Silicon nitride ceramic development in Thales Alenia Space: qualification achiement and further developments for future applications

NASA Astrophysics Data System (ADS)

Cornillon, L.; Devilliers, C.; Behar-Lafenetre, S.; Ait-Zaid, S.; Berroth, K.; Bravo, A. C.

2017-11-01

Dealing with ceramic materials for more than two decades, Thales Alenia Space - France has identified Silicon Nitride Si3N4 as a high potential material for the manufacturing of stiff, stable and lightweight truss structure for future large telescopes. Indeed, for earth observation or astronomic observation, space mission requires more and more telescopes with high spatial resolution, which leads to the use of large primary mirrors, and a long distance between primary and secondary mirrors. Therefore current and future large space telescopes require a huge truss structure to hold and locate precisely the mirrors. Such large structure requires very strong materials with high specific stiffness and a low coefficient of thermal expansion (CTE). Based on the silicon nitride performances and on the know how of FCT Ingenieurkeramik to manufacture complex parts, Thales Alenia Space (TAS) has engaged, in cooperation with FCT, activities to develop and qualify silicon nitride parts for other applications for space projects.

Planning Assembly Of Large Truss Structures In Outer Space

NASA Technical Reports Server (NTRS)

De Mello, Luiz S. Homem; Desai, Rajiv S.

1992-01-01

Report dicusses developmental algorithm used in systematic planning of sequences of operations in which large truss structures assembled in outer space. Assembly sequence represented by directed graph called "assembly graph", in which each arc represents joining of two parts or subassemblies. Algorithm generates assembly graph, working backward from state of complete assembly to initial state, in which all parts disassembled. Working backward more efficient than working forward because it avoids intermediate dead ends.

Pd3MnH0.61

NASA Astrophysics Data System (ADS)

Villars, P.; Cenzual, K.; Daams, J.; Gladyshevskii, R.; Shcherban, O.; Dubenskyy, V.; Kuprysyuk, V.; Savysyuk, I.; Zaremba, R.

This document is part of Subvolume A10 'Structure Types. Part 10: Space Groups (140) I4/mcm - (136) P42/mnm' of Volume 43 'Crystal Structures of Inorganic Compounds' of Landolt-Börnstein - Group III 'Condensed Matter'.

KMo4O6 form II

NASA Astrophysics Data System (ADS)

Villars, P.; Cenzual, K.; Gladyshevskii, R.; Shcherban, O.; Dubenskyy, V.; Kuprysyuk, V.; Savysyuk, I.; Zaremba, R.

This document is part of Subvolume A11 'Structure Types. Part 11: Space Groups (135) P42/mbc - (123) P4/mmm' of Volume 43 'Crystal Structures of Inorganic Compounds' of Landolt-Börnstein - Group III 'Condensed Matter'.

(H3O)2TiF6

NASA Astrophysics Data System (ADS)

Villars, P.; Cenzual, K.; Daams, J.; Gladyshevskii, R.; Shcherban, O.; Dubenskyy, V.; Kuprysyuk, V.; Savysyuk, I.

This document is part of Subvolume A8 `Structure Types. Part 8: Space Groups (156) P3m1 - (148) R-3' of Volume 43 `Crystal Structures of Inorganic Compounds' of Landolt-Börnstein - Group III `Condensed Matter'.

Large Space Antenna Systems Technology, part 1

NASA Technical Reports Server (NTRS)

Lightner, E. B. (Compiler)

1983-01-01

A compilation of the unclassified papers presented at the NASA Conference on Large Space Antenna Systems Technology covers the following areas: systems, structures technology, control technology, electromagnetics, and space flight test and evaluation.

NaSi4O8(OH)•4H2O

NASA Astrophysics Data System (ADS)

Villars, P.; Cenzual, K.; Daams, J.; Gladyshevskii, R.; Shcherban, O.; Dubenskyy, V.; Kuprysyuk, V.; Savysyuk, I.

This document is part of Subvolume A9 `Structure Types. Part 9: Space Groups (148) R-3 - (141) I41' of Volume 43 `Crystal Structures of Inorganic Compounds' of Landolt-Börnstein - Group III `Condensed Matter'.

Technology for the Future: In-Space Technology Experiments Program, part 2

NASA Technical Reports Server (NTRS)

Breckenridge, Roger A. (Compiler); Clark, Lenwood G. (Compiler); Willshire, Kelli F. (Compiler); Beck, Sherwin M. (Compiler); Collier, Lisa D. (Compiler)

1991-01-01

The purpose of the Office of Aeronautics and Space Technology (OAST) In-Space Technology Experiments Program In-STEP 1988 Workshop was to identify and prioritize technologies that are critical for future national space programs and require validation in the space environment, and review current NASA (In-Reach) and industry/ university (Out-Reach) experiments. A prioritized list of the critical technology needs was developed for the following eight disciplines: structures; environmental effects; power systems and thermal management; fluid management and propulsion systems; automation and robotics; sensors and information systems; in-space systems; and humans in space. This is part two of two parts and contains the critical technology presentations for the eight theme elements and a summary listing of critical space technology needs for each theme.

The Cultural Evolution of Structured Languages in an Open-Ended, Continuous World.

PubMed

Carr, Jon W; Smith, Kenny; Cornish, Hannah; Kirby, Simon

2017-05-01

Language maps signals onto meanings through the use of two distinct types of structure. First, the space of meanings is discretized into categories that are shared by all users of the language. Second, the signals employed by the language are compositional: The meaning of the whole is a function of its parts and the way in which those parts are combined. In three iterated learning experiments using a vast, continuous, open-ended meaning space, we explore the conditions under which both structured categories and structured signals emerge ex nihilo. While previous experiments have been limited to either categorical structure in meanings or compositional structure in signals, these experiments demonstrate that when the meaning space lacks clear preexisting boundaries, more subtle morphological structure that lacks straightforward compositionality-as found in natural languages-may evolve as a solution to joint pressures from learning and communication. Copyright © 2016 The Authors. Cognitive Science published by Wiley Periodicals, Inc. on behalf of Cognitive Science Society.

Rb3TlBr6•1.14H2O

NASA Astrophysics Data System (ADS)

Villars, P.; Cenzual, K.; Daams, J.; Gladyshevskii, R.; Shcherban, O.; Dubenskyy, V.; Kuprysyuk, V.; Savysyuk, I.; Zaremba, R.

This document is part of Subvolume A10 'Structure Types. Part 10: Space Groups (140) I4/mcm - (136) P42/mnm' of Volume 43 'Crystal Structures of Inorganic Compounds' of Landolt-Börnstein - Group III 'Condensed Matter'.

High temperature turbine engine structure

DOEpatents

Boyd, Gary L.

1991-01-01

A high temperature turbine engine includes a rotor portion having axially stacked adjacent ceramic rotor parts. A ceramic/ceramic joint structure transmits torque between the rotor parts while maintaining coaxial alignment and axially spaced mutually parallel relation thereof despite thermal and centrifugal cycling.

NaGa[TeO3]2[H2O]2.4

NASA Astrophysics Data System (ADS)

Villars, P.; Cenzual, K.; Daams, J.; Gladyshevskii, R.; Shcherban, O.; Dubenskyy, V.; Melnichenko-Koblyuk, N.; Pavlyuk, O.; Savysyuk, I.; Stoyko, S.; Sysa, L.

This document is part of Subvolume A6 `Structure Types. Part 6: Space Groups (166) R-3m - (160) R3m' of Volume 43 `Crystal Structures of Inorganic Compounds' of Landolt-Börnstein - Group III `Condensed Matter'.

Large Space Systems Technology, Part 2, 1981

NASA Technical Reports Server (NTRS)

Boyer, W. J. (Compiler)

1982-01-01

Four major areas of interest are covered: technology pertinent to large antenna systems; technology related to the control of large space systems; basic technology concerning structures, materials, and analyses; and flight technology experiments. Large antenna systems and flight technology experiments are described. Design studies, structural testing results, and theoretical applications are presented with accompanying validation data. These research studies represent state-of-the art technology that is necessary for the development of large space systems. A total systems approach including structures, analyses, controls, and antennas is presented as a cohesive, programmatic plan for large space systems.

Fractal structures in centrifugal flywheel governor system

NASA Astrophysics Data System (ADS)

Rao, Xiao-Bo; Chu, Yan-Dong; Lu-Xu; Chang, Ying-Xiang; Zhang, Jian-Gang

2017-09-01

The global structure of nonlinear response of mechanical centrifugal governor, forming in two-dimensional parameter space, is studied in this paper. By using three kinds of phases, we describe how responses of periodicity, quasi-periodicity and chaos organize some self-similarity structures with parameters varying. For several parameter combinations, the regular vibration shows fractal characteristic, that is, the comb-shaped self-similarity structure is generated by alternating periodic response with intermittent chaos, and Arnold's tongues embedded in quasi-periodic response are organized according to Stern-Brocot tree. In particular, a new type of mixed-mode oscillations (MMOs) is found in the periodic response. These unique structures reveal the natural connection of various responses between part and part, part and the whole in parameter space based on self-similarity of fractal. Meanwhile, the remarkable and unexpected results are to contribute a valid dynamic reference for practical applications with respect to mechanical centrifugal governor.

Microgravity

NASA Image and Video Library

2000-04-20

Cindy Barnes of University Space Research Association (USRA) at NASA's Marshall Space Flight Center pipettes a protein solution in preparation to grow crystals as part of NASA's structural biology program. Research on Earth helps scientists define conditions and specimens they will use in space experiments.

Personnel occupied woven envelope robot

NASA Technical Reports Server (NTRS)

Wessling, F. C.

1986-01-01

The use of nonmetallic or fabric structures for space application is considered. The following structures are suggested: (1) unpressurized space hangars; (2) extendable tunnels for soft docking; and (3) manned habitat for space stations, storage facilities, and work structures. The uses of the tunnel as a passageway: for personnel and equipment, eliminating extravehicular activity, for access to a control cabin on a space crane and between free flyers and the space station are outlined. The personnal occupied woven envelope robot (POWER) device is shown. The woven envelope (tunnel) acts as part of the boom of a crane. Potential applications of POWER are outlined. Several possible deflection mechanisms and design criteria are determined.

14 CFR Appendix C to Part 27 - Criteria for Category A

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 1 2012-01-01 2012-01-01 false Criteria for Category A C Appendix C to... AIRWORTHINESS STANDARDS: NORMAL CATEGORY ROTORCRAFT Pt. 27, App. C Appendix C to Part 27—Criteria for Category A... tail rotor structure. 29.861(a)—Fire protection of structure, controls, and other parts. 29.901(c...

14 CFR Appendix C to Part 27 - Criteria for Category A

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 1 2014-01-01 2014-01-01 false Criteria for Category A C Appendix C to... AIRWORTHINESS STANDARDS: NORMAL CATEGORY ROTORCRAFT Pt. 27, App. C Appendix C to Part 27—Criteria for Category A... tail rotor structure. 29.861(a)—Fire protection of structure, controls, and other parts. 29.901(c...

Solid Freeform Fabrication: An Enabling Technology for Future Space Missions

NASA Technical Reports Server (NTRS)

Taminger, Karen M. B.; Hafley, Robert A.; Dicus, Dennis L.

2002-01-01

The emerging class of direct manufacturing processes known as Solid Freeform Fabrication (SFF) employs a focused energy beam and metal feedstock to build structural parts directly from computer aided design (CAD) data. Some variations on existing SFF techniques have potential for application in space for a variety of different missions. This paper will focus on three different applications ranging from near to far term to demonstrate the widespread potential of this technology for space-based applications. One application is the on-orbit construction of large space structures, on the order of tens of meters to a kilometer in size. Such structures are too large to launch intact even in a deployable design; their extreme size necessitates assembly or erection of such structures in space. A low-earth orbiting satellite with a SFF system employing a high-energy beam for high deposition rates could be employed to construct large space structures using feedstock launched from Earth. A second potential application is a small, multifunctional system that could be used by astronauts on long-duration human exploration missions to manufacture spare parts. Supportability of human exploration missions is essential, and a SFF system would provide flexibility in the ability to repair or fabricate any part that may be damaged or broken during the mission. The system envisioned would also have machining and welding capabilities to increase its utility on a mission where mass and volume are extremely limited. A third example of an SFF application in space is a miniaturized automated system for structural health monitoring and repair. If damage is detected using a low power beam scan, the beam power can be increased to perform repairs within the spacecraft or satellite structure without the requirement of human interaction or commands. Due to low gravity environment for all of these applications, wire feedstock is preferred to powder from a containment, handling, and safety standpoint. The energy beams may be either electron beam or laser, and the developments required for either energy source to achieve success in these applications will be discussed.

Post-Flight Estimation of Motion of Space Structures: Part 1

NASA Technical Reports Server (NTRS)

Brugarolas, Paul; Breckenridge, William

2008-01-01

A computer program estimates the relative positions and orientations of two space structures from data on the angular positions and distances of fiducial objects on one structure as measured by a target tracking electronic camera and laser range finders on another structure. The program is written specifically for determining the relative alignments of two antennas, connected by a long truss, deployed in outer space from a space shuttle. The program is based partly on transformations among the various coordinate systems involved in the measurements and on a nonlinear mathematical model of vibrations of the truss. The program implements a Kalman filter that blends the measurement data with data from the model. Using time series of measurement data from the tracking camera and range finders, the program generates time series of data on the relative position and orientation of the antennas. A similar program described in a prior NASA Tech Briefs article was used onboard for monitoring the structures during flight. The present program is more precise and designed for use on Earth in post-flight processing of the measurement data to enable correction, for antenna motions, of scientific data acquired by use of the antennas.

Robust on-off pulse control of flexible space vehicles

NASA Technical Reports Server (NTRS)

Wie, Bong; Sinha, Ravi

1993-01-01

The on-off reaction jet control system is often used for attitude and orbital maneuvering of various spacecraft. Future space vehicles such as the orbital transfer vehicles, orbital maneuvering vehicles, and space station will extensively use reaction jets for orbital maneuvering and attitude stabilization. The proposed robust fuel- and time-optimal control algorithm is used for a three-mass spacing model of flexible spacecraft. A fuel-efficient on-off control logic is developed for robust rest-to-rest maneuver of a flexible vehicle with minimum excitation of structural modes. The first part of this report is concerned with the problem of selecting a proper pair of jets for practical trade-offs among the maneuvering time, fuel consumption, structural mode excitation, and performance robustness. A time-optimal control problem subject to parameter robustness constraints is formulated and solved. The second part of this report deals with obtaining parameter insensitive fuel- and time- optimal control inputs by solving a constrained optimization problem subject to robustness constraints. It is shown that sensitivity to modeling errors can be significantly reduced by the proposed, robustified open-loop control approach. The final part of this report deals with sliding mode control design for uncertain flexible structures. The benchmark problem of a flexible structure is used as an example for the feedback sliding mode controller design with bounded control inputs and robustness to parameter variations is investigated.

Greek classicism in living structure? Some deductive pathways in animal morphology.

PubMed

Zweers, G A

1985-01-01

Classical temples in ancient Greece show two deterministic illusionistic principles of architecture, which govern their functional design: geometric proportionalism and a set of illusion-strengthening rules in the proportionalism's "stochastic margin". Animal morphology, in its mechanistic-deductive revival, applies just one architectural principle, which is not always satisfactory. Whether a "Greek Classical" situation occurs in the architecture of living structure is to be investigated by extreme testing with deductive methods. Three deductive methods for explanation of living structure in animal morphology are proposed: the parts, the compromise, and the transformation deduction. The methods are based upon the systems concept for an organism, the flow chart for a functionalistic picture, and the network chart for a structuralistic picture, whereas the "optimal design" serves as the architectural principle for living structure. These methods show clearly the high explanatory power of deductive methods in morphology, but they also make one open end most explicit: neutral issues do exist. Full explanation of living structure asks for three entries: functional design within architectural and transformational constraints. The transformational constraint brings necessarily in a stochastic component: an at random variation being a sort of "free management space". This variation must be a variation from the deterministic principle of the optimal design, since any transformation requires space for plasticity in structure and action, and flexibility in role fulfilling. Nevertheless, finally the question comes up whether for animal structure a similar situation exists as in Greek Classical temples. This means that the at random variation, that is found when the optimal design is used to explain structure, comprises apart from a stochastic part also real deviations being yet another deterministic part. This deterministic part could be a set of rules that governs actualization in the "free management space".

The Information Is In the Maps: Representations & Algorithms for Mapping among Geometric Data

DTIC Science & Technology

2015-09-30

space of all maps is a huge space and an important part of the project has addressed the problem of finding compact representations and encodings...understanding the relationships among its parts, or its connections to other data sets that may share the same or similar structure. Towards this end, we have...for the much smaller spaces of interesting maps within a specific application. The machinery developed here has proven of use across a broad spectrum

Quantization of wave equations and hermitian structures in partial differential varieties

PubMed Central

Paneitz, S. M.; Segal, I. E.

1980-01-01

Sufficiently close to 0, the solution variety of a nonlinear relativistic wave equation—e.g., of the form □ϕ + m2ϕ + gϕp = 0—admits a canonical Lorentz-invariant hermitian structure, uniquely determined by the consideration that the action of the differential scattering transformation in each tangent space be unitary. Similar results apply to linear time-dependent equations or to equations in a curved asymptotically flat space-time. A close relation of the Riemannian structure to the determination of vacuum expectation values is developed and illustrated by an explicit determination of a perturbative 2-point function for the case of interaction arising from curvature. The theory underlying these developments is in part a generalization of that of M. G. Krein and collaborators concerning stability of differential equations in Hilbert space and in part a precise relation between the unitarization of given symplectic linear actions and their full probabilistic quantization. The unique causal structure in the infinite symplectic group is instrumental in these developments. PMID:16592923

Space Shuttle Projects

NASA Image and Video Library

1978-03-01

A liquid hydrogen tank of the Shuttle's external tank (ET) is installed into the S-1C Test Stand for a structural test at the Marshall Space Flight Center. At 154-feet long and more than 27-feet in diameter, the ET is the largest component of the Space Shuttle, the structural backbone of the entire Shuttle system, and is the only part of the vehicle that is not reusable. The ET is manufactured at the Michoud Assembly Facility near New Orleans, Louisiana, by the Martin Marietta Corporation under management of the Marshall Space Flight Center.

Space Construction Experiment Definition Study (SCEDS), part 3. Volume 2: Study results

NASA Technical Reports Server (NTRS)

1983-01-01

The essential controls and dynamics community needs for a large space structures is addressed by the basic Space Construction Experiments (SCE)/MAST configuration and enhanced configurations for follow-on flights. The SCE/MAST can be integrated on a single structures technology experiments platform (STEP). The experiment objectives can be accomplished without the need for EVA and it is anticipated that further design refinements will eliminate the requirement to use the remote manipulator system.

Integrated Modeling Activities for the James Webb Space Telescope: Optical Jitter Analysis

NASA Technical Reports Server (NTRS)

Hyde, T. Tupper; Ha, Kong Q.; Johnston, John D.; Howard, Joseph M.; Mosier, Gary E.

2004-01-01

This is a continuation of a series of papers on the integrated modeling activities for the James Webb Space Telescope(JWST). Starting with the linear optical model discussed in part one, and using the optical sensitivities developed in part two, we now assess the optical image motion and wavefront errors from the structural dynamics. This is often referred to as "jitter: analysis. The optical model is combined with the structural model and the control models to create a linear structural/optical/control model. The largest jitter is due to spacecraft reaction wheel assembly disturbances which are harmonic in nature and will excite spacecraft and telescope structural. The structural/optic response causes image quality degradation due to image motion (centroid error) as well as dynamic wavefront error. Jitter analysis results are used to predict imaging performance, improve the structural design, and evaluate the operational impact of the disturbance sources.

14 CFR 33.70 - Engine life-limited parts.

Code of Federal Regulations, 2014 CFR

2014-01-01

... parts are rotor and major static structural parts whose primary failure is likely to result in a....70 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT AIRWORTHINESS STANDARDS: AIRCRAFT ENGINES Design and Construction; Turbine Aircraft Engines § 33.70 Engine life...

Technology for the Future: In-Space Technology Experiments Program, part 1

NASA Technical Reports Server (NTRS)

Breckenridge, Roger A. (Compiler); Clark, Lenwood G. (Compiler); Willshire, Kelli F. (Compiler); Beck, Sherwin M. (Compiler); Collier, Lisa D. (Compiler)

1991-01-01

The purpose of the Office of Aeronautics and Space Technology (OAST) In-Space Technology Experiment Program (In-STEP) 1988 Workshop was to identify and prioritize technologies that are critical for future national space programs and require validation in the space environment, and review current NASA (In-Reach) and industry/university (Out-Reach) experiments. A prioritized list of the critical technology needs was developed for the following eight disciplines: structures; environmental effects; power systems and thermal management; fluid management and propulsion systems; automation and robotics; sensors and information systems; in-space systems; and humans in space. This is part one of two parts and is the executive summary and experiment description. The executive summary portion contains keynote addresses, strategic planning information, and the critical technology needs summaries for each theme. The experiment description portion contains brief overviews of the objectives, technology needs and backgrounds, descriptions, and development schedules for current industry, university, and NASA space flight technology experiments.

KSC-00pp1300

NASA Image and Video Library

2000-09-12

KENNEDY SPACE CENTER, Fla. -- While the morning sun paints the sky pale gold, the structures on Launch Pad 39A are silhouetted in brown. Space Shuttle Discovery can be seen on the other side of the Fixed Service Structure; the Rotating Service Structure at right is still open. At left is the 300,000-gallon water tank that is part of the sound suppression system during launches. Discovery will launch on mission STS-92 Oct. 5, 2000

KSC00pp1300

NASA Image and Video Library

2000-09-12

KENNEDY SPACE CENTER, Fla. -- While the morning sun paints the sky pale gold, the structures on Launch Pad 39A are silhouetted in brown. Space Shuttle Discovery can be seen on the other side of the Fixed Service Structure; the Rotating Service Structure at right is still open. At left is the 300,000-gallon water tank that is part of the sound suppression system during launches. Discovery will launch on mission STS-92 Oct. 5, 2000

A study of space shuttle structural integrity test and assessment. Part 1

NASA Technical Reports Server (NTRS)

Anderson, R. E.; Poe, R. G.

1972-01-01

The ultrasonics technique for assessing the structural integrity of the primary surface of the space shuttle vehicles is discussed and evaluated. Analysis was made of transducers, transducer coupling test structure fabrication, flaws, and ultrasonic testing. Graphs of microphone response curves from the initial noise tests, accelerometer response curves from the final noise tests, and microphone curves from the final noise tests are included along with a glossary, bibliography, and results.

NASA Workshop on Computational Structural Mechanics 1987, part 3

NASA Technical Reports Server (NTRS)

Sykes, Nancy P. (Editor)

1989-01-01

Computational Structural Mechanics (CSM) topics are explored. Algorithms and software for nonlinear structural dynamics, concurrent algorithms for transient finite element analysis, computational methods and software systems for dynamics and control of large space structures, and the use of multi-grid for structural analysis are discussed.

Structural design and analysis for an ultra low CTE optical bench for the Hubble Space Telescope corrective optics

NASA Technical Reports Server (NTRS)

Neam, Douglas C.; Gerber, John D.

1992-01-01

The stringent stability requirements of the Corrective Optics Space Telescope Axial Replacement (COSTAR) necessitates a Deployable Optical Bench (DOB) with both a low CTE and high resonant frequency. The DOB design consists of a monocoque thin shell structure which marries metallic machined parts with graphite epoxy formed structure. Structural analysis of the DOB has been integrated into the laminate design and optimization process. Also, the structural analytical results are compared with vibration and thermal test data to assess the reliability of the analysis.

Space Tug Point Design Study. Volume 3: Design Definition. Part 2: Insulation, Meteoroid Protection, Structures, Mass Properties, GSE, Reliability and Safety

NASA Technical Reports Server (NTRS)

1973-01-01

A study was conducted to determine the configuration and performance of a space tug. Detailed descriptions of the insulation, meteoroid protection, primary structure, and ground support equipment are presented. Technical assessments leading to the concept selection are analyzed. The tug mass properties, reliability, and safety assessments are included.

Low temperature storage container for transporting perishables to space station

NASA Technical Reports Server (NTRS)

Owen, James W. (Inventor); Dean, William G. (Inventor)

1989-01-01

Two storage containers are disclosed within which food or biological samples may be stored for transfer in a module by the space shuttle to a space station while maintaining the food or samples at very low temperatures. The container is formed in two parts, each part having an inner shell and an outer shell disposed about the inner shell. The space between the shells is filled with a continuous wrap multi-layer insulation and a getter material. The two parts of the container have interlocking members and when connected together are sealed for preventing leakage from the space between the shells. After the two parts are filled with frozen food or samples they are connected together and a vacuum is drawn in the space between the shells and the container is stored in the module. For the extremely low temperature requirements of biological samples, an internal liner having a phase change material charged by a refrigerant coil is disposed in the space between the shells, and the container is formed from glass fiber material including honeycomb structural elements. All surfaces of the glass fiber which face the vacuum space are lined with a metal foil.

STS-133 Discovery

NASA Image and Video Library

2010-11-03

The space shuttle Discovery is seen on launch Pad 39a after the Rotating Service Structure (RSS) is rolled back on Wednesday, Nov. 3, 2010 at the NASA Kennedy Space Center in Cape Canaveral, Fla. During space shuttle Discovery's final spaceflight, the STS-133 crew members will take important spare parts to the International Space Station along with the Express Logistics Carrier-4. Photo Credit: (NASA/Bill Ingalls)

Status of DSMT research program

NASA Technical Reports Server (NTRS)

Mcgowan, Paul E.; Javeed, Mehzad; Edighoffer, Harold H.

1991-01-01

The status of the Dynamic Scale Model Technology (DSMT) research program is presented. DSMT is developing scale model technology for large space structures as part of the Control Structure Interaction (CSI) program at NASA Langley Research Center (LaRC). Under DSMT a hybrid-scale structural dynamics model of Space Station Freedom was developed. Space Station Freedom was selected as the focus structure for DSMT since the station represents the first opportunity to obtain flight data on a complex, three-dimensional space structure. Included is an overview of DSMT including the development of the space station scale model and the resulting hardware. Scaling technology was developed for this model to achieve a ground test article which existing test facilities can accommodate while employing realistically scaled hardware. The model was designed and fabricated by the Lockheed Missile and Space Co., and is assembled at LaRc for dynamic testing. Also, results from ground tests and analyses of the various model components are presented along with plans for future subassembly and matted model tests. Finally, utilization of the scale model for enhancing analysis verification of the full-scale space station is also considered.

Preparing to Test for Deep Space

NASA Image and Video Library

2015-07-15

A structural steel section is lifted into place atop the B-2 Test Stand at NASA’s Stennis Space Center as part of modification work to prepare for testing the core stage of NASA’s new Space Launch System. The section is part of the Main Propulsion Test Article (MPTA) framework, which will support the SLS core stage for testing. The existing framework was installed on the stand in the late 1970s to test the shuttle MPTA. However, that framework had to be repositioned and modified to accommodate the larger SLS stage. About 1 million pounds of structural steel has been added, extending the framework about 100 feet higher and providing a new look to the Stennis skyline. Stennis will test the actual flight core stage for the first uncrewed SLS mission, Exploration Mission-1.

Space station system analysis study. Part 3: Documentation. Volume 2: Technical report. [structural design and construction

NASA Technical Reports Server (NTRS)

1977-01-01

An analysis of construction operation is presented as well as power system sizing requirements. Mission hardware requirements are reviewed in detail. Space construction base and design configurations are also examined.

Development of mechanical structure for the compact space IR camera MIRIS

NASA Astrophysics Data System (ADS)

Moon, Bongkon; Jeong, Woong-Seob; Cha, Sang-Mok; Park, Youngsik; Ree, Chang-Hee; Lee, Dae-Hee; Park, Sung-Joon; Nam, Uk-Won; Park, Jang-Hyun; Ka, Nung Hyun; Lee, Mi Hyun; Lee, Duk-Hang; Pyo, Jeonghyun; Rhee, Seung-Woo; Park, Jong-Oh; Lee, Hyung-Mok; Matsumoto, Toshio; Yang, Sun Choel; Han, Wonyong

2010-07-01

MIRIS is a compact near-infrared camera with a wide field of view of 3.67°×3.67° in the Korea Science and Technology Satellite 3 (STSAT-3). MIRIS will be launched warm and cool the telescope optics below 200K by pointing to the deep space on Sun-synchronous orbit. In order to realize the passive cooling, the mechanical structure was designed to consider thermal analysis results on orbit. Structural analysis was also conducted to ensure safety and stability in launching environments. To achieve structural and thermal requirements, we fabricated the thermal shielding parts such as Glass Fiber Reinforced Plastic (GFRP) pipe supports, a Winston cone baffle, aluminum-shield plates, a sunshade, a radiator and 30 layers of Multi Layer Insulation (MLI). These structures prevent the heat load from the spacecraft and the earth effectively, and maintain the temperature of the telescope optics within operating range. A micro cooler was installed in a cold box including a PICNIC detector and a filter-wheel, and cooled the detector down to a operating temperature range. We tested the passive cooling in the simulated space environment and confirmed that the required temperature of telescope can be achieved. Driving mechanism of the filter-wheel and the cold box structure were also developed for the compact space IR camera. Finally, we present the assembly procedures and the test result for the mechanical parts of MIRIS.

NASA Engineering Design Challenges: Spacecraft Structures. EP-2008-09-121-MSFC

ERIC Educational Resources Information Center

Haddad, Nick; McWilliams, Harold; Wagoner, Paul

2007-01-01

NASA (National Aeronautics and Space Administration) Engineers at Marshall Space Flight Center along with their partners at other NASA centers, and in private industry, are designing and beginning to develop the next generation of spacecraft to transport cargo, equipment, and human explorers to space. These vehicles are part of the Constellation…

KSC00pp1374

NASA Image and Video Library

2000-09-15

KENNEDY SPACE CENTER, FLA. -- STS-92 Commander Brian Duffy is seated at the controls of Discovery to take part in a simulated countdown. The countdown is part of Terminal Countdown Demonstration Test (TCDT) activities that he and other crew members have been performing. STS-92 is scheduled to launch Oct. 5 at 9:38 p.m. EDT on the fifth flight to the International Space Station. It will carry two elements of the Space Station, the Integrated Truss Structure Z1 and the third Pressurized Mating Adapter. The mission is also the 100th flight in the Shuttle program

KSC-00pp1374

NASA Image and Video Library

2000-09-15

KENNEDY SPACE CENTER, FLA. -- STS-92 Commander Brian Duffy is seated at the controls of Discovery to take part in a simulated countdown. The countdown is part of Terminal Countdown Demonstration Test (TCDT) activities that he and other crew members have been performing. STS-92 is scheduled to launch Oct. 5 at 9:38 p.m. EDT on the fifth flight to the International Space Station. It will carry two elements of the Space Station, the Integrated Truss Structure Z1 and the third Pressurized Mating Adapter. The mission is also the 100th flight in the Shuttle program

Dimensionally stable composite structures and composite mirrors for spaceborne optical instruments

NASA Astrophysics Data System (ADS)

Sippel, Rudolf; Stute, Thomas; Erdl, Günther

2018-04-01

This paper, "Dimensionally stable composite structures and composite mirrors for spaceborne optical instruments," was presented as part of International Conference on Space Optics—ICSO 1997, held in Toulouse, France.

Orbital assembly and maintenance study. Executive summary. [space erectable structures/structural design criteria

NASA Technical Reports Server (NTRS)

Gorman, D.; Grant, C.; Kyrias, G.; Lord, C.; Rombach, J. P.; Salis, M.; Skidmore, R.; Thomas, R.

1975-01-01

A sound, practical approach for the assembly and maintenance of very large structures in space is presented. The methods and approaches for assembling two large structures are examined. The maintenance objectives include the investigation of methods to maintain five geosynchronous satellites. The two assembly examples are a 200-meter-diameter radio astronomy telescope and a 1,000-meter-diameter microwave power transmission system. The radio astronomy telescope operates at an 8,000-mile altitude and receives RF signals from space. The microwave power transmission system is part of a solar power satellite that will be used to transmit converted solar energy to microwave ground receivers. Illustrations are included.

Dielectric image line groove antennas for millimeterwaves

NASA Astrophysics Data System (ADS)

Solbach, K.; Wolff, I.

Grooves in the ground plane of dielectric image lines are proposed as a new radiating structure. A figure is included showing the proposed groove structure as a discontinuity in a dielectric image line. A wave incident on the dielectric image line is partly reflected by the discontinuity, partly transmitted across the groove, and partly radiated into space above the line. In a travelling-wave antenna, a number of grooves are arranged below a dielectric guide, with spacings around one guide wavelength to produce a beam in the upper half space. A prescribed aperture distribution can be effected by tapering the series radiation resistance of the grooves. This can be done by adjusting the depths of the grooves with a constant width or by varying the widths of the grooves with a constant depth. Attention is also given to circular grooves. Here, the widths of the holes are chosen so that they can be considered as waveguides operating far below the cut-off frequency of the fundamental circular waveguide mode.

KSC-98pc458

NASA Image and Video Library

1998-04-06

KENNEDY SPACE CENTER, FLA. -- The Long Spacer, a component of the International Space Station, arrives and is moved to its test stand in the northeast corner of the high bay in KSC's Space Station Processing Facility. The Long Spacer provides structural support for the outboard Photovoltaic Modules that supply power to the station. Now just a structure, the Long Spacer will have attached to it as part of processing a heat dissipation radiator and two Pump and Flow Control subassemblies that circulate ammonia to cool the solar array electronics. Also to be mounted are ammonia fluid lines as part of the cooling system and the cabling necessary for power and control of the station. The Long Spacer becomes an integral part of a station truss segment when it is mated with the Integrated Equipment Assembly, which stores the electrical power generated by the solar arrays for use by the station modules. The Long Spacer is being processed in preparation for STS-97, currently planned for launch aboard Discovery in April 1999

KSC-98pc456

NASA Image and Video Library

1998-04-06

KENNEDY SPACE CENTER, FLA. -- The Long Spacer, a component of the International Space Station, arrives and is moved to its test stand in the northeast corner of the high bay in KSC's Space Station Processing Facility. The Long Spacer provides structural support for the outboard Photovoltaic Modules that supply power to the station. Now just a structure, the Long Spacer will have attached to it as part of processing a heat dissipation radiator and two Pump and Flow Control subassemblies that circulate ammonia to cool the solar array electronics. Also to be mounted are ammonia fluid lines as part of the cooling system and the cabling necessary for power and control of the station. The Long Spacer becomes an integral part of a station truss segment when it is mated with the Integrated Equipment Assembly, which stores the electrical power generated by the solar arrays for use by the station modules. The Long Spacer is being processed in preparation for STS-97, currently planned for launch aboard Discovery in April 1999

KSC-98pc459

NASA Image and Video Library

1998-04-06

KENNEDY SPACE CENTER, FLA. -- The Long Spacer, a component of the International Space Station, arrives and is moved to its test stand in the northeast corner of the high bay in KSC's Space Station Processing Facility. The Long Spacer provides structural support for the outboard Photovoltaic Modules that supply power to the station. Now just a structure, the Long Spacer will have attached to it as part of processing a heat dissipation radiator and two Pump and Flow Control subassemblies that circulate ammonia to cool the solar array electronics. Also to be mounted are ammonia fluid lines as part of the cooling system and the cabling necessary for power and control of the station. The Long Spacer becomes an integral part of a station truss segment when it is mated with the Integrated Equipment Assembly, which stores the electrical power generated by the solar arrays for use by the station modules. The Long Spacer is being processed in preparation for STS-97, currently planned for launch aboard Discovery in April 1999

KSC-98pc457

NASA Image and Video Library

1998-04-06

KENNEDY SPACE CENTER, FLA. -- The Long Spacer, a component of the International Space Station, arrives and is moved to its test stand in the northeast corner of the high bay in KSC's Space Station Processing Facility. The Long Spacer provides structural support for the outboard Photovoltaic Modules that supply power to the station. Now just a structure, the Long Spacer will have attached to it as part of processing a heat dissipation radiator and two Pump and Flow Control subassemblies that circulate ammonia to cool the solar array electronics. Also to be mounted are ammonia fluid lines as part of the cooling system and the cabling necessary for power and control of the station. The Long Spacer becomes an integral part of a station truss segment when it is mated with the Integrated Equipment Assembly, which stores the electrical power generated by the solar arrays for use by the station modules. The Long Spacer is being processed in preparation for STS-97, currently planned for launch aboard Discovery in April 1999

Radially dependent angular acceleration of twisted light.

PubMed

Webster, Jason; Rosales-Guzmán, Carmelo; Forbes, Andrew

2017-02-15

While photons travel in a straight line at constant velocity in free space, the intensity profile of structured light may be tailored for acceleration in any degree of freedom. Here we propose a simple approach to control the angular acceleration of light. Using Laguerre-Gaussian modes as our twisted beams carrying orbital angular momentum, we show that superpositions of opposite handedness result in a radially dependent angular acceleration as they pass through a focus (waist plane). Due to conservation of orbital angular momentum, we find that propagation dynamics are complex despite the free-space medium: the outer part of the beam (rings) rotates in an opposite direction to the inner part (petals), and while the outer part accelerates, the inner part decelerates. We outline the concepts theoretically and confirm them experimentally. Such exotic structured light beams are topical due to their many applications, for instance in optical trapping and tweezing, metrology, and fundamental studies in optics.

Estimating Relative Positions of Outer-Space Structures

NASA Technical Reports Server (NTRS)

Balian, Harry; Breckenridge, William; Brugarolas, Paul

2009-01-01

A computer program estimates the relative position and orientation of two structures from measurements, made by use of electronic cameras and laser range finders on one structure, of distances and angular positions of fiducial objects on the other structure. The program was written specifically for use in determining errors in the alignment of large structures deployed in outer space from a space shuttle. The program is based partly on equations for transformations among the various coordinate systems involved in the measurements and on equations that account for errors in the transformation operators. It computes a least-squares estimate of the relative position and orientation. Sequential least-squares estimates, acquired at a measurement rate of 4 Hz, are averaged by passing them through a fourth-order Butterworth filter. The program is executed in a computer aboard the space shuttle, and its position and orientation estimates are displayed to astronauts on a graphical user interface.

Structural Design of Glass and Ceramic Components for Space System Safety

NASA Technical Reports Server (NTRS)

Bernstein, Karen S.

2007-01-01

Manned space flight programs will always have windows as part of the structural shell of the crew compartment. Astronauts and cosmonauts need to and enjoy looking out of the spacecraft windows at Earth, at approaching vehicles, at scientific objectives and at the stars. With few exceptions spacecraft windows have been made of glass, and the lessons learned over forty years of manned space flight have resulted in a well-defined approach for using this brittle, unforgiving material in NASA's vehicles, in windows and other structural applications. This chapter will outline the best practices that have developed at NASA for designing, verifying and accepting glass (and ceramic) windows and other components for safe and reliable use in any space system.

Assembly considerations for large reflectors

NASA Technical Reports Server (NTRS)

Bush, H.

1988-01-01

The technologies developed at LaRC in the area of erectable instructures are discussed. The information is of direct value to the Large Deployable Reflector (LDR) because an option for the LDR backup structure is to assemble it in space. The efforts in this area, which include development of joints, underwater assembly simulation tests, flight assembly/disassembly tests, and fabrication of 5-meter trusses, led to the use of the LaRC concept as the baseline configuration for the Space Station Structure. The Space Station joint is linear in the load and displacement range of interest to Space Station; the ability to manually assemble and disassemble a 45-foot truss structure was demonstrated by astronauts in space as part of the ACCESS Shuttle Flight Experiment. The structure was built in 26 minutes 46 seconds, and involved a total of 500 manipulations of untethered hardware. Also, the correlation of the space experience with the neutral buoyancy simulation was very good. Sections of the proposed 5-meter bay Space Station truss have been built on the ground. Activities at LaRC have included the development of mobile remote manipulator systems (which can traverse the Space Station 5-meter structure), preliminary LDR sun shield concepts, LDR construction scenarios, and activities in robotic assembly of truss-type structures.

Consultative Committee for Space Data Systems recommendation for space data system standards: Telecommand. Part 2.1: Command operation procedures

NASA Technical Reports Server (NTRS)

1991-01-01

This recommendation contains the detailed specification of the logic required to carry out the Command Operations Procedures of the Transfer Layer. The Recommendation for Telecommand--Part 2, Data Routing Service contains the standard data structures and data communication procedures used by the intermediate telecommand system layers (the Transfer and Segmentation Layers). In particular, it contains a brief description of the Command Operations Procedures (COP) within the Transfer Layer. This recommendation contains the detailed definition of the COP's in the form of state tables, along with definitions of the terms used. It is assumed that the reader of this document is familiar with the data structures and terminology of part 2. In case of conflict between the description of the COP's in part 2 and in this recommendation, the definition in this recommendation will take precedence. In particular, this document supersedes section 4.3.3.1 through 4.3.3.4 of part 2.

Innovative Approaches to Space-Based Manufacturing and Rapid Prototyping of Composite Materials

NASA Technical Reports Server (NTRS)

Hill, Charles S.

2012-01-01

The ability to deploy large habitable structures, construct, and service exploration vehicles in low earth orbit will be an enabling capability for continued human exploration of the solar system. It is evident that advanced manufacturing methods to fabricate replacement parts and re-utilize launch vehicle structural mass by converting it to different uses will be necessary to minimize costs and allow flexibility to remote crews engaged in space travel. Recent conceptual developments and the combination of inter-related approaches to low-cost manufacturing of composite materials and structures are described in context leading to the possibility of on-orbit and space-based manufacturing.

Interactive computer graphics and its role in control system design of large space structures

NASA Technical Reports Server (NTRS)

Reddy, A. S. S. R.

1985-01-01

This paper attempts to show the relevance of interactive computer graphics in the design of control systems to maintain attitude and shape of large space structures to accomplish the required mission objectives. The typical phases of control system design, starting from the physical model such as modeling the dynamics, modal analysis, and control system design methodology are reviewed and the need of the interactive computer graphics is demonstrated. Typical constituent parts of large space structures such as free-free beams and free-free plates are used to demonstrate the complexity of the control system design and the effectiveness of the interactive computer graphics.

Concept-Development of a Structure Supported Membrane for Deployable Space Applications - From Nature to Manufacture and Testing

NASA Technical Reports Server (NTRS)

Zander, Martin; Belvin, W. K.

2012-01-01

Current space applications of membrane structures include large area solar power arrays, solar sails, antennas, and numerous other large aperture devices like the solar shades of the new James Webb Space Telescope. These expandable structural systems, deployed in-orbit to achieve the desired geometry, are used to collect, reflect and/or transmit electromagnetic radiation. This work, a feasibility study supporting a diploma thesis, describes the systematic process for developing a biologically inspired concept for a structure supported (integrated) membrane, that features a rip stop principle, makes self-deployment possible and is part of an ultra-light weight space application. Novel manufacturing of membrane prototypes and test results are presented for the rip-stop concepts. Test data showed that the new membrane concept has a higher tear resistance than neat film of equivalent mass.

Structural Safety of a Hubble Space Telescope Science Instrument

NASA Technical Reports Server (NTRS)

Lou, M. C.; Brent, D. N.

1993-01-01

This paper gives an overview of safety requirements related to structural design and verificationof payloads to be launched and/or retrieved by the Space Shuttle. To demonstrate the generalapproach used to implement these requirements in the development of a typical Shuttle payload, theWide Field/Planetary Camera II, a second generation science instrument currently being developed bythe Jet Propulsion Laboratory (JPL) for the Hubble Space Telescope is used as an example. Inaddition to verification of strength and dynamic characteristics, special emphasis is placed upon thefracture control implementation process, including parts classification and fracture controlacceptability.

Development of deployable structures for large space platform systems, part 1

NASA Technical Reports Server (NTRS)

Cox, R. L.; Nelson, R. A.

1982-01-01

Eight deployable platform design objectives were established: autodeploy/retract; fully integrated utilities; configuration variability; versatile payload and subsystem interfaces; structural and packing efficiency; 1986 technology readiness; minimum EVA/RMS; and Shuttle operational compatibility.

The Cultural Evolution of Structured Languages in an Open-Ended, Continuous World

ERIC Educational Resources Information Center

Carr, Jon W.; Smith, Kenny; Cornish, Hannah; Kirby, Simon

2017-01-01

Language maps signals onto meanings through the use of two distinct types of structure. First, the space of meanings is discretized into categories that are shared by all users of the language. Second, the signals employed by the language are compositional: The meaning of the whole is a function of its parts and the way in which those parts are…

Space Shuttle Endeavour STS-134

NASA Image and Video Library

2011-04-29

An faint profile outline of the space shuttle Endeavour is seen projected in the sky as powerful xenon lights illuminate launch pad 39a shortly after the rollback of the Rotating Service Structure (RSS) from Endeavour, Thursday, April 28, 2011, at Kennedy Space Center in Cape Canaveral, Fla. During the 14-day mission, Endeavour and the STS-134 crew will deliver the Alpha Magnetic Spectrometer (AMS) and spare parts including two S-band communications antennas, a high-pressure gas tank and additional spare parts for Dextre. Launch is targeted for Friday, April 29 at 3:47 p.m. EDT. Photo credit: (NASA/Bill Ingalls)

Body-Building: A Female Student's Use of the Transitional Spaces of a Painting Degree Course to Explore Her Sexual Desirability and Aesthetics as a "Grotesque" Female Body

ERIC Educational Resources Information Center

Chittenden, Tara

2013-01-01

Whilst a part of the fine art degree course is about teaching technical skills and learning from tutor/peer group crits, a larger part is about the facilitation of a "safe" and structured space in which students gain the confidence to experiment with personal ideas, to hone a self-critical reflection and understand who they are as individuals,…

Neutron-detecting apparatuses and methods of fabrication

DOEpatents

Dahal, Rajendra P.; Huang, Jacky Kuan-Chih; Lu, James J. Q.; Danon, Yaron; Bhat, Ishwara B.

2015-10-06

Neutron-detecting structures and methods of fabrication are provided which include: a substrate with a plurality of cavities extending into the substrate from a surface; a p-n junction within the substrate and extending, at least in part, in spaced opposing relation to inner cavity walls of the substrate defining the plurality of cavities; and a neutron-responsive material disposed within the plurality of cavities. The neutron-responsive material is responsive to neutrons absorbed for releasing ionization radiation products, and the p-n junction within the substrate spaced in opposing relation to and extending, at least in part, along the inner cavity walls of the substrate reduces leakage current of the neutron-detecting structure.

Advanced technology requirements for large space structures. Part 5: Atlas program requirements

NASA Technical Reports Server (NTRS)

Katz, E.; Lillenas, A. N.; Broddy, J. A.

1977-01-01

The results of a special study which identifies and assigns priorities to technology requirements needed to accomplish a particular scenario of future large area space systems are described. Proposed future systems analyzed for technology requirements included large Electronic Mail, Microwave Radiometer, and Radar Surveillance Satellites. Twenty technology areas were identified as requirements to develop the proposed space systems.

OAST Space Theme Workshop. Volume 2: Theme summary. 2: Space industrialization (no. 8). A. Theme statement. B. 26 April 1976 presentation. C. Summary statement. D. Initiative action (form 5)

NASA Technical Reports Server (NTRS)

1976-01-01

Enabling technology needs and other requirements to support space industrialization include: large space structures; fabrication and joining processes; single stage to orbit and heavy lift launch vehicles; nuclear and solar space power systems; robotics, manipulators, and teleoperators; biotechnology in space; artificial gravity; the utilization of lunar materials for construction; and the extraction of oxygen and metals from lunar resources. New initiatives (FY 1978) directly supportive or partly related to space industrialization are listed.

Design concept for the microwave interrogation structure in PARCS

NASA Technical Reports Server (NTRS)

Dick, G. J.; Klipstein, W. M.; Heavner, T. P.; Jefferts, S. R.

2002-01-01

In this paper we will describe key aspects of the conceptual design of the microwave interrogation structure in the laser-cooled cesium frequency standard that is part of the Primary Atomic Reference Clock in Space (PARCS) experiment.

Collision avoidance in space

NASA Technical Reports Server (NTRS)

Kessler, D. J.; Cour-Palais, B. G.; Taylor, R. E.; Landry, P. M.

1980-01-01

Collisions in earth orbital space between operational payloads and various forms of space debris (nonoperational payloads, nonfunctional mission-related objects and fragments resulting from collisions and explosions) are discussed and possible means of avoiding them are considered. From 10,000 to 15,000 objects are estimated to be in earth orbital space, most of which represent spacecraft fragments and debris too small to be detected and tracked by earth-based sensors, and it is considered likely that some of them will be or have already been involved in direct collisions with the ever increasing number of operational satellites and space stations. Means of protecting proposed large space structures and smaller spacecraft from significant damage by larger space objects, particularly in the 400-4000 km altitude range where most debris occurs, include structural redundancy and the double shielding of sensitive components. Other means of collision avoidance are the collection or relocation of satellites, rocket bodies and other objects by the Space Shuttle, the prevention of explosions and the disposal of spent rocket parts by reentry. Finally, a management structure would be required to administer guidelines for the prevention and elimination of space debris.

Use of designed sequences in protein structure recognition.

PubMed

Kumar, Gayatri; Mudgal, Richa; Srinivasan, Narayanaswamy; Sandhya, Sankaran

2018-05-09

Knowledge of the protein structure is a pre-requisite for improved understanding of molecular function. The gap in the sequence-structure space has increased in the post-genomic era. Grouping related protein sequences into families can aid in narrowing the gap. In the Pfam database, structure description is provided for part or full-length proteins of 7726 families. For the remaining 52% of the families, information on 3-D structure is not yet available. We use the computationally designed sequences that are intermediately related to two protein domain families, which are already known to share the same fold. These strategically designed sequences enable detection of distant relationships and here, we have employed them for the purpose of structure recognition of protein families of yet unknown structure. We first measured the success rate of our approach using a dataset of protein families of known fold and achieved a success rate of 88%. Next, for 1392 families of yet unknown structure, we made structural assignments for part/full length of the proteins. Fold association for 423 domains of unknown function (DUFs) are provided as a step towards functional annotation. The results indicate that knowledge-based filling of gaps in protein sequence space is a lucrative approach for structure recognition. Such sequences assist in traversal through protein sequence space and effectively function as 'linkers', where natural linkers between distant proteins are unavailable. This article was reviewed by Oliviero Carugo, Christine Orengo and Srikrishna Subramanian.

Space Shuttle Technical Conference, part 1

NASA Technical Reports Server (NTRS)

Chaffee, N. (Compiler)

1985-01-01

Articles providing a retrospective presentation and documentation of the key scientific and engineering achievements of the Space Shuttle Program are compiled. Topics areas include: (1) integrated avionics; (2) guidance, navigation, and control; (3) aerodynamics; (4) structures; (5) life support; environmental control; and crew station; and (6) ground operations.

33 CFR 174.3 - Definitions.

Code of Federal Regulations, 2014 CFR

2014-07-01

... spaces inside its structure. Certificate of number means the certificate required by 33 CFR 173.21... harvesting of fish which, either in whole or in part, is intended to enter commerce through sale, barter, or...-purpose accommodation spaces with low freeboard and little or no foredeck or cockpit. Hull identification...

33 CFR 174.3 - Definitions.

Code of Federal Regulations, 2013 CFR

2013-07-01

... spaces inside its structure. Certificate of number means the certificate required by 33 CFR 173.21... harvesting of fish which, either in whole or in part, is intended to enter commerce through sale, barter, or...-purpose accommodation spaces with low freeboard and little or no foredeck or cockpit. Hull identification...

33 CFR 174.3 - Definitions.

Code of Federal Regulations, 2012 CFR

2012-07-01

... spaces inside its structure. Certificate of number means the certificate required by 33 CFR 173.21... harvesting of fish which, either in whole or in part, is intended to enter commerce through sale, barter, or...-purpose accommodation spaces with low freeboard and little or no foredeck or cockpit. Hull identification...

Assembly of Space CFRP Structures with Racing Sailing Boats Technology

NASA Astrophysics Data System (ADS)

Nieto, Jose; Yuste, Laura; Pipo, Alvaro; Santarsiero, Pablo; Bureo, Rafael

2014-06-01

Carbon Fiber Reinforced Plastic (CFRP) is commonly used in space applications to get structures with good mechanical performances and a reduced mass. Most of larger parts of spatial structures are already made of CFRP but the achieved weight saving may be jeopardized by the use of metallic brackets as joining elements. This paper describes the work carried out to study and evaluate ways of reducing weight and costs of the joints between structural elements commonly used in space applications.The main objective of this project is to adapt design solutions coming from the racing sailing boats technology to space applications: the use of out-of autoclave (OoA) cured CFRP joints. In addition to that other CFRP solution common in space business, 3D- RTM Bracket, has been evaluated.This development studies the manufacturing and assembly feasibility making use of these CFRP technologies.This study also compares traditional metallic solutions with innovative CFRP ones in terms of mechanical performances at elementary level. Weight and cost of presented solutions are also compared.

KSC-08pd3441

NASA Image and Video Library

2008-10-29

CAPE CANAVERAL, Fla. – On Launch Pad 39A at NASA's Kennedy Space Center in Florida, STS-126 Mission Specialists Sandra Magnus, Shane Kimbrough and Heidemarie Stefanyshyn-Piper have taken their seats in a slidewire basket, part of the emergency escape system on the 195-foot level of the fixed service structure. They have taken part in a simulated countdown in space shuttle Endeavour. The crew is at Kennedy to take part in the Terminal Countdown Demonstration Test, which includes equipment familiarization, emergency exit training and the simulated countdown. On the STS-126 mission, space shuttle Endeavour's crew will deliver equipment and supplies to the International Space Station in preparation for expansion from a three- to six-person resident crew aboard the complex. The mission also will include four spacewalks to service the station’s Solar Alpha Rotary Joints. Endeavour is targeted to launch Nov. 14. Photo credit: NASA/Troy Cryder

Hamiltonian flow over saddles for exploring molecular phase space structures

NASA Astrophysics Data System (ADS)

Farantos, Stavros C.

