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Sample records for adaptive deployable entry

  1. Adaptable Deployable Entry and Placement Technology (ADEPT)

    NASA Video Gallery

    The Adaptable, Deployable Entry Placement Technology (ADEPT) Project will test and demonstrate a deployable aeroshell concept as a viable thermal protection system for entry, descent, and landing o...

  2. Adaptable, Deployable Entry and Placement Technology (ADEPT) for Future Mars Missions

    NASA Technical Reports Server (NTRS)

    Wercinski, P.; Venkatapathy, E.; Gage, P.; Prabhu, D.; Smith, B.; Cassell, A.; Yount, B.; Allen, G.

    2013-01-01

    The concept of a mechanically deploy- able hypersonic decelerator, developed initially for high mass (40 MT) human Mars missions, is currently funded by OCT for technology maturation. The ADEPT (Adaptive, Deployable Entry and Placement Technology) project has broad, game-changing applicability to in situ science missions to Venus, Mars, and the Outer Planets.

  3. 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

  4. Thermal and Structural Performance of Woven Carbon Cloth For Adaptive Deployable Entry and Placement Technology

    NASA Technical Reports Server (NTRS)

    Arnold, James O.; Peterson, Keith H.; Yount, Bryan C.; Schneider, Nigel; Chavez-Garcia, Jose

    2013-01-01

    Arcjet testing and analysis of a three-dimensional (3D) woven carbon fabric has shown that it can be used as a thermal protection system and as a load bearing structural component for a low ballistic coefficient hypersonic decelerator called ADEPT (Adaptive Deployable Entry and Placement Technology). Results of arcjet tests proved that the 3D woven carbon fabric can withstand flight-like heating while under flight-like biaxial mechanical loads representative of those encountered during shallow entry flight path angles into the atmosphere of Venus. Importantly, the arcjet test results have been used to extend a preliminary material thermal response model based on previous testing of the same 3D woven carbon fabric under uni-axial mechanical loading.

  5. Arcjet Testing of Woven Carbon Cloth for Use on Adaptive Deployable Entry Placement Technology

    NASA Technical Reports Server (NTRS)

    Arnold, James O.; laub, Bernard; Chen, Yih-Kang; Prabhu, Dinesh K.; Bittner, M. E.; Venkatapathy, Ethiraj

    2013-01-01

    This paper describes arcjet testing and analysis that has successfully demonstrated the viability of three dimensional woven carbon cloth for dual use in the Adaptive Deployable Entry Placement Technology (ADEPT). ADEPT is an umbrella-like entry system that is folded for stowage in the launch vehicle s shroud and deployed in space prior to reaching the atmospheric interface. A key feature of the ADEPT concept is its lower ballistic coefficient for delivery of a given payload than those for conventional, rigid body entry systems. The benefits that accrue from the lower ballistic coefficient include factor of ten reductions of deceleration forces and entry heating. The former enables consideration of new classes of scientific instruments for solar system exploration while the latter enables the design of a more efficient thermal protection system. The carbon cloth now base lined for ADEPT has a dual use in that it serves as ADEPT s thermal protection system and as the "skin" that transfers aerodynamic deceleration loads to its umbrella-like substructure. The arcjet testing described in this paper was conducted for some of the higher heating conditions for a future Venus mission using the ADEPT concept, thereby showing that the carbon cloth can perform in a relevant entry environment. The ADEPT project considered the carbon cloth to be mission enabling and was carrying it as a major risk during Fiscal Year 2012. The testing and analysis reported here played a major role in retiring that risk and is highly significant to the success and possible adoption of ADEPT for future NASA missions. Finally, this paper also describes a preliminary engineering level code, based on the arcjet data, that can be used to estimate cloth thickness for future missions using ADEPT and to predict carbon cloth performance in future arcjet tests.

  6. Adaptable Deployable Entry & Placement Technology (ADEPT) for Cubesat Delivery to Mars Surface

    NASA Technical Reports Server (NTRS)

    Wercinski, Paul

    2014-01-01

    The Adaptable, Deployable Entry and Placement Technology (ADEPT), uses a mechanical skeleton to deploy a revolutionary carbon fabric system that serves as both heat shield and primary structure during atmospheric entry. The NASA ADEPT project, currently funded by the Game Changing Development Program in STMD is currently focused on 1m class hypersonic decelerators for the delivery of very small payloads ( 5 kg) to locations of interest in an effort to leverage low-cost platforms to rapidly mature the technology while simultaneously delivering high-value science. Preliminary mission design and aerothermal performance testing in arcjets have shown the ADEPT system is quite capable of safe delivery of cubesats to Mars surface. The ability of the ADEPT to transit to Mars in a stowed configuration (similar to an umbrella) provides options for integration with the Mars 2020 cruise stage, even to consider multiple ADEPTs. System-level test campaigns are underway for FY15 execution or planning for FY16. These include deployment testing, wind tunnel testing, system-level arc jet testing, and a sounding rocket flight test. The goal is system level maturation (TRL 6) at a 1m class Mars design reference mission configuration.

  7. Adaptable, Deployable Entry and Placement Technology (ADEPT) Overview of FY15 Accomplishments

    NASA Technical Reports Server (NTRS)

    Wercinski, P.; Brivkalns, C.; Cassell, A.; Chen, Y.-K.; Boghozian, T.; Chinnapongse, R.; Gasch, M.; Kruger, C.; Makino, A.; Milos, F.; Nishioka, O.; Smith, B.; Squire, T.; Venkatapathy, E.; Yount, B.; Zarchi, K.

    2015-01-01

    ADEPT is an atmospheric entry architecture for missions to most planetary bodies with atmospheres: Current Technology development project funded under STMD Game Changing Development Program (FY12 start); stowed inside the launch vehicle shroud and deployed in space prior to entry; low ballistic coefficient (less than 50 kilograms per square meter) provides a benign deceleration and thermal environment to the payload; High-temperature ribs support three dimensional woven carbon fabric to generate drag and withstand high heating.

  8. Viability of 3 D Woven Carbon Cloth and Advanced Carbon-Carbon Ribs for Adaptive Deployable Entry Placement Technology (ADEPT) for Future NASA Missions

    NASA Technical Reports Server (NTRS)

    Venkatapathy, Ethiraj; Arnold, James O.; Peterson, K. H.; Blosser, M. L.

    2013-01-01

    This paper describes aerothermodynamic and thermal structural testing that demonstrate the viability of three dimensional woven carbon cloth and advanced carbon-carbon (ACC) ribs for use in the Adaptive Deployable Entry Placement Technology (ADEPT). ADEPT is an umbrella-like entry system that is folded for stowage in the launch vehicle's shroud and deployed prior to reaching the atmeopheric interface. A key feature of the ADEPT concept is a lower ballistic coefficient for delivery of a given payload than seen with conventional, rigid body entry systems. The benefits that accrue from the lower ballistic coefficient incllude factor-of-ten reductions of deceleration forces and entry heating. The former enables consideration of new classes of scientific instruments for solar system exploration while the latter enables the design of a more efficient thermal protection system. The carbon cloth base lined for ADEPT has a dual use in that it serves as the thermal protection system and as the "skin" that transfers aerdynamic deceleration loads to its umbrella-like substructure. Arcjet testing described in this paper was conducted for some of the higher heating conditions for a future Venus mission using the ADEPT concept, thereby showing that the carbon cloth can perform in a relevant entry environment. Recently completed the thermal structural testing of the cloth attached to a representative ACC rib design is also described. Finally, this paper describes a preliminary engineering level code, based on the arcjet data, that can be used to estimate cloth thickness for future ADEPT missions and to predict carbon cloth performance in future arcjet tests.

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

    NASA Technical Reports Server (NTRS)

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

    2012-01-01

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

  10. Investigation of Transonic Wake Dynamics for Mechanically Deployable Entry Systems

    NASA Technical Reports Server (NTRS)

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

    2012-01-01

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

  11. 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.

  12. Longitudinal stability analysis of a suborbital re-entry demonstrator for a deployable capsule

    NASA Astrophysics Data System (ADS)

    Iacovazzo, Michele; Carandente, Valerio; Savino, Raffaele; Zuppardi, Gennaro

    2015-01-01

    In the field of atmospheric re-entry technology several research and industrial projects are based on the design of deployable, umbrella-like Thermal Protection Systems (TPSs) and aero-brakes. These systems are made of flexible, high temperature resistant fabrics, folded at launch and deployed in space for de-orbit and re-entry operations. This technology is very promising for low cost research and industrial applications, but requires to be validated by experimental flight tests. The University of Naples "Federico II" is currently working on the development of different down-scaled technological demonstrators for this kind of capsule to be launched by different classes of sounding rockets. In the present work an aerodynamic longitudinal stability analysis for a possible, suborbital re-entry demonstrator, has been performed in continuum and rarefied regimes. The longitudinal stability behavior of the capsule, along the entire re-entry path, has been investigated in the whole range of angle of attack and, in particular, around the nominal and the reverse equilibrium re-entry attitudes (i.e. around 0° and 180°, respectively) to implement a proper re-entry strategy able not to compromise the effectiveness of the flying system.

  13. 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.

  14. Study on Mini Re-Entry System Using Deployable Membrane Aeroshell

    NASA Astrophysics Data System (ADS)

    Koyama, Masashi; Suzuki, Kojiro; Imamura, Osamu; Yamada, Kazuhiko

    An aeroshell made from membrane material have an advantage of reduction in the aerodynamic heating, because its small mass and large area enable us to make the low-ballistic-coefficient flight, in which the vehicle decelerates at very high altitude with low atmospheric density. In this paper, we propose a new concept of mini re-entry system for small satellites. This vehicle is called "FEATHER" (Flexible Expanded Aeroshell with Tiny payload Harness for Entry and Recovery). "FEATHER" is a novel re-entry and recovery system, featuring the autonomous aeroshell deployment, the low-ballistic-coefficient re-entry with less severe aerodynamicc heating and so on. FEATHER is composed of the membrane aeroshell made from the high-temperature cloth called ZYLON®, an outer frame made of Shape Memory Alloy (SMA) and a payload. When the aeroshell receives the aerodynamic heating, the temperature of SMA frame rises and restores the circular shape as memorized beforehand. Then the membrane aeroshell is automatically deployed. Therefore the vehicle can achieve the low-ballistic-coefficient flight with a drastic reduction in the aerodynamic heating without any additional sensors, controllers and actuators. The preliminary studies made on FEATHER system so far including the hypersonic wind tunnel experiments are presented in this paper.

  15. Adaptive structures for deployment/construction of structures in space

    NASA Technical Reports Server (NTRS)

    Wada, Ben K.; Utku, Senol

    1992-01-01

    The application of adaptive structures to the structural design of space structures is examined with attention given to facilitating their construction in space and enhancing reliability. A modified approach based on traditional techniques is presented which incorporates the loads analysis by Wada (1979) and the application of adaptive structures to control structural motion. An analytical technique is described for the deployment/construction of the structure in which each step of the assembly sequence is analyzed. The use of adaptive structures is shown to permit the static adjustment of the structure after assembly in its operational environment. The concepts presented to incorporate adaptive structures in the deployment of large space structures are expected to improve the reliability and reduce the cost of the total systems.

  16. Deployment and Drop Test of Inflatable Aeroshell for Atmospheric Entry Capsule with using Large Scientific Balloon

    NASA Astrophysics Data System (ADS)

    Yamada, Kazuhiko; Suzuki, Kojiro; Honma, Naohiko; Abe, Daisuke; Makino, Hitoshi; Nagata, Yasunori; Kimura, Yusuke; Koyama, Masashi; Akita, Daisuke; Hayashi, Koichi; Abe, Takashi

    A deployable and flexible aeroshell for atmospheric entry vehicles has attracted attention as an innovative space transportation system in the near future, because the large-area, low-mass aeroshell dramatically reduces aerodynamic heating and achieves a soft landing without a conventional parachute system thanks to its low ballistic coefficient. Various concepts of flexible aeroshell have been proposed in the past. Our group are researching and developing a flare-type membrane aeroshell sustained by inflatable torus. As a part of the development, a deployment and drop test of a capsule-type experimental vehicle with a 1.264-m-diameter flare-type membrane aeroshell sustained by inflatable torus was carried out using a large scientific balloon in August, 2009. The objectives of this experiment are 1) to demonstrate the remote inflation system of inflatable aeroshell, 2) to acquire aerodynamic performance of a low ballistic coefficient vehicle including an inflatable structure in subsonic region, and 3) to observe behavior and deformation of the flexible aeroshell during free flight. In this test, the inflatable aeroshell was deployed at an altitude 24.6km by radio command from ground station. After deployment, the experimental vehicle was dropped from the balloon and underwent free flight. The flight data and images of the aeroshell collected using onboard sensors were transmitted successfully during the flight by the telemetry system. The data showed that the vehicle was almost stable in free flight condition and the inflatable aeroshell was collapsed at expected altitude. This deployment and drop test was very successful and useful data for design of actual atmospheric-entry vehicles with inflatable structure was acquired as planned.

  17. RITD - Adapting Mars Entry, Descent and Landing System for Earth

    NASA Astrophysics Data System (ADS)

    Haukka, H.; Heilimo, J.; Harri, A.-M.; Aleksashkin, S.; Koryanov, V.; Arruego, I.; Schmidt, W.; Finchenko, V.; Martynov, M.; Ponomarenko, A.; Kazakovtsev, V.; Martin, S.

    2015-10-01

    We have developed an atmospheric re-entry and descent system concept based on inflatable hypersonic decelerator techniques that were originally developed for Mars. The ultimate goal of this EU-funded RITD-project (Re-entry: Inflatable Technology Development) was to assess the benefits of this technology when deploying small payloads from low Earth orbits to the surface of the Earth with modest costs. The principal goal was to assess and develop a preliminary EDLS design for the entire relevant range of aerodynamic regimes expected to be encountered in Earth's atmosphere during entry, descent and landing. Low Earth Orbit (LEO) and even Lunar applications envisaged include the use of the EDLS approach in returning payloads of 4-8 kg down to the surface.

  18. A Study on Earth Re-entry Capsules with Deployable Aerobrakes for Recoverable Microgravity Experiments

    NASA Astrophysics Data System (ADS)

    Carandente, Valerio; Savino, Raffaele; D'Oriano, Vera; Fortezza, Raimondo

    2015-06-01

    Deployable aerobrakes for Earth re-entry capsules may offer many advantages in the near future, including the opportunity to recover on Earth scientific payloads from the Space with reduced risks and costs with respect to conventional systems. Such capsules can be accommodated in the selected launcher in folded configuration optimizing the available volume and, when planned by the mission profile, the aerobrake can be deployed in order to increase the surface exposed to the hypersonic flow and therefore to reduce the ballistic parameter. This can offer as main advantage the opportunity to perform an aerodynamic de-orbit of the system without the need of a dedicated propulsive subsystem and an atmospheric re-entry with reduced aerothermal and mechanical loads making possible the use of relatively lightweight and cheap thermal protection system materials. To ensure the recovery of the capsule, the deployable surface can be modulated to obtain the aerodynamic control of the de-orbit trajectory in order to correctly target the capsule towards the selected landing site for post-flight analyses and operations. The main objective of the work is to present a number of feasible mission profiles for orbital platforms to/from Low Earth Orbit aimed in particular at scientific experiments in microgravity conditions. In addition, a suborbital scenario for a technological demonstrator, useful to experimentally verify the system applicability before the design of orbital missions, is also presented and discussed.

  19. RITD - Adapting Mars Entry, Descent and Landing System for Earth

    NASA Astrophysics Data System (ADS)

    Heilimo, Jyri; Harri, Ari-Matti; Aleksashkin, Sergei; Koryanov, Valeri; Arruego, Ignacio; Schmidt, Walter; Haukka, Harri; Finchenko, Valeri; Martynov, Maxim; Ponomarenko, Andrey; Kazakovtsev, Victor; Martin, Susana

    2015-04-01

    We have developed an atmospheric re-entry and descent system concept based on inflatable hypersonic decelerator techniques that were originally developed for Mars. The ultimate goal of this EU-funded RITD-project (Re-entry: Inflatable Technology Development) was to assess the benefits of this technology when deploying small payloads from low Earth orbits to the surface of the Earth with modest costs. The principal goal was to assess and develop a preliminary EDLS design for the entire relevant range of aerodynamic regimes expected to be encountered in Earth's atmosphere during entry, descent and landing. Low Earth Orbit (LEO) and even Lunar applications envisaged include the use of the EDLS approach in returning payloads of 4-8 kg down to the surface. Our development and assessments show clearly that this kind of inflatable technology originally developed for the Martian atmosphere, is feasible for use by Earth entry and descent applications. The preliminary results are highly promising indicating that the current Mars probe design could be used as it is for the Earth. According tp our analyses, the higher atmospheric pressure at an altitude of 12 km and less requires an additional pressurizing device for the in atable system increasing the entry mass by approximately 2 kg. These analyses involved the calculation of 120 different atmospheric entry and descent trajectories. The analysis of the existing technologies and current trends have indicated that the kind of inflatable technology pursued by RITD has high potential to enhance the European space technology expertise. This kind of technology is clearly feasible for utilization by Earth entry and descent applications.

  20. Autonomous atmospheric entry on mars: Performance improvement using a novel adaptive control algorithm

    NASA Astrophysics Data System (ADS)

    Ulrich, Steve; de Lafontaine, Jean

    2007-12-01

    Upcoming landing missions to Mars will require on-board guidance and control systems in order to meet the scientific requirement of landing safely within hundreds of meters to the target of interest. More specifically, in the longitudinal plane, the first objective of the entry guidance and control system is to bring the vehicle to its specified velocity at the specified altitude (as required for safe parachute deployment), while the second objective is to reach the target position in the longitudinal plane. This paper proposes an improvement to the robustness of the constant flight path angle guidance law for achieving the first objective. The improvement consists of combining this guidance law with a novel adaptive control scheme, derived from the so-called Simple Adaptive Control (SAC) technique. Monte-Carlo simulation results are shown to demonstrate the accuracy and the robustness of the proposed guidance and adaptive control system.

  1. Entry Abort Determination Using Non-Adaptive Neural Networks for Mars Precision Landers

    NASA Technical Reports Server (NTRS)

    Graybeal, Sarah R.; Kranzusch, Kara M.

    2005-01-01

    The 2009 Mars Science Laboratory (MSL) will attempt the first precision landing on Mars using a modified version of the Apollo Earth entry guidance program. The guidance routine, Entry Terminal Point Controller (ETPC), commands the deployment of a supersonic parachute after converging the range to the landing target. For very dispersed cases, ETPC may not converge the range to the target and safely command parachute deployment within Mach number and dynamic pressure constraints. A full-lift up abort can save 85% of these failed trajectories while abandoning the precision landing objective. Though current MSL requirements do not call for an abort capability, an autonomous abort capability may be desired, for this mission or future Mars precision landers, to make the vehicle more robust. The application of artificial neural networks (NNs) as an abort determination technique was evaluated by personnel at the National Aeronautics and Space Administration (NASA) Johnson Space Center (JSC). In order to implement an abort, a failed trajectory needs to be recognized in real time. Abort determination is dependent upon several trajectory parameters whose relationships to vehicle survival are not well understood, and yet the lander must be trained to recognize unsafe situations. Artificial neural networks (NNs) provide a way to model these parameters and can provide MSL with the artificial intelligence necessary to independently declare an abort. Using the 2009 Mars Science Laboratory (MSL) mission as a case study, a non-adaptive NN was designed, trained and tested using Monte Carlo simulations of MSL descent and incorporated into ETPC. Neural network theory, the development history of the MSL NN, and initial testing with severe dust storm entry trajectory cases are discussed in Reference 1 and will not be repeated here. That analysis demonstrated that NNs are capable of recognizing failed descent trajectories and can significantly increase the survivability of MSL for very

  2. Aero-thermo-dynamic analysis of a low ballistic coefficient deployable capsule in Earth re-entry

    NASA Astrophysics Data System (ADS)

    Zuppardi, G.; Savino, R.; Mongelluzzo, G.

    2016-10-01

    The paper deals with a microsatellite and the related deployable recovery capsule. The aero-brake is folded at launch and deployed in space and is able to perform a de-orbiting controlled re-entry. This kind of capsule, with a flexible, high temperature resistant fabric, thanks to its lightness and modulating capability, can be an alternative to the current "conventional" recovery capsules. The present authors already analyzed the trajectory and the aerodynamic behavior of low ballistic coefficient capsules during Earth re-entry and Mars entry. In previous studies, aerodynamic longitudinal stability analysis and evaluation of thermal and aerodynamic loads for a possible suborbital re-entry demonstrator were carried out in both continuum and rarefied regimes. The present study is aimed at providing preliminary information about thermal and aerodynamic loads and longitudinal stability for a similar deployable capsule, as well as information about the electronic composition of the plasma sheet and its possible influence on radio communications at the altitudes where GPS black-out could occur. Since the computer tests were carried out at high altitudes, therefore in rarefied flow fields, use of Direct Simulation Monte Carlo codes was mandatory. The computations involved both global aerodynamic quantities (drag and longitudinal moment coefficients) and local aerodynamic quantities (heat flux and pressure distributions along the capsule surface). The results verified that the capsule at high altitude (150 km) is self-stabilizing; it is stable around the nominal attitude or at zero angle of attack and unstable around the reverse attitude or at 180° angle of attack. The analysis also pointed out the presence of extra statically stable equilibrium trim points.

  3. Adaptation of mammalian auditory hair cell mechanotransduction is independent of calcium entry.

    PubMed

    Peng, Anthony W; Effertz, Thomas; Ricci, Anthony J

    2013-11-20

    Adaptation is a hallmark of hair cell mechanotransduction, extending the sensory hair bundle dynamic range while providing mechanical filtering of incoming sound. In hair cells responsive to low frequencies, two distinct adaptation mechanisms exist, a fast component of debatable origin and a slow myosin-based component. It is generally believed that Ca(2+) entry through mechano-electric transducer channels is required for both forms of adaptation. This study investigates the calcium dependence of adaptation in the mammalian auditory system. Recordings from rat cochlear hair cells demonstrate that altering Ca(2+) entry or internal Ca(2+) buffering has little effect on either adaptation kinetics or steady-state adaptation responses. Two additional findings include a voltage-dependent process and an extracellular Ca(2+) binding site, both modulating the resting open probability independent of adaptation. These data suggest that slow motor adaptation is negligible in mammalian auditory cells and that the remaining adaptation process is independent of calcium entry.

  4. RITD - Adapting Mars Entry, Descent and Landing System for Earth

    NASA Astrophysics Data System (ADS)

    Heilimo, Jyri; Aleksashkin, Sergey; Martynov, Maxim; Schmidt, Walter; Harri, Ari-Matti; Vsevolod Koryanov, D.; Kazakovtcev, Victor; Haukka, Harri; Arruego, Ignacio; Finchenko, Valery; Ostresko, Boris; Ponomarenko, Andrei; Martin, Susanna; Siili, Tero

    Abstract A new generation of inflatable Entry, Descent and Landing System (EDLS) or Mars has been developed. It is used in both the initial atmospheric entry and atmospheric descent before the semi-hard impact of the penetrator into Martian surface. The EDLS applicability to Earth’s atmosphere is studied by the EU/RITD [1] project. Project focuses to the analysis and tests of the transonic behaviour of this compact and light weight payload entry system at the Earth re-entry 1. EDLS for Earth The dynamical stability of the craft is analysed, concentrating on the most critical part of the atmospheric re-entry, the transonic phase. In Martian atmosphere the MetNet vehicle stability during the transonic phase is understood. However, in the more dense Earth’s atmosphere, the transonic phase is shorter and turbulence more violent. Therefore, the EDLS has to be sufficiently dynamically stable to overcome the forces tending to deflect the craft from its nominal trajectory and attitude. The preliminary design of the inflatable EDLS for Earth will be commenced once the scaling of the re-entry system and the dynamical stability analysis have been performed. The RITD-project concentrates on mission and applications achievable with the current MetNet-type (i.e. “Mini-1” category) of lander, and on requirements posed by other type Earth re-entry concepts. 2. Entry Angle Determination for Mini-1 - lander For successful Earth landing, the suitable re-entry angle and velocity with specific descent vehicle (DV) mass and heat flux parameters need to be determined. These key parameters in determining the Earth re-entry for DV are: - qmax (kW/m2): maximal specific heat flux, - Q (MJ/m2): specific integral heat flux to DV front shield, - m (kg): descent vehicle (DV) mass, - V (m/s): re-entry velocity and - theta(deg.): flight-path angle at Earth re-entry For Earth re-entry, the calculation results in the optimal value of entry velocity for MetNet (“Mini-1” category) -type

  5. RITD - Adapting Mars Entry, Descent and Landing System for Earth

    NASA Astrophysics Data System (ADS)

    Heilimo, Jyri; Harri, Ari-Matti; Aleksashkin, Sergey; Koryanov, Vsevolod; Arruego, Ignacio; Schmidt, Walter; Haukka, Harri; Finchenko, Valery; Martynov, Maxim; Ostresko, Boris; Ponomarenko, Andrey; Kazakovtsev, Viktor; Martin, Susanna; Siili, Tero

    2014-05-01

    A new generation of inflatable Entry, Descent and Landing System (EDLS) for Mars has been developed. It is used in both the initial atmospheric entry and atmospheric descent before the semi-hard impact of the penetrator into Martian surface. The EDLS applicability to Earth's atmosphere is studied by the EU/RITD [1] project. Project focuses to the analysis and tests of the transonic behaviour of this compact and light weight payload entry system at the Earth re-entry. 1. EDLS for Earth The dynamical stability of the craft is analysed, concentrating on the most critical part of the atmospheric re-entry, the transonic phase. In Martian atmosphere the MetNet vehicle stability during the transonic phase is understood. However, in the more dense Earth's atmosphere, the transonic phase is shorter and turbulence more violent. Therefore, the EDLS has to be sufficiently dynamically stable to overcome the forces tending to deflect the craft from its nominal trajectory and attitude. The preliminary design of the inflatable EDLS for Earth will be commenced once the scaling of the re-entry system and the dynamical stability analysis have been performed. The RITD-project concentrates on mission and applications achievable with the current MetNet-type (i.e. 'Mini-1' category) of lander, and on requirements posed by other type Earth re-entry concepts. 2. Entry Angle Determination for Mini-1 - lander For successful Earth landing, the suitable re-entry angle and velocity with specific descent vehicle (DV) mass and heat flux parameters need to be determined. These key parameters in determining the Earth re-entry for DV are: qmax (kW/m2): maximal specific heat flux, Q (MJ/m2): specific integral heat flux to DV front shield, m (kg): descent vehicle (DV) mass, V (m/s): re-entry velocity and Θ (deg.): flight-path angle at Earth re-entry For Earth re-entry, the calculation results in the optimal value of entry velocity for MetNet ('Mini-1' category) -type lander, with mass of 22kg, being

  6. Deploying the testbed for the VLT adaptive optics facility: ASSIST

    NASA Astrophysics Data System (ADS)

    Stuik, Remko; La Penna, Paolo; Dupuy, Christophe; de Haan, Menno; Arsenault, Robin; Boland, Wilfried; Elswijk, Eddy; ter Horst, Rik; Hubin, Norbert; Madec, Pierre-Yves; Molster, Frank; Wiegers, Emiel

    2012-07-01

    The ESO Very Large Telescope Adaptive Optics Facility (VLT-AOF) will transform the VLT Unit Telescope 4 to an Adaptive Telescope. In absence of an intermediate focus before the Adaptive Secondary in this Ritchey-Chrétien type telescope and in order to reduce the testing and calibration of the system on-sky, ASSIST, The Adaptive Secondary Setup and Instrument STimulator, was developed. It provides an off-sky testing facility for the ESO AOF and will provide a full testing environment for three elements of the VLT Adaptive Optics Facility: the Deformable Secondary Mirror (DSM) and the AO modules for MUSE and HAWK-I (GALACSI and GRAAL). ASSIST was delivered to ESO Garching, where it was assembled and tested. Currently ASSIST is being integrated with the Deformable Secondary Mirror, the first step in the full system testing of the two AO systems for the VLT AOF on ASSIST. This paper briefly reviews the design and properties of ASSIST and reports on the first results of ASSIST in stand-alone mode.

  7. 76 FR 60006 - Joint Europe Africa Deployment & Distribution Conference 2011: “Adapting To Challenge and Change”

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-09-28

    ... of the Secretary Joint Europe Africa Deployment & Distribution Conference 2011: ``Adapting To... Joint Europe Africa Deployment and Distribution Conference (JEADDC), featuring a keynote address, panel..., capabilities, initiatives, issues, and concerns in Africa and Europe. The keynote speaker will be...

  8. Adaptive sliding mode control of tethered satellite deployment with input limitation

    NASA Astrophysics Data System (ADS)

    Ma, Zhiqiang; Sun, Guanghui

    2016-10-01

    This paper proposes a novel adaptive sliding mode tension control method for the deployment of tethered satellite, where the input tension limitation is taken into account. The underactuated governing equations of the tethered satellites system are firstly derived based on Lagrangian mechanics theory. Considering the fact that the tether can only resist axial stretching, the tension input is modelled as input limitation. New adaptive sliding mode laws are addressed to guarantee the stability of the tethered satellite deployment with input disturbance, meanwhile to eliminate the effect of the limitation features of the tension input. Compared with the classic control strategy, the newly proposed adaptive sliding mode control law can deploy the satellite with smaller overshoot of the in-plane angle and implement the tension control reasonably and effectively in engineering practice. The numerical results validate the effectiveness of the proposed methods.

  9. In vivo deployment of mechanically adaptive nanocomposites for intracortical microelectrodes

    PubMed Central

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

    2012-01-01

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

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

    PubMed

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

    2014-02-01

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

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

    PubMed Central

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

    2014-01-01

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

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

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

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

  13. Wide field of view adaptive optical system for lightweight deployable telescope technologies

    NASA Astrophysics Data System (ADS)

    McComas, Brian K.; Cermak, Michael A.; Friedman, Edward J.

    2003-02-01

    A NASA research contract (NAS1-00116) was awarded to Ball Aerospace & Technologies Corp. in January 2000 to study wide field-of-view adaptive optical systems. These systems will be required on future high resolution Earth remote sensing systems that employ large, flexible, lightweight, deployed primary mirrors. The deformations from these primary mirrors will introduce aberrations into the optical system, which must be removed by corrective optics. For economic reasons, these remote sensing systems must have a large field-of-view (a few degrees). Unlike ground-based adaptive optical systems, which have a negligible field-of-view, the adaptive optics on these space-based remote sensing systems will be required to correct for the deformations in the primary mirror over the entire field-of-view. A new error function, which is an enhancement to conventional adaptive optics, for wide field-of-view optical systems will be introduced. This paper will present the goals of the NASA research project and its progress. The initial phase of this research project is a demonstration of the wide field-of-view adaptive optics theory. A breadboard has been designed and built for this purpose. The design and assembly of the breadboard will be presented, along with the final results for this phase of the research project. Finally, this paper will show the applicability of wide field-of-view adaptive optics to space-based astronomical systems.

  14. Calcium entry into stereocilia drives adaptation of the mechanoelectrical transducer current of mammalian cochlear hair cells.

    PubMed

    Corns, Laura F; Johnson, Stuart L; Kros, Corné J; Marcotti, Walter

    2014-10-14

    Mechanotransduction in the auditory and vestibular systems depends on mechanosensitive ion channels in the stereociliary bundles that project from the apical surface of the sensory hair cells. In lower vertebrates, when the mechanoelectrical transducer (MET) channels are opened by movement of the bundle in the excitatory direction, Ca(2+) entry through the open MET channels causes adaptation, rapidly reducing their open probability and resetting their operating range. It remains uncertain whether such Ca(2+)-dependent adaptation is also present in mammalian hair cells. Hair bundles of both outer and inner hair cells from mice were deflected by using sinewave or step mechanical stimuli applied using a piezo-driven fluid jet. We found that when cochlear hair cells were depolarized near the Ca(2+) reversal potential or their hair bundles were exposed to the in vivo endolymphatic Ca(2+) concentration (40 µM), all manifestations of adaptation, including the rapid decline of the MET current and the reduction of the available resting MET current, were abolished. MET channel adaptation was also reduced or removed when the intracellular Ca(2+) buffer 1,2-Bis(2-aminophenoxy)ethane-N,N,N',N'-tetraacetic acid (BAPTA) was increased from a concentration of 0.1 to 10 mM. The findings show that MET current adaptation in mouse auditory hair cells is modulated similarly by extracellular Ca(2+), intracellular Ca(2+) buffering, and membrane potential, by their common effect on intracellular free Ca(2+).

  15. World-wide deployment of Robo-AO visible-light robotic laser adaptive optics systems

    NASA Astrophysics Data System (ADS)

    Baranec, Christoph; Riddle, Reed; Law, Nicholas Michael; Lu, Jessica R.; Tonry, John; Tully, R. Brent; Wright, Shelley; Kulkarni, Shrinivas; Severson, Scott; Choi, Philip; Ramaprakash, A.; Chun, Mark; Connelley, Mike; Tokunaga, Alan; Hall, Donald

    2015-08-01

    In the next few years, several modest-sized telescopes around the world will be upgraded with autonomous laser adaptive optics systems based on the Robo-AO prototype deployed at the Palomar Observatory 1.5-m telescope. The prototype commenced scientific operations in June 2012 and more than 19,000 observations have since been performed at the ~0.12" visible-light diffraction limit. We are planning to move the prototype system to the 2.1-m telescope at Kitt Peak for a 3-year deployment which will serve a consortium of users including Caltech, the University of Hawai`i, IUCAA, NCU and institutions in China. Additionally, 2 months per year will be made available to the US astronomical community.New Robo-AO systems are in various stages of development: a clone by IUCAA for the 2-m IGO telescope in India; a natural guide star variant, KAPAO, by Pomona College at the 1-m Table Mountain telescope in California; and second generation Robo-AO systems are planned for the 3-m IRTF and 2.2-m University of Hawai'i telescopes on Maunakea, Hawai`i. The latter will exploit Maunakea's excellent observing conditions to provide higher Strehl ratios, sharper imaging, ~0.07", and correction to lambda = 400 nm. An additional infrared integral-field spectrograph will be fed by the UH 2.2-m Robo-AO system to quickly classify transients, such as supernovae and asteroids, discovered by the ATLAS system in Hawai`i.

