 4:31 p.m. EST on Dec. 6. Schlegel, who represents the European Space Agency, will make his second shuttle flight. Atlantis will carry the Columbus Lab, Europe’s largest contribution to the construction of the International Space Station. It will support scientific and technological research in a microgravity environment. Columbus, a program of ESA, is a multifunctional, pressurized laboratory that will be permanently attached to Node 2 of the space station to carry out experiments in materials science, fluid physics and biosciences, as well as to perform a number of technological applications. Photo credit: NASA/Kim Shiflett

NASA TechPort Entry for Coiled Brine Recovery Assembly (CoBRA) CL IR&D Project

NASA Technical Reports Server (NTRS)

Pensinger, Stuart

2014-01-01

The Coiled Brine Recovery Assembly (CoBRA) project will result in a proof-of-concept demonstration for a lightweight, compact, affordable, regenerable and disposable solution to brine water recovery. The heart of CoBRA is an evaporator that produces water vapor from brine. This evaporator leverages a novel design that enables passive transport of brine from place to place within the system. While it will be necessary to build or modify a system for testing the CoBRA concept, the emphasis of this project will be on developing the evaporator itself. This project will utilize a “test early, test often” approach, building at least one trial evaporator to guide the design of the final product.

Communications Blackout Predictions for Atmospheric Entry of Mars Science Laboratory

NASA Technical Reports Server (NTRS)

Morabito, David D.; Edquist, Karl T.

2005-01-01

The Mars Science Laboratory (MSL) is expected to be a long-range, long-duration science laboratory rover on the Martian surface. MSL will provide a significant milestone that paves the way for future landed missions to Mars. NASA is studying options to launch MSL as early as 2009. There are three elements to the spacecraft; carrier (cruise stage), entry vehicle, and rover. The rover will have a UHF proximity link as the primary path for EDL communications and may have an X-band direct-to-Earth link as a back-up. Given the importance of collecting critical event telemetry data during atmospheric entry, it is important to understand the ability of a signal link to be maintained, especially during the period near peak convective heating. The received telemetry during entry (or played back later) will allow for the performance of the Entry-Descent-Landing technologies to be assessed. These technologies include guided entry for precision landing, a new sky-crane landing system and powered descent. MSL will undergo an entry profile that may result in a potential communications blackout caused by ionized particles for short periods near peak heating. The vehicle will use UHF and possibly X-band during the entry phase. The purpose of this rep0rt is to quantify or bound the likelihood of any such blackout at UHF frequencies (401 MHz) and X-band frequencies (8.4 GHz). Two entry trajectory scenarios were evaluated: a stressful entry trajectory to quantify an upper-bound for any possible blackout period, and a nominal trajectory to quantify likelihood of blackout for such cases.

KSC-2011-5200

NASA Image and Video Library

2011-07-08

CAPE CANAVERAL, Fla. -- Dressed in their bright-orange launch-and-entry suits, the final four astronauts to launch aboard a space shuttle enjoy a light moment with a card game in their Astronaut Crew Quarters in the Operations and Checkout Building at NASA's Kennedy Space Center in Florida. The veteran astronauts are scheduled to lift off aboard space shuttle Atlantis at 11:26 a.m. EDT on July 8 for their mission to the International Space Station. STS-135 will deliver the Raffaello multi-purpose logistics module packed with supplies and spare parts for the orbiting outpost. Atlantis also will fly the Robotic Refueling Mission experiment that will investigate the potential for robotically refueling existing satellites in orbit. In addition, Atlantis will return with a failed ammonia pump module to help NASA better understand the failure mechanism and improve pump designs for future systems. STS-135 will be the 33rd flight of Atlantis, the 37th shuttle mission to the space station, and the 135th and final mission of NASA's Space Shuttle Program. For more information visit, www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts135/index.html. Photo credit: NASA/Kim Shiflett

KSC-2011-5201

NASA Image and Video Library

2011-07-08

CAPE CANAVERAL, Fla. -- Dressed in their bright-orange launch-and-entry suits, the final four astronauts to launch aboard a space shuttle enjoy a light moment with a card game in their Astronaut Crew Quarters in the Operations and Checkout Building at NASA's Kennedy Space Center in Florida. The veteran astronauts are scheduled to lift off aboard space shuttle Atlantis at 11:26 a.m. EDT on July 8 for their mission to the International Space Station. STS-135 will deliver the Raffaello multi-purpose logistics module packed with supplies and spare parts for the orbiting outpost. Atlantis also will fly the Robotic Refueling Mission experiment that will investigate the potential for robotically refueling existing satellites in orbit. In addition, Atlantis will return with a failed ammonia pump module to help NASA better understand the failure mechanism and improve pump designs for future systems. STS-135 will be the 33rd flight of Atlantis, the 37th shuttle mission to the space station, and the 135th and final mission of NASA's Space Shuttle Program. For more information visit, www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts135/index.html. Photo credit: NASA/Kim Shiflett

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.

STS-70 Commander Terence 'Tom' Henricks suits up

NASA Technical Reports Server (NTRS)

1995-01-01

STS-70 Commander Terence 'Tom' Henricks is donning his launch/entry suit in the Operations and Checkout Building with help from a suit technician. Henricks, who is about to make his third trip into space, and four crew members will depart shortly for Launch Pad 39B, where the Space Shuttle Discovery is undergoing final preparations for a liftoff scheduled during a two and a half hour launch window opening at 9:41 a.m. EDT.

STS-70 Mission Specialist Nancy Jane Currie suits up

NASA Technical Reports Server (NTRS)

1995-01-01

STS-70 Mission Specialist Nancy Jane Currie is donning her launch/entry suit in the Operations and Checkout Building with help from a suit technician. Currie has flown in space once before, on STS-57. Currie and four crew mates will depart shortly for Launch Pad 39B, where the Space Shuttle Discovery is undergoing final preparations for a liftoff scheduled during a two and a half hour launch window opening at 9:41 a.m. EDT.

Re-entry simulation chamber for thermo-mechanical characterisation of space materials

NASA Astrophysics Data System (ADS)

Liedtke, Volker

2003-09-01

During re-entry, materials and components are subject to very high thermal and mechanical loads. Any failure may cause loss of mission. Therefore, materials and components have to be tested under most rigid conditions to verify the suitability of the material and to verify the design of the components. The Re-Entry Simulation Chamber (RESiC) at ARC Seibersdorf research (ARCS) allows simulating the high thermal loads as well as complex mechanical load profiles that may occur during a re-entry; additionally, the influence of chemical reactions of materials with gaseous components of the atmosphere can be studied. The high vacuum chamber (better than 1×10-6 mbar) has a diameter of 650 mm and allows a sample height of 500 mm, or 1000 mm with extension flange. The gas dosing system is designed to emulate the increasing atmospheric pressure during the re-entry trajectory of a vehicle. Heating is performed by a 30 kW induction generator that allows a sufficiently rapid heating of larger components; electrically conductive materials such as metals or carbon fibre reinforced ceramics are directly heated, while for electrical insulators, susceptor plates or tubes will be employed. The uniaxial servo-hydraulic testing machine has a maximum load of 70 kN, either static or with a frequency of up to 70 Hz, with any given load profile (sinus, rectangular, triangular, ...). Strain measurements will be done by non-contacting laser speckle system for maximum flexibility and minimum instrumentation time effort (currently under application testing), or by strain gauges. All relevant process parameters are controlled and recorded by microcomputer. The highly sophisticated control software allows a convenient and reliable multi-channel data acquisition, e.g. temperatures at various positions of the test piece, pressure, loads, strains, and any other test data according to customer specifications; the data format is suitable for any further data processing. During the set-up and operation testing, the device has successfully been employed for thermal shock testing, thermal cycling and gas cycling tests, thermomechanical tests and combinations thereof, e.g. sintering or hot-pressing. During the current final test series, the device will be completed, further optimised and shall be fully operational in summer 2003.

Creative PDB`s (parts databases)

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

Cote, T.J.

1998-12-31

PDB component property entries and creative picklists can make the schematic entry process and downstream tools such as BOM generation more useful. This presentation will show how creative PDB`s can enhance the design process. Examples of PDB entries developed at Los Alamos National Laboratory will be discussed.

Macromolecular Structure Database. Final Progress Report

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

Gilliland, Gary L.

2003-09-23

The central activity of the PDB continues to be the collection, archiving and distribution of high quality structural data to the scientific community on a timely basis. In support of these activities NIST has continued its roles in developing the physical archive, in developing data uniformity, in dealing with NMR issues and in the distribution of PDB data through CD-ROMs. The physical archive holdings have been organized, inventoried, and a database has been created to facilitate their use. Data from individual PDB entries have been annotated to produce uniform values improving tremendously the accuracy of results of queries. Working withmore » the NMR community we have established data items specific for NMR that will be included in new entries and facilitate data deposition. The PDB CD-ROM production has continued on a quarterly basis, and new products are being distributed.« less

19 CFR 159.64 - Distribution of offset.

Code of Federal Regulations, 2012 CFR

2012-04-01

... will occur between a Clearing Account and a Special Fund Account when an entry upon which antidumping... upon the amount actually collected on the entry and in the Clearing Account. Following liquidation, additional transfers will be made on the liquidated entry to the corresponding Special Account, as additional...

19 CFR 159.64 - Distribution of offset.

Code of Federal Regulations, 2011 CFR

2011-04-01

... will occur between a Clearing Account and a Special Fund Account when an entry upon which antidumping... upon the amount actually collected on the entry and in the Clearing Account. Following liquidation, additional transfers will be made on the liquidated entry to the corresponding Special Account, as additional...

19 CFR 159.64 - Distribution of offset.

Code of Federal Regulations, 2014 CFR

2014-04-01

... will occur between a Clearing Account and a Special Fund Account when an entry upon which antidumping... upon the amount actually collected on the entry and in the Clearing Account. Following liquidation, additional transfers will be made on the liquidated entry to the corresponding Special Account, as additional...

19 CFR 159.64 - Distribution of offset.

Code of Federal Regulations, 2013 CFR

2013-04-01

... will occur between a Clearing Account and a Special Fund Account when an entry upon which antidumping... upon the amount actually collected on the entry and in the Clearing Account. Following liquidation, additional transfers will be made on the liquidated entry to the corresponding Special Account, as additional...

19 CFR 159.64 - Distribution of offset.

Code of Federal Regulations, 2010 CFR

2010-04-01

... will occur between a Clearing Account and a Special Fund Account when an entry upon which antidumping... upon the amount actually collected on the entry and in the Clearing Account. Following liquidation, additional transfers will be made on the liquidated entry to the corresponding Special Account, as additional...

STS-77 MS Andrew Thomas suits up

NASA Technical Reports Server (NTRS)

1996-01-01

STS-77 Mission Specialist Andrew S. W. Thomas finishes donning his launch/entry suit in the Operations and Checkout Building with assistance from a suit technician. A native of South Australia, the rookie astronaut joins a crew of five veterans on the fourth Shuttle flight of 1996. They will depart shortly for Launch Pad 39B, where the Space Shuttle Endeavour is undergoing final preparations for liftoff during a two-and-a-half hour launch window opening at 6:30 a.m. EDT, May 19.

KSC-2011-2693

NASA Image and Video Library

2011-04-01

CAPE CANAVERAL, Fla. - STS-134 Mission Specialist Greg Chamitoff gives a thumbs-up as he takes his seat aboard space shuttle Endeavour during the Terminal Countdown Demonstration Test (TCDT) on Launch Pad 39A at NASA's Kennedy Space Center in Florida. Part of TCDT includes practicing the final hours of a real launch day when astronauts put on their launch-and-entry suits, ride to the pad in the Astrovan and strap into the shuttle. Endeavour's six crew members are targeted to launch April 19 at 7:48 p.m. EDT. They will deliver the Express Logistics Carrier-3, Alpha Magnetic Spectrometer-2 (AMS), a high-pressure gas tank, additional spare parts for the Dextre robotic helper and micrometeoroid debris shields to the International Space Station. This will be the final spaceflight for Endeavour. For more information visit, www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts134/index.html. Photo credit: NASA/Kim Shiflett

KSC-2011-2686

NASA Image and Video Library

2011-04-01

CAPE CANAVERAL, Fla. - In the White Room of Launch Pad 39A at NASA's Kennedy Space Center in Florida, STS-134 Commander Mark Kelly prepares to board space shuttle Endeavour during the Terminal Countdown Demonstration Test (TCDT). Part of TCDT includes practicing the final hours of a real launch day when astronauts put on their launch-and-entry suits, ride to the pad in the Astrovan and strap into the shuttle. Endeavour's six crew members are targeted to launch April 19 at 7:48 p.m. EDT. They will deliver the Express Logistics Carrier-3, Alpha Magnetic Spectrometer-2 (AMS), a high-pressure gas tank, additional spare parts for the Dextre robotic helper and micrometeoroid debris shields to the International Space Station. This will be the final spaceflight for Endeavour. For more information visit, www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts134/index.html. Photo credit: NASA/Jim Grossmann

KSC-2011-2689

NASA Image and Video Library

2011-04-01

CAPE CANAVERAL, Fla. -- In the White Room of Launch Pad 39A at NASA's Kennedy Space Center in Florida, STS-134 Mission Specialist Michael Fincke prepares to board space shuttle Endeavour during the Terminal Countdown Demonstration Test (TCDT). Part of TCDT includes practicing the final hours of a real launch day when astronauts put on their launch-and-entry suits, ride to the pad in the Astrovan and strap into the shuttle. Endeavour's six crew members are targeted to launch April 19 at 7:48 p.m. EDT. They will deliver the Express Logistics Carrier-3, Alpha Magnetic Spectrometer-2 (AMS), a high-pressure gas tank, additional spare parts for the Dextre robotic helper and micrometeoroid debris shields to the International Space Station. This will be the final spaceflight for Endeavour. For more information visit, www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts134/index.html. Photo credit: NASA/Jim Grossmann

KSC-2011-2694

NASA Image and Video Library

2011-04-01

CAPE CANAVERAL, Fla. -- STS-134 Pilot Greg H. Johnson gives a thumbs-up as he takes his seat aboard space shuttle Endeavour during the Terminal Countdown Demonstration Test (TCDT) on Launch Pad 39A at NASA's Kennedy Space Center in Florida. Part of TCDT includes practicing the final hours of a real launch day when astronauts put on their launch-and-entry suits, ride to the pad in the Astrovan and strap into the shuttle. Endeavour's six crew members are targeted to launch April 19 at 7:48 p.m. EDT. They will deliver the Express Logistics Carrier-3, Alpha Magnetic Spectrometer-2 (AMS), a high-pressure gas tank, additional spare parts for the Dextre robotic helper and micrometeoroid debris shields to the International Space Station. This will be the final spaceflight for Endeavour. For more information visit, www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts134/index.html. Photo credit: NASA/Kim Shiflett

On-Orbit Maneuver Calibrations for the Stardust Spacecraft

NASA Technical Reports Server (NTRS)

Nandi, Sumita; Kennedy, Brian; Williams, Kenneth E.; Byrnes, Dennis V.

2006-01-01

The Stardust spacecraft, launched February 7, 1999, successfully delivered its sample return capsule to the Utah Test and Training Range on January 15, 2006. The entry maneuver strategy included a trajectory correction at entry minus 10 days (TCM18) targeted to entry with the inclusion of a final biased fixed direction maneuver at entry minus 29 hours (TCM19). To meet the stringent entry targeting requirements necessary for human safety and capsule integrity, a campaign of maneuver calibrations were undertaken in summers of 2003 and 2005 to improve performance for both maneuvers. The results of the calibration program are reported here. The in-flight calibrations included a series of several turns to various final attitudes via deadband walks about each of the three spacecraft axes, as well as 12 in-place burns with magnitudes between 0.5 and 1.0 m/s, the range initially expected for TCM19. The turn and burn calibrations as well as the performance of TCM 17, 18 and 19 are discussed.

KSC-2014-4397

NASA Image and Video Library

2014-10-13

CAPE CANAVERAL, Fla. – Inside the Launch Abort System Facility at NASA's Kennedy Space Center in Florida, preparations are underway to remove the window covers on Orion before the fourth and final Ogive panel is installed around the spacecraft and Launch Abort System. The Ogive panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The work marked the final major assembly steps for the spacecraft before it is transported to Space Launch Complex 37 at Cape Canaveral Air Force Station in November. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Ben Smegelsky

KSC-2014-4259

NASA Image and Video Library

2014-10-13

CAPE CANAVERAL, Fla. – Inside the Launch Abort System Facility at NASA’s Kennedy Space Center in Florida, a crane brings the fourth and final Ogive panel closer for installation on Orion's Launch Abort System. The panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The work marked the final major assembly steps for the spacecraft before it is transported to Space Launch Complex 37 at Cape Canaveral Air Force Station in November. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Kim Shiflett

KSC-2014-4400

NASA Image and Video Library

2014-10-13

CAPE CANAVERAL, Fla. – Inside the Launch Abort System Facility at NASA’s Kennedy Space Center in Florida, a window cover has been carefully removed from the Orion spacecraft before the fourth and final Ogive panel is installed around the spacecraft and Launch Abort System. The Ogive panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The work marked the final major assembly steps for the spacecraft before it is transported to Space Launch Complex 37 at Cape Canaveral Air Force Station in November. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Ben Smegelsky

KSC-2014-4399

NASA Image and Video Library

2014-10-13

CAPE CANAVERAL, Fla. – Inside the Launch Abort System Facility at NASA's Kennedy Space Center in Florida, a technician carefully removes the window covers on Orion before the fourth and final Ogive panel is installed around the spacecraft and Launch Abort System. The Ogive panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The work marked the final major assembly steps for the spacecraft before it is transported to Space Launch Complex 37 at Cape Canaveral Air Force Station in November. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Ben Smegelsky

STS-92 MS Wisoff gets suit checked in the White Room before launch

NASA Technical Reports Server (NTRS)

2000-01-01

STS-92 Mission Specialist Peter J.K. '''Jeff''' Wisoff reaches out to shake the hand of Danny Wyatt, KSC NASA Quality Assurance specialist, after completing final check of his launch and entry suit in the White Room before entering Discovery. The White Room is an environmentally controlled area at the end of the Orbiter Access Arm that provides entry to the orbiter as well as emergency egress if needed. The arm remains in the extended position until 7 minutes 24 seconds before launch. Wisoff and the rest of the crew are undertaking the fifth flight to the International Space Station for construction. Discovery carries a payload that includes the Integrated Truss Structure Z-1, first of 10 trusses that will form the backbone of the Space Station, and the third Pressurized Mating Adapter that will provide a Shuttle docking port for solar array installation on the sixth Station flight and Lab installation on the seventh Station flight. The mission includes four spacewalks for the construction activities. Discovery's landing is expected Oct. 22 at 2:10 p.m. EDT.

KSC-00pp1566

NASA Image and Video Library

2000-10-11

STS-92 Mission Specialist Peter J.K. “Jeff” Wisoff reaches out to shake the hand of Danny Wyatt, KSC NASA Quality Assurance specialist, after completing final check of his launch and entry suit in the White Room before entering Discovery. The White Room is an environmentally controlled area at the end of the Orbiter Access Arm that provides entry to the orbiter as well as emergency egress if needed. The arm remains in the extended position until 7 minutes 24 seconds before launch. Wisoff and the rest of the crew are undertaking the fifth flight to the International Space Station for construction. Discovery carries a payload that includes the Integrated Truss Structure Z-1, first of 10 trusses that will form the backbone of the Space Station, and the third Pressurized Mating Adapter that will provide a Shuttle docking port for solar array installation on the sixth Station flight and Lab installation on the seventh Station flight. The mission includes four spacewalks for the construction activities. Discovery’s landing is expected Oct. 22 at 2:10 p.m. EDT

KSC00pp1566

NASA Image and Video Library

2000-10-11

STS-92 Mission Specialist Peter J.K. “Jeff” Wisoff reaches out to shake the hand of Danny Wyatt, KSC NASA Quality Assurance specialist, after completing final check of his launch and entry suit in the White Room before entering Discovery. The White Room is an environmentally controlled area at the end of the Orbiter Access Arm that provides entry to the orbiter as well as emergency egress if needed. The arm remains in the extended position until 7 minutes 24 seconds before launch. Wisoff and the rest of the crew are undertaking the fifth flight to the International Space Station for construction. Discovery carries a payload that includes the Integrated Truss Structure Z-1, first of 10 trusses that will form the backbone of the Space Station, and the third Pressurized Mating Adapter that will provide a Shuttle docking port for solar array installation on the sixth Station flight and Lab installation on the seventh Station flight. The mission includes four spacewalks for the construction activities. Discovery’s landing is expected Oct. 22 at 2:10 p.m. EDT

The Development of a Nonequilibrium Radiative Heat Transfer Computational Model for High Altitude Entry Vehicle Flowfield Methods

NASA Technical Reports Server (NTRS)

Carlson, Leland A.

1995-01-01

This final report will attempt to concisely summarize the activities and accomplishments associated with NASA Grant and to include pertinent documents in an appendix. The project initially had one primary and several secondary objectives. The original primary objective was to couple into the NASA Johnson Space Center (JSC) nonequilibrium chemistry Euler equation entry vehicle flowfield code, INEQ3D, the Texas A&M University (TAMU) local thermodynamic nonequilibrium (LTNE) radiation model. This model had previously been developed and verified under NASA Langley and NASA Johnson sponsorship as part of a viscous shock layer entry vehicle flowfield code. The secondary objectives were: (1) to investigate the necessity of including the radiative flux term in the vibrational-electron-electronic (VEE) energy equation as well as in the global energy equation, (2) to determine the importance of including the small net change in electronic energy between products and reactants which occurs during a chemical reaction, and (3) to study the effect of atom-atom impact ionization reactions on entry vehicle nonequilibrium flowfield chemistry and radiation. For each, of these objectives, it was assumed that the code would be applicable to lunar return entry conditions, i.e. altitude above 75 km, velocity greater, than 11 km/sec, where nonequilibrium chemistry and radiative heating phenomena would be significant. In addition, it was tacitly assumed that as part of the project the code would be applied to a variety of flight conditions and geometries.

Precourt prepares for entry seated at the commander's station

NASA Image and Video Library

1997-06-05

STS084-318-035 (15-24 May 1997) --- Attired in the partial pressure launch and entry garment, astronaut Charles J. Precourt, commander, performs final checkout procedures prior to the re-entry phase of the STS-84 mission. The photo was taken with a 35mm camera by one of the Space Shuttle Atlantis' rear station-seated crewmembers.

Effect of A-Level Subject Choice and Entry Tariff on Final Degree and Level 1 Performance in Biosciences

ERIC Educational Resources Information Center

King, Nicola C.; Aves, Stephen J.

2012-01-01

Following the publication of the higher education white paper increasing entry tariff and widening participation have become even more important issues for universities. This report examines the relationship between entry tariff and undergraduate achievement in Biosciences at the University of Exeter. We show that, whilst there is a significant…

Adventures in Parallel Processing: Entry, Descent and Landing Simulation for the Genesis and Stardust Missions

NASA Technical Reports Server (NTRS)

Lyons, Daniel T.; Desai, Prasun N.

2005-01-01

This paper will describe the Entry, Descent and Landing simulation tradeoffs and techniques that were used to provide the Monte Carlo data required to approve entry during a critical period just before entry of the Genesis Sample Return Capsule. The same techniques will be used again when Stardust returns on January 15, 2006. Only one hour was available for the simulation which propagated 2000 dispersed entry states to the ground. Creative simulation tradeoffs combined with parallel processing were needed to provide the landing footprint statistics that were an essential part of the Go/NoGo decision that authorized release of the Sample Return Capsule a few hours before entry.

32 CFR 245.27 - Data entry.

Code of Federal Regulations, 2014 CFR

2014-07-01

... 32 National Defense 2 2014-07-01 2014-07-01 false Data entry. 245.27 Section 245.27 National... Under ESCAT § 245.27 Data entry. Aircraft will file IFR or VFR flight plans, assigned a discrete... entered in the remarks section of the flight plan. The EATPL number will be passed with flight plan data...

32 CFR 245.27 - Data entry.

Code of Federal Regulations, 2013 CFR

2013-07-01

... 32 National Defense 2 2013-07-01 2013-07-01 false Data entry. 245.27 Section 245.27 National... Under ESCAT § 245.27 Data entry. Aircraft will file IFR or VFR flight plans, assigned a discrete... entered in the remarks section of the flight plan. The EATPL number will be passed with flight plan data...

32 CFR 245.27 - Data entry.

Code of Federal Regulations, 2012 CFR

2012-07-01

... 32 National Defense 2 2012-07-01 2012-07-01 false Data entry. 245.27 Section 245.27 National... Under ESCAT § 245.27 Data entry. Aircraft will file IFR or VFR flight plans, assigned a discrete... entered in the remarks section of the flight plan. The EATPL number will be passed with flight plan data...

32 CFR 245.27 - Data entry.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 32 National Defense 2 2010-07-01 2010-07-01 false Data entry. 245.27 Section 245.27 National... Under ESCAT § 245.27 Data entry. Aircraft will file IFR or VFR flight plans, assigned a discrete... entered in the remarks section of the flight plan. The EATPL number will be passed with flight plan data...

32 CFR 245.27 - Data entry.

Code of Federal Regulations, 2011 CFR

2011-07-01

... 32 National Defense 2 2011-07-01 2011-07-01 false Data entry. 245.27 Section 245.27 National... Under ESCAT § 245.27 Data entry. Aircraft will file IFR or VFR flight plans, assigned a discrete... entered in the remarks section of the flight plan. The EATPL number will be passed with flight plan data...

Overview of the MEDLI Project

NASA Technical Reports Server (NTRS)

Gazarik, Michael J.; Hwang, Helen; Little, Alan; Cheatwood, Neil; Wright, Michael; Herath, Jeff

2007-01-01

The Mars Science Laboratory Entry, Descent, and Landing Instrumentation (MEDLI) Project's objectives are to measure aerothermal environments, sub-surface heatshield material response, vehicle orientation, and atmospheric density for the atmospheric entry and descent phases of the Mars Science Laboratory (MSL) entry vehicle. The flight science objectives of MEDLI directly address the largest uncertainties in the ability to design and validate a robust Mars entry system, including aerothermal, aerodynamic and atmosphere models, and thermal protection system (TPS) design. The instrumentation suite will be installed in the heatshield of the MSL entry vehicle. The acquired data will support future Mars entry and aerocapture missions by providing measured atmospheric data to validate Mars atmosphere models and clarify the design margins for future Mars missions. MEDLI thermocouple and recession sensor data will significantly improve the understanding of aeroheating and TPS performance uncertainties for future missions. MEDLI pressure data will permit more accurate trajectory reconstruction, as well as separation of aerodynamic and atmospheric uncertainties in the hypersonic and supersonic regimes. This paper provides an overview of the project including the instrumentation design, system architecture, and expected measurement response.

2014 Summer Series - Ethiraj Venkatapathy - Mary Poppins Approach to Human Mars Mission Entry, Descent and Landing

NASA Image and Video Library

2014-06-17

NASA is investing in a number of technologies to extend Entry, Descent and Landing (EDL) capabilities to enable Human Missions to Mars. These technologies will also enable robotic Science missions. Human missions will require landing payloads of 10?s of metric tons, not possible with today's technology. Decelerating from entry speeds around 15,000 miles per hour to landing in a matter of minutes will require very large drag or deceleration. The one way to achieve required deceleration is to deploy a large surface that can be stowed during launch and deployed prior to entry. This talk will highlight a simple concept similar to an umbrella. Though the concept is simple, the size required for human Mars missions and the heating encountered during entry are significant challenges. The mechanically deployable system can also enable robotic science missions to Venus and is also equally applicable for bringing back cube-satellites and other small payloads. The scalable concept called Adaptive Deployable Entry and Placement Technology (ADEPT) is under development and is the focus of this talk.

Overview of the MEDLI Project

NASA Technical Reports Server (NTRS)

Gazarik, Michael J.; Little, Alan; Cheatwood, F. Neil; Wright, Michael J.; Herath, Jeff A.; Martinez, Edward R.; Munk, Michelle; Novak, Frank J.; Wright, Henry S.

2008-01-01

The Mars Science Laboratory Entry, Descent, and Landing Instrumentation (MEDLI) Project s objectives are to measure aerothermal environments, sub-surface heatshield material response, vehicle orientation, and atmospheric density for the atmospheric entry and descent phases of the Mars Science Laboratory (MSL) entry vehicle. The flight science objectives of MEDLI directly address the largest uncertainties in the ability to design and validate a robust Mars entry system, including aerothermal, aerodynamic and atmosphere models, and thermal protection system (TPS) design. The instrumentation suite will be installed in the heatshield of the MSL entry vehicle. The acquired data will support future Mars entry and aerocapture missions by providing measured atmospheric data to validate Mars atmosphere models and clarify the design margins for future Mars missions. MEDLI thermocouple and recession sensor data will significantly improve the understanding of aeroheating and TPS performance uncertainties for future missions. MEDLI pressure data will permit more accurate trajectory reconstruction, as well as separation of aerodynamic and atmospheric uncertainties in the hypersonic and supersonic regimes. This paper provides an overview of the project including the instrumentation design, system architecture, and expected measurement response.

EntrySat: A 3U CubeStat to study the reentry atmospheric environment

NASA Astrophysics Data System (ADS)

Anthony, Sournac; Raphael, Garcia; David, Mimoun; Jeremie, Chaix

2016-04-01

ISAE France Entrysat has for main scientific objective the study of uncontrolled atmospheric re-entry. This project, is developed by ISAE in collaboration with ONERA and University of Toulouse, is funded by CNES, in the overall frame of the QB50 project. This nano-satellite is a 3U Cubesat measuring 34*10*10 cm3, similar to secondary debris produced during the break up of a spacecraft. EntrySat will collect the external and internal temperatures, pressure, heat flux, attitude variations and drag force of the satellite between ≈150 and 90 km before its destruction in the atmosphere, and transmit them during the re-entry using the IRIDIUM satellite network. The result will be compared with the computations of MUSIC/FAST, a new 6-degree of freedom code developed by ONERA to predict the trajectory of space debris. In order to fulfil the scientific objectives, the satellite will acquire 18 re-entry sensors signals, convert them and compress them, thanks to an electronic board developed by ISAE students in cooperation with EREMS. In order to transmit these data every second during the re-entry phase, the satellite will use an IRIDIUM connection. In order to keep a stable enough attitudes during this phase, a simple attitude orbit and control system using magnetotorquers and an inertial measurement unit (IMU) is developed at ISAE by students. A commercial GPS board is also integrated in the satellite into Entry Sat to determine its position and velocity which are necessary during the re-entry phase. This GPS will also be used to synchronize the on-board clock with the real-time UTC data. During the orbital phase (≈2 year) EntrySat measurements will be recorded transmitted through a more classical "UHF/VHF" connection. Preference for presentation: Poster Most suitable session: Author for correspondence: Dr Raphael F. Garcia ISAE 10, ave E. Belin, 31400 Toulouse, France Raphael.GARCIA@isae.fr +33 5 61 33 81 14

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.

MAPS: The Organization of a Spatial Database System Using Imagery, Terrain, and Map Data

DTIC Science & Technology

1983-06-01

segments which share the same pixel position. Finally, in any largo system, a logical partitioning of the database must be performed in order to avoid...34theodore roosevelt memoria entry 0; entry 1: Virginia ’northwest Washington* 2 en 11" ies for "crossover" for ’theodore roosevelt memor i entry 0

Journal of Chinese Society of Astronautics (Selected Articles),

DTIC Science & Technology

1983-03-10

Graphics Disclaimer...................... ..... .. . .. .. . . ... Calculation of Minimum Entry Heat Transfer Shape of a Space * Vehicle , by, Zhou Qi...the best quality copy available. ..- ii CALCULATION OF MINIMUM ENTRY HEAT TRANSFER SHAPE OF A SPACE VEHICLE Zhou Qi cheng ABSTRACT This paper dealt...entry heat transfer shape under specified fineness ratio and total vehicle weight conditions could be obtained using a variational method. Finally, the

ENTRYSAT: A 3U Cubesat to Study the Re-Entry Atmospheric Environment

NASA Astrophysics Data System (ADS)

Garcia, R. F.; Chaix, J.; Mimoun, D.; EntrySat student Team

2014-04-01

The EntrySat is a 3U CubeSat designed to study the uncontrolled atmospheric re-entry. The project, developed by ISAE in collaboration with ONERA, is funded by CNES and is intended to be launched in January 2016, in the context of the QB50 network. The scientific goal is to relate the kinematics of the satellite with the aerothermodynamic environment during re-entry. In particular, data will be compared with the computations of MUSIC/FAST, a new 6-degree of freedom code developed by ONERA to predict the trajectory of space debris. According to these requirements, the satellite will measure the temperature, pressure, heat flux, and drag force during re-entry, as well as the trajectory and attitude of the satellite. One of the major technological challenges is the retrieval of data during the re-entry phase, which will be based on the Iridium satellite network. The system design is based on the use of commercial COTS components, and is mostly developed by students from ISAE. As such, the EntrySat has an important educational value in the formation of young engineers.

The Unparalleled Systems Engineering of MSL's Backup Entry, Descent, and Landing System: Second Chance

NASA Technical Reports Server (NTRS)

Roumeliotis, Chris; Grinblat, Jonathan; Reeves, Glenn

2013-01-01

Second Chance (SECC) was a bare bones version of Mars Science Laboratory's (MSL) Entry Descent & Landing (EDL) flight software that ran on Curiosity's backup computer, which could have taken over swiftly in the event of a reset of Curiosity's prime computer, in order to land her safely on Mars. Without SECC, a reset of Curiosity's prime computer would have lead to catastrophic mission failure. Even though a reset of the prime computer never occurred, SECC had the important responsibility as EDL's guardian angel, and this responsibility would not have seen such success without unparalleled systems engineering. This paper will focus on the systems engineering behind SECC: Covering a brief overview of SECC's design, the intense schedule to use SECC as a backup system, the verification and validation of the system's "Do No Harm" mandate, the system's overall functional performance, and finally, its use on the fateful day of August 5th, 2012.

Risk Assessment During the Final Phase of an Uncontrolled Re-Entry

NASA Astrophysics Data System (ADS)

Gaudel, A.; Hourtolle, C.; Goester, J. F.; Fuentes, N.

2013-09-01

As French National Space Agency, CNES is empowered to monitor compliance with technical regulations of the French Space Operation Act, FSOA, and to take all necessary measures to ensure the safety of people, property, public health and environment for all space operations involving French responsibility at international level.Therefore, CNES developed ELECTRA that calculates the risk for ground population involved in three types of events: rocket launching, controlled re-entry and uncontrolled re-entry. For the first two cases, ELECTRA takes into account degraded cases due to a premature stop of propulsion.Major evolutions were implemented recently on ELECTRA to meet new users' requirements, like the risk assessment during the final phase of uncontrolled re-entry, that can be combined with the computed risk for each country involved by impacts.The purpose of this paper is to provide an overview of the ELECTRA method and main functionalities, and then to highlight these recent improvements.

Development of Supersonic Retro-Propulsion for Future Mars Entry, Descent, and Landing Systems

NASA Technical Reports Server (NTRS)

Edquist, Karl T.; Dyakonov, Artem A.; Shidner, Jeremy D.; Studak, Joseph W.; Tiggers, Michael A.; Kipp, Devin M.; Prakash, Ravi; Trumble, Kerry A.; Dupzyk, Ian C.; Korzun, Ashley M.

2010-01-01

Recent studies have concluded that Viking-era entry system technologies are reaching their practical limits and must be succeeded by new methods capable of delivering large payloads (greater than 10 metric tons) required for human exploration of Mars. One such technology, termed Supersonic Retro-Propulsion, has been proposed as an enabling deceleration technique. However, in order to be considered for future NASA flight projects, this technology will require significant maturation beyond its current state. This paper proposes a roadmap for advancing the component technologies to a point where Supersonic Retro-Propulsion can be reliably used on future Mars missions to land much larger payloads than are currently possible using Viking-based systems. The development roadmap includes technology gates that are achieved through testing and/or analysis, culminating with subscale flight tests in Earth atmosphere that demonstrate stable and controlled flight. The component technologies requiring advancement include large engines capable of throttling, computational models for entry vehicle aerodynamic/propulsive force and moment interactions, aerothermodynamic environments modeling, entry vehicle stability and control methods, integrated systems engineering and analyses, and high-fidelity six degree-of-freedom trajectory simulations. Quantifiable metrics are also proposed as a means to gage the technical progress of Supersonic Retro-Propulsion. Finally, an aggressive schedule is proposed for advancing the technology through sub-scale flight tests at Earth by 2016.

Aerothermodynamic Environments Definition for the Mars Science Laboratory Entry Capsule

NASA Technical Reports Server (NTRS)

Edquist, Karl T.; Dyakonov, Artem A.; Wright, Michael J.; Tang, Chun Y.

2007-01-01

An overview of the aerothermodynamic environments definition status is presented for the Mars Science Laboratory entry vehicle. The environments are based on Navier-Stokes flowfield simulations on a candidate aeroshell geometry and worst-case entry heating trajectories. Uncertainties for the flowfield predictions are based primarily on available ground data since Mars flight data are scarce. The forebody aerothermodynamics analysis focuses on boundary layer transition and turbulent heating augmentation. Turbulent transition is expected prior to peak heating, a first for Mars entry, resulting in augmented heat flux and shear stress at the same heatshield location. Afterbody computations are also shown with and without interference effects of reaction control system thruster plumes. Including uncertainties, analysis predicts that the heatshield may experience peaks of 225 W/sq cm for turbulent heat flux, 0.32 atm for stagnation pressure, and 400 Pa for turbulent shear stress. The afterbody heat flux without thruster plume interference is predicted to be 7 W/sq cm on the backshell and 10 W/sq cm on the parachute cover. If the reaction control jets are fired near peak dynamic pressure, the heat flux at localized areas could reach as high as 76 W/sq cm on the backshell and 38 W/sq cm on the parachute cover, including uncertainties. The final flight environments used for hardware design will be updated for any changes in the aeroshell configuration, heating design trajectories, or uncertainties.

The role of compositionality in standardized problem list generation.

PubMed

Elkin, P L; Tuttle, M; Keck, K; Campbell, K; Atkin, G; Chute, C G

1998-01-01

Compositionality is the ability of a Vocabulary System to record non-atomic strings. In this manuscript we define the types of composition, which can occur. We will then propose methods for both server based and client-based composition. We will differentiate the terms Pre-Coordination, Post-Coordination, and User-Directed Coordination. A simple grammar for the recording of terms with concept level identification will be presented, with examples from the Unified Medical Language System's (UMLS) Metathesaurus. We present an implementation of a Window's NT based client application and a remote Internet Based Vocabulary Server, which makes use of this method of compositionality. Finally we will suggest a research agenda which we believe is necessary to move forward toward a more complete understanding of compositionality. This work has the promise of paving the way toward a robust and complete Problem List Entry Tool.

Forecast and capacity planning for Nogales' ports of entry : [summary].

DOT National Transportation Integrated Search

2009-12-01

This document provides the final report of the activities performed under the project : Nogales POEs Traffic Study: Forecast and Capacity Planning for Nogales Ports of Entry : sponsored by the Arizona Department of Transportation (ADOT) under Gran...

Port-of-entry Advanced Sorting System (PASS) operational test : final report

DOT National Transportation Integrated Search

1998-12-01

In 1992 the Oregon Department of Transportation undertook an operational test of the Port-of-Entry Advanced Sorting System (PASS), which uses a two-way communication automatic vehicle identification system, integrated with weigh-in-motion, automatic ...

77 FR 19642 - Low Enriched Uranium From France: Final Results of Antidumping Duty Changed Circumstances Review

Federal Register 2010, 2011, 2012, 2013, 2014

2012-04-02

... in U.S. customs territory, and (ii) are re-exported within eighteen (18) months of entry of the LEU... amend the scope of the order and to extend the deadline for the re-exportation of this sole LEU entry... transporter(s) while in U.S. customs territory, and (ii) are re-exported within eighteen (18) months of entry...

Guidance, Navigation, and Control Techniques and Technologies for Active Satellite Removal

NASA Astrophysics Data System (ADS)

Ortega Hernando, Guillermo; Erb, Sven; Cropp, Alexander; Voirin, Thomas; Dubois-Matra, Olivier; Rinalducci, Antonio; Visentin, Gianfranco; Innocenti, Luisa; Raposo, Ana

2013-09-01

This paper shows an internal feasibility analysis to de- orbit a non-functional satellite of big dimensions by the Technical Directorate of the European Space Agency ESA. The paper focuses specifically on the design of the techniques and technologies for the Guidance, Navigation, and Control (GNC) system of the spacecraft mission that will capture the satellite and ultimately will de-orbit it on a controlled re-entry.The paper explains the guidance strategies to launch, rendezvous, close-approach, and capture the target satellite. The guidance strategy uses chaser manoeuvres, hold points, and collision avoidance trajectories to ensure a safe capture. It also details the guidance profile to de-orbit it in a controlled re-entry.The paper continues with an analysis of the required sensing suite and the navigation algorithms to allow the homing, fly-around, and capture of the target satellite. The emphasis is placed around the design of a system to allow the rendezvous with an un-cooperative target, including the autonomous acquisition of both the orbital elements and the attitude of the target satellite.Analysing the capture phase, the paper provides a trade- off between two selected capture systems: the net and the tentacles. Both are studied from the point of view of the GNC system.The paper analyses as well the advanced algorithms proposed to control the final compound after the capture that will allow the controlled de-orbiting of the assembly in a safe place in the Earth.The paper ends proposing the continuation of this work with the extension to the analysis of the destruction process of the compound in consecutive segments starting from the entry gate to the rupture and break up.