2018-03-01

Despite using potential energy surfaces, multivariable functions on molecular configuration space, to comprehend chemical dynamics for decades, the real happenings in molecules occur in phase space, in which the states of a classical dynamical system are completely determined by the coordinates and their conjugate momenta. Theoretical and numerical results are presented, employing alanine dipeptide as a model system, to support the view that geometrical structures in phase space dictate the dynamics of molecules, the fingerprints of which are traced by following the Hamiltonian flow above saddles. By properly selecting initial conditions in alanine dipeptide, we have found internally free rotor trajectories the existence of which can only be justified in a phase space perspective. This article is part of the theme issue `Modern theoretical chemistry'.

X-cephalometric study of different parts of the upper airway space and changes in hyoid position following mandibular fractures.

PubMed

Chen, L-J; Zhao, M-C; Pan, X-F; Wei, Y-Q; Wang, D-Y

2013-09-01

This study analyses the different parts of the upper airway space and the changes in hyoid position. The results provide a clinical reference for developing timely and effective treatment programmes for patients with mandibular fractures caused by maxillofacial trauma. Standard X-cephalometric measurements of the lateral skull of 210 subjects were taken. The subjects were divided into four fracture groups: condylar, mandibular angle, mandibular body, and parasymphyseal. The radiographs of the mandibular fracture groups were compared with the normal occlusion group to analyse the upper airway space and the changes in hyoid position. Different types of fractures have different effects on the upper airway space. Bilateral mandibular body fracture and the parasymphyseal fracture have a significant influence on the lower oropharyngeal and laryngopharyngeal airway spaces, with serious obstructions severely restricting the ventilatory function of patients. Fractures at different parts of the mandibular structure are closely related to the upper airway and hyoid position.

A new concept in telescope design SIC as the only material for mirrors and structure

NASA Astrophysics Data System (ADS)

Fruit, Michel; Antoine, Pascal; Bougoin, Michel

2018-04-01

This paper, "A new concept in telescope design SIC as the only material for mirrors and structure," was presented as part of International Conference on Space Optics—ICSO 1997, held in Toulouse, France.

CeSiCò - a new technology for lightweight and cost effective space instruments structures and mirrors

NASA Astrophysics Data System (ADS)

Devilliers, Christophe; Krödel, Matthias

2017-11-01

Alcatel Alenia Space and ECM have jointly developed a new ceramic material to produce lightweight, stiff, stable and cost effective structures and mirrors for space instrument the CesicÒ. Its intrinsic properties, added to ample manufacturing capabilities allow to manufacture stiff and lightweight cost effective mirrors and structure for space instruments. Different scale 1 flight representative CesicÒ optical structures have been manufactured and successfully tested under very strong dynamic environment and cryogenic condition down to 30K CesicÒ is also envisaged for large and lightweight space telescopes mirrors, a large CesicÒ 1 meter class mirror with an area mass of less than 25 Kg/m2 has been sized again launch loads and WFE performance and manufactured. CesicÒ applicability for large focal plane have been demonstrated through different scale 1 breadboards. Based on these successful results, AlcatelAleniaSpace and ECM are now in position to propose for space this technology with new innovative concepts thanks to the CesicÒ manufacturing capabilities. CesicÒ has therefore been selected for the structure and mirrors parts of a flight instrument payload and the manufacturing of the flight hardware is already underway. An high temperature high gain lightweight antenna breadboard is also under manufacturing for Bepi colombo mission. CesicÒ is therefore a good candidate for future challenging space instruments and is currently proposed for Japan and US space projects.

76 FR 13580 - Bus Testing; Calculation of Average Passenger Weight and Test Vehicle Weight

Federal Register 2010, 2011, 2012, 2013, 2014

2011-03-14

... occupied per standing passenger from 1.5 to 1.75 square feet, and updating the Structural Strength and... standing passenger from 1.5 square feet of free floor space to 1.75 square feet of free floor space to... (assumed to be each 1.75 square foot of free floor space). * * * * * 3. Amend Appendix A to part 665 by...

Metal-Matrix Composite Parts With Metal Inserts

NASA Technical Reports Server (NTRS)

Majkowski, T.; Kashalikar, U.

1995-01-01

Developmental fabrication process produces metal-matrix composite (MMC) parts with integral metal inserts. With inserts, MMC parts readily joined to similar parts by use of brazing, welding, or mechanical fasteners. Process conceived to make strong, lightweight components of structures erected in outer space. Also useful on Earth, in such automotive parts as rocker arms, cylinder liners, and pistons. Potential industrial applications include parts subjected to high stresses at high temperatures, as in power-generation, mining, and oil-drilling equipment.

STS-110 M.S. Smith and Ross in slidewire basket during TCDT

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- STS-110 Mission Specialists Steven L. Smith (left) and Jerry L. Ross (right) get ready to climb out of the slidewire basket, part of emergency egress equipment on the launch pad.. The crew is taking part in Terminal Countdown Demonstration Test activities, which also include a simulated launch countdown, held at KSC prior to each Space Shuttle flight. Scheduled for launch April 4, the 11-day mission will feature Shuttle Atlantis docking with the International Space Station (ISS) and delivering the S0 truss, the centerpiece-segment of the primary truss structure that will eventually extend over 300 feet.

47 CFR 25.113 - Station licenses and launch authority.

Code of Federal Regulations, 2013 CFR

2013-10-01

... is required by part 17 of this chapter, must include the FCC Antenna Structure Registration Number(s) for the affected structure(s). If no such number has been assigned at the time the application is...) Construction permits are not required for U.S.-licensed space stations. Construction of such stations may...

Human Factors Research Under Ground-Based and Space Conditions. Part 1

NASA Technical Reports Server (NTRS)

1997-01-01

Session TP2 includes short reports concerning: (1) Human Factors Engineering of the International space Station Human Research Facility; (2) Structured Methods for Identifying and Correcting Potential Human Errors in Space operation; (3) An Improved Procedure for Selecting Astronauts for Extended Space Missions; (4) The NASA Performance Assessment Workstation: Cognitive Performance During Head-Down Bedrest; (5) Cognitive Performance Aboard the Life and Microgravity Spacelab; and (6) Psychophysiological Reactivity Under MIR-Simulation and Real Micro-G.

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

Singh, Surendra; Jauriqui, Leanne; Sloan, Trista

We have used Process Compensated Resonant Testing (PCRT) for studying structural integrity and functional performance of ceramic balls used in various auxiliary power units (APUs), propulsion engines, and defense and space missiles. The results show that PCRT is successful in sorting acceptable parts from parts with defects such as micro-structural changes, C-cracks, and scuffs. However, PCRT suffers from limitations, generally not determining the type, size or location of the anomaly. The pursuit of improvements to PCRT is an on-going process.

Canadian Activities in Space Debris Mitigation Technologies

NASA Astrophysics Data System (ADS)

Nikanpour, Darius; Jiang, Xin Xiang; Goroshin, Samuel; Haddad, Emile; Kruzelecky, Roman; Hoa, Suong; Merle, Philippe; Kleiman, Jacob; Gendron, Stephane; Higgins, Andrew; Jamroz, Wes

The space environment, and in particular the Low Earth Orbit (LEO), is becoming increasingly populated with space debris which include fragments of dysfunctional spacecraft parts and materials traveling at speeds up to 15 km per second. These pose an escalating potential threat to LEO spacecraft, the international space station, and manned missions. This paper presents the Canadian activities to address the concerns over space debris in terms of debris mitigation measures and technologies; these include novel spacecraft demise technologies to safely decommission the spacecraft at the end of the mission, integrated self-healing material technologies for spacecraft structures to facilitate self-repair and help maintain the spacecraft structural and thermal performance, hypervelocity ground test capability to predict the impact of space debris on spacecraft performance, and ways of raising awareness within the space community through participation in targeted Science and Technology conferences and international forums.

Space construction system analysis. Part 2: Construction analysis

NASA Technical Reports Server (NTRS)

Roebuck, J. A.; Buck, P. A.; Gimlich, G. W.; Greenberg, H. S.; Hart, R. J.; Indrikis, J.; Lefever, A. E.; Lillenas, A. N.; Mcbaine, C. K.

1980-01-01

The construction methods specific to the end to end construction process for building the ETVP in low Earth orbit, using the space shuttle orbiter as a construction base, are analyzed. The analyses concerned three missions required to build the basic platform. The first mission involved performing the fabrication of beams in space and assembling the beams into a basic structural framework. The second mission was to install the forward support structure and aft support structure, the forward assembly, and a TT&C antenna. The third mission plan was to complete the construction of the platform and activate it to begin operations in low Earth orbit. The integration of the activities for each mission is described along with the construction requirements and construction logic.

Space Research and Technology Program: Program and specific objectives, document approval

NASA Technical Reports Server (NTRS)

1982-01-01

A detailed view of the Space Research and Technology program work breakdown structure is provided down to the specific objective level. Goals or objectives at each of these levels are set forth. The specific objective narratives are structured into several parts. First, a short paragraph statement of the specific objective is given. This is followed by a list of subobjectives. A list of targets is then provided for those areas of the specific objective that are amenable to a quantitative description of technical accomplishment and schedule. Fluid and thermal physics, materials and structures, computer science and electronics, space energy conversion, multidisciplinary research, controls and human factors, chemical propulsion, spacecraft systems, transportation systems, platform systems, and spacecraft systems technology comprise the principal research programs.

KSC-08pd3443

NASA Image and Video Library

2008-10-29

CAPE CANAVERAL, Fla. – On Launch Pad 39A at NASA's Kennedy Space Center in On Launch Pad 39A at NASA's Kennedy Space Center in Florida, STS-126 crew members climb into a slidewire basket on the 195-foot level of the fixed service structure. They have taken part in a simulated countdown in space shuttle Endeavour. The crew is at Kennedy to take part in the Terminal Countdown Demonstration Test, which includes equipment familiarization, emergency exit training and the simulated countdown. On the STS-126 mission, space shuttle Endeavour's crew will deliver equipment and supplies to the International Space Station in preparation for expansion from a three- to six-person resident crew aboard the complex. The mission also will include four spacewalks to service the station’s Solar Alpha Rotary Joints. Endeavour is targeted to launch Nov. 14. Photo credit: NASA/Troy Cryder

Evaluation of Advanced Composite Structures Technologies for Application to NASA's Vision for Space Exploration

NASA Technical Reports Server (NTRS)

Tenney, Darrel R.

2008-01-01

AS&M performed a broad assessment survey and study to establish the potential composite materials and structures applications and benefits to the Constellation Program Elements. Trade studies were performed on selected elements to determine the potential weight or performance payoff from use of composites. Weight predictions were made for liquid hydrogen and oxygen tanks, interstage cylindrical shell, lunar surface access module, ascent module liquid methane tank, and lunar surface manipulator. A key part of this study was the evaluation of 88 different composite technologies to establish their criticality to applications for the Constellation Program. The overall outcome of this study shows that composites are viable structural materials which offer from 20% to 40% weight savings for many of the structural components that make up the Major Elements of the Constellation Program. NASA investment in advancing composite technologies for space structural applications is an investment in America's Space Exploration Program.

Astronauts Bob Behnken and Eric Boe walk the Crew Access Arm at

NASA Image and Video Library

2017-08-30

Astronauts Bob Behnken, left, and Eric Boe walk down the Crew Access Arm being built by SpaceX for Launch Complex 39A at NASA’s Kennedy Space Center in Florida. The access arm will be installed on the launch pad, providing a bridge between the launch tower it’s the Fixed Service Structure, as noted below, and SpaceX’s Dragon 2 spacecraft for astronauts flying to the International Space Station on the company’s Falcon 9 rocket as part of NASA’s Commercial Crew Program. The access arm is being readied for installation in early 2018. It will be installed 70 feet higher than the former space shuttle access arm on the launch pad’s Fixed Service Structure. SpaceX continues to modify the historic launch site from its former space shuttle days, removing more than 500,000 pounds of steel from the pad structure, including the Rotating Service Structure that was once used for accessing the payload bay of the shuttle. SpaceX also is using the modernized site to launch commercial payloads, as well as cargo resupply missions to and from the International Space Station for NASA. The first SpaceX launch from the historic Apollo and space shuttle site was this past February. NASA’s Commercial Crew Program is working with private companies, Boeing and SpaceX, with a goal of once again flying people to and from the International Space Station, launching from the United States.

Space transfer concepts and analyses for exploration missions

NASA Technical Reports Server (NTRS)

Woodcock, Gordon R.

1992-01-01

The current technical effort is part of the third phase of a broad-scoped and systematic study of space transfer concepts for human lunar and Mars missions. The study addressed the technical issues relating to the First Lunar Outpost (FLO) habitation vehicle with emphasis in the structure, power, life support system, and radiation environment.

Probabilistic Sizing and Verification of Space Ceramic Structures

NASA Astrophysics Data System (ADS)

Denaux, David; Ballhause, Dirk; Logut, Daniel; Lucarelli, Stefano; Coe, Graham; Laine, Benoit

2012-07-01

Sizing of ceramic parts is best optimised using a probabilistic approach which takes into account the preexisting flaw distribution in the ceramic part to compute a probability of failure of the part depending on the applied load, instead of a maximum allowable load as for a metallic part. This requires extensive knowledge of the material itself but also an accurate control of the manufacturing process. In the end, risk reduction approaches such as proof testing may be used to lower the final probability of failure of the part. Sizing and verification of ceramic space structures have been performed by Astrium for more than 15 years, both with Zerodur and SiC: Silex telescope structure, Seviri primary mirror, Herschel telescope, Formosat-2 instrument, and other ceramic structures flying today. Throughout this period of time, Astrium has investigated and developed experimental ceramic analysis tools based on the Weibull probabilistic approach. In the scope of the ESA/ESTEC study: “Mechanical Design and Verification Methodologies for Ceramic Structures”, which is to be concluded in the beginning of 2012, existing theories, technical state-of-the-art from international experts, and Astrium experience with probabilistic analysis tools have been synthesized into a comprehensive sizing and verification method for ceramics. Both classical deterministic and more optimised probabilistic methods are available, depending on the criticality of the item and on optimisation needs. The methodology, based on proven theory, has been successfully applied to demonstration cases and has shown its practical feasibility.

Methods for evaluating the predictive accuracy of structural dynamic models

NASA Technical Reports Server (NTRS)

Hasselman, Timothy K.; Chrostowski, Jon D.

1991-01-01

Modeling uncertainty is defined in terms of the difference between predicted and measured eigenvalues and eigenvectors. Data compiled from 22 sets of analysis/test results was used to create statistical databases for large truss-type space structures and both pretest and posttest models of conventional satellite-type space structures. Modeling uncertainty is propagated through the model to produce intervals of uncertainty on frequency response functions, both amplitude and phase. This methodology was used successfully to evaluate the predictive accuracy of several structures, including the NASA CSI Evolutionary Structure tested at Langley Research Center. Test measurements for this structure were within + one-sigma intervals of predicted accuracy for the most part, demonstrating the validity of the methodology and computer code.

A-1 Test Stand work

NASA Technical Reports Server (NTRS)

2010-01-01

A structural steel beam to support the new thrust measurement system on the A-1 Test Stand at NASA's John C. Stennis Space Center is lifted to waiting employees for installation. The beam is part of the thrust takeout structure needed to support the new measurement system. Four such beams have been installed at the stand in preparation for installation of the system in upcoming weeks. Operators are preparing the stand for testing the next generation of rocket engines for the U.S. space program.

Explorers Program Management

NASA Technical Reports Server (NTRS)

Volpe, Frank; Comberiate, Anthony B. (Technical Monitor)

2001-01-01

The mission of the Explorer Program is to provide frequent flight opportunities for world-class scientific investigations from space within the following space science themes: 1) Astronomical Search for Origins and Planetary Systems; 2) Structure and Evolution of the Universe; and 3) The Sun-Earth Connection. America's space exploration started with Explorer 1 which was launched February 1, 1958 and discovered the Van Allen Radiation Belts. Over 75 Explorer missions have flown. The program seeks to enhance public awareness of, and appreciation for, space science and to incorporate. educational and public outreach activities as integral parts of space science investigations.

KSC-08pd3444

NASA Image and Video Library

2008-10-29

CAPE CANAVERAL, Fla. – On Launch Pad 39A at NASA's Kennedy Space Center in Florida, STS-126 crew members head for the slidewire baskets on the 195-foot level of the fixed service structure. They have taken part in a simulated countdown in space shuttle Endeavour. The crew is at Kennedy to take part in the Terminal Countdown Demonstration Test, which includes equipment familiarization, emergency exit training and the simulated countdown. On the STS-126 mission, space shuttle Endeavour's crew will deliver equipment and supplies to the International Space Station in preparation for expansion from a three- to six-person resident crew aboard the complex. The mission also will include four spacewalks to service the station’s Solar Alpha Rotary Joints. Endeavour is targeted to launch Nov. 14. Photo credit: NASA/Troy Cryder

KSC-08pd3445

NASA Image and Video Library

2008-10-29

CAPE CANAVERAL, Fla. – On Launch Pad 39A at NASA's Kennedy Space Center in Florida, STS-126 crew members climb into a slidewire basket on the 195-foot level of the fixed service structure. They have taken part in a simulated countdown in space shuttle Endeavour. The crew is at Kennedy to take part in the Terminal Countdown Demonstration Test, which includes equipment familiarization, emergency exit training and the simulated countdown. On the STS-126 mission, space shuttle Endeavour's crew will deliver equipment and supplies to the International Space Station in preparation for expansion from a three- to six-person resident crew aboard the complex. The mission also will include four spacewalks to service the station’s Solar Alpha Rotary Joints. Endeavour is targeted to launch Nov. 14. Photo credit: NASA/Troy Cryder

KSC-08pd3442

NASA Image and Video Library

2008-10-29

CAPE CANAVERAL, Fla. – On Launch Pad 39A at NASA's Kennedy Space Center in Florida, STS-126 crew members head for the slidewire baskets on the 195-foot level of the fixed service structure. They have taken part in a simulated countdown in space shuttle Endeavour. The crew is at Kennedy to take part in the Terminal Countdown Demonstration Test, which includes equipment familiarization, emergency exit training and the simulated countdown. On the STS-126 mission, space shuttle Endeavour's crew will deliver equipment and supplies to the International Space Station in preparation for expansion from a three- to six-person resident crew aboard the complex. The mission also will include four spacewalks to service the station’s Solar Alpha Rotary Joints. Endeavour is targeted to launch Nov. 14. Photo credit: NASA/Troy Cryder

KSC-02pd0390

NASA Image and Video Library

2002-04-03

KENNEDY SPACE CENTER, FLA. -- Space Shuttle Atlantis is revealed as the Rotating Service Structure rolls back into launch position. The RSS provides protected access to the orbiter for changeout and servicing of payloads at the pad. The structure has access platforms at five levels to provide access to the payload bay. The Shuttle rests on the Mobile Launcher Platform (MLP), which straddles the flame trench below. The flame trench is part of the Flame Deflector System that insulates pad structures from the intense heat of the launch. Above the golden external tank is the vent hood (known as the "beanie cap") at the end of the gaseous oxygen vent arm. Vapors are created as the liquid oxygen in the external tank boil off. The hood vents the gaseous oxygen vapors away from the Space Shuttle vehicle. Mission STS-110 is scheduled to launch April 4 on its 11-day mission to the International Space Station

3D Printing in Zero G Technology Demonstration Mission: Summary of On-Orbit Operations, Material Testing, and Future Work

NASA Technical Reports Server (NTRS)

Prater, Tracie; Bean, Quincy; Werkheiser, Niki; Ordonez, Erick; Ledbetter, Frank; Ryan, Richard; Newton, Steve

2016-01-01

Human space exploration to date has been limited to low Earth orbit and the moon. The International Space Station (ISS), an orbiting laboratory 200 miles above the earth, provides a unique and incredible opportunity for researchers to prove out the technologies that will enable humans to safely live and work in space for longer periods of time and venture farther into the solar system. The ability to manufacture parts in-space rather than launch them from earth represents a fundamental shift in the current risk and logistics paradigm for human spaceflight. In particularly, additive manufacturing (or 3D printing) techniques can potentially be deployed in the space environment to enhance crew safety (by providing an on-demand part replacement capability) and decrease launch mass by reducing the number of spare components that must be launched for missions where cargo resupply is not a near-term option. In September 2014, NASA launched the 3D Printing in Zero G technology demonstration mission to the ISS to explore the potential of additive manufacturing for in-space applications and demonstrate the capability to manufacture parts and tools on-orbit. The printer for this mission was designed and operated by the company Made In Space under a NASA SBIR (Small Business Innovation Research) phase III contract. The overarching objectives of the 3D print mission were to use ISS as a testbed to further maturation of enhancing technologies needed for long duration human exploration missions, introduce new materials and methods to fabricate structure in space, enable cost-effective manufacturing for structures and mechanisms made in low-unit production, and enable physical components to be manufactured in space on long duration missions if necessary. The 3D print unit for fused deposition modeling (FDM) of acrylonitrile butadiene styrene (ABS) was integrated into the ISS Microgravity Science Glovebox (MSG) in November 2014 and phase I printing operations took place from November through December of that year. Phase I flight operations yielded 14 unique parts (21 total specimens) that could be directly compared against ground-based prints of identical geometry manufactured using the printer prior to its launch to ISS. The 3DP unit functioned safely and produced specimens necessary to advance the understanding of the critical design and operational parameters for the FDM process as affected by the microgravity environment. From the standpoint of operations, 3DP demonstrated the ability to remove parts from the build-tray on-orbit, teleoperate the printer from the ground, perform critical maintenance functions within defined human factors limits, produce a functional tool that could be evaluated for form/fit/function, and uplink a new part file from the ground and produce it on the printer. The flight parts arrived at NASA Marshall Space Flight Center in Huntsville, Alabama in April 2015, where they underwent months of testing in the materials and processes laboratory. Ground and flight prints completed the following phases of testing: photographic/visual inspection, mass and density evaluation, structured light scanning, XRay and CT, mechanical testing, optical microscopy, scanning electron microscopy, and chemical analysis. This presentation will discuss the results of this testing as well as phase II operations for the printer, which took place in June and July of 2016. Lessons learned from the tech demo and their impacts on the design and development of the second generation 3D printer for ISS, the Additive Manufacturing Facility (AMF) by Made In Space will also be presented. In addition, progress in other elements of NASA's In Space Manufacturing (ISM) initiative such as the on-demand ISM utilization catalog, in-space Recycler ISS Technology Demonstration development, launch packaging recycling, in-space printable electronics, development of higher strength polymeric materials for 3D printing and Additive Construction by Mobile Emplacement (ACME) will also be addressed.

Retroreflector field tracker. [noncontact optical position sensor for space application

NASA Technical Reports Server (NTRS)

Wargocki, F. E.; Ray, A. J.; Hall, G. E.

1984-01-01

An electrooptical position-measuring instrument, the Retroreflector Field Tracker or RFT, is described. It is part of the Dynamic Augmentation Experiment - a part of the payload of Space Shuttle flight 41-D in Summer 1984. The tracker measures and outputs the position of 23 reflective targets placed on a 32-m solar array to provide data for determination of the dynamics of the lightweight structure. The sensor uses a 256 x 256 pixel CID detector; the processor electronics include three Z-80 microprocessors. A pulsed laser diode illuminator is used.

KSC-00padig088

NASA Image and Video Library

2000-11-08

STS-97 Mission Specialist Marc Garneau, who is with the Canadian Space Agency, settles into his seat in Space Shuttle Endeavour on Launch Pad 39B. He and the rest of the crew are taking part in a simulated launch countdown, part of Terminal Countdown Demonstration Test activities that also include emergency egress training and familiarization with the payload. Mission STS-97 is the sixth construction flight to the International Space Station. Its payload includes the P6 Integrated Truss Structure and a photovoltaic (PV) module, with giant solar arrays that will provide power to the Station. The mission includes two spacewalks to complete the solar array connections. STS-97 is scheduled to launch Nov. 30 at about 10:05 p.m. EST

SLS Engine Section Test Article Moves From NASA Barge Pegasus To Test Stand at NASA’s Marshall Space Flight Center

NASA Image and Video Library

2017-05-18

The NASA barge Pegasus made its first trip to NASA’s Marshall Space Flight Center in Huntsville, Alabama on May 15. It arrived carrying the first piece of Space Launch System hardware built at NASA's Michoud Assembly Facility in New Orleans. The barge left Michoud on April 28 with the core stage engine section test article, traveling 1,240 miles by river to Marshall. The rocket's engine section is the bottom of the core stage and houses the four RS-25 engines. The engine section test article was moved from the barge to Marshall’s Building 4619 where it will be tested. The bottom part of the test article is structurally the same as the engine section that will be flown as part of the SLS core stage. The shiny metal top part simulates the rocket's liquid hydrogen tank, which is the fuel tank that joins to the engine section. The test article will endure tests that pull, push, and bend it, subjecting it to millions of pounds of force. This ensures the structure can withstand the incredible stresses produced by the 8.8 million pounds of thrust during launch and ascent.

Focused conformational sampling in proteins

NASA Astrophysics Data System (ADS)

Bacci, Marco; Langini, Cassiano; Vymětal, Jiří; Caflisch, Amedeo; Vitalis, Andreas

2017-11-01

A detailed understanding of the conformational dynamics of biological molecules is difficult to obtain by experimental techniques due to resolution limitations in both time and space. Computer simulations avoid these in theory but are often too short to sample rare events reliably. Here we show that the progress index-guided sampling (PIGS) protocol can be used to enhance the sampling of rare events in selected parts of biomolecules without perturbing the remainder of the system. The method is very easy to use as it only requires as essential input a set of several features representing the parts of interest sufficiently. In this feature space, new states are discovered by spontaneous fluctuations alone and in unsupervised fashion. Because there are no energetic biases acting on phase space variables or projections thereof, the trajectories PIGS generates can be analyzed directly in the framework of transition networks. We demonstrate the possibility and usefulness of such focused explorations of biomolecules with two loops that are part of the binding sites of bromodomains, a family of epigenetic "reader" modules. This real-life application uncovers states that are structurally and kinetically far away from the initial crystallographic structures and are also metastable. Representative conformations are intended to be used in future high-throughput virtual screening campaigns.

Space Shuttle Projects

NASA Image and Video Library

1978-09-29

This photo depicts the installation of an External Tank (ET) into the Marshall Space Flight Center Dynamic Test Stand, building 4550. It is being mated to the Solid Rocket Boosters (SRB's) for a Mated Vertical Ground Vibration Test (MVGVT). At 154-feet long and more than 27-feet in diameter, the ET is the largest component of the Space Shuttle, the structural backbone of the entire Shuttle system, and is the only part of the vehicle that is not reusable.

Security aspects of space operations data

NASA Technical Reports Server (NTRS)

Schmitz, Stefan

1993-01-01

This paper deals with data security. It identifies security threats to European Space Agency's (ESA) In Orbit Infrastructure Ground Segment (IOI GS) and proposes a method of dealing with its complex data structures from the security point of view. It is part of the 'Analysis of Failure Modes, Effects Hazards and Risks of the IOI GS for Operations, including Backup Facilities and Functions' carried out on behalf of the European Space Operations Center (ESOC). The security part of this analysis has been prepared with the following aspects in mind: ESA's large decentralized ground facilities for operations, the multiple organizations/users involved in the operations and the developments of ground data systems, and the large heterogeneous network structure enabling access to (sensitive) data which does involve crossing organizational boundaries. An IOI GS data objects classification is introduced to determine the extent of the necessary protection mechanisms. The proposal of security countermeasures is oriented towards the European 'Information Technology Security Evaluation Criteria (ITSEC)' whose hierarchically organized requirements can be directly mapped to the security sensitivity classification.

Introduction

NASA Astrophysics Data System (ADS)

Carotenuto, Luigi

This chapter introduces the context, objectives and structure of the book. This book aims both to contribute to disseminate the knowledge about the scientific research conducted in space and to promote new exploitation of existing data in this field. While space experiments are characterised by a long time for preparation, high costs and few opportunities, significant scientific value is expected from the resulting data for almost scientific disciplines. In this context, ISS is a unique experimental environment for research. As part of its Seventh Framework Programme, the European Commission intends to support further exploitation and valorisation of space experimental data. This book was realised as part of the ULISSE project, co-funded by the European Union. The book intends to provide an introduction to space research with a focus on the experiments performed on the ISS and related disciplines. The book also intends to be a useful guide, not only for scientists but also for teachers, students and newcomers to space research activities.

SpaceX-3 KSC Payloads: Biotube, Bric, Apex2-2

NASA Image and Video Library

2014-03-07

CAPE CANAVERAL, Fla. - In the Space Station Processing Facility at NASA's Kennedy Space Center in Florida, Allison Caron, a QinetiQ mechanical engineer, checks out part of the Biotube experiment which will be launched to the International Space Station aboard a SpaceX Dragon spacecraft. Scheduled for launch on March 16 atop a Falcon 9 rocket, Dragon will be marking its fourth trip to the space station. The SpaceX-3 mission is the third of 12 flights contracted by NASA to resupply the orbiting laboratory. For more information, visit http://www.nasa.gov/mission_pages/station/structure/launch/index.html Photo credit: NASA/Kim Shiflett

"You're Really Gonna Kick Us All Out?" Sustaining Safe Spaces for Community-Based HIV Prevention and Control among Black Men Who Have Sex with Men.

PubMed

Garcia, Jonathan; Parker, Caroline; Parker, Richard G; Wilson, Patrick A; Philbin, Morgan M; Hirsch, Jennifer S

2015-01-01

Black men who have sex with men (BMSM) experience among the highest rates of HIV infection in the United States. We conducted a community-based ethnography in New York City to identify the structural and environmental factors that influence BMSMs vulnerability to HIV and their engagement with HIV prevention services. Methods included participant observation at community-based organizations (CBOs) in New York City, in-depth interviews with 31 BMSM, and 17 key informant interviews. Our conceptual framework shows how creating and sustaining safe spaces could be a critical environmental approach to reduce vulnerability to HIV among BMSM. Participant observation, in-depth and key informant interviews revealed that fear and mistrust characterized men's relation to social and public institutions, such as churches, schools, and the police. This fear and mistrust created HIV vulnerability among the BMSM in our sample by challenging engagement with services. Our findings suggest that to be successful, HIV prevention efforts must address these structural and environmental vulnerabilities. Among the CBOs that we studied, "safe spaces" emerged as an important tool for addressing these environmental vulnerabilities. CBOs used safe spaces to provide social support, to address stigma, to prepare men for the workforce, and to foster a sense of community among BMSM. In addition, safe spaces were used for HIV and STI testing and treatment campaigns. Our ethnographic findings suggest that safe spaces represent a promising but so far under-utilized part of HIV prevention infrastructure. Safe spaces seem integral to high impact comprehensive HIV prevention efforts, and may be considered more appropriately as part of HIV capacity-building rather than being nested within program-specific funding structures.

41 CFR 102-85.35 - What definitions apply to this part?

Code of Federal Regulations, 2010 CFR

2010-07-01

... professional techniques of planning, layout and interior design to determine the best internal location and the..., due to its layout, design, location, or other characteristics, is unlikely to be needed by another GSA... space means surface land, structures, or areas within structures designed and designated for the purpose...

Structural Damage Prediction and Analysis for Hypervelocity Impact: Consulting

NASA Technical Reports Server (NTRS)

1995-01-01

A portion of the contract NAS8-38856, 'Structural Damage Prediction and Analysis for Hypervelocity Impacts,' from NASA Marshall Space Flight Center (MSFC), included consulting which was to be documented in the final report. This attachment to the final report contains memos produced as part of that consulting.

DNA condensation and size effects of DNA condensation agent

NASA Astrophysics Data System (ADS)

Liu, Yan-Hui; Jiang, Chong-Ming; Guo, Xin-Miao; Tang, Yan-Lin; Hu, Lin

2013-08-01

Based on the model of the strong correlation of counterions condensed on DNA molecule, by tailoring interaction potential, interduplex spacing and correlation spacing between condensed counterions on DNA molecule and interduplex spacing fluctuation strength, toroidal configuration, rod-like configuration and two-hole configurations are possible. The size effects of counterion structure on the toroidal structure can be detected by this model. The autocorrelation function of the tangent vectors is found as an effective way to detect the structure of toroidal conformations and the generic pathway of the process of DNA condensation. The generic pathway of all of the configurations involves an initial nucleation loop, and the next part of the DNA chain is folded on the top of the initial nucleation loop with different manners, in agreement with the recent experimental results.

Langley's CSI evolutionary model: Phase 2

NASA Technical Reports Server (NTRS)

Horta, Lucas G.; Reaves, Mercedes C.; Elliott, Kenny B.; Belvin, W. Keith; Teter, John E.

1995-01-01

Phase 2 testbed is part of a sequence of laboratory models, developed at NASA Langley Research Center, to enhance our understanding on how to model, control, and design structures for space applications. A key problem with structures that must perform in space is the appearance of unwanted vibrations during operations. Instruments, design independently by different scientists, must share the same vehicle causing them to interact with each other. Once in space, these problems are difficult to correct and therefore, prediction via analysis design, and experiments is very important. Phase 2 laboratory model and its predecessors are designed to fill a gap between theory and practice and to aid in understanding important aspects in modeling, sensor and actuator technology, ground testing techniques, and control design issues. This document provides detailed information on the truss structure and its main components, control computer architecture, and structural models generated along with corresponding experimental results.

Self-consistent adjoint analysis for topology optimization of electromagnetic waves

NASA Astrophysics Data System (ADS)

Deng, Yongbo; Korvink, Jan G.

2018-05-01

In topology optimization of electromagnetic waves, the Gâteaux differentiability of the conjugate operator to the complex field variable results in the complexity of the adjoint sensitivity, which evolves the original real-valued design variable to be complex during the iterative solution procedure. Therefore, the self-inconsistency of the adjoint sensitivity is presented. To enforce the self-consistency, the real part operator has been used to extract the real part of the sensitivity to keep the real-value property of the design variable. However, this enforced self-consistency can cause the problem that the derived structural topology has unreasonable dependence on the phase of the incident wave. To solve this problem, this article focuses on the self-consistent adjoint analysis of the topology optimization problems for electromagnetic waves. This self-consistent adjoint analysis is implemented by splitting the complex variables of the wave equations into the corresponding real parts and imaginary parts, sequentially substituting the split complex variables into the wave equations with deriving the coupled equations equivalent to the original wave equations, where the infinite free space is truncated by the perfectly matched layers. Then, the topology optimization problems of electromagnetic waves are transformed into the forms defined on real functional spaces instead of complex functional spaces; the adjoint analysis of the topology optimization problems is implemented on real functional spaces with removing the variational of the conjugate operator; the self-consistent adjoint sensitivity is derived, and the phase-dependence problem is avoided for the derived structural topology. Several numerical examples are implemented to demonstrate the robustness of the derived self-consistent adjoint analysis.

Open for business: A New Approach to Commercialisation of the International Space Station

NASA Astrophysics Data System (ADS)

Master Of Space Studies 1998-1999 (MSS4) Class

2000-01-01

The International Space Station (ISS) is the result of collaboration between fifteen countries (IGA, 1998). Originally planned as a scientific facility, a shift in policy of the partners has recently occurred towards commercialisation of the Station. Open for Business: A New Approach to Commercialisation of the International Space Station is written in response to this policy shift. It sets out to identify the major constraints in which the potential commercial user must operate and proposes solutions for both commercial user and the partner space agencies to facilitate this commercialisation process. In a time when space-faring nations face reduced fiscal resources and increasing pressure from their constituencies to justify the huge costs of the ISS, commercialising utilisation seems a logical solution. Clearly, successful commercialisation can help recover some of the development and operating costs of the ISS. The structure of Open for Business is divided into two main parts. Part One is entitled ``Constraint and Solutions.'' It proposes new solutions to existing constraint to ISS commercialisation in areas of policy, law, technology and business. The conclusions of Part One are integrated and unified into A New Approach towards ISS commercialisation. This approach is then applied in Part Two to two case studies: the International Space Satellite Servicing Station (I4S) and protein crystallization. Open for Business then concludes with a recommended approach to the future of ISS commercialisation. .

Priorities in national space strategies and governance of the member states of the European Space Agency

NASA Astrophysics Data System (ADS)

Adriaensen, Maarten; Giannopapa, Christina; Sagath, Daniel; Papastefanou, Anastasia

2015-12-01

The European Space Agency (ESA) has twenty Member States with a variety of strategic priorities and governance structures regarding their space activities. A number of countries engage in space activities exclusively though ESA, while others have also their own national space programme. Some consider ESA as their prime space agency and others have additionally their own national agency with respective programmes. The main objective of this paper is to provide an up-to date overview and a holistic assessment of strategic priorities and the national space governance structures in 20 ESA Member States. This analysis and assessment has been conducted by analysing the Member States public documents, information provided at ESA workshop on this topic and though unstructured interviews. The paper is structured to include two main elements: priorities and trends in national space strategies and space governance in ESA Member States. The first part of this paper focuses on the content and analysis of the national space strategies and indicates the main priorities and trends in Member States. The priorities are categorised with regards to technology domains, the role of space in the areas of sustainability and the motivators that boost engagement in space. These vary from one Member State to another and include with different levels of engagement in technology domains amongst others: science and exploration, navigation, Earth observation, human space flight, launchers, telecommunications, and integrated applications. Member States allocate a different role of space as enabling tool adding to the advancement of sustainability areas including: security, resources, environment and climate change, transport and communication, energy, and knowledge and education. The motivators motivating reasoning which enhances or hinders space engagement also differs. The motivators identified are industrial competitiveness, job creation, technology development and transfer, social benefits, international cooperation, and European non-dependence. The second part of the paper provides a categorisation of national space governance structures in ESA Member States. Different governance models are identified depending on the responsible ministries for space for a number of space related organisations and ESA. In the case of ESA, these can typically vary from the more traditional ministry of science and/or education, the ministry of industry and/or innovation to the more recent ones being the ministry of economy and the ministry of transport. Recognising the transverse nature of space and its potential as a tool for a number of policies like agriculture, environment, maritime, disaster management, etc., other ministries are more and more getting involved in space activities. The development and implementation of the space strategy and policy of a Member State is realised though the engagement of an implementing entity. The type, role and activity vary from Member State to Member State.

PARTS: Probabilistic Alignment for RNA joinT Secondary structure prediction

PubMed Central

Harmanci, Arif Ozgun; Sharma, Gaurav; Mathews, David H.

2008-01-01

A novel method is presented for joint prediction of alignment and common secondary structures of two RNA sequences. The joint consideration of common secondary structures and alignment is accomplished by structural alignment over a search space defined by the newly introduced motif called matched helical regions. The matched helical region formulation generalizes previously employed constraints for structural alignment and thereby better accommodates the structural variability within RNA families. A probabilistic model based on pseudo free energies obtained from precomputed base pairing and alignment probabilities is utilized for scoring structural alignments. Maximum a posteriori (MAP) common secondary structures, sequence alignment and joint posterior probabilities of base pairing are obtained from the model via a dynamic programming algorithm called PARTS. The advantage of the more general structural alignment of PARTS is seen in secondary structure predictions for the RNase P family. For this family, the PARTS MAP predictions of secondary structures and alignment perform significantly better than prior methods that utilize a more restrictive structural alignment model. For the tRNA and 5S rRNA families, the richer structural alignment model of PARTS does not offer a benefit and the method therefore performs comparably with existing alternatives. For all RNA families studied, the posterior probability estimates obtained from PARTS offer an improvement over posterior probability estimates from a single sequence prediction. When considering the base pairings predicted over a threshold value of confidence, the combination of sensitivity and positive predictive value is superior for PARTS than for the single sequence prediction. PARTS source code is available for download under the GNU public license at http://rna.urmc.rochester.edu. PMID:18304945

KSC-08pd2574

NASA Image and Video Library

2008-09-05

CAPE CANAVERAL, Fla. – In the Payload Hazardous Servicing Facility at NASA’s Kennedy Space Center, crew members with the STS-125 mission get a close look at some of the equipment associated with their mission to service NASA’s Hubble Space Telescope. Mission Specialist Michael Good points out part of the Flight Support Structure to Mission Specialist Andrew Feustel, right. The Soft Capture Mechanism is above him. The mechanism will enable the future rendezvous, capture and safe disposal of NASA's Hubble Space Telescope by either a crewed or robotic mission. The ring-like device attaches to Hubble’s aft bulkhead. The STS-125 crew is taking part in a crew equipment interface test, which provides experience handling tools, equipment and hardware they will use on their mission. Space shuttle Atlantis is targeted to launch on the STS-125 mission Oct. 10. Photo credit: NASA/Kim Shiflett

KSC-08pd3440

NASA Image and Video Library

2008-10-29

CAPE CANAVERAL, Fla. – On Launch Pad 39A at NASA's Kennedy Space Center in Florida, STS-126 Mission Specialists (from left) Sandra Magnus, Shane Kimbrough and Heidemarie Stefanyshyn-Piper make their way to the slidewire baskets on the 195-foot level of the fixed service structure after taking part in a simulated countdown in space shuttle Endeavour. The crew is at Kennedy to take part in the Terminal Countdown Demonstration Test, which includes equipment familiarization, emergency exit training and the simulated countdown. On the STS-126 mission, space shuttle Endeavour's crew will deliver equipment and supplies to the International Space Station in preparation for expansion from a three- to six-person resident crew aboard the complex. The mission also will include four spacewalks to service the station’s Solar Alpha Rotary Joints. Endeavour is targeted to launch Nov. 14. Photo credit: NASA/Troy Cryder

Using Pharmacies in a Structural Intervention to Distribute Low Dead Space Syringes to Reduce HIV and HCV Transmission in People Who Inject Drugs

PubMed Central

Johnson, Terence L.; Zule, William A.; Carda-Auten, Jessica; Golin, Carol E.

2015-01-01

Ongoing injection drug use contributes to the HIV and HCV epidemics in people who inject drugs. In many places, pharmacies are the primary source of sterile syringes for people who inject drugs; thus, pharmacies provide a viable public health service that reduces blood-borne disease transmission. Replacing the supply of high dead space syringes with low dead space syringes could have far-reaching benefits that include further prevention of disease transmission in people who inject drugs and reductions in dosing inaccuracies, medication errors, and medication waste in patients who use syringes. We explored using pharmacies in a structural intervention to increase the uptake of low dead space syringes as part of a comprehensive strategy to reverse these epidemics. PMID:25880955

Space Shuttle Corrosion Protection Performance

NASA Technical Reports Server (NTRS)

Curtis, Cris E.

2007-01-01

The reusable Manned Space Shuttle has been flying into Space and returning to earth for more than 25 years. The launch pad environment can be corrosive to metallic substrates and the Space Shuttles are exposed to this environment when preparing for launch. The Orbiter has been in service well past its design life of 10 years or 100 missions. As part of the aging vehicle assessment one question under evaluation is how the thermal protection system and aging protective coatings are performing to insure structural integrity. The assessment of this cost resources and time. The information is invaluable when minimizing risk to the safety of Astronauts and Vehicle. This paper will outline a strategic sampling plan and some operational improvements made by the Orbiter Structures team and Corrosion Control Review Board.

Using Pharmacies in a Structural Intervention to Distribute Low Dead Space Syringes to Reduce HIV and HCV Transmission in People Who Inject Drugs.

PubMed

Oramasionwu, Christine U; Johnson, Terence L; Zule, William A; Carda-Auten, Jessica; Golin, Carol E

2015-06-01

Ongoing injection drug use contributes to the HIV and HCV epidemics in people who inject drugs. In many places, pharmacies are the primary source of sterile syringes for people who inject drugs; thus, pharmacies provide a viable public health service that reduces blood-borne disease transmission. Replacing the supply of high dead space syringes with low dead space syringes could have far-reaching benefits that include further prevention of disease transmission in people who inject drugs and reductions in dosing inaccuracies, medication errors, and medication waste in patients who use syringes. We explored using pharmacies in a structural intervention to increase the uptake of low dead space syringes as part of a comprehensive strategy to reverse these epidemics.

Application of Remote-Sensing Observations for Detecting Patterns of Localization of PGM Mineralization of Western Bushveld

NASA Astrophysics Data System (ADS)

Milovsky, G. A.; Ishmukhametova, V. T.; Orlyankin, V. N.; Shemyakina, E. M.

2017-12-01

The differentiated Bushveld complex is studied by remote-space and gravimagnetic methods. The syncline of Western Bushveld is recognized in the southwestern part of the complex, which is characterized by a radial and ring structure of the higher order. The structures, which control the localization of Pt mineralization, are revealed and the possible use of the Landsat 7 ETM+ multizonal space survey is shown for recognizing the rocks of the Basal, Critical, Main, and Upper zones of the norite complex of Western Bushveld.

STS-110 payload S0 Truss is moved to payload canister in O&C

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- The Integrated Truss Structure S0 arrives at the payload canister in the Operations and Checkout Building for transfer to the launch pad for mission STS-110. Part of the payload on Space Shuttle Atlantis, the S0 truss will be attached to the U.S. Lab, 'Destiny,' on the 11-day mission, becoming the backbone of the orbiting International Space Station (ISS). Launch is scheduled for April 4.

Webb Space Telescope Update on This Week @NASA – January 12, 2018

NASA Image and Video Library

2018-01-12

The James Webb Space Telescope’s cryogenic vacuum testing at our Johnson Space Center verified it’s ready for the cold, harsh environment of space, and its mission to uncover a part of the universe we have not seen. From distant worlds orbiting other stars, to mysterious cosmic structures, Webb could help answer questions about our universe and our place in it. Launch of Webb is set for 2019. Also, Flight through Orion Nebula, 360 Degree View from the Center of the Galaxy, and Raging Water on Launch Pad!

KSC-2014-3264

NASA Image and Video Library

2014-07-23

CAPE CANAVERAL, Fla. – Steel structures surround High Bay 3 inside the Vehicle Assembly Building, or VAB, at NASA’s Kennedy Space Center in Florida. In view, high above, is the 175-ton crane. Banners note the heights of the Saturn V, Space Launch System, or SLS, and shuttle on the steel structure. Modifications are underway in the VAB to prepare High Bay 3 for a new platform system. The modifications are part of a centerwide refurbishment initiative under the Ground Systems Development and Operations Program. High bay 3 is being refurbished to accommodate NASA’s Space Launch System and a variety of other spacecraft. For more information, visit http://www.nasa.gov/exploration/systems/ground/index.html. Photo credit: NASA/Dimitri Gerondidakis

Key issues in theoretical and functional pneumatic design

NASA Astrophysics Data System (ADS)

Xu, Z. G.; Yang, D. Y.; Liu, W. M.; Liu, T. T.

2017-10-01

This paper studies the energy release of the pneumatic engine in different thermodynamic processes, the isothermal process is the highest power output process, while adiabatic process is the lowest energy output process, and the energy release of the pneumatic engine is a multi-state thermodynamic process between them. Therefore heat exchanging should be increased between the pneumatic engine and the outer space, the gas expansion process in the cylinder should be as close as possible to the isothermal process. Heat exchange should be increased between the cylinder and the external spaces. Secondly, the fin structure is studied to increase the heat exchanging between the cylinder body and the outside space. The upper part has fin structures and the lower cylinder has no fin structure, this structure improved the working efficiency of pneumatic engine. Finally the cam and the hydraulic bottle of pneumatic engines are designed. Simulation and theoretical calculation are used to the analysis of the whole structure, which lay the foundation for the manufacturing and design of the pneumatic engines.

Space Construction Automated Fabrication Experiment Definition Study (SCAFEDS), part 2

NASA Technical Reports Server (NTRS)

1978-01-01

The techniques, processes, and equipment required for automatic fabrication and assembly of structural elements in using Shuttle as a launch vehicle, and construction were defined. Additional construction systems operational techniques, processes, and equipment which can be developed and demonstrated in the same program to provide further risk reduction benefits to future large space systems were identified and examined.

Engineering report. Part 3: NASA lightweight wheel and brake sub-system. Lightweight brake development. [for application to space shuttle

NASA Technical Reports Server (NTRS)

Bok, L. D.

1973-01-01

The development of light weight wheel and brake systems designed to meet the space shuttle type requirements was investigated. The study includes the use of carbon graphite composite and beryllium as heat sink materials and the compatibility of these heat sink materials with the other structural components of the wheel and brake.

SLS Engine Section Test Article Loaded on Barge Pegasus at NASA's Michoud Assembly Facility

NASA Image and Video Library

2017-04-27

A NASA move team loaded the engine section structural qualification test article for the Space Launch System into the barge Pegasus docked in the harbor at NASA's Michoud Assembly Facility in New Orleans. The rocket's engine section is the bottom of the core stage and houses the four RS-25 engines. The engine section test article was moved from Building 103, Michoud’s 43-acre rocket factory, to the barge where it was loaded for a river trip to NASA’s Marshall Space Flight Center in Huntsville, Alabama. The bottom part of the test article is structurally the same as the engine section that will be flown as part of the SLS core stage. The shiny metal top part simulates the rocket's liquid hydrogen tank, which is the fuel tank that joins to the engine section. The barge Pegasus will travel 1,240 miles by river to Marshall and endure tests that pull, push, and bend it, subjecting it to millions of pounds of force. This ensures the structure can withstand the incredible stresses produced by the 8.8 million pounds of thrust during launch and ascent.

The Aurora space launcher concept

NASA Astrophysics Data System (ADS)

Kopp, Alexander; Stappert, Sven; Mattsson, David; Olofsson, Kurt; Marklund, Erik; Kurth, Guido; Mooij, Erwin; Roorda, Evelyne

2017-11-01

This paper gives an overview about the Aurora reusable space launcher concept study that was initiated in late-2015/early-2016. Within the Aurora study, several spaceplane-like vehicle configurations with different geometries, propulsion systems and mission profiles will be designed, investigated and evaluated with respect to their technical and economic feasibility. The first part of this paper will discuss the study logic and the current status of the Aurora studies and introduces the first vehicle configurations and their system design status. As the identification of highly efficient structural designs is of particular interest for Aurora, the structural design and analysis approach will be discussed in higher level of detail. A special design feature of the Aurora vehicle configurations is the utilization of the novel thin-ply composite material technology for structural mass reductions. Therefore, the second part of this paper will briefly discuss this technology and investigate the application and potential mass savings on vehicle level within simplified structural analysis studies. The results indicate that significant mass savings could be possible. Finally, an outlook on the next steps is provided.

The Aurora space launcher concept

NASA Astrophysics Data System (ADS)

Kopp, Alexander; Stappert, Sven; Mattsson, David; Olofsson, Kurt; Marklund, Erik; Kurth, Guido; Mooij, Erwin; Roorda, Evelyne

2018-06-01

This paper gives an overview about the Aurora reusable space launcher concept study that was initiated in late-2015/early-2016. Within the Aurora study, several spaceplane-like vehicle configurations with different geometries, propulsion systems and mission profiles will be designed, investigated and evaluated with respect to their technical and economic feasibility. The first part of this paper will discuss the study logic and the current status of the Aurora studies and introduces the first vehicle configurations and their system design status. As the identification of highly efficient structural designs is of particular interest for Aurora, the structural design and analysis approach will be discussed in higher level of detail. A special design feature of the Aurora vehicle configurations is the utilization of the novel thin-ply composite material technology for structural mass reductions. Therefore, the second part of this paper will briefly discuss this technology and investigate the application and potential mass savings on vehicle level within simplified structural analysis studies. The results indicate that significant mass savings could be possible. Finally, an outlook on the next steps is provided.

Thermal insulation of a cryogenic tank for a space telescope using a pretensioned suspension of Fiber Reinforced Composite (FRC)

NASA Astrophysics Data System (ADS)

Bongers, Bernd; Haider, Otmar; Tauber, Wolfgang

1990-09-01

For the thermal insulation of cryogenic tanks in satellite applications Fiber Reinforced Composite (FRC) materials are preferable because of their low thermal conductivity and high tensile strength compared to metallic materials. At the Infrared Space Observatory (ISO) satellite the main Liquid Helium (LHe) tank is suspended by one spatial framework and eight pretensioned chain strands at each side. Frameworks and chain strands are acting as a thermal barrier and therefore made of FRC. To meet the various and, in parts contractive requirements, sophisticated design approaches are chosen for the structural parts.

Experiments in thrusterless robot locomotion control for space applications. Ph.D. Thesis

NASA Technical Reports Server (NTRS)

Jasper, Warren Joseph

1990-01-01

While performing complex assembly tasks or moving about in space, a space robot should minimize the amount of propellant consumed. A study is presented of space robot locomotion and orientation without the use of thrusters. The goal was to design a robot control paradigm that will perform thrusterless locomotion between two points on a structure, and to implement this paradigm on an experimental robot. A two arm free flying robot was constructed which floats on a cushion of air to simulate in 2-D the drag free, zero-g environment of space. The robot can impart momentum to itself by pushing off from an external structure in a coordinated two arm maneuver, and can then reorient itself by activating a momentum wheel. The controller design consists of two parts: a high level strategic controller and a low level dynamic controller. The control paradigm was verified experimentally by commanding the robot to push off from a structure with both arms, rotate 180 degs while translating freely, and then to catch itself on another structure. This method, based on the computed torque, provides a linear feedback law in momentum and its derivatives for a system of rigid bodies.

