Earth Science

NASA Image and Video Library

1993-03-29

Small Expendable Deployer System (SEDS) is a tethered date collecting satellite and is intended to demonstrate a versatile and economical way of delivering smaller payloads to higher orbits or downward toward Earth's atmosphere. 19th Navstar Global Positioning System Satellite mission joined with previously launched satellites used for navigational purposes and geodite studies. These satellites are used commercially as well as by the military.

Artist's Concept of Propulsive Small Expendable Deployer System (ProSEDS)

NASA Technical Reports Server (NTRS)

1999-01-01

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

Propulsive Small Expendable Deployer System (ProSEDS)

NASA Technical Reports Server (NTRS)

1999-01-01

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

Expendable oceanographic sensor apparatus

DOEpatents

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

1993-01-01

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

Thermal Orbital Environmental Parameter Study on the Propulsive Small Expendable Deployer System (ProSEDS) Using Earth Radiation Budget Experiment (ERBE) Data

NASA Technical Reports Server (NTRS)

Sharp, John R.; McConnaughey, Paul K. (Technical Monitor)

2002-01-01

The natural thermal environmental parameters used on the Space Station Program (SSP 30425) were generated by the Space Environmental Effects Branch at NASA's Marshall Space Flight Center (MSFC) utilizing extensive data from the Earth Radiation Budget Experiment (ERBE), a series of satellites which measured low earth orbit (LEO) albedo and outgoing long-wave radiation. Later, this temporal data was presented as a function of averaging times and orbital inclination for use by thermal engineers in NASA Technical Memorandum TM 4527. The data was not presented in a fashion readily usable by thermal engineering modeling tools and required knowledge of the thermal time constants and infrared versus solar spectrum sensitivity of the hardware being analyzed to be used properly. Another TM was recently issued as a guideline for utilizing these environments (NASA/TM-2001-211221) with more insight into the utilization by thermal analysts. This paper gives a top-level overview of the environmental parameters presented in the TM and a study of the effects of implementing these environments on an ongoing MSFC project, the Propulsive Small Expendable Deployer System (ProSEDS), compared to conventional orbital parameters that had been historically used.

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

PubMed Central

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

2017-01-01

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

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

NASA Technical Reports Server (NTRS)

Wray, S. T., Jr.

1975-01-01

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

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

NASA Technical Reports Server (NTRS)

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

1994-01-01

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

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

DTIC Science & Technology

1988-05-01

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

MARS PATHFINDER PYRO SYSTEMS SWITCHING ACTIVITY

NASA Technical Reports Server (NTRS)

1996-01-01

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

Final design of a space debris removal system

NASA Technical Reports Server (NTRS)

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

1990-01-01

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

Final design of a space debris removal system

NASA Astrophysics Data System (ADS)

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

1990-12-01

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

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

NASA Astrophysics Data System (ADS)

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

2011-12-01

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

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

NASA Astrophysics Data System (ADS)

Legnos, P. J.

2013-12-01

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

ProSEDS Telemetry System Utilization of GPS Position Data for Transmitter Cycling

NASA Technical Reports Server (NTRS)

Kennedy, Paul; Sims, Herb

2000-01-01

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

Can nurse practitioners and physicians beat parochialism into plowshares?

PubMed

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

2002-01-01

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

Space Station tethered waste disposal

NASA Technical Reports Server (NTRS)

Rupp, Charles C.

1988-01-01

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

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

NASA Technical Reports Server (NTRS)

Maddux, Gary A.

1998-01-01

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

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

NASA Technical Reports Server (NTRS)

1972-01-01

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

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

NASA Technical Reports Server (NTRS)

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

1977-01-01

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

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

NASA Astrophysics Data System (ADS)

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

2017-10-01

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

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

NASA Technical Reports Server (NTRS)

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

1990-01-01

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

KSC-97PC903

NASA Image and Video Library

1997-05-17

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

MARS PATHFINDER CAMERA TEST IN SAEF-2

NASA Technical Reports Server (NTRS)

1996-01-01

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

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

DTIC Science & Technology

2010-07-01

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

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

NASA Technical Reports Server (NTRS)

1971-01-01

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

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

NASA Technical Reports Server (NTRS)

Fester, Dale A.

1991-01-01

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

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

NASA Technical Reports Server (NTRS)

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

2013-01-01

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

Safety testing of lithium cells

NASA Technical Reports Server (NTRS)

Liberto, Nick

1991-01-01

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

Safety testing of lithium cells

NASA Astrophysics Data System (ADS)

Liberto, Nick

1991-05-01

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

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

NASA Technical Reports Server (NTRS)

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

1998-01-01

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

SPECS: Orbital debris removal

NASA Technical Reports Server (NTRS)

1991-01-01

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

Pathfinder

NASA Image and Video Library

2001-07-01

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

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

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

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

1981-01-01

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

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

NASA Technical Reports Server (NTRS)

Deininger, William D.; Vondra, Robert J.

1989-01-01

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

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

NASA Technical Reports Server (NTRS)

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

2004-01-01

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

20 CFR 437.20 - Standards for financial management systems.

Code of Federal Regulations, 2010 CFR

2010-04-01

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

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

NASA Astrophysics Data System (ADS)

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

2016-12-01

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

Investigation of Propulsion System Requirements for Spartan Lite

NASA Technical Reports Server (NTRS)

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

1998-01-01

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

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

DTIC Science & Technology

1992-06-01

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

21 CFR 1403.20 - Standards for financial management systems.

Code of Federal Regulations, 2010 CFR

2010-04-01

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

Pathfinder

NASA Image and Video Library

1999-03-01

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

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

NASA Technical Reports Server (NTRS)

1971-01-01

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

Small Body Science via Swarms of Nano-Satellites

NASA Astrophysics Data System (ADS)

Ernst, Sebastian M.; Lewis, John S.

2015-04-01

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

JPSS-1 P-Pod Installation

NASA Image and Video Library

2017-10-31

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

JPSS-1 P-Pod Installation

NASA Image and Video Library

2017-10-31

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

JPSS-1 P-Pod Installation

NASA Image and Video Library

2017-10-31

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

SEDS1 mission software verification using a signal simulator

NASA Technical Reports Server (NTRS)

Pierson, William E.

1992-01-01

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

Electrical Power Systems for NASA's Space Transportation Program

NASA Technical Reports Server (NTRS)

Lollar, Louis F.; Maus, Louis C.

1998-01-01

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

Expendable vs reusable propulsion systems cost sensitivity

NASA Technical Reports Server (NTRS)

Hamaker, Joseph W.; Dodd, Glenn R.

1989-01-01

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

KSC-10941f07

NASA Image and Video Library

1997-05-27

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

An opportunity cost model of subjective effort and task performance

PubMed Central

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

2013-01-01

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

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

NASA Technical Reports Server (NTRS)

1984-01-01

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

Space platform expendables resupply concept definition study

NASA Technical Reports Server (NTRS)

1985-01-01

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

Space platform expendables resupply concept definition study, volume 2

NASA Technical Reports Server (NTRS)

1984-01-01

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

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

NASA Astrophysics Data System (ADS)

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

1995-04-01

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

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

NASA Technical Reports Server (NTRS)

Wolfe, R. R.

1974-01-01

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

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

PubMed Central

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

2017-01-01

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

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

PubMed

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

2017-01-01

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

Pathfinder

NASA Image and Video Library

1999-03-25

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

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

NASA Technical Reports Server (NTRS)

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

1989-01-01

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

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

PubMed

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

2014-09-01

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

New computer and communications environments for light armored vehicles

NASA Astrophysics Data System (ADS)

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

2002-08-01

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

MARS PATHFINDER CAMERA TEST IN SAEF-2

NASA Technical Reports Server (NTRS)

1996-01-01

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

NASA work unit system users manual

NASA Technical Reports Server (NTRS)

1972-01-01

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

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

NASA Technical Reports Server (NTRS)

1970-01-01

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

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

NASA Astrophysics Data System (ADS)

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

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

NASA Technical Reports Server (NTRS)

1993-01-01

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

ANTS/PAM: Future Exploration of the Asteroid Belt

NASA Astrophysics Data System (ADS)

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

2004-05-01

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

Aircraft Surveys of the Beaufort Sea Seasonal Ice Zone

NASA Astrophysics Data System (ADS)

Morison, J.

2016-02-01

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

The commercial implications of the EELV program

NASA Astrophysics Data System (ADS)

Sasso, Steven E.

1998-01-01

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

Artist's Concept of X-37 Re-entry

NASA Technical Reports Server (NTRS)

1999-01-01

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

Advanced Concept

NASA Image and Video Library

1999-08-13

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

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

NASA Technical Reports Server (NTRS)

1971-01-01

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

The K-1 Active Dispenser for Orbit Transfer

NASA Astrophysics Data System (ADS)

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

2002-01-01

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

Distributed sensor network for local-area atmospheric modeling

NASA Astrophysics Data System (ADS)

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

2003-09-01

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

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

NASA Technical Reports Server (NTRS)

1971-01-01

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

Technical Challenges and Lessons from the Migration of the GLOBE Data and Information System to Utilize Cloud Computing Service

NASA Technical Reports Server (NTRS)

Moses, John F.; Memarsadeghi, Nargess; Overoye, David; Littlefield, Brain

2017-01-01

The Global Learning and Observation to Benefit the Environment (GLOBE) Data and Information System supports an international science and education program with capabilities to accept local environment observations, archive, display and visualize them along with global satellite observations. Since its inception twenty years ago, the Web and database system has been upgraded periodically to accommodate the changes in technology and the steady growth of GLOBEs education community and collection of observations. Recently, near the end-of-life of the system hardware, new commercial computer platform options were explored and a decision made to utilize Cloud services. Now the GLOBE DIS has been fully deployed and maintained using Amazon Cloud services for over two years now. This paper reviews the early risks, actual challenges, and some unexpected findings as a result of the GLOBE DIS migration. We describe the plans, cost drivers and estimates, highlight adjustments that were made and suggest improvements. We present the trade studies for provisioning, for load balancing, networks, processing, storage, as well as production, staging and backup systems. We outline the migration teams skills and required level of effort for transition, and resulting changes in the overall maintenance and operations activities. Examples include incremental adjustments to processing capacity and frequency of backups, and efforts previously expended on hardware maintenance that were refocused onto application-specific enhancements.

Technical Challenges and Lessons from the Migration of the GLOBE Data and Information System to Utilize Cloud Computing Service

NASA Technical Reports Server (NTRS)

Moses, John F.; Memarsadeghi, Nargess; Overoye, David; Littlefield, Bryan

2016-01-01

The Global Learning and Observation to Benefit the Environment (GLOBE) Data and Information System supports an international science and education program with capabilities to accept local environment observations, archive, display and visualize them along with global satellite observations. Since its inception twenty years ago, the Web and database system has been upgraded periodically to accommodate the changes in technology and the steady growth of GLOBEs education community and collection of observations. Recently, near the end-of-life of the system hardware, new commercial computer platform options were explored and a decision made to utilize Cloud services. Now the GLOBE DIS has been fully deployed and maintained using Amazon Cloud services for over two years now. This paper reviews the early risks, actual challenges, and some unexpected findings as a result of the GLOBE DIS migration. We describe the plans, cost drivers and estimates, highlight adjustments that were made and suggest improvements. We present the trade studies for provisioning, for load balancing, networks, processing, storage, as well as production, staging and backup systems. We outline the migration teams skills and required level of effort for transition, and resulting changes in the overall maintenance and operations activities. Examples include incremental adjustments to processing capacity and frequency of backups, and efforts previously expended on hardware maintenance that were refocused onto application-specific enhancements.

Technical Challenges and Lessons from the Migration of the GLOBE Data and Information System to Utilize Cloud Computing Service

NASA Astrophysics Data System (ADS)

Moses, J. F.; Memarsadeghi, N.; Overoye, D.; Littlefield, B.

2016-12-01

The Global Learning and Observation to Benefit the Environment (GLOBE) Data and Information System supports an international science and education program with capabilities to accept local environment observations, archive, display and visualize them along with global satellite observations. Since its inception twenty years ago, the Web and database system has been upgraded periodically to accommodate the changes in technology and the steady growth of GLOBE's education community and collection of observations. Recently, near the end-of-life of the system hardware, new commercial computer platform options were explored and a decision made to utilize Cloud services. Now the GLOBE DIS has been fully deployed and maintained using Amazon Cloud services for over two years now. This paper reviews the early risks, actual challenges, and some unexpected findings as a result of the GLOBE DIS migration. We describe the plans, cost drivers and estimates, highlight adjustments that were made and suggest improvements. We present the trade studies for provisioning, for load balancing, networks, processing , storage, as well as production, staging and backup systems. We outline the migration team's skills and required level of effort for transition, and resulting changes in the overall maintenance and operations activities. Examples include incremental adjustments to processing capacity and frequency of backups, and efforts previously expended on hardware maintenance that were refocused onto application-specific enhancements.

14 CFR 420.19 - Launch site location review-general.

Code of Federal Regulations, 2010 CFR

2010-01-01

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

24 CFR 84.35 - Supplies and other expendable property.

Code of Federal Regulations, 2010 CFR

2010-04-01

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

The Application of a Residual Risk Evaluation Technique Used for Expendable Launch Vehicles

NASA Technical Reports Server (NTRS)

Latimer, John A.

2009-01-01

This presentation provides a Residual Risk Evaluation Technique (RRET) developed by Kennedy Space Center (KSC) Safety and Mission Assurance (S&MA) Launch Services Division. This technique is one of many procedures used by S&MA at KSC to evaluate residual risks for each Expendable Launch Vehicle (ELV) mission. RRET is a straight forward technique that incorporates the proven methodology of risk management, fault tree analysis, and reliability prediction. RRET derives a system reliability impact indicator from the system baseline reliability and the system residual risk reliability values. The system reliability impact indicator provides a quantitative measure of the reduction in the system baseline reliability due to the identified residual risks associated with the designated ELV mission. An example is discussed to provide insight into the application of RRET.

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

NASA Technical Reports Server (NTRS)

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

2004-01-01

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

MARS PATHFINDER CAMERA TEST IN SAEF-2

NASA Technical Reports Server (NTRS)

1996-01-01

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

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

NASA Technical Reports Server (NTRS)

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

2003-01-01

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

Prospects for commercialization of SELV-based in-space operations

NASA Technical Reports Server (NTRS)

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

1995-01-01

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

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

NASA Technical Reports Server (NTRS)

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

1985-01-01

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

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

PubMed

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

2016-01-01

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

The development status of candidate life support technology for a space station

NASA Technical Reports Server (NTRS)

Samonski, F. H., Jr.

1984-01-01

The establishment of a permanently-manned Space Station has recently been selected as the next major step in the U.S. space program. The requirements of a manned operations base in space appear to be best satisfied by on-board Environmental Control/Life Support Systems (ECLSS) which are free from, or have minimum dependence on, use of expendables and the frequent earth resupply missions which are part of systems using expendables. The present investigation is concerned with the range of regenerative life support system options which NASA is developing to be available for the Space Station designer. An air revitalization system is discussed, taking into account devices concerned with the carbon dioxide concentration, approaches of CO2 reduction, oxygen generation, trace contaminant control, and atmospheric quality monitoring. Attention is also given to an independent air revitalization system, nitrogen generation, a water reclamation system, a waste management system, applications of the technology, and future development requirements.

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

NASA Technical Reports Server (NTRS)

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

2001-01-01

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

Upper Ocean Momentum Response to Hurricane Forcing

NASA Astrophysics Data System (ADS)

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

2016-02-01

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

Space shuttle phase B extension, volume 1

NASA Technical Reports Server (NTRS)

1971-01-01

In order to define a system which would significantly reduce payload delivery costs, activities were extended to modifications of the reusable space shuttle design concept. Considered were systems using orbiters with external propellant tanks and an interim expendable booster which allowed phased development of the usable orbiter and booster. Analyzed were: Merits of internal and external propellant tanks and the impact of external LH2 compared to L02 and LH2; impact of cargo bay size; impact abort; merit of expendable booster options; and merit of a phased development program. Studies showed that external L02/LH2 and the continued use of the J-2S engine on the orbiter reduced program cost and risk.

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

NASA Astrophysics Data System (ADS)

Ohar, Orest P.; Lizotte, Todd E.

2009-08-01

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

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

NASA Technical Reports Server (NTRS)

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

2016-01-01

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

14 CFR 1214.502 - Definitions.

Code of Federal Regulations, 2010 CFR

2010-01-01

... Aeronautics and Space NATIONAL AERONAUTICS AND SPACE ADMINISTRATION SPACE FLIGHT Mission Critical Space System Personnel Reliability Program § 1214.502 Definitions. (a) Mission Critical Space Systems. The Space Shuttle and other critical space systems, including Space Station Freedom, designated Expendable Launch...

EC/LSS thermal control system study for the space shuttle

NASA Technical Reports Server (NTRS)

Howell, H. R.

1972-01-01

The results of a parametric weight analysis of heat rejection systems for the space shuttle orbiter are presented. Integrating the suborbital heat rejection system with the overall heat rejection system design and the possible use of a common system for both on-orbit and suborbital operations require an overall system and parametric analyses applicable to all mission phases. The concept of equivalent weights, with weight penalties assigned for power, induced aircraft drag and radiator area is used to determine weight estimates for the following candidate systems: vapor cycle refrigeration, gas cycle refrigeration, radiators (space and atmospheric convectors), expendable heat sinks, and ram air. The orbiter power penalty, ram air penalty, and radiator weight penalty are analyzed. The vapor compression system and an expendable fluid system utilizing a multifluid spraying flash evaporator are selected as the two most promising systems. These are used for maximum on-orbit heat rejection in combination with or as a supplement to a space radiator.

14 CFR 415.127 - Flight safety system design and operation data.

Code of Federal Regulations, 2010 CFR

2010-01-01

... Expendable Launch Vehicle From a Non-Federal Launch Site § 415.127 Flight safety system design and operation...: flight termination system; command control system; tracking; telemetry; communications; flight safety... control system. (7) Flight termination system component storage, operating, and service life. A listing of...

Advanced transportation system study: Manned launch vehicle concepts for two way transportation system payloads to LEO

NASA Technical Reports Server (NTRS)

Duffy, James B.

1993-01-01

The purpose of the Advanced Transportation System Study (ATSS) task area 1 study effort is to examine manned launch vehicle booster concepts and two-way cargo transfer and return vehicle concepts to determine which of the many proposed concepts best meets NASA's needs for two-way transportation to low earth orbit. The study identified specific configurations of the normally unmanned, expendable launch vehicles (such as the National Launch System family) necessary to fly manned payloads. These launch vehicle configurations were then analyzed to determine the integrated booster/spacecraft performance, operations, reliability, and cost characteristics for the payload delivery and return mission. Design impacts to the expendable launch vehicles which would be required to perform the manned payload delivery mission were also identified. These impacts included the implications of applying NASA's man-rating requirements, as well as any mission or payload unique impacts. The booster concepts evaluated included the National Launch System (NLS) family of expendable vehicles and several variations of the NLS reference configurations to deliver larger manned payload concepts (such as the crew logistics vehicle (CLV) proposed by NASA JSC). Advanced, clean sheet concepts such as an F-1A engine derived liquid rocket booster (LRB), the single stage to orbit rocket, and a NASP-derived aerospace plane were also included in the study effort. Existing expendable launch vehicles such as the Titan 4, Ariane 5, Energia, and Proton were also examined. Although several manned payload concepts were considered in the analyses, the reference manned payload was the NASA Langley Research Center's HL-20 version of the personnel launch system (PLS). A scaled up version of the PLS for combined crew/cargo delivery capability, the HL-42 configuration, was also included in the analyses of cargo transfer and return vehicle (CTRV) booster concepts. In addition to strictly manned payloads, two-way cargo transportation systems (CTRV's) were also examined. The study provided detailed design and analysis of the performance, reliability, and operations of these concepts. The study analyzed these concepts as unique systems and also analyzed several combined CTRV/booster configurations as integrated launch systems (such as for launch abort analyses). Included in the set of CTRV concepts analyzed were the medium CTRV, the integral CTRV (in both a pressurized and unpressurized configuration), the winged CTRV, and an attached cargo carrier for the PLS system known as the PLS caboose.

Is It Worth It? - the Economics of Reusable Space Transportation

NASA Technical Reports Server (NTRS)

Webb, Richard

2016-01-01

Over the past several decades billions of dollars have been invested by governments and private companies in the pursuit of lower cost access to space through earth-to-orbit (ETO) space transportation systems. Much of that investment has been focused on the development and operation of various forms of reusable transportation systems. From the Space Shuttle to current efforts by private commercial companies, the overarching belief of those making such investments has been that reusing system elements will be cheaper than utilizing expendable systems that involve throwing away costly engines, avionics, and other hardware with each flight. However, the view that reusable systems are ultimately a "better" approach to providing ETO transportation is not held universally by major stakeholders within the space transportation industry. While the technical feasibility of at least some degree of reusability has been demonstrated, there continues to be a sometimes lively debate over the merits and drawbacks of reusable versus expendable systems from an economic perspective. In summary, is it worth it? Based on our many years of direct involvement with the business aspects of several expendable and reusable transportation systems, it appears to us that much of the discussion surrounding reusability is hindered by a failure to clearly define and understand the financial and other metrics by which the financial "goodness" of a reusable or expandable approach is measured. As stakeholders, the different users and suppliers of space transportation have a varied set of criteria for determining the relative economic viability of alternative strategies, including reusability. Many different metrics have been used to measure the affordability of space transportation, such as dollars per payload pound (kilogram) to orbit, cost per flight, life cycle cost, net present value/internal rate of return, and many others. This paper will examine the key considerations that influence stakeholders as they make space transportation investment decisions, including primary metrics by which various stakeholders measure financial goodness and other factors that significantly shape decisions to invest in reusable or expendable systems. It must be noted at the outset that reusable systems take many forms and perform different transportation functions including, but not limited to, ETO payload delivery. The discussion in this paper is limited to the economics of ETO transportation systems.

Artificial intelligent decision support for low-cost launch vehicle integrated mission operations

NASA Astrophysics Data System (ADS)

Szatkowski, Gerard P.; Schultz, Roger

1988-11-01

The feasibility, benefits, and risks associated with Artificial Intelligence (AI) Expert Systems applied to low cost space expendable launch vehicle systems are reviewed. This study is in support of the joint USAF/NASA effort to define the next generation of a heavy-lift Advanced Launch System (ALS) which will provide economical and routine access to space. The significant technical goals of the ALS program include: a 10 fold reduction in cost per pound to orbit, launch processing in under 3 weeks, and higher reliability and safety standards than current expendables. Knowledge-based system techniques are being explored for the purpose of automating decision support processes in onboard and ground systems for pre-launch checkout and in-flight operations. Issues such as: satisfying real-time requirements, providing safety validation, hardware and Data Base Management System (DBMS) interfacing, system synergistic effects, human interfaces, and ease of maintainability, have an effect on the viability of expert systems as a useful tool.

Artificial intelligent decision support for low-cost launch vehicle integrated mission operations

NASA Technical Reports Server (NTRS)

Szatkowski, Gerard P.; Schultz, Roger

1988-01-01

The feasibility, benefits, and risks associated with Artificial Intelligence (AI) Expert Systems applied to low cost space expendable launch vehicle systems are reviewed. This study is in support of the joint USAF/NASA effort to define the next generation of a heavy-lift Advanced Launch System (ALS) which will provide economical and routine access to space. The significant technical goals of the ALS program include: a 10 fold reduction in cost per pound to orbit, launch processing in under 3 weeks, and higher reliability and safety standards than current expendables. Knowledge-based system techniques are being explored for the purpose of automating decision support processes in onboard and ground systems for pre-launch checkout and in-flight operations. Issues such as: satisfying real-time requirements, providing safety validation, hardware and Data Base Management System (DBMS) interfacing, system synergistic effects, human interfaces, and ease of maintainability, have an effect on the viability of expert systems as a useful tool.

Space Tug systems study. Volume 2: Compendium

NASA Technical Reports Server (NTRS)

1974-01-01

Possible storable propellant configurations and program plans are evaluated for the space tug. Alternatives examined include: use of existing expendable stages modified for use with shuttle, followed by a space tug at a later date; use of a modified growth version of existing expendable stages for greater performance and potential reuse, followed by a space tug at a later date; use of a low development cost, reusable, interim space tug available at shuttle initial operational capability (IOC) that could be evolved to greater system capabilities at a later date; and use a direct developed tug with maximum potential to be available at some specified time after space shuttle IOC. The capability options were narrowed down to three final options for detailed program definition.

20 CFR 437.20 - Standards for financial management systems.

Code of Federal Regulations, 2011 CFR

2011-04-01

... 20 Employees' Benefits 2 2011-04-01 2011-04-01 false Standards for financial management systems... Financial Administration § 437.20 Standards for financial management systems. (a) A State must expend and... of applicable statutes. (b) The financial management systems of other grantees and subgrantees must...

20 CFR 437.20 - Standards for financial management systems.

Code of Federal Regulations, 2012 CFR

2012-04-01

... 20 Employees' Benefits 2 2012-04-01 2012-04-01 false Standards for financial management systems... Financial Administration § 437.20 Standards for financial management systems. (a) A State must expend and... of applicable statutes. (b) The financial management systems of other grantees and subgrantees must...

20 CFR 437.20 - Standards for financial management systems.

Code of Federal Regulations, 2014 CFR

2014-04-01

... 20 Employees' Benefits 2 2014-04-01 2014-04-01 false Standards for financial management systems... Financial Administration § 437.20 Standards for financial management systems. (a) A State must expend and... of applicable statutes. (b) The financial management systems of other grantees and subgrantees must...

20 CFR 437.20 - Standards for financial management systems.

Code of Federal Regulations, 2013 CFR

2013-04-01

... 20 Employees' Benefits 2 2013-04-01 2013-04-01 false Standards for financial management systems... Financial Administration § 437.20 Standards for financial management systems. (a) A State must expend and... of applicable statutes. (b) The financial management systems of other grantees and subgrantees must...

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

NASA Technical Reports Server (NTRS)

1979-01-01

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

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

NASA Technical Reports Server (NTRS)

1997-01-01

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

KSC-97pc679

NASA Image and Video Library

1997-04-21

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

KSC-97pc729

NASA Image and Video Library

1997-04-22

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

KSC-97pc677

NASA Image and Video Library

1997-04-21

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

Backflushing system rapidly cleans fluid filters

NASA Technical Reports Server (NTRS)

Descamp, V. A.; Boex, M. W.; Hussey, M. W.; Larson, T. P.

1973-01-01

Self contained unit can backflush filter elements in fraction of the time expended by presently used equipment. This innovation may be of interest to manufacturers of hydraulic and pneumatic systems as well as to chemical, food, processing, and filter manufacturing industries.