The aerodynamic challenges of the design and development of the space shuttle orbiter

NASA Technical Reports Server (NTRS)

Young, J. C.; Underwood, J. M.; Hillje, E. R.; Whitnah, A. M.; Romere, P. O.; Gamble, J. D.; Roberts, B. B.; Ware, G. M.; Scallion, W. I.; Spencer, B., Jr.

1985-01-01

The major aerodynamic design challenge at the beginning of the United States Space Transportation System (STS) research and development phase was to design a vehicle that would fly as a spacecraft during early entry and as an aircraft during the final phase of entry. The design was further complicated because the envisioned vehicle was statically unstable during a portion of the aircraft mode of operation. The second challenge was the development of preflight aerodynamic predictions with an accuracy consistent with conducting a manned flight on the initial orbital flight. A brief history of the early contractual studies is presented highlighting the technical results and management decisions influencing the aerodynamic challenges. The configuration evolution and the development of preflight aerodynamic predictions will be reviewed. The results from the first four test flights shows excellent agreement with the preflight aerodynamic predictions over the majority of the flight regimes. The only regimes showing significant disagreement is confined primarily to early entry, where prediction of the basic vehicle trim and the influence of the reaction control system jets on the flow field were found to be deficient. Postflight results are analyzed to explain these prediction deficiencies.

76 FR 18062 - U.S. Securities; Sale and Issue of Marketable Book-Entry Treasury Bills, Notes, and Bonds; Book...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-04-01

...; Sale and Issue of Marketable Book-Entry Treasury Bills, Notes, and Bonds; Book-Entry Treasury Bonds... longer be opened and transfers of securities from other book-entry systems will no longer be [email protected] . SUPPLEMENTARY INFORMATION: Legacy Treasury Direct [supreg] is a book- entry, non...

Design and characterization of ebolavirus GP prehairpin intermediate mimics as drug targets

PubMed Central

Clinton, Tracy R; Weinstock, Matthew T; Jacobsen, Michael T; Szabo-Fresnais, Nicolas; Pandya, Maya J; Whitby, Frank G; Herbert, Andrew S; Prugar, Laura I; McKinnon, Rena; Hill, Christopher P; Welch, Brett D; Dye, John M; Eckert, Debra M; Kay, Michael S

2015-01-01

Ebolaviruses are highly lethal filoviruses that cause hemorrhagic fever in humans and nonhuman primates. With no approved treatments or preventatives, the development of an anti-ebolavirus therapy to protect against natural infections and potential weaponization is an urgent global health need. Here, we describe the design, biophysical characterization, and validation of peptide mimics of the ebolavirus N-trimer, a highly conserved region of the GP2 fusion protein, to be used as targets to develop broad-spectrum inhibitors of ebolavirus entry. The N-trimer region of GP2 is 90% identical across all ebolavirus species and forms a critical part of the prehairpin intermediate that is exposed during viral entry. Specifically, we fused designed coiled coils to the N-trimer to present it as a soluble trimeric coiled coil as it appears during membrane fusion. Circular dichroism, sedimentation equilibrium, and X-ray crystallography analyses reveal the helical, trimeric structure of the designed N-trimer mimic targets. Surface plasmon resonance studies validate that the N-trimer mimic binds its native ligand, the C-peptide region of GP2. The longest N-trimer mimic also inhibits virus entry, thereby confirming binding of the C-peptide region during viral entry and the presence of a vulnerable prehairpin intermediate. Using phage display as a model system, we validate the suitability of the N-trimer mimics as drug screening targets. Finally, we describe the foundational work to use the N-trimer mimics as targets in mirror-image phage display, which will be used to identify d-peptide inhibitors of ebolavirus entry. PMID:25287718

Design and characterization of ebolavirus GP prehairpin intermediate mimics as drug targets.

PubMed

Clinton, Tracy R; Weinstock, Matthew T; Jacobsen, Michael T; Szabo-Fresnais, Nicolas; Pandya, Maya J; Whitby, Frank G; Herbert, Andrew S; Prugar, Laura I; McKinnon, Rena; Hill, Christopher P; Welch, Brett D; Dye, John M; Eckert, Debra M; Kay, Michael S

2015-04-01

Ebolaviruses are highly lethal filoviruses that cause hemorrhagic fever in humans and nonhuman primates. With no approved treatments or preventatives, the development of an anti-ebolavirus therapy to protect against natural infections and potential weaponization is an urgent global health need. Here, we describe the design, biophysical characterization, and validation of peptide mimics of the ebolavirus N-trimer, a highly conserved region of the GP2 fusion protein, to be used as targets to develop broad-spectrum inhibitors of ebolavirus entry. The N-trimer region of GP2 is 90% identical across all ebolavirus species and forms a critical part of the prehairpin intermediate that is exposed during viral entry. Specifically, we fused designed coiled coils to the N-trimer to present it as a soluble trimeric coiled coil as it appears during membrane fusion. Circular dichroism, sedimentation equilibrium, and X-ray crystallography analyses reveal the helical, trimeric structure of the designed N-trimer mimic targets. Surface plasmon resonance studies validate that the N-trimer mimic binds its native ligand, the C-peptide region of GP2. The longest N-trimer mimic also inhibits virus entry, thereby confirming binding of the C-peptide region during viral entry and the presence of a vulnerable prehairpin intermediate. Using phage display as a model system, we validate the suitability of the N-trimer mimics as drug screening targets. Finally, we describe the foundational work to use the N-trimer mimics as targets in mirror-image phage display, which will be used to identify D-peptide inhibitors of ebolavirus entry. © 2014 The Protein Society.

KSC-02pd0382

NASA Image and Video Library

2002-04-02

KENNEDY SPACE CENTER, FLA. -- STS-110 Mission Specialist Ellen Ochoa has a final check of her launch and entry suit in preparation for launch April 4. This flight will be her fourth. The STS-110 payload includes the S0 Integrated Truss Structure (ITS), the Canadian Mobile Transporter, power distribution system modules, a heat pipe radiator for cooling, computers and a pair of rate gyroscopes. The 11-day mission is the 13th assembly flight to the ISS and includes four spacewalks to attach the S0 truss to the U.S. Lab Destiny

KSC-02pd0386

NASA Image and Video Library

2002-04-02

KENNEDY SPACE CENTER, FLA. -- STS-110 Mission Specialist Lee Morin undergoes final check of his launch and entry suit. Morin will be taking his first Shuttle flight. The STS-110 payload includes the S0 Integrated Truss Structure (ITS), the Canadian Mobile Transporter, power distribution system modules, a heat pipe radiator for cooling, computers and a pair of rate gyroscopes. The 11-day mission is the 13th assembly flight to the ISS and includes four spacewalks to attach the S0 truss to the U.S. Lab Destiny. Launch is scheduled for April 4

Cargo Movement Operations System (CMOS). Final Software Product Specification Increment 1

DTIC Science & Technology

1991-02-17

NO ( ] COMMENT DISPOSITION: COMMENT STATUS: OPEN [ ] CLOSED [ ] ORIGINATOR CONTROL NUMBER: SPSl-0002 PROGRAM OFFICE CONTROL NUMBER: DATA ITEM DISCREPANCY WORKSHEET CDRI NUMBER: A014-02 DATE: 02/17/91 ORIGINATOR NAME: Vivian L. Martin OFFICE SYMBOL: SAIC TELEPHONE NUMBER: 272-2999 SUBSTANTIVE: X EDITORIAL: PAGE NUMBER: E-1 PARA NUMBER: 10. COMMENT OR RECOMMENDED CHANGE: Footnote the AUTOEXEC.BAT entry to indicate that it is identified as CUlAO001 in the SDD (20 Dec 90). RATIONALE: This will synchronize the SPS with the SDD. CMOS PMO ACCEPTS

Entry, Descent, and Landing With Propulsive Deceleration

NASA Technical Reports Server (NTRS)

Palaszewski, Bryan

2012-01-01

The future exploration of the Solar System will require innovations in transportation and the use of entry, descent, and landing (EDL) systems at many planetary landing sites. The cost of space missions has always been prohibitive, and using the natural planetary and planet s moons atmospheres for entry, descent, and landing can reduce the cost, mass, and complexity of these missions. This paper will describe some of the EDL ideas for planetary entry and survey the overall technologies for EDL that may be attractive for future Solar System missions.

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.

Safety concerns for first entry operations of orbiting spacecraft

NASA Technical Reports Server (NTRS)

Wilson, Steven H.; Limero, Thomas F.; James, John T.

1994-01-01

The Space Station Freedom crew will face operational problems unique to the spacecraft environment due to the absence of convection currents and the confined atmosphere within the habitable modules. Airborne contaminants from the materials offgassing or contingency incidents like thermodegradation may accumulate until they reach hazardous concentrations. Flow modeling and experiences from previous space flight missions confirm that caution must be exercised during first-entry operations. A review of the first-entry procedures performed during the Skylab Program will be presented to highlight the necessity for carefully planned operations. Many of the environmental conditions that can be expected on the Space Station are analogous to those which exist in confined storage or work spaces in the industrial setting. Experience with closed-loop environmental operations (e.g., atmospheric control of submarines) have also demonstrated that the buildup of trace contaminant gases could result in conditions that lead to mission termination or loss of crew. Consequently, some first-entry issues for the Station can be addressed by comparing them to familiar techniques developed on Earth. The instruments of the Environmental Health System (EHS) will provide the necessary monitoring capability to protect crew health and safety during the planned first-entry procedures of the MTC phase of the SSF Program. The authors of this paper will describe those procedures and will cite an example of the consequences when proper first-entry procedures are not followed.

KSC-2014-4398

NASA Image and Video Library

2014-10-13

CAPE CANAVERAL, Fla. – Inside the Launch Abort System Facility at NASA's Kennedy Space Center in Florida, a technician on a work platform carefully removes the window covers on Orion before the fourth and final Ogive panel is installed around the spacecraft and Launch Abort System. The Ogive panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The work marked the final major assembly steps for the spacecraft before it is transported to Space Launch Complex 37 at Cape Canaveral Air Force Station in November. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Ben Smegelsky

KSC-2014-2867

NASA Image and Video Library

2014-06-08

CAPE CANAVERAL, Fla. -- Inside the Operations and Checkout Building high bay at NASA's Kennedy Space Center in Florida, the Orion service module has been secured in the Final Assembly and System Testing, or FAST, cell. The Orion crew module will be stacked on the service module in the FAST cell and then both modules will be put through their final system tests for Exploration Flight Test-1, or EFT-1, before rolling out of the facility for integration with the United Launch Alliance Delta IV Heavy rocket. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion, EFT-1, is scheduled to launch later this year atop a Delta IV rocket from Cape Canaveral Air Force Station in Florida to an altitude of 3,600 miles above the Earth's surface. The two-orbit, four-hour flight test will help engineers evaluate the systems critical to crew safety including the heat shield, parachute system and launch abort system. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Glenn Benson

KSC-2014-2866

NASA Image and Video Library

2014-06-08

CAPE CANAVERAL, Fla. -- Inside the Operations and Checkout Building high bay at NASA's Kennedy Space Center in Florida, the Orion service module has been secured in the Final Assembly and System Testing, or FAST, cell. The Orion crew module will be stacked on the service module in the FAST cell and then both modules will be put through their final system tests for Exploration Flight Test-1, or EFT-1, before rolling out of the facility for integration with the United Launch Alliance Delta IV Heavy rocket. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion, EFT-1, is scheduled to launch later this year atop a Delta IV rocket from Cape Canaveral Air Force Station in Florida to an altitude of 3,600 miles above the Earth's surface. The two-orbit, four-hour flight test will help engineers evaluate the systems critical to crew safety including the heat shield, parachute system and launch abort system. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Glenn Benson

Human Mars Lander Design for NASA's Evolvable Mars Campaign

NASA Technical Reports Server (NTRS)

Polsgrove, Tara; Chapman, Jack; Sutherlin, Steve; Taylor, Brian; Fabisinski, Leo; Collins, Tim; Cianciolo Dwyer, Alicia; Samareh, Jamshid; Robertson, Ed; Studak, Bill;

Current Investments in the NASA Entry Systems Modeling Project

NASA Technical Reports Server (NTRS)

Wright, Michael; Barnhardt, Michael; Hughes, Monica

2017-01-01

This talk will provide an overview of investments in the Entry Systems Modeling project, along with some context of where the effort sits in the overall Space Technology EDL Portfolio. Technical highlights, particularly with referent to work on Ablation Modeling, will be given. Future directions will be discussed.

19 CFR 159.10 - Notice of liquidation and date of liquidation for informal, mail, and baggage entries.

Code of Federal Regulations, 2014 CFR

2014-04-01

... the merchandise is released under such an entry free of duty; and (3) The date a free entry is...-rate quota, because of a missing document which, if for free entry, is not produced prior to the... liquidation appearing on the receipt issued for any money collected on the entry will be voided. When the...

19 CFR 159.10 - Notice of liquidation and date of liquidation for informal, mail, and baggage entries.

Code of Federal Regulations, 2011 CFR

2011-04-01

... the merchandise is released under such an entry free of duty; and (3) The date a free entry is...-rate quota, because of a missing document which, if for free entry, is not produced prior to the... liquidation appearing on the receipt issued for any money collected on the entry will be voided. When the...

19 CFR 159.10 - Notice of liquidation and date of liquidation for informal, mail, and baggage entries.

Code of Federal Regulations, 2013 CFR

2013-04-01

... the merchandise is released under such an entry free of duty; and (3) The date a free entry is...-rate quota, because of a missing document which, if for free entry, is not produced prior to the... liquidation appearing on the receipt issued for any money collected on the entry will be voided. When the...

19 CFR 159.10 - Notice of liquidation and date of liquidation for informal, mail, and baggage entries.

Code of Federal Regulations, 2012 CFR

2012-04-01

... the merchandise is released under such an entry free of duty; and (3) The date a free entry is...-rate quota, because of a missing document which, if for free entry, is not produced prior to the... liquidation appearing on the receipt issued for any money collected on the entry will be voided. When the...

The severe acute respiratory syndrome: impact on travel and tourism.

PubMed

Wilder-Smith, Annelies

2006-03-01

SARS and travel are intricately interlinked. Travelers belonged to those primarily affected in the early stages of the outbreak, travelers became vectors of the disease, and finally, travel and tourism themselves became the victims. The outbreak of SARS created international anxiety because of its novelty, its ease of transmission in certain settings, and the speed of its spread through jet travel, combined with extensive media coverage. The psychological impacts of SARS, coupled with travel restrictions imposed by various national and international authorities, have diminished international travel in 2003, far beyond the limitations to truly SARS hit areas. Governments and press, especially in non SARS affected areas, have been slow to strike the right balance between timely and frequent risk communication and placing risk in the proper context. Screening at airport entry points is costly, has a low yield and is not sufficient in itself. The low yield in detecting SARS is most likely due to a combination of factors, such as travel advisories which resulted in reduced travel to and from SARS affected areas, implementation of effective pre-departure screening at airports in SARS-hit countries, and a rapid decline in new cases at the time when screening was finally introduced. Rather than investing in airport screening measures to detect rare infectious diseases, investments should be used to strengthen screening and infection control capacities at points of entry into the healthcare system. If SARS reoccurs, the subsequent outbreak will be smaller and more easily contained if the lessons learnt from the recent epidemic are applied. Lessons learnt during the outbreak in relation to international travel will be discussed.

Applying Foreign Entry Market Strategies to UK Higher Education Transnational Education Models

ERIC Educational Resources Information Center

Lindsay, Victoria; Antoniou, Christos

2016-01-01

We take a multidisciplinary approach mapping the models used by UK higher education (HE) institutions against established international business foreign market entry strategies. We review the conditions in host markets that facilitate market entry and consider how these will determine foreign market entry strategy. We specifically consider four…

19 CFR 181.92 - Definitions and general NAFTA advance ruling practice.

Code of Federal Regulations, 2010 CFR

2010-04-01

... undertaken but has not resulted in any arrival or in the filing of any entry or entry summary or other... arrival, entry or otherwise will be resolved by that office in accordance with the principles and... consideration. (3) Completed NAFTA transactions. A question arising in connection with an entry of merchandise...

19 CFR 181.92 - Definitions and general NAFTA advance ruling practice.

Code of Federal Regulations, 2011 CFR

2011-04-01

... undertaken but has not resulted in any arrival or in the filing of any entry or entry summary or other... arrival, entry or otherwise will be resolved by that office in accordance with the principles and... consideration. (3) Completed NAFTA transactions. A question arising in connection with an entry of merchandise...

19 CFR 181.92 - Definitions and general NAFTA advance ruling practice.

Code of Federal Regulations, 2012 CFR

2012-04-01

... undertaken but has not resulted in any arrival or in the filing of any entry or entry summary or other... arrival, entry or otherwise will be resolved by that office in accordance with the principles and... consideration. (3) Completed NAFTA transactions. A question arising in connection with an entry of merchandise...

7 CFR 319.24-3 - Marking as condition of entry.

Code of Federal Regulations, 2011 CFR

2011-01-01

... INSPECTION SERVICE, DEPARTMENT OF AGRICULTURE FOREIGN QUARANTINE NOTICES Corn Diseases Regulations Governing Entry of Indian Corn Or Maize § 319.24-3 Marking as condition of entry. Every bag or other container of corn offered for entry shall be plainly marked with such numbers or marks as will make it easily...

7 CFR 319.24-3 - Marking as condition of entry.

Code of Federal Regulations, 2010 CFR

2010-01-01

... INSPECTION SERVICE, DEPARTMENT OF AGRICULTURE FOREIGN QUARANTINE NOTICES Corn Diseases Regulations Governing Entry of Indian Corn Or Maize § 319.24-3 Marking as condition of entry. Every bag or other container of corn offered for entry shall be plainly marked with such numbers or marks as will make it easily...

Orion Flight Test-1 Thermal Protection System Instrumentation

NASA Technical Reports Server (NTRS)

Kowal, T. John

2011-01-01

The Orion Crew Exploration Vehicle (CEV) was originally under development to provide crew transport to the International Space Station after the retirement of the Space Shuttle, and to provide a means for the eventual return of astronauts to the Moon. With the current changes in the future direction of the United States human exploration programs, the focus of the Orion project has shifted to the project s first orbital flight test, designated Orion Flight Test 1 (OFT-1). The OFT-1 is currently planned for launch in July 2013 and will demonstrate the Orion vehicle s capability for performing missions in low Earth orbit (LEO), as well as extensibility beyond LEO for select, critical areas. Among the key flight test objectives are those related to validation of the re-entry aerodynamic and aerothermal environments, and the performance of the thermal protection system (TPS) when exposed to these environments. A specific flight test trajectory has been selected to provide a high energy entry beyond that which would be experienced during a typical low Earth orbit return, given the constraints imposed by the possible launch vehicles. This trajectory resulted from a trade study that considered the relative benefit of conflicting objectives from multiple subsystems, and sought to provide the maximum integrated benefit to the re-entry state-of-the-art. In particular, the trajectory was designed to provide: a significant, measureable radiative heat flux to the windward surface; data on boundary transition from laminar to turbulent flow; and data on catalytic heating overshoot on non-ablating TPS. In order to obtain the necessary flight test data during OFT-1, the vehicle will need to have an adequate quantity of instrumentation. A collection of instrumentation is being developed for integration in the OFT-1 TPS. In part, this instrumentation builds upon the work performed for the Mars Science Laboratory Entry, Descent and Landing Instrument (MEDLI) suite to instrument the OFT-1 ablative heat shield. The MEDLI integrated sensor plugs and pressure sensors will be adapted for compatibility with the Orion TPS design. The sensor plugs will provide in-depth temperature data to support aerothermal and TPS model correlation, and the pressure sensors will provide a flush air data system for validation of the entry and descent aerodynamic environments. In addition, a radiometer design will be matured to measure the radiative component of the reentry heating at two locations on the heat shield. For the back shell, surface thermocouple and pressure port designs will be developed and applied which build upon the heritage of the Space Shuttle Program for instrumentation of reusable surface insulation (RSI) tiles. The quantity and location of the sensors has been determined to balance the needs of the reentry disciplines with the demands of the hardware development, manufacturing and integration. Measurements which provided low relative value and presented significant engineering development effort were, unfortunately, eliminated. The final TPS instrumentation has been optimized to target priority test objectives. The data obtained will serve to provide a better understanding of reentry environments for the Orion capsule design, reduce margins, and potentially reduce TPS mass or provide TPS extensibility for alternative missions.

KSC-2011-5550

NASA Image and Video Library

2011-07-13

CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, space shuttle Discovery -- its nose encased in protective plastic, its cockpit windows covered, and strongbacks attached to its payload bay doors -- awaits entry into the Vehicle Assembly Building, or VAB, after rolling from Orbiter Processing Facility-2, or OPF-2. Discovery will be stored inside the VAB for approximately one month while shuttle Atlantis undergoes processing in OPF-2 following its final mission, STS-135. Discovery flew its 39th and final mission, STS-133, in February and March 2011, and currently is being prepared for public display at the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia. For more information about Discovery's Transition and Retirement, visit www.nasa.gov/mission_pages/shuttle/launch/discovery_rss_collection_archive_1.html. Photo credit: NASA/Frankie Martin

7 CFR 1530.109 - Reporting.

Code of Federal Regulations, 2012 CFR

2012-01-01

... AGRICULTURE THE REFINED SUGAR RE-EXPORT PROGRAM, THE SUGAR CONTAINING PRODUCTS RE-EXPORT PROGRAM, AND THE... transaction; (2) The date of the entry, transfer (only a refiner shall report transfers to the Licensing... license number; (5) The country of origin (entry of raw sugar) or final destination (refined exports...

7 CFR 1530.109 - Reporting.

Code of Federal Regulations, 2013 CFR

2013-01-01

... AGRICULTURE THE REFINED SUGAR RE-EXPORT PROGRAM, THE SUGAR CONTAINING PRODUCTS RE-EXPORT PROGRAM, AND THE... transaction; (2) The date of the entry, transfer (only a refiner shall report transfers to the Licensing... license number; (5) The country of origin (entry of raw sugar) or final destination (refined exports...

7 CFR 1530.109 - Reporting.

Code of Federal Regulations, 2014 CFR

2014-01-01

... AGRICULTURE THE REFINED SUGAR RE-EXPORT PROGRAM, THE SUGAR CONTAINING PRODUCTS RE-EXPORT PROGRAM, AND THE... transaction; (2) The date of the entry, transfer (only a refiner shall report transfers to the Licensing... license number; (5) The country of origin (entry of raw sugar) or final destination (refined exports...

7 CFR 1530.109 - Reporting.

Code of Federal Regulations, 2011 CFR

2011-01-01

... AGRICULTURE THE REFINED SUGAR RE-EXPORT PROGRAM, THE SUGAR CONTAINING PRODUCTS RE-EXPORT PROGRAM, AND THE... transaction; (2) The date of the entry, transfer (only a refiner shall report transfers to the Licensing... license number; (5) The country of origin (entry of raw sugar) or final destination (refined exports...

7 CFR 1530.109 - Reporting.

Code of Federal Regulations, 2010 CFR

2010-01-01

... AGRICULTURE THE REFINED SUGAR RE-EXPORT PROGRAM, THE SUGAR CONTAINING PRODUCTS RE-EXPORT PROGRAM, AND THE... transaction; (2) The date of the entry, transfer (only a refiner shall report transfers to the Licensing... license number; (5) The country of origin (entry of raw sugar) or final destination (refined exports...

8 CFR 1.1 - Definitions.

Code of Federal Regulations, 2011 CFR

2011-01-01

... successive re-delegation, the terms mean, to the extent that authority has been delegated to such official... having changed. Such status terminates upon entry of a final administrative order of exclusion... come into the United States at a port-of-entry, or an alien seeking transit through the United States...

75 FR 82243 - Security Zones; Moored Cruise Ships, Port of San Diego, CA

Federal Register 2010, 2011, 2012, 2013, 2014

2010-12-30

...The Coast Guard is establishing a temporary security zone regulation from December 21, 2010, through June 20, 2011. The security zones created by this rule will encompass all navigable waters extending from the surface to the sea floor, within a 100 yard radius around any cruise ship that is moored at any berth within the San Diego port area inside the sea buoys bounding the Port of San Diego. This temporary final rule is necessary to provide for the safety of the cruise ship, vessels, and users of the waterway. Entry into these security zones will be prohibited unless specifically authorized by the Captain of the Port (COTP) San Diego, or his or her designated representative. This rule will also suspend paragraph (b)(2) of 33 CFR 165.1108, a related regulation.

Exploring transduction mechanisms of protein transduction domains (PTDs) in living cells utilizing single-quantum dot tracking (SQT) technology.

PubMed

Suzuki, Yasuhiro

2012-01-01

Specific protein domains known as protein transduction domains (PTDs) can permeate cell membranes and deliver proteins or bioactive materials into living cells. Various approaches have been applied for improving their transduction efficacy. It is, therefore, crucial to clarify the entry mechanisms and to identify the rate-limiting steps. Because of technical limitations for imaging PTD behavior on cells with conventional fluorescent-dyes, how PTDs enter the cells has been a topic of much debate. Utilizing quantum dots (QDs), we recently tracked the behavior of PTD that was derived from HIV-1 Tat (TatP) in living cells at the single-molecule level with 7-nm special precision. In this review article, we initially summarize the controversy on TatP entry mechanisms; thereafter, we will focus on our recent findings on single-TatP-QD tracking (SQT), to identify the major sequential steps of intracellular delivery in living cells and to discuss how SQT can easily provide direct information on TatP entry mechanisms. As a primer for SQT study, we also discuss the latest findings on single particle tracking of various molecules on the plasma membrane. Finally, we discuss the problems of QDs and the challenges for the future in utilizing currently available QD probes for SQT. In conclusion, direct identification of the rate-limiting steps of PTD entry with SQT should dramatically improve the methods for enhancing transduction efficiency.

Two-IMU FDI performance of the sequential probability ratio test during shuttle entry

NASA Technical Reports Server (NTRS)

Rich, T. M.

1976-01-01

Performance data for the sequential probability ratio test (SPRT) during shuttle entry are presented. Current modeling constants and failure thresholds are included for the full mission 3B from entry through landing trajectory. Minimum 100 percent detection/isolation failure levels and a discussion of the effects of failure direction are presented. Finally, a limited comparison of failures introduced at trajectory initiation shows that the SPRT algorithm performs slightly worse than the data tracking test.

The electrical ground support equipment for the ExoMars 2016 DREAMS scientific instrument

NASA Astrophysics Data System (ADS)

Molfese, C.; Schipani, P.; Marty, L.; Esposito, F.; D'Orsi, S.; Mannetta, M.; Debei, S.; Bettanini, C.; Aboudan, A.; Colombatti, G.; Mugnuolo, R.; Marchetti, E.; Pirrotta, S.

2014-08-01

This paper describes the Electrical Ground Support Equipment (EGSE) of the Dust characterization, Risk assessment, and Environment Analyser on the Martian Surface (DREAMS) scientific instrument, an autonomous surface payload package to be accommodated on the Entry, Descendent and landing Module (EDM) of the ExoMars 2016 European Space Agency (ESA) mission. DREAMS will perform several kinds of measurements, such as the solar irradiance with different optical detectors in the UVA band (315-400nm), NIR band (700-1100nm) and in "total luminosity" (200 -1100 nm). It will also measure environmental parameters such as the intensity of the electric field, temperature, pressure, humidity, speed and direction of the wind. The EGSE is built to control the instrument and manage the data acquisition before the integration of DREAMS within the Entry, Descendent and landing Module (EDM) and then to retrieve data from the EDM Central Checkout System (CCS), after the integration. Finally it will support also the data management during mission operations. The EGSE is based on commercial off-the-shelf components and runs custom software. It provides power supply and simulates the spacecraft, allowing the exchange of commands and telemetry according to the protocol defined by the spacecraft prime contractor. This paper describes the architecture of the system, as well as its functionalities to test the DREAMS instrument during all development activities before the ExoMars 2016 launch.

Supporting adolescent girls to stay in school, reduce child marriage and reduce entry into sex work as HIV risk prevention in north Karnataka, India: protocol for a cluster randomised controlled trial.

PubMed

Beattie, Tara S; Bhattacharjee, Parinita; Isac, Shajy; Davey, Calum; Javalkar, Prakash; Nair, Sapna; Thalinja, Raghavendra; Sudhakar, Gautam; Collumbien, Martine; Blanchard, James F; Watts, Charlotte; Moses, Stephen; Heise, Lori

2015-03-25

Low caste adolescent girls living in rural northern Karnataka are at increased risk of school drop-out, child marriage, and entry into sex-work, which enhances their vulnerability to HIV, early pregnancy and adverse maternal and child health outcomes. This protocol describes the evaluation of Samata, a comprehensive, multi-level intervention designed to address these structural drivers of HIV risk and vulnerability. The Samata study is a cluster randomised controlled trial that will be conducted in eighty village clusters (40 intervention; 40 control) in Bijapur and Bagalkot districts in northern Karnataka. The intervention seeks to reach low caste girls and their families; adolescent boys; village communities; high school teachers and school governing committees; and local government officials. All low caste (scheduled caste/tribe) adolescent girls attending 7th standard (final year of primary school) will be recruited into the study in two consecutive waves, one year apart. Girls (n = 2100), their families (n = 2100) and school teachers (n = 650) will be interviewed at baseline and at endline. The study is designed to assess the impact of the intervention on four primary outcomes: the proportion of low caste girls who (i) enter into secondary school; (ii) complete secondary school; (iii) marry before age 15; and (iv) engage in sex before age 15. Observers assessing the outcomes will be blinded to group assignment. The primary outcome will be an adjusted, cluster-level intention to treat analysis, comparing outcomes in intervention and control villages at follow-up. We will also conduct survival analyses for the following secondary outcomes: marriage, sexual debut, pregnancy and entry into sex work. Complementary monitoring and evaluation, qualitative and economic research will be used to explore and describe intervention implementation, the pathways through which change occurs, and the cost-effectiveness of the intervention. This is an innovative trial of a comprehensive intervention to improve the quality of life and reduce HIV vulnerability among marginalised girls in northern Karnataka. The findings will be of interest to programme implementers, policy makers and evaluation researchers working in the development, education, and sexual and reproductive health fields. ClinicalTrials.Gov NCT01996241 . 16th November 2013.

ExoMars 2016 arrives at Mars

NASA Astrophysics Data System (ADS)

Svedhem, Hakan; Vago, Jorge L.; ExoMars Team

2016-10-01

The Trace Gas Orbiter (TGO) and the Schiaparelli Entry, descent and landing Demonstrator Model (EDM) will arrive at Mars on 19 October 2016. The TGO and the EDM are part of the first step of the ExoMars Programme. They will be followed by a Rover and a long lived Surface Platform to be launched in 2020.The EDM is attached to the TGO for the full duration of the cruise to Mars and will be separated three days before arrival at Mars. After separation the TGO will perform a deflection manoeuvre and, on 19 October (during the EDM landing), enter into a highly elliptical near equatorial orbit. TGO will remain in this parking orbit until January 2017, when the orbital plane inclination will be changed to 74 degrees and aerobraking to the final 400 km near circular orbit will start. The final operational orbit is expected to be reached at the end of 2017.The TGO scientific payload consists of four instruments. These are: ACS and NOMAD, both infrared spectrometers for atmospheric measurements in solar occultation mode and in nadir mode, CASSIS, a multichannel camera with stereo imaging capability, and FREND, an epithermal neutron detector for search of subsurface hydrogen. The mass of the TGO is 3700 kg, including fuel. The EDM, with a mass of 600 kg, is mounted on top of the TGO as seen in its launch configuration. The main objective of the EDM is to demonstrate the capability of performing a safe entry, descent and landing on the surface, but it does carry a descent camera and a small battery powered meteorological package that may operate for a few days on the surface.The ExoMars programme is a joint activity by the European Space Agency(ESA) and ROSCOSMOS, Russia. ESA is providing the TGO spacecraft and Schiaparelli (EDM) and two of the TGO instruments and ROSCOSMOS is providing the launcher and the other two TGO instruments. After the arrival of the ExoMars 2020 mission at the surface of Mars, the TGO will handle the communication between the Earth and the Rover and Surface Platform through its (NASA provided) UHF communication system. The 2016 mission was launched by a Russian Proton rocket from Baikonur on 14 March 2016.

Development of Occupational Therapy Proficiency Examinations. Therapist Level, Assistant Level. Final Report.

ERIC Educational Resources Information Center

Professional Examination Service, New York, NY.

Criterion-referenced proficiency examinations have been prepared for entry level occupational therapists and entry level occupational therapy assistants. Item development was based on a task inventory solicited from occupational therapists throughout the country, with six occupational therapists reviewing test development. A small scale pilot test…

In-School Youth Manpower: A Guide to Local Strategies and Methods. Final Report.

ERIC Educational Resources Information Center

Systems Research Inc., Lansing, MI.

Intended for use by individuals responsible for establishing and directing youth school/work programs, this manual presents the following ten functions important in any youth school/work program: enrollee entry, enrollee orientation; employer entry; employer orientation; matching and alignment; program monitoring; counseling; supportive services;…

A Secondary-Level Curriculum in Industrial Electronics and Robotics. Final Report.

ERIC Educational Resources Information Center

Besancon, Francis E.

A curriculum was developed to provide the electromechanical skills necessary to operate and repair industrial robots to students at the secondary and adult vocational levels. To determine requirements for entry-level positions in the robotics industry, manufacturers and employers of industrial robots were contacted. No particular entry-level…

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 system saturation. The comparison of the performance criteria has led to a down select and guidance merger that will take the best ideas from each algorithm to create one skip entry guidance algorithm for the Orion vehicle.

Risk factors associated with academic difficulty in an Australian regionally located medical school.

PubMed

Malau-Aduli, Bunmi S; O'Connor, Teresa; Ray, Robin A; van der Kruk, Yolanda; Bellingan, Michelle; Teague, Peta-Ann

2017-12-28

Despite the highly selective admission processes utilised by medical schools, a significant cohort of medical students still face academic difficulties and are at a higher risk of delayed graduation or outright dismissal. This study used survival analysis to identify the non-academic and academic risk factors (and their relative risks) associated with academic difficulty at a regionally located medical school. Retrospective non-academic and academic entry data for all medical students who were enrolled at the time of the study (2009-2014) were collated and analysed. Non-academic variables included age at commencement of studies, gender, Indigenous status, origin, first in family to go to University (FIF), non-English speaking background (NESB), socio-economic status (SES) and rurality expressed as Australian Standard Geographical Classification-Remoteness Area (ASGC-RA). Academic variables included tertiary entrance exam score expressed as overall position (OP) and interview score. In addition, post-entry mid- and end-of-year summative assessment data in the first and second years of study were collated. The results of the survival analysis indicated that FIF, Indigenous and very remote backgrounds, as well as low post-entry Year 1 (final) and Year 2 (mid-year and final) examination scores were strong risk factors associated with academic difficulty. A high proportion of the FIF students who experienced academic difficulty eventually failed and exited the medical program. Further exploratory research will be required to identify the specific needs of this group of students in order to develop appropriate and targeted academic support programs for them. This study has highlighted the need for medical schools to be proactive in establishing support interventions/strategies earlier rather than later, for students experiencing academic difficulty because, the earlier such students can be flagged, the more likely they are able to obtain positive academic outcomes.

Characterization of resistance to rhabdovirus and retrovirus infection in a human myeloid cell line.

PubMed

Boso, Guney; Somia, Nikunj V

2015-01-01

Viruses interact with various permissive and restrictive factors in host cells throughout their replication cycle. Cell lines that are non-permissive to viral infection have been particularly useful in discovering host cell proteins involved in viral life cycles. Here we describe the characterization of a human myeloid leukemia cell line, KG-1, that is resistant to infection by retroviruses and a Rhabdovirus. We show that KG-1 cells are resistant to infection by Vesicular Stomatits Virus as well as VSV Glycoprotein (VSVG) pseudotyped retroviruses due to a defect in binding. Moreover our results indicate that entry by xenotropic retroviral envelope glycoprotein RD114 is impaired in KG-1 cells. Finally we characterize a post- entry block in the early phase of the retroviral life cycle in KG-1 cells that renders the cell line refractory to infection. This cell line will have utility in discovering proteins involved in infection by VSV and HIV-1.

Reusable Launch Vehicle Attitude Control Using a Time-Varying Sliding Mode Control Technique

NASA Technical Reports Server (NTRS)

Shtessel, Yuri B.; Zhu, J. Jim; Daniels, Dan; Jackson, Scott (Technical Monitor)

2002-01-01

In this paper we present a time-varying sliding mode control (TVSMC) technique for reusable launch vehicle (RLV) attitude control in ascent and entry flight phases. In ascent flight the guidance commands Euler roll, pitch and yaw angles, and in entry flight it commands the aerodynamic angles of bank, attack and sideslip. The controller employs a body rate inner loop and the attitude outer loop, which are separated in time-scale by the singular perturbation principle. The novelty of the TVSMC is that both the sliding surface and the boundary layer dynamics can be varied in real time using the PD-eigenvalue assignment technique. This salient feature is used to cope with control command saturation and integrator windup in the presence of severe disturbance or control effector failure, which enhances the robustness and fault tolerance of the controller. The TV-SMC ascent and descent designs are currently being tested with high fidelity, 6-DOF dispersion simulations. The test results will be presented in the final version of this paper.

Finite Element Modeling and Analysis of Mars Entry Aeroshell Baseline Concept

NASA Technical Reports Server (NTRS)

Ahmed, Samee W.; Lane, Brittney M.

2017-01-01

The structure that is developed and analyzed in this project must be able to survive all the various load conditions that it will encounter along its course to Mars with the minimal amount of weight and material. At this stage, the goal is to study the capability of the structure using a finite element model (FEM). This FEM is created using a python script, and is numerically solved in Nastran. The purpose of the model is to achieve an optimization of mass given specific constraints on launch and entry. The generation and analysis of the baseline Rigid Mid-Range Lift to Drag Ratio Aeroshell model is a continuation and an improvement on previous work done for the FEM. The model is generated using Python programming with the axisymmetric placement of nodes for beam and shell elements. The shells are assigned a honeycomb sandwich material with an aluminum honeycomb core and composite face sheets, and the beams are assigned the same material as the shell face sheets. There are two load cases assigned to the model: Earth launch and Mars entry. The Earth launch case consists of pressure, gravity, and vibration loads, and the Mars entry case consists of just pressure and gravity loads. The Earth launch case was determined to be the driving case, though the analyses are performed for both cases to ensure the constraints are satisfied. The types of analysis performed with the model are design optimization, statics, buckling, normal modes, and frequency response, the last of which is only for the Earth launch load case. The final results indicated that all of the requirements are satisfied except the thermal limits, which could not yet be tested, and the normal modes for the Mars entry. However, the frequency limits during Mars entry are expected to be much higher than the lower frequency limits set for the analysis. In addition, there are still improvements that can be made in order to reduce the weight while still meeting all requirements.

KSC-02pd0384

NASA Image and Video Library

2002-04-02

KENNEDY SPACE CENTER, FLA. -- As he undergoes a final check on his launch and entry suit, STS-110 Mission Specialist Jerry Ross shows his delight in the upcoming launch. Ross will be making a record-breaking seventh Shuttle flight. The STS-110 payload includes the S0 Integrated Truss Structure (ITS), the Canadian Mobile Transporter, power distribution system modules, a heat pipe radiator for cooling, computers and a pair of rate gyroscopes. The 11-day mission is the 13th assembly flight to the ISS and includes four spacewalks to attach the S0 truss to the U.S. Lab Destiny. Launch is scheduled for April 4

KSC-02pd0383

NASA Image and Video Library

2002-04-02

KENNEDY SPACE CENTER, FLA. -- STS-110 Mission Specialist Steven Smith gives a thumbs up for launch as he has a final check of his launch and entry suit. This flight will be his fourth. The STS-110 payload includes the S0 Integrated Truss Structure (ITS), the Canadian Mobile Transporter, power distribution system modules, a heat pipe radiator for cooling, computers and a pair of rate gyroscopes. The 11-day mission is the 13th assembly flight to the ISS and includes four spacewalks to attach the S0 truss to the U.S. Lab Destiny. Launch is scheduled for April 4

75 FR 4911 - Food Stamp Program: Eligibility and Certification Provisions of the Farm Security and Rural...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-01-29

...This final rule implements 11 provisions of the Farm Security and Rural Investment Act of 2002 (FSRIA) that establish new eligibility and certification requirements for the receipt of food stamps. The provisions of the final rule will simplify program administration, allow States greater flexibility, and provide enhanced access to eligible populations. This rule will allow States, at their option, to treat legally obligated child support payments to a non-household member as an income exclusion rather than a deduction; allow a State option to exclude certain types of income and resources that are not counted under the State's Temporary Assistance for Needy Families (TANF) cash assistance or Medicaid programs; replace the current, fixed standard deduction with a deduction that varies according to household size and is adjusted annually for cost-of-living increases; allow States to simplify the Standard Utility Allowance (SUA) if the State elects to use the SUA rather than actual utility costs for all households; allow States to use a standard deduction from income of $143 per month for homeless households with some shelter expenses; allow States to disregard reported changes in deductions during certification periods (except for changes associated with new residence or earned income) until the next recertification; increase the resource limit for households with a disabled member from $2,000 to $3,000 consistent with the limit for households with an elderly member; allow States to extend simplified reporting of changes to all households; require State agencies that have a Web site to post applications on these sites in the same languages that the State uses for its written applications; allow States to extend from the current 3 months up to 5 months the period of time households may receive transitional food stamp benefits when they cease to receive TANF cash assistance; and restore food stamp eligibility to qualified aliens who are otherwise eligible and who are receiving disability benefits regardless of date of entry, are under 18 years of age regardless of date of entry, or have lived in the United States for 5 years as qualified aliens beginning on the date of entry.