A Mechanical Harmony to NASA's Webb Telescope Sunshield

NASA Image and Video Library

2017-12-08

NASA's James Webb Space Telescope has a giant custom-built, kite-shaped sunshield driven by mechanics that will fold and unfold with a harmonious synchronicity 1 million miles from Earth. Like a car, many mechanical pieces in the Webb telescope's sunshield will work together to open it from its stored folded position in the rocket that will carry it into space. According to car manufacturers, a single car can have about 30,000 parts, counting every part down to the smallest screws. Like getting all of the parts in a car to operate together, the mechanical parts of the sunshield have to work in the same way. The sunshield support structure contains well over 7,000 flight parts, including springs, bearings, pulleys, magnets, etc. In addition, the sunshield has hundreds of custom fabricated pieces. Most mechanical pieces were developed exclusively for the sunshield, with a few from existing designs. Read more: go.nasa.gov/2cXcQMT

44 CFR 79.6 - Eligibility.

Code of Federal Regulations, 2010 CFR

2010-10-01

... buildings and/or structures to areas outside of the floodplain to convert the property to open space use in... protection of wetlands, part 10 of this chapter, Environmental considerations, § 60.3 of this subchapter...

KSC-2010-5488

NASA Image and Video Library

2010-11-03

CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, xenon lights illuminate space shuttle Discovery on Launch Pad 39A following the retraction of the rotating service structure. The structure provides weather protection and access to the shuttle while it awaits lift off on the pad. Launch of Discovery on the STS-133 mission to the International Space Station is set for 3:29 p.m. on Nov. 4. During the 11-day mission, Discovery and its six crew members will deliver the Permanent Multipurpose Module, packed with supplies and critical spare parts, as well as Robonaut 2, to the orbiting laboratory. Discovery, which will fly its 39th mission, is scheduled to be retired following STS-133. This will be the 133rd Space Shuttle Program mission and the 35th shuttle voyage to the space station. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Troy Cryder

Manual for obscuration code with space station applications

NASA Technical Reports Server (NTRS)

Marhefka, R. J.; Takacs, L.

1986-01-01

The Obscuration Code, referred to as SHADOW, is a user-oriented computer code to determine the case shadow of an antenna in a complex environment onto the far zone sphere. The surrounding structure can be composed of multiple composite cone frustums and multiply sided flat plates. These structural pieces are ideal for modeling space station configurations. The means of describing the geometry input is compatible with the NEC-BASIC Scattering Code. In addition, an interactive mode of operation has been provided for DEC VAX computers. The first part of this document is a user's manual designed to give a description of the method used to obtain the shadow map, to provide an overall view of the operation of the computer code, to instruct a user in how to model structures, and to give examples of inputs and outputs. The second part is a code manual that details how to set up the interactive and non-interactive modes of the code and provides a listing and brief description of each of the subroutines.

LDEF mechanical systems

NASA Technical Reports Server (NTRS)

Spear, W. Steve; Dursch, Harry W.

1992-01-01

Following LDEF retrieval, a number of studies were made of mechanical hardware and structure flown on the LDEF. The primary objectives are to determine the effects of long term space exposure on (1) mechanisms either used on LDEF or as part of individual experiments; (2) LDEF structural components; and (3) fasteners. Results from examination and testing of LDEF structure, fasteners, LDEF end support beam, environment exposure control canisters, experiment tray clamps, LDEF grapple fixtures, and viscous damper are presented. The most significant finding is the absence of space exposure related cold welding. The instances of seizure or removal difficulties initially attributed to cold welding were shown to have resulted from installation galling damage or improper removal techniques. Widespread difficulties encountered with removal of stainless steel fasteners underscore the need for effective thread lubrication schemes to ensure successful application of proposed orbital replacement units onboard Space Station Freedom.

Neutral Buoyancy Simulator-NB32-Large Space Structure Assembly

NASA Technical Reports Server (NTRS)

1980-01-01

Once the United States' space program had progressed from Earth's orbit into outerspace, the prospect of building and maintaining a permanent presence in space was realized. To accomplish this feat, NASA launched a temporary workstation, Skylab, to discover the effects of low gravity and weightlessness on the human body, and also to develop tools and equipment that would be needed in the future to build and maintain a more permanent space station. The structures, techniques, and work schedules had to be carefully designed to fit this unique construction site. The components had to be lightweight for transport into orbit, yet durable. The station also had to be made with removable parts for easy servicing and repairs by astronauts. All of the tools necessary for service and repairs had to be designed for easy manipulation by a suited astronaut. Construction methods had to be efficient due to the limited time the astronauts could remain outside their controlled environment. In lieu of all the specific needs for this project, an environment on Earth had to be developed that could simulate a low gravity atmosphere. A Neutral Buoyancy Simulator (NBS) was constructed by NASA Marshall Space Flight Center (MSFC) in 1968. Since then, NASA scientists have used this facility to understand how humans work best in low gravity and also provide information about the different kinds of structures that can be built. As part of this experimentation, the Experimental Assembly of Structures in Extravehicular Activity (EASE) project was developed as a joint effort between MFSC and the Massachusetts Institute of Technology (MIT). The EASE experiment required that crew members assemble small components to form larger components, working from the payload bay of the space shuttle. Pictured is an entire unit that has been constructed and is sitting in the bottom of a mock-up shuttle cargo bay pallet.

SIC material and technology for space optics

NASA Astrophysics Data System (ADS)

Bougoin, Michel

2017-11-01

Taking benefit from its very high specific stiffness and its exclusive thermal stability, the SiCSPACE material is now used for the fabrication of scientific and commercial lightweight space telescopes. This paper gives a review of the characteristics of this sintered silicon carbide. The BOOSTEC facilities and the technology described here allow to manufacture large structural components or mirrors (up to several meters) at cost effective condition, from a single part to mass production. Several examples of SiC space optical components are presented.

Space Construction Experiment Definition Study (SCEDS), part 1. Volume 2: Study results

NASA Technical Reports Server (NTRS)

1981-01-01

A basic Space Shuttle flight experiment which will provide needed data on the construction of large space systems from the Orbiter was defined. The predicted dynamic behavior of a representative large structure, on-orbit construction operations, and Orbiter control during and after construction were studied. Evolutionary or supplemental flight experiments for the development or augmentation of a basic flight experiment were identified and defined. The study was divided into six major tasks with appropriate sub-tasks noted.

A soft actuation system for segmented reflector articulation and isolation

NASA Technical Reports Server (NTRS)

Agronin, Michael L.; Jandura, Louise

1990-01-01

Segmented reflectors have been proposed for space based applications such as optical communication and large diameter telescopes. An actuation system for mirrors in a space based segmented mirror array was developed as part of NASA's Precision Segmented Reflector program. The actuation system, called the Articulated Panel Module (APM), provides 3 degrees of freedom mirror articulation, gives isolation from structural motion, and simplifies space assembly of the mirrors to the reflector backup truss. A breadboard of the APM was built and is described.

Jets on Comet Borrelly

NASA Image and Video Library

2001-11-03

This very long exposure was taken by NASA Deep Space 1 to show detailed structures in the faint parts of comet Borrelly inner coma. As a result, the nucleus has been greatly over-exposed and its shape appears distorted.

Space Shuttle Crawler Transporter Vibration Analysis in Support of Rollout Fatigue Load Spectra Verification Program

NASA Technical Reports Server (NTRS)

Margasahayam, Ravi N.; Meyer, Karl A.; Nerolich, Shaun M.; Burton, Roy C.; Gosselin, Armand M.

2004-01-01

The Crawler Transporter (CT), designed and built for the Apollo Program in the 1960's and surpassing its initial operational life, has become an integral part of the Space Shuttle Program (SSP). The CT transports the Space Shuttle Vehicle (SSV) stack, atop the Mobile Launch Platform (MLP), from the Vehicle Assembly Building (VAB) to the launch pad. This support structure provides hydraulic jacking, leveling and load equalization for the 12 million pound stack on its 3.5-5.0 mile rollout to the launch pad. Major elements of the SSV, consisting of the orbiter, solid rocket boosters (SRB) and external tank (ET) have required fatigue analyses as part of the mission life certification. Compared to rollout vibration, the SSV sees relatively high vibration loads during launch, ascent, descent and landing phases of the mission. Although preliminary measured SRB vibration levels during rollout were of low amplitude and frequency, the duration of the rollout phase is typically high, from 5-6 hours. As part of an expanded mission life assessment, additional certification effort was initiated to define fatigue load spectra for rollout. This study addresses the CT vibration analyses in support of the rollout fatigue study. Structural models developed for modal and vibration analyses were used to identify unique CT, CT/MLP and CT/MLP/SRB vibration characteristics for comparison to instrumented rollout tests. Whereas the main structural and vibration characteristics of the SSV are well defined, minimum analytical and vibration test data on the Crawler Transporter were available. Unique vibration characteristics of the CT are attributable to the drive mechanism, hydraulic jacking system, structural framing and the CT-to-MLP support pad restraints. Initial tests performed on the CT/MLP/SRB configuration showed reasonable correlation with predicted mode shapes and frequencies.

Sensorimotor coordination and the structure of space.

PubMed

McCollum, Gin

2003-01-01

Embedded in neural and behavioral organization is a structure of sensorimotor space. Both this embedded spatial structure and the structure of physical space inform sensorimotor control. This paper reviews studies in which the gravitational vertical and horizontal are crucial. The mathematical expressions of spatial geometry in these studies indicate methods for investigating sensorimotor control in freefall. In freefall, the spatial structure introduced by gravitation - the distinction between vertical and horizontal - does not exist. However, an astronaut arriving in space carries the physiologically-embedded distinction between horizontal and vertical learned on earth. The physiological organization based on this distinction collapses when the strong otolith activity and other gravitational cues for sensorimotor behavior become unavailable. The mathematical methods in this review are applicable in understanding the changes in physiological organization as an astronaut adapts to sensorimotor control in freefall. Many mathematical languages are available for characterizing the logical structures in physiological organization. Here, group theory is used to characterize basic structure of physical and physiological spaces. Dynamics and topology allow the grouping of trajectory ranges according to the outcomes or attractors. The mathematics of ordered structures express complex orderings, such as in multiphase movements in which different parts of the body are moving in different phase sequences. Conditional dynamics, which combines dynamics with the mathematics of ordered structures, accommodates the parsing of movement sequences into trajectories and transitions. Studies reviewed include those of the sit-to-stand movement and early locomotion, because of the salience of gravitation in those behaviors. Sensorimotor transitions and the conditions leading to them are characterized in conditional dynamic control structures that do not require thinking of an organism as an input-output device. Conditions leading to sensorimotor transitions on earth assume the presence of a gravitational vertical which is lacking in space. Thus, conditions used on earth for sensorimotor transitions may become ambiguous in space. A platform study in which sensorimotor transition conditions are ambiguous and are related to motion sickness is reviewed.

KSC-08pd3446

NASA Image and Video Library

2008-10-29

CAPE CANAVERAL, Fla. – On Launch Pad 39A at NASA's Kennedy Space Center in Florida, STS-126 crew members gather near the slidewire baskets on the 195-foot level of the fixed service structure. From left are Mission Specialists Donald Pettit, Sandra Magnus, Heidemarie Stefanyshyn-Piper and Steve Bowen. They have taken part in a simulated countdown in space shuttle Endeavour followed by emergency escape procedures. The crew is at Kennedy to take part in the Terminal Countdown Demonstration Test, which includes equipment familiarization, emergency exit training and the simulated countdown. On the STS-126 mission, space shuttle Endeavour's crew will deliver equipment and supplies to the International Space Station in preparation for expansion from a three- to six-person resident crew aboard the complex. The mission also will include four spacewalks to service the station’s Solar Alpha Rotary Joints. Endeavour is targeted to launch Nov. 14. Photo credit: NASA/Troy Cryder

IAE - Inflatable Antenna Experiment

NASA Image and Video Library

1996-05-20

STS077-150-129 (20 May 1996) --- Following its deployment from the Space Shuttle Endeavour, the Spartan 207/Inflatable Antenna Experiment (IAE) payload is backdropped over the Atlantic Ocean and Hampton Roads, Virginia. (Hold photograph vertically with land mass at top.) Virginia Beach and part of Newport News can be delineated in the upper left quadrant of the frame. The view was photographed with a large format still camera on the first full day of in-space operations by the six-member crew. Managed by Goddard Space Flight Center (GSFC), Spartan is designed to provide short-duration, free-flight opportunities for a variety of scientific studies. The Spartan configuration on this flight is unique in that the IAE is part of an additional separate unit which is ejected once the experiment is completed. The IAE experiment will lay the groundwork for future technology development in inflatable space structures, which will be launched and then inflated like a balloon on-orbit.

Advanced Space Transportation Program (ASTP)

NASA Image and Video Library

2000-09-07

The `once upon a time' science fiction concept of a space elevator has been envisioned and studied as a real mass transportation system in the latter part of the 21st century. David Smitherman of NASA's Marshall Space Flight Center's Advanced Projects Office has compiled plans for such an elevator. The space elevator concept is a structure extending from the surface of the Earth to geostationary Earth orbit (GEO) at 35,786 km in altitude. The tower would be approximately 50 km tall with a cable tethered to the top. Its center mass would be at GEO such that the entire structure orbits the Earth in sync with the Earth's rotation maintaining a stationary position over its base attachment at the equator. Electromagnetic vehicles traveling along the cable could serve as a mass transportation system for transporting people, payloads, and power between space and Earth. This illustration by artist Pat Rawling shows the concept of a space elevator as viewed from the geostationary transfer station looking down the length of the elevator towards the Earth.

Space transfer concepts and analysis for exploration missions

NASA Technical Reports Server (NTRS)

Woodcock, Gordon R.

1992-01-01

The current technical effort is part of the third phase of a broad-scoped and systematic study of space transfer concepts for human lunar and Mars missions. The study addressed the technical issues relating to the First Lunar Outpost (FLO) habitation vehicle with emphasis on the structure, power, life support system, and radiation environment for a baseline habitat with specific alternatives for the baseline.

Identifying Network Structure, Influencers and Social Mood in Digital Spheres: A Sentiment and Content Analysis of Down Syndrome Awareness

ERIC Educational Resources Information Center

Sani-Bozkurt, Sunagul

2018-01-01

Down syndrome is a sensitive subject and one that requires efforts being made to improve conditions for individuals with Down syndrome across multiple dimensions. Social awareness is one of the important dimensions for the inclusion of individuals with Down syndrome. Online spaces, as well as offline spaces, are an important part of our daily…

A neuroanatomical model of space-based and object-centered processing in spatial neglect.

PubMed

Pedrazzini, Elena; Schnider, Armin; Ptak, Radek

2017-11-01

Visual attention can be deployed in space-based or object-centered reference frames. Right-hemisphere damage may lead to distinct deficits of space- or object-based processing, and such dissociations are thought to underlie the heterogeneous nature of spatial neglect. Previous studies have suggested that object-centered processing deficits (such as in copying, reading or line bisection) result from damage to retro-rolandic regions while impaired spatial exploration reflects damage to more anterior regions. However, this evidence is based on small samples and heterogeneous tasks. Here, we tested a theoretical model of neglect that takes in account the space- and object-based processing and relates them to neuroanatomical predictors. One hundred and one right-hemisphere-damaged patients were examined with classic neuropsychological tests and structural brain imaging. Relations between neglect measures and damage to the temporal-parietal junction, intraparietal cortex, insula and middle frontal gyrus were examined with two structural equation models by assuming that object-centered processing (involved in line bisection and single-word reading) and space-based processing (involved in cancelation tasks) either represented a unique latent variable or two distinct variables. Of these two models the latter had better explanatory power. Damage to the intraparietal sulcus was a significant predictor of object-centered, but not space-based processing, while damage to the temporal-parietal junction predicted space-based, but not object-centered processing. Space-based processing and object-centered processing were strongly intercorrelated, indicating that they rely on similar, albeit partly dissociated processes. These findings indicate that object-centered and space-based deficits in neglect are partly independent and result from superior parietal and inferior parietal damage, respectively.

An approach to determination of shunt circuits parameters for damping vibrations

NASA Astrophysics Data System (ADS)

Matveenko; Iurlova; Oshmarin; Sevodina; Iurlov

2018-04-01

This paper considers the problem of natural vibrations of a deformable structure containing elements made of piezomaterials. The piezoelectric elements are connected through electrodes to an external electric circuit, which consists of resistive, inductive and capacitive elements. Based on the solution of this problem, the parameters of external electric circuits are searched for to allow optimal passive control of the structural vibrations. The solution to the problem is complex natural vibration frequencies, the real part of which corresponds to the circular eigenfrequency of vibrations and the imaginary part corresponds to its damping rate (damping ratio). The analysis of behaviour of the imaginary parts of complex eigenfrequencies in the space of external circuit parameters allows one to damp given modes of structure vibrations. The effectiveness of the proposed approach is demonstrated using a cantilever-clamped plate and a shell structure in the form of a semi-cylinder connected to series resonant ? circuits.

The Implications of 3D Thermal Structure on 1D Atmospheric Retrieval

NASA Astrophysics Data System (ADS)

Blecic, Jasmina; Dobbs-Dixon, Ian; Greene, Thomas

2017-10-01

Using the atmospheric structure from a 3D global radiation-hydrodynamic simulation of HD 189733b and the open-source Bayesian Atmospheric Radiative Transfer (BART) code, we investigate the difference between the secondary-eclipse temperature structure produced with a 3D simulation and the best-fit 1D retrieved model. Synthetic data are generated by integrating the 3D models over the Spitzer, the Hubble Space Telescope (HST), and the James Web Space Telescope (JWST) bandpasses, covering the wavelength range between 1 and 11 μm where most spectroscopically active species have pronounced features. Using the data from different observing instruments, we present detailed comparisons between the temperature-pressure profiles recovered by BART and those from the 3D simulations. We calculate several averages of the 3D thermal structure and explore which particular thermal profile matches the retrieved temperature structure. We implement two temperature parameterizations that are commonly used in retrieval to investigate different thermal profile shapes. To assess which part of the thermal structure is best constrained by the data, we generate contribution functions for our theoretical model and each of our retrieved models. Our conclusions are strongly affected by the spectral resolution of the instruments included, their wavelength coverage, and the number of data points combined. We also see some limitations in each of the temperature parametrizations, as they are not able to fully match the complex curvatures that are usually produced in hydrodynamic simulations. The results show that our 1D retrieval is recovering a temperature and pressure profile that most closely matches the arithmetic average of the 3D thermal structure. When we use a higher resolution, more data points, and a parametrized temperature profile that allows more flexibility in the middle part of the atmosphere, we find a better match between the retrieved temperature and pressure profile and the arithmetic average. The Spitzer and HST simulated observations sample deep parts of the planetary atmosphere and provide fewer constraints on the temperature and pressure profile, while the JWST observations sample the middle part of the atmosphere, providing a good match with the middle and most complex part of the arithmetic average of the 3D temperature structure.

Data-Driven Hierarchical Structure Kernel for Multiscale Part-Based Object Recognition

PubMed Central

Wang, Botao; Xiong, Hongkai; Jiang, Xiaoqian; Zheng, Yuan F.

2017-01-01

Detecting generic object categories in images and videos are a fundamental issue in computer vision. However, it faces the challenges from inter and intraclass diversity, as well as distortions caused by viewpoints, poses, deformations, and so on. To solve object variations, this paper constructs a structure kernel and proposes a multiscale part-based model incorporating the discriminative power of kernels. The structure kernel would measure the resemblance of part-based objects in three aspects: 1) the global similarity term to measure the resemblance of the global visual appearance of relevant objects; 2) the part similarity term to measure the resemblance of the visual appearance of distinctive parts; and 3) the spatial similarity term to measure the resemblance of the spatial layout of parts. In essence, the deformation of parts in the structure kernel is penalized in a multiscale space with respect to horizontal displacement, vertical displacement, and scale difference. Part similarities are combined with different weights, which are optimized efficiently to maximize the intraclass similarities and minimize the interclass similarities by the normalized stochastic gradient ascent algorithm. In addition, the parameters of the structure kernel are learned during the training process with regard to the distribution of the data in a more discriminative way. With flexible part sizes on scale and displacement, it can be more robust to the intraclass variations, poses, and viewpoints. Theoretical analysis and experimental evaluations demonstrate that the proposed multiscale part-based representation model with structure kernel exhibits accurate and robust performance, and outperforms state-of-the-art object classification approaches. PMID:24808345

Construction in space - Toward a fresh definition of the man/machine relation

NASA Technical Reports Server (NTRS)

Watters, H. H.; Stokes, J. W.

1979-01-01

The EVA (extravehicular activity) project forming part of the space construction process is reviewed. The manual EVA constuction, demonstrated by the crew of Skylab 3 by assembling a modest space structure in the form of the twin-pole sunshade, is considered, indicating that the experiment dispelled many doubts about man's ability to execute routine and contingency EVA operations. Tests demonstrating the feasibility of remote teleoperator rendezvous, station keeping, and docking operations, using hand controllers for direct input and television for feedback, are noted. Future plans for designing space construction machines are mentioned.

Animals in biomedical space research

NASA Technical Reports Server (NTRS)

Phillips, R. W.

1986-01-01

Rat and squirrel monkeys experiments have been planned in concert with human experiments to help answer fundamental questions concerning the effect of weightlessness on mammalism function. For the most part, these experiments focus on identified changes noted in humans during space flight. Utilizing space laboratory facilities, manipulative experiments can be completed while animals are still in orbit. Other experiments are designed to study changes in gravity receptor structure and function and the effect of weightlessness on early vertibrate development. Following these preliminary animal experiments on Spacelab Shuttle flights, longer term programs of animal investigation will be conducted on Space Station.

The STS-92 crew checks out equipment they will use on their mission to the International Space Stati

NASA Technical Reports Server (NTRS)

1999-01-01

In the Space Station Processing Facility, STS-92 Mission Specialist Jeff Wisoff practices removing a wire harness from the Pressurized Mating Adapter-3, part of the payload on the STS-92 mission to the International Space Station (ISS). STS-92 is targeted for launch in December 1999. Other crew members visiting KSC are Commander Brian Duffy and Mission Specialists Koichi Wakata, Leroy Chiao, Michael Lopez-Alegria and Bill McArthur. STS-92 is the fourth U.S. flight for construction of the International Space Station. The payload also includes an integrated truss structure.

Concept Definition Study for In-Space Structural Characterization of a Lightweight Solar Array

NASA Technical Reports Server (NTRS)

Woods-Vedeler, Jessica A.; Pappa, Richard S.; Jones, Thomas W.; Spellman, Regina; Scott, Willis; Mockensturm, Eric M.; Liddle, Donn; Oshel, Ed; Snyder, Michael

2002-01-01

A Concept Definition Study (CDS) was conducted to develop a proposed "Lightweight High-Voltage Stretched-Lens Concentrator Solar Array Experiment" under NASA's New Millennium Program Space Technology-6 (NMP ST-6) activity. As part of a multi-organizational team, NASA Langley Research Center's role in this proposed experiment was to lead Structural Characterization of the solar array during the flight experiment. In support of this role, NASA LaRC participated in the CDS to de.ne an experiment for static, dynamic, and deployment characterization of the array. In this study, NASA LaRC traded state-of-the-art measurement approaches appropriate for an in-space, STS-based flight experiment, provided initial analysis and testing of the lightweight solar array and lens elements, performed a lighting and photogrammetric simulation in conjunction with JSC, and produced an experiment concept definition to meet structural characterization requirements.

Reusable module for the storage, transportation, and supply of multiple propellants in a space environment

NASA Technical Reports Server (NTRS)

Mazanek, Daniel D. (Inventor); Mankins, John C. (Inventor)

2004-01-01

A space module has an outer structure designed for traveling in space, a docking mechanism for facilitating a docking operation therewith in space, a first storage system storing a first propellant that burns as a result of a chemical reaction therein, a second storage system storing a second propellant that burns as a result of electrical energy being added thereto, and a bi-directional transfer interface coupled to each of the first and second storage systems to transfer the first and second propellants into and out thereof. The space module can be part of a propellant supply architecture that includes at least two of the space modules placed in an orbit in space.

KSC-00padig089

NASA Image and Video Library

2000-11-08

STS-97 Mission Specialist Joe Tanner settles into his seat in Space Shuttle Endeavour on Launch Pad 39B. He and the rest of the crew are taking part in a simulated launch countdown, part of Terminal Countdown Demonstration Test activities that also include emergency egress training and familiarization with the payload. Mission STS-97 is the sixth construction flight to the International Space Station. Its payload includes the P6 Integrated Truss Structure and a photovoltaic (PV) module, with giant solar arrays that will provide power to the Station. The mission includes two spacewalks to complete the solar array connections. STS-97 is scheduled to launch Nov. 30 at 10:05 p.m. EST

Meteorite as raw material for Direct Metal Printing: A proof of concept study

NASA Astrophysics Data System (ADS)

Lietaert, Karel; Thijs, Lore; Neirinck, Bram; Lapauw, Thomas; Morrison, Brian; Lewicki, Chris; Van Vaerenbergh, Jonas

2018-02-01

Asteroid mining as such is not a new concept, as it has been described in science fiction for more than a century and some of its aspects have been studied by academia for more than 30 years. Recently, there is a renewed interest in this subject due the more and more concrete plans for long-duration space missions and the need for resources to support industrial activity in space. The use of locally available resources would greatly improve the economics and sustainability of such missions. Due to its economy in material, use of additive manufacturing (AM) provides an interesting route to valorize these resources for the production of spare parts, tools and large-scale structures optimized for their local microgravity environment. Proof of concept has already been provided for AM of moon regolith. In this paper the concept of In-Situ Resource Utilization is extended towards the production of metallic objects using powdered iron meteorite as raw material. The meteorite-based powder was used to produce a structural part but further research is needed to obtain a high density part without microcracks.

The FLECS expandable module concept for future space missions and an overall description on the material validation

NASA Astrophysics Data System (ADS)

Mileti, Sandro; Guarrera, Giuseppe; Marchetti, Mario; Ferrari, Giorgio; Nebiolo, Marco; Augello, Gerlando; Bitetti, Grazia; Carnà, Emiliano; Marranzini, Andrea; Mazza, Fabio

2006-07-01

The future space exploration missions aim to reduce the costs associated with design, fabrication and launch for ISS, Moon and Mars modules, while simultaneously increasing the useful volume. Flexible and inflatable structures offer many advantages over conventional structures for space applications. Principal among the advantages is the ability to package these structures into small volumes for launch. Design maturation and the development of advanced materials and fabrication processes have made the concept of an inflatable module achievable in the near future. The Multipurpose Expandable Module (FLECS) Project sponsored by ASI (Italian Space Agency) whose prime contractor is Alcatel Alenia Space Italia, links the conventional and traditional technology of modules with the innovative solutions of inflatable technology. This project emphasizes on demonstrating the capability in using inflatable technology on space structures aiming to substitute the conventional modules in future manned missions. FLECS has been designed using advanced textiles and films in order to guarantee the structural reliability necessary for the deployment and packaging configurations. A non-linear structural analysis has been conducted using several numerical codes that simulate the deployed structural characteristics achieving also the damping resistance during the packaging. All the materials used for the flexible parts have been selected through a series of mechanical tests in order to validate the more appropriate ones for the mission. The multi-layer pneumatic retention bladder and the intermediate restraint layer are composed of polymer sheets, ortho-fabrics and elastomers like polyurethanes. The External protection shield is configured using several layers of impact absorption materials and also several layers of space environment (UV, IR, atomic oxygen) protection materials such as Kapton, Mylar and Nextel. The validation of the fabrics, the films and the final prototype assembly are tested in the Space Environment Simulator (SAS), located in the SASLab laboratory of the Aerospace Engineering Department of the “La Sapienza” University of Rome.

Analysis and sizing of Mars aerobrake structure

NASA Technical Reports Server (NTRS)

Raju, I. S.; Craft, W. J.

1993-01-01

A cone-sphere aeroshell structure for aerobraking into Martian atmosphere is studied. Using this structural configuration, a space frame load-bearing structure is proposed. To generate this structure efficiently and to perform a variety of studies of several configurations, a mesh generator that utilizes only a few configurational parameters is developed. A finite element analysis program that analyzes space frame structures was developed. A sizing algorithm that arrives at a minimum mass configuration was developed and integrated into the finite element analysis program. A typical 135-ft-diam aerobrake configuration was analyzed and sized. The minimum mass obtained in this study using high modulus graphite/epoxy composite material members is compared with the masses obtained from two other aerobrake structures using lightweight erectable tetrahedral truss and part-spherical truss configurations. Excellent agreement for the minimum mass was obtained with the three different aerobrake structures. Also, the minimum mass using the present structure was obtained when the supports were not at the base but at about 75 percent of the base diameter.

Size effects on rhodium nanoparticles related to hydrogen-storage capability.

PubMed

Song, Chulho; Yang, Anli; Sakata, Osami; Kumara, L S R; Hiroi, Satoshi; Cui, Yi-Tao; Kusada, Kohei; Kobayashi, Hirokazu; Kitagawa, Hiroshi

2018-06-06

To unveil the origin of the hydrogen-storage properties of rhodium nanoparticles (Rh NPs), we investigated the electronic and crystal structures of the Rh NPs using various synchrotron based X-ray techniques. Electronic structure studies revealed that the hydrogen-storage capability of Rh NPs could be attributed to their more unoccupied d-DOSs than that of the bulk near the Fermi level. Crystal structure studies indicated that lattice distortion and mean-square displacement increase while coordination number decreases with decreasing particle size and the hydrogen-absorption capability of Rh NPs improves to a greater extent with increased structural disorder in the local structure than with that in the mean structure. The smallest Rh NPs, having the largest structural disorder/increased vacancy spaces and the smallest coordination number, exhibited excellent hydrogen-storage capacity. Finally, from the bond-orientational order analysis, we confirmed that the localized disordering is distributed more over the surface part than the core part and hydrogen can be trapped on the surface part of Rh NPs which increases with a decrease in NP diameter.

Junior Primary Greek School Pupils' Perceptions of the City's Public Open Spaces and Especially of the Urban Square: A Case Study

ERIC Educational Resources Information Center

Papageorgiou, Nikoletta; Galani, Apostolia; Mavrikaki, Evangelia

2016-01-01

This work--part of a wider project aimed at engaging first year primary school pupils in public open-space design--explores the perceptions of junior primary school children as to the urban square. Data collection tools comprised semi-structured interviews, sketches and storytelling via puppet-animation. Our findings have shown that--according to…

Neutral Buoyancy Simulator: MSFC-Langley joint test of large space structures component assembly:

NASA Technical Reports Server (NTRS)

1979-01-01

Once the United States' space program had progressed from Earth's orbit into outerspace, the prospect of building and maintaining a permanent presence in space was realized. To accomplish this feat, NASA launched a temporary workstation, Skylab, to discover the effects of low gravity and weightlessness on the human body, and also to develop tools and equipment that would be needed in the future to build and maintain a more permanent space station. The structures, techniques, and work schedules had to be carefully designed to fit this unique construction site. The components had to be lightweight for transport into orbit, yet durable. The station also had to be made with removable parts for easy servicing and repairs by astronauts. All of the tools necessary for service and repairs had to be designed for easy manipulation by a suited astronaut. And construction methods had to be efficient due to limited time the astronauts could remain outside their controlled environment. In lieu of all the specific needs for this project, an environment on Earth had to be developed that could simulate a low gravity atmosphere. A Neutral Buoyancy Simulator (NBS) was constructed by NASA Marshall Space Flight Center (MSFC) in 1968. Since then, NASA scientists have used this facility to understand how humans work best in low gravity and also provide information about the different kinds of structures that can be built. With the help of the NBS, building a space station became more of a reality. In a joint venture between NASA/Langley Research Center in Hampton, VA and MSFC, the Assembly Concept for Construction of Erectable Space Structures (ACCESS) was developed and demonstrated at MSFC's NBS. The primary objective of this experiment was to test the ACCESS structural assembly concept for suitability as the framework for larger space structures and to identify ways to improve the productivity of space construction. Pictured is a demonstration of ACCESS.

Neutral Buoyancy Test - Large Space Structure

NASA Technical Reports Server (NTRS)

1979-01-01

Once the United States' space program had progressed from Earth's orbit into outerspace, the prospect of building and maintaining a permanent presence in space was realized. To accomplish this feat, NASA launched a temporary workstation, Skylab, to discover the effects of low gravity and weightlessness on the human body, and also to develop tools and equipment that would be needed in the future to build and maintain a more permanent space station. The structures, techniques, and work schedules had to be carefully designed to fit this unique construction site. The components had to be lightweight for transport into orbit, yet durable. The station also had to be made with removable parts for easy servicing and repairs by astronauts. All of the tools necessary for service and repairs had to be designed for easy manipulation by a suited astronaut. Construction methods had to be efficient due to the limited time the astronauts could remain outside their controlled environment. In lieu of all the specific needs for this project, an environment on Earth had to be developed that could simulate a low gravity atmosphere. A Neutral Buoyancy Simulator (NBS) was constructed by NASA Marshall Space Flight Center (MSFC) in 1968. Since then, NASA scientists have used this facility to understand how humans work best in low gravity and also provide information about the different kinds of structures that can be built. With the help of the NBS, building a space station became more of a reality. In a joint venture between NASA/Langley Research Center in Hampton, Virginia and the MSFC, the Assembly Concept for Construction of Erectable Space Structures (ACCESS) was developed and demonstrated at MSFC's NBS. The primary objective of this experiment was to test the ACCESS structural assembly concept for suitability as the framework for larger space structures and to identify ways to improve the productivity of space construction. Pictured is a demonstration of ACCESS.

Neutral Buoyancy Test - NB-18 - Large Space Structure Assembly

NASA Technical Reports Server (NTRS)

1979-01-01

Once the United States' space program had progressed from Earth's orbit into outerspace, the prospect of building and maintaining a permanent presence in space was realized. To accomplish this feat, NASA launched a temporary workstation, Skylab, to discover the effects of low gravity and weightlessness on the human body, and also to develop tools and equipment that would be needed in the future to build and maintain a more permanent space station. The structures, techniques, and work schedules had to be carefully designed to fit this unique construction site. The components had to be lightweight for transport into orbit, yet durable. The station also had to be made with removable parts for easy servicing and repairs by astronauts. All of the tools necessary for service and repairs had to be designed for easy manipulation by a suited astronaut. Construction methods had to be efficient due to the limited time the astronauts could remain outside their controlled environment. In lieu of all the specific needs for this project, an environment on Earth had to be developed that could simulate a low gravity atmosphere. A Neutral Buoyancy Simulator (NBS) was constructed by NASA Marshall Space Flight Center (MSFC) in 1968. Since then, NASA scientists have used this facility to understand how humans work best in low gravity and also provide information about the different kinds of structures that can be built. With the help of the NBS, building a space station became more of a reality. In a joint venture between NASA/Langley Research Center in Hampton, Virginia and the MSFC, the Assembly Concept for Construction of Erectable Space Structures (ACCESS) was developed and demonstrated at MSFC's NBS. The primary objective of this experiment was to test the ACCESS structural assembly concept for suitability as the framework for larger space structures and to identify ways to improve the productivity of space construction. Pictured is a demonstration of ACCESS.

Shuttle Program Loads Integration: Going From Concept to Operations and Staying Successful

NASA Technical Reports Server (NTRS)

Bernstein, Karen; James, George; Mackey, alden; Murphy, Neil C.; Brolliar, Steve

2011-01-01

From the beginning of the Shuttle Program to its end, integrated loads and dynamics analyses and tests have been critical in shaping the vehicle design and operational decisions for NASA and its customers. Starting with scaled models and simple mathematical simulations of the structural dynamics, engineers defined the required structural stiffness and predicted the limit loads for each element of the system. Early structural tests provided reasonable confidence that the models and predictions were good. The first launch of the Space Shuttle brought surprises, though, when the ignition overpressure event caused a forward fuel tank support strut to buckle, among several unexpected effects. The launch pad and other ground equipment became an integral part of the system integration, especially where the acoustic and pressure environments of ignition and lift-off were concerned. Following the Challenger accident, operating limits were changed in response to new understandings of how the integrated system performed. Controlling loads while maximizing performance was a key tenet of the Performance Enhancement design process, which enabled construction of the International Space Station. During the return to flight after the Columbia accident, engineers grew to understand that loads during the roll maneuver were also important to the vehicle s structural margin and life. At this point the crawler transport from the Vehicle Assembly Building to the launch pad also became a part of the integrated loads analysis. Even in the last years of the Space Shuttle Program, new data still provided interesting insights into this complicated and fascinating spaceship. This paper will present some examples of the important findings by the team of specialists that supported the Integrated Loads and Dynamics Panel for the Space Shuttle Program.

Integrated support structure

NASA Technical Reports Server (NTRS)

Bruneau, Stephen D.; Campbell, John T.; Struven, Christopher A.

1990-01-01

This Major Qualifying Project is part of the Advanced Space Design Program at WPI. The goal is to design a support structure for a NASA GetAway Special experimental canister. The payload integration, weight, volume, and structural integrity of the canister as specified by NASA guidelines were studied. The end result is a complete set of design drawings with interface drawings and data to specify the design and leave a base on which the next group can concentrate.

Structural dynamics payload loads estimates

NASA Technical Reports Server (NTRS)

Engels, R. C.

1982-01-01

Methods for the prediction of loads on large space structures are discussed. Existing approaches to the problem of loads calculation are surveyed. A full scale version of an alternate numerical integration technique to solve the response part of a load cycle is presented, and a set of short cut versions of the algorithm developed. The implementation of these techniques using the software package developed is discussed.

STS-110 payload S0 Truss is moved to payload canister in O&C

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- Workers in the Operations and Checkout Building watch as the Integrated Truss Structure S0 is lowered into the payload canister. The S0 truss will soon be on its way to the launch pad for mission STS-110. Part of the payload on Space Shuttle Atlantis, the S0 truss will be attached to the U.S. Lab, 'Destiny,' on the 11-day mission, becoming the backbone of the orbiting International Space Station (ISS). Launch is scheduled for April 4.

KSC-02pd0303

NASA Image and Video Library

2002-03-18

KENNEDY SPACE CENTER, FLA. -- STS-110 Mission Specialist Jerry Ross waits his turn at driving the M-113 armored personnel carrier, part of Terminal Countdown Demonstration Test activities. In the background, right, is Mission Specialist Lee Morin. TCDT includes emergency egress training and a simulated launch countdown, and is held at KSC prior to each Space Shuttle flight. Scheduled for launch April 4, the 11-day mission will feature Shuttle Atlantis docking with the International Space Station (ISS) and delivering the S0 truss, the centerpiece-segment of the primary truss structure that will eventually extend over 300 feet

STS-110 M.S. Smith suits up for TCDT

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- STS-110 Mission Specialist Steven Smith relaxes during suit fit, which is part of Terminal Countdown Demonstration Test activities. The TCDT is held at KSC prior to each Space Shuttle flight to provide flight crews an opportunity to participate in simulated launch countdown activities. Scheduled for launch April 4, the 11-day mission will feature Shuttle Atlantis docking with the International Space Station (ISS) and delivering the S0 truss, the centerpiece-segment of the primary truss structure that will eventually extend over 300 feet.

STS-110 M.S. Smith driving M-113 personnel carrier during TCDT

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- STS-110 Mission Specialist Steven Smith waits his turn at driving the M-113 armored personnel carrier, part of Terminal Countdown Demonstration Test activities. TCDT includes emergency egress training and a simulated launch countdown, and is held at KSC prior to each Space Shuttle flight. Scheduled for launch April 4, the 11-day mission will feature Shuttle Atlantis docking with the International Space Station (ISS) and delivering the S0 truss, the centerpiece-segment of the primary truss structure that will eventually extend over 300 feet.

KSC-99pp0224

NASA Image and Video Library

1999-02-09

In the Space Station Processing Facility, STS-92 Mission Specialist Jeff Wisoff practices removing a wire harness from the Pressurized Mating Adapter-3, part of the payload on the STS-92 mission to the International Space Station (ISS). STS-92 is targeted for launch in December 1999. Other crew members visiting KSC are Commander Brian Duffy and Mission Specialists Koichi Wakata, Leroy Chiao, Michael Lopez-Alegria and Bill McArthur. STS-92 is the fourth U.S. flight for construction of the International Space Station. The payload also includes an integrated truss structure

Around Marshall

NASA Image and Video Library

1980-05-06

Once the United States' space program had progressed from Earth's orbit into outerspace, the prospect of building and maintaining a permanent presence in space was realized. To accomplish this feat, NASA launched a temporary workstation, Skylab, to discover the effects of low gravity and weightlessness on the human body, and also to develop tools and equipment that would be needed in the future to build and maintain a more permanent space station. The structures, techniques, and work schedules had to be carefully designed to fit this unique construction site. The components had to be lightweight for transport into orbit, yet durable. The station also had to be made with removable parts for easy servicing and repairs by astronauts. All of the tools necessary for service and repairs had to be designed for easy manipulation by a suited astronaut. Construction methods had to be efficient due to the limited time the astronauts could remain outside their controlled environment. In lieu of all the specific needs for this project, an environment on Earth had to be developed that could simulate a low gravity atmosphere. A Neutral Buoyancy Simulator (NBS) was constructed by NASA Marshall Space Flight Center (MSFC) in 1968. Since then, NASA scientists have used this facility to understand how humans work best in low gravity and also provide information about the different kinds of structures that can be built. As part of this experimentation, the Experimental Assembly of Structures in Extravehicular Activity (EASE) project was developed as a joint effort between MFSC and the Massachusetts Institute of Technology (MIT). The EASE experiment required that crew members assemble small components to form larger components, working from the payload bay of the space shuttle. Pictured is an entire unit that has been constructed and is sitting in the bottom of a mock-up shuttle cargo bay pallet.

Space environmental effects on spacecraft: LEO materials selection guide, part 1

NASA Astrophysics Data System (ADS)

Silverman, Edward M.

1995-08-01

This document provides performance properties on major spacecraft materials and subsystems that have been exposed to the low-Earth orbit (LEO) space environment. Spacecraft materials include metals, polymers, composites, white and black paints, thermal-control blankets, adhesives, and lubricants. Spacecraft subsystems include optical components, solar cells, and electronics. Information has been compiled from LEO short-term spaceflight experiments (e.g., space shuttle) and from retrieved satellites of longer mission durations (e.g., Long Duration Exposure Facility). Major space environment effects include atomic oxygen (AO), ultraviolet radiation, micrometeoroids and debris, contamination, and particle radiation. The main objective of this document is to provide a decision tool to designers for designing spacecraft and structures. This document identifies the space environments that will affect the performance of materials and components, e.g., thermal-optical property changes of paints due to UV exposures, AO-induced surface erosion of composites, dimensional changes due to thermal cycling, vacuum-induced moisture outgassing, and surface optical changes due to AO/UV exposures. Where appropriate, relationships between the space environment and the attendant material/system effects are identified. Part 1 covers spacecraft design considerations for the space environment; advanced composites; polymers; adhesives; metals; ceramics; protective coatings; and lubricants, greases, and seals.

Novelty Detection in and Between Different Modalities

NASA Astrophysics Data System (ADS)

Veflingstad, Henning; Yildirim, Sule

2008-01-01

Our general aim is to reflect the advances in artificial intelligence and cognitive science fields to space exploration studies such that next generation space rovers can benefit from these advances. We believe next generation space rovers can benefit from the studies related to employing conceptual representations in generating structured thought. This way, rovers need not be equipped with all necessary steps of an action plan to execute in space exploration but they can autonomously form representations of their world and reason on them to make intelligent decision. As part of this approach, autonomous novelty detection is an important feature of next generation space rovers. This feature allows a rover to make further decisions about exploring a rock sample more closely or not and on its own. This way, a rover will use less of its time for communication between the earth and itself and more of its time for achieving its assigned tasks in space. In this paper, we propose an artificial neural network based novelty detection mechanism that next generation space rovers can employ as part of their intelligence. We also present an implementation of such a mechanism and present its reliability in detecting novelty.

Space environmental effects on spacecraft: LEO materials selection guide, part 1

NASA Technical Reports Server (NTRS)

Silverman, Edward M.

1995-01-01

This document provides performance properties on major spacecraft materials and subsystems that have been exposed to the low-Earth orbit (LEO) space environment. Spacecraft materials include metals, polymers, composites, white and black paints, thermal-control blankets, adhesives, and lubricants. Spacecraft subsystems include optical components, solar cells, and electronics. Information has been compiled from LEO short-term spaceflight experiments (e.g., space shuttle) and from retrieved satellites of longer mission durations (e.g., Long Duration Exposure Facility). Major space environment effects include atomic oxygen (AO), ultraviolet radiation, micrometeoroids and debris, contamination, and particle radiation. The main objective of this document is to provide a decision tool to designers for designing spacecraft and structures. This document identifies the space environments that will affect the performance of materials and components, e.g., thermal-optical property changes of paints due to UV exposures, AO-induced surface erosion of composites, dimensional changes due to thermal cycling, vacuum-induced moisture outgassing, and surface optical changes due to AO/UV exposures. Where appropriate, relationships between the space environment and the attendant material/system effects are identified. Part 1 covers spacecraft design considerations for the space environment; advanced composites; polymers; adhesives; metals; ceramics; protective coatings; and lubricants, greases, and seals.

Progress in the Visualization and Mining of Chemical and Target Spaces.

PubMed

Medina-Franco, José L; Aguayo-Ortiz, Rodrigo

2013-12-01

Chemogenomics is a growing field that aims to integrate the chemical and target spaces. As part of a multi-disciplinary effort to achieve this goal, computational methods initially developed to visualize the chemical space of compound collections and mine single-target structure-activity relationships, are being adapted to visualize and mine complex relationships in chemogenomics data sets. Similarly, the growing evidence that clinical effects are many times due to the interaction of single or multiple drugs with multiple targets, is encouraging the development of novel methodologies that are integrated in multi-target drug discovery endeavors. Herein we review advances in the development and application of approaches to generate visual representations of chemical space with particular emphasis on methods that aim to explore and uncover relationships between chemical and target spaces. Also, progress in the data mining of the structure-activity relationships of sets of compounds screened across multiple targets are discussed in light of the concept of activity landscape modeling. Copyright © 2013 WILEY-VCH Verlag GmbH & Co. KGaA, Weinheim.

KSC-07pd3389

NASA Image and Video Library

2007-11-19

KENNEDY SPACE CENTER, FLA. -- During a training session, space shuttle Atlantis STS-122 Mission Specialist Hans Schlegel releases a slidewire basket, part of the emergency exit system on the fixed service structure on Launch Pad 39A, as Mission Specialist Rex Walheim looks on. Schlegel is with the European Space Agency. Seven slidewire baskets are available to carry the crew from the level of the pad's Orbiter Access Arm to a safe landing site below, if needed. Each basket can hold up to three people. A braking system catch net and drag chain slow, and then halt, the baskets as they travel down the wire at approximately 55 miles per hour. The journey takes about half a minute. A bunker is located in the landing zone 1,200 feet west of the pad, with an M-113 armored personnel carrier stationed nearby. The STS-122 crew is at NASA's Kennedy Space Center to take part in terminal countdown demonstration test, or TCDT, activities, a standard part of launch preparations. The TCDT provides astronauts and ground crews with equipment familiarization and a simulated launch countdown before launch. On mission STS-122, Atlantis will deliver the European Space Agency's Columbus module to the International Space Station. Columbus is a multifunctional, pressurized laboratory that will be permanently attached to U.S. Node 2, called Harmony, and will expand the research facilities aboard the station. Launch is targeted for Dec. 6. Photo credit: NASA/Kim Shiflett

Manned maneuvering unit: User's guide

NASA Technical Reports Server (NTRS)

Lenda, J. A.

1978-01-01

The space shuttle will provide an opportunity to extend and enhance the crew's inherent capabilities in orbit by allowing them to operate effectively outside of their spacecraft by means of extravehicular activity. For this role, the shuttle crew will have a new, easier to don and operate space suit with integral life support system, and a self-contained propulsive backpack. The backpack, called the manned maneuvering unit, will allow the crew to operate beyond the confines of the Shuttle cargo bay and fly to any part of their own spacecraft or to nearby free-flying payloads or structure. This independent mobility will be used to support a wide variety of activities including free-space transfer of cargo and personnel, inspection and monitoring of orbital operations, and construction and assembly of large structures in orbit.

Atomic Oxygen Erosion Yield Predictive Tool for Spacecraft Polymers in Low Earth Orbit

NASA Technical Reports Server (NTRS)

Bank, Bruce A.; de Groh, Kim K.; Backus, Jane A.

2008-01-01

A predictive tool was developed to estimate the low Earth orbit (LEO) atomic oxygen erosion yield of polymers based on the results of the Polymer Erosion and Contamination Experiment (PEACE) Polymers experiment flown as part of the Materials International Space Station Experiment 2 (MISSE 2). The MISSE 2 PEACE experiment accurately measured the erosion yield of a wide variety of polymers and pyrolytic graphite. The 40 different materials tested were selected specifically to represent a variety of polymers used in space as well as a wide variety of polymer chemical structures. The resulting erosion yield data was used to develop a predictive tool which utilizes chemical structure and physical properties of polymers that can be measured in ground laboratory testing to predict the in-space atomic oxygen erosion yield of a polymer. The properties include chemical structure, bonding information, density and ash content. The resulting predictive tool has a correlation coefficient of 0.914 when compared with actual MISSE 2 space data for 38 polymers and pyrolytic graphite. The intent of the predictive tool is to be able to make estimates of atomic oxygen erosion yields for new polymers without requiring expensive and time consumptive in-space testing.

IAE - Inflatable Antenna Experiment

NASA Image and Video Library

1996-06-10

STS077-705-016 (20 May 1996) --- Following its deployment from the Space Shuttle Endeavour, the Inflatable Antenna Experiment (IAE) part of the Spartan 207 payload nears completion of its inflation process over California?s Pacific Coast near Santa Barbara and Point Conception. The view was photographed with a handheld 70mm camera during the first full day of orbital operations by the six-member crew. Managed by Goddard Space Flight Center (GSFC), Spartan is designed to provide short-duration, free-flight opportunities for a variety of scientific studies. The Spartan configuration on this flight is unique in that the IAE is part of an additional separate unit which is ejected once the experiment is completed. The IAE experiment will lay the groundwork for future technology development in inflatable space structures, which will be launched and then inflated like a balloon on-orbit.

Space Shuttle Projects

NASA Image and Video Library

1977-02-01

This photograph shows an inside view of a liquid hydrogen tank for the Space Shuttle external tank (ET) Main Propulsion Test Article (MPTA). The ET provides liquid hydrogen and liquid oxygen to the Shuttle's three main engines during the first 8.5 minutes of flight. At 154-feet long and more than 27-feet in diameter, the ET is the largest component of the Space Shuttle, the structural backbone of the entire Shuttle system, and is the only part of the vehicle that is not reusable. The ET is manufactured at the Michoud Assembly Facility near New Orleans, Louisiana, by the Martin Marietta Corporation under management of the Marshall Space Flight Center.

Space Shuttle Projects

NASA Image and Video Library

1978-05-01

This photograph shows a liquid oxygen tank for the Shuttle External Tank (ET) during a hydroelastic modal survey test at the Marshall Space Flight Center. The ET provides liquid hydrogen and liquid oxygen to the Shuttle's three main engines during the first 8.5 minutes of flight. At 154-feet long and more than 27-feet in diameter, the ET is the largest component of the Space Shuttle, the structural backbone of the entire Shuttle system, and is the only part of the vehicle that is not reusable. The ET is manufactured at the Michoud Assembly Facility near New Orleans, Louisiana, by the Martin Marietta Corporation under management of the Marshall Space Flight Center.

STS-110 M.S. Smith, Ross, and Walheim in Atlantis during TCDT

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- (Left to right) STS-110 Mission Specialists Steven Smith, Jerry Ross and Rex Walheim settle into their seats aboard Space Shuttle Atlantis prior to a simulated launch countdown. The simulation is part of Terminal Countdown Demonstration Test activities. TCDT also includes emergency egress training and is held at KSC prior to each Space Shuttle flight. Scheduled for launch April 4, the 11-day mission will feature Shuttle Atlantis docking with the International Space Station (ISS) and delivering the S0 truss, the centerpiece-segment of the primary truss structure that will eventually extend over 300 feet.

TDRS-L NASA Social Tour

NASA Image and Video Library

2014-01-23

CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, social media participants were given an opportunity to go inside the spaceport's Vehicle Assembly Building. After serving through the Apollo and Space Shuttle Programs, the structure now is undergoing renovations to accommodate future launch vehicles and to continue as a major part of America's efforts to explore space. The social media participants gathered at the Florida spaceport for the launch of the Tracking and Data Relay Satellite, or TDRS-L spacecraft. Their visit included tours of key facilities and participating in presentations by key NASA leaders who updated the space agency's current efforts. Photo credit: NASA/Dan Casper

Space Construction Experiment Definition Study (SCEDS), part 2. Volume 2: Study results

NASA Technical Reports Server (NTRS)

1982-01-01

The Space Construction Experiment (SCE) was defined for integration into the Space Shuttle. This included development of flight assignment data, revision and update of preliminary mission timelines and test plans, analysis of flight safety issues, and definition of ground operations scenarios. New requirements for the flight experiment and changes for a large space antenna feed mask test article were incorporated. The program plan and cost estimates were updated. Revised SCE structural dynamics characteristics were provided for simulation and analysis of experimental tests to define and verify control limits and interactions effects between the SCE and the Orbiter digital automatic pilot.

Minimum accommodation for aerobrake assembly, phase 2

NASA Technical Reports Server (NTRS)

Katzberg, Stephen J.; Haynes, Davy A.; Tutterow, Robin D.; Watson, Judith J.; Russell, James W.

1994-01-01

A multi-element study was done to assess the practicality of a Space Station Freedom-based aerobrake system for the Space Exploration Initiative. The study was organized into six parts related to structure, aerodynamics, robotics and assembly, thermal protection system, inspection, and verification, all tied together by an integration study. The integration activity managed the broad issues related to meeting mission requirements. This report is a summary of the issues addressed by the integration team.

Tackling sun intrusion: a challenge of close collaboration of thermal, mechanical, structural and optical engineers

NASA Astrophysics Data System (ADS)

Kroneberger, Monika; Calleri, Andrea; Ulfers, Hendrik; Klossek, Andreas; Goepel, Michael

2017-09-01

The Meteosat Third Generation (MTG) program will ensure the continuity and enhancement of meteorological data from geostationary orbit as currently provided by the Meteosat Second Generation (MSG) system. OHB-Munich, as part of the core team consortium of the industrial prime contractor for the space segment Thales Alenia Space (France), is responsible for the Flexible Combined Imager - Telescope Assembly (FCI-TA) as well as the Infrared Sounder (IRS).