Design of a Solar Sail Mission to Mars

NASA Technical Reports Server (NTRS)

Feaux, K.; Jordan, W.; Killough, G.; Miller, R.; Plunk, V.

1989-01-01

A new area of interest in space vehicles is the solar sail. Various applications for which it has been considered are attitude control of satellites, focusing light on the jungles of Vietnam, and a Halley's comet rendezvous. Although for various reasons these projects were never completed, new interest in solar sails has arisen. The solar sail is an alternative to the rocket-propelled space vehicle as an interplanetary cargo vehicle, and manufacture of solar sails on the space station is a possibility. Solar sails have several advantages over rockets, including an unlimited power supply and low maintenance. The purpose of this project is to design a solar sail mission to Mars. The spacecraft will efficiently journey to Mars powered only by a solar sail. The vehicle weighs 487.16 kg and will be launchable on an expendable launch vehicle. The project includes an investigation of options to minimize cost, weight, and flight duration. The design of the sail and its deployment system are a major part of the project, as is the actual mission planning. Various topics researched include solar power, material, space environment, thermal control, trajectories, and orbit transfer. Various configurations are considered in order to determine the optimal structure. Another design consideration is the control system of the vehicle. This system includes the attitude control and the communication system of the sail. This project will aid in determining the feasibility of a solar sail and will raise public interest in space research.

21 CFR 1403.20 - Standards for financial management systems.

Code of Federal Regulations, 2011 CFR

2011-04-01

... 21 Food and Drugs 9 2011-04-01 2011-04-01 false Standards for financial management systems. 1403... Financial Administration § 1403.20 Standards for financial management systems. (a) A State must expend and... of applicable statutes. (b) The financial management systems of other grantees and subgrantees must...

21 CFR 1403.20 - Standards for financial management systems.

Code of Federal Regulations, 2013 CFR

2013-04-01

... 21 Food and Drugs 9 2013-04-01 2013-04-01 false Standards for financial management systems. 1403... Financial Administration § 1403.20 Standards for financial management systems. (a) A State must expend and... of applicable statutes. (b) The financial management systems of other grantees and subgrantees must...

21 CFR 1403.20 - Standards for financial management systems.

Code of Federal Regulations, 2012 CFR

2012-04-01

... 21 Food and Drugs 9 2012-04-01 2012-04-01 false Standards for financial management systems. 1403... Financial Administration § 1403.20 Standards for financial management systems. (a) A State must expend and... of applicable statutes. (b) The financial management systems of other grantees and subgrantees must...

10 CFR 600.220 - Standards for financial management systems.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 10 Energy 4 2013-01-01 2013-01-01 false Standards for financial management systems. 600.220... Post-Award Requirements § 600.220 Standards for financial management systems. (a) A State must expend... prohibitions of applicable statutes. (b) The financial management systems of other grantees and subgrantees...

10 CFR 600.220 - Standards for financial management systems.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 10 Energy 4 2012-01-01 2012-01-01 false Standards for financial management systems. 600.220... Post-Award Requirements § 600.220 Standards for financial management systems. (a) A State must expend... prohibitions of applicable statutes. (b) The financial management systems of other grantees and subgrantees...

10 CFR 600.220 - Standards for financial management systems.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 10 Energy 4 2014-01-01 2014-01-01 false Standards for financial management systems. 600.220... Post-Award Requirements § 600.220 Standards for financial management systems. (a) A State must expend... prohibitions of applicable statutes. (b) The financial management systems of other grantees and subgrantees...

21 CFR 1403.20 - Standards for financial management systems.

Code of Federal Regulations, 2014 CFR

2014-04-01

... 21 Food and Drugs 9 2014-04-01 2014-04-01 false Standards for financial management systems. 1403... Financial Administration § 1403.20 Standards for financial management systems. (a) A State must expend and... of applicable statutes. (b) The financial management systems of other grantees and subgrantees must...

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

Federal Register 2010, 2011, 2012, 2013, 2014

2011-08-23

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

7 CFR 3019.35 - Supplies and other expendable property.

Code of Federal Regulations, 2010 CFR

2010-01-01

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

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

NASA Astrophysics Data System (ADS)

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

2008-12-01

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

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

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

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

14 CFR 1214.502 - Definitions.

Code of Federal Regulations, 2011 CFR

2011-01-01

... and other critical space systems, including Space Station Freedom, designated Expendable Launch... 14 Aeronautics and Space 5 2011-01-01 2010-01-01 true Definitions. 1214.502 Section 1214.502 Aeronautics and Space NATIONAL AERONAUTICS AND SPACE ADMINISTRATION SPACE FLIGHT Mission Critical Space System...

14 CFR 1214.502 - Definitions.

Code of Federal Regulations, 2013 CFR

2013-01-01

... and other critical space systems, including Space Station Freedom, designated Expendable Launch... 14 Aeronautics and Space 5 2013-01-01 2013-01-01 false Definitions. 1214.502 Section 1214.502 Aeronautics and Space NATIONAL AERONAUTICS AND SPACE ADMINISTRATION SPACE FLIGHT Mission Critical Space System...

14 CFR 1214.502 - Definitions.

Code of Federal Regulations, 2012 CFR

2012-01-01

... and other critical space systems, including Space Station Freedom, designated Expendable Launch... 14 Aeronautics and Space 5 2012-01-01 2012-01-01 false Definitions. 1214.502 Section 1214.502 Aeronautics and Space NATIONAL AERONAUTICS AND SPACE ADMINISTRATION SPACE FLIGHT Mission Critical Space System...

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

NASA Technical Reports Server (NTRS)

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

2015-01-01

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

Advanced Extravehicular Protective System (AEPS) study

NASA Technical Reports Server (NTRS)

Williams, J. L.; Webbon, B. W.; Copeland, R. J.

1972-01-01

A summary is presented of Advanced Extravehicular Protective Systems (AEPS) for the future missions beyond Skylab in earth orbit, on the lunar surface, and on the Martian surface. The study concentrated on the origination of regenerable life support concepts for use in portable extravehicular protective systems, and included evaluation and comparison with expendable systems, and selection of life support subsystems. The study was conducted in two phases. In the first phase, subsystem concepts for performing life support functions in AEPS which are regenerable or partially regenerable were originated, and in addition, expendable subsystems were considered. Parametric data for each subsystem concept were evolved including subsystem weight and volume, power requirement, thermal control requirement; base regeneration equipment weight and volume, requirement. The second phase involved an evaluation of the impact of safety considerations involving redundant and/or backup systems on the selection of the regenerable life support subsystems. In addition, the impact of the space shuttle program on regenerable life support subsystem development was investigated.

43 CFR 12.935 - Supplies and other expendable property.

Code of Federal Regulations, 2010 CFR

2010-10-01

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

29 CFR 99.205 - Basis for determining Federal awards expended.

Code of Federal Regulations, 2010 CFR

2010-07-01

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

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

Code of Federal Regulations, 2011 CFR

2011-10-01

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

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

Code of Federal Regulations, 2010 CFR

2010-10-01

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

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

ERIC Educational Resources Information Center

Eysenck, Michael W.; Eysenck, M. Christine

1979-01-01

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

Future Launch Vehicle Structures - Expendable and Reusable Elements

NASA Astrophysics Data System (ADS)

Obersteiner, M. H.; Borriello, G.

2002-01-01

Further evolution of existing expendable launch vehicles will be an obvious element influencing the future of space transportation. Besides this reusability might be the change with highest potential for essential improvement. The expected cost reduction and finally contributing to this, the improvement of reliability including safe mission abort capability are driving this idea. Although there are ideas of semi-reusable launch vehicles, typically two stages vehicles - reusable first stage or booster(s) and expendable second or upper stage - it should be kept in mind that the benefit of reusability will only overwhelm if there is a big enough share influencing the cost calculation. Today there is the understanding that additional technology preparation and verification will be necessary to master reusability and get enough benefits compared with existing launch vehicles. This understanding is based on several technology and system concepts preparation and verification programmes mainly done in the US but partially also in Europe and Japan. The major areas of necessary further activities are: - System concepts including business plan considerations - Sub-system or component technologies refinement - System design and operation know-how and capabilities - Verification and demonstration oriented towards future mission mastering: One of the most important aspects for the creation of those coming programmes and activities will be the iterative process of requirements definition derived from concepts analyses including economical considerations and the results achieved and verified within technology and verification programmes. It is the intention of this paper to provide major trends for those requirements focused on future launch vehicles structures. This will include the aspects of requirements only valid for reusable launch vehicles and those common for expendable, semi-reusable and reusable launch vehicles. Structures and materials is and will be one of the important technology areas to be improved. This includes: - Primary structures - Thermal protection systems (for high and low temperatures) - Hot structures (leading edges, engine cowling, ...) - Tanks (for various propellants and fluids, cryo, ...) Requirements to be considered are including materials properties and a variety of loads definition - static and dynamic. Based on existing knowledge and experience for expendable LV (Ariane, ...) and aircraft there is the need to established a combined understanding to provide the basis for an efficient RLV design. Health monitoring will support the cost efficient operation of future reusable structures, but will also need a sound understanding of loads and failure mechanisms as basis. Risk mitigation will ask for several steps of demonstration towards a cost efficient RLV (structures) operation. Typically this has or will start with basic technology, to be evolved to components demonstration (TPS, tanks, ...) and finally to result in the demonstration of the cost efficient reuse operation. This paper will also include a programmatic logic concerning future LV structures demonstration.

Simultaneous Deep-Ocean Operations With Autonomous and Remotely Operated Vehicles

NASA Astrophysics Data System (ADS)

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

2005-12-01

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

Manta A New BroadBand OBS

NASA Astrophysics Data System (ADS)

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

2017-12-01

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

45 CFR 1174.20 - Standards for financial management systems.

Code of Federal Regulations, 2010 CFR

2010-10-01

... 45 Public Welfare 3 2010-10-01 2010-10-01 false Standards for financial management systems. 1174... Financial Administration § 1174.20 Standards for financial management systems. (a) A State must expand and account for grant funds in accordance with State laws and procedures for expending and accounting for its...

22 CFR 135.20 - Standards for financial management systems.

Code of Federal Regulations, 2010 CFR

2010-04-01

... 22 Foreign Relations 1 2010-04-01 2010-04-01 false Standards for financial management systems. 135... Financial Administration § 135.20 Standards for financial management systems. (a) A State must expand and account for grant funds in accordance with State laws and procedures for expending and accounting for its...

34 CFR 80.20 - Standards for financial management systems.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 34 Education 1 2010-07-01 2010-07-01 false Standards for financial management systems. 80.20... Financial Administration § 80.20 Standards for financial management systems. (a) A State must expand and account for grant funds in accordance with State laws and procedures for expending and accounting for its...

45 CFR 1183.20 - Standards for financial management systems.

Code of Federal Regulations, 2010 CFR

2010-10-01

... 45 Public Welfare 3 2010-10-01 2010-10-01 false Standards for financial management systems. 1183... Financial Administration § 1183.20 Standards for financial management systems. (a) A State must expand and account for grant funds in accordance with State laws and procedures for expending and accounting for its...

10 CFR 600.220 - Standards for financial management systems.

Code of Federal Regulations, 2011 CFR

2011-01-01

... subgrant award documents, etc. (7) Cash management. Procedures for minimizing the time elapsing between the... 10 Energy 4 2011-01-01 2011-01-01 false Standards for financial management systems. 600.220... Post-Award Requirements § 600.220 Standards for financial management systems. (a) A State must expend...

The Perils of Prototyping.

ERIC Educational Resources Information Center

Lowry, Christina; Little, Robert

1985-01-01

The benefits of prototyping as a basis for system design include better specifications, earlier discovery of omissions and extensions, and the likelihood of salvaging much of the effort expended on the prototype. Risks and methods of prototyping during rapid systems development are also noted. (Author/MLW)

Conceptual Design of an Electric Sail Technology Demonstration Mission Spacecraft

NASA Technical Reports Server (NTRS)

Wiegmann, Bruce M.

2017-01-01

There is great interest in examining the outer planets of our solar system and Heliopause region (edge of Solar System) and beyond regions of interstellar space by both the Planetary and Heliophysics communities. These needs are well docu-mented in the recent National Academy of Sciences Decadal Surveys. There is significant interest in developing revolutionary propulsion techniques that will enable such Heliopause scientific missions to be completed within 10 to15 years of the launch date. One such enabling propulsion technique commonly known as Electric Sail (E-Sail) propulsion employs positively charged bare wire tethers that extend radially outward from a rotating spacecraft spinning at a rate of one revolution per hour. Around the positively charged bare-wire tethers, a Debye Sheath is created once positive voltage is applied. This sheath stands off of the bare wire tether at a sheath diameter that is proportional to the voltage in the wire coupled with the flux density of solar wind ions within the solar system (or the location of spacecraft in the solar system. The protons that are expended from the sun (solar wind) at 400 to 800 km/sec are electrostatically repelled away from these positively charged Debye sheaths and propulsive thrust is produced via the resulting momentum transfer. The amount of thrust produced is directly proportional to the total wire length. The Marshall Space Flight Center (MSFC) Electric Sail team is currently funded via a two year Phase II NASA Innovative Advanced Concepts (NIAC) awarded in July 2015. The team's current activities are: 1) Developing a Particle in Cell (PIC) numeric engineering model from the experimental data collected at MSFC's Solar Wind Facility on the interaction between simulated solar wind interaction with a charged bare wire that can be applied to a variety of missions, 2) The development of the necessary tether deployers and tethers to enable successful de-ployment of multiple, multi km length bare tethers, 3) Controllability of the space-craft via a voltage bias to steer itself through the solar system to destinations of discovery. These activities once demonstrated analytically, will require a technology demonstration mission (TDM) around the year2020 to demonstrate that all systems work together seamlessly before a Heliophysics Electrostatic Rapid Transit System (HERTS) mission could be initiated. A notional TDM spacecraft that meets the requirements of such a mission will be showcased in this paper.

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

NASA Astrophysics Data System (ADS)

Boyle, J. P.

2016-02-01

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

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

NASA Astrophysics Data System (ADS)

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

2014-12-01

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

Systems Innovation and Education Management Systems (EMS)

ERIC Educational Resources Information Center

Rao, Nageswararao A. V.

2006-01-01

Many researchers and practitioners contend that all institutions respond to changing market need and can create competitive advantage through innovation and creativity. Each year, institutions expend significant resources developing new products and processes and yet research shows that more than half these initiatives fail. Successful…

Advanced extravehicular protective systems study, volume 1

NASA Technical Reports Server (NTRS)

Sutton, J. G.; Heimlich, P. F.; Tepper, E. H.

1972-01-01

An appraisal was made of advanced portable and emergency life support systems concepts for space station, space shuttle, lunar base, and Mars EVA missions. Specifications are given, and the methodology is described. Subsystem studies and systems integration efforts are summarized. Among the conclusions are the following: (1) For long duration missions, a configuration incorporating a regenerable CO2 control subsystem and a thermal control subsystem utilizing a minimum of expendables decreases the vehicle penalty of present configurations. (2) For shorter duration missions, a configuration incorporating an expendable water thermal control subsystem is the most competitive subsystem; regenerable CO2 control subsystems if properly developed are competitive with nonregenerable counterparts. (3) The CO2 reduction and oxygen reclamation withing the parent vehicle is only competitive when there are three or more parent vehicle resupply periods. (4) For long duration emergency systems of one hour or more, inherent redundancy within the primary configuration to provide emergency thermal control is the most competitive approach.

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

Code of Federal Regulations, 2010 CFR

2010-10-01

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

An Accounting View of Management in Higher Education

ERIC Educational Resources Information Center

Sperry, John B.

1975-01-01

Presents a system based on fund accounting highlighting the accountability for resources that have been allocated and expended for the purpose specified but providing relevant cost data for effective educational management. (Author/PG)

14 CFR 401.5 - Definitions.

Code of Federal Regulations, 2011 CFR

2011-01-01

.... Expendable launch vehicle means a launch vehicle whose propulsive stages are flown only once. Experimental... during a launch or reentry. Flight safety system means a system designed to limit or restrict the hazards... States. Launch includes the flight of a launch vehicle and includes pre- and post-flight ground...

14 CFR 401.5 - Definitions.

Code of Federal Regulations, 2012 CFR

2012-01-01

.... Expendable launch vehicle means a launch vehicle whose propulsive stages are flown only once. Experimental... during a launch or reentry. Flight safety system means a system designed to limit or restrict the hazards... States. Launch includes the flight of a launch vehicle and includes pre- and post-flight ground...

14 CFR 401.5 - Definitions.

Code of Federal Regulations, 2010 CFR

2010-01-01

.... Expendable launch vehicle means a launch vehicle whose propulsive stages are flown only once. Experimental... during a launch or reentry. Flight safety system means a system designed to limit or restrict the hazards... States. Launch includes the flight of a launch vehicle and includes pre- and post-flight ground...

Polymer matrix nanocomposites for automotive structural components

DOE PAGES

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

2016-12-06

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

Polymer matrix nanocomposites for automotive structural components

NASA Astrophysics Data System (ADS)

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

2016-12-01

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

Polymer matrix nanocomposites for automotive structural components.

PubMed

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

2016-12-06

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

Oceanographic Measurements Program Review.

DTIC Science & Technology

1982-03-01

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

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

Code of Federal Regulations, 2010 CFR

2010-10-01

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

Economic analysis of new space transportation systems: Executive summary

NASA Technical Reports Server (NTRS)

1971-01-01

An economic analysis of alternative space transportation systems is presented. Results indicate that the expendable systems represent modest investments, but the recurring costs of operation would remain high. The space shuttle and tug system requires a substantial investment, but would substantially reduce the recurring costs of operation. Economic benefits and costs of the different systems are also analyzed. Findings are summarized.

Study of extraterrestrial disposal of radioactive wastes. Part 1: Space transportation and destination considerations for extraterrestrial disposal of radioactive wastes. [feasibility of using space shuttle

NASA Technical Reports Server (NTRS)

Thompson, R. L.; Ramler, J. R.; Stevenson, S. M.

1974-01-01

A feasibility study of extraterrestrial disposal of radioactive waste is reported. This report covers the initial work done on only one part of the NASA study, that evaluates and compares possible space destinations and space transportation systems. The currently planned space shuttle was found to be more cost effective than current expendable launch vehicles by about a factor of 2. The space shuttle requires a third stage to perform the waste disposal missions. Depending on the particular mission, this third stage could be either a reusable space tug or an expendable stage such as a Centaur.

Automated Guideway Network Traffic Modeling

DOT National Transportation Integrated Search

1972-02-01

In the literature concerning automated guideway transportation systems, such as dual mode, a great deal of effort has been expended on the use of deterministic reservation schemes and the problem of merging streams of vehicles. However, little attent...

Vehicle systems

NASA Technical Reports Server (NTRS)

Bales, Tom; Modlin, Tom; Suddreth, Jack; Wheeler, Tom; Tenney, Darrel R.; Bayless, Ernest O.; Lisagor, W. Barry; Bolstad, Donald A.; Croop, Harold; Dyer, J.

1993-01-01

Perspectives of the subpanel on expendable launch vehicle structures and cryotanks are: (1) new materials which provide the primary weight savings effect on vehicle mass/size; (2) today's investment; (3) typically 10-20 years to mature and fully characterize new materials.

45 CFR 2541.200 - Standards for financial management systems.

Code of Federal Regulations, 2010 CFR

2010-10-01

... 45 Public Welfare 4 2010-10-01 2010-10-01 false Standards for financial management systems. 2541... STATE AND LOCAL GOVERNMENTS Post-Award Requirements § 2541.200 Standards for financial management... for expending and accounting for its own funds. Fiscal control and accounting procedures of the State...

Space shuttle environmental and thermal control life support system computer program

NASA Technical Reports Server (NTRS)

1972-01-01

A computer program for the design and operation of the space shuttle environmental and thermal control life support system is presented. The subjects discussed are: (1) basic optimization program, (2) off design performance, (3) radiator/evaporator expendable usage, (4) component weights, and (5) computer program operating procedures.

23 CFR 1200.13 - Special funding conditions for Section 402 grants.

Code of Federal Regulations, 2013 CFR

2013-04-01

.... (b) Automated traffic enforcement systems prohibition. The State may not expend funds apportioned to the State under 23 U.S.C. 402 to carry out a program to purchase, operate, or maintain an automated traffic enforcement system. The term “automated traffic enforcement system” includes any camera which...

23 CFR 1200.13 - Special funding conditions for Section 402 grants.

Code of Federal Regulations, 2014 CFR

2014-04-01

.... (b) Automated traffic enforcement systems prohibition. The State may not expend funds apportioned to the State under 23 U.S.C. 402 to carry out a program to purchase, operate, or maintain an automated traffic enforcement system. The term “automated traffic enforcement system” includes any camera which...

Laser System Reliability

DTIC Science & Technology

1977-03-01

system acquisition cycle since they provide necessary inputs to comparative analyses, cost/benefit trade -offs, and system simulations. In addition, the...Management Program from above performs the function of analyzing the system trade -offs with respect to reliability to determine a reliability goal...one encounters the problem of comparing present dollars with future dollars. In this analysis, we are trading off costs expended initially (or at

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

NASA Technical Reports Server (NTRS)

1997-01-01

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

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

NASA Technical Reports Server (NTRS)

1997-01-01

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

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

NASA Technical Reports Server (NTRS)

1997-01-01

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

KSC-97pc678

NASA Image and Video Library

1997-04-21

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

KSC-97pc680

NASA Image and Video Library

1997-04-21

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

KSC-97pc682

NASA Image and Video Library

1997-04-21

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

KSC-97pc681

NASA Image and Video Library

1997-04-21

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

Cassini orbiter arrives at SLF

NASA Technical Reports Server (NTRS)

1997-01-01

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

Cassini orbiter arrives at SLF

NASA Technical Reports Server (NTRS)

1997-01-01

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

Precision Control Module For UV Laser 3D Micromachining

NASA Astrophysics Data System (ADS)

Wu, Wen-Hong; Hung, Min-Wei; Chang, Chun-Li

2011-01-01

UV laser has been widely used in various micromachining such as micro-scribing or patterning processing. At present, most of the semiconductors, LEDs, photovoltaic solar panels and touch panels industries need the UV laser processing system. However, most of the UV laser processing applications in the industries utilize two dimensional (2D) plane processing. And there are tremendous business opportunities that can be developed, such as three dimensional (3D) structures of micro-electromechanical (MEMS) sensor or the precision depth control of indium tin oxide (ITO) thin films edge insulation in touch panels. This research aims to develop a UV laser 3D micromachining module that can create the novel applications for industries. By special designed beam expender in optical system, the focal point of UV laser can be adjusted quickly and accurately through the optical path control lens of laser beam expender optical system. Furthermore, the integrated software for galvanometric scanner and focal point adjustment mechanism is developed as well, so as to carry out the precise 3D microstructure machining.

Expendable launch vehicle transportation for the space station

NASA Technical Reports Server (NTRS)

Corban, Robert R.

1988-01-01

Logistics transportation will be a critical element in determining the Space Station Freedom's level of productivity and possible evolutionary options. The current program utilizes the Space Shuttle as the only logistics support vehicle. Augmentation of the total transportation capability by expendable launch vehicles (ELVs) may be required to meet demanding requirements and provide for enhanced manifest flexibility. The total operational concept from ground operations to final return of support hardware or its disposal is required to determine the ELV's benefits and impacts to the Space Station Freedom program. The characteristics of potential medium and large class ELVs planned to be available in the mid-1990's (both U.S. and international partners' vehicles) indicate a significant range of possible transportation systems with varying degrees of operational support capabilities. The options available for development of a support infrastructure in terms of launch vehicles, logistics carriers, transfer vehicles, and return systems is discussed.

NASA's New Orbital Space Plane: A Bridge to the Future

NASA Technical Reports Server (NTRS)

Davis, Stephan R.; Engler, Leah M.; Fisher, Mark F.; Dumbacher, Dan L.; Boswell, Barry E.

2003-01-01

NASA is developing a new spacecraft system called the Orbital Space Plane (OSP). The OSP will be launched on an expendable launch vehicle and serve to augment the shuttle in support of the International Space Station by transporting astronauts to and from the International Space Station and by providing a crew rescue system.

23 CFR 140.602 - Requirements and conditions.

Code of Federal Regulations, 2011 CFR

2011-04-01

... construction of projects on the Federal-aid primary or Interstate system, or extensions of any of the Federal...)(4), may claim payment of any portion of such sums apportioned to it for expenditures on such system... proceeds of bonds have actually been expended in the construction of projects. (b) Any interest earned and...

23 CFR 140.602 - Requirements and conditions.

Code of Federal Regulations, 2012 CFR

2012-04-01

... construction of projects on the Federal-aid primary or Interstate system, or extensions of any of the Federal...)(4), may claim payment of any portion of such sums apportioned to it for expenditures on such system... proceeds of bonds have actually been expended in the construction of projects. (b) Any interest earned and...

23 CFR 140.602 - Requirements and conditions.

Code of Federal Regulations, 2010 CFR

2010-04-01

... construction of projects on the Federal-aid primary or Interstate system, or extensions of any of the Federal...)(4), may claim payment of any portion of such sums apportioned to it for expenditures on such system... proceeds of bonds have actually been expended in the construction of projects. (b) Any interest earned and...

Evaluation of an Intervention Program to Increase Immunization Compliance among School Children

ERIC Educational Resources Information Center

Luthy, Karlen E.; Thorpe, Aubrey; Dymock, Leah Clark; Connely, Samantha

2011-01-01

State immunization laws necessitate compliance for students enrolling in a public or private school system. In support of state laws, school nurses expend hours to achieve immunization compliance with school-age children. For the purpose of creating a more efficient system, researchers implemented an educational and incentive program in local…

From Earth to Orbit: An assessment of transportation options

NASA Technical Reports Server (NTRS)

Gavin, Joseph G., Jr.; Blond, Edmund; Brill, Yvonne C.; Budiansky, Bernard; Cooper, Robert S.; Demisch, Wolfgang H.; Hawk, Clark W.; Kerrebrock, Jack L.; Lichtenberg, Byron K.; Mager, Artur

1992-01-01

The report assesses the requirements, benefits, technological feasibility, and roles of Earth-to-Orbit transportation systems and options that could be developed in support of future national space programs. Transportation requirements, including those for Mission-to-Planet Earth, Space Station Freedom assembly and operation, human exploration of space, space science missions, and other major civil space missions are examined. These requirements are compared with existing, planned, and potential launch capabilities, including expendable launch vehicles (ELV's), the Space Shuttle, the National Launch System (NLS), and new launch options. In addition, the report examines propulsion systems in the context of various launch vehicles. These include the Advanced Solid Rocket Motor (ASRM), the Redesigned Solid Rocket Motor (RSRM), the Solid Rocket Motor Upgrade (SRMU), the Space Shuttle Main Engine (SSME), the Space Transportation Main Engine (STME), existing expendable launch vehicle engines, and liquid-oxygen/hydrocarbon engines. Consideration is given to systems that have been proposed to accomplish the national interests in relatively cost effective ways, with the recognition that safety and reliability contribute to cost-effectiveness. Related resources, including technology, propulsion test facilities, and manufacturing capabilities are also discussed.