CNES-NASA Studies of the Mars Sample Return Orbiter Aerocapture Phase

NASA Technical Reports Server (NTRS)

Fraysse, H.; Powell, R.; Rousseau, S.; Striepe, S.

2000-01-01

A Mars Sample Return (MSR) mission has been proposed as a joint CNES (Centre National d'Etudes Spatiales) and NASA effort in the ongoing Mars Exploration Program. The MSR mission is designed to return the first samples of Martian soil to Earth. The primary elements of the mission are a lander, rover, ascent vehicle, orbiter, and an Earth entry vehicle. The Orbiter has been allocated only 2700 kg on the launch phase to perform its part of the mission. This mass restriction has led to the decision to use an aerocapture maneuver at Mars for the orbiter. Aerocapture replaces the initial propulsive capture maneuver with a single atmospheric pass. This atmospheric pass will result in the proper apoapsis, but a periapsis raise maneuver is required at the first apoapsis. The use of aerocapture reduces the total mass requirement by approx. 45% for the same payload. This mission will be the first to use the aerocapture technique. Because the spacecraft is flying through the atmosphere, guidance algorithms must be developed that will autonomously provide the proper commands to reach the desired orbit while not violating any of the design parameters (e.g. maximum deceleration, maximum heating rate, etc.). The guidance algorithm must be robust enough to account for uncertainties in delivery states, atmospheric conditions, mass properties, control system performance, and aerodynamics. To study this very critical phase of the mission, a joint CNES-NASA technical working group has been formed. This group is composed of atmospheric trajectory specialists from CNES, NASA Langley Research Center and NASA Johnson Space Center. This working group is tasked with developing and testing guidance algorithms, as well as cross-validating CNES and NASA flight simulators for the Mars atmospheric entry phase of this mission. The final result will be a recommendation to CNES on the algorithm to use, and an evaluation of the flight risks associated with the algorithm. This paper will describe the aerocapture phase of the MSR mission, the main principles of the guidance algorithms that are under development, the atmospheric entry simulators developed for the evaluations, the process for the evaluations, and preliminary results from the evaluations.

31 CFR 363.125 - How is payment made on a book-entry savings bond?

Code of Federal Regulations, 2012 CFR

2012-07-01

... 31 Money and Finance:Treasury 2 2012-07-01 2012-07-01 false How is payment made on a book-entry... GOVERNING SECURITIES HELD IN TREASURYDIRECT Book-Entry Savings Bonds Purchased Through TreasuryDirect Payment § 363.125 How is payment made on a book-entry savings bond? We will make payment by the ACH method...

31 CFR 351.63 - How are redemption payments made for my redeemed book-entry Series EE savings bonds?

Code of Federal Regulations, 2010 CFR

2010-07-01

... my redeemed book-entry Series EE savings bonds? 351.63 Section 351.63 Money and Finance: Treasury... PUBLIC DEBT OFFERING OF UNITED STATES SAVINGS BONDS, SERIES EE Book-Entry Series EE Savings Bonds § 351.63 How are redemption payments made for my redeemed book-entry Series EE savings bonds? We will make...

31 CFR 363.125 - How is payment made on a book-entry savings bond?

Code of Federal Regulations, 2013 CFR

2013-07-01

... 31 Money and Finance:Treasury 2 2013-07-01 2013-07-01 false How is payment made on a book-entry... GOVERNING SECURITIES HELD IN TREASURYDIRECT Book-Entry Savings Bonds Purchased Through TreasuryDirect Payment § 363.125 How is payment made on a book-entry savings bond? We will make payment by the ACH method...

31 CFR 363.125 - How is payment made on a book-entry savings bond?

Code of Federal Regulations, 2010 CFR

2010-07-01

... 31 Money and Finance: Treasury 2 2010-07-01 2010-07-01 false How is payment made on a book-entry... GOVERNING SECURITIES HELD IN TREASURYDIRECT Book-Entry Savings Bonds Purchased Through TreasuryDirect Payment § 363.125 How is payment made on a book-entry savings bond? We will make payment by the ACH method...

31 CFR 363.125 - How is payment made on a book-entry savings bond?

Code of Federal Regulations, 2014 CFR

2014-07-01

... 31 Money and Finance: Treasury 2 2014-07-01 2014-07-01 false How is payment made on a book-entry... GOVERNING SECURITIES HELD IN TREASURYDIRECT Book-Entry Savings Bonds Purchased Through TreasuryDirect Payment § 363.125 How is payment made on a book-entry savings bond? We will make payment by the ACH method...

31 CFR 359.48 - How are redemption payments made for my redeemed book-entry Series I savings bonds?

Code of Federal Regulations, 2011 CFR

2011-07-01

... my redeemed book-entry Series I savings bonds? 359.48 Section 359.48 Money and Finance: Treasury... PUBLIC DEBT OFFERING OF UNITED STATES SAVINGS BONDS, SERIES I Book-Entry Series I Savings Bonds § 359.48 How are redemption payments made for my redeemed book-entry Series I savings bonds? We will make...

31 CFR 351.63 - How are redemption payments made for my redeemed book-entry Series EE savings bonds?

Code of Federal Regulations, 2011 CFR

2011-07-01

... my redeemed book-entry Series EE savings bonds? 351.63 Section 351.63 Money and Finance: Treasury... PUBLIC DEBT OFFERING OF UNITED STATES SAVINGS BONDS, SERIES EE Book-Entry Series EE Savings Bonds § 351.63 How are redemption payments made for my redeemed book-entry Series EE savings bonds? We will make...

31 CFR 363.125 - How is payment made on a book-entry savings bond?

Code of Federal Regulations, 2011 CFR

2011-07-01

... 31 Money and Finance:Treasury 2 2011-07-01 2011-07-01 false How is payment made on a book-entry... GOVERNING SECURITIES HELD IN TREASURYDIRECT Book-Entry Savings Bonds Purchased Through TreasuryDirect Payment § 363.125 How is payment made on a book-entry savings bond? We will make payment by the ACH method...

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.

KSC-2011-2654

NASA Image and Video Library

2011-04-01

CAPE CANAVERAL, Fla. -- During a simulated launch countdown, STS-134 Mission Specialist Greg Chamitoff checks the fit of his bright-orange, launch-and-entry suit in the Operations and Checkout Building at NASA's Kennedy Space Center in Florida. Next, Chamitoff and his crewmates will walk out to the waiting Astrovan. As part of the Terminal Countdown Demonstration Test (TCDT), the crew members will ride to the pad in their silver Astrovan and strap into space shuttle Endeavour to practice the steps that will be taken on launch day. Endeavour's six crew members are targeted to launch April 19 at 7:48 p.m. EDT. They will deliver the Express Logistics Carrier-3, Alpha Magnetic Spectrometer-2 (AMS), a high-pressure gas tank, additional spare parts for the Dextre robotic helper and micrometeoroid debris shields to the International Space Station. This will be the final spaceflight for Endeavour. For more information visit, www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts134/index.html. Photo credit: NASA/Kim Shiflett

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.

The entry-level occupational therapy clinical doctorate: advantages, challenges, and international issues to consider.

PubMed

Brown, Ted; Crabtree, Jeffrey L; Mu, Keli; Wells, Joe

2015-04-01

Internationally, occupational therapy education has gone through several paradigm shifts during the last few decades, moving from certificate to diploma to bachelors to masters and now in some instances to clinical doctorate as the entry-level professional credential to practice. In the United States there is a recommendation under consideration by the American Occupational Therapy Association (AOTA) that by 2025, all occupational therapy university programs will move to the clinical doctorate level. It should be noted, however, that the AOTA Board can only make recommendations and it is the Accreditation Council for Occupational Therapy Education (ACOTE) who has regulatory authority to approve such a change. What are the potential implications for the profession, our clients, and funders of occupational therapy services? What are the primary drivers for the move towards the clinical doctorate being the educational entry point? Is the next step in the evolution of occupational therapy education globally a shift to the entry-level clinical doctorate? This article reviews current literature and discusses issues about the occupational therapy entry-level clinical doctorate. The published evidence available about the occupational therapy entry-level clinical doctorate is summarized and the perceived or frequently cited pros and cons of moving to the clinical doctorate as the singular entry point to occupational therapy practice are considered. The potential impacts of the introduction of the clinical doctorate as the entry-to-practice qualification across the United States on the occupational therapy community internationally will be briefly discussed. If the United States moves toward the entry-level clinical doctorate as the only educational starting point for the profession, will other jurisdictions follow suit? Further discourse and investigation of this issue both inside and outside of the United States is needed so that informed decisions can be made.

Predictors of student success in entry-level science courses

NASA Astrophysics Data System (ADS)

Singh, Mamta K.

Although the educational evaluation process is useful and valuable and is supported by the Higher Education Act, a strong research base for program evaluation of college entry-level science courses is still lacking. Studies in science disciplines such as, biology, chemistry, and physics have addressed various affective and demographic factors and their relationships to student achievement. However, the literature contains little information that specifically addresses student biology content knowledge skills (basics and higher order thinking skills) and identifies factors that affect students' success in entry-level college science courses. These gate-keeping courses require detailed evaluation if the goal of an institution is to increase students' performance and success in these courses. These factors are, in fact, a stepping stone for increasing the number of graduates in Science, Technology, Engineering, and Mathematics (STEM) majors. The present study measured students' biology content knowledge and investigated students' performance and success in college biology, chemistry, and physics entry-level courses. Seven variables---gender, ethnicity, high school Grade Point Average (GPA), high school science, college major, school financial aid support, and work hours were used as independent variables and course final performance as a dichotomous dependent variable. The sample comprised voluntary student participants in entry-level science courses. The study attempted to explore eight research questions. Content knowledge assessments, demographic information analysis, multiple regression analysis, and binary logistic regression analysis were used to address research questions. The results suggested that high school GPA was a consistently good predictor of students' performance and success in entry-level science courses. Additionally, high school chemistry was a significant predictor variable for student success in entry-level biology and chemistry courses. Similarly, students' performance and success in entry-level physics courses were influenced by high school physics. Finally, the study developed student success equation with high school GAP and high school chemistry as good predictors of students' success in entry-level science courses.

Determining Performance Levels of Competencies for Job Entry. Final Report. Marketing and Retail Sales Programs.

ERIC Educational Resources Information Center

Hillmer, Warren; And Others

To provide input for curriculum evaluation, a study to identify basic competencies required for entry-level positions in the marketing/merchandising field was conducted in Wisconsin vocational education districts. Marketing and merchandising graduates and their employers were surveyed by mailed questionnaire to determine the degree of performance…

Validation and Development of Competencies for Meeting Planners. Final Report.

ERIC Educational Resources Information Center

Walk, Mary H.

A study was conducted to determine the entry-level requirements for meeting planners. The study benefited from the definition of the body of knowledge that had already been done for a professional meeting planner certificate by the Association of Professional Meeting Planners International. To document the competencies needed for an entry-level…

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.

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

KSC-2014-2863

NASA Image and Video Library

2014-06-06

CAPE CANAVERAL, Fla. -- Inside the Operations and Checkout Building high bay at NASA's Kennedy Space Center in Florida, NASA and Lockheed Martin engineers and technicians monitor the progress as a crane lowers the Orion service module into the Final Assembly and System Testing, or FAST, cell. The Orion crew module will be stacked on the service module in the FAST cell and then both modules will be put through their final system tests for Exploration Flight Test-1, or EFT-1, before rolling out of the facility for integration with the United Launch Alliance Delta IV Heavy rocket. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion, EFT-1, is scheduled to launch later this year atop a Delta IV rocket from Cape Canaveral Air Force Station in Florida to an altitude of 3,600 miles above the Earth's surface. The two-orbit, four-hour flight test will help engineers evaluate the systems critical to crew safety including the heat shield, parachute system and launch abort system. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Glenn Benson

KSC-2014-2855

NASA Image and Video Library

2014-06-06

CAPE CANAVERAL, Fla. -- Inside the Operations and Checkout Building high bay at NASA's Kennedy Space Center in Florida, NASA and Lockheed Martin technicians and engineers prepare to move the Orion service module to the Final Assembly and System Testing, or FAST, cell further down the aisle. The Orion crew module will be stacked on the service module in the FAST cell and then both modules will be put through their final system tests for Exploration Flight Test-1, or EFT-1, prior to rolling out of the facility for integration with the United Launch Alliance Delta IV Heavy rocket. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion, EFT-1, is scheduled to launch later this year atop a Delta IV rocket from Cape Canaveral Air Force Station in Florida to an altitude of 3,600 miles above the Earth's surface. The two-orbit, four-hour flight test will help engineers evaluate the systems critical to crew safety including the heat shield, parachute system and launch abort system. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Glenn Benson

KSC-2014-2862

NASA Image and Video Library

2014-06-06

CAPE CANAVERAL, Fla. -- Inside the Operations and Checkout Building high bay at NASA's Kennedy Space Center in Florida, a Lockheed Martin technician monitors the progress as a crane lowers the Orion service module into the Final Assembly and System Testing, or FAST, cell further down the aisle. The Orion crew module will be stacked on the service module in the FAST cell and then both modules will be put through their final system tests for Exploration Flight Test-1, or EFT-1, before rolling out of the facility for integration with the United Launch Alliance Delta IV Heavy rocket. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion, EFT-1, is scheduled to launch later this year atop a Delta IV rocket from Cape Canaveral Air Force Station in Florida to an altitude of 3,600 miles above the Earth's surface. The two-orbit, four-hour flight test will help engineers evaluate the systems critical to crew safety including the heat shield, parachute system and launch abort system. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Glenn Benson

KSC-2014-2860

NASA Image and Video Library

2014-06-06

CAPE CANAVERAL, Fla. -- Inside the Operations and Checkout Building high bay at NASA's Kennedy Space Center in Florida, NASA and Lockheed Martin engineers and technicians help guide the Orion service module into the Final Assembly and System Testing, or FAST, cell. The Orion crew module will be stacked on the service module in the FAST cell and then both modules will be put through their final system tests for Exploration Flight Test-1, or EFT-1, before rolling out of the facility for integration with the United Launch Alliance Delta IV Heavy rocket. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion, EFT-1, is scheduled to launch later this year atop a Delta IV rocket from Cape Canaveral Air Force Station in Florida to an altitude of 3,600 miles above the Earth's surface. The two-orbit, four-hour flight test will help engineers evaluate the systems critical to crew safety including the heat shield, parachute system and launch abort system. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Glenn Benson

KSC-2014-2861

NASA Image and Video Library

2014-06-06

CAPE CANAVERAL, Fla. -- Inside the Operations and Checkout Building high bay at NASA's Kennedy Space Center in Florida, NASA and Lockheed Martin engineers and technicians monitor the progress as a crane lowers the Orion service module into the Final Assembly and System Testing, or FAST, cell. The Orion crew module will be stacked on the service module in the FAST cell and then both modules will be put through their final system tests for Exploration Flight Test-1, or EFT-1, before rolling out of the facility for integration with the United Launch Alliance Delta IV Heavy rocket. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion, EFT-1, is scheduled to launch later this year atop a Delta IV rocket from Cape Canaveral Air Force Station in Florida to an altitude of 3,600 miles above the Earth's surface. The two-orbit, four-hour flight test will help engineers evaluate the systems critical to crew safety including the heat shield, parachute system and launch abort system. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Glenn Benson

The effects of market structure and payment rate on the entry of private health plans into the Medicare market.

PubMed

Frakt, Austin B; Pizer, Steven D; Feldman, Roger

2012-01-01

Private insurance firms participating in Medicare can offer up to three principal plan types: coordinated care plans (CCPs), prescription drug plans (PDPs), and private fee-for-service (PFFS) plans. Firms can make entry and marketing decisions separately across plan types and geographic regions. In this study, we estimate firm-level models of Medicare private plan entry using data from the years 2007 to 2009. Our models include a measure of market structure and separately identify CCP, PDP, and PFFS entry. We find evidence that entry barriers associated with CCP market concentration affect all three product types. We also find evidence of cross-product competition and common cost or demand factors that make entry with certain product combinations more likely. We predict that the market presence of CCPs and PFFS plans will decrease and that of PDPs will increase in response to payment reductions included in the new health reform law.

KSC-2009-2042

NASA Image and Video Library

2009-03-15

CAPE CANAVERAL, Fla. – In the Operations and Checkout Building at NASA's Kennedy Space Center in Florida, STS-119 Commander Lee Archambault puts on his launch-and-entry suit for the launch of space shuttle Discovery. The crew will be heading for Launch Pad 39A and liftoff of Discovery, scheduled for 7:43 p.m. EDT on March 15. An earlier launch attempt March 11 was scrubbed at 2:36 p.m. due to a gaseous hydrogen leak from the external tank at the Ground Umbilical Carrier Plate during tanking. A seven-inch quick disconnect and two seals were replaced. The STS-119 mission is the 28th to the International Space Station and the 125th space shuttle flight. Discovery will deliver the final pair of power-generating solar array wings and the S6 truss segment. Installation of S6 will signal the station's readiness to house a six-member crew for conducting increased science. Photo credit: NASA/Kim Shiflett

KSC-2009-2034

NASA Image and Video Library

2009-03-15

CAPE CANAVERAL, Fla. – In the Operations and Checkout Building at NASA's Kennedy Space Center in Florida, STS-119 Mission Specialist Joseph Acaba is helped putting on his boots with his launch-and-entry suit. The crew will be heading for Launch Pad 39A and liftoff of space shuttle Discovery, scheduled for 7:43 p.m. EDT on March 15. An earlier launch attempt March 11 was scrubbed at 2:36 p.m. due to a gaseous hydrogen leak from the external tank at the Ground Umbilical Carrier Plate during tanking. A seven-inch quick disconnect and two seals were replaced. The STS-119 mission is the 28th to the International Space Station and the 125th space shuttle flight. Discovery will deliver the final pair of power-generating solar array wings and the S6 truss segment. Installation of S6 will signal the station's readiness to house a six-member crew for conducting increased science. Photo credit: NASA/Kim Shiflett

KSC-2009-2041

NASA Image and Video Library

2009-03-15

CAPE CANAVERAL, Fla. – In the Operations and Checkout Building at NASA's Kennedy Space Center in Florida, STS-119 Pilot Tony Antonelli puts on his launch-and-entry suit for the launch of space shuttle Discovery. The crew will be heading for Launch Pad 39A and liftoff of Discovery, scheduled for 7:43 p.m. EDT on March 15. An earlier launch attempt March 11 was scrubbed at 2:36 p.m. due to a gaseous hydrogen leak from the external tank at the Ground Umbilical Carrier Plate during tanking. A seven-inch quick disconnect and two seals were replaced. The STS-119 mission is the 28th to the International Space Station and the 125th space shuttle flight. Discovery will deliver the final pair of power-generating solar array wings and the S6 truss segment. Installation of S6 will signal the station's readiness to house a six-member crew for conducting increased science. Photo credit: NASA/Kim Shiflett

KSC-2009-2036

NASA Image and Video Library

2009-03-15

CAPE CANAVERAL, Fla. – In the Operations and Checkout Building at NASA's Kennedy Space Center in Florida, STS-119 Mission Specialist Joseph Acaba has his helmet fitted on his launch-and-entry suit. The crew will be heading for Launch Pad 39A and liftoff of space shuttle Discovery, scheduled for 7:43 p.m. EDT on March 15. An earlier launch attempt March 11 was scrubbed at 2:36 p.m. due to a gaseous hydrogen leak from the external tank at the Ground Umbilical Carrier Plate during tanking. A seven-inch quick disconnect and two seals were replaced. The STS-119 mission is the 28th to the International Space Station and the 125th space shuttle flight. Discovery will deliver the final pair of power-generating solar array wings and the S6 truss segment. Installation of S6 will signal the station's readiness to house a six-member crew for conducting increased science. Photo credit: NASA/Kim Shiflett

More than just immune evasion: Hijacking complement by Plasmodium falciparum.

PubMed

Schmidt, Christoph Q; Kennedy, Alexander T; Tham, Wai-Hong

2015-09-01

Malaria remains one of the world's deadliest diseases. Plasmodium falciparum is responsible for the most severe and lethal form of human malaria. P. falciparum's life cycle involves two obligate hosts: human and mosquito. From initial entry into these hosts, malaria parasites face the onslaught of the first line of host defence, the complement system. In this review, we discuss the complex interaction between complement and malaria infection in terms of hosts immune responses, parasite survival and pathogenesis of severe forms of malaria. We will focus on the role of complement receptor 1 and its associated polymorphisms in malaria immune complex clearance, as a mediator of parasite rosetting and as an entry receptor for P. falciparum invasion. Complement evasion strategies of P. falciparum parasites will also be highlighted. The sexual forms of the malaria parasites recruit the soluble human complement regulator Factor H to evade complement-mediated killing within the mosquito host. A novel evasion strategy is the deployment of parasite organelles to divert complement attack from infective blood stage parasites. Finally we outline the future challenge to understand the implications of these exploitation mechanisms in the interplay between successful infection of the host and pathogenesis observed in severe malaria. Copyright © 2015 Elsevier Ltd. All rights reserved.

76 FR 13703 - New Origin Entry Separation & Containerization Standards

Federal Register 2010, 2011, 2012, 2013, 2014

2011-03-14

... requirements for mailings and the number of pieces required per presort level will remain the same. Except as... for Periodicals piece processing based on the origin entry point. Prepare container (pallet) placards... for a reduction of sack handling and the expedited processing of individual pieces, and will result in...

77 FR 5767 - Application(s) for Duty-Free Entry of Scientific Instruments

Federal Register 2010, 2011, 2012, 2013, 2014

2012-02-06

... x-ray analysis. The data collected will be applied to energy storage and conversion, environmental...: The instrument will be used to study superstructures formed by semiconductor and metal nanoparticles... semiconductors, metals, ceramics, polymers, etc. Justification for Duty-Free Entry: There are no instruments of...

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.

HSV-1 infection of human corneal epithelial cells: receptor-mediated entry and trends of re-infection.

PubMed

Shah, Arpeet; Farooq, Asim V; Tiwari, Vaibhav; Kim, Min-Jung; Shukla, Deepak

2010-11-20

The human cornea is a primary target for herpes simplex virus-1 (HSV-1) infection. The goals of the study were to determine the cellular modalities of HSV-1 entry into human corneal epithelial (HCE) cells. Specific features of the study included identifying major entry receptors, assessing pH dependency, and determining trends of re-infection. A recombinant HSV-1 virus expressing beta-galactosidase was used to ascertain HSV-1 entry into HCE cells. Viral replication within cells was confirmed using a time point plaque assay. Lysosomotropic agents were used to test for pH dependency of entry. Flow cytometry and immunocytochemistry were used to determine expression of three cellular receptors--nectin-1, herpesvirus entry mediator (HVEM), and paired immunoglobulin-like 2 receptor alpha (PILR-a). The necessity of these receptors for viral entry was tested using antibody-blocking. Finally, trends of re-infection were investigated using viral entry assay and flow cytometry post-primary infection. Cultured HCE cells showed high susceptibility to HSV-1 entry and replication. Entry was demonstrated to be pH dependent as blocking vesicular acidification decreased entry. Entry receptors expressed on the cell membrane include nectin-1, HVEM, and PILR-α. Receptor-specific antibodies blocked entry receptors, reduced viral entry and indicated nectin-1 as the primary receptor used for entry. Cells re-infected with HSV-1 showed a decrease in entry, which was correlated to decreased levels of nectin-1 as demonstrated by flow cytometry. HSV-1 is capable of developing an infection in HCE cells using a pH dependent entry process that involves primarily nectin-1 but also the HVEM and PILR-α receptors. Re-infected cells show decreased levels of entry, correlated with a decreased level of nectin-1 receptor expression.

Flexible Ablators: Applications and Arcjet Testing

NASA Technical Reports Server (NTRS)

Arnold, James O.; Venkatapathy, Ethiraj; Beck, Robin A S.; Mcguire, Kathy; Prabhu, Dinesh K.; Gorbunov, Sergey

2011-01-01

Flexible ablators were conceived in 2009 to meet the technology pull for large, human Mars Exploration Class, 23 m diameter hypersonic inflatable aerodynamic decelerators. As described elsewhere, they have been recently undergoing initial technical readiness (TRL) advancement by NASA. The performance limits of flexible ablators in terms of maximum heat rates, pressure and shear remain to be defined. Further, it is hoped that this emerging technology will vastly expand the capability of future NASA missions involving atmospheric entry systems. This paper considers four topics of relevance to flexible ablators: (1) Their potential applications to near/far term human and robotic missions (2) Brief consideration of the balance between heat shield diameter, flexible ablator performance limits, entry vehicle controllability and aft-body shear layer impingement of interest to designers of very large entry vehicles, (3) The approach for developing bonding processes of flexible ablators for use on rigid entry bodies and (4) Design of large arcjet test articles that will enable the testing of flexible ablators in flight-like, combined environments (heat flux, pressure, shear and structural tensile loading). Based on a review of thermal protection system performance requirements for future entry vehicles, it is concluded that flexible ablators have broad applications to conventional, rigid entry body systems and are enabling to large deployable (both inflatable and mechanical) heat shields. Because of the game-changing nature of flexible ablators, it appears that NASA's Office of the Chief Technologist (OCT) will fund a focused, 3-year TRL advancement of the new materials capable of performance in heat fluxes in the range of 200-600 W/sq. cm. This support will enable the manufacture and use of the large-scale arcjet test designs that will be a key element of this OCT funded activity.

Career Assessment, Remediation, Education, Employment, and Re-entry Program (CAREER). El Paso Community College Career Grant. Final Report.

ERIC Educational Resources Information Center

LaFleur, Carol A.

Objectives of the Career Assessment, Remediation, Education, Employment, and Re-entry (CAREER) project were to establish a series of intensive, short-term job training programs using competency-based instruction to serve Hispanic persons who were economically disadvantaged, displaced, unemployed, or underemployed, as well as Hispanic females who…

Transition, Retraining, and Change for Entry. Final Report from July 1, 1983 - August 31, 1984.

ERIC Educational Resources Information Center

VanderLugt, Marilyn J.

Goals of the "Transition, Retraining, and Change for Entry" project were to provide counseling and/or group support for single heads of households or persons entering nontraditional employment and to provide placement services for the target group. A third goal was to disseminate information about the value of and opportunities in…

Study of the Effectiveness of OCR for Decentralized Data Capture and Conversion. Final Report.

ERIC Educational Resources Information Center

Liston, David M.; And Others

The ERIC network conversion to an OCR (Optical Character Recognition) mode of data entry was studied to analyze the potential effectiveness of OCR data entry for future EPC/s (Editorial Processing Centers). Study results are also applicable to any other system involving decentralized bibliographic data capture and conversion functions. The report…

31 CFR 363.55 - May I transfer my book-entry savings bonds to another person?

Code of Federal Regulations, 2010 CFR

2010-07-01

... REGULATIONS GOVERNING SECURITIES HELD IN TREASURYDIRECT Book-Entry Savings Bonds Purchased Through Treasury... a minimum amount of $25. The transfer may only be made as a gift or in response to a final judgment... is a gift or a specified exception. (b) We do not permit the transfer of savings bonds for...

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.

32 CFR 761.11 - Persons: Individual authorizations.

Code of Federal Regulations, 2014 CFR

2014-07-01

... ADMINISTRATION, AND THE TRUST TERRITORY OF THE PACIFIC ISLANDS Entry Authorization § 761.11 Persons: Individual... may be empowered to do or for forwarding the application to the nearest Entry Control Commander...) Applications for entry authorizations will be made on the standard form Statement of Personal History, DD 398...

The Adaptable, Deployable Entry and Placement Technology (ADEPT)

NASA Technical Reports Server (NTRS)

Wercinski, Paul

2017-01-01

The initial system-level development of the nano-ADEPT architecture will culminate in the launch of a 0.7 meter deployed diameter ADEPT sounding rocket flight experiment named, SR-1. Launch is planned for August 2017. The test will utilize the NASA Flight Opportunities Program sounding rocket platform provided by UP Aerospace to launch SR-1 to an apogee over 100 km and achieve re-entry conditions with a peak velocity near Mach 3. The SR-1 flight experiment will demonstrate most of the primary end-to-end mission stages including: launch in a stowed configuration, separation and deployment in exo-atmospheric conditions, and passive ballistic re-entry of a 70-degree half-angle faceted cone geometry.

The Design Process of Physical Security as Applied to a U.S. Border Point of Entry

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

Wagner, G.G.

1998-10-26

This paper describes the design process of physical security as applied to a U.S. Border Port of Entry (PoE). Included in this paper are descriptions of the elements that compose U.S. border security. The physical security design will describe the various elements that make up the process as well as the considerations that must be taken into account when dealing with system integration of those elements. The distinctions between preventing unlawful entry and exit of illegal contraband will be emphasized.

Study on goaf gas control technology of gob-side entry driving

NASA Astrophysics Data System (ADS)

Ren, Qihan; Yuan, Benqing; Li, Qiansi

2018-01-01

The 1112 (1) track gate roadway of Gu Qiao coal mine of Huainan mining group adopt the method of gob-side entry driving, the gas emission is large during the driving of the roadway, the gas in the goaf seriously influences the safe driving of the roadway. Equalizing method, drilling drainage method, jet grouting method and other goaf gas controlling measures has been adopted. Finally, it effectively solves the safety threat of gas in goaf to roadway driving, it provides a good reference for the gas control of the gob-side entry.

Automated Re-Entry System using FNPEG

NASA Technical Reports Server (NTRS)

Johnson, Wyatt R.; Lu, Ping; Stachowiak, Susan J.

2017-01-01

This paper discusses the implementation and simulated performance of the FNPEG (Fully Numerical Predictor-corrector Entry Guidance) algorithm into GNC FSW (Guidance, Navigation, and Control Flight Software) for use in an autonomous re-entry vehicle. A few modifications to FNPEG are discussed that result in computational savings -- a change to the state propagator, and a modification to cross-range lateral logic. Finally, some Monte Carlo results are presented using a representative vehicle in both a high-fidelity 6-DOF (degree-of-freedom) sim as well as in a 3-DOF sim for independent validation.

75 FR 20850 - Submission for OMB Review; Comment Request

Federal Register 2010, 2011, 2012, 2013, 2014

2010-04-21

... in the efforts to make system changes. Grantees will complete systems web-based data entry on goals... grantee and key staff-partner interview 249 2 1.60 797 guide EBHV grantee systems web-based data entry... prevent child maltreatment. An evaluation study will address four domains: (1) Systems change to develop...

30 CFR 75.371 - Mine ventilation plan; contents.

Code of Federal Regulations, 2013 CFR

2013-07-01

... (see § 75.325(a)(3)). (k) The minimum mean entry air velocity in exhausting face ventilation systems where coal is being cut, mined, drilled for blasting, or loaded, if the velocity will be less than 60... loaded, where at least 60 feet per minute or some other minimum mean entry air velocity will be...

30 CFR 75.371 - Mine ventilation plan; contents.

Code of Federal Regulations, 2014 CFR

2014-07-01

... (see § 75.325(a)(3)). (k) The minimum mean entry air velocity in exhausting face ventilation systems where coal is being cut, mined, drilled for blasting, or loaded, if the velocity will be less than 60... loaded, where at least 60 feet per minute or some other minimum mean entry air velocity will be...

30 CFR 75.371 - Mine ventilation plan; contents.

Code of Federal Regulations, 2012 CFR

2012-07-01

... (see § 75.325(a)(3)). (k) The minimum mean entry air velocity in exhausting face ventilation systems where coal is being cut, mined, drilled for blasting, or loaded, if the velocity will be less than 60... loaded, where at least 60 feet per minute or some other minimum mean entry air velocity will be...

Mission and Navigation Design for the 2009 Mars Science Laboratory Mission

NASA Technical Reports Server (NTRS)

D'Amario, Louis A.

2008-01-01

NASA s Mars Science Laboratory mission will launch the next mobile science laboratory to Mars in the fall of 2009 with arrival at Mars occurring in the summer of 2010. A heat shield, parachute, and rocket-powered descent stage, including a sky crane, will be used to land the rover safely on the surface of Mars. The direction of the atmospheric entry vehicle lift vector will be controlled by a hypersonic entry guidance algorithm to compensate for entry trajectory errors and counteract atmospheric and aerodynamic dispersions. The key challenges for mission design are (1) develop a launch/arrival strategy that provides communications coverage during the Entry, Descent, and Landing phase either from an X-band direct-to-Earth link or from a Ultra High Frequency link to the Mars Reconnaissance Orbiter for landing latitudes between 30 deg North and 30 deg South, while satisfying mission constraints on Earth departure energy and Mars atmospheric entry speed, and (2) generate Earth-departure targets for the Atlas V-541 launch vehicle for the specified launch/arrival strategy. The launch/arrival strategy employs a 30-day baseline launch period and a 27-day extended launch period with varying arrival dates at Mars. The key challenges for navigation design are (1) deliver the spacecraft to the atmospheric entry interface point (Mars radius of 3522.2 km) with an inertial entry flight path angle error of +/- 0.20 deg (3 sigma), (2) provide knowledge of the entry state vector accurate to +/- 2.8 km (3 sigma) in position and +/- 2.0 m/s (3 sigma) in velocity for initializing the entry guidance algorithm, and (3) ensure a 99% probability of successful delivery at Mars with respect to available cruise stage propellant. Orbit determination is accomplished via ground processing of multiple complimentary radiometric data types: Doppler, range, and Delta-Differential One-way Ranging (a Very Long Baseline Interferometry measurement). The navigation strategy makes use of up to five interplanetary trajectory correction maneuvers to achieve entry targeting requirements. The requirements for cruise propellant usage and atmospheric entry targeting and knowledge are met with ample margins.

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 quantification results from the recent uncontrolled re-entry of the Phobos-Grunt satellite will be presented and discussed. This work performed under the auspices of the U.S. Department of Energy by Lawrence Livermore National Laboratory under Contract DE-AC52-07NA27344.

KSC-2014-4249

NASA Image and Video Library

2014-10-12

CAPE CANAVERAL, Fla. – Installation of four Ogive panels on Orion's Launch Abort System continues inside the Launch Abort System Facility at NASA’s Kennedy Space Center in Florida. The panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The work marked the final major assembly steps for the spacecraft before it is transported to Space Launch Complex 37 at Cape Canaveral Air Force Station in November. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Daniel Casper

Woven Thermal Protection System Based Heat-shield for Extreme Entry Environments Technology (HEEET)

NASA Technical Reports Server (NTRS)

Ellerby, Donald; Venkatapathy, Ethiraj; Stackpoole, Margaret; Chinnapongse, Ronald; Munk, Michelle; Dillman, Robert; Feldman, Jay; Prabhu, Dinesh; Beerman, Adam

2013-01-01

NASA's future robotic missions utilizing an entry system into Venus and the outer planets, namely, Saturn, Uranus, Neptune, result in extremely high entry conditions that exceed the capabilities of state of the art low to mid density ablators such as PICA or Avcoat. Therefore mission planners typically assume the use of a fully dense carbon phenolic heat shield similar to what was flown on Pioneer Venus and Galileo. Carbon phenolic is a robust TPS material however its high density and relatively high thermal conductivity constrain mission planners to steep entries, with high heat fluxes and pressures and short entry durations, in order for CP to be feasible from a mass perspective. The high entry conditions pose challenges for certification in existing ground based test facilities and the longer-term sustainability of CP will continue to pose challenges. In 2012 the Game Changing Development Program (GCDP) in NASA's Space Technology Mission Directorate funded NASA ARC to investigate the feasibility of a Woven Thermal Protection System (WTPS) to meet the needs of NASA's most challenging entry missions. This project was highly successful demonstrating that a Woven TPS solution compares favorably to CP in performance in simulated reentry environments and provides the opportunity to manufacture graded materials that should result in overall reduced mass solutions and enable a much broader set of missions than does CP. Building off the success of the WTPS project GCDP has funded a follow on project to further mature and scale up the WTPS concept for insertion into future NASA robotic missions. The matured WTPS will address the CP concerns associated with ground based test limitations and sustainability. This presentation will briefly discuss results from the WTPS Project and the plans for WTPS maturation into a heat-shield for extreme entry environment.

Woven Thermal Protection System Based Heat-shield for Extreme Entry Environments Technology (HEEET)

NASA Technical Reports Server (NTRS)

Chinnapongse, Ronald; Ellerbe, Donald; Stackpoole, Maragaret; Venkatapathy, Ethiraj; Beerman, Adam; Feldman, Jay; Peterson Keith; Prabhu, Dinesh; Dillman, Robert; Munk, Michelle

2013-01-01

NASA's future robotic missions utilizing an entry system into Venus and the outer planets, namely, Saturn, Uranus, Neptune, result in extremely severe entry conditions that exceed the capabilities of state of the art low to mid density ablators such as PICA or Avcoat. Therefore mission planners typically assume the use of a fully dense carbon phenolic heat shield similar to what was flown on Pioneer Venus and Galileo. Carbon phenolic (CP) is a robust TPS material however its high density and relatively high thermal conductivity constrain mission planners to steep entries, with high heat fluxes and pressures and short entry durations, in order for CP to be feasible from a mass perspective. The high entry conditions pose challenges for certification in existing ground based test facilities and the longer-­-term sustainability of CP will continue to pose challenges. In 2012 the Game Changing Development Program (GCDP) in NASA's Space Technology Mission Directorate funded NASA ARC to investigate the feasibility of a Woven Thermal Protection System (WTPS) to meet the needs of NASA's most challenging entry missions. This project was highly successful demonstrating that a Woven TPS solution compares favorably to CP in performance in simulated reentry environments and provides the opportunity to manufacture graded materials that should result in overall reduced mass solutions and enable a much broader set of missions than does CP. Building off the success of the WTPS project GCDP has funded a follow on project to further mature and scale up the WTPS concept for insertion into future NASA robotic missions. The matured WTPS will address the CP concerns associated with ground based test limitations and sustainability. This presentation will briefly discuss results from the WTPS Project and the plans for WTPS maturation into a heat-­-shield for extreme entry environment.

ExoMars 2016 Status and Future Plans

NASA Astrophysics Data System (ADS)

Svedhem, Håkan; Vago, Jorge

2017-04-01

The ExoMars programme is a joint activity by the European Space Agency(ESA) and ROSCOSMOS, Russia. It consists of the ExoMars 2016 mission, launched 14 March 2016, with the Trace Gas Orbiter, TGO, and the Entry Descent and Landing Demonstrator, EDM, named Schiaparelli, and the ExoMars 2020 mission, to be launched in May 2020, carrying a lander and a rover. TGO and EDM arrived at Mars on 19 October 2016. After a nominal entry and first phase of the descent, the EDM failed at an altitude of about 4 km and fell freely to the surface, near the centre of the landing ellipse in Meridiani Planum. The communication link was maintain up until the failure and a large data set was acquired, allowing for a complete analysis of the first successful part of the mission, and an investigation of the on board anomaly leading to the failure. The TGO spacecraft was inserted into a highly elliptical 4 sol period, near equatorial, capture orbit. Two orbits in late November were dedicated to instrument calibration and initial science observations, where an excellent performance of all instruments could be confirmed. In January 2017 the orbital plane will be changed to its final inclination of 74 degrees and the period will be reduced to one Sol. Early March two orbits are scheduled for another set of instrument observations, after which a long period of aerobraking will commence. The final operational orbit, with a 2 hour period, is expected to be reached early 2018. The TGO scientific payload consists of four instruments. These are: ACS and NOMAD, both infrared spectrometers for atmospheric measurements in solar occultation mode and in nadir mode, CASSIS, a multichannel camera with stereo imaging capability, and FREND, an epithermal neutron detector for search of subsurface hydrogen. The mass of the TGO is 3700 kg, including fuel and the mass of EDM was 600 kg. The EDM was carried to Mars by the TGO and was separated three days before arrival at Mars. This presentation will cover a brief description of the 2016 mission, results from the initial phase since arrival, present status, and future activities.

STS-76 Payload Cmdr Ronald Sega suits up

NASA Technical Reports Server (NTRS)

1996-01-01

STS-76 Payload Commander Ronald M. Sega is donning his launch/entry suit in the Operations and Checkout Building with assistance from a suit technician. The third docking between the Russian Space Station Mir and the U.S. Space Shuttle marks the second trip into space for Sega, who recently served a five-month assignment in Russia as operations director for NASA activities there. Once suitup activities are completed the six-member STS-76 flight crew will depart for Launch Pad 39B, where the Space Shuttle Atlantis is undergoing final preparations for liftoff during an approximately seven-minute launch window opening around 3:13 a.m. EST, March 22.

43 CFR 2524.3 - Time extended to make final proof.

Code of Federal Regulations, 2012 CFR

2012-10-01

... 43 Public Lands: Interior 2 2012-10-01 2012-10-01 false Time extended to make final proof. 2524.3 Section 2524.3 Public Lands: Interior Regulations Relating to Public Lands (Continued) BUREAU OF LAND... Entries Within a Reclamation Project § 2524.3 Time extended to make final proof. When the time for...