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

    NASA Technical Reports Server (NTRS)

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

    2015-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Spratlin, Kenneth Milton

    1987-01-01

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

  18. Experimental Adaptation of Wild-Type Canine Distemper Virus (CDV) to the Human Entry Receptor CD150

    PubMed Central

    Bieringer, Maria; Han, Jung Woo; Kendl, Sabine; Khosravi, Mojtaba; Plattet, Philippe; Schneider-Schaulies, Jürgen

    2013-01-01

    Canine distemper virus (CDV), a close relative of measles virus (MV), is widespread and well known for its broad host range. When the goal of measles eradication may be achieved, and when measles vaccination will be stopped, CDV might eventually cross the species barrier to humans and emerge as a new human pathogen. In order to get an impression how fast such alterations may occur, we characterized required adaptive mutations to the human entry receptors CD150 (SLAM) and nectin-4 as first step to infect human target cells. Recombinant wild-type CDV-A75/17red adapted quickly to growth in human H358 epithelial cells expressing human nectin-4. Sequencing of the viral attachment proteins (hemagglutinin, H, and fusion protein, F) genes revealed that no adaptive alteration was required to utilize human nectin-4. In contrast, the virus replicated only to low titres (102 pfu/ml) in Vero cells expressing human CD150 (Vero-hSLAM). After three passages using these cells virus was adapted to human CD150 and replicated to high titres (105 pfu/ml). Sequence analyses revealed that only one amino acid exchange in the H-protein at position 540 Asp→Gly (D540G) was required for functional adaptation to human CD150. Structural modelling suggests that the adaptive mutation D540G in H reflects the sequence alteration from canine to human CD150 at position 70 and 71 from Pro to Leu (P70L) and Gly to Glu (G71E), and compensates for the gain of a negative charge in the human CD150 molecule. Using this model system our data indicate that only a minimal alteration, in this case one adaptive mutation, is required for adaptation of CDV to the human entry receptors, and help to understand the molecular basis why this adaptive mutation occurs. PMID:23554862

  19. Experimental adaptation of wild-type canine distemper virus (CDV) to the human entry receptor CD150.

    PubMed

    Bieringer, Maria; Han, Jung Woo; Kendl, Sabine; Khosravi, Mojtaba; Plattet, Philippe; Schneider-Schaulies, Jürgen

    2013-01-01

    Canine distemper virus (CDV), a close relative of measles virus (MV), is widespread and well known for its broad host range. When the goal of measles eradication may be achieved, and when measles vaccination will be stopped, CDV might eventually cross the species barrier to humans and emerge as a new human pathogen. In order to get an impression how fast such alterations may occur, we characterized required adaptive mutations to the human entry receptors CD150 (SLAM) and nectin-4 as first step to infect human target cells. Recombinant wild-type CDV-A75/17(red) adapted quickly to growth in human H358 epithelial cells expressing human nectin-4. Sequencing of the viral attachment proteins (hemagglutinin, H, and fusion protein, F) genes revealed that no adaptive alteration was required to utilize human nectin-4. In contrast, the virus replicated only to low titres (10(2) pfu/ml) in Vero cells expressing human CD150 (Vero-hSLAM). After three passages using these cells virus was adapted to human CD150 and replicated to high titres (10(5) pfu/ml). Sequence analyses revealed that only one amino acid exchange in the H-protein at position 540 Asp→Gly (D540G) was required for functional adaptation to human CD150. Structural modelling suggests that the adaptive mutation D540G in H reflects the sequence alteration from canine to human CD150 at position 70 and 71 from Pro to Leu (P70L) and Gly to Glu (G71E), and compensates for the gain of a negative charge in the human CD150 molecule. Using this model system our data indicate that only a minimal alteration, in this case one adaptive mutation, is required for adaptation of CDV to the human entry receptors, and help to understand the molecular basis why this adaptive mutation occurs.

  20. Variable effect of a fiber length QTL deployed within several regionally adapted cultivars

    Technology Transfer Automated Retrieval System (TEKTRAN)

    Originally identified from Sealand 883, this QTL had a significant effect on fiber length in the testing population, but varied by as much as 3 to 4 fold depending on the genetic background in which it was deployed. It is the purpose of this project to examine the effect of this QTL in four differen...

  1. Effects of a Military Parenting Program on Parental Distress and Suicidal Ideation: After Deployment Adaptive Parenting Tools.

    PubMed

    Gewirtz, Abigail H; DeGarmo, David S; Zamir, Osnat

    2016-04-01

    Few studies have examined whether parenting prevention programs might mitigate risk for suicidality in parents, yet parent suicidality is a strong risk factor for offspring suicidality. We report results from a randomized controlled trial of a parenting program for deployed National Guard and Reserve families with a school-aged child. Intent-to-treat analyses showed that random assignment to the parenting program (ADAPT) was associated with improved parenting locus of control (LOC). Improved parenting LOC was concurrently associated with strengthened emotion regulation which predicted reductions in psychological distress and suicidal ideation at 12 months postbaseline. Results are discussed in the context of ongoing efforts to reduce suicide rates in military populations.

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

    ERIC Educational Resources Information Center

    Engeswick, Lynnette Marie

    2011-01-01

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

  3. Adaptive Software Architecture Based on Confident HCI for the Deployment of Sensitive Services in Smart Homes

    PubMed Central

    Vega-Barbas, Mario; Pau, Iván; Martín-Ruiz, María Luisa; Seoane, Fernando

    2015-01-01

    Smart spaces foster the development of natural and appropriate forms of human-computer interaction by taking advantage of home customization. The interaction potential of the Smart Home, which is a special type of smart space, is of particular interest in fields in which the acceptance of new technologies is limited and restrictive. The integration of smart home design patterns with sensitive solutions can increase user acceptance. In this paper, we present the main challenges that have been identified in the literature for the successful deployment of sensitive services (e.g., telemedicine and assistive services) in smart spaces and a software architecture that models the functionalities of a Smart Home platform that are required to maintain and support such sensitive services. This architecture emphasizes user interaction as a key concept to facilitate the acceptance of sensitive services by end-users and utilizes activity theory to support its innovative design. The application of activity theory to the architecture eases the handling of novel concepts, such as understanding of the system by patients at home or the affordability of assistive services. Finally, we provide a proof-of-concept implementation of the architecture and compare the results with other architectures from the literature. PMID:25815449

  4. Adaptive software architecture based on confident HCI for the deployment of sensitive services in Smart Homes.

    PubMed

    Vega-Barbas, Mario; Pau, Iván; Martín-Ruiz, María Luisa; Seoane, Fernando

    2015-03-25

    Smart spaces foster the development of natural and appropriate forms of human-computer interaction by taking advantage of home customization. The interaction potential of the Smart Home, which is a special type of smart space, is of particular interest in fields in which the acceptance of new technologies is limited and restrictive. The integration of smart home design patterns with sensitive solutions can increase user acceptance. In this paper, we present the main challenges that have been identified in the literature for the successful deployment of sensitive services (e.g., telemedicine and assistive services) in smart spaces and a software architecture that models the functionalities of a Smart Home platform that are required to maintain and support such sensitive services. This architecture emphasizes user interaction as a key concept to facilitate the acceptance of sensitive services by end-users and utilizes activity theory to support its innovative design. The application of activity theory to the architecture eases the handling of novel concepts, such as understanding of the system by patients at home or the affordability of assistive services. Finally, we provide a proof-of-concept implementation of the architecture and compare the results with other architectures from the literature.

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

    NASA Technical Reports Server (NTRS)

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

    2006-01-01

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

  6. Stardust Entry Reconstruction

    NASA Technical Reports Server (NTRS)

    Desai, Prasun N.; Qualls, Garry D.

    2008-01-01

    An overview of the reconstruction analyses performed for the Stardust capsule entry is described. The results indicate that the actual entry was very close to the pre-entry predictions. The capsule landed 8.1 km north-northwest of the desired target at Utah Test and Training Range. Analyses of infrared video footage and radar range data (obtained from tracking stations) during the descent show that drogue parachute deployment was 4.8 s later than the pre-entry prediction, while main parachute deployment was 19.3 s earlier than the pre-set timer indicating that main deployment was actually triggered by the backup baroswitch. Reconstruction of a best estimated trajectory revealed that the aerodynamic drag experienced by the capsule during hypersonic flight was within 1% of pre-entry predications. Observations of the heatshield support the pre-entry estimates of small hypersonic angles of attack, since there was very little, if any, charring of the shoulder region or the aftbody. Through this investigation, an overall assertion can be made that all the data gathered from the Stardust capsule entry were consistent with flight performance close to nominal pre-entry predictions. Consequently, the design principles and methodologies utilized for the flight dynamics, aerodynamics, and aerothermodynamics analyses have been corroborated.

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

    NASA Astrophysics Data System (ADS)

    Kelley, Owen A.

    2013-02-01

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

  8. 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.

  9. Deployable antenna

    NASA Technical Reports Server (NTRS)

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

    2006-01-01

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

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

    NASA Technical Reports Server (NTRS)

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

    2012-01-01

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

  11. Deployable Soft Composite Structures

    NASA Astrophysics Data System (ADS)

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

    2016-02-01

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

  12. Deployable Soft Composite Structures

    PubMed Central

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

    2016-01-01

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

  13. Deployable Soft Composite Structures.

    PubMed

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

    2016-02-19

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

  14. Mars Science Laboratory Entry Guidance

    NASA Technical Reports Server (NTRS)

    Mendeck, Gavin F.

    2011-01-01

    The Mars Science Laboratory will be the first Mars mission to attempt a guided entry with the objective of safely delivering the entry vehicle to a survivable parachute deploy state within 12.5 km of the pre-designated parachute deploy coordinates. The Entry Terminal Point Controller guidance algorithm is derived from the final phase Apollo Command Module guidance and, like Apollo, modulates the bank angle to control range based on deviations in range, altitude rate, and drag acceleration from a reference trajectory. For application to Mars landers which must make use of the tenuous Martian atmosphere, it is critical to balance the lift of the vehicle to minimize the range while still ensuring a safe deploy altitude. An overview of the process to generate optimized guidance settings is presented, discussing improvements made over the last nine years. Performance tradeoffs between ellipse size and deploy altitude will be presented, along with imposed constraints of entry acceleration and heating. Performance sensitivities to the bank reversal deadbands, heading alignment, attitude initialization error, and entry delivery errors are presented.

  15. Deployment Health

    DTIC Science & Technology

    2006-08-11

    memorandum, “Improved Occupational and Environmental Health Surveillance Reporting and Archiving” (Reference (e)); and assigns responsibilities for...Injury (DI) to control or reduce Occupational and Environmental Health (OEH) risks; to document and link OEH exposures with deployed personnel, including...infectious disease threats, environmental health risks, toxic industrial chemical threats, and developments in biotechnology and biomedical subjects

  16. MSL EDL Entry Guidance using the Entry Terminal Point Controller

    NASA Technical Reports Server (NTRS)

    2006-01-01

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

  17. Modulated Entry

    NASA Technical Reports Server (NTRS)

    Grant, Frederick C.

    1960-01-01

    The technique of modulation, or variable coefficients, is discussed and the analytical formulation is reviewed. Representative numerical results of the use of modulation are shown for the lifting and nonlifting cases. These results include the effects of modulation on peak acceleration, entry corridor, and heat absorption. Results are given for entry at satellite speed and escape speed. The indications are that coefficient modulation on a vehicle with good lifting capability offers the possibility of sizable loading reductions or, alternatively, wider corridors; thus, steep entries become practical from the loading standpoint. The amount of steepness depends on the acceptable heating penalty. The price of sizable fractions of the possible gains does not appear to be excessive.

  18. 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.

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

    NASA Technical Reports Server (NTRS)

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

    2013-01-01

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

  20. Development, Deployment, and Cost Effectiveness of a Self-Administered Stereo Non Mydriatic Automated Retinal Camera (SNARC) Containing Automated Retinal Lesion (ARL) Detection Using Adaptive Optics

    DTIC Science & Technology

    2010-10-01

    diabetes and healthy eating habits . REQ ID REQUIREMENT NAME DESCRIPTION VERS NEW VERS UPD. HealthyEating_1 Nutrition Data Entry By Category...user to track the time they ate a meal/ snack . 1.0 1.0 HealthyEating_3 Daily Nutrition Feedback Provides user feedback on their progress towards

  1. Deployable Crew Quarters

    NASA Technical Reports Server (NTRS)

    Izenson, Michael G.; Chen, Weibo

    2008-01-01

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

  2. Aerocapture Inflatable Decelerator for Planetary Entry

    NASA Technical Reports Server (NTRS)

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

    2007-01-01

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

  3. Award 1 Title: Acoustic Communications 2011 Experiment: Deployment Support and Post Experiment Data Handling and Analysis. Award 2 Title: Exploiting Structured Dependencies in the Design of Adaptive Algorithms for Underwater Communication Award. 3 Title: Coupled Research in Ocean Acoustics and Signal Processing for the Next Generation of Underwater Acoustic Communication Systems

    DTIC Science & Technology

    2015-09-30

    Exploiting Structured Dependencies in the Design of Adaptive Algorithms for Underwater Communication Award #3 Title Coupled Research in Ocean Acoustics...depend on the physical oceanography and pushing the state of the art in our understanding of adaptive signal processing algorithms relevant to...deployable VHF acoustic data transmission and acquisition system. 3. Develop signal models and processing algorithms that reduce to the extent

  4. MSL Entry, Descent and Landing Performance and Environments

    NASA Technical Reports Server (NTRS)

    Lockwood, Mary Kae; Dwyer-Cianciola, Alicia; Dyakonov, Artem; Edquist, Karl; Powell, Dick; Striepe, Scott; Way, David; Graves, Claude; Carman, Gil; Sostaric, Ron

    2005-01-01

    A viewgraph presentation on the MARS Science Laboratory (MSL) Entry, Descent and Landing (EDL) performance and environments is shown. The topics include: 1) High Altitude and Precision Landing; 2) Guided, Lifting, Ballistic Trade; 3) Supersonic Chute Deploy Altitude; 4) Guided, Lifting, Ballistic Landing Footprint Video; 5) Transition Indicator at Peak Heating Point on Trajectory; 6) Aeroheating at Peak Heating Point on Trajectory Nominal, No Uncertainty Included; 7) Comparison to Previous Missions; 8) Pork Chop Plots - EDL Performance for Mission Design; 9) Max Heat Rate Est (CBE+Uncert) W/cm2; 10) Nominal Super Chute Deploy Alt Above MOLA (km); 11) Monte Carlo; 12) MSL Option M2 Entry, Descent and Landing; 13) Entry Performance; 14) Entry Aeroheating and Entry g's; 15) Terminal Descent; and 16) How An Ideal Chute Deployment Altitude Varies with Time of Year and Latitude (JSC Chart).

  5. Adaptation.

    PubMed

    Broom, Donald M

    2006-01-01

    The term adaptation is used in biology in three different ways. It may refer to changes which occur at the cell and organ level, or at the individual level, or at the level of gene action and evolutionary processes. Adaptation by cells, especially nerve cells helps in: communication within the body, the distinguishing of stimuli, the avoidance of overload and the conservation of energy. The time course and complexity of these mechanisms varies. Adaptive characters of organisms, including adaptive behaviours, increase fitness so this adaptation is evolutionary. The major part of this paper concerns adaptation by individuals and its relationships to welfare. In complex animals, feed forward control is widely used. Individuals predict problems and adapt by acting before the environmental effect is substantial. Much of adaptation involves brain control and animals have a set of needs, located in the brain and acting largely via motivational mechanisms, to regulate life. Needs may be for resources but are also for actions and stimuli which are part of the mechanism which has evolved to obtain the resources. Hence pigs do not just need food but need to be able to carry out actions like rooting in earth or manipulating materials which are part of foraging behaviour. The welfare of an individual is its state as regards its attempts to cope with its environment. This state includes various adaptive mechanisms including feelings and those which cope with disease. The part of welfare which is concerned with coping with pathology is health. Disease, which implies some significant effect of pathology, always results in poor welfare. Welfare varies over a range from very good, when adaptation is effective and there are feelings of pleasure or contentment, to very poor. A key point concerning the concept of individual adaptation in relation to welfare is that welfare may be good or poor while adaptation is occurring. Some adaptation is very easy and energetically cheap and

  6. 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.

  7. Deployable Pipe-Z

    NASA Astrophysics Data System (ADS)

    Zawidzki, Machi

    2016-10-01

    This paper presents a concept of deployable Pipe-Z (dPZ): a modular structural system which takes advantage of the robustness of rigid-panel mechanism and allows to create free-form links which are also reconfigurable and deployable. The concept presented can be applied for building habitats and infrastructures for human exploration of oceans and outer space. dPZ structures can adapt to changing requirements e.g. mission objectives, crew condition and technological developments. Furthermore, such lightweight and adaptable structural concept can assist in sustainable exploration development. After brief introduction, the concept of Pipe-Z (PZ) is presented. Next, the reconfigurability of PZ is explained and illustrated with continuous and collision-free transition from a PZ forming a Trefoil knot to a Figure-eight knot. The following sections introduce, explain and illustrate the folding mechanism of a single foldable Pipe-Z module (fPZM) and entire dPZ structure. The latter is illustrated with asynchronous (delayed) unfolding of a relatively complex Unknot. Several applications of PZ are suggested, namely for underwater and deep-space and surface habitats, for permanent, but in particular, temporary or emergency passages. As an example, a scenario of a failure of one of the modules of the International Space Station is presented where a rigid structure of 40 fPZMs bypasses the "dead link". A low-fidelity prototype of a 6-module octagonal dPZ is presented; several folding schemes including concentric toric rings are demonstrated. Practical issues of pressurization and packing are briefly discussed.

  8. Adapt

    NASA Astrophysics Data System (ADS)

    Bargatze, L. F.

    2015-12-01

    Active Data Archive Product Tracking (ADAPT) is a collection of software routines that permits one to generate XML metadata files to describe and register data products in support of the NASA Heliophysics Virtual Observatory VxO effort. ADAPT is also a philosophy. The ADAPT concept is to use any and all available metadata associated with scientific data to produce XML metadata descriptions in a consistent, uniform, and organized fashion to provide blanket access to the full complement of data stored on a targeted data server. In this poster, we present an application of ADAPT to describe all of the data products that are stored by using the Common Data File (CDF) format served out by the CDAWEB and SPDF data servers hosted at the NASA Goddard Space Flight Center. These data servers are the primary repositories for NASA Heliophysics data. For this purpose, the ADAPT routines have been used to generate data resource descriptions by using an XML schema named Space Physics Archive, Search, and Extract (SPASE). SPASE is the designated standard for documenting Heliophysics data products, as adopted by the Heliophysics Data and Model Consortium. The set of SPASE XML resource descriptions produced by ADAPT includes high-level descriptions of numerical data products, display data products, or catalogs and also includes low-level "Granule" descriptions. A SPASE Granule is effectively a universal access metadata resource; a Granule associates an individual data file (e.g. a CDF file) with a "parent" high-level data resource description, assigns a resource identifier to the file, and lists the corresponding assess URL(s). The CDAWEB and SPDF file systems were queried to provide the input required by the ADAPT software to create an initial set of SPASE metadata resource descriptions. Then, the CDAWEB and SPDF data repositories were queried subsequently on a nightly basis and the CDF file lists were checked for any changes such as the occurrence of new, modified, or deleted

  9. Deployable Temporary Shelter

    NASA Technical Reports Server (NTRS)

    Shaffer, Joe R.; Headley, David E.

    1993-01-01

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

  10. Synchronously Deployable Truss Structures

    NASA Technical Reports Server (NTRS)

    Rhodes, M. D.; Hedgepeth, J. M.

    1986-01-01

    Structure lightweight, readily deployed, and has reliable joints. New truss concept, designated as "pac truss," developed. Features easy deployment without need for complex mechanisms. Structures of this type deployed in free flight by controlled release of stored energy in torsional springs at selected hinges located throughout structure. Double-folding technique used in beam model applicable to flat planar trusses, allowing structures of large expanse to fold into compact packages and be deployed for space-platform applications.

  11. Solar array deployment mechanism

    NASA Technical Reports Server (NTRS)

    Calassa, Mark C.; Kackley, Russell

    1995-01-01

    This paper describes a Solar Array Deployment Mechanism (SADM) used to deploy a rigid solar array panel on a commercial spacecraft. The application required a deployment mechanism design that was not only lightweight, but also could be produced and installed at the lowest possible cost. This paper covers design, test, and analysis of a mechanism that meets these requirements.

  12. Deployer: A Robot-Deploying Robot

    DTIC Science & Technology

    2003-04-01

    6: Bandicoot 11 Figure 7: Deployer mast in a.) retracted, b.) extending, and c.) fully extended positions. 13 Figure 8: Wombat climbing stairs with...mast in a.) retracted, b.)extending, and c.) fully extended positions. 13 Deploy er Outfitting - Wombat The second Urban Robot, Wombat (Fig.8), was...equipped with a single, rear-mounted ISIS transceiver and a Swarm Radio to communicate with all of the Joeys. In addition, Wombat was equipped with

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

    NASA Technical Reports Server (NTRS)

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

    2010-01-01

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

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

    NASA Technical Reports Server (NTRS)

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

    2010-01-01

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

  15. Analytical theories for spacecraft entry into planetary atmospheres and design of planetary probes

    NASA Astrophysics Data System (ADS)

    Saikia, Sarag J.

    flight path angles. The analytical theory is very accurate for moderate to large entry angles and for any entry speed. A new analytical theory is developed for ballistic entry at circular speed for zero initial flight path angle and for ballistic entry at circular speed for very small to large initial flight path angles. Two separate solutions for zero and non-zero initial flight path angles are needed to avoid a singularity. The classical Yaroshevskii's solution enters as the zero-order term in the solutions. Using the new solutions, other important expressions are developed such as time-of-flight, range, deceleration, and aerodynamic heating parameters (e.g. average heat input, stagnation-point heat rate, and total stagnation-point heat load). Large-scale human exploration of Mars and in situ exploration of Venus pose great challenges for entry, descent, and landing of spacecraft. The Adaptive Deployable Entry and Placement Technology (ADEPT), a mechanically deployable decelerator, presents an enabling alternative to the traditional rigid aeroshell technology. ADEPT helps in lowering the ballistic coefficient of an entry vehicle and also presents attractive options for lifting and guided entry. Optimal trajectory solutions which minimize peak deceleration and peak heat-flux are computed for four different control strategies. The deployable decelerator for human Mars missions (requiring a landed mass of 40 mt) presents an acceptable entry environment---peak heat-flux of < 80 W/cm2, and peak deceleration of less than 4 G (compared to 200 W/cm2 and 15 G for Mars Science Laboratory respectively). For lifting and guided entry for Venus in situ missions, ADEPT could lead to a two-order-of-magnitude decrease in peak deceleration and to a 50% decrease in peak heat-flux compared to conventional rigid aeroshell technology. There exist a number of attractive trajectory candidates for round-trip human missions to Mars and Venus. However, the speeds the spacecraft will encounter

  16. Technology for Entry Probes

    NASA Technical Reports Server (NTRS)

    Cutts, James A.; Arnold, James; Venkatapathy, Ethiraj; Kolawa, Elizabeth; Munk, Michelle; Wercinski, Paul; Laub, Bernard

    2005-01-01

    A viewgraph describing technologies for entry probes is presented. The topics include: 1) Entry Phase; 2) Descent Phase; 3) Long duration atmospheric observations; 4) Survivability at high temperatures; and 5) Summary.

  17. Large Deployable Shroud

    NASA Technical Reports Server (NTRS)

    Jacquemin, G. G.

    1987-01-01

    Preliminary design proposed for large, lightweight telescope shroud or light shield carried to orbit in single Space Shuttle cargo load. Shroud concept applied on Earth in portable, compactly storable displays or projection screens. Large telescope shroud includes four deployable masts erecting eight walls of hinged panels of polyimide film. Panels stored fanfolded before deployment and threaded on guide wires unwinding from spools and remain taut during deployment.

  18. Deployable geodesic truss structure

    NASA Technical Reports Server (NTRS)

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

    1987-01-01

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

  19. Disposable telemetry cable deployment system

    DOEpatents

    Holcomb, David Joseph

    2000-01-01

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

  20. Orion Capsule Handling Qualities for Atmospheric Entry

    NASA Technical Reports Server (NTRS)

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

    2011-01-01

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

  1. Trajectory Reconstruction for the Genesis Entry

    NASA Technical Reports Server (NTRS)

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

    2005-01-01

    An overview of the reconstruction analyses performed for the Genesis capsule entry is described. The results indicate that the actual entry prior to the drogue deployment failure was very close to the pre-entry predictions. The capsule landed 8.3 km south of the desired target at Utah Test and Training Range. Analysis on infrared video footage (obtained from the tracking stations) during the descent estimated the onset of the capsule tumble at Mach 0.9. Frequency analysis on the infrared video data indicates that the aerodynamics generated for the Genesis capsule reasonably predicted the drag and static stability. Observations of the heatshield support the pre-entry simulation estimates of a small hypersonic angles-of-attack, since there is very little, if any, charring of the shoulder region or the afterbody. Through this investigation, an overall assertion can be made that all the data gathered from the Genesis entry is consistent with flight performance close to the nominal pre-entry prediction. Consequently, the design principles and methodologies utilized for the flight dynamics, aerodynamics, and aerothermodynamics analyses have been corroborated.

  2. Modeling EERE Deployment Programs

    SciTech Connect

    Cort, K. A.; Hostick, D. J.; Belzer, D. B.; Livingston, O. V.

    2007-11-01

    This report compiles information and conclusions gathered as part of the “Modeling EERE Deployment Programs” project. The purpose of the project was to identify and characterize the modeling of deployment programs within the EERE Technology Development (TD) programs, address possible improvements to the modeling process, and note gaps in knowledge in which future research is needed.

  3. Deployable Aeroshell Flexible Thermal Protection System Testing

    NASA Technical Reports Server (NTRS)

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

    2009-01-01

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

  4. Clinical data entry.

    PubMed Central

    van Mulligen, E. M.; Stam, H.; van Ginneken, A. M.

    1998-01-01

    Routine capture of patient data for a computer-based patient record system remains a subject of study. Time constraints that require fast data entry and maximal expression power are in favor of free text data entry. However, using patient data directly for decision support systems, for quality assessment, etc. requires structured data entry, which appears to be more tedious and time consuming. In this paper, a prototype clinical data entry application is described that combines free text and structured data entry in one single application and allows clinicians to smoothly switch between these two different input styles. A knowledge base involving a semantic network of clinical data entry terms and their properties and relationships is used by this application to support structured data entry. From structured data, sentences are generated and shown in a text processor together with the free text. This presentation metaphor allows for easy integrated presentation of structured data and free text. Images Figure 1 Figure 2 PMID:9929186

  5. 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.

  6. 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.

  7. From Deploying Individuals to Deploying Departments

    DTIC Science & Technology

    2010-06-01

    the help of regulators, lawyers, customs of!cials, and private sector and regional market experts to develop comprehensive and effective solutions...the management of deploying and rede - ploying personnel across the government. Continuous Education, Training, and Exercising. Classroom education...domestic agencies must con- duct periodic exercises in order to socialize new participants and to re!ne existing processes and policies in the forward and

  8. Modeling EERE deployment programs

    SciTech Connect

    Cort, K. A.; Hostick, D. J.; Belzer, D. B.; Livingston, O. V.

    2007-11-01

    The purpose of the project was to identify and characterize the modeling of deployment programs within the EERE Technology Development (TD) programs, address possible improvements to the modeling process, and note gaps in knowledge for future research.

  9. Deployment and Children

    MedlinePlus

    ... Nutrition Fitness Sports Oral Health Emotional Wellness Building Resilience Sleep Growing Healthy Healthy Children > Healthy Living > Emotional Wellness > Building Resilience > Deployment and Children Healthy Living Listen Español Text ...

  10. Glory Solar Array Deployment

    NASA Video Gallery

    The Glory spacecraft uses Orbital Sciences Corporation Space Systems Group's LEOStar-1 bus design, with deployable, four-panel solar arrays. This conceptual animation reveals Glory's unique solar a...

  11. Entry at Venus

    NASA Technical Reports Server (NTRS)

    Venkatapathy, Ethiraj; Smith, Brandon

    2016-01-01

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

  12. Umbilical Deployment Device

    NASA Technical Reports Server (NTRS)

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

    2011-01-01

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

  13. Synchronously deployable truss structure

    NASA Technical Reports Server (NTRS)

    Bush, H. G. (Inventor); Mikulas, M., Jr. (Inventor); Wallsom, E. (Inventor)

    1986-01-01

    A collapsible-expandable truss structure, including first and second spaced surface truss layers having an attached core layer is described. The surface truss layers are composed of a plurality of linear struts arranged in multiple triangular configurations. Each linear strut is hinged at the center and hinge connected at each end to a nodular joint. A passive spring serves as the expansion force to move the folded struts from a stowed collapsed position to a deployed operative final truss configuration. A damper controls the rate of spring expansion for the synchronized deployment of the truss as the folded configuration is released for deployment by the restrain belts. The truss is synchronously extended under the control of motor driven spools.

  14. Mining Deployment Optimization

    NASA Astrophysics Data System (ADS)

    Čech, Jozef

    2016-09-01

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

  15. Entry, Descent, and Landing Performance of the Mars Phoenix Lander

    NASA Technical Reports Server (NTRS)

    Desai, Prasun N.; Prince, Jill L.; Wueen, Eric M.; Cruz, Juan R.; Grover, Myron R.

    2008-01-01

    On May 25, 2008, the Mars Phoenix Lander successfully landed on the northern arctic plains of Mars. An overview of a preliminary reconstruction analysis performed on each entry, descent, and landing phase to assess the performance of Phoenix as it descended is presented and a comparison to pre-entry predictions is provided. The landing occurred 21 km further downrange than the predicted landing location. Analysis of the flight data revealed that the primary cause of Phoenix s downrange landing was a higher trim total angle of attack during the hypersonic phase of the entry, which resulted in Phoenix flying a slightly lifting trajectory. The cause of this higher trim attitude is not known at this time. Parachute deployment was 6.4 s later than prediction. This later deployment time was within the variations expected and is consistent with a lifting trajectory. The parachute deployment and inflation process occurred as expected with no anomalies identified. The subsequent parachute descent and powered terminal landing also behaved as expected. A preliminary reconstruction of the landing day atmospheric density profile was found to be lower than the best apriori prediction, ranging from a few percent less to a maximum of 8%. A comparison of the flight reconstructed trajectory parameters shows that the actual Phoenix entry, descent, and landing was close to pre-entry predictions. This reconstruction investigation is currently ongoing and the results to date are in the process of being refined.

  16. Modeling EERE Deployment Programs

    SciTech Connect

    Cort, Katherine A.; Hostick, Donna J.; Belzer, David B.; Livingston, Olga V.

    2007-11-08

    The purpose of this report is to compile information and conclusions gathered as part of three separate tasks undertaken as part of the overall project, “Modeling EERE Deployment Programs,” sponsored by the Planning, Analysis, and Evaluation office within the Department of Energy’s Office of Energy Efficiency and Renewable Energy (EERE). The purpose of the project was to identify and characterize the modeling of deployment programs within the EERE Technology Development (TD) programs, address improvements to modeling in the near term, and note gaps in knowledge where future research is needed.

  17. Remote Systems Design & Deployment

    SciTech Connect

    Bailey, Sharon A.; Baker, Carl P.; Valdez, Patrick LJ

    2009-08-28

    The Pacific Northwest National Laboratory (PNNL) was tasked by Washington River Protection Solutions, LLC (WRPS) to provide information and lessons learned relating to the design, development and deployment of remote systems, particularly remote arm/manipulator systems. This report reflects PNNL’s experience with remote systems and lays out the most important activities that need to be completed to successfully design, build, deploy and operate remote systems in radioactive and chemically contaminated environments. It also contains lessons learned from PNNL’s work experiences, and the work of others in the national laboratory complex.

  18. 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.

  19. Technology development for deployable aerodynamic decelerators at Mars

    NASA Astrophysics Data System (ADS)

    Masciarelli, James P.

    2002-01-01

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

  20. Large, Easily Deployable Structures

    NASA Technical Reports Server (NTRS)

    Agan, W. E.

    1983-01-01

    Study of concepts for large space structures will interest those designing scaffolding, radio towers, rescue equipment, and prefabricated shelters. Double-fold, double-cell module was selected for further design and for zero gravity testing. Concept is viable for deployment by humans outside space vehicle as well as by remotely operated manipulator.

  1. Parametric Cost Deployment

    NASA Technical Reports Server (NTRS)

    Dean, Edwin B.

    1995-01-01

    Parametric cost analysis is a mathematical approach to estimating cost. Parametric cost analysis uses non-cost parameters, such as quality characteristics, to estimate the cost to bring forth, sustain, and retire a product. This paper reviews parametric cost analysis and shows how it can be used within the cost deployment process.

  2. Deployable video conference table

    NASA Technical Reports Server (NTRS)

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

    1993-01-01

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

  3. Fusion Power Deployment

    SciTech Connect

    J.A. Schmidt; J.M. Ogden

    2002-02-06

    Fusion power plants could be part of a future portfolio of non-carbon dioxide producing energy supplies such as wind, solar, biomass, advanced fission power, and fossil energy with carbon dioxide sequestration. In this paper, we discuss key issues that could impact fusion energy deployment during the last half of this century. These include geographic issues such as resource availability, scale issues, energy storage requirements, and waste issues. The resource needs and waste production associated with fusion deployment in the U.S. should not pose serious problems. One important feature of fusion power is the fact that a fusion power plant should be locatable within most local or regional electrical distribution systems. For this reason, fusion power plants should not increase the burden of long distance power transmission to our distribution system. In contrast to fusion power, regional factors could play an important role in the deployment of renewable resources such as wind, solar and biomass or fossil energy with CO2 sequestration. We examine the role of these regional factors and their implications for fusion power deployment.

  4. Deployment & Market Transformation (Brochure)

    SciTech Connect

    Not Available

    2012-04-01

    NREL's deployment and market transformation (D and MT) activities encompass the laboratory's full range of technologies, which span the energy efficiency and renewable energy spectrum. NREL staff educates partners on how they can advance sustainable energy applications and also provides clients with best practices for reducing barriers to innovation and market transformation.

  5. 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.