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

DTIC Science & Technology

1993-08-01

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

The October 1973 NASA mission model analysis and economic assessment

NASA Technical Reports Server (NTRS)

1974-01-01

Results are presented of the 1973 NASA Mission Model Analysis. The purpose was to obtain an economic assessment of using the Shuttle to accommodate the payloads and requirements as identified by the NASA Program Offices and the DoD. The 1973 Payload Model represents a baseline candidate set of future payloads which can be used as a reference base for planning purposes. The cost of implementing these payload programs utilizing the capabilities of the shuttle system is analyzed and compared with the cost of conducting the same payload effort using expendable launch vehicles. There is a net benefit of 14.1 billion dollars as a result of using the shuttle during the 12-year period as compared to using an expendable launch vehicle fleet.

About Regional Energy Deployment System Model-ReEDS | Regional Energy

Science.gov Websites

Deployment System Model | Energy Analysis | NREL About Regional Energy Deployment System Model -ReEDS About Regional Energy Deployment System Model-ReEDS The Regional Energy Deployment System (ReEDS ) is a long-term, capacity-expansion model for the deployment of electric power generation technologies

School Funding in Michigan: Common Myths. A Mackinac Center Report

ERIC Educational Resources Information Center

Van Beek, Michael

2010-01-01

Michigan's state-run school system is the largest and most expensive government service taxpayers support. It employs more than 350,000 people who work in one of the more than 4,100 different entities. The total amount this system expends each year adds up to more than $20 billion. Given the enormity and complexity of the system, it's no surprise…

From the Provider-Led to an Employer-Led System: Implications of Apprenticeship Reform on the Private Training Market

ERIC Educational Resources Information Center

Chankseliani, Maia; Relly, Susan James

2015-01-01

Despite expending a great deal of public money, and after many government-led "reforms" to develop an apprenticeship system that rivals those found in other countries, the apprenticeship system in England still faces a number of challenges and failings, not least in the private training market. This paper explores the landscape of…

Optimum rocket propulsion for energy-limited transfer

NASA Technical Reports Server (NTRS)

Zuppero, Anthony; Landis, Geoffrey A.

1991-01-01

In order to effect large-scale return of extraterrestrial resources to Earth orbit, it is desirable to optimize the propulsion system to maximize the mass of payload returned per unit energy expended. This optimization problem is different from the conventional rocket propulsion optimization. A rocket propulsion system consists of an energy source plus reaction mass. In a conventional chemical rocket, the energy source and the reaction mass are the same. For the transportation system required, however, the best system performance is achieved if the reaction mass used is from a locally available source. In general, the energy source and the reaction mass will be separate. One such rocket system is the nuclear thermal rocket, in which the energy source is a reactor and the reaction mass a fluid which is heated by the reactor and exhausted. Another energy-limited rocket system is the hydrogen/oxygen rocket where H2/O2 fuel is produced by electrolysis of water using a solar array or a nuclear reactor. The problem is to choose the optimum specific impulse (or equivalently exhaust velocity) to minimize the amount of energy required to produce a given mission delta-v in the payload. The somewhat surprising result is that the optimum specific impulse is not the maximum possible value, but is proportional to the mission delta-v. In general terms, at the beginning of the mission it is optimum to use a very low specific impulse and expend a lot of reaction mass, since this is the most energy efficient way to transfer momentum. However, as the mission progresses, it becomes important to minimize the amount of reaction mass expelled, since energy is wasted moving the reaction mass. Thus, the optimum specific impulse will increase with the mission delta-v. Optimum I(sub sp) is derived for maximum payload return per energy expended for both the case of fixed and variable I(sub sp) engines. Sample missions analyzed include return of water payloads from the moons of Mars and of Saturn.

Starshade orbital maneuver study for WFIRST

NASA Astrophysics Data System (ADS)

Soto, Gabriel; Sinha, Amlan; Savransky, Dmitry; Delacroix, Christian; Garrett, Daniel

2017-09-01

The Wide Field Infrared Survey Telescope (WFIRST) mission, scheduled for launch in the mid-2020s will perform exoplanet science via both direct imaging and a microlensing survey. An internal coronagraph is planned to perform starlight suppression for exoplanet imaging, but an external starshade could be used to achieve the required high contrasts with potentially higher throughput. This approach would require a separately-launched occulter spacecraft to be positioned at exact distances from the telescope along the line of sight to a target star system. We present a detailed study to quantify the Δv requirements and feasibility of deploying this additional spacecraft as a means of exoplanet imaging. The primary focus of this study is the fuel use of the occulter while repositioning between targets. Based on its design, the occulter is given an offset distance from the nominal WFIRST halo orbit. Target star systems and look vectors are generated using Exoplanet Open-Source Imaging Simulator (EXOSIMS); a boundary value problem is then solved between successive targets. On average, 50 observations are achievable with randomly selected targets given a 30-day transfer time. Individual trajectories can be optimized for transfer time as well as fuel usage to be used in mission scheduling. Minimizing transfer time reduces the total mission time by up to 4.5 times in some simulations before expending the entire fuel budget. Minimizing Δv can generate starshade missions that achieve over 100 unique observations within the designated mission lifetime of WFIRST.

Access to Space : The Future of U.S. Space Transportation Systems

DOT National Transportation Integrated Search

1990-04-01

The United States now has an operating, mixed fleet comprised of reusable Space Shuttle orbiters and expendable launch vehicles (ELVs). The government and the private sector have invested in new launch technologies and established a fledgling private...

NASA software specification and evaluation system design, part 1

NASA Technical Reports Server (NTRS)

1976-01-01

The research to develop methods for reducing the effort expended in software and verification is reported. The development of a formal software requirements methodology, a formal specifications language, a programming language, a language preprocessor, and code analysis tools are discussed.

Factors Influencing Post-Adoptive Enterprise Resource Planning (ERP) Utilization

ERIC Educational Resources Information Center

McGinnis, Thomas C.

2011-01-01

Organizations expend a great deal of time, effort and money on the implementation of enterprise resource planning (ERP) systems. They are considered the price of entry for large organizations to do business. Yet the success rate of ERP systems is poor. IS literature suggests that one possible reason for this is the underutilization of these…

Consortium for Robotics & Unmanned Systems Education & Research (CRUSER)

DTIC Science & Technology

2012-09-30

as facilities at Camp Roberts, Calif. and frequent experimentation events, the Many vs. Many ( MvM ) Autonomous Systems Testbed provides the...and expediently translate theory to practice. The MvM Testbed is designed to integrate technological advances in hardware (inexpensive, expendable...designed to leverage the MvM Autonomous Systems Testbed to explore practical and operationally relevant avenues to counter these “swarm” opponents, and

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

PubMed

Schmitt-Rodermund, Eva; Vondracek, Fred W

2002-02-01

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

Comparative evaluation of existing expendable upper stages for space shuttle

NASA Technical Reports Server (NTRS)

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

1974-01-01

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

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

NASA Technical Reports Server (NTRS)

Engle, Carl; Herald, Stephen; Watkins, Casey

2005-01-01

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

A web-server of cell type discrimination system.

PubMed

Wang, Anyou; Zhong, Yan; Wang, Yanhua; He, Qianchuan

2014-01-01

Discriminating cell types is a daily request for stem cell biologists. However, there is not a user-friendly system available to date for public users to discriminate the common cell types, embryonic stem cells (ESCs), induced pluripotent stem cells (iPSCs), and somatic cells (SCs). Here, we develop WCTDS, a web-server of cell type discrimination system, to discriminate the three cell types and their subtypes like fetal versus adult SCs. WCTDS is developed as a top layer application of our recent publication regarding cell type discriminations, which employs DNA-methylation as biomarkers and machine learning models to discriminate cell types. Implemented by Django, Python, R, and Linux shell programming, run under Linux-Apache web server, and communicated through MySQL, WCTDS provides a friendly framework to efficiently receive the user input and to run mathematical models for analyzing data and then to present results to users. This framework is flexible and easy to be expended for other applications. Therefore, WCTDS works as a user-friendly framework to discriminate cell types and subtypes and it can also be expended to detect other cell types like cancer cells.

A Web-Server of Cell Type Discrimination System

PubMed Central

Zhong, Yan

2014-01-01

Discriminating cell types is a daily request for stem cell biologists. However, there is not a user-friendly system available to date for public users to discriminate the common cell types, embryonic stem cells (ESCs), induced pluripotent stem cells (iPSCs), and somatic cells (SCs). Here, we develop WCTDS, a web-server of cell type discrimination system, to discriminate the three cell types and their subtypes like fetal versus adult SCs. WCTDS is developed as a top layer application of our recent publication regarding cell type discriminations, which employs DNA-methylation as biomarkers and machine learning models to discriminate cell types. Implemented by Django, Python, R, and Linux shell programming, run under Linux-Apache web server, and communicated through MySQL, WCTDS provides a friendly framework to efficiently receive the user input and to run mathematical models for analyzing data and then to present results to users. This framework is flexible and easy to be expended for other applications. Therefore, WCTDS works as a user-friendly framework to discriminate cell types and subtypes and it can also be expended to detect other cell types like cancer cells. PMID:24578634

48 CFR 1452.237-70 - Information Collection.

Code of Federal Regulations, 2014 CFR

2014-10-01

... 48 Federal Acquisition Regulations System 5 2014-10-01 2014-10-01 false Information Collection... Information Collection. As prescribed in 1437.7102, insert the following clause: Information Collection... information on identical items from ten or more public respondents, no action shall be taken or funds expended...

Space transportation and destination considerations for extraterrestrial disposal of radioactive waste

NASA Technical Reports Server (NTRS)

Zimmerman, A. V.; Thompson, R. L.; Lubick, R. J.

1973-01-01

A feasibility study is summarized of extraterrestrial (space) disposal of radioactive waste. The initial work on the evaluation and comparison of possible space destinations and launch vehicles is reported. Only current or planned space transportation systems were considered. The currently planned space shuttle was found to be more cost effective than current expendable launch vehicles, by about a factor of two. The space shuttle will require a third stage to perform the disposal missions. Depending on the particular mission this could be either a reusable space tug or an expendable stage such as a Centaur. Of the destinations considered, high earth orbits (between geostationary and lunar orbit altitudes), solar orbits (such as a 0.90 AU circular solar orbit) or a direct injection to solar system escape appear to be the best candidates. Both earth orbits and solar orbits have uncertainties regarding orbit stability and waste package integrity for times on the order of a million years.

Advanced Extravehicular Protective Systems (AEPS) study

NASA Technical Reports Server (NTRS)

Williams, J. L.; Copeland, R. J.; Webbon, B. W.

1971-01-01

A description is given of life support subsystem concepts for advanced extravehicular protective systems (AEPS) intended for use on future orbital, lunar surface, and Mars surface missions in the late 1970's and 1980's. Primary interest was centered around the thermal control and carbon dioxide control subsystems because they offer the greatest potential for total weight savings. Emphasis was placed on the generation of regenerable subsystem concepts; however, partially regenerable and expendable concepts were also considered. Previously conceived and developed subsystem concepts were included in the study. Concepts were evaluated on the basis of subsystem weight and volume, and subsystem contribution to parent vehicle weight and volume, which included spares, regeneration equipment, expendables, expandables storage penalty, power penalty, and process heating or cooling penalty. Results are presented showing total weight and volume penalty as a function of total mission extravehicular activity (EVA) hours, and showing EVA weight and volume as a function of EVA duration. Subsystem concepts are recommended for each life support function, and secondary concepts which should be developed are also identified.

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

Code of Federal Regulations, 2012 CFR

2012-07-01

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

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

Code of Federal Regulations, 2011 CFR

2011-07-01

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

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

Code of Federal Regulations, 2013 CFR

2013-07-01

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

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

Code of Federal Regulations, 2014 CFR

2014-07-01

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

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

Code of Federal Regulations, 2010 CFR

2010-07-01

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

Early Program Development

NASA Image and Video Library

1970-01-01

In 1970, NASA initiated Phase A contracts to study alternate Space Shuttle designs in addition to the two-stage fully-reusable Space Shuttle system already under development. A number of alternate systems were developed to ensure the development of the optimum earth-to-orbit system, including the Stage-and-a-half Chemical Interorbital Shuttle, shown here. The concept would utilize a reusable marned spacecraft with an onboard propulsion system attached to an expendable fuel tank to provide supplementary propellants.

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

PubMed

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

2014-10-03

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

Membrane water deaerator investigation. [fluid filter breadboard model

NASA Technical Reports Server (NTRS)

Elam, J.; Ruder, J.; Strumpf, H.

1974-01-01

The purpose of the membrane water deaerator program was to develop data on a breadboard hollow fiber membrane unit that removes both dissolved and evolved gas from a water transfer system in order to: (1) assure a hard fill of the EVLSS expendable water tank; (2) prevent flow blockage by gas bubbles in circulating systems; and (3) prevent pump cavitation.

Descriptive Summaries of the Research Development Test & Evaluation Army Appropriation FY 1983. Supporting Data FY 1983, Budget Estimate Submitted to Congress February 1982. Volume II.

DTIC Science & Technology

1982-02-01

Defense (BHD) Advanced Technology Program is a broadly based rsearch and development effort designed to exploit new and emerging technologies...11-363 DK13 NON -COMMUNICATIONS ELECTRONIC COUNTERMEASURES SYSTEMS .............................. .11-368 DK14 EXPENDABLE JAMMERS...NAVSTAR GLOBAL POSITIONING SYSTEMS (GPS) USER EQUIPMENT .................................. 111-366 DEFENSEWIDE MISSION SUPPORT 6.37.38.A NON -SYSTEMS

38 CFR 43.20 - Standards for financial management systems.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 38 Pensions, Bonuses, and Veterans' Relief 2 2010-07-01 2010-07-01 false Standards for financial... LOCAL GOVERNMENTS Post-Award Requirements Financial Administration § 43.20 Standards for financial... procedures for expending and accounting for its own funds. Fiscal control and accounting procedures of the...

40 CFR 31.20 - Standards for financial management systems.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 40 Protection of Environment 1 2010-07-01 2010-07-01 false Standards for financial management... LOCAL GOVERNMENTS Post-Award Requirements Financial Administration § 31.20 Standards for financial... procedures for expending and accounting for its own funds. Fiscal control and accounting procedures of the...

Financing Continuing Education in Mental Health.

ERIC Educational Resources Information Center

Southern Regional Education Board, Atlanta, GA.

Based on a study of the component parts of the mental health continuing education system, this publication presents guidelines for the following fiscal functions: determining funding needs, obtaining funds, budgeting funds, expending funds, and cost accounting. In addition to considering these components, the guidelines explore principal issues in…

A modular design for rapid-response telecoms and navigation missions

NASA Astrophysics Data System (ADS)

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

2004-11-01

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

Patient credentialing as a population health management strategy: a diabetes case study.

PubMed

Watson, Lindsay L; Bluml, Benjamin M; Skoufalos, Alexandria

2015-06-01

When given the opportunity to become actively involved in the decision-making process, patients can positively impact their health outcomes. Understanding how to empower patients to become informed consumers of health care services is an important strategy for addressing disparities and variability in care. Patient credentialing identifies people who have a certain diagnosis and have achieved certain levels of competency in understanding and managing their disease. Patient credentialing was developed to meet 3 core purposes: (1) enhance patient engagement by increasing personal accountability for health outcomes, (2) create a mass customization strategy for providers to deliver high-quality, patient-centered collaborative care, and (3) provide payers with a foundation for properly aligning health benefit incentives. The Patient Self-Management Credential for Diabetes, a first-of-its-kind, psychometrically validated tool, has been deployed within 3 practice-based research initiatives as a component of innovative diabetes care. Results from these projects show improved clinical outcomes, reduced health care costs, and a relationship between credential achievement levels and clinical markers of diabetes. Implementing patient credentialing as part of collaborative care delivered within various settings across the health care system may be an effective way to reduce disparities, improve access to care and appropriate treatments, incentivize patient engagement in managing their health, and expend time and resources in a customized way to meet individual needs.

Cassini orbiter is moved to PHSF after arriving at SLF

NASA Technical Reports Server (NTRS)

1997-01-01

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

41 CFR 105-71.120 - Standards for financial management systems.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 41 Public Contracts and Property Management 3 2010-07-01 2010-07-01 false Standards for financial... GOVERNMENTS 71.12-Post-Award Requirements/Financial Administration § 105-71.120 Standards for financial... procedures for expending and accounting for its own funds. Fiscal control and accounting procedures of the...

Overview of rocket engine control

NASA Technical Reports Server (NTRS)

Lorenzo, Carl F.; Musgrave, Jeffrey L.

1991-01-01

The issues of Chemical Rocket Engine Control are broadly covered. The basic feedback information and control variables used in expendable and reusable rocket engines, such as Space Shuttle Main Engine, are discussed. The deficiencies of current approaches are considered and a brief introduction to Intelligent Control Systems for rocket engines (and vehicles) is presented.

40 CFR 35.3540 - Requirements for funding set-aside activities.

Code of Federal Regulations, 2010 CFR

2010-07-01

... workplan describing how it will expend funds needed to provide technical assistance to public water systems... OTHER FEDERAL ASSISTANCE STATE AND LOCAL ASSISTANCE Drinking Water State Revolving Funds § 35.3540 Requirements for funding set-aside activities. (a) General. If a State makes a grant or enters into a...

40 CFR 35.3540 - Requirements for funding set-aside activities.

Code of Federal Regulations, 2011 CFR

2011-07-01

... workplan describing how it will expend funds needed to provide technical assistance to public water systems... OTHER FEDERAL ASSISTANCE STATE AND LOCAL ASSISTANCE Drinking Water State Revolving Funds § 35.3540 Requirements for funding set-aside activities. (a) General. If a State makes a grant or enters into a...

An Experimental Study of a Catalytic Combustor for an Expendable Turbojet Engine

DTIC Science & Technology

1978-03-01

automobiles have catalytic converters in their exhaust systems for oxidizing unburned hydrocarbons, carbon monoxide, etc., to produce a cleaner exhaust. A...1 ratio for automobiles . Other noble metals are sometimes used, in varying ratio and loading (amount of catalyst. per area) configerations (Ref 7). 2

48 CFR 1852.228-78 - Cross-waiver of liability for NASA expendable launch vehicle launches.

Code of Federal Regulations, 2011 CFR

2011-10-01

... space exploration, use, and investment. The purpose of this clause is to extend this cross-waiver... Regulations System NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLAUSES AND FORMS SOLICITATION PROVISIONS AND... shall be broadly construed to achieve the objective of encouraging participation in space activities. (b...

Software design studies emphasizing Project LOGOS

NASA Technical Reports Server (NTRS)

1972-01-01

The results of a research project on the development of computer software are presented. Research funds of $200,000 were expended over a three year period for software design and projects in connection with Project LOGOS (computer-aided design and certification of computing systems). Abstracts of theses prepared during the project are provided.

Reducing work zone crashes by using vehicle's flashers as a warning sign : final report

DOT National Transportation Integrated Search

2009-01-01

Rural two-lane highways constitute a large percentage of the highway system in Kansas. Preserving, expending, : and enhancing these highways require the set-up of a large number of one-lane, two-way work zones where traffic : safety has been a severe...

Observed ocean thermal response to Hurricanes Gustav and Ike

NASA Astrophysics Data System (ADS)

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

2016-01-01

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

Simple, Robust Cryogenic Propellant Depot for Near Term Applications

NASA Technical Reports Server (NTRS)

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

2011-01-01

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

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

DOT National Transportation Integrated Search

1997-01-01

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

GPM Solar Array Gravity Negated Deployment Testing

NASA Technical Reports Server (NTRS)

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

2014-01-01

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

Conceptual design of a piloted Mars sprint life support system

NASA Technical Reports Server (NTRS)

Cullingford, H. S.; Novara, M.

1988-01-01

This paper presents the conceptual design of a life support system sustaining a crew of six in a piloted Mars sprint. The requirements and constraints of the system are discussed along with its baseline performance parameters. An integrated operation is achieved with air, water, and waste processing and supplemental food production. The design philosophy includes maximized reliability considerations, regenerative operations, reduced expendables, and fresh harvest capability. The life support system performance will be described with characteristics of the associated physical-chemical subsystems and a greenhouse.

77 FR 11418 - Airworthiness Directives; Various Transport Category Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-02-27

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

77 FR 38000 - Airworthiness Directives; Various Transport Category Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2012-06-26

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

14 CFR 420.19 - Launch site location review-general.

Code of Federal Regulations, 2011 CFR

2011-01-01

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

Toward understanding the ecological impact of transportation corridors

Treesearch

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

2011-01-01

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

10 CFR 600.135 - Supplies and other expendable property.

Code of Federal Regulations, 2010 CFR

2010-01-01

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

45 CFR 2543.35 - Supplies and other expendable property.

Code of Federal Regulations, 2010 CFR

2010-10-01

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

49 CFR 110.70 - Financial administration.

Code of Federal Regulations, 2010 CFR

2010-10-01

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

29 CFR 778.217 - Reimbursement for expenses.

Code of Federal Regulations, 2011 CFR

2011-07-01

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

48 CFR 1852.228-78 - Cross-waiver of liability for NASA expendable launch vehicle launches.

Code of Federal Regulations, 2012 CFR

2012-10-01

... Damage Caused by Space Objects, entered into force on 1 September 1972, in which the person, entity, or... Regulations System NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLAUSES AND FORMS SOLICITATION PROVISIONS AND... parties related entities to encourage participation in space exploration, use, and investment. The purpose...

Visa Cards Save Thousands.

ERIC Educational Resources Information Center

Schafer, Eldon G.

A thorough review of Lane Community College's purchase order system revealed that 62% of all purchase orders processed in 1981-82 were for amounts under $100; that these orders made up only 3.5% of the dollars expended in acquiring materials and services for college operations; and that each purchase order cost the college $75 in supplies and…

48 CFR 1819.7209 - Credit agreements.

Code of Federal Regulations, 2013 CFR

2013-10-01

... 48 Federal Acquisition Regulations System 6 2013-10-01 2013-10-01 false Credit agreements. 1819... agreements. (a) The credit permits the mentor to include the cost it expends on a mentor-protégé agreement as... Plan. The following provisions apply to all credit mentor-protégé agreements: (1) Developmental...

Progressive and cumulative fabric effects of multiple hydroentangling impacts at different water pressures on greige cotton substrate

USDA-ARS?s Scientific Manuscript database

A practical study was conducted to determine the effects of the hydroentangling jet strip’s orifice size and the hydroentangling water pressure on the energy expended and the properties of the resulting nonwoven fabrics produced on a commercial-grade hydro-entanglement (HE) system, using greige cott...

76 FR 33275 - Agency Information Collection Activities; Submission to OMB for Review and Approval; Comment...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-06-08

... storage, conveyor transfer points, bagging and bulk loading and unloading systems. These standards rely on... part shall maintain a file of these measurements, and retain the file for at least two years following... total time, effort, or financial resources expended by persons to generate, maintain, retain, or...

Testing Evaluation of the Electrochemical Organic Content Analyzer

NASA Technical Reports Server (NTRS)

Davenport, R. J.

1979-01-01

The breadboard electrochemical organic content analyzer was evalauted for aerospace applications. An awareness of the disadvantages of expendables in some systems resulted in an effort to investigate ways of reducing the consumption of the analyzer's electrolyte from the rate of 5.17 kg/30 days. It was found that the electrochemical organic content analyzer can result in an organic monitor in the water quality monitor having a range of 0.1 to 100 mg/1 total organic carbon for a large number of common organic solutes. In a flight version it is anticipated the analyzer would occupy .0002 cu m, weigh 1.4 kg, and require 10 W or less of power. With the optimum method of injecting electrolyte into the sample (saturation of the sample with a salt) it would expend only 0.04 kg of electrolyte during 30 days of continuous operation.

Fourth-generation Mars vehicle concepts

NASA Astrophysics Data System (ADS)

Sherwood, Brent

1994-09-01

Conceptual designs for fourth-generation crew-carrying Mars transfer and excursion vehicles, fully integrated to state-of-the-art standards, are presented. The resulting vehicle concepts are sized for six crew members, and can support all opposition and conjunction opportunities in or after 2014. The modular, reusable transfer ship is launched to Earth orbit on six 185-ton-class boosters and assembled there robotically. Its dual nuclear-thermal rocket engines use liquid hydrogen propollant. The payload consists of a microgravity habitation system and an expendable lift-to-drag = 1.6 lander capable of aeromaneuvering to sites within +/- 20 deg of the equator. This lander can deliver either an expendable, storable-bipropellant crew-carrying ascent vehicle, or 40 tons of cargo, and it is capable of limited surface mobility to support base buildup. Multiple cargo landers sent ahead on robotic transfer vehicles deliver the supplies and equipment required for long-duration surface missions.

Benefits of Government Incentives for Reusable Launch Vehicle Development

NASA Technical Reports Server (NTRS)

Shaw, Eric J.; Hamaker, Joseph W.; Prince, Frank A.

1998-01-01

Many exciting new opportunities in space, both government missions and business ventures, could be realized by a reduction in launch prices. Reusable launch vehicle (RLV) designs have the potential to lower launch costs dramatically from those of today's expendable and partially-expendable vehicles. Unfortunately, governments must budget to support existing launch capability, and so lack the resources necessary to completely fund development of new reusable systems. In addition, the new commercial space markets are too immature and uncertain to motivate the launch industry to undertake a project of this magnitude and risk. Low-cost launch vehicles will not be developed without a mature market to service; however, launch prices must be reduced in order for a commercial launch market to mature. This paper estimates and discusses the various benefits that may be reaped from government incentives for a commercial reusable launch vehicle program.

How much work is expended for respiration?

PubMed

Johnson, A T

1993-01-01

The rate of work expended to move air in the respiratory system has been determined for five different airflow waveshapes, a non-linear respiratory model and five exercise levels. As expected, the rectangular waveshape was the most efficient. Model conditions were then changed one a time: (i) starting lung volume was allowed to vary, (ii) exhalation flow limitation was added, (iii) respiration was considered to be a metabolic burden determining part of the ventilation requirement and (iv) a respirator mask was added. Although there is no direct work advantage to varying initial lung volume, such volume changes appear to be dictated by the asymmetry of lung recoil pressure about the lung relaxation volume; allowing the work of respiration to become a metabolic burden clearly shows why respiratory waveforms change from rest to exercise; and, adding a respirator imposes a severe respiratory burden on the wearer engaging in moderate, heavy and very heavy exercise.