43 CFR 2524.3 - Time extended to make final proof.

Code of Federal Regulations, 2013 CFR

2013-10-01

... 43 Public Lands: Interior 2 2013-10-01 2013-10-01 false Time extended to make final proof. 2524.3 Section 2524.3 Public Lands: Interior Regulations Relating to Public Lands (Continued) BUREAU OF LAND... Entries Within a Reclamation Project § 2524.3 Time extended to make final proof. When the time for...

43 CFR 2524.3 - Time extended to make final proof.

Code of Federal Regulations, 2011 CFR

2011-10-01

... 43 Public Lands: Interior 2 2011-10-01 2011-10-01 false Time extended to make final proof. 2524.3 Section 2524.3 Public Lands: Interior Regulations Relating to Public Lands (Continued) BUREAU OF LAND... Entries Within a Reclamation Project § 2524.3 Time extended to make final proof. When the time for...

43 CFR 2524.3 - Time extended to make final proof.

Code of Federal Regulations, 2014 CFR

2014-10-01

... 43 Public Lands: Interior 2 2014-10-01 2014-10-01 false Time extended to make final proof. 2524.3 Section 2524.3 Public Lands: Interior Regulations Relating to Public Lands (Continued) BUREAU OF LAND... Entries Within a Reclamation Project § 2524.3 Time extended to make final proof. When the time for...

76 FR 69755 - National Customs Automation Program Test Concerning Automated Commercial Environment (ACE...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-11-09

... include functionality specific to the filing of entry data for formal and informal consumption entries... three (3) optional data elements to CBP at any time prior to the arrival of the merchandise on the conveyance transporting the cargo to the United States. This data will fulfill merchandise entry requirements...

50 CFR 635.41 - Products denied entry.

Code of Federal Regulations, 2014 CFR

2014-10-01

... Products denied entry. (a) [Reserved] (b) All shipments of tuna or tuna-like species, or their products, in.... (c) All shipments of tuna or tuna-like species, or their products, in any form, harvested in the..., and unregulated fishing will be denied entry into the United States. (d) All shipments of tuna or tuna...

50 CFR 635.41 - Products denied entry.

Code of Federal Regulations, 2012 CFR

2012-10-01

... Products denied entry. (a) [Reserved] (b) All shipments of tuna or tuna-like species, or their products, in.... (c) All shipments of tuna or tuna-like species, or their products, in any form, harvested in the..., and unregulated fishing will be denied entry into the United States. (d) All shipments of tuna or tuna...

50 CFR 635.41 - Products denied entry.

Code of Federal Regulations, 2011 CFR

2011-10-01

... Products denied entry. (a) All shipments of Atlantic bigeye tuna, or its products, in any form, harvested.... (b) All shipments of tuna or tuna-like species, or their products, in any form, harvested in the... record of authorized vessels will be denied entry into the United States. (c) All shipments of tuna or...

50 CFR 635.41 - Products denied entry.

Code of Federal Regulations, 2010 CFR

2010-10-01

... Products denied entry. (a) All shipments of Atlantic bigeye tuna, or its products, in any form, harvested.... (b) All shipments of tuna or tuna-like species, or their products, in any form, harvested in the... record of authorized vessels will be denied entry into the United States. (c) All shipments of tuna or...

7 CFR 319.55-3 - Ports of entry.

Code of Federal Regulations, 2010 CFR

2010-01-01

..., DEPARTMENT OF AGRICULTURE FOREIGN QUARANTINE NOTICES Rice Rules and Regulations § 319.55-3 Ports of entry. (a) For importations of seed or paddy rice from the Republic of Mexico, permits will be issued for entry... Quarantine Programs. (b) For importations of rice straw and rice hulls from all foreign countries, permits...

7 CFR 319.55-3 - Ports of entry.

Code of Federal Regulations, 2011 CFR

2011-01-01

..., DEPARTMENT OF AGRICULTURE FOREIGN QUARANTINE NOTICES Rice Rules and Regulations § 319.55-3 Ports of entry. (a) For importations of seed or paddy rice from the Republic of Mexico, permits will be issued for entry... Quarantine Programs. (b) For importations of rice straw and rice hulls from all foreign countries, permits...

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.

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.

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.

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.

Development of a Screening Methodology for Entry into Medical Technical Training Courses. Final Report for Period October 1975-April 1977.

ERIC Educational Resources Information Center

Leisey, Sandra A.; Guinn, Nancy

At the request of the Air Force School of Aviation Medicine, a project was initiated to evaluate the current screening process used for entry into three medical technical training courses: Aeromedical Specialist, Environmental Health Specialist, and Physiological Training Specialist. A sample of 1,003 students were administered the General…

Simulation of planetary entry radiative heating with a CO2 gasdynamic laser

NASA Technical Reports Server (NTRS)

Lundell, J. H.; Dickey, R. R.; Howe, J. T.

1975-01-01

Heating encountered during entry into the atmospheres of Jupiter, Saturn, and Uranus is described, followed by a discussion of the use of a CO2 gasdynamic laser to simulate the radiative component of the heating. Operation and performance of the laser is briefly described. Finally, results of laser tests of some candidate heat-shield materials are presented.

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.

Mars Pathfinder flight system integration and test.

NASA Astrophysics Data System (ADS)

Muirhead, B. K.

This paper describes the system integration and test experiences, problems and lessons learned during the assembly, test and launch operations (ATLO) phase of the Mars Pathfinder flight system scheduled to land on the surface of Mars on July 4, 1997. The Mars Pathfinder spacecraft consists of three spacecraft systems: cruise stage, entry vehicle and lander. The cruise stage carries the entry and lander vehicles to Mars and is jettisoned prior to entry. The entry vehicle, including aeroshell, parachute and deceleration rockets, protects the lander during the direct entry and reduces its velocity from 7.6 to 0 km/s in stages during the 5 min entry sequence. The lander's touchdown is softened by airbags which are retracted once stopped on the surface. The lander then uprights itself, opens up fully and begins surface operations including deploying its camera and rover. This paper overviews the system design and the results of the system integration and test activities, including the entry, descent and landing subsystem elements. System test experiences including science instruments, the microrover, Sojourner, and software are discussed. The final qualification of the entry, descent and landing subsystems during this period is also discussed.

Mars Science Laboratory Entry Capsule Aerothermodynamics and Thermal Protection System

NASA Technical Reports Server (NTRS)

Edquist, Karl T.; Hollis, Brian R.; Dyakonov, Artem A.; Laub, Bernard; Wright, Michael J.; Rivellini, Tomasso P.; Slimko, Eric M.; Willcockson, William H.

2007-01-01

The Mars Science Laboratory (MSL) spacecraft is being designed to carry a large rover (greater than 800 kg) to the surface of Mars using a blunt-body entry capsule as the primary decelerator. The spacecraft is being designed for launch in 2009 and arrival at Mars in 2010. The combination of large mass and diameter with non-zero angle-of-attack for MSL will result in unprecedented convective heating environments caused by turbulence prior to peak heating. Navier-Stokes computations predict a large turbulent heating augmentation for which there are no supporting flight data1 and little ground data for validation. Consequently, an extensive experimental program has been established specifically for MSL to understand the level of turbulent augmentation expected in flight. The experimental data support the prediction of turbulent transition and have also uncovered phenomena that cannot be replicated with available computational methods. The result is that the flight aeroheating environments predictions must include larger uncertainties than are typically used for a Mars entry capsule. Finally, the thermal protection system (TPS) being used for MSL has not been flown at the heat flux, pressure, and shear stress combinations expected in flight, so a test program has been established to obtain conditions relevant to flight. This paper summarizes the aerothermodynamic definition analysis and TPS development, focusing on the challenges that are unique to MSL.

75 FR 12250 - Notification of the Imposition of Conditions of Entry for Certain Vessels Arriving to the United...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-03-15

... Republic of Timor-Leste. DATES: The requirements announced in this notice will become effective March 29, 2010. ADDRESSES: This notice will be available for inspection and copying at the Docket Management... arriving from ports that are not maintaining effective anti- terrorism measures and to deny entry into the...

8. Detail, typical shedroofed entry on south side. The current ...

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

8. Detail, typical shed-roofed entry on south side. The current project will replace these with similar structures that will allow handicap access to the lean-to portion of the building containing offices, restrooms, and other employee spaces. - Interurban Electric Railway Bridge Yard Shop, Interstate 80 at Alameda County Postmile 2.0, Oakland, Alameda County, CA

76 FR 54788 - Notice of Permanent Closure of Public Lands in Clackamas and Multnomah Counties, OR

Federal Register 2010, 2011, 2012, 2013, 2014

2011-09-02

..., State, and local government permittees and contractors conducting authorized activities; members of.... The BLM will post closure signs at main entry points to this area and take steps to install physical barriers at the BRWMU boundary. The affected lands will be represented as closed to public entry in maps...

ATV-3 undock from ISS

NASA Image and Video Library

2012-09-28

ISS033-E-007940 (28 Sept. 2012) --- European Space Agency's "Edoardo Amaldi" Automated Transfer Vehicle-3 (ATV-3) begins its relative separation from the International Space Station during the Expedition 33 mission. The ATV-3 undocked from the aft port of the Zvezda Service Module at 5:44 p.m. (EDT) on Sept. 28, 2012. The ATV-3 is scheduled to deorbit on Oct. 2 for a fiery re-entry over the Pacific Ocean that will destroy the trash-filled spacecraft. Inside the ATV-3 is the Re-Entry Breakup Recorder that will record various data such as temperature, pressure and speed as the resupply craft burns up during its return to Earth. Experts will use that data to design safer and more predictable destructive re-entry techniques.

ATV-3 undock from ISS

NASA Image and Video Library

2012-09-28

ISS033-E-008016 (28 Sept. 2012) --- European Space Agency's "Edoardo Amaldi" Automated Transfer Vehicle-3 (ATV-3) begins its relative separation from the International Space Station during the Expedition 33 mission. The ATV-3 undocked from the aft port of the Zvezda Service Module at 5:44 p.m. (EDT) on Sept. 28, 2012. The ATV-3 is scheduled to deorbit on Oct. 2 for a fiery re-entry over the Pacific Ocean that will destroy the trash-filled spacecraft. Inside the ATV-3 is the Re-Entry Breakup Recorder that will record various data such as temperature, pressure and speed as the resupply craft burns up during its return to Earth. Experts will use that data to design safer and more predictable destructive re-entry techniques.

ATV-3 undock from ISS

NASA Image and Video Library

2012-09-28

ISS033-E-007980 (28 Sept. 2012) --- European Space Agency's "Edoardo Amaldi" Automated Transfer Vehicle-3 (ATV-3) begins its relative separation from the International Space Station during the Expedition 33 mission. The ATV-3 undocked from the aft port of the Zvezda Service Module at 5:44 p.m. (EDT) on Sept. 28, 2012. The ATV-3 is scheduled to deorbit on Oct. 2 for a fiery re-entry over the Pacific Ocean that will destroy the trash-filled spacecraft. Inside the ATV-3 is the Re-Entry Breakup Recorder that will record various data such as temperature, pressure and speed as the resupply craft burns up during its return to Earth. Experts will use that data to design safer and more predictable destructive re-entry techniques.

ATV-3 undock from ISS

NASA Image and Video Library

2012-09-28

ISS033-E-007915 (28 Sept. 2012) --- European Space Agency's "Edoardo Amaldi" Automated Transfer Vehicle-3 (ATV-3) begins its relative separation from the International Space Station during the Expedition 33 mission. The ATV-3 undocked from the aft port of the Zvezda Service Module at 5:44 p.m. (EDT) on Sept. 28, 2012. The ATV-3 is scheduled to deorbit on Oct. 2 for a fiery re-entry over the Pacific Ocean that will destroy the trash-filled spacecraft. Inside the ATV-3 is the Re-Entry Breakup Recorder that will record various data such as temperature, pressure and speed as the resupply craft burns up during its return to Earth. Experts will use that data to design safer and more predictable destructive re-entry techniques.

ATV-3 undock from ISS

NASA Image and Video Library

2012-09-28

ISS033-E-007920 (28 Sept. 2012) --- European Space Agency's "Edoardo Amaldi" Automated Transfer Vehicle-3 (ATV-3) begins its relative separation from the International Space Station during the Expedition 33 mission. The ATV-3 undocked from the aft port of the Zvezda Service Module at 5:44 p.m. (EDT) on Sept. 28, 2012. The ATV-3 is scheduled to deorbit on Oct. 2 for a fiery re-entry over the Pacific Ocean that will destroy the trash-filled spacecraft. Inside the ATV-3 is the Re-Entry Breakup Recorder that will record various data such as temperature, pressure and speed as the resupply craft burns up during its return to Earth. Experts will use that data to design safer and more predictable destructive re-entry techniques.

Navigation and EDL for the Mars Exploration Rovers

NASA Technical Reports Server (NTRS)

Watkins, Michael M.; Han, Dongsuk

2006-01-01

A viewgraph presentation on Deep Space Navigation, and Entry, Decent, and Landing (EDL) for Mars Exploration Rovers is shown. The contents include: 1) JPL Spacecraft Operating across the Solar System; 2) 2003 - 2004: The Busiest Period in JPL's History; 3) Deep Space Navigation Will Enable Many of the New NASA Missions; 4) What Exactly is Navigation vs. GNC for Deep Space?; 5) Cruise and Approach: Why is Deep Space Navigation So Difficult?; 6) Project Importance of GNC: Landing Site Selection; 7) Planetary Communications and Tracking; 8) Tracking Data Types; 9) Delta Differential One-Way Range (deltaDOR); 10) All Solutions Leading up to TCM-4 Design; 11) Entry Flight Path Sensitivities; 12) MER Navigation Results; 13) Atmospheric Entry Targeting and Delivery; 14) Landing Ellipse Orientation; 15) MER Landing Site Trade Example; 16) Entry, Descent and Landing: Entry Guidance or What Things Do We NOT do for MER Landings (but we will later...); 17) Entering Martian Space 8:29 p.m. PST (ERT); 18) Entry, Descent and Landing; 19) Entry, Descent and Landing: Terminal Guidance; 20) The Challenge Going from 12,000 mph to Zero in Less Than Six Minutes; 21) Spirit Landing Location; 22) Entry, Descent and Landing: The Future; 23) Powered Descent Time-Line; and 24) Updated Sky Crane Maneuver Description. A short summary is also given on planetary guidance, navigation and control as it pertains to EDL systems

Aerodynamic and Aerothermal TPS Instrumentation Reference Guide

NASA Technical Reports Server (NTRS)

Woollard, Bryce A.; Braun, Robert D.; Bose, Deepack

2016-01-01

The hypersonic regime of planetary entry combines the most severe environments that an entry vehicle will encounter with the greatest amount of uncertainty as to the events unfolding during that time period. This combination generally leads to conservatism in the design of an entry vehicle, specifically that of the thermal protection system (TPS). Each planetary entry provides a valuable aerodynamic and aerothermal testing opportunity; the utilization of this opportunity is paramount in better understanding how a specific entry vehicle responds to the demands of the hypersonic entry environment. Previous efforts have been made to instrument entry vehicles in order to collect data during the entry period and reconstruct the corresponding vehicle response. The purpose of this paper is to cumulatively document past TPS instrumentation designs for applicable planetary missions, as well as to list pertinent results and any explainable shortcomings.

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

Diversion at re-entry using criminogenic CBT: Review and prototypical program development.

PubMed

Heilbrun, Kirk; Pietruszka, Victoria; Thornewill, Alice; Phillips, Sarah; Schiedel, Rebecca

2017-09-01

Society and the criminal justice system prioritize the reduction of reoffending risk as part of any criminal justice intervention. The Sequential Intercept Model identifies five points of interception at which justice-involved individuals can be diverted into a more rehabilitative alternative: (1) law enforcement/emergency services; (2) booking/initial court hearings; (3) jails/courts; (4) re-entry; and (5) community corrections/community support. The present article focuses on diversion as part of Intercept 5 - re-entry planning and specialized services in the community. We describe the challenges associated with diversion at this stage, and review the relevant research. Next, we describe a "criminogenic cognitive behavioral therapy" project that has been developed and implemented as part of a federal re-entry court. Finally, we discuss the implications of the challenges of intervention at this stage, and the recently developed "Re-entry Project," for research, policy, and practice. Copyright © 2017 John Wiley & Sons, Ltd.

Re-entry Adjustment and Job Embeddedness: The Mediating Role of Professional Identity in Indonesian Returnees.

PubMed

Andrianto, Sonny; Jianhong, Ma; Hommey, Confidence; Damayanti, Devi; Wahyuni, Honey

2018-01-01

The present study examined the relationship between difficulty in re-entry adjustment and job embeddedness, considering the mediating role of sense of professional identity. The online data on demographic characteristics, difficulty on re-entry adjustment, sense of professional identity, and job embeddedness were collected from 178 Indonesian returnees from multiple organizations. The results showed that difficulty in re-entry adjustment was a significant predictor of a sense of professional identity; a sense of professional identity was a significant predictor of job embeddedness. Furthermore, sense of professional identity is an effective mediating variable, bridging the relationship between post-return conditions to the home country and work atmosphere. Finally, the key finding of this study was that sense of professional identity mediated the effect of difficulty in re-entry adjustment on job embeddedness. The theoretical and practical implications, study limitations, and future research needs of our findings are noted.

Root Architecture Responses: In Search of Phosphate1

PubMed Central

Kanno, Satomi; Nussaume, Laurent

2014-01-01

Soil phosphate represents the only source of phosphorus for plants and, consequently, is its entry into the trophic chain. This major component of nucleic acids, phospholipids, and energy currency of the cell (ATP) can limit plant growth because of its low mobility in soil. As a result, root responses to low phosphate favor the exploration of the shallower part of the soil, where phosphate tends to be more abundant, a strategy described as topsoil foraging. We will review the diverse developmental strategies that can be observed among plants by detailing the effect of phosphate deficiency on primary and lateral roots. We also discuss the formation of cluster roots: an advanced adaptive strategy to cope with low phosphate availability observed in a limited number of species. Finally, we will put this work into perspective for future research directions. PMID:25341534

Aerothermodynamic Design of the Mars Science Laboratory Backshell and Parachute Cone

NASA Technical Reports Server (NTRS)

Edquist, Karl T.; Dyakonov, Artem A.; Wright, Michael J.; Tang, Chun Y.

2009-01-01

Aerothermodynamic design environments are presented for the Mars Science Laboratory entry capsule backshell and parachute cone. The design conditions are based on Navier-Stokes flowfield simulations on shallow (maximum total heat load) and steep (maximum heat flux) design entry trajectories from a 2009 launch. Transient interference effects from reaction control system thruster plumes were included in the design environments when necessary. The limiting backshell design heating conditions of 6.3 W/sq cm for heat flux and 377 J/sq cm for total heat load are not influenced by thruster firings. Similarly, the thrusters do not affect the parachute cover lid design environments (13 W/sq cm and 499 J/sq cm). If thruster jet firings occur near peak dynamic pressure, they will augment the design environments at the interface between the backshell and parachute cone (7 W/sq cm and 174 J/sq cm). Localized heat fluxes are higher near the thruster fairing during jet firings, but these areas did not require additional thermal protection material. Finally, heating bump factors were developed for antenna radomes on the parachute cone

Exomars Mission Verification Approach

NASA Astrophysics Data System (ADS)

Cassi, Carlo; Gilardi, Franco; Bethge, Boris

According to the long-term cooperation plan established by ESA and NASA in June 2009, the ExoMars project now consists of two missions: A first mission will be launched in 2016 under ESA lead, with the objectives to demonstrate the European capability to safely land a surface package on Mars, to perform Mars Atmosphere investigation, and to provide communi-cation capability for present and future ESA/NASA missions. For this mission ESA provides a spacecraft-composite, made up of an "Entry Descent & Landing Demonstrator Module (EDM)" and a Mars Orbiter Module (OM), NASA provides the Launch Vehicle and the scientific in-struments located on the Orbiter for Mars atmosphere characterisation. A second mission with it launch foreseen in 2018 is lead by NASA, who provides spacecraft and launcher, the EDL system, and a rover. ESA contributes the ExoMars Rover Module (RM) to provide surface mobility. It includes a drill system allowing drilling down to 2 meter, collecting samples and to investigate them for signs of past and present life with exobiological experiments, and to investigate the Mars water/geochemical environment, In this scenario Thales Alenia Space Italia as ESA Prime industrial contractor is in charge of the design, manufacturing, integration and verification of the ESA ExoMars modules, i.e.: the Spacecraft Composite (OM + EDM) for the 2016 mission, the RM for the 2018 mission and the Rover Operations Control Centre, which will be located at Altec-Turin (Italy). The verification process of the above products is quite complex and will include some pecu-liarities with limited or no heritage in Europe. Furthermore the verification approach has to be optimised to allow full verification despite significant schedule and budget constraints. The paper presents the verification philosophy tailored for the ExoMars mission in line with the above considerations, starting from the model philosophy, showing the verification activities flow and the sharing of tests between the different levels (system, modules, subsystems, etc) and giving an overview of the main test defined at Spacecraft level. The paper is mainly focused on the verification aspects of the EDL Demonstrator Module and the Rover Module, for which an intense testing activity without previous heritage in Europe is foreseen. In particular the Descent Module has to survive to the Mars atmospheric entry and landing, its surface platform has to stay operational for 8 sols on Martian surface, transmitting scientific data to the Orbiter. The Rover Module has to perform 180 sols mission in Mars surface environment. These operative conditions cannot be verified only by analysis; consequently a test campaign is defined including mechanical tests to simulate the entry loads, thermal test in Mars environment and the simulation of Rover operations on a 'Mars like' terrain. Finally, the paper present an overview of the documentation flow defined to ensure the correct translation of the mission requirements in verification activities (test, analysis, review of design) until the final verification close-out of the above requirements with the final verification reports.

Sliding mode control for Mars entry based on extended state observer

NASA Astrophysics Data System (ADS)

Lu, Kunfeng; Xia, Yuanqing; Shen, Ganghui; Yu, Chunmei; Zhou, Liuyu; Zhang, Lijun

2017-11-01

This paper addresses high-precision Mars entry guidance and control approach via sliding mode control (SMC) and Extended State Observer (ESO). First, differential flatness (DF) approach is applied to the dynamic equations of the entry vehicle to represent the state variables more conveniently. Then, the presented SMC law can guarantee the property of finite-time convergence of tracking error, which requires no information on high uncertainties that are estimated by ESO, and the rigorous proof of tracking error convergence is given. Finally, Monte Carlo simulation results are presented to demonstrate the effectiveness of the suggested approach.

Hypersonic Navier Stokes Comparisons to Orbiter Flight Data

NASA Technical Reports Server (NTRS)

Campbell, Charles H.; Nompelis, Ioannis; Candler, Graham; Barnhart, Michael; Yoon, Seokkwan

2009-01-01

Hypersonic chemical nonequilibrium simulations of low earth orbit entry flow fields are becoming increasingly commonplace as software and computational capabilities become more capable. However, development of robust and accurate software to model these environments will always encounter a significant barrier in developing a suite of high quality calibration cases. The US3D hypersonic nonequilibrium Navier Stokes analysis capability has been favorably compared to a number of wind tunnel test cases. Extension of the calibration basis for this software to Orbiter flight conditions will provide an incremental increase in confidence. As part of the Orbiter Boundary Layer Transition Flight Experiment and the Hypersonic Thermodynamic Infrared Measurements project, NASA is performing entry flight testing on the Orbiter to provide valuable aerothermodynamic heating data. An increase in interest related to orbiter entry environments is resulting from this activity. With the advent of this new data, comparisons of the US3D software to the new flight testing data is warranted. This paper will provide information regarding the framework of analyses that will be applied with the US3D analysis tool. In addition, comparisons will be made to entry flight testing data provided by the Orbiter BLT Flight Experiment and HYTHIRM projects. If data from digital scans of the Orbiter windward surface become available, simulations will also be performed to characterize the difference in surface heating between the CAD reference OML and the digitized surface provided by the surface scans.

KSC-2014-2856

NASA Image and Video Library

2014-06-06

CAPE CANAVERAL, Fla. -- Inside the Operations and Checkout Building high bay at NASA's Kennedy Space Center in Florida, a Lockheed Martin technician monitors the progress as a crane is used to lift the Orion service module from a test stand and move it to the Final Assembly and System Testing, or FAST, cell further down the aisle. The Orion crew module will be stacked on the service module in the FAST cell and then both modules will be put through their final system tests for Exploration Flight Test-1, or EFT-1, prior to rolling out of the facility for integration with the United Launch Alliance Delta IV Heavy rocket. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion, EFT-1, is scheduled to launch later this year atop a Delta IV rocket from Cape Canaveral Air Force Station in Florida to an altitude of 3,600 miles above the Earth's surface. The two-orbit, four-hour flight test will help engineers evaluate the systems critical to crew safety including the heat shield, parachute system and launch abort system. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Glenn Benson

KSC-2014-2858

NASA Image and Video Library

2014-06-06

CAPE CANAVERAL, Fla. -- Inside the Operations and Checkout Building high bay at NASA's Kennedy Space Center in Florida, NASA and Lockheed Martin engineers and technicians monitor the progress as a crane is used to move the Orion service module to the Final Assembly and System Testing, or FAST, cell further down the aisle. The Orion crew module will be stacked on the service module in the FAST cell and then both modules will be put through their final system tests for Exploration Flight Test-1, or EFT-1, before rolling out of the facility for integration with the United Launch Alliance Delta IV Heavy rocket. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion, EFT-1, is scheduled to launch later this year atop a Delta IV rocket from Cape Canaveral Air Force Station in Florida to an altitude of 3,600 miles above the Earth's surface. The two-orbit, four-hour flight test will help engineers evaluate the systems critical to crew safety including the heat shield, parachute system and launch abort system. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Glenn Benson

KSC-2014-2859

NASA Image and Video Library

2014-06-06

CAPE CANAVERAL, Fla. -- Inside the Operations and Checkout Building high bay at NASA's Kennedy Space Center in Florida, NASA and Lockheed Martin engineers and technicians monitor the progress as a crane is used to move the Orion service module to the Final Assembly and System Testing, or FAST, cell further down the aisle. The Orion crew module will be stacked on the service module in the FAST cell and then both modules will be put through their final system tests for Exploration Flight Test-1, or EFT-1, before rolling out of the facility for integration with the United Launch Alliance Delta IV Heavy rocket. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion, EFT-1, is scheduled to launch later this year atop a Delta IV rocket from Cape Canaveral Air Force Station in Florida to an altitude of 3,600 miles above the Earth's surface. The two-orbit, four-hour flight test will help engineers evaluate the systems critical to crew safety including the heat shield, parachute system and launch abort system. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Glenn Benson

KSC-2014-2857

NASA Image and Video Library

2014-06-06

CAPE CANAVERAL, Fla. -- Inside the Operations and Checkout Building high bay at NASA's Kennedy Space Center in Florida, NASA and Lockheed Martin technicians and engineers monitor the progress as a crane is used to lift the Orion service module from a test stand and move it to the Final Assembly and System Testing, or FAST, cell further down the aisle. The Orion crew module will be stacked on the service module in the FAST cell and then both modules will be put through their final system tests for Exploration Flight Test-1, or EFT-1, before rolling out of the facility for integration with the United Launch Alliance Delta IV Heavy rocket. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion, EFT-1, is scheduled to launch later this year atop a Delta IV rocket from Cape Canaveral Air Force Station in Florida to an altitude of 3,600 miles above the Earth's surface. The two-orbit, four-hour flight test will help engineers evaluate the systems critical to crew safety including the heat shield, parachute system and launch abort system. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Glenn Benson

Arsenic and Antimony Removal from Drinking Water by Point-of-Entry Reverse Osmosis Coupled with Dual Plumbing Distribution - U.S. EPA Demonstration Project at Carmel Elementary School in Carmel, ME -Final Performance Evaluation Report

EPA Science Inventory

This report documents the activities performed for and the results obtained from the arsenic and antimony removal treatment technology demonstration project at the Carmel Elementary School (CES) in Carmel, ME. An innovative approach of employing point of entry (POE) reverse osmo...

Development of Curriculum Content for a Unique Career Ladder Multi-Entry/Multi-Exit Nursing Program. Final Report.

ERIC Educational Resources Information Center

Rosbach, Ellen M.

A project was undertaken to develop the curriculum content for a unique career ladder multi-entry/multi-exit nursing program that would provide training for nurse aides, practical nurses, and registered nurses. The major objectives of the project were to conduct a review of the literature on curriculum materials presently in use, to develop 11…

Thermal Protection Materials: Development, Characterization and Evaluation

NASA Technical Reports Server (NTRS)

Johnson, Silvia M.

2012-01-01

Thermal protection materials and systems (TPS) are used to protect space vehicles from the heat experienced during entry into an atmosphere. The application for these materials is very specialized as are the materials. They must have specific properties to withstand conditions during specific entries. There is no one-size-fits-all TPS as the conditions experienced by a material are very dependent upon the atmosphere, the entry speed, the size and shape of the vehicle, and the location on the vehicle. However, all TPS must be reliable and efficient to ensure mission safety, that is to protect the vehicle while ensuring that payload is maximized. Types of TPS will be reviewed in relation to types of missions and applications. Both reusable and ablative materials will be discussed. Approaches to characterizing and evaluating these materials will be presented. The role of heritage versus new materials will be described.

Thermal Protection System Development, Testing and Qualification

NASA Astrophysics Data System (ADS)

Venkatapathy, Ethiraj; Arnold, James; Laub, B.; Hartman, G. J.

The science community currently has interest in planetary entry probe missions to improve our understanding of the atmospheres of Saturn and Venus [1,2]. As in the case of the Galileo entry probe, such data are critical to the understanding of not only the individual planets but also to further knowledge regarding the formation of the solar system. It is believed that Saturn probes to depths corresponding to 10 bars will be sufficient [1] to provide the desired scientific data. The heating rates for the "shallow" Saturn probes and Venus are in the range of 2 - 5KW/cm2 . It is clear that new, mid-density Thermal Protection System (TPS) materials for such probes can be mission-enabling for mass efficiency [3] and also make the use of smaller vehicles possible from advancements in scientific instrumentation [4]. Past consideration of new Jovian multiprobe missions has been considered problematic without the Giant Planet Arcjet Facility that was used to qualify Carbon Phenolic for the Galileo Probe. This paper describes emerging TPS technology and the proposed use of an affordable, small 5 MW arc jet that can be used for TPS development in test gases appropriate for the aforementioned, new planetary probe applications. Emerging TPS technologies of interest include a mid-density, chopped molded carbon phenolic (CMCP) material around 0.8g/cc and a densified variant of phenolic impregnated carbon ablator (PICA) around 0.5g/cc. The small 5 MW arc jet facility, called the Development Arcjet Facility (DAF) and the methodology of testing TPS, both based on previous work, are discussed. Finally, the applications to Earth entry appropriate to speeds greater than lunar return (11km/s) are discussed as will facility-to-facility validation using air as a test gas. The use of other facilities for development, qualification and certification of TPS for Saturn and Venus is also discussed. [1] Atreya, S. K., et. al. Formation of Giant Planets and Their Atmospheres: Entry Probes for Saturn and Beyond; 5 th International Planetary Probe Workshop, June 25-29, Bordeaux, France. [2] Baines, K. H, et. al, Exploring Venus with Balloons: Science Objectives and Mission Architectures. 5 th International Planetary Probe Workshop, June 25-29 Bordeaux, France.

Estimating the Stoichiometry of HIV Neutralization

PubMed Central

Magnus, Carsten; Regoes, Roland R.

2010-01-01

HIV-1 virions infect target cells by first establishing contact between envelope glycoprotein trimers on the virion's surface and CD4 receptors on a target cell, recruiting co-receptors, fusing with the cell membrane and finally releasing the genetic material into the target cell. Specific experimental setups allow the study of the number of trimer-receptor-interactions needed for infection, i.e., the stoichiometry of entry and also the number of antibodies needed to prevent one trimer from engaging successfully in the entry process, i.e., the stoichiometry of (trimer) neutralization. Mathematical models are required to infer the stoichiometric parameters from these experimental data. Recently, we developed mathematical models for the estimations of the stoichiometry of entry [1]. In this article, we show how our models can be extended to investigate the stoichiometry of trimer neutralization. We study how various biological parameters affect the estimate of the stoichiometry of neutralization. We find that the distribution of trimer numbers—which is also an important determinant of the stoichiometry of entry—influences the estimated value of the stoichiometry of neutralization. In contrast, other parameters, which characterize the experimental system, diminish the information we can extract from the data about the stoichiometry of neutralization, and thus reduce our confidence in the estimate. We illustrate the use of our models by re-analyzing previously published data on the neutralization sensitivity [2], which contains measurements of neutralization sensitivity of viruses with different envelope proteins to antibodies with various specificities. Our mathematical framework represents the formal basis for the estimation of the stoichiometry of neutralization. Together with the stoichiometry of entry, the stoichiometry of trimer neutralization will allow one to calculate how many antibodies are required to neutralize a virion or even an entire population of virions. PMID:20333245

Bibliographic Resources for the Historian of Astronomy

NASA Astrophysics Data System (ADS)

Corbin, B. G.

1999-12-01

Many large library collections now have online bibliographic catalogs on the web. These provide many hidden resources for the historian of astronomy. Special searching techniques will allow the historian to scan bibliographic records of hundreds of entries relating to biographies of astronomers, collected works of astronomers, ancient and medieval astronomy and many other historical subjects. Abstract databases such as the Astrophysics Data System and ARIBIB are also adding much historical bibliographic information. ARIBIB will eventually contain scanned images of the Astronomischer Jahresbericht containing bibliographic entries for all literature of astronomy from 1899 to 1968 and Astronomy and Astrophysics Abstracts from 1969 to present. Commercial services such as UnCover and FirstSearch provide a means of reaching bibliographic entries for journal and book literature in the history of astronomy which were not easily located in the past. A broad overview of these collections and services will be given, and searching techniques for finding ``hidden" bibliographic data will be presented. Web page addresses will be given for all sources covered.

Determination of aerodynamic stability and drag of the Titan 3 C SRM during entry

NASA Technical Reports Server (NTRS)

Ramsey, P. E.

1974-01-01

An experimental aerodynamic investigation was conducted in the NASA/MSFC 14-inch Trisonic Wind Tunnel on a 0.00736 scale model of Titan 3 C Solid Rocket Motor (SRM). Static stability and drag data were obtained for Mach numbers of 0.6 to 4.96, angles of attack of minus 10 deg to 190 deg, and roll angles of 0 to 360 deg. The resulting data will be used to predict the dynamic motions of the SRM during entry which will then be compared to flight data. This comparison will improve and lend credibility to methods for predicting the entry dynamics of the space shuttle Solid Rocket Booster (SRB), which is needed for recovery studies and design of the parachute recovery system.

MarcoPolo-R: Mission and Spacecraft Design

NASA Astrophysics Data System (ADS)

Peacocke, L.; Kemble, S.; Chapuy, M.; Scheer, H.

2013-09-01

The MarcoPolo-R mission is a candidate for the European Space Agency's medium-class Cosmic Vision programme, with the aim to obtain a 100 g sample of asteroid surface material and return it safely to the Earth. Astrium is one of two industrial contractors currently studying the mission to Phase A level, and the team has been working on the mission and spacecraft design since January 2012. Asteroids are some of the most primitive bodies in our solar system and are key to understanding the formation of the Earth, Sun and other planetary bodies. A returned sample would allow extensive analyses in the large laboratory-sized instruments here on Earth that are not possible with in-situ instruments. This analysis would also increase our understanding of the composition and structure of asteroids, and aid in plans for asteroid deflection techniques. In addition, the mission would be a valuable precursor for missions such as Mars Sample Return, demonstrating a high speed Earth re-entry and hard landing of an entry capsule. Following extensive mission analysis of both the baseline asteroid target 1996 FG3 and alternatives, a particularly favourable trajectory was found to the asteroid 2008 EV5 resulting in a mission duration of 4.5 to 6 years. In October 2012, the MarcoPolo-R baseline target was changed to 2008 EV5 due to its extremely primitive nature, which may pre-date the Sun. This change has a number of advantages: reduced DeltaV requirements, an orbit with a more benign thermal environment, reduced communications distances, and a reduced complexity propulsion system - all of which simplify the spacecraft design significantly. The single spacecraft would launch between 2022 and 2024 on a Soyuz-Fregat launch vehicle from Kourou. Solar electric propulsion is necessary for the outward and return transfers due to the DeltaV requirements, to minimise propellant mass. Once rendezvous with the asteroid is achieved, an observation campaign will begin to characterise the asteroid properties and map the surface in detail. Five potential sampling sites will be selected and closely observed in a local characterisation phase, leading to a single preferred sampling site being identified. The baseline instruments are a Narrow Angle Camera, a Mid-Infrared Spectrometer, a Visible Near-Infrared Spectrometer, a Radio Science Experiment, and a Close-up Camera. For the sampling phase, the spacecraft will perform a touch-and-go manoeuvre. A boom with a sampling mechanism at the end will be deployed, and the spacecraft will descend using visual navigation to touch the asteroid for some seconds. The rotary brush sampling mechanism will be activated on touchdown to obtain a good quality sample comprising regolith dust and pebbles. Low touchdown velocities and collision avoidance are critical at this point to prevent damage to the spacecraft and solar arrays. The spacecraft will then move away, returning to a safe orbit, and the sample will be transferred to an Earth Re-entry Capsule. After a final post-sampling characterisation campaign, the spacecraft will perform the return transfer to Earth. The Earth Re-entry Capsule will be released to directly enter the Earth's atmosphere, and is designed to survive a hard landing with no parachute deceleration. Once recovered, the asteroid sample would be extracted in a sample curation facility in preparation for the full analysis campaign. This presentation will describe Astrium's MarcoPolo-R mission and spacecraft design, with a focus on the innovative aspects of the design.

The Protein-DNA Interface database

PubMed Central

2010-01-01

The Protein-DNA Interface database (PDIdb) is a repository containing relevant structural information of Protein-DNA complexes solved by X-ray crystallography and available at the Protein Data Bank. The database includes a simple functional classification of the protein-DNA complexes that consists of three hierarchical levels: Class, Type and Subtype. This classification has been defined and manually curated by humans based on the information gathered from several sources that include PDB, PubMed, CATH, SCOP and COPS. The current version of the database contains only structures with resolution of 2.5 Å or higher, accounting for a total of 922 entries. The major aim of this database is to contribute to the understanding of the main rules that underlie the molecular recognition process between DNA and proteins. To this end, the database is focused on each specific atomic interface rather than on the separated binding partners. Therefore, each entry in this database consists of a single and independent protein-DNA interface. We hope that PDIdb will be useful to many researchers working in fields such as the prediction of transcription factor binding sites in DNA, the study of specificity determinants that mediate enzyme recognition events, engineering and design of new DNA binding proteins with distinct binding specificity and affinity, among others. Finally, due to its friendly and easy-to-use web interface, we hope that PDIdb will also serve educational and teaching purposes. PMID:20482798

The Protein-DNA Interface database.

PubMed

Norambuena, Tomás; Melo, Francisco

2010-05-18

The Protein-DNA Interface database (PDIdb) is a repository containing relevant structural information of Protein-DNA complexes solved by X-ray crystallography and available at the Protein Data Bank. The database includes a simple functional classification of the protein-DNA complexes that consists of three hierarchical levels: Class, Type and Subtype. This classification has been defined and manually curated by humans based on the information gathered from several sources that include PDB, PubMed, CATH, SCOP and COPS. The current version of the database contains only structures with resolution of 2.5 A or higher, accounting for a total of 922 entries. The major aim of this database is to contribute to the understanding of the main rules that underlie the molecular recognition process between DNA and proteins. To this end, the database is focused on each specific atomic interface rather than on the separated binding partners. Therefore, each entry in this database consists of a single and independent protein-DNA interface.We hope that PDIdb will be useful to many researchers working in fields such as the prediction of transcription factor binding sites in DNA, the study of specificity determinants that mediate enzyme recognition events, engineering and design of new DNA binding proteins with distinct binding specificity and affinity, among others. Finally, due to its friendly and easy-to-use web interface, we hope that PDIdb will also serve educational and teaching purposes.

Mars Science Laboratory Entry, Descent and Landing System Overview

NASA Technical Reports Server (NTRS)

Steltzner, Adam D.; San Martin, A. Miguel; Rivellini, Tomasso P.; Chen, Allen

2013-01-01

The Mars Science Laboratory project recently places the Curiosity rove on the surface of Mars. With the success of the landing system, the performance envelope of entry, descent and landing capabilities has been extended over the previous state of the art. This paper will present an overview to the MSL entry, descent and landing system design and preliminary flight performance results.

Ink dating, part I: Statistical distribution of selected ageing parameters in a ballpoint inks reference population.