  6. Regulated deployment mechanism for a panel like appendage

    NASA Astrophysics Data System (ADS)

    Bueno, José Ignacio; Vázquez, Javier; Gavira, José Manuel; Migliorero, Gerard

    2001-09-01

    The definition of a cost effective deployment mechanism to deploy 180° panel like appendages in a safe way and with minimum end stroke deployment shock has been a challenge that led the design to achieve a low cost, light, compact, simple, flexible, modular, and low power demanding configuration. This mechanism is composed of an active hinge, that includes an optimised helical torsion spring with a deployment regulator in parallel, and a passive hinge, that includes the end stop and the monitorisation. The main functions of the mechanisms are decoupled in order to make the mechanism as flexible as possible to be adapted to very different needs such as different deployment torque, deployment angle, stiffness, interfaces, monitorisation, etc. The deployment mechanism is provided with a very compact novel deployment regulator based on the progressive melting of a band made of a low melting temperature metal alloy, that is cylindrically disposed. The deployment mechanism has been subject to a qualification test campaign including an extensive characterisation of the deployment regulator.

  7. Large Deployable Reflector (LDR)

    NASA Technical Reports Server (NTRS)

    Alff, W. H.

    1980-01-01

    The feasibility and costs were determined for a 1 m to 30 m diameter ambient temperature, infrared to submillimeter orbiting astronomical telescope which is to be shuttle-deployed, free-flying, and have a 10 year orbital life. Baseline concepts, constraints on delivery and deployment, and the sunshield required are examined. Reflector concepts, the optical configuration, alignment and pointing, and materials are also discussed. Technology studies show that a 10 m to 30 m diameter system which is background and diffraction limited at 30 micron m is feasible within the stated time frame. A 10 m system is feasible with current mirror technology, while a 30 m system requires technology still in development.

  8. Dedicated Deployable Aerobraking Structure

    NASA Technical Reports Server (NTRS)

    Giersch, Louis R.; Knarr, Kevin

    2010-01-01

    A dedicated deployable aerobraking structure concept was developed that significantly increases the effective area of a spacecraft during aerobraking by up to a factor of 5 or more (depending on spacecraft size) without substantially increasing total spacecraft mass. Increasing the effective aerobraking area of a spacecraft (without significantly increasing spacecraft mass) results in a corresponding reduction in the time required for aerobraking. For example, if the effective area of a spacecraft is doubled, the time required for aerobraking is roughly reduced to half the previous value. The dedicated deployable aerobraking structure thus enables significantly shorter aerobraking phases, which results in reduced mission cost, risk, and allows science operations to begin earlier in the mission.

  9. Treatment Deployment Evaluation Tool

    SciTech Connect

    M. A. Rynearson; M. M. Plum

    1999-08-01

    The U.S. Department of Energy (DOE) is responsible for the final disposition of legacy spent nuclear fuel (SNF). As a response, DOE's National Spent Nuclear Fuel Program (NSNFP) has been given the responsibility for the disposition of DOE-owned SNF. Many treatment technologies have been identified to treat some forms of SNF so that the resulting treated product is acceptable by the disposition site. One of these promising treatment processes is the electrometallurgical treatment (EMT) currently in development; a second is an Acid Wash Decladding process. The NSNFP has been tasked with identifying possible strategies for the deployment of these treatment processes in the event that a treatment path is deemed necessary. To support the siting studies of these strategies, economic evaluations are being performed to identify the least-cost deployment path. This model (tool) was developed to consider the full scope of costs, technical feasibility, process material disposition, and schedule attributes over the life of each deployment alternative. Using standard personal computer (PC) software, the model was developed as a comprehensive technology economic assessment tool using a Life-Cycle Cost (LCC) analysis methodology. Model development was planned as a systematic, iterative process of identifying and bounding the required activities to dispose of SNF. To support the evaluation process, activities are decomposed into lower level, easier to estimate activities. Sensitivity studies can then be performed on these activities, defining cost issues and testing results against the originally stated problem.

  10. Treatment Deployment Evaluation Tool

    SciTech Connect

    Rynearson, Michael Ardel; Plum, Martin Michael

    1999-08-01

    The U.S. Department of Energy (DOE) is responsible for the final disposition of legacy spent nuclear fuel (SNF). As a response, DOE's National Spent Nuclear Fuel Program (NSNFP) has been given the responsibility for the disposition of DOE -owned SNF. Many treatment technologies have been identified to treat some forms of SNF so that the resulting treated product is acceptable by the disposition site. One of these promising treatment processes is the electrometallurgical treatment (EMT) currently in development; a second is an Acid Wash Decladding process. The NSNFP has been tasked with identifying possible strategies for the deployment of these treatment processes in the event that the treatment path is deemed necessary. To support the siting studies of these strategies, economic evaluations are being performed to identify the least-cost deployment path. This model (tool) was developed to consider the full scope of costs, technical feasibility, process material disposition, and schedule attributes over the life of each deployment alternative. Using standard personal computer (PC) software, the model was developed as a comprehensive technology economic assessment tool using a Life-Cycle Cost (LCC) analysis methodology. Model development was planned as a systematic, iterative process of identifying and bounding the required activities to dispose of SNF. To support the evaluation process, activities are decomposed into lower level, easier to estimate activities. Sensitivity studies can then be performed on these activities, defining cost issues and testing results against the originally stated problem.

  11. Newly Deployed Sojourner Rover

    NASA Technical Reports Server (NTRS)

    1999-01-01

    This 8-image mosaic was acquired during the late afternoon (near 5pm LST, note the long shadows) on Sol 2 as part of the predeploy 'insurance panorama' and shows the newly deployed rover sitting on the Martian surface. This color image was generated from images acquired at 530,600, and 750 nm. The insurance panorama was designed as 'insurance' against camera failure upon deployment. Had the camera failed, the losslessly-compressed, multispectral insurance panorama would have been the main source of image data from the IMP.

    However, the camera deployment was successful, leaving the insurance panorama to be downlinked to Earth several weeks later. Ironically enough, the insurance panorama contains some of the best quality image data because of the lossless data compression and relatively dust-free state of the camera and associated lander/rover hardware on Sol 2.

    Mars Pathfinder is the second in NASA's Discovery program of low-cost spacecraft with highly focused science goals. The Jet Propulsion Laboratory, Pasadena, CA, developed and manages the Mars Pathfinder mission for NASA's Office of Space Science, Washington, D.C. JPL is an operating division of the California Institute of Technology (Caltech). The IMP was developed by the University of Arizona Lunar and Planetary Laboratory under contract to JPL. Peter Smith is the Principal investigator.

  12. Deployable Reflector for Solar Cells

    NASA Technical Reports Server (NTRS)

    Johnson, K. L.

    1982-01-01

    Unfoldable-membrane-reflector concept leads to mobile photovoltaic generators. Hinged containers swing open for deployment, and counterbalance beam swings into position. Folded reflector membranes are unfolded as deployment mast is extended, until stretched out flat.

  13. Deployment of a Curved Truss

    NASA Technical Reports Server (NTRS)

    Giersch, Louis R.; Knarr, Kevin

    2010-01-01

    Structures capable of deployment into complex, three-dimensional trusses have well known space technology applications such as the support of spacecraft payloads, communications antennas, radar reflectors, and solar concentrators. Such deployable trusses could also be useful in terrestrial applications such as the rapid establishment of structures in military and emergency service situations, in particular with regard to the deployment of enclosures for habitat or storage. To minimize the time required to deploy such an enclosure, a single arch-shaped truss is preferable to multiple straight trusses arranged vertically and horizontally. To further minimize the time required to deploy such an enclosure, a synchronous deployment with a single degree of freedom is also preferable. One method of synchronizing deployment of a truss is the use of a series of gears; this makes the deployment sequence predictable and testable, allows the truss to have a minimal stowage volume, and the deployed structure exhibits the excellent stiffness-to-mass and strength-to-mass ratios characteristic of a truss. A concept for using gears with varying ratios to deploy a truss into a curved shape has been developed and appears to be compatible with both space technology applications as well as potential use in terrestrial applications such as enclosure deployment. As is the case with other deployable trusses, this truss is formed using rigid elements (e.g., composite tubes) along the edges, one set of diagonal elements composed of either cables or folding/hinged rigid members, and the other set of diagonal elements formed by a continuous cable that is tightened by a motor or hand crank in order to deploy the truss. Gears of varying ratios are used to constrain the deployment to a single degree of freedom, making the deployment synchronous, predictable, and repeatable. The relative sizes of the gears and the relative dimensions of the diagonal elements determine the deployed geometry (e

  14. National Missile Defense Contingency Deployment.

    DTIC Science & Technology

    1995-01-01

    Defense Organization PMCS IDEA PAPER TITLE: National Missile Defense, Contingency Deployment Planning PMCS CLASS: 95C AUTHOR: Clifford E. Reeves... NATIONAL MISSILE DEFENSE CONTINGENCY DEPLOYMENT INTRODUCTION The author feels it is vital to start strategic planning for the development of operational...PROFESSIONAL MILITARY COMPTROLLER SCHOOL IDEA PAPER TITLE NATIONAL MISSILE DEFENSE CONTINGENCY DEPLOYMENT AUTHOR CLIFFORD E. REEVES GS-15, OSD

  15. Shuttle entry guidance

    NASA Technical Reports Server (NTRS)

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

    1978-01-01

    This paper describes the design of the entry guidance for the Space Shuttle Orbiter. This guidance provides the steering commands for trajectory control from initial penetration of the earth's atmosphere until the terminal area guidance is activated at an earth-relative speed of 2500 fps. At this point, the Orbiter is at a distance of about 50 nmi from the runway threshold, and at an altitude of about 80,000 ft. The entry guidance design is based on an analytic solution of the equations of motion defining the drag acceleration profile that meets the terminal criteria of the entry flight while maintaining the flight within systems and operational constraints. Guidance commands, which are based on a control law that ensures damping of oscillatory type trajectory motion, are computed to steer the Orbiter to this drag acceleration profile.

  16. Orbiter entry aerothermodynamics

    NASA Technical Reports Server (NTRS)

    Ried, R. C.

    1985-01-01

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

  17. Mobile physician order entry.

    PubMed

    Ying, Alan

    2003-01-01

    Because both computerized physician order entry (CPOE) systems and mobile technologies such as handheld devices have the potential to greatly impact the industry's future, IT vendors, hospitals, and clinicians are simply merging them into a logical convergence--"CPOE on a handheld"--with an expectation of full functionality on all platforms: computer workstations, rolling laptops, tablet PCs, and handheld devices. For these trends to succeed together, however, this expectation must be revised to establish a distinct category--mobile physician order entry (MPOE)--that is different from CPOE in form, function, and implementation.

  18. Self-Deployable Membrane Structures

    NASA Technical Reports Server (NTRS)

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

    2010-01-01

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

  19. Joint for deployable structures

    NASA Technical Reports Server (NTRS)

    Craighead, N. D., II; Preliasco, R. J.; Hult, T. D. (Inventor)

    1985-01-01

    A joint is described for connecting a pair of beams to pivot them between positions in alignment or beside one another, which is of light weight and which operates in a controlled manner. The joint includes a pair of fittings and at least one center link having opposite ends pivotally connected to opposite fittings and having axes that pass through centerplates of the fittings. A control link having opposite ends pivotally connected to the different fittings controls their relative orientations, and a toggle assemly holds the fittings in the deployed configuration wherein they are aligned. The fittings have stops that lie on one side of the centerplane opposite the toggle assembly.

  20. Very Low Head Turbine Deployment in Canada

    NASA Astrophysics Data System (ADS)

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

    2014-03-01

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

  1. ALMR deployment economic analysis

    SciTech Connect

    Delene, J.G.; Fuller, L.C.; Hudson, C.R.

    1993-06-01

    This analysis seeks to model and evaluate the economics of the use of Advanced Liquid Metal Reactors (ALMR) as a component of this country`s future electricity generation mix. The ALMR concept has the ability to utilize as fuel the fissile material contained in previously irradiated nuclear fuel (i.e., spent fuel). While not a requirement for the successful deployment of ALMR power plant technology, the reprocessing of spent fuel from light water reactors (LWR) is necessary for any rapid introduction of ALMR power plants. In addition, the reprocessing of LWR spent fuel may reduce the number of high level waste repositories needed in the future by burning the long-lived actinides produced in the fission process. With this study, the relative economics of a number of potential scenarios related to these issues are evaluated. While not encompassing the full range of all possibilities, the cases reported here provide an indication of the potential costs, timings, and relative economic attractiveness of ALMR deployment.

  2. Economics of ALMR deployment

    SciTech Connect

    Delene, J.G.; Fuller, L.C.; Hudson, C.R.

    1994-12-31

    The Advanced Liquid Metal Reactor (ALMR) has the potential to extend the economic life of the nuclear option and of reducing the number of high level waste repositories which will eventually be needed in an expanding nuclear economy. This paper reports on an analysis which models and evaluates the economics of the use of ALMRs as a component of this country`s future electricity generation mix. The ALMR concept has the ability to utilize as fuel the fissile material contained in previously irradiated nuclear fuel (i.e., spent fuel) or from surplus weapons grade material. While not a requirement for the successful deployment of ALMR power plant technology, the reprocessing of spent fuel from light water reactors (LWR) is necessary for any rapid introduction of ALMR power plants. In addition, the reprocessing of LWR spent fuel may reduce the number of high level waste repositories needed in the future by burning the long-lived actinides produced in the fission process. With this study, the relative economics of a number of potential scenarios related to these issues are evaluated. While not encompassing the full range of all possibilities, the cases reported here provide an indication of the potential costs, timings, and relative economic attractiveness of ALMR deployment.

  3. Field Deployable DNA analyzer

    SciTech Connect

    Wheeler, E; Christian, A; Marion, J; Sorensen, K; Arroyo, E; Vrankovich, G; Hara, C; Nguyen, C

    2005-02-09

    This report details the feasibility of a field deployable DNA analyzer. Steps for swabbing cells from surfaces and extracting DNA in an automatable way are presented. Since enzymatic amplification reactions are highly sensitive to environmental contamination, sample preparation is a crucial step to make an autonomous deployable instrument. We perform sample clean up and concentration in a flow through packed bed. For small initial samples, whole genome amplification is performed in the packed bed resulting in enough product for subsequent PCR amplification. In addition to DNA, which can be used to identify a subject, protein is also left behind, the analysis of which can be used to determine exposure to certain substances, such as radionuclides. Our preparative step for DNA analysis left behind the protein complement as a waste stream; we determined to learn if the proteins themselves could be analyzed in a fieldable device. We successfully developed a two-step lateral flow assay for protein analysis and demonstrate a proof of principle assay.

  4. Atmospheric Entry Studies for Uranus

    NASA Technical Reports Server (NTRS)

    Agrawal, Parul; Allen, Gary A.; Hwang, Helen; Prabhu, Dinesh; Aliaga, Jose; Marley, Mark; McGuire, Kathy; Huynh, Loc; Garcia, Joseph; Moses, Robert; Winski, Rick; Skylanskiy, Evgeniy

    2013-01-01

    The Objectives of this work are: 1) Establish a range of probe atmospheric entry environments based on the Uranus Flagship mission outlined in the Planetary Science Decadal Survey for two launch windows: Year 2021 and 2034. 2) Define Uranus entry trade space by performing parametric studies, by varying vehicle mass and size and entry Flight Path Angle (FPA). 3) Investigate various trajectory options, including direct ballistic entry and aero-capture entry. 4) Identify entry technologies that could be leveraged to enable a viable mission to Uranus that meets science objectives.

  5. Think Exit at Entry

    ERIC Educational Resources Information Center

    O'Rourke, Tom; Satterfield, Coy E.

    2005-01-01

    This paper describes the "Think Exit at Entry" program that has become the guiding principle for the Georgia Department of Juvenile Justice (DJJ). The Georgia DJJ believes that the transition process begins the day the youth enters the system and continues well after release from the institution. Literature points the need for transition…

  6. Aerial Deployment and Inflation System for Mars Helium Balloons

    NASA Technical Reports Server (NTRS)

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

    2009-01-01

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

  7. Parachute Swivel Mechanism for planetary entry

    NASA Technical Reports Server (NTRS)

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

    1993-01-01

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

  8. Orion Entry Flight Control Stability and Performance

    NASA Technical Reports Server (NTRS)

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

    2007-01-01

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

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

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

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

  10. Deployable Wireless Camera Penetrators

    NASA Technical Reports Server (NTRS)

    Badescu, Mircea; Jones, Jack; Sherrit, Stewart; Wu, Jiunn Jeng

    2008-01-01

    A lightweight, low-power camera dart has been designed and tested for context imaging of sampling sites and ground surveys from an aerobot or an orbiting spacecraft in a microgravity environment. The camera penetrators also can be used to image any line-of-sight surface, such as cliff walls, that is difficult to access. Tethered cameras to inspect the surfaces of planetary bodies use both power and signal transmission lines to operate. A tether adds the possibility of inadvertently anchoring the aerobot, and requires some form of station-keeping capability of the aerobot if extended examination time is required. The new camera penetrators are deployed without a tether, weigh less than 30 grams, and are disposable. They are designed to drop from any altitude with the boost in transmitting power currently demonstrated at approximately 100-m line-of-sight. The penetrators also can be deployed to monitor lander or rover operations from a distance, and can be used for surface surveys or for context information gathering from a touch-and-go sampling site. Thanks to wireless operation, the complexity of the sampling or survey mechanisms may be reduced. The penetrators may be battery powered for short-duration missions, or have solar panels for longer or intermittent duration missions. The imaging device is embedded in the penetrator, which is dropped or projected at the surface of a study site at 90 to the surface. Mirrors can be used in the design to image the ground or the horizon. Some of the camera features were tested using commercial "nanny" or "spy" camera components with the charge-coupled device (CCD) looking at a direction parallel to the ground. Figure 1 shows components of one camera that weighs less than 8 g and occupies a volume of 11 cm3. This camera could transmit a standard television signal, including sound, up to 100 m. Figure 2 shows the CAD models of a version of the penetrator. A low-volume array of such penetrator cameras could be deployed from an

  11. Results of the parabolic flight tests of the rapunzel deployer

    NASA Astrophysics Data System (ADS)

    Sabath, D.; Krischke, M.; Kast, W.; Kowalczyk, M.; Kruijff, M.; van der Heide, E.

    The tether assisted re-entry of small payloads is a highly interesting tool for space transportation especially for the return of small payloads from Space Station ISSA. The small tether mission Rapunzel was initiated in 1991 by the Institute of Astronautics, TU München and the Kayser-Threde Company, to design a low cost and feasible tether experiment for the verification of the tether assisted re-entry. Together with the Samara State Aerospace University, Russia, a mission concept on a Russian Resurs or Photon capsule was developed. Based on this mission a deployer has been designed, mainly based on technology of the textile industry, which insures high reliability at low cost. Recently a similar configuration is being discussed for the ESA-TSE mission. The main work during the recent time was the development and test of the breadboard model of the deployer system. After successfully completing initial ground tests with the deployer, further tests during the ESA Parabolic Flight campaign in November 1995 were conducted. After a short introduction of the overall mission scenario, the planned configuration in orbit, this paper will present the results of the microgravity test campaign onboard the KC-135 aircraft and compare them with the ground test. The deployer showed a good performance during all tests, including ejection of the end-mass, deployment, and braking. Problems that occurred during the tests will be discussed, and solutions for the detected flaws and the results of the redesign now in progress will be presented. These verifications have shown the feasibility of the concept and will lay the base for the planned development of the flight model of the deployer.

  12. Thermally stable deployable structure

    NASA Technical Reports Server (NTRS)

    Kegg, Colleen M.

    1988-01-01

    A deployable structure which meets stringent thermal and strength requirements in a space environment was developed. A mast with a very low coefficient of thermal expansion (CTE) was required to limit the movement from thermal distortion over the temperature range of -200 C to 80 C to .064 cm (.025 in). In addition, a high bending strength over the temperature range and weight less than 18.1 kg (40 lbs) was needed. To meet all of the requirements, a composite, near-zero CTE structure was developed. The measured average CTE over the temperature range for the mast was .70 x .000001/C (.38 x .000001/F). The design also has the advantage of being adjustable to attain other specific CTE if desired.

  13. Complex Deployed Responsive Service

    NASA Astrophysics Data System (ADS)

    Parry, Glenn; McLening, Marc; Caldwell, Nigel; Thompson, Rob

    A pizza restaurant must provide product, in the form of the food and drink, and service in the way this is delivered to the customer. Providing this has distinct operational challenges, but what if the restaurant also provides a home delivery service? The service becomes deployed as the customer is no-longer co-located with the production area. The business challenge is complicated as service needs to be delivered within a geographic region, to time or the pizza will be cold, and within a cost that is not ­prohibitive. It must also be responsive to short term demand; needing to balance the number of staff it has available to undertake deliveries against a forecast of demand.

  14. 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.

  15. Enterprise Technologies Deployment for Agile Manufacturing

    SciTech Connect

    Neal, R.E.

    1992-11-01

    This report is intended for high-level technical planners who are responsible for planning future developments for their company or Department of Energy/Defense Programs (DOE/DP) facilities. On one hand, the information may be too detailed or contain too much manufacturing technology jargon for a high-level, nontechnical executive, while at the same time an expert in any of the four infrastructure fields (Product Definition/Order Entry, Planning and Scheduling, Shop Floor Management, and Intelligent Manufacturing Systems) will know more than is conveyed here. The purpose is to describe a vision of technology deployment for an agile manufacturing enterprise. According to the 21st Century Manufacturing Enterprise Strategy, the root philosophy of agile manufacturing is that ``competitive advantage in the new systems will belong to agile manufacturing enterprises, capable of responding rapidly to demand for high-quality, highly customized products.`` Such agility will be based on flexible technologies, skilled workers, and flexible management structures which collectively will foster cooperative initiatives in and among companies. The remainder of this report is dedicated to sharpening our vision and to establishing a framework for defining specific project or pre-competitive project goals which will demonstrate agility through technology deployment.

  16. Enterprise Technologies Deployment for Agile Manufacturing

    SciTech Connect

    Neal, R.E.

    1992-11-01

    This report is intended for high-level technical planners who are responsible for planning future developments for their company or Department of Energy/Defense Programs (DOE/DP) facilities. On one hand, the information may be too detailed or contain too much manufacturing technology jargon for a high-level, nontechnical executive, while at the same time an expert in any of the four infrastructure fields (Product Definition/Order Entry, Planning and Scheduling, Shop Floor Management, and Intelligent Manufacturing Systems) will know more than is conveyed here. The purpose is to describe a vision of technology deployment for an agile manufacturing enterprise. According to the 21st Century Manufacturing Enterprise Strategy, the root philosophy of agile manufacturing is that competitive advantage in the new systems will belong to agile manufacturing enterprises, capable of responding rapidly to demand for high-quality, highly customized products.'' Such agility will be based on flexible technologies, skilled workers, and flexible management structures which collectively will foster cooperative initiatives in and among companies. The remainder of this report is dedicated to sharpening our vision and to establishing a framework for defining specific project or pre-competitive project goals which will demonstrate agility through technology deployment.

  17. DLMS Voice Data Entry.

    DTIC Science & Technology

    1980-06-01

    RUN program features a syntactic structure based upon a group of subroutines to perform a group of functions involved in data entry for the DLMS...Code # 120 AGRICULTURAL 430 10 HOSPITAL GABLE 632 121 STOCKYARD 433 151 OBSERVATORY .640 122 WIND I LL 434 152 OBSERVATORY DOME 641 123 CEMETARY BLGS ...associated with each word or group of words. To illustrate the procedure to be followed with the CREATE program, an example is in order. In this example

  18. Deployable Fresnel Rings

    NASA Technical Reports Server (NTRS)

    Kennedy, Timothy F.; Fink, Patrick W.; Chu, Andrew W.; Lin, Gregory Y.

    2014-01-01

    Deployable Fresnel rings (DFRs) significantly enhance the realizable gain of an antenna. This innovation is intended to be used in combination with another antenna element, as the DFR itself acts as a focusing or microwave lens element for a primary antenna. This method is completely passive, and is also completely wireless in that it requires neither a cable, nor a connector from the antenna port of the primary antenna to the DFR. The technology improves upon the previous NASA technology called a Tri-Sector Deployable Array Antenna in at least three critical aspects. In contrast to the previous technology, this innovation requires no connector, cable, or other physical interface to the primary communication radio or sensor device. The achievable improvement in terms of antenna gain is significantly higher than has been achieved with the previous technology. Also, where previous embodiments of the Tri-Sector antenna have been constructed with combinations of conventional (e.g., printed circuit board) and conductive fabric materials, this innovation is realized using only conductive and non-conductive fabric (i.e., "e-textile") materials, with the possible exception of a spring-like deployment ring. Conceptually, a DFR operates by canceling the out-of-phase radiation at a plane by insertion of a conducting ring or rings of a specific size and distance from the source antenna, defined by Fresnel zones. Design of DFRs follow similar procedures to those outlined for conventional Fresnel zone rings. Gain enhancement using a single ring is verified experimentally and through computational simulation. The experimental test setup involves a microstrip patch antenna that is directly behind a single-ring DFR and is radiating towards a second microstrip patch antenna. The first patch antenna and DFR are shown. At 2.42 GHz, the DFR improves the transmit antenna gain by 8.6 dB, as shown in Figure 2, relative to the wireless link without the DFR. A figure illustrates the

  19. Two Concepts for Deployable Trusses

    NASA Technical Reports Server (NTRS)

    Renfro, John W.

    2010-01-01

    Two concepts that could be applied separately or together have been suggested to enhance the utility of deployable truss structures. The concepts were intended originally for application to a truss structure to be folded for compact stowage during transport and subsequently deployed in outer space. The concepts may also be applicable, with some limitations, to deployable truss structures designed to be used on Earth. The first concept involves a combination of features that would help to maximize reliability of a structure while minimizing its overall mass, the complexity of its deployment system, and the expenditure of energy for deployment. The deployment system would be integrated into the truss: some of the truss members would contain folding/unfolding-detent mechanisms similar to those in umbrellas; other truss members would contain shape-memory-alloy (SMA) coil actuators (see Figure 1). Upon exposure to sunlight, the SMA actuators would be heated above their transition temperature, causing them to extend to their deployment lengths. The extension of the actuators would cause the structure to unfold and, upon completion of unfolding, the umbrellalike mechanisms would lock the unfolded truss in the fully deployed configuration. The use of solar heating to drive deployment would eliminate the need to carry a deployment power source. The actuation scheme would offer high reliability in that the truss geometry would be such that deployment could be completed even if all actuators were not functioning. Of course, in designing for operation in normal Earth gravitation, it would be necessary to ensure that the SMA actuators could apply forces large enough to overcome the deploymentresisting forces attributable to the weights of the members. The second concept is that of an improved design for the joints in folding members. Before describing this design,

  20. Deploying the Mental Eye

    PubMed Central

    Koenderink, Jan; van Doorn, Andrea

    2015-01-01

    Three observers performed a task designed to quantify their “pictorial relief” in visual awareness for a photograph of a piece of sculpture. In separate sessions, they were instructed to assume one of two “mental viewpoints.” The main objective was to investigate whether human observers have such command. All three observers could redirect their “mental view direction” by up to 20°. These observers experience “paradoxical monocular” stereopsis, whereas a sizable fraction of the population does not. Moreover, they had some experience in assuming various “viewing modes.” Whereas one cannot generalize to the population at large, these findings at least prove that it is possible to direct the mental viewpoint actively. This is of importance to the visual arts. For instance, academic drawings require one to be simultaneously aware of a “viewing” (for the drawing) and an “illumination direction” (for the shading). Being able to mentally deploy various vantage points is a crucial step from the “visual field” to the “visual space.” PMID:27648221

  1. Device Measures Angle Of Deployment

    NASA Technical Reports Server (NTRS)

    Jermakian, Joel B.

    1991-01-01

    Simple electromechanical device indicates angular position of unfolding panel during and after deployment. Resistance of potentiometer gradually increases as unfolding of solar panel about hinge moves wiper of potentiometer. At full deployment, panel pushes and opens normally closed switch. Designed for use on panel of solar photovoltaic cells in spacecraft, modified for use in other, similar position-indicating applications.

  2. Rapidly Deployed Modular Telemetry System

    NASA Technical Reports Server (NTRS)

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

    2013-01-01

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

  3. Adapted Canoeing for the Handicapped.

    ERIC Educational Resources Information Center

    Frith, Greg H.; Warren, L. D.

    1984-01-01

    Safety as well as instructional recommendations are offered for adapting canoeing as a recreationial activity for handicapped students. Major steps of the instructional program feature orientation to the water and canoe, entry and exit techinques, and mobility procedures. (CL)

  4. Deployment simulation of a deployable reflector for earth science application

    NASA Astrophysics Data System (ADS)

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

    2015-10-01

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

  5. Entry Systems Panel

    NASA Technical Reports Server (NTRS)

    Rasky, Daniel J.; Rummler, Donald R.; Bersch, Charlie; Dixon, Sidney C.

    1993-01-01

    As general findings, lessons learned from shuttle are: (1) bridge established between development center (JSC) Research Centers (ARC, LARC), and industry (RI, LMSC, Corning, Mansville, 3M LTV, Union Carbide, Hexcel) for shuttle TPS; (2) not all test results adequately analyzed or in hindsight, completely encompassing all failure modes; (3) gap heating effects from ground facilities not totally indicative of flight experience; (4) need to design with operations in mind (not just to cost) example: moisture intrusion of GR/EP, many other examples; (5) RSI- developed as point design for maneuvering entry vehicle of high L/D; and (6) RSI - 15 years from invention to use on flight hardware.

  6. 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.

  7. Entry guidance and entry autopilot (STS-1 baseline)

    NASA Astrophysics Data System (ADS)

    Harpold, J. C.; Hill, O.

    1980-08-01

    Preliminary entry guidance and autopilot software formulations, for use in the Mission Control Center (MCC) entry processor, are presented. The MCC requirements are met by a definition of coordinate systems, a list of parameter definitions for the software formulations, a description of the entry guidance detailed formulation requirements, a description of the detailed autopilot formualtion requirements, a description of the targeting routine, and a set of formulation flow charts.

  8. Entry guidance and entry autopilot (STS-1 baseline)

    NASA Technical Reports Server (NTRS)

    Harpold, J. C.; Hill, O.

    1980-01-01

    Preliminary entry guidance and autopilot software formulations, for use in the Mission Control Center (MCC) entry processor, are presented. The MCC requirements are met by a definition of coordinate systems, a list of parameter definitions for the software formulations, a description of the entry guidance detailed formulation requirements, a description of the detailed autopilot formualtion requirements, a description of the targeting routine, and a set of formulation flow charts.

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

    NASA Technical Reports Server (NTRS)

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

    2012-01-01

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

  10. New concepts in deployable beam structures

    NASA Technical Reports Server (NTRS)

    Rhodes, M. D.

    1985-01-01

    The design of deployable structures involves a complicated tradeoff of packaging efficiency, the overall mechanism associated with deploying and latching beam joints, and the requirements and complexity of the beam deployer/repacker. Three longeron deployable beams, controllable geometry beams, and hybrid deployable/erectable beam concepts are evaluated.

  11. 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.

  12. 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.

  13. Trading Robustness Requirements in Mars Entry Trajectory Design

    NASA Technical Reports Server (NTRS)

    Lafleur, Jarret M.

    2009-01-01

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

  14. Advertising and generic market entry.

    PubMed

    Königbauer, Ingrid

    2007-03-01

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

  15. Membrane fusion during poxvirus entry.

    PubMed

    Moss, Bernard

    2016-12-01

    Poxviruses comprise a large family of enveloped DNA viruses that infect vertebrates and invertebrates. Poxviruses, unlike most DNA viruses, replicate in the cytoplasm and encode enzymes and other proteins that enable entry, gene expression, genome replication, virion assembly and resistance to host defenses. Entry of vaccinia virus, the prototype member of the family, can occur at the plasma membrane or following endocytosis. Whereas many viruses encode one or two proteins for attachment and membrane fusion, vaccinia virus encodes four proteins for attachment and eleven more for membrane fusion and core entry. The entry-fusion proteins are conserved in all poxviruses and form a complex, known as the Entry Fusion Complex (EFC), which is embedded in the membrane of the mature virion. An additional membrane that encloses the mature virion and is discarded prior to entry is present on an extracellular form of the virus. The EFC is held together by multiple interactions that depend on nine of the eleven proteins. The entry process can be divided into attachment, hemifusion and core entry. All eleven EFC proteins are required for core entry and at least eight for hemifusion. To mediate fusion the virus particle is activated by low pH, which removes one or more fusion repressors that interact with EFC components. Additional EFC-interacting fusion repressors insert into cell membranes and prevent secondary infection. The absence of detailed structural information, except for two attachment proteins and one EFC protein, is delaying efforts to determine the fusion mechanism.

  16. Analysis of spacecraft entry into Mars atmosphere

    NASA Astrophysics Data System (ADS)

    Nakajima, Ken; Nagano, Koutarou

    1991-07-01

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

  17. SMAP Launch and Deployment Sequence

    NASA Video Gallery

    This video combines file footage of a Delta II rocket and computer animation to depict the launch and deployment of NASA's Soil Moisture Active Passive satellite. SMAP is scheduled to launch on Nov...

  18. Deployable Wastewater Treatment Technology Evaluation

    DTIC Science & Technology

    2006-05-31

    AFRL/MLQD is expanding the Deployable Waste Disposal System to include bare base wastewater treatment. The goal of AFRL/MLQD is for the deployable... wastewater treatment system to be integrated into a waste treatment system that will treat both solid and aqueous waste. The US Army (TARDEC) and the... Air Force (AAC/WMO) have been involved in preliminary studies that provide extensive useful background information for this project. These studies show

  19. The Deployment Life Study. Appendixes

    DTIC Science & Technology

    2014-01-01

    prepare children for deployment | Have you talked with a professional (like someone in children and youth services) about how to help | your...military sponsored, school sponsored, or | non-military deployment support activities (such as Guard youth programs or Operation Purple Camp?) Baseline...assistance provided by the military | | 7 Complementary child care provided by the military | | 8 Children and Youth Services | | 9 Relief/aid

  20. Deployable antenna phase A study

    NASA Technical Reports Server (NTRS)

    Schultz, J.; Bernstein, J.; Fischer, G.; Jacobson, G.; Kadar, I.; Marshall, R.; Pflugel, G.; Valentine, J.

    1979-01-01

    Applications for large deployable antennas were re-examined, flight demonstration objectives were defined, the flight article (antenna) was preliminarily designed, and the flight program and ground development program, including the support equipment, were defined for a proposed space transportation system flight experiment to demonstrate a large (50 to 200 meter) deployable antenna system. Tasks described include: (1) performance requirements analysis; (2) system design and definition; (3) orbital operations analysis; and (4) programmatic analysis.