Experimental evaluation of expendable supersonic nozzle concepts

NASA Technical Reports Server (NTRS)

Baker, V.; Kwon, O.; Vittal, B.; Berrier, B.; Re, R.

1990-01-01

Exhaust nozzles for expendable supersonic turbojet engine missile propulsion systems are required to be simple, short and compact, in addition to having good broad-range thrust-minus-drag performance. A series of convergent-divergent nozzle scale model configurations were designed and wind tunnel tested for a wide range of free stream Mach numbers and nozzle pressure ratios. The models included fixed geometry and simple variable exit area concepts. The experimental and analytical results show that the fixed geometry configurations tested have inferior off-design thrust-minus-drag performance in the transonic Mach range. A simple variable exit area configuration called the Axi-Quad nozzle, combining features of both axisymmetric and two-dimensional convergent-divergent nozzles, performed well over a broad range of operating conditions. Analytical predictions of the flow pattern as well as overall performance of the nozzles, using a fully viscous, compressible CFD code, compared very well with the test data.

Space Station fluid management logistics

NASA Technical Reports Server (NTRS)

Dominick, Sam M.

1990-01-01

Viewgraphs and discussion on space station fluid management logistics are presented. Topics covered include: fluid management logistics - issues for Space Station Freedom evolution; current fluid logistics approach; evolution of Space Station Freedom fluid resupply; launch vehicle evolution; ELV logistics system approach; logistics carrier configuration; expendable fluid/propellant carrier description; fluid carrier design concept; logistics carrier orbital operations; carrier operations at space station; summary/status of orbital fluid transfer techniques; Soviet progress tanker system; and Soviet propellant resupply system observations.

Shuttle user analysis (study 2.2). Volume 3: Business risk and value of operations in space (BRAVO). Part 5: Analysis of GSFC Earth Observation Satellite (EOS) system mission model using BRAVO techniques

NASA Technical Reports Server (NTRS)

1975-01-01

Cost comparisons were made between three modes of operation (expend, ground refurbish, and space resupply) for the Earth Observation System (EOS-B) to furnish data to NASA on alternative ways to use the shuttle/EOS. Results of the analysis are presented in tabular form.

Development of a solar-powered residential air conditioner

NASA Technical Reports Server (NTRS)

1975-01-01

The initial objective of the program was the optimization (in terms of cost and performance) of a Rankine cycle mechanical refrigeration system which utilizes thermal energy from a flat solar collector for air conditioning residential buildings. However, feasibility investigations of the adsorption process revealed that a dessicant-type air conditioner offers many significant advantages. As a result, limited efforts were expended toward the optimization of such a system.

Robotic Waterblasting

NASA Technical Reports Server (NTRS)

2004-01-01

The Waterblast Research Cell supports development of automated systems that remove thermal protection materials and coatings from space flight hardware. These systems remove expended coatings without harsh chemicals or damaging underlying material. Potential applications of this technology include the removal of coatings from industrial machinery, aircraft, and other large structures. Use of the robot improves worker safety by reducing the exposure of persornel to high-pressure water. This technology is a proactive alternative to hazardous chemical strippers.

Water-Energy Correlations: Analysis of Water Technologies, Processes and Systems in Rural and Urban India

NASA Astrophysics Data System (ADS)

Murumkar, A. R.; Gupta, S.; Kaurwar, A.; Satankar, R. K.; Mounish, N. K.; Pitta, D. S.; Virat, J.; Kumar, G.; Hatte, S.; Tripathi, R. S.; Shedekar, V.; George, K. J.; Plappally, A. K.

2015-12-01

In India, the present value of water, both potable and not potable, bears no relation to the energy of water production. However, electrical energy spent on ground water extraction alone is equivalent to the nation's hydroelectric capacity of 40.1 GWh. Likewise, desalinating 1m3 water of the Bay of Bengal would save three times the energy for potable ground water extraction along the coast of the Bay. It is estimated that every second woman in rural India expends 0.98 kWhe/m3/d for bringing water for household needs. Yet, the water-energy nexus remains to be a topic which is gravely ignored. This is largely caused by factors such as lack of awareness, defective public policies, and intrusive cultural practices. Furthermore, there are instances of unceasing dereliction towards water management and maintenance of the sparsely distributed water and waste water treatment plants across the country. This pollutes the local water across India apart from other geogenic impurities. Additionally, product aesthetics and deceptive advertisements take advantage of the abulia generated by users' ignorance of technical specifications of water technologies and processes in mismanagement of water use. Accordingly, urban residents are tempted to expend on energy intensive water technologies at end use. This worsens the water-energy equation at urban households. Cooking procedures play a significant role in determining the energy expended on water at households. The paper also evaluates total energy expense involved in cultivating some major Kharif and Rabi crops. Manual and traditional agricultural practices are more prominent than mechanized and novel agricultural techniques. The specific energy consumption estimate for different water technologies will help optimize energy expended on water in its life cycles. The implication of the present study of water-energy correlation will help plan and extend water management infrastructure at different locations across India.

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

NASA Astrophysics Data System (ADS)

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

2016-10-01

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

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

NASA Technical Reports Server (NTRS)

Palo, Thomas E.

2007-01-01

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

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

Federal Register 2010, 2011, 2012, 2013, 2014

2011-11-22

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

Supporting Knowledge Transfer in IS Deployment Projects

NASA Astrophysics Data System (ADS)

Schönström, Mikael

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

Recent Ground Hold and Rapid Depressurization Testing of Multilayer Systems

NASA Technical Reports Server (NTRS)

Johnson, Wesley L.

2014-01-01

In the development of flight insulation systems for large cryogenic orbital storage (spray on foam and multilayer insulation), testing need include all environments that are experienced during flight. While large efforts have been expended on studying, bounding, and modeling the orbital performance of the insulation systems, little effort has been expended on the ground hold and ascent phases of a mission. Historical cryogenic in-space systems that have flown have been able to ignore these phases of flight due to the insulation system being within a vacuum jacket. In the development phase of the Nuclear Mars Vehicle and the Shuttle Nuclear Vehicle, several insulation systems were evaluated for the full mission cycle. Since that time there had been minimal work on these phases of flight until the Constellation program began investigating cryogenic service modules and long duration upper stages. With the inception of the Cryogenic Propellant Storage and Transfer Technology Demonstration Mission, a specific need was seen for the data and as such, several tests were added to the Cryogenic Boil-off Reduction System liquid hydrogen test matrix to provide more data on a insulation system. Testing was attempted with both gaseous nitrogen (GN2) and gaseous helium (GHe) backfills. The initial tests with nitrogen backfill were not successfully completed due to nitrogen liquefaction and solidification preventing the rapid pumpdown of the vacuum chamber. Subsequent helium backfill tests were successful and showed minimal degradation. The results are compared to the historical data.

High Gain Antenna System Deployment Mechanism Integration, Characterization, and Lessons Learned

NASA Technical Reports Server (NTRS)

Parong, Fil; Russell, Blair; Garcen, Walter; Rose, Chris; Johnson, Chris; Huber, Craig

2014-01-01

The integration and deployment testing of the High Gain Antenna System (HGAS) for the Global Precipitation Measurement mission is summarized. The HGAS deployment mechanism is described. The gravity negation system configuration and its influence on vertical, ground-based deployment tests are presented with test data and model predictions. A focus is made on the late discovery and resolution of a potentially mission-degrading deployment interference condition. The interaction of the flight deployment mechanism, gravity-negation mechanism, and use of dynamic modeling is described and lessons learned presented

High Gain Antenna System Deployment Mechanism Integration, Characterization, and Lessons Learned

NASA Technical Reports Server (NTRS)

Parong, Fil; Russell, Blair; Garcen, Walter; Rose, Chris; Johnson, Chris; Huber, Craig

2014-01-01

The integration and deployment testing of the High Gain Antenna System for the Global Precipitation Measurement mission is summarized. The HGAS deployment mechanism is described. The gravity negation system configuration and its influence on vertical, ground-based, deployment tests are presented with test data and model predictions. A focus is made on the late discovery and resolution of a potentially mission degrading deployment interference condition. The interaction of the flight deployment mechanism, gravity negation mechanism, and use of dynamic modeling is described and lessons learned presented.

Low-thrust chemical orbit to orbit propulsion system propellant management study

NASA Technical Reports Server (NTRS)

Dergance, R. H.

1980-01-01

Propellant requirements, tankage configurations, preferred propellant management techniques, propulsion systems weights, and technology deficiencies for low thrust expendable propulsion systems are examined. A computer program was utilized which provided a complete propellant inventory (including boil-off for cryogenic cases), pressurant and propellant tank dimensions for a given ullage, pressurant requirements, insulation requirements, and miscellaneous masses. The output also includes the masses of all tanks; the mass of the insulation, engines and other components; total wet system and burnout mass; system mass fraction; total impulse and burn time.

Space Station Environmental Control/Life Support System engineering

NASA Technical Reports Server (NTRS)

Miller, C. W.; Heppner, D. B.

1985-01-01

The present paper is concerned with a systems engineering study which has provided an understanding of the overall Space Station ECLSS (Environmental Control and Life Support System). ECLSS/functional partitioning is considered along with function criticality, technology alternatives, a technology description, single thread systems, Space Station architectures, ECLSS distribution, mechanical schematics per space station, and Space Station ECLSS characteristics. Attention is given to trade studies and system synergism. The Space Station functional description had been defined by NASA. The ECLSS will utilize technologies which embody regenerative concepts to minimize the use of expendables.

An innovative deployable solar panel system for Cubesats

NASA Astrophysics Data System (ADS)

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

2014-02-01

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

Air Force Reusable Booster System: A Quick-look, Design Focused Modeling and Cost Analysis Study

NASA Technical Reports Server (NTRS)

Zapata, Edgar

2011-01-01

This paper presents a method and an initial analysis of the costs of a reusable booster system (RBS) as envisioned by the US Department of Defense (DoD) and numerous initiatives that form the concept of Operationally Responsive Space (ORS). This paper leverages the knowledge gained from decades of experience with the semi-reusable NASA Space Shuttle to understand how the costs of a military next generation semi-reusable space transport might behave in the real world - and how it might be made as affordable as desired. The NASA Space Shuttle had a semi-expendable booster, that being the reusable Solid Rocket MotorslBoosters (SRMlSRB) and the expendable cryogenic External Tank (ET), with a reusable cargo and crew capable orbiter. This paper will explore DoD concepts that invert this architectural arrangement, using a reusable booster plane that flies back to base soon after launch, with the in-space elements of the launch system being the expendable portions. Cost estimating in the earliest stages of any potential, large scale program has limited usefulness. As a result, the emphasis here is on developing an approach, a structure, and the basic concepts that could continue to be matured as the program gains knowledge. Where cost estimates are provided, these results by necessity carry many caveats and assumptions, and this analysis becomes more about ways in which drivers of costs for diverse scenarios can be better understood. The paper is informed throughout with a design-for-cost philosophy whereby the design and technology features of the proposed RBS (who and what, the "architecture") are taken as linked at the hip to a desire to perform a certain mission (where and when), and together these inform the cost, responsiveness, performance and sustainability (how) of the system. Concepts for developing, acquiring, producing or operating the system will be shown for their inextricable relationship to the "architecture" of the system, and how these too relate to costs. Design and technology features bear special relevance to early program research and development directions. Given the uncertainties involved in both their actual performance promise and their relation to costs of operational systems, this later relationship is also given special attention.

Design considerations for implementation of large scale automatic meter reading systems

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

Mak, S.; Radford, D.

1995-01-01

This paper discusses the requirements imposed on the design of an AMR system expected to serve a large (> 1 million) customer base spread over a large geographical area. Issues such as system throughput response time, and multi-application expendability are addressed, all of which are intimately dependent on the underlying communication system infrastructure, the local geography, the customer base, and the regulatory environment. A methodology for analysis, assessment, and design of large systems is presented. For illustration, two communication systems -- a low power RF/PLC system and a power frequency carrier system -- are analyzed and discussed.

Flight qualification of mortar-actuated parachute deployment systems

NASA Technical Reports Server (NTRS)

Pleasants, J. E.

1975-01-01

A brief discussion outlines background of mortar use in parachute deployment systems. A description of the system operation is presented. Effects of the environment on performance are discussed as well as the instrumentation needed to assess this performance. Power unit qualification and lot qualification for shear pins and cartridges is delineated. Functional mortar system tests are described. Finally, bridle deployment and parachute deployment are discussed.

Benefit from NASA

NASA Image and Video Library

2004-04-15

The Waterblast Research Cell supports development of automated systems that remove thermal protection materials and coatings from space flight hardware. These systems remove expended coatings without harsh chemicals or damaging underlying material. Potential applications of this technology include the removal of coatings from industrial machinery, aircraft, and other large structures. Use of the robot improves worker safety by reducing the exposure of persornel to high-pressure water. This technology is a proactive alternative to hazardous chemical strippers.

Representative shuttle evaporative heat sink

NASA Technical Reports Server (NTRS)

Hixon, C. W.

1978-01-01

The design, fabrication, and testing of a representative shuttle evaporative heat sink (RSEHS) system which vaporizes an expendable fluid to provide cooling for the shuttle heat transport fluid loop is reported. The optimized RSEHS minimum weight design meets or exceeds the shuttle flash evaporator system requirements. A cold trap which cryo-pumps flash evaporator exhaust water from the CSD vacuum chamber test facility to prevent water contamination of the chamber pumping equipment is also described.

Rover deployment system for lunar landing mission

NASA Astrophysics Data System (ADS)

Sutoh, Masataku; Hoshino, Takeshi; Wakabayashi, Sachiko

2017-09-01

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

Aerospace vehicle water-waste management

NASA Technical Reports Server (NTRS)

Pecoraro, J. N.

1973-01-01

The collection and disposal of human wastes, such as urine and feces, in a spacecraft environment are performed in an aesthetic and reliable manner to prevent degradation of crew performance. The waste management system controls, transfers, and processes materials such as feces, emesis, food residues, used expendables, and other wastes. The requirements, collection, transport, and waste processing are described.

26 CFR 1.1081-4 - Exchanges of property for property by corporations.

Code of Federal Regulations, 2011 CFR

2011-04-01

... within the provisions of paragraph (b) of this section if it were not for the fact that the property... the integration or simplification of the holding company system of which the transferor corporation is...) of this section if it were not for the fact that the amount expended or invested is less than the...

26 CFR 1.1081-4 - Exchanges of property for property by corporations.

Code of Federal Regulations, 2013 CFR

2013-04-01

... within the provisions of paragraph (b) of this section if it were not for the fact that the property... the integration or simplification of the holding company system of which the transferor corporation is...) of this section if it were not for the fact that the amount expended or invested is less than the...

26 CFR 1.1081-4 - Exchanges of property for property by corporations.

Code of Federal Regulations, 2014 CFR

2014-04-01

... within the provisions of paragraph (b) of this section if it were not for the fact that the property... the integration or simplification of the holding company system of which the transferor corporation is...) of this section if it were not for the fact that the amount expended or invested is less than the...

78 FR 12068 - Agency Information Collection Activities: Submission to OMB for Review and Approval; Public...

Federal Register 2010, 2011, 2012, 2013, 2014

2013-02-21

... mandate of section 340B(a)(5)(C) to develop audit guidelines and because of the potential for disputes... guidelines for audit of covered entities. Burden Statement: Burden in this context means the time expended by... time needed to review instructions, to develop, acquire, install and utilize technology and systems for...

25 CFR 900.43 - What are the general financial management system standards that apply to a tribal organization...

Code of Federal Regulations, 2010 CFR

2010-04-01

... standards that apply to a tribal organization carrying out a self-determination contract? 900.43 Section 900... organization carrying out a self-determination contract? A tribal organization shall expend and account for..., DEPARTMENT OF HEALTH AND HUMAN SERVICES CONTRACTS UNDER THE INDIAN SELF-DETERMINATION AND EDUCATION...

25 CFR 900.43 - What are the general financial management system standards that apply to a tribal organization...

Code of Federal Regulations, 2012 CFR

2012-04-01

... standards that apply to a tribal organization carrying out a self-determination contract? 900.43 Section 900... organization carrying out a self-determination contract? A tribal organization shall expend and account for..., DEPARTMENT OF HEALTH AND HUMAN SERVICES CONTRACTS UNDER THE INDIAN SELF-DETERMINATION AND EDUCATION...

25 CFR 900.43 - What are the general financial management system standards that apply to a tribal organization...

Code of Federal Regulations, 2014 CFR

2014-04-01

... standards that apply to a tribal organization carrying out a self-determination contract? 900.43 Section 900... organization carrying out a self-determination contract? A tribal organization shall expend and account for..., DEPARTMENT OF HEALTH AND HUMAN SERVICES CONTRACTS UNDER THE INDIAN SELF-DETERMINATION AND EDUCATION...

25 CFR 900.43 - What are the general financial management system standards that apply to a tribal organization...

Code of Federal Regulations, 2011 CFR

2011-04-01

... standards that apply to a tribal organization carrying out a self-determination contract? 900.43 Section 900... organization carrying out a self-determination contract? A tribal organization shall expend and account for..., DEPARTMENT OF HEALTH AND HUMAN SERVICES CONTRACTS UNDER THE INDIAN SELF-DETERMINATION AND EDUCATION...

25 CFR 900.43 - What are the general financial management system standards that apply to a tribal organization...

Code of Federal Regulations, 2013 CFR

2013-04-01

... standards that apply to a tribal organization carrying out a self-determination contract? 900.43 Section 900... organization carrying out a self-determination contract? A tribal organization shall expend and account for..., DEPARTMENT OF HEALTH AND HUMAN SERVICES CONTRACTS UNDER THE INDIAN SELF-DETERMINATION AND EDUCATION...

School-Based Budgets: Getting, Spending, and Accounting.

ERIC Educational Resources Information Center

Herman, Jerry L.; Herman, Janice L.

With the advent of large interest in school-based management came the task of inventing a different type of budgeting system--one that delegated the many tasks of developing a budget, expending the allocated funds, and controlling those expenditures in a way that did not exceed the allocation to the site level. This book explores the various means…

County Library Service to Rural Schools. Bulletin, 1930, No. 20

ERIC Educational Resources Information Center

Lathrop, Edith A.

1930-01-01

An efficient county library contemplates maximum service for money expended. Situated at the county seat or at some other centrally located place within the county, its book stock is carried to every resident of the county through a system branches, stations, and school deposits, and the services of an automobile and the parcel post. A trained…

Engineering Model Propellant Feed System Development for an Iodine Hall Thruster Demonstration Mission

NASA Technical Reports Server (NTRS)

Polzin, Kurt A.

2016-01-01

CUBESATS are relatively new spacecraft platforms that are typically deployed from a launch vehicle as a secondary payload, providing low-cost access to space for a wide range of end-users. These satellites are comprised of building blocks having dimensions of 10x10x10 cu cm and a mass of 1.33 kg (a 1-U size). While providing low-cost access to space, a major operational limitation is the lack of a propulsion system that can fit within a CubeSat and is capable of executing high (Delta)v maneuvers. This makes it difficult to use CubeSats on missions requiring certain types of maneuvers (i.e. formation flying, spacecraft rendezvous). Recently, work has been performed investigating the use of iodine as a propellant for Hall-effect thrusters (HETs) 2 that could subsequently be used to provide a high specific impulse path to CubeSat propulsion. 3, 4 Iodine stores as a dense solid at very low pressures, making it acceptable as a propellant on a secondary payload. It has exceptionally high ?Isp (density times specific impulse), making it an enabling technology for small satellite near-term applications and providing the potential for systems-level advantages over mid-term high power electric propulsion options. Iodine flow can also be thermally regulated, subliming at relatively low temperature (< 100 C) to yield I2 vapor at or below 50 torr. At low power, the measured performance of an iodine-fed HET is very similar to that of a state-of-the-art xenon-fed thruster. Just as importantly, the current-voltage discharge characteristics of low power iodine-fed and xenon-fed thrusters are remarkably similar, potentially reducing development and qualifications costs by making it possible to use an already-qualified xenon-HET PPU in an iodine-fed system. Finally, a cold surface can be installed in a vacuum test chamber on which expended iodine propellant can deposit. In addition, the temperature doesn't have to be extremely cold to maintain a low vapor pressure in the vacuum chamber (it is under 10(exp -6) torr at -75 C), making it possible to 'cryopump' the propellant with lower-cost recirculating refrigerant-based systems as opposed to using liquid nitrogen or low temperature gaseous helium cryopanels. In the present paper, we describe the design and testing of the engineering model propellant feed system for iSAT (see Fig. 1). The feed system is based around an iodine propellant reservoir and two proportional control valves (PFCVs) that meter the iodine flow to the cathode and anode. The flow is split upstream of the PFCVs to both components can be fed from a common reservoir. Testing of the reservoir is reported to demonstrate that the design is capable of delivering the required propellant flow rates to operate the thruster. The tubing and reservoir are fabricated from hastelloy to resist corrosion by the heated gaseous iodine propellant. The reservoir, tubing, and PFCVs are heated to ensure the sublimed propellant will not re-deposit within the feed system. Heating is accomplished through a number of individual zones to control the overall power expended on heating the system and insulation is employed to minimize the amount of power used to heat the system prior to thruster operation.

Seasonal Ice Zone Reconnaissance Surveys Coordination

DTIC Science & Technology

2016-03-30

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

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

Federal Register 2010, 2011, 2012, 2013, 2014

2012-02-17

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

Storytelling as Research/Research as Storytelling

ERIC Educational Resources Information Center

Lewis, Patrick J.

2011-01-01

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

Microchemical Analysis Of Space Operation Debris

NASA Technical Reports Server (NTRS)

Cummings, Virginia J.; Kim, Hae Soo

1995-01-01

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

Qualification of the Tropical Rainfall Measuring Mission Solar Array Deployment System

NASA Technical Reports Server (NTRS)

Lawrence, Jon

1998-01-01

The Tropical Rainfall Measuring Mission (TRMM) solar arrays are placed into orbital configuration by a complex deployment system. Its two wings each comprise twin seven square solar panels located by a twelve foot articulated boom. The four spring-driven hinge lines per wing are rate-limited by viscous dampers. The wings are stowed against the spacecraft kinematically, and released by five pyrotechnically-actuated mechanisms. Since deployment failure would be catastrophic, a total of 17 deployment tests were completed to qualify the system for the worst cast launch environment. This successful testing culminated in the flawless deployment of the solar arrays on orbit, 15 minutes after launch in November 1997. The custom gravity negation system used to perform deployment testing is modular to allow its setup in several locations, including the launch site in Japan. Both platform and height can be varied, to meet the requirements of the test configuration and the test facility. Its air pad floatation system meets tight packaging requirements, allowing installation while stowed against the spacecraft without breaking any flight interfaces, and avoiding interference during motion. This system was designed concurrently with the deployment system, to facilitate its installation, to aid in the integration of the flight system to the spacecraft, while demonstrating deployment capabilities. Critical parameters for successful testing were alignment of deployment axes and tables to gravity, alignment of table seams to minimize discontinuities, and minimizing pressure drops in the air supply system. Orbital performance was similar to that predicted by ground testing.

77 FR 15019 - Groundfish Fisheries of the Exclusive Economic Zone Off Alaska and Pacific Halibut Fisheries...

Federal Register 2010, 2011, 2012, 2013, 2014

2012-03-14

.... The new funding and deployment system would allow NMFS to determine when and where to deploy observers... requirements for vessels and processing plants at 50 CFR 679.50. The new funding and deployment system would... funding and deployment system. The proposed amendments would divide the existing Observer Program into two...

Deployer Performance Results for the TSS-1 Mission

NASA Technical Reports Server (NTRS)

Marshall, Leland S.; Geiger, Ronald V.

1995-01-01

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

Imagining Sisyphus happy: DNA barcoding and the unnamed majority.

PubMed

Blaxter, Mark

2016-09-05

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

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

NASA Technical Reports Server (NTRS)

1987-01-01

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

Loosely Coupled GPS-Aided Inertial Navigation System for Range Safety

NASA Technical Reports Server (NTRS)

Heatwole, Scott; Lanzi, Raymond J.

2010-01-01

The Autonomous Flight Safety System (AFSS) aims to replace the human element of range safety operations, as well as reduce reliance on expensive, downrange assets for launches of expendable launch vehicles (ELVs). The system consists of multiple navigation sensors and flight computers that provide a highly reliable platform. It is designed to ensure that single-event failures in a flight computer or sensor will not bring down the whole system. The flight computer uses a rules-based structure derived from range safety requirements to make decisions whether or not to destroy the rocket.

Deploying advanced public transportation systems in Birmingham

DOT National Transportation Integrated Search

2003-08-01

Advanced Public Transportation Systems (APTS) technologies have been deployed by many urban transit systems in order to improve efficiency, reduce operating costs, and improve service quality. The majority of : these deployments, however, have been i...

Deployable System for Crash-Load Attenuation

NASA Technical Reports Server (NTRS)

Kellas, Sotiris; Jackson, Karen E.

2007-01-01

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

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

NASA Technical Reports Server (NTRS)

1982-01-01

Generic deployable spacecraft configurations and deployable platform systems concepts were identified. Sizing, building block concepts, orbiter packaging, thermal analysis, cost analysis, and mass properties analysis as related to platform systems integration are considered. Technology needs are examined and the major criteria used in concept selection are delineated. Requirements for deployable habitat modules, tunnels, and OTV hangars are considered.

Technical and Economical Feasibility of SSTO and TSTO Launch Vehicles

NASA Astrophysics Data System (ADS)

Lerch, Jens

This paper discusses whether it is more cost effective to launch to low earth orbit in one or two stages, assuming current or near future technologies. First the paper provides an overview of the current state of the launch market and the hurdles to introducing new launch vehicles capable of significantly lowering the cost of access to space and discusses possible routes to solve those problems. It is assumed that reducing the complexity of launchers by reducing the number of stages and engines, and introducing reusability will result in lower launch costs. A number of operational and historic launch vehicle stages capable of near single stage to orbit (SSTO) performance are presented and the necessary steps to modify them into an expendable SSTO launcher and an optimized two stage to orbit (TSTO) launcher are shown, through parametric analysis. Then a ballistic reentry and recovery system is added to show that reusable SSTO and TSTO vehicles are also within the current state of the art. The development and recurring costs of the SSTO and the TSTO systems are estimated and compared. This analysis shows whether it is more economical to develop and operate expendable or reusable SSTO or TSTO systems under different assumption for launch rate and initial investment.