PubMed

Koenig, Agnès; Weyermann, Céline

2018-01-01

The development of ink dating methods requires an important amount of work in order to be reliably applicable in practice. Major tasks include the definition of ageing parameters to monitor ink ageing. An adequate parameter should ideally fulfil the following criteria: it should evolve as a function of time in a monotonic way, be measurable in a majority of ink entries, be as accurate and reproducible as possible, and finally it should not be influenced too much by transfer and storage conditions. This work aimed at evaluating the potential of seven ageing parameters for ink dating purposes: the phenoxyethanol quantity, relative peak areas (RPA), three solvent loss ratios (R%, R%*, NR%) and two solvent loss parameters (R NORM, NR NORM ). These were calculated over approximately one year for 25 inks selected from a large database to represent different ageing behaviours. Ink entries were analysed using liquid extraction followed by GC/MS analysis. Results showed that natural ageing parameters (NR% and NR NORM ) were not suitable ageing parameters for ink entries older than a few weeks. RPA used other compounds present in ink formulations in combination to PE in order to normalise the results. However, it presented particular difficulties as they could not be defined for all inks and were thus applicable only for 64% of the studied inks. Finally, the PE quantity, R% and R NORM allowed to follow the ageing of the selected inks over the whole time frame and were identified as the most promising. These were thus selected to test three different interpretation models in the second part of this article. The possibilities and limitations of ink dating methods will be discussed in a legal perspective. Copyright © 2017 The Chartered Society of Forensic Sciences. Published by Elsevier B.V. All rights reserved.

Outer planet atmospheric entry probes - An overview of technology readiness

NASA Technical Reports Server (NTRS)

Vojvodich, N. S.; Reynolds, R. T.; Grant, T. L.; Nachtsheim, P. R.

1975-01-01

Entry probe systems for characterizing, by in situ measurements, the atmospheric properties, chemical composition, and cloud structure of the planets Saturn, Uranus, and Jupiter are examined from the standpoint of unique mission requirements, associated subsystem performance, and degree of commonality of design. Past earth entry vehicles (PAET) and current planetary spacecraft (Pioneer Venus probes and Viking lander) are assessed to identify the extent of potential subsystem inheritance, as well as to establish the significant differences, in both form and function, relative to outer planet requirements. Recent research results are presented and reviewed for the most critical probe technology areas, including: science accommodation, telecommunication, and entry heating and thermal protection. Finally presented is a brief discussion of the use of decision analysis techniques for quantifying various probe heat-shield test alternatives and performance risk.

Is there a bone-nail specific entry point? Automated fit quantification of tibial nail designs during the insertion for six different nail entry points.

PubMed

Amarathunga, J P; Schuetz, M A; Yarlagadda, K V D; Schmutz, B

2015-04-01

Intramedullary nailing is the standard fixation method for displaced diaphyseal fractures of tibia. Selection of the correct nail insertion point is important for axial alignment of bone fragments and to avoid iatrogenic fractures. However, the standard entry point (SEP) may not always optimise the bone-nail fit due to geometric variations of bones. This study aimed to investigate the optimal entry for a given bone-nail pair using the fit quantification software tool previously developed by the authors. The misfit was quantified for 20 bones with two nail designs (ETN and ETN-Proximal Bend) related to the SEP and 5 entry points which were 5 mm and 10 mm away from the SEP. The SEP was the optimal entry point for 50% of the bones used. For the remaining bones, the optimal entry point was located 5 mm away from the SEP, which improved the overall fit by 40% on average. However, entry points 10 mm away from the SEP doubled the misfit. The optimised bone-nail fit can be achieved through the SEP and within the range of a 5 mm radius, except posteriorly. The study results suggest that the optimal entry point should be selected by considering the fit during insertion and not only at the final position. Copyright © 2015 IPEM. Published by Elsevier Ltd. All rights reserved.

19 CFR 4.9 - Formal entry.

Code of Federal Regulations, 2010 CFR

2010-04-01

... delivered to the consul of the nation to which such vessel belongs, in which event the vessel master will... who fails to make entry as required by this section or who presents or transmits electronically any...

KSC-2009-2044

NASA Image and Video Library

2009-03-15

CAPE CANAVERAL, Fla. – In the Operations and Checkout Building at NASA's Kennedy Space Center in Florida, STS-119 Mission Specialist Steve Swanson adjusts his helmet as he puts on the launch-and-entry suit for the launch of space shuttle Discovery. The crew will be heading for Launch Pad 39A and liftoff of Discovery, scheduled for 7:43 p.m. EDT on March 15. An earlier launch attempt March 11 was scrubbed at 2:36 p.m. due to a gaseous hydrogen leak from the external tank at the Ground Umbilical Carrier Plate during tanking. A seven-inch quick disconnect and two seals were replaced. The STS-119 mission is the 28th to the International Space Station and the 125th space shuttle flight. Discovery will deliver the final pair of power-generating solar array wings and the S6 truss segment. Installation of S6 will signal the station's readiness to house a six-member crew for conducting increased science. Photo credit: NASA/Kim Shiflett

KSC-2009-2045

NASA Image and Video Library

2009-03-15

CAPE CANAVERAL, Fla. – In the Operations and Checkout Building at NASA's Kennedy Space Center in Florida, STS-119 Mission Specialist Steve Swanson completes putting on the launch-and-entry suit, with the helmet, for the launch of space shuttle Discovery. The crew will be heading for Launch Pad 39A and liftoff of Discovery, scheduled for 7:43 p.m. EDT on March 15. An earlier launch attempt March 11 was scrubbed at 2:36 p.m. due to a gaseous hydrogen leak from the external tank at the Ground Umbilical Carrier Plate during tanking. A seven-inch quick disconnect and two seals were replaced. The STS-119 mission is the 28th to the International Space Station and the 125th space shuttle flight. Discovery will deliver the final pair of power-generating solar array wings and the S6 truss segment. Installation of S6 will signal the station's readiness to house a six-member crew for conducting increased science. Photo credit: NASA/Kim Shiflett

KSC-2009-2046

NASA Image and Video Library

2009-03-15

CAPE CANAVERAL, Fla. – In the Operations and Checkout Building at NASA's Kennedy Space Center in Florida, STS-119 Commander Lee Archambault fits the helmet on his launch-and-entry suit for the launch of space shuttle Discovery. The crew will be heading for Launch Pad 39A and liftoff of Discovery, scheduled for 7:43 p.m. EDT on March 15. An earlier launch attempt March 11 was scrubbed at 2:36 p.m. due to a gaseous hydrogen leak from the external tank at the Ground Umbilical Carrier Plate during tanking. A seven-inch quick disconnect and two seals were replaced. The STS-119 mission is the 28th to the International Space Station and the 125th space shuttle flight. Discovery will deliver the final pair of power-generating solar array wings and the S6 truss segment. Installation of S6 will signal the station's readiness to house a six-member crew for conducting increased science. Photo credit: NASA/Kim Shiflett

KSC-2009-2043

NASA Image and Video Library

2009-03-15

CAPE CANAVERAL, Fla. – – In the Operations and Checkout Building at NASA's Kennedy Space Center in Florida, STS-119 Pilot Tony Antonelli adds the helmet as he puts on his launch-and-entry suit for the launch of space shuttle Discovery. The crew will be heading for Launch Pad 39A and liftoff of Discovery, scheduled for 7:43 p.m. EDT on March 15. An earlier launch attempt March 11 was scrubbed at 2:36 p.m. due to a gaseous hydrogen leak from the external tank at the Ground Umbilical Carrier Plate during tanking. A seven-inch quick disconnect and two seals were replaced. The STS-119 mission is the 28th to the International Space Station and the 125th space shuttle flight. Discovery will deliver the final pair of power-generating solar array wings and the S6 truss segment. Installation of S6 will signal the station's readiness to house a six-member crew for conducting increased science. Photo credit: NASA/Kim Shiflett

KSC-2009-2033

NASA Image and Video Library

2009-03-15

CAPE CANAVERAL, Fla. – In the Operations and Checkout Building at NASA's Kennedy Space Center in Florida, STS-119 Mission Specialist John Phillips is eager for launch as he puts on his launch-and-entry suit. The crew will be heading for Launch Pad 39A and liftoff of space shuttle Discovery, scheduled for 7:43 p.m. EDT on March 15. An earlier launch attempt March 11 was scrubbed at 2:36 p.m. due to a gaseous hydrogen leak from the external tank at the Ground Umbilical Carrier Plate during tanking. A seven-inch quick disconnect and two seals were replaced. The STS-119 mission is the 28th to the International Space Station and the 125th space shuttle flight. Discovery will deliver the final pair of power-generating solar array wings and the S6 truss segment. Installation of S6 will signal the station's readiness to house a six-member crew for conducting increased science. Photo credit: NASA/Kim Shiflett

KSC-2009-2039

NASA Image and Video Library

2009-03-15

CAPE CANAVERAL, Fla. – In the Operations and Checkout Building at NASA's Kennedy Space Center in Florida, STS-119 Mission Specialist John Phillips completes putting on his launch-and-entry suit, including the helmet, for the launch of space shuttle Discovery. The crew will be heading for Launch Pad 39A and liftoff of Discovery, scheduled for 7:43 p.m. EDT on March 15. An earlier launch attempt March 11 was scrubbed at 2:36 p.m. due to a gaseous hydrogen leak from the external tank at the Ground Umbilical Carrier Plate during tanking. A seven-inch quick disconnect and two seals were replaced. The STS-119 mission is the 28th to the International Space Station and the 125th space shuttle flight. Discovery will deliver the final pair of power-generating solar array wings and the S6 truss segment. Installation of S6 will signal the station's readiness to house a six-member crew for conducting increased science. Photo credit: NASA/Kim Shiflett

KSC-2009-2035

NASA Image and Video Library

2009-03-15

CAPE CANAVERAL, Fla. – In the Operations and Checkout Building at NASA's Kennedy Space Center in Florida, STS-119 Mission Specialist Richard Arnold is eager for launch as he puts on his launch-and-entry suit. The crew will be heading for Launch Pad 39A and liftoff of space shuttle Discovery, scheduled for 7:43 p.m. EDT on March 15. An earlier launch attempt March 11 was scrubbed at 2:36 p.m. due to a gaseous hydrogen leak from the external tank at the Ground Umbilical Carrier Plate during tanking. A seven-inch quick disconnect and two seals were replaced. The STS-119 mission is the 28th to the International Space Station and the 125th space shuttle flight. Discovery will deliver the final pair of power-generating solar array wings and the S6 truss segment. Installation of S6 will signal the station's readiness to house a six-member crew for conducting increased science. Photo credit: NASA/Kim Shiflett

KSC-2009-2037

NASA Image and Video Library

2009-03-15

CAPE CANAVERAL, Fla. – In the Operations and Checkout Building at NASA's Kennedy Space Center in Florida, STS-119 Mission Specialist Koichi Wakata is helped with his boots as he puts on his launch-and-entry suit. The crew will be heading for Launch Pad 39A and liftoff of space shuttle Discovery, scheduled for 7:43 p.m. EDT on March 15. An earlier launch attempt March 11 was scrubbed at 2:36 p.m. due to a gaseous hydrogen leak from the external tank at the Ground Umbilical Carrier Plate during tanking. A seven-inch quick disconnect and two seals were replaced. The STS-119 mission is the 28th to the International Space Station and the 125th space shuttle flight. Discovery will deliver the final pair of power-generating solar array wings and the S6 truss segment. Installation of S6 will signal the station's readiness to house a six-member crew for conducting increased science. Photo credit: NASA/Kim Shiflett

KSC-2009-2040

NASA Image and Video Library

2009-03-15

CAPE CANAVERAL, Fla. – In the Operations and Checkout Building at NASA's Kennedy Space Center in Florida, STS-119 Mission Specialist Richard Arnold completes putting on his launch-and-entry suit, including the helmet, for the launch of space shuttle Discovery. The crew will be heading for Launch Pad 39A and liftoff of Discovery, scheduled for 7:43 p.m. EDT on March 15. An earlier launch attempt March 11 was scrubbed at 2:36 p.m. due to a gaseous hydrogen leak from the external tank at the Ground Umbilical Carrier Plate during tanking. A seven-inch quick disconnect and two seals were replaced. The STS-119 mission is the 28th to the International Space Station and the 125th space shuttle flight. Discovery will deliver the final pair of power-generating solar array wings and the S6 truss segment. Installation of S6 will signal the station's readiness to house a six-member crew for conducting increased science. Photo credit: NASA/Kim Shiflett

The dark sides of capillary morphogenesis gene 2

PubMed Central

Deuquet, Julie; Lausch, Ekkehart; Superti-Furga, Andrea; van der Goot, F Gisou

2012-01-01

Capillary morphogenesis gene 2 (CMG2) is a type I membrane protein involved in the homeostasis of the extracellular matrix. While it shares interesting similarities with integrins, its exact molecular role is unknown. The interest and knowledge about CMG2 largely stems from the fact that it is involved in two diseases, one infectious and one genetic. CMG2 is the main receptor of the anthrax toxin, and knocking out this gene in mice renders them insensitive to infection with Bacillus anthracis spores. On the other hand, mutations in CMG2 lead to a rare but severe autosomal recessive disorder in humans called Hyaline Fibromatosis Syndrome (HFS). We will here review what is known about the structure of CMG2 and its ability to mediate anthrax toxin entry into cell. We will then describe the limited knowledge available concerning the physiological role of CMG2. Finally, we will describe HFS and the consequences of HFS-associated mutations in CMG2 at the molecular and cellular level. PMID:22215446

76 FR 62765 - Certain Kitchen Appliance Shelving and Racks From the People's Republic of China: Preliminary...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-10-11

...The Department of Commerce (``Department'') is conducting an administrative review of the antidumping duty order on certain kitchen appliance shelving and racks from the People's Republic of China (``PRC''), covering the period of review (``POR'') of March 5, 2009, through August 31, 2010.\\1\\ The Department has preliminarily determined that sales have been made below normal value (``NV'') by the respondents examined in this administrative review. If these preliminary results are adopted in our final results of this review, the Department will instruct U.S. Customs and Border Protection (``CBP'') to assess antidumping duties on all appropriate entries of subject merchandise during the period of review. ---------------------------------------------------------------------------

Kamstrupp's wow-effect: re-examined and expanded

NASA Astrophysics Data System (ADS)

King, Elizabeth M.; Dickmann, Ellyn M.; Johnson, Barbara Z.

2016-12-01

This review examines Anne Katrine Kamstrupp's article "The wow-effect in science teacher education; technology; sociomateriality." In the discussion below we explore three key areas of her ethnographic research. First, we reconsider Kamstrupp's article through the lens of technology as a pedagogical choice and philosophy. This is followed by our discussion of aspects of her study within the context of a basic understanding that entry-level pre-service teachers need to fully understand both the process of learning and scientific principles as these are important foundational factors in determining whether or not the wow-effect will occur as expected. Finally, our review team presents multiple areas in Kamstrupp's article as potential points for further elaboration.

Different Infectivity of HIV-1 Strains Is Linked to Number of Envelope Trimers Required for Entry

PubMed Central

Brandenberg, Oliver F.; Magnus, Carsten; Rusert, Peter; Regoes, Roland R.; Trkola, Alexandra

2015-01-01

HIV-1 enters target cells by virtue of envelope glycoprotein trimers that are incorporated at low density in the viral membrane. How many trimers are required to interact with target cell receptors to mediate virus entry, the HIV entry stoichiometry, still awaits clarification. Here, we provide estimates of the HIV entry stoichiometry utilizing a combined approach of experimental analyses and mathematical modeling. We demonstrate that divergent HIV strains differ in their stoichiometry of entry and require between 1 to 7 trimers, with most strains depending on 2 to 3 trimers to complete infection. Envelope modifications that perturb trimer structure lead to an increase in the entry stoichiometry, as did naturally occurring antibody or entry inhibitor escape mutations. Highlighting the physiological relevance of our findings, a high entry stoichiometry correlated with low virus infectivity and slow virus entry kinetics. The entry stoichiometry therefore directly influences HIV transmission, as trimer number requirements will dictate the infectivity of virus populations and efficacy of neutralizing antibodies. Thereby our results render consideration of stoichiometric concepts relevant for developing antibody-based vaccines and therapeutics against HIV. PMID:25569556

Radiative Heat Transfer During Atmosphere Entry at Parabolic Velocity

NASA Technical Reports Server (NTRS)

Yoshikawa, Kenneth K.; Wick, Bradford H.

1961-01-01

Stagnation point radiative heating rates for manned vehicles entering the earth's atmosphere at parabolic velocity are presented and compared with corresponding laminar convective heating rates. The calculations were made for both nonlifting and lifting entry trajectories for vehicles of varying nose radius, weight-to-area ratio, and drag. It is concluded from the results presented that radiative heating will be important for the entry conditions considered.

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 evaluation of the IRDT's aerothermodynamic behaviour. DASA was responsible for integration of the sensor package and is ESA's co-investigator for evaluation of the application aspects of this new technology. In addition to the sensor package, the mission will accommodate a collection of special stones to study the physical and chemical modifications in sedimentary rocks, i.e. simulated meteorites, during atmospheric infall. Co-investors of this experiment are Dr. André Brack (CNRS, Orleans) and Dr. Gero Kurat (Vienna University). This experiment is being co-sponsored by ESA. The Russian/European Starsem launch company and NPO Lavochkin, the Russian company that developed the original IRDT technology, will be responsible for launch, orbit control, re-entry and recovery of the sensor package under contract with the International Science & Technology Centre (Moscow). ESA, the European Commission and DASA are co-funding this contract, contributing $600K each.

KSC-00pp1563

NASA Image and Video Library

2000-10-11

STS-92 Mission Specialist William S. McArthur Jr. undergoes final suit check in the White Room before entering Discovery. The White Room is an environmentally controlled area at the end of the Orbiter Access Arm that provides entry to the orbiter as well as emergency egress if needed. The arm remains in the extended position until 7 minutes 24 seconds before launch. McArthur and the rest of the crew are making the fifth flight to the International Space Station for construction. Discovery carries a payload that includes the Integrated Truss Structure Z-1, first of 10 trusses that will form the backbone of the Space Station, and the third Pressurized Mating Adapter that will provide a Shuttle docking port for solar array installation on the sixth Station flight and Lab installation on the seventh Station flight. The mission includes four spacewalks for the construction activities. Discovery’s landing is expected Oct. 22 at 2:10 p.m. EDT

KSC-00pp1569

NASA Image and Video Library

2000-10-11

STS-92 Commander Brian Duffy is helped with final suit check in the White Room before entering Discovery. The White Room is an environmentally controlled area at the end of the Orbiter Access Arm that provides entry to the orbiter as well as emergency egress if needed. The arm remains in the extended position until 7 minutes 24 seconds before launch. Duffy and the rest of the crew are undertaking the fifth flight to the International Space Station for construction. Discovery carries a payload that includes the Integrated Truss Structure Z-1, first of 10 trusses that will form the backbone of the Space Station, and the third Pressurized Mating Adapter that will provide a Shuttle docking port for solar array installation on the sixth Station flight and Lab installation on the seventh Station flight. The mission includes four spacewalks for the construction activities. Discovery’s landing is expected Oct. 22 at 2:10 p.m. EDT

F-35 Engine Quality Assurance Inspection

DTIC Science & Technology

2015-04-27

area nor protected from common FOD items. The F135 engine final assembly area had FOD signage at the two entry lobbies of the building; however...there were no FOD signage within the engine final assembly areas. Pratt & Whitney FOD procedures also did not prevent common FOD items from entering

Auditing an Online Self-reported Interventional Radiology Adverse Event Database for Compliance and Accuracy.

PubMed

Burch, Ezra A; Shyn, Paul B; Chick, Jeffrey F; Chauhan, Nikunj R

2017-04-01

The purpose of this study was to determine whether auditing an online self-reported interventional radiology quality assurance database improves compliance with record entry or improves the accuracy of adverse event (AE) reporting and grading. Physicians were trained in using the database before the study began. An audit of all database entries for the first 3 months, or the first quarter, was performed, at which point physicians were informed of the audit process; entries for the subsequent 3 months, or the second quarter, were again audited. Results between quarters were compared. Compliance with record entry improved from the first to second quarter, but reminders were necessary to ensure 100% compliance with record entry. Knowledge of the audit process did not significantly improve self-reporting of AE or accuracy of AE grading. However, auditing significantly changed the final AE reporting rates and grades. Copyright © 2016 American College of Radiology. Published by Elsevier Inc. All rights reserved.

Advances in Procedural Techniques - Antegrade

PubMed Central

Wilson, William; Spratt, James C.

2014-01-01

There have been many technological advances in antegrade CTO PCI, but perhaps most importantly has been the evolution of the “hybrid’ approach where ideally there exists a seamless interplay of antegrade wiring, antegrade dissection re-entry and retrograde approaches as dictated by procedural factors. Antegrade wire escalation with intimal tracking remains the preferred initial strategy in short CTOs without proximal cap ambiguity. More complex CTOs, however, usually require either a retrograde or an antegrade dissection re-entry approach, or both. Antegrade dissection re-entry is well suited to long occlusions where there is a healthy distal vessel and limited “interventional” collaterals. Early use of a dissection re-entry strategy will increase success rates, reduce complications, and minimise radiation exposure, contrast use as well as procedural times. Antegrade dissection can be achieved with a knuckle wire technique or the CrossBoss catheter whilst re-entry will be achieved in the most reproducible and reliable fashion by the Stingray balloon/wire. It should be avoided where there is potential for loss of large side branches. It remains to be seen whether use of newer dissection re-entry strategies will be associated with lower restenosis rates compared with the more uncontrolled subintimal tracking strategies such as STAR and whether stent insertion in the subintimal space is associated with higher rates of late stent malapposition and stent thrombosis. It is to be hoped that the algorithms, which have been developed to guide CTO operators, allow for a better transfer of knowledge and skills to increase uptake and acceptance of CTO PCI as a whole. PMID:24694104

KSC-2014-4251

NASA Image and Video Library

2014-10-12

CAPE CANAVERAL, Fla. – Inside the Launch Abort System Facility at NASA’s Kennedy Space Center in Florida, technicians have installed two of the four Ogive panels on Orion's Launch Abort System. The panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The work marked the final major assembly steps for the spacecraft before it is transported to Space Launch Complex 37 at Cape Canaveral Air Force Station in November. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Daniel Casper

KSC-2014-4247

NASA Image and Video Library

2014-10-11

CAPE CANAVERAL, Fla. – The first of four Ogive panels is lifted by crane for installation on Orion's Launch Abort System inside the Launch Abort System Facility at NASA’s Kennedy Space Center in Florida. The panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The work marked the final major assembly steps for the spacecraft before it is transported to Space Launch Complex 37 at Cape Canaveral Air Force Station in November. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Kim Shiflett

KSC-2014-4256

NASA Image and Video Library

2014-10-13

CAPE CANAVERAL, Fla. – Technicians on work platforms monitor the progress as a crane brings the third of four Ogive panels closer for installation on Orion's Launch Abort System inside the Launch Abort System Facility at NASA’s Kennedy Space Center in Florida. The panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The work marked the final major assembly steps for the spacecraft before it is transported to Space Launch Complex 37 at Cape Canaveral Air Force Station in November. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Ben Smegelsky

KSC-2014-4250

NASA Image and Video Library

2014-10-12

CAPE CANAVERAL, Fla. – Technicians on work platforms continue the installation of four Ogive panels on Orion's Launch Abort System inside the Launch Abort System Facility at NASA’s Kennedy Space Center in Florida. The panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The work marked the final major assembly steps for the spacecraft before it is transported to Space Launch Complex 37 at Cape Canaveral Air Force Station in November. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Daniel Casper

KSC-2014-4248

NASA Image and Video Library

2014-10-11

CAPE CANAVERAL, Fla. – Inside the Launch Abort System Facility at NASA’s Kennedy Space Center in Florida, technicians monitor the progress as a crane moves the first of four Ogive panels closer for installation on Orion's Launch Abort System. The panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The work marked the final major assembly steps for the spacecraft before it is transported to Space Launch Complex 37 at Cape Canaveral Air Force Station in November. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Kim Shiflett

KSC-2014-4255

NASA Image and Video Library

2014-10-13

CAPE CANAVERAL, Fla. – Inside the Launch Abort System Facility at NASA's Kennedy Space Center in Florida, a crane brings the third of four Ogive panels closer for installation on Orion's Launch Abort System. The panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The work marked the final major assembly steps for the spacecraft before it is transported to Space Launch Complex 37 at Cape Canaveral Air Force Station in November. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Ben Smegelsky

KSC-2014-4258

NASA Image and Video Library

2014-10-13

CAPE CANAVERAL, Fla. – Inside the Launch Abort System Facility at NASA’s Kennedy Space Center in Florida, technicians attach the third of four Ogive panels on Orion's Launch Abort System. The panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The work marked the final major assembly steps for the spacecraft before it is transported to Space Launch Complex 37 at Cape Canaveral Air Force Station in November. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Ben Smegelsky

KSC-2014-4257

NASA Image and Video Library

2014-10-13

CAPE CANAVERAL, Fla. – Inside the Launch Abort System Facility at NASA’s Kennedy Space Center in Florida, technicians attach the third of four Ogive panels on Orion's Launch Abort System. The panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The work marked the final major assembly steps for the spacecraft before it is transported to Space Launch Complex 37 at Cape Canaveral Air Force Station in November. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Ben Smegelsky

KSC-2014-4246

NASA Image and Video Library

2014-10-11

CAPE CANAVERAL, Fla. – The first of four Ogive panels is lifted by crane for installation on Orion's Launch Abort System inside the Launch Abort System Facility at NASA’s Kennedy Space Center in Florida. The panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The work marked the final major assembly steps for the spacecraft before it is transported to Space Launch Complex 37 at Cape Canaveral Air Force Station in November. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Kim Shiflett

28 CFR 68.54 - Administrative review of a final order of an Administrative Law Judge in cases arising under...

Code of Federal Regulations, 2010 CFR

2010-07-01

... 5 U.S.C. 557, to review any final order of an Administrative Law Judge in accordance with the... request for administrative review within ten (10) days of the date of entry of the Administrative Law... Administrative Hearing Officer may review an Administrative Law Judge's final order on his or her own initiative...

75 FR 12175 - Application(s) for Duty-Free Entry of Scientific Instruments

Federal Register 2010, 2011, 2012, 2013, 2014

2010-03-15

..., micro and nano-sized phenomena from a variety of sources. The samples will be fixed, sectioned and attached to grids to be viewed in the instrument. Justification for Duty-Free Entry: There are no domestic...

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.

Simulation of launch and re-entry acceleration profiles for testing of shuttle and unmanned microgravity research payloads

NASA Astrophysics Data System (ADS)

Cassanto, J. M.; Ziserman, H. I.; Chapman, D. K.; Korszun, Z. R.; Todd, P.

Microgravity experiments designed for execution in Get-Away Special canisters, Hitchhiker modules, and Reusable Re-entry Satellites will be subjected to launch and re-entry accelerations. Crew-dependent provisions for preventing acceleration damage to equipment or products will not be available for these payloads during flight; therefore, the effects of launch and re-entry accelerations on all aspects of such payloads must be evaluated prior to flight. A procedure was developed for conveniently simulating the launch and re-entry acceleration profiles of the Space Shuttle (3.3 and 1.7 × g maximum, respectively) and of two versions of NASA's proposed materials research Re-usable Re-entry Satellite (8 × g maximum in one case and 4 × g in the other). By using the 7 m centrifuge of the Gravitational Plant Physiology Laboratory in Philadelphia it was found possible to simulate the time dependence of these 5 different acceleration episodes for payload masses up to 59 kg. A commercial low-cost payload device, the “Materials Dispersion Apparatus” of Instrumentation Technology Associates was tested for (1) integrity of mechanical function, (2) retention of fluid in its compartments, and (3) integrity of products under simulated re-entry g-loads. In particular, the sharp rise from 1 g to maximum g-loading that occurs during re-entry in various unmanned vehicles was successfully simulated, conditions were established for reliable functioning of the MDA, and crystals of 5 proteins suspended in compartments filled with mother liquor were subjected to this acceleration load.

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.

Planetary Entry Probes and Mass Spectroscopy: Tools and Science Results from In Situ Studies of Planetary Atmospheres and Surfaces

NASA Technical Reports Server (NTRS)

Niemann, Hasso B.

2007-01-01

Probing the atmospheres and surfaces of the planets and their moons with fast moving entry probes has been a very useful and essential technique to obtain in situ or quasi in situ scientific data (ground truth) which could not otherwise be obtained from fly by or orbiter only missions and where balloon, aircraft or lander missions are too complex and costly. Planetary entry probe missions have been conducted successfully on Venus, Mars, Jupiter and Titan after having been first demonstrated in the Earth's atmosphere. Future missions will hopefully also include more entry probe missions back to Venus and to the outer planets. 1 he success of and science returns from past missions, the need for more and better data, and a continuously advancing technology generate confidence that future missions will be even more successful with respect to science return and technical performance. I'he pioneering and tireless work of Al Seiff and his collaborators at the NASA Ames Research Center had provided convincing evidence of the value of entry probe science and how to practically implement flight missions. Even in the most recent missions involving entry probes i.e. Galileo and Cassini/Huygens A1 contributed uniquely to the science results on atmospheric structure, turbulence and temperature on Jupiter and Titan.

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)

Russian contribution to the ExoMars project

NASA Astrophysics Data System (ADS)

Zelenyi, L.; Korablev, O.; Rodionov, D.; Khartov, V.; Martynov, M.; Lukyanchikov, A.

2014-04-01

The ExoMars ESA-led mission is dedicated to study of Mars and in particular its habitability. It consists of two launches, one planned in 2016 to deliver to Mars a telecommunication and science orbiter Trace Gas Orbiter (TGO) and a demonstrator of entry into the atmosphere and landing on the Mars surface, Entry, Descent and Landing Demonstrator Module (EDM). In 2018 a rover with drilling capability will be delivered to the surface of Mars. Since 2012 this mission, previously planned in cooperation with NASA is being developed in cooperation with Roscosmos. Both launches are planned with Proton-Breeze. In 2016 Russia contributes a significant part of the TGO science payload. In 2018 the landing will be provided by a joint effort capitalizing on the EDM technology. Russia contributes few science instruments for the rover, and leads the development of a long-living geophysical platform on the surface of Mars. Russian science instruments for TGO, the Atmospheric Chemistry Suite (ACS) and the Fine Resolution Epithermal Neutrons Detector (FREND) constituent a half of its scientific payload, European instrument being NOMAD for mapping and detection of trace species, and CASSIS camera for high-resolution mapping of target areas. The ACS package consists of three spectrometers covering spectral range from 0.7 to 17 μm with spectral resolving power reaching 50000. It is dedicated to studies of the composition of the Martian atmosphere and the Martian climate. FREND is a neutron detector with a collimation module, which significantly narrows the field of view of the instrument, allowing to create higher resolution maps of hydrogen-abundant regions on Mars. The spatial resolution of FREND will be ~40 km from the 400- km TGO orbit that is ~10 times better than HEND on Mars-Odyssey. Additionally, FREND includes a dosimeter module for monitoring radiation levels in orbit around Mars. In the 2018 mission, Russia takes the major responsibility of the descent module. The primary goal of the descent module consists of the delivery of the 300-kg rover on the surface. The full mass of the module should not exceed 2000 kg. An aerodynamic shield and a parachute system assure the entry phase. A descent scenario with integrated retro-propulsion engines and landing on feet is being developed. Subsystems of the descend module are supplied by both Roscosmos and ESA. On the rover, Russia contributes two science instruments. ADRON-RM is a passive neutron detector to assess water contents in the Mars surface along the rover track. ISEM is a pencil-beam infrared spectrometer mounted at the mast of the rover and is primarily dedicated for the assessment of mineralogical composition, operating in coordination with high-resolution channel of PANCAM. Both instruments will assist with planning rover traverse, rover targeting operations, and sample selection. A major effort of the Russian science is concentrated on the 2018 landing platform. This is the part of the descent module remaining immobile after the rover egress. The platform, or the longliving geophysical station shall have guaranteed lifetime of one Martian year, and will be able to accommodate up to 50 kg of science payload. The final list of science investigations, which is yet to be finalized, includes the meteorological station, instruments to analyse atmospheric composition, geophysical instruments. Other investigations will provide analyses of the surface/shallow subsurface material complimentary to these on the rover, and other experiments, if resources permit. Current status of the project and the developments will be presented

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 maintenance case. The 2008 entry assessment was divided into two sections (see Figure 1). Entry I was the first, high speed portion of a lunar return and Entry II was the second, lower speed portion of a lunar return, which is similar (but not identical) to a typical ISS return.

Predictors of re-entry into the child protection system in Singapore: a cumulative ecological-transactional risk model.

PubMed

Li, Dongdong; Chu, Chi Meng; Ng, Wei Chern; Leong, Wai

2014-11-01

This study examines the risk factors of re-entry for 1,750 child protection cases in Singapore using a cumulative ecological-transactional risk model. Using administrative data, the present study found that the overall percentage of Child Protection Service (CPS) re-entry in Singapore is 10.5% based on 1,750 cases, with a range from 3.9% (within 1 year) to 16.5% (within 8 years after case closure). One quarter of the re-entry cases were observed to occur within 9 months from case closure. Seventeen risk factors, as identified from the extant literature, were tested for their utility to predict CPS re-entry in this study using a series of Cox regression analyses. A final list of seven risk factors (i.e., children's age at entry, case type, case closure result, duration of case, household income, family size, and mother's employment status) was used to create a cumulative risk score. The results supported the cumulative risk model in that higher risk score is related to higher risk of CPS re-entry. Understanding the prevalence of CPS re-entry and the risk factors associated with re-entry is the key to informing practice and policy in a culturally relevant way. The results from this study could then be used to facilitate critical case management decisions in order to enhance positive outcomes of families and children in Singapore's care system. Copyright © 2014 Elsevier Ltd. All rights reserved.

Life in the Universe? Is anybody out there?

NASA Astrophysics Data System (ADS)

2001-07-01

What is our understanding at the beginning of the 21st century? Is there any scientific evidence for other forms of life? How can you define life? What signs are we looking for? What would the reaction be if other forms of life were discovered? The European Organization for Nuclear Research (CERN), the European Space Agency and the European Southern Observatory, in cooperation with the European Association for Astronomy Education, have organised a competition to find out what young people in Europe think. The European Molecular Biology Laboratory and the European Synchrotron Radiation Facility are also involved. This "Life in the Universe" project is being mounted in collaboration with the research directorate of the European Commission for the European Week of Science and Technology in November this year. Competitions are already under way in 23 European countries to find the best projects from school students aged between 14 and 19. Entries can be in one of two categories: scientific or artistic. The projects can therefore be essays, newspapers, websites, artworks, poetry or even a theatrical or musical performance. Two winning teams (one in each category) from each country will be invited to a final event at CERN in Geneva on 8-11 November to present their projects to an international panel of experts at a special event devoting three days to enquiring into the possibility of other life forms existing in our Universe. This final event will be broadcast all over the world via the Internet. The home base of the "Life in the Universe" project is a vibrant website www.lifeinuniverse.org where details of the programme can be found. It is still under development but already has a wealth of information and links to the national websites, where all entries are posted. Is there other life in the Universe? We do not know - but the search is on!

Entry, Descent, and Landing technological barriers and crewed MARS vehicle performance analysis

NASA Astrophysics Data System (ADS)

Subrahmanyam, Prabhakar; Rasky, Daniel

2017-05-01

Mars has been explored historically only by robotic crafts, but a crewed mission encompasses several new engineering challenges - high ballistic coefficient entry, hypersonic decelerators, guided entry for reaching intended destinations within acceptable margins for error in the landing ellipse, and payload mass are all critical factors for evaluation. A comprehensive EDL parametric analysis has been conducted in support of a high mass landing architecture by evaluating three types of vehicles -70° Sphere Cone, Ellipsled and SpaceX hybrid architecture called Red Dragon as potential candidate options for crewed entry vehicles. Aerocapture at the Martian orbit of about 400 km and subsequent Entry-from-orbit scenarios were investigated at velocities of 6.75 km/s and 4 km/s respectively. A study on aerocapture corridor over a range of entry velocities (6-9 km/s) suggests that a hypersonic L/D of 0.3 is sufficient for a Martian aerocapture. Parametric studies conducted by varying aeroshell diameters from 10 m to 15 m for several entry masses up to 150 mt are summarized and results reveal that vehicles with entry masses in the range of about 40-80 mt are capable of delivering cargo with a mass on the order of 5-20 mt. For vehicles with an entry mass of 20 mt to 80 mt, probabilistic Monte Carlo analysis of 5000 cases for each vehicle were run to determine the final landing ellipse and to quantify the statistical uncertainties associated with the trajectory and attitude conditions during atmospheric entry. Strategies and current technological challenges for a human rated Entry, Descent, and Landing to the Martian surface are presented in this study.

Regolith-Derived Heat Shield for Planetary Body Entry and Descent System with In-Situ Fabrication

NASA Technical Reports Server (NTRS)

Hogue, Michael D.; Mueller, Robert P.; Sibille, Laurent; Hintze, Paul E.; Rasky, Daniel J.

2012-01-01

High-mass planetary surface access is one of NASA's Grand Challenges involving entry, descent, and landing (EDL). Heat shields fabricated in-situ can provide a thermal protection system for spacecraft that routinely enter a planetary atmosphere. Fabricating the heat shield from extraterrestrial regolith will avoid the costs of launching the heat shield mass from Earth. This project will investigate three methods to fabricate heat shield using extraterrestrial regolith.

Roles of Engineering Correlations in Hypersonic Entry Boundary Layer Transition Prediction

NASA Technical Reports Server (NTRS)

Campbell, Charles H.; King, Rudolph A.; Kergerise, Michael A.; Berry, Scott A.; Horvath, Thomas J.

2010-01-01

Efforts to design and operate hypersonic entry vehicles are constrained by many considerations that involve all aspects of an entry vehicle system. One of the more significant physical phenomenon that affect entry trajectory and thermal protection system design is the occurrence of boundary layer transition from a laminar to turbulent state. During the Space Shuttle Return To Flight activity following the loss of Columbia and her crew of seven, NASA's entry aerothermodynamics community implemented an engineering correlation based framework for the prediction of boundary layer transition on the Orbiter. The methodology for this implementation relies upon the framework of correlation techniques that have been in use for several decades. What makes the Orbiter boundary layer transition correlation implementation unique is that a statistically significant data set was acquired in multiple ground test facilities, flight data exists to assist in establishing a better correlation and the framework was founded upon state of the art chemical nonequilibrium Navier Stokes flow field simulations. The basic tenets that guided the formulation and implementation of the Orbiter Return To Flight boundary layer transition prediction capability will be reviewed as a recommended format for future empirical correlation efforts. The validity of this approach has since been demonstrated by very favorable comparison of recent entry flight testing performed with the Orbiter Discovery, which will be graphically summarized. These flight data can provide a means to validate discrete protuberance engineering correlation approaches as well as high fidelity prediction methods to higher confidence. The results of these Orbiter engineering and flight test activities only serve to reinforce the essential role that engineering correlations currently exercise in the design and operation of entry vehicles. The framework of information-related to the Orbiter empirical boundary layer transition prediction capability will be utilized to establish a fresh perspective on this role, to illustrate how quantitative statistical evaluations of empirical correlations can and should be used to assess accuracy and to discuss what the authors' perceive as a recent heightened interest in the application of high fidelity numerical modeling of boundary layer transition. Concrete results will also be developed related to empirical boundary layer transition onset correlations. This will include assessment of the discrete protuberance boundary layer transition onset data assembled for the Orbiter configuration during post-Columbia Return To Flight. Assessment of these data will conclude that momentum thickness Reynolds number based correlations have superior coefficients and uncertainty in comparison to roughness height based Reynolds numbers, aka Re(sub k) or Re(sub kk). In addition, linear regression results from roughness height Reynolds number based correlations will be evaluated, leading to a hypothesis that non-continuum effects play a role in the processes associated with incipient boundary layer transition on discrete protuberances.

KSC-2011-5243

NASA Image and Video Library

2011-07-08

CAPE CANAVERAL, Fla. -- A media event was held for the Multi-Purpose Crew Vehicle (MPCV) that was on display in a tent on the grounds of the Press Site at NASA's Kennedy Space Center in Florida during launch activities for space shuttle Atlantis' STS-135 mission to the International Space Station. The MPCV is based on the Orion design requirements for traveling beyond low Earth orbit and will serve as the exploration vehicle that will carry the crew to space, provide emergency abort capability, sustain the crew during the space travel, and provide safe re-entry from deep space return velocities. Atlantis began its final flight, with Commander Chris Ferguson, Pilot Doug Hurley and Mission Specialists Sandy Magnus and Rex Walheim on board, at 11:29 a.m. EDT July 8 to deliver the Raffaello multi-purpose logistics module packed with supplies and spare parts to the station. Also in Atlantis' payload bay is the Robotic Refueling Mission experiment that will investigate the potential for robotically refueling existing satellites in orbit. In addition, Atlantis will return with a failed ammonia pump module to help NASA better understand the failure mechanism and improve pump designs for future systems. STS-135 is the 33rd flight of Atlantis, the 37th shuttle mission to the space station, and the 135th and final mission of NASA's Space Shuttle Program. For more information, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts135/index.html. Photo credit: NASA/Jim Grossmann

Geoscience for Alaska's D-1 Lands: A preliminary report

USGS Publications Warehouse

Schmidt, Jeanine M.; Gamble, B.M.; Labay, Keith A.