The P4 truss is moved to a workstand in the SSPF

NASA Technical Reports Server (NTRS)

2000-01-01

After its move across the Space Station Processing Facility, the International Space Station's P4 truss rests in its workstand. Part of the 10-truss, girder-like structure that will ultimately extend the length of a football field, the P4 is the second port truss segment that will attach to the first port truss segment (P1 truss). The P4 is scheduled for mission 12A in September 2002.

STS-110 payload S0 Truss is moved to payload canister in O&C

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- In the Operations and Checkout Building, the Integrated Truss Structure S0 is ready to be moved to the payload canister for transport to the launch pad for mission STS-110. Part of the payload, the S0 truss will become the backbone of the orbiting International Space Station (ISS), at the center of the 10-truss, girderlike structure that will ultimately extend the length of a football field on the ISS. The S0 truss will be attached to the U.S. Lab, 'Destiny,' on the 11-day mission. Launch is scheduled for April 4.

Modification Of The Manufacturing Process Of A Composite Structure- From System Needs To Elementary Tests

NASA Astrophysics Data System (ADS)

Touzard, Jerome; Veilleraud, Frederic; Collias, Michael

2012-07-01

The SYLDA5 structure (SYstème de Lancement Double Ariane 5 - Ariane 5 dual launch system) is a lightweight carbon composite structure designed and manufactured by Astrium Space Transportation at Les Mureaux premises. In order to improve the manufacturing process of t he SYLDA5, a proposal was made by SYLDA5 technical team to change the manufacturing process of the composite sandwich parts. The SYLDA5 is however one of the main contributors in the dynamic behaviour of the upper part of Ariane 5 launcher and plays an important role in the qualification of the launcher. The present paper describes the overall qualification logic retained, from System requirements to material tests and to global System qualification, in a classical V- type design cycle. It demonstrates the necessity to take into account System needs when modifying a part of it, especially when the System is qualified with actual characteristics of t he parts that may not be defined in product’s initial requirements.

GASCAN 2 payload integration

NASA Technical Reports Server (NTRS)

Brown, Henry B., Jr.; Buzby, Jared G.; Doyle, Barbara J.; Wibisono, Benedict C.

1994-01-01

This MQP is an ongoing part of the NASA Advanced Space Design Program which examines the integration of the WPI/MITRE Get Away Special Canister (GASCan 2). GASCan 2 contains the Ionospheric Properties and Propagation, Micro-Gravity Ignition, and Rotational Fluid Flow experiments, as well as the integrated support structure. The objectives this year were to finalize the power supply system, connections for experiments, mechanical design of the IPPE's antenna, and to update the structural and vibrational analysis of the integrated support structure.

Model-based active control of a continuous structure subjected to moving loads

NASA Astrophysics Data System (ADS)

Stancioiu, D.; Ouyang, H.

2016-09-01

Modelling of a structure is an important preliminary step of structural control. The main objectives of the modelling, which are almost always antagonistic are accuracy and simplicity of the model. The first part of this study focuses on the experimental and theoretical modelling of a structure subjected to the action of one or two decelerating moving carriages modelled as masses. The aim of this part is to obtain a simple but accurate model which will include not only the structure-moving load interaction but also the actuators dynamics. A small scale rig is designed to represent a four-span continuous metallic bridge structure with miniature guiding rails. A series of tests are run subjecting the structure to the action of one or two minicarriages with different loads that were launched along the structure at different initial speeds. The second part is dedicated to model based control design where a feedback controller is designed and tested against the validated model. The study shows that a positive position feedback is able to improve system dynamics but also shows some of the limitations of state- space methods for this type of system.

n/a

NASA Image and Video Library

1975-10-10

This diagram illustrates the Space Shuttle mission sequence. The Space Shuttle was approved as a national program in 1972 and developed through the 1970s. Part spacecraft and part aircraft, the Space Shuttle orbiter, the brain and the heart of the Space Transportation System (STS), required several technological advances, including thousands of insulating tiles able to stand the heat of reentry over the course of many missions, as well as sophisticated engines that could be used again and again without being thrown away. The airplane-like orbiter has three main engines, that burn liquid hydrogen and oxygen stored in the large external tank, the single largest structure in the Shuttle. Attached to the tank are two solid rocket boosters that provide the vehecile with most of the thrust needed for liftoff. Two minutes into the flight, the spent solids drop into the ocean to be recovered and refurbished for reuse, while the orbiter engines continue burning until approximately 8 minutes into the flight. After the mission is completed, the orbiter lands on a runway like an airplane.

Several Flame Balls Burning

NASA Technical Reports Server (NTRS)

2003-01-01

The Structure of Flameballs at Low Lewis Numbers (SOFBALL) experiments aboard the space shuttle in 1997 a series of sturningly successful burns. This sequence was taken during STS-94, July 12, 1997, MET:10/08:18 (approximate). It was thought these extremely dim flameballs (1/20 the power of a kitchen match) could last up to 200 seconds -- in fact, they can last for at least 500 seconds. This has ramifications in fuel-spray design in combustion engines, as well as fire safety in space. The SOFBALL principal investigator was Paul Ronney, University of Southern California, Los Angeles. The experiment was part of the space research investigations conducted during the Microgravity Science Laboratory-1R mission (STS-94, July 1-17 1997). Advanced combustion experiments will be a part of investigations planned for the International Space Station. (925KB, 9-second MPEG spanning 10 minutes, screen 320 x 240 pixels; downlinked video, higher quality not available) A still JPG composite of this movie is available at http://mix.msfc.nasa.gov/ABSTRACTS/MSFC-0300186.html.

Flame Balls

NASA Technical Reports Server (NTRS)

2003-01-01

The Structure of Flameballs at Low Lewis Numbers (SOFBALL) experiments aboard the space shuttle in 1997 a series of sturningly successful burns. This sequence was taken during STS-94, July 12, 1997, MET:10/08:18 (approximate). It was thought these extremely dim flameballs (1/20 the power of a kitchen match) could last up to 200 seconds -- in fact, they can last for at least 500 seconds. This has ramifications in fuel-spray design in combustion engines, as well as fire safety in space. The SOFBALL principal investigator was Paul Ronney, University of Southern California, Los Angeles. The experiment was part of the space research investigations conducted during the Microgravity Science Laboratory-1R mission (STS-94, July 1-17 1997). Advanced combustion experiments will be a part of investigations planned for the International Space Station. (563KB JPEG, 1798 x 1350 pixels; downlinked video, higher quality not available) The MPG from which this composite was made is available at http://mix.msfc.nasa.gov/ABSTRACTS/MSFC-0300187.html.

KSC-00padig087

NASA Image and Video Library

2000-11-08

STS-97 Mission Specialist Carlos Noriega settles into his seat in Space Shuttle Endeavour on Launch Pad 39B. He and the rest of the crew are taking part in a simulated launch countdown, part of Terminal Countdown Demonstration Test activities that also include emergency egress training and familiarization with the payload. Mission STS-97 is the sixth construction flight to the International Space Station. Its payload includes the P6 Integrated Truss Structure and a photovoltaic (PV) module, with giant solar arrays that will provide power to the Station. The mission includes two spacewalks to complete the solar array connections. STS-97 is scheduled to launch Nov. 30 at about 10:05 p.m. EST

Utilization of steel in industrialized highway bridge systems.

DOT National Transportation Integrated Search

1974-01-01

The space frame concept presented in this report represents the results of an effort to minimize on-site construction time while utilizing steel to provide a high quality but competitive type of bridge structure. A necessary part of the effort was th...

The Implications of 3D Thermal Structure on 1D Atmospheric Retrieval

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

Blecic, Jasmina; Dobbs-Dixon, Ian; Greene, Thomas, E-mail: jasmina@nyu.edu

Using the atmospheric structure from a 3D global radiation-hydrodynamic simulation of HD 189733b and the open-source Bayesian Atmospheric Radiative Transfer (BART) code, we investigate the difference between the secondary-eclipse temperature structure produced with a 3D simulation and the best-fit 1D retrieved model. Synthetic data are generated by integrating the 3D models over the Spitzer , the Hubble Space Telescope ( HST ), and the James Web Space Telescope ( JWST ) bandpasses, covering the wavelength range between 1 and 11 μ m where most spectroscopically active species have pronounced features. Using the data from different observing instruments, we present detailedmore » comparisons between the temperature–pressure profiles recovered by BART and those from the 3D simulations. We calculate several averages of the 3D thermal structure and explore which particular thermal profile matches the retrieved temperature structure. We implement two temperature parameterizations that are commonly used in retrieval to investigate different thermal profile shapes. To assess which part of the thermal structure is best constrained by the data, we generate contribution functions for our theoretical model and each of our retrieved models. Our conclusions are strongly affected by the spectral resolution of the instruments included, their wavelength coverage, and the number of data points combined. We also see some limitations in each of the temperature parametrizations, as they are not able to fully match the complex curvatures that are usually produced in hydrodynamic simulations. The results show that our 1D retrieval is recovering a temperature and pressure profile that most closely matches the arithmetic average of the 3D thermal structure. When we use a higher resolution, more data points, and a parametrized temperature profile that allows more flexibility in the middle part of the atmosphere, we find a better match between the retrieved temperature and pressure profile and the arithmetic average. The Spitzer and HST simulated observations sample deep parts of the planetary atmosphere and provide fewer constraints on the temperature and pressure profile, while the JWST observations sample the middle part of the atmosphere, providing a good match with the middle and most complex part of the arithmetic average of the 3D temperature structure.« less

Space environmental effects on spacecraft: LEO materials selection guide, part 2

NASA Astrophysics Data System (ADS)

Silverman, Edward M.

1995-08-01

This document provides performance properties on major spacecraft materials and subsystems that have been exposed to the low-Earth orbit (LEO) space environment. Spacecraft materials include metals, polymers, composites, white and black paints, thermal-control blankets, adhesives, and lubricants. Spacecraft subsystems include optical components, solar cells, and electronics. Information has been compiled from LEO short-term spaceflight experiments (e.g., space shuttle) and from retrieved satellites of longer mission durations (e.g., Long Duration Exposure Facility). Major space environment effects include atomic oxygen (AO), ultraviolet radiation, micrometeoroids and debris, contamination, and particle radiation. The main objective of this document is to provide a decision tool to designers for designing spacecraft and structures. This document identifies the space environments that will affect the performance of materials and components, e.g., thermal-optical property changes of paints due to UV exposures, AO-induced surface erosion of composites, dimensional changes due to thermal cycling, vacuum-induced moisture outgassing, and surface optical changes due to AO/UV exposures. Where appropriate, relationships between the space environment and the attendant material/system effects are identified. Part 2 covers thermal control systems, power systems, optical components, electronic systems, and applications.

Space environmental effects on spacecraft: LEO materials selection guide, part 2

NASA Technical Reports Server (NTRS)

Silverman, Edward M.

1995-01-01

This document provides performance properties on major spacecraft materials and subsystems that have been exposed to the low-Earth orbit (LEO) space environment. Spacecraft materials include metals, polymers, composites, white and black paints, thermal-control blankets, adhesives, and lubricants. Spacecraft subsystems include optical components, solar cells, and electronics. Information has been compiled from LEO short-term spaceflight experiments (e.g., space shuttle) and from retrieved satellites of longer mission durations (e.g., Long Duration Exposure Facility). Major space environment effects include atomic oxygen (AO), ultraviolet radiation, micrometeoroids and debris, contamination, and particle radiation. The main objective of this document is to provide a decision tool to designers for designing spacecraft and structures. This document identifies the space environments that will affect the performance of materials and components, e.g., thermal-optical property changes of paints due to UV exposures, AO-induced surface erosion of composites, dimensional changes due to thermal cycling, vacuum-induced moisture outgassing, and surface optical changes due to AO/UV exposures. Where appropriate, relationships between the space environment and the attendant material/system effects are identified. Part 2 covers thermal control systems, power systems, optical components, electronic systems, and applications.

About the atomic structures of icosahedral quasicrystals

NASA Astrophysics Data System (ADS)

Quiquandon, Marianne; Gratias, Denis

2014-01-01

This paper is a survey of the crystallographic methods that have been developed these last twenty five years to decipher the atomic structures of the icosahedral stable quasicrystals since their discovery in 1982 by D. Shechtman. After a brief recall of the notion of quasiperiodicity and the natural description of Z-modules in 3-dim as projection of regular lattices in N>3-dim spaces, we give the basic geometrical ingredients useful to describe icosahedral quasicrystals as irrational 3-dim cuts of ordinary crystals in 6-dim space. Atoms are described by atomic surfaces (ASs) that are bounded volumes in the internal (or perpendicular) 3-dim space and the intersections of which with the physical space are the actual atomic positions. The main part of the paper is devoted to finding the major properties of quasicrystalline icosahedral structures. As experimentally demonstrated, they can be described with a surprisingly few high symmetry ASs located at high symmetry special points in 6-dim space. The atomic structures are best described by aggregations and intersections of high symmetry compact interpenetrating atomic clusters. We show here that the experimentally relevant clusters are derived from one generic cluster made of two concentric triacontahedra scaled by τ and an external icosidodecahedron. Depending on which ones of the orbits of this cluster are eventually occupied by atoms, the actual atomic clusters are of type Bergman, Mackay, Tsai and others….

Growing a hypercubical output space in a self-organizing feature map.

PubMed

Bauer, H U; Villmann, T

1997-01-01

Neural maps project data from an input space onto a neuron position in a (often lower dimensional) output space grid in a neighborhood preserving way, with neighboring neurons in the output space responding to neighboring data points in the input space. A map-learning algorithm can achieve an optimal neighborhood preservation only, if the output space topology roughly matches the effective structure of the data in the input space. We here present a growth algorithm, called the GSOM or growing self-organizing map, which enhances a widespread map self-organization process, Kohonen's self-organizing feature map (SOFM), by an adaptation of the output space grid during learning. The GSOM restricts the output space structure to the shape of a general hypercubical shape, with the overall dimensionality of the grid and its extensions along the different directions being subject of the adaptation. This constraint meets the demands of many larger information processing systems, of which the neural map can be a part. We apply our GSOM-algorithm to three examples, two of which involve real world data. Using recently developed methods for measuring the degree of neighborhood preservation in neural maps, we find the GSOM-algorithm to produce maps which preserve neighborhoods in a nearly optimal fashion.

KSC-99pp0400

NASA Image and Video Library

1999-04-08

KENNEDY SPACE CENTER, FLA. -- A host robot, Starquester 2000, helps describe for visitors the accomplishments of unsung space heroes space probes and their role in space exploration. The walk-through Robot Scouts exhibit is part of the $13 million expansion to KSC's Visitor Complex. Other additions include a walk-through Robot Scouts exhibit, a wildlife exhibit, and the film Quest for Life in a new 300-seat theater, plus an International Space Station-themed ticket plaza, featuring a structure of overhanging solar panels and astronauts performing assembly tasks. Inaugurated three decades ago, the Visitor Complex is now one of the top five tourist attractions in Florida. It is located on S.R. 407, east of I-95, within the Merritt Island National Wildlife Refuge

Animals in biomedical space research

NASA Astrophysics Data System (ADS)

Phillips, Robert W.

The use of experimental animals has been a major component of biomedical research progress. Using animals in space presents special problems, but also provides special opportunities. Rat and squirrel monkeys experiments have been planned in concert with human experiments to help answer fundamental questions concerning the effect of weightlessness on mammalian function. For the most part, these experiments focus on identified changes noted in humans during space flight. Utilizing space laboratory facilities, manipulative experiments can be completed while animals are still in orbit. Other experiments are designed to study changes in gravity receptor structure and function and the effect of weightlessness on early vertebrate development. Following these preliminary animals experiments on Spacelab Shuttle flights, longer term programs of animal investigation will be conducted on Space Station.

Cohomology and deformation of 𝔞𝔣𝔣(1|1) acting on differential operators

NASA Astrophysics Data System (ADS)

Basdouri, Khaled; Omri, Salem

We consider the 𝔞𝔣𝔣(1|1)-module structure on the spaces of differential operators acting on the spaces of weighted densities. We compute the second differential cohomology of the Lie superalgebra 𝔞𝔣𝔣(1|1) with coefficients in differential operators acting on the spaces of weighted densities. We classify formal deformations of the 𝔞𝔣𝔣(1|1)-module structure on the superspaces of symbols of differential operators. We prove that any formal deformation of a given infinitesimal deformation of this structure is equivalent to its infinitesimal part. This work is the simplest superization of a result by Basdouri [Deformation of 𝔞𝔣𝔣(1)-modules of pseudo-differential operators and symbols, J. Pseudo-differ. Oper. Appl. 7(2) (2016) 157-179] and application of work by Basdouri et al. [First cohomology of 𝔞𝔣𝔣(1) and 𝔞𝔣𝔣(1|1) acting on linear differential operators, Int. J. Geom. Methods Mod. Phys. 13(1) (2016)].

A horizontal inflatable habitat for SEI

NASA Astrophysics Data System (ADS)

Kennedy, Kriss J.

The inflatable habitat described in this paper is a horizontally-oriented cylindrical pneumatic structure. It is part of NASA's ongoing effort to study inflatables as alternative habitats for the Space Exploration Initiative. This inflatable habitat provides a living and working environment for a crew of 12. It is an 8-m diameter by 45.34-m cylinder containing 2145 cu m of volume. Two levels of living and working areas make up the 547 sq m of floor space.

The P4 truss is moved to a workstand in the SSPF

NASA Technical Reports Server (NTRS)

2000-01-01

In the Space Station Processing Facility, workers get ready to lower the International Space Station's P4 truss onto a workstand. Part of the 10-truss, girder-like structure that will ultimately extend the length of a football field, the P4 is the second port truss segment that will attach to the first port truss segment (P1 truss). The P4 is scheduled for mission 12A in September 2002.

Space Construction Experiment Definition Study (SCEDS), part 1. Volume 1: Executive summary

NASA Technical Reports Server (NTRS)

1981-01-01

Definition was completed on a basic flight experiment which will provide data on the construction of large space systems from the orbiter which could not be practicably obtained from ground tests. Dynamic behavior of a representative large structure was predicted. On-orbit construction operations were studied. Orbiter control during and after construction was investigated. Evolutionary or supplemental flight experiments for the development of augmentation of a basic flight experiment were identified and defined.

The STS-98 crew poses for group photo near top of FSS

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- The STS-98 crew poses for a group photo on the 215-foot level of the Fixed Service Structure at Launch Pad 39A. Dressed in their orange launch and entry suits are (left to right) Commander Ken Cockrell, Mission Specialist Marsha Ivins, Pilot Mark Polansky and Mission Specialists Robert Curbeam and Thomas Jones. Behind them can be seen the white nose cone of a solid rocket booster and the orange external tank on Space Shuttle Atlantis. The crew is taking part in emergency egress training and a simulated launch countdown as part of Terminal Countdown Demonstration Test activities. STS-98 is the seventh construction flight to the International Space Station, carrying as payload the U.S. Lab Destiny, a key element in the construction of the ISS. Launch of STS-98 is scheduled for Jan. 19 at 2:11 a.m. EST.

Multilingual space terminology data bank. updating, improvement and evolution

NASA Astrophysics Data System (ADS)

Bensaid, R.; Astor, J.-L.

2002-01-01

In the context of the work done by the French terminological space group, to update the IAA multilingual space terminological data bank and to define rules for future updates it is proposed in the first part, to add to the actual IAA basic list, a selection of six hundred more terms, proposed since 1993, in the different "papers" presented during the last three IAA multilingual astronautical terminology symposia. This selection will concern more specifically the terms related to astrodynamics, aerospace biology and medicine, earth observation and remote sensing, radiolocation and mobile communications. To improve the structure and the possible uses of the data bank it is proposed to divide the terms of the basic list into themes. In the second part a list of scientific and technical themes has been put forward for discussion. This list is compatible with the actual IAA scientific committees.

Geologic interpretation of space shuttle radar images of Indonesia

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

Sabing, F.F.

1983-11-01

The National Aeronautics and Space Administration (NASA) space shuttle mission in November 1981 acquired images of parts of the earth with a synthetic aperture radar system at a wavelength of 23.5 cm (9.3 in.) and spatial resolution of 38 m (125 ft). This report describes the geologic interpretation of 1:250,000-scale images of Irian Jaya and eastern Kalimantan, Indonesia, where the all-weather capability of radar penetrates the persistent cloud cover. The inclined look direction of radar enhances subtle topographic features that may be the expression of geologic structures. On the Indonesian images, the following terrain categories are recognizable for geologic mapping:more » carbonate, clastic, volcanic, alluvial and coastal, melange, and metamorphic, as well as undifferentiated bedrock. Regional and local geologic structures are well expressed on the images.« less

The P4 truss is moved to a workstand in the SSPF

NASA Technical Reports Server (NTRS)

2000-01-01

Suspended by an overhead crane in the Space Station Processing Facility, the International Space Station's P4 truss moves toward a workstand. Below and behind it on the floor is the Multi- Purpose Logistics Module Raffaello, another segment of the Space Station. Part of the 10-truss, girder-like structure that will ultimately extend the length of a football field, the P4 is the second port truss segment that will attach to the first port truss segment (P1 truss). The P4 is scheduled for mission 12A in September 2002.

STS-110 M.S. Ross in M-113 personnel carrier during TCDT

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- STS-110 Mission Specialist Jerry Ross waits his turn at driving the M-113 armored personnel carrier, part of Terminal Countdown Demonstration Test activities. In the background, right, is Mission Specialist Lee Morin. TCDT includes emergency egress training and a simulated launch countdown, and is held at KSC prior to each Space Shuttle flight. Scheduled for launch April 4, the 11-day mission will feature Shuttle Atlantis docking with the International Space Station (ISS) and delivering the S0 truss, the centerpiece-segment of the primary truss structure that will eventually extend over 300 feet.

STS-110 M.S. Morin in M-113 personnel carrier during TCDT

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- Waiting his turn at driving the M-113 armored personnel carrier is STS-110 Mission Specialist Lee Morin. The driving is part of Terminal Countdown Demonstration Test activities, which include emergency egress training and a simulated launch countdown. The TCDT is held at KSC prior to each Space Shuttle flight. Scheduled for launch April 4, the 11-day mission will feature Shuttle Atlantis docking with the International Space Station (ISS) and delivering the S0 truss, the centerpiece-segment of the primary truss structure that will eventually extend over 300 feet.

STS-110 Pilot Frick in M-113 personnel carrier during TCDT

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- STS-110 Pilot Stephen Frick waits inside the M-113 armored personnel carrier to begin training on driving the vehicle, which is part of Terminal Countdown Demonstration Test activities. TCDT includes emergency egress training and a simulated launch countdown. The TCDT is held at KSC prior to each Space Shuttle flight. Scheduled for launch April 4, the 11-day mission will feature Shuttle Atlantis docking with the International Space Station (ISS) and delivering the S0 truss, the centerpiece-segment of the primary truss structure that will eventually extend over 300 feet.

STS-110 M.S. Ochoa in M-113 personnel carrier during TCDT

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- STS-110 Mission Specialist Ellen Ochoa waits her turn at driving the M-113 armored personnel carrier, part of Terminal Countdown Demonstration Test activities. In the background, right, is Pilot Stephen Frick. TCDT includes emergency egress training and a simulated launch countdown. The TCDT is held at KSC prior to each Space Shuttle flight. Scheduled for launch April 4, the 11-day mission will feature Shuttle Atlantis docking with the International Space Station (ISS) and delivering the S0 truss, the centerpiece-segment of the primary truss structure that will eventually extend over 300 feet.

Moduli of quantum Riemannian geometries on <=4 points

NASA Astrophysics Data System (ADS)

Majid, S.; Raineri, E.

2004-12-01

We classify parallelizable noncommutative manifold structures on finite sets of small size in the general formalism of framed quantum manifolds and vielbeins introduced previously [S. Majid, Commun. Math. Phys. 225, 131 (2002)]. The full moduli space is found for ⩽3 points, and a restricted moduli space for 4 points. Generalized Levi-Cività connections and their curvatures are found for a variety of models including models of a discrete torus. The topological part of the moduli space is found for ⩽9 points based on the known atlas of regular graphs. We also remark on aspects of quantum gravity in this approach.

Contents of payload bay of the STS-68 Space Shuttle Endeavour

NASA Image and Video Library

1994-09-30

STS068-267-079 (30 September-11 October 1994) --- The rear windows of the Space Shuttle Endeavour reflect sunlight in this view of part of the cargo bay, 115 nautical miles above the Earth. The Space Radar Laboratory (SRL-2) Multipurpose Experiment Support Structure (MPESS) is seen at bottom frame. Also partially seen are other experiments including other components of the primary payload. They are the antenna for the Spaceborne Imaging Radar (SIR-C), the X-band Synthetic Aperture Radar (X-SAR), the device for Measurement of Air Pollution from Satellites (MAPS) and some Getaway Special (GAS) canisters.

Principal fiber bundle description of number scaling for scalars and vectors: application to gauge theory

NASA Astrophysics Data System (ADS)

Benioff, Paul

2015-05-01

The purpose of this paper is to put the description of number scaling and its effects on physics and geometry on a firmer foundation, and to make it more understandable. A main point is that two different concepts, number and number value are combined in the usual representations of number structures. This is valid as long as just one structure of each number type is being considered. It is not valid when different structures of each number type are being considered. Elements of base sets of number structures, considered by themselves, have no meaning. They acquire meaning or value as elements of a number structure. Fiber bundles over a space or space time manifold, M, are described. The fiber consists of a collection of many real or complex number structures and vector space structures. The structures are parameterized by a real or complex scaling factor, s. A vector space at a fiber level, s, has, as scalars, real or complex number structures at the same level. Connections are described that relate scalar and vector space structures at both neighbor M locations and at neighbor scaling levels. Scalar and vector structure valued fields are described and covariant derivatives of these fields are obtained. Two complex vector fields, each with one real and one imaginary field, appear, with one complex field associated with positions in M and the other with position dependent scaling factors. A derivation of the covariant derivative for scalar and vector valued fields gives the same vector fields. The derivation shows that the complex vector field associated with scaling fiber levels is the gradient of a complex scalar field. Use of these results in gauge theory shows that the imaginary part of the vector field associated with M positions acts like the electromagnetic field. The physical relevance of the other three fields, if any, is not known.

Design optimization of space structures

NASA Technical Reports Server (NTRS)

Felippa, Carlos

1991-01-01

The topology-shape-size optimization of space structures is investigated through Kikuchi's homogenization method. The method starts from a 'design domain block,' which is a region of space into which the structure is to materialize. This domain is initially filled with a finite element mesh, typically regular. Force and displacement boundary conditions corresponding to applied loads and supports are applied at specific points in the domain. An optimal structure is to be 'carved out' of the design under two conditions: (1) a cost function is to be minimized, and (2) equality or inequality constraints are to be satisfied. The 'carving' process is accomplished by letting microstructure holes develop and grow in elements during the optimization process. These holes have a rectangular shape in two dimensions and a cubical shape in three dimensions, and may also rotate with respect to the reference axes. The properties of the perforated element are obtained through an homogenization procedure. Once a hole reaches the volume of the element, that element effectively disappears. The project has two phases. In the first phase the method was implemented as the combination of two computer programs: a finite element module, and an optimization driver. In the second part, focus is on the application of this technique to planetary structures. The finite element part of the method was programmed for the two-dimensional case using four-node quadrilateral elements to cover the design domain. An element homogenization technique different from that of Kikuchi and coworkers was implemented. The optimization driver is based on an augmented Lagrangian optimizer, with the volume constraint treated as a Courant penalty function. The optimizer has to be especially tuned to this type of optimization because the number of design variables can reach into the thousands. The driver is presently under development.

SLS Engine Section Test Article Arrives at Marshall on NASA Barge Pegasus

NASA Image and Video Library

2017-05-16

The NASA barge Pegasus made it’s first trip to NASA’s Marshall Space Flight Center in Huntsville, Alabama on May 15. It arrived carrying the first piece of Space Launch System hardware built at NASA's Michoud Assembly Facility in New Orleans. The barge left Michoud on April 28 with the core stage engine section test article, traveling 1,240 miles by river to Marshall. The rocket's engine section is the bottom of the core stage and houses the four RS-25 engines. The engine section test article will be moved to Marshall’s Building 4619 where it will be tested. The bottom part of the test article is structurally the same as the engine section that will be flown as part of the SLS core stage. The shiny metal top part simulates the rocket's liquid hydrogen tank, which is the fuel tank that joins to the engine section. The test article will endure tests that pull, push, and bend it, subjecting it to millions of pounds of force. This ensures the structure can withstand the incredible stresses produced by the 8.8 million pounds of thrust during launch and ascent.

Scale for positive aspects of caregiving experience: development, reliability, and factor structure.

PubMed

Kate, N; Grover, S; Kulhara, P; Nehra, R

2012-06-01

OBJECTIVE. To develop an instrument (Scale for Positive Aspects of Caregiving Experience [SPACE]) that evaluates positive caregiving experience and assess its psychometric properties. METHODS. Available scales which assess some aspects of positive caregiving experience were reviewed and a 50-item questionnaire with a 5-point rating was constructed. In all, 203 primary caregivers of patients with severe mental disorders were asked to complete the questionnaire. Internal consistency, test-retest reliability, cross-language reliability, split-half reliability, and face validity were evaluated. Principal component factor analysis was run to assess the factorial validity of the scale. RESULTS. The scale developed as part of the study was found to have good internal consistency, test-retest reliability, cross-language reliability, split-half reliability, and face validity. Principal component factor analysis yielded a 4-factor structure, which also had good test-retest reliability and cross-language reliability. There was a strong correlation between the 4 factors obtained. CONCLUSION. The SPACE developed as part of this study has good psychometric properties.

Study on Parallel 2-DOF Rotation Machanism in Radar

NASA Astrophysics Data System (ADS)

Jiang, Ming; Hu, Xuelong; Liu, Lei; Yu, Yunfei

The spherical parallel machine has become the world's academic and industrial focus of the field in recent years due to its simple and economical manufacture as well as its structural compactness especially suitable for areas where space gesture changes. This paper dwells upon its present research and development home and abroad. The newer machine (RGRR-II) can rotate around the axis z within 360° and the axis y1 from -90° to +90°. It has the advantages such as less moving parts (only 3 parts), larger ratio of work space to machine size, zero mechanic coupling, no singularity. Constructing rotation machine with spherical parallel 2-DOF rotation join (RGRR-II) may realize semispherical movement with zero dead point and extent the range. Control card (PA8000NT Series CNC) is installed in the computer. The card can run the corresponding software which realizes radar movement control. The machine meets the need of radars in plane and satellite which require larger detection range, lighter weight and compacter structure.

KSC-07pd3388

NASA Image and Video Library

2007-11-19

KENNEDY SPACE CENTER, FLA. -- The space shuttle Atlantis STS-122 crew receives instruction on slidewire basket operation, part of the emergency exit system on the fixed service structure on Launch Pad 39A. Standing in the basket, from left, are Mission Specialists Leland Melvin, Hans Schlegel and Rex Walheim. Schlegel is with the European Space Agency. Seven slidewire baskets are available to carry the crew from the level of the pad's Orbiter Access Arm to a safe landing site below, if needed. Each basket can hold up to three people. A braking system catch net and drag chain slow, and then halt, the baskets as they travel down the wire at approximately 55 miles per hour. The journey takes about half a minute. A bunker is located in the landing zone 1,200 feet west of the pad, with an M-113 armored personnel carrier stationed nearby. The STS-122 crew is at NASA's Kennedy Space Center to take part in terminal countdown demonstration test, or TCDT, activities, a standard part of launch preparations. The TCDT provides astronauts and ground crews with equipment familiarization and a simulated launch countdown before launch. On mission STS-122, Atlantis will deliver the European Space Agency's Columbus module to the International Space Station. Columbus is a multifunctional, pressurized laboratory that will be permanently attached to U.S. Node 2, called Harmony, and will expand the research facilities aboard the station. Launch is targeted for Dec. 6. Photo credit: NASA/Kim Shiflett

The P-1 truss in the O&C

NASA Technical Reports Server (NTRS)

2000-01-01

Part of the P-1 truss is seen as it rests in a workstand in the Operations and Checkout Building. Scheduled to fly in spring of 2002, the P-1 is part of a total 10-truss, girder-like structure that will ultimately extend the length of a football field. Astronauts will attach the 14- by 15-foot structure to the port side of the center truss, S0, during the spring assembly flight. The 33,000-pound P-1 will house the thermal radiator rotating joint (TRRJ) that will rotate the International Space Station's radiators away from the sun to increase their maximum cooling efficiency.

System analysis study of space platform and station accommodations for life sciences research facilities. Volume 1: Executive summary. Phase A: Conceptual design and programmatics

NASA Technical Reports Server (NTRS)

1985-01-01

The study was conducted in 3 parts over a 3 year period. The study schedule and the documentation associated with each study part is given. This document summarized selected study results from the conceptual design and programmatics segment of the effort. The objectives were: (1) to update requirements and tradeoffs and develop a detailed design and mission requirements document; (2) to develop conceptual designs and mission descriptions; and (3) to develop programmatic, i.e., work breakdown structure and work breakdown structure dictionary, estimated cost, and implementing plans and schedules.

KSC-07pd3394

NASA Image and Video Library

2007-11-19

KENNEDY SPACE CENTER, FLA. -- The space shuttle Atlantis STS-122 crew receives instruction on slidewire basket operation, part of the emergency exit system on the fixed service structure on Launch Pad 39A. From left, Mission Specialists Rex Walheim, Leopold Eyharts and Leland Melvin gain first-hand experience inside one of the baskets. Seven slidewire baskets are available to carry the crew from the level of the pad's Orbiter Access Arm to this landing site, if needed. Each basket can hold up to three people. A braking system catch net and drag chain slow, and then halt, the baskets as they travel down the wire at approximately 55 miles per hour. The journey takes about half a minute. A bunker is located in the landing zone 1,200 feet west of the pad, with an M-113 armored personnel carrier stationed nearby. The STS-122 crew is at NASA's Kennedy Space Center to take part in terminal countdown demonstration test, or TCDT, activities, a standard part of launch preparations. The TCDT provides astronauts and ground crews with equipment familiarization and a simulated launch countdown before launch. On mission STS-122, Atlantis will deliver the European Space Agency's Columbus module to the International Space Station. Columbus is a multifunctional, pressurized laboratory that will be permanently attached to U.S. Node 2, called Harmony, and will expand the research facilities aboard the station. Launch is targeted for Dec. 6. Photo credit: NASA/Kim Shiflett

The structural geometry and development of the central Appalachian fold-and thrust belt across the Pennsylvania salient: The effects of syntectonic loading

NASA Astrophysics Data System (ADS)

Evans, Mark

2017-04-01

The Pennsylvania salient is a classic arcuate fold-and-thrust belt that was deformed during the Late Paleozoic Alleghenian orogeny. 38 regional cross-sections with an along-strike spacing of 5 to 10 km were constructed, and show that the structural geometry varies significantly from the 030°-striking southwestern segment to 060°-striking northeastern segment. The primary competent lithotectonic unit is the 2 to 3 km thick Cambro-Ordovician carbonate sequence which is detached along a Cambrian clastic unit. The 5 to 7 km thick preserved Upper Paleozoic sequence is less homogeneous, and locally exhibits significant internal deformation. In the southwest part of the salient, the hinterland part of the fold belt is defined by a series of imbricated Cambro-Ordovician carbonate horses with leading-edge fault-propagation style folds that have a structural amplitude of 5 to 7 km. In the central part of the fold belt, the Broadtop synclinorium exhibits little to no imbrication of the Cambro-Ordovician unit, while in the western part of the belt toward the foreland, two additional carbonate horses with leading-edge fault-propagation style folds comprise the Wills Mt. anticlinorium. In the central and eastern parts of the salient, the structural geometry toward the foreland is defined by a duplex with 4 -5 imbricate horses of Cambro-Ordovician carbonates that transitions to an antiformal stack of two to three carbonate thrust sheets comprising the Nittany anticlinorium. Toward the hinterland, the Cambro-Ordovician carbonate sequence is faulted into broadly-spaced fault-related folds, and includes the regionally continuous (>160 km) Jacks Mt. - Berwick anticline that spans both limbs of the salient. Upon retrodeformation of the cross sections, the 060°-striking northeastern segment restoration path curves 25°-30° to the east, while the 030°-striking southwestern segment curves 20°-25° to the south. The major fault underlying the presently curved Jacks Mt. - Berwick anticline structure, as well as those structures toward the hinterland, restore to a nearly straight fault traces oriented 045°-050°. The relatively straight restored faults require a rigid indenter colliding from the southeast to impose the curvature to the salient. The regional variation in structural style and ramp spacing may be related to the distribution of Late Carboniferous to Permian syn-tectonic loads during thrusting. Paleo-overburden thicknesses were determined from fluid inclusion microthermometry data of CH4±CO2 and aqueous fluid inclusions from syn-tectonic veins. In general, on the retrodeformed sections, restored overburdens are typically less above anticlinoria (<1.5 to 4.0 km), while much larger (4.3 to 6.1 km) above synclinoria. This suggests that syn-tectonic loading in the synclinoria due to sedimentation and/or overthrusting increased pore-fluid pressure enabling forelandward transport. Areas with less syntectonic overburden were prone to develop high-amplitude fold structures.

Space Shuttle Projects

NASA Image and Video Library

1977-03-01

This photograph shows the liquid hydrogen tank and liquid oxygen tank for the Space Shuttle external tank (ET) being assembled in the weld assembly area of the Michoud Assembly Facility (MAF). The ET provides liquid hydrogen and liquid oxygen to the Shuttle's three main engines during the first eight 8.5 minutes of flight. At 154-feet long and more than 27-feet in diameter, the ET is the largest component of the Space Shuttle, the structural backbone of the entire Shuttle system, and the only part of the vehicle that is not reusable. The ET is manufactured at the Michoud Assembly Facility near New Orleans, Louisiana, by the Martin Marietta Corporation under management of the Marshall Space Flight Center.

Analysis and testing of a soft actuation system for segmented reflector articulation and isolation

NASA Technical Reports Server (NTRS)

Jandura, Louise; Agronin, Michael L.

1991-01-01

Segmented reflectors have been proposed for space-based applications such as optical communication and large-diameter telescopes. An actuation system for mirrors in a space-based segmented mirror array has been developed as part of the National Aeronautics and Space Administration-sponsored Precision Segmented Reflector program. The actuation system, called the Articulated Panel Module (APM), articulates a mirror panel in 3 degrees of freedom in the submicron regime, isolates the panel from structural motion, and simplifies space assembly of the mirrors to the reflector backup truss. A breadboard of the APM has been built and is described. Three-axis modeling, analysis, and testing of the breadboard is discussed.

Lunar Contour Crafting: A Novel Technique for ISRU-Based Habitat Development

NASA Technical Reports Server (NTRS)

Khoshnevis, Behrokh; Bodiford, Melanie P.; Burks, Kevin H.; Ethridge, Ed; Tucker, Dennis; Kim, Won; Toutanji, Houssam; Fiske, Michael R.

2005-01-01

1. Habitat Structures at MSFC is one element of the In-Situ Fabrication and Repair (ISFR) Program: ISFR develops technologies for fabrication, repair and recycling of tools, parts, and habitats/structures using in-situ resources. ISRU - based habitat structures are considered Class III. 2. Habitat Structure Purpose: Develop Lunar and/or Martian habitat structures for manned missions that maximize the use of in-situ resources to address the following agency topics: bioastronautics critical path roadmap; strategic technical challenges defined in H&RT formulation plan: margins and redundancy; modularity, robotic network, space resource utilization; autonomy, affordable logistics pre-positioning.

Quantum theory in real Hilbert space: How the complex Hilbert space structure emerges from Poincaré symmetry

NASA Astrophysics Data System (ADS)

Moretti, Valter; Oppio, Marco

As earlier conjectured by several authors and much later established by Solèr (relying on partial results by Piron, Maeda-Maeda and other authors), from the lattice theory point of view, Quantum Mechanics may be formulated in real, complex or quaternionic Hilbert spaces only. Stückelberg provided some physical, but not mathematically rigorous, reasons for ruling out the real Hilbert space formulation, assuming that any formulation should encompass a statement of Heisenberg principle. Focusing on this issue from another — in our opinion, deeper — viewpoint, we argue that there is a general fundamental reason why elementary quantum systems are not described in real Hilbert spaces. It is their basic symmetry group. In the first part of the paper, we consider an elementary relativistic system within Wigner’s approach defined as a locally-faithful irreducible strongly-continuous unitary representation of the Poincaré group in a real Hilbert space. We prove that, if the squared-mass operator is non-negative, the system admits a natural, Poincaré invariant and unique up to sign, complex structure which commutes with the whole algebra of observables generated by the representation itself. This complex structure leads to a physically equivalent reformulation of the theory in a complex Hilbert space. Within this complex formulation, differently from what happens in the real one, all selfadjoint operators represent observables in accordance with Solèr’s thesis, and the standard quantum version of Noether theorem may be formulated. In the second part of this work, we focus on the physical hypotheses adopted to define a quantum elementary relativistic system relaxing them on the one hand, and making our model physically more general on the other hand. We use a physically more accurate notion of irreducibility regarding the algebra of observables only, we describe the symmetries in terms of automorphisms of the restricted lattice of elementary propositions of the quantum system and we adopt a notion of continuity referred to the states viewed as probability measures on the elementary propositions. Also in this case, the final result proves that there exists a unique (up to sign) Poincaré invariant complex structure making the theory complex and completely fitting into Solèr’s picture. This complex structure reveals a nice interplay of Poincaré symmetry and the classification of the commutant of irreducible real von Neumann algebras.

A NEW THREE-DIMENSIONAL SOLAR WIND MODEL IN SPHERICAL COORDINATES WITH A SIX-COMPONENT GRID

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

Feng, Xueshang; Zhang, Man; Zhou, Yufen, E-mail: fengx@spaceweather.ac.cn

In this paper, we introduce a new three-dimensional magnetohydrodynamics numerical model to simulate the steady state ambient solar wind from the solar surface to 215 R {sub s} or beyond, and the model adopts a splitting finite-volume scheme based on a six-component grid system in spherical coordinates. By splitting the magnetohydrodynamics equations into a fluid part and a magnetic part, a finite volume method can be used for the fluid part and a constrained-transport method able to maintain the divergence-free constraint on the magnetic field can be used for the magnetic induction part. This new second-order model in space andmore » time is validated when modeling the large-scale structure of the solar wind. The numerical results for Carrington rotation 2064 show its ability to produce structured solar wind in agreement with observations.« less

On the emergence of the structure of physics

NASA Astrophysics Data System (ADS)

Majid, S.

2018-04-01

We consider Hilbert's problem of the axioms of physics at a qualitative or conceptual level. This is more pressing than ever as we seek to understand how both general relativity and quantum theory could emerge from some deeper theory of quantum gravity, and in this regard I have previously proposed a principle of self-duality or quantum Born reciprocity as a key structure. Here, I outline some of my recent work around the idea of quantum space-time as motivated by this non-standard philosophy, including a new toy model of gravity on a space-time consisting of four points forming a square. This article is part of the theme issue `Hilbert's sixth problem'.

On the emergence of the structure of physics.

PubMed

Majid, S

2018-04-28

We consider Hilbert's problem of the axioms of physics at a qualitative or conceptual level. This is more pressing than ever as we seek to understand how both general relativity and quantum theory could emerge from some deeper theory of quantum gravity, and in this regard I have previously proposed a principle of self-duality or quantum Born reciprocity as a key structure. Here, I outline some of my recent work around the idea of quantum space-time as motivated by this non-standard philosophy, including a new toy model of gravity on a space-time consisting of four points forming a square.This article is part of the theme issue 'Hilbert's sixth problem'. © 2018 The Author(s).

STS-110 payload S0 Truss is moved to payload canister in O&C

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- In the Operations and Checkout Building, an overhead crane carries the Integrated Truss Structure S0 from its workstand toward the payload canister. The S0 truss will be transported to the launch pad for mission STS-110. Part of the payload, the S0 truss will become the backbone of the orbiting International Space Station (ISS), at the center of the 10-truss, girderlike structure that will ultimately extend the length of a football field on the ISS. The S0 truss will be attached to the U.S. Lab, 'Destiny,' on the 11-day mission. Launch is scheduled for April 4.

Attitude control of the space construction base: A modular approach

NASA Technical Reports Server (NTRS)

Oconnor, D. A.

1982-01-01

A planar model of a space base and one module is considered. For this simplified system, a feedback controller which is compatible with the modular construction method is described. The systems dynamics are decomposed into two parts corresponding to base and module. The information structure of the problem is non-classical in that not all system information is supplied to each controller. The base controller is designed to accommodate structural changes that occur as the module is added and the module controller is designed to regulate its own states and follow commands from the base. Overall stability of the system is checked by Liapunov analysis and controller effectiveness is verified by computer simulation.

The Space Shuttle focused-technology program - Lessons learned

NASA Technical Reports Server (NTRS)

Fitzgerald, P. E., Jr.; Gabris, E. A.

1983-01-01

The results of a focused technology program (FTP), its management structure, the development of the Space Shuttle, and lessons applicable to future space programs such as a space station are discussed. A committee was formed by NASA in 1969 to define the technologies necessary for a reusable spacecraft. Basic and applied research assessments were featured at the beginning of the process. Working groups were established to cover all necessary areas, e.g., Operations, Structures and Materials, Aerothermodynamics, etc., and tasks were distributed to appropriate NASA centers. Funding was drawn from existing budgets. The FTP proceeded successfully because of an understanding of the respective roles of industry and government, the willingness of industry to invest early in a new technology, and the unclassified status of information generated by the program. The in-house design and technology transfer methods that brought the project to a technology demonstration phase are explored, noting the necessity for users to take part in the development within their field.

Biomineral nanoparticles are space-filling

NASA Astrophysics Data System (ADS)

Yang, Li; Killian, Christopher E.; Kunz, Martin; Tamura, Nobumichi; Gilbert, P. U. P. A.

2011-02-01

Sea urchin biominerals have been shown to form from aggregating nanoparticles of amorphous calcium carbonate (ACC), which then crystallize into macroscopic single crystals of calcite. Here we measure the surface areas of these biominerals and find them to be comparable to those of space-filling macroscopic geologic calcite crystals. These biominerals differ from synthetic mesocrystals, which are invariably porous. We propose that space-filling ACC is the structural precursor for echinoderm biominerals.Sea urchin biominerals have been shown to form from aggregating nanoparticles of amorphous calcium carbonate (ACC), which then crystallize into macroscopic single crystals of calcite. Here we measure the surface areas of these biominerals and find them to be comparable to those of space-filling macroscopic geologic calcite crystals. These biominerals differ from synthetic mesocrystals, which are invariably porous. We propose that space-filling ACC is the structural precursor for echinoderm biominerals. This article was submitted as part of a Themed Issue on Crystallization and Formation Mechanisms of Nanostructures. Other papers on this topic can be found in issue 11 of vol. 2 (2010). This issue can be found from the Nanoscale homepage [http://www.rsc.org/nanoscale

Around Marshall

NASA Image and Video Library

1979-03-22

Once the United States' space program had progressed from Earth's orbit into outerspace, the prospect of building and maintaining a permanent presence in space was realized. To accomplish this feat, NASA launched a temporary workstation, Skylab, to discover the effects of low gravity and weightlessness on the human body, and also to develop tools and equipment that would be needed in the future to build and maintain a more permanent space station. The structures, techniques, and work schedules had to be carefully designed to fit this unique construction site. The components had to be lightweight for transport into orbit, yet durable. The station also had to be made with removable parts for easy servicing and repairs by astronauts. All of the tools necessary for service and repairs had to be designed for easy manipulation by a suited astronaut. And construction methods had to be efficient due to limited time the astronauts could remain outside their controlled environment. In lieu of all the specific needs for this project, an environment on Earth had to be developed that could simulate a low gravity atmosphere. A Neutral Buoyancy Simulator (NBS) was constructed by NASA Marshall Space Flight Center (MSFC) in 1968. Since then, NASA scientists have used this facility to understand how humans work best in low gravity and also provide information about the different kinds of structures that can be built. With the help of the NBS, building a space station became more of a reality. In a joint venture between NASA/Langley Research Center in Hampton, VA and MSFC, the Assembly Concept for Construction of Erectable Space Structures (ACCESS) was developed and demonstrated at MSFC's NBS. The primary objective of this experiment was to test the ACCESS structural assembly concept for suitability as the framework for larger space structures and to identify ways to improve the productivity of space construction. Pictured is a demonstration of ACCESS.

Around Marshall

NASA Image and Video Library

1977-07-13

Once the United States' space program had progressed from Earth's orbit into outerspace, the prospect of building and maintaining a permanent presence in space was realized. To accomplish this feat, NASA launched a temporary workstation, Skylab, to discover the effects of low gravity and weightlessness on the human body, and also to develop tools and equipment that would be needed in the future to build and maintain a more permanent space station. The structures, techniques, and work schedules had to be carefully designed to fit this unique construction site. The components had to be lightweight for transport into orbit, yet durable. The station also had to be made with removable parts for easy servicing and repairs by astronauts. All of the tools necessary for service and repairs had to be designed for easy manipulation by a suited astronaut. And construction methods had to be efficient due to limited time the astronauts could remain outside their controlled environment. In lieu of all the specific needs for this project, an environment on Earth had to be developed that could simulate a low gravity atmosphere. A Neutral Buoyancy Simulator (NBS) was constructed by NASA Marshall Space Flight Center (MSFC) in 1968. Since then, NASA scientists have used this facility to understand how humans work best in low gravity and also provide information about the different kinds of structures that can be built. With the help of the NBS, building a space station became more of a reality. In a joint venture between NASA/Langley Research Center in Hampton, VA and MSFC, the Assembly Concept for Construction of Erectable Space Structures (ACCESS) was developed and demonstrated at MSFC's NBS. The primary objective of this experiment was to test the ACCESS structural assembly concept for suitability as the framework for larger space structures and to identify ways to improve the productivity of space construction. Pictured is a demonstration of ACCESS.

Around Marshall

NASA Image and Video Library

1979-04-16

Once the United States' space program had progressed from Earth's orbit into outerspace, the prospect of building and maintaining a permanent presence in space was realized. To accomplish this feat, NASA launched a temporary workstation, Skylab, to discover the effects of low gravity and weightlessness on the human body, and also to develop tools and equipment that would be needed in the future to build and maintain a more permanent space station. The structures, techniques, and work schedules had to be carefully designed to fit this unique construction site. The components had to be lightweight for transport into orbit, yet durable. The station also had to be made with removable parts for easy servicing and repairs by astronauts. All of the tools necessary for service and repairs had to be designed for easy manipulation by a suited astronaut. Construction methods had to be efficient due to the limited time the astronauts could remain outside their controlled environment. In lieu of all the specific needs for this project, an environment on Earth had to be developed that could simulate a low gravity atmosphere. A Neutral Buoyancy Simulator (NBS) was constructed by NASA Marshall Space Flight Center (MSFC) in 1968. Since then, NASA scientists have used this facility to understand how humans work best in low gravity and also provide information about the different kinds of structures that can be built. With the help of the NBS, building a space station became more of a reality. In a joint venture between NASA/Langley Research Center in Hampton, Virginia and the MSFC, the Assembly Concept for Construction of Erectable Space Structures (ACCESS) was developed and demonstrated at MSFC's NBS. The primary objective of this experiment was to test the ACCESS structural assembly concept for suitability as the framework for larger space structures and to identify ways to improve the productivity of space construction. Pictured is a demonstration of ACCESS.

Activities relating to understanding the initiation, organization and structure of moist convection in the Southeast environment

NASA Technical Reports Server (NTRS)

Mcnider, Richard T.

1992-01-01

In the spring and summer of 1986, NASA/Marshall Space Flight Center (MSFC) will sponsor the Satellite Precipitation And Cloud Experiment (SPACE) to be conducted in the Central Tennessee, Northern Alabama, and Northeastern Mississippi area. The field program will incorporate high altitude flight experiments associated with meteorological remote sensor development for future space flight, and an investigation of precipitation processes associated with mesoscale and small convective systems. In addition to SPACE, the MIcroburst and Severe Thunderstorm (MIST) program, sponsored by the National Science Foundation (NSF), and the FAA-Lincoln Laboratory Operational Weather Study (FLOWS), sponsored by the Federal Aviation Administration (FAA), will take place concurrently within the SPACE experiment area. All three programs (under the joint acronym COHMEX (COoperative Huntsville Meteorological EXperiment)) will provide a data base for detailed analysis of mesoscale convective systems while providing ground truth comparisons for remote sensor evaluation. The purpose of this document is to outline the experiment design criteria for SPACE, and describe the special observing facilities and data sets that will be available under the COHMEX joint program. In addition to the planning of SPACE-COHMEX, this document covers three other parts of the program. The field program observations' main activity was the operation of an upper air rawinsonde network to provide ground truth for aircraft and spacecraft observations. Another part of the COHMEX program involved using boundary layer mesoscale models to study and simulate the initiation and organization of moist convection due to mesoscale thermal and mechanical circulations. The last part of the program was the collection, archival and distribution of the resulting COHMEX-SPACE data sets.

Fiber Optic Strain Measurements In Filament-Wound Graphite-Epoxy Tubes Containing Embedded Fibers

NASA Astrophysics Data System (ADS)

Rogowski, R. S.; Heyman, J. S.; Holben, M. S.; Egalon, C.; Dehart, D. W.; Doederlein, T.; Koury, J.