Reusability aspects for space transportation rocket engines: programmatic status and outlook

NASA Astrophysics Data System (ADS)

Preclik, D.; Strunz, R.; Hagemann, G.; Langel, G.

2011-09-01

Rocket propulsion systems belong to the most critical subsystems of a space launch vehicle, being illustrated in this paper by comparing different types of transportation systems. The aspect of reusability is firstly discussed for the space shuttle main engine, the only rocket engine in the world that has demonstrated multiple reuses. Initial projections are contrasted against final reusability achievements summarizing three decades of operating the space shuttle main engine. The discussion is then extended to engines employed on expendable launch vehicles with an operational life requirement typically specifying structural integrities up to 20 cycles (start-ups) and an accumulated burning time of about 6,000 s (Vulcain engine family). Today, this life potential substantially exceeds the duty cycle of an expendable engine. It is actually exploited only during the development and qualification phase of an engine when system reliability is demonstrated on ground test facilities with a reduced number of hardware sets that are subjected to an extended number of test cycles and operation time. The paper will finally evaluate the logic and effort necessary to qualify a reusable engine for a required reliability and put this result in context of possible cost savings realized from reuse operations over a time span of 25 years.

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

NASA Technical Reports Server (NTRS)

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

2016-01-01

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

Human Exploration and Settlement of the Moon Using LUNOX-Augmented NTR Propulsion

NASA Technical Reports Server (NTRS)

Borowski, Stanley K.; Culver, Donald W.; Bulman, Melvin J.

1995-01-01

An innovative trimodal nuclear thermal rocket (NTR) concept is described which combines conventional liquid hydrogen (LH2)-cooled NTR, Brayton cycle power generation and supersonic combustion ramjet (scramjet) technologies. Known as the liquid oxygen (LOX) augmented NTR (LANTR), this concept utilizes the large divergent section of the NTR nozzle as an 'afterburner' into which LOX is injected and supersonically combusted with nuclear preheated hydrogen emerging from the LANTR's choked sonic throat--'scramjet propulsion in reverse.' By varying the oxygen-to-hydrogen mixture ratio (MR), the LANTR can operate over a wide range of thrust and specific impulse (Isp) values while the reactor core power level remains relatively constant. As the MR varies from zero to seven, the thrust-to-weight ratio for a 15 thousand pound force (klbf) NTR increases by approximately 440%--from 3 to 13--while the Isp decreases by only approximately 45%--from 940 to 515 seconds. This thrust augmentation feature of the LANTR means that 'big engine' performance can be obtained using smaller more affordable, easier to test NTR engines. 'Reoxidizing' the bipropellant LANTR system in low lunar orbit (LLO) with high density 'lunar-derived' LOX (LUNOX) enables a reusable, reduced size and mass lunar transfer vehicle (LTV) which can be deployed and resupplied using two 66 t-class Shuttle-derived launch vehicles. The reusable LANTR can also transport 200 to 300% more payload on each piloted round trip mission than an expendable 'all LH2' NTR system. As initial outposts grow to eventual lunar settlements and LUNOX production capacity increases, the LANTR concept can also enable a rapid 'commuter' shuttle capable of 36 to 24 hour 'one way' trips to the Moon and back with reasonable size vehicles and initial mass in low Earth orbit (IMLEO) requirements.

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

NASA Technical Reports Server (NTRS)

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

2000-01-01

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

Human exploration and settlement of the Moon using LUNOX-augmented NTR propulsion

NASA Astrophysics Data System (ADS)

Borowski, Stanley K.; Culver, Donald W.; Bulman, Melvin J.

1995-10-01

An innovative trimodal nuclear thermal rocket (NTR) concept is described which combines conventional liquid hydrogen (LH2)-cooled NTR, Brayton cycle power generation and supersonic combustion ramjet (scramjet) technologies. Known as the liquid oxygen (LOX) augmented NTR (LANTR), this concept utilizes the large divergent section of the NTR nozzle as an 'afterburner' into which LOX is injected and supersonically combusted with nuclear preheated hydrogen emerging from the LANTR's choked sonic throat--'scramjet propulsion in reverse.' By varying the oxygen-to-hydrogen mixture ratio (MR), the LANTR can operate over a wide range of thrust and specific impulse (Isp) values while the reactor core power level remains relatively constant. As the MR varies from zero to seven, the thrust-to-weight ratio for a 15 thousand pound force (klbf) NTR increases by approximately 440%--from 3 to 13--while the Isp decreases by only approximately 45%--from 940 to 515 seconds. This thrust augmentation feature of the LANTR means that 'big engine' performance can be obtained using smaller more affordable, easier to test NTR engines. 'Reoxidizing' the bipropellant LANTR system in low lunar orbit (LLO) with high density 'lunar-derived' LOX (LUNOX) enables a reusable, reduced size and mass lunar transfer vehicle (LTV) which can be deployed and resupplied using two 66 t-class Shuttle-derived launch vehicles. The reusable LANTR can also transport 200 to 300% more payload on each piloted round trip mission than an expendable 'all LH2' NTR system. As initial outposts grow to eventual lunar settlements and LUNOX production capacity increases, the LANTR concept can also enable a rapid 'commuter' shuttle capable of 36 to 24 hour 'one way' trips to the Moon and back with reasonable size vehicles and initial mass in low Earth orbit (IMLEO) requirements.

Human exploration and settlement of the moon using lunox-augmented NTR propulsion

NASA Astrophysics Data System (ADS)

Borowski, Stanley K.; Culver, Donald W.; Bulman, Melvin J.

1995-01-01

An innovative trimodal nuclear thermal rocket (NTR) concept is described which combines conventional liquid hydrogen (LH2)-cooled NTR, Brayton cycle power generation and supersonic combustion ramjet (scramjet) technologies. Known as the liquid oxygen (LOS)-augmented NTR (LANTR), this concept utilizes the large divergent section of the NTR nozzle as an ``afterburner'' into which LOX is injected and supersonically combusted with nuclear preheated hydrogen emerging from the LANTR's choked sonic throat—``scramjet propulsion in reverse.'' By varying the oxygen-to-hydrogen mixture ratio (MR), the LANTR can operate over a wide range of thrust and specific impulse (Isp) values while the reactor core power level remains relatively constant. As the MR varies from zero to seven, the thrust-to-weight ratio for a 15 thousand pound force (klbf) NTR increases by ˜440%—from 3 to 13—while the Isp decreases by only ˜45%—from 940 to 515 seconds. This thrust augmentation feature of the LANTR means that ``big engine'' performance can be obtained using smaller, more affordable, easier to test NTR engines. ``Reoxidizing'' the bipropellant LANTR system in low lunar orbit (LLO) with high density ``lunar-derived'' LOX (LUNOX) enables a reusable, reduced size and mass lunar transfer vehicle (LTV) which can be deployed and resupplied using two 66 t-class Shuttle-derived launch vehicles. The reusable LANTR can also transport 200 to 300% more payload on each piloted round trip mission than an expendable ``all LH2'' NTR system. As initial outposts grow to eventual lunar settlements and LUNOX production capacity increases, the LANTR concept can also enable a rapid ``commuter'' shuttle capable of 36 to 24 hour ``one way'' trip to the Moon and back with reasonable size vehicles and initial mass in low Earth orbit (IMLEO) requirements.

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

ERIC Educational Resources Information Center

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

2012-01-01

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

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

ERIC Educational Resources Information Center

Gilbert, Harvey R.; Ferrand, Carole T.

1987-01-01

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

A space release/deployment system actuated by shape memory wires

NASA Astrophysics Data System (ADS)

Fragnito, Marino; Vetrella and, Sergio

2002-11-01

In this paper, the design of an innovative hold down/release and deployment device actuated by shape memory wires, to be used for the first time for the S MA RT microsatellite solar wings is shown. The release and deployment mechanisms are actuated by a Shape Memory wire (Nitinol), which allows a complete symmetrical and synchronous release, in a very short time, of the four wings in pairs. The hold down kinematic mechanism is preloaded to avoid vibration nonlinearities and unwanted deployment at launch. The deployment mechanism is a simple pulley system. The stiffness of the deployed panel-hinge system needs to be dimensioned in order to meet the on-orbit requirement for attitude control. One-way roller clutches are used to keep the panel at the desired angle during the mission. An ad hoc software has been developed to simulate both the release and deployment operations, coupling the SMA wire behavior with the system mechanics.

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

DOT National Transportation Integrated Search

2001-09-05

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

Shuttle/Agena study. Volume 2, part 1: Program requirements, conclusions, recommendations

NASA Technical Reports Server (NTRS)

1972-01-01

An evaluation to determine the compatibility of the Agena with the space transportation system for use as an expendable third stage to the space shuttle was conducted. The Agena was considered for those missions requiring additional propulsion capability beyond that used for low earth orbit. The study defines the interface requirements imposed on both the Agena and the shuttle system and identifies those areas where the Agena must be improved or modified to satisfy mission requirements.

Feasibility Assessment of ITS Deployment Analysis System (IDAS) for ITS Evaluation

DOT National Transportation Integrated Search

2003-12-01

This study investigated the feasibility of utilizing the ITS Deployment Analysis System (IDAS) program version 2.2 as a tool for evaluating Intelligent Transportation Systems (ITS) deployment plans. Firstly, an online survey was conducted among metro...

Rapidly Deployed Modular Telemetry System

NASA Technical Reports Server (NTRS)

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

2013-01-01

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

Deployment Mechanism for Thermal Pointing System

NASA Technical Reports Server (NTRS)

Koski, Kraig

2014-01-01

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

Economics of the solid rocket booster for space shuttle

NASA Technical Reports Server (NTRS)

Rice, W. C.

1979-01-01

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

An Evaluation of Measurements Used to Drive Competitiveness in a Depot Maintenance Environment

DTIC Science & Technology

1992-09-01

it’s hard to define," and explained that he treats the money allocated to a given project as "inventory." As that money is expended toward the project...performiance. A new masurlement system combining meassures from ODHES and TOC with other measures was recomminded. 14. SUBJECT TERMS 1S. NUMBER OF PAGES

Making Data Work Harder: OCLC Shows How Data Mined from Systems like WorldCat Can Add Value for Librarians and Users

ERIC Educational Resources Information Center

Lavoie, Brian; Dempsey, Lorcan; Connaway, Lynn Silipigni

2006-01-01

If librarians want to improve their visibility and value in the increasingly crowded digital information spaces, where users expect good results without expending much time or effort, they must learn to repurpose data to create added value. Since librarians already possess valuable data sources, like circulation statistics, reference transactions,…

Space Station evolution study

NASA Technical Reports Server (NTRS)

Evans, David B.

1993-01-01

This is the Space Station Freedom (SSF) Evolution Study 1993 Final Report, performed under NASA Contract NAS8-38783, Task Order 5.1. This task examined: (1) the feasibility of launching current National Space Transportation System (NSTS) compatible logistics elements on expendable launch vehicles (ELV's) and the associated modifications, and (2) new, non-NSTS logistics elements for launch on ELV's to augment current SSF logistics capability.

A semireusable launch vehicle concept as a reference system for reusability analyses

NASA Astrophysics Data System (ADS)

Kleinau, W.

A two-stage concept called AR-X1, which uses H2O2 propellant and the HM 60 engine is presented. The first stage is reusable, the second expendable. The use of LH2/LOX in the first stage reduces the number of stages for geosynchronous transfer orbit (GTO) missions because of the higher performance. An 8 Mg payload can be injected in GTO (launch mass = 435 Mg). The first stage comprises four parallel stretched second stage tanks with 320 Mg propellants (total) and eight HM 60 engines arranged within the heat shield, plus one central HM 60 thruster for the soft landing maneuver. Engine performance is increased by adapting the expansion ratio to the external pressure. Trajectory calculations show that the first stage flight range is 1 500 km. Braking before touchdown is performed by retro thrust, requiring 2.5 to 3 Mg propellants. First-stage reuse reduces cost per launch by 50% compared with an expendable three stage design.

Expendable launch vehicle propulsion

NASA Technical Reports Server (NTRS)

Fuller, Paul N.

1991-01-01

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

The October 1973 expendable launch vehicle traffic model, revision 2

NASA Technical Reports Server (NTRS)

1974-01-01

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

Seasonal Ice Zone Reconnaissance Surveys Coordination

DTIC Science & Technology

2014-09-30

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

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

ERIC Educational Resources Information Center

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

2010-01-01

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

New life for expendable launchers

NASA Astrophysics Data System (ADS)

Lopez, Ramon L.; Waskul, Greg

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

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

Code of Federal Regulations, 2013 CFR

2013-10-01

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

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

Code of Federal Regulations, 2011 CFR

2011-10-01

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

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

Code of Federal Regulations, 2010 CFR

2010-10-01

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

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

Code of Federal Regulations, 2012 CFR

2012-10-01

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

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

Code of Federal Regulations, 2014 CFR

2014-10-01

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

Performance Efficient Launch Vehicle Recovery and Reuse

NASA Technical Reports Server (NTRS)

Reed, John G.; Ragab, Mohamed M.; Cheatwood, F. McNeil; Hughes, Stephen J.; Dinonno, J.; Bodkin, R.; Lowry, Allen; Brierly, Gregory T.; Kelly, John W.

2016-01-01

For decades, economic reuse of launch vehicles has been an elusive goal. Recent attempts at demonstrating elements of launch vehicle recovery for reuse have invigorated a debate over the merits of different approaches. The parameter most often used to assess the cost of access to space is dollars-per-kilogram to orbit. When comparing reusable vs. expendable launch vehicles, that ratio has been shown to be most sensitive to the performance lost as a result of enabling the reusability. This paper will briefly review the historical background and results of recent attempts to recover launch vehicle assets for reuse. The business case for reuse will be reviewed, with emphasis on the performance expended to recover those assets, and the practicality of the most ambitious reuse concept, namely propulsive return to the launch site. In 2015, United Launch Alliance (ULA) announced its Sensible, Modular, Autonomous Return Technology (SMART) reuse plan for recovery of the booster module for its new Vulcan launch vehicle. That plan employs a non-propulsive approach where atmospheric entry, descent and landing (EDL) technologies are utilized. Elements of such a system have a wide variety of applications, from recovery of launch vehicle elements in suborbital trajectories all the way to human space exploration. This paper will include an update on ULA's booster module recovery approach, which relies on Hypersonic Inflatable Aerodynamic Decelerator (HIAD) and Mid-Air Retrieval (MAR) technologies, including its concept of operations (ConOps). The HIAD design, as well as parafoil staging and MAR concepts, will be discussed. Recent HIAD development activities and near term plans including scalability, next generation materials for the inflatable structure and heat shield, and gas generator inflation systems will be provided. MAR topics will include the ConOps for recovery, helicopter selection and staging, and the state of the art of parachute recovery systems using large parafoils for space asset recovery and high altitude deployment. The next proposed HIAD flight demonstration is called HULA (for HIAD on ULA), and will feature a 6m diameter HIAD. An update for the HULA concept will be provided in this paper. As proposed, this demonstration will fly as a secondary payload on an Atlas mission. The Centaur upper stage provides the reentry pointing, deorbit burn, and entry vehicle spin up. The flight test will culminate with a recovery of the HIAD using MAR. HULA will provide data from a Low Earth Orbit (LEO) return aeroheating environment that enables predictive model correlation and refinement. The resultant reduction in performance uncertainties should lead to design efficiencies that are increasingly significant at larger scales. Relevance to human scale Mars EDL using a HIAD will also be presented, and the applicability of the data generated from both HULA and SMART Vulcan flights, and its value for NASA's human exploration efforts will be discussed. A summary and conclusion will follow.

KSC-05PD-0502B

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. At Astrotech in Titusville, Fla., Boeing technicians hold guide wires attached to the crane lifting the GOES-N satellite. Since its arrival on March 11, the satellite has been undergoing final testing by Boeing Satellite Systems of the imaging system, instrumentation, communications and power systems. Geostationary Operational Environmental Satellites (GOES) are sponsored by NASAs Goddard Space Flight Center and the National Oceanic and Atmospheric Administration. GOES-N is targeted to launch May 4 onboard a Boeing expendable launch vehicle Delta IV (4,2) with a 3-burn second stage operation.

Vibroacoustic Payload Environment Prediction System (VAPEPS): VAPEPS management center remote access guide

NASA Technical Reports Server (NTRS)

Fernandez, J. P.; Mills, D.

1991-01-01

A Vibroacoustic Payload Environment Prediction System (VAPEPS) Management Center was established at the JPL. The center utilizes the VAPEPS software package to manage a data base of Space Shuttle and expendable launch vehicle payload flight and ground test data. Remote terminal access over telephone lines to the computer system, where the program resides, was established to provide the payload community a convenient means of querying the global VAPEPS data base. This guide describes the functions of the VAPEPS Management Center and contains instructions for utilizing the resources of the center.

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

NASA Astrophysics Data System (ADS)

Otsuka, Keisuke; Wang, Yinan; Makihara, Kanjuro

2017-11-01

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

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

NASA Astrophysics Data System (ADS)

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

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

Advanced Deployable Structural Systems for Small Satellites

NASA Technical Reports Server (NTRS)

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

2016-01-01

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

Advanced air revitalization for optimized crew and plant environments

NASA Technical Reports Server (NTRS)

Lee, M. G.; Grigger, David J.; Brown, Mariann F.

1991-01-01

The Hybrid Air Revitalization System (HARS) closed ecosystem concept presented encompasses electrochemical CO2 and O2 separators, in conjunction with a mechanical condenser/separator for maintaining CO2, O2, and humidity levels in crew and plant habitats at optimal conditions. HARS requires no expendables, and allows flexible process control on the bases of electrochemical cell current, temperature, and airflow rate variations. HARS capacity can be easily increased through the incorporation of additional chemical cells. Detailed system flowcharts are provided.

Space Launch System (SLS) Mission Planner's Guide

NASA Technical Reports Server (NTRS)

Smith, David Alan

2017-01-01

The purpose of this Space Launch System (SLS) Mission Planner's Guide (MPG) is to provide future payload developers/users with sufficient insight to support preliminary SLS mission planning. Consequently, this SLS MPG is not intended to be a payload requirements document; rather, it organizes and details SLS interfaces/accommodations in a manner similar to that of current Expendable Launch Vehicle (ELV) user guides to support early feasibility assessment. Like ELV Programs, once approved to fly on SLS, specific payload requirements will be defined in unique documentation.

A Data Definition Language for GLAD (Graphic Language for Databases).

DTIC Science & Technology

1986-06-20

basic premises. These principles state that a DBMS interface must be descriptive, powerful, easy-to use and easy to learn . This thesis proposes a data...basic premises. These principles state that a DBMS interface must be descriptive, powerful, easy to use and easy to learn . This thesis proposes a data...criteria will be the most successful. 9 If a system is hard to learn , of those capable of mastering the system few may be willing to expend the time and

Development of deployable structures for large space platforms. Volume 2: Design development

NASA Technical Reports Server (NTRS)

Greenberg, H. S.

1983-01-01

Design evolution, test article design, test article mass properties, and structural analysis of deployable platform systems are discussed. Orbit transfer vehicle (OTV) hangar development, OTV hangar concept selection, and manned module development are discussed. Deployable platform systems requirements, material data base, technology development needs, concept selection and deployable volume enclosures are also discussed.

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

NASA Technical Reports Server (NTRS)

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

2015-01-01

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

Successful approaches to deploying a Metropolitan Intelligent Transportation System.

DOT National Transportation Integrated Search

1999-03-01

To identify and evaluate the institutional structures and working relationships associated with the deployment and integration of Intelligent Transportation Systems (ITS) products and services at the Model Deployment Initiatives (MDIs), the Volpe Cen...

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

NASA Astrophysics Data System (ADS)

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

2002-01-01

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

Methodology for Variable Fidelity Multistage Optimization under Uncertainty

DTIC Science & Technology

2011-03-31

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

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

NASA Technical Reports Server (NTRS)

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

2007-01-01

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

Deployment/retraction mechanism for solar maximum mission high gain antenna system

NASA Technical Reports Server (NTRS)

Bennett, N.; Preiswerk, P.

1979-01-01

A mechanism called a deployment/retraction assembly (DRA) which provides not only a stable, but a deployable platform for the high gain antenna system (HGAS) aboard the Solar Maximum Mission (SMM) spacecraft is described. The DRA also has the capability to retract the system upon command.

Satellite Power Systems (SPS) concept definition study. Volume 7: SPS program plan and economic analysis

NASA Technical Reports Server (NTRS)

Hanley, G.

1978-01-01

The economic and programmatic requirements for a recommended SPS solar photovoltaic baseline concept were analyzed. Costs are determined for the DDT&E; initial capital investment (covers initial procurement and emplacement of each SPS plant and equipment); replacement capital investment (capital asset replacement over the SPS operating life); operations and maintenance (expendables, minor maintenance, repair crews); and taxes/insurance.

43 CFR 2881.5 - What acronyms and terms are used in the regulations in this part?

Code of Federal Regulations, 2012 CFR

2012-10-01

... of 1920, as amended (30 U.S.C. 185). TAPS means the Trans-Alaska Oil Pipeline System. TUP means a... Federal government expends or uses in processing a right-of-way application or in monitoring the... authorizations issued under FLPMA (43 U.S.C. 1761 et seq.). Monitoring means those actions, subject to § 2886.11...

43 CFR 2881.5 - What acronyms and terms are used in the regulations in this part?

Code of Federal Regulations, 2014 CFR

2014-10-01

... of 1920, as amended (30 U.S.C. 185). TAPS means the Trans-Alaska Oil Pipeline System. TUP means a... Federal government expends or uses in processing a right-of-way application or in monitoring the... authorizations issued under FLPMA (43 U.S.C. 1761 et seq.). Monitoring means those actions, subject to § 2886.11...

43 CFR 2881.5 - What acronyms and terms are used in the regulations in this part?

Code of Federal Regulations, 2013 CFR

2013-10-01

... of 1920, as amended (30 U.S.C. 185). TAPS means the Trans-Alaska Oil Pipeline System. TUP means a... Federal government expends or uses in processing a right-of-way application or in monitoring the... authorizations issued under FLPMA (43 U.S.C. 1761 et seq.). Monitoring means those actions, subject to § 2886.11...

43 CFR 2881.5 - What acronyms and terms are used in the regulations in this part?

Code of Federal Regulations, 2011 CFR

2011-10-01

... of 1920, as amended (30 U.S.C. 185). TAPS means the Trans-Alaska Oil Pipeline System. TUP means a... Federal government expends or uses in processing a right-of-way application or in monitoring the... authorizations issued under FLPMA (43 U.S.C. 1761 et seq.). Monitoring means those actions, subject to § 2886.11...

From Insurgency to Stability. Volume 1: Key Capabilities and Practices

DTIC Science & Technology

2011-01-01

newly arrived personnel to understand the status of ongoing projects and whether individual contractors are performing to the contract...identifying where project funds are expended wastefully and where performance is substandard). That said, while an improved system to monitor...been disappoint- ing. Experiences there have shown that “capacity - building ” in the jus- tice sector does not necessarily produce better performance

Analysis of Lean Six Sigma in the Army Contracting Process

DTIC Science & Technology

2011-12-01

Management UAS Unmanned Aircraft Systems UCC Uniform Commercial Code USA/CMO Under Secretary of the Army/Chief Management Officer WMA Warfighter...to when online banking was first introduced. Marketing campaigns were launched across the region, countless hours were expended, and billions of...would not happen without its fair share of challenges. In 2005, GAO added Business Transformation to its list of High Risk topics (Successful

Cost of Quality Evaluation Methodologies Handbook

DTIC Science & Technology

1988-07-28

policy. 2. Use multiple vendors for major procurements. 3. Establish a formal vendor qualification process. 4. Conduct joint quality planning; agree...and from which extrapolations and inter- polations may be extracted for estimating purposes. COST OF QUALITY - The costs of all efforts expended to...PRODUCIBILITY - The relative ease of producing an item or system which is governed by the characteristics and features of a design that enable

Prostate cancer, benign prostatic hyperplasia and physical activity in Shanghai, China.

PubMed

Lacey, J V; Deng, J; Dosemeci, M; Gao, Y T; Mostofi, F K; Sesterhenn, I A; Xie, T; Hsing, A W

2001-04-01

Studies suggest that increased levels of physical activity might decrease the risk of prostate cancer. We ascertained lifetime measures of activity in a population-based case-control study of prostate cancer in Shanghai, China to investigate physical activity in a population where the incidence of prostate cancer is low but rising. In all, 238 men with prostate cancer, diagnosed 1993-1995, were identified through a rapid reporting system. A second group of 206 men with benign prostatic hyperplasia (BPH) was matched to prostate cancer cases, and 471 age-matched and population-based controls were identified from urban Shanghai. Through personal interviews, we ascertained all daily, occupational, and recreational activities at ages 20-29, ages 40-49, and in 1988 to generate hours spent sleeping, sitting, in moderate activity, and in vigorous activity. Time spent per week in different activities was converted to metabolic equivalents (MET-h) and energy expended. Time spent in, MET-h of, and energy expended in physical activities were not consistently related to either prostate cancer or BPH when compared to controls. Few men reported regular vigorous activity. Occupational activity, based on an energy expenditure index using job titles, was suggestively associated with a decreased risk of BPH, but not associated with prostate cancer. Associations did not vary according to age or stage of prostate cancer at diagnosis. Our results, based on regular physical activity, occupational activity, hours in activities, MET-h, and energy expended, did not support a protective role of physical activity in prostate cancer or BPH for men in a low-risk population.

Mixed Methods Approach to Assessing an Informal Buddy Support System for Canadian Forces Reservists

DTIC Science & Technology

2011-04-01

implemented, perceptions regarding the effectiveness of the system, changes recommended as well as benefits and drawbacks of the system. In order to...families, and provide a better understanding of the system in general, including variations in how it is implemented, perceptions regarding the...Participant perceptions of the system Pre deployment experiences During deployment Post deployment experiences Recommendations made by

Verification and Validation Testing of the Parachute Decelerator System Prior to the First Supersonic Flight Dynamics Test for the Low Density Supersonic Decelerator Program

NASA Technical Reports Server (NTRS)

Gallon, John C.; Witkowski, Allen

2015-01-01

The Parachute Decelerator System (PDS) is comprised of all components associated with the supersonic parachute and its associated deployment. During the Supersonic Flight Dynamics Test (SFDT), for the Low Density Supersonic Decelerators Program, the PDS was required to deploy the supersonic parachute in a defined fashion. The PDS hardware includes three major subsystems that must function together. The first subsystem is the Parachute Deployment Device (PDD), which acts as a modified pilot deployment system. It is comprised of a pyrotechnic mortar, a Kevlar ballute, a lanyard actuated pyrotechnic inflation aid, and rigging with its associated thermal protection material (TPS). The second subsystem is the supersonic parachute deployment hardware. This includes all of the parachute specific rigging that includes the parachute stowage can and the rigging including TPS and bridle stiffeners for bridle management during deployment. The third subsystem is the Supersonic Parachute itself, which includes the main parachute and deployment bags. This paper summarizes the verification and validation of the deployment process, from the initialization of the PDS system through parachute bag strip that was done prior to the first SFDT.