2007-01-01

Purpose of This Report This interim report follows from the June 2006 recommendations to Congress by the BLM concerning disposition of the d-1 lands. That report recommended lifting of a significant number of d-1 PLOs, through the ongoing land management process within the BLM (e.g. resource management planning areas), or through Congressional action. The strategic actions outlined in this document refer only to Federal lands under US Bureau of Land Management (BLM) jurisdiction that 1) are affected by temporary withdrawals from mineral entry and mineral leasing by PLOs made pursuant to the Section 17(d)(1) of the ANCSA; 2) have been identified by the BLM as candidates for possible lifting of these PLOs and restrictions (U.S. Bureau of Land Management, 2006); and 3) lie outside of current Federal parks, preserves, monuments, refuges, reserves, wilderness areas and military installations that are closed to mineral entry, because within those areas the potential lifting of the d-1 restrictions has no practical effect. The resulting lands discussed here comprise approximately 121,000 km2 (29.9 million acres) of Alaska (Table 1) that, pending final resolution of Native and State land claims, will or may remain under Federal (BLM) control, and could be opened to mineral entry. For the purposes of this report, only these 29.9 million acres will hereafter be referred to as 'd-1' lands. This report gives a brief overview of the spatial distribution and physiographic setting, mineral occurrences, and mineral resource potential of the d-1lands. It outlines further geoscience information which could be compiled, collected, and evaluated in order to make a more accurate and comprehensive examination of the potential for undiscovered, locatable mineral resources on these Federal lands. This information is intended to provide guidance to USGS program managers and Federal land managers on matters of future exploration, access needs, and consequences of land status changes.

Maneuver Analysis and Targeting Strategy for the Stardust Re-Entry Capsule

NASA Technical Reports Server (NTRS)

Helfrich, Clifford E.; Bhat, Ram; Kangas, Julie; Wilson, Roby; Wong, Mau; Potts, Chris; Williams, Ken

2006-01-01

Stardust employed biased maneuvers to limit turns and minimize execution errors. Biased maneuvers also addressed planetary protection and safety issues. Stardust utilized a fixed-direction burn for the final maneuver to match the prevailing attitude so no turns were needed. Performance of the final burn was calibrated in flight.

78 FR 13860 - Application(s) for Duty-Free Entry of Scientific Instruments

Federal Register 2010, 2011, 2012, 2013, 2014

2013-03-01

... human diseases including cancer, cardiovascular disease, immunodeficiency and dementia. Justification... organism levels. The data will be used to improve management of human diseases including cancer, cardiovascular disease, immunodeficiency and dementia. Justification for Duty-Free Entry: There are no...

Hypersonic Cruise and Re-Entry Radio Frequency Blackout Mitigation: Alleviating the Communications Blackout Problem

NASA Technical Reports Server (NTRS)

Manning, Robert M.

2017-01-01

The work presented here will be a review of a NASA effort to provide a method to transmit and receive RF communications and telemetry through a re-entry plasma thus alleviating the classical RF blackout phenomenon.

Numerical and experimental study of the thermal degradation process during the atmospheric re-entry of a TiAl6V4 tank

NASA Astrophysics Data System (ADS)

Prévereaud, Y.; Vérant, J.-L.; Balat-Pichelin, M.; Moschetta, J.-M.

2016-05-01

To answer the question of space debris survivability during atmospheric entry ONERA uses its software named MUSIC/FAST. So, the first part of this paper is dedicated to the presentation of the ONERA tool and its validation by comparison with flight data and CFD computations. However, the influence of oxidation on the thermal degradation process and material properties in atmospheric entry conditions is still unknown. A second step is then devoted to the presentation of an experimental campaign investigating TA6V oxidation in atmospheric entry conditions, as the most of the debris found on ground are made of this material. Experiments have been realized using the MESOX facility implemented at the 6 kW solar furnace in PROMES-CNRS laboratory. Finally, an application of MUSIC/FAST is proposed on the atmospheric re-entry of a generic TA6V tank. Aiming at degradation assessment, a sensitive study to initial conditions is conducted. To complete computational analysis regarding degradation process by melting, a numerical analysis of the influence of oxidation on the thermal wall degradation during the tank atmospheric re-entry is presented as well.

The restructuring and future of {open_quotes}Mendelian Inheritance in Man{close_quotes} (MIM)

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

Pearson, P.L.; Francomano, C.; Antonarakis, S.

1994-09-01

Victor McKusick`s catalog {open_quotes}Mendelian Inheritance in Man{close_quotes} represents the most comprehensive compendum of human genetic disease information available today and has appeared as a series in book form for the last 30 years. The 11th edition will contain almost 7000 entries: approximately 2800 descriptions of human genetic disorders, 700 combined disorder/gene descriptions and 3500 pure gene descriptions. Until recently the content of the catalogs was maintained solely by McKusick with a support staff. However, a distributed editing system has now been established with the following primary components. New entries are initiated in Baltimore by science writers under the guidance ofmore » the senior editors and McKusick, following which the information is made immediately available to the public through online access. The subject editors can then review and edit the new or modified information without impeding the timeliness of entering new information. Entries are being reconstructured so that clinical disorder and gene information is divided into separate entries which will better represent the frequently complex relationship of gene mutations to individual clinical disorders in the data files. Further, each entry is being subdivided into logical topics which will enhance the power of electronic searching, making links between topics and improving readability. The old division of entries into autosomal dominant and recessive, etc., is being abandoned in favor of clinical disorder (phenotypes) and gene catalogs. The information is maintained in an SGML format which facilitates the production of many different types of output varying from the traditional book form to CD ROMs and various online formats including IRx, WAIS, Gopher and World Wide Web. This latter offers the exciting possibility of making hypertext links between entries and other data resources, including photographic, sound and video clips as part of the total MIM information.« less

Paramyxovirus fusion and entry: multiple paths to a common end.

PubMed

Chang, Andres; Dutch, Rebecca E

2012-04-01

The paramyxovirus family contains many common human pathogenic viruses, including measles, mumps, the parainfluenza viruses, respiratory syncytial virus, human metapneumovirus, and the zoonotic henipaviruses, Hendra and Nipah. While the expression of a type 1 fusion protein and a type 2 attachment protein is common to all paramyxoviruses, there is considerable variation in viral attachment, the activation and triggering of the fusion protein, and the process of viral entry. In this review, we discuss recent advances in the understanding of paramyxovirus F protein-mediated membrane fusion, an essential process in viral infectivity. We also review the role of the other surface glycoproteins in receptor binding and viral entry, and the implications for viral infection. Throughout, we concentrate on the commonalities and differences in fusion triggering and viral entry among the members of the family. Finally, we highlight key unanswered questions and how further studies can identify novel targets for the development of therapeutic treatments against these human pathogens.

Command generator tracker based direct model reference adaptive tracking guidance for Mars atmospheric entry

NASA Astrophysics Data System (ADS)

Li, Shuang; Peng, Yuming

2012-01-01

In order to accurately deliver an entry vehicle through the Martian atmosphere to the prescribed parachute deployment point, active Mars entry guidance is essential. This paper addresses the issue of Mars atmospheric entry guidance using the command generator tracker (CGT) based direct model reference adaptive control to reduce the adverse effect of the bounded uncertainties on atmospheric density and aerodynamic coefficients. Firstly, the nominal drag acceleration profile meeting a variety of constraints is planned off-line in the longitudinal plane as the reference model to track. Then, the CGT based direct model reference adaptive controller and the feed-forward compensator are designed to robustly track the aforementioned reference drag acceleration profile and to effectively reduce the downrange error. Afterwards, the heading alignment logic is adopted in the lateral plane to reduce the crossrange error. Finally, the validity of the guidance algorithm proposed in this paper is confirmed by Monte Carlo simulation analysis.

Radiation-Hardened Circuitry Using Mask-Programmable Analog Arrays. Final Report

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

Britton, Jr., Charles L.; Ericson, Milton Nance; Bobrek, Miljko

As the recent accident at Fukushima Daiichi so vividly demonstrated, telerobotic technologies capable of withstanding high radiation environments need to be readily available to enable operations, repair, and recovery under severe accident scenarios where human entry is extremely dangerous or not possible. Telerobotic technologies that enable remote operation in high dose rate environments have undergone revolutionary improvement over the past few decades. However, much of this technology cannot be employed in nuclear power environments due the radiation sensitivity of the electronics and the organic insulator materials currently in use. This is the final report of the activities involving the NEETmore » 2 project Radiation Hardened Circuitry Using Mask-Programmable Analog Arrays. We present a detailed functional block diagram of the proposed data acquisition system, the thought process leading to technical decisions, the implemented system, and the tested results from the systems. This system will be capable of monitoring at least three parameters of importance to nuclear reactor monitoring: temperature, radiation level, and pressure.« less

Space Radiation Transport Methods Development

NASA Technical Reports Server (NTRS)

Wilson, J. W.; Tripathi, R. K.; Qualls, G. D.; Cucinotta, F. A.; Prael, R. E.; Norbury, J. W.; Heinbockel, J. H.; Tweed, J.

2002-01-01

Improved spacecraft shield design requires early entry of radiation constraints into the design process to maximize performance and minimize costs. As a result, we have been investigating high-speed computational procedures to allow shield analysis from the preliminary design concepts to the final design. In particular, we will discuss the progress towards a full three-dimensional and computationally efficient deterministic code for which the current HZETRN evaluates the lowest order asymptotic term. HZETRN is the first deterministic solution to the Boltzmann equation allowing field mapping within the International Space Station (ISS) in tens of minutes using standard Finite Element Method (FEM) geometry common to engineering design practice enabling development of integrated multidisciplinary design optimization methods. A single ray trace in ISS FEM geometry requires 14 milliseconds and severely limits application of Monte Carlo methods to such engineering models. A potential means of improving the Monte Carlo efficiency in coupling to spacecraft geometry is given in terms of reconfigurable computing and could be utilized in the final design as verification of the deterministic method optimized design.

Lunar Entry Downmode Options for Orion

NASA Technical Reports Server (NTRS)

Smith, Kelly M.; Rea, Jeremy

2016-01-01

For Exploration Missions 1 and 2, the Orion capsules will be entering the Earth's atmosphere with speeds in excess of 11 km/s. In the event of a degraded Guidance, Navigation, and Control system, attempting the nominal guided entry may be inadvisable due to the potential for failures that result in a loss of vehicle (or crew, when crew are aboard). In such a case, a method of assuring Earth capture, water landing, and observence of trajectory constraints (heating, loads) is desired. Such a method should also be robust to large state uncertainty and variations in entry interface states. This document will explore four approaches evaluated and their performance in ensuring a safe return of the Orion capsule in the event of onboard system degradation.

Earth Entry Vehicle Design for Sample Return Missions Using M-SAPE

NASA Technical Reports Server (NTRS)

Samareh, Jamshid

2015-01-01

Most mission concepts that return sample material to Earth share one common element: an Earth entry vehicle (EEV). The primary focus of this paper is the examination of EEV design space for relevant sample return missions. Mission requirements for EEV concepts can be divided into three major groups: entry conditions (e.g., velocity and flight path angle), payload (e.g., mass, volume, and g-load limit), and vehicle characteristics (e.g., thermal protection system, structural topology, and landing concepts). The impacts of these requirements on the EEV design have been studied with an integrated system analysis tool, and the results will be discussed in details. In addition, through sensitivities analyses, critical design drivers that have been identified will be reviewed.

Mars Reconnaissance Orbiter Navigation Strategy for Dual Support of Insight and ExoMars Entry, Descent and Landing Demonstrator Module in 2016

NASA Technical Reports Server (NTRS)

Wagner, Sean V.; Menon, Premkumar R.; Chung, Min-Kun J.; Williams, Jessica L.

2015-01-01

Mars Reconnaissance Orbiter (MRO) will support NASA's InSight Mission and ESA's ExoMars Entry, Descent and Landing Demonstrator Module (EDM) in the fall of 2016 when both landers arrive at Mars. MRO provided relay support during the Entry, Descent and Landing (EDL) sequences of Mars Phoenix Lander in 2008 and the Mars Science Laboratory in 2012. Unlike these missions, MRO will coordinate between two EDL events separated by only three weeks: InSight on September 28, 2016 and EDM on October 19, 2016. This paper describes MRO Navigation's maneuver strategy to move MRO's ascending node to meet the In- Sight EDL phasing requirement and support EDM.

A Multifunctional Hot Structure Heatshield Concept for Planetary Entry

NASA Technical Reports Server (NTRS)

Walker, Sandra P.; Daryabeigi, Kamran; Samareh, Jamshid A.; Wagner, Robert; Waters, Allen

2015-01-01

A multifunctional hot structure heatshield concept is being developed to provide technology enhancements with significant benefits compared to the current state-of-the-art heatshield technology. These benefits can potentially enable future planetary missions. The concept is unique in integrating the function of the thermal protection system with the primary load carrying structural component. An advanced carbon-carbon material system has been evaluated for the load carrying structure, which will be utilized on the outer surface of the heatshield, and thus will operate as a hot structure exposed to the severe aerodynamic heating associated with planetary entry. Flexible, highly efficient blanket insulation is sized for use underneath the hot structure to maintain required operational internal temperatures. The approach followed includes developing preliminary designs to demonstrate feasibility of the concept and benefits over a traditional, baseline design. Where prior work focused on a concept for an Earth entry vehicle, the current efforts presented here are focused on developing a generic heatshield model and performing a trade study for a Mars entry application. This trade study includes both structural and thermal evaluation. The results indicate that a hot structure concept is a feasible alternative to traditional heatshields and may offer advantages that can enable future entry missions.

77 FR 75491 - Entry-Level Driver Training; Public Listening Session

Federal Register 2010, 2011, 2012, 2013, 2014

2012-12-20

... identified are supported by research and data analyses, including cost/benefit considerations. The session...-27748] Entry-Level Driver Training; Public Listening Session AGENCY: Federal Motor Carrier Safety Administration (FMCSA), DOT. ACTION: Notice of public listening session. SUMMARY: FMCSA announces that it will...

19 CFR 360.101 - Steel import licensing.

Code of Federal Regulations, 2010 CFR

2010-04-01

... Customs Duties INTERNATIONAL TRADE ADMINISTRATION, DEPARTMENT OF COMMERCE STEEL IMPORT MONITORING AND... timely completion of entry. (c) Foreign Trade Zone entries. All shipments of covered steel products into a foreign trade zones (FTZ), known as FTZ admissions, will require an import license prior to the...

19 CFR 360.101 - Steel import licensing.

Code of Federal Regulations, 2014 CFR

2014-04-01

... Customs Duties INTERNATIONAL TRADE ADMINISTRATION, DEPARTMENT OF COMMERCE STEEL IMPORT MONITORING AND... timely completion of entry. (c) Foreign Trade Zone entries. All shipments of covered steel products into a foreign trade zones (FTZ), known as FTZ admissions, will require an import license prior to the...

19 CFR 360.101 - Steel import licensing.

Code of Federal Regulations, 2012 CFR

2012-04-01

... Customs Duties INTERNATIONAL TRADE ADMINISTRATION, DEPARTMENT OF COMMERCE STEEL IMPORT MONITORING AND... timely completion of entry. (c) Foreign Trade Zone entries. All shipments of covered steel products into a foreign trade zones (FTZ), known as FTZ admissions, will require an import license prior to the...

19 CFR 360.101 - Steel import licensing.

Code of Federal Regulations, 2011 CFR

2011-04-01

... Customs Duties INTERNATIONAL TRADE ADMINISTRATION, DEPARTMENT OF COMMERCE STEEL IMPORT MONITORING AND... timely completion of entry. (c) Foreign Trade Zone entries. All shipments of covered steel products into a foreign trade zones (FTZ), known as FTZ admissions, will require an import license prior to the...

19 CFR 360.101 - Steel import licensing.

Code of Federal Regulations, 2013 CFR

2013-04-01

... Customs Duties INTERNATIONAL TRADE ADMINISTRATION, DEPARTMENT OF COMMERCE STEEL IMPORT MONITORING AND... timely completion of entry. (c) Foreign Trade Zone entries. All shipments of covered steel products into a foreign trade zones (FTZ), known as FTZ admissions, will require an import license prior to the...

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

NASA Technical Reports Server (NTRS)

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

2016-01-01

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

Cygnus Orbital ATK OA-6 Final Hatch Closure

NASA Image and Video Library

2016-03-06

Inside the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center in Florida, the hatch is closed for the upcoming flight of a Cygnus cargo vessel. The spacecraft is scheduled for the upcoming Orbital ATK Commercial Resupply Services-6 mission to deliver hardware and supplies to the International Space Station. When members of the ISS Expedition 47 crew open the hatch, they will be greeted with a sign noting the spacecraft was named SS Rick Husband in honor of the commander of the STS-107 mission. On that flight, the crew of the space shuttle Columbia was lost during re-entry on Feb. 1, 2003. The Cygnus is scheduled to lift off atop a United Launch Alliance Atlas V rocket on March 22.

76 FR 15216 - Security Zones; Cruise Ships, Port of San Diego, CA

Federal Register 2010, 2011, 2012, 2013, 2014

2011-03-21

...The Coast Guard is amending its regulations for Security Zones; Cruise Ships, Port of San Diego, California, by providing a common description of all security zones created by this section to encompass only navigable waters within a 100 yard radius around any cruise ship that is located within the San Diego port area landward of the sea buoys bounding the Port of San Diego. This final rule removes a reference to shore area that is no longer necessary to provide for the safety of the cruise ship, vessels, and users of the waterway. Entry into these security zones will be prohibited unless specifically authorized by the Captain of the Port (COTP) San Diego, or a COTP designated representative.

Migrant Home Attendants: Regulation and Practice in 7 Countries

PubMed Central

Garms-Homolová, Vjenka; Bentwich, Miriam

2013-01-01

We compared regulation and working and living conditions of foreign home attendants in 7 countries (Canada, Germany, Israel, Singapore, Spain, United Kingdom, United States). We conducted a literature search in the PSYCinfo, MEDLINE, and Google Scholar databases for 2002 to 2012. We found substantial between-country differences in the legal status of migrant caregivers and regulations regarding working and living conditions and drew 3 conclusions. Improving regulations will likely improve not only the well-being of foreign home attendants but also the care they provide. Countries in which many foreign home attendants work without specific legal entry programs should rethink their policies. Finally, requiring an employer’s recommendation to obtain permanent residency may constrain foreign workers from registering complaints or leaving suboptimal employment situations. PMID:24134377

Parametric Robust Control and System Identification: Unified Approach

NASA Technical Reports Server (NTRS)

Keel, L. H.

1996-01-01

During the period of this support, a new control system design and analysis method has been studied. This approach deals with control systems containing uncertainties that are represented in terms of its transfer function parameters. Such a representation of the control system is common and many physical parameter variations fall into this type of uncertainty. Techniques developed here are capable of providing nonconservative analysis of such control systems with parameter variations. We have also developed techniques to deal with control systems when their state space representations are given rather than transfer functions. In this case, the plant parameters will appear as entries of state space matrices. Finally, a system modeling technique to construct such systems from the raw input - output frequency domain data has been developed.

The entry-level occupational therapy clinical doctorate: The next education wave of change in Canada?

PubMed

Brown, Ted; Crabtree, Jeffrey L; Wells, Joe; Mu, Keli

2016-12-01

Currently, Canada and the United States are the only two countries that mandate entry to the occupational therapy profession at the master's level. There was a recommendation considered by the American Occupational Therapy Association that by 2025 all education programs would move to the clinical doctorate level. In August 2015, the Accreditation Council for Occupational Therapy Education made the formal decision that for now, the entry-level qualification for occupational therapists in the United States will remain at both the master's and clinical doctorate levels. This article presents an overview of the types of doctorates available, the pros and cons of moving to the clinical doctorate, and some potential questions that will need to be considered. Is the next step in the educational progression of occupational therapy in Canada the entry-level clinical doctorate? What are the potential implications for the profession, our clients, and funders? Further discourse and investigation of this issue is needed.

Free Flight Ground Testing of ADEPT in Advance of the Sounding Rocket One Flight Experiment

NASA Technical Reports Server (NTRS)

Smith, B. P.; Dutta, S.

2017-01-01

The Adaptable Deployable Entry and Placement Technology (ADEPT) project will be conducting the first flight test of ADEPT, titled Sounding Rocket One (SR-1), in just two months. The need for this flight test stems from the fact that ADEPT's supersonic dynamic stability has not yet been characterized. The SR-1 flight test will provide critical data describing the flight mechanics of ADEPT in ballistic flight. These data will feed decision making on future ADEPT mission designs. This presentation will describe the SR-1 scientific data products, possible flight test outcomes, and the implications of those outcomes on future ADEPT development. In addition, this presentation will describe free-flight ground testing performed in advance of the flight test. A subsonic flight dynamics test conducted at the Vertical Spin Tunnel located at NASA Langley Research Center provided subsonic flight dynamics data at high and low altitudes for multiple center of mass (CoM) locations. A ballistic range test at the Hypervelocity Free Flight Aerodynamics Facility (HFFAF) located at NASA Ames Research Center provided supersonic flight dynamics data at low supersonic Mach numbers. Execution and outcomes of these tests will be discussed. Finally, a hypothesized trajectory estimate for the SR-1 flight will be presented.

PCMdb: Pancreatic Cancer Methylation Database

NASA Astrophysics Data System (ADS)

Nagpal, Gandharva; Sharma, Minakshi; Kumar, Shailesh; Chaudhary, Kumardeep; Gupta, Sudheer; Gautam, Ankur; Raghava, Gajendra P. S.

2014-02-01

Pancreatic cancer is the fifth most aggressive malignancy and urgently requires new biomarkers to facilitate early detection. For providing impetus to the biomarker discovery, we have developed Pancreatic Cancer Methylation Database (PCMDB, http://crdd.osdd.net/raghava/pcmdb/), a comprehensive resource dedicated to methylation of genes in pancreatic cancer. Data was collected and compiled manually from published literature. PCMdb has 65907 entries for methylation status of 4342 unique genes. In PCMdb, data was compiled for both cancer cell lines (53565 entries for 88 cell lines) and cancer tissues (12342 entries for 3078 tissue samples). Among these entries, 47.22% entries reported a high level of methylation for the corresponding genes while 10.87% entries reported low level of methylation. PCMdb covers five major subtypes of pancreatic cancer; however, most of the entries were compiled for adenocarcinomas (88.38%) and mucinous neoplasms (5.76%). A user-friendly interface has been developed for data browsing, searching and analysis. We anticipate that PCMdb will be helpful for pancreatic cancer biomarker discovery.

Heatshield for Extreme Entry Environment Technology (HEEET) Enabling Missions Beyond Heritage Carbon Phenolic

NASA Technical Reports Server (NTRS)

Stackpoole, M.; Boghozian, T.; Chavez-Garcia, J.; Ellerby, D.; Fowler, M.; Gage, P.; Gasch, M.; Gonzales, G.; Kazemba, C.; Kellermann, C.;

An Interim Report on NASA's Draft Space Technology Roadmaps

NASA Technical Reports Server (NTRS)

2011-01-01

NASA has developed a set of 14 draft roadmaps to guide the development of space technologies under the leadership of the NASA Office of the Chief Technologist (OCT). Each of these roadmaps focuses on a particular technology area (TA). The roadmaps are intended to foster the development of advanced technologies and concepts that address NASA's needs and contribute to other aerospace and national needs. OCT requested that the National Research Council conduct a study to review the draft roadmaps, gather and assess relevant community input, and make recommendations and suggest priorities to inform NASA's decisions as it finalizes its roadmaps. The statement of task states that "based on the results of the community input and its own deliberations, the steering committee will prepare a brief interim report that addresses high-level issues associated with the roadmaps, such as the advisability of modifying the number or technical focus of the draft NASA roadmaps." This interim report, which does not include formal recommendations, addresses that one element of the study charge. NASA requested this interim report so that it would have the opportunity to make an early start in modifying the draft roadmaps based on feedback from the panels and steering committee. The final report will address all other tasks in the statement of task. In particular, the final report will include a prioritization of technologies, will describe in detail the prioritization process and criteria, and will include specific recommendations on a variety of topics, including many of the topics mentioned in this interim report. In developing both this interim report and the final report to come, the steering committee draws on the work of six study panels organized by technical area, loosely following the organization of the 14 roadmaps, as follows: A Panel 1: Propulsion and Power TA01 Launch Propulsion Systems TA02 In-Space Propulsion Technologies TA03 Space Power and Energy Storage Systems TA13 Ground and Launch Systems Processing B Panel 2: Robotics, Communications, and Navigation TA04 Robotics, TeleRobotics, and Autonomous Systems TA05 Communication and Navigation Systems C Panel 3: Instruments and Computing TA08 Science Instruments, Observatories, and Sensor Systems TA11 Modeling, Simulation, Information Technology, and Data Processing D Panel 4: Human Health and Surface Exploration TA06 Human Health, Life Support, and Habitation Systems TA07 Human Exploration Destination Systems E Panel 5: Materials Panel TA10 Nanotechnology TA12 Materials, Structures, Mechanical Systems, and Manufacturing TA14 Thermal Management Systems F Panel 6: Entry, Descent, and Landing Panel TA09 Entry, Descent, and Landing Systems In addition to drawing on the expertise represented on the steering committee and panels, the committee obtained input from each of 14 public workshops held on each of the 14 roadmaps. At these 1-day workshops, invited speakers, guests, and members of the public engaged in discussions on the different technology areas and their value to NASA. Broad community input was also solicited from a public website, where more than 240 public comments were received on the draft roadmaps in response to application of criteria (such as benefit, risk and reasonableness, and alignment with NASA and national goals) that the steering committee established. This interim report reflects the results of deliberations by the steering committee in light of these public inputs as well as additional inputs from the six panels. The steering committee's final report will be completed early in 2012. That report will prioritize the technologies that span the entire scope of the 14 roadmaps and provide additional guidance on crosscutting themes and other relevant topics.

The Hemagglutinin of Bat-Associated Influenza Viruses Is Activated by TMPRSS2 for pH-Dependent Entry into Bat but Not Human Cells

PubMed Central

Hoffmann, Markus; Krüger, Nadine; Zmora, Pawel; Wrensch, Florian; Herrler, Georg; Pöhlmann, Stefan

2016-01-01

New World bats have recently been discovered to harbor influenza A virus (FLUAV)-related viruses, termed bat-associated influenza A-like viruses (batFLUAV). The internal proteins of batFLUAV are functional in mammalian cells. In contrast, no biological functionality could be demonstrated for the surface proteins, hemagglutinin (HA)-like (HAL) and neuraminidase (NA)-like (NAL), and these proteins need to be replaced by their human counterparts to allow spread of batFLUAV in human cells. Here, we employed rhabdoviral vectors to study the role of HAL and NAL in viral entry. Vectors pseudotyped with batFLUAV-HAL and -NAL were able to enter bat cells but not cells from other mammalian species. Host cell entry was mediated by HAL and was dependent on prior proteolytic activation of HAL and endosomal low pH. In contrast, sialic acids were dispensable for HAL-driven entry. Finally, the type II transmembrane serine protease TMPRSS2 was able to activate HAL for cell entry indicating that batFLUAV can utilize human proteases for HAL activation. Collectively, these results identify viral and cellular factors governing host cell entry driven by batFLUAV surface proteins. They suggest that the absence of a functional receptor precludes entry of batFLUAV into human cells while other prerequisites for entry, HAL activation and protonation, are met in target cells of human origin. PMID:27028521

Angle of Attack Modulation for Mars Entry Terminal State Optimization

NASA Technical Reports Server (NTRS)

Lafleur, Jarret M.; Cerimele, Christopher J.

2009-01-01

From the perspective of atmospheric entry, descent, and landing (EDL), one of the most foreboding destinations in the solar system is Mars due in part to its exceedingly thin atmosphere. To benchmark best possible scenarios for evaluation of potential Mars EDL system designs, a study is conducted to optimize the entry-to-terminal-state portion of EDL for a variety of entry velocities and vehicle masses, focusing on the identification of potential benefits of enabling angle of attack modulation. The terminal state is envisioned as one appropriate for the initiation of terminal descent via parachute or other means. A particle swarm optimizer varies entry flight path angle, ten bank profile points, and ten angle of attack profile points to find maximum-final-altitude trajectories for a 10 30 m ellipsled at 180 different combinations of values for entry mass, entry velocity, terminal Mach number, and minimum allowable altitude. Parametric plots of maximum achievable altitude are shown, as are examples of optimized trajectories. It is shown that appreciable terminal state altitude gains (2.5-4.0 km) over pure bank angle control may be possible if angle of attack modulation is enabled for Mars entry vehicles. Gains of this magnitude could prove to be enabling for missions requiring high-altitude landing sites. Conclusions are also drawn regarding trends in the bank and angle of attack profiles that produce the optimal trajectories in this study, and directions for future work are identified.

Microbe-independent entry of oomycete RxLR effectors and fungal RxLR-like effectors into plant and animal cells is specific and reproducible.

PubMed

Tyler, Brett M; Kale, Shiv D; Wang, Qunqing; Tao, Kai; Clark, Helen R; Drews, Kelly; Antignani, Vincenzo; Rumore, Amanda; Hayes, Tristan; Plett, Jonathan M; Fudal, Isabelle; Gu, Biao; Chen, Qinghe; Affeldt, Katharyn J; Berthier, Erwin; Fischer, Gregory J; Dou, Daolong; Shan, Weixing; Keller, Nancy P; Martin, Francis; Rouxel, Thierry; Lawrence, Christopher B

2013-06-01

A wide diversity of pathogens and mutualists of plant and animal hosts, including oomycetes and fungi, produce effector proteins that enter the cytoplasm of host cells. A major question has been whether or not entry by these effectors can occur independently of the microbe or requires machinery provided by the microbe. Numerous publications have documented that oomycete RxLR effectors and fungal RxLR-like effectors can enter plant and animal cells independent of the microbe. A recent reexamination of whether the RxLR domain of oomycete RxLR effectors is sufficient for microbe-independent entry into host cells concluded that the RxLR domains of Phytophthora infestans Avr3a and of P. sojae Avr1b alone are NOT sufficient to enable microbe-independent entry of proteins into host and nonhost plant and animal cells. Here, we present new, more detailed data that unambiguously demonstrate that the RxLR domain of Avr1b does show efficient and specific entry into soybean root cells and also into wheat leaf cells, at levels well above background nonspecific entry. We also summarize host cell entry experiments with a wide diversity of oomycete and fungal effectors with RxLR or RxLR-like motifs that have been independently carried out by the seven different labs that coauthored this letter. Finally we discuss possible technical reasons why specific cell entry may have been not detected by Wawra et al. (2013).

HSV-1 interaction to 3-O-sulfated heparan sulfate in mouse-derived DRG explant and profiles of inflammatory markers during virus infection.

PubMed

Sharthiya, Harsh; Seng, Chanmoly; Van Kuppevelt, T H; Tiwari, Vaibhav; Fornaro, Michele

2017-06-01

The molecular mechanism of herpes simplex virus (HSV) entry and the associated inflammatory response in the nervous system remain poorly understood. Using mouse-derived ex vivo dorsal root ganglia (DRG) explant model and single cell neurons (SCNs), in this study, we provided a visual evidence for the expression of heparan sulfate (HS) and 3-O-sulfated heparan sulfate (3-OS HS) followed by their interactions with HSV-1 glycoprotein B (gB) and glycoprotein D (gD) during cell entry. Upon heparanase treatment of DRG-derived SCN, a significant inhibition of HSV-1 entry was observed suggesting the involvement of HS role during viral entry. Finally, a cytokine array profile generated during HSV-1 infection in DRG explant indicated an enhanced expression of chemokines (LIX, TIMP-2, and M-CSF)-known regulators of HS. Taken together, these results highlight the significance of HS during HSV-1 entry in DRG explant. Further investigation is needed to understand which isoforms of 3-O-sulfotransferase (3-OST)-generated HS contributed during HSV-1 infection and associated cell damage.

Protecting Astronaut Health at First Entry into Vehicles Visiting the international Space Station: Insights from Whole-Module Offgas Testing

NASA Technical Reports Server (NTRS)

Meyers, Valerie

2014-01-01

NASA has accumulated considerable experience in offgas testing of whole modules prior to their docking with the International Space Station (ISS). Since 1998, the Space Toxicology Office has performed offgas testing of the Lab module, both MPLM modules, US Airlock, Node 1, Node 2, Node 3, ATV1, HTV1, and three commercial vehicles. The goal of these tests is twofold: first, to protect the crew from adverse health effects of accumulated volatile pollutants when they first enter the module on orbit, and secondly, to determine the additional pollutant load that the ISS air revitalization systems must handle. In order to predict the amount of accumulated pollutants, the module is sealed for at least 1/5th the worst-case time interval that could occur between the last clean air purge and final hatch closure on the ground and the crew's first entry on orbit. This time can range from a few days to a few months. Typically, triplicate samples are taken at pre-planned times throughout the test. Samples are then analyzed by gas chromatography and mass spectrometry, and the rate of accumulation of pollutants is then extrapolated over time. The analytical values are indexed against 7-day spacecraft maximum allowable concentrations (SMACs) to provide a prediction of the total toxicity value (T-value) at the time of first entry. This T-value and the toxicological effects of specific pollutants that contribute most to the overall toxicity are then used to guide first entry operations. Finally, results are compared to first entry samples collected on orbit to determine the predictive ability of the ground-based offgas test.

A Pilot Study for Gainful Employment in Home Economics. Final Report. Volume IV, A Suggested Curriculum Guide for Preparing Food Service Workers for Entry Level Jobs.

ERIC Educational Resources Information Center

Cozine, June; And Others

Curriculum guidelines for teacher use in organizing and teaching a course to prepare 11th and 12th grade students for entry level food service occupations were developed as part of a pilot study which is reported in VT 006 870. The 1-year program requires 2 hours daily plus 10 hours per week on-the-job work experience. Content areas are: (1)…

Consensus statements on occupational therapy education and professional development related to driving and community mobility.

PubMed

Stav, Wendy B

2014-04-01

Professional and postprofessional education for occupational therapy practitioners in the area of driving and community mobility has been inconsistent and not sufficient to meet the growing community mobility needs of the aging population. This article reviews the current expectations of entry-level occupational therapy education, the postprofessional credentialing opportunities, and the professional development path for occupational therapy practitioners. Finally, consensus statements are presented to move both entry-level and professional education forward in the area of driving and community mobility.

A Pilot Study for Gainful Employment in Home Economics. Final Report. Volume III, A Suggested Curriculum Guide for Preparing Clothing Service Workers for Entry Level Jobs.

ERIC Educational Resources Information Center

Cozine, June; And Others

Curriculum guidelines for teacher use in organizing and teaching a course to prepare 11th and 12th grade students for entry level clothing service occupations were developed as part of a pilot study which is reported in VT 006 870. The 1-year program requires 2 hours daily; a 1-hour lab experience or on-the-job work experience is suggested for the…

Hospitality Industry Technology Training (HITT). Final Performance Report, April 1, 1989-December 31, 1990.

ERIC Educational Resources Information Center

Mount Hood Community Coll., Gresham, OR.

This final performance report includes a third-party evaluation and a replication guide. The first section describes a project to develop and implement an articulated curriculum for grades 8-14 to prepare young people for entry into hospitality/tourism-related occupations. It discusses the refinement of existing models, pilot test, curriculum…

GRoW Buffalo Final Report

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

Bohm, Martha

This document provides final reporting on the GRoW Home, University at Buffalo's entry to the 2015 Solar Decathlon competition in Irvine, CA. The report summarizes fundraising efforts, documents media outreach, lists online presence, analyzes the organizer's communication, describes post-competition life of the house and future employment plans for student team members. Last, it suggests improvements for future decathlons.

Recent Progress in Entry Radiation Measurements in the NASA Ames Electric ARC Shock Tube Facility

NASA Technical Reports Server (NTRS)

Cruden, Brett A.

2012-01-01

The Electric Arc Shock Tube (EAST) at NASA Ames Research Center is NASA's only working shock tube capable of obtaining conditions representative of entry in a multitude of planetary atmospheres. The facility is capable of mapping spectroscopic signatures of a wide range of planetary entries from the Vacuum Ultraviolet through Mid-Wave Infrared (120-5500 nm). This paper summarizes the tests performed in EAST for Earth, Mars and Venus entries since 2008, then focuses on a specific test case for CO2/N2 mixtures. In particular, the paper will focus on providing information for the proper interpretation of the EAST data.

Structures and Mechanisms Design Concepts for Adaptive Deployable Entry Placement Technology

NASA Technical Reports Server (NTRS)

Yount, Bryan C.; Arnold, James O.; Gage, Peter J.; Mockelman, Jeffrey; Venkatapathy, Ethiraj

2012-01-01

System studies have shown that large deployable aerodynamic decelerators such as the Adaptive Deployable Entry and Placement Technology (ADEPT) concept can revolutionize future robotic and human exploration missions involving atmospheric entry, descent and landing by significantly reducing the maximum heating rate, total heat load, and deceleration loads experienced by the spacecraft during entry [1-3]. ADEPT and the Hypersonic Inflatable Aerodynamic Decelerator (HIAD) [4] share the approach of stowing the entry system in the shroud of the launch vehicle and deploying it to a much larger diameter prior to entry. The ADEPT concept provides a low ballistic coefficient for planetary entry by employing an umbrella-like deployable structure consisting of ribs, struts and a fabric cover that form an aerodynamic decelerator capable of undergoing hypersonic flight. The ADEPT "skin" is a 3-D woven carbon cloth that serves as a thermal protection system (TPS) and as a structural surface that transfers aerodynamic forces to the underlying ribs [5]. This paper focuses on design activities associated with integrating ADEPT components (cloth, ribs, struts and mechanisms) into a system that can function across all configurations and environments of a typical mission concept: stowed during launch, in-space deployment, entry, descent, parachute deployment and separation from the landing payload. The baseline structures and mechanisms were selected via trade studies conducted during the summer and fall of 2012. They are now being incorporated into the design of a ground test article (GTA) that will be fabricated in 2013. It will be used to evaluate retention of the stowed configuration in a launch environment, mechanism operation for release, deployment and locking, and static strength of the deployed decelerator. Of particular interest are the carbon cloth interfaces, underlying hot structure, (Advanced Carbon- Carbon ribs) and other structural components (nose cap, struts, and main body) designed to withstand the pressure and extremely high heating experienced during planetary entry.

Aerothermodynamics of Blunt Body Entry Vehicles. Chapter 3

NASA Technical Reports Server (NTRS)

Hollis, Brian R.; Borrelli, Salvatore

2011-01-01

In this chapter, the aerothermodynamic phenomena of blunt body entry vehicles are discussed. Four topics will be considered that present challenges to current computational modeling techniques for blunt body environments: turbulent flow, non-equilibrium flow, rarefied flow, and radiation transport. Examples of comparisons between computational tools to ground and flight-test data will be presented in order to illustrate the challenges existing in the numerical modeling of each of these phenomena and to provide test cases for evaluation of Computational Fluid Dynamics (CFD) code predictions.

Aerothermodynamics of blunt body entry vehicles

NASA Astrophysics Data System (ADS)

Hollis, Brian R.; Borrelli, Salvatore

2012-01-01

In this chapter, the aerothermodynamic phenomena of blunt body entry vehicles are discussed. Four topics will be considered that present challenges to current computational modeling techniques for blunt body environments: turbulent flow, non-equilibrium flow, rarefied flow, and radiation transport. Examples of comparisons between computational tools to ground and flight-test data will be presented in order to illustrate the challenges existing in the numerical modeling of each of these phenomena and to provide test cases for evaluation of computational fluid dynamics (CFD) code predictions.

Application of the FADS system on the Re-entry Module

NASA Astrophysics Data System (ADS)

Zhen, Huang

2016-07-01

The aerodynamic model for Flush Air Data Sensing System (FADS) is built based on the surface pressure distribution obtained through the pressure orifices laid on specific positions of the surface,and the flight parameters,such as angle of attack,angle of side-slip,Mach number,free-stream static pressure and dynamic pressure are inferred from the aerodynamic model.The flush air data sensing system (FADS) has been used on several flight tests of aircraft and re-entry vehicle,such as,X-15,space shuttle,F-14,X-33,X-43A and so on. This paper discusses the application of the FADS on the re-entry module with blunt body to obtain high-precision aerodynamic parameters.First of all,a basic theory and operating principle of the FADS is shown.Then,the applications of the FADS on typical aircrafts and re-entry vehicles are described.Thirdly,the application mode on the re-entry module with blunt body is discussed in detail,including aerodynamic simulation,pressure distribution,trajectory reconstruction and the hardware shoule be used,such as flush air data sensing system(FADS),inertial navigation system (INS),data acquisition system,data storage system.Finally,ablunt module re-entry flight test from low earth orbit (LEO) is planned to obtain aerodynamic parameters and amend the aerodynamic model with this FADS system data.The results show that FADS system can be applied widely in re-entry module with blunt bodies.

Data entry and error embedding system

NASA Technical Reports Server (NTRS)

Woo, Daniel N. (Inventor); Woo, Jr., John (Inventor)

1998-01-01

A data entry and error embedding system in which, first, a document is bitmapped and recorded in a first memory. Then, it is displayed, and portions of it to be replicated by data entry are underlayed by a window, into which window replicated data is entered in location and size such that it is juxtaposed just below that which is replicated, enhancing the accuracy of replication. Second, with this format in place, selected portions of the replicated data are altered by the insertion of character or word substitutions, thus the embedding of errors. Finally, a proofreader would endeavor to correct the error embedded data and a record of his or her changes recorded. In this manner, the skill level of the proofreader and accuracy of the data are computed.

Entry, Descent, and Landing Operations Analysis for the Mars Phoenix Lander

NASA Technical Reports Server (NTRS)

Prince, Jill L.; Desai, Prasun N.; Queen, Eric M.; Grover, Myron R.