  1. Water Entry of Projectiles

    NASA Astrophysics Data System (ADS)

    Truscott, Tadd T.; Epps, Brenden P.; Belden, Jesse

    2014-01-01

    The free-surface impact of solid objects has been investigated for well over a century. This canonical problem is influenced by many physical parameters, including projectile geometry, material properties, fluid properties, and impact parameters. Through advances in high-speed imaging and visualization techniques, discoveries about the underlying physics have improved our understanding of these phenomena. Improvements to analytical and numerical models have led to critical insights into cavity formation, the depth and time of pinch-off, forces, and trajectories for myriad different impact parameters. This topic spans a wide range of regimes, from low-speed entry phenomena dominated by surface tension to high-speed ballistics, for which cavitation is important. This review surveys experimental, theoretical, and numerical studies over this broad range, utilizing canonical images where possible to enhance intuition and insight into the rich phenomena.

  2. Shuttle entry guidance revisited

    NASA Astrophysics Data System (ADS)

    Mease, Kenneth D.; Kremer, Jean-Paul

    1992-08-01

    The Shuttle entry guidance concept is reviewed which is aimed at tracking a reference drag trajectory that leads to the specified range and velocity for the initiation of the terminal energy management phase. An approximate method of constructing the domain of attraction is proposed, and its validity is ascertained by simulation. An alternative guidance law yielding global exponential tracking in the absence of control saturation is derived using a feedback linearization method. It is noted that the alternative guidance law does not improve on the stability and performance of the current guidance law, for the operating domain and control capability of the Shuttle. It is suggested that the new guidance law with a larger operating domain and increased lift-to-drag capability would be superior.

  3. Shuttle entry guidance revisited

    NASA Technical Reports Server (NTRS)

    Mease, Kenneth D.; Kremer, Jean-Paul

    1992-01-01

    The Shuttle entry guidance concept is reviewed which is aimed at tracking a reference drag trajectory that leads to the specified range and velocity for the initiation of the terminal energy management phase. An approximate method of constructing the domain of attraction is proposed, and its validity is ascertained by simulation. An alternative guidance law yielding global exponential tracking in the absence of control saturation is derived using a feedback linearization method. It is noted that the alternative guidance law does not improve on the stability and performance of the current guidance law, for the operating domain and control capability of the Shuttle. It is suggested that the new guidance law with a larger operating domain and increased lift-to-drag capability would be superior.

  4. System definition study of deployable, non-metallic space structures

    NASA Technical Reports Server (NTRS)

    Stimler, F. J.

    1984-01-01

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

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

    PubMed Central

    GP, Douglas; RA, Deula; SE, Connor

    2003-01-01

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

  6. MODEP Modified DEPLOY Program. Volume II - Appendixes.

    DTIC Science & Technology

    requirements for PBV’s (post boost vehicles) carrying a number of objects which are deployed to various target geometries. Since MODEP lacks some of the...capabilities of the DEPLOY program, such as a sizing option, an active deployment option, and a deployed objects pattern analysis option, MODEP is...intended to supplement rather than replace the DEPLOY program. The capabilities not found in the DEPLOY program but contained in MODEP are the

  7. MODEP Modified DEPLOY Program Volume I.

    DTIC Science & Technology

    requirements for PBV’s (post boost vehicles) carrying a number of objects which are deployed to various target geometries. Since MODEP lacks some of the...capabilities of the DEPLOY program, such as a sizing option, an active deployment option, and a deployed objects pattern analysis option, MODEP is...intended to supplement rather than replace the DEPLOY program. The capabilities not found in the DEPLOY program but contained in MODEP are the

  8. Trajectory and atmospheric structure from entry probes: Demonstration of a real-time reconstruction technique using a simple direct-to-Earth radio link

    NASA Astrophysics Data System (ADS)

    Withers, Paul

    2010-12-01

    The reconstruction of the trajectory and atmospheric structure associated with an entry probe has traditionally relied upon onboard accelerometer measurements. Here we outline an equivalent reconstruction technique that uses Doppler-shifted direct-to-Earth transmissions instead. A critical assumption is that the entry probe's angle of attack is zero. The technique is successfully demonstrated on the atmospheric entry of the Mars Exploration Rover Opportunity, terminating at parachute deployment. This technique can be applied in real-time, which supports mission operations and public engagement. It can also be applied to entry probes that fail during their high-risk atmospheric entry.

  9. Trajectory And Atmospheric Structure From Entry Probes: Demonstration Of A Real-time Reconstruction Technique Using A Simple Direct-to-earth Radio Link

    NASA Astrophysics Data System (ADS)

    Withers, Paul

    2010-10-01

    The reconstruction of the trajectory and atmospheric structure associated with an entry probe has traditionally relied upon onboard accelerometer measurements. Here we outline an equivalent reconstruction technique that uses Doppler-shifted direct-to-Earth transmissions instead. A critical assumption is that the entry probe's angle of attack is zero. The technique is successfully demonstrated on the atmospheric entry of the Mars Exploration Rover Opportunity, terminating at parachute deployment. This technique can be applied in real-time, which supports mission operations and public engagement. It can also be applied to entry probes that fail during their high-risk atmospheric entry.

  10. 19 CFR 10.31 - Entry; bond.

    Code of Federal Regulations, 2010 CFR

    2010-04-01

    ... not over $250, the form prescribed for the informal entry of importations by mail, in baggage, or by... consumption entry summary, each temporary importation bond entry summary shall include: (i) The HTSUS... consumption entry on the date of the original arrival. (d) (e) The entry or invoice shall: (1) Describe...

  11. Centrifugal regulator for control of deployment rates of deployable elements

    NASA Technical Reports Server (NTRS)

    Vermalle, J. C.

    1980-01-01

    The requirements, design, and performance of a centrifugal regulator aimed at limiting deployment rates of deployable elements are discussed. The overall mechanism is comprised of four distinct functional parts in a machined housing: (1) the centrifugal brake device, which checks the payout of a deployment cable; (2) the reducing gear, which produces the spin rate necesary for the braking device; (3) the payout device, which allows the unwinding of the cable; and (4) the locking device, which prevents untimely unwinding. The centrifugal regulator is set into operation by a threshold tension of the cable which unlocks the mechanism and allows unwinding. The pulley of the windout device drives the centrifugal brake with the help of the reducing gear. The centrifugal force pushes aside weights that produce friction of the studs in a cylindrical housing. The mechanism behaved well at qualification temperature and vibrations.

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

    ERIC Educational Resources Information Center

    Denton, David W.

    2012-01-01

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

  13. Newberry Seismic Deployment Fieldwork Report

    SciTech Connect

    Wang, J; Templeton, D C

    2012-03-21

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

  14. Deployable teleradiology: Bosnia and beyond.

    PubMed

    Levine, B A; Cleary, K; Mun, S K

    1998-03-01

    The United States military has been an effective proponent of digital imaging and teleradiology for the past 15 years [1]. A digital imaging network that eliminates the use of x-ray film makes military medicine requirements simpler. X-ray film requirements include storage of new, unexposed films, storage and use of chemicals and water for processing, and disposal of chemicals. In some deployed situations, the chemical discharge needs to be collected and shipped out of the area. Therefore, the ability to implement electronic imaging and eliminate or greatly reduce the dependence on film, chemicals, and water are intrinsically important to military medicine. In December 1995, the United States government began deployment of 20,000 United States troops to Bosnia-Herzegovina as part of NATO's peacekeeping implementation force (IFOR) operation. A full complement of military medical support facilities was established in Bosnia. An army base in Hungary was the location from which the deployment was staged. The project to deploy telemedicine and teleradiology capabilities to the medical treatment facilities (MTF) in Bosnia and Hungary became known as PrimeTime III [2]. This paper deals with the deployable teleradiology (DEPRAD) system that was installed by the Imaging Science and Information Systems (ISIS) Center, Department of Radiology, Georgetown Medical Center, Washington, DC, at a number of facilities to implement filmless radiology and teleradiology services in support of PrimeTime III.

  15. Regular Deployment of Wireless Sensors to Achieve Connectivity and Information Coverage

    PubMed Central

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

    2016-01-01

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

  16. 19 CFR 142.17 - One entry summary for multiple entries.

    Code of Federal Regulations, 2011 CFR

    2011-04-01

    ... 19 Customs Duties 2 2011-04-01 2011-04-01 false One entry summary for multiple entries. 142.17...; DEPARTMENT OF THE TREASURY (CONTINUED) ENTRY PROCESS Entry Summary Documentation § 142.17 One entry summary for multiple entries. (a) Requirements. Except as provided in paragraph (b) of this section, the...

  17. 19 CFR 142.17 - One entry summary for multiple entries.

    Code of Federal Regulations, 2010 CFR

    2010-04-01

    ... 19 Customs Duties 2 2010-04-01 2010-04-01 false One entry summary for multiple entries. 142.17...; DEPARTMENT OF THE TREASURY (CONTINUED) ENTRY PROCESS Entry Summary Documentation § 142.17 One entry summary for multiple entries. (a) Requirements. Except as provided in paragraph (b) of this section, the...

  18. 19 CFR 142.17 - One entry summary for multiple entries.

    Code of Federal Regulations, 2013 CFR

    2013-04-01

    ... 19 Customs Duties 2 2013-04-01 2013-04-01 false One entry summary for multiple entries. 142.17...; DEPARTMENT OF THE TREASURY (CONTINUED) ENTRY PROCESS Entry Summary Documentation § 142.17 One entry summary for multiple entries. (a) Requirements. Except as provided in paragraph (b) of this section, the...

  19. 19 CFR 142.17 - One entry summary for multiple entries.

    Code of Federal Regulations, 2012 CFR

    2012-04-01

    ... 19 Customs Duties 2 2012-04-01 2012-04-01 false One entry summary for multiple entries. 142.17...; DEPARTMENT OF THE TREASURY (CONTINUED) ENTRY PROCESS Entry Summary Documentation § 142.17 One entry summary for multiple entries. (a) Requirements. Except as provided in paragraph (b) of this section, the...

  20. Deployable truss structure advanced technology

    NASA Technical Reports Server (NTRS)

    Dyer, J. E.; Dudeck, M. P.

    1986-01-01

    The 5-meter technology antenna program demonstrated the overall feasibility of integrating a mesh reflector surface with a deployable truss structure to achieve a precision surface contour compatible with future, high-performance antenna requirements. Specifically, the program demonstrated: the feasibility of fabricating a precision, edge-mounted, deployable, tetrahedral truss structure; the feasibility of adjusting a truss-supported mesh reflector contour to a surface error less than 10 mils rms; and good RF test performance, which correlated well with analytical predictions. Further analysis and testing (including flight testing) programs are needed to fully verify all the technology issues, including structural dynamics, thermodynamics, control, and on-orbit RF performance, which are associated with large, deployable, truss antenna structures.

  1. GOCE Re-Entry Campaign

    NASA Astrophysics Data System (ADS)

    Bastida, B.; Flohrer, T.; Lemmens, S.; Krag, H.

    2015-03-01

    Every year ESA, through the Space Debris Office, participates to an Inter-Agency Space Debris Coordination Committee (IADC) Re-entry Test Campaign.. For the campaign of 2013, ESA’s proposal to select GOCE's re-entry was accepted. The campaign opened on the 21st October 2013 after fuel depletion of the drag-compensating ion propulsion. GOCE was expected to enter into a phase of attitude-controlled fine-pointing mode (FPM) until the attitude controllers would be unable to cope with the atmospheric torques and then the satellite would enter in a phase of fully uncontrolled flight. In this paper, we present the evolution of ESA’s daily predictions on the re-entry epoch using different sources of orbital information. The uncertainties on the spacecraft operability (i.e. the physical limits of the attitude controller) led to a non-standard re-entry scenario were different attitudes had to be considered (instead of the commonly assumed random tumbling mode case that is used whenever no information on the physical properties of a re-entering object is available). A daily assessment of the status, in coordination with the flight control team, was required and implied a continuous update on the predicted failure point of the attitude controller. This in turn imposed the need for considering an asymmetric re-entry window. These operation-bound uncertainties were simulated to predict the attitude evolution after failure at different altitudes and their effects evaluated to be taken into account for the re-entry predictions. We present ESA’s re-entry prediction activities for GOCE, internally, and within the IADC, and address specific technical aspects and challenges for re-entry predictions, which are related to the expected and occurred attitude of GOCE during the final re-entry phase.

  2. ESA Venus Entry Probe Study

    NASA Technical Reports Server (NTRS)

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

    2005-01-01

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

  3. Sample acquisition and instrument deployment

    NASA Technical Reports Server (NTRS)

    Boyd, Robert C.

    1995-01-01

    Progress is reported in developing the Sample Acquisition and Instrument Deployment (SAID) system, a robotic system for deploying science instruments and acquiring samples for analysis. The system is a conventional four degree of freedom manipulator 2 meters in length. A baseline design has been achieved through analysis and trade studies. The design considers environmental operating conditions on the surface of Mars, as well as volume constraints on proposed Mars landers. Control issues have also been studied, and simulations of joint and tip movements have been performed. The systems have been fabricated and tested in environmental chambers, as well as soil testing and robotic control testing.

  4. ROBODEXS; Multi-robot Deployment & Extraction System

    DTIC Science & Technology

    2012-04-03

    Deployment & Extraction System (ROBODEXS) is a result of our development research to improve marsupial robotic deployment at safe standoff distances. The...Keywords: ROBODEXS, Marsupial , Deployment, Extraction, Multiple UGV, Modular, Scalable, Robot, Unmanned 1. INTRODUCTION Until recently, small...down to the ground level for deployment.. Research has shown commercial robotics developers have also experimented with marsupial capabilities, allowing

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

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

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

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

    NASA Technical Reports Server (NTRS)

    Way, David W.

    2011-01-01

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

  7. Entry Dispersion Analysis for the Genesis Sample Return Capsule

    NASA Technical Reports Server (NTRS)

    Desai, Prasun N.; Cheatwood, F. McNeil

    2005-01-01

    Genesis will be the first mission to return samples from beyond the Earth-Moon system. The spacecraft will be inserted into a halo orbit about the L1 (Sun-Earth) libration point where it will remain for two years collecting solar wind particles. Upon Earth return, the sample return capsule, which is passively controlled, will descend under parachute to Utah. The present study describes the analysis of the entry, descent, and landing scenario of the returning sample capsule. The robustness of the entry sequence is assessed through a Monte Carlo dispersion analysis where the impact of off-nominal conditions is ascertained. The dispersion results indicate that the capsule attitude excursions near peak heating and drogue chute deployment are within Genesis mission limits. Additionally, the size of the resulting 3-sigma landing ellipse is 47.8 km in downrange by 15.2 km in crossrange, which is within the Utah Test and Training Range boundaries.

  8. Entry Dispersion Analysis for the Genesis Sample Return Capsule

    NASA Technical Reports Server (NTRS)

    Desai, Prasun N.; Cheatwood, F. McNeil

    1999-01-01

    Genesis will be the first mission to return samples from beyond the Earth-Moon system. The spacecraft will be inserted into a halo orbit about the L1 (Sun- Earth) libration point where it will remain for two years collecting solar wind particles. Upon Earth return, the sample return capsule, which is passively controlled, will descend under parachute to Utah. The present study describes the analysis of the entry, descent, and landing scenario of the returning sample capsule. The robustness of the entry sequence is assessed through a Monte Carlo dispersion analysis where the impact of off-nominal conditions is ascertained. The dispersion results indicate that the capsule attitude excursions near peak heating and drogue chute deployment are within Genesis mission limits. Additionally, the size of the resulting 3-sigma landing ellipse is 47.8 km in downrange by 15.2 km in crossrange, which is within the Utah Test and Training Range boundaries.

  9. Entry Dispersion Analysis for the Genesis Sample Return Capsule

    NASA Technical Reports Server (NTRS)

    Desai, Prasun, N.; Cheatwood, F. McNeil

    1999-01-01

    Genesis will be the first mission to return samples from beyond the Earth-Moon system. The spacecraft will be inserted into a halo orbit about the L1 (Sun- Earth) libration point where it will remain for two years collecting solar wind particles. Upon Earth return, the sample return capsule, which is passively controlled, will descend under parachute to Utah. The present study describes the analysis of the entry, descent, and landing scenario of the returning sample cap- sule. The robustness of the entry sequence is assessed through a Monte Carlo dispersion analysis where the impact of off-nominal conditions is ascertained. The dispersion results indicate that the capsule attitude excursions near peak heating and drogue chute deployment are within Genesis mission limits. Additionally, the size of the resulting 3-sigma landing ellipse is 47.8 km in downrange by 15.2 km in crossrange, which is within the Utah Test and Training Range boundaries.

  10. Overview of the Phoenix Entry, Descent and Landing System Architecture

    NASA Technical Reports Server (NTRS)

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

    2008-01-01

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

  11. Avionics architecture studies for the entry research vehicle

    NASA Technical Reports Server (NTRS)

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

    1989-01-01

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

  12. Handling Qualities of a Capsule Spacecraft During Atmospheric Entry

    NASA Technical Reports Server (NTRS)

    Bilimoria, Karl D.; Mueller, Eric R.

    2010-01-01

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

  13. Escape from Human Immunodeficiency Virus Type 1 (HIV-1) Entry Inhibitors

    PubMed Central

    De Feo, Christopher J.; Weiss, Carol D.

    2012-01-01

    The human immunodeficiency virus (HIV) enters cells through a series of molecular interactions between the HIV envelope protein and cellular receptors, thus providing many opportunities to block infection. Entry inhibitors are currently being used in the clinic, and many more are under development. Unfortunately, as is the case for other classes of antiretroviral drugs that target later steps in the viral life cycle, HIV can become resistant to entry inhibitors. In contrast to inhibitors that block viral enzymes in intracellular compartments, entry inhibitors interfere with the function of the highly variable envelope glycoprotein as it continuously adapts to changing immune pressure and available target cells in the extracellular environment. Consequently, pathways and mechanisms of resistance for entry inhibitors are varied and often involve mutations across the envelope gene. This review provides a broad overview of entry inhibitor resistance mechanisms that inform our understanding of HIV entry and the design of new inhibitors and vaccines. PMID:23342377

  14. Deployable antenna kinematics using tensegrity structure design

    NASA Astrophysics Data System (ADS)

    Knight, Byron Franklin

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

  15. Entry, Descent, Landing Animation (Animation)

    NASA Technical Reports Server (NTRS)

    2005-01-01

    [figure removed for brevity, see original site] Click on the image for Entry, Descent, Landing animation

    This animation illustrates the path the Stardust return capsule will follow once it enters Earth's atmosphere.

  16. Atmospheric maneuvering during Martian entry

    NASA Astrophysics Data System (ADS)

    Tauber, Michael E.; Bowles, Jeffrey V.; Yang, Lily

    A comparative-advantages study is made of two different Martian atmospheric entry maneuvers, on the basis of calculation results for the case of a vehicle with a maximum L/D ratio of 2.3. Entries from a highly elliptical Martian orbit at 5 km/sec are more difficult than those from a lower altitude and speed orbit at 3.5 km/sec, due to their more stringent guidance requirements. Efforts to reduce the deceleration for the higher speed entry by lift-modulation achieved a 40-percent reduction, but at the cost of a 50-percent decrease in lateral range. The lower-speed entry's gliding trajectory is noted to encounter a far more benign atmospheric environment.

  17. Re-entry Experiment Launch

    NASA Video Gallery

    On August 10, 2009, NASA successfully launched the Inflatable Re-entry Vehicle Experiment (IRVE) and proved that spacecraft can use inflatable heat shields to reduce speed and provide protection du...

  18. Atmospheric Entry of Carbonate Micrometeoroids

    NASA Astrophysics Data System (ADS)

    Micca Longo, G.; Longo, S.

    2017-02-01

    Micrometeoroids have similarities in chemistry and mineralogy to the CI, CM, and CR chondrites. A first study of carbonate micrometeoroids atmospheric entry is performed. A thermal decomposition model of initially pure magnesium carbonate is proposed.

  19. 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

  20. A Rapidly Deployable Bridge System

    DTIC Science & Technology

    2013-01-15

    A Rapidly Deployable Bridge System Gareth R. Thomas1 and Bernard J. Sia2 1ATA Engineering, 11995 El Camino Real, San Diego, CA 92130; PH (858) 480...PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) ATA Engineering,11995 El Camino Real,San Diego,CA,92130 8. PERFORMING ORGANIZATION REPORT NUMBER

  1. HCPV deployment by Aerojet Rocketdyne

    NASA Astrophysics Data System (ADS)

    McDowell, Michael; Miner, Kris; Ghosal, Kanchan; Lilly, Doug

    2014-09-01

    Aerojet Rocketdyne (AR), with essential support from HCPV module supplier, Semprius, is implementing a HCPV commercialization process by deploying HCPV systems of increasing scope and size. The process is designed to gather field data, create learning opportunities and reduce risk while leading to large scale commercial field of HCPV systems. The process steps, key lessons learned, performance data and design decisions are presented.

  2. Lightweight, Self-Deployable Wheels

    NASA Technical Reports Server (NTRS)

    Chmielewski, Artur; Sokolowski, Witold; Rand, Peter

    2003-01-01

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

  3. Space deployable truss structure design

    NASA Technical Reports Server (NTRS)

    Coyner, J. V., Jr.; Tobey, W. H.

    1981-01-01

    The development status of the deployable box truss structure is summarized. Potential applications for this structural system are described. Structural and component design requirements derived from these applications are discussed. Components of prototype 4.6 m cubes which incorporate graphite/epoxy structural members, fittings, and mechanisms are described. The benefits of the component designs and their respective manufacturing processes are presented.

  4. OMV Deployed From Space Station

    NASA Technical Reports Server (NTRS)

    1986-01-01

    In this 1986 artist's concept, the Orbital Maneuvering Vehicle (OMV), at right, prepares to reboost the Hubble Space Telescope after being deployed from an early Space Station configuration (left). As envisioned by Marshall Space Flight Center plarners, the OMV would be a remotely-controlled free-flying space tug which would place, rendezvous, dock, and retrieve orbital payloads.

  5. Military Deployments: Evaluating Teacher Knowledge

    ERIC Educational Resources Information Center

    Thomas, Richard M.

    2011-01-01

    This mixed method study examined the possible influence of a military deployment online tutorial on teacher knowledge. DoDEA and public school teachers were the two groups used for the study. From this exploratory study, the researcher also wanted to explore if teachers would find professional development provided in an online tutorial relevant…

  6. Optimal deployment of missile interceptors

    SciTech Connect

    Bohachevsky, I.O.; Johnson, M.E.; Stein, M.L.

    1987-03-01

    Ballistic missile defenses composed of one- and two layers of interceptors that protect multiple assets from attacks by several types of warheads are modeled mathematically. Investigated are the most effective divisions of resources between midcourse and terminal defenses and the optimal deployments of terminal interceptors.

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

    NASA Technical Reports Server (NTRS)

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

    2006-01-01

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

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

    NASA Technical Reports Server (NTRS)

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

    2007-01-01

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

  9. Advances in Anesthesia Delivery in the Deployed Setting.

    PubMed

    Wilson, John E; Barras, William P

    2016-01-01

    Lessons learned over the past decade and a half of combat casualty management has brought about numerous advances in trauma anesthesia practice. In the post-Vietnam era, deployable anesthesia equipment centered on the capability to provide a balanced anesthetic technique, utilizing a combination of volatile gas and intravenous anesthetic adjuncts. The evolution of the modern battlefield has forced anesthesia providers across the military to adapt to mission requirements that often dictate a surgical capability that is more rapidly mobile and less reliant on logistical support. Institutional medical equipment development has focused on fielding a lighter, more mobile volatile gas delivery method. Despite numerous advances in anesthetic gas delivery, many veteran anesthesia providers have come to recognize the value of alternative anesthetic techniques in the deployed setting. One of the most appealing advances in combat anesthesia practice is the emergence of total intravenous anesthetics (TIVA) for trauma management and resuscitation. Although there have been numerous developments in anesthetic equipment for use in the deployed setting, TIVA has many advantages over volatile gas administration. Future research, development, and education should focus on TIVA and the ability to provide this as an alternative safe anesthetic for patients in austere environments. It is imperative to retain the lessons we have learned in order to adapt more effectively in future conflicts. This accumulation of knowledge must inform future innovative solutions to the challenges of casualty management in a deployed setting.

  10. 19 CFR 191.143 - Drawback entry.

    Code of Federal Regulations, 2014 CFR

    2014-04-01

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

  11. 19 CFR 191.143 - Drawback entry.

    Code of Federal Regulations, 2013 CFR

    2013-04-01

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

  12. 19 CFR 191.143 - Drawback entry.

    Code of Federal Regulations, 2012 CFR

    2012-04-01

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

  13. 19 CFR 191.143 - Drawback entry.

    Code of Federal Regulations, 2010 CFR

    2010-04-01

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

  14. 19 CFR 191.143 - Drawback entry.

    Code of Federal Regulations, 2011 CFR

    2011-04-01

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

  15. Lunar Entry Downmode Options for Orion

    NASA Technical Reports Server (NTRS)

    Smith, Kelly; Rea, Jeremy

    2016-01-01

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

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

    PubMed

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

    2015-10-01

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

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

    PubMed Central

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

    2015-01-01

    The ongoing Ebola virus (EBOV) disease (EVD) epidemic in Western Africa is the largest EVD outbreak recorded to date and requires the rapid development and deployment of antiviral measures. The viral glycoprotein (GP) facilitates host cell entry and, jointly with cellular interaction partners, constitutes a potential target for antiviral intervention. However, it is unknown whether the GPs of the currently and previously circulating EBOVs use the same mechanisms for cellular entry and are thus susceptible to inhibition by the same antivirals and cellular defenses. Here, we show that the GPs of the EBOVs circulating in 1976 and 2014 transduce the same spectrum of target cells, use the same cellular factors for host cell entry, and are comparably susceptible to blockade by antiviral interferon-induced transmembrane proteins and neutralizing antibody KZ52. Thus, the viruses responsible for the ongoing EVD epidemic should be fully susceptible to established antiviral strategies targeting GP and cellular entry factors. PMID:25840443

  18. 19 CFR 142.16 - Entry summary documentation.

    Code of Federal Regulations, 2010 CFR

    2010-04-01

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

  19. Promoting international deployment of greenhouse gas technologies

    SciTech Connect

    Brown, M.A.; Kelley, J.S.; Voss, M.K.

    1995-12-31

    Increasing emission of greenhouse gases from human activities are predicted to lead to significant global warming and possible undesirable Environmental effects by the middle of the next century. These gases trap solar energy that is reradiated from the earth`s surface, raising its temperature. The gases-carbon dioxide, methane, nitrous oxide, and chlorofluorocarbons (CFCs)-are emitted as the result of a wide range of anthropogenic activities, including the production and conversion of energy from fossil fuels, the operation of air conditioning and refrigeration equipment, and coal mining, domestic sewage treatment, and the manufacture of cement and nylon. To slow global warming, technologies are being developed, promoted, and deployed to reduce these emissions. To make a practical response to global environmental issues such as greenhouse gas emissions, it is recognized that international collaboration is needed. Because of the accelerating pace of technology innovation and the increasingly interconnected world economy, national efforts to adapt to global environmental challenges are no longer sufficient. Through international collaboration, scarce resources can be shared and technological solutions can be adapted and replicated. ORNL is responsible for managing and supporting the U.S, involvement in many of the implementing agreements. In addition to collaborating with GREENTIE, ORNL is involved with the following other IEA implementing agreements, either as executive committee members, national team leaders, or operating agents: the Center for the Analysis and Dissemination of Demonstrated Energy Technologies, Heat Pump Program, Buildings and Community Systems, Alternative Motor Fuels, and Fusion Energy Stellerator Concept.

  20. Rapidly deployable emergency communication system

    DOEpatents

    Gladden, Charles A.; Parelman, Martin H.

    1979-01-01

    A highly versatile, highly portable emergency communication system which permits deployment in a very short time to cover both wide areas and distant isolated areas depending upon mission requirements. The system employs a plurality of lightweight, fully self-contained repeaters which are deployed within the mission area to provide communication between field teams, and between each field team and a mobile communication control center. Each repeater contains a microcomputer controller, the program for which may be changed from the control center by the transmission of digital data within the audible range (300-3,000 Hz). Repeaters are accessed by portable/mobile transceivers, other repeaters, and the control center through the transmission and recognition of digital data code words in the subaudible range.

  1. Arusha Rover Deployable Medical Workstation

    NASA Technical Reports Server (NTRS)

    Boswell, Tyrone; Hopson, Sonya; Marzette, Russell; Monroe, Gilena; Mustafa, Ruqayyah

    2014-01-01

    The NSBE Arusha rover concept offers a means of human transport and habitation during long-term exploration missions on the moon. This conceptual rover calls for the availability of medical supplies and equipment for crew members in order to aid in mission success. This paper addresses the need for a dedicated medical work station aboard the Arusha rover. The project team investigated multiple options for implementing a feasible deployable station to address both the medical and workstation layout needs of the rover and crew. Based on layout specifications and medical workstation requirements, the team has proposed a deployable workstation concept that can be accommodated within the volumetric constraints of the Arusha rover spacecraft

  2. Automated Anti-Virus Deployment

    DTIC Science & Technology

    2004-11-01

    External collaborators and visitors also need to keep in contact with their home laboratories or institutes, using the Internet to exchange e - mails or...layered defence system deployed with other components like host or network- based intrusion detection, global and personal firewalls, logical network...and provides the standard services that are requested to a modern enterprise network: office automation, e - mail , Internet access and workgroup file

  3. Sequential deployment of truss structures

    NASA Technical Reports Server (NTRS)

    Hedgebeth, J. M.

    1982-01-01

    The geometry investigated most intensively was the triangular tetrahedral truss. A square type truss having the same topology was also investigated. The tetrahedral truss is composed of surface struts and core members. In the deployable form, the entire truss is viewed as being made up of a number of parallel truss ribs connected to each other by interrib struts and members. The packaging efficiency of the truss was evaluated.

  4. Air Deployed Oceanographic Mooring (ADOM).

    DTIC Science & Technology

    1983-08-01

    Ocean Electronic Applications, Inc. Naval Air Development Center 50 W. Mashta Drive, 44, Key Biscayne , F. 33149 Warminster, PA 18974 Summ ary program...or in the bomb bay . Dimensions were limited to tution (Mooring Mechanics). The University of Miami 330 cm (130 in.) in length, 71 cm (28 in.) in dia... Biscayne , Florida. Data was tele- attaching the ADOM to the cross. The 1981 deployment metered over a three day period. The data is demon- was only

  5. Deployable M-Braced Truss

    NASA Technical Reports Server (NTRS)

    Mikulas, M. M., Jr.; Rhodes, M. D.

    1985-01-01

    Tension/compression and shear separated structurally in deployable beam. M-Braced Sections Packaged using combination of hinges and telescoping sections. When upper sections telescope into base, diagonals hinge, telescope, and rotate along batten. Components of M-braced truss fabricated from conventional metallic materials or nonmetallic materials such as graphite/epoxy. Applications include masts for antenna feed horns and ribs for solar array blankets.

  6. Lifecycle Readiness and Ship Deployment

    DTIC Science & Technology

    2013-06-01

    The physical fatigue associated with ship motions has significant consequences for today’s minimally manned ships. “Because of minimally sized...a deployment. The inefficiencies in performance may develop from lack of training, different personal aptitude, and individual’s mental or physical ...exacerbation of symptoms known as the avalanche phenomenon follows which includes: increased salivation, bodily warmth , and light- headedness” (Stevens

  7. Expected Deployment Dynamics of Proseds

    NASA Technical Reports Server (NTRS)

    Lorenzini, E. C.; Cosmo, M. L.; Welzyn, K.

    2003-01-01

    The control law for The Propulsive Small Expendable Deployment System (ProSEDS) deployment is a modification of the control routine that was successfully used in the flight of SEDS-II. Unlike SEDS, the tether of ProSEDS consists of different sections with different mechanical characteristics. A non-linear control trajectory in phase-space (i.e., the reference profile) is fed forward to the controller to guide the satellite, at the tether tip, to the desired final state under nominal conditions and no external perturbations. A linear feedback control is applied by the brake to keep the actual trajectory as close as possible to the reference. The paper also shows the results of simulations of deployment dynamics with and without noise. The control law has thus far been developed and tested on the ground for the original ProSEDS tether configuration of 15 km. A new reference will have to be designed and tested for other tether configurations.

  8. Design of amall deployable satellite

    NASA Astrophysics Data System (ADS)

    Zumbo, S.; Leofanti, J.; Corradi, S.; Allegri, G.; Marchetti, M.

    2003-08-01

    One of the scientific satellite programmes of Rome University "La Sapienza", called DeSat, is here reported, with major emphasis on the mechanical and structure subsystems. The principal payload of the entire system is represented by a titanium recirculating ball screw boom whose mass reaches one third of the total mass budget. The goal of the mission is to space qualify a new micro-satellite multipurpose platform, called LEO-MicroBAR, and to qualify the titanium linear actuator. Both the two systems have been developed by the Aerospace and Astronautics Engineering Department (AAED). The boom will be used to investigate the validity of its design for space applications, like precise off platform positioning of devices and instruments, GPS interferometry, sensor measurements and robotics. It will be shielded against space interactions by a titanium bellow system whose main functions will be impact protection, antirotation, boom passive thermal control. The satellite geometry, when the boom is in deployed configuration, is highly stretched and the name "deployable satellite" was natural. The large deployment mechanism, compared to the small bus, has influenced the design of every satellite subsystem leading to innovative solutions in terms of design, materials, equipment and instruments.

  9. 19 CFR 143.36 - Form of immediate delivery, entry and entry summary.

    Code of Federal Regulations, 2010 CFR

    2010-04-01

    ... 19 Customs Duties 2 2010-04-01 2010-04-01 false Form of immediate delivery, entry and entry summary. 143.36 Section 143.36 Customs Duties U.S. CUSTOMS AND BORDER PROTECTION, DEPARTMENT OF HOMELAND SECURITY; DEPARTMENT OF THE TREASURY (CONTINUED) SPECIAL ENTRY PROCEDURES Electronic Entry Filing § 143.36 Form of immediate delivery, entry and...