Relatchable launch restraint mechanism for deployable booms

NASA Technical Reports Server (NTRS)

Warden, Robert M.

1990-01-01

A new Relatchable Launch Mechanism was developed which enables a deployable system to be restrained and released repeatedly rather than the normal one shot release systems of the past. The deployable systems are of the self extending type which rely on a lanyard attached to a drive motor to control the deployment and retraction. The Relatch Mechanism uses the existing drive motor to also actuate the latch. The design and kinematics of the Relatch Mechanism as used on two flight programs are described.

In-Situ Resource Utilization for Space Exploration: Resource Processing, Mission-Enabling Technologies, and Lessons for Sustainability on Earth and Beyond

NASA Technical Reports Server (NTRS)

Hepp, A. F.; Palaszewski, B. A.; Landis, G. A.; Jaworske, D. A.; Colozza, A. J.; Kulis, M. J.; Heller, R. S.

2015-01-01

As humanity begins to reach out into the solar system, it has become apparent that supporting a human or robotic presence in transit andor on station requires significant expendable resources including consumables (to support people), fuel, and convenient reliable power. Transporting all necessary expendables is inefficient, inconvenient, costly, and, in the final analysis, a complicating factor for mission planners and a significant source of potential failure modes. Over the past twenty-five years, beginning with the Space Exploration Initiative, researchers at the NASA Glenn Research Center (GRC), academic collaborators, and industrial partners have analyzed, researched, and developed successful solutions for the challenges posed by surviving and even thriving in the resource limited environment(s) presented by near-Earth space and non-terrestrial surface operations. In this retrospective paper, we highlight the efforts of the co-authors in resource simulation and utilization, materials processing and consumable(s) production, power systems and analysis, fuel storage and handling, propulsion systems, and mission operations. As we move forward in our quest to explore space using a resource-optimized approach, it is worthwhile to consider lessons learned relative to efficient utilization of the (comparatively) abundant natural resources and improving the sustainability (and environment) for life on Earth. We reconsider Lunar (and briefly Martian) resource utilization for potential colonization, and discuss next steps moving away from Earth.

In-Situ Resource Utilization for Space Exploration: Resource Processing, Mission-Enabling Technologies, and Lessons for Sustainability on Earth and Beyond

NASA Technical Reports Server (NTRS)

Hepp, A. F.; Palaszewski, B. A.; Landis, G. A.; Jaworske, D. A.; Colozza, A. J.; Kulis, M. J.; Heller, Richard S.

2014-01-01

As humanity begins to reach out into the solar system, it has become apparent that supporting a human or robotic presence in transit and/or on station requires significant expendable resources including consumables (to support people), fuel, and convenient reliable power. Transporting all necessary expendables is inefficient, inconvenient, costly, and, in the final analysis, a complicating factor for mission planners and a significant source of potential failure modes. Over the past twenty-five years, beginning with the Space Exploration Initiative, researchers at the NASA Glenn Research Center (GRC), academic collaborators, and industrial partners have analyzed, researched, and developed successful solutions for the challenges posed by surviving and even thriving in the resource limited environment(s) presented by near-Earth space and non-terrestrial surface operations. In this retrospective paper, we highlight the efforts of the co-authors in resource simulation and utilization, materials processing and consumable(s) production, power systems and analysis, fuel storage and handling, propulsion systems, and mission operations. As we move forward in our quest to explore space using a resource-optimized approach, it is worthwhile to consider lessons learned relative to efficient utilization of the (comparatively) abundant natural resources and improving the sustainability (and environment) for life on Earth. We reconsider Lunar (and briefly Martian) resource utilization for potential colonization, and discuss next steps moving away from Earth.

NASA/DOD Control/Structures Interaction Technology, 1986

NASA Technical Reports Server (NTRS)

Wright, Robert L. (Compiler)

1986-01-01

Control/structures interactions, deployment dynamics and system performance of large flexible spacecraft are discussed. Spacecraft active controls, deployable truss structures, deployable antennas, solar power systems for space stations, pointing control systems for space station gimballed payloads, computer-aided design for large space structures, and passive damping for flexible structures are among the topics covered.

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

Code of Federal Regulations, 2014 CFR

2014-10-01

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

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

Code of Federal Regulations, 2010 CFR

2010-10-01

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

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

Code of Federal Regulations, 2011 CFR

2011-10-01

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

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

Code of Federal Regulations, 2013 CFR

2013-10-01

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

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

Code of Federal Regulations, 2012 CFR

2012-10-01

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

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

PubMed Central

2017-01-01

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

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

PubMed Central

Staiano, Amanda E.; Calvert, Sandra L.

2013-01-01

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

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

NASA Technical Reports Server (NTRS)

1984-01-01

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

Regenerable thermal control and carbon dioxide control techniques for use in advanced extravehicular protective systems

NASA Technical Reports Server (NTRS)

Williams, J. L.; Copeland, R. J.; Nebbon, B. W.

1972-01-01

The most promising closed CO2 control concept identified by this study is the solid pellet, Mg(OH2)2 system. Two promising approaches to closed thermal control were identified. The AHS system uses modular fusible heat sinks, with a contingency evaporative mode, to allow maximum EVA mobility. The AHS/refrigerator top-off subsystem requires an umbilical to minimize expendables, but less EVA time is used to operate the system, since there is no requirement to change modules. Both of these subsystems are thought to be practical solutions to the problem of providing closed heat rejection for an EVA system.

Organizational Culture and the Deployment of Agile Methods: The Competing Values Model View

NASA Astrophysics Data System (ADS)

Iivari, Juhani; Iivari, Netta

A number of researchers have identified organizational culture as a factor that potentially affects the deployment of agile systems development methods. Inspired by the study of Iivari and Huisman (2007), which focused on the deployment of traditional systems development methods, the present paper proposes a number of hypotheses about the influence of organizational culture on the deployment of agile methods.

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

NASA Astrophysics Data System (ADS)

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

2014-12-01

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

Lessons Learned in the Livingstone 2 on Earth Observing One Flight Experiment

NASA Technical Reports Server (NTRS)

Hayden, Sandra C.; Sweet, Adam J.; Shulman, Seth

2005-01-01

The Livingstone 2 (L2) model-based diagnosis software is a reusable diagnostic tool for monitoring complex systems. In 2004, L2 was integrated with the JPL Autonomous Sciencecraft Experiment (ASE) and deployed on-board Goddard's Earth Observing One (EO-1) remote sensing satellite, to monitor and diagnose the EO-1 space science instruments and imaging sequence. This paper reports on lessons learned from this flight experiment. The goals for this experiment, including validation of minimum success criteria and of a series of diagnostic scenarios, have all been successfully net. Long-term operations in space are on-going, as a test of the maturity of the system, with L2 performance remaining flawless. L2 has demonstrated the ability to track the state of the system during nominal operations, detect simulated abnormalities in operations and isolate failures to their root cause fault. Specific advances demonstrated include diagnosis of ambiguity groups rather than a single fault candidate; hypothesis revision given new sensor evidence about the state of the system; and the capability to check for faults in a dynamic system without having to wait until the system is quiescent. The major benefits of this advanced health management technology are to increase mission duration and reliability through intelligent fault protection, and robust autonomous operations with reduced dependency on supervisory operations from Earth. The work-load for operators will be reduced by telemetry of processed state-of-health information rather than raw data. The long-term vision is that of making diagnosis available to the onboard planner or executive, allowing autonomy software to re-plan in order to work around known component failures. For a system that is expected to evolve substantially over its lifetime, as for the International Space Station, the model-based approach has definite advantages over rule-based expert systems and limit-checking fault protection systems, as these do not scale well. The model-based approach facilitates reuse of the L2 diagnostic software; only the model of the system to be diagnosed and telemetry monitoring software has to be rebuilt for a new system or expanded for a growing system. The hierarchical L2 model supports modularity and expendability, and as such is suitable solution for integrated system health management as envisioned for systems-of-systems.

A spin-recovery parachute system for light general-aviation airplanes

NASA Technical Reports Server (NTRS)

Bradshaw, C.

1980-01-01

A tail mounted spin recovery parachute system was designed and developed for use on light general aviation airplanes. The system was designed for use on typical airplane configurations, including low wing, high wing, single engine and twin engine designs. A mechanically triggered pyrotechnic slug gun is used to forcibly deploy a pilot parachute which extracts a bag that deploys a ring slot spin recovery parachute. The total system weighs 8.2 kg. System design factors included airplane wake effects on parachute deployment, prevention of premature parachute deployment, positive parachute jettison, compact size, low weight, system reliability, and pilot and ground crew safety. Extensive ground tests were conducted to qualify the system. The recovery parachute was used successfully in flight 17 times.

Local evaluation for the Cumberland gap tunnel regional ITS deployment.

DOT National Transportation Integrated Search

2010-12-01

This report is the local evaluation of an Intelligent Transportation System deployment for the Cumberland Gap Tunnel and U.S. 25E corridor in Tennessee and Kentucky. This report examines the planning for the deployment and the systems and components ...

Cable-catenary large antenna concept

NASA Technical Reports Server (NTRS)

Akle, W.

1985-01-01

Deployable to very large diameters (over 1000 ft), while still remaining compatible with a complete satellite system launch by STS, the cable-catenary antenna comprises: 8 radial deployable boom masts; a deployable hub and feed support center mast; balanced front and back, radial and circumferential catenary cabling for highly accurate (mm) surface control; no interfering cabling in the antenna field; and an RF reflecting mesh supported on the front catenaries. Illustrations show the antenna-satellite system deployed and stowed configurations; the antenna deployment sequence; the design analysis logic; the sizing analysis output, and typical parametric design data.

Space station structures development

NASA Technical Reports Server (NTRS)

Teller, V. B.

1986-01-01

A study of three interrelated tasks focusing on deployable Space Station truss structures is discussed. Task 1, the development of an alternate deployment system for linear truss, resulted in the preliminary design of an in-space reloadable linear motor deployer. Task 2, advanced composites deployable truss development, resulted in the testing and evaluation of composite materials for struts used in a deployable linear truss. Task 3, assembly of structures in space/erectable structures, resulted in the preliminary design of Space Station pressurized module support structures. An independent, redundant support system was developed for the common United States modules.

Assessment of Army Contracting Command’s Contract Management Processes (TACOM and RDECOM)

DTIC Science & Technology

2011-04-01

Management Processes (TACOM and RDECOM)” was prepared for and funded by the Acquisition Program, Graduate School of Business & Public Policy, Naval...system and the Evolved Expendable Launch Vehicle rocket program. Rendon has taught contract management courses for the UCLA Government Contracts...program; he was also a senior faculty member for the Keller Graduate School of Management, where he taught MBA courses in project management and

Impact Sensors for Use with Electronic Fuzes

DTIC Science & Technology

1975-12-01

corroborated the major features of a theoretical analysis. More work is needed to 10R. Wasser , Impact Switch Tests, US Naval Ordnance...might be more fruitful if more effort were expended on electro- mechanical systems. One principle that could be applied to such a l0R. Wasser ...Switches for Artillery Fuzes, Part I: Development, Harry Diamond Laboratories TM-72-18 (July 1972). (10) R. Wasser , Impact Switch TestP, US Naval

Ballastic signature identification systems study

NASA Technical Reports Server (NTRS)

Reich, A.; Hine, T. L.

1976-01-01

The results are described of an attempt to establish a uniform procedure for documenting (recording) expended bullet signatures as effortlessly as possible and to build a comprehensive library of these signatures in a form that will permit the automated comparison of a new suspect bullet with the prestored library. The ultimate objective is to achieve a standardized format that will permit nationwide interaction between police departments, crime laboratories, and other interested law enforcement agencies.

KSC-03pd0023

NASA Image and Video Library

2003-01-05

KENNEDY SPACE CENTER, FLA. -- In the Multi-Purpose Processing Facility, a technician cleans NASA's Solar Radiation and Climate Experiment (SORCE) before its mating to the Pegasus XL Expendable Launch Vehicle. Built by Orbital Sciences Space Systems Group, SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere. The launch of SORCE is scheduled for Jan. 25 at 3:14 p.m. from Cape Canaveral Air Force Station, Fla.

Near Earth Asteroid Scout Solar Sail Engineering Development Unit Test Suite

NASA Technical Reports Server (NTRS)

Lockett, Tiffany Russell; Few, Alexander; Wilson, Richard

2017-01-01

The Near Earth Asteroid (NEA) Scout project is a 6U reconnaissance mission to investigate a near Earth asteroid utilizing an 86m(sub 2) solar sail as the primary propulsion system. This will be the largest solar sail NASA has launched to date. NEA Scout is currently manifested on the maiden voyage of the Space Launch System in 2018. In development of the solar sail subsystem, design challenges were identified and investigated for packaging within a 6U form factor and deployment in cis-lunar space. Analysis was able to capture understanding of thermal, stress, and dynamics of the stowed system as well as mature an integrated sail membrane model for deployed flight dynamics. Full scale system testing on the ground is the optimal way to demonstrate system robustness, repeatability, and overall performance on a compressed flight schedule. To physically test the system, the team developed a flight sized engineering development unit with design features as close to flight as possible. The test suite included ascent vent, random vibration, functional deployments, thermal vacuum, and full sail deployments. All of these tests contributed towards development of the final flight unit. This paper will address several of the design challenges and lessons learned from the NEA Scout solar sail subsystem engineering development unit. Testing on the component level all the way to the integrated subsystem level. From optical properties of the sail material to fold and spooling the single sail, the team has developed a robust deployment system for the solar sail. The team completed several deployments of the sail system in preparation for flight at half scale (4m) and full scale (6.8m): boom only, half scale sail deployment, and full scale sail deployment. This paper will also address expected and received test results from ascent vent, random vibration, and deployment tests.

Summary of the study of disposal of nuclear waste into space

NASA Technical Reports Server (NTRS)

Rom, F. E.

1973-01-01

The space shuttle together with expendable and nonexpendable orbital stages such as the space tug or Centaur can safely dispose of waste material by ejecting it from the solar system. The safety problems associated with all phases of launching and operation (normal, emergency, and accident) of such a system are being examined. It appears that solutions can be found that should make the risks acceptable when compared to the benefits to be obtained from the disposal of the nuclear waste. The techniques proposed to make such a system acceptable need to be carefully verified by further study and experiment.

The StarBooster System: A Cargo Aircraft for Space

NASA Technical Reports Server (NTRS)

Davis, Hubert P.; Dula, Arthur M.; McLaughlin, Don; Frassanito, John; Andrews, Jason (Editor)

1999-01-01

Starcraft Boosters has developed a different approach for lowering the cost of access to space. We propose developing a new aircraft that will house an existing expendable rocket stage. This vehicle, termed StarBooster, will be the first stage of a family of launch vehicles. By combining these elements, we believe we can reduce the cost and risk of fielding a new partially reusable launch system. This report summarizes the work performed on the StarBooster concept since the company's inception in 1996. Detailed analyses are on-going and future reports will focus on the maturation of the vehicle and system design.

Vibroacoustic payload environment prediction system (VAPEPS): Data base management center remote access guide

NASA Technical Reports Server (NTRS)

Thomas, V. C.

1986-01-01

A Vibroacoustic Data Base Management Center has been established at the Jet Propulsion Laboratory (JPL). The center utilizes the Vibroacoustic Payload Environment Prediction System (VAPEPS) software package to manage a data base of shuttle and expendable launch vehicle flight and ground test data. Remote terminal access over telephone lines to a dedicated VAPEPS computer system has been established to provide the payload community a convenient means of querying the global VAPEPS data base. This guide describes the functions of the JPL Data Base Management Center and contains instructions for utilizing the resources of the center.

White Paper on Dish Stirling Technology: Path Toward Commercial Deployment

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

Andraka, Charles E.; Stechel, Ellen; Becker, Peter

2016-07-01

Dish Stirling energy systems have been developed for distributed and large-scale utility deployment. This report summarizes the state of the technology in a joint project between Stirling Energy Systems, Sandia National Laboratories, and the Department of Energy in 2011. It then lays out a feasible path to large scale deployment, including development needs and anticipated cost reduction paths that will make a viable deployment product.

Test Frame for Gravity Offload Systems

NASA Technical Reports Server (NTRS)

Murray, Alexander R.

2005-01-01

Advances in space telescope and aperture technology have created a need to launch larger structures into space. Traditional truss structures will be too heavy and bulky to be effectively used in the next generation of space-based structures. Large deployable structures are a possible solution. By packaging deployable trusses, the cargo volume of these large structures greatly decreases. The ultimate goal is to three dimensionally measure a boom's deployment in simulated microgravity. This project outlines the construction of the test frame that supports a gravity offload system. The test frame is stable enough to hold the gravity offload system and does not interfere with deployment of, or vibrations in, the deployable test boom. The natural frequencies and stability of the frame were engineered in FEMAP. The test frame was developed to have natural frequencies that would not match the first two modes of the deployable beam. The frame was then modeled in Solidworks and constructed. The test frame constructed is a stable base to perform studies on deployable structures.

Level-2 Milestone 6007: Sierra Early Delivery System Deployed to Secret Restricted Network

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

Bertsch, A. D.

This report documents the delivery and installation of Shark, a CORAL Sierra early delivery system deployed on the LLNL SRD network. Early ASC program users have run codes on the machine in support of application porting for the final Sierra system which will be deployed at LLNL in CY2018. In addition to the SRD resource, Shark, unclassified resources, Rzmanta and Ray, have been deployed on the LLNL Restricted Zone and Collaboration Zone networks in support of application readiness for the Sierra platform.

Intelligent Transportation Systems (ITS) in Texas: Deployment Summary and Case Study of Deployment Methodologies

DOT National Transportation Integrated Search

2000-06-01

The state of the intelligent transportation systems (ITS) program in Texas is summarized and analyzed. The report first reviews the types of ITS deployments within each Texas Department of Transportation district. The methods used to plan, design, co...

Tethered Satellite System (TSS-1R)-Post Flight (STS-75) Engineering Performance Report

NASA Technical Reports Server (NTRS)

Lavoie, Anthony R.

1996-01-01

The first mission of the Tethered Satellite deployer was flown onboard Atlantis in 1992 during the Space Transportation System (STS) flight STS-46. Due to a mechanical interference with the level wind mechanism the satellite was only Deployed to 256 m rather than the planned 20,000 m. Other problems were also experienced during the STS-46 flight and several modifications were made to the Deployer and Satellite. STS-75 was a reflight of the Tethered Satellite System 1 (TSS-1) designated as Tethered Satellite System 1 Reflight (TSS-1 R) onboard Columbia. As on STS-46, the TSS payload consisted of the Deployer, the Satellite, 3 cargo bay mounted experiments: Shuttle Electrodynamic Tether System (SETS), Shuttle Potential and Return Electron Experiment (SPREE), Deployer Core Equipment (DCORE) 4 Satellite mounted experiments: Research on Electrodynamics Tether Effects (RETE), Research on Orbital Plasma Electrodynamics (ROPE), Satellite Core Instruments (SCORE), Tether Magnetic Field Experiment (TEMAG) and an aft flight deck camera: Tether Optical Phenomena Experiment (TOP). Following successful pre-launch, launch and pre-deployment orbital operations, the Deployer deployed the Tethered Satellite to 19,695 m at which point the tether broke within the Satellite Deployment Boom (SDB). The planned length for On-Station I (OST1) was 20,700 m The Satellite flew away from the Orbiter with the tether attached. The satellite was "safed" and placed in a limited power mode via the RF link. The Satellite was contacted periodically during overflights of ground stations. Cargo bay science activities continued for the period of time allocated to TSS-1 R operations.

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

PubMed

Zohdi, T I

2017-04-01

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

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

DTIC Science & Technology

2015-01-01

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

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

NASA Technical Reports Server (NTRS)

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

2012-01-01

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

Identification of Classified Information in Unclassified DoD Systems During the Audit of Internal Controls and Data Reliability in the Deployable Disbursing System

DTIC Science & Technology

2009-02-17

Identification of Classified Information in Unclassified DoD Systems During the Audit of Internal Controls and Data Reliability in the Deployable...TITLE AND SUBTITLE Identification of Classified Information in Unclassified DoD Systems During the Audit of Internal Controls and Data Reliability...Systems During the Audit ofInternal Controls and Data Reliability in the Deployable Disbursing System (Report No. D-2009-054) Weare providing this

Design Validation Methodology Development for an Aircraft Sensor Deployment System

NASA Astrophysics Data System (ADS)

Wowczuk, Zenovy S.

The OCULUS 1.0 Sensor Deployment concept design, was developed in 2004 at West Virginia University (WVU), outlined the general concept of a deployment system to be used on a C-130 aircraft. As a sequel, a new system, OCULUS 1.1, has been developed and designed. The new system transfers the concept system design to a safety of flight design, and also enhanced to a pre-production system to be used as the test bed to gain full military certification approval. The OCULUS 1.1 system has an implemented standard deployment system/procedure to go along with a design suited for military certification and implementation. This design process included analysis of the system's critical components and the generation of a critical component holistic model to be used as an analysis tool for future payload modification made to the system. Following the completion of the OCULUS 1.1 design, preparations and procedures for obtaining military airworthiness certification are described. The airworthiness process includes working with the agency overseeing all modifications to the normal operating procedures made to military C-130 aircraft and preparing the system for an experimental flight test. The critical steps in his process include developing a complete documentation package that details the analysis performed on the OCULUS 1.1 system and also the design of experiment flight test plan to analyze the system. Following the approval of the documentation and design of experiment an experimental flight test of the OCULUS 1.1 system was performed to verify the safety and airworthiness of the system. This test proved successfully that the OCULUS 1.1 system design was airworthy and approved for military use. The OCULUS 1.1 deployment system offers an open architecture design that is ideal for use as a sensor testing platform for developmental airborne sensors. The system's patented deployment methodology presents a simplistic approach to reaching the systems final operating position which offers the most robust field of view area of rear ramp deployment systems.

Expanding the role of the nurse practitioner in the deployed setting.

PubMed

Dargis, Julie; Horne, Theresa; Tillman-Ortiz, Sophie; Scherr, Diane; Yackel, Edward E

2006-08-01

Today's military is experiencing rapid advances in technology and in manpower utilization. The Army Medical Department is redesigning the structure and function of deployable hospital systems as part of this effort. The transformation of deployable hospital systems requires that a critical analysis of manpower utilization be undertaken to optimize the employment of soldier-medics. The objective of this article was to describe the use of nurse practitioners as primary care providers during deployment. The lived experiences of five nurse practitioners deployed to Operation Iraqi Freedom are presented. Data gathered during the deployment and an analysis of the literature clearly support expanded and legitimized roles for these health care professionals in future conflicts and peacekeeping operations.

Structural active cooling applications for the Space Shuttle.

NASA Technical Reports Server (NTRS)

Masek, R. V.; Niblock, G. A.; Huneidi, F.

1972-01-01

Analytic and experimental studies have been conducted to evaluate a number of active cooling approaches to structural thermal protection for the Space Shuttle. The primary emphasis was directed toward the thermal protection system. Trade study results are presented for various heat shield material and TPS arrangements. Both metallic and reusable surface insulation (RSI) concepts were considered. Active systems heat sinks consisted of hydrogen, phase change materials, and expendable water. If consideration is given only to controlling the surface temperature, passive TPS was found to provide the most efficient system. Use of active cooling which incorporates some interior temperature control made the thermally less efficient RSI system more attractive.

System Engineering and Technical Challenges Overcome in the J-2X Rocket Engine Development Project

NASA Technical Reports Server (NTRS)

Ballard, Richard O.

2012-01-01

Beginning in 2006, NASA initiated the J-2X engine development effort to develop an upper stage propulsion system to enable the achievement of the primary objectives of the Constellation program (CxP): provide continued access to the International Space Station following the retirement of the Space Station and return humans to the moon. The J-2X system requirements identified to accomplish this were very challenging and the time expended over the five years following the beginning of the J- 2X effort have been noteworthy in the development of innovations in both the fields for liquid rocket propulsion and system engineering.

Spacecraft configuration study for second generation mobile satellite system

NASA Technical Reports Server (NTRS)

Louie, M.; Vonstentzsch, W.; Zanella, F.; Hayes, R.; Mcgovern, F.; Tyner, R.

1985-01-01

A high power, high performance communicatons satellite bus being developed is designed to satisfy a broad range of multimission payload requirements in a cost effective manner and is compatible with both STS and expendable launchers. Results are presented of tradeoff studies conducted to optimize the second generation mobile satellite system for its mass, power, and physical size. Investigations of the 20-meter antenna configuration, transponder linearization techniques, needed spacecraft modifications, and spacecraft power, dissipation, mass, and physical size indicate that the advanced spacecraft bus is capable of supporting the required payload for the satellite.

Gossamer-1: Mission concept and technology for a controlled deployment of gossamer spacecraft

NASA Astrophysics Data System (ADS)

Seefeldt, Patric; Spietz, Peter; Sproewitz, Tom; Grundmann, Jan Thimo; Hillebrandt, Martin; Hobbie, Catherin; Ruffer, Michael; Straubel, Marco; Tóth, Norbert; Zander, Martin

2017-01-01

Gossamer structures for innovative space applications, such as solar sails, require technology that allows their controlled and thereby safe deployment. Before employing such technology for a dedicated science mission, it is desirable, if not necessary, to demonstrate its reliability with a Technology Readiness Level (TRL) of six or higher. The aim of the work presented here is to provide reliable technology that enables the controlled deployment and verification of its functionality with various laboratory tests, thereby qualifying the hardware for a first demonstration in low Earth orbit (LEO). The development was made in the Gossamer-1 project of the German Aerospace Center (DLR). This paper provides an overview of the Gossamer-1 mission and hardware development. The system is designed based on the requirements of a technology demonstration mission. The design rests on a crossed boom configuration with triangular sail segments. Employing engineering models, all aspects of the deployment were tested under ambient environment. Several components were also subjected to environmental qualification testing. An innovative stowing and deployment strategy for a controlled deployment, as well as the designs of the bus system, mechanisms and electronics are described. The tests conducted provide insights into the deployment process and allow a mechanical characterization of that deployment process, in particular the measurement of the deployment forces. Deployment on system level could be successfully demonstrated to be robust and controllable. The deployment technology is on TRL four approaching level five, with a qualification model for environmental testing currently being built.