2008-01-01

The Mars Phoenix lander was launched August 4, 2007 and remained in cruise for ten months before landing in the northern plains of Mars in May 2008. The one-month Entry, Descent, and Landing (EDL) operations phase prior to entry consisted of daily analyses, meetings, and decisions necessary to determine if trajectory correction maneuvers and environmental parameter updates to the spacecraft were required. An overview of the Phoenix EDL trajectory simulation and analysis that was performed during the EDL approach and operations phase is described in detail. The evolution of the Monte Carlo statistics and footprint ellipse during the final approach phase is also provided. The EDL operations effort accurately delivered the Phoenix lander to the desired landing region on May 25, 2008.

Control of communicable disease; foreign--requirements for importers of nonhuman primates (NHP). Final rule.

PubMed

2013-02-15

The Centers for Disease Control and Prevention (CDC), located within the Department of Health and Human Services (HHS), is amending regulations for the importation of live nonhuman primates (NHPs) by extending existing requirements for the importation of Macaca fascicularis (cynomolgus), Chlorocebus aethiops (African green), and Macaca mulatta (rhesus) monkeys to all NHPs with the exception of the filovirus testing requirement. Filovirus testing will only be required for Old World NHPs in quarantine that have illness consistent with filovirus infection or that die for any reason other than trauma during quarantine. HHS/CDC is also finalizing a provision to reduce the frequency at which importers of cynomolgus, African green, and rhesus monkeys are required to renew their special permits (from every 180 days to every 2 years). HHS/CDC is incorporating existing guidelines into the regulations and adding new provisions to address the following: NHPs imported as part of an animal act; NHPs imported or transferred by zoological societies; the transfer of NHPs from approved laboratories; and non-live imported NHP products. Finally, HHS/CDC is also requiring that all NHPs be imported only through ports of entry where a HHS/CDC quarantine station is located.

Re-Entry Point Targeting for LEO Spacecraft using Aerodynamic Drag

NASA Technical Reports Server (NTRS)

Omar, Sanny; Bevilacqua, Riccardo; Fineberg, Laurence; Treptow, Justin; Johnson, Yusef; Clark, Scott

2016-01-01

Most Low Earth Orbit (LEO) spacecraft do not have thrusters and re-enter atmosphere in random locations at uncertain times. Objects pose a risk to persons, property, or other satellites. Has become a larger concern with the recent increase in small satellites. Working on a NASA funded project to design a retractable drag device to expedite de-orbit and target a re-entry location through modulation of the drag area. Will be discussing the re-entry point targeting algorithm here.

Grid resolution and solution convergence for Mars Pathfinder forebody

NASA Technical Reports Server (NTRS)

Nettelhorst, Heather L.; Mitcheltree, Robert A.

1994-01-01

As part of the Discovery Program, NASA Plans to launch a series of probes to Mars. The Mars Pathfinder project is the first of this series with a scheduled Mars arrival in July 1997. The entry vehicle will perform a direct entry into the atmosphere and deliver a lander to the surface. Predicting the entry vehicle's flight performance and designing the forebody heatshield requires knowledge of the expected aerothermodynamic environment. Much of this knowledge can be obtained through computational fluid dynamic (CFD) analysis.

Mars Science Laboratory Entry, Descent and Landing System Development Challenges and Preliminary Flight Performance

NASA Technical Reports Server (NTRS)

Steltzner, Adam D.; San Martin, A. Miguel; Rivellini, Tommaso P.

2013-01-01

The Mars Science Laboratory project recently landed the Curiosity rover on the surface of Mars. With the success of the landing system, the performance envelope of entry, descent, and landing capabilities has been extended over the previous state of the art. This paper will present an overview of the MSL entry, descent, and landing system, a discussion of a subset of its development challenges, and include a discussion of preliminary results of the flight reconstruction effort.

Sample Returns Missions in the Coming Decade

NASA Technical Reports Server (NTRS)

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

2000-01-01

In the coming decade, several missions will attempt to return samples to Earth from varying parts of the solar system. These samples will provide invaluable insight into the conditions present during the early formation of the solar system, and possibly give clues to how life began on Earth. A description of five sample return missions is presented (Stardust, Genesis, Muses-C. Mars Sample Return, and Comet Nucleus Sample Return). An overview of each sample return mission is given, concentrating particularly on the technical challenges posed during the Earth entry, descent, and landing phase of the missions. Each mission faces unique challenges in the design of an Earth entry capsule. The design of the entry capsule must address the aerodynamic, heating, deceleration, landing, and recovery requirements for the safe return of samples to Earth.

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 conditions. For a lander an accurate landing point could be achieved by providing the lander with a small gliding capacity, using the large potential energy available from being subsonic at high altitude. Alternatively the ballute can be retained to act as a parachute or soft-landing device, or to float the payload as a buoyant aerobot. As expected, the ballute has smaller size for relatively small entry speeds, such as for Mars and Titan, or for the extensive atmosphere of a low-gravity planet such as Pluto. Details of a ballute to place a small Mars orbiter and a small Pluto lander will be given to illustrate the concept. The author will discuss presently available ballute materials and a development program of aerodynamic tests and materials that would be required for ballutes to achieve their full potential.

19 CFR 122.64 - Other aircraft.

Code of Federal Regulations, 2010 CFR

2010-04-01

... Duties U.S. CUSTOMS AND BORDER PROTECTION, DEPARTMENT OF HOMELAND SECURITY; DEPARTMENT OF THE TREASURY... the port of entry (regardless of whether it is an international airport) nearest the final departure airport. ...

19 CFR 122.64 - Other aircraft.

Code of Federal Regulations, 2013 CFR

2013-04-01

... Duties U.S. CUSTOMS AND BORDER PROTECTION, DEPARTMENT OF HOMELAND SECURITY; DEPARTMENT OF THE TREASURY... the port of entry (regardless of whether it is an international airport) nearest the final departure airport. ...

19 CFR 122.64 - Other aircraft.

Code of Federal Regulations, 2012 CFR

2012-04-01

... Duties U.S. CUSTOMS AND BORDER PROTECTION, DEPARTMENT OF HOMELAND SECURITY; DEPARTMENT OF THE TREASURY... the port of entry (regardless of whether it is an international airport) nearest the final departure airport. ...

19 CFR 122.64 - Other aircraft.

Code of Federal Regulations, 2011 CFR

2011-04-01

... Duties U.S. CUSTOMS AND BORDER PROTECTION, DEPARTMENT OF HOMELAND SECURITY; DEPARTMENT OF THE TREASURY... the port of entry (regardless of whether it is an international airport) nearest the final departure airport. ...

19 CFR 122.64 - Other aircraft.

Code of Federal Regulations, 2014 CFR

2014-04-01

... Duties U.S. CUSTOMS AND BORDER PROTECTION, DEPARTMENT OF HOMELAND SECURITY; DEPARTMENT OF THE TREASURY... the port of entry (regardless of whether it is an international airport) nearest the final departure airport. ...

The emerging dental workforce: why dentistry? A quantitative study of final year dental students' views on their professional career

PubMed Central

Gallagher, Jennifer E; Patel, Resmi; Donaldson, Nora; Wilson, Nairn HF

2007-01-01

Background Dental graduates are joining a profession experiencing changes in systems of care, funding and skill mix. Research into the motivation and expectations of the emerging workforce is vital to inform professional and policy decisions. The objective of this research was to investigate final year dental students' perceived motivation for their choice of career in relation to sex, ethnicity and mode of entry. Methods Self-administered questionnaire survey of all final year dental students at King's College London. Data were entered into SPSS; statistical analysis included Chi Squared tests for linear association, multiple regression, factor analysis and logistic regression. Results A response of 90% (n = 126) was achieved. The majority were aged 23 years (59%), female (58%) and Asian (70%). One in 10 were mature students. Eighty per cent identified 11 or more 'important' or 'very important' influences, the most common of which were related to features of the job: 'regular working hours' (91%), 'degree leading to recognised job' (90%) and 'job security' (90%). There were significant differences in important influences by sex (males > females: 'able to run own business'; females > males: 'a desire to work with people'), ethnic group (Asians > white: 'wish to provide public service', 'influence of friends', 'desire to work in healthcare', having 'tried an alternative career/course' and 'work experience') and mode of entry (mature > early entry: 'a desire to work with people'). Multivariate analysis suggested 61% of the variation in influences is explained by five factors: the 'professional job' (31%), 'healthcare-people' (11%), 'academic-scientific' (8%), 'careers-advising' (6%), and 'family/friends' (6%). The single major influence on choice of career was a 'desire to work with people'; Indian students were twice as likely to report this as white or other ethnic groups. Conclusion Final year dental students report a wide range of important influences on their choice of dentistry, with variation by sex, ethnicity and mode of entry in relation to individual influences. Features of the 'professional job', followed by 'healthcare and people' were the most important underlying factors influencing choice of career. PMID:17573967

A Study on Re-entry Predictions of Uncontrolled Space Objects for Space Situational Awareness

NASA Astrophysics Data System (ADS)

Choi, Eun-Jung; Cho, Sungki; Lee, Deok-Jin; Kim, Siwoo; Jo, Jung Hyun

2017-12-01

The key risk analysis technologies for the re-entry of space objects into Earth’s atmosphere are divided into four categories: cataloguing and databases of the re-entry of space objects, lifetime and re-entry trajectory predictions, break-up models after re-entry and multiple debris distribution predictions, and ground impact probability models. In this study, we focused on re- entry prediction, including orbital lifetime assessments, for space situational awareness systems. Re-entry predictions are very difficult and are affected by various sources of uncertainty. In particular, during uncontrolled re-entry, large spacecraft may break into several pieces of debris, and the surviving fragments can be a significant hazard for persons and properties on the ground. In recent years, specific methods and procedures have been developed to provide clear information for predicting and analyzing the re-entry of space objects and for ground-risk assessments. Representative tools include object reentry survival analysis tool (ORSAT) and debris assessment software (DAS) developed by National Aeronautics and Space Administration (NASA), spacecraft atmospheric re-entry and aerothermal break-up (SCARAB) and debris risk assessment and mitigation analysis (DRAMA) developed by European Space Agency (ESA), and semi-analytic tool for end of life analysis (STELA) developed by Centre National d’Etudes Spatiales (CNES). In this study, various surveys of existing re-entry space objects are reviewed, and an efficient re-entry prediction technique is suggested based on STELA, the life-cycle analysis tool for satellites, and DRAMA, a re-entry analysis tool. To verify the proposed method, the re-entry of the Tiangong-1 Space Lab, which is expected to re-enter Earth’s atmosphere shortly, was simulated. Eventually, these results will provide a basis for space situational awareness risk analyses of the re-entry of space objects.

19 CFR 163.11 - Audit procedures.

Code of Federal Regulations, 2014 CFR

2014-04-01

... how the results of the sampling will be projected over the universe of transactions for purposes of... results over the universe of transactions is the process by which the results obtained from the sample entries actually examined are applied to the universe of entries set within the time period and scope of...

19 CFR 163.11 - Audit procedures.

Code of Federal Regulations, 2012 CFR

2012-04-01

... how the results of the sampling will be projected over the universe of transactions for purposes of... results over the universe of transactions is the process by which the results obtained from the sample entries actually examined are applied to the universe of entries set within the time period and scope of...

19 CFR 163.11 - Audit procedures.

Code of Federal Regulations, 2013 CFR

2013-04-01

... how the results of the sampling will be projected over the universe of transactions for purposes of... results over the universe of transactions is the process by which the results obtained from the sample entries actually examined are applied to the universe of entries set within the time period and scope of...

78 FR 73516 - Privacy Act of 1974; System of Records

Federal Register 2010, 2011, 2012, 2013, 2014

2013-12-06

... proposed action will be effective on January 6, 2014 unless comments are received which result in a..., Social Security Number (SSN), and case docket number and may include the individual's home address and... entry and replace with ``Paper file folders and electronic storage media.'' Retrievability: Delete entry...

Potential for Integrating Entry Guidance into the Multi-Disciplinary Entry Vehicle Optimization Environment

NASA Technical Reports Server (NTRS)

D'souza, Sarah N.; Kinney, David J.; Garcia, Joseph A.; Sarigul-Klijn, Nesrin

2014-01-01

The state-of-the-art in vehicle design decouples flight feasible trajectory generation from the optimization process of an entry spacecraft shape. The disadvantage to this decoupled process is seen when a particular aeroshell does not meet in-flight requirements when integrated into Guidance, Navigation, and Control simulations. It is postulated that the integration of a guidance algorithm into the design process will provide a real-time, rapid trajectory generation technique to enhance the robustness of vehicle design solutions. The potential benefit of this integration is a reduction in design cycles (possible cost savings) and increased accuracy in the aerothermal environment (possible mass savings). This work examines two aspects: 1) the performance of a reference tracking guidance algorithm for five different geometries with the same reference trajectory and 2) the potential of mass savings from improved aerothermal predictions. An Apollo Derived Guidance (ADG) algorithm is used in this study. The baseline geometry and five test case geometries were flown using the same baseline trajectory. The guided trajectory results are compared to separate trajectories determined in a vehicle optimization study conducted for NASA's Mars Entry, Descent, and Landing System Analysis. This study revealed several aspects regarding the potential gains and required developments for integrating a guidance algorithm into the vehicle optimization environment. First, the generation of flight feasible trajectories is only as good as the robustness of the guidance algorithm. The set of dispersed geometries modelled aerodynamic dispersions that ranged from +/-1% to +/-17% and a single extreme case was modelled where the aerodynamics were approximately 80% less than the baseline geometry. The ADG, as expected, was able to guide the vehicle into the aeroshell separation box at the target location for dispersions up to 17%, but failed for the 80% dispersion cases. Finally, the results revealed that including flight feasible trajectories for a set of dispersed geometries has the potential to save mass up to 430 kg.

Research on intercultural effectiveness and its relevance to multicultural crews in space.

PubMed

Kealey, Daniel J

2004-07-01

The planning for and managing of missions in space is changing dramatically due to, among other things, the involvement of more and more national cultures. In light of the need to better understand the influence and management of cultural differences among the crewmembers who will live and work in space in the future, the aim of this paper is threefold. First, some of the key research findings on intercultural effectiveness on Earth are presented and their relevance to the functioning of multicultural crews in space is discussed. Second, issues that will need to be addressed in order to maximize the effective functioning of multicultural teams in space are identified. These include improving the procedures for the screening and selection, intercultural training, monitoring and support, and debriefing and re-entry of astronauts and their families. Finally, the paper concludes with the presentation and discussion of some of the key activities that will need to be undertaken to address these issues and, thereby, enhance the overall functioning of multicultural teams living and working in space.

Developing a competency framework for U.S. state food and feed testing laboratory personnel.

PubMed

Kaml, Craig; Weiss, Christopher C; Dezendorf, Paul; Ishida, Maria; Rice, Daniel H; Klein, Ron; Salfinger, Yvonne

2014-01-01

A competency-based training curriculum framework for U.S. state food and feed testing laboratories personnel is being developed by the International Food Protection Training Institute (IFPTI) and three partners. The framework will help laboratories catalog existing training courses/modules, identify training gaps, inform training curricula, and create career-spanning professional development learning paths, ensuring consistent performance expectations and increasing confidence in shared test results. Ultimately, the framework will aid laboratories in meeting the requirements of ISO/IEC 17025 (2005) international accreditation and the U.S. Food Safety Modernization Act (U.S. Public Law 111-353). In collaboration with the Association of Food and Drug Officials, the Association of Public Health Laboratories, and the Association of American Feed Control Officials, IFPTI is carrying out the project in two phases. In 2013, an expert panel of seven subject matter experts developed competency and curriculum frameworks for five professional levels (entry, mid-level, expert, supervisor/manager, and senior administration) across four competency domains (technical, communication, programmatic, and leadership) including approximately 80 competencies. In 2014 the expert panel will elicit feedback from peers and finalize the framework.

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.

Orbiter Gap Filler Bending Model for Re-entry

NASA Technical Reports Server (NTRS)

Campbell, Charles H.

2007-01-01

Pressure loads on a protruding gap filler during an Orbiter reentry are investigated to evaluate the likelihood of extraction due to pressure loads, and to ascertain how much bending will be induced by re-entry pressure loads. Oblique shock wave theory is utilized to develop a representation of the pressure loads induced on a gap filler for the ISSHVFW trajectory, representative of a heavy weight ISS return. A free body diagram is utilized to react the forces induced by the pressure forces. Preliminary results developed using these methods demonstrate that pressure loads, alone, are not likely causes of gap filler extraction during reentry. Assessment of the amount a gap filler will bend over is presented. Implications of gap filler bending during re-entry include possible mitigation of early boundary layer transition concerns, uncertainty in ground based measurement of protruding gap fillers from historical Orbiter flight history, and uncertainty in the use of Orbiter gap fillers for boundary layer prediction calibration. Authors will be added to the author list as appropriate.

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.; 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 simulation tools to spherical geometries of diameters ranging from 1 to 100 m for an entry velocity of 20 km/s and stagnation pressures ranging from 1 to 100 atm; (ii) the influence of shape and departure of heating environment predictions from those for a simple spherical geometry; (iii) assessment of thermal response models for silica subject to intense radiation; and (iv) results for porosity-driven gross fragmentation of meteors, idealized as a collection of smaller objects. Lessons learned from these simulations will be used to help understand the Chelyabinsk meteor entry up to its first point of fragmentation.

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.;

KSC-2011-3574

NASA Image and Video Library

2011-05-16

CAPE CANAVERAL, Fla. -- Space shuttle Endeavour's six STS-134 astronauts, dressed in their orange launch-and-entry suits, wave to news media and other spectators in front of the Astrovan parked in front of the Operations and Checkout Building at NASA's Kennedy Space Center in Florida. The modified Airstream recreational vehicle, which has transported astronauts to their spacecraft since 1984, will take the crew to Launch Pad 39A. From left, are Mission Specialists Greg Chamitoff, Andrew Feustel, Roberto Vittori with the European Space Agency and Michael Fincke, Pilot Greg H. Johnson, and Commander Mark Kelly. STS-134 will deliver the Alpha Magnetic Spectrometer-2 (AMS), Express Logistics Carrier-3, a high-pressure gas tank and additional spare parts for the Dextre robotic helper to the International Space Station. May 16 at 8:56 a.m. will be the second launch attempt for Endeavour. The first attempt on April 29 was scrubbed because of an issue associated with a faulty power distribution box called the aft load control assembly-2 (ALCA-2). STS-134 will be the final spaceflight for Endeavour. For more information visit, www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts134/index.html. Photo credit: NASA/Kim Shiflett

Canal switch and re-entry phenomenon in benign paroxysmal positional vertigo: difference between immediate and delayed occurrence.

PubMed

Dispenza, F; DE Stefano, A; Costantino, C; Rando, D; Giglione, M; Stagno, R; Bennici, E

2015-04-01

This prospective study was designed to evaluate the differences between immediate and delayed canal re-entry of otoliths after therapeutic manoeuvres in patients with benign paroxysmal positional vertigo (BPPV). A total of 196 patients with BPPV were visited and 127 matched our inclusion criteria. The mean age was 54.74 years. The horizontal semicircular canal (HSC) was involved in 30 cases and the posterior semicircular canal (PSC) in 97 patients. Patients with hearing loss in the ear affected by BPPV have a more recurrent form, compared to those with normal hearing. An immediate canal re-entry was recorded in 3 patients with HSC BPPV, all with geotropic nystagmus. In 7 patients with PSC BPPV, the immediate canal re-entry was detected and the delayed form was noted in 5 patients. The patients with the delayed canal re-entry underwent more than 2 previous manoeuvres. The canal re-entry was not related to the manoeuvre performed. The timing of the Dix-Hallpike test to verify the resolution of the BPPV had a significant role in immediate canal re-entry. A recurrence in the follow-up at least one month after treatment was recorded in 20 patients and was more frequent in patients that had canal re-entry. The canal re-entry or canal switch is a clinical entity that should be kept in mind of the neurotologist when approaching BPPV patients. It is important to distinguish it from recurrence when delayed and from manoeuvre failure when immediate. The timing of manoeuvre performing, in particular the final verification test after therapeutic sessions, is important to prevent the immediate reflux of particles into canals.

75 FR 11005 - Final Theft Data; Motor Vehicle Theft Prevention Standard

Federal Register 2010, 2011, 2012, 2013, 2014

2010-03-10

..., Inc. (Nissan). In its comments, VW informed the agency that the entries for the Audi RS4, Audi A8, Audi A4/A4 Quattro/S4/S4 Avant and Audi RS4 were listed with incorrect manufacturer designations. The final theft data has been revised to reflect that Audi is the manufacturer for [[Page 11007

78 FR 73837 - Glycine From the People's Republic of China: Final Rescission of Antidumping Duty New Shipper...

Federal Register 2010, 2011, 2012, 2013, 2014

2013-12-09

... Jiheng Fine Chemical Company, Ltd. (Donghua Fine Chemical).\\1\\ For these final results, we continue to find that, because Donghua Fine Chemical appears to be affiliated with PRC-companies that have had...). We also continue to find that Donghua Fine Chemical failed to report its first U.S. entry and/or U.S...

43 CFR 2523.1 - Collection of purchase money and fees; issuance of final certificate.

Code of Federal Regulations, 2014 CFR

2014-10-01

...) DESERT-LAND ENTRIES Payments § 2523.1 Collection of purchase money and fees; issuance of final... paid for all lands entered under the desert land law. (b) If the entryman is dead and proof is made by... determining, if possible, whether or not, prior to the passage of the Act of March 28, 1908, any desert-land...

43 CFR 2523.1 - Collection of purchase money and fees; issuance of final certificate.

Code of Federal Regulations, 2012 CFR

2012-10-01

...) DESERT-LAND ENTRIES Payments § 2523.1 Collection of purchase money and fees; issuance of final... paid for all lands entered under the desert land law. (b) If the entryman is dead and proof is made by... determining, if possible, whether or not, prior to the passage of the Act of March 28, 1908, any desert-land...

43 CFR 2523.1 - Collection of purchase money and fees; issuance of final certificate.

Code of Federal Regulations, 2013 CFR

2013-10-01

...) DESERT-LAND ENTRIES Payments § 2523.1 Collection of purchase money and fees; issuance of final... paid for all lands entered under the desert land law. (b) If the entryman is dead and proof is made by... determining, if possible, whether or not, prior to the passage of the Act of March 28, 1908, any desert-land...

43 CFR 2523.1 - Collection of purchase money and fees; issuance of final certificate.

Code of Federal Regulations, 2011 CFR

2011-10-01

...) DESERT-LAND ENTRIES Payments § 2523.1 Collection of purchase money and fees; issuance of final... paid for all lands entered under the desert land law. (b) If the entryman is dead and proof is made by... determining, if possible, whether or not, prior to the passage of the Act of March 28, 1908, any desert-land...

Staff and Program Development for a New Pupil Personnel Services Professional: Final Report 1.

ERIC Educational Resources Information Center

Ruch, Charles P.

This is the first in a series of final reports to the Office of Education on the Northeastern EPDA/PPS Center-Satellite Project. This multi-year, multi-institutional project was an attempt to redesign the training of pupil personnel specialists for the schools through preservice training for entry-level personnel and pre- or inservice training for…

Overview of the Mars Sample Return Earth Entry Vehicle

NASA Technical Reports Server (NTRS)

Dillman, Robert; Corliss, James

2008-01-01

NASA's Mars Sample Return (MSR) project will bring Mars surface and atmosphere samples back to Earth for detailed examination. Langley Research Center's MSR Earth Entry Vehicle (EEV) is a core part of the mission, protecting the sample container during atmospheric entry, descent, and landing. Planetary protection requirements demand a higher reliability from the EEV than for any previous planetary entry vehicle. An overview of the EEV design and preliminary analysis is presented, with a follow-on discussion of recommended future design trade studies to be performed over the next several years in support of an MSR launch in 2018 or 2020. Planned topics include vehicle size for impact protection of a range of sample container sizes, outer mold line changes to achieve surface sterilization during re-entry, micrometeoroid protection, aerodynamic stability, thermal protection, and structural materials selection.

Cancer biomarkers: the role of structured data reporting.

PubMed

Simpson, Ross W; Berman, Michael A; Foulis, Philip R; Divaris, Dimitrios X G; Birdsong, George G; Mirza, Jaleh; Moldwin, Richard; Spencer, Samantha; Srigley, John R; Fitzgibbons, Patrick L

2015-05-01

The College of American Pathologists has been producing cancer protocols since 1986 to aid pathologists in the diagnosis and reporting of cancer cases. Many pathologists use the included cancer case summaries as templates for dictation/data entry into the final pathology report. These summaries are now available in a computer-readable format with structured data elements for interoperability, packaged as "electronic cancer checklists." Most major vendors of anatomic pathology reporting software support this model. To outline the development and advantages of structured electronic cancer reporting using the electronic cancer checklist model, and to describe its extension to cancer biomarkers and other aspects of cancer reporting. Peer-reviewed literature and internal records of the College of American Pathologists. Accurate and usable cancer biomarker data reporting will increasingly depend on initial capture of this information as structured data. This process will support the standardization of data elements and biomarker terminology, enabling the meaningful use of these datasets by pathologists, clinicians, tumor registries, and patients.

STS-92 MS McArthur gets suit checked in the White Room before launch

NASA Technical Reports Server (NTRS)

2000-01-01

STS-92 Mission Specialist William S. McArthur Jr. undergoes final suit check in the White Room before entering Discovery. The White Room is an environmentally controlled area at the end of the Orbiter Access Arm that provides entry to the orbiter as well as emergency egress if needed. The arm remains in the extended position until 7 minutes 24 seconds before launch. McArthur and the rest of the crew are making the fifth flight to the International Space Station for construction. Discovery carries a payload that includes the Integrated Truss Structure Z-1, first of 10 trusses that will form the backbone of the Space Station, and the third Pressurized Mating Adapter that will provide a Shuttle docking port for solar array installation on the sixth Station flight and Lab installation on the seventh Station flight. The mission includes four spacewalks for the construction activities. Discovery's landing is expected Oct. 22 at 2:10 p.m. EDT.

STS-92 Commander Duffy gets suit checked in the White Room before launch

NASA Technical Reports Server (NTRS)

2000-01-01

STS-92 Commander Brian Duffy is helped with final suit check in the White Room before entering Discovery. The White Room is an environmentally controlled area at the end of the Orbiter Access Arm that provides entry to the orbiter as well as emergency egress if needed. The arm remains in the extended position until 7 minutes 24 seconds before launch. Duffy and the rest of the crew are undertaking the fifth flight to the International Space Station for construction. Discovery carries a payload that includes the Integrated Truss Structure Z-1, first of 10 trusses that will form the backbone of the Space Station, and the third Pressurized Mating Adapter that will provide a Shuttle docking port for solar array installation on the sixth Station flight and Lab installation on the seventh Station flight. The mission includes four spacewalks for the construction activities. Discovery's landing is expected Oct. 22 at 2:10 p.m. EDT.

Sensitivity of Asteroid Impact Risk to Uncertainty in Asteroid Properties and Entry Parameters

NASA Astrophysics Data System (ADS)

Wheeler, Lorien; Mathias, Donovan; Dotson, Jessie L.; NASA Asteroid Threat Assessment Project

2017-10-01

A central challenge in assessing the threat posed by asteroids striking Earth is the large amount of uncertainty inherent throughout all aspects of the problem. Many asteroid properties are not well characterized and can range widely from strong, dense, monolithic irons to loosely bound, highly porous rubble piles. Even for an object of known properties, the specific entry velocity, angle, and impact location can swing the potential consequence from no damage to causing millions of casualties. Due to the extreme rarity of large asteroid strikes, there are also large uncertainties in how different types of asteroids will interact with the atmosphere during entry, how readily they may break up or ablate, and how much surface damage will be caused by the resulting airbursts or impacts.In this work, we use our Probabilistic Asteroid Impact Risk (PAIR) model to investigate the sensitivity of asteroid impact damage to uncertainties in key asteroid properties, entry parameters, or modeling assumptions. The PAIR model combines physics-based analytic models of asteroid entry and damage in a probabilistic Monte Carlo framework to assess the risk posed by a wide range of potential impacts. The model samples from uncertainty distributions of asteroid properties and entry parameters to generate millions of specific impact cases, and models the atmospheric entry and damage for each case, including blast overpressure, thermal radiation, tsunami inundation, and global effects. To assess the risk sensitivity, we alternately fix and vary the different input parameters and compare the effect on the resulting range of damage produced. The goal of these studies is to help guide future efforts in asteroid characterization and model refinement by determining which properties most significantly affect the potential risk.

Parametric Thermal Soak Model for Earth Entry Vehicles

NASA Technical Reports Server (NTRS)

Agrawal, Parul; Samareh, Jamshid; Doan, Quy D.

2013-01-01

The analysis and design of an Earth Entry Vehicle (EEV) is multidisciplinary in nature, requiring the application many disciplines. An integrated tool called Multi Mission System Analysis for Planetary Entry Descent and Landing or M-SAPE is being developed as part of Entry Vehicle Technology project under In-Space Technology program. Integration of a multidisciplinary problem is a challenging task. Automation of the execution process and data transfer among disciplines can be accomplished to provide significant benefits. Thermal soak analysis and temperature predictions of various interior components of entry vehicle, including the impact foam and payload container are part of the solution that M-SAPE will offer to spacecraft designers. The present paper focuses on the thermal soak analysis of an entry vehicle design based on the Mars Sample Return entry vehicle geometry and discusses a technical approach to develop parametric models for thermal soak analysis that will be integrated into M-SAPE. One of the main objectives is to be able to identify the important parameters and to develop correlation coefficients so that, for a given trajectory, can estimate the peak payload temperature based on relevant trajectory parameters and vehicle geometry. The models are being developed for two primary thermal protection (TPS) materials: 1) carbon phenolic that was used for Galileo and Pioneer Venus probes and, 2) Phenolic Impregnated Carbon Ablator (PICA), TPS material for Mars Science Lab mission. Several representative trajectories were selected from a very large trade space to include in the thermal analysis in order to develop an effective parametric thermal soak model. The selected trajectories covered a wide range of heatload and heatflux combinations. Non-linear, fully transient, thermal finite element simulations were performed for the selected trajectories to generate the temperature histories at the interior of the vehicle. Figure 1 shows the finite element model that was used for the simulations. The results indicate that it takes several hours for the thermal energy to soak into the interior of the vehicle and achieve maximum payload temperatures. In addition, a strong correlation between the heatload and peak payload container temperature is observed that will help establishing the parametric thermal soak model.

77 FR 68103 - Michigan State University, et al.; Notice of Decision on Applications for Duty-Free Entry of...

Federal Register 2010, 2011, 2012, 2013, 2014

2012-11-15

... DEPARTMENT OF COMMERCE International Trade Administration Michigan State University, et al.; Notice of Decision on Applications for Duty-Free Entry of Scientific Instruments This is a decision... (OH) radicals. The hydroxyl which is excited using ultraviolet light (283 nm) will then fluoresce and...

The Desk Guide to Training and Work Advisement.

ERIC Educational Resources Information Center

Kuenstler, Gail Baugher

Specific education and training requirements for entry to all major occupations at a variety of levels are presented, and work information is provided (including how to figure out the requirements for entry into the vast number of occupations, understanding which training programs will actually lead to a good job, helping the client isolate…

32 CFR 552.168 - Fort Lewis Area Access Office.

Code of Federal Regulations, 2011 CFR

2011-07-01

... issued to each person authorized access. The permit is not transferable. Entry to the Fort Lewis range... valid for one year. When a permit expires, the holder must re-register to renew privileges, and a new... been coordinated and approved, Area Access will determine when called for entry whether the area...

32 CFR 552.168 - Fort Lewis Area Access Office.

Code of Federal Regulations, 2012 CFR

2012-07-01

... issued to each person authorized access. The permit is not transferable. Entry to the Fort Lewis range... valid for one year. When a permit expires, the holder must re-register to renew privileges, and a new... been coordinated and approved, Area Access will determine when called for entry whether the area...

32 CFR 552.168 - Fort Lewis Area Access Office.

Code of Federal Regulations, 2010 CFR

2010-07-01

... issued to each person authorized access. The permit is not transferable. Entry to the Fort Lewis range... valid for one year. When a permit expires, the holder must re-register to renew privileges, and a new... been coordinated and approved, Area Access will determine when called for entry whether the area...

32 CFR 552.168 - Fort Lewis Area Access Office.

Code of Federal Regulations, 2013 CFR

2013-07-01

... issued to each person authorized access. The permit is not transferable. Entry to the Fort Lewis range... valid for one year. When a permit expires, the holder must re-register to renew privileges, and a new... been coordinated and approved, Area Access will determine when called for entry whether the area...

78 FR 14914 - Addition of Certain Persons to the Entity List

Federal Register 2010, 2011, 2012, 2013, 2014

2013-03-08

.... This person will be listed on the Entity List under Germany, Russia, and Taiwan. DATES: Effective date... different countries for the person being added to the Entity List, consist of single entries in Russia... one person being listed under three separate entries, T -Platforms, a company headquartered in Russia...

77 FR 63424 - Announcement of Competition Under the America COMPETES Reauthorization Act of 2011: Veterans...

Federal Register 2010, 2011, 2012, 2013, 2014

2012-10-16

...), relating to contact information. e. Section 4(d), relating to optional descriptive materials. 3. If... means it determines suitable to evaluate any entry, award points and determine any winner in this... Compatible. c. Functional Evaluation. VA will evaluate an entry that has demonstrated Technical Compatibility...

The Entry Experiences, Challenges, and Mediating Strategies of Public School Superintendents

ERIC Educational Resources Information Center

Sutton, David M.

2012-01-01

The public school superintendent's role has changed substantially over time, and the work of superintendents is more complex, demanding, and challenging than ever before. Recent studies indicate that 70% to 80% of the nation's superintendents will leave their positions over the next five years, suggesting the imminent entry of many new…

29 CFR 1910.146 - Permit-required confined spaces.

Code of Federal Regulations, 2010 CFR

2010-07-01

... demonstrate that continuous forced air ventilation alone is sufficient to maintain that permit space safe for... accidental fall through the opening and that will protect each employee working in the space from foreign...) The employer shall verify that the space is safe for entry and that the pre-entry measures required by...

5 CFR 300.706 - Office of Personnel Management adjudication.

Code of Federal Regulations, 2010 CFR

2010-01-01

... written explanation, as described in § 300.705. The Associate Director for Career Entry or his or her... determinations. (c) The Associate Director for Career Entry or his or her designee will notify the individual and... discretion of the Associate Director. There is no further right to administrative review. (d) The Director of...

Reference pricing with endogenous generic entry.

PubMed

Brekke, Kurt R; Canta, Chiara; Straume, Odd Rune

2016-12-01

Reference pricing intends to reduce pharmaceutical expenditures by increasing demand elasticity and stimulating generic competition. We develop a novel model where a brand-name producer competes in prices with several generics producers in a market with brand-biased and brand-neutral consumers. Comparing with coinsurance, we show that reference pricing, contrary to policy makers' intentions, discourages generic entry, as it induces the brand-name producer to price more aggressively. Thus, the net effect of reference pricing on drug prices is ambiguous, implying that reference pricing can be counterproductive in reducing expenditures. However, under price regulation, we show that reference pricing may stimulate generic entry, since a binding price cap weakens the aggressive price response by the brand-name producer. This may explain mixed empirical results on the competitive effects of reference pricing. Finally, we show that reference pricing may be welfare improving when accounting for brand preferences despite its adverse effects on entry and prices. Copyright © 2016 Elsevier B.V. All rights reserved.

Paramyxovirus Fusion and Entry: Multiple Paths to a Common End

PubMed Central

Chang, Andres; Dutch, Rebecca E.

2012-01-01

The paramyxovirus family contains many common human pathogenic viruses, including measles, mumps, the parainfluenza viruses, respiratory syncytial virus, human metapneumovirus, and the zoonotic henipaviruses, Hendra and Nipah. While the expression of a type 1 fusion protein and a type 2 attachment protein is common to all paramyxoviruses, there is considerable variation in viral attachment, the activation and triggering of the fusion protein, and the process of viral entry. In this review, we discuss recent advances in the understanding of paramyxovirus F protein-mediated membrane fusion, an essential process in viral infectivity. We also review the role of the other surface glycoproteins in receptor binding and viral entry, and the implications for viral infection. Throughout, we concentrate on the commonalities and differences in fusion triggering and viral entry among the members of the family. Finally, we highlight key unanswered questions and how further studies can identify novel targets for the development of therapeutic treatments against these human pathogens. PMID:22590688

Energetic Particles Investigation (EPI). [during pre-entry of Galileo Probe in Jovian magnetosphere

NASA Technical Reports Server (NTRS)

Fischer, H. M.; Mihalov, J. D.; Lanzerotti, L. J.; Wibberenz, G.; Rinnert, K.; Gliem, F. O.; Bach, J.

1992-01-01

The EPI instrument operates during the pre-entry phase of the Galileo Probe. The main objective is the study of the energetic particle population in the inner Jovian magnetosphere and in the upper atmosphere. This will be achieved through omnidirectional measurements of electrons, protons, alpha-particles and heavy ions (Z greater than 2) and recording intensity profiles with a spatial resolution of about 0.02 Jupiter radii. Sectored data will also be obtained for electrons, protons, and alpha-particles to determine directional anisotropies and particle pitch angle distributions. The detector assembly is a two-element telescope using totally depleted circular silicon surface-barrier detectors surrounded by cylindrical tungsten shielding. The lower energy threshold of the particle species investigated during the Probe's pre-entry phase is determined by the material thickness of the Probe's rear heat shield which is required for heat protection of the scientific payload during entry into the Jovian atmosphere. The EPI instrument is combined with the Lightning and Radio Emission Detector and both instruments share one interface of the Probe's power, command, and data unit.

Inertial measurement unit pre-processors and post-flight STS-1 comparisons

NASA Technical Reports Server (NTRS)

Findlay, J. T.; Mcconnell, J. G.

1981-01-01

The flight results show that the relative tri-redundant Inertial Measurement Unit IMU performance throughout the entire entry flight was within the expected accuracy. Comparisons are presented which show differences in the accumulated sensed velocity changes as measured by the tri-redundant IMUs (in Mean Equator and Equinox of 1950.0), differences in the equivalent inertial Euler angles as measured with respect to the M50 system, and finally, preliminary instrument calibrations determined relative to the ensemble average measurement set. Also, differences in the derived body axes rates and accelerations are presented. Because of the excellent performance of the IMUs during the STS-1 entry, the selection as to which particular IMU would best serve as the dynamic data source for entry reconstruction is arbitrary.

Analytic theory of orbit contraction and ballistic entry into planetary atmospheres

NASA Technical Reports Server (NTRS)

Longuski, J. M.; Vinh, N. X.

1980-01-01

A space object traveling through an atmosphere is governed by two forces: aerodynamic and gravitational. On this premise, equations of motion are derived to provide a set of universal entry equations applicable to all regimes of atmospheric flight from orbital motion under the dissipate force of drag through the dynamic phase of reentry, and finally to the point of contact with the planetary surface. Rigorous mathematical techniques such as averaging, Poincare's method of small parameters, and Lagrange's expansion, applied to obtain a highly accurate, purely analytic theory for orbit contraction and ballistic entry into planetary atmospheres. The theory has a wide range of applications to modern problems including orbit decay of artificial satellites, atmospheric capture of planetary probes, atmospheric grazing, and ballistic reentry of manned and unmanned space vehicles.

Computerized physician order entry from a chief information officer perspective.

PubMed

Cotter, Carole M

2004-12-01

Designing and implementing a computerized physician order entry system in the critical care units of a large urban hospital system is an enormous undertaking. With their significant potential to improve health care and significantly reduce errors, the time for computerized physician order entry or physician order management systems is past due. Careful integrated planning is the key to success, requiring multidisciplinary teams at all levels of clinical and administrative management to work together. Articulated from the viewpoint of the Chief Information Officer of Lifespan, a not-for-profit hospital system in Rhode Island, the vision and strategy preceding the information technology plan, understanding the system's current state, the gap analysis between current and future state, and finally, building and implementing the information technology plan are described.

ADEPT SR-1 Flight Experiment

NASA Technical Reports Server (NTRS)

Wercinski, Paul F.

2017-01-01

The ADEPT architecture represents a completely new approach for entry vehicle design using a high-performance carbon fabric to serve as the primary drag surface of the mechanically deployed decelerator and to protect the payload from hypersonic aerothermal heating during entry. The initial system-level development of the nano-ADEPT architecture will culminate in the launch of a 0.7-m deployed diameter ADEPT sounding rocket flight experiment. The SR-1 sounding rocket flight experiment is a critical milestone in the technology maturation plan for ADEPT and will generate performance data on in-space deployment and aerodynamic stability.

Shuttle program. MCC level C formulation requirements: Shuttle TAEM guidance and flight control

NASA Technical Reports Server (NTRS)

Carman, G. L.

1980-01-01

The Level C requirements for the shuttle orbiter terminal area energy management (TAEM) guidance and flight control functions to be incorporated into the Mission Control Center entry profile planning processor are defined. This processor will be used for preentry evaluation of the entry through landing maneuvers, and will include a simplified three degree-of-freedom model of the body rotational dynamics that is necessary to account for the effects of attitude response on the trajectory dynamics. This simulation terminates at TAEM-autoland interface.

STS-104 Commander Lindsey talks to media at the SLF after arriving for launch

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- After arriving at the Shuttle Landing Facility, the STS-104 crew stopped to talk to the media. At the microphone is Commander Steven W. Lindsey; at right is Pilot Charles O. Hobaugh. The crew is at KSC to make final preparations for their launch. Other crew members are Mission Specialists James F. Reilly, Janet Lynn Kavandi and Michael L. Gernhardt. The launch of Atlantis on mission STS-104 is scheduled for July 12 from Launch Pad 39B. The mission is the 10th assembly flight to the International Space Station and carries the Joint Airlock Module, which will become the primary path for spacewalk entry and departure using both U.S. spacesuits and the Russian Orlan spacesuit for EVA activity.