1989-01-01

Several planned United States Air Force (USAF) and National Aeronautics and Space Administration (NASA) space systems such as Space Based Radar (SBR), Space Based Laser (SBL), and Space Station, pose serious vibration and control issues. Their low system mass combined with their large size, precision pointing/shape control and rapid retargetting requirements, will result in an unprecedented degree of interaction between the system controller and the modes of vibration of the structure. The resulting structural vibrations and/or those caused by foreign objects impacting the space structure could seriously degrade system performance, making it virtually impossible for passive structural systems to perform their missions. Therefore an active vibration control system which will sense these natural and spurious vibrations, evaluate them and dampen them out is required. This active vibration control system must be impervious to the space environment and electromagnetic interference, have very low weight, and in essence become part of the structure itself. The concept of smart structures meets these criteria. Smart structures is defined as the embedment of sensors, actuators, and possibly microprocessors in the material which forms the structure, a concept that is particularly applicable to advanced composites. These sensors, actuators, and microprocessors will work interactively to sense, evaluate, and dampen those vibrations which pose a threat to large flexible space systems (LSS). The sensors will also be capable of sensing any degradation to the structure. The Air Force Astronautics Laboratory (AFAL) has been working in the area of dynamics and control of LSS for the past five years. Several programs involving both contractual and in-house efforts to develop sensors and actuators for controlling LSS have been initiated. Presently the AFAL is developing a large scale laboratory which will have the capacity of performing large angle retargetting manuevers and vibration analysis on LSS. Advanced composite materials have been fabricated for the last seven years, consisting mostly of rocket components such as: nozzles, payload shrouds, exit cones, and nose cones. Recently, however, AFAL has been fabricating composite components such as trusses, tubes and flat panels for space applications. Research on fiber optic sensors at NASA Langley Research Center (NASA LaRC) dates back to 1979. Recently an optical phase locked loop (OPLL) has been developed that can be used to make strain and temperature measurements. Static and dynamic strain measurements have been demonstrated using this device.' To address future space requirements, AFAL and NASA have initiated a program to design, fabricate, and experimentally test composite struts and panels with embedded sensors, actuators, and microprocessors that can be used to control vibration and motion in space structures.

KSC-00padig090

NASA Image and Video Library

2000-11-08

Commander Brent Jett looks toward Pilot Mike Broomfield, on his right, as they get comfortable in their seats in the cockpit of Space Shuttle Endeavour on Launch Pad 39B. Along with the rest of the crew, they are taking part in a simulated launch countdown, part of Terminal Countdown Demonstration Test activities that also include emergency egress training and familiarization with the payload. Mission STS-97 is the sixth construction flight to the International Space Station. Its payload includes the P6 Integrated Truss Structure and a photovoltaic (PV) module, with giant solar arrays that will provide power to the Station. The mission includes two spacewalks to complete the solar array connections. STS-97 is scheduled to launch Nov. 30 at about 10:05 p.m. EST

STS-92 crew takes part in a Leak Seal Kit Fit Check in the SSPF

NASA Technical Reports Server (NTRS)

1999-01-01

In the Space Station Processing Facility, STS-92 crew members take part in a Leak Seal Kit Fit Check in connection with the Pressurized Mating Adapter -3 in the background. From left are Mission Specialist Peter J.K. 'Jeff' Wisoff (Ph.D.), Pilot Pamela A. Melroy, Commander Brian Duffy, Mission Specialist Koichi Wakata, who represents the National Space Development Agency of Japan (NASDA), Brian Warkentine, with JSC, and a Boeing worker at right. Also participating are other crew members Mission Specialists Leroy Chiao (Ph.D.), Michael E. Lopez-Alegria and William Surles 'Bill' McArthur Jr. The mission payload also includes an integrated truss structure (Z-1 truss). Launch of STS-92 is scheduled for Feb. 24, 2000.

KSC-00pp1297

NASA Image and Video Library

2000-09-12

KENNEDY SPACE CENTER, Fla. -- A long view of Launch Complex 39 is caught by the early morning sun. Left of center is Launch Pad 39A with Space Shuttle Discovery. At its left is the 300,000-gallon water tank that is part of the sound suppression system. Hoses from the tank can be seen coiling under the pad, next to the opening of the flame trench, part of the flame detector system. In the foreground is a retention pond; another is at right center. At far right, the ball-shaped structure is a 850,000-gallon storage tank for the cryogenic liquid oxygen, one of the propellants of the orbiter’s main engines. On the horizon can be seen the 525-foot tall Vehicle Assembly Building

Space Solar Power Technical Interchange Meeting 2: SSP TIM 2

NASA Technical Reports Server (NTRS)

Sanders, Jim; Hawk, Clark W.

1998-01-01

The 2nd Space Solar Power Technical Interchange Meeting (SSP TIM 2) was conducted September 21st through 24th with the first part consisting of a Plenary session. The summary results of this Plenary session are contained in part one of this report. The attendees were then organized into Working Breakout Sessions and Integrated Product Team (IPT) Sessions for the purpose of conducting in-depth discussions in specific topic areas and developing a consensus as to appropriate study plans and actions to be taken. The Second part covers the Plenary Summary Session, which contains the summary results of the Working Breakout Sessions and IPT Sessions. The appendix contains the list of attendees. The ob'jective was to provide an update for the study teams and develop plans for subsequent study activities. This SSP TIM 2 was initiated and the results reported electronically over the Internet. The International Space Station (ISS) could provide the following opportunities for conducting research and technology (R&T) which are applicable to SSP: (1) Automation and Robotics, (2) Advanced Power Generation, (3) Advanced Power Management & Distribution (PMAD), (4) Communications Systems and Networks, (5) Energy Storage, (6) In Space Propulsion (ISP), (7) Structural Dynamics and Control, and Assembly and (8) Wireless Power Transmission.

KSC-00pp0773

NASA Image and Video Library

2000-06-17

In the Space Shuttle Processing Facility, workers get ready to attach cables to a high-gain antenna that will be lifted and attached to the Integrated Truss Structure (ITS) Z1. The Z1, part of the payload on mission STS-92 (flight 3A) to be launched in mid-fall, is an early exterior framework for the International Space Station. It will allow the first U.S. solar arrays, on mission STS-97 (flight 4A), to be temporarily installed on Unity for early power

The P4 truss is moved to a workstand in the SSPF

NASA Technical Reports Server (NTRS)

2000-01-01

In the Space Station Processing Facility, workers oversee the removal of the P4 truss from the truck that transported it from Tulsa, Okla. Part of the 10-truss, girder-like structure that will ultimately extend the length of a football field on the International Space Station, the P4 is the second port truss segment that will attach to the first port truss segment (P1 truss). The P4 is scheduled for mission 12A in September 2002.

Modification of cytogenetic and physiological effects of space flight factors by biologically active compounds

NASA Technical Reports Server (NTRS)

Aliyev, A. A.; Mekhti-Zade, E. R.; Mashinskiy, A. L.; Alekperov, U. K.

1986-01-01

Physiological and cytogenetic changes in the Welsh onion plants induced by a short (82 days) and long term (522 days) space flight are expressed in decrease of seed germination, inhibition of stem growth, depression of cell division in root meristem, and increase in the number of structural chromosome rearrangements. The treatment of such plants with solutions of a-tocopherol, auxin, and kinetin decreased the level of chromosome aberrations to the control one and normalized cell divisions and growth partly or completely.

Engineering report. Part 2: NASA wheel and brake material tradeoff study for space shuttle type environmental requirements

NASA Technical Reports Server (NTRS)

Bok, L. D.

1973-01-01

The study included material selection and trade-off for the structural components of the wheel and brake optimizing weight vs cost and feasibility for the space shuttle type application. Analytical methods were used to determine section thickness for various materials, and a table was constructed showing weight vs. cost trade-off. The wheel and brake were further optimized by considering design philosophies that deviate from standard aircraft specifications, and designs that best utilize the materials being considered.

Inclusions, Porosity, and Fatigue of AlSi10Mg Parts Produced by Selective Laser Melting

NASA Astrophysics Data System (ADS)

Tang, Ming

Additive manufacturing (AM) has experienced remarkable growth in the past decade with applications in both rapid prototyping and rapid manufacturing for functional end-usable parts. As one of the most promising AM processes, selective laser melting (SLM) can be used to fabricate metal products line by line and layer upon layer within a powder bed system. Such process allows the building of parts with customized shapes, which brings higher design flexibility than traditional casting and wrought manufacturing. In this work, AlSi10Mg powder is chosen as the raw material for producing parts by SLM, since aluminum alloys are widely used in automotive and aerospace industries thanks to an excellent combination of low density and competitive mechanical properties. However, there remain multiple drawbacks which limit further applications of aluminum parts produced by SLM: lack of prediction of solidification microstructure, few studies on fatigue properties, and cost and time caused by the limited production rate. All these issues were studied in this work and summarized as follows: Rapid movement of the melt pool (at a speed around 1 m/s) in SLM of metal powder directly implies rapid solidification. In this research, the length scale of the as-built microstructure of parts built with the alloy AlSi10Mg was measured and compared with the well-known relationship between cell size and cooling rate. Cooling rates during solidification were estimated using the Rosenthal equation. It was found that the solidification structure is the expected cellular combination of silicon with alpha-aluminum. The dependence of the measured cell spacing on the calculated cooling rate follows the well-established relationship for aluminum alloys. The implication is that cell spacing can be manipulated by changing the heat input. Microscopy of polished sections through particles of the metal powder used to build the parts showed that the particles have a dendritic-eutectic structure; the dendrite arm spacings in metal powder particles of different diameters were measured and also agree with literature correlations, showing the expected increase in secondary dendrite arm spacing with increasing particle diameter. It is well-known that the fatigue behavior of cast aluminum alloy parts is largely determined by the internal defects, particularly pores and inclusions, such as oxides. This study shows that such imperfections are also present in AlSi10Mg parts produced by SLM, and serve as sites for failure initiation. The effect of hatch spacing and building orientation on tensile and fatigue properties was tested. Similar defects were found both on polished cross-sections and on fracture surfaces. The results imply that the oxide-driven pores dominate the fatigue resistance of the samples in this work. The larger oxide particles which are associated with the crack initiation likely form by oxidation of metal vapor during part manufacture. Residual porosity in parts produced by SLM mainly results from lack-of-fusion, entrapped gas, pores left in powder, evaporation of elements, and collapse of key-holes. Lack-of-fusion porosity is caused by the the insufficient overlap of melt pools in powder bed fusion and is particularly detrimental to fatigue performance due to the stress concentration at the sharp edges of the pores. The third part of this work deals with predicting lack-of-fusion porosity quantitatively by a geometrically-based model and designing processing parameters for build rate improvement without introducing porosity. The inputs into the simulation are hatch spacing, layer thickness, melt-pool cross-sectional area, and hatch rotation angle. Comparison with several data sets from the literature shows that the simulations correctly predict process conditions at which lack-of-fusion porosity becomes apparent, as well as the rate at which porosity increases with changes in process conditions such as beam speed, layer thickness, and hatch spacing. Relative to the default processing parameters provided by the manufacturer, the build rate can be improved by adjusting hatch spacing and layer thickness, and increasing the platform temperature. The simulations also show that the volume fraction of lack-of-fusion porosity is independent of hatch rotation angle. A unique combination of zero rotation and half hatch spacing as the beam offset between adjacent layers is proposed for build rate optimization.

Around Marshall

NASA Image and Video Library

1978-07-21

Once the United States' space program had progressed from Earth's orbit into outerspace, the prospect of building and maintaining a permanent presence in space was realized. To accomplish this feat, NASA launched a temporary workstation, Skylab, to discover the effects of low gravity and weightlessness on the human body, and also to develop tools and equipment that would be needed in the future to build and maintain a more permanent space station. The structures, techniques, and work schedules had to be carefully designed to fit this unique construction site. The components had to be lightweight for transport into orbit, yet durable. The station also had to be made with removable parts for easy servicing and repairs by astronauts. All of the tools necessary for service and repairs had to be designed for easy manipulation by a suited astronaut. And construction methods had to be efficient due to limited time the astronauts could remain outside their controlled environment. In lieu of all the specific needs for this project, an environment on Earth had to be developed that could simulate a low gravity atmosphere. A Neutral Buoyancy Simulator (NBS) was constructed by NASA Marshall Space Flight Center (MSFC) in 1968. Since then, NASA scientists have used this facility to understand how humans work best in low gravity and also provide information about the different kinds of structures that can be built. Included in the plans for the space station was a space telescope. This telescope would be attached to the space station and directed towards outerspace. Astronomers hoped that the space telescope would provide a look at space that is impossible to see from Earth because of Earth's atmosphere and other man made influences. Pictured is a large structure that is being used as the antenna base for the space telescope.

Space Materials Handbook. 3rd; ed.

NASA Technical Reports Server (NTRS)

Rittenhouse, John B.; Singletary, John B.

1969-01-01

This edition is the result of an extensive revision and reworking of the second edition of the Space Materials Handbook along with the incorporation of entirely new subject matter coverage and new materials data. All of the most significant material, phenomena, properties, and principles covered in the original Handbook are presented and expanded in this revised and updated version. However, treatment of theoretical aspects has been condensed in order that more emphasis could be placed on the extensive new materials knowledge and data obtained from the design and successful launching of a wide variety of space systems. The handbook is organized into four parts, namely: space environment, effect of space environment on materials, materials in space, and biological interaction with spacecraft materials. Information on mechanical, physical, and chemical properties and characteristics is given for a wide variety of metallic and nonmetallic materials. The effects of natural and induced environments on materials are appraised. Materials categories include coverage of thermal control materials, optical materials, adhesives, organic structural materials, inorganic structural materials, electronic components and materials, materials for sealing applications, and lubrication materials. In addition, a comprehensive multiple citation index is incorporated which gives ready access to information on specific subject areas with regard to their locations within the Handbook.

Effective electron-density map improvement and structure validation on a Linux multi-CPU web cluster: The TB Structural Genomics Consortium Bias Removal Web Service.

PubMed

Reddy, Vinod; Swanson, Stanley M; Segelke, Brent; Kantardjieff, Katherine A; Sacchettini, James C; Rupp, Bernhard

2003-12-01

Anticipating a continuing increase in the number of structures solved by molecular replacement in high-throughput crystallography and drug-discovery programs, a user-friendly web service for automated molecular replacement, map improvement, bias removal and real-space correlation structure validation has been implemented. The service is based on an efficient bias-removal protocol, Shake&wARP, and implemented using EPMR and the CCP4 suite of programs, combined with various shell scripts and Fortran90 routines. The service returns improved maps, converted data files and real-space correlation and B-factor plots. User data are uploaded through a web interface and the CPU-intensive iteration cycles are executed on a low-cost Linux multi-CPU cluster using the Condor job-queuing package. Examples of map improvement at various resolutions are provided and include model completion and reconstruction of absent parts, sequence correction, and ligand validation in drug-target structures.

Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors

NASA Technical Reports Server (NTRS)

Seda, Jorge F. (Inventor); Dunbar, Lawrence W. (Inventor); Gliebe, Philip R. (Inventor); Szucs, Peter N. (Inventor); Brauer, John C. (Inventor); Johnson, James E. (Inventor); Moniz, Thomas (Inventor); Steinmetz, Gregory T. (Inventor)

2003-01-01

An aircraft gas turbine engine assembly includes an inter-turbine frame axially located between high and low pressure turbines. Low pressure turbine has counter rotating low pressure inner and outer rotors with low pressure inner and outer shafts which are at least in part rotatably disposed co-axially within a high pressure rotor. Inter-turbine frame includes radially spaced apart radially outer first and inner second structural rings disposed co-axially about a centerline and connected by a plurality of circumferentially spaced apart struts. Forward and aft sump members having forward and aft central bores are fixedly joined to axially spaced apart forward and aft portions of the inter-turbine frame. Low pressure inner and outer rotors are rotatably supported by a second turbine frame bearing mounted in aft central bore of aft sump member. A mount for connecting the engine to an aircraft is located on first structural ring.

Repeatability and uncertainty analyses of light gas gun test data

NASA Technical Reports Server (NTRS)

Schonberg, William P.; Cooper, David

1994-01-01

All large spacecraft are susceptible to high-speed impacts by meteoroids and pieces of orbiting space debris which can damage flight-critical systems and in turn lead to catastrophic failure. One way to obtain information on the response of a structure to a meteoroid impact or an orbital debris impact is to simulate the impact conditions of interest in the laboratory and analyze the resulting damage to a target structure. As part of the Phase B and C/D development activities for the Space Station Freedom, 950 impact tests were performed using the NASA/Marshall Space Flight Center (MSFC) light gas gun from 1985-1991. This paper presents the results of impact phenomena repeatability and data uncertainty studies performed using the information obtained from those tests. The results of these studies can be used to assess the utility of individual current and future NASA/MSFC impact test results in the design of long-duration spacecraft.

Space Station

NASA Image and Video Library

1986-08-01

In response to President Reagan's directive to NASA to develop a permanent marned Space Station within a decade, part of the State of the Union message to Congress on January 25, 1984, NASA and the Administration adopted a phased approach to Station development. This approach provided an initial capability at reduced costs, to be followed by an enhanced Space Station capability in the future. This illustration depicts a configuration with enhanced capabilities. It builds on the horizontal boom and module pattern of the revised baseline. This configuration would feature dual keels, two vertical spines 105-meters long joined by upper and lower booms. The structure carrying the modules would become a transverse boom of a basically rectangular structure. The two new booms, 45-meters in length, would provide extensive accommodations for attached payloads, and would offer a wide field of view. Power would be increased significantly, with the addition if a 50-kW solar dynamic power system.

Effect of Atmospheric Absorption Bands on the Optimal Design of Multijunction Solar Cells

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

McMahon, William E.; Friedman, Daniel J.; Geisz, John F.

Designing terrestrial multijunction (MJ) cells with 5+ junctions is challenging, in part because the presence of atmospheric absorption bands creates a design space with numerous local maxima. Here we introduce a new taxonomical structure which facilitates both numerical convergence and the visualization of the resulting designs.

A real-space approach to the X-ray phase problem

NASA Astrophysics Data System (ADS)

Liu, Xiangan

Over the past few decades, the phase problem of X-ray crystallography has been explored in reciprocal space in the so called direct methods . Here we investigate the problem using a real-space approach that bypasses the laborious procedure of frequent Fourier synthesis and peak picking. Starting from a completely random structure, we move the atoms around in real space to minimize a cost function. A Monte Carlo method named simulated annealing (SA) is employed to search the global minimum of the cost function which could be constructed in either real space or reciprocal space. In the hybrid minimal principle, we combine the dual space costs together. One part of the cost function monitors the probability distribution of the phase triplets, while the other is a real space cost function which represents the discrepancy between measured and calculated intensities. Compared to the single space cost functions, the dual space cost function has a greatly improved landscape and therefore could prevent the system from being trapped in metastable states. Thus, the structures of large molecules such as virginiamycin (C43H 49N7O10 · 3CH0OH), isoleucinomycin (C60H102N 6O18) and hexadecaisoleucinomycin (HEXIL) (C80H136 N8O24) can now be solved, whereas it would not be possible using the single cost function. When a molecule gets larger, the configurational space becomes larger, and the requirement of CPU time increases exponentially. The method of improved Monte Carlo sampling has demonstrated its capability to solve large molecular structures. The atoms are encouraged to sample the high density regions in space determined by an approximate density map which in turn is updated and modified by averaging and Fourier synthesis. This type of biased sampling has led to considerable reduction of the configurational space. It greatly improves the algorithm compared to the previous uniform sampling. Hence, for instance, 90% of computer run time could be cut in solving the complex structure of isoleucinomycin. Successful trial calculations include larger molecular structures such as HEXIL and a collagen-like peptide (PPG). Moving chemical fragment is proposed to reduce the degrees of freedom. Furthermore, stereochemical parameters are considered for geometric constraints and for a cost function related to chemical energy.

Attending to space within and between objects: Implications from a patient with Balint’s syndrome

PubMed Central

Robertson, Lynn C.; Treisman, Anne

2007-01-01

Neuropsychological conditions such as Balint’s syndrome have shown that perceptual organization of parts into a perceptual unit can be dissociated from the ability to localize objects relative to each other. Neural mechanisms that code the spatial structure within individual objects or words may seem to be intact, while between-object structure is compromised. Here we investigate the nature of within-object spatial processing in a patient with Balint’s syndrome (RM). We suggest that within-object spatial structure can be determined (a) directly by explicit spatial processing of between-part relations, mediated by the same dorsal pathway as between-object spatial relations; or (b) indirectly by the discrimination of object identities, which may involve implicit processing of between-part relations and which is probably mediated by the ventral system. When this route is ruled out, by testing discrimination of differences in part location that do not change the identity of the object, we find no evidence of explicit within-object spatial coding in a patient without functioning parietal lobes. PMID:21049339

Compensation of Gravity-Induced Structural Deformations on a Beam- Waveguide Antenna Using a Deformable Mirror

NASA Technical Reports Server (NTRS)

Imbriale, W. A.; Moore, M.; Rochblatt, D. J.; Veruttipong, W.

1995-01-01

At the NASA Deep Space Network (DSN) Goldstone Complex, a 34-meter- diameter beam-waveguide antenna, DSS-13, was constructed in 1988-1990 and has become an integral part of an advanced systems program and a test bed for technologies being developed to introduce Ka-band (32 GHz) frequencies into the DSN. A method for compensating the gravity- induced structural deformations in this large antenna is presented.

The Shock and Vibration Digest, Volume 17, Number 10

DTIC Science & Technology

1985-10-01

Venkayya, V.B. and Tischler, V.A., 49. Calico , R.A., Jr. and Tnyfault, D.V., "Frequency Control and the Effect on the "Decoupled Large Space Structure...Hurwitz presented. The threshold concept is de- Numerical Structural Mechanics scribed, as are receiver operating charac- Branch (Code 1844 ) teristic...Part Vibration and Dynamics of Off Road Vehi- 2 - Realistic Complex Elements des M. Apetaur I.A. Craighead, P.R. Brown Prague Univ. of Tech

Microplasma Ionization of Volatile Organics for Improving Air/Water Monitoring Systems On-Board the International Space Station

NASA Astrophysics Data System (ADS)

Bernier, Matthew C.; Alberici, Rosana M.; Keelor, Joel D.; Dwivedi, Prabha; Zambrzycki, Stephen C.; Wallace, William T.; Gazda, Daniel B.; Limero, Thomas F.; Symonds, Josh M.; Orlando, Thomas M.; Macatangay, Ariel; Fernández, Facundo M.

2016-07-01

Low molecular weight polar organics are commonly observed in spacecraft environments. Increasing concentrations of one or more of these contaminants can negatively impact Environmental Control and Life Support (ECLS) systems and/or the health of crew members, posing potential risks to the success of manned space missions. Ambient plasma ionization mass spectrometry (MS) is finding effective use as part of the analytical methodologies being tested for next-generation space module environmental analysis. However, ambient ionization methods employing atmospheric plasmas typically require relatively high operation voltages and power, thus limiting their applicability in combination with fieldable mass spectrometers. In this work, we investigate the use of a low power microplasma device in the microhollow cathode discharge (MHCD) configuration for the analysis of polar organics encountered in space missions. A metal-insulator-metal (MIM) structure with molybdenum foil disc electrodes and a mica insulator was used to form a 300 μm diameter plasma discharge cavity. We demonstrate the application of these MIM microplasmas as part of a versatile miniature ion source for the analysis of typical volatile contaminants found in the International Space Station (ISS) environment, highlighting their advantages as low cost and simple analytical devices.

Microplasma Ionization of Volatile Organics for Improving Air/Water Monitoring Systems On-Board the International Space Station.

PubMed

Bernier, Matthew C; Alberici, Rosana M; Keelor, Joel D; Dwivedi, Prabha; Zambrzycki, Stephen C; Wallace, William T; Gazda, Daniel B; Limero, Thomas F; Symonds, Josh M; Orlando, Thomas M; Macatangay, Ariel; Fernández, Facundo M

2016-07-01

Low molecular weight polar organics are commonly observed in spacecraft environments. Increasing concentrations of one or more of these contaminants can negatively impact Environmental Control and Life Support (ECLS) systems and/or the health of crew members, posing potential risks to the success of manned space missions. Ambient plasma ionization mass spectrometry (MS) is finding effective use as part of the analytical methodologies being tested for next-generation space module environmental analysis. However, ambient ionization methods employing atmospheric plasmas typically require relatively high operation voltages and power, thus limiting their applicability in combination with fieldable mass spectrometers. In this work, we investigate the use of a low power microplasma device in the microhollow cathode discharge (MHCD) configuration for the analysis of polar organics encountered in space missions. A metal-insulator-metal (MIM) structure with molybdenum foil disc electrodes and a mica insulator was used to form a 300 μm diameter plasma discharge cavity. We demonstrate the application of these MIM microplasmas as part of a versatile miniature ion source for the analysis of typical volatile contaminants found in the International Space Station (ISS) environment, highlighting their advantages as low cost and simple analytical devices. Graphical Abstract ᅟ.

Thyroid function appears to be significantly reduced in Space-borne MDS mice

NASA Astrophysics Data System (ADS)

Saverio Ambesi-Impiombato, Francesco; Curcio, Francesco; Fontanini, Elisabetta; Perrella, Giuseppina; Spelat, Renza; Zambito, Anna Maria; Damaskopoulou, Eleni; Peverini, Manola; Albi, Elisabetta

It is known that prolonged space flights induced changes in human cardiovascular, muscu-loskeletal and nervous systems whose function is regulated by the thyroid gland but, until now, no data were reported about thyroid damage during space missions. We have demonstrated in vitro that, during space missions (Italian Soyuz Mission "ENEIDE" in 2005, Shuttle STS-120 "ESPERIA" in 2007), thyroid in vitro cultured cells did not respond to thyroid stimulating hor-mone (TSH) treatment; they appeared healthy and alive, despite their being in a pro-apopotic state characterised by a variation of sphingomyelin metabolism and consequent increase in ce-ramide content. The insensitivity to TSH was largely due to a rearrangement of specific cell membrane microdomains, acting as platforms for TSH-receptor (TEXUS-44 mission in 2008). To study if these effects were present also in vivo, as part of the Mouse Drawer System (MDS) Tissue Sharing Program, we performed experiments in mice maintained onboard the Interna-tional Space Station during the long-duration (90 days) exploration mission STS-129. After return to earth, the thyroids isolated from the 3 animals were in part immediately frozen to study the morphological modification in space and in part immediately used to study the effect of TSH treatment. For this purpose small fragments of tissue were treated with 10-7 or 10-8 M TSH for 1 hour by using untreated fragments as controls. Then the fragments were fixed with absolute ethanol for 10 min at room temperature and centrifuged for 20 min. at 3000 x g. The supernatants were used for cAMP analysis whereas the pellet were used for protein amount determination and for immunoblotting analysis of TSH-receptor, sphingomyelinase and sphingomyelin-synthase. The results showed a modification of the thyroid structure and also the values of cAMP production after treatment with 10-7 M TSH for 1 hour were significantly lower than those obtained in Earth's gravity. The treatment with TSH induced relevant quanti-tative variations of TSH-receptor, sphingomyelinase and sphingomyelin-synthase, probably due to membrane microdomain structure modifications which in turn, as it occurs in vitro, influence the cellular response to TSH treatment.

KSC-00pp0952

NASA Image and Video Library

2000-07-19

KENNEDY SPACE CENTER, FLA. -- As part of Crew Equipment Interface Test (CEIT) activities at SPACEHAB, members of the STS-106 crew check out a Maximum Envelope Support Structure (MESS) rack they will be using during their mission to the International Space Station. Seen here (with backs to camera, in uniform) are Mission Specialist Richard A. Mastracchio, Pilot Scott D. Altman, Boris V. Morukov, and Edward T. Lu (at right). Also taking part in the CEIT are Commander Terrence W. Wilcutt and Mission Specialists Yuri I. Malenchenko and Daniel C. Burbank. Malenchenko and Morukov represent the Russian Aviation and Space Agency. STS-106 is scheduled to launch Sept. 8, 2000, at 8:31 a.m. EDT from Launch Pad 39B on an 11-day mission. The seven-member crew will prepare the Space Station for its first resident crew and begin outfitting the newly arrived Zvezda Service Module. They will perform support tasks on orbit, transfer supplies and prepare the Zvezda living quarters for the first long-duration crew, dubbed “Expedition One,” which is due to arrive at the Station in late fall

KSC00pp0952

NASA Image and Video Library

2000-07-19

KENNEDY SPACE CENTER, FLA. -- As part of Crew Equipment Interface Test (CEIT) activities at SPACEHAB, members of the STS-106 crew check out a Maximum Envelope Support Structure (MESS) rack they will be using during their mission to the International Space Station. Seen here (with backs to camera, in uniform) are Mission Specialist Richard A. Mastracchio, Pilot Scott D. Altman, Boris V. Morukov, and Edward T. Lu (at right). Also taking part in the CEIT are Commander Terrence W. Wilcutt and Mission Specialists Yuri I. Malenchenko and Daniel C. Burbank. Malenchenko and Morukov represent the Russian Aviation and Space Agency. STS-106 is scheduled to launch Sept. 8, 2000, at 8:31 a.m. EDT from Launch Pad 39B on an 11-day mission. The seven-member crew will prepare the Space Station for its first resident crew and begin outfitting the newly arrived Zvezda Service Module. They will perform support tasks on orbit, transfer supplies and prepare the Zvezda living quarters for the first long-duration crew, dubbed “Expedition One,” which is due to arrive at the Station in late fall

Fabrication Infrastructure to Enable Efficient Exploration and Utilization of Space

NASA Technical Reports Server (NTRS)

Howell, Joe T.; Fikes, John C.; McLemore, Carole A.; Manning, Curtis W.; Good, Jim

2007-01-01

Unlike past one-at-a-time mission approaches, system-of-systems infrastructures will be needed to enable ambitious scenarios for sustainable future space exploration and utilization. Fabrication infrastructure will be needed to support habitat structure development, tools and mechanical part fabrication, as well as repair and replacement of ground support and space mission hardware such as life support items, vehicle components and crew systems. The fabrication infrastructure will need the In Situ Fabrication and Repair (ISFR) element, which is working in conjunction with the In Situ Resources Utilization (ISRU) element, to live off the land. The ISFR Element supports the entire life cycle of Exploration by: reducing downtime due to failed components; decreasing risk to crew by recovering quickly from degraded operation of equipment; improving system functionality with advanced geometry capabilities; and enhancing mission safety by reducing assembly part counts of original designs where possible. This paper addresses the fabrication infrastructures that support efficient, affordable, reliable infrastructures for both space exploration systems and logistics; these infrastructures allow sustained, affordable and highly effective operations on the Moon, Mars and beyond.

STS-110 payload S0 Truss is moved to payload canister in O&C

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- In the Operations and Checkout Building, an overhead crane carries the Integrated Truss Structure S0 to the payload canister which will transport it to the launch pad for mission STS-110. Seen below the truss is the Multi-Purpose Logistics Module Donatello, currently not in use. The S0 truss will be part of the payload on Space Shuttle Atlantis. The S0 truss will be attached to the U.S. Lab, 'Destiny,' on the 11-day mission, becoming the backbone of the orbiting International Space Station (ISS). Launch is scheduled for April 4.

KSC-00pp1371

NASA Image and Video Library

2000-09-15

STS-92 Mission Specialist Koichi Wakata of Japan (center) gets help from United Space Alliance Mechanical Technician Vinny Difranzo (left) and NASA Quality Assurance Specialist Danny Wyatt (right) in suiting up in the White Room. Wakata and other crew members are taking part in a simulated countdown KSC for Terminal Countdown Demonstration Test (TCDT) activities. STS-92 is scheduled to launch Oct. 5 at 9:38 p.m. EDT on the fifth flight to the International Space Station. It will carry two elements of the Space Station, the Integrated Truss Structure Z1 and the third Pressurized Mating Adapter. The mission is also the 100th flight in the Shuttle program

KSC00pp1371

NASA Image and Video Library

2000-09-15

STS-92 Mission Specialist Koichi Wakata of Japan (center) gets help from United Space Alliance Mechanical Technician Vinny Difranzo (left) and NASA Quality Assurance Specialist Danny Wyatt (right) in suiting up in the White Room. Wakata and other crew members are taking part in a simulated countdown KSC for Terminal Countdown Demonstration Test (TCDT) activities. STS-92 is scheduled to launch Oct. 5 at 9:38 p.m. EDT on the fifth flight to the International Space Station. It will carry two elements of the Space Station, the Integrated Truss Structure Z1 and the third Pressurized Mating Adapter. The mission is also the 100th flight in the Shuttle program

Expedition 6 crew group photo during TCDT

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. - The Expedition 6 crew poses for a photo on 195-foot level of the Fixed Service Structure on Launch Pad 39A. From left are astronaut Donald Pettit, Commander Ken Bowersox and cosmonaut Nikolai Budarin. Along with the STS-113 crew, they have been participating in emergency egress training, part of Terminal Countdown Demonstration Test activities in preparation for their launch. The 16th assembly flight to the International Space Station, STS-113 will carry the Port 1 (P1) truss aboard Space Shuttle Endeavour, as well as Expedition 6, who will replace Expedition 5 on the Station. The mission is scheduled to launch Nov. 10, 2002.

STS-110 Commander Bloomfield in M-113 personnel carrier during TCDT

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- STS-110 Commander Michael Bloomfield is eager to take his turn turn at driving the M-113 armored personnel carrier, part of Terminal Countdown Demonstration Test activities. To his left is Mission Specialist Steven Smith. TCDT includes emergency egress training and a simulated launch countdown, and is held at KSC prior to each Space Shuttle flight. Scheduled for launch April 4, the 11-day mission will feature Shuttle Atlantis docking with the International Space Station (ISS) and delivering the S0 truss, the centerpiece-segment of the primary truss structure that will eventually extend over 300 feet.

Automatic Fastening Large Structures: a New Approach

NASA Technical Reports Server (NTRS)

Lumley, D. F.

1985-01-01

The external tank (ET) intertank structure for the space shuttle, a 27.5 ft diameter 22.5 ft long externally stiffened mechanically fastened skin-stringer-frame structure, was a labor intensitive manual structure built on a modified Saturn tooling position. A new approach was developed based on half-section subassemblies. The heart of this manufacturing approach will be 33 ft high vertical automatic riveting system with a 28 ft rotary positioner coming on-line in mid 1985. The Automatic Riveting System incorporates many of the latest automatic riveting technologies. Key features include: vertical columns with two sets of independently operating CNC drill-riveting heads; capability of drill, insert and upset any one piece fastener up to 3/8 inch diameter including slugs without displacing the workpiece offset bucking ram with programmable rotation and deep retraction; vision system for automatic parts program re-synchronization and part edge margin control; and an automatic rivet selection/handling system.

Third Conference on Fibrous Composites in Flight Vehicle Design, part 1

NASA Technical Reports Server (NTRS)

1976-01-01

The use of fibrous composite materials in the design of aircraft and space vehicle structures and their impact on future vehicle systems are discussed. The topics covered include: flight test work on composite components, design concepts and hardware, specialized applications, operational experience, certification and design criteria. Contributions to the design technology base include data concerning material properties, design procedures, environmental exposure effects, manufacturing procedures, and flight service reliability. By including composites as baseline design materials, significant payoffs are expected in terms of reduced structural weight fractions, longer structural life, reduced fuel consumption, reduced structural complexity, and reduced manufacturing cost.

Precise Truss Assembly Using Commodity Parts and Low Precision Welding

NASA Technical Reports Server (NTRS)

Komendera, Erik; Reishus, Dustin; Dorsey, John T.; Doggett, W. R.; Correll, Nikolaus

2014-01-01

Hardware and software design and system integration for an intelligent precision jigging robot (IPJR), which allows high precision assembly using commodity parts and low-precision bonding, is described. Preliminary 2D experiments that are motivated by the problem of assembling space telescope optical benches and very large manipulators on orbit using inexpensive, stock hardware and low-precision welding are also described. An IPJR is a robot that acts as the precise "jigging", holding parts of a local structure assembly site in place, while an external low precision assembly agent cuts and welds members. The prototype presented in this paper allows an assembly agent (for this prototype, a human using only low precision tools), to assemble a 2D truss made of wooden dowels to a precision on the order of millimeters over a span on the order of meters. The analysis of the assembly error and the results of building a square structure and a ring structure are discussed. Options for future work, to extend the IPJR paradigm to building in 3D structures at micron precision are also summarized.

The newly expanded KSC Visitors Complex features a new ticket plaza, information center, exhibits an

NASA Technical Reports Server (NTRS)

1999-01-01

A host robot, Starquester 2000, helps describe for visitors the accomplishments of unsung space heroes - space probes - and their role in space exploration. The walk-through Robot Scouts exhibit is part of the $13 million expansion to KSC's Visitor Complex. Other additions include a walk-through Robot Scouts exhibit, a wildlife exhibit, and the film Quest for Life in a new 300-seat theater, plus an International Space Station-themed ticket plaza, featuring a structure of overhanging solar panels and astronauts performing assembly tasks. Inaugurated three decades ago, the Visitor Complex is now one of the top five tourist attractions in Florida. It is located on S.R. 407, east of I-95, within the Merritt Island National Wildlife Refuge.

Structural Health Management for Future Aerospace Vehicles

NASA Technical Reports Server (NTRS)

Prosser, W. H.; Allison, S. G.; Woodard, S. E.; Wincheski, R. A.; Cooper, E. G.; Price, D. C.; Hedley, M.; Prokopenko, M.; Scott, D. A.; Tessler, A.

2004-01-01

Structural Health Management (SHM) will be of critical importance to provide the safety, reliability and affordability necessary for the future long duration space missions described in America's Vision for Space Exploration. Long duration missions to the Moon, Mars and beyond cannot be accomplished with the current paradigm of periodic, ground based structural integrity inspections. As evidenced by the Columbia tragedy, this approach is also inadequate for the current Shuttle fleet, thus leading to its initial implementation of on-board SHM sensing for impact detection as part of the return to flight effort. However, future space systems, to include both vehicles as well as structures such as habitation modules, will require an integrated array of onboard in-situ sensing systems. In addition, advanced data systems architectures will be necessary to communicate, store and process massive amounts of SHM data from large numbers of diverse sensors. Further, improved structural analysis and design algorithms will be necessary to incorporate SHM sensing into the design and construction of aerospace structures, as well as to fully utilize these sensing systems to provide both diagnosis and prognosis of structural integrity. Ultimately, structural integrity information will feed into an Integrated Vehicle Health Management (IVHM) system that will provide real-time knowledge of structural, propulsion, thermal protection and other critical systems for optimal vehicle management and mission control. This paper will provide an overview of NASA research and development in the area of SHM as well as to highlight areas of technology improvement necessary to meet these future mission requirements.

Information retrieval for a document writing assistance program

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

Corral, M.L.; Simon, A.; Julien, C.

This paper presents an Information Retrieval mechanism to facilitate the writing of technical documents in the space domain. To address the need for document exchange between partners in a given project, documents are standardized. The writing of a new document requires the re-use of existing documents or parts thereof. These parts can be identified by {open_quotes}tagging{close_quotes} the logical structure of documents and restored by means of a purpose-built Information Retrieval System (I.R.S.). The I.R.S. implemented in our writing assistance tool uses natural language queries and is based on a statistical linguistic approach which is enhanced by the use of documentmore » structure module.« less

Small part ultrasound in childhood and adolescence.

PubMed

Wunsch, R; von Rohden, L; Cleaveland, R; Aumann, V

2014-09-01

Small-part sonography refers to the display of small, near-surface structures using high-frequency linear array transducers. Traditional applications for small part ultrasound imaging include visualization and differential diagnostic evaluation in unclear superficial bodily structures with solid, liquid and mixed texture, as well as similar structures in nearly superficial organs such as the thyroid glands and the testes. Furthermore indications in the head and neck regions are the assessment of the outer CSF spaces in infants, the sonography of the orbit, the sonography of the walls of the large neck vessels, the visualization of superficially situated lymph nodes and neoplasms. Clinical evidence concludes that sonography, having of all imaging modalities the highest spatial resolution in the millimeter- and micrometer range (100-1000μm), can be considered the best suited technique for examining superficial pathological formations and near-surface organs. In addition, it delivers important information about characteristic, often pathognomonic tissue architecture in pathological processes. Copyright © 2014 Elsevier Ireland Ltd. All rights reserved.

A mechanical adapter for installing mission equipment on large space structures

NASA Technical Reports Server (NTRS)

Lefever, A. E.; Totah, R. S.

1980-01-01

A mechanical attachment adapter was designed, constructed, and tested. The adapter was was included in a simulation program that investigated techniques for assembling erectable structures under simulated zero-g conditions by pressure-suited subjects in a simulated EVA mode. The adapter was utilized as an interface attachment between a simulated equipment module and one node point of a tetrahedral structural cell. The mating performance of the adapter, a self-energized mechanism, was easily and quickly demonstrated and required little effort on the part of the test subjects.

Buckling analysis of the quadripod structure for the NASA 70-meter antenna

NASA Technical Reports Server (NTRS)

Chian, Chian T.

1987-01-01

As part of the effort to extend the diameter of three Deep Space Network large earth antennas from 64 meters to 70 meters, a slim profiled quadripod structure was designed to support a 7.7 meter diameter subreflector for the 70 meter antenna. The new quadripod design, which particularly emphasizes reduced radio frequency blockage, is achieved by means of a narrow cross sectional profile of the legs. Buckling analysis, using NASTRAN, was conducted in this study to verify the safety margin for the quadripod structural stability.

KSC-07pd3387

NASA Image and Video Library

2007-11-19

KENNEDY SPACE CENTER, FLA. -- The space shuttle Atlantis STS-122 crew receives instruction on slidewire basket operation, part of the emergency exit system on the fixed service structure on Launch Pad 39A. Standing, from left, are Mission Specialists Stanley Love; Leopold Eyharts' backup, Frank De Winne; and Pilot Alan Poindexter. Standing in the basket, from left, are Mission Specialists Hans Schlegel, Leland Melvin and Rex Walheim. Schlegel, Eyharts and De Winne are with the European Space Agency. Eyharts will remain on the International Space Station as a flight engineer for Expedition 16 following the STS-122 mission. Seven slidewire baskets are available to carry the crew from the level of the pad's Orbiter Access Arm to a safe landing site below, if needed. Each basket can hold up to three people. A braking system catch net and drag chain slow, and then halt, the baskets as they travel down the wire at approximately 55 miles per hour. The journey takes about half a minute. A bunker is located in the landing zone 1,200 feet west of the pad, with an M-113 armored personnel carrier stationed nearby. The STS-122 crew is at NASA's Kennedy Space Center to take part in terminal countdown demonstration test, or TCDT, activities, a standard part of launch preparations. The TCDT provides astronauts and ground crews with equipment familiarization and a simulated launch countdown before launch. On mission STS-122, Atlantis will deliver the European Space Agency's Columbus module to the International Space Station. Columbus is a multifunctional, pressurized laboratory that will be permanently attached to U.S. Node 2, called Harmony, and will expand the research facilities aboard the station. Launch is targeted for Dec. 6. Photo credit: NASA/Kim Shiflett

KSC-07pd3386

NASA Image and Video Library

2007-11-19

KENNEDY SPACE CENTER, FLA. -- The space shuttle Atlantis STS-122 crew receives instruction on slidewire basket operation, part of the emergency exit system on the fixed service structure on Launch Pad 39A. From left are Mission Specialists Stanley Love; Leopold Eyharts' backup, Frank De Winne; Leland Melvin and Hans Schlegel; Pilot Alan Poindexter; and Commander Steve Frick, with his back to the camera. Schlegel, Eyharts and De Winne are with the European Space Agency. Eyharts will remain on the International Space Station as a flight engineer for Expedition 16 following the STS-122 mission. Seven slidewire baskets are available to carry the crew from the level of the pad's Orbiter Access Arm to a safe landing site below, if needed. Each basket can hold up to three people. A braking system catch net and drag chain slow, and then halt, the baskets as they travel down the wire at approximately 55 miles per hour. The journey takes about half a minute. A bunker is located in the landing zone 1,200 feet west of the pad, with an M-113 armored personnel carrier stationed nearby. The STS-122 crew is at NASA's Kennedy Space Center to take part in terminal countdown demonstration test, or TCDT, activities, a standard part of launch preparations. The TCDT provides astronauts and ground crews with equipment familiarization and a simulated launch countdown before launch. On mission STS-122, Atlantis will deliver the European Space Agency's Columbus module to the International Space Station. Columbus is a multifunctional, pressurized laboratory that will be permanently attached to U.S. Node 2, called Harmony, and will expand the research facilities aboard the station. Launch is targeted for Dec. 6. Photo credit: NASA/Kim Shiflett

Design Through Manufacturing: The Solid Model-Finite Element Analysis Interface

NASA Technical Reports Server (NTRS)

Rubin, Carol

2002-01-01

State-of-the-art computer aided design (CAD) presently affords engineers the opportunity to create solid models of machine parts reflecting every detail of the finished product. Ideally, in the aerospace industry, these models should fulfill two very important functions: (1) provide numerical. control information for automated manufacturing of precision parts, and (2) enable analysts to easily evaluate the stress levels (using finite element analysis - FEA) for all structurally significant parts used in aircraft and space vehicles. Today's state-of-the-art CAD programs perform function (1) very well, providing an excellent model for precision manufacturing. But they do not provide a straightforward and simple means of automating the translation from CAD to FEA models, especially for aircraft-type structures. Presently, the process of preparing CAD models for FEA consumes a great deal of the analyst's time.

Studying of shale organic matter structure and pore space transformations during hydrocarbon generation

NASA Astrophysics Data System (ADS)

Giliazetdinova, Dina; Korost, Dmitry; Gerke, Kirill

2016-04-01

Due to the increased interest in the study of the structure, composition, and oil and gas potential of unconventional hydrocarbon resources, investigations of the transformation of the pore space of rocks and organic matter alterations during the generation of hydrocarbon fluids are getting attention again. Due to the conventional hydrocarbon resources decreasing, there will be a necessity to develop new unconventional hydrocarbon resources. Study of the conditions and processes of hydrocarbon generation, formation and transformation of the pore space in these rocks is pivotal to understand the mechanisms of oil formation and determine the optimal and cost effective ways for their industrial exploration. In this study, we focus on organic matter structure and its interaction with the pore space of shales during hydrocarbon generation and report some new results. Collected rock samples from Domanic horizon of South-Tatar arch were heated in the pyrolyzer to temperatures closely corresponding to different catagenesis stages. X-ray microtomography method and SEM were used to monitor changes in the morphology of the pore space and organic matter structure within studied shale rocks. By routine measurements we made sure that all samples (10 in total) had similar composition of organic and mineral phases. All samples in the collection were grouped according to initial structure and amount of organics and processed separately to: 1) study the influence of organic matter content on the changing morphology of the rock under thermal effects; 2) study the effect of initial structure on the primary migration processes for samples with similar organic matter content. An additional experiment was conducted to study the dynamics of changes in the structure of the pore space and prove the validity of our approach. At each stage of heating the morphology of altered rocks was characterized by formation of new pores and channels connecting primary voids. However, it was noted that the samples with a relatively low content of the organic matter had less changes in pore space morphology, in contrast to rocks with a high organic content. Second part of the study also revealed significant differences in resulting pore structures depending on initial structure of the unaltered rocks and connectivity of original organics. Significant changes in the structure of the pore space were observed during the sequential heating in the range from 260 C to 430 C, which corresponds to the most intense stage of the hydrocarbons formation. This work was partially supported by RSF grant 14-17-00658.

KSC-07pd3395

NASA Image and Video Library

2007-11-19

KENNEDY SPACE CENTER, FLA. -- The space shuttle Atlantis STS-122 crew receives instruction on slidewire basket operation, part of the emergency exit system on the fixed service structure on Launch Pad 39A. Here, Mission Specialist Rex Walheim practices getting out of one of the baskets as Mission Specialists Leopold Eyharts and Leland Melvin steady it. Seven slidewire baskets are available to carry the crew from the level of the pad's Orbiter Access Arm to this landing site, if needed. Each basket can hold up to three people. A braking system catch net and drag chain slow, and then halt, the baskets as they travel down the wire at approximately 55 miles per hour. The journey takes about half a minute. A bunker is located in the landing zone 1,200 feet west of the pad, with an M-113 armored personnel carrier stationed nearby. The STS-122 crew is at NASA's Kennedy Space Center to take part in terminal countdown demonstration test, or TCDT, activities, a standard part of launch preparations. The TCDT provides astronauts and ground crews with equipment familiarization and a simulated launch countdown before launch. On mission STS-122, Atlantis will deliver the European Space Agency's Columbus module to the International Space Station. Columbus is a multifunctional, pressurized laboratory that will be permanently attached to U.S. Node 2, called Harmony, and will expand the research facilities aboard the station. Launch is targeted for Dec. 6. Photo credit: NASA/Kim Shiflett

KSC-07pd3392

NASA Image and Video Library

2007-11-19

KENNEDY SPACE CENTER, FLA. -- The space shuttle Atlantis STS-122 crew receives instruction on slidewire basket operation, part of the emergency exit system on the fixed service structure on Launch Pad 39A. Seen here near the catch nets in the landing zone are, from left, Mission Specialists Leopold Eyharts, Hans Schlegel and Rex Walheim; Commander Steve Frick; Mission Specialists Stanley Love and Leland Melvin; and Pilot Alan Poindexter. Seven slidewire baskets are available to carry the crew from the level of the pad's Orbiter Access Arm to this landing site, if needed. Each basket can hold up to three people. A braking system catch net and drag chain slow, and then halt, the baskets as they travel down the wire at approximately 55 miles per hour. The journey takes about half a minute. A bunker is located in the landing zone 1,200 feet west of the pad, with an M-113 armored personnel carrier stationed nearby. The STS-122 crew is at NASA's Kennedy Space Center to take part in terminal countdown demonstration test, or TCDT, activities, a standard part of launch preparations. The TCDT provides astronauts and ground crews with equipment familiarization and a simulated launch countdown before launch. On mission STS-122, Atlantis will deliver the European Space Agency's Columbus module to the International Space Station. Columbus is a multifunctional, pressurized laboratory that will be permanently attached to U.S. Node 2, called Harmony, and will expand the research facilities aboard the station. Launch is targeted for Dec. 6. Photo credit: NASA/Kim Shiflett

KSC-07pd3393

NASA Image and Video Library

2007-11-19

KENNEDY SPACE CENTER, FLA. -- The space shuttle Atlantis STS-122 crew receives instruction on slidewire basket operation, part of the emergency exit system on the fixed service structure on Launch Pad 39A. From left, Mission Specialists Stanley Love and Hans Schlegel and Commander Steve Frick gain first-hand experience inside one of the baskets. Seven slidewire baskets are available to carry the crew from the level of the pad's Orbiter Access Arm to this landing site, if needed. Each basket can hold up to three people. A braking system catch net and drag chain slow, and then halt, the baskets as they travel down the wire at approximately 55 miles per hour. The journey takes about half a minute. A bunker is located in the landing zone 1,200 feet west of the pad, with an M-113 armored personnel carrier stationed nearby. The STS-122 crew is at NASA's Kennedy Space Center to take part in terminal countdown demonstration test, or TCDT, activities, a standard part of launch preparations. The TCDT provides astronauts and ground crews with equipment familiarization and a simulated launch countdown before launch. On mission STS-122, Atlantis will deliver the European Space Agency's Columbus module to the International Space Station. Columbus is a multifunctional, pressurized laboratory that will be permanently attached to U.S. Node 2, called Harmony, and will expand the research facilities aboard the station. Launch is targeted for Dec. 6. Photo credit: NASA/Kim Shiflett

KSC-06pd0924

NASA Image and Video Library

2006-05-23

KENNEDY SPACE CENTER, FLA. -- From inside the payload changeout room on the rotating service structure on Launch Pad 39B, the multi-purpose logistics module Leonardo is being moved into Space Shuttle Discovery's payload bay. The payload ground-handling mechanism (PGHM) is used to transfer the module into the payload bay. Leonardo is a reusable logistics carrier. It is the primary delivery system used to resupply and return station cargo requiring a pressurized environment. Leonardo is part of the payload on mission STS-121. Other payloads include the integrated cargo carrier with the mobile transporter reel assembly and a spare pump module, and the lightweight multi-purpose experiment support structure carrier. Discovery is scheduled to launch in a window extending from July 1 through July 19. Photo credit: NASA/Jack Pfaller

KSC-06pd0927

NASA Image and Video Library

2006-05-23

KENNEDY SPACE CENTER, FLA. -- From inside the payload changeout room on the rotating service structure on Launch Pad 39B, the multi-purpose logistics module Leonardo is lowered into Space Shuttle Discovery's payload bay. The payload ground-handling mechanism (PGHM) is used to transfer the module into the payload bay. Leonardo is a reusable logistics carrier. It is the primary delivery system used to resupply and return station cargo requiring a pressurized environment. Leonardo is part of the payload on mission STS-121. Other payloads include the integrated cargo carrier with the mobile transporter reel assembly and a spare pump module, and the lightweight multi-purpose experiment support structure carrier. Discovery is scheduled to launch in a window extending from July 1 through July 19. Photo credit: NASA/Jack Pfaller

In-Flight Suppression of a De-Stabilized F/A-18 Structural Mode Using the Space Launch System Adaptive Augmenting Control System

NASA Technical Reports Server (NTRS)

Wall, John; VanZwieten, Tannen; Giiligan Eric; Miller, Chris; Hanson, Curtis; Orr, Jeb

2015-01-01

Adaptive Augmenting Control (AAC) has been developed for NASA's Space Launch System (SLS) family of launch vehicles and implemented as a baseline part of its flight control system (FCS). To raise the technical readiness level of the SLS AAC algorithm, the Launch Vehicle Adaptive Control (LVAC) flight test program was conducted in which the SLS FCS prototype software was employed to control the pitch axis of Dryden's specially outfitted F/A-18, the Full Scale Advanced Systems Test Bed (FAST). This presentation focuses on a set of special test cases which demonstrate the successful mitigation of the unstable coupling of an F/A-18 airframe structural mode with the SLS FCS.