Technical support package: Large, easily deployable structures. NASA Tech Briefs, Fall 1982, volume 7, no. 1

NASA Technical Reports Server (NTRS)

1982-01-01

Design and test data for packaging, deploying, and assembling structures for near term space platform systems, were provided by testing light type hardware in the Neutral Buoyancy Simulator. An optimum or near optimum structural configuration for varying degrees of deployment utilizing different levels of EVA and RMS was achieved. The design of joints and connectors and their lock/release mechanisms were refined to improve performance and operational convenience. The incorporation of utilities into structural modules to determine their effects on packaging and deployment was evaluated. By simulation tests, data was obtained for stowage, deployment, and assembly of the final structural system design to determine construction timelines, and evaluate system functioning and techniques.

Activity Behaviours in Lean and Morbidly Obese Pregnant Women.

PubMed

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

2018-05-17

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

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

PubMed

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

2018-04-01

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

An optical fiber expendable seawater temperature/depth profile sensor

NASA Astrophysics Data System (ADS)

Zhao, Qiang; Chen, Shizhe; Zhang, Keke; Yan, Xingkui; Yang, Xianglong; Bai, Xuejiao; Liu, Shixuan

2017-10-01

Marine expendable temperature/depth profiler (XBT) is a disposable measuring instrument which can obtain temperature/depth profile data quickly in large area waters and mainly used for marine surveys, scientific research, military application. The temperature measuring device is a thermistor in the conventional XBT probe (CXBT)and the depth data is only a calculated value by speed and time depth calculation formula which is not an accurate measurement result. Firstly, an optical fiber expendable temperature/depth sensor based on the FBG-LPG cascaded structure is proposed to solve the problems of the CXBT, namely the use of LPG and FBG were used to detect the water temperature and depth, respectively. Secondly, the fiber end reflective mirror is used to simplify optical cascade structure and optimize the system performance. Finally, the optical path is designed and optimized using the reflective optical fiber end mirror. The experimental results show that the sensitivity of temperature and depth sensing based on FBG-LPG cascade structure is about 0.0030C and 0.1%F.S. respectively, which can meet the requirements of the sea water temperature/depth observation. The reflectivity of reflection mirror is in the range from 48.8% to 72.5%, the resonant peak of FBG and LPG are reasonable and the whole spectrum are suitable for demodulation. Through research on the optical fiber XBT (FXBT), the direct measurement of deep-sea temperature/depth profile data can be obtained simultaneously, quickly and accurately. The FXBT is a new all-optical seawater temperature/depth sensor, which has important academic value and broad application prospect and is expected to replace the CXBT in the future.

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

NASA Astrophysics Data System (ADS)

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

1981-09-01

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

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

NASA Technical Reports Server (NTRS)

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

1981-01-01

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

Technology Demonstration Missions

NASA Technical Reports Server (NTRS)

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

2015-01-01

Technology Demonstration Missions (TDM) is in its third year of execution, being initiated in 2010 and baselined in January of 2012. There are 11 projects that NASA Marshall Space Flight Center (MSFC) has contributed to or led: (1) Evolvable Cryogenics (eCryo): Cyrogenic Propellant Storage and Transfer Engineering Development Unit (EDU), a proof of manufacturability effort, used to enhance knowledge and technology related to handling cryogenic propellants, specifically liquid hydrogen. (2) Composites for Exploration Upper Stage (CEUS): Design, build, test, and address flight certification of a large composite shell suitable for the second stage of the Space Launch System (SLS). (3) Deep Space Atomic Clock (DSAC): Spaceflight to demo small, low-mass atomic clock that can provide unprecedented stability for deep space navigation. (4) Green Propellant Infusion Mission (GPIM): Demo of high-performance, green propellant propulsion system suitable for Evolved Expendable Launch Vehicle (EELV) Secondary Payload Adapter (ESPA)-class spacecraft. (5) Human Exploration Telerobotics (HET): Demonstrating how telerobotics, remote control of a variety of robotic systems, can take routine, highly repetitive, dangerous or long-duration tasks out of human hands. (6) Laser Communication Relay Demo (LCRD): Demo to advance optical communications technology toward infusion into deep space and near Earth operational systems, while growing the capabilities of industry sources. (7) Low Density Supersonic Decelerator (LDSD): Demo new supersonic inflatable decelerator and parachute technologies to enable Mars landings of larger payloads with greater precision at a wider range of altitudes. (8) Mars Science Laboratory (MSL) Entry Descent & Landing Instrumentation (MEDLI): Demo of embedded sensors embedded in the MSL heat shield, designed to record the heat and atmospheric pressure experienced during the spacecraft's high-speed, hot entry in the Martian atmosphere. (9) Solar Electric Propulsion (SEP): 50-kW class spacecraft that uses flexible blanket solar arrays for power generation and an electric propulsion system that delivers payload from low-Earth orbit to higher orbits. (10) Solar Sail Demonstration (SSD): Demo to validate sail deployment techniques for solar sails that are propelled by the pressure of sunlight. (11) Terrestrial HIAD Orbit Reentry (THOR): Demo of a 3.7-m Hypersonic Inflatable Aerodynamic Decelerator (HIAD) entry vehicle to test second generation aerothermal performance and modeling.

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

NASA Astrophysics Data System (ADS)

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

1990-08-01

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

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

DTIC Science & Technology

2014-03-22

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

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

DTIC Science & Technology

2014-09-30

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

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

Code of Federal Regulations, 2013 CFR

2013-04-01

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

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

Code of Federal Regulations, 2014 CFR

2014-04-01

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

Studies of two phase flow

NASA Technical Reports Server (NTRS)

Witte, Larry C.

1994-01-01

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

Strategic deployment plan : intelligent transportation system (ITS) : early deployment study, Kansas City metropolitan bi-state area

DOT National Transportation Integrated Search

1997-01-01

Intelligent transportation systems (ITS) are systems that utilize advanced technologies, including computer, communications and process control technologies, to improve the efficiency and safety of the transportation system. These systems encompass a...

Aircraft Pilot Situational Awareness Interface for Airborne Operation of Network Controlled Unmanned Systems (US)

DTIC Science & Technology

2008-03-01

operator, can be operated autonomously or remotely, can be expendable or recoverable, and can carry a lethal or nonlethal payload. Ballistic or semi ...states that vehicles should be recoverable, and that ballistic or semi - ballistic vehicles, cruise missiles, and artillery projectiles are not considered...2007-2032. 32 Nicola Tesla and his telautomatons (robots); Tesla further demonstrated remote control of objects by wireless in an exhibition in 1898

Buying a Shuttle ticket

NASA Technical Reports Server (NTRS)

Moore, W. F.; Forsythe, C.

1977-01-01

A preliminary draft policy for reimbursement for Space Shuttle flights has been developed by NASA in the form of pricing criteria for Space Transportation System (STS) users in domestic and foreign government and industry. The reimbursement policy, the transition from expendable launch vehicles to STS, the new user services, and the interaction of the economics of new user services and STS cost to fly are discussed in the present paper. Current efforts to develop new users are noted.

A Review of United States Air Force and Department of Defense Aerospace Propulsion Needs

DTIC Science & Technology

2006-01-01

evolved expendable launch vehicle EHF extremely high frequency EMA electromechanical actuator EMDP engine model derivative program EMTVA...condition. A key aspect of the model was which of the two methods was used—parameters of the system or propulsion variables produced in the design ... models for turbopump analysis and design . In addition, the skills required to design a high -performance turbopump are very specialized and must be

LANDSAT D to test thematic mapper, inaugurate operational system

NASA Technical Reports Server (NTRS)

1982-01-01

NASA will launch the Landsat D spacecraft on July 9, 1982 aboard a new, up-rated Delta 3920 expendable launch vehicle. LANDSAT D will incorporate two highly sophisticated sensors; the flight proven multispectral scanner; and a new instrument expected to advance considerably the remote sensing capabilities of Earth resources satellites. The new sensor, the thematic mapper, provides data in seven spectral (light) bands with greatly improved spectral, spatial and radiometric resolution.

KSC-03pd0021

NASA Image and Video Library

2003-01-05

KENNEDY SPACE CENTER, FLA. -- The Pegasus XL Expendable Launch Vehicle is on a workstand in the Multi-Purpose Processing Facility. The Pegasus XL will carry NASA's Solar Radiation and Climate Experiment (SORCE) into orbit. Built by Orbital Sciences Space Systems Group, SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere. The launch of SORCE is scheduled for Jan. 25 at 3:14 p.m. from Cape Canaveral Air Force Station, Fla.

KSC-03pd0022

NASA Image and Video Library

2003-01-05

KENNEDY SPACE CENTER, FLA. -- The Pegasus XL Expendable Launch Vehicle is on a workstand in the Multi-Purpose Processing Facility. The Pegasus XL will carry NASA's Solar Radiation and Climate Experiment (SORCE) into orbit. Built by Orbital Sciences Space Systems Group, SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere. The launch of SORCE is scheduled for Jan. 25 at 3:14 p.m. from Cape Canaveral Air Force Station, Fla.

AMF 1 Site Science

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

Miller, Mark Alan

This report documents progress on DOE Grant# DE-FG02-08ER64531 funded by the Department of Energy’s Atmospheric Systems Research (ASR) program covering the period between its inception in 2008 and its conclusion in 2014. The Atmospheric Radiation Measurement (ARM) Program’s Mobile Facility #1 (AMF#1) is a collection of state-of-the art atmospheric sensing systems including remote and in situ instrumentation designed to characterize the atmospheric column above and in the immediate vicinity of the deployment location. The grant discussed in this report funded the activities of the AMF#1 Site Scientist Team. Broad responsibilities of this team included examining new deployment sites and recommendingmore » instrument deployment configurations; data quality control during the early stages of deployments and for certain instruments through the course of the deployment; scientific outreach in the host country or location (particularly international deployments); scientific research oriented toward basic questions about cloud physics and radiation transfer in the deployment region; and training of Ph.D. students to conduct future research relevant to the Atmospheric Systems Research (ASR) program.« less

Tethered Satellite System Project Overview

NASA Technical Reports Server (NTRS)

Laue, J. H.

1985-01-01

The Skyhook concept is reviewed and the use of a tethered satellite system (TSS) to enable scientific investigations from the shuttle using a closed loop control system is examined. The tethered satellite system has capabilities for deployment toward or away from Earth, for multiple round trip missions, and for deployment at distances up to 100 KN from the orbiter. The deployer, which consists of an entendable boom, a reel for the tether, and the tether itself, permits deployment and retrieval at a safe distance, allows alignment of the force vector of the tether through the center of gravity of the shuttle, and gives some initial gravity gradient separation to aid in deployment and ultimate retrieval of the tethered satellite. Charts show TSS activities in terms of systems studies, key guidelines, Italian and U.S. responsibilities, user activities, and major science and applications accommodation features. Scientific objectives for TSS-1 and TSS-2 verification missions and the current status of the project are also given.

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

NASA Technical Reports Server (NTRS)

Abelson, Robert D.; Satter, Celeste M.

2005-01-01

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

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

PubMed

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

2017-12-01

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

Transjugular liver biopsy with use of the shark jaw needle: diagnostic yield, complications, and cost-effectiveness.

PubMed

Psooy, B J; Clark, T W; Beecroft, J R; Malatjalian, D

2001-01-01

Obtaining transjugular liver biopsy specimens with use of single-use needle systems is expensive, whereas biopsy specimens obtained with use of reusable needle systems are frequently associated with inadequate core specimens. The authors report their experience with the reusable Cook Shark Jaw biopsy needle, including diagnostic yield, complications, and cost-effectiveness. A retrospective audit was performed of a cohort of 134 patients who underwent 136 transjugular liver biopsies with use of a reusable 16-gauge Shark Jaw needle during a 30-month period. Specimen adequacy and complication rates were assessed and direct costs of expendable components calculated. Cost-effectiveness was expressed as cost-per-successful biopsy. Biopsies were technically successful in 126 of 136 (93%) patients, with diagnostic histologic core specimens obtained in 124 of 126 (98%) patients, for an overall success rate of 91%. Complications included capsular penetration in six (4.4%) patients, cardiac arrhythmia in two (1.5%) patients, and puncture site hematoma or bleeding in 10 (7.4%) patients. Three tract embolizations were performed for capsular penetration. No instances of subcapsular hematoma, hemoperitoneum, or sepsis occurred, and no deaths were attributed to the procedure. The cost of expendable components totaled $103 per biopsy, corresponding to a cost-effectiveness of $113/successful biopsy. Transjugular liver biopsy specimens obtained with use of the Shark Jaw needle have a diagnostic yield comparable to those obtained with use of single-use biopsy systems, at a substantially lower cost with no increase in serious complications.

Deployable antenna phase A study

NASA Technical Reports Server (NTRS)

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

1979-01-01

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

Integrated corridor management analysis, modeling, and simulation for the I–15 corridor in San Diego, California—post-deployment analysis plan.

DOT National Transportation Integrated Search

2016-11-01

Post-Deployment Analysis, Modeling, and Simulation (AMS) activities focus on identifying impacts and benefits of the as-deployed Integrated Corridor Management (ICM) system. The as-deployed ICM strategies may differ from as-planned ...

Integrated corridor management : analysis, modeling, and simulation for the U.S.-15 corridor in Dallas, Texas—post-deployment analysis plan.

DOT National Transportation Integrated Search

2016-10-01

Post-Deployment Analysis, Modeling, and Simulation (AMS) activities focus on identifying impacts and benefits of the as-deployed Integrated Corridor Management (ICM) system. The as-deployed ICM strategies may differ from as-planned ...

Automated Information System (AIS) Support for FMF Units When Deployed or in Combat (1985-1995).

DTIC Science & Technology

1982-04-13

1995 ) MAJOR T. J. DUNN DEPUTY CHIEF OF STAFF FOR DEVELOPMENTAL COORDINATION DEVELOPMENT CENTER MARINE CORPS DEVELOPMENT AND EDUCATION COMMAND...Support for FMF Units When Deployed or in Combat (1985- 1995 ) (Deployed AIS-88) Study (SCN: 60-81-02) 1. The objectives of the study were: a. To...S. TYPE OF REPORT 6 PERIOD COVERED Automated Information System (AIS) Support for Final Report FMF Units When Deployed or in Combat (1985- 1995 ) 6

Strategic deployment. Two decades of experience provide important lessons on how to deploy emergency resources.

PubMed

Fitch, Jay

2002-02-01

When it comes to deployment, one size (approach) doesn't fit all. Progressive public safety and EMS systems will recognize that a successful plan can thoughtfully balance system performance and human needs. Inventive people who learned how to do things better, cheaper and faster built America. Providing optimum system coverage, improved response times and quality care for patients fits the same mold. Sophisticated and accountable EMS systems readily accept this as part of their mandate.

Marine Seismic System At-Sea-Test Deployment Operation

DTIC Science & Technology

1981-10-09

ton crane can handle deck loads. An early version Deloo type ASK ( Automatic Stationkeeping) system is used to maintain position over a deployed short...b --- 00 - Ir RPT 006-007EV "A 126283 [ I iMIIE SEISMIC SYSTEM I AT-SEA-TEST DEP OYiN OFERATION I GLOBAL MARINE DEVELOPMENT INC 2302 Martin Street...Seismic System At-Sea-Test Deployment Operation 6. PERFORNING *o. REPORT NUMOER IPT 006-007 7. AUTNMORI) O. CONTRACT Ol GRANT NUMOERIa iR. Wallerstedt

On the Path to SunShot. Emerging Issues and Challenges in Integrating Solar with the Distribution System

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

Palmintier, Bryan; Broderick, Robert; Mather, Barry

2016-05-01

This report analyzes distribution-integration challenges, solutions, and research needs in the context of distributed generation from PV (DGPV) deployment to date and the much higher levels of deployment expected with achievement of the U.S. Department of Energy's SunShot targets. Recent analyses have improved estimates of the DGPV hosting capacities of distribution systems. This report uses these results to statistically estimate the minimum DGPV hosting capacity for the contiguous United States using traditional inverters of approximately 170 GW without distribution system modifications. This hosting capacity roughly doubles if advanced inverters are used to manage local voltage and additional minor, low-cost changesmore » could further increase these levels substantially. Key to achieving these deployment levels at minimum cost is siting DGPV based on local hosting capacities, suggesting opportunities for regulatory, incentive, and interconnection innovation. Already, pre-computed hosting capacity is beginning to expedite DGPV interconnection requests and installations in select regions; however, realizing SunShot-scale deployment will require further improvements to DGPV interconnection processes, standards and codes, and compensation mechanisms so they embrace the contributions of DGPV to system-wide operations. SunShot-scale DGPV deployment will also require unprecedented coordination of the distribution and transmission systems. This includes harnessing DGPV's ability to relieve congestion and reduce system losses by generating closer to loads; minimizing system operating costs and reserve deployments through improved DGPV visibility; developing communication and control architectures that incorporate DGPV into system operations; providing frequency response, transient stability, and synthesized inertia with DGPV in the event of large-scale system disturbances; and potentially managing reactive power requirements due to large-scale deployment of advanced inverter functions. Finally, additional local and system-level value could be provided by integrating DGPV with energy storage and 'virtual storage,' which exploits improved management of electric vehicle charging, building energy systems, and other large loads. Together, continued innovation across this rich distribution landscape can enable the very-high deployment levels envisioned by SunShot.« less

Robotics for Nuclear Material Handling at LANL:Capabilities and Needs

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

Harden, Troy A; Lloyd, Jane A; Turner, Cameron J

Nuclear material processing operations present numerous challenges for effective automation. Confined spaces, hazardous materials and processes, particulate contamination, radiation sources, and corrosive chemical operations are but a few of the significant hazards. However, automated systems represent a significant safety advance when deployed in place of manual tasks performed by human workers. The replacement of manual operations with automated systems has been desirable for nearly 40 years, yet only recently are automated systems becoming increasingly common for nuclear materials handling applications. This paper reviews several automation systems which are deployed or about to be deployed at Los Alamos National Laboratory formore » nuclear material handling operations. Highlighted are the current social and technological challenges faced in deploying automated systems into hazardous material handling environments and the opportunities for future innovations.« less

Remote Systems Design & Deployment

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

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

2009-08-28

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

Operationally Efficient Propulsion System Study (OEPSS) data book. Volume 2: Ground operations problems

NASA Technical Reports Server (NTRS)

Waldrop, Glen S.

1990-01-01

Operations problems and cost drivers were identified for current propulsion systems and design and technology approaches were identified to increase the operational efficiency and to reduce operations costs for future propulsion systems. To provide readily usable data for the ALS program, the results of the OEPSS study were organized into a series of OEPSS Data Books. This volume presents a detailed description of 25 major problems encountered during launch processing of current expendable and reusable launch vehicles. A concise description of each problem and its operational impact on launch processing is presented, along with potential solutions and technology recommendation.

Economics in ground operations of the Space Shuttle

NASA Technical Reports Server (NTRS)

Gray, R. H.

1973-01-01

The physical configuration, task versatility, and typical mission profile of the Space Shuttle are illustrated and described, and a comparison of shuttle and expendable rocket costs is discussed, with special emphasis upon savings to be achieved in ground operations. A review of economies achieved by engineering design improvements covers the automated checkout by onboard shuttle systems, the automated launch processing system, the new maintenance concept, and the analogy of Space Shuttle and airline repetitive operations. The Space Shuttle is shown to represent a new level in space flight technology, particularly, the sophistication of the systems and procedures devised for its support and ground operations.

Application of a data base management system to a finite element model

NASA Technical Reports Server (NTRS)

Rogers, J. L., Jr.

1980-01-01

In today's software market, much effort is being expended on the development of data base management systems (DBMS). Most commercially available DBMS were designed for business use. However, the need for such systems within the engineering and scientific communities is becoming apparent. A potential DBMS application that appears attractive is the handling of data for finite element engineering models. The applications of a commercially available, business-oriented DBMS to a structural engineering, finite element model is explored. The model, DBMS, an approach to using the DBMS, advantages and disadvantages are described. Plans for research on a scientific and engineering DBMS are discussed.

Active controls: A look at analytical methods and associated tools

NASA Technical Reports Server (NTRS)

Newsom, J. R.; Adams, W. M., Jr.; Mukhopadhyay, V.; Tiffany, S. H.; Abel, I.

1984-01-01

A review of analytical methods and associated tools for active controls analysis and design problems is presented. Approaches employed to develop mathematical models suitable for control system analysis and/or design are discussed. Significant efforts have been expended to develop tools to generate the models from the standpoint of control system designers' needs and develop the tools necessary to analyze and design active control systems. Representative examples of these tools are discussed. Examples where results from the methods and tools have been compared with experimental data are also presented. Finally, a perspective on future trends in analysis and design methods is presented.

Global Deployment Anaylsis System Algorithm Description (With Updates)

DTIC Science & Technology

1998-09-01

Global Deployment Analysis System Algorithm Description (with Updates) By Noetics , Inc. For U.S. Army Concepts Analysis Agency Contract...t "O -Q £5.3 Q 20000224 107 aQU’no-bi-o^f r This Algorithm Description for the Global Deployment Analysis System (GDAS) was prepared by Noetics ...support for Paradox Runtime will be provided by the GDAS developers, CAA and Noetics Inc., and not by Borland International. GDAS for Windows has

Self-Deployable Membrane Structures

NASA Technical Reports Server (NTRS)

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

2010-01-01

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

Airport Surface Traffic Control Systems Deployment Analysis

DOT National Transportation Integrated Search

1974-01-01

The report summarizes the findings of an analysis of ASTC (Airport Surface Traffic Control) system requirements and develops estimates of the deployment potential of proposed system alternatives. The tower control problem areas were investigated by a...

Airport Surface Control Systems Development Analysis Expanded

DOT National Transportation Integrated Search

1990-01-01

A previous MITRE Technical Report, Airport Surface Traffic Control Systems Deployment Analysis, FAA-RD-74-6, presented an analysis of ASTC (Airport Surface Traffic Control) system requirements and developed estimates of the deployment potential of pr...

Parental Deployment and Youth in Military Families: Exploring Uncertainty and Ambiguous Loss

ERIC Educational Resources Information Center

Huebner, Angela J.; Mancini, Jay A.; Wilcox, Ryan M.; Grass, Saralyn R.; Grass, Gabriel A.

2007-01-01

Parental deployment has substantial effects on the family system, among them ambiguity and uncertainty. Youth in military families are especially affected by parental deployment because their coping repertoire is only just developing; the requirements of deployment become additive to normal adolescent developmental demands. Focus groups were used…

Autonomous intelligent military robots: Army ants, killer bees, and cybernetic soldiers

NASA Astrophysics Data System (ADS)

Finkelstein, Robert

The rationale for developing autonomous intelligent robots in the military is to render conventional warfare systems ineffective and indefensible. The Desert Storm operation demonstrated the effectiveness of such systems as unmanned air and ground vehicles and indicated the future possibilities of robotic technology. Robotic military vehicles would have the advantages of expendability, low cost, lower complexity compared to manned systems, survivability, maneuverability, and a capability to share in instantaneous communication and distributed processing of combat information. Basic characteristics of intelligent systems and hierarchical control systems with sensor inputs are described. Genetic algorithms are seen as a means of achieving appropriate levels of intelligence in a robotic system. Potential impacts of robotic technology in the military are outlined.

Extended mission life support systems

NASA Technical Reports Server (NTRS)

Quattrone, P. D.

1985-01-01

Extended manned space missions which include interplanetary missions require regenerative life support systems. Manned mission life support considerations are placed in perspective and previous manned space life support system technology, activities and accomplishments in current supporting research and technology (SR&T) programs are reviewed. The life support subsystem/system technologies required for an enhanced duration orbiter (EDO) and a space operations center (SOC), regenerative life support functions and technology required for manned interplanetary flight vehicles, and future development requirements are outlined. The Space Shuttle Orbiters (space transportation system) is space cabin atmosphere is maintained at Earth ambient pressure of 14.7 psia (20% O2 and 80% N2). The early Shuttle flights will be seven-day flights, and the life support system flight hardware will still utilize expendables.

Deployment simulation of a deployable reflector for earth science application

NASA Astrophysics Data System (ADS)

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

2015-10-01

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

Design and Fabrication of Nereid-UI: A Remotely Operated Underwater Vehicle for Oceanographic Access Under Ice

NASA Astrophysics Data System (ADS)

Whitcomb, L. L.; Bowen, A. D.; Yoerger, D.; German, C. R.; Kinsey, J. C.; Mayer, L. A.; Jakuba, M. V.; Gomez-Ibanez, D.; Taylor, C. L.; Machado, C.; Howland, J. C.; Kaiser, C. L.; Heintz, M.; Pontbriand, C.; Suman, S.; O'hara, L.

2013-12-01

The Woods Hole Oceanographic Institution and collaborators from the Johns Hopkins University and the University of New Hampshire are developing for the Polar Science Community a remotely-controlled underwater robotic vehicle capable of being tele-operated under ice under remote real-time human supervision. The Nereid Under-Ice (Nereid-UI) vehicle will enable exploration and detailed examination of biological and physical environments at glacial ice-tongues and ice-shelf margins, delivering high-definition video in addition to survey data from on board acoustic, chemical, and biological sensors. Preliminary propulsion system testing indicates the vehicle will be able to attain standoff distances of up to 20 km from an ice-edge boundary, as dictated by the current maximum tether length. The goal of the Nereid-UI system is to provide scientific access to under-ice and ice-margin environments that is presently impractical or infeasible. FIBER-OPTIC TETHER: The heart of the Nereid-UI system is its expendable fiber optic telemetry system. The telemetry system utilizes many of the same components pioneered for the full-ocean depth capable HROV Nereus vehicle, with the addition of continuous fiber status monitoring, and new float-pack and depressor designs that enable single-body deployment. POWER SYSTEM: Nereid-UI is powered by a pressure-tolerant lithium-ion battery system composed of 30 Ah prismatic pouch cells, arranged on a 90 volt bus and capable of delivering 15 kW. The cells are contained in modules of 8 cells, and groups of 9 modules are housed together in oil-filled plastic boxes. The power distribution system uses pressure tolerant components extensively, each of which have been individually qualified to 10 kpsi and operation between -20 C and 40 C. THRUSTERS: Nereid-UI will employ eight identical WHOI-designed thrusters, each with a frameless motor, oil-filled and individually compensated, and designed for low-speed (500 rpm max) direct drive. We expect an end-to-end propulsive efficiency of between 0.3 and 0.4 at a transit speed of 1 m/s based on testing conducted at WHOI. CAMERAS: Video imagery is one of the principal products of Nereid-UI. Two fiber-optic telemetry wavelengths deliver 1.5 Gb/s uncompressed HDSDI video to the support vessel in real time, supporting a Kongsberg OE14-522 hyperspherical pan and tilt HD camera and several utility cameras. PROJECT STATUS: The first shallow-water vehicle trials are scheduled for September 2013. The trials are designed to test core vehicle systems particularly the power system, main computer and control system, thrusters, video and telemetry system, and to refine camera, lighting and acoustic sensor placement for piloted and closed-loop control, especially as pertains to working near the underside of ice. Remaining vehicle design tasks include finalizing the single-body deployment concept and depressor, populating the scientific sensing suite, and the software development necessary to implement the planned autonomous return strategy. Final design and fabrication for these remaining components of the vehicle system will proceed through fall 2013, with trials under lake ice in early 2014, and potential polar trials beginning in 2014-15. SUPPORT: NSF OPP (ANT-1126311), WHOI, James Family Foundation, and George Frederick Jewett Foundation East.