  10. Technology transfer for adaptation

    NASA Astrophysics Data System (ADS)

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

    2014-09-01

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

  11. Dissecting Virus Entry: Replication-Independent Analysis of Virus Binding, Internalization, and Penetration Using Minimal Complementation of β-Galactosidase

    PubMed Central

    Burkard, Christine; Bloyet, Louis-Marie; Wicht, Oliver; van Kuppeveld, Frank J.; Rottier, Peter J. M.; de Haan, Cornelis A. M.; Bosch, Berend Jan

    2014-01-01

    Studies of viral entry into host cells often rely on the detection of post-entry parameters, such as viral replication or the expression of a reporter gene, rather than on measuring entry per se. The lack of assays to easily detect the different steps of entry severely hampers the analysis of this key process in virus infection. Here we describe novel, highly adaptable viral entry assays making use of minimal complementation of the E. coli β-galactosidase in mammalian cells. Enzyme activity is reconstituted when a small intravirion peptide (α-peptide) is complementing the inactive mutant form ΔM15 of β-galactosidase. The method allows to dissect and to independently detect binding, internalization, and fusion of viruses during host cell entry. Here we use it to confirm and extend current knowledge on the entry process of two enveloped viruses: vesicular stomatitis virus (VSV) and murine hepatitis coronavirus (MHV). PMID:25025332

  12. The water entry of water

    NASA Astrophysics Data System (ADS)

    Speirs, Nathan; Pan, Zhao; Belden, Jesse; Truscott, Tadd

    2016-11-01

    Though water entry has been studied for over a century, there has been a disconnect between solid object water entry and research on liquid impacting on a liquid pool. In addition, few have studied multiple objects impacting a liquid bath sequentially. We show that the impact of multi-droplet streams and liquid jets on a liquid pool display similar behavior to solid body water entry. In particular, the cavities of both droplet streams and jets exhibit three types of cavity seal previously found for hydrophobic spheres at low Bond numbers. Additionally, low-frequency droplet streams create three novel cavity seal types, which can be predicted with a new non-dimensional frequency. The cavity depth for both droplet and jet impact is rationalized by an energy scaling analysis. Finally, we examine the similarities and differences in cavity dynamics for multi-droplet streams and continuous liquid jets.

  13. Stabilometric Platform Measurements to Determine Post-Deployment Adaptation

    DTIC Science & Technology

    2011-04-01

    of economic loss and if they had social support. The results were that 22.1% exhibited little or no symptoms of traumatic stress, 13.5% exhibited...trauma from an abusive past. Ozer, E.J., Best, S.R., & Lipsey , T.L. (2008). Predictors of posttraumatic stress disorder and symptoms in

  14. A Self-Deploying, Depth-Adaptive Coastal Oceanographic Mooring

    DTIC Science & Technology

    2007-11-02

    Institution Woods Hole, MA RICHARD BURNES Neptune Sciences, Inc. Slidell, LA BRUCE BRICKER Planning Systems Inc. Long Beach, MS April 27, 1998...Boyd, Daniel E. Frye*, Don Peters*, Richard Arthur*, Richard Burnest, Bruce Brickerft 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) Naval...WITH CONDUCTIVITY/TEMPERATURE 11 THERMISTORS AT 2.5 METERS (PROTOTYPE CONFIGURATION) INDUCTIVE MODEM TUCK ’ WITH CTD 11 THERMISTORS AT 5 METERS

  15. Adaptive Introspection and Deployment for Robust Long Duration Autonomy

    DTIC Science & Technology

    2014-09-30

    Duration Autonomy Nathan Michael, Sebastian Scherer Carnegie Mellon University 5000 Forbes Avenue Pittsburgh PA, 15213-3890 phone: (412) 268...7816 fax: (412) 268-1338 email: nmichael@cmu.edu, scherer@cmu.edu Award Number: N000141310821 LONG-TERM GOALS Long duration autonomy ...integrative experimental framework toward evaluating the approaches developed through the first two tasks. Task 1: Introspection for Robust Autonomy

  16. 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.

  17. 19 CFR 141.64 - Review and correction of entry and entry summary documentation.

    Code of Federal Regulations, 2010 CFR

    2010-04-01

    ... SECURITY; DEPARTMENT OF THE TREASURY (CONTINUED) ENTRY OF MERCHANDISE Presentation of Entry Papers § 141.64... be reviewed before acceptance to ensure that all entry and statistical requirements are complied...

  18. Post-Flight EDL Entry Guidance Performance for the 2011 Mars Science Laboratory Mission

    NASA Technical Reports Server (NTRS)

    Mendeck, G.; McGrew, L.

    2013-01-01

    Mars Science Laboratory landed Curiosity in Gale Crater on 5 Aug 2012. Curiosity landed successfully only 2.2 km away from the expected target given the onboard navigation state. Better than the average Apollo capsule splashdown miss distance. A late bank reversal and a suspected tail wind contributed to this slight miss. Entry guidance is derived from the Apollo capsule "final phase" logic and adjusts the range flown during entry by varying the direction of the lift vector (i.e., bank angle). Refinement of the guidance gains and alternative parachute deploy triggers to reduce the ellipse size will be studied for future Mars landing missions.

  19. RSG Deployment Case Testing Results

    SciTech Connect

    Owsley, Stanley L.; Dodson, Michael G.; Hatchell, Brian K.; Seim, Thomas A.; Alexander, David L.; Hawthorne, Woodrow T.

    2005-09-01

    The RSG deployment case design is centered on taking the RSG system and producing a transport case that houses the RSG in a safe and controlled manner for transport. The transport case was driven by two conflicting constraints, first that the case be as light as possible, and second that it meet a stringent list of Military Specified requirements. The design team worked to extract every bit of weight from the design while striving to meet the rigorous Mil-Spec constraints. In the end compromises were made primarily on the specification side to control the overall weight of the transport case. This report outlines the case testing results.

  20. Numerical Skip-Entry Guidance

    NASA Technical Reports Server (NTRS)

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

    2006-01-01

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

  1. Planetary Landers and Entry Probes

    NASA Astrophysics Data System (ADS)

    Ball, Andrew J.; Garry, James R. C.; Lorenz, Ralph D.; Kerzhanovich, Viktor V.

    2007-05-01

    Preface; Acknowledgements; Part I. Engineering Issues Specific to Entry Probes, Landers or Penetrators: 1. Mission goals and system engineering; 2. Accommodation, launch, cruise and arrival from orbit or interplanetary trajectory; 3. Entering atmospheres; 4. Descent through an atmosphere; 5. Descent to an airless body; 6. Planetary balloons, aircraft, submarines and cryobots; 7. Arrival at a surface; 8. Thermal control of landers and entry probes; 9. Power systems; 10. Communication and tracking of entry probes; 11. Radiation environment; 12. Surface activities: arms, drills, moles and mobility; 13. Structures; 14. Contamination of spacecraft and planets; Part II. Previous Atmosphere/Surface Vehicles and Their Payloads: 15. Destructive impact probes; 16. Atmospheric entry probes; 17. Pod landers; 18. Legged landers; 19. Payload delivery penetrators; 20. Small body surface missions; Part III. 'Case Studies': 21. Surveyor landers; 22. Galileo probe; 23. Huygens; 24. Mars Pathfinder and Sojourner; 25. Deep Space 2 Mars microprobes; 26. Rosetta lander Philae; 27. Mars exploration rovers: Spirit and Opportunity; Appendix: Some key parameters for bodies in the Solar System; List of acronyms; Bibliography; References; Index.

  2. Planetary Landers and Entry Probes

    NASA Astrophysics Data System (ADS)

    Ball, Andrew; Garry, James; Lorenz, Ralph; Kerzhanovich, Viktor

    2010-02-01

    Preface; Acknowledgements; Part I. Engineering Issues Specific to Entry Probes, Landers or Penetrators: 1. Mission goals and system engineering; 2. Accommodation, launch, cruise and arrival from orbit or interplanetary trajectory; 3. Entering atmospheres; 4. Descent through an atmosphere; 5. Descent to an airless body; 6. Planetary balloons, aircraft, submarines and cryobots; 7. Arrival at a surface; 8. Thermal control of landers and entry probes; 9. Power systems; 10. Communication and tracking of entry probes; 11. Radiation environment; 12. Surface activities: arms, drills, moles and mobility; 13. Structures; 14. Contamination of spacecraft and planets; Part II. Previous Atmosphere/Surface Vehicles and Their Payloads: 15. Destructive impact probes; 16. Atmospheric entry probes; 17. Pod landers; 18. Legged landers; 19. Payload delivery penetrators; 20. Small body surface missions; Part III. 'Case Studies': 21. Surveyor landers; 22. Galileo probe; 23. Huygens; 24. Mars Pathfinder and Sojourner; 25. Deep Space 2 Mars microprobes; 26. Rosetta lander Philae; 27. Mars exploration rovers: Spirit and Opportunity; Appendix: Some key parameters for bodies in the Solar System; List of acronyms; Bibliography; References; Index.

  3. Lifting Entry & Atmospheric Flight (LEAF) Applications at Solar System Bodies.

    NASA Astrophysics Data System (ADS)

    Lee, G.; Sen, B.; Polidan, R. S.

    2015-12-01

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

  4. Deployment Mechanism for Thermal Pointing System

    NASA Technical Reports Server (NTRS)

    Koski, Kraig

    2014-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Johnson, Joel A.

    2008-01-01

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

  6. Fabrication and Testing of a Passive Re-Deployable Radiator for Autonomous Thermal Control

    NASA Astrophysics Data System (ADS)

    Nagano, Hosei; Matsumoto, Kan; Ohnishi, Akira; Higuchi, Ken; Nagasaka, Yuji

    2007-01-01

    This paper presents the development of a lightweight 100W-class re-deployable radiator with environment-adaptive functions. This radiator, reversible thermal panel (RTP), which consists of flexible high thermal conductive graphite sheets and a single crystal shape memory alloy as a passive reversible actuator, changes its function from a radiator to a solar absorber by deploying/stowing the reversible fin upon changes in the heat dissipation and thermal environment. A deployment/stowing test in atmospheric condition and a thermal vacuum test were conducted. The fin deployment angle could be changed from 0 deg to 140 deg with the change of the RTP temperature from -40 C to +40 C in the deployment/stowing test using a constant temperature chamber. Autonomous thermal control function was demonstrated in the thermal vacuum test although the fin could not be entirely stowed under cold condition.

  7. 19 CFR 141.91 - Entry without required invoice.

    Code of Federal Regulations, 2010 CFR

    2010-04-01

    ... summary (or the entry, if there is no entry summary) documentation, unless the invoice is needed for... the date of the entry summary (or the entry, if there is no entry summary) is required to be filed... required invoice is not available in proper form at the time the entry or entry summary documentation...

  8. Treatment of PTSD-Related Anger in Troops Returning From Hazardous Deployments

    DTIC Science & Technology

    2009-03-01

    are to 1) adapt an existing evidence-based cognitive-behavioral intervention (CBI) for the treatment of anger to specific needs of military personnel... Treatment of Trauma Related Anger in Troops Returning from Hazardous Deployments. Association for Behavioral and Cognitive Therapy Annual Meeting, Orlando...AD Award Number: W81XWH-05-1-0171 TITLE: “ Treatment of PTSD-Related Anger in Troops Returning From Hazardous Deployments

  9. The role of digital data entry in participatory environmental monitoring.

    PubMed

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

    2016-12-01

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

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

    NASA Technical Reports Server (NTRS)

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

    2011-01-01

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

  11. 19 CFR 149.6 - Entry and entry summary documentation and Importer Security Filing submitted via a single...

    Code of Federal Regulations, 2010 CFR

    2010-04-01

    ... 19 Customs Duties 2 2010-04-01 2010-04-01 false Entry and entry summary documentation and Importer...) IMPORTER SECURITY FILING § 149.6 Entry and entry summary documentation and Importer Security Filing... of this part via the same electronic transmission as entry or entry/entry summary...

  12. 19 CFR 149.6 - Entry and entry summary documentation and Importer Security Filing submitted via a single...

    Code of Federal Regulations, 2013 CFR

    2013-04-01

    ... 19 Customs Duties 2 2013-04-01 2013-04-01 false Entry and entry summary documentation and Importer...) IMPORTER SECURITY FILING § 149.6 Entry and entry summary documentation and Importer Security Filing... of this part via the same electronic transmission as entry or entry/entry summary...

  13. 19 CFR 149.6 - Entry and entry summary documentation and Importer Security Filing submitted via a single...

    Code of Federal Regulations, 2014 CFR

    2014-04-01

    ... 19 Customs Duties 2 2014-04-01 2014-04-01 false Entry and entry summary documentation and Importer...) IMPORTER SECURITY FILING § 149.6 Entry and entry summary documentation and Importer Security Filing... of this part via the same electronic transmission as entry or entry/entry summary...

  14. 19 CFR 149.6 - Entry and entry summary documentation and Importer Security Filing submitted via a single...

    Code of Federal Regulations, 2011 CFR

    2011-04-01

    ... 19 Customs Duties 2 2011-04-01 2011-04-01 false Entry and entry summary documentation and Importer...) IMPORTER SECURITY FILING § 149.6 Entry and entry summary documentation and Importer Security Filing... of this part via the same electronic transmission as entry or entry/entry summary...

  15. 19 CFR 149.6 - Entry and entry summary documentation and Importer Security Filing submitted via a single...

    Code of Federal Regulations, 2012 CFR

    2012-04-01

    ... 19 Customs Duties 2 2012-04-01 2012-04-01 false Entry and entry summary documentation and Importer...) IMPORTER SECURITY FILING § 149.6 Entry and entry summary documentation and Importer Security Filing... of this part via the same electronic transmission as entry or entry/entry summary...

  16. 32 CFR 770.28 - Entry restrictions.

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... LIMITING PUBLIC ACCESS TO PARTICULAR INSTALLATIONS Base Entry Regulations for Naval Installations in the... State of Hawaii, entry into a naval installation is not permitted without the permission of...

  17. 32 CFR 770.50 - Entry restrictions.

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ... LIMITING PUBLIC ACCESS TO PARTICULAR INSTALLATIONS Base Entry Regulations for Puget Sound Naval Shipyard, Bremerton, Washington § 770.50 Entry restrictions. Except for military personnel and civilian employees...

  18. 32 CFR 770.50 - Entry restrictions.

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... LIMITING PUBLIC ACCESS TO PARTICULAR INSTALLATIONS Base Entry Regulations for Puget Sound Naval Shipyard, Bremerton, Washington § 770.50 Entry restrictions. Except for military personnel and civilian employees...

  19. 32 CFR 770.50 - Entry restrictions.

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ... LIMITING PUBLIC ACCESS TO PARTICULAR INSTALLATIONS Base Entry Regulations for Puget Sound Naval Shipyard, Bremerton, Washington § 770.50 Entry restrictions. Except for military personnel and civilian employees...

  20. 32 CFR 770.50 - Entry restrictions.

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ... LIMITING PUBLIC ACCESS TO PARTICULAR INSTALLATIONS Base Entry Regulations for Puget Sound Naval Shipyard, Bremerton, Washington § 770.50 Entry restrictions. Except for military personnel and civilian employees...

  1. 32 CFR 770.50 - Entry restrictions.

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... LIMITING PUBLIC ACCESS TO PARTICULAR INSTALLATIONS Base Entry Regulations for Puget Sound Naval Shipyard, Bremerton, Washington § 770.50 Entry restrictions. Except for military personnel and civilian employees...

  2. Mars pathfinder lander deployment mechanisms

    NASA Technical Reports Server (NTRS)

    Gillis-Smith, Greg R.

    1996-01-01

    The Mars Pathfinder Lander employs numerous mechanisms, as well as autonomous mechanical functions, during its Entry, Descent and Landing (EDL) Sequence. This is the first US lander of its kind, since it is unguided and airbag-protected for hard landing using airbags, instead of retro rockets, to soft land. The arrival condition, location, and orientation of the Lander will only be known by the computer on the Lander. The Lander will then autonomously perform the appropriate sequence to retract the airbags, right itself, and open, such that the Lander is nearly level with no airbag material covering the solar cells. This function uses two different types of mechanisms - the Airbag Retraction Actuators and the Lander Petal Actuators - which are designed for the high torque, low temperature, dirty environment and for limited life application. The development of these actuators involved investigating low temperature lubrication, Electrical Discharge Machining (EDM) to cut gears, and gear design for limited life use.

  3. Overview of entry risk predictions

    NASA Astrophysics Data System (ADS)

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

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

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

    NASA Technical Reports Server (NTRS)

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

    1984-01-01

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

  5. Visual Analysis in a Deployable Antenna Experiment

    NASA Astrophysics Data System (ADS)

    Kimura, S.; Takeuchi, M.; Fukase, Y.; Harima, K.; Sato, H.; Yoshida, T.

    2002-01-01

    in space under the size constraints of available delivery vehicles. A large space antenna should make it possible to improve the telecommunication bandwidth and reduce the size of ground terminals. reliable and precise deployment. Since the antenna is a highly complex structure, monitoring the deployment process and the detection of anomalies are also important. The deployed antenna should be collimated to achieve its optimal performance. such as tension and acceleration sensors. With a visual analysis, we can acquire information at many locations without complex wiring, which can increase the complexity of the system. Therefore, visual analysis should be used in conjunction with other methods for monitoring large deployable antennas. combination of cross-correlations between images and approximation at sub-pixel precision enables us to detect shifts in images with a precision of up to 0.01 pixels. This method is effective for monitoring and collimation of a deployable antenna. broadcast technologies which was developed by the National Space Development Agency of Japan (NASDA) under the cooperation with Communications Research Lab. and NTT Network Innovation Lab.. One of the most important missions of ETS-VIII is to construct a large deployable antenna for S-band telecommunication. In December 2001, the LDREX mission, which was a preliminary experiment for the large deployable antenna of ETS-VIII , was performed as an Ariane-5 auxiliary payload (ASAP). A 6m scale model of the ETS-VIII deployable antenna was launched and deployed in geo-transfer orbit (GTO). During this experiment, anomalies occurred in the deployable antenna, and deployment was aborted. analysis method. Using this analysis, we detected vibrating features of the deployable antenna , which were useful for explaining the anomalies deployable antenna.

  6. 32 CFR 809a.3 - Unauthorized entry.

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ... 32 National Defense 6 2013-07-01 2013-07-01 false Unauthorized entry. 809a.3 Section 809a.3 National Defense Department of Defense (Continued) DEPARTMENT OF THE AIR FORCE ADMINISTRATION INSTALLATION ENTRY POLICY, CIVIL DISTURBANCE INTERVENTION AND DISASTER ASSISTANCE Installation Entry Policy §...

  7. 19 CFR 122.42 - Aircraft entry.

    Code of Federal Regulations, 2010 CFR

    2010-04-01

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

  8. 32 CFR 770.18 - Entry restrictions.

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ... LIMITING PUBLIC ACCESS TO PARTICULAR INSTALLATIONS Base Entry Regulations for Naval Submarine Base, Bangor, Silverdale, Washington § 770.18 Entry restrictions. Except for military personnel and civilian employees of the United States in the performance of their official duties, entry upon Naval Submarine Base,...

  9. 32 CFR 770.18 - Entry restrictions.

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... LIMITING PUBLIC ACCESS TO PARTICULAR INSTALLATIONS Base Entry Regulations for Naval Submarine Base, Bangor, Silverdale, Washington § 770.18 Entry restrictions. Except for military personnel and civilian employees of the United States in the performance of their official duties, entry upon Naval Submarine Base,...

  10. 32 CFR 770.18 - Entry restrictions.

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ... LIMITING PUBLIC ACCESS TO PARTICULAR INSTALLATIONS Base Entry Regulations for Naval Submarine Base, Bangor, Silverdale, Washington § 770.18 Entry restrictions. Except for military personnel and civilian employees of the United States in the performance of their official duties, entry upon Naval Submarine Base,...

  11. 32 CFR 770.18 - Entry restrictions.

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ... LIMITING PUBLIC ACCESS TO PARTICULAR INSTALLATIONS Base Entry Regulations for Naval Submarine Base, Bangor, Silverdale, Washington § 770.18 Entry restrictions. Except for military personnel and civilian employees of the United States in the performance of their official duties, entry upon Naval Submarine Base,...

  12. 32 CFR 770.18 - Entry restrictions.

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... LIMITING PUBLIC ACCESS TO PARTICULAR INSTALLATIONS Base Entry Regulations for Naval Submarine Base, Bangor, Silverdale, Washington § 770.18 Entry restrictions. Except for military personnel and civilian employees of the United States in the performance of their official duties, entry upon Naval Submarine Base,...

  13. 32 CFR 770.51 - Entry procedures.

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... 32 National Defense 5 2011-07-01 2011-07-01 false Entry procedures. 770.51 Section 770.51 National... ACCESS TO PARTICULAR INSTALLATIONS Base Entry Regulations for Puget Sound Naval Shipyard, Bremerton, Washington § 770.51 Entry procedures. (a) Any person or group of persons desiring the advance consent of...

  14. 32 CFR 770.51 - Entry procedures.

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ... 32 National Defense 5 2014-07-01 2014-07-01 false Entry procedures. 770.51 Section 770.51 National... ACCESS TO PARTICULAR INSTALLATIONS Base Entry Regulations for Puget Sound Naval Shipyard, Bremerton, Washington § 770.51 Entry procedures. (a) Any person or group of persons desiring the advance consent of...

  15. 32 CFR 770.51 - Entry procedures.

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... 32 National Defense 5 2010-07-01 2010-07-01 false Entry procedures. 770.51 Section 770.51 National... ACCESS TO PARTICULAR INSTALLATIONS Base Entry Regulations for Puget Sound Naval Shipyard, Bremerton, Washington § 770.51 Entry procedures. (a) Any person or group of persons desiring the advance consent of...

  16. 32 CFR 770.51 - Entry procedures.

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ... 32 National Defense 5 2012-07-01 2012-07-01 false Entry procedures. 770.51 Section 770.51 National... ACCESS TO PARTICULAR INSTALLATIONS Base Entry Regulations for Puget Sound Naval Shipyard, Bremerton, Washington § 770.51 Entry procedures. (a) Any person or group of persons desiring the advance consent of...

  17. 32 CFR 763.4 - Entry restrictions.

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... 32 National Defense 5 2011-07-01 2011-07-01 false Entry restrictions. 763.4 Section 763.4 National Defense Department of Defense (Continued) DEPARTMENT OF THE NAVY ISLANDS UNDER NAVY JURISDICTION RULES GOVERNING PUBLIC ACCESS Entry Regulations for Kaho'olawe Island, Hawaii § 763.4 Entry restrictions....

  18. 19 CFR 122.42 - Aircraft entry.

    Code of Federal Regulations, 2013 CFR

    2013-04-01

    ... 19 Customs Duties 1 2013-04-01 2013-04-01 false Aircraft entry. 122.42 Section 122.42 Customs... AIR COMMERCE REGULATIONS Aircraft Entry and Entry Documents; Electronic Manifest Requirements for Passengers, Crew Members, and Non-Crew Members Onboard Commercial Aircraft Arriving In, Continuing...

  19. 19 CFR 122.42 - Aircraft entry.

    Code of Federal Regulations, 2012 CFR

    2012-04-01

    ... 19 Customs Duties 1 2012-04-01 2012-04-01 false Aircraft entry. 122.42 Section 122.42 Customs... AIR COMMERCE REGULATIONS Aircraft Entry and Entry Documents; Electronic Manifest Requirements for Passengers, Crew Members, and Non-Crew Members Onboard Commercial Aircraft Arriving In, Continuing...

  20. 19 CFR 122.42 - Aircraft entry.

    Code of Federal Regulations, 2014 CFR

    2014-04-01

    ... 19 Customs Duties 1 2014-04-01 2014-04-01 false Aircraft entry. 122.42 Section 122.42 Customs... AIR COMMERCE REGULATIONS Aircraft Entry and Entry Documents; Electronic Manifest Requirements for Passengers, Crew Members, and Non-Crew Members Onboard Commercial Aircraft Arriving In, Continuing...

  1. 19 CFR 122.42 - Aircraft entry.

    Code of Federal Regulations, 2011 CFR

    2011-04-01

    ... 19 Customs Duties 1 2011-04-01 2011-04-01 false Aircraft entry. 122.42 Section 122.42 Customs... AIR COMMERCE REGULATIONS Aircraft Entry and Entry Documents; Electronic Manifest Requirements for Passengers, Crew Members, and Non-Crew Members Onboard Commercial Aircraft Arriving In, Continuing...

  2. 10 CFR 1048.3 - Unauthorized entry.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

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

  3. 10 CFR 1048.3 - Unauthorized entry.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

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

  4. Passive Earth Entry Vehicle Landing Test

    NASA Technical Reports Server (NTRS)

    Kellas, Sotiris

    2017-01-01

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

  5. Method for deploying multiple spacecraft

    NASA Technical Reports Server (NTRS)

    Sharer, Peter J. (Inventor)

    2007-01-01

    A method for deploying multiple spacecraft is disclosed. The method can be used in a situation where a first celestial body is being orbited by a second celestial body. The spacecraft are loaded onto a single spaceship that contains the multiple spacecraft and the spacecraft is launched from the second celestial body towards a third celestial body. The spacecraft are separated from each other while in route to the third celestial body. Each of the spacecraft is then subjected to the gravitational field of the third celestial body and each of the spacecraft assumes a different, independent orbit about the first celestial body. In those situations where the spacecraft are launched from Earth, the Sun can act as the first celestial body, the Earth can act as the second celestial body and the Moon can act as the third celestial body.

  6. 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.

  7. 19 CFR 143.36 - Form of immediate delivery, entry and entry summary.

    Code of Federal Regulations, 2011 CFR

    2011-04-01

    ... Form of immediate delivery, entry and entry summary. (a) Electronic form of data. If Customs determines... 19 Customs Duties 2 2011-04-01 2011-04-01 false Form of immediate delivery, entry and entry summary. 143.36 Section 143.36 Customs Duties U.S. CUSTOMS AND BORDER PROTECTION, DEPARTMENT OF...

  8. 76 FR 82315 - Agency Information Collection Activities: Entry/Immediate Delivery Application and Simplified Entry

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-12-30

    ... Delivery Application and Simplified Entry AGENCY: U.S. Customs and Border Protection, Department of... Delivery Application (Forms 3461 and 3461 ALT) and Simplified Entry. This is a proposed revision and... forms of information. Title: Entry/Immediate Delivery Application and Simplified Entry. OMB Number:...

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

    PubMed

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

    2016-07-01

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

  10. Orion Exploration Flight Test-1 Contingency Drogue Deploy Velocity Trigger

    NASA Technical Reports Server (NTRS)

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

    2013-01-01

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

  11. TQM and lean strategy deployment in Italian hospitals.

    PubMed

    Chiarini, Andrea; Baccarani, Claudio

    2016-10-03

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

  12. Re-entry residency training

    PubMed Central

    Jamieson, Jean L.; Webber, Eric M.; Sivertz, Kristin S.

    2010-01-01

    ABSTRACT OBJECTIVE To identify and quantify the reasons general practitioners and family physicians consider retraining and their reasons for not pursuing further training. DESIGN Population-based mailed survey. SETTING British Columbia. PARTICIPANTS Family physicians and general practitioners identified by the College of Physicians and Surgeons of British Columbia. MAIN OUTCOME MEASURES Practising physicians’ level of awareness of the University of British Columbia’s re-entry training program, the number and demographic characteristics of those who had considered retraining, their specialties of interest, and the barriers and possible inducements to retraining. RESULTS Only half of the survey respondents were aware of the re-entry training program at the University of British Columbia. A small but substantial number of practising general practitioners and family physicians were interested in taking specialty training from the Royal College of Physicians and Surgeons of Canada. While several training programs were particularly popular (ie, anesthesia and psychiatry—18.5% of respondents for each), almost every specialty training program was mentioned. Physicians identified the length and hours of training, financial issues, family issues, and the need for relocation as obstacles to retraining. The availability of part-time training, regional training, and return-of-service financial assistance were all identified as potential inducements. CONCLUSION To meet the needs of practising physicians, re-entry training programs will need to consider flexibility, where feasible, with regard to choice of specialty, intensity, and location of postgraduate training. PMID:20547505

  13. Fragmentation and ablation during entry

    SciTech Connect

    Canavan, G.H.

    1997-09-01

    This note discusses objects that both fragment and ablate during entry, using the results of previous reports to describe the velocity, pressure, and fragmentation of entering objects. It shows that the mechanisms used there to describe the breakup of non-ablating objects during deceleration remain valid for most ablating objects. It treats coupled fragmentation and ablation during entry, building on earlier models that separately discuss the entry of objects that are hard, whose high heat of ablation permits little erosion, and those who are strong whose strength prevents fragmentation, which are discussed in ``Radiation from Hard Objects,`` ``Deceleration and Radiation of Strong, Hard, Asteroids During Atmospheric Impact,`` and ``Meteor Signature Interpretation.`` This note provides a more detailed treatment of the further breakup and separation of fragments during descent. It replaces the constraint on mass per unit area used earlier to determine the altitude and magnitude of peak power radiation with a detailed analytic solution of deceleration. Model predictions are shown to be in agreement with the key features of numerical calculations of deceleration. The model equations are solved for the altitudes of maximum radiation, which agree with numerical integrations. The model is inverted analytically to infer object size and speed from measurements of peak power and altitude to provide a complete model for the approximate inversion of meteor data.

  14. Adapting Entry-Level Engineering Courses to Emphasize Critical Thinking

    ERIC Educational Resources Information Center

    Hagerty, D. Joseph; Rockaway, Thomas D.

    2012-01-01

    The University of Louisville recently developed a Quality Enhancement Plan (QEP) to improve undergraduate instruction across all disciplines as part of its ongoing accreditation requirements. Central elements of the plan are emphasis on critical thinking; integration of critical thinking throughout the curriculum; service learning for…

  15. 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.

  16. Deployable and retractable telescoping tubular structure development

    NASA Technical Reports Server (NTRS)

    Thomson, M. W.

    1994-01-01

    A new deployable and retractable telescoping boom capable of high deployed stiffness and strength is described. Deployment and retraction functions are controlled by simple, reliable, and fail-safe latches between the tubular segments. The latch and a BI-STEM (Storable Tubular Extendible Member) actuator work together to eliminate the need for the segments to overlap when deployed. This yields an unusually lightweight boom and compact launch configuration. An aluminum space-flight prototype with three joints displays zero structural deadband, low hysteresis, and high damping. The development approach and difficulties are discussed. Test results provide a joint model for sizing flight booms of any diameter and length.

  17. GPM Solar Array Gravity Negated Deployment Testing

    NASA Technical Reports Server (NTRS)

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

    2014-01-01

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

  18. Development of modular cable mesh deployable antenna

    NASA Astrophysics Data System (ADS)

    Meguro, Akira; Mitsugi, Jin; Andou, Kazuhide

    1993-03-01

    This report describes a concept and key technologies for the modular mesh deployable antenna. The antenna reflector composed of independently manufactured and tested modules is presented. Each module consists of a mesh surface, a cable network, and a deployable truss structure. The cable network comprises three kinds of cables, surface, tie, and back cables. Adjustment of tie cable lengths improves the surface accuracy. Synchronous deployment truss structures are considered as a supporting structure. Their design method, BBM's (Bread Board Model) and deployment analysis are also explained.

  19. Methods and Apparatus for Deployable Swirl Vanes

    NASA Technical Reports Server (NTRS)

    Shah, Parthiv N. (Inventor)

    2017-01-01

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

  20. Study on Low-ballistic-coefficient Atmospheric-entry Technology Using Flexible Aeroshell

    NASA Astrophysics Data System (ADS)

    Yamada, Kazuhiko; Kimura, Yusuke; Akita, Daisuke; Abe, Takashi; Suzuki, Kojiro; Imamura, Osamu; Koyama, Masashi; Hayashi, A. Koichi

    A Low-ballistic-coefficient atmospheric-entry technology using a flexible aeroshell is promising for a space transportation system because it can reduce the aerodynamic heating during re-entry and the terminal velocity dramatically. Its technology will lead to realize a safer, cheaper and more universal space transportation system. Our group has researched various important subjects in order to apply the flexible aeroshell to actual atmospheric-entry missions. Two topics of them are reported in this paper. First topic is a measurement of aerodynamic characteristics of the flare-type aeroshell. The relation between the Mach number and the drag coefficient of the capsule-type vehicle with the flexible and rigid flare-type aeroshell were obtained using the supersonic and transonic wind tunnel. Second topic is a development of the inflatable aeroshell. The deployment demonstration in a vacuum chamber and the structural tests of an inflatable torus tube were carried out.

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

    PubMed Central

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

    2014-01-01

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

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

    PubMed

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

    2014-12-01

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

  3. Coupled Elastic-Thermal Dynamics of Deployable Mesh Reflectors

    NASA Technical Reports Server (NTRS)

    Shi, H.; Yang, B.; Thomson, M.; Fang, H.

    2011-01-01

    This paper presents a coupled elastic-thermal dynamic model and a quasi-static strategy on the analysis of the reflector dynamics in the space mission. The linearized model, its natural frequencies and mode shapes are then derived upon the nonlinear static equilibrium of the structure. The numerical example is provided to fully adapt the strategy and investigate the dynamic behaviors of the structure. Finally the proposed method is applied on the sample of the deployable mesh reflector and the simulation results are presented. The research work delivered in the paper will be used to design the feedback surface in future.

  4. Atmospheric Entry Experiments at IRS

    NASA Astrophysics Data System (ADS)

    Auweter-Kurtz, M.; Endlich, P.; Herdrich, G.; Kurtz, H.; Laux, T.; Löhle, S.; Nazina, N.; Pidan, S.