A deformable spherical planet exploration robot

NASA Astrophysics Data System (ADS)

Liang, Yi-shan; Zhang, Xiu-li; Huang, Hao; Yang, Yan-feng; Jin, Wen-tao; Sang, Zhong-xun

2013-03-01

In this paper, a deformable spherical planet exploration robot has been introduced to achieve the task of environmental detection in outer space or extreme conditions. The robot imitates the morphology structure and motion mechanism of tumbleweeds. The robot is wind-driven. It consists of an axle, a spherical steel skeleton and twelve airbags. The axle is designed as two parts. The robot contracts by contracting the two-part axle. The spherical robot installs solar panels to provide energy for its control system.

Gateway: An earth orbiting transportation node

NASA Technical Reports Server (NTRS)

1988-01-01

University of Texas Mission Design (UTMD) has outlined the components that a space based transportation facility must include in order to support the first decade of Lunar base buildup. After studying anticipated traffic flow to and from the hub, and taking into account crew manhour considerations, propellant storage, orbital transfer vehicle maintenance requirements, and orbital mechanics, UTMD arrived at a design for the facility. The amount of activity directly related to supporting Lunar base traffic is too high to allow the transportation hub to be part of the NASA Space Station. Instead, a separate structure should be constructed and dedicated to handling all transportation-related duties. UTMD found that the structure (named Gateway) would need a permanent crew of four to perform maintenance tasks on the orbital transfer and orbital maneuvering vehicles and to transfer payload from launch vehicles to the orbital transfer vehicles. In addition, quarters for 4 more persons should be allocated for temporary accommodation of Lunar base crew passing through Gateway. UTMD was careful to recommend an expendable structure that can adapt to meet the growing needs of the American space program.

A structured overview of trends and technologies used in dynamic hand orthoses.

PubMed

Bos, Ronald A; Haarman, Claudia J W; Stortelder, Teun; Nizamis, Kostas; Herder, Just L; Stienen, Arno H A; Plettenburg, Dick H

2016-06-29

The development of dynamic hand orthoses is a fast-growing field of research and has resulted in many different devices. A large and diverse solution space is formed by the various mechatronic components which are used in these devices. They are the result of making complex design choices within the constraints imposed by the application, the environment and the patient's individual needs. Several review studies exist that cover the details of specific disciplines which play a part in the developmental cycle. However, a general collection of all endeavors around the world and a structured overview of the solution space which integrates these disciplines is missing. In this study, a total of 165 individual dynamic hand orthoses were collected and their mechatronic components were categorized into a framework with a signal, energy and mechanical domain. Its hierarchical structure allows it to reach out towards the different disciplines while connecting them with common properties. Additionally, available arguments behind design choices were collected and related to the trends in the solution space. As a result, a comprehensive overview of the used mechatronic components in dynamic hand orthoses is presented.

Fascial reinforcement fixing the bronchi to the heart: its anatomy and clinical significance.

PubMed

Nakanishi, Kozo; Goto, Hidenori; Ito, Tomokazu

2017-12-01

The details of the mediastinal fascia have been scarcely described and the bronchopericardial membrane is the only known structure that is present between the bronchi and the pericardium. However, the anatomical description of this structure is unclear. This study aimed to investigate the fascial structures between the bronchi and the pericardium based on surgical findings. The connective tissues in the mid-mediastinum were observed surgically when lung lobectomy, including mediastinal lymph node dissection for lung cancer, was performed at our institute from April 2011 to March 2016. In total, 96 lobectomies were performed in 94 patients. A firm fibrous structure connecting the tracheobronchus and the fibrous pericardium was observed. It fixes the central bronchi to the pericardium and is composed of three parts. The largest part exists in front of the carina, its appearance is membranous, and runs behind the pulmonary artery. The other parts run over the right pulmonary artery and diverge at its superior trunk. The location at which all these structures fuse to the pericardium is the venous part of the hilum cordis (VHC). The results showed that connections of the dense fibrous tissues existed between the tracheobronchus and VHC. The structure not only works as a ligament that fixes the bronchi to the mid-mediastinum, but also divides the mid-mediastinum into two compartments: the Baréty and subcarinal spaces. The anatomy of the structure observed in this study differs from the previous description of the bronchopericardial membrane.

KSC-07pd1362

NASA Image and Video Library

2007-06-04

KENNEDY SPACE CENTER, FLA. -- After their arrival at KSC, STS-117 crew members take part in a payload bay walkdown on Launch Pad 39A to look at the cargo in Space Shuttle Atlantis. In the bucket are Mission Specialists Patrick Forrester (with camera) and Steven Swanson (far right). The payload includes the S3/S4 integrated truss structure for the International Space Station. STS-117 is scheduled to launch at 7:38 p.m. June 8. During the 11-day mission and three spacewalks, the crew will work with flight controllers at NASA's Johnson Space Center in Houston to install the 17-ton segment on the station's girder-like truss and deploy the set of solar arrays, S3/S4. The mission will increase the space station's power capability in preparation for the arrival of new science modules from the European and Japanese space agencies. Photo credit: NASA/Kim Shiflett

STS-92 crew takes part in a Leak Seal Kit Fit Check in the SSPF

NASA Technical Reports Server (NTRS)

1999-01-01

In the Space Station Processing Facility, STS-92 crew members discuss the Pressurized Mating Adapter -3 (PMA-3), in the background, with Boeing workers. From left are Pilot Pamela A. Melroy and Mission Specialists Koichi Wakata, who represents the National Space Development Agency of Japan (NASDA), and Peter J.K. 'Jeff' Wisoff (Ph.D.). The STS-92 crew are taking part in a Leak Seal Kit Fit Check in connection with the PMA-3. Other crew members participating are Commander Brian Duffy and Mission Specialists Leroy Chiao (Ph.D.), Michael E. Lopez-Alegria and William Surles 'Bill' McArthur Jr. The mission payload also includes an integrated truss structure (Z-1 truss). Launch of STS-92 is scheduled for Feb. 24, 2000.

STS-92 crew takes part in a Leak Seal Kit Fit Check in the SSPF

NASA Technical Reports Server (NTRS)

1999-01-01

In the Space Station Processing Facility, STS-92 crew members discuss the Pressurized Mating Adapter -3 in the background with workers from Boeing. At the far left is Mission Specialist William Surles 'Bill' McArthur Jr.; facing the camera are Pilot Pamela A. Melroy and Mission Specialist Koichi Wakata, who represents the National Space Development Agency of Japan (NASDA). Also participating are other crew members Commander Brian Duffy and Mission Specialists Leroy Chiao (Ph.D.), Peter J.K. 'Jeff' Wisoff (Ph.D.), Michael E. Lopez-Alegria and William Surles 'Bill' McArthur Jr. The crew are taking part in a Leak Seal Kit Fit Check. The mission payload also includes an integrated truss structure (Z-1 truss). Launch of STS-92 is scheduled for Feb. 24, 2000.

STS-92 crew takes part in a Leak Seal Kit Fit Check in the SSPF

NASA Technical Reports Server (NTRS)

1999-01-01

In the Space Station Processing Facility, STS-92 crew members discuss the Pressurized Mating Adapter -3 (PMA-3) in the background with Boeing workers. From left are Pilot Pamela A. Melroy and Mission Specialists Koichi Wakata, who represents the National Space Development Agency of Japan (NASDA), and Peter J.K. 'Jeff' Wisoff (Ph.D.). The STS-92 crew are taking part in a Leak Seal Kit Fit Check in connection with the PMA-3. Other crew members participating are Commander Brian Duffy and Mission Specialists Leroy Chiao (Ph.D.), Michael E. Lopez-Alegria and William Surles 'Bill' McArthur Jr. The mission payload also includes an integrated truss structure (Z-1 truss). Launch of STS-92 is scheduled for Feb. 24, 2000.

The novel support structure design of high stability for space borne primary reflector

NASA Astrophysics Data System (ADS)

Yu, Fei; Ding, Lin; Tan, Ting; Pei, Jing-yang.; Zhao, Xue-min; Bai, Shao-jun

2018-01-01

The novel support structure design of high stability for space borne primary mirror is presented. The structure is supported by a ball head support rod, for statically determinate support of reflector. The ball head assembly includes the supporting rod, nesting, bushing and other important parts. The liner bushing of the resistant material is used to fit for ball head approximated with the reflector material, and then the bad impact of thermal mismatch could be minimized to minimum. In order to ensure that the structure of the support will not be damaged, the glue spots for limitation is added around the reflector, for position stability of reflector. Through analysis and calculation, it can be seen that the novel support structure would not transfer the external stresses to the reflector, and the external stresses usually result from thermal mismatch and assembly misalignment. The novel method is useful for solving the problem of the bad influence form thermal stress and assembly force. In this paper, the supporting structure is introduced and analyzed in detail. The simulation results show that the ball head support reflector works more stably.

Post-Flight Estimation of Motion of Space Structures: Part 2

NASA Technical Reports Server (NTRS)

Brugarolas, Paul; Breckenridge, William

2008-01-01

A computer program related to the one described in the immediately preceding article estimates the relative position of two space structures that are hinged to each other. The input to the program consists of time-series data on distances, measured by two range finders at different positions on one structure, to a corner-cube retroreflector on the other structure. Given a Cartesian (x,y,z) coordinate system and the known x coordinate of the retroreflector relative to the y,z plane that contains the range finders, the program estimates the y and z coordinates of the retroreflector. The estimation process involves solving for the y,z coordinates of the intersection between (1) the y,z plane that contains the retroreflector and (2) spheres, centered on the range finders, having radii equal to the measured distances. In general, there are two such solutions and the program chooses the one consistent with the design of the structures. The program implements a Kalman filter. The output of the program is a time series of estimates of the relative position of the structures.

The Ecosystems SAR (EcoSAR) an Airborne P-band Polarimetric InSAR for the Measurement of Vegetation Structure, Biomass and Permafrost

NASA Technical Reports Server (NTRS)

Rincon, Rafael F.; Fatoyinbo, Temilola; Ranson, K. Jon; Osmanoglu, Batuhan; Sun, Guoqing; Deshpande, Manohar D.; Perrine, Martin L.; Du Toit, Cornelis F.; Bonds, Quenton; Beck, Jaclyn;

CuLi2Sn and Cu2LiSn: Characterization by single crystal XRD and structural discussion towards new anode materials for Li-ion batteries.

PubMed

Fürtauer, Siegfried; Effenberger, Herta S; Flandorfer, Hans

2014-12-01

The stannides CuLi 2 Sn (CSD-427095) and Cu 2 LiSn (CSD-427096) were synthesized by induction melting of the pure elements and annealing at 400 °C. The phases were reinvestigated by X-ray powder and single-crystal X-ray diffractometry. Within both crystal structures the ordered CuSn and Cu 2 Sn lattices form channels which host Cu and Li atoms at partly mixed occupied positions exhibiting extensive vacancies. For CuLi 2 Sn, the space group F-43m. was verified (structure type CuHg 2 Ti; a =6.295(2) Å; wR 2 ( F ²)=0.0355 for 78 unique reflections). The 4( c ) and 4( d ) positions are occupied by Cu atoms and Cu+Li atoms, respectively. For Cu 2 LiSn, the space group P 6 3 / mmc was confirmed (structure type InPt 2 Gd; a =4.3022(15) Å, c =7.618(3) Å; wR 2 ( F ²)=0.060 for 199 unique reflections). The Cu and Li atoms exhibit extensive disorder; they are distributed over the partly occupied positions 2( a ), 2( b ) and 4( e ). Both phases seem to be interesting in terms of application of Cu-Sn alloys as anode materials for Li-ion batteries.

Tree-space statistics and approximations for large-scale analysis of anatomical trees.

PubMed

Feragen, Aasa; Owen, Megan; Petersen, Jens; Wille, Mathilde M W; Thomsen, Laura H; Dirksen, Asger; de Bruijne, Marleen

2013-01-01

Statistical analysis of anatomical trees is hard to perform due to differences in the topological structure of the trees. In this paper we define statistical properties of leaf-labeled anatomical trees with geometric edge attributes by considering the anatomical trees as points in the geometric space of leaf-labeled trees. This tree-space is a geodesic metric space where any two trees are connected by a unique shortest path, which corresponds to a tree deformation. However, tree-space is not a manifold, and the usual strategy of performing statistical analysis in a tangent space and projecting onto tree-space is not available. Using tree-space and its shortest paths, a variety of statistical properties, such as mean, principal component, hypothesis testing and linear discriminant analysis can be defined. For some of these properties it is still an open problem how to compute them; others (like the mean) can be computed, but efficient alternatives are helpful in speeding up algorithms that use means iteratively, like hypothesis testing. In this paper, we take advantage of a very large dataset (N = 8016) to obtain computable approximations, under the assumption that the data trees parametrize the relevant parts of tree-space well. Using the developed approximate statistics, we illustrate how the structure and geometry of airway trees vary across a population and show that airway trees with Chronic Obstructive Pulmonary Disease come from a different distribution in tree-space than healthy ones. Software is available from http://image.diku.dk/aasa/software.php.

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

NASA Image and Video Library

2016-10-13

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

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

NASA Image and Video Library

2016-10-13

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

Public Spaces as the Reflection of Society and its Culture

NASA Astrophysics Data System (ADS)

Siláči, Ivan; Vitková, L.'ubica

2017-10-01

Spatial structure of places has gone through significant changes in the last 70 years, caused by modernistic approach towards urban design. This approach has brought retraction from traditional spatial form and has started introducing free form design of urban spaces since the 1960’s. Tighter urban structure has started to be applied since the 1980’s, but in a less significant way than in other developed European countries, as a result of starting mass-housing period. However modernistic approach legacy is quite heavily maintained and present in our cities. Single-use commercial areas and family-house “landscapes” located mostly on the outside of city border represent the mentioned system. In those structures, a man usually identifies himself with his own house or apartment rather than with space that commonly surrounds him. Therefore, the role of spaces, their image perceived by men and their character is more and more important. Supporting the distinctive individual character of a city and its places and the identification with districts is fundamental. Urban resident and occupant identify himself with the city and urban environment via arrangement of spaces. Social sustainability is an integral part of the effective urban development. Quality of public spaces, which support the city of neighborhoods, vibrant city and short distance city are the important pillars of sustainability. Cultural environment and the sense of place is another important dimension of sustainability. The paper is focused on mapping and evaluation of the public spaces in Bratislava with the emphasis of their social development and cultural value, as factors of their identity.

KSC-99pp0407

NASA Image and Video Library

1999-04-08

KENNEDY SPACE CENTER, FLA. -- The newly added Robot Scouts exhibit at the KSC Visitor Complex is situated next to the Rocket Garden. Part of the $13 million expansion to the Visitor Complex, the exhibit helps describe for visitors the accomplishments of unsung space heroes space probes and their role in space exploration. It also includes a display of how data from robotic probes might be used to build a human habitat for Mars. Visitors can witness a simulated Martian sunset. Other additions include a new foyer, films, and an International Space Station-themed ticket plaza, featuring a structure of overhanging solar panels and astronauts performing assembly tasks. The KSC Visitor Complex was inaugurated three decades ago and is now one of the top five tourist attractions in Florida. It is located on S.R. 407, east of I-95, within the Merritt Island National Wildlife Refuge

14 CFR 31.43 - Fitting factor.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Fitting factor. 31.43 Section 31.43... STANDARDS: MANNED FREE BALLOONS Design Construction § 31.43 Fitting factor. (a) A fitting factor of at least... structure. This factor applies to all parts of the fitting, the means of attachment, and the bearing on the...

14 CFR 27.619 - Special factors.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Special factors. 27.619 Section 27.619... STANDARDS: NORMAL CATEGORY ROTORCRAFT Design and Construction General § 27.619 Special factors. (a) The special factors prescribed in §§ 27.621 through 27.625 apply to each part of the structure whose strength...

14 CFR 29.619 - Special factors.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Special factors. 29.619 Section 29.619... STANDARDS: TRANSPORT CATEGORY ROTORCRAFT Design and Construction General § 29.619 Special factors. (a) The special factors prescribed in §§ 29.621 through 29.625 apply to each part of the structure whose strength...

14 CFR 23.619 - Special factors.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Special factors. 23.619 Section 23.619... Special factors. The factor of safety prescribed in § 23.303 must be multiplied by the highest pertinent special factors of safety prescribed in §§ 23.621 through 23.625 for each part of the structure whose...

Boeing CST-100 Heat Shield Testing

NASA Image and Video Library

2017-05-31

A heat shield is used during separation test activities with Boeing's Starliner structural test article. The test article is undergoing rigorous qualification testing at the company's Huntington Beach Facility in California. Boeing’s CST-100 Starliner will launch on the Atlas V rocket to the International Space Station as part of NASA’s Commercial Crew Program.

USSR and Eastern Europe Scientific Abstracts, Geophysics, Astronomy and Space, Number 388

DTIC Science & Technology

1977-01-18

Andromeda and then using data for over 100 other systems. It was possible to clarify in great detail the structure of the most interesting galaxies of...Galaxy and the nebula Andromeda constitute parts of a common hypergalaxy. The observatory has a new 1.5-m telescope. It will enable Tyravere

Microgravity

NASA Image and Video Library

2000-04-20

Edward Snell, a National Research Council research fellow at NASA's Marshall Space Flight Center (MSFC), prepares a protein crystal for analysis by x-ray crystallography as part of NASA's structural biology program. The small, individual crystals are bombarded with x-rays to produce diffraction patterns, a map of the intensity of the x-rays as they reflect through the crystal.

The 25 kW power module evolution study. Part 3: Conceptual designs for power module evolution. Volume 4: Design analyses

NASA Technical Reports Server (NTRS)

1979-01-01

Topics covered include growth options evaluation, mass properties, attitude control and structural dynamics, contamination evaluation, berthing concepts, orbit reboost options and growth kit concepts. Systems support elements and space support equipment are reviewed with emphasis on power module operations and technology planning.

14 CFR 23.251 - Vibration and buffeting.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 1 2011-01-01 2011-01-01 false Vibration and buffeting. 23.251 Section 23... Requirements § 23.251 Vibration and buffeting. There must be no vibration or buffeting severe enough to result in structural damage, and each part of the airplane must be free from excessive vibration, under any...

14 CFR 23.251 - Vibration and buffeting.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Vibration and buffeting. 23.251 Section 23... Requirements § 23.251 Vibration and buffeting. There must be no vibration or buffeting severe enough to result in structural damage, and each part of the airplane must be free from excessive vibration, under any...

Decentralized Control of a Large Space Structure as Applied to the CSDL 2 Model.

DTIC Science & Technology

1982-12-01

and are arranged by their respective controller assignments. The individual modes may be identified by the imaginary parts of the eigen- values, as...August 1958 to Phillip Z. and Hanako Y. Aldridge in Johnson Air Force Base, Japan. After a childhood in the United States, he returned to Japan

Space Shuttle Technical Conference, Part 2

NASA Technical Reports Server (NTRS)

Chaffee, Norman (Compiler)

1985-01-01

The retrospective presentation provides technical disciplinary focus in the following technical areas: (1) integrated avionics; (2) guidance, navigation, and control; (3) aerodynamics; (4) structures; (5) life support, environmental control, and crew station; (6) ground operations; (7) propulsion and power; (8) communications and tracking; (9) mechanics and mechanical systems; and (10) thermal and contamination environments and protection systems.

History of Chandra X-Ray Observatory

NASA Image and Video Library

1999-09-01

After barely 2 months in space, the Chandra X-Ray Observatory (CXO) took this sturning image of the Crab Nebula, the spectacular remains of a stellar explosion, revealing something never seen before, a brilliant ring around the nebula's heart. The image shows the central pulsar surrounded by tilted rings of high-energy particles that appear to have been flung outward over a distance of more than a light-year from the pulsar. Perpendicular to the rings, jet-like structures produced by high-energy particles blast away from the pulsar. Hubble Space Telescope images have shown moving knots and wisps around the neutron star, and previous x-ray images have shown the outer parts of the jet and hinted at the ring structure. With CXO's exceptional resolution, the jet can be traced all the way in to the neutron star, and the ring pattern clearly appears. The image was made with CXO's Advanced Charge-Coupled Device (CCD) Imaging Spectrometer (ACIS) and High Energy Transmission Grating. The Crab Nebula, easily the most intensively studied object beyond our solar system, has been observed using virtually every astronomical instrument that could see that part of the sky

Unstable flow structures in the Blasius boundary layer.

PubMed

Wedin, H; Bottaro, A; Hanifi, A; Zampogna, G

2014-04-01

Finite amplitude coherent structures with a reflection symmetry in the spanwise direction of a parallel boundary layer flow are reported together with a preliminary analysis of their stability. The search for the solutions is based on the self-sustaining process originally described by Waleffe (Phys. Fluids 9, 883 (1997)). This requires adding a body force to the Navier-Stokes equations; to locate a relevant nonlinear solution it is necessary to perform a continuation in the nonlinear regime and parameter space in order to render the body force of vanishing amplitude. Some states computed display a spanwise spacing between streaks of the same length scale as turbulence flow structures observed in experiments (S.K. Robinson, Ann. Rev. Fluid Mech. 23, 601 (1991)), and are found to be situated within the buffer layer. The exact coherent structures are unstable to small amplitude perturbations and thus may be part of a set of unstable nonlinear states of possible use to describe the turbulent transition. The nonlinear solutions survive down to a displacement thickness Reynolds number Re * = 496 , displaying a 4-vortex structure and an amplitude of the streamwise root-mean-square velocity of 6% scaled with the free-stream velocity. At this Re* the exact coherent structure bifurcates supercritically and this is the point where the laminar Blasius flow starts to cohabit the phase space with alternative simple exact solutions of the Navier-Stokes equations.

Neutral Buoyancy Simulator-NB32-Assembly of Large Space Structure

NASA Technical Reports Server (NTRS)

1980-01-01

Once the United States' space program had progressed from Earth's orbit into outerspace, theprospect of building and maintaining a permanent presence in space was realized. To accomplish this feat, NASA launched a temporary workstation, Skylab, to discover the effects of low gravity and weightlessness on the human body, and also to develop tools and equipment that would be needed in the future to build and maintain a more permanent space station. The structures, techniques, and work schedules had to be carefully designed to fit this unique construction site. The components had to be lightweight for transport into orbit, yet durable. The station also had to be made with removable parts for easy servicing and repairs by astronauts. All of the tools necessary for service and repairs had to be designed for easy manipulation by a suited astronaut. Construction methods had to be efficient due to the limited time the astronauts could remain outside their controlled environment. In lieu of all the specific needs for this project, an environment on Earth had to be developed that could simulate a low gravity atmosphere. A Neutral Buoyancy Simulator (NBS) was constructed by NASA's Marshall Space Flight Center (MSFC) in 1968. Since then, NASA scientists have used this facility to understand how humans work best in low gravity and also provide information about the different kinds of structures that can be built. Pictured is a Massachusetts Institute of Technology (MIT) student working in a spacesuit on the Experimental Assembly of Structures in Extravehicular Activity (EASE) project which was developed as a joint effort between MFSC and MIT. The EASE experiment required that crew members assemble small components to form larger components, working from the payload bay of the space shuttle. The MIT student in this photo is assembling two six-beam tetrahedrons.

KSC-2011-5181

NASA Image and Video Library

2011-07-07

CAPE CANAVERAL, Fla. -- At Launch Pad 39A at NASA's Kennedy Space Center in Florida space shuttle Atlantis is reflected in a pond near the pad after the retraction of the rotating service structure (RSS). The structure provides weather protection and access to the shuttle while it awaits liftoff on the pad. RSS retract marks a major milestone in Atlantis' STS-135 mission countdown. Atlantis and its crew of four; Commander Chris Ferguson, Pilot Doug Hurley, Mission Specialists Sandy Magnus and Rex Walheim will lift off at 11:26 a.m. EDT on July 8 to deliver the Raffaello multi-purpose logistics module packed with supplies and spare parts for the International Space Station. Atlantis also will fly the Robotic Refueling Mission experiment that will investigate the potential for robotically refueling existing satellites in orbit. In addition, Atlantis will return with a failed ammonia pump module to help NASA better understand the failure mechanism and improve pump designs for future systems. STS-135 is the 33rd flight of Atlantis, the 37th shuttle mission to the space station, and the 135th and final mission of NASA's Space Shuttle Program. For more information, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts135/index.html. Photo credit: Jim Grossmann

KSC-2011-5182

NASA Image and Video Library

2011-07-07

CAPE CANAVERAL, Fla. -- At Launch Pad 39A at NASA's Kennedy Space Center in Florida space shuttle Atlantis is reflected in a pond near the pad after the retraction of the rotating service structure (RSS). The structure provides weather protection and access to the shuttle while it awaits liftoff on the pad. RSS retract marks a major milestone in Atlantis' STS-135 mission countdown. Atlantis and its crew of four; Commander Chris Ferguson, Pilot Doug Hurley, Mission Specialists Sandy Magnus and Rex Walheim will lift off at 11:26 a.m. EDT on July 8 to deliver the Raffaello multi-purpose logistics module packed with supplies and spare parts for the International Space Station. Atlantis also will fly the Robotic Refueling Mission experiment that will investigate the potential for robotically refueling existing satellites in orbit. In addition, Atlantis will return with a failed ammonia pump module to help NASA better understand the failure mechanism and improve pump designs for future systems. STS-135 is the 33rd flight of Atlantis, the 37th shuttle mission to the space station, and the 135th and final mission of NASA's Space Shuttle Program. For more information, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts135/index.html. Photo credit: Jim Grossmann

Cases for Additive Manufacturing on the International Space Station

NASA Technical Reports Server (NTRS)

Cooper, Kenneth G.; McLemore, Carole; Anderson, Theodore " Ted"

2012-01-01

There are thousands of plastic or non-structural metal components on the International Space Station (ISS), any of which could require replacing sometime between resupply missions. While these may not be life critical, it can cause significant delays to flight projects that have to wait several weeks to months to receive a key part one that could have been designed and built on-board the ISS within a few hours. A plastic deposition additive manufacturing process is a low-energy, low-mass solution to many common needs on board the ISS.

What is dorso-lateral in the subthalamic Nucleus (STN)?--a topographic and anatomical consideration on the ambiguous description of today's primary target for deep brain stimulation (DBS) surgery.

PubMed

Coenen, Volker A; Prescher, Andreas; Schmidt, Thorsten; Picozzi, Piero; Gielen, Frans L H

2008-11-01

The most frequently used target for DBS in advanced Parkinson Disease (PD) is the sensorimotor subthalamic nucleus (STN), anatomically referred to as dorso-lateral STN [3]. Ambiguities arise, regarding the true meaning of this description in the STN. Does "dorsal" indicate posterior or superior? At its best, this definition assigns two directions in space to a three-dimensional structure. This paper evaluates the ambiguity and describes the sensorimotor part of the STN in stereotactic space.

KSC-06pd2359

NASA Image and Video Library

2006-10-14

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, STS-116 Pilot William Oefelein checks the cockpit window of Discovery as part of a Crew Equipment Interface Test (CEIT). A CEIT allows astronauts to become familiar with equipment and hardware they will use on the mission. STS-116 will be mission No. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Kim Shiflett

KSC-06pd2358

NASA Image and Video Library

2006-10-14

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, STS-116 Commander Mark Polansky checks the cockpit window of Discovery as part of a Crew Equipment Interface Test (CEIT). A CEIT allows astronauts to become familiar with equipment and hardware they will use on the mission. STS-116 will be mission No. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Kim Shiflett

KSC-06pd2357

NASA Image and Video Library

2006-10-14

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, STS-116 Commander Mark Polansky checks the cockpit window as part of a Crew Equipment Interface Test (CEIT). A CEIT allows astronauts to become familiar with equipment and hardware they will use on the mission. STS-116 will be mission No. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Kim Shiflett

KSC-06pd2360

NASA Image and Video Library

2006-10-14

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, STS-116 Pilot William Oefelein checks the cockpit window of Discovery as part of a Crew Equipment Interface Test (CEIT). A CEIT allows astronauts to become familiar with equipment and hardware they will use on the mission. STS-116 will be mission No. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Kim Shiflett

KSC-2009-3797

NASA Image and Video Library

2009-06-20

CAPE CANAVERAL, Fla. – The slings from a large crane are being attached to the orbiter access arm, which ends in the White Room, that is part of the fixed service structure, or FSS, on Launch Pad 39B at NASA's Kennedy Space Center in Florida. The White Room provided entry into space shuttles that were on the pad. The arm is being removed from the FSS for the pad's conversion as launch site for the Constellation Program's Ares I-X. The launch of the Ares I-X flight test is targeted for August 2009. Photo credit: NASA/Kim Shiflett

KSC-2009-3800

NASA Image and Video Library

2009-06-20

CAPE CANAVERAL, Fla. – The slings from a large crane are in place on the orbiter access arm, which ends in the White Room, that is part of the fixed service structure, or FSS, on Launch Pad 39B at NASA's Kennedy Space Center in Florida. The White Room provided entry into space shuttles that were on the pad. The arm is being removed from the FSS for the pad's conversion as launch site for the Constellation Program's Ares I-X. The launch of the Ares I-X flight test is targeted for August 2009. Photo credit: NASA/Kim Shiflett

KSC-2009-3799

NASA Image and Video Library

2009-06-20

CAPE CANAVERAL, Fla. – The slings from a large crane are in place on the orbiter access arm, which ends in the White Room, that is part of the fixed service structure, or FSS, on Launch Pad 39B at NASA's Kennedy Space Center in Florida. The White Room provided entry into space shuttles that were on the pad. The arm is being removed from the FSS for the pad's conversion as launch site for the Constellation Program's Ares I-X. The launch of the Ares I-X flight test is targeted for August 2009. Photo credit: NASA/Kim Shiflett

KSC-2009-3798

NASA Image and Video Library

2009-06-20

CAPE CANAVERAL, Fla. – The slings from a large crane are being attached to the orbiter access arm, which ends in the White Room, that is part of the fixed service structure, or FSS, on Launch Pad 39B at NASA's Kennedy Space Center in Florida. The White Room provided entry into space shuttles that were on the pad. The arm is being removed from the FSS for the pad's conversion as launch site for the Constellation Program's Ares I-X. The launch of the Ares I-X flight test is targeted for August 2009. Photo credit: NASA/Kim Shiflett

Method and apparatus for fabrication of high gradient insulators with parallel surface conductors spaced less than one millimeter apart

DOEpatents

Sanders, David M.; Decker, Derek E.

1999-01-01

Optical patterns and lithographic techniques are used as part of a process to embed parallel and evenly spaced conductors in the non-planar surfaces of an insulator to produce high gradient insulators. The approach extends the size that high gradient insulating structures can be fabricated as well as improves the performance of those insulators by reducing the scale of the alternating parallel lines of insulator and conductor along the surface. This fabrication approach also substantially decreases the cost required to produce high gradient insulators.

Shuttle Experimental Radar for Geological Exploration (SERGE) project: Field work relating to the Shuttle Experimental Radar A (SIR-A) in Brazil (phase 2)

NASA Technical Reports Server (NTRS)

Balieiro, M. G.; Martini, P. R.; Dossantos, J. R.; Demattos, J. T.

1984-01-01

The ground observations undertaken over the northern position of Minas Gerais State, and part of Distrito Federal from 7 to 12 December 1982, along the Space Shuttle 2 flying orbit 22 of November 1981 are described. Field data related mostly with lithology, geological structures and forest cover, and specific geomorphological and pedological aspects were collected. Ground data are applied to evaluate the SIR-A Experiment, developed in the Space Shuttle-2 mission for natural resources mapping and prospecting.

Direct use of linear time-domain aerodynamics in aeroservoelastic analysis: Aerodynamic model

NASA Technical Reports Server (NTRS)

Woods, J. A.; Gilbert, Michael G.

1990-01-01

The work presented here is the first part of a continuing effort to expand existing capabilities in aeroelasticity by developing the methodology which is necessary to utilize unsteady time-domain aerodynamics directly in aeroservoelastic design and analysis. The ultimate objective is to define a fully integrated state-space model of an aeroelastic vehicle's aerodynamics, structure and controls which may be used to efficiently determine the vehicle's aeroservoelastic stability. Here, the current status of developing a state-space model for linear or near-linear time-domain indicial aerodynamic forces is presented.

Navier-Stokes structure of merged layer flow on the spherical nose of a space vehicle

NASA Technical Reports Server (NTRS)

Jain, A. C.; Woods, G. H.

1988-01-01

Hypersonic merged layer flow on the forepart of a spherical surface of a space vehicle has been investigated on the basis of the full steady-state Navier-Stokes equations using slip and temperature jump boundary conditions at the surface and free-stream conditions far from the surface. The shockwave-like structure was determined as part of the computations. Using an equivalent body concept, computations were carried out under conditions that the Aeroassist Flight Experiment (AFE) Vehicle would encounter at 15 and 20 seconds in its flight path. Emphasis was placed on understanding the basic nature of the flow structure under low density conditions. Particular attention was paid to the understanding of the structure of the outer shockwave-like region as the fluid expands around the sphere. Plots were drawn for flow profiles and surface characteristics to understand the role of dissipation processes in the merged layer of the spherical nose of the vehicle.

Physics of the Space Environment

NASA Astrophysics Data System (ADS)

Vasyliünas, Vytenis M.

This book, one in the Cambridge Atmospheric and Space Science Series, joins a growing list of advanced-level textbooks in a field of study and research known under a variety of names: space plasma physics, solar-terrestrial or solar-planetary relations, space weather, or (the official name of the relevant AGU section) space physics and aeronomy. On the basis of graduate courses taught by the author in various departments at the University of Michigan, complete with problems and with appendices of physical constants and mathematical identities, this is indeed a textbook, systematic and severe in its approach. The book is divided into three parts, in length ratios of roughly 6:4:5. Part I, “Theoretical Description of Gases and Plasmas,” starts by writing down Maxwell's equations and the Lorentz transformation (no nonsense about any introductory material of a descriptive or historical nature) and proceeds through particle orbit theory, kinetics, and plasma physics with fluid and MHD approximations to waves, shocks, and energetic particle transport. Part II, “The Upper Atmosphere,” features chapters on the terrestrial upper atmosphere, airglow and aurora, and the ionosphere. Part III, “Sun-Earth Connection,” deals with the Sun, the solar wind, cosmic rays, and the terrestrial magnetosphere. The book thus covers, with two exceptions, just about all the topics of interest to Space Physics and Aeronomy scientists, and then some (the chapter on the Sun, for instance, briefly discusses also topics of the solar interior: thermonuclear energy generation, equilibrium structure, energy transfer, with a page or two on each). One exception reflects a strong geocentric bias: there is not one word in the main text on magnetospheres and ionospheres of other planets and their interaction with the solar wind (they are mentioned in a few problems). The other exception: the chapter on the terrestrial magnetosphere lacks a systematic exposition of the theory of magnetosphereionosphere coupling.

Extremely high resolution 3D electrical resistivity tomography to depict archaeological subsurface structures

NASA Astrophysics Data System (ADS)

Al-Saadi, Osamah; Schmidt, Volkmar; Becken, Michael; Fritsch, Thomas

2017-04-01

Electrical resistivity tomography (ERT) methods have been increasingly used in various shallow depth archaeological prospections in the last few decades. These non-invasive techniques are very useful in saving time, costs, and efforts. Both 2D and 3D ERT techniques are used to obtain detailed images of subsurface anomalies. In two surveyed areas near Nonnweiler (Germany), we present the results of the full 3D setup with a roll-along technique and of the quasi-3D setup (parallel and orthogonal profiles in dipole-dipole configuration). In area A, a dipole-dipole array with 96 electrodes in a uniform rectangular survey grid has been used in full 3D to investigate a presumed Roman building. A roll-along technique has been utilized to cover a large part of the archaeological site with an electrode spacing of 1 meter and with 0.5 meter for a more detailed image. Additional dense parallel 2D profiles have been carried out in dipole-dipole array with 0.25 meter electrode spacing and 0.25 meter between adjacent profiles in both direction for higher- resolution subsurface images. We have designed a new field procedure, which used an electrode array fixed in a frame. This facilitates efficient field operation, which comprised 2376 electrode positions. With the quasi 3D imaging, we confirmed the full 3D inversion model but at a much better resolution. In area B, dense parallel 2D profiles were directly used to survey the second target with also 0.25 meter electrode spacing and profiles separation respectively. The same field measurement design has been utilized and comprised 9648 electrode positions in total. The quasi-3D inversion results clearly revealed the main structures of the Roman construction. These ERT inversion results coincided well with the archaeological excavation, which has been done in some parts of this area. The ERT result successfully images parts from the walls and also smaller internal structures of the Roman building.

Environmental filtering structures tree functional traits combination and lineages across space in tropical tree assemblages.

PubMed

Asefa, Mengesha; Cao, Min; Zhang, Guocheng; Ci, Xiuqin; Li, Jie; Yang, Jie

2017-03-09

Environmental filtering consistently shapes the functional and phylogenetic structure of species across space within diverse forests. However, poor descriptions of community functional and lineage distributions across space hamper the accurate understanding of coexistence mechanisms. We combined environmental variables and geographic space to explore how traits and lineages are filtered by environmental factors using extended RLQ and fourth-corner analyses across different spatial scales. The dispersion patterns of traits and lineages were also examined in a 20-ha tropical rainforest dynamics plot in southwest China. We found that environmental filtering was detected across all spatial scales except the largest scale (100 × 100 m). Generally, the associations between functional traits and environmental variables were more or less consistent across spatial scales. Species with high resource acquisition-related traits were associated with the resource-rich part of the plot across the different spatial scales, whereas resource-conserving functional traits were distributed in limited-resource environments. Furthermore, we found phylogenetic and functional clustering at all spatial scales. Similar functional strategies were also detected among distantly related species, suggesting that phylogenetic distance is not necessarily a proxy for functional distance. In summary, environmental filtering considerably structured the trait and lineage assemblages in this species-rich tropical rainforest.

Capability Investment Strategy to Enable JPL Future Space Missions

NASA Technical Reports Server (NTRS)

Lincoln, William; Merida, Sofia; Adumitroaie, Virgil; Weisbin, Charles R.

2006-01-01

The Jet Propulsion Laboratory (JPL) formulates and conducts deep space missions for NASA (the National Aeronautics and Space Administration). The Chief Technologist of JPL has responsibility for strategic planning of the laboratory's advanced technology program to assure that the required technological capabilities to enable future missions are ready as needed. The responsibilities include development of a Strategic Plan (Antonsson, E., 2005). As part of the planning effort, a structured approach to technology prioritization, based upon the work of the START (Strategic Assessment of Risk and Technology) (Weisbin, C.R., 2004) team, was developed. The purpose of this paper is to describe this approach and present its current status relative to the JPL technology investment.

STS-113 crew group photo during TCDT

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- The STS-113 crew poses for a photo on 195-foot level of the Fixed Service Structure on Launch Pad 39A. From left are Mission Specialist John Herrington, Pilot Paul Lockhart, Commander James Wetherbee and Mission Specialist Michael Lopez-Alegria. Along with the Expedition 6 crew, they have been participating in emergency egress training, part of Terminal Countdown Demonstration Test activities in preparation for their launch. The 16th assembly flight to the International Space Station, STS-113 will carry the Port 1 (P1) truss aboard Space Shuttle Endeavour, as well as Expedition 6, who will replace Expedition 5 on the Station. The mission is scheduled to launch Nov. 10, 2002.

STS-110 crew in M-113 personnel carrier during TCDT

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- With fellow crew members Mission Specialists Rex Walheim and Ellen Ochoa (waving her arm) and a trainer aboard, STS-110 Pilot Stephen Frick stirs up dust behind the M-113 armored personnel carrier as he practices driving it. The training is part of Terminal Countdown Demonstration Test activities, which include emergency egress training and a simulated launch countdown. The TCDT is held at KSC prior to each Space Shuttle flight. Scheduled for launch April 4, the 11-day mission will feature Shuttle Atlantis docking with the International Space Station (ISS) and delivering the S0 truss, the centerpiece-segment of the primary truss structure that will eventually extend over 300 feet.

STS-110 M.S. Ochoa in M-113 personnel carrier during TCDT

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- STS-110 Mission Specialist Ellen Ochoa practices driving the M-113 armored personnel carrier, part of Terminal Countdown Demonstration Test activities. Accompanying her are fellow crew members Mission Specialist Rex Walheim (far left) and Pilot Stephen Frink (second from left). In front is the trainer. TCDT includes emergency egress training and a simulated launch countdown. The TCDT is held at KSC prior to each Space Shuttle flight. Scheduled for launch April 4, the 11-day mission will feature Shuttle Atlantis docking with the International Space Station (ISS) and delivering the S0 truss, the centerpiece-segment of the primary truss structure that will eventually extend over 300 feet.

The Shock and Vibration Bulletin: Proceedings on the Symposium on ShocK and Vibration (52nd) Held in New Orleans, Louisiana on 26-28 October 1981. Part 2. Invited Papers, Space Shuttle Loads and Dynamics, Space Shuttle Data Systems, Shock Testing, Shock Analysis Space Shuttle Thermal Protection Systems

DTIC Science & Technology

1982-05-01

discovered during posttest inspection. The unit had experienced 2 As- designed damper, 0.92-1-.14 grams 8 tests for a total of 330 seconds of opera- 3...a Modeling DAMPED STRUCTURE DESIGN USING FINITE ELEMENT ANALYSIS M. F. Klunmner and M. L. Drake, University of Dayti-n Resatch Institute, Dayton, OH...IN DYNAMICS T. E. Simkins, U.S. Army Armament Research and Development Command, Watervliet, NY Stucturd Dynamics A PROCEDURE FOR DESIGNING OVERDAMPED

STS-110 M.S. Ross and Smith in M-113 personnel carrier during TCDT

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- With STS-110 Mission Specialists Jerry Ross (far left) and Steven Smith (third from left) on board, Commander Michael Bloomfield scatters dust as he practices driving the M-113 armored personnel carrier. The driving is part of Terminal Countdown Demonstration Test activities, which include emergency egress training and a simulated launch countdown. The TCDT is held at KSC prior to each Space Shuttle flight. Scheduled for launch April 4, the 11-day mission will feature Shuttle Atlantis docking with the International Space Station (ISS) and delivering the S0 truss, the centerpiece-segment of the primary truss structure that will eventually extend over 300 feet.

KSC00pp1477

NASA Image and Video Library

2000-10-02

KENNEDY SPACE CENTER, FLA. -- The STS-92 crew poses for a group photo in front of the Integrated Truss Structure Z-1, part of the payload on their mission. From left, they are Mission Specialist Koichi Wakata of Japan; Pilot Pamela Ann Melroy; Mission Specialists Leroy Chiao, Michael E. Lopez-Alegria, Peter J.K. “Jeff” Wisoff and William S. McArthur Jr.; and Commander Brian Duffy. The crew has been inspecting the payload in preparation for launch Oct. 5, 2000. The mission is the fifth flight for the construction of the International Space Station. The payload also includes the third Pressurized Mating Adapter. During the 11-day mission, four extravehicular activities (EVAs), or space walks, are planned

KSC-00pp1477

NASA Image and Video Library

2000-10-02

KENNEDY SPACE CENTER, FLA. -- The STS-92 crew poses for a group photo in front of the Integrated Truss Structure Z-1, part of the payload on their mission. From left, they are Mission Specialist Koichi Wakata of Japan; Pilot Pamela Ann Melroy; Mission Specialists Leroy Chiao, Michael E. Lopez-Alegria, Peter J.K. “Jeff” Wisoff and William S. McArthur Jr.; and Commander Brian Duffy. The crew has been inspecting the payload in preparation for launch Oct. 5, 2000. The mission is the fifth flight for the construction of the International Space Station. The payload also includes the third Pressurized Mating Adapter. During the 11-day mission, four extravehicular activities (EVAs), or space walks, are planned

KSC-2014-3262

NASA Image and Video Library

2014-07-23

CAPE CANAVERAL, Fla. – A view looking down from one of the higher levels in the Vehicle Assembly Building, or VAB, reveals High Bay 3 at NASA’s Kennedy Space Center in Florida. Banners note the heights of the Saturn V, Space Launch System, or SLS, and shuttle on the steel structure. Modifications are underway to prepare High Bay 3 for a new platform system. The modifications are part of a centerwide refurbishment initiative under the Ground Systems Development and Operations Program. High bay 3 is being refurbished to accommodate NASA’s Space Launch System and a variety of other spacecraft. For more information, visit http://www.nasa.gov/exploration/systems/ground/index.html. Photo credit: NASA/Dimitri Gerondidakis

KSC-08pd2858

NASA Image and Video Library

2008-09-23

CAPE CANAVERAL, Fla. - STS-125 Pilot Gregory C. Johnson serves as a “guinea pig” to demonstrate emergency escape apparatus from the 195-foot level of the fixed service structure on Launch Pad 39A at NASA's Kennedy Space Center in Florida. Looking on are Mission Specialists Andrew Feustel, Megan McArthur and Mike Massimino. The crew is at Kennedy to take part in terminal countdown demonstration test, or TCDT, activities before launching on space shuttle Atlantis’ mission to service NASA’s Hubble Space Telescope. TCDT provides astronauts and ground crews with an opportunity to participate in various simulated countdown activities, including equipment familiarization, emergency training and a simulated launch countdown. Atlantis is targeted to launch Oct. 10. Photo credit: NASA/Kim Shiflett

KSC-04PD-2687

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. A shipping container transporting part of the new Orbiter Boom Sensor System (OBSS) is delivered by truck to the Remote Manipulator System lab in the Vehicle Assembly Building (VAB). Once the entire structure has arrived, the OBSS will be assembled and undergo final checkout and testing in the lab prior to being transferred to the Orbiter Processing Facility (OPF) for installation on Space Shuttle Discovery. The 50-foot-long OBSS will be attached to the Remote Manipulator System, or Shuttle arm, and is one of the new safety measures for Return to Flight, equipping the orbiter with cameras and laser systems to inspect the Shuttle's Thermal Protection System while in space. Discovery is slated to fly mission STS-114 once Space Shuttle launches resume. The launch planning window is May 12 to June 3, 2005.

IAE - Inflatable Antenna Experiment

NASA Image and Video Library

1996-05-20

STS077-150-010 (20 May 1996) --- Soon after leaving the cargo bay of the Space Shuttle Endeavour, the Spartan 207/Inflatable Antenna Experiment (IAE) payload goes through its inflation process, backdropped over clouds. The view was photographed with a large format still camera on the first full day of in-space operations by the six-member crew. Managed by Goddard Space Flight Center (GSFC), Spartan is designed to provide short-duration, free-flight opportunities for a variety of scientific studies. The Spartan configuration on this flight is unique in that the IAE is part of an additional separate unit which is ejected once the experiment is completed. The IAE experiment will lay the groundwork for future technology development in inflatable space structures, which will be launched and then inflated like a balloon on-orbit.

Enabling the 2nd Generation in Space: Building Blocks for Large Scale Space Endeavours

NASA Astrophysics Data System (ADS)

Barnhardt, D.; Garretson, P.; Will, P.

Today the world operates within a "first generation" space industrial enterprise, i.e. all industry is on Earth, all value from space is from bits (data essentially), and the focus is Earth-centric, with very limited parts of our population and industry participating in space. We are limited in access, manoeuvring, on-orbit servicing, in-space power, in-space manufacturing and assembly. The transition to a "Starship culture" requires the Earth to progress to a "second generation" space industrial base, which implies the need to expand the economic sphere of activity of mankind outside of an Earth-centric zone and into CIS-lunar space and beyond, with an equal ability to tap the indigenous resources in space (energy, location, materials) that will contribute to an expanding space economy. Right now, there is no comfortable place for space applications that are not discovery science, exploration, military, or established earth bound services. For the most part, space applications leave out -- or at least leave nebulous, unconsolidated, and without a critical mass -- programs and development efforts for infrastructure, industrialization, space resources (survey and process maturation), non-traditional and persistent security situational awareness, and global utilities -- all of which, to a far greater extent than a discovery and exploration program, may help determine the elements of a 2nd generation space capability. We propose a focus to seed the pre-competitive research that will enable global industry to develop the necessary competencies that we currently lack to build large scale space structures on-orbit, that in turn would lay the foundation for long duration spacecraft travel (i.e. key technologies in access, manoeuvrability, etc.). This paper will posit a vision-to-reality for a step wise approach to the types of activities the US and global space providers could embark upon to lay the foundation for the 2nd generation of Earth in space.

3D Printing in Zero-G Experiment, In Space Manufacturing (LPS, 4)

NASA Technical Reports Server (NTRS)

Bean, Quincy; Cooper, Ken; Werkheiser, Niki

2015-01-01

The 3D Printing in Zero-G Experiment has been an ongoing effort for several years. In June 2014 the technology demonstration 3D printer was launched to the International Space Station. In November 2014 the first 21 parts were manufactured in orbit marking the beginning of a paradigm shift that will allow astronauts to be more self-sufficient and pave the way to larger scale orbital manufacturing. Prior to launch the 21 parts were built on the ground with the flight unit with the same feedstock. These ground control samples are to be tested alongside the flight samples in order to determine if there is a measurable difference between parts built on the ground vs. parts built in space. As of this writing, testing has not yet commenced. Tests to be performed are structured light scanning for volume and geometric discrepancies, CT scanning for density measurement, destructive testing of mechanical samples, and SEM analysis for inter-laminar adhesion discrepancies. Additionally, an ABS material characterization was performed on mechanical samples built from the same CAD files as the flight and ground samples on different machine / feedstock combinations. The purpose of this testing was twofold: first to obtain mechanical data in order to have a baseline comparison for the flight and ground samples and second to ascertain if there is a measurable difference between machines and feedstock.

Cryogenic expansion joint for large superconducting magnet structures

DOEpatents

Brown, Robert L.

1978-01-01

An expansion joint is provided that accommodates dimensional changes occurring during the cooldown and warm-up of large cryogenic devices such as superconducting magnet coils. Flattened tubes containing a refrigerant such as gaseous nitrogen (N.sub.2) are inserted into expansion spaces in the structure. The gaseous N.sub.2 is circulated under pressure and aids in the cooldown process while providing its primary function of accommodating differential thermal contraction and expansion in the structure. After lower temperatures are reached and the greater part of the contraction has occured, the N.sub.2 liquefies then solidifies to provide a completely rigid structure at the cryogenic operating temperatures of the device.

Determination of Structural Parameters from EXAFS (Extended X-Ray Absorption Fine Structure): Application to Solutions and Catalysts.

DTIC Science & Technology

1984-05-23

the disorder was accurately known. Inverse Transform To isolate the EAFS contribution due to a single feature in the Fourier transform, the inverse ...is associated with setting the "fold" components to 27 zero in r-space. An inverse transform (real part) of the major feature of the Fig. 4 Fourier...phase of the resulting inverse transform represents only any differences between the material being studied and the reference. This residual is

Structural-Thermal-Optical-Performance (STOP) Analysis

NASA Technical Reports Server (NTRS)

Bolognese, Jeffrey; Irish, Sandra

2015-01-01

The presentation will be given at the 26th Annual Thermal Fluids Analysis Workshop (TFAWS 2015) hosted by the Goddard Spaceflight Center (GSFC) Thermal Engineering Branch (Code 545). A STOP analysis is a multidiscipline analysis, consisting of Structural, Thermal and Optical Performance Analyses, that is performed for all space flight instruments and satellites. This course will explain the different parts of performing this analysis. The student will learn how to effectively interact with each discipline in order to accurately obtain the system analysis results.

The 25 kW power module evolution study. Part 3: Conceptual design for power module evolution. Volume 6: WBS and dictionary

NASA Technical Reports Server (NTRS)

1979-01-01

Program elements of the power module (PM) system, are identified, structured, and defined according to the planned work breakdown structure. Efforts required to design, develop, manufacture, test, checkout, launch and operate a protoflight assembled 25 kW, 50 kW and 100 kW PM include the preparation and delivery of related software, government furnished equipment, space support equipment, ground support equipment, launch site verification software, orbital verification software, and all related data items.

Lightning Protection and Structural Bonding for the B2 Test Stand

NASA Technical Reports Server (NTRS)

Kinard, Brandon

2015-01-01

With the privatization of the space industry, NASA has entered a new era. To explore deeper parts of the solar system, NASA is developing a new spacecraft, the Space Launch System (SLS), capable of reaching these destinations, such as an asteroid or Mars. However, the test stand that is capable of testing the stage has been unused for many years. In addition to the updating/repair of the stand, more steel is being added to fully support the SLS. With all these modifications, the lightning protection system must be brought up to code to assure the protection of all personnel and assets. Structural bonding is a part of the lightning protection system. The focus of this project was to assure proper structural bonding. To begin, all relevant technical standards and the construction specifications were reviewed. This included both the specifications for the lightning protection and for general construction. The drawings were reviewed as well. From the drawings, bolted structural joints were reviewed to determine whether bonding was necessary. Several bolted joints were determined to need bonding according to the notes in the drawings. This exceeds the industry standards. The bolted joints are an electrically continuous joint. During tests, the stand experiences heavy vibration that may weaken the continuity of the bolted joint. Therefore, the secondary bonding is implemented to ensure that the structural joint has low resistance. If the structural joint has a high resistance because of corrosion, a potential gradient can occur that can cause a side flash. Damage, injury, or death can occur from a side flash so they are to be prevented. A list of the identified structural joints was compiled and sent to the contractor to be bonded. That covers the scope of this project.

United Space Alliance, LLC Windchill As-Built Highlights

NASA Technical Reports Server (NTRS)

Richmond, Dena M.