An Examination of the Effects of a Quality Circles Program on Attitudinal Variables in Two DoD Installations

DTIC Science & Technology

1983-09-28

organization, the leader, the group, the reward system, and the individual’s attitudes, skills, and effort expended ( Szilagyi & Wallace , 1980), The...hesiveness are consistent with group tasks and goals. Szilagyi and Wallace (1980) write that the highest levels of group performance are found in highly...organizational commitment. Administrative Science Quarterly, March 1977, 46-56. Szilagyi , A. D., Jr., & Wallace , M. J., Jr. Organizational behavior and

The economics of satellite maintenance

NASA Technical Reports Server (NTRS)

Derocher, W. L., Jr.; Sosnay, R. G.

1975-01-01

The primary goal of the space transportation system - to reduce the cost of space programs while satisfying their mission requirements - can be enhanced by the proper choice of a satellite-maintenance concept. This paper develops the life-cycle costs of performing an automated satellite program during the shuttle era in three competitive modes: expendable, ground-refurbishable, and in-orbit maintainable. In-orbit maintenance is shown to be the most economic maintenance mode for both low- and high-earth orbits.

Role of polysaccharides in Pseudomonas aeruginosa biofilm development

PubMed Central

Ryder, Cynthia; Byrd, Matthew; Wozniak, Daniel J.

2008-01-01

During the past decade, there has been a renewed interest in using P. aeruginosa as a model system for biofilm development and pathogenesis. Since the biofilm matrix represents a critical interface between the bacterium and the host or its environment, considerable effort has been expended to acquire a more complete understanding of the matrix composition. Here, we focus on recent developments regarding the roles of alginate, Psl, and Pel polysaccharides in the biofilm matrix. PMID:17981495

Analysis of NASA’s Post-Challenger Response and Relationship to the Columbia Accident and Investigation

DTIC Science & Technology

2006-09-01

Washington DC 20503. 1. AGENCY USE ONLY (Leave blank) 2. REPORT DATE September 2006 3. REPORT TYPE AND DATES COVERED Master’s Thesis 4. TITLE...recommendations that developed from this broader investigation. This examination will be used to determine to what extent the Commissions findings...system “partially” reusable by using an expendable, external tank to feed the orbiter’s engines and two strap-on reusable boosters to provide the

Design and fabrication of composite blades for the Mod-1 wind turbine generator

NASA Technical Reports Server (NTRS)

Batesole, W. R.; Gunsallus, C. T.

1981-01-01

The design, tooling, fabrication, quality control, and testing phases carried out to date, as well as testing still planned are described. Differences from the 150 foot blade which were introduced for cost and manufacturing improvement purposes are discussed as well as the lightning protection system installed in the blades. Actual costs and manhours expended for Blade No. 2 are provided as a base, along with a projection of costs for the blade in production.

Earth Science

NASA Image and Video Library

1992-07-24

A Delta II rocket carrying the Geomagnetic Tail Lab (GEOTAIL) spacecraft lifts off at Launch Complex 17, Kennedy Space Center (KSC) into a cloud-dappled sky. This liftoff marks the first Delta launch under the medium expendable launch vehicle services contract between NASA and McDonnell Douglas Space Systems Co. The GEOTAIL mission, a joint US/Japanese project, is the first in a series of five satellites to study the interactions between the Sun, the Earth's magnetic field, and the Van Allen radiation belts.

Aeromechanics and Vehicle Configuration Demonstrations. Volume 3: A Hybrid Probabilistic Method for Estimate Design Margin

DTIC Science & Technology

2014-02-01

infrastructure–satellites provide communications , remote sensing, radio -based navigation through the global positioning system, and world-wide, coordinated...to be expendable. For the Saturn V stages, #501 is the first Saturn V launched while #506 is the rocket used for the Apollo 11 mission after having...Air Force AGENCY ACRONYM(S) AFRL/RQHV 11 . SPONSORING/MONITORING AGENCY REPORT NUMBER(S) AFRL-RQ-WP-TR-2014-0005V3 12. DISTRIBUTION/AVAILABILITY

Shuttle Derived In-Line Heavy Lift Vehicle

NASA Technical Reports Server (NTRS)

Greenwood, Terry; Twichell, Wallace; Ferrari, Daniel; Kuck, Frederick

2005-01-01

This paper introduces an evolvable Space Shuttle derived family of launch vehicles. It details the steps in the evolution of the vehicle family, noting how the evolving lift capability compares with the evolving lift requirements. A system description is given for each vehicle. The cost of each development stage is described. Also discussed are demonstration programs, the merits of the SSME vs. an expendable rocket engine (RS-68), and finally, the next steps needed to refine this concept.

Shuttle Propulsion Overview - The Design Challenges

NASA Technical Reports Server (NTRS)

Owen, James W.

2011-01-01

The major elements of the Space Shuttle Main Propulsion System include two reusable solid rocket motors integrated into recoverable solid rocket boosters, an expendable external fuel and oxidizer tank, and three reusable Space Shuttle Main Engines. Both the solid rocket motors and space shuttle main engines ignite prior to liftoff, with the solid rocket boosters separating about two minutes into flight. The external tank separates, about eight and a half minutes into the flight, after main engine shutdown and is safely expended in the ocean. The SSME's, integrated into the Space Shuttle Orbiter aft structure, are reused after post landing inspections. The configuration is called a stage and a half as all the propulsion elements are active during the boost phase, with only the SSME s continuing operation to achieve orbital velocity. Design and performance challenges were numerous, beginning with development work in the 1970's. The solid rocket motors were large, and this technology had never been used for human space flight. The SSME s were both reusable and very high performance staged combustion cycle engines, also unique to the Space Shuttle. The multi body side mount configuration was unique and posed numerous integration and interface challenges across the elements. Operation of the system was complex and time consuming. This paper describes the design challenges and key areas where the design evolved during the program.

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

DTIC Science & Technology

1988-12-01

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

Final Report

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

Segre, Carlo, Ph.D.

2005-03-30

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

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

NASA Technical Reports Server (NTRS)

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

1975-01-01

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

Small Space Launch: Origins & Challenges

NASA Astrophysics Data System (ADS)

Freeman, T.; Delarosa, J.

2010-09-01

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

Satellite Sensornet Gateway Technology Infusion Through Rapid Deployments for Environmental Sensing

NASA Astrophysics Data System (ADS)

Benzel, T.; Silva, F.; Deschon, A.; Ye, W.; Cho, Y.

2008-12-01

The Satellite Sensornet Gateway (SSG) is an ongoing ESTO Advanced Information Systems Technology project, at the University of Southern California. The major goal of SSG is to develop a turnkey solution for building environmental observation systems based on sensor networks. Our system has been developed through an iterative series of deployment-driven design, build, test, and revise which maximizes technology infusion to the earth scientist. We have designed a robust and flexible sensor network called Sensor Processing and Acquisition Network (SPAN). Our SPAN architecture emphasizes a modular and extensible design, such that core building blocks can be reused to develop different scientific observation systems. To support rapid deployment at remote locations, we employ satellite communications as the backhaul to relay in-situ sensor data to a central database. To easily support various science applications, we have developed a unified sensor integration framework that allows streamlined integration of different sensors to the system. Our system supports heterogeneous sets of sensors, from industry-grade products to research- specific prototypes. To ensure robust operation in harsh environments, we have developed mechanisms to monitor system status and recover from potential failures along with additional remote configuration and QA/QC functions. Here we briefly describe the deployments, the key science missions of the deployments and the role that the SSG technology played in each mission. We first deployed our SSG technology at the James Reserve in February 2007. In a joint deployment with the NEON project, SDSC, and UC Riverside, we set up a meteorological station, using a diverse set of sensors, with the objective of validating our basic technology components in the field. This system is still operational and streaming live sensor data. At Stunt Ranch, a UC Reserve near Malibu, CA, we partnered with UCLA biologist Phillip Rundel in order to study the drought impact on deep and shallow rooted plants. Our system was deployed in December 2007 and monitors sap flow on various plant species, while using a satellite link for real-time data access. In April 2008, in a joint deployment with UCLA, UC Merced, and GLEON, our SSG technology was used to study the impact of agricultural run off in a series of salt lakes near Bahia Blanca, Argentina. Our system collected meteorological data that were combined with water quality measurements taken from boats and buoys. Our SSG technology was used at the PASI workshop in June 2008 at the La Selva Biological Research Station in Costa Rica. As part of a two-week curriculum, students from throughout the americas used our system to collect measurements in the rain forest and later analyzed the data. La Selva plans to install several SSG nodes throughout the reserve and make mobile nodes available for visiting researchers to use in their research. We are currently planning a deployment with environmental engineer Tom Harmon from UC Merced to build an autonomous water quality flow path and reactive transport observation system near Merced, CA. SSG technology will be deployed to monitor soil, groundwater, and surface water parameters. In China's Guizhou Province, we are collaborating with researcher Sarah Rothenberg, who is studying mercury cycling in rice paddies. Our SSG system will collect soil parameters such as pH and ORP, in addition to environmental measurements such as PAR, and UV. This presentation will describe the SSG project, the SPAN prototype and our experience with technology infusion from the deployments. class="ab'>

Lessons Learned in the Development of Gamma-Rover (GRover) Inspection Device

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

Valdez, Patrick LJ; Alzheimer, James M.; Catalan, Michael A.

2006-02-11

The Gamma-Rover (GRover) is an electrically powered crawler designed to visually inspect and characterize the radiological conditions within the B-Cell and D-Cell ventilation ducting in support of the Hanford Site’s 324 Building Stabilization/Deactivation Project. Due to the bid opening of the Department of Energy’s River Corridor Project prior to deployment, GRover has not yet been deployed. The delay in deployment has allowed the designers to develop lessons learned from the original development in order to propose improvements when the system is deployed in the future. Gamma field information is detected with a pair of Eberline DA1-8/RMS systems. One system ismore » mounted directly on the crawler, while the second is mounted on the deployment platform. Four web cameras on a pair of CAT-5e/USB channels provide video feedback from both the crawler and the deployment platform. The drive system was designed to overcome a potentially difficult path of the duct, which included three ninety-degree bends. Mockups of the duct bends yielded high friction on the tether, and a drive system to overcome this friction was especially difficult to design into such a small package. Deployment was to be performed during a routine air filter change-out. As such, a specialized deployment platform was designed to pass through the existing filter housing. GRover would be required to be staged within the hot cell prior to the filter change-out and could therefore be dosed in excess of 8 hours. Thus, the platform also had to protect the electronics from radiation damage for an extended period of time.« less

Closed-Loop Control for Sonic Fatigue Testing Systems

NASA Technical Reports Server (NTRS)

Rizzi, Stephen A.; Bossaert, Guido

2001-01-01

This article documents recent improvements to the acoustic control system of the Thermal Acoustic Fatigue Apparatus (TAFA), a progressive wave tube test facility at the NASA Langley Research Center, Hampton, VA. A brief summary of past acoustic performance is first given to serve as a basis of comparison with the new performance data using a multiple-input, closed-loop, narrow-band controller. Performance data in the form of test section acoustic power spectral densities and coherence are presented for a variety of input spectra including uniform, band-limited random and an expendable launch vehicle payload bay environment.

Organizing for low cost space operations - Status and plans

NASA Technical Reports Server (NTRS)

Lee, C.

1976-01-01

Design features of the Space Transportation System (vehicle reuse, low cost expendable components, simple payload interfaces, standard support systems) must be matched by economical operational methods to achieve low operating and payload costs. Users will be responsible for their own payloads and will be charged according to the services they require. Efficient use of manpower, simple documentation, simplified test, checkout, and flight planning are firm goals, together with flexibility for quick response to varying user needs. Status of the Shuttle hardware, plans for establishing low cost procedures, and the policy for user charges are discussed.

Study of alternate space shuttle concepts

NASA Technical Reports Server (NTRS)

1971-01-01

A study of alternate space shuttle concepts was conducted to examine the stage-and-one-half concept and its potential for later conversion and use in the two stage reusable shuttle system. A study of external hydrogen tank concepts was conducted to determine the issues involved in the design and production of a low-cost expendable tank system. The major objectives of the study were to determine: (1) realistic drop tank program cost estimates, (2) estimated drop tank program cost for selected specific designs, and (3) change in program cost due to variations in design and manufacturing concepts and changes in program assumptions.

Stress Prediction System

NASA Technical Reports Server (NTRS)

1995-01-01

NASA wanted to know how astronauts' bodies would react under various gravitational pulls and space suit weights. Under contract to NASA, the University of Michigan's Center for Ergonomics developed a model capable of predicting what type of stress and what degree of load a body could stand. The algorithm generated was commercialized with the ISTU (Isometric Strength Testing Unit) Functional Capacity Evaluation System, which simulates tasks such as lifting a heavy box or pushing a cart and evaluates the exertion expended. It also identifies the muscle group that limits the subject's performance. It is an effective tool of personnel evaluation, selection and job redesign.

The Study on University Financial Management under Knowledge Economy

NASA Astrophysics Data System (ADS)

Yongfan, Xu

The coming of knowledge economy creates unprecedented situation of economy development. The trend of education's globalization as well as communication means frequently updated severely hit the system of financial management. Along with the deep going of education industrialization, and development of logistics management socialization, system and content of university financial management are increasingly expending and getting more and more complex that result in new challenge and problems to financial management. In order to step up with university development of internationalization and the logistics development of socialization, the financial management has to reform in response to this new challenge and trend.

Definition and design of an experiment to test raster scanning with rotating unbalanced-mass devices on gimbaled payloads

NASA Technical Reports Server (NTRS)

Lightsey, W. D.; Alhorn, D. C.; Polites, M. E.

1992-01-01

An experiment designed to test the feasibility of using rotating unbalanced-mass (RUM) devices for line and raster scanning gimbaled payloads, while expending very little power is described. The experiment is configured for ground-based testing, but the scan concept is applicable to ground-based, balloon-borne, and space-based payloads, as well as free-flying spacecraft. The servos used in scanning are defined; the electronic hardware is specified; and a computer simulation model of the system is described. Simulation results are presented that predict system performance and verify the servo designs.

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

NASA Technical Reports Server (NTRS)

Lorenzini, E.; Arnold, D. A.; Grossi, M. D.; Gullahorn, G. E.

1985-01-01

The deployment maneuver of three axis vertical constellations with elastic tethers is analyzed. The deployment strategy devised previously was improved. Dampers were added to the system. Effective algorithms for damping out the fundamental vibrational modes of the system were implemented. Simulations of a complete deployment and a subsequent station keeping phase of a three mass constellation is shown.

An electromechanical actuation system for an expendable launch vehicle

NASA Technical Reports Server (NTRS)

Burrows, Linda M.; Roth, Mary Ellen

1992-01-01

A major effort at the NASA Lewis Research Center in recent years has been to develop electro-mechanical actuators (EMA's) to replace the hydraulic systems used for thrust vector control (TVC) on launch vehicles. This is an attempt ot overcome the inherent inefficiencies and costs associated with the existing hydraulic structures. General Dynamics Space Systems Division, under contract to NASA Lewis, is developing 18.6 kW (25 hp), 29.8 kW (40 hp), and 52.2 kW (70 hp) peak EMA systems to meet the power demands for TVC on a family of vehicles developed for the National Launch System. These systems utilize a pulse population modulated converter and field-oriented control scheme to obtain independent control of both the voltage and frequency. These techniques allow an induction motor to be operated at its maximum torque at all times. At NASA Lewis, we are building on this technology to develop our own in-house system capable of meeting the peak power requirements for an expendable launch vehicle (ELV) such as the Atlas. Our EMA will be capable of delivering 22.4 kW (30 hp) peak power with a nominal of 6.0 kW (8 hp). This system differs from the previous ones in two areas: (1) the use of advanced control methods, and (2) the incorporation of built-in-test. The advanced controls are essential for minimizing the controller size, while the built-in-test is necessary to enhance the system reliability and vehicle health monitoring. The ultimate goal of this program is to demonstrate an EMA which will be capable of self-test and easy integration into other projects. This paper will describe the effort underway at NASA Lewis to develop an EMA for an Atlas class ELV. An explanation will be given for each major technology block, and the status of each major technology block and the status of the overall program will be reported.

Review of deployment technology for tethered satellite systems

NASA Astrophysics Data System (ADS)

Yu, B. S.; Wen, H.; Jin, D. P.

2018-03-01

Tethered satellite systems (TSSs) have attracted significant attention due to their potential and valuable applications for scientific research. With the development of various launched on-orbit missions, the deployment of tethers is considered a crucial technology for operation of a TSS. Both past orbiting experiments and numerical results have shown that oscillations of the deployed tether due to the Coriolis force and environmental perturbations are inevitable and that the impact between the space tether and end-body at the end of the deployment process leads to complicated nonlinear phenomena. Hence, a set of suitable control methods plays a fundamental role in tether deployment. This review article summarizes previous work on aspects of the dynamics, control, and ground-based experiments of tether deployment. The relevant basic principles, analytical expressions, simulation cases, and experimental results are presented as well.

Development of Bonded Joint Technology for a Rigidizable-Inflatable Deployable Truss

NASA Technical Reports Server (NTRS)

Smeltzer, Stanley S., III

2006-01-01

Microwave and Synthetic Aperture Radar antenna systems have been developed as instrument systems using truss structures as their primary support and deployment mechanism for over a decade. NASA Langley Research Center has been investigating fabrication, modular assembly, and deployment methods of lightweight rigidizable/inflatable linear truss structures during that time for large spacecraft systems. The primary goal of the research at Langley Research Center is to advance these existing state-of-the-art joining and deployment concepts to achieve prototype system performance in a relevant space environment. During 2005, the development, fabrication, and testing of a 6.7 meter multi-bay, deployable linear truss was conducted at Langley Research Center to demonstrate functional and precision metrics of a rigidizable/inflatable truss structure. The present paper is intended to summarize aspects of bonded joint technology developed for the 6.7 meter deployable linear truss structure while providing a brief overview of the entire truss fabrication, assembly, and deployment methodology. A description of the basic joint design, surface preparation investigations, and experimental joint testing of component joint test articles will be described. Specifically, the performance of two room temperature adhesives were investigated to obtain qualitative data related to tube folding testing and quantitative data related to tensile shear strength testing. It was determined from the testing that a polyurethane-based adhesive best met the rigidizable/inflatable truss project requirements.

Ridership impacts of South Florida's EASY smart card.

DOT National Transportation Integrated Search

2013-07-01

Smart card-based Automated Fare Collection Systems (AFCS) are being increasingly deployed in transit systems across the US. Miami-Dade Transit (MDT) has recently deployed such a system branded as the EASY Card. The South Florida Regional Transportati...

Front air bag nondeployments in frontal crashes fatal to drivers or right-front passengers.

PubMed

Braver, Elisa R; McCartt, Anne T; Sherwood, Christopher P; Zuby, David S; Blanar, Laura; Scerbo, Marge

2010-04-01

Public concern has arisen about the reliability of front air bags because Fatality Analysis Reporting System (FARS) data indicate many nondeployed air bags in fatal frontal crashes. However, the accuracy of air bag deployment, the variable in question, is uncertain. This study aimed to provide more certain estimates of nondeployment incidence in fatal frontal crashes. Fatally injured passenger vehicle drivers and right-front passengers in frontal crashes were identified in two U.S. databases for calendar years 1998-2006 and model years 1994-2006: FARS, a census of police-reported fatal crashes on public roads, and National Automotive Sampling System/Crashworthiness Data System (NASS/CDS), a probability sample of tow-away crashes. NASS/CDS contains subsets of fatal crashes in FARS and collects detailed data using crash investigators. Front air bag deployment coding for front-seat occupant fatalities was compared in FARS and NASS/CDS, and case reviews were conducted. Among FARS frontal deaths with available deployment status (N = 43,169), front air bags were coded as not deployed for 18 percent of front occupants. In comparison, NASS/CDS (N = 628) reported 9 percent (weighted estimate) nondeployment among front occupants killed. Among crashes common to both databases, NASS/CDS reported deployments for 45 percent of front occupant deaths for which FARS had coded nondeployments. Detailed case reviews of NASS/CDS crashes indicated highly accurate coding for deployment status. Based on this case review, 8 percent (weighted estimate) of front occupant deaths in frontal crashes appeared to involve air bag nondeployments; 1-2 percent of front occupant deaths represented potential system failures where deployments would have been expected. Air bag deployments appeared unwarranted in most nondeployments based on crash characteristics. FARS data overstate the magnitude of the problem of air bag deployment failures; steps should be taken to improve coding. There are inherent uncertainties in judgments about whether or not air bags would be expected to deploy in some crashes. Continued monitoring of air bag performance is warranted.

The Design of Power System Stability Controller Based on the PCH Theory and Improved Genetic Algorithm

NASA Astrophysics Data System (ADS)

Liu, Zhijian; Yin, Donghui; Yan, Jun

2017-05-01

Low frequency oscillation is still frequently happened in the power system and it affects the safety and stability of power system directly. With the continuously expending of the interconnection scale of power grid, the risk of low frequency oscillation becomes more and more noticeable. Firstly, the basic theory of port-controlled Hamilton (PCH) and its application is analyzed. Secondly, based on the PCH theory and the dynamic model of system, from the viewpoint of energy, the nonlinear stability controller of power system is designed. By the improved genetic algorithm, the parameters of the PCH model are optimized. Finally, a simulation model with PCH is built to vary the effectiveness of the method proposed in this paper.

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

NASA Technical Reports Server (NTRS)

Housner, Jerrold M.

1989-01-01

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

iFlorida model deployment final evaluation report.

DOT National Transportation Integrated Search

2009-01-01

This document is the final report for the evaluation of the USDOT-sponsored Surface Transportation Security and Reliability Information System Model Deployment, or iFlorida Model Deployment. This report discusses findings in the following areas: ITS ...

iFlorida model deployment final evaluation report

DOT National Transportation Integrated Search

2009-01-01

This document is the final report for the evaluation of the USDOT-sponsored Surface Transportation Security and Reliability Information System Model Deployment, or iFlorida Model Deployment. This report discusses findings in the following areas: ITS ...

ITS strategic deployment plan : executive summary

DOT National Transportation Integrated Search

1997-02-27

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

Image-Based Environmental Monitoring Sensor Application Using an Embedded Wireless Sensor Network

PubMed Central

Paek, Jeongyeup; Hicks, John; Coe, Sharon; Govindan, Ramesh

2014-01-01

This article discusses the experiences from the development and deployment of two image-based environmental monitoring sensor applications using an embedded wireless sensor network. Our system uses low-power image sensors and the Tenet general purpose sensing system for tiered embedded wireless sensor networks. It leverages Tenet's built-in support for reliable delivery of high rate sensing data, scalability and its flexible scripting language, which enables mote-side image compression and the ease of deployment. Our first deployment of a pitfall trap monitoring application at the James San Jacinto Mountain Reserve provided us with insights and lessons learned into the deployment of and compression schemes for these embedded wireless imaging systems. Our three month-long deployment of a bird nest monitoring application resulted in over 100,000 images collected from a 19-camera node network deployed over an area of 0.05 square miles, despite highly variable environmental conditions. Our biologists found the on-line, near-real-time access to images to be useful for obtaining data on answering their biological questions. PMID:25171121

Image-based environmental monitoring sensor application using an embedded wireless sensor network.

PubMed

Paek, Jeongyeup; Hicks, John; Coe, Sharon; Govindan, Ramesh

2014-08-28

This article discusses the experiences from the development and deployment of two image-based environmental monitoring sensor applications using an embedded wireless sensor network. Our system uses low-power image sensors and the Tenet general purpose sensing system for tiered embedded wireless sensor networks. It leverages Tenet's built-in support for reliable delivery of high rate sensing data, scalability and its flexible scripting language, which enables mote-side image compression and the ease of deployment. Our first deployment of a pitfall trap monitoring application at the James San Cannot Mountain Reserve provided us with insights and lessons learned into the deployment of and compression schemes for these embedded wireless imaging systems. Our three month-long deployment of a bird nest monitoring application resulted in over 100,000 images collected from a 19-camera node network deployed over an area of 0.05 square miles, despite highly variable environmental conditions. Our biologists found the on-line, near-real-time access to images to be useful for obtaining data on answering their biological questions.

Orbit Determination Support for the Microwave Anisotropy Probe (MAP)

NASA Technical Reports Server (NTRS)

Bauer, Frank (Technical Monitor); Truong, Son H.; Cuevas, Osvaldo O.; Slojkowski, Steven

2003-01-01

NASA's Microwave Anisotropy Probe (MAP) was launched from the Cape Canaveral Air Force Station Complex 17 aboard a Delta II 7425-10 expendable launch vehicle on June 30, 2001. The spacecraft received a nominal direct insertion by the Delta expendable launch vehicle into a 185-km circular orbit with a 28.7deg inclination. MAP was then maneuvered into a sequence of phasing loops designed to set up a lunar swingby (gravity-assisted acceleration) of the spacecraft onto a transfer trajectory to a lissajous orbit about the Earth-Sun L2 Lagrange point, about 1.5 million km from Earth. Because of its complex orbital characteristics, the mission provided a unique challenge for orbit determination (OD) support in many orbital regimes. This paper summarizes the premission trajectory covariance error analysis, as well as actual OD results. The use and impact of the various tracking stations, systems, and measurements will be also discussed. Important lessons learned from the MAP OD support team will be presented. There will be a discussion of the challenges presented to OD support including the effects of delta-Vs at apogee as well as perigee, and the impact of the spacecraft attitude mode on the OD accuracy and covariance analysis.

Greater Portland intelligent transportation systems (ITS) early deployment plan

DOT National Transportation Integrated Search

1998-03-01

The Greater Portland Intelligent Transportation Systems Early Deployment Plan is a strategic vision of how smart technology can be applied to help improve mobility in Maines largest metropolitan area.