    2002-01-01

    Entering the atmosphere of celestial bodies, spacecrafts encounter gases at velocities of several km/s, thereby being subjected to great heat loads. The thermal protection systems and the environment (plasma) have to be investigated by means of computational and ground facility based simulations. For more than a decade, plasma wind tunnels at IRS have been used for the investigation of TPS materials. Nevertheless, ground tests and computer simulations cannot re- place space flights completely. Particularly, entry mission phases encounter challenging problems, such as hypersonic aerothermodynamics. Concerning the TPS, radiation-cooled materials used for reuseable spacecrafts and ablator tech- nologies are of importance. Besides the mentioned technologies, there is the goal to manage guidance navigation, con- trol, landing technology and inflatable technologies such as ballutes that aim to keep vehicles in the atmosphere without landing. The requirement to save mass and energy for planned interplanetary missions such as Mars Society Balloon Mission, Mars Sample Return Mission, Mars Express or Venus Sample Return mission led to the need for manoeuvres like aerocapture, aero-breaking and hyperbolic entries. All three are characterized by very high kinetic vehicle energies to be dissipated by the manoeuvre. In this field flight data are rare. The importance of these manoeuvres and the need to increase the knowledge of required TPS designs and behavior during such mission phases point out the need of flight experiments. As result of the experience within the plasma diagnostic tool development and the plasma wind tunnel data base, flight experiments like the PYrometric RE-entry EXperiment PYREX were developed, fully qualified and successfully flown. Flight experiments such as the entry spectrometer RESPECT and PYREX on HOPE-X are in the conceptual phase. To increase knowledge in the scope of atmospheric manoeuvres and entries, data bases have to be created combining both

  5. Solar Adaptive Optics.

    PubMed

    Rimmele, Thomas R; Marino, Jose

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

  6. Mechanically scanned deployable antenna study

    NASA Technical Reports Server (NTRS)

    1983-01-01

    The conceptual design of a Mechanically Scanned Deployable Antenna which is launched by the STS (Space Shuttle) to provide radiometric brightness temperature maps of the Earth and oceans at selected frequency bands in the frequency range of 1.4 GHz to 11 GHz is presented. Unlike previous scanning radiometric systems, multiple radiometers for each frequency are required in order to fill in the resolution cells across the swath created by the 15 meter diameter spin stabilized system. This multiple beam radiometric system is sometimes designated as a ""whiskbroom'' system in that it combines the techniques of the scanning and ""pushbroom'' type systems. The definition of the feed system including possible feed elements and location, determination of the fundamental reflector feed offset geometry including offset angles and f/D ratio, preliminary estimates of the beam efficiency of the feed reflector system, a summary of reflector mesh losses at the proposed radiometric frequency bands, an overall conceptual configuration design and preliminary structural and thermal analyses are included.

  7. Gripper deploying and inverting linkage

    DOEpatents

    Minichan, R.L.; Killian, M.A.

    1993-03-02

    An end effector deploying and inverting linkage. The linkage comprises an air cylinder mounted in a frame or tube, a sliding bracket next to the air cylinder, a stopping bracket depending from the frame and three, pivotally-attached links that are attached to the end effector and to each other in such a way as to be capable of inverting the end effector and translating it laterally. The first of the three links is a straight element that is moved up and down by the shaft of the air cylinder. The second link is attached at one end to the stopping bracket and to the side of the end effector at the other end. The first link is attached near the middle of the second, sharply angled link so that, as the shaft of the air cylinder moves up and down, the second link rotates about an axis perpendicular to the frame and inverts and translates the end effector. The rotation of the second link is stopped at both ends when the link engages stops on the stopping bracket. The third link, slightly angled, is attached to the sliding bracket at one end and to the end of the end effector at the other. The third helps to control the end effector in its motion.

  8. Gripper deploying and inverting linkage

    DOEpatents

    Minichan, Richard L.; Killian, Mark A.

    1993-01-01

    An end effector deploying and inverting linkage. The linkage comprises an air cylinder mounted in a frame or tube, a sliding bracket next to the air cylinder, a stopping bracket depending from the frame and three, pivotally-attached links that are attached to the end effector and to each other in such a way as to be capable of inverting the end effector and translating it laterally. The first of the three links is a straight element that is moved up and down by the shaft of the air cylinder. The second link is attached at one end to the stopping bracket and to the side of the end effector at the other end. The first link is attached near the middle of the second, sharply angled link so that, as the shaft of the air cylinder moves up and down, the second link rotates about an axis perpendicular to the frame and inverts and translates the end effector. The rotation of the second link is stopped at both ends when the link engages stops on the stopping bracket. The third link, slightly angled, is attached to the sliding bracket at one end and to the end of the end effector at the other. The third helps to control the end effector in its motion.

  9. The Phys4Entry database

    NASA Astrophysics Data System (ADS)

    Laricchiuta, Annarita

    2012-10-01

    The Phys4Entry DB is a database of state-selected dynamical information for elementary processes relevant to the state-to-state kinetic modeling of planetary-atmosphere entry conditions. The DB is intended to the challenging goal of complementing the information in the existing web-access databases, collecting and validating data of collisional dynamics of elementary processes involving ground and excited chemical species, with resolution on the electronic, vibrational and rotational degrees of freedom. Four relevant classes of elementary processes are considered, i.e. electron-molecule collisions, atom/molecule-molecule collisions, atom/molecule surface interaction and photon-induced processes, constructing a taxonomy for process classification. Data populating the DB are largely originated by the coordinated research activity done in the frame of the Phys4Entry FP7 project, considering different theoretical approaches from quantum to semi-classical or quasi-classical molecular dynamics. Nevertheless the results, obtained in the Bari plasma chemistry labs in years of research devoted to the construction of reliable state-to-state kinetic models for hydrogen and air plasmas, are also transferred to the DB. Two DB interfaces have been created for different roles allowed to different actions: the contributor, uploading new processes, and the inquirer, submitting queries, to access the complete information about the records, through a graphical tool, displaying energy or roto-vibrational dependence of dynamical data, or through the export action to download ascii datafiles. The DB is expected to have a significant impact on the modeling community working also in scientific fields different from the aerothermodynamics (i.e. fusion, environment, ), making practicable the state-to-state approach.

  10. Atlas F entry aerothermic study

    NASA Technical Reports Server (NTRS)

    1972-01-01

    The feasibility of obtaining heat transfer data on an expended Atlas F booster launch vehicle was investigated in the altitude range of 300,000 to 200,000 feet during entry conditions, with a velocity in the range of 20,000 to 25,000 feet per second, and through a range of vehicle attitudes of plus or minus 90 degrees. These data are desired for correlation with turbulent heat transfer and boundary layer transition data obtained from wind tunnel test facilities. The data would also be valuable in assessing rarified gas and surface catalicity effects in a real gas environment.

  11. Quality Function Deployment in Launch Operations

    DTIC Science & Technology

    1990-11-23

    tool in translating these requirements throughout the whole process of design, development, manufacture, and operations. This report explores the...Command operational requirements. 4 2. QUALITY FUNCTION DEPLOYMENT OVERVIEW Quality Function Deployment (QFD) is a planning tool to improve the process...Finish Process Control Production Control Insulation Welding Forming Machining Trimming Composites Fabrication Environmental Control 0 33 In order to

  12. Army Deployments of OIF and OEF

    DTIC Science & Technology

    2010-01-01

    Congress Cataloging -in-Publication Data Bonds, Tim, 1962– Army deployments to OIF and OEF / Timothy M. Bonds, Dave Baiocchi, Laurie L. McDonald. p...for a short period one or more times to those with 365 days of continuous deployed duty. (The previous “ tachometer ” chart, in contrast, better

  13. Deployable System for Crash-Load Attenuation

    NASA Technical Reports Server (NTRS)

    Kellas, Sotiris; Jackson, Karen E.

    2007-01-01

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

  14. Air deployment of satellite-tracked drifters

    SciTech Connect

    Cheney, R.E.; Richardson, P.L.; Blumenthal, B.P.

    1980-05-20

    Six free-drifting buoys tracked by the Nimbus 6 satellite were successfully launched by C-130 aircraft in a series of deployments during 1977-1979. The buoys were launched in Gulf Stream rings which had been identified with airborne XBT surveys and satellite infrared images. This is the first operational test of these air-deployable buoys.

  15. Military Children: When Parents Are Deployed Overseas

    ERIC Educational Resources Information Center

    Fitzsimons, Virginia M.; Krause-Parello, Cheryl A.

    2009-01-01

    Members of the Armed Services and Reserve Unit Members, both male and female, are being deployed to distant lands for long periods of time, disrupting family life and causing stressful times for the adults and children in the family. Traditionally, the mother of the military family was left to be the caregiver after the deployment of the…

  16. Experimental thermal mechanics of deployable boom structures

    NASA Technical Reports Server (NTRS)

    Predmore, R.

    1972-01-01

    An apparatus was developed for thermal distortion measurements on deployable boom structures. The calibration procedure and thermal static bending plus twist measurements are considered. The thermal mechanics test facility is described. A table is presented for several examples of spacecraft applications of thermal static distortion measurements on 3-m deployable booms.

  17. Seismic SMHD -- Rotational Sensor Development and Deployment

    SciTech Connect

    Laughlin, Darren; Pierson, Bob; Brune, Bob

    2016-06-20

    The U.S. Department of Energy (DOE) and Applied Technology Associates (ATA) are funding development and deployment of a new generation of rotational sensors for validation of rotational seismic applications. The sensors employ Magnetohydrodynamic (MHD) principles with broadband response, high dynamic range, low noise floor, proven ruggedness, and high repeatability. This paper presents current status of sensor development and deployment opportunities.

  18. Self-deploying photovoltaic power system

    NASA Technical Reports Server (NTRS)

    Colozza, Anthony J. (Inventor)

    1993-01-01

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

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

    PubMed Central

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

    2017-01-01

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

  20. Military children: when parents are deployed overseas.

    PubMed

    Fitzsimons, Virginia M; Krause-Parello, Cheryl A

    2009-02-01

    Members of the Armed Services and Reserve Unit Members, both male and female, are being deployed to distant lands for long periods of time, disrupting family life and causing stressful times for the adults and children in the family. Traditionally, the mother of the military family was left to be the caregiver after the deployment of the husband/father. Today, extended family members as well as mothers or fathers are asked to serve as caregivers for dependent children of deployed servicemen and servicewomen. This article provides information about the challenges families face and the psychosocial developmental needs of children and families during the five stages of military deployment: predeployment, deployment, sustainment, redeployment, and postdeployment. School nurses can offer children and families support and link them with available resources and networks that will assist them with their needs.

  1. Cost-effective optical transponders for deployed metropolitan area networks

    NASA Astrophysics Data System (ADS)

    Nanou, Maki; Politi, Christina (Tanya); Stavdas, Alexandros; Glentis, George-Othon; Georgoulakis, Kristina; Emeretlis, Andreas; Theodoridis, George

    2016-12-01

    Improving the performance of electronic and optoelectronic components has enabled the investigation of transmitting optical channels with data rates greater than 40 Gb/s, over infrastructures that were initially supporting 10 Gb/s transport. However, for transporting high capacity channels, over long distances, considerable signal processing is necessary, with current emphasis being on digital techniques. Meanwhile in the context of optical networking where spectrally adjacent channels may cross different routes to interconnect the same source destination nodes, adaptive transmission systems become vital. This paper will suggest, compare and develop the necessary transponder technologies that enable transportation of 40 Gb/s channels over deployed Metropolitan Area optical Networks (MAN) infrastructure with emphasis on the interplay between realistic performance, feasibility and complexity/cost. Specifically it will investigate utilizing deployed optical infrastructure for transporting 40 Gb/s DQPSK channels in conjunction with various high performance, low complexity electronic equalizers that can compensate the corresponding linear impairment enhancement that accompanies this upgrade, namely Chromatic Dispersion and Polarization Mode Dispersion while they can be implemented in a single FPGA. It is shown that resource constraint performance evaluation is vital and the exact technology choice is related to the deployed infrastructure.

  2. Nanosatellite Launch Adapter System (NLAS)

    NASA Technical Reports Server (NTRS)

    Yost, Bruce D.; Hines, John W.; Agasid, Elwood F.; Buckley, Steven J.

    2010-01-01

    The utility of small spacecraft based on the University cubesat standard is becoming evident as more and more agencies and organizations are launching or planning to include nanosatellites in their mission portfolios. Cubesats are typically launched as secondary spacecraft in enclosed, containerized deployers such as the CalPoly Poly Picosat Orbital Deployer (P-POD) system. The P-POD allows for ease of integration and significantly reduces the risk exposure to the primary spacecraft and mission. NASA/ARC and the Operationally Responsive Space office are collaborating to develop a Nanosatellite Launch Adapter System (NLAS), which can accommodate multiple cubesat or cubesat-derived spacecraft on a single launch vehicle. NLAS is composed of the adapter structure, P-POD or similar spacecraft dispensers, and a sequencer/deployer system. This paper describes the NLAS system and it s future capabilities, and also provides status on the system s development and potential first use in space.

  3. Overview of entry risk predictions

    NASA Astrophysics Data System (ADS)

    Mrozinski, R. B.; Mendeck, G. F.; Cutri-Kohart, R. M.

    2004-01-01

    This paper discusses many aspects of "casualty expectation", defined as the expected number of people suffering death or injury due to a spacecraft entry event, normally used when planning the end-of-life disposal of satellites. United States guidelines state a disposal via atmospheric entry should be controlled rather than uncontrolled whenever casualty expectation estimates exceed a specified limit. Since this guideline can have serious impacts on the cost, lifetime, and even the mission and functionality of a satellite, it is critical that casualty expectation ( Ec) be estimated well, and decision-makers understand all assumptions and limitations inherent in the result. This paper begins with an overview of relevant United States guidelines. The equation the space industry typically uses to estimate Ec is presented, along with its sensitivity to typical assumptions, models, and initial condition uncertainties. An alternate quantity is introduced, called "probability of casualty", or Pc. Two examples are given of both Ec and Pc estimations. Because Ec and Pc are dependent on variables with significant uncertainty, confidence in the estimates themselves can be challenged. Fortunately, a precise value is rarely needed. Results typically are well above or well below guideline limits to the extent that even if all variable values were certain, the resulting recommended course of action would not change. Ec and Pc are then ideal to use in relative analyses using a standard tool to assess compliance with guidelines.

  4. Optimal firm growth under the threat of entry.

    PubMed

    Kort, Peter M; Wrzaczek, Stefan

    2015-10-01

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

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

    NASA Technical Reports Server (NTRS)

    Lu, Ping; Shen, Zuojun

    2003-01-01

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

  6. Preventing re-entry to foster care.

    PubMed

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

    2013-01-01

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

  7. Classifying climate change adaptation frameworks

    NASA Astrophysics Data System (ADS)

    Armstrong, Jennifer

    2014-05-01

    Complex socio-ecological demographics are factors that must be considered when addressing adaptation to the potential effects of climate change. As such, a suite of deployable climate change adaptation frameworks is necessary. Multiple frameworks that are required to communicate the risks of climate change and facilitate adaptation. Three principal adaptation frameworks have emerged from the literature; Scenario - Led (SL), Vulnerability - Led (VL) and Decision - Centric (DC). This study aims to identify to what extent these adaptation frameworks; either, planned or deployed are used in a neighbourhood vulnerable to climate change. This work presents a criterion that may be used as a tool for identifying the hallmarks of adaptation frameworks and thus enabling categorisation of projects. The study focussed on the coastal zone surrounding the Sizewell nuclear power plant in Suffolk in the UK. An online survey was conducted identifying climate change adaptation projects operating in the study area. This inventory was analysed to identify the hallmarks of each adaptation project; Levels of dependency on climate model information, Metrics/units of analysis utilised, Level of demographic knowledge, Level of stakeholder engagement, Adaptation implementation strategies and Scale of adaptation implementation. The study found that climate change adaptation projects could be categorised, based on the hallmarks identified, in accordance with the published literature. As such, the criterion may be used to establish the matrix of adaptation frameworks present in a given area. A comprehensive summary of the nature of adaptation frameworks in operation in a locality provides a platform for further comparative analysis. Such analysis, enabled by the criterion, may aid the selection of appropriate frameworks enhancing the efficacy of climate change adaptation.

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

    NASA Technical Reports Server (NTRS)

    Murray, James E.; Tartabini, Paul V.

    2001-01-01

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

  9. Titan Explorer Entry, Descent and Landing Trajectory Design

    NASA Technical Reports Server (NTRS)

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

    2006-01-01

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

  10. 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.

  11. 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.

  12. Airborne Observation of the Hayabusa Sample Return Capsule Re-Entry

    NASA Technical Reports Server (NTRS)

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

    2011-01-01

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

  13. Overview of Deployed EDS Technologies

    SciTech Connect

    Martz, H E; Crawford, C

    2009-09-24

    The term explosive detection system (EDS) is used by the TSA to describe equipment that is certified to detect explosives in checked bags. The EDS, as certified, by the TSL must consist of device for interrogating a bag and an automated detection algorithm (ATD) for evaluating the results of the interrogation. We only consider CT as the interrogation device in this report. A schematic drawing of a CT-based EDS is shown in Figure 2. The output of the ATD is the binary decision of alarm or non-alarm. Alarms may true- or false-positives. Non-alarms may be true- or false-negatives. False positives are also denoted false alarms. The true detection means that the ATD reports an alarm when a threat is present in the scanned bag. The probability of detecting a threat given that a threat is present is denoted the probability of detection (PD). The probability of false alarm (PFA) is the case when an alarm is reported when a threat is not present in a bag. Certification in this context means passing tests for PD and PFA at the TSL. The results of the EDS include CT cross-sectional images of the bag and specifics about the alarmed objects generated by ATD. These results are presented on a display so that a person may override the decision of ATD and declare the alarm to be a non-alarm. This process is denoted clearing. Bags that are not cleared by the person are sent to a secondary inspection process. Here the bags may be opened or assessed with explosive trace detection (ETD) in order to clear the bags. Bags that are not cleared at this point are evaluated by an ordinance disposal team. The CT scanner along with ATD is denoted Level 1 screening. The process of clearing on a display is denoted Level 2 screening. Secondary inspection is denoted Level 3 screening. Vendors of the deployed EDSs supply the TSA with equipment for all three levels. Therefore, the term EDS may include the equipment provided for Levels 1, 2 and 3. A schematic diagram of an EDS and the levels of

  14. Adaptive Technologies for Training and Education

    ERIC Educational Resources Information Center

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

    2012-01-01

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

  15. Structures for remotely deployable precision antennas

    NASA Technical Reports Server (NTRS)

    Hedgepeth, John M.

    1989-01-01

    There is a need for completely deployable large antenna reflectors capable of efficiently handling millimeter-wave electromagnetic radiation. The structural concepts and technologies that are appropriate to fully automated deployment of dish-type antennas with solid reflector surfaces were studied. First, the structural requirements are discussed. Then, existing concepts for fully deployable antennas are described and assessed relative to the requirements. Finally, several analyses are presented that evaluate the effects of beam steering and segmented reflector design on the accuracy of the antenna.

  16. Dynamic Deployment Simulations of Inflatable Space Structures

    NASA Technical Reports Server (NTRS)

    Wang, John T.

    2005-01-01

    The feasibility of using Control Volume (CV) method and the Arbitrary Lagrangian Eulerian (ALE) method in LSDYNA to simulate the dynamic deployment of inflatable space structures is investigated. The CV and ALE methods were used to predict the inflation deployments of three folded tube configurations. The CV method was found to be a simple and computationally efficient method that may be adequate for modeling slow inflation deployment sine the inertia of the inflation gas can be neglected. The ALE method was found to be very computationally intensive since it involves the solving of three conservative equations of fluid as well as dealing with complex fluid structure interactions.

  17. Breastfeeding during military deployment: a soldier's story.

    PubMed

    Sleutel, Martha Rider

    2012-01-01

    Thousands of women of childbearing age are serving and being deployed in the United States military. U.S. Department of Defense policies related to breastfeeding and deployment are inconsistent among the different branches of the military and sometimes conflict with evidence-based guidelines about optimal breastfeeding practices. This is the story of an active duty soldier who was deployed while breastfeeding and the obstacles she encountered trying to send breast milk home to her son. The article explores policy, health and professional practice implications.

  18. Middleware Automated Deployment Utilities - MRW Suite

    SciTech Connect

    Anderson, Mathew; Bowen, Brian; Coles, Dwight; Cleal, Thomas; Quarles, Elliott; Gurule, Kaitlyn; Kagie, Matthew

    2014-09-18

    The Middleware Automated Deployment Utilities consists the these three components: MAD: Utility designed to automate the deployment of java applications to multiple java application servers. The product contains a front end web utility and backend deployment scripts. MAR: Web front end to maintain and update the components inside database. MWR-Encrypt: Web utility to convert a text string to an encrypted string that is used by the Oracle Weblogic application server. The encryption is done using the built in functions if the Oracle Weblogic product and is mainly used to create an encrypted version of a database password.

  19. Deployable M-braced truss structure

    NASA Technical Reports Server (NTRS)

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

    1986-01-01

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

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

    PubMed

    Botti, Lucia; Ferrari, Emilio; Mora, Cristina

    2017-04-01

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

  1. VESL for Data Entry: A Competency-based Curriculum Guide. Project OSCAER.

    ERIC Educational Resources Information Center

    Lopez-Valadez, Jeanne, Ed.; Pankratz, David, Ed.

    This guide is intended for vocational educators developing the vocational English as a second language (VESL) component of a course in data entry. The introductory section examines assumptions about second language learning and instruction and VESL classes, local adaptations of the curriculum, and sample VESL lessons. The chapter on language…

  2. Coronary angioscopy before and after stent deployment

    NASA Astrophysics Data System (ADS)

    Denardo, Scott J.; Schatz, Richard A.; Rocha-Singh, Krishna J.; Wong, S. Chiu; Morris, Nancy A.; Strumpf, Robert K.; Heuser, Richard R.; Teirstein, Paul

    1993-09-01

    Coronary angioscopy was used in an attempt to visualize the internal architecture of cardiac vessels before and after deployment of Palmaz-Schatz stents in 50 patients. The vessel was successfully visualized in 48 (96%) of these patients. In 24 patients, angioscopy was performed both after preliminary balloon angioplasty and then again after stent deployment. In all 24 patients the diameter of the lumen appeared larger after stent deployment as compared to after balloon angioplasty. In 16 of these 24 patients a dissection was documented by angioscopy after balloon angioplasty. The dissection was absent after stent deployment in all 16 patients. In seven patients, thrombus that was not apparent by angiography was visualized by angioscopy. Moreover, in four patients, thrombus that was suggested by angiography could not be confirmed by angioscopy.

  3. A Deployable Primary Mirror for Space Telescopes

    NASA Technical Reports Server (NTRS)

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

    1999-01-01

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

  4. Tethered satellite system deployer flight thermal performance

    NASA Astrophysics Data System (ADS)

    Chapter, John J.

    The Tethered Satellite System (TSS) is a Space Shuttle payload that was flown on July 31, 1992. Though anomalies prevented full deployment, the duration of the mission was approximately as planned, so it was possible to assess system thermal performance. The deployer, which supports the satellite and controls tether movement, has a thermal design that includes multilayer insulation, heaters, and the Spacelab Freon Loop. The deployer Thermal Subsystem met all requirements, and there were no anomalies during the flight. This paper summarizes the TSS deployer thermal design and compares pre- and post-flight thermal analyses. It also decribes simplified personal-computer thermal models of the TSS-1 and presents analysis results for the as-flown timeline.

  5. Thermally isolated deployable shield for spacecraft

    NASA Technical Reports Server (NTRS)

    Redmon, John W., Jr. (Inventor); Miller, Andre E. (Inventor); Lawson, Bobby E. (Inventor); Cobb, William E. (Inventor)

    1991-01-01

    A thermally isolated deployable shield for spacecraft is provided utilizing a plurality of lattice panels stowable generally against the craft and deployable to some fixed distance from the craft. The lattice panels are formed from replaceable shield panels affixed to lattice structures. The lattice panels generally encircle the craft providing 360 degree coverage therearound. Actuation means are provided from translating the shield radially outward from the craft and thermally isolating the shield from the craft. The lattice panels are relatively flexible, allowing the shield to deploy to variable diameters while retaining uniform curvature thereof. Restraining means are provided for holding the shield relatively tight in its stowed configuration. Close-out assemblies provide light sealing and protection of the annular spaces between the deployed shield and the crafts end structure.

  6. Demonstration and Deployment Strategy Workshop: Summary

    SciTech Connect

    none,

    2014-05-01

    This report is based on the proceedings of the U.S. Department of Energy Bioenergy Technologies Office Demonstration and Deployment Strategy Workshop, held on March 12–13, 2014, at Argonne National Laboratory.

  7. Analysis of Security Contractors in Deployed Environments

    DTIC Science & Technology

    2006-12-01

    of Security Contractors in Deployed Environments 6. AUTHOR(S) Herron, Jennifer F Santiago, Gregory 5 . FUNDING NUMBERS 7. PERFORMING ORGANIZATION... 5 II. DEFINITIONS AND BACKGROUND .....................................................................7 A. DEFINITIONS...Firms..................................35 5 . Legal Authority over Security Firms ...............................................35 C

  8. Guam: U.S. Defense Deployments

    DTIC Science & Technology

    2013-11-15

    the Air Force and Navy to counter challenges to U.S. freedom of action, defeat adversaries with sophisticated anti- access and area-denial (A2/AD...Force Base in North Dakota ) to deploy to Andersen arrived in February 2004. B-52 bombers can each carry 20 AGM-86C/D conventional air-launched...negotiate with sovereign countries on force deployments or face the risks of losing bases or access . Defense Secretary Donald Rumsfeld visited Guam in

  9. Deployable radiator with flexible line loop

    NASA Technical Reports Server (NTRS)

    Keeler, Bryan V. (Inventor); Lehtinen, Arthur Mathias (Inventor); McGee, Billy W. (Inventor)

    2003-01-01

    Radiator assembly (10) for use on a spacecraft (12) is provided including at least one radiator panel assembly (26) repeatably movable between a panel stowed position (28) and a panel deployed position (36), at least two flexible lines (40) in fluid communication with the at least one radiator panel assembly (26) and repeatably movable between a stowage loop (42) and a flattened deployed loop (44).

  10. Towards the Ubiquitous Deployment of DNSSEC

    DTIC Science & Technology

    2016-01-01

    TECHNICAL REPORT 3. DATES COVERED (From - To) JAN 2011 – JUN 2015 4. TITLE AND SUBTITLE TOWARDS THE UBIQUITOUS DEPLOYMENT OF DNSSEC 5a. CONTRACT NUMBER...NOTES 14. ABSTRACT This report describes the effort performed under contract number FA8750-11-C-0088 for supporting the ubiquitous deployment of DNSSEC...outreach, standardization and education related activities. As part of our effort on this contract , we have made a number of contributions towards

  11. Deployment of Military Mothers during Wartime

    DTIC Science & Technology

    2012-11-12

    months old if you’re not breastfeeding because I think the younger they are, the less long term effects it’s going to have on them. I don’t think he...been back. Several of the mothers of young children were still breastfeeding while they prepared to deploy. [P34] I was still breastfeeding ... breastfeeding a lot more than that. To preserve their bond, an area of importance in the pre-deployment phase was setting up communication pathways

  12. Supporting spouses during a military deployment.

    PubMed

    Tollefson, Thora T

    2008-01-01

    US National Guard and Reserves members are deploying at the highest rates since World War II, leaving behind spouses in community settings without the full support of the military. Deployment may create or intensify existing stressors to spouses and bring about changes in coping strategies. The goal of this article is to increase the healthcare provider's knowledge about the stressors these spouses may experience and provide resources in case they may require extra support and assistance.

  13. State perspectives on clean coal technology deployment

    SciTech Connect

    Moreland, T.

    1997-12-31

    State governments have been funding partners in the Clean Coal Technology program since its beginnings. Today, regulatory and market uncertainties and tight budgets have reduced state investment in energy R and D, but states have developed program initiatives in support of deployment. State officials think that the federal government must continue to support these technologies in the deployment phase. Discussions of national energy policy must include attention to the Clean Coal Technology program and its accomplishments.

  14. Affects of Multiple Deployments on Families

    DTIC Science & Technology

    2009-03-11

    are faced with during lengthy deployments. “Certainly, the nature of the deployment and the role of the service member in the military action can...and sadness. Preschoolers may display regressive behavior, irritation, sadness, and aggressiveness and may have somatic complaints. School-age...may also be hesitant to be affectionate with the returned parent. Preschoolers may feel scared or angry. School-age children may crave attention from

  15. DRAGON - 8U Nanosatellite Orbital Deployer

    NASA Technical Reports Server (NTRS)

    Dobrowolski, Marcin; Grygorczuk, Jerzy; Kedziora, Bartosz; Tokarz, Marta; Borys, Maciej

    2014-01-01

    The Space Research Centre of the Polish Academy of Sciences (SRC PAS) together with Astronika company have developed an Orbital Deployer called DRAGON for ejection of the Polish scientific nanosatellite BRITE-PL Heweliusz (Fig. 1). The device has three unique mechanisms including an adopted and scaled lock and release mechanism from the ESA Rosetta mission MUPUS instrument. This paper discusses major design restrictions of the deployer, unique design features, and lessons learned from development through testing.

  16. 19 CFR 10.78 - Entry.

    Code of Federal Regulations, 2011 CFR

    2011-04-01

    ... Entry. (a) No entry shall be required for fish or other marine products taken on the high seas by... or other products are brought into port by the taking vessel or are transferred at sea to another... enterprise conducted under the American flag by vessels of the United States on the high seas or in...

  17. 19 CFR 10.78 - Entry.

    Code of Federal Regulations, 2014 CFR

    2014-04-01

    ... Entry. (a) No entry shall be required for fish or other marine products taken on the high seas by... or other products are brought into port by the taking vessel or are transferred at sea to another... enterprise conducted under the American flag by vessels of the United States on the high seas or in...

  18. 19 CFR 10.78 - Entry.

    Code of Federal Regulations, 2013 CFR

    2013-04-01

    ... Entry. (a) No entry shall be required for fish or other marine products taken on the high seas by... or other products are brought into port by the taking vessel or are transferred at sea to another... enterprise conducted under the American flag by vessels of the United States on the high seas or in...

  19. 19 CFR 10.78 - Entry.

    Code of Federal Regulations, 2010 CFR

    2010-04-01

    ... Entry. (a) No entry shall be required for fish or other marine products taken on the high seas by... or other products are brought into port by the taking vessel or are transferred at sea to another... enterprise conducted under the American flag by vessels of the United States on the high seas or in...

  20. 19 CFR 10.78 - Entry.

    Code of Federal Regulations, 2012 CFR

    2012-04-01

    ... Entry. (a) No entry shall be required for fish or other marine products taken on the high seas by... or other products are brought into port by the taking vessel or are transferred at sea to another... enterprise conducted under the American flag by vessels of the United States on the high seas or in...

  1. 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...

  2. 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...

  3. 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...

  4. 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...

  5. 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...

  6. 21 CFR 1316.05 - Entry.

    Code of Federal Regulations, 2010 CFR

    2010-04-01

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

  7. 32 CFR 770.19 - Entry procedures.

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ... ACCESS TO PARTICULAR INSTALLATIONS Base Entry Regulations for Naval Submarine Base, Bangor, Silverdale, Washington § 770.19 Entry procedures. (a) Any person or group of persons desiring the advance consent of the... Commanding Officer, Naval Submarine Base, Bangor, 1100 Hunley Road, Silverdale, WA 98315. (b) Each...

  8. 32 CFR 770.19 - Entry procedures.

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... ACCESS TO PARTICULAR INSTALLATIONS Base Entry Regulations for Naval Submarine Base, Bangor, Silverdale, Washington § 770.19 Entry procedures. (a) Any person or group of persons desiring the advance consent of the... Commanding Officer, Naval Submarine Base, Bangor, 1100 Hunley Road, Silverdale, WA 98315. (b) Each...

  9. 32 CFR 770.19 - Entry procedures.

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ... ACCESS TO PARTICULAR INSTALLATIONS Base Entry Regulations for Naval Submarine Base, Bangor, Silverdale, Washington § 770.19 Entry procedures. (a) Any person or group of persons desiring the advance consent of the... Commanding Officer, Naval Submarine Base, Bangor, 1100 Hunley Road, Silverdale, WA 98315. (b) Each...

  10. 32 CFR 770.19 - Entry procedures.

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... ACCESS TO PARTICULAR INSTALLATIONS Base Entry Regulations for Naval Submarine Base, Bangor, Silverdale, Washington § 770.19 Entry procedures. (a) Any person or group of persons desiring the advance consent of the... Commanding Officer, Naval Submarine Base, Bangor, 1100 Hunley Road, Silverdale, WA 98315. (b) Each...

  11. 32 CFR 770.19 - Entry procedures.

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ... ACCESS TO PARTICULAR INSTALLATIONS Base Entry Regulations for Naval Submarine Base, Bangor, Silverdale, Washington § 770.19 Entry procedures. (a) Any person or group of persons desiring the advance consent of the... Commanding Officer, Naval Submarine Base, Bangor, 1100 Hunley Road, Silverdale, WA 98315. (b) Each...

  12. Space X First Entry Sample Analysis

    NASA Technical Reports Server (NTRS)

    James, John T.

    2012-01-01

    The toxicological assessment of one sample collected on May 26, 2012 and returned to earth on May 31, 2012 was analyzed for pollutants that had offgassed into the Dragon capsule by the time of first entry operations performed by the ISS crew. The components identified in the first-entry sample and their contributions to the total T-value are shown.

  13. Specification of the Model 3 Entry Lexicon.

    ERIC Educational Resources Information Center

    Rhode, Mary

    The Model 3 communication skills lexicon consists of three lists of words developed by the Southwest Regional Laboratory (SWRL) for use in communication skills instruction in K-6. This report documents the procedures followed in compiling the entry lexicon, the first component of the Model 3 communication skills lexicon. The entry lexicon is…

  14. 78 FR 77550 - Integrated Corridor Management Deployment Planning Grants

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-23

    ... Federal Highway Administration Integrated Corridor Management Deployment Planning Grants AGENCY: Federal... is extending the application period for the Integrated Corridor Management Deployment Planning Grants... Integrated Corridor Management Deployment Planning Grants. The purpose of this notice was to invite...

  15. A gendered perspective on military deployment.

    PubMed

    Kelly, Patricia J; Nilsson, Johanna; Berkel, Laverne

    2014-01-01

    Military deployment, especially in combat or dangerous areas, can have a strong influence on subsequent mental health. This effect may be intensified as a result of the potential stigma that admission of mental health problems indicates weakness. Additional mental health issues exist for female soldiers from the National Guard who are pulled from non-military environments to work under dangerous conditions far from home and traditional social support. Minimal documentation is available about the day-to-day, gendered experiences of deployment for this group of female soldiers. To provide background for appropriate training and support, the aim of this study was to understand better the experiences of military deployment for women in the National Guard. We used content analysis to analyze individual, semi-structured interviews with a sample of 42 women from 7 U.S. National Guard units who were deployed in combat areas. Four general themes emerged about deployment experience: the general environment of stress, heterogeneous job responsibilities, home comes with you, and gendered stress. Military efforts are needed to address gender-specific issues associated with deployment and to develop resilience training that will optimize the mental health of female soldiers.

  16. A Deployable Primary Mirror for Space Telescopes

    NASA Technical Reports Server (NTRS)

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

    1999-01-01

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

  17. Designing Planar Deployable Objects via Scissor Structures.

    PubMed

    Zhang, Ran; Wang, Shiwei; Chen, Xuejin; Ding, Chao; Jiang, Luo; Zhou, Jie; Liu, Ligang

    2016-02-01

    Scissor structure is used to generate deployable objects for space-saving in a variety of applications, from architecture to aerospace science. While deployment from a small, regular shape to a larger one is easy to design, we focus on a more challenging task: designing a planar scissor structure that deploys from a given source shape into a specific target shape. We propose a two-step constructive method to generate a scissor structure from a high-dimensional parameter space. Topology construction of the scissor structure is first performed to approximate the two given shapes, as well as to guarantee the deployment. Then the geometry of the scissor structure is optimized in order to minimize the connection deflections and maximize the shape approximation. With the optimized parameters, the deployment can be simulated by controlling an anchor scissor unit. Physical deployable objects are fabricated according to the designed scissor structures by using 3D printing or manual assembly. We show a number of results for different shapes to demonstrate that even with fabrication errors, our designed structures can deform fluently between the source and target shapes.

  18. Offloading techniques for large deployable space structures

    NASA Technical Reports Server (NTRS)

    Caravaggio, Levino; Golob, Alex

    1992-01-01

    The validation and verification of large deployable space structures are continual challenges which face the integration and test engineer today. Spar Aerospace Limited has worked on various programs in which such structure validation was required and faces similar tasks in the future. This testing is reported and the different offloading and deployment methods which were used, as well as the proposed methods which will be used on future programs, are described. Past programs discussed include the Olympus solar array ambient and thermal vacuum deployments, and the Anik-E array and reflector deployments. The proposed MSAT reflector and boom ambient deployment tests, as well as the proposed RADARSAT Synthetic Aperture Radar (SAR) ambient and thermal vacuum deployment tests will also be presented. A series of tests relating to various component parts of the offloading equipment systems was required. These tests included the characterization and understanding of linear bearings and large (180 in-lbf) constant force spring motors in a thermal vacuum environment, and the results from these tests are presented.

  19. Joints in deployable space truss structures

    NASA Technical Reports Server (NTRS)

    Rhodes, M.

    1988-01-01

    Since the response of deployable structural concepts being considered for the Large Deployable Reflector (LDR) backup structure will be dominated by the response of joints, the joint characteristics are significant. An overview is given of the research activities at LaRC on the static behavior of joints for deployable space truss structures. Since a pin-clevis-type joint will be utilized in deployable structures, an experimental research program to characterize the joint parameters which affect stiffness was conducted. An experimental research program was conducted on a second type of joint, referred to as a near-center latch joint. It was used in the center of members on the deployable truss structure for the Control of Flexible Structures (COFS) flight experiment. The test results of the near-center latch joint and the member with the joints indicated that the stiffness of the near-center joint is linear and stiffer than the stiffness of the total member, and that non-linearities in the stiffness characteristics of the total member were due to bending introduced at the ends of the member. The resulting data indicates that stiff linear folding joints can be designed and that bending load paths should be avoided whenever possible. In summary, for deployable structures, special attention to the joint and the structure design is required to minimize the undesirable structural non-linearities.

  20. New Antenna Deployment, Pointing and Supporting Mechanism

    NASA Technical Reports Server (NTRS)

    Costabile, V.; Lumaca, F.; Marsili, P.; Noni, G.; Portelli, C.

    1996-01-01

    On ITALSAT Flight 2, the Italian telecommunications satellite, the two L-Ka antennas (Tx and Rx) use two large deployable reflectors (2000-mm diameter), whose deployment and fine pointing functions are accomplished by means of an innovative mechanism concept. The Antenna Deployment & Pointing Mechanism and Supporting Structure (ADPMSS) is based on a new configuration solution, where the reflector and mechanisms are conceived as an integrated, self-contained assembly. This approach is different from the traditional configuration solution. Typically, a rigid arm is used to deploy and then support the reflector in the operating position, and an Antenna Pointing Mechanism (APM) is normally interposed between the reflector and the arm for steering operation. The main characteristics of the ADPMSS are: combined implementation of deployment, pointing, and reflector support; optimum integration of active components and interface matching with the satellite platform; structural link distribution to avoid hyperstatic connections; very light weight and; high performance in terms of deployment torque margin and pointing range/accuracy. After having successfully been subjected to all component-level qualification and system-level acceptance tests, two flight ADPMSS mechanisms (one for each antenna) are now integrated on ITALSAT F2 and are ready for launch. This paper deals with the design concept, development, and testing program performed to qualify the ADPMSS mechanism.

  1. Cell entry of Lassa virus induces tyrosine phosphorylation of dystroglycan.

    PubMed

    Moraz, Marie-Laurence; Pythoud, Christelle; Turk, Rolf; Rothenberger, Sylvia; Pasquato, Antonella; Campbell, Kevin P; Kunz, Stefan

    2013-05-01

    The extracellular matrix (ECM) receptor dystroglycan (DG) serves as a cellular receptor for the highly pathogenic arenavirus Lassa virus (LASV) that causes a haemorrhagic fever with high mortality in human. In the host cell, DG provides a molecular link between the ECM and the actin cytoskeleton via the adapter proteins utrophin or dystrophin. Here we investigated post-translational modifications of DG in the context of LASV cell entry. Using the tyrosine kinase inhibitor genistein, we found that tyrosine kinases are required for efficient internalization of virus particles, but not virus-receptor binding. Engagement of cellular DG by LASV envelope glycoprotein (LASV GP) in human epithelial cells induced tyrosine phosphorylation of the cytoplasmic domain of DG. LASV GP binding to DG further resulted in dissociation of the adapter protein utrophin from virus-bound DG. This virus-induced dissociation of utrophin was affected by genistein treatment, suggesting a role of receptor tyrosine phosphorylation in the process.

  2. Cell entry of Lassa virus induces tyrosine phosphorylation of dystroglycan

    PubMed Central

    Moraz, Marie-Laurence; Pythoud, Christelle; Turk, Rolf; Rothenberger, Sylvia; Pasquato, Antonella; Campbell, Kevin P.; Kunz, Stefan

    2013-01-01

    The extracellular matrix (ECM) receptor dystroglycan (DG) serves as a cellular receptor for the highly pathogenic arenavirus Lassa virus (LASV) that causes a hemorrhagic fever with high mortality in man. In the host cell, DG provides a molecular link between the ECM and the actin cytoskeleton via the adapter proteins utrophin or dystrophin. Here we investigated post-translational modifications of DG in the context of LASV cell entry. Using the tyrosine kinase inhibitor genistein, we found that tyrosine kinases are required for efficient internalization of virus particles, but not virus-receptor binding. Engagement of cellular DG by LASV envelope glycoprotein (LASV GP) in human epithelial cells induced tyrosine phosphorylation of the cytoplasmic domain of DG. LASV GP binding to DG further resulted in dissociation of the adapter protein utrophin from virus-bound DG. This virus-induced dissociation of utrophin was affected by genistein treatment, suggesting a role of receptor tyrosine phosphorylation in the process. PMID:23279385

  3. Airborne Observation of the Hayabusa Sample Return Capsule Re-Entry

    NASA Technical Reports Server (NTRS)

    Grinstead, Jay H.; Jenniskens, Peter M.; Cassell, Alan M.; Albers, Jim; Winterm Michael

    2011-01-01

    The Japan Aerospace Exploration Agency (JAXA) recently completed their Hayabusa asteroid exploration mission. Launched in 2003, Hayabusa made contact with, and retrieved a sample from, the near-Earth asteroid Itokawa in 2005. The sample return capsule (SRC) re-entered over the Woomera Test Range (WTR) in southern Australia on June 13, 2010, at approximately 11:21 pm local time (09:51 UTC). The SRC re-entry velocity was 12.2 km/s, making it the second-fastest Earth return velocity behind NASA s Stardust sample return capsule re-entry in 2006. From a space technology development perspective, Hayabusa s re-entry functioned as a rare flight experiment of an entry vehicle and its thermal protection system. In collaboration with the SETI Institute, NASA deployed its DC-8 airborne laboratory and a team of international researchers to Australia to observe the re-entry of the SRC. The use of an airborne platform enables observation above most clouds and weather and greatly diminishes atmospheric absorption of the optical signals. The DC-8 s flight path was engineered and flown to provide a view of the spacecraft that bracketed the heat pulse to the capsule. A suite of imaging instruments on board the DC-8 successfully recorded the luminous portion of the re-entry event. For approximately 70 seconds, the spectroscopic and radiometric instruments acquired images and spectra of the capsule, its wake, and destructive re-entry of the spacecraft bus. Figure 1 shows a perspective view of the WTR, the SRC re-entry trajectory, and the flight path of the DC-8. The SRC was jettisoned from the spacecraft bus approximately 3 hours prior to entry interface. Due to thruster failures on the spacecraft, it could not be diverted from the entry path and followed the trajectory of the SRC, where it burned up in the atmosphere between approximately 100 and 50 km altitude. Fortuitously, the separation distance between the spacecraft and SRC was sufficient to clearly resolve the SRC from the

  4. 19 CFR 143.35 - Procedure for electronic entry summary.

    Code of Federal Regulations, 2010 CFR

    2010-04-01

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

  5. 19 CFR 142.3 - Entry documentation required.

    Code of Federal Regulations, 2010 CFR

    2010-04-01

    ... 19 Customs Duties 2 2010-04-01 2010-04-01 false Entry documentation required. 142.3 Section 142.3... TREASURY (CONTINUED) ENTRY PROCESS Entry Documentation § 142.3 Entry documentation required. (a) Contents. Except as provided in paragraph (b) of this section, the entry documentation required to secure...

  6. 19 CFR 143.35 - Procedure for electronic entry summary.

    Code of Federal Regulations, 2011 CFR

    2011-04-01

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

  7. 50 CFR 91.22 - Display of contest entries.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... 50 Wildlife and Fisheries 9 2012-10-01 2012-10-01 false Display of contest entries. 91.22 Section... Administering the Contest § 91.22 Display of contest entries. The Federal Duck Stamp Office assigns all eligible entries a number as entries are received. That office displays the entries in numerical order at...

  8. 50 CFR 91.22 - Display of contest entries.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... 50 Wildlife and Fisheries 8 2011-10-01 2011-10-01 false Display of contest entries. 91.22 Section... Administering the Contest § 91.22 Display of contest entries. The Federal Duck Stamp Office assigns all eligible entries a number as entries are received. That office displays the entries in numerical order at...

  9. 50 CFR 91.22 - Display of contest entries.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... 50 Wildlife and Fisheries 9 2013-10-01 2013-10-01 false Display of contest entries. 91.22 Section... Administering the Contest § 91.22 Display of contest entries. The Federal Duck Stamp Office assigns all eligible entries a number as entries are received. That office displays the entries in numerical order at...

  10. 50 CFR 91.22 - Display of contest entries.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... 50 Wildlife and Fisheries 9 2014-10-01 2014-10-01 false Display of contest entries. 91.22 Section... Administering the Contest § 91.22 Display of contest entries. The Federal Duck Stamp Office assigns all eligible entries a number as entries are received. That office displays the entries in numerical order at...

  11. 50 CFR 91.22 - Display of contest entries.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 50 Wildlife and Fisheries 6 2010-10-01 2010-10-01 false Display of contest entries. 91.22 Section... Administering the Contest § 91.22 Display of contest entries. The Federal Duck Stamp Office assigns all eligible entries a number as entries are received. That office displays the entries in numerical order at...

  12. 50 CFR 679.83 - Rockfish Program entry level fishery.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... 50 Wildlife and Fisheries 11 2011-10-01 2011-10-01 false Rockfish Program entry level fishery. 679... ALASKA Rockfish Program § 679.83 Rockfish Program entry level fishery. (a) Rockfish entry level fishery—(1) General. A rockfish entry level harvester and rockfish entry level processor may participate...

  13. 50 CFR 679.83 - Rockfish Program entry level fishery.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

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

  14. Equilibrium radiative heating tables for Earth entry

    NASA Technical Reports Server (NTRS)

    Sutton, Kenneth; Hartung, Lin C.

    1990-01-01

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

  15. Thermal Soak Analysis of Earth Entry Vehicles

    NASA Technical Reports Server (NTRS)

    Agrawal, Parul; Sepka, Steven A.; Aliaga, Jose F.; Venkatapathy, Ethiraj; Samareh, Jamshid A.

    2012-01-01

    The Multi-Mission Earth Entry Vehicle project is developing an integrated tool called Multi Mission System Analysis for Planetary Entry Descent and Landing that will provide key technology solutions including mass sizing, aerodynamics, aerothermodynamics, and thermal and structural analysis for any given sample return mission. Thermal soak analysis and temperature predictions of various components including the payload container of the entry vehicle are part of the solution that this tool will offer to mission 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 the tool.

  16. A module concept for a cable-mesh deployable antenna

    NASA Technical Reports Server (NTRS)

    Meguro, Akira

    1993-01-01

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

  17. The Design of a Portable and Deployable Solar Energy System for Deployed Military Applications

    DTIC Science & Technology

    2011-04-01

    The Design of a Portable and Deployable Solar Energy System for Deployed Military Applications Justin Tyner, Matt Coates, Dave Holloway, Kyle...energy systems and to specifically design a portable solar energy system for use tailored for a deployed military/combat unit. We considered ease...where diesel generators are superior and areas where the solar energy systems are superior. The remainder of this paper outlines our process and

  18. The VII Corps Deployment to Saudi Arabia: An Analysis of Deployment Transportation Planning and Management

    DTIC Science & Technology

    1993-06-04

    as VII Corps did during the Gulf War. Transportation Managemen t Deployment of forces relies on the careful management of the transportation assets...disobedient, was wasting money and a lot of people’s time and was slowing the deployment down. Further, if containers were not stuffed and pulled soon, the...ships are easier to load 71 and there would have been less time wasted waiting for ships to move to and from the berths. The Deployment Process When MG

  19. 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

  20. Modulation of Calcium Entry by Mitochondria.

    PubMed

    Fonteriz, Rosalba; Matesanz-Isabel, Jessica; Arias-Del-Val, Jessica; Alvarez-Illera, Pilar; Montero, Mayte; Alvarez, Javier

    2016-01-01

    The role of mitochondria in intracellular Ca(2+) signaling relies mainly in its capacity to take up Ca(2+) from the cytosol and thus modulate the cytosolic [Ca(2+)]. Because of the low Ca(2+)-affinity of the mitochondrial Ca(2+)-uptake system, this organelle appears specially adapted to take up Ca(2+) from local high-Ca(2+) microdomains and not from the bulk cytosol. Mitochondria would then act as local Ca(2+) buffers in cellular regions where high-Ca(2+) microdomains form, that is, mainly close to the cytosolic mouth of Ca(2+) channels, both in the plasma membrane and in the endoplasmic reticulum (ER). One of the first targets proposed already in the 1990s to be regulated in this way by mitochondria were the store-operated Ca(2+) channels (SOCE). Mitochondria, by taking up Ca(2+) from the region around the cytosolic mouth of the SOCE channels, would prevent its slow Ca(2+)-dependent inactivation, thus keeping them active for longer. Since then, evidence for this mechanism has accumulated mainly in immunitary cells, where mitochondria actually move towards the immune synapse during T cell activation. However, in many other cell types the available data indicate that the close apposition between plasma and ER membranes occurring during SOCE activation precludes mitochondria from getting close to the Ca(2+)-entry sites. Alternative pathways for mitochondrial modulation of SOCE, both Ca(2+)-dependent and Ca(2+)-independent, have also been proposed, but further work will be required to elucidate the actual mechanisms at work. Hopefully, the recent knowledge of the molecular nature of the mitochondrial Ca(2+) uniporter will allow soon more precise studies on this matter.

  1. Qualification and In-Flight Demonstration of a European Tether Deployment and Momentum Transfer System on YES2

    NASA Astrophysics Data System (ADS)

    Kruijff, M.; van der Heide, E. J.

    2008-08-01

    This paper highlights the design, qualification and mission performance of a comprehensive tethered momentum transfer technology on ESA's second Young Engineers' Satellite (YES2), aiming specifically on the tether deployer. The deployer is designed with a broad range of near-term tether applications in mind and therefore opens up novel possibilities e.g. small satellite missions. The system contains the following critical elements. The tether, including features to enhance safety, wound up in controlled manner onto a spool core; optical deployment sensors and electronics; a "barberpole" friction brake controlled by a stepper motor; and a triple cutter system. A spring-based ejection system and, on the subsatellite side, a timer/release system facilitate the stagings required for accurate tethered momentum transfer. In addition a small, 6 kg re-entry capsule was developed with 1 kg scientific payload and parachute system. On September 25th, 2007, YES2 deployed a 32 km tether in orbit and gathered a wealth of data. This paper aims to provide an overview of the design, qualification and flight performance of the tether deployer hardware. This performance is compared to the design and from this can be concluded a suitability of the hardware for tether deployment and tethered momentum transfer.

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

    NASA Astrophysics Data System (ADS)

    Raskin, Boris

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

  3. A Model for Designing Adaptive Laboratory Evolution Experiments.

    PubMed

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

    2017-04-15

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

  4. Viral cell recognition and entry.

    PubMed Central

    Rossmann, M. G.

    1994-01-01

    Rhinovirus infection is initiated by the recognition of a specific cell-surface receptor. The major group of rhinovirus serotypes attach to intercellular adhesion molecule-1 (ICAM-1). The attachment process initiates a series of conformational changes resulting in the loss of genomic RNA from the virion. X-ray crystallography and sequence comparisons suggested that a deep crevice or canyon is the site on the virus recognized by the cellular receptor molecule. This has now been verified by electron microscopy of human rhinovirus 14 (HRV14) and HRV16 complexed with a soluble component of ICAM-1. A hydrophobic pocket underneath the canyon is the site of binding of various hydrophobic drug compounds that can inhibit attachment and uncoating. This pocket is also associated with an unidentified, possibly cellular in origin, "pocket factor." The pocket factor binding site overlaps the binding site of the receptor. It is suggested that competition between the pocket factor and receptor regulates the conformational changes required for the initiation of the entry of the genomic RNA into the cell. PMID:7849588

  5. LABORATORY VOICE DATA ENTRY SYSTEM.

    SciTech Connect

    PRAISSMAN,J.L.SUTHERLAND,J.C.

    2003-04-01

    We have assembled a system using a personal computer workstation equipped with standard office software, an audio system, speech recognition software and an inexpensive radio-based wireless microphone that permits laboratory workers to enter or modify data while performing other work. Speech recognition permits users to enter data while their hands are holding equipment or they are otherwise unable to operate a keyboard. The wireless microphone allows unencumbered movement around the laboratory without a ''tether'' that might interfere with equipment or experimental procedures. To evaluate the potential of voice data entry in a laboratory environment, we developed a prototype relational database that records the disposal of radionuclides and/or hazardous chemicals Current regulations in our laboratory require that each such item being discarded must be inventoried and documents must be prepared that summarize the contents of each container used for disposal. Using voice commands, the user enters items into the database as each is discarded. Subsequently, the program prepares the required documentation.

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

    PubMed Central

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

    2015-01-01

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

  7. Results of W-87/Mk21 Deployment Separation Shock Tests

    SciTech Connect

    Avalle, C.A.

    1999-04-21

    This report summarizes results of the W-87/Mk21 Deployment Separation Shock Tests conducted at the Survivability and Vulnerability Integration Center (SVIC) Hill Air Force Base in Ogden, Utah, from 10/5/98 to 10/8/98. Specific details regarding the test plan and procedures can be found in the Master Test Plan listed in the references. Test Objectives: (1) Evaluate the performance of a set of servo accelerometers during and post Re-entry Vehicle (RV) separation events. These ultra-sensitive accelerometers ({mu}g) needed operate during and after the separation shock events and these tests would serve as confirmation of proper functioning. These sensors were later flown on FrU-15, a development flight unit supporting the Instrumented High Fidelity Joint Test Assembly Program, as part of an experimental Inertial Measurement Unit (IMU) measure RV dynamics during RV mechanical separation and spin-up. (2) Measure separation shock response at the IMU accelerometer locations. (3) Measure separation shock response at locations on the warhead and RV common to locations used on MMIII separation tests conducted at LMMS Valley Forge for data comparison.

  8. Hybrid Deployable Foam Antennas and Reflectors

    NASA Technical Reports Server (NTRS)

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

    2006-01-01

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

  9. Lightweight, Self-Deploying Foam Antenna Structures

    NASA Technical Reports Server (NTRS)

    Sokolowski, Witold; Levin, Steven; Rand, Peter

    2004-01-01

    Lightweight, deployable antennas for a variety of outer-space and terrestrial applications would be designed and fabricated according to the concept of cold hibernated elastic memory (CHEM) structures, according to a proposal. Mechanically deployable antennas now in use are heavy, complex, and unreliable, and they utilize packaging volume inefficiently. The proposed CHEM antenna structures would be simple and would deploy themselves without need for any mechanisms and, therefore, would be more reliable. The proposed CHEM antenna structures would also weigh less, could be packaged in smaller volumes, and would cost less, relative to mechanically deployable antennas. The CHEM concept was described in two prior NASA Tech Briefs articles: "Cold Hibernated Elastic Memory (CHEM) Expandable Structures" (NPO-20394), Vol. 23, No. 2 (February 1999), page 56; and "Solar Heating for Deployment of Foam Structures" (NPO-20961), Vol. 25, No. 10 (October 2001), page 36. To recapitulate from the cited prior articles: The CHEM concept is one of utilizing opencell foams of shape-memory polymers (SMPs) to make lightweight, reliable, simple, and inexpensive structures that can be alternately (1) compressed and stowed compactly or (2) expanded, then rigidified for use. A CHEM structure is fabricated at full size from a block of SMP foam in its glassy state [at a temperature below the glass-transition temperature (Tg) of the SMP]. The structure is heated to the rubbery state of the SMP (that is, to a temperature above Tg) and compacted to a small volume. After compaction, the structure is cooled to the glassy state of the SMP. The compacting force can then be released and the structure remains compact as long as the temperature is kept below Tg. Upon subsequent heating of the structure above Tg, the simultaneous elastic recovery of the foam and its shape-memory effect cause the structure to expand to its original size and shape. Once thus deployed, the structure can be rigidified by

  10. 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.

  11. Multifunctional Deployment Hinges Rigidified by Ultraviolet

    NASA Technical Reports Server (NTRS)

    Kerslake, Thomas W.; Simburger, Edward J.; Matusmoto, James; Giants, Thomas W.; Garcia, Alexander; Perry, Alan; Rawal, Suraj; Marshall, Craig; Lin, John Kun Hung; Day, Jonathan Robert; Scarborough, Stephen Emerson

    2005-01-01

    Multifunctional hinges have been developed for deploying and electrically connecting panels comprising planar arrays of thin-film solar photovoltaic cells. In the original intended application of these hinges, the panels would be facets of a 32-sided (and approximately spherical) polyhedral microsatellite (see figure), denoted a PowerSphere, that would be delivered to orbit in a compact folded configuration, then deployed by expansion of gas in inflation bladders. Once deployment was complete, the hinges would be rigidified to provide structural connections that would hold the panels in their assigned relative positions without backlash. Such hinges could also be used on Earth for electrically connecting and structurally supporting solar panels that are similarly shipped in compact form and deployed at their destinations. As shown in section A-A in the figure, a hinge of this type is partly integrated with an inflation bladder and partly integrated with the frame of a solar panel. During assembly of the hinge, strip extensions from a flexible circuit harness on the bladder are connected to corresponding thin-film conductors on the solar panel by use of laser welding and wrap-around contacts. The main structural component of the hinge is a layer of glass fiber impregnated with an ultraviolet-curable resin. After deployment, exposure to ultraviolet light from the Sun cures the resin, thereby rigidifying the hinge.

  12. Environmental issues affecting clean coal technology deployment

    SciTech Connect

    Miller, M.J.

    1997-12-31

    The author outlines what he considers to be the key environmental issues affecting Clean Coal Technology (CCT) deployment both in the US and internationally. Since the international issues are difficult to characterize given different environmental drivers in various countries and regions, the primary focus of his remarks is on US deployment. However, he makes some general remarks, particularly regarding the environmental issues in developing vs. developed countries and how these issues may affect CCT deployment. Further, how environment affects deployment depends on which particular type of clean coal technology one is addressing. It is not the author`s intention to mention many specific technologies other than to use them for the purposes of example. He generally categorizes CCTs into four groups since environment is likely to affect deployment for each category somewhat differently. These four categories are: Precombustion technologies such as coal cleaning; Combustion technologies such as low NOx burners; Postcombustion technologies such as FGD systems and postcombustion NOx control; and New generation technologies such as gasification and fluidized bed combustion.

  13. Advances in spacecraft atmospheric entry guidance

    NASA Astrophysics Data System (ADS)

    Benito Manrique, Joel

    In order to advance entry guidance technology two different research areas have been explored with the objective of increasing the reachable landing area and the landing accuracy for future Mars missions. Currently only the northern hemisphere of Mars is available for landing due to its low elevation. Only low elevation landing sites have the necessary atmospheric density to allow landing using current Entry, Descent and Landing (EDL) technology. In order to reach most of the Ancient Highlands, the majority of the southern hemisphere, advanced EDL technology is needed in multiple fields, including entry guidance. The first research area is the definition and applications of reachable and controllable sets for entry. The definition of the reachable and controllable sets provides a framework for the study of the capabilities of an entry vehicle in a given planet. Reachable and controllable sets can be used to comprehensively characterize the envelope of trajectories that a vehicle can fly, the sites it can reach and the entry states that can be accommodated. The sets can also be used for the evaluation of trajectory planning algorithms and to assist in the selection of the entry or landing sites. In essence, the reachable and controllable sets offer a powerful vehicle and trajectory analysis and design framework that allows for better mission design choices. In order to illustrate the use of the sets, they are computed for a representative Mars mission using two different vehicle configurations. The sets characterize the impact of the vehicle configuration on the entry capability. Furthermore, the sets are used to find the best skip-entry trajectory for a return from the Moon mission, highlighting the utility of the sets in atmospheric maneuvers other than entry. The second research area is the development of the components of an entry guidance algorithm that allow high elevation landing and provide as well high landing accuracy. The approach taken follows the

  14. 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.

  15. Adjustable Bracket For Entry Of Welding Wire

    NASA Technical Reports Server (NTRS)

    Gilbert, Jeffrey L.; Gutow, David A.

    1993-01-01

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

  16. Parachute design for Galileo Jupiter entry probe

    NASA Technical Reports Server (NTRS)

    Rodier, R. W.; Thuss, R. C.; Terhune, J. E.

    1981-01-01

    This paper discusses the parachute subsystem used on an atmospheric entry probe that will descend through the clouds of Jupiter. The entry probe is a part of the Galileo Project to be launched in 1985 aboard the Space Shuttle; the entry probe will encounter the planet in 1988. The parachute subsystem consists of a pilot parachute and a main parachute, and both are of conventional conical ribbon design. Key considerations in the design of the parachutes and a summary of the parachute subsystem test program, which includes two air drop tests and a systems drop test (balloon launched), are presented.

  17. Available hardware for automated entry control

    SciTech Connect

    Holmes, J.P.

    1990-11-01

    Automated entry control has become an increasingly important issue at facilities where budget constraints are limiting options for manned entry control points. Three questions are immediately raised when automated entry control is considered: What hardware is available How much does it cost How effective is it in maintaining security Ongoing work at Sandia National Labs is attempting to answer these questions and establish a data base for use by facility security managers working the problem of how to maintain security on a limited budget. 14 refs.

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

    PubMed

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

    2014-11-01

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

  19. 9 CFR 93.806 - Animals refused entry.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

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

  20. 9 CFR 93.806 - Animals refused entry.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

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

  1. 9 CFR 93.806 - Animals refused entry.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

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

  2. 9 CFR 93.806 - Animals refused entry.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

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

  3. 9 CFR 93.806 - Animals refused entry.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

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

  4. Research on lightweight passive deployment mechanism for the secondary mirror in the deployable space telescope

    NASA Astrophysics Data System (ADS)

    Zhong, Peifeng; Li, Chuang; Jing, Nan; Chong, Yaqin; Ren, Guorui

    2016-10-01

    In this paper, a new type of lightweight passive deployment mechanism based on the tape spring and the shape memory alloy is presented for the secondary mirror of a deployable space telescope. In this passive deployment mechanism for the secondary mirror, the high elastic potential energy of the folded tape springs is used as driving force when the support structure is extended, and the high stiffness characteristics of the circular arc cross section of the tape spring can be used to achieve structure self-locking after deployment. Then a deployable space telescope combined with lightweight passive deployable mechanism for the secondary mirror is designed for applying to nanosatellite imaging. Furthermore, a lock-release device is designed to achieve the function of locking the folded structure and releasing on orbit by taking advantage of the phase transformation characteristics of shape memory alloy with temperature changing. Finally, the correction method for the deployment error of secondary mirror is discussed. The temperature of the tape springs is controlled respectively to make a required length change. This can achieve the purpose of adjusting the position of the secondary mirror and improve the deployment accuracy.

  5. Deployment of human-machine dialogue systems.

    PubMed Central

    Roe, D B

    1995-01-01

    The deployment of systems for human-to-machine communication by voice requires overcoming a variety of obstacles that affect the speech-processing technologies. Problems encountered in the field might include variation in speaking style, acoustic noise, ambiguity of language, or confusion on the part of the speaker. The diversity of these practical problems encountered in the "real world" leads to the perceived gap between laboratory and "real-world" performance. To answer the question "What applications can speech technology support today?" the concept of the "degree of difficulty" of an application is introduced. The degree of difficulty depends not only on the demands placed on the speech recognition and speech synthesis technologies but also on the expectations of the user of the system. Experience has shown that deployment of effective speech communication systems requires an iterative process. This paper discusses general deployment principles, which are illustrated by several examples of human-machine communication systems. Images Fig. 1 PMID:7479719

  6. Preliminary design method for deployable spacecraft beams

    NASA Technical Reports Server (NTRS)

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

    1995-01-01

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

  7. Deploying Embodied AI into Virtual Worlds

    NASA Astrophysics Data System (ADS)

    Burden, David J. H.

    The last two years have seen the start of commercial activity within virtual worlds. Unlike computer games where Non-Player-Character avatars are common, in most virtual worlds they are the exception — and until recently in Second Life they were non-existent. However there is real commercial scope for Als in these worlds — in roles from virtual sales staff and tutors to personal assistants. Deploying an embodied AI into a virtual world offers a unique opportunity to evaluate embodied Als, and to develop them within an environment where human and computer are on almost equal terms. This paper presents an architecture being used for the deployment of chatbot driven avatars within the Second Life virtual world, looks at the challenges of deploying an AI within such a virtual world, the possible implications for the Turing Test, and identifies research directions for the future.

  8. Deploying Darter A Cray XC30 System

    SciTech Connect

    Fahey, Mark R; Budiardja, Reuben D; Crosby, Lonnie D; McNally, Stephen T

    2014-01-01

    TheUniversityofTennessee,KnoxvilleacquiredaCrayXC30 supercomputer, called Darter, with a peak performance of 248.9 Ter- aflops. Darter was deployed in late March of 2013 with a very aggressive production timeline - the system was deployed, accepted, and placed into production in only 2 weeks. The Spring Experiment for the Center for Analysis and Prediction of Storms (CAPS) largely drove the accelerated timeline, as the experiment was scheduled to start in mid-April. The Consortium for Advanced Simulation of Light Water Reactors (CASL) project also needed access and was able to meet their tight deadlines on the newly acquired XC30. Darter s accelerated deployment and op- erations schedule resulted in substantial scientific impacts within the re- search community as well as immediate real-world impacts such as early severe tornado warnings

  9. Thermal static bending of deployable interlocked booms

    NASA Technical Reports Server (NTRS)

    Staugaitis, C. L.; Predmore, R. E.

    1973-01-01

    Metal ribbons processed with a heat-forming treatment are enabled to form tubelike structures when deployed from a roll. Deployable booms of this have been utilized for gravity-gradient stabilization on the RAE, ATS, and Nimbus D satellites. An experimental thermal-mechanics test apparatus was developed to measure the thermal static bending and twist of booms up to 3 meters long. The apparatus was calibrated by using the correlation between calculated and observed thermal bending of a seamless tube. Thermal static bending values of 16 interlocked deployable booms were observed to be within a factor of 2.5 of the values calculated from seamless-tube theory. Out-of-Sun-plane thermal bending was caused by complex heat transfer across the interlocked seam. Significant thermal static twisting was not observed.

  10. Deployment Instabilities of Lobed-Pumpkin Balloon

    NASA Astrophysics Data System (ADS)

    Nakashino, Kyoichi

    A lobed-pumpkin balloon, currently being developed in ISAS/JAXA as well as in NASA, is a promising vehicle for long duration scientific observations in the stratosphere. Recent ground and flight experiments, however, have revealed that the balloon has deployment instabilities under certain conditions. In order to overcome the instability problems, a next generation SPB called 'tawara' type balloon has been proposed, in which an additional cylindrical part is appended to the standard lobed-pumpkin balloon. The present study investigates the deployment stability of tawara type SPB in comparison to that of standard lobed-pumpkin SPB through eigenvalue analysis on the basis of finite element methods. Our numerical results show that tawara type SPB enjoys excellent deployment performance over the standard lobed-pumpkin SPBs.

  11. The Propulsive Small Expendable Deployer System Experiment

    NASA Technical Reports Server (NTRS)

    Johnson, Les; Estes, Robert D.; Lorenzini, Enrico; Martinez-Sanchez, Manual; Sanmartin, Juan

    1999-01-01

    Relatively short electrodynamic tethers can extract orbital energy to 'push' against a planetary magnetic field to achieve propulsion without the expenditure of propellant. The Propulsive Small Expendable Deployer System experiment will use the flight-proven Small Expendable Deployer System (SEDS) to deploy a 5 km bare copper tether from a Delta II upper stage to achieve approximately 0.4 N drag thrust, thus lowering the altitude of the stage. The experiment will use a predominantly 'bare' tether for current collection in lieu of the endmass collector and insulated tether approach used on previous missions. The flight experiment is a precursor to a more ambitious electrodynamic tether upper stage demonstration mission which will be capable of orbit raising, lowering and inclination changes - all using electrodynamic thrust. The expected performance of the tether propulsion system during the experiment is described.

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

    NASA Astrophysics Data System (ADS)

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

    2016-10-01

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

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

    NASA Technical Reports Server (NTRS)

    HayaRamos, Rodrigo; Boneti, Davide

    2007-01-01

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

  14. Mathematical Interpretation of Observational Data of the Stardust SRC Re-Entry

    NASA Astrophysics Data System (ADS)

    Gritsevich, M. I.

    2009-01-01

    STARDUST spacecraft was launched on February 7, 1999. STARDUST is the first U.S. Space mission dedicated solely to the exploration of a comet, and the first robotic mission designed to return extraterrestrial material from outside the orbit of the Moon. But studying of observational data of the STARDUST Sample Return Capsule's (SRC) entry into Earth's atmosphere on January 15, 2006, also represent a big interest. At a velocity of 12.8 km/s (assumed to be at an altitude of 125 km) SRC was the fastest ever attempted re-entry of a human made space vehicle. The return trajectory of the SRC is very similar to that of natural cosmic bodies. Entry begins when the spacecraft reorients for SRC release from the spacecraft bus and ends with parachute deployment. In the present report, an analytical model of the atmospheric entry is calculated using the data of actual observations, by selecting the parameters describing rate of deceleration of the body during its hypersonic flight. Model was applied to the observational data of STARDUST Sample Return Capsule (a hypersonic phase). The estimate of mass of SRC obtained using the data of actual observations is quite close to its real value of 45.8 kg.

  15. Retrieval of the ESA Huygens Probe Entry and Descent Trajectory at Titan

    NASA Astrophysics Data System (ADS)

    Kazeminejad, B.; Atkinson, D. H.; Lebreton, J.-P.; Witasse, O.; Perez, M.; DTWG Team

    2005-08-01

    The Huygens probe was released from the Cassini spacecraft on December 25, 2004 and arrived at Titan for atmospheric entry and surface descent on January 14, 2005. The Huygens entry and descent trajectory reconstruction commenced with the Huygens probe state vector at the entry interface point (defined to be at an altitude of 1270 km above the surface of Titan) as provided by the Cassini Navigation Team at JPL. Integration of the equations of motion using measured accelerations provided the Huygens trajectory beyond the point of initial parachute deployment. From the surface, the Huygens descent trajectory was reconstructed upwards using pressure and temperature measurements from the Atmospheric Structure Instrument, N2/CH4 mole fractions from the Gas Chromatograph and Mass Spectrometer, and the impact time measured by the Surface Science Package penetrometer. Longitudinal drift was provided by the Huygens Doppler Wind Experiment. The entry and descent phases of the trajectory reconstructions were merged by adjustment of the initial state vector. The Huygens trajectory was reconstructed to be maximally consistent with all available science and engineering data.

  16. Reintegration Difficulty of Military Couples Following Deployment

    DTIC Science & Technology

    2015-07-01

    couples; mental health; anxiety; depression ; posttraumatic stress; relationship satisfaction; relational turbulence 16. SECURITY CLASSIFICATION OF: 17...guidelines for reintegration. 2. Keywords reintegration difficulty; military couples; mental health; anxiety; depression ; posttraumatic stress...transitions such as the entry into middle school and the arrival of puberty, combating the onset of symptoms of depression and anxiety (e.g

  17. A User-Driven and Data-Driven Approach for Supporting Teachers in Reflection and Adaptation of Adaptive Tutorials

    ERIC Educational Resources Information Center

    Ben-Naim, Dror; Bain, Michael; Marcus, Nadine

    2009-01-01

    It has been recognized that in order to drive Intelligent Tutoring Systems (ITSs) into mainstream use by the teaching community, it is essential to support teachers through the entire ITS process: Design, Development, Deployment, Reflection and Adaptation. Although research has been done on supporting teachers through design to deployment of ITSs,…

  18. Mars pathfinder Rover egress deployable ramp assembly

    NASA Technical Reports Server (NTRS)

    Spence, Brian R.; Sword, Lee F.

    1996-01-01

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

  19. Clevis joint for deployable space structures

    NASA Technical Reports Server (NTRS)

    Rhodes, Marvin D. (Inventor)

    1990-01-01

    This invention relates generally to pin clevis joints, and more particularly, to zero play pin clevis joints for connecting structural members of a deployable space structure. A joint includes a pin, a tang, and a shackle. The pin is tapered at the same angle as the bores extending through the projections of the shackle and the tang. A spring washer biases the tang onto the tapered sidewall of the pin. The invention solves the free play problem associated with deployable space structures by using a tapered pin which is held in tapered holes by the spring washers.

  20. Research on testing software for rapid cloud deployment

    NASA Astrophysics Data System (ADS)

    Chen, Yuanjin; Huang, Junfei; Ji, Xin

    2017-01-01

    Software testing is an important way to ensure the quality of software systems and services, but the ever-changing needs of software testing, in particular the size of the dynamic test requirements getting stronger. The traditional deployment way of testing software is complex and it is difficult to scale to meet the dynamic test requirements. With the rapid development of cloud computing technology, traditional testing software after modified can run in the cloud as well. This paper proposed building a cloud service platform based on cloud service provider, which combines several of cloud service to adapt to software testing. With this cloud service platform, software developer can run their testing software in the cloud quickly and test scale can stretch dynamically. Furthermore, it is possible to reduce the cost of testing because of the pay-for-use cloud computing.

  1. SMOS PLM MIRAS hold-down release and deployment mechanisms

    NASA Astrophysics Data System (ADS)

    Bueno, José I.; García, Ignacio; Plaza, Miguel A.

    2005-07-01

    The hold-down, release and deployment mechanisms designed for SMOS PLM MIRAS have been a challenging activity in terms of design compromise, schedule and cost effectiveness. The existing design coming from previous phase was totally reanalysed to be adapted to a specific mission with extra requirements, making the previous design not totally valid as it was conceptually conceived. Novel concepts were implemented to maintain the feasibility of the design, providing compliance to new and more restrictive requirements. Exhaustive testing proved those concepts and provided the necessary maturity to be valid for flight. This paper is focused on all those new concepts and novelties implemented in phase C/D for the SMOS PLM Instrument Mechanisms as to reach the compliance to the applicable specification.

  2. Development of Norms for the Post-deployment Reintegration Scale

    DTIC Science & Technology

    2010-09-01

    perspective. Recognizing the importance of successful post-deployment reintegration to optimal operational readiness, Canadian military researchers...of successful post-deployment reintegration to optimal operational readiness, Canadian military researchers developed the Army Post- Deployment... successful post-deployment reintegration to optimal operational readiness, and attempting to address the gaps and limitations of existing

  3. Generic aerocapture atmospheric entry study, volume 1

    NASA Technical Reports Server (NTRS)

    1980-01-01

    An atmospheric entry study to fine a generic aerocapture vehicle capable of missions to Mars, Saturn, and Uranus is reported. A single external geometry was developed through atmospheric entry simulations. Aerocapture is a system design concept which uses an aerodynamically controlled atmospheric entry to provide the necessary velocity depletion to capture payloads into planetary orbit. Design concepts are presented which provide the control accuracy required while giving thermal protection for the mission payload. The system design concepts consist of the following elements: (1) an extendable biconic aerodynamic configuration with lift to drag ratio between 1.0 and 2.0; (2) roll control system concepts to control aerodynamic lift and disturbance torques; (3) aeroshell design concepts capable of meeting dynamic pressure loads during aerocapture; and (4) entry thermal protection system design concepts to meet thermodynamic loads during aerocapture.

  4. Remodeling of Calcium Entry Pathways in Cancer.

    PubMed

    Villalobos, Carlos; Sobradillo, Diego; Hernández-Morales, Miriam; Núñez, Lucía

    2016-01-01

    Ca(2+) entry pathways play important roles in control of many cellular functions, including long-term proliferation, migration and cell death. In recent years, it is becoming increasingly clear that, in some types of tumors, remodeling of Ca(2+) entry pathways could contribute to cancer hallmarks such as excessive proliferation, cell migration and invasion as well as resistance to cell death or survival. In this chapter we briefly review findings related to remodeling of Ca(2+) entry pathways in cancer with emphasis on the mechanisms that contribute to increased store-operated Ca(2+) entry (SOCE) and store-operated currents (SOCs) in colorectal cancer cells. Finally, since SOCE appears critically involved in colon tumorogenesis, the inhibition of SOCE by aspirin and other NSAIDs and its possible contribution to colon cancer chemoprevention is reviewed.

  5. Multiscale perspectives of virus entry via endocytosis.

    PubMed

    Barrow, Eric; Nicola, Anthony V; Liu, Jin

    2013-06-05

    Most viruses take advantage of endocytic pathways to gain entry into host cells and initiate infections. Understanding of virus entry via endocytosis is critically important for the design of antiviral strategies. Virus entry via endocytosis is a complex process involving hundreds of cellular proteins. The entire process is dictated by events occurring at multiple time and length scales. In this review, we discuss and evaluate the available means to investigate virus endocytic entry, from both experimental and theoretical/numerical modeling fronts, and highlight the importance of multiscale features. The complexity of the process requires investigations at a systems biology level, which involves the combination of different experimental approaches, the collaboration of experimentalists and theorists across different disciplines, and the development of novel multiscale models.

  6. Entry/Exit Port testing, test report

    SciTech Connect

    Winkelman, R.H.

    1993-05-01

    The Waste Receiving and Processing Module I (WRAP-1) facility must have the ability to allow 55-gallon drums to enter and exit glovebox enclosures. An Entry/Exit Port (Appendix 1, Figure 1), designed by United Engineers and Constructors (UE&C), is one method chosen for drum transfer. The Entry/Exit Port is to be used for entry of 55-gallon drums into both process entry gloveboxes, exit of 55-gallon drum waste pucks from the low-level waste (LLW) glovebox, and loadout of waste from the restricted waste management glovebox. The Entry/Exit Port relies on capture velocity air flow and a neoprene seal to provide alpha confinement when the Port is in the open and closed positions, respectively. Since the glovebox is in a slight vacuum, air flow is directed into the glovebox through the space between the overpack drum and glovebox floor. The air flow is to direct any airborne contamination into the glovebox. A neoprene seal is used to seal the Port door to the glovebox floor, thus maintaining confinement in the closed position. Entry/Exit Port testing took place February 17, 1993, through April 14, 1993, in the 305 building of Westinghouse Hanford Company. Testing was performed in accordance with the Entry/Exit Port Testing Test Plan, document number WHC-SD-WO26-TP-005. A prototype Entry/Exit Port built at the Hanford Site was tested using fluorescent paint pigment and smoke candles as simulant contaminants. This test report is an interim test report. Further developmental testing is required to test modifications made to the Port as the original design of the Port did not provide complete confinement during all stages of operation.

  7. 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)

  8. Nine Degrees-of-Freedom Parachute Model for Exomars Entry Descent and Landing

    NASA Astrophysics Data System (ADS)

    Calantropio, F.; Langlois, S.; Portigliotti, S.; Parisch, M.; DeSanctis, S.

    2012-08-01

    The interest of the planetary re-entry programs and the acknowledgment that the parachute simplified (drag equivalent) models are affected by limitations in their applicability, drove the need to develop the capability of simulate the EDL parachute phase with an additional 3 DoF body which works as decelerator of a 6 DoF forebody.The proposed model summarizes the capability to simulate the complete parachute behavior, which includes different phases as the ejection, the deployment, the inflation and the steady state descent, by means of a reduced set of the equations used to model the decelerator to a minimum of 3 DoF.

  9. Dynamics of an Unstabilized Spacecraft During the Deployment of an Elastic Pantograph Structure

    NASA Astrophysics Data System (ADS)

    Zakrzhevskii, A. E.; Khoroshilov, V. S.

    2014-05-01

    An unstabilized spacecraft with a pantograph structure deployed in orbit to carry solar batteries is the subject of study. The objective of the study is to construct a mathematical model of this system taking into account the elastic properties of elements of the pantograph in longitudinal and transverse directions. This model is based on the Lagrangian formalism as applied to a mechanical system with rheonomic constraints. The expressions for the coefficients of the equations of motions are obtained using Mathematica 5©. A Fortran application software package is used for numerical simulation of dynamic processes. This package can be adapted, if necessary, to study other structures. The behavior of the spacecraft during the deployment of the pantograph is numerically analyzed using different values of spacecraft parameters and the parameters of the deployment process in the gravity field.

  10. Decision tools for bacterial blight resistance gene deployment in rice-based agricultural ecosystems

    PubMed Central

    Dossa, Gerbert S.; Sparks, Adam; Cruz, Casiana Vera; Oliva, Ricardo

    2015-01-01

    Attempting to achieve long-lasting and stable resistance using uniformly deployed rice varieties is not a sustainable approach. The real situation appears to be much more complex and dynamic, one in which pathogens quickly adapt to resistant varieties. To prevent disease epidemics, deployment should be customized and this decision will require interdisciplinary actions. This perspective article aims to highlight the current progress on disease resistance deployment to control bacterial blight in rice. Although the model system rice-Xanthomonas oryzae pv. oryzae has distinctive features that underpin the need for a case-by-case analysis, strategies to integrate those elements into a unique decision tool could be easily extended to other crops. PMID:25999970

  11. Decision tools for bacterial blight resistance gene deployment in rice-based agricultural ecosystems.

    PubMed

    Dossa, Gerbert S; Sparks, Adam; Cruz, Casiana Vera; Oliva, Ricardo

    2015-01-01

    Attempting to achieve long-lasting and stable resistance using uniformly deployed rice varieties is not a sustainable approach. The real situation appears to be much more complex and dynamic, one in which pathogens quickly adapt to resistant varieties. To prevent disease epidemics, deployment should be customized and this decision will require interdisciplinary actions. This perspective article aims to highlight the current progress on disease resistance deployment to control bacterial blight in rice. Although the model system rice-Xanthomonas oryzae pv. oryzae has distinctive features that underpin the need for a case-by-case analysis, strategies to integrate those elements into a unique decision tool could be easily extended to other crops.

  12. Hypersonic and planetary entry flight mechanics

    NASA Technical Reports Server (NTRS)

    Vinh, N. X.; Busemann, A.; Culp, R. D.

    1980-01-01

    The book treats hypersonic flight trajectories and atmospheric entry flight mechanics in light of their importance for space shuttle entry. Following a review of the structures of planetary atmospheres and aerodynamic forces, equations are derived for flight over a spherical planet, and the performance of long-range hypervelocity vehicles in extra-atmospheric flight is analyzed. Consideration is then given to vehicle trajectories in the powered and atmospheric reentry phases of flight, and several first-order solutions are derived for various planetary entry situations. The second-order theory of Loh for entry trajectories is presented along with the classical theories of Yaroshevskii and Chapman for entry into planetary atmospheres, and the thermal problems encountered in hypersonic flight are analyzed. A unified theory for entry into planetary atmospheres is then introduced which allows the performance of a general type of lifting vehicle to be studied, and applied to the analysis of orbit contraction due to atmospheric drag, flight with lift modulation and lateral maneuvers.

  13. Models of radon entry: A review

    SciTech Connect

    Gadgil, A.J.

    1991-08-01

    This paper reviews existing models of radon entry into houses. The primary mechanism of radon entry in houses with high indoor concentrations is, in most cases, convective entry of radon bearing soil-gas from the surrounding soil. The driving force for this convective entry is the small indoor-outdoor pressure difference arising from the stack effect and other causes. Entry points for the soil-gas generally are the cracks or gaps in the building substructure, or though other parts of the building shell in direct contact with the soil, although entry may also occur by flow though permeable concrete or cinder block walls of the substructure. Models using analytical solutions to idealized geometrical configurations with simplified boundary conditions obtain analytical tractability of equations to be solved at the cost of severe approximations; their strength is in the insights they offer with their solutions. Models based on lumped parameters attempt to characterize the significant physical behavioral characteristics of the soil-gas and radon flow. When realistic approximations are desired for the boundary conditions and terms in the governing equations, numerical models must be used; these are usually based on finite difference or finite element solutions to the governing equations. Limited data are now available for experimental verification of model predictions. The models are briefly reviewed and their strengths and limitations are discussed.

  14. Well engineering for re-entry operations

    SciTech Connect

    1996-10-01

    Oil and gas operators are constantly looking at their existing assets for ways to increase their value. Several operators consider a re-entry program as the principle leveraging technology in strategic acquisitions. Much of the current re-entry operations effort targets the longer reach sidetrack and multilateral well markets. The key to this effort, whether it involves coiled tubing drilling, short radius drilling or multilateral well technologies, is re-entry well engineering. The engineer evaluating a re-entry prospect must apply significant levels of reservoir engineering, rock mechanics, completion engineering and drilling engineering to properly design the well and develop successful procedures. Re-entry drilling means that the operator is working with proven or probable reserves. Completion design and engineering are the most important aspects of well design once the target has been selected. Ultimately, the completion design selected will dictate the type of re-entry program: slot recovery, drilling out below the current casing shoe, or section milling and whipstock sidetracking. It can also dictate the principle aspects of the drilling program. The acceptable wellbore inclination build rates (dogleg severity), wellbore length, and drilling fluid selection are commonly influenced and even dictated by the completion design. These factors are discussed.

  15. Nipah virus entry can occur by macropinocytosis

    SciTech Connect

    Pernet, Olivier; Pohl, Christine; Ainouze, Michelle; Kweder, Hasan; Buckland, Robin

    2009-12-20

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

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

    NASA Technical Reports Server (NTRS)

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

    1976-01-01

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

  17. Los Alamos National Laboratory Tritium Technology Deployments Large Scale Demonstration and Deployment Project

    SciTech Connect

    McFee, J.; Blauvelt, D.; Stallings, E.; Willms, S.

    2002-02-26

    This paper describes the organization, planning and initial implementation of a DOE OST program to deploy proven, cost effective technologies into D&D programs throughout the complex. The primary intent is to accelerate closure of the projects thereby saving considerable funds and at the same time being protective of worker health and the environment. Most of the technologies in the ''toolkit'' for this program have been demonstrated at a DOE site as part of a Large Scale Demonstration and Deployment Project (LSDDP). The Mound Tritium D&D LSDDP served as the base program for the technologies being deployed in this project but other LSDDP demonstrated technologies or ready-for-use commercial technologies will also be considered. The project team will evaluate needs provided by site D&D project managers, match technologies against those needs and rank deployments using a criteria listing. After selecting deployments the project will purchase the equipment and provide a deployment engineer to facilitate the technology implementation. Other cost associated with the use of the technology will be borne by the site including operating staff, safety and health reviews etc. A cost and performance report will be prepared following the deployment to document the results.

  18. Diogenes, Dogfaced Soldiers, and Deployment Music Videos

    ERIC Educational Resources Information Center

    Carter, Geoffrey; Williamson, Bill

    2010-01-01

    This webtext explores the cynical/kynical humor of soldier videos, suggesting that amateur videos paradoxically both undercut authority and honor effective leaders, both make light of and also publicly reveal deployment hardships, both distance the performers from military groupthink and celebrate unit camaraderie.

  19. Solar array deployment from a spinning spacecraft

    NASA Technical Reports Server (NTRS)

    Carlin, A. H.; Gardner, J. B.; Lassen, H. A.

    1974-01-01

    Cylindrical drum, wrapped with flexible solar array of solar cells mounted on Mylar sheet, is held by two end-fittings with cable (under tension) passing through axel of drum. Drum is held to end-fittings by axial cable through drum axel; drum is released for deployment when cable is cut at each end and end-fittings spring outward.

  20. Military Deployment and Elementary Student Achievement

    ERIC Educational Resources Information Center

    Phelps, Terri; Dunham, Mardis; Lyons, Robert

    2010-01-01

    This study investigated the impact that military deployment has upon academic achievement of elementary school students. TerraNova test scores of 137 fourth and fifth grade students in two elementary schools with a high proportion of military dependent children were examined for two consecutive years. Although the academic test performance fell…

  1. Launch Deployment Assembly Human Engineering Analysis

    NASA Technical Reports Server (NTRS)

    Loughead, T.

    1996-01-01

    This report documents the human engineering analysis performed by the Systems Branch in support of the 6A cargo element design. The human engineering analysis is limited to the extra vehicular activities (EVA) which are involved in removal of various cargo items from the LDA and specific activities concerning deployment of the Space Station Remote Manipulator System (SSRMS).

  2. Strategic Deployment Requirements for an Expeditionary Army

    DTIC Science & Technology

    2007-03-29

    operations will directly depend on effective integration of Army combat system development, deployment infrastructure and evolution of strategic lift...Enduring Freedom, (Air Force Historical Research Agency, 14 November 2002), 6. 40 Eastward, the pilings of the bridge were Moron (Spain), Rhein

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

    SciTech Connect

    Esposito, Anthony M.; Cheung, Pamela; Swartz, Talia H.; Li, Hongru; Tsibane, Tshidi; Durham, Natasha D.; Basler, Christopher F.; Felsenfeld, Dan P.; Chen, Benjamin K.

    2016-03-15

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

  4. Identification of and At-Risk Interventions for Pre-Deployment Psychophysiologic Predictors of PostDeployment Mental Health Outcomes

    DTIC Science & Technology

    2014-06-01

    symptoms. Low HRV is associated with increased physical and emotional stress . The time between pre-deployment SDNN and post-deployment PTSD symptom...objective pre-deployment predictors for post- deployment post-traumatic stress disorder (PTSD) and to test two pre-deployment interventions designed...laptop computers. Task 4: Modify existing video game stress inoculation biofeedback training for use in the study (Mos. 1-6): • Modify existing

  5. Deployment Experiences of British Army Wives Before, During and After Deployment: Satisfaction with Military Life and Use of Support Networks

    DTIC Science & Technology

    2006-04-01

    RTO-MP-HFM-134 38 - 1 Deployment Experiences of British Army Wives Before, During and After Deployment: Satisfaction with Military Life ...Experiences of British Army Wives Before, During and After Deployment: Satisfaction with Military Life and Use of Support Networks. In Human Dimensions...COVERED - 4. TITLE AND SUBTITLE Deployment Experiences of British Army Wives Before, During and After Deployment: Satisfaction with Military Life

  6. 19 CFR 142.44 - Entry number range.

    Code of Federal Regulations, 2010 CFR

    2010-04-01

    ... 19 Customs Duties 2 2010-04-01 2010-04-01 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...

  7. 19 CFR 142.44 - Entry number range.

    Code of Federal Regulations, 2011 CFR

    2011-04-01

    ... 19 Customs Duties 2 2011-04-01 2011-04-01 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...

  8. 19 CFR 142.44 - Entry number range.

    Code of Federal Regulations, 2012 CFR

    2012-04-01

    ... 19 Customs Duties 2 2012-04-01 2012-04-01 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...

  9. 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...

  10. 19 CFR 142.44 - Entry number range.

    Code of Federal Regulations, 2014 CFR

    2014-04-01

    ... 19 Customs Duties 2 2014-04-01 2014-04-01 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...

  11. 7 CFR 319.24-5 - Condition of entry.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

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

  12. 7 CFR 319.24-5 - Condition of entry.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

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

  13. 7 CFR 319.24-5 - Condition of entry.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

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

  14. 7 CFR 319.24-5 - Condition of entry.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

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

  15. 7 CFR 319.24-5 - Condition of entry.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

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

  16. 7 CFR 319.8-26 - Material refused entry.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ..., or other expenses incidental to the safeguarding or disposal of material refused entry by the... 7 Agriculture 5 2014-01-01 2014-01-01 false Material refused entry. 319.8-26 Section 319.8-26... Provisions § 319.8-26 Material refused entry. Any material refused entry for noncompliance with...

  17. 7 CFR 319.8-26 - Material refused entry.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ..., or other expenses incidental to the safeguarding or disposal of material refused entry by the... 7 Agriculture 5 2011-01-01 2011-01-01 false Material refused entry. 319.8-26 Section 319.8-26... Provisions § 319.8-26 Material refused entry. Any material refused entry for noncompliance with...

  18. 7 CFR 319.8-26 - Material refused entry.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ..., or other expenses incidental to the safeguarding or disposal of material refused entry by the... 7 Agriculture 5 2012-01-01 2012-01-01 false Material refused entry. 319.8-26 Section 319.8-26... Provisions § 319.8-26 Material refused entry. Any material refused entry for noncompliance with...

  19. 7 CFR 319.8-26 - Material refused entry.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ..., or other expenses incidental to the safeguarding or disposal of material refused entry by the... 7 Agriculture 5 2010-01-01 2010-01-01 false Material refused entry. 319.8-26 Section 319.8-26... Provisions § 319.8-26 Material refused entry. Any material refused entry for noncompliance with...

  20. 48 CFR 52.225-8 - Duty-Free Entry.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... 48 Federal Acquisition Regulations System 2 2012-10-01 2012-10-01 false Duty-Free Entry. 52.225-8...-Free Entry. As prescribed in 25.1101(e), insert the following clause: Duty-Free Entry (OCT 2010) (a... accorded duty-free entry. (c) Except as provided in paragraph (d) of this clause or elsewhere in...

  1. 48 CFR 52.225-8 - Duty-Free Entry.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... 48 Federal Acquisition Regulations System 2 2013-10-01 2013-10-01 false Duty-Free Entry. 52.225-8...-Free Entry. As prescribed in 25.1101(e), insert the following clause: Duty-Free Entry (OCT 2010) (a... accorded duty-free entry. (c) Except as provided in paragraph (d) of this clause or elsewhere in...

  2. 48 CFR 52.225-8 - Duty-Free Entry.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... 48 Federal Acquisition Regulations System 2 2011-10-01 2011-10-01 false Duty-Free Entry. 52.225-8...-Free Entry. As prescribed in 25.1101(e), insert the following clause: Duty-Free Entry (OCT 2010) (a... accorded duty-free entry. (c) Except as provided in paragraph (d) of this clause or elsewhere in...

  3. 48 CFR 52.225-8 - Duty-Free Entry.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 48 Federal Acquisition Regulations System 2 2010-10-01 2010-10-01 false Duty-Free Entry. 52.225-8...-Free Entry. As prescribed in 25.1101(e), insert the following clause: Duty-Free Entry (OCT 2010) (a... accorded duty-free entry. (c) Except as provided in paragraph (d) of this clause or elsewhere in...

  4. 7 CFR 319.8-26 - Material refused entry.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ..., or other expenses incidental to the safeguarding or disposal of material refused entry by the... 7 Agriculture 5 2013-01-01 2013-01-01 false Material refused entry. 319.8-26 Section 319.8-26... Provisions § 319.8-26 Material refused entry. Any material refused entry for noncompliance with...

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

    PubMed Central

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

    2016-01-01

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

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

    PubMed

    Yap, Florence G H; Yen, Hong-Hsu

    2016-12-30

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

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

    PubMed Central

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

    2016-01-01

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

  8. Rhizobacteria Bacillus subtilis restricts foliar pathogen entry through stomata.

    PubMed

    Kumar, Amutha Sampath; Lakshmanan, Venkatachalam; Caplan, Jeffrey L; Powell, Deborah; Czymmek, Kirk J; Levia, Delphis F; Bais, Harsh P

    2012-11-01

    Plants exist in a complex multitrophic environment, where they interact with and compete for resources with other plants, microbes and animals. Plants have a complex array of defense mechanisms, such as the cell wall being covered with a waxy cuticle serving as a potent physical barrier. Although some pathogenic fungi infect plants by penetrating through the cell wall, many bacterial pathogens invade plants primarily through stomata on the leaf surface. Entry of the foliar pathogen, Pseudomonas syringae pathovar tomato DC3000 (hereafter PstDC3000), into the plant corpus occurs through stomatal openings, and consequently a key plant innate immune response is the transient closure of stomata, which delays disease progression. Here, we present evidence that the root colonization of the rhizobacteria Bacillus subtilis FB17 (hereafter FB17) restricts the stomata-mediated pathogen entry of PstDC3000 in Arabidopsis thaliana. Root binding of FB17 invokes abscisic acid (ABA) and salicylic acid (SA) signaling pathways to close light-adapted stomata. These results emphasize the importance of rhizospheric processes and environmental conditions as an integral part of the plant innate immune system against foliar bacterial infections.

  9. Rebuilding a Maintenance Program After Deployment

    DTIC Science & Technology

    2011-12-01

    experience came a lack of oversight of subordinate unit maintenance programs, which led to errors in initial data entry into unit Standard Army Maintenance...unclassified b. ABSTRACT unclassified c. THIS PAGE unclassified Standard Form 298 (Rev. 8-98) Prescribed by ANSI Std Z39-18 September–December...what leaders should be checking during command maintenance, demonstrated capabilities, and reinforced maintenance standards . Classes ranged from 10 to

  10. Wing Deployment Sequence #2: The deployable, inflatable wing technology demonstrator experiment airc

    NASA Technical Reports Server (NTRS)

    2001-01-01

    Wing Deployment Sequence #2: The deployable, inflatable wing technology demonstrator experiment aircraft's wings continue deploying following separation from its carrier aircraft during a flight conducted by the NASA Dryden Flight Research Center, Edwards, California. The inflatable wing project represented a basic flight research effort by Dryden personnel. Three successful flights of the I2000 inflatable wing aircraft occurred. During the flights, the team air-launched the radio-controlled (R/C) I2000 from an R/C utility airplane at an altitude of 800-1000 feet. As the I2000 separated from the carrier aircraft, its inflatable wings 'popped-out,' deploying rapidly via an on-board nitrogen bottle. The aircraft remained stable as it transitioned from wingless to winged flight. The unpowered I2000 glided down to a smooth landing under complete control.

  11. Wing Deployment Sequence #3: The deployable, inflatable wing technology demonstrator experiment airc

    NASA Technical Reports Server (NTRS)

    2001-01-01

    Wing Deployment Sequence #3: The deployable, inflatable wing technology demonstrator experiment aircraft's wings fully deployed during flight following separation from its carrier aircraft during a flight conducted by the NASA Dryden Flight Research Center, Edwards, Californiaornia. The inflatable wing project represented a basic flight research effort by Dryden personnel. Three successful flights of the I2000 inflatable wing aircraft occurred. During the flights, the team air-launched the radio-controlled (R/C) I2000 from an R/C utility airplane at an altitude of 800-1000 feet. As the I2000 separated from the carrier aircraft, its inflatable wings 'popped-out,' deploying rapidly via an on-board nitrogen bottle. The aircraft remained stable as it transitioned from wingless to winged flight. The unpowered I2000 glided down to a smooth landing under complete control.

  12. Wing Deployment Sequence #1: The deployable, inflatable wing technology demonstrator experiment airc

    NASA Technical Reports Server (NTRS)

    2001-01-01

    Wing Deployment Sequence #1: The deployable, inflatable wing technology demonstrator experiment aircraft's wings begin deploying following separation from its carrier aircraft during a flight conducted by the NASA Dryden Flight Research Center, Edwards, California. The inflatable wing project represented a basic flight research effort by Dryden personnel. Three successful flights of the I2000 inflatable wing aircraft occurred. During the flights, the team air-launched the radio-controlled (R/C) I2000 from an R/C utility airplane at an altitude of 800-1000 feet. As the I2000 separated from the carrier aircraft, its inflatable wings 'popped-out,' deploying rapidly via an on-board nitrogen bottle. The aircraft remained stable as it transitioned from wingless to winged flight. The unpowered I2000 glided down to a smooth landing under complete control.

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

    NASA Astrophysics Data System (ADS)

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

    2017-02-01

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

  14. Entry Year Pilot Project: A Reflective Approach to Mentoring Ohio's Entry Year Teachers.

    ERIC Educational Resources Information Center

    Murray, Susan R.; Hillkirk, Keith

    This monograph describes Ohio University College of Education's Entry Year Pilot Project. The College of Education was awarded grant money to create and implement a mentoring program to help entry-year teachers through their first year and through the Praxis III assessment. The project involved beginning teachers, school-level mentors, and…

  15. 76 FR 66875 - Informal Entry Limit and Removal of a Formal Entry Requirement

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-28

    ... reduced the value of that amount in real terms. Consequently, CBP proposes to raise the current informal... reduce the administrative burden on importers and other entry filers. Moreover, CBP proposes to remove... proposed change will reduce the overall administrative burden on importers and ] other entry filers...

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

    NASA Technical Reports Server (NTRS)

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

    2013-01-01

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

  17. Effect of Cognitive Entry Behaviors and Affective Entry Characteristics on Learning Level

    ERIC Educational Resources Information Center

    Çaliskan, Muhittin

    2014-01-01

    In this study, the effect of cognitive entry behaviors and affective entry characteristics on learning level was investigated. The study was conducted on 258 first year students attending the Faculty of Education in the autumn semester of the 2011-2012 academic year. The study was conducted using the relational survey model and data was collected…

  18. Autophagy, Immunity, and Microbial Adaptations

    PubMed Central

    Deretic, Vojo; Levine, Beth

    2009-01-01

    Autophagy adjusts cellular biomass and function in response to diverse stimuli, including infection. Autophagy plays specific roles in shaping immune system development, fueling host innate and adaptive immune responses, and directly controlling intracellular microbes as a cell-autonomous innate defense. As an evolutionary counterpoint, intracellular pathogens have evolved to block autophagic microbicidal defense and subvert host autophagic responses for their survival or growth. The ability of eukaryotic pathogens to deploy their own autophagic machinery may also contribute to microbial pathogenesis. Thus, a complex interplay between autophagy and microbial adaptations against autophagy governs the net outcome of host-microbe encounters. PMID:19527881

  19. Economic Conditions and Factors Affecting New Nuclear Power Deployment

    SciTech Connect

    Harrison, Thomas J.

    2014-10-01

    analysis. In both cases, the profitable price point is decreased, making more markets open to profitable entry. Overall, the economic attractiveness of a nuclear power construction project is not only a function of its own costs, but a function of the market into which it is deployed. Many of the market characteristics are out of the control of the potential nuclear power plant operators. The decision-making process for the power industry in general is complicated by the short-term market volatility in both the wholesale electricity market and the commodity (natural gas) market. Decisions based on market conditions today may be rendered null and void in six months. With a multiple-year lead time, nuclear power plants are acutely vulnerable to market corrections.

  20. Treatment of PTSD-Related Anger in Troops Returning from Hazardous Deployments

    DTIC Science & Technology

    2010-03-01

    objectives of this research were to adapt a cognitive-behavioral intervention (CBI) for the treatment of anger to specific needs of military personnel...condition (Supportive Intervention , SI); 23 started treatment . A mean of 8.9 and 9.2 sessions were completed for CBI and SI, respectively. Sixteen...behavioral intervention (CBI) for the treatment of anger to specific needs of military personnel returning from hazardous deployments, and 2) conduct