2011-01-01

Work Order execution data from Solumina As Worked BOM (As-Built) in Solumina (Slide 2) sent to Windchill Windchill receives As Worked BOM data and 'marries' the Solumina execution data to the Part Instance/Product Structure/As-Design (Slide 3 As-Design and Slide 4 &5 As-Built) Manage the As-Built to As-Design delta's via the interface and Part Instance Attributes (Slide 6) including Work Order data and any CMcomments Produce an As-Built to As-Design report that also includes all Part Instance Attribute data (no screenshot as this is still in development) Utilize Windchill and Solumina 'Out of the Box' functionality

Alternative difference analysis scheme combining R -space EXAFS fit with global optimization XANES fit for X-ray transient absorption spectroscopy

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

Zhan, Fei; Tao, Ye; Zhao, Haifeng

Time-resolved X-ray absorption spectroscopy (TR-XAS), based on the laser-pump/X-ray-probe method, is powerful in capturing the change of the geometrical and electronic structure of the absorbing atom upon excitation. TR-XAS data analysis is generally performed on the laser-on minus laser-off difference spectrum. Here, a new analysis scheme is presented for the TR-XAS difference fitting in both the extended X-ray absorption fine-structure (EXAFS) and the X-ray absorption near-edge structure (XANES) regions.R-space EXAFS difference fitting could quickly provide the main quantitative structure change of the first shell. The XANES fitting part introduces a global non-derivative optimization algorithm and optimizes the local structure changemore » in a flexible way where both the core XAS calculation package and the search method in the fitting shell are changeable. The scheme was applied to the TR-XAS difference analysis of Fe(phen) 3spin crossover complex and yielded reliable distance change and excitation population.« less

Near minimum-time maneuvers of the advanced space structures technology research experiment (ASTREX) test article: Theory and experiments

NASA Technical Reports Server (NTRS)

Vadali, Srinivas R.; Carter, Michael T.

1994-01-01

The Phillips Laboratory at the Edwards Air Force Base has developed the Advanced Space Structures Technology Research Experiment (ASTREX) facility to serve as a testbed for demonstrating the applicability of proven theories to the challenges of spacecraft maneuvers and structural control. This report describes the work performed on the ASTREX test article by Texas A&M University under contract NAS119373 as a part of the Control-Structure Interaction (CSI) Guest Investigator Program. The focus of this work is on maneuvering the ASTREX test article with compressed air thrusters that can be throttled, while attenuating structural excitation. The theoretical foundation for designing the near minimum-time thrust commands is based on the generation of smooth, parameterized optimal open-loop control profiles, and the determination of control laws for final position regulation and tracking using Lyapunov stability theory. Details of the theory, mathematical modeling, model updating, and compensation for the presence of 'real world' effects are described and the experimental results are presented. The results show an excellent match between theory and experiments.

Alternative difference analysis scheme combining R-space EXAFS fit with global optimization XANES fit for X-ray transient absorption spectroscopy.

PubMed

Zhan, Fei; Tao, Ye; Zhao, Haifeng

2017-07-01

Time-resolved X-ray absorption spectroscopy (TR-XAS), based on the laser-pump/X-ray-probe method, is powerful in capturing the change of the geometrical and electronic structure of the absorbing atom upon excitation. TR-XAS data analysis is generally performed on the laser-on minus laser-off difference spectrum. Here, a new analysis scheme is presented for the TR-XAS difference fitting in both the extended X-ray absorption fine-structure (EXAFS) and the X-ray absorption near-edge structure (XANES) regions. R-space EXAFS difference fitting could quickly provide the main quantitative structure change of the first shell. The XANES fitting part introduces a global non-derivative optimization algorithm and optimizes the local structure change in a flexible way where both the core XAS calculation package and the search method in the fitting shell are changeable. The scheme was applied to the TR-XAS difference analysis of Fe(phen) 3 spin crossover complex and yielded reliable distance change and excitation population.

Aeroacoustics of Space Vehicles

NASA Technical Reports Server (NTRS)

Panda, Jayanta

2014-01-01

While for airplanes the subject of aeroacoustics is associated with community noise, for space vehicles it is associated with vibro-acoustics and structural dynamics. Surface pressure fluctuations encountered during launch and travel through lower part of the atmosphere create intense vibro-acoustics environment for the payload, electronics, navigational equipment, and a large number of subsystems. All of these components have to be designed and tested for flight-certification. This presentation will cover all three major sources encountered in manned and unmanned space vehicles: launch acoustics, ascent acoustics and abort acoustics. Launch pads employ elaborate acoustic suppression systems to mitigate the ignition pressure waves and rocket plume generated noise during the early part of the liftoff. Recently we have used large microphone arrays to identify the noise sources during liftoff and found that the standard model by Eldred and Jones (NASA SP-8072) to be grossly inadequate. As the vehicle speeds up and reaches transonic speed in relatively denser part of the atmosphere, various shock waves and flow separation events create unsteady pressure fluctuations that can lead to high vibration environment, and occasional coupling with the structural modes, which may lead to buffet. Examples of wind tunnel tests and computational simulations to optimize the outer mold line to quantify and reduce the surface pressure fluctuations will be presented. Finally, a manned space vehicle needs to be designed for crew safety during malfunctioning of the primary rocket vehicle. This brings the subject of acoustic environment during abort. For NASAs Multi-Purpose Crew Vehicle (MPCV), abort will be performed by lighting rocket motors atop the crew module. The severe aeroacoustics environments during various abort scenarios were measured for the first time by using hot helium to simulate rocket plumes in the Ames unitary plan wind tunnels. Various considerations used for the helium simulation and the final confirmation from a flight test will be presented.

KSC-07pd3390

NASA Image and Video Library

2007-11-19

KENNEDY SPACE CENTER, FLA. -- During a training session on emergency exit from the fixed service structure on Launch Pad 39A, space shuttle Atlantis STS-122 Mission Specialists Hans Schlegel, left, and Rex Walheim watch a slidewire basket descend to the landing zone. Schlegel is with the European Space Agency. Seven slidewire baskets are available to carry the crew from the level of the pad's Orbiter Access Arm to a safe landing site below, if needed. Each basket can hold up to three people. A braking system catch net and drag chain slow, and then halt, the baskets as they travel down the wire at approximately 55 miles per hour. The journey takes about half a minute. A bunker is located in the landing zone 1,200 feet west of the pad, with an M-113 armored personnel carrier stationed nearby. The STS-122 crew is at NASA's Kennedy Space Center to take part in terminal countdown demonstration test, or TCDT, activities, a standard part of launch preparations. The TCDT provides astronauts and ground crews with equipment familiarization and a simulated launch countdown before launch. On mission STS-122, Atlantis will deliver the European Space Agency's Columbus module to the International Space Station. Columbus is a multifunctional, pressurized laboratory that will be permanently attached to U.S. Node 2, called Harmony, and will expand the research facilities aboard the station. Launch is targeted for Dec. 6. Photo credit: NASA/Kim Shiflett

The properties of borderlines in discontinuous conservative systems

NASA Astrophysics Data System (ADS)

Wang, X.-M.; Fang, Z.-J.

2006-02-01

The properties of the set of borderline images in discontinuous conservative systems are commonly investigated. The invertible system in which a stochastic web was found in 1999 is re-discussed here. The result shows that the set of images of the borderline actually forms the same stochastic web. The web has two typical local fine structures. Firstly, in some parts of the web the borderline crosses the manifold of hyperbolic points so that the chaotic diffusion is damped greatly; secondly, in other parts of phase space many holes and elliptic islands appear in the stochastic layer. This local structure shows infinite self-similarity. The noninvertible system in which the so-called chaotic quasi-attractor was found in [X.-M. Wang et al., Eur. Phys. J. D 19, 119 (2002)] is also studied here. The numerical investigation shows that such a chaotic quasi-attractor is confined by the preceding lower order images of the borderline. The mechanism of this confinement is revealed: a forbidden zone exists that any orbit can not visit, which is the sub-phase space of one side of the first image of the borderline. Each order of the images of the forbidden zone can be qualitatively divided into two sub-phase regions: one is the so-called escaping region that provides the orbit with an escaping channel, the other is the so-called dissipative region where the contraction of phase space occurs.

KSC-06pd0926

NASA Image and Video Library

2006-05-23

KENNEDY SPACE CENTER, FLA. -- From inside the payload changeout room on the rotating service structure on Launch Pad 39B, workers maneuver the multi-purpose logistics module Leonardo into Space Shuttle Discovery's payload bay (at left). The payload ground-handling mechanism (PGHM) is used to transfer the module into the payload bay. Leonardo is a reusable logistics carrier. It is the primary delivery system used to resupply and return station cargo requiring a pressurized environment. Leonardo is part of the payload on mission STS-121. Other payloads include the integrated cargo carrier with the mobile transporter reel assembly and a spare pump module, and the lightweight multi-purpose experiment support structure carrier. Discovery is scheduled to launch in a window extending from July 1 through July 19. Photo credit: NASA/Jack Pfaller

KSC-06pd0925

NASA Image and Video Library

2006-05-23

KENNEDY SPACE CENTER, FLA. -- From inside the payload changeout room on the rotating service structure on Launch Pad 39B, the multi-purpose logistics module Leonardo is being moved into Space Shuttle Discovery's payload bay (at left). The payload ground-handling mechanism (PGHM) is used to transfer the module into the payload bay. Leonardo is a reusable logistics carrier. It is the primary delivery system used to resupply and return station cargo requiring a pressurized environment. Leonardo is part of the payload on mission STS-121. Other payloads include the integrated cargo carrier with the mobile transporter reel assembly and a spare pump module, and the lightweight multi-purpose experiment support structure carrier. Discovery is scheduled to launch in a window extending from July 1 through July 19. Photo credit: NASA/Jack Pfaller

Exploring the free energy surface using ab initio molecular dynamics

DOE PAGES

Samanta, Amit; Morales, Miguel A.; Schwegler, Eric

2016-04-22

Efficient exploration of the configuration space and identification of metastable structures are challenging from both computational as well as algorithmic perspectives. Here, we extend the recently proposed orderparameter aided temperature accelerated sampling schemes to efficiently and systematically explore free energy surfaces, and search for metastable states and reaction pathways within the framework of density functional theory based molecular dynamics. The sampling method is applied to explore the relevant parts of the configuration space in prototypical materials SiO 2 and Ti to identify the different metastable structures corresponding to different phases in these materials. In addition, we use the string methodmore » in collective variables to study the melting pathways in the high pressure cotunnite phase of SiO 2 and the hcp to fcc phase transition in Ti.« less

14 CFR Appendix A to Part 1221 - Congressional Space Medal of Honor

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 5 2013-01-01 2013-01-01 false Congressional Space Medal of Honor A Appendix A to Part 1221 Aeronautics and Space NATIONAL AERONAUTICS AND SPACE ADMINISTRATION THE NASA SEAL AND OTHER DEVICES, AND THE CONGRESSIONAL SPACE MEDAL OF HONOR Pt. 1221, App. A Appendix A to Part 1221...

14 CFR Appendix A to Part 1221 - Congressional Space Medal of Honor

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 5 2011-01-01 2010-01-01 true Congressional Space Medal of Honor A Appendix A to Part 1221 Aeronautics and Space NATIONAL AERONAUTICS AND SPACE ADMINISTRATION THE NASA SEAL AND OTHER DEVICES, AND THE CONGRESSIONAL SPACE MEDAL OF HONOR Pt. 1221, App. A Appendix A to Part 1221...

The Fifth NASA/DOD Controls-Structures Interaction Technology Conference, part 2

NASA Technical Reports Server (NTRS)

Newsom, Jerry R. (Compiler)

1993-01-01

This publication is a compilation of the papers presented at the Fifth NASA/DoD Controls-Structures Interaction (CSI) Technology Conference held in Lake Tahoe, Nevada, March 3-5, 1992. The conference, which was jointly sponsored by the NASA Office of Aeronautics and Space Technology and the Department of Defense, was organized by the NASA Langley Research Center. The purpose of this conference was to report to industry, academia, and government agencies on the current status of controls-structures interaction technology. The agenda covered ground testing, integrated design, analysis, flight experiments and concepts.

PHYSICAL CHARACTERISTICS AND NON-KEPLERIAN ORBITAL MOTION OF 'PROPELLER' MOONS EMBEDDED IN SATURN'S RINGS

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

Tiscareno, Matthew S.; Burns, Joseph A.; Hedman, Matthew M.

2010-08-01

We report the discovery of several large 'propeller' moons in the outer part of Saturn's A ring, objects large enough to be followed over the 5 year duration of the Cassini mission. These are the first objects ever discovered that can be tracked as individual moons, but do not orbit in empty space. We infer sizes up to 1-2 km for the unseen moonlets at the center of the propeller-shaped structures, though many structural and photometric properties of propeller structures remain unclear. Finally, we demonstrate that some propellers undergo sustained non-Keplerian orbit motion.

An approximate methods approach to probabilistic structural analysis

NASA Technical Reports Server (NTRS)

Mcclung, R. C.; Millwater, H. R.; Wu, Y.-T.; Thacker, B. H.; Burnside, O. H.

1989-01-01

A probabilistic structural analysis method (PSAM) is described which makes an approximate calculation of the structural response of a system, including the associated probabilistic distributions, with minimal computation time and cost, based on a simplified representation of the geometry, loads, and material. The method employs the fast probability integration (FPI) algorithm of Wu and Wirsching. Typical solution strategies are illustrated by formulations for a representative critical component chosen from the Space Shuttle Main Engine (SSME) as part of a major NASA-sponsored program on PSAM. Typical results are presented to demonstrate the role of the methodology in engineering design and analysis.

The Fifth NASA/DOD Controls-Structures Interaction Technology Conference, part 1

NASA Technical Reports Server (NTRS)

Newsom, Jerry R. (Compiler)

1993-01-01

This publication is a compilation of the papers presented at the Fifth NASA/DoD Controls-Structures Interaction (CSI) Technology Conference held in Lake Tahoe, Nevada, March 3-5, 1992. The conference, which was jointly sponsored by the NASA Office of Aeronautics and Space Technology and the Department of Defense, was organized by the NASA Langley Research Center. The purpose of this conference was to report to industry, academia, and government agencies on the current status of controls-structures interaction technology. The agenda covered ground testing, integrated design, analysis, flight experiments and concepts.

Self-Alining Quick-Connect Joint

NASA Technical Reports Server (NTRS)

Lucy, M. H.

1983-01-01

Quick connect tapered joint used with minimum manipulation and force. Split ring retainer holds locking ring in place. Minimal force required to position male in female joint, at which time split-ring retainers are triggered to release split locking rings. Originally developed to assemble large space structures, joint is simple, compact, strong, lightweight, self alining, and has no loose parts.

KSC-2009-5101

NASA Image and Video Library

2009-09-10

CAPE CANAVERAL, Fla. – Near the top of the fixed service structure on NASA Kennedy Space Center's Launch Pad 39B, the new stabilizing arm (white) has been attached. The hardware is being reconfigured for launch of NASA's Ares I-X rocket, part of the agency's Constellation Program. The Ares I-X flight test is targeted for Oct. 31. Photo credit: NASA/Troy Cryder

KSC-2009-5103

NASA Image and Video Library

2009-09-10

CAPE CANAVERAL, Fla. – On NASA Kennedy Space Center's Launch Pad 39B, a second stabilizing arm is lifted for installation at the top of the fixed service structure. The hardware is being reconfigured for launch of NASA's Ares I-X rocket, part of the agency's Constellation Program. The Ares I-X flight test is targeted for Oct. 31. Photo credit: NASA/Troy Cryder

X-ray Crystallography Facility

NASA Technical Reports Server (NTRS)

2000-01-01

Edward Snell, a National Research Council research fellow at NASA's Marshall Space Flight Center (MSFC), prepares a protein crystal for analysis by x-ray crystallography as part of NASA's structural biology program. The small, individual crystals are bombarded with x-rays to produce diffraction patterns, a map of the intensity of the x-rays as they reflect through the crystal.

Engineering in the 21st century

NASA Technical Reports Server (NTRS)

Mccarthy, J. F., Jr.

1978-01-01

Reasonable evolutionary trends in federal outlays for aerospace research and development predict a continuing decline in real resources (1970 dollars) until the mid eighties, and a growth thereafter to the 1970 level by 2000, still well below the 1966 peak. Employment levels will parallel this trend with no shortage of available personnel foreseen. These trends characterize a maturing industry. Shifts in outlook toward the economic use of resources, rather than minimum risk at any cost, and toward missions aligned with societal needs and broad national goals will accompany these trends. These shifts in outlook will arise in part in academia, and will, in turn, influence engineering education. By 2000, space technology will have achieved major advances in the management of information, in space transportation, in space structures, and in energy. The economics of space systems must be the primary consideration if the space program foreseen for the 21st century is to become an actuality.

STS-102 crew poses on the FSS at Launch Pad 39B during TCDT

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- The STS-102 crew poses for a photo on the 215-foot level of the Fixed Service Structure. Behind them is Space Shuttle Discovery. Standing, left to right, are Mission Specialist Susan Helms, Pilot James Kelly, Mission Specialists Andrew Thomas and Paul Richards, Commander James Wetherbee and Mission Specialists Yury Usachev and James Voss. The crew is taking part in Terminal Countdown Demonstration Test activities, which include emergency exit training and a simulated launch countdown. STS-102 is the eighth construction flight to the International Space Station, with Space Shuttle Discovery carrying the Multi-Purpose Logistics Module Leonardo. Voss, Helms and Usachev are the Expedition Two crew who will be the second resident crew on the International Space Station. They will replace Expedition One, who will return to Earth with Discovery. Launch on mission STS-102 is scheduled for March 8.

KSC00pp0478

NASA Image and Video Library

2000-04-07

KENNEDY SPACE CENTER, FLA. -- As part of Terminal Countdown Demonstration (TCDT) activities, the STS-101 crew practices emergency egress from the orbiter at the 195-foot level of the Fixed Service Structure. Shown heading down the easily identified exit path, known as the "yellow brick road," are Mission Specialists Susan J. Helms (leading), Yury Usachev of Russia and James Voss. The TCDT also includes a simulated launch countdown and familiarization with the payload. During their mission to the International Space Station, the STS-101 crew will be delivering logistics and supplies, plus preparing the Station for the arrival of the Zvezda Service Module, expected to be launched by Russia in July 2000. Also, the crew will conduct one space walk to perform maintenance on the Space Station. This will be the third assembly flight to the Space Station. STS-101 is scheduled to launch April 24 at 4:15 p.m. from Launch Pad 39A

KSC-00pp0478

NASA Image and Video Library

2000-04-07

KENNEDY SPACE CENTER, FLA. -- As part of Terminal Countdown Demonstration (TCDT) activities, the STS-101 crew practices emergency egress from the orbiter at the 195-foot level of the Fixed Service Structure. Shown heading down the easily identified exit path, known as the "yellow brick road," are Mission Specialists Susan J. Helms (leading), Yury Usachev of Russia and James Voss. The TCDT also includes a simulated launch countdown and familiarization with the payload. During their mission to the International Space Station, the STS-101 crew will be delivering logistics and supplies, plus preparing the Station for the arrival of the Zvezda Service Module, expected to be launched by Russia in July 2000. Also, the crew will conduct one space walk to perform maintenance on the Space Station. This will be the third assembly flight to the Space Station. STS-101 is scheduled to launch April 24 at 4:15 p.m. from Launch Pad 39A

Dendritic Growth Morphologies in Al-Zn Alloys—Part II: Phase-Field Computations

NASA Astrophysics Data System (ADS)

Dantzig, J. A.; Di Napoli, Paolo; Friedli, J.; Rappaz, M.

2013-12-01

In Part I of this article, the role of the Zn content in the development of solidification microstructures in Al-Zn alloys was investigated experimentally using X-ray tomographic microscopy. The transition region between dendrites found at low Zn content and dendrites found at high Zn content was characterized by textured seaweed-type structures. This Dendrite Orientation Transition (DOT) was explained by the effect of the Zn content on the weak anisotropy of the solid-liquid interfacial energy of Al. In order to further support this interpretation and to elucidate the growth mechanisms of the complex structures that form in the DOT region, a detailed phase-field study exploring anisotropy parameters' space is presented in this paper. For equiaxed growth, our results essentially recapitulate those of Haxhimali et al.[1] in simulations for pure materials. We find distinct regions of the parameter space associated with and dendrites, separated by a region where hyperbranched dendrites are observed. In simulations of directional solidification, we find similar behavior at the extrema, but in this case, the anisotropy parameters corresponding to the hyperbranched region produce textured seaweeds. As noted in the experimental work reported in Part I, these structures are actually dendrites that prefer to grow misaligned with respect to the thermal gradient direction. We also show that in this region, the dendrites grow with a blunted tip that oscillates and splits, resulting in an oriented trunk that continuously emits side branches in other directions. We conclude by making a correlation between the alloy composition and surface energy anisotropy parameters.

Assessment of Technologies for the Space Shuttle External Tank Thermal Protection System and Recommendations for Technology Improvement. Part 2; Structural Analysis Technologies and Modeling Practices

NASA Technical Reports Server (NTRS)

Knight, Norman F., Jr.; Nemeth, Michael P.; Hilburger, Mark W.

2004-01-01

A technology review and assessment of modeling and analysis efforts underway in support of a safe return to flight of the thermal protection system (TPS) for the Space Shuttle external tank (ET) are summarized. This review and assessment effort focuses on the structural modeling and analysis practices employed for ET TPS foam design and analysis and on identifying analysis capabilities needed in the short-term and long-term. The current understanding of the relationship between complex flight environments and ET TPS foam failure modes are reviewed as they relate to modeling and analysis. A literature review on modeling and analysis of TPS foam material systems is also presented. Finally, a review of modeling and analysis tools employed in the Space Shuttle Program is presented for the ET TPS acreage and close-out foam regions. This review includes existing simplified engineering analysis tools are well as finite element analysis procedures.

Autonomous docking system for space structures and satellites

NASA Astrophysics Data System (ADS)

Prasad, Guru; Tajudeen, Eddie; Spenser, James

2005-05-01

Aximetric proposes Distributed Command and Control (C2) architecture for autonomous on-orbit assembly in space with our unique vision and sensor driven docking mechanism. Aximetric is currently working on ip based distributed control strategies, docking/mating plate, alignment and latching mechanism, umbilical structure/cord designs, and hardware/software in a closed loop architecture for smart autonomous demonstration utilizing proven developments in sensor and docking technology. These technologies can be effectively applied to many transferring/conveying and on-orbit servicing applications to include the capturing and coupling of space bound vehicles and components. The autonomous system will be a "smart" system that will incorporate a vision system used for identifying, tracking, locating and mating the transferring device to the receiving device. A robustly designed coupler for the transfer of the fuel will be integrated. Advanced sealing technology will be utilized for isolation and purging of resulting cavities from the mating process and/or from the incorporation of other electrical and data acquisition devices used as part of the overall smart system.

Aerocapture Technology Developments from NASA's In-Space Propulsion Technology Program

NASA Technical Reports Server (NTRS)

Munk, Michelle M.; Moon, Steven A.

2007-01-01

This paper will explain the investment strategy, the role of detailed systems analysis, and the hardware and modeling developments that have resulted from the past 5 years of work under NASA's In-Space Propulsion Program (ISPT) Aerocapture investment area. The organizations that have been funded by ISPT over that time period received awards from a 2002 NASA Research Announcement. They are: Lockheed Martin Space Systems, Applied Research Associates, Inc., Ball Aerospace, NASA's Ames Research Center, and NASA's Langley Research Center. Their accomplishments include improved understanding of entry aerothermal environments, particularly at Titan, demonstration of aerocapture guidance algorithm robustness at multiple bodies, manufacture and test of a 2-meter Carbon-Carbon "hot structure," development and test of evolutionary, high-temperature structural systems with efficient ablative materials, and development of aerothermal sensors that will fly on the Mars Science Laboratory in 2009. Due in large part to this sustained ISPT support for Aerocapture, the technology is ready to be validated in flight.

Conservative Allowables Determined by a Tsai-Hill Equivalent Criterion for Design of Satellite Composite Parts

NASA Astrophysics Data System (ADS)

Pommatau, Gilles

2014-06-01

The present paper deals with the industrial application, via a software developed by Thales Alenia Space, of a new failure criterion named "Tsai-Hill equivalent criterion" for composite structural parts of satellites. The first part of the paper briefly describes the main hypothesis and the possibilities in terms of failure analysis of the software. The second parts reminds the quadratic and conservative nature of the new failure criterion, already presented in ESA conference in a previous paper. The third part presents the statistical calculation possibilities of the software, and the associated sensitivity analysis, via results obtained on different composites. Then a methodology, proposed to customers and agencies, is presented with its limitations and advantages. It is then conclude that this methodology is an efficient industrial way to perform mechanical analysis on quasi-isotropic composite parts.

Research on the Problem of High-Precision Deployment for Large-Aperture Space-Based Science Instruments

NASA Technical Reports Server (NTRS)

Lake, Mark S.; Peterson, Lee D.; Hachkowski, M. Roman; Hinkle, Jason D.; Hardaway, Lisa R.

1998-01-01

The present paper summarizes results from an ongoing research program conducted jointly by the University of Colorado and NASA Langley Research Center since 1994. This program has resulted in general guidelines for the design of high-precision deployment mechanisms, and tests of prototype deployable structures incorporating these mechanisms have shown microdynamically stable behavior (i.e., dimensional stability to parts per million). These advancements have resulted from the identification of numerous heretofore unknown microdynamic and micromechanical response phenomena, and the development of new test techniques and instrumentation systems to interrogate these phenomena. In addition, recent tests have begun to interrogate nanomechanical response of materials and joints and have been used to develop an understanding of nonlinear nanodynamic behavior in microdynamically stable structures. The ultimate goal of these efforts is to enable nano-precision active control of micro-precision deployable structures (i.e., active control to a resolution of parts per billion).

Microgravity

NASA Image and Video Library

2002-08-08

In addition to drop tower activities, students assembled a plastic pipe structure underwater in a SCUBA exercise similar to training astronauts receive at NASA Johnson Space Center. This was part of the second Dropping in a Microgravity Environment (DIME) competition held April 23-25, 2002, at NASA's Glenn Research Center. Competitors included two teams from Sycamore High School, Cincinnati, OH, and one each from Bay High School, Bay Village, OH, and COSI Academy, Columbus, OH. DIME is part of NASA's education and outreach activities. Details are on line at http://microgravity.grc.nasa.gov/DIME_2002.html.

Normal state of metallic hydrogen sulfide

NASA Astrophysics Data System (ADS)

Kudryashov, N. A.; Kutukov, A. A.; Mazur, E. A.

2017-02-01

A generalized theory of the normal properties of metals in the case of electron-phonon (EP) systems with a nonconstant density of electron states has been used to study the normal state of the SH3 and SH2 phases of hydrogen sulfide at different pressures. The frequency dependence of the real Re Σ (ω) and imaginary ImΣ (ω) parts of the self-energy Σ (ω) part (SEP) of the Green's function of the electron Σ (ω), real part Re Z (ω), and imaginary part Im Z (ω) of the complex renormalization of the mass of the electron; the real part Re χ (ω) and the imaginary part Imχ (ω) of the complex renormalization of the chemical potential; and the density of electron states N (ɛ) renormalized by strong electron-phonon interaction have been calculated. Calculations have been carried out for the stable orthorhombic structure (space group Im3¯ m) of the hydrogen sulfide SH3 for three values of the pressure P = 170, 180, and 225 GPa; and for an SH2 structure with a symmetry of I4/ mmm ( D4 h1¯7) for three values of pressure P = 150, 180, and 225 GP at temperature T = 200 K.

The VIMOS Public Extragalactic Redshift Survey (VIPERS) . Galaxy clustering and redshift-space distortions at z ≃ 0.8 in the first data release

NASA Astrophysics Data System (ADS)

de la Torre, S.; Guzzo, L.; Peacock, J. A.; Branchini, E.; Iovino, A.; Granett, B. R.; Abbas, U.; Adami, C.; Arnouts, S.; Bel, J.; Bolzonella, M.; Bottini, D.; Cappi, A.; Coupon, J.; Cucciati, O.; Davidzon, I.; De Lucia, G.; Fritz, A.; Franzetti, P.; Fumana, M.; Garilli, B.; Ilbert, O.; Krywult, J.; Le Brun, V.; Le Fèvre, O.; Maccagni, D.; Małek, K.; Marulli, F.; McCracken, H. J.; Moscardini, L.; Paioro, L.; Percival, W. J.; Polletta, M.; Pollo, A.; Schlagenhaufer, H.; Scodeggio, M.; Tasca, L. A. M.; Tojeiro, R.; Vergani, D.; Zanichelli, A.; Burden, A.; Di Porto, C.; Marchetti, A.; Marinoni, C.; Mellier, Y.; Monaco, P.; Nichol, R. C.; Phleps, S.; Wolk, M.; Zamorani, G.

2013-09-01

We present the general real- and redshift-space clustering properties of galaxies as measured in the first data release of the VIPERS survey. VIPERS is a large redshift survey designed to probe in detail the distant Universe and its large-scale structure at 0.5 < z < 1.2. We describe in this analysis the global properties of the sample and discuss the survey completeness and associated corrections. This sample allows us to measure the galaxy clustering with an unprecedented accuracy at these redshifts. From the redshift-space distortions observed in the galaxy clustering pattern we provide a first measurement of the growth rate of structure at z = 0.8: fσ8 = 0.47 ± 0.08. This is completely consistent with the predictions of standard cosmological models based on Einstein gravity, although this measurement alone does not discriminate between different gravity models. Based on observations collected at the European Southern Observatory, Cerro Paranal, Chile, using the Very Large Telescope under programmes 182.A-0886 and partly 070.A-9007. Also based on observations obtained with MegaPrime/MegaCam, a joint project of CFHT and CEA/DAPNIA, at the Canada-France-Hawaii Telescope (CFHT), which is operated by the National Research Council (NRC) of Canada, the Institut National des Sciences de l'Univers of the Centre National de la Recherche Scientifique (CNRS) of France, and the University of Hawaii. This work is based in part on data products produced at TERAPIX and the Canadian Astronomy Data Centre as part of the Canada-France-Hawaii Telescope Legacy Survey, a collaborative project of NRC and CNRS. The VIPERS web site is http://www.vipers.inaf.it/

Development and Applications of Advanced Electronic Structure Methods

NASA Astrophysics Data System (ADS)

Bell, Franziska

This dissertation contributes to three different areas in electronic structure theory. The first part of this thesis advances the fundamentals of orbital active spaces. Orbital active spaces are not only essential in multi-reference approaches, but have also become of interest in single-reference methods as they allow otherwise intractably large systems to be studied. However, despite their great importance, the optimal choice and, more importantly, their physical significance are still not fully understood. In order to address this problem, we studied the higher-order singular value decomposition (HOSVD) in the context of electronic structure methods. We were able to gain a physical understanding of the resulting orbitals and proved a connection to unrelaxed natural orbitals in the case of Moller-Plesset perturbation theory to second order (MP2). In the quest to find the optimal choice of the active space, we proposed a HOSVD for energy-weighted integrals, which yielded the fastest convergence in MP2 correlation energy for small- to medium-sized active spaces to date, and is also potentially transferable to coupled-cluster theory. In the second part, we studied monomeric and dimeric glycerol radical cations and their photo-induced dissociation in collaboration with Prof. Leone and his group. Understanding the mechanistic details involved in these processes are essential for further studies on the combustion of glycerol and carbohydrates. To our surprise, we found that in most cases, the experimentally observed appearance energies arise from the separation of product fragments from one another rather than rearrangement to products. The final chapters of this work focus on the development, assessment, and application of the spin-flip method, which is a single-reference approach, but capable of describing multi-reference problems. Systems exhibiting multi-reference character, which arises from the (near-) degeneracy of orbital energies, are amongst the most interesting in chemistry, biology and materials science, yet amongst the most challenging to study with electronic structure methods. In particular, we explored a substituted dimeric BPBP molecule with potential tetraradical character, which gained attention as one of the most promising candidates for an organic conductor. Furthermore, we extended the spin-flip approach to include variable orbital active spaces and multiple spin-flips. This allowed us to perform wave-function-based studies of ground- and excited-states of polynuclear metal complexes, polyradicals, and bond-dissociation processes involving three or more bonds.

Improvement of Predictive Ability by Uniform Coverage of the Target Genetic Space

PubMed Central

Bustos-Korts, Daniela; Malosetti, Marcos; Chapman, Scott; Biddulph, Ben; van Eeuwijk, Fred

2016-01-01

Genome-enabled prediction provides breeders with the means to increase the number of genotypes that can be evaluated for selection. One of the major challenges in genome-enabled prediction is how to construct a training set of genotypes from a calibration set that represents the target population of genotypes, where the calibration set is composed of a training and validation set. A random sampling protocol of genotypes from the calibration set will lead to low quality coverage of the total genetic space by the training set when the calibration set contains population structure. As a consequence, predictive ability will be affected negatively, because some parts of the genotypic diversity in the target population will be under-represented in the training set, whereas other parts will be over-represented. Therefore, we propose a training set construction method that uniformly samples the genetic space spanned by the target population of genotypes, thereby increasing predictive ability. To evaluate our method, we constructed training sets alongside with the identification of corresponding genomic prediction models for four genotype panels that differed in the amount of population structure they contained (maize Flint, maize Dent, wheat, and rice). Training sets were constructed using uniform sampling, stratified-uniform sampling, stratified sampling and random sampling. We compared these methods with a method that maximizes the generalized coefficient of determination (CD). Several training set sizes were considered. We investigated four genomic prediction models: multi-locus QTL models, GBLUP models, combinations of QTL and GBLUPs, and Reproducing Kernel Hilbert Space (RKHS) models. For the maize and wheat panels, construction of the training set under uniform sampling led to a larger predictive ability than under stratified and random sampling. The results of our methods were similar to those of the CD method. For the rice panel, all training set construction methods led to similar predictive ability, a reflection of the very strong population structure in this panel. PMID:27672112

From genomics to chemical genomics: new developments in KEGG

PubMed Central

Kanehisa, Minoru; Goto, Susumu; Hattori, Masahiro; Aoki-Kinoshita, Kiyoko F.; Itoh, Masumi; Kawashima, Shuichi; Katayama, Toshiaki; Araki, Michihiro; Hirakawa, Mika

2006-01-01

The increasing amount of genomic and molecular information is the basis for understanding higher-order biological systems, such as the cell and the organism, and their interactions with the environment, as well as for medical, industrial and other practical applications. The KEGG resource () provides a reference knowledge base for linking genomes to biological systems, categorized as building blocks in the genomic space (KEGG GENES) and the chemical space (KEGG LIGAND), and wiring diagrams of interaction networks and reaction networks (KEGG PATHWAY). A fourth component, KEGG BRITE, has been formally added to the KEGG suite of databases. This reflects our attempt to computerize functional interpretations as part of the pathway reconstruction process based on the hierarchically structured knowledge about the genomic, chemical and network spaces. In accordance with the new chemical genomics initiatives, the scope of KEGG LIGAND has been significantly expanded to cover both endogenous and exogenous molecules. Specifically, RPAIR contains curated chemical structure transformation patterns extracted from known enzymatic reactions, which would enable analysis of genome-environment interactions, such as the prediction of new reactions and new enzyme genes that would degrade new environmental compounds. Additionally, drug information is now stored separately and linked to new KEGG DRUG structure maps. PMID:16381885

Structural Verification of the First Orbital Wonder of the World - The Structural Testing and Analysis of the International Space Station (ISS)

NASA Technical Reports Server (NTRS)

Zipay, John J.; Bernstein, Karen S.; Bruno, Erica E.; Deloo, Phillipe; Patin, Raymond

2012-01-01

The International Space Station (ISS) can be considered one of the structural engineering wonders of the world. On par with the World Trade Center, the Colossus of Rhodes, the Statue of Liberty, the Great Pyramids, the Petronas towers and the Burj Khalifa skyscraper of Dubai, the ambition and scope of the ISS structural design, verification and assembly effort is a truly global success story. With its on-orbit life projected to be from its beginning in 1998 to the year 2020 (and perhaps beyond), all of those who participated in its development can consider themselves part of an historic engineering achievement representing all of humanity. The structural design and verification of the ISS could be the subject of many scholarly papers. Several papers have been written on the structural dynamic characterization of the ISS once it was assembled on-orbit [1], but the ground-based activities required to assure structural integrity and structural life of the individual elements from delivery to orbit through assembly and planned on-orbit operations have never been totally summarized. This paper is intended to give the reader an overview of some of the key decisions made during the structural verification planning for the elements of the U.S. On-Orbit Segment (USOS) as well as to summarize the many structural tests and structural analyses that were performed on its major elements. An effort is made for this paper to be summarily comprehensive, but as with all knowledge capture efforts of this kind, there are bound to be errors of omission. Should the reader discover any of these, please feel free to contact the principal author. The ISS (Figure 1) is composed of pre-integrated truss segments and pressurized elements supplied by NASA, the Russian Federal Space Agency (RSA), the European Space Agency (ESA) and the Japanese Aerospace Exploration Agency (JAXA). Each of these elements was delivered to orbit by a launch vehicle and connected to one another either robotically or autonomously. The primary structure of each element was assembled and verified by teams of responsible structural engineers within and among their respective agencies and agency contractors.

KSC-04PD-2689

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. A shipping container housing part of the new Orbiter Boom Sensor System (OBSS) is lifted from a truck into the Remote Manipulator System lab in the Vehicle Assembly Building (VAB). Once the entire structure has arrived, the OBSS will be assembled and undergo final checkout and testing in the lab prior to being transferred to the Orbiter Processing Facility (OPF) for installation on Space Shuttle Discovery. The 50-foot- long OBSS will be attached to the Remote Manipulator System, or Shuttle arm, and is one of the new safety measures for Return to Flight, equipping the orbiter with cameras and laser systems to inspect the Shuttle's Thermal Protection System while in space. Discovery is slated to fly mission STS-114 once Space Shuttle launches resume. The launch planning window is May 12 to June 3, 2005.

Securing Safety with Sensors

NASA Technical Reports Server (NTRS)

2004-01-01

The Robot Systems Technology Branch at NASA's Johnson Space Center collaborated with the Defense Advanced Research Projects Agency to design Robonaut, a humanoid robot developed to assist astronauts with Extra Vehicular Activities (EVA) such as space structure assembly and repair operations. By working side-by-side with astronauts or going where risks are too great for people, Robonaut is expected to expand the Space Agency s ability for construction and discovery. NASA engineers equipped Robonaut with human-looking, dexterous hands complete with five fingers to accomplish its tasks. The Robonaut hand is one of the first being developed for space EVA use and is the closest in size and capability to a suited astronaut s hand. As part of the development process, an advanced sensor system was needed to provide an improved method to measure the movement and forces exerted by Robonaut s forearms and hands.

KSC-08pd2572

NASA Image and Video Library

2008-09-05

CAPE CANAVERAL, Fla. – In the Payload Hazardous Servicing Facility at NASA’s Kennedy Space Center, crew members with the STS-125 mission get a close look at some of the equipment associated with their mission to service NASA’s Hubble Space Telescope. Looking at the Soft Capture Mechanism on the Flight Support Structure are a technician (pointing) and Mission Specialists Mike Massimino and Michael Good. The mechanism will enable the future rendezvous, capture and safe disposal of NASA's Hubble Space Telescope by either a crewed or robotic mission. The ring-like device attaches to Hubble’s aft bulkhead. The STS-125 crew is taking part in a crew equipment interface test, which provides experience handling tools, equipment and hardware they will use on their mission. Space shuttle Atlantis is targeted to launch on the STS-125 mission Oct. 10. Photo credit: NASA/Kim Shiflett

STS-112 crew during TCDT activities with M-113 carrier

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, Fla. - The STS-112 crew poses for a photo on the back of the M-113 armored personnel carrier they practiced driving as part of Terminal Countdown Demonstration Test activities. From left are Mission Specialist David Wolf, Pilot Pamela Melroy, Mission Specialist Sandra Magnus, Commander Jeffrey Ashby, and Mission Specialists Piers Sellers and Fyodor Yurchikhin, who is with the Russian Space Agency. Mission STS-112 aboard Space Shuttle Atlantis is scheduled to launch no earlier than Oct. 2, between 2 and 6 p.m. EDT. STS-112 is the 15th assembly mission to the International Space Station. Atlantis will be carrying the S1 Integrated Truss Structure, the first starboard truss segment. The S1 will be attached to the central truss segment, S0, during the 11-day mission.

STS-102 crew poses on the FSS at Launch Pad 39B during TCDT

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- At the 195-foot level on the Fixed Service Structure, Launch Pad 39B, members of the STS-102 crew relax after emergency escape training. From left are Mission Specialists Paul Richards, Andrew Thomas and Susan Helms, and Commander James Wetherbee. The crew is at KSC for Terminal Countdown Demonstration Test activities, which include the emergency training and a simulated launch countdown. STS-102 is the eighth construction flight to the International Space Station, with Space Shuttle Discovery carrying the Multi-Purpose Logistics Module Leonardo. Helms is part of the Expedition Two crew who will be on the mission to replace Expedition One on the International Space Station. Expedition One will return to Earth with Discovery. Launch on mission STS-102 is scheduled for March 8.

STS-102 crew poses on the FSS at Launch Pad 39B during TCDT

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- At the 195-foot level on the Fixed Service Structure, Launch Pad 39B, members of the STS-102 crew relax after emergency escape training. At left is Pilot James Kelly; in the center and right are Mission Specialists Yury Usachev and James Voss. The crew is at KSC for Terminal Countdown Demonstration Test activities, which include the emergency training and a simulated launch countdown. STS-102 is the eighth construction flight to the International Space Station, with Space Shuttle Discovery carrying the Multi-Purpose Logistics Module Leonardo. Usachev and Voss are part of the Expedition Two crew who will be on the mission to replace Expedition One on the International Space Station. Expedition One will return to Earth with Discovery. Launch on mission STS-102 is scheduled for March 8.

IAE - Inflatable Antenna Experiment

NASA Image and Video Library

1996-05-20

STS077-150-044 (20 May 1996) --- Following its deployment from the Space Shuttle Endeavour, the Spartan 207/Inflatable Antenna Experiment (IAE) payload is backdropped over the Grand Canyon. After the IAE completed its inflation process in free-flight, this view was photographed with a large format still camera. The activity came on the first full day of in-space operations by the six-member crew. Managed by Goddard Space Flight Center (GSFC), Spartan is designed to provide short-duration, free-flight opportunities for a variety of scientific studies. The Spartan configuration on this flight is unique in that the IAE is part of an additional separate unit which is ejected once the experiment is completed. The IAE experiment will lay the groundwork for future technology development in inflatable space structures, which will be launched and then inflated like a balloon on-orbit.

IAE - Inflatable Antenna Experiment

NASA Image and Video Library

1996-05-20

STS077-150-022 (20 May 1996) --- After leaving the cargo bay of the Space Shuttle Endeavour, the Spartan 207/Inflatable Antenna Experiment (IAE) payload goes through the final stages its inflation process, backdropped over clouds and blue water. The view was photographed with a large format still camera on the first full day of in-space operations by the six-member crew. Managed by Goddard Space Flight Center (GSFC), Spartan is designed to provide short-duration, free-flight opportunities for a variety of scientific studies. The Spartan configuration on this flight is unique in that the IAE is part of an additional separate unit which is ejected once the experiment is completed. The IAE experiment will lay the groundwork for future technology development in inflatable space structures, which will be launched and then inflated like a balloon on-orbit.

Following its deployment from the Space Shuttle Endeavour, the Spartan 207/Inflatable Antenna

NASA Technical Reports Server (NTRS)

1996-01-01

STS-77 ESC VIEW --- Following its deployment from the Space Shuttle Endeavour, the Spartan 207/Inflatable Antenna Experiment (IAE) payload is backdropped against a wall of grayish clouds. The view was photographed with an Electronic Still Camera (ESC) and downlinked to flight controllers on the first full day of orbital operations by the six-member crew. Managed by Goddard Space Flight Center (GSFC), Spartan is designed to provide short-duration, free-flight opportunities for a variety of scientific studies. The Spartan configuration on this flight is unique in that the IAE is part of an additional separate unit which is ejected once the experiment is completed. The IAE experiment will lay the groundwork for future technology development in inflatable space structures, which will be launched and then inflated like a balloon on-orbit. GMT: 08:14:57.

Following its deployment from the Space Shuttle Endeavour, the Spartan 207/Inflatable Antenna

NASA Technical Reports Server (NTRS)

1996-01-01

STS-77 ESC VIEW --- Following its deployment from the Space Shuttle Endeavour, the Spartan 207/Inflatable Antenna Experiment (IAE) payload is backdropped over clouds and water. The view was photographed with an Electronic Still Camera (ESC) and downlinked to flight controllers on the first full day of orbital operations by the six-member crew. Managed by Goddard Space Flight Center (GSFC), Spartan is designed to provide short-duration, free-flight opportunities for a variety of scientific studies. The Spartan configuration on this flight is unique in that the IAE is part of an additional separate unit which is ejected once the experiment is completed. The IAE experiment will lay the groundwork for future technology development in inflatable space structures, which will be launched and then inflated like a balloon on-orbit. GMT: 08:12:50.

Following its deployment from the Space Shuttle Endeavour, the Spartan 207/Inflatable Antenna

NASA Technical Reports Server (NTRS)

1996-01-01

STS-77 ESC VIEW --- Following its deployment from the Space Shuttle Endeavour, the Spartan 207/Inflatable Antenna Experiment (IAE) payload is backdropped over clouds and water. The view was photographed with an Electronic Still Camera (ESC) and downlinked to flight controllers on the first full day of orbital operations by the six-member crew. Managed by Goddard Space Flight Center (GSFC), Spartan is designed to provide short-duration, free-flight opportunities for a variety of scientific studies. The Spartan configuration on this flight is unique in that the IAE is part of an additional separate unit which is ejected once the experiment is completed. The IAE experiment will lay the groundwork for future technology development in inflatable space structures, which will be launched and then inflated like a balloon on-orbit. GMT: 08:04:38.

Experimental evaluation of active-member control of precision structures

NASA Technical Reports Server (NTRS)

Fanson, James; Blackwood, Gary; Chu, Cheng-Chih

1989-01-01

The results of closed loop experiments that use piezoelectric active-members to control the flexible motion of a precision truss structure are described. These experiments are directed toward the development of high-performance structural systems as part of the Control/Structure Interaction (CSI) program at JPL. The focus of CSI activity at JPL is to develop the technology necessary to accurately control both the shape and vibration levels in the precision structures from which proposed large space-based observatories will be built. Structural error budgets for these types of structures will likely be in the sub-micron regime; optical tolerances will be even tighter. In order to achieve system level stability and local positioning at this level, it is generally expected that some form of active control will be required.

Finite Element Analysis of an Energy Absorbing Sub-floor Structure

NASA Technical Reports Server (NTRS)

Moore, Scott C.

1995-01-01

As part of the Advanced General Aviation Transportation Experiments program, the National Aeronautics and Space Administration's Langley Research Center is conducting tests to design energy absorbing structures to improve occupant survivability in aircraft crashes. An effort is currently underway to design an Energy Absorbing (EA) sub-floor structure which will reduce occupant loads in an aircraft crash. However, a recent drop test of a fuselage specimen with a proposed EA sub-floor structure demonstrated that the effects of sectioning the fuselage on both the fuselage section's stiffness and the performance of the EA structure were not fully understood. Therefore, attempts are underway to model the proposed sub-floor structure on computers using the DYCAST finite element code to provide a better understanding of the structure's behavior in testing, and in an actual crash.

Damping Goes the Distance in Golf

NASA Technical Reports Server (NTRS)

2004-01-01

In the late 1980s, Dr. Benjamin Dolgin of NASA s Jet Propulsion Laboratory developed a concept for a high-damping graphite/viscoelastic material for the Strategic Defense Initiative (popularly referred to as "Star Wars"), as part of a space-based laser anti-missile program called "Asterix." Dolgin drummed up this concept with the intention of stabilizing weapons launch platforms in space, where there is no solid ground to firmly support these structures. Without the inclusion of high-damping material, the orbital platforms were said to vibrate for 20 minutes after force was applied - a rate deemed "unacceptable" by leaders of the Strategic Defense Initiative.

STS-47 MS Davis and Pilot Brown monitor ISAIAH on OV-105's middeck

NASA Image and Video Library

1992-09-20

STS047-02-018 (12 - 20 Sept 1992) --- Astronauts N. Jan Davis, mission specialist, and Curtis L. Brown, Jr., pilot, oversee the progress of some of the 180 female Oriental Hornets onboard the Space Shuttle Endeavour. The insects are part of the Israeli Space Agency Investigation About Hornets (ISAIAH) experiment. The objective of this experiment is to examine the effects of microgravity on the orientation, reproductive capability and social activity of the hornets. Also, the direction of comb-building by hornet workers in microgravity, as well as the structural integrity of the combs, will be examined.

National Space Transportation and Support Study/technology requirements and plans

NASA Technical Reports Server (NTRS)

Walberg, G. D.; Gasperich, F. J., Jr.; Scheyhing, E. R.

1986-01-01

This paper presents a generic technology plan which has been developed as part of the National Space Transportation and Support Study. This program, which addresses a wide variety of potentially high payoff technology areas, is structured to promote both enhanced vehicle performance and greatly improved operational efficiency and includes both evolutionary and breakthrough technologies. The plan is presented in terms of disciplinary plan elements, which were developed by joint NASA/USAF disciplinary working groups, and as a set of demonstration projects which serve as focal points for the overall plan and drive the development of the many interrelated disciplinary activities.

The definition of the V zone for the safety space of functional surgery of the tongue.

PubMed

Hou, Tiening; Shao, Jinyan; Fang, Songhua

2012-01-01

To define safety space for functional surgery of the tongue. Prospective nonrandomized study. Computed tomographic angiography of the lingual artery was performed in 107 in-patients with obstructive sleep apnea syndrome and 17 controls. The safety space was ascertained according to the course of lingual artery. The course of the lingual artery, termed the Big Dipper bowl of the tongue, was similar in each group. The tissue above the lingual artery and the vacuity of the hypoglossal/lingual artery neurovascular bundle (HLNVB) formed a three-dimensional structure. The anterior part was named the V prozone. Its anterior border was the tangent plane of the deep lingual artery, its posterior border the circumvallate papilla, its width the interval of bilateral margins at the corresponding parts of the tongue, and its height the level of the middle lingual frenulum. The posterior portion between the bilateral dorsal arteries in the tongue base was named the V postzone. Its width was 31.42±3.82 mm when the tongue was in a resting position, and its height was the distance from the foramen cecum to the bottom of the epiglottic vallecula. The inferior part under the intrinsic lingual muscles was named the hypoglossal floor. It is a relatively restricted surgery zone. The V zone of the tongue without HLNVB travelling provides enough of safety space for functional surgery on the tongue. Copyright © 2011 The American Laryngological, Rhinological, and Otological Society, Inc.

Space images processing methodology for assessment of atmosphere pollution impact on forest-swamp territories

NASA Astrophysics Data System (ADS)

Polichtchouk, Yuri; Tokareva, Olga; Bulgakova, Irina V.

2003-03-01

Methodical problems of space images processing for assessment of atmosphere pollution impact on forest ecosystems using geoinformation systems are developed. An approach to quantitative assessment of atmosphere pollution impact on forest ecosystems is based on calculating relative squares of forest landscapes which are inside atmosphere pollution zones. Landscape structure of forested territories in the southern part of Western Siberia are determined on the basis of procession of middle resolution space images from spaceborn Resource-O. Particularities of atmosphere pollution zones modeling caused by gas burning in torches on territories of oil fields are considered. Pollution zones were revealed by modeling of contaminants dispersal in atmosphere with standard models. Polluted landscapes squares are calculated depending on atmosphere pollution level.

Extraction of process zones and low-dimensional attractive subspaces in stochastic fracture mechanics

PubMed Central

Kerfriden, P.; Schmidt, K.M.; Rabczuk, T.; Bordas, S.P.A.

2013-01-01

We propose to identify process zones in heterogeneous materials by tailored statistical tools. The process zone is redefined as the part of the structure where the random process cannot be correctly approximated in a low-dimensional deterministic space. Such a low-dimensional space is obtained by a spectral analysis performed on pre-computed solution samples. A greedy algorithm is proposed to identify both process zone and low-dimensional representative subspace for the solution in the complementary region. In addition to the novelty of the tools proposed in this paper for the analysis of localised phenomena, we show that the reduced space generated by the method is a valid basis for the construction of a reduced order model. PMID:27069423

STS-92 crew takes part in a Leak Seal Kit Fit Check in the SSPF

NASA Technical Reports Server (NTRS)

1999-01-01

STS-92 Mission Specialist Koichi Wakata, with the National Space Development Agency of Japan (NASDA), and Pilot Pamela A. Melroy take a break during a Leak Seal Kit Fit Check of the Pressurized Mating Adapter -3 in the Space Station Processing Facility. Also participating are the other crew members Commander Brian Duffy and Mission Specialists Leroy Chiao (Ph.D.), Peter J.K. 'Jeff' Wisoff (Ph.D.), Michael E. Lopez-Alegria and William Surles 'Bill' McArthur Jr. STS-92 is the fourth U.S. flight for construction of the International Space Station. The mission payload also includes an integrated truss structure (Z-1 truss). Launch of STS-92 is scheduled for Feb. 24, 2000.

KSC-00pp0373

NASA Image and Video Library

2000-03-21

KENNEDY SPACE CENTER, FLA. -- Workers in the Payload Changeout Room (PCR) at Launch Pad 39A check out the SPACEHAB Double Module before moving into the PCR. Part of the Rotating Service Structure, the PCR is an environmentally controlled facility supporting cargo delivery to the pad and vertical installation in the orbiter cargo bay. The primary payloads on mission STS-101, the module and ICC contain internal logistics and resupply cargo for restoring full redundancy to the International Space Station power system in preparation for the arrival of the next pressurized module, the Russian-built Zvezda. The payloads will be transferred to Space Shuttle Atlantis after Atlantis rolls out to the pad. Launch of Atlantis on mission STS-101 is scheduled no earlier than April 17, 2000

KSC00pp0373

NASA Image and Video Library

2000-03-21

KENNEDY SPACE CENTER, FLA. -- Workers in the Payload Changeout Room (PCR) at Launch Pad 39A check out the SPACEHAB Double Module before moving into the PCR. Part of the Rotating Service Structure, the PCR is an environmentally controlled facility supporting cargo delivery to the pad and vertical installation in the orbiter cargo bay. The primary payloads on mission STS-101, the module and ICC contain internal logistics and resupply cargo for restoring full redundancy to the International Space Station power system in preparation for the arrival of the next pressurized module, the Russian-built Zvezda. The payloads will be transferred to Space Shuttle Atlantis after Atlantis rolls out to the pad. Launch of Atlantis on mission STS-101 is scheduled no earlier than April 17, 2000

Damping of composite plate for space structures: Prediction and measurement methods

NASA Astrophysics Data System (ADS)

Marchetti, M.; Morganti, F.; Mucciante, L.; Bruno, C.