Immune System Dysregulation, Viral Reactivation and Stress During Short-Duration Spaceflight

NASA Technical Reports Server (NTRS)

Pierson, Duane; Sams, Clarence; Crucian, Brian; Mehta, Satish; Stowe, Raymond; Uchakin, Peter; Quiriarte, Heather

2010-01-01

The objective of this NASA Short-Duration Bioastronautics Investigation (SDBI) was to assess spaceflight-associated immune dysregulation. Many previous studies have investigated this phenomenon post-flight, and found altered distribution and function of the peripheral leukocyte populations. Alterations in cytokine production profiles have also been reported. Unfortunately, post-flight data may be altered by the stress associated with high-G re-entry and readaptation to unit gravity following deconditioning. Therefore, the current study collected blood and saliva samples from crewmembers immediately before landing, and returned those samples to Earth for terrestrial analysis. Assays include peripheral comprehensive immunophenotype, T cell function, cytokine profiles, viral-specific immunity, latent viral reactivation (EBV, CMV, VZV), and stress hormone measurements. A total of 18 short duration crewmembers completed the study and the final data will be presented.

Planetary entry experiments

NASA Technical Reports Server (NTRS)

Craig, Roger A.

1994-01-01

The final report summarizes the results from three research areas: (1) window design for the radiometric measurement of the forebody radiative heating experienced by atmospheric entry spaceraft; (2) survey of the current understanding of chemical species on selected solar system bodies and assess the importance of measurements with regard to vehicle environment and with regard to understanding of planetary atmospheres with emphasis on Venus, Mars, and Titan; and (3) measure and analyze the radiation (VUV to near-IR) from the shock heated gas cap of a blunt body in an Ames arc Jet wind-tunnel facility.

Designing Computerized Provider Order Entry Software in Iran: The Nurses' and Physicians' Viewpoints.

PubMed

Khammarnia, Mohammad; Sharifian, Roxana; Zand, Farid; Keshtkaran, Ali; Barati, Omid

2016-09-01

This study aimed to identify the functional requirements of computerized provider order entry software and design this software in Iran. This study was conducted using review documentation, interview, and focus group discussions in Shiraz University of Medical Sciences, as the medical pole in Iran, in 2013-2015. The study sample consisted of physicians (n = 12) and nurses (n = 2) in the largest hospital in the southern part of Iran and information technology experts (n = 5) in Shiraz University of Medical Sciences. Functional requirements of the computerized provider order entry system were examined in three phases. Finally, the functional requirements were distributed in four levels, and accordingly, the computerized provider order entry software was designed. The software had seven main dimensions: (1) data entry, (2) drug interaction management system, (3) warning system, (4) treatment services, (5) ability to write in software, (6) reporting from all sections of the software, and (7) technical capabilities of the software. The nurses and physicians emphasized quick access to the computerized provider order entry software, order prescription section, and applicability of the software. The software had some items that had not been mentioned in other studies. Ultimately, the software was designed by a company specializing in hospital information systems in Iran. This study was the first specific investigation of computerized provider order entry software design in Iran. Based on the results, it is suggested that this software be implemented in hospitals.

Tyrosine kinases activate store-mediated Ca2+ entry in human platelets through the reorganization of the actin cytoskeleton.

PubMed Central

Rosado, J A; Graves, D; Sage, S O

2000-01-01

We have recently reported that store-mediated Ca(2+) entry in platelets is likely to be mediated by a reversible trafficking and coupling of the endoplasmic reticulum with the plasma membrane, a model termed 'secretion-like coupling'. In this model the actin cytoskeleton plays a key regulatory role. Since tyrosine kinases have been shown to be important for Ca(2+) entry in platelets and other cells, we have now investigated the possible involvement of tyrosine kinases in the secretion-like-coupling model. Treatment of platelets with thrombin or thapsigargin induced actin polymerization by a calcium-independent pathway. Methyl 2,5-dihydroxycinnamate, a tyrosine kinase inhibitor, prevented thrombin- or thapsigargin-induced actin polymerization. The effects of tyrosine kinases in store-mediated Ca(2+) entry were found to be entirely dependent on the actin cytoskeleton. PP1, an inhibitor of the Src family of proteins, partially inhibited store-mediated Ca(2+) entry. In addition, depletion of intracellular Ca(2+) stores stimulated cytoskeletal association of the cytoplasmic tyrosine kinase pp60(src), a process that was sensitive to treatment with cytochalasin D and PP1, but not to inhibition of Ras proteins using prenylcysteine analogues. Finally, combined inhibition of both Ras proteins and tyrosine kinases resulted in complete inhibition of Ca(2+) entry, suggesting that these two families of proteins have independent effects in the activation of store-mediated Ca(2+) entry in human platelets. PMID:11023829

Final STS-11 (41-B) best estimate trajectory products: Development and results from the first Cape landing

NASA Technical Reports Server (NTRS)

Kelly, G. M.; Mcconnell, J. G.; Findlay, J. T.; Heck, M. L.; Henry, M. W.

1984-01-01

The STS-11 (41-B) postflight data processing is completed and the results published. The final reconstructed entry trajectory is presented. The various atmospheric sources available for this flight are discussed. Aerodynamic Best Estimate of Trajectory BET generation and plots from this file are presented. A definition of the major maneuvers effected is given. Physical constants, including spacecraft mass properties; final residuals from the reconstruction process; trajectory parameter listings; and an archival section are included.

Technology Investments in the NASA Entry Systems Modeling Project

NASA Technical Reports Server (NTRS)

Barnhardt, Michael; Wright, Michael; Hughes, Monica

2017-01-01

The Entry Systems Modeling (ESM) technology development project, initiated in 2012 under NASAs Game Changing Development (GCD) Program, is engaged in maturation of fundamental research developing aerosciences, materials, and integrated systems products for entry, descent, and landing(EDL)technologies [1]. To date, the ESM project has published over 200 papers in these areas, comprising the bulk of NASAs research program for EDL modeling. This presentation will provide an overview of the projects successes and challenges, and an assessment of future investments in EDL modeling and simulation relevant to NASAs mission

Reliability-based trajectory optimization using nonintrusive polynomial chaos for Mars entry mission

NASA Astrophysics Data System (ADS)

Huang, Yuechen; Li, Haiyang

2018-06-01

This paper presents the reliability-based sequential optimization (RBSO) method to settle the trajectory optimization problem with parametric uncertainties in entry dynamics for Mars entry mission. First, the deterministic entry trajectory optimization model is reviewed, and then the reliability-based optimization model is formulated. In addition, the modified sequential optimization method, in which the nonintrusive polynomial chaos expansion (PCE) method and the most probable point (MPP) searching method are employed, is proposed to solve the reliability-based optimization problem efficiently. The nonintrusive PCE method contributes to the transformation between the stochastic optimization (SO) and the deterministic optimization (DO) and to the approximation of trajectory solution efficiently. The MPP method, which is used for assessing the reliability of constraints satisfaction only up to the necessary level, is employed to further improve the computational efficiency. The cycle including SO, reliability assessment and constraints update is repeated in the RBSO until the reliability requirements of constraints satisfaction are satisfied. Finally, the RBSO is compared with the traditional DO and the traditional sequential optimization based on Monte Carlo (MC) simulation in a specific Mars entry mission to demonstrate the effectiveness and the efficiency of the proposed method.

Mapping PDB chains to UniProtKB entries.

PubMed

Martin, Andrew C R

2005-12-01

UniProtKB/SwissProt is the main resource for detailed annotations of protein sequences. This database provides a jumping-off point to many other resources through the links it provides. Among others, these include other primary databases, secondary databases, the Gene Ontology and OMIM. While a large number of links are provided to Protein Data Bank (PDB) files, obtaining a regularly updated mapping between UniProtKB entries and PDB entries at the chain or residue level is not straightforward. In particular, there is no regularly updated resource which allows a UniProtKB/SwissProt entry to be identified for a given residue of a PDB file. We have created a completely automatically maintained database which maps PDB residues to residues in UniProtKB/SwissProt and UniProtKB/trEMBL entries. The protocol uses links from PDB to UniProtKB, from UniProtKB to PDB and a brute-force sequence scan to resolve PDB chains for which no annotated link is available. Finally the sequences from PDB and UniProtKB are aligned to obtain a residue-level mapping. The resource may be queried interactively or downloaded from http://www.bioinf.org.uk/pdbsws/.

75 FR 47720 - Final Theft Data; Motor Vehicle Theft Prevention Standard

Federal Register 2010, 2011, 2012, 2013, 2014

2010-08-09

..., Inc. (Nissan). In its comments, VW informed the agency that the entries for the Audi RS4, Audi A8, Audi A4/A4 Quattro/S4/S4 Avant and Audi RS4 were listed with incorrect manufacturer designations. The final theft data has been revised to reflect that Audi is the manufacturer for the Audi RS4, Audi A8...

Exploring the Impacts of Accelerated Delivery on Student Learning, Achievement and Satisfaction

ERIC Educational Resources Information Center

Wilkins, Stephen; Martin, Susan; Walker, Ian

2010-01-01

This case study examines the impacts on student learning, achievement and satisfaction when year 13 (final year) students at a large UK sixth-form college take a GCE A level in one year instead of the usual two years. Data relating to the entry qualifications and final A level grades achieved by 879 students on both accelerated and non-accelerated…

Vocational Curriculum Modification. Teaching Technical Language to Learning Handicapped Students. Project HIRE: A Curriculum Management System for Instructing the Handicapped. Final Report, Volume 1.

ERIC Educational Resources Information Center

Gardner, David C.; And Others

Volume 1 of the final report on Project HIRE reports the design, development, field-testing, and refining of self-instructional packages to teach entry level technical vocabulary to learning handicapped students mainstreamed in vocational programs. Volume 2, a management handbook, reports the methods and findings concerning development of…

Developing and Testing Simulated Occupational Experiences for Distributive Education Students in Rural Communities: Volume III: Training Plans: Final Report.

ERIC Educational Resources Information Center

Virginia Polytechnic Inst. and State Univ., Blacksburg.

Volume 3 of a three volume final report presents prototype job training plans developed as part of a research project which pilot tested a distributive education program for rural schools utilizing a retail store simulation plan. The plans are for 15 entry-level and 15 career-level jobs in seven categories of distributive business (department…

Analysis of Mars Pathfinder Entry Data, Aerothermal Heating, and Heat Shield Material Response

NASA Technical Reports Server (NTRS)

Milos, Frank; Chen, Y. K.; Tran, H. K.; Rasky, Daniel J. (Technical Monitor)

1997-01-01

The Mars Pathfinder heatshield contained several thermocouples and resistance thermometers. A description of the experiment, the entry data, and analysis of the entry environment and material response is presented. In particular, the analysis addresses uncertainties of the data and the fluid dynamics and material response models. The calculations use the latest trajectory and atmosphere reconstructions for the Pathfinder entry. A modified version of the GIANTS code is used for CFD (computational fluid dynamics) analyses, and FIAT is used for material response. The material response and flowfield are coupled appropriately. Three different material response models are considered. The analysis of Pathfinder entry data for validation of aerothermal heating and material response models is complicated by model uncertainties and unanticipated data-acquisition and processing problems. We will discuss these issues as well as ramifications of the data and analysis for future Mars missions.

Woven Thermal Protection System (WTPS) a Novel Approach to Meet Nasa's Most Demanding Reentry Missions

NASA Technical Reports Server (NTRS)

Stackpoole, Margaret M.; Ellerby, Donald T.; Gasch, Matt; Ventkatapathy, Ethiraj; Beerman, Adam; Boghozian, Tane; Gonzales, Gregory; Feldman, Jay; Peterson, Keith; Prabhu, Dinesh

2014-01-01

NASA's future robotic missions to Venus and other planets, namely, Saturn, Uranus, Neptune, result in extremely high entry conditions that exceed the capabilities of current mid density ablators (PICA or Avcoat). Therefore mission planners assume the use of a fully dense carbon phenolic heatshield similar to what was flown on Pioneer Venus and Galileo. Carbon phenolic is a robust TPS, however, its high density and thermal conductivity constrain mission planners to steep entries, high fluxes, pressures and short entry durations, in order for CP to be feasible from a mass perspective. The high entry conditions pose certification challenges in existing ground based test facilities. In 2012 the Game Changing Development Program in NASA's Space Technology Mission Directorate funded NASA ARC to investigate the feasibility of a Woven Thermal Protection System to meet the needs of NASA's most challenging entry missions. This presentation will summarize the maturation of the WTPS project.

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.

75 FR 44940 - Withdrawal of Application for Duty-Free Entry of Scientific Instruments

Federal Register 2010, 2011, 2012, 2013, 2014

2010-07-30

... Entry of Scientific Instruments Applications may be examined between 8:30 A.M. and 5:00 P.M. in Room... determine, inter alia, whether instruments of equivalent scientific value, for the purposes for which the... scientific instrument. They noted that the instrument will be used at a show/demonstration. As noted in the...

76 FR 52936 - Withdrawal of Application for Duty-Free Entry of Scientific Instruments

Federal Register 2010, 2011, 2012, 2013, 2014

2011-08-24

... Entry of Scientific Instruments Applications may be examined between 8:30 a.m. and 5 p.m. in Room 3720... determine, inter alia, whether instruments of equivalent scientific value, for the purposes for which the... scientific instrument. They noted that the instrument will be cleared through Customs with duty paid by the...

20 CFR 645.420 - What factors will be used in measuring State performance?

Code of Federal Regulations, 2010 CFR

2010-04-01

... measure State performance: (1) Job entry rate as measured by the proportion of WtW participants who enter either subsidized employment or unsubsidized employment, (2) Substantive job entry rate as measured by... employment of 30 hours or more per week, (3) Retention as measured by the proportion of WtW participants who...

KSC-06pd2223

NASA Image and Video Library

2006-09-26

KENNEDY SPACE CENTER, FLA. - Workers mingle around the west door entry to the crew exploration vehicle (CEV) environment in the Operations and Checkout Building. A ribbon-cutting officially reactivated the entry. During the rest of the decade, KSC will transition from launching space shuttles to launching new vehicles in NASA’s Vision For Space Exploration. Photo credit: NASA/Kim Shiflett

9 CFR 98.34 - Import permits for poultry semen and animal semen.

Code of Federal Regulations, 2010 CFR

2010-01-01

... eartag; the region of origin; the name and address of the exporter; the port of embarkation in the foreign region; the mode of transportation, route of travel, and the port of entry in the United States... delivery will be made from the port of entry. Additional information may be required in the form of...

9 CFR 98.34 - Import permits for poultry semen and animal semen.

Code of Federal Regulations, 2011 CFR

2011-01-01

... eartag; the region of origin; the name and address of the exporter; the port of embarkation in the foreign region; the mode of transportation, route of travel, and the port of entry in the United States... delivery will be made from the port of entry. Additional information may be required in the form of...

31 CFR 357.24 - Availability and disclosure of Legacy Treasury Direct ® records.

Code of Federal Regulations, 2012 CFR

2012-07-01

... REGULATIONS GOVERNING BOOK-ENTRY TREASURY BONDS, NOTES AND BILLS HELD IN TREASURY/RESERVE AUTOMATED DEBT ENTRY... Privacy Act (5 U.S.C. 552a), information relating to those accounts will be released only to the owner...) Sufficient information is provided to identify the Legacy Treasury Direct account. (c) Conditions for release...

31 CFR 357.24 - Availability and disclosure of Legacy Treasury Direct ® records.

Code of Federal Regulations, 2013 CFR

2013-07-01

... REGULATIONS GOVERNING BOOK-ENTRY TREASURY BONDS, NOTES AND BILLS HELD IN TREASURY/RESERVE AUTOMATED DEBT ENTRY... Privacy Act (5 U.S.C. 552a), information relating to those accounts will be released only to the owner...) Sufficient information is provided to identify the Legacy Treasury Direct account. (c) Conditions for release...

31 CFR 357.24 - Availability and disclosure of Legacy Treasury Direct ® records.

Code of Federal Regulations, 2011 CFR

2011-07-01

... REGULATIONS GOVERNING BOOK-ENTRY TREASURY BONDS, NOTES AND BILLS HELD IN TREASURY/RESERVE AUTOMATED DEBT ENTRY... Privacy Act (5 U.S.C. 552a), information relating to those accounts will be released only to the owner...) Sufficient information is provided to identify the Legacy Treasury Direct account. (c) Conditions for release...

31 CFR 357.24 - Availability and disclosure of Legacy Treasury Direct ® records.

Code of Federal Regulations, 2014 CFR

2014-07-01

... REGULATIONS GOVERNING BOOK-ENTRY TREASURY BONDS, NOTES AND BILLS HELD IN TREASURY/RESERVE AUTOMATED DEBT ENTRY... Privacy Act (5 U.S.C. 552a), information relating to those accounts will be released only to the owner...) Sufficient information is provided to identify the Legacy Treasury Direct account. (c) Conditions for release...

9 CFR 93.321 - Import permits and applications for inspection for horses.

Code of Federal Regulations, 2010 CFR

2010-01-01

... States from Mexico, the importer or his or her agent shall deliver to the veterinary inspector at the port of entry an application, in writing, for inspection, so that the veterinary inspector and customs... veterinary inspector at the port of entry will provide the importer or his or her agent with a written...

9 CFR 93.321 - Import permits and applications for inspection for horses.

Code of Federal Regulations, 2011 CFR

2011-01-01

... States from Mexico, the importer or his or her agent shall deliver to the veterinary inspector at the port of entry an application, in writing, for inspection, so that the veterinary inspector and customs... veterinary inspector at the port of entry will provide the importer or his or her agent with a written...

7 CFR 319.8-8 - Lint, linters, and waste.

Code of Federal Regulations, 2012 CFR

2012-01-01

... Importation and Entry of Cotton and Covers § 319.8-8 Lint, linters, and waste. (a) Compressed to high density. (1)(i) Entry of lint, linters, and waste, compressed to high density, will be authorized subject to... to high density arriving at a port in the State of California where there are no approved fumigation...

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.

High-speed rail turnout literature review : final report.

DOT National Transportation Integrated Search

2016-08-01

High-speed rail (HSR) turnout design criteria generally address unbalanced lateral acceleration or cant deficiency (CD), cant deficiency change rate (CDCR), and entry and exit jerk. Various countries have adopted different design values for their HSR...

Construction records study : final report.

DOT National Transportation Integrated Search

1975-09-01

The purpose of this study was to determine the extent of change and revision necessary for efficient record keeping and to revise the record keeping process in the field, eliminating irrelevant entries. This study attempted to standardize field recor...

A space radiation transport method development

NASA Technical Reports Server (NTRS)

Wilson, J. W.; Tripathi, R. K.; Qualls, G. D.; Cucinotta, F. A.; Prael, R. E.; Norbury, J. W.; Heinbockel, J. H.; Tweed, J.

2004-01-01

Improved spacecraft shield design requires early entry of radiation constraints into the design process to maximize performance and minimize costs. As a result, we have been investigating high-speed computational procedures to allow shield analysis from the preliminary design concepts to the final design. In particular, we will discuss the progress towards a full three-dimensional and computationally efficient deterministic code for which the current HZETRN evaluates the lowest-order asymptotic term. HZETRN is the first deterministic solution to the Boltzmann equation allowing field mapping within the International Space Station (ISS) in tens of minutes using standard finite element method (FEM) geometry common to engineering design practice enabling development of integrated multidisciplinary design optimization methods. A single ray trace in ISS FEM geometry requires 14 ms and severely limits application of Monte Carlo methods to such engineering models. A potential means of improving the Monte Carlo efficiency in coupling to spacecraft geometry is given in terms of re-configurable computing and could be utilized in the final design as verification of the deterministic method optimized design. Published by Elsevier Ltd on behalf of COSPAR.

Mars2020 Entry, Descent, and Landing Instrumentation 2 (MEDLI2) Do No Harm Test Series

NASA Technical Reports Server (NTRS)

Swanson, Gregory; Santos, Jose; White, Todd; Bruce, Walt; Kuhl, Chris; Wright, Henry

2017-01-01

A total of seventeen instrumented thermal sensor plugs, eight pressure transducers, two heat flux sensors, and one radiometer are planned to be utilized on the Mars 2020 missions thermal protection system (TPS) as part of the Mars Entry, Descent, and Landing Instrumentation II (MEDLI2) project. Of the MEDLI2 instrumentation, eleven instrumented thermal plugs and seven pressure transducers will be installed on the heatshield of the Mars 2020 vehicle while the rest will be installed on the backshell. The goal of the MEDLI2 instrumentation is to directly inform the large performance uncertainties that contribute to the design and validation of a Mars entry system. A better understanding of the entry environment and TPS performance could lead to reduced design margins enabling a greater payload mass-fraction and smaller landing ellipses. To prove that the MEDLI2 system will not degrade the performance of the Mars 2020 TPS, an Aerothermal Do No Harm (DNH) test series was designed and conducted. Like Mars 2020s predecessor, Mars Science Laboratory (MSL), the heatshield material will be Phenolic Impregnated Carbon Ablator (PICA); the Mars 2020 entry conditions are enveloped by the MSL design environments, therefore the development and qualification testing performed during MEDLI is sufficient to show that the similar MEDLI2 heatshield instrumentation will not degrade PICA performance. However, given that MEDLI did not include any backshell instrumentation, the MEDLI2 team was required to design and execute a DNH test series utilizing the backshell TPS material (SLA-561V) with the intended flight sensor suite. To meet the requirements handed down from Mars 2020, the MEDLI2 DNH test series emphasized the interaction between the MEDLI2 sensors and sensing locations with the surrounding backshell TPS and substrucutre. These interactions were characterized by performing environmental testing of four 12 by 12 test panels, which mimicked the construction of the backshell TPS and the integration of the MEDLI2 sensors as seen in Figure 1. The testing included thermal vacuumcycling, random vibration, shock, and arc jet testing. The test panels were fabricated by Lockheed Martin, establishing techniques that will be utilized during the Mars 2020 vehicle installation. Each test panel included one thermal sensor plug (two embedded thermocouples), one heat flux sensor, and multiple pressure port holes for evaluation.This presentation will discuss the planning and execution of the MEDLI2 DNH test series. Selected highlights and results of each environmental test will be presented, and lessons learned will be addressed that will feed forward into the planning for the MEDLI2 flight system certification testing.

The Glycoproteins of All Filovirus Species Use the Same Host Factors for Entry into Bat and Human Cells but Entry Efficiency Is Species Dependent.

PubMed

Hoffmann, Markus; González Hernández, Mariana; Berger, Elisabeth; Marzi, Andrea; Pöhlmann, Stefan

2016-01-01

Ebola and marburgviruses, members of the family Filoviridae, can cause severe hemorrhagic fever in humans. The ongoing Ebola virus (EBOV) disease epidemic in Western Africa claimed more than 11,300 lives and was associated with secondary cases outside Africa, demonstrating that filoviruses pose a global health threat. Bats constitute an important natural reservoir of filoviruses, including viruses of the recently identified Cuevavirus genus within the Filoviridae family. However, the interactions of filoviruses with bat cells are incompletely understood. Here, we investigated whether filoviruses employ different strategies to enter human and bat cells. For this, we examined host cell entry driven by glycoproteins (GP) from all filovirus species into cell lines of human and fruit bat origin. We show that all GPs were able to mediate entry into human and most fruit bat cell lines with roughly comparable efficiency. In contrast, the efficiency of entry into the cell line EidNi/41 derived from a straw-colored fruit bat varied markedly between the GPs of different filovirus species. Furthermore, inhibition studies demonstrated that filoviruses employ the same host cell factors for entry into human, non-human primate and fruit bat cell lines, including cysteine proteases, two pore channels and NPC1 (Niemann-Pick C1 molecule). Finally, processing of GP by furin and the presence of the mucin-like domain in GP were dispensable for entry into both human and bat cell lines. Collectively, these results show that filoviruses rely on the same host cell factors for entry into human and fruit bat cells, although the efficiency of the usage of these factors might differ between filovirus species.

The Glycoproteins of All Filovirus Species Use the Same Host Factors for Entry into Bat and Human Cells but Entry Efficiency Is Species Dependent

PubMed Central

Hoffmann, Markus; González Hernández, Mariana; Berger, Elisabeth; Marzi, Andrea; Pöhlmann, Stefan

2016-01-01

Ebola and marburgviruses, members of the family Filoviridae, can cause severe hemorrhagic fever in humans. The ongoing Ebola virus (EBOV) disease epidemic in Western Africa claimed more than 11,300 lives and was associated with secondary cases outside Africa, demonstrating that filoviruses pose a global health threat. Bats constitute an important natural reservoir of filoviruses, including viruses of the recently identified Cuevavirus genus within the Filoviridae family. However, the interactions of filoviruses with bat cells are incompletely understood. Here, we investigated whether filoviruses employ different strategies to enter human and bat cells. For this, we examined host cell entry driven by glycoproteins (GP) from all filovirus species into cell lines of human and fruit bat origin. We show that all GPs were able to mediate entry into human and most fruit bat cell lines with roughly comparable efficiency. In contrast, the efficiency of entry into the cell line EidNi/41 derived from a straw-colored fruit bat varied markedly between the GPs of different filovirus species. Furthermore, inhibition studies demonstrated that filoviruses employ the same host cell factors for entry into human, non-human primate and fruit bat cell lines, including cysteine proteases, two pore channels and NPC1 (Niemann-Pick C1 molecule). Finally, processing of GP by furin and the presence of the mucin-like domain in GP were dispensable for entry into both human and bat cell lines. Collectively, these results show that filoviruses rely on the same host cell factors for entry into human and fruit bat cells, although the efficiency of the usage of these factors might differ between filovirus species. PMID:26901159

Mutagenesis Studies of the H5 Influenza Hemagglutinin Stem Loop Region*

PubMed Central

Antanasijevic, Aleksandar; Basu, Arnab; Bowlin, Terry L.; Mishra, Rama K.; Rong, Lijun; Caffrey, Michael

2014-01-01

Influenza outbreaks, particularly the pandemic 1918 H1 and avian H5 strains, are of high concern to public health. The hemagglutinin envelope protein of influenza plays a critical role in viral entry and thus is an attractive target for inhibition of virus entry. The highly conserved stem loop region of hemagglutinin has been shown to undergo critically important conformational changes during the entry process and, moreover, to be a site for inhibition of virus entry by antibodies, small proteins, and small drug-like molecules. In this work we probe the structure-function properties of the H5 hemagglutinin stem loop region by site-directed mutagenesis. We find that most mutations do not disrupt expression, proteolytic processing, incorporation into virus, or receptor binding; however, many of the mutations disrupt the entry process. We further assess the effects of mutations on inhibition of entry by a neutralizing monoclonal antibody (C179) and find examples of increased and decreased sensitivity to the antibody, consistent with the antibody binding site observed by x-ray crystallography. In addition, we tested the sensitivity of the mutants to MBX2329, a small molecule inhibitor of influenza entry. Interestingly, the mutants exhibit increased and decreased sensitivities to MBX2329, which gives further insight into the binding site of the compound on HA and potential mechanisms of escape. Finally, we have modeled the binding site of MBX2329 using molecular dynamics and find that the resulting structure is in good agreement with the mutagenesis results. Together these studies underscore the importance of the stem loop region to HA function and suggest potential sites for therapeutic intervention of influenza entry. PMID:24947513

Mutagenesis studies of the H5 influenza hemagglutinin stem loop region.

PubMed

Antanasijevic, Aleksandar; Basu, Arnab; Bowlin, Terry L; Mishra, Rama K; Rong, Lijun; Caffrey, Michael

2014-08-08

Influenza outbreaks, particularly the pandemic 1918 H1 and avian H5 strains, are of high concern to public health. The hemagglutinin envelope protein of influenza plays a critical role in viral entry and thus is an attractive target for inhibition of virus entry. The highly conserved stem loop region of hemagglutinin has been shown to undergo critically important conformational changes during the entry process and, moreover, to be a site for inhibition of virus entry by antibodies, small proteins, and small drug-like molecules. In this work we probe the structure-function properties of the H5 hemagglutinin stem loop region by site-directed mutagenesis. We find that most mutations do not disrupt expression, proteolytic processing, incorporation into virus, or receptor binding; however, many of the mutations disrupt the entry process. We further assess the effects of mutations on inhibition of entry by a neutralizing monoclonal antibody (C179) and find examples of increased and decreased sensitivity to the antibody, consistent with the antibody binding site observed by x-ray crystallography. In addition, we tested the sensitivity of the mutants to MBX2329, a small molecule inhibitor of influenza entry. Interestingly, the mutants exhibit increased and decreased sensitivities to MBX2329, which gives further insight into the binding site of the compound on HA and potential mechanisms of escape. Finally, we have modeled the binding site of MBX2329 using molecular dynamics and find that the resulting structure is in good agreement with the mutagenesis results. Together these studies underscore the importance of the stem loop region to HA function and suggest potential sites for therapeutic intervention of influenza entry. © 2014 by The American Society for Biochemistry and Molecular Biology, Inc.

Improving laboratory data entry quality using Six Sigma.

PubMed

Elbireer, Ali; Le Chasseur, Julie; Jackson, Brooks

2013-01-01

The Uganda Makerere University provides clinical laboratory support to over 70 clients in Uganda. With increased volume, manual data entry errors have steadily increased, prompting laboratory managers to employ the Six Sigma method to evaluate and reduce their problems. The purpose of this paper is to describe how laboratory data entry quality was improved by using Six Sigma. The Six Sigma Quality Improvement (QI) project team followed a sequence of steps, starting with defining project goals, measuring data entry errors to assess current performance, analyzing data and determining data-entry error root causes. Finally the team implemented changes and control measures to address the root causes and to maintain improvements. Establishing the Six Sigma project required considerable resources and maintaining the gains requires additional personnel time and dedicated resources. After initiating the Six Sigma project, there was a 60.5 percent reduction in data entry errors from 423 errors a month (i.e. 4.34 Six Sigma) in the first month, down to an average 166 errors/month (i.e. 4.65 Six Sigma) over 12 months. The team estimated the average cost of identifying and fixing a data entry error to be $16.25 per error. Thus, reducing errors by an average of 257 errors per month over one year has saved the laboratory an estimated $50,115 a year. The Six Sigma QI project provides a replicable framework for Ugandan laboratory staff and other resource-limited organizations to promote quality environment. Laboratory staff can deliver excellent care at a lower cost, by applying QI principles. This innovative QI method of reducing data entry errors in medical laboratories may improve the clinical workflow processes and make cost savings across the health care continuum.

Three essays on auction markets

NASA Astrophysics Data System (ADS)

Shunda, Nicholas James

This dissertation contains a series of theoretical investigations of auction markets. The essays it contains cover wholesale electricity markets, a popular selling mechanism on eBay, and supplier entry into multi-unit procurement auctions. The study in Chapter 1 compares the procurement cost-minimizing and productive efficiency performance of the auction mechanism used by independent system operators in wholesale electricity auction markets in the U.S. with that of a proposed alternative. The current practice allocates energy contracts as if the auction featured a discriminatory final payment method when, in fact, the markets are uniform price auctions. The proposed alternative explicitly accounts for the market-clearing price during the allocation phase. We find that the proposed alternative largely outperforms the current practice on the basis of procurement costs in the context of simple auction markets featuring both day-ahead and real-time auctions and that the procurement cost advantage of the alternative is complete when we simulate the effects of increased competition. We also find that a tradeoff between the objectives of procurement cost minimization and productive efficiency emerges in our simple auction markets and persists in the face of increased competition. The study in Chapter 2 considers a possible rationale for an auction with a buy price. In an auction with a buy price, the seller provides bidders with an option to end the auction early by accepting a transaction at a posted price. The "Buy-It-Now" option on eBay is a leading example of an auction with a buy price. The study develops a model of an auction with a buy price in which bidders use the auction's reserve price and buy price to formulate a reference price. The model both explains why a revenue-maximizing seller would want to augment her auction with a buy price and demonstrates that the seller sets a higher reserve price when she can affect the bidders' reference price through the auction's reserve price and buy price than when she can affect the bidders' reference price through the auction's reserve price only. Introducing a small reference-price effect can shrink the range of buy prices bidders are willing to exercise. The comparative statics properties of bidding behavior are in sharp contrast to equilibrium behavior in other models where the existence and size of the auction's buy price have no effect on bidding behavior. The study in Chapter 3 investigates endogenous entry in multi-unit auctions. We formulate and study models of multi-unit discriminatory and uniform price auctions and investigate the entry incentives and procurement costs they generate in equilibrium. We study two types of endogenous entry: in auctions with "interim entry costs," suppliers know their private cost information before deciding whether or not to undertake entry; in auctions with ex ante entry costs, suppliers do not know their private cost information before deciding whether or not to enter. The discriminatory and uniform price auctions are efficient and procurement cost equivalent in all the environments we study. With interim entry costs, the two auctions provide identical entry incentives. In contrast, with ex ante entry costs, suppliers enter the discriminatory auction at a higher rate than they enter the uniform price auction.

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.

ClinicalTrials.gov as a data source for semi-automated point-of-care trial eligibility screening.

PubMed

Pfiffner, Pascal B; Oh, JiWon; Miller, Timothy A; Mandl, Kenneth D

2014-01-01

Implementing semi-automated processes to efficiently match patients to clinical trials at the point of care requires both detailed patient data and authoritative information about open studies. To evaluate the utility of the ClinicalTrials.gov registry as a data source for semi-automated trial eligibility screening. Eligibility criteria and metadata for 437 trials open for recruitment in four different clinical domains were identified in ClinicalTrials.gov. Trials were evaluated for up to date recruitment status and eligibility criteria were evaluated for obstacles to automated interpretation. Finally, phone or email outreach to coordinators at a subset of the trials was made to assess the accuracy of contact details and recruitment status. 24% (104 of 437) of trials declaring on open recruitment status list a study completion date in the past, indicating out of date records. Substantial barriers to automated eligibility interpretation in free form text are present in 81% to up to 94% of all trials. We were unable to contact coordinators at 31% (45 of 146) of the trials in the subset, either by phone or by email. Only 53% (74 of 146) would confirm that they were still recruiting patients. Because ClinicalTrials.gov has entries on most US and many international trials, the registry could be repurposed as a comprehensive trial matching data source. Semi-automated point of care recruitment would be facilitated by matching the registry's eligibility criteria against clinical data from electronic health records. But the current entries fall short. Ultimately, improved techniques in natural language processing will facilitate semi-automated complex matching. As immediate next steps, we recommend augmenting ClinicalTrials.gov data entry forms to capture key eligibility criteria in a simple, structured format.

Appraising fire effects

Treesearch

Robert M. Loomis; Donna M. Paananen

1989-01-01

Fire effects in the central hardwood forest vary greatly. Depending on a number of factors, some trees will be killed immediately; others will be injured and die in a year or more; still others will incur basal wounds that can provide entry for decay; and some trees will not be affected.

Advanced Aero-Propulsive Mid-Lift-to-Drag Ratio Entry Vehicle for Future Exploration Missions

NASA Technical Reports Server (NTRS)

Campbell, C. H.; Stosaric, R. R; Cerimele, C. J.; Wong, K. A.; Valle, G. D.; Garcia, J. A.; Melton, J. E.; Munk, M. M.; Blades, E.; Kuruvila, G.;

Venus Atmospheric Maneuverable Platform (VAMP) - A Low Cost Venus Exploration Concept

NASA Astrophysics Data System (ADS)

Lee, G.; Polidan, R. S.; Ross, F.

2015-12-01

The Northrop Grumman Aerospace Systems and L-Garde team has been developing an innovative mission concept: a long-lived, maneuverable platform to explore the Venus upper atmosphere. This capability is an implementation of our Lifting Entry Atmospheric Flight (LEAF) system concept, and the Venus implementation is called the Venus Atmospheric Maneuverable Platform (VAMP). The VAMP concept utilizes an ultra-low ballistic coefficient (< 50 Pa), semi-buoyant aircraft that deploys prior to entering the Venus atmosphere, enters without an aeroshell, and provides a long-lived (months to a year) maneuverable vehicle capable of carrying science instruments to explore the Venus upper atmosphere. In this presentation we provide an update on the air vehicle design and a low cost pathfinder mission concept that can be implemented in the near-term. The presentation also provides an overview of our plans for future trade studies, analyses, and prototyping to advance and refine the concept. We will discuss the air vehicle's entry concepts of operations (CONOPs) and atmospheric science operations. We will present a strawman concept of a VAMP pathfinder, including ballistic coefficient, planform area, percent buoyancy, wing span, vehicle mass, power supply, propulsion, materials considerations, structural elements, and instruments accommodation. In this context, we will discuss the following key factors impacting the design and performance of VAMP: Entry into the Venus atmosphere, including descent profile, heating rate, total heat load, stagnation, and acreage temperatures Impact of maximum altitude on air vehicle design and entry heating Candidate thermal protection system (TPS) requirements We will discuss the interdependencies of the above factors and the manner in which the VAMP pathfinder concept's characteristics affect the CONOPs and the science objectives. We will show how the these factors provide constraints as well as enable opportunities for novel long duration scientific studies of the Venus upper atmosphere that support Venus science goals. We will also discuss how the VAMP platform itself can facilitate some of these science measurements.

A Survey of Supersonic Retropropulsion Technology for Mars Entry, Descent, and Landing

NASA Technical Reports Server (NTRS)

Korzun, Ashley M.; Cruz, Juan R.; Braun, Robert D.

2007-01-01

This paper presents a literature survey on supersonic retropropulsion technology as it applies to Mars entry, descent, and landing (EDL). The relevance of this technology to the feasibility of Mars EDL is shown to increase with ballistic coefficient to the point that it is likely required for human Mars exploration. The use of retropropulsion to decelerate an entry vehicle from hypersonic or supersonic conditions to a subsonic velocity is the primary focus of this review. Discussed are systems-level studies, general flowfield characteristics, static aerodynamics, vehicle and flowfield stability considerations, and aerothermodynamics. The experimental and computational approaches used to develop retropropulsion technology are also reviewed. Finally, the applicability and limitations of the existing literature and current state-of-the-art computational tools to future missions are discussed in the context of human and robotic Mars exploration.

A Mars/phobos Transportation System

NASA Technical Reports Server (NTRS)

1989-01-01

A transportation system will be necessary to support construction and operation of bases on Phobos and Mars beginning in the year 2020 or later. An approach to defining a network of vehicles and the types of vehicles which may be used in the system are presented. The network will provide a convenient, integrated means for transporting robotically constructed bases to Phobos and Mars. All the technology needed for the current plan is expected to be available for use at the projected date of cargo departure from the Earth system. The modular design of the transportation system provides easily implemented contingency plans, so that difficulties with any one vehicle will have a minimal effect on the progress of the total mission. The transportation network proposed consists of orbital vehicles and atmospheric entry vehicles. Initially, only orbital vehicles will participate in the robotic construction phase of the Phobos base. The Interplanetary Transfer Vehicle (ITV) will carry the base and construction equipment to Phobos where the Orbital Maneuvering Vehicles (OMV's) will participate in the initial construction of the base. When the Mars base is ready to be sent, one or more ITV's will be used to transport the atmospheric entry vehicles from Earth. These atmospheric vehicles are the One Way Landers (OWL's) and the Ascent/Descent Vehicles (ADV's). They will be used to carry the base components and/or construction equipment. The OMV's and the Orbital Transfer Vehicles (OTV's) will assist in carrying the atmospheric entry vehicles to low Martian orbit where the OWL's or ADV's will descent to the planet surface. The ADV's were proposed to accommodate expansion of the system. Additionally, a smaller version of the ADV class is capable of transporting personnel between Mars and Phobos.

Plans and Status of Wind-Tunnel Testing Employing an Aeroservoelastic Semispan Model

NASA Technical Reports Server (NTRS)

Perry, Boyd, III; Silva, Walter A.; Florance, James R.; Wieseman, Carol D.; Pototzky, Anthony S.; Sanetrik, Mark D.; Scott, Robert C.; Keller, Donald F.; Cole, Stanley R.; Coulson, David A.

2007-01-01

This paper presents the research objectives, summarizes the pre-wind-tunnel-test experimental results to date, summarizes the analytical predictions to date, and outlines the wind-tunnel-test plans for an aeroservoelastic semispan wind-tunnel model. The model is referred to as the Supersonic Semispan Transport (S4T) Active Controls Testbed (ACT) and is based on a supersonic cruise configuration. The model has three hydraulically-actuated surfaces (all-movable horizontal tail, all-movable ride control vane, and aileron) for active controls. The model is instrumented with accelerometers, unsteady pressure transducers, and strain gages and will be mounted on a 5-component sidewall balance. The model will be tested twice in the Langley Transonic Dynamics Tunnel (TDT). The first entry will be an "open-loop" model-characterization test; the second entry will be a "closed-loop" test during which active flutter suppression, gust load alleviation and ride quality control experiments will be conducted.

77 FR 61654 - Notice of Final Federal Agency Actions on Proposed Highway in California

Federal Register 2010, 2011, 2012, 2013, 2014

2012-10-10

...This notice announces actions taken by the FHWA and other Federal agencies that are final within the meaning of 23 U.S.C. 139(l)(1). The actions relate to the proposed State Route 11 and Otay Mesa East Land Port of Entry in the City and County of San Diego, State of California. These actions grant licenses, permits, and approvals for the project.