Composite materials are extensively used for space structures: the sandwich and laminate panels are now part of the current manufacturing technology for spacecraft and antenna reflectors. Depending on the applications, some mechanical parameters are considered driving in the design, in order to satisfy the required structural performance. Among them, the knowledge of the damping is necessary to evaluate the dynamic behaviour of the structures. That particularly applies to the composite structures for space applications; for which an optimization of their mass versus their stiffness is attempted to take into account both launch and on station environments. The prediction of the damping factors of composites is rather difficult since it depends not only on the nature of the materials, which are in general neither homogeneous nor isotropic, but also on the kind of structures (i.e. size and shape) and on the manufacturing methodology, due to the strong non-linearity in the material behaviour. All the above is also impacted by the tendency of these materials to microcracking under stress. This phenomenon, mainly correlated to the cyclic loads introduced by thermal ageing, produces a variation of damping with time. For these reasons an evaluation of the damping characteristics of this kind of structure has been generally obtained by tests on full scale hardware or specimens with suitable dimension, being any prediction method rather difficult to apply. The purpose of this work is to study the damping behaviour of Gr/Ep, Kevlar/Ep and Glass Fiber/Ep composites which are extensively used in space structures, starting from test results on beam and plate shaped specimens. Experimental evidence will be fitted in an analytical and numerical study, the purpose of which is to correlate the energy dissipated in the composite to the lamination typology. Using a Finite Element Method, the amount of energy dissipated for each mode will be also evaluated, providing the correlations with the test results obtained with a modal analyzer.

In-Space Recycler Technology Demonstration

NASA Technical Reports Server (NTRS)

Hoyt, Rob; Werkheiser, NIKI; Kim, Tony

2016-01-01

In 2014, a 3D printer was installed and used successfully on the International Space Station (ISS), creating the first additively manufactured part in space. While additive manufacturing is a game changing technology for exploration missions, the process still requires raw feedstock material to fabricate parts. Without a recycling capability, a large supply of feedstock would need to be stored onboard, which negates the logistical benefits of these capabilities. Tethers Unlimited, Inc. (TUI), received a Small Business Innovation Research (SBIR) award to design and build the first In-space Recycler for demonstration aboard the ISS in 2017. To fully test this technology in microgravity, parts will be 3D printed, recycled into reusable filament, and then reprinted into new parts. Recycling scrap into printer filament is quite challenging in that a recycler must be able to handle a large variety of possible scrap configurations and densities. New challenges include: dealing with inevitable contamination of the scrap material, minimizing damage to the molecular structure of the plastic during reprocessing, managing a larger volume of hot liquid plastic, and exercising greater control over the cooling/resolidification of the material. TUI has developed an architecture that addresses these challenges by combining standard, proven technologies with novel, patented processes developed through this effort. Results show that the filament diameter achieved is more consistent than commercial filament, with only minimal degradation of material properties over recycling steps. In May 2016, TUI completed fabrication of a flight prototype, which will ultimately progress to the demonstration unit for the ISS as a testbed for future exploration missions. This capability will provide significant cost savings by reducing the launch mass and volume required for printer feedstock as well as reduce waste that must be stored or disposed.

KSC00pp0637

NASA Image and Video Library

2000-05-18

KENNEDY SPACE CENTER, Fla. -- After rollback of the Rotating Service Structure, Space Shuttle Atlantis can be seen atop the mobile launcher platform (MLP) on Launch Pad 39A. Below the MLP is the flame trench, part of the flame deflector system that insulates pad structures from the intense heat of launch. Made of concrete and refractory brick, the trench is 490 feet long, 48 feet wide and 40 feet high. At the top of the orange external tank can be seen the Gaseous Oxygen Vent Hood, often called the "beanie cap." The hood helps vent gaseous oxygen vapors away from the Space Shuttle. The hood will be raised and retracted two and a half minutes before launch. Abutting the side of Atlantis is the orbiter access arm with the environmental chamber known as the White Room at the end. The White Room provides access to the crew compartment. This will be the third assembly flight to the International Space Station. Liftoff of Space Shuttle Atlantis for the 10-day STS-101 mission is scheduled for about 6:12 a.m. EDT from Launch Pad 39A. Landing is targeted for May 29 at 2:19 a.m. EDT. This is the 98th Shuttle flight and the 21st flight for Shuttle Atlantis

KSC-00pp0637

NASA Image and Video Library

2000-05-18

KENNEDY SPACE CENTER, Fla. -- After rollback of the Rotating Service Structure, Space Shuttle Atlantis can be seen atop the mobile launcher platform (MLP) on Launch Pad 39A. Below the MLP is the flame trench, part of the flame deflector system that insulates pad structures from the intense heat of launch. Made of concrete and refractory brick, the trench is 490 feet long, 48 feet wide and 40 feet high. At the top of the orange external tank can be seen the Gaseous Oxygen Vent Hood, often called the "beanie cap." The hood helps vent gaseous oxygen vapors away from the Space Shuttle. The hood will be raised and retracted two and a half minutes before launch. Abutting the side of Atlantis is the orbiter access arm with the environmental chamber known as the White Room at the end. The White Room provides access to the crew compartment. This will be the third assembly flight to the International Space Station. Liftoff of Space Shuttle Atlantis for the 10-day STS-101 mission is scheduled for about 6:12 a.m. EDT from Launch Pad 39A. Landing is targeted for May 29 at 2:19 a.m. EDT. This is the 98th Shuttle flight and the 21st flight for Shuttle Atlantis

The Dyad as a Centerless Structure: a Philosophical, Sociological and Psychoanalytic Study.

PubMed

Cohen, Tsiky

2018-06-04

This paper attempts to elucidate the phenomenological experience produced in the dyad from a structural perspective. It proposes to regard the dyadic configuration as a "centerless structure", containing the highest potential for actualization as "free play", both in a negative sense and a positive one. In the first part of the paper, the author uses Wittgenstein's "family- resemblances" method, to illustrate how the descriptions given to diverse dyadic relations in different domains and disciplines, share similarities and closeness with two main types of dyadic relations: a "synonymy relation" based on a common sense of similarity and likeness and an "antonymy relation" characterized by dominant and complementary relations. Although the two types of relations reflect through additional social forms, the author proposes that what is unique to the dyad structure is the repetitive movement that takes place, back and forth, between them. It indicates a lack of structural function that can organize, regulate and balance the intersubjective space. In the second part of the paper, inspired by Derrida and Simmel (Derrida, 1966; Simmel, 1950), the author suggests that the dyadic configuration struggles to produce a structured, stable center of meaning, and therefore it encourages the structure's free play potential.

Anomalous transport regimes and asymptotic concentration distributions in the presence of advection and diffusion on a comb structure

NASA Astrophysics Data System (ADS)

Dvoretskaya, Olga A.; Kondratenko, Peter S.

2009-04-01

We study the transport of impurity particles on a comb structure in the presence of advection. The main body concentration and asymptotic concentration distributions are obtained. Seven different transport regimes occur on the comb structure with finite teeth: classical diffusion, advection, quasidiffusion, subdiffusion, slow classical diffusion, and two kinds of slow advection. Quasidiffusion deserves special attention. It is characterized by a linear growth of the mean-square displacement. However, quasidiffusion is an anomalous transport regime. We established that a change in transport regimes in time leads to a change in regimes in space. Concentration tails have a cascade structure, namely, consisting of several parts.

A beam splitter of natural light guiding system based on dichroic prism for ecological illumination

NASA Astrophysics Data System (ADS)

Li, Yu-Chi; Chen, Yi-Yung; Whang, Allen Jong-Woei

2009-08-01

In thremmatology, many researches focus on ecological illumination for improving the growing speed of animal or plant. According to the Trichromatic theory, any specific color can be made up of red, green, and blue light. Sunlight has full spectrum so it is the most applicable source. A Natural Light Guiding System includes collecting, transmitting, and lighting parts. In our research, we would like to design a beam splitter in the transmitting part to separate the sunlight into red, green, and blue light for ecological illumination. We use high pass and low pass dichroic coatings in a prism, called dichroic prism, to be the beam splitter to separate the wavelength. For measuring the spectra of the exit beams, we build a space with the Natural Light Guiding System. In the space, the spectra of sunlight outside and inside the space and the exit beams of the beam splitter are measured. Finally, we use prismatic structure to design the beam splitter, and optimize the surface of the element with aspheric surface and Fresnel surface to reduce the beam angle of exit light.

STS-106 crew spends time at SPACEHAB for CEIT

NASA Technical Reports Server (NTRS)

2000-01-01

As part of Crew Equipment Interface Test (CEIT) activities at SPACEHAB, members of the STS-106 crew check out a Maximum Envelope Support Structure (MESS) rack they will be using during their mission to the International Space Station. Seen here (with backs to camera, in uniform) are Mission Specialist Richard A. Mastracchio, Pilot Scott D. Altman, Boris V. Morukov, and Edward T. Lu (at right). Also taking part in the CEIT are Commander Terrence W. Wilcutt and Mission Specialists Yuri I. Malenchenko and Daniel C. Burbank. Malenchenko and Morukov represent the Russian Aviation and Space Agency. STS-106 is scheduled to launch Sept. 8, 2000, at 8:31 a.m. EDT from Launch Pad 39B on an 11-day mission. The seven-member crew will prepare the Space Station for its first resident crew and begin outfitting the newly arrived Zvezda Service Module. They will perform support tasks on orbit, transfer supplies and prepare the Zvezda living quarters for the first long-duration crew, dubbed '''Expedition One,''' which is due to arrive at the Station in late fall.

ELECTRON MICROSCOPE AND X-RAY DIFFRACTION STUDIES ON A HOMOLOGOUS SERIES OF SATURATED PHOSPHATIDYLCHOLINES.

PubMed

ELBERS, P F; VERVERGAERT, P H

1965-05-01

Three homologous saturated phosphatidylcholines were studied by electron microscopy after tricomplex fixation. The results are compared with those obtained by x-ray diffraction analysis of the same and some other homologous compounds, in the dry crystalline state and after tricomplex fixation. By electron microscopy alternating dark and light bands are observed which are likely to correspond to phosphatide double layers. X-Ray diffraction reveals the presence of lamellar structures of regular spacing. The layer spacings obtained by both methods are in good agreement. From the electron micrographs the width of the polar parts of the double layers can be derived directly. The width of the carboxylglycerylphosphorylcholine moiety of the layers is found by extrapolating the x-ray diffraction data to zero chain length of the fatty acids. When from this width the contribution of the carboxylglyceryl part of the molecules is subtracted, again we find good agreement with the electron microscope measurements. An attempt has been made to account for the different layer spacings measured in terms of orientation of the molecules within the double layers.

Launch Vehicle Stage Adapter from Start to Stack

NASA Image and Video Library

2016-10-16

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

Inclusion and Art Education: "Welcome to the Big Room, Everything's Alright"

ERIC Educational Resources Information Center

Penketh, Claire

2017-01-01

This article offers an exploration of the art room as part of a broader project to consider the ways in which normative practices in art and design education can include and exclude students. The art classroom is explored here as a "disrupted space" and one that can promote movement between the structures and boundaries that affect our…

Composite Structures Damage Tolerance Analysis Methodologies

NASA Technical Reports Server (NTRS)

Chang, James B.; Goyal, Vinay K.; Klug, John C.; Rome, Jacob I.

2012-01-01

This report presents the results of a literature review as part of the development of composite hardware fracture control guidelines funded by NASA Engineering and Safety Center (NESC) under contract NNL04AA09B. The objectives of the overall development tasks are to provide a broad information and database to the designers, analysts, and testing personnel who are engaged in space flight hardware production.

Integrated Structural and Cable Connector

NASA Technical Reports Server (NTRS)

Totah, R. S.

1982-01-01

Ball-and-socket coupling includes fiber-optic cable. Three steps couple two parts of fiber-optic cable: ball is inserted into socket; cone is released in, and cable moves toward plug. Sleeve is pulled to end of its travel and cable and plug are mated. Device is a quick-connect/disconnect coupling that has application in hazardous environments, such as space, undersea and nuclear installations.

Chandra X-Ray Observatory Image of Crab Nebula

NASA Technical Reports Server (NTRS)

1999-01-01

After barely 2 months in space, the Chandra X-Ray Observatory (CXO) took this sturning image of the Crab Nebula, the spectacular remains of a stellar explosion, revealing something never seen before, a brilliant ring around the nebula's heart. The image shows the central pulsar surrounded by tilted rings of high-energy particles that appear to have been flung outward over a distance of more than a light-year from the pulsar. Perpendicular to the rings, jet-like structures produced by high-energy particles blast away from the pulsar. Hubble Space Telescope images have shown moving knots and wisps around the neutron star, and previous x-ray images have shown the outer parts of the jet and hinted at the ring structure. With CXO's exceptional resolution, the jet can be traced all the way in to the neutron star, and the ring pattern clearly appears. The image was made with CXO's Advanced Charge-Coupled Device (CCD) Imaging Spectrometer (ACIS) and High Energy Transmission Grating. The Crab Nebula, easily the most intensively studied object beyond our solar system, has been observed using virtually every astronomical instrument that could see that part of the sky

Space, self, and the theater of consciousness.

PubMed

Trehub, Arnold

2007-06-01

Over a decade ago, I introduced a large-scale theory of the cognitive brain which explained for the first time how the human brain is able to create internal models of its intimate world and invent models of a wider universe. An essential part of the theoretical model is an organization of neuronal mechanisms which I have named the Retinoid Model [Trehub, A. (1977). Neuronal models for cognitive processes: Networks for learning, perception and imagination. Journal of Theoretical Biology, 65, 141-169; Trehub, A. (1991). The Cognitive Brain: MIT Press]. This hypothesized brain system has structural and dynamic properties enabling it to register and appropriately integrate disparate foveal stimuli into a perspectival, egocentric representation of an extended 3D world scene including a neuronally tokened locus of the self which, in this theory, is the neuronal origin of retinoid space. As an integral part of the larger neuro-cognitive model, the retinoid system is able to perform many other useful perceptual and higher cognitive functions. In this paper, I draw on the hypothesized properties of this system to argue that neuronal activity within the retinoid structure constitutes the phenomenal content of consciousness and the unique sense of self that each of us experiences.

A spatial data handling system for retrieval of images by unrestricted regions of user interest

NASA Technical Reports Server (NTRS)

Dorfman, Erik; Cromp, Robert F.

1992-01-01

The Intelligent Data Management (IDM) project at NASA/Goddard Space Flight Center has prototyped an Intelligent Information Fusion System (IIFS), which automatically ingests metadata from remote sensor observations into a large catalog which is directly queryable by end-users. The greatest challenge in the implementation of this catalog was supporting spatially-driven searches, where the user has a possible complex region of interest and wishes to recover those images that overlap all or simply a part of that region. A spatial data management system is described, which is capable of storing and retrieving records of image data regardless of their source. This system was designed and implemented as part of the IIFS catalog. A new data structure, called a hypercylinder, is central to the design. The hypercylinder is specifically tailored for data distributed over the surface of a sphere, such as satellite observations of the Earth or space. Operations on the hypercylinder are regulated by two expert systems. The first governs the ingest of new metadata records, and maintains the efficiency of the data structure as it grows. The second translates, plans, and executes users' spatial queries, performing incremental optimization as partial query results are returned.

Staging in polyacetylene-iodine conductors

NASA Astrophysics Data System (ADS)

Baughman, R. H.; Murthy, N. S.; Miller, G. G.; Shacklette, L. W.

1983-07-01

Evidence is presented for the existence of highly conducting polyacetylene complexes with structures related to high-stage graphite, as well as structures related to first-stage graphite. X-ray diffraction measurements on polyacetylene-iodine complexes indicate equatorial lines at 7.7-8.0 and 13.8-14.3 Å. The shorter spacing arises in part from a structure in which iodine-rich planes alternate with planes of polyacetylene chains. The longer spacing, which disappears upon atmospheric exposure, is consistent with a structure analogous to third-stage graphite in which dopant-rich planes are separated by three close-packed planes of polyacetylene chains. The third-stage complex can be viewed as a perturbation of the structure of undoped polyacetylene, with the region between dopant layers consisting essentially of a one unit cell thickness of the parent polymer structure. Packing calculations for this model, in which a linear column of anions (I3- and/or I5-) displaces either every chain or every other chain in the dopant-rich layer, provide an interlayer spacing which is equal to that observed. Evidence consistent with third-stage structures (with both fractional occupation and complete occupation of the dopant plane) is also found by reexamination of published sorption data, which provides slope changes at close to the calculated limiting compositions for these structures [(CHI0.056)x and (CHI0.13)x]. However, a first-stage structure with alternating dopant arrays and polymer chains in the dopant plane [for which (CHI0.13)x is calculated] provides a better explanation for the second slope change, as well as for the composition obtained under dynamic vacuum, (CHI0.14)x. These results for iodine complexes are compared with those derived for the group VA halide complexes of polyacetylene.

Compression Buckling Behavior of Large-Scale Friction Stir Welded and Riveted 2090-T83 Al-Li Alloy Skin-Stiffener Panels

NASA Technical Reports Server (NTRS)

Hoffman, Eric K.; Hafley, Robert A.; Wagner, John A.; Jegley, Dawn C.; Pecquet, Robert W.; Blum, Celia M.; Arbegast, William J.

2002-01-01

To evaluate the potential of friction stir welding (FSW) as a replacement for traditional rivet fastening for launch vehicle dry bay construction, a large-scale friction stir welded 2090-T83 aluminum-lithium (Al-Li) alloy skin-stiffener panel was designed and fabricated by Lockheed-Martin Space Systems Company - Michoud Operations (LMSS) as part of NASA Space Act Agreement (SAA) 446. The friction stir welded panel and a conventional riveted panel were tested to failure in compression at the NASA Langley Research Center (LaRC). The present paper describes the compression test results, stress analysis, and associated failure behavior of these panels. The test results provide useful data to support future optimization of FSW processes and structural design configurations for launch vehicle dry bay structures.

An Examination of Radiation Induced Tensile Failure of Stressed and Unstressed Polymer Films Flown on MISSE-6

NASA Technical Reports Server (NTRS)

Miller, Sharon K.; Sechkar, Edward A.

2012-01-01

Thin film polymers are used in many spacecraft applications for thermal control (multilayer insulation and sunshields), as lightweight structural members (solar array blankets, inflatable/deployable structures) and have been proposed for propulsion (solar sails). Polymers in these applications are often under a tensile load and are directly exposed to the space environment, therefore it is important to understand the effect of stress in combination with the environment on the durability of these polymer films. The purpose of the Polymer Film Tensile Experiment, flown as part of Materials International Space Station Experiment 6 (MISSE 6), was to expose a variety of polymer films to the low Earth orbital environment under both relaxed and tension conditions. This paper describes the results of post flight tensile testing of these samples.

Searching for City Centre of Stalowa Wola

NASA Astrophysics Data System (ADS)

Ciepiela, Agnieszka

2017-10-01

In cities that have historic urban layout, with a clearly separated main representative space - the main square, or the main street (a pedestrian area), specifying the location of the centre is not difficult neither for residents nor for people from the “outside". Interesting is a situation in which, in the structure of the city there is no clearly designated main public space equipped with all the necessary services, and the period of location and development of urban system falls on the twentieth century. One example of such city in Poland is Stalowa Wola - founded in 1938 as part of the Central Industrial District. The city was located not far away from Rozwadów town, which, because of the development of Stalowa Wola, was absorbed by the new structure and became a district of the bigger city.

Analysis of Eddy Current Capabilities for the Detection of Outer Diameter Stress Corrosion Cracking in Small Bore Metallic Structures

NASA Technical Reports Server (NTRS)

Wincheski, Buzz; Williams, Phillip; Simpson, John

2007-01-01

The use of eddy current techniques for the detection of outer diameter damage in tubing and many complex aerospace structures often requires the use of an inner diameter probe due to a lack of access to the outside of the part. In small bore structures the probe size and orientation are constrained by the inner diameter of the part, complicating the optimization of the inspection technique. Detection of flaws through a significant remaining wall thickness becomes limited not only by the standard depth of penetration, but also geometrical aspects of the probe. Recently, an orthogonal eddy current probe was developed for detection of such flaws in Space Shuttle Primary Reaction Control System (PRCS) Thrusters. In this case, the detection of deeply buried stress corrosion cracking by an inner diameter eddy current probe was sought. Probe optimization was performed based upon the limiting spatial dimensions, flaw orientation, and required detection sensitivity. Analysis of the probe/flaw interaction was performed through the use of finite and boundary element modeling techniques. Experimental data for the flaw detection capabilities, including a probability of detection study, will be presented along with the simulation data. The results of this work have led to the successful deployment of an inspection system for the detection of stress corrosion cracking in Space Shuttle Primary Reaction Control System (PRCS) Thrusters.

KSC-01pp1334

NASA Image and Video Library

2001-07-19

KENNEDY SPACE CENTER, Fla. -- On the 195-foot level of the Fixed Service Structure, Launch Pad 39A, the STS-105 and Expedition Three crews listen to instructions about use of the slidewire basket, part of emergency egress training at the pad. From left are Expedition Three Commander Frank Culbertson, STS-105 Pilot Rick Sturckow; cosmonauts Mikhail Tyurin and Vladimir Nikolaevich Dezhurov; Mission Specialist Patrick Forrester, Commander Scott Horowitz and Mission Specialist Daniel Barry. Both crews are at KSC to take part in Terminal Countdown Demonstration Test activities, which include the emergency egress training, a simulated launch countdown and familiarization with the payload. Mission STS-105 will be transporting the Expedition Three crew, several payloads and scientific experiments to the International Space Station aboard Discovery. The current Expedition Two crew members on the Station will return to Earth on Discovery. Launch of Discovery is scheduled no earlier than Aug. 9, 2001

Beginning the 21st century with advanced Automatic Parts Identification (API)

NASA Technical Reports Server (NTRS)

Schramm, Fred; Roxby, Don

1994-01-01

Under the direction of the NASA George C. Marshall Space Flight Center, Huntsville, Alabama, the development and commercialization of an advanced Automated Parts Indentification (API) system is being undertaken by Rockwell International Corporation. The new API system is based on a variable sized, machine-readable, two-dimensioanl matrix symbol that can be applied directly onto most metallic and nonmetallic materials using safe, permanent marking methods. Its checkerboard-like structure is the most space efficient of all symbologies. This high data-density symbology can be applied to products of different material sizes and geometries using application-dependent, computer-driven marking devices. The high fidelity markings produced by these devices can then be captured using a specially designed camera linked to any IBM-compatible computer. Applications of compressed symbology technology will reduce costs and improve quality, productivity, and processes in a wide variety of federal and commercial applications.

STS-105 and Expedition Three crews get slidewire training at Launch Pad 39A

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- On the 195-foot level of the Fixed Service Structure, Launch Pad 39A, the STS-105 and Expedition Three crews listen to instructions about use of the slidewire basket, part of emergency egress training at the pad. From left are Expedition Three Commander Frank Culbertson, STS-105 Pilot Rick Sturckow; cosmonauts Mikhail Tyurin and Vladimir Nikolaevich Dezhurov; Mission Specialist Patrick Forrester, Commander Scott Horowitz and Mission Specialist Daniel Barry. Both crews are at KSC to take part in Terminal Countdown Demonstration Test activities, which include the emergency egress training, a simulated launch countdown and familiarization with the payload. Mission STS-105 will be transporting the Expedition Three crew, several payloads and scientific experiments to the International Space Station aboard Discovery. The current Expedition Two crew members on the Station will return to Earth on Discovery. Launch of Discovery is scheduled no earlier than Aug. 9, 2001.

Commercial opportunities utilizing the International Space Station

NASA Astrophysics Data System (ADS)

Kearney, Michael E.; Mongan, Phil; Overmyer, Carolyn M.; Jackson, Kenneth

1998-01-01

The International Space Station (ISS) has the unique capability of providing a low-g environment for both short- and long-duration experimentation. This environment can provide a unique and competitive research capability to industry; but until recently, utilization of this environment by the private sector has been limited if not totally unavailable. NASA has recently expressed an interest in the commercial development of space and this is now an integral part of the Agency's enabling legislation through the Space Act. NASA's objective is to foster the use of the space environment for the development of commercial products and processes. Through alliances and agreements with several commercial companies and universities, SPACEHAB, Inc., has built a comprehensive package of services designed to provide low-cost reliable access to space for experimenters. These services provide opportunities to support engineering test beds for materials exposure analysis, to mitigate structural failures as observed on the Hubble Space Telescope; materials processing, remote sensing; space environment definition; and electronic experiments. The intent of this paper is to identify commercial opportunities for utilizing the International Space Station and provide examples of several facilities currently being designed and manufactured by commercial companies with the purpose of providing access to the space environment for commercial users.

AnchorDock: Blind and Flexible Anchor-Driven Peptide Docking.

PubMed

Ben-Shimon, Avraham; Niv, Masha Y

2015-05-05

The huge conformational space stemming from the inherent flexibility of peptides is among the main obstacles to successful and efficient computational modeling of protein-peptide interactions. Current peptide docking methods typically overcome this challenge using prior knowledge from the structure of the complex. Here we introduce AnchorDock, a peptide docking approach, which automatically targets the docking search to the most relevant parts of the conformational space. This is done by precomputing the free peptide's structure and by computationally identifying anchoring spots on the protein surface. Next, a free peptide conformation undergoes anchor-driven simulated annealing molecular dynamics simulations around the predicted anchoring spots. In the challenging task of a completely blind docking test, AnchorDock produced exceptionally good results (backbone root-mean-square deviation ≤ 2.2Å, rank ≤15) for 10 of 13 unbound cases tested. The impressive performance of AnchorDock supports a molecular recognition pathway that is driven via pre-existing local structural elements. Copyright © 2015 Elsevier Ltd. All rights reserved.

Life Predicted in a Probabilistic Design Space for Brittle Materials With Transient Loads

NASA Technical Reports Server (NTRS)

Nemeth, Noel N.; Palfi, Tamas; Reh, Stefan

2005-01-01

Analytical techniques have progressively become more sophisticated, and now we can consider the probabilistic nature of the entire space of random input variables on the lifetime reliability of brittle structures. This was demonstrated with NASA s CARES/Life (Ceramic Analysis and Reliability Evaluation of Structures/Life) code combined with the commercially available ANSYS/Probabilistic Design System (ANSYS/PDS), a probabilistic analysis tool that is an integral part of the ANSYS finite-element analysis program. ANSYS/PDS allows probabilistic loads, component geometry, and material properties to be considered in the finite-element analysis. CARES/Life predicts the time dependent probability of failure of brittle material structures under generalized thermomechanical loading--such as that found in a turbine engine hot-section. Glenn researchers coupled ANSYS/PDS with CARES/Life to assess the effects of the stochastic variables of component geometry, loading, and material properties on the predicted life of the component for fully transient thermomechanical loading and cyclic loading.

Development and demonstration of manufacturing processes for fabricating graphite/Larc-160 polyimide structural elements, part 4, paragraph B

NASA Technical Reports Server (NTRS)

1981-01-01

Progress in the development of processes for production of Celion/LARC-160 graphite-polyimide materials, quality control, and the fabrication of Space Shuttle composite structure components is reported. Liquid chromatographic analyses of three repeatibility batches were performed and are compared to previous Hexcel standard production and to variables study LARC-160 intermediate resins. Development of processes for chopped fiber molding are described and flexural strength, elastic modulus, and other physical and mechanical properties of the molding are presented.

From Lunar Regolith to Fabricated Parts: Technology Developments and the Utilization of Moon Dirt

NASA Technical Reports Server (NTRS)

McLemore, C. A.; Fikes, J. C.; McCarley, K. S.; Good, J. E.; Gilley, S. D.; Kennedy, J. P.

2008-01-01

The U.S. Space Exploration Policy has as a cornerstone the establishment of an outpost on the moon. This lunar outpost wil1 eventually provide the necessary planning, technology development, testbed, and training for manned missions in the future beyond the Moon. As part of the overall activity, the National Aeronautics and Space Administration (NASA) is investigating how the in situ resources can be utilized to improve mission success by reducing up-mass, improving safety, reducing risk, and bringing down costs for the overall mission. Marshall Space Flight Center (MSFC), along with other NASA centers, is supporting this endeavor by exploring how lunar regolith can be mined for uses such as construction, life support, propulsion, power, and fabrication. An infrastructure capable of fabrication and nondestructive evaluation will be needed to support habitat structure development and maintenance, tools and mechanical parts fabrication, as well as repair and replacement of space-mission hardware such as life-support items, vehicle components, and crew systems, This infrastructure will utilize the technologies being developed under the In Situ Fabrication and Repair (ISFR) element, which is working in conjunction with the technologies being developed under the In Situ Resources Utilization (ISRU) element, to live off the land. The ISFR Element supports the Space Exploration Initiative by reducing downtime due to failed components; decreasing risk to crew by recovering quickly from degraded operation of equipment; improving system functionality with advanced geometry capabilities; and enhancing mission safety by reducing assembly part counts of original designs where possible. This paper addresses the need and plan for understanding the properties of the lunar regolith to determine the applicability of using this material in a fabrication process. This effort includes the development of high fidelity simulants that will be used in fabrication processes on the ground to drive down risk and increase the Technology Readiness Level (TRL) prior to implementing this capability on the moon. Also discussed in this paper is the on-going research using Electron Beam Melting (EBM) technology as a possible solution to manufacturing parts and spares on the Moon's surface.

Histological studies on the marsupium of two terrestrial isopods (Crustacea, Isopoda, Oniscidea)

PubMed Central

Csonka, Diána; Halasy, Katalin; Hornung, Elisabeth

2015-01-01

Abstract The marsupium, a brood pouch in peracarid crustaceans (Crustacea, Malacostraca) has evolved in terrestrial environment for providing nutrition and optimal conditions for embryogenesis. In the present study we give details on the histology and ultrastructure of its constituting elements such as oostegites and cotyledons. Marsupia of two different eco-morphological types of woodlice, namely the non-conglobating species Trachelipus rathkii Brandt, 1833 and the conglobating species Cylisticus convexus De Geer, 1778 were investigated. Light microscopic (LM) studies showed some differences in the main structure of the two species’ brood pouch: in Trachelipus rathkii, a ‘clinger’ type woodlice, the oostegites bend outwards during brood incubation as growing offspring require more space, while in Cylisticus convexus, a ‘roller’ type isopod, the sternites arch into the body cavity to ensure space for developing offspring and still allowing conglobation of the gravid females. The quantitative analysis of the oostegites’ cuticle proved that the outer part is about 2.5 - 3 times thicker compared to the inner part in both species. Electron microscopic (TEM) examinations show only small histological differences in the oostegites and cotyledon structure of the two species. Cellular elements and moderately electron dense fleecy precipitate are found in the hemolymph space between the two cuticles of oostegites. The cells contain PAS positive polysaccharide areas. TEM studies revealed some differences in the cotyledon ultrastructure of the two species. Cotyledons of Trachelipus rathkii consist of cells with cristate mitochondria and granular endoplasmic reticulum with cisterns. Cotyledons of Cylisticus convexus consist of cells with densely cristate mitochondria and ribosomes attached to vesicular membrane structures. In both species cells with electron dense bodies were observed. We conclude that - besides the differences in marsupial shapes - the fine structure of the oostegites and cotyledons is hardly affected by the eco-morphological type, specifically the conglobating or non-conglobating character of the studied species. PMID:26261442

Systems Analysis and Structural Design of an Unpressurized Cargo Delivery Vehicle

NASA Technical Reports Server (NTRS)

Wu, K. Chauncey; Cruz, Jonathan N.; Antol, Jeffrey; Sasamoto, Washito A.

2007-01-01

The International Space Station will require a continuous supply of replacement parts for ongoing maintenance and repair after the planned retirement of the Space Shuttle in 2010. These parts are existing line-replaceable items collectively called Orbital Replacement Units, and include heavy and oversized items such as Control Moment Gyroscopes and stowed radiator arrays originally intended for delivery aboard the Space Shuttle. Current resupply spacecraft have limited to no capability to deliver these external logistics. In support of NASA's Exploration Systems Architecture Study, a team at Langley Research Center designed an Unpressurized Cargo Delivery Vehicle to deliver bulk cargo to the Space Station. The Unpressurized Cargo Delivery Vehicle was required to deliver at least 13,200 lbs of cargo mounted on at least 18 Flight Releasable Attachment Mechanisms. The Crew Launch Vehicle design recommended in the Exploration Systems Architecture Study would be used to launch one annual resupply flight to the International Space Station. The baseline vehicle design developed here has a cargo capacity of 16,000 lbs mounted on up to 20 Flight Releasable Attachment Mechanisms. Major vehicle components are a 5.5m-diameter cargo module containing two detachable cargo pallets with the payload, a Service Module to provide propulsion and power, and an aerodynamic nose cone. To reduce cost and risk, the Service Module is identical to the one used for the Crew Exploration Vehicle design.

KSC-07pd3391

NASA Image and Video Library

2007-11-19

KENNEDY SPACE CENTER, FLA. -- During a training session on emergency exit from the fixed service structure on Launch Pad 39A, space shuttle Atlantis STS-122 Commander Steve Frick, left, and Mission Specialist Leland Melvin watch a slidewire basket descend to the landing zone. Seven slidewire baskets are available to carry the crew from the level of the pad's Orbiter Access Arm to a safe landing site below, if needed. Each basket can hold up to three people. A braking system catch net and drag chain slow, and then halt, the baskets as they travel down the wire at approximately 55 miles per hour. The journey takes about half a minute. A bunker is located in the landing zone 1,200 feet west of the pad, with an M-113 armored personnel carrier stationed nearby. The STS-122 crew is at NASA's Kennedy Space Center to take part in terminal countdown demonstration test, or TCDT, activities, a standard part of launch preparations. The TCDT provides astronauts and ground crews with equipment familiarization and a simulated launch countdown before launch. On mission STS-122, Atlantis will deliver the European Space Agency's Columbus module to the International Space Station. Columbus is a multifunctional, pressurized laboratory that will be permanently attached to U.S. Node 2, called Harmony, and will expand the research facilities aboard the station. Launch is targeted for Dec. 6. Photo credit: NASA/Kim Shiflett

Structural Analysis Using NX Nastran 9.0

NASA Technical Reports Server (NTRS)

Rolewicz, Benjamin M.

2014-01-01

NX Nastran is a powerful Finite Element Analysis (FEA) software package used to solve linear and non-linear models for structural and thermal systems. The software, which consists of both a solver and user interface, breaks down analysis into four files, each of which are important to the end results of the analysis. The software offers capabilities for a variety of types of analysis, and also contains a respectable modeling program. Over the course of ten weeks, I was trained to effectively implement NX Nastran into structural analysis and refinement for parts of two missions at NASA's Kennedy Space Center, the Restore mission and the Orion mission.

Unraveling the Helix Nebula: Its Structure and Knots

NASA Astrophysics Data System (ADS)

O'Dell, C. R.; McCullough, Peter R.; Meixner, Margaret

2004-11-01

Through Hubble Space Telescope (HST) imaging of the inner part of the main ring of the Helix Nebula, together with CTIO 4 m images of the fainter outer parts, we have a view of unprecedented quality of the nearest bright planetary nebula. These images have allowed us to determine that the main ring of the nebula is composed of an inner disk of about 499" diameter (0.52 pc) surrounded by an outer ring (in reality a torus) of 742" diameter (0.77 pc) whose plane is highly inclined to the plane of the disk. This outer ring is surrounded by an outermost ring of 1500" (1.76 pc) diameter, which is flattened on the side colliding with the ambient interstellar medium. The inner disk has an extended distribution of low-density gas along its rotational axis of symmetry, and the disk is optically thick to ionizing radiation, as is the outer ring. Published radial velocities of the knots provide support for the two-component structure of the main ring of the nebula and for the idea that the knots found there are expanding along with the nebular material from which they recently originated. These velocities indicate a spatial expansion velocity of the inner disk of 40 and 32 km s-1 for the outer ring, which yields expansion ages of 6560 and 12,100 yr, respectively. The outermost ring may be partially ionized through scattered recombination continuum from the inner parts of the nebula, but shocks certainly are occurring in it. This outermost ring probably represents a third period of mass loss by the central star. There is one compact, outer object that is unexplained, showing shock structures indicating a different orientation of the gas flow from that of the nebula. There is a change in the morphology of the knots as a function of the distance from the local ionization front. This supports a scenario in which the knots are formed in or near the ionization front and are then sculpted by the stellar radiation from the central star as the ionization front advances beyond them. Based in part on observations with the NASA/ESA Hubble Space Telescope, obtained at the Space Telescope Science Institute, which is operated by the Association of Universities for Research in Astronomy, Inc., under NASA contract NAS5-26555. Based in part on observations obtained at the Cerro Tololo Inter-American Observatory, which is operated by the Association of Universities for Research in Astronomy, Inc., under a Cooperative Agreement with the National Science Foundation.

14 CFR 413.1 - Scope of this part.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Scope of this part. 413.1 Section 413.1 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION LICENSING LICENSE APPLICATION PROCEDURES § 413.1 Scope of this part. (a) This part explains how to...

CASTRO: A NEW COMPRESSIBLE ASTROPHYSICAL SOLVER. II. GRAY RADIATION HYDRODYNAMICS

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

Zhang, W.; Almgren, A.; Bell, J.

We describe the development of a flux-limited gray radiation solver for the compressible astrophysics code, CASTRO. CASTRO uses an Eulerian grid with block-structured adaptive mesh refinement based on a nested hierarchy of logically rectangular variable-sized grids with simultaneous refinement in both space and time. The gray radiation solver is based on a mixed-frame formulation of radiation hydrodynamics. In our approach, the system is split into two parts, one part that couples the radiation and fluid in a hyperbolic subsystem, and another parabolic part that evolves radiation diffusion and source-sink terms. The hyperbolic subsystem is solved explicitly with a high-order Godunovmore » scheme, whereas the parabolic part is solved implicitly with a first-order backward Euler method.« less

Size effects of primary/secondary twins on the atomistic deformation mechanisms in hierarchically nanotwinned metals

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

Yuan, Fuping; Wu, Xiaolei

2013-05-28

A series of large-scale molecular dynamics simulations have been performed to investigate the tensile properties of nanotwinned (NT) copper with hierarchically twinned structures (HTS). For the same grain size d and the same spacing of primary twins {lambda}{sub 1}, the average flow stress first increases as the spacing of secondary twins {lambda}{sub 2} decreases, reaching a maximum at a critical {lambda}{sub 2}, and then decreases as {lambda}{sub 2} becomes even smaller. The smaller the spacing for {lambda}{sub 1}, the smaller the critical spacing for {lambda}{sub 2}. There exists a transition in dominating deformation mechanisms, occurring at a critical spacing ofmore » {lambda}{sub 2} for which strength is maximized. Above the critical spacing of {lambda}{sub 2}, the deformation mechanisms are dominated by the two Hall-Petch type strengthening mechanisms: (a) partial dislocations emitted from grain boundaries (GBs) travel across other GBs and twin boundaries (TBs); (b) partial dislocations emitted from TBs travel across other TBs. Below the critical spacing of {lambda}{sub 2}, the deformation mechanism is dominated by the two softening mechanisms: (a) Partial dislocations emitted from boundaries of the primary twins travel parallel to the TBs of the secondary twins, leading to detwinning of the secondary twins; (b) Boundaries of the primary twins shift entirely, leading to thickening in one part of primary twins and thinning in the other part of primary twins. The present results should provide insights to design the microstructures for reinforcing the mechanical properties in the NT metals with HTS.« less

Neutral Buoyancy Simulator: MSFC-Langley joint test of large space structures component assembly:

NASA Technical Reports Server (NTRS)

1978-01-01

Once the United States' space program had progressed from Earth's orbit into outerspace, the prospect of building and maintaining a permanent presence in space was realized. To accomplish this feat, NASA launched a temporary workstation, Skylab, to discover the effects of low gravity and weightlessness on the human body, and also to develop tools and equipment that would be needed in the future to build and maintain a more permanent space station. The structures, techniques, and work schedules had to be carefully designed to fit this unique construction site. The components had to be lightweight for transport into orbit, yet durable. The station also had to be made with removable parts for easy servicing and repairs by astronauts. All of the tools necessary for service and repairs had to be designed for easy manipulation by a suited astronaut. And construction methods had to be efficient due to limited time the astronauts could remain outside their controlled environment. In lieu of all the specific needs for this project, an environment on Earth had to be developed that could simulate a low gravity atmosphere. A Neutral Buoyancy Simulator (NBS) was constructed by NASA Marshall Space Flight Center (MSFC) in 1968. Since then, NASA scientists have used this facility to understand how humans work best in low gravity and also provide information about the different kinds of structures that can be built. Another facet of the space station would be electrical cornectors which would be used for powering tools the astronauts would need for construction, maintenance and repairs. Shown is an astronaut training during an underwater electrical connector test in the NBS.

Neutral Buoyancy Test NB-14 Large Space Structure Assembly

NASA Technical Reports Server (NTRS)

1977-01-01

Once the United States' space program had progressed from Earth's orbit into outerspace, the prospect of building and maintaining a permanent presence in space was realized. To accomplish this feat, NASA launched a temporary workstation, Skylab, to discover the effects of low gravity and weightlessness on the human body, and also to develop tools and equipment that would be needed in the future to build and maintain a more permanent space station. The structures, techniques, and work schedules had to be carefully designed to fit this unique construction site. The components had to be lightweight for transport into orbit, yet durable. The station also had to be made with removable parts for easy servicing and repairs by astronauts. All of the tools necessary for service and repairs had to be designed for easy manipulation by a suited astronaut. And construction methods had to be efficient due to limited time the astronauts could remain outside their controlled environment. In lieu of all the specific needs for this project, an environment on Earth had to be developed that could simulate a low gravity atmosphere. A Neutral Buoyancy Simulator (NBS) was constructed by NASA Marshall Space Flight Center (MSFC) in 1968. Since then, NASA scientists have used this facility to understand how humans work best in low gravity and also provide information about the different kinds of structures that can be built.Pictured is an experiment where the astronaut is required to move a large object which weighed 19,000 pounds. It was moved with realitive ease once the astronaut became familiar with his environment and his near weightless condition. Experiments of this nature provided scientists with the information needed regarding weight and mass allowances astronauts could manage in preparation for building a permanent space station in the future.

Study of multipactor suppression of microwave components using perforated waveguide technology for space applications

NASA Astrophysics Data System (ADS)

Ye, Ming; Li, Yun; He, Yongning; Daneshmand, Mojgan

2017-05-01

With the development of space technology, microwave components with increased power handling capability and reduced weight have been urgently required. In this work, the perforated waveguide technology is proposed to suppress the multipactor effect of high power microwave components. Meanwhile, this novel method has the advantage of reducing components' weight, which makes it to have great potential in space applications. The perforated part of the waveguide components can be seen as an electron absorber (namely, its total electron emission yield is zero) since most of the electrons impacting on this part will go out of the components. Based on thoroughly benchmarked numerical simulation procedures, we simulated an S band and an X band waveguide transformer to conceptually verify this idea. Both electron dynamic simulations and electrical loss simulations demonstrate that the perforation technology can improve the multipactor threshold at least ˜8 dB while maintaining the acceptable insertion loss level compared with its un-perforated components. We also found that the component with larger minimum gap is easier to achieve multipactor suppression. This effect is interpreted by a parallel plate waveguide model. What's more, to improve the multipactor threshold of the X band waveguide transformer with a minimum gap of ˜0.1 mm, we proposed a perforation structure with the slope edge and explained its mechanism. Future study will focus on further optimization of the perforation structure, size, and distribution to maximize the comprehensive performances of microwave components.

Method and apparatus for performing in-situ vacuum-assisted metal to glass sealing

DOEpatents

Kramer, D.P.; Massey, R.T.

1985-07-18

A method and apparatus for assembling and fusing glass to metal in a glass-metal electrical component is disclosed. The component includes a metallic shell formed with upper and lower cylindrical recesses connected together by longitudinal passages, a pair of metal rings and plural metal pins assembled to define electrical feed-throughs. The component parts are assembled on a fixture having a sleeve-like projection and a central mounting projection establishing concentric nesting surfaces to which the metal rings are slip-fitted in concentric alignment with each other spaced from sidewalls of the lower recess. The pins are in electrical contact with the metal rings. A glass pre-form is seated within the upper recess. The assembled structure is heated to a temperature sufficient to melt the glass pre-form which flows under gravity through the passages into the lower recess to provide an insulative seal between the metal parts. The gravity flow of glass is assisted by applying vacuum to the lower recess, ensuring that all spaces between the metal parts are filled with sealing glass without formation of bubbles.

Method and apparatus for performing in-situ vacuum-assisted metal to glass sealing

DOEpatents

Kramer, Daniel P.; Massey, Richard T.

1986-01-01

A method and apparatus for assembling and fusing glass to metal in a glass-metal electrical component is disclosed. The component includes a metallic shell formed with upper and lower cylindrical recesses connected together by longitudinal passages, a pair of metal rings and plural metal pins assembled to define electrical feed-throughs. The component parts are assembled on a fixture having a sleeve-like projection and a central mounting projection establishing concentric nesting surfaces to which the metal rings are slip-fitted in concentric alignment with each other spaced from sidewalls of the lower recess. The pins are in electrical contact with the metal rings. A glass pre-form is seated within the upper recess. The assembled structure is heated to a temperature sufficient to melt the glass pre-form which flows under gravity through the passages into the lower recess to provide an insulative seal between the metal parts. The gravity flow of glass is assisted by applying vacuum to the lower recess, ensuring that all spaces between the metal parts are filled with sealing glass without formation of bubbles.

A 3D visualization system for molecular structures

NASA Technical Reports Server (NTRS)

Green, Terry J.

1989-01-01

The properties of molecules derive in part from their structures. Because of the importance of understanding molecular structures various methodologies, ranging from first principles to empirical technique, were developed for computing the structure of molecules. For large molecules such as polymer model compounds, the structural information is difficult to comprehend by examining tabulated data. Therefore, a molecular graphics display system, called MOLDS, was developed to help interpret the data. MOLDS is a menu-driven program developed to run on the LADC SNS computer systems. This program can read a data file generated by the modeling programs or data can be entered using the keyboard. MOLDS has the following capabilities: draws the 3-D representation of a molecule using stick, ball and ball, or space filled model from Cartesian coordinates, draws different perspective views of the molecule; rotates the molecule on the X, Y, Z axis or about some arbitrary line in space, zooms in on a small area of the molecule in order to obtain a better view of a specific region; and makes hard copy representation of molecules on a graphic printer. In addition, MOLDS can be easily updated and readily adapted to run on most computer systems.

A Method for Assessing the Accuracy of a Photogrammetry System for Precision Deployable Structures

NASA Technical Reports Server (NTRS)

Moore, Ashley

2005-01-01

The measurement techniques used to validate analytical models of large deployable structures are an integral Part of the technology development process and must be precise and accurate. Photogrammetry and videogrammetry are viable, accurate, and unobtrusive methods for measuring such large Structures. Photogrammetry uses Software to determine the three-dimensional position of a target using camera images. Videogrammetry is based on the same principle, except a series of timed images are analyzed. This work addresses the accuracy of a digital photogrammetry system used for measurement of large, deployable space structures at JPL. First, photogrammetry tests are performed on a precision space truss test article, and the images are processed using Photomodeler software. The accuracy of the Photomodeler results is determined through, comparison with measurements of the test article taken by an external testing group using the VSTARS photogrammetry system. These two measurements are then compared with Australis photogrammetry software that simulates a measurement test to predict its accuracy. The software is then used to study how particular factors, such as camera resolution and placement, affect the system accuracy to help design the setup for the videogrammetry system that will offer the highest level of accuracy for measurement of deploying structures.

Hypervelocity Impact Evaluation of Metal Foam Core Sandwich Structures

NASA Technical Reports Server (NTRS)

Yasensky, John; Christiansen, Eric L.

2007-01-01

A series of hypervelocity impact (HVI) tests were conducted by the NASA Johnson Space Center (JSC) Hypervelocity Impact Technology Facility (HITF) [1], building 267 (Houston, Texas) between January 2003 and December 2005 to test the HVI performance of metal foams, as compared to the metal honeycomb panels currently in service. The HITF testing was conducted at the NASA JSC White Sands Testing Facility (WSTF) at Las Cruces, New Mexico. Eric L. Christiansen, Ph.D., and NASA Lead for Micro-Meteoroid Orbital Debris (MMOD) Protection requested these hypervelocity impact tests as part of shielding research conducted for the JSC Center Director Discretionary Fund (CDDF) project. The structure tested is a metal foam sandwich structure; a metal foam core between two metal facesheets. Aluminum and Titanium metals were tested for foam sandwich and honeycomb sandwich structures. Aluminum honeycomb core material is currently used in Orbiter Vehicle (OV) radiator panels and in other places in space structures. It has many desirable characteristics and performs well by many measures, especially when normalized by density. Aluminum honeycomb does not perform well in Hypervelocity Impact (HVI) Testing. This is a concern, as honeycomb panels are often exposed to space environments, and take on the role of Micrometeoroid / Orbital Debris (MMOD) shielding. Therefore, information on possible replacement core materials which perform adequately in all necessary functions of the material would be useful. In this report, HVI data is gathered for these two core materials in certain configurations and compared to gain understanding of the metal foam HVI performance.

DIME Students Participate in SCUBA Lesson Spring 2002

NASA Technical Reports Server (NTRS)

2002-01-01

In addition to drop tower activities, students assembled a plastic pipe structure underwater in a SCUBA exercise similar to training astronauts receive at NASA Johnson Space Center. This was part of the second Dropping in a Microgravity Environment (DIME) competition held April 23-25, 2002, at NASA's Glenn Research Center. Competitors included two teams from Sycamore High School, Cincinnati, OH, and one each from Bay High School, Bay Village, OH, and COSI Academy, Columbus, OH. DIME is part of NASA's education and outreach activities. Details are on line at http://microgravity.grc.nasa.gov/DIME_2002.html.

Labeling RDF Graphs for Linear Time and Space Querying

NASA Astrophysics Data System (ADS)

Furche, Tim; Weinzierl, Antonius; Bry, François

Indices and data structures for web querying have mostly considered tree shaped data, reflecting the view of XML documents as tree-shaped. However, for RDF (and when querying ID/IDREF constraints in XML) data is indisputably graph-shaped. In this chapter, we first study existing indexing and labeling schemes for RDF and other graph datawith focus on support for efficient adjacency and reachability queries. For XML, labeling schemes are an important part of the widespread adoption of XML, in particular for mapping XML to existing (relational) database technology. However, the existing indexing and labeling schemes for RDF (and graph data in general) sacrifice one of the most attractive properties of XML labeling schemes, the constant time (and per-node space) test for adjacency (child) and reachability (descendant). In the second part, we introduce the first labeling scheme for RDF data that retains this property and thus achieves linear time and space processing of acyclic RDF queries on a significantly larger class of graphs than previous approaches (which are mostly limited to tree-shaped data). Finally, we show how this labeling scheme can be applied to (acyclic) SPARQL queries to obtain an evaluation algorithm with time and space complexity linear in the number of resources in the queried RDF graph.

Intelligent Flexible Materials for Space Structures: Expandable Habitat Engineering Development Unit

NASA Technical Reports Server (NTRS)

Hinkle, Jon; Sharpe, George; Lin, John; Wiley, Cliff; Timmers, Richard

2010-01-01

Expandable habitable elements are an enabling technology for human exploration in space and on planetary surfaces. Large geometries can be deployed from a small launch volume, allowing greater mission capability while reducing mass and improving robustness over traditional rigid shells. This report describes research performed by ILC Dover under the Intelligent Flexible Materials for Space Structures program on the design and manufacture of softgoods for LaRC's Expandable Habitat Engineering Development Unit (EDU). The EDU is a full-scale structural test article of an expandable hybrid habitat, integrating an expandable softgoods center section with two rigid end caps. The design of the bladder, restraint layer and a mock-up Thermal Micrometeoroid Cover is detailed together with the design of the interface hardware used to attach them to the end caps. The integration and design of two windows and a floor are also covered. Analysis was performed to study the effects of the open weave design, and to determine the correct webbing and fabric configuration. Stress analyses were also carried out on the interfaces between the softgoods and the end caps and windows. Testing experimentally determined the strength of the fabric and straps, and component testing was used to proof several critical parts of the design. This program established new manufacturing and design techniques that can be applied to future applications in expandable structures.

STS-101 Mission Specialists Helms, Usachev and Voss practice emergency exit

NASA Technical Reports Server (NTRS)

2000-01-01

As part of Terminal Countdown Demonstration (TCDT) activities, the STS-101 crew practices emergency egress from the orbiter at the 195-foot level of the Fixed Service Structure. Shown heading down the easily identified exit path, known as the 'yellow brick road,' are Mission Specialists Susan J. Helms (leading), Yuri Usachev of Russia and James Voss. The TCDT also includes a simulated launch countdown and familiarization with the payload. During their mission to the International Space Station, the STS- 101 crew will be delivering logistics and supplies, plus preparing the Station for the arrival of the Zvezda Service Module, expected to be launched by Russia in July 2000. Also, the crew will conduct one space walk to perform maintenance on the Space Station. This will be the third assembly flight to the Space Station. STS-101 is scheduled to launch April 24 at 4:15 p.m. from Launch Pad 